Heat Treater's Guide Practices and Procedures for Nonferrous Alloys Harry Chandler, Editor Veronica Flint, Manager of Book Acquisitions Grace M. Davidson, Manager of Book Production Randall L. Boring, Production Project Coordinator Cheryl L. Powers, Production Project Coordinator Alexandru Popaz Pauna, Production Project Coordinator
AS~
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Library of Congress Cataloging Card Number: 96-85651 ISBN: 0-87170-565-6 SAN: 204-7586
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Table of Contents Introduction. . . . . . . . . . . . . . . . . . . . . . . .. Diffusion Process. . . . . . . . . . . . . . . .. Annealing Cold-Worked Metals ..... Homogenization of Castings. . . . . . .. Precipitation Hardening Treatments . . . . . . . . . . . . . . . . . .. Developing Two-Phase Structures. . ..
1 1 1 4 5 6
Superalloys . . . . . . . . . . . . . . . . . . . . . . . . . .. 9 Heat Treating Superalloys. . . . . . . . . . . .. 11 Characteristics " 11 Heat Treating Practice " 12 Nickel-Base Alloys " 17 Astroloy . . . . . . . . . . . . . . . . . . . . . .. 17 D-979 '" 19 IN 100 19 IN 102 25 Incoloy 901 " 26 Inconel 706 " 29 Inconel X 750 .. . .. . .. . 30 Incone1751 33 Hastelloy B " 33 Hastelloy B-2 " 33 Hastelloy C " 35 Hastelloy C-4. . . . . . . . . . . . . . . . . .. 36 Hastelloy C-276 " 37 Hastelloy N " 37 Hastelloy S '" 37 Hastelloy W " 38 Hastelloy X . . . . . . . . . . . . . . . . . . .. 38 Haynes 214 39 Haynes 230 " 40 Nimonic 86 . . . . . . . . . . . . .. 40 Custom Age 625 PLUS " 40 Haynes 242 " 40 Incone1702 " 41 Incone1718 " 41 Inconel721 59 Inconel 722 " 59 C-263 59 Pyromet 31 " 59 Nimonic 80A . . . . . . . . . . . . . . . . . .. 60 Nimonic 90 " 62 Pyromet 860 " 62 Refractory 26 " 63 Rene 41 63 Rene 95 68 Rene 100 69 Udimet 500 " 69 Udimet 520 " 70 Udimet 700 " 70 Udimet 710 " 74 UnitempAF2-lDA 74 Waspaloy " 76 Nimonic PE16 " 81 Nimonic PK33 " 81 Inconel 600 " 81 Inconel 601 " 88 Inconel 604 . . . . . . . . . . . . . . . . . . .. 88 Incone1617 " 88
Inconel 625 88 Nimonic 75 97 RA-333 97 NA-224 97 Cobalt-Base Alloys 98 S-816 98 Stellite 6B 98 Haynes 25; L-605 99 Haynes 188 . . . . . . . . . . . . . . . . . . . . 102 MP35N 105 MP159 106 Air-Resist 213 106 Elgiloy. . . . . . . . . . . . . . . . . . . . . . . . 106 V-36 107 UMCo-50 107 Iron-Base Alloys 108 A-286 .. '" 108 W-545 112 V-57 112 Incoloy 800 112 Incoloy 801 114 Incoloy 802 115 Incoloy 807 115 Incoloy 825 115 Incoloy 903 117 Incoloy 907 117 Incoloy 909 117 Incoloy 925 118 16-25-6 118 17-14 CuMo 119 19-9DL 119 N-155 119 RA-330 120 Discaloy. . . . . . . . . . . . . . . . . . . . . . . 120 Haynes 556 121 Pyromet CTX-l. 122 PyrometCTX-3 122 Nickel. 123 Heat Treating Nickel . . . . . . . . . . . . . . . . 125 Nickel 200 126 Nicke1201 126 Monel 400 127 Monel R-405 127 Monel K-500 127 Aluminum Alloys 129 Heat Treating Aluminum Alloys 131 Strengthening by Heat Treatment 135 Hardening of Cast Alloys . . . . . . . . . 140 Stress Relief 140 Effects of Reheating . . . . . . . . . . . . . 140 Annealing . . . . . . . . . . . . . . . . . . . . . 141 Grain Growth 142 Dimensional Changes during Heat Treatment. 142 Quality Assurance 142 Temper Designations for Heat-Treatable AluminumAlloys 144 Properties of Wrought Aluminum and Wrought Aluminum Alloys. . . .. 146 V
1050 1060 1100 1145 1199 1350 2011 2014, Alclad 2014 2017 2024, Alclad 2024. . . . . . . . . . . . . .. 2048 2124 2218 2219, Alclad 2219 2319 2618 3003, Alclad 3003 3004, Alclad 3004 3105 4032 4043 '" 5005 5050 5052 5056, Alclad 5056 5083 5086, Alclad 5086 5154 5182 5252 5254 5356 5454 5456 5457 5652 5657 6005 6009 6010 6061, Alclad 6061. . . . . . . . . . . . . . . 6063 6066 6070 6101 6151 6201 , 6205 6262 6351 6463 7005 7039 7049 7050 7072 7075, A1clad7075 7175 7178, Alclad 7178 7475
149 150 151 153 153 154 155 155 159 159 169 171 173 174 178 179 180 182 184 184 185 185 186 187 188 189 191 191 192 193 193 194 194 195 197 198 198 200 200 201 201 206 208 208 209 210 211 211 212 213 214 214 215 217 218 221 221 238 239 241
Aluminum Casting Alloys. . . . . . . . . . .. 201.0 204.0 206.0, A206.0 208.0 238.0 242.0 295.0 296.0 308.0 319.0 332.0 336.0 339.0 354.0 355.0, C355.0 356.0, A356.0 357.0, A357.0 359.0 360.0, A360.0 . . . . . . . . . . . . . . . . .. 380.0, A380.0 383.0 384.0, A384.0 390.0, A390.0 . . . . . . . . . . . . . . . . .. 413.0, M13.0 443.0, A443.0, B443.0, C443.0 514.0 518.0 520.0 535.0, A535.0, B535.0 712.0 713.0 771.0 850.0 Heat Treating Aluminum-Lithium Alloys Weldalite 049 . . . . . . . . . . . . . . . . .. 2090 2091 8090 CP276 Heat Treating Aluminum PIM Parts . . . . Heat Treatable Grades . . . . . . . . . .. Applications . . . . . . . . . . . . . . . . . .. Heat Treating Technology Copper Alloys . . . . . . . . . . . . . . . . . . . . . . . Heat Treating Copper Alloys. . . . . . . . .. Homogenizing . . . . . . . . . . . . . . . .. Annealing. . . . . . . . . . . . . . . . . . . .. Stress Relieving . . . . . . . . . . . . . . . . Hardening. . . . . . . . . . . . . . . . . . . . . Copper-Beryllium Alloys Copper-Chromium Alloys Copper-Zirconium Alloys. . . . . . . . . Miscellaneous PrecipitationHardening Alloys ... . . . . . . . . . Spinodal-Hardening Alloys Copper-Aluminum (Aluminum Bronze) Alloys Copper Casting Alloys Wrought Coppers and Copper Alloys . . . CIOIOO and C10200 CI0300 CI0400, C10500, ClO700 CI0800 CllOOO(99.95Cu-0.040) C11l00 (99.95Cu-0.040-0.01Cd)
244 244 245 246 248 248 249 250 251 251 252 252 252 253 253 255 257 259 259 260 261 261 262 262 263 264 264 265 265 266 266 267 267 268 269 269 271 274 276 279 280 280 280 280 283 285 285 285 286 287 288 290 290 291 291 291 292 295 295 298 298 300 300 306
C1l300, C1l400, C1l500, C1l600 (99.96Cu + Ag - 0040) , C12500,CI2700,C12800,CI2900, C13000 C14300, C14310 (99.90Cu-O.lCd; 99.8Cu-0.2Cd) , Cl4500 (99.5Cu-0.Te) , Cl4700 (99.6Cu-OA5) , Cl5000 (99.85Cu-0.15Zr) C15100 (99.9Cu-0.1Zr) , C15500 (99.75Cu-0.llMg0.06P) Cl5710 (99.8Cu-0.2Ah03) , C15720 (99.6Cu-0.4Ah03) , C15735 (99.3Cu-0.7Ah03) Cl6200 (99Cu-1Cd) C17000 (98Cu-1.7Be-0.3Co) , Cl7200, C17300 , C17410 (99.2Cu-0.3Be-0.5Co) , C17500 (97Cu-0.50Be-2.5Co) , C17600 , Cl8100 (99Cu-0.8Cr-0.16Zr0.04Mg) , C18200, C18400, C18500 (99Cu-1Cr) C18700 (99Cu-1Pb) , Cl9200 (98.97Cu-1.0Fe-0.03P) .. , Cl9210 (99.87Cu-0.lFe-0.03P) .. , C19400 (Cu-2.35Fe-0.03P0.12Zn) , Cl9500 (97Cu-1.5Fe-0.1P0.8Co-0.6Sn) , C19700 (99.15Cu-0.6Fe-0.2P0.05Mg) , C21000 (95Cu-5Zn) , C22000 (90Cu-IOZn) , C22600 (87.5Cu-12.5Zn) , C23000 (85Cu-15Zn) , C24000 (80Cu-20Zn) , C26000(70Cu-30Zn) C26800, C27000 (65Cu-35Zn) , C28000 (60Cu-40Zn) C31400 (89Cu-9.lZn-1.9Pb) , C31600 (89Cu-8.1Zn-1.9Pb1Ni) , C33000 (66Cu-33.5Zn-0.5Pb) , C33200 (66Cu-32AZn-1.6Pb) , C33500 (65Cu-34.5Zn-0.5Pb) , C34000 (65Cu-34Zn-1Pb) C342PO(62Cu-36.2Zn-2Pb) , C35300 (62Cu-36.2Zn-1.8Pb) C34900 (62Cu-37.5Zn-0.3Pb) , C35000 (65.5Cu-36AZn-l.lPb) C35600 (62Cu-35.5Zn-2.5Pb) , C36000 (61.5Cu-35.5Zn-3Pb) , C36500,C36600,C36700,C36800 (60Cu-39AZn-0.6Pb) , C37000 (60Cu-39Zn-lPb) , C37700 (60Cu-38Zn-2Pb) C38500 (57Cu-40Zn-3Pb) C40500 (95Cu-4Zn-1Sn) , C40800 (95Cu-2Sn-3Zn) C41100 (91Cu-8.5Zn-0.5Sn) C41500 (91Cu-7.2Zn-1.8Sn) , C41900 (90.5Cu-4.35Zn5.l5Sn) , C42200 (87.5Cu-ll.4Zn-l.lSn)
vi
306 308 309 309 309 310 312 312 313 313 314 314 314 316 320 321 323 323 324 325 325 326 326 328 328 328 330 331 332 334 334 339 341 343 343 343 344 344 345 345 345 346 347 347 347 349 349 349 350 351 351 351 352 353 353
C42500 (88.5Cu-9.5Zn-2Sn) C43000 (87Cu-IO.8Zn-2.2Sn) C43400 (85Cu-14.3Zn-0.7Sn) C44300,C44400,C44500 (71Cu-28Zn-lSn) C46400,C46500,C46600,C46700 (60Cu-39.2Zn-0.8Sn) C48200 (60.5Cu-38Zn-0.8Sn0.7Pb) C48500 (60Cu-37.5Zn-1.8Pb0.7Sn) C50500 (98.7Cu-1.3Sn) C51000 (94.8Cu-5Sn-0.2P) C51100 (95.6Cu-4.2Sn-0.2P) C52100 (92Cu-8Sn) C52400 (90Cu-IOSn) C54400 (88Cu-4Pb-4Sn-4Zn) C60600 (95Cu-5Al) C60800 (95Cu-5Al) C61000 (92Cu-8Al) C61300 (90Cu-7AI-0.3Sn) C61400 (91Cu-7AI-2Fe) C61500 (90Cu-8AI-2Ni) C62300 (87Cu-IOAI-3Fe) C62400 (86Cu-llAI-3Fe) C62500 (82.7Cu-4.3Fe-13Al) C63800 (95Cu-2.8AI-1.8SiOAOCo)
C65100 (98.5Cu-1.5Si) C65400 (95ACu-3.0Si-1.5SnO.lCr) C65500 (97Cu-3Si) C68800 (73.5Cu-22.7Zn-3AAlOACo)
,
C69000 (73.3Cu-22.7Zn-3AAl0.6Ni) , C69400 (81.5Cu-14.5Zn-4Si) C70400 (92ACu-5.5Ni-1.5Fe0.6Mn) C70600 (90Cu-IONi) C71000 (80Cu-20Ni) C71500 (70Cu-30Ni) C71900 (67.2Cu-30Ni-2.8Cr) C72200 (83Cu-16.5Ni-0.5Cr) C72500 (88.2Cu-9.5Ni-2.3Sn) C74500 (65Cu-25Zn-IONi) C75200 (65Cu-18Ni-17Zn) C75400 (65Cu-20Zn-15Ni) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) C78200 (65Cu-25Zn-8Ni-2Pb) Copper Casting Alloys C81300 C81400 , C81500 , C81800 (97Cu-1.5Co-IAgOABe) C82000 (97Cu-2.5Co-0.5Be) C82200 (98Cu-1.5Ni-0.5Be) C82400 (98Cu-1.7Be-0.3Co) C82500 (97.2Cu-2Be-0.5Co0.25Si) C82600 (97Cu-2ABe-0.5Co) C82800 (96.6Cu-2.6Be-0.5Co0.3Si) C83300
353 354 . 354 354 356 358 359 359 360 361 361 362 363 363 363 364 364 365 '366 367 368 368 369 370 370 370 371 372 372 373 373 375 376 377 378 378 378 379 380 381 381 382 393 383 383 383 384 384 385 386 386 387 388 389
C86100, C86200 (64Cu-24Zn3Fe-5Al~~n) .. . . . . . . . . . . .. 389 C86300 (64Cu-26Zn-3Fe3AI-4~n) . . . . . . . . . . . . . . . . .. 390 C86400 (59Cu-0.75Sn-0.75Pb-37Zn1.25Fe-0.75AI-0.5~n) 390 C86500 (58Cu-39Zn-1.3Fe-lAlO.5~n) 390 C86700 391 C86800 391 C87300 (formerly C87200). . . . . .. 392 C87600 392 C8761O 392 C87500, C87800 (82Cu~Si14Zn) 393 C87900 393 C92200 (88Cu-6Sn-l.SPb4.5Zn) 393 C92300 (87Cu-8Sn-1Pb-4Zn) . . . .. 394 C92500 (87Cu-llSn-1Pb-1Ni) .... 394 C92600 (87Cu-lOSn-1Pb-2Zn). . .. 395 C92700 (88Cu-lOSn-2Pb) 395 C92900 (84Cu-lOSn-2.5Pb3.5Ni) 395 C93200 (83Cu-7Sn-7Pb-3Zn) 395 C93400 396 C93500 (85Cu-5Sn-9Pb-1Zn). . . .. 396 C93700 (80Cu-lOSn-lOPb) 396 C93800 (78Cu-7Sn-15Pb) 397 C95200 (88Cu-3Fe-9Al) . . . . . . . .. 398 <::95300 (89Cu-1Fe-lOA1) 398 C95400 (85Cu-4Fe-llAl) and C95410 399 C95500 (81Cu~Fe-4Ni-llAl) 399 C95600 (91Cu-2Si-7Al) 399 C95700 (75Cu-3Fe-8AI-2Ni12~n) 400 C95800 (82Cu-4Fe-9AI-4Nil~n) 400 C96600 (69.5Cu-30Ni-0.5Be). . . .. 400 C97300 (56Cu-2Sn-lOPb20Zn-12Nij 401 C97600 (64Cu-4Sn-4Pb-8Zn20Ni) 401 C97800 (66.5Cu-5Sn-l.5Pb-2Zn25Ni) 401 C99400 (90ACu-2.2Ni-2.0Fe1.2Al-1.2Si-3.0Zn). . . . . . . . . .. 401 C99500 402 '" 402 C99750 .. '" Beryllium copper 21C (97Cu2Be-1Co) 402 Beryllium copper nickel 72C (68.8Cu-30Ni-1.2Be) 403 Heat Treating Beryllium Copper Alloys . . . . . . . . . . . . . . . . . .. 404 Solution Annealing .. . . . . . . . . . .. 404 Age Hardening. . . . . . . . . . . . . . . .. 404 Underaging, Peak Aging, and Overaging Treatments . . . . . . .. 404 Sintering Copper-Based Materials 412 Production Sintering of Bronze 412 Production Sintering of Brass and Nickel Silvers . . . . . . . . . .. 412 Magnesium Alloys 415 Heat Treating Magnesium Alloys. . . . .. 417 Types of Heat Treatment. . . . . . . .. 417
Effects of Major Variables Wrought Magnesium Alloys AZ3IB,AZ31C AZ61A AZ80A HK31A ~21A
~31A
ZC71 ZK60A Cast Magnesium Alloys A~100A
AZ63A. AZ81A AZ91A,AZ91B,AZ91C, AZ9ID, AZ91E AZ92A. EQ21 ; EZ33A HK31A HZ32A QE22A. QH21A WE43 WE54 ZC63 ZE41A ZE63A ZH62A. ZK51A. ZK61A.
420 423 423 424 425 427 429 430 431 431 432 432 433 435 436 438 439 440 441 443 444 446 447 448 450 450 452 453 454 456
Titanium Alloys 457 Heat Treating Titamiun Alloys 459 Alloy Types and Response to Heat Treatment. 459 Stress Relieving 460 Annealing 460 Solution Treating and Aging 461 High Purity Titanium 463 Commercially Pure and Modified Titanium . . . . . . . . . . . . . . . . . . . . . .. 467 Unalloyed Titanium, ASN Grade 1, UNS R50250 467 Unalloyed Titanium, AST~ Grade 2, UNS R50400 469 Unalloyed Titanium, AST~ Grade 3, UNS R50550 471 Unalloyed Titanium, Grade 4, UNS R50700 472 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 474 Ti-0.3~o-0.8Ni, AST~ Grade 12, R53400 476 Alpha and Near-Alpha Alloys 478 Ti-3AI-2.5V 478 Ti-5AI-2.5Sn 483 Ti-6AI-2Nb-ITa-0.8~o 488 Ti-6AI-2Sn-4Zr-2~o-0.08Si. 492 Ti-8Al-l~~-1 V 498 TillETAL 1100 502 IMI230 504 IMI417 505 IMI679 506 IMI685 509 IMI 829 510 IMI 834 511
vii
Alpha-Beta Alloys
514 514 Ti-6AI-2Sn-4Zr-6~o 517 Ti-6A1-4V 522 Ti-6A1-6V-2Sn 536 Ti-7AI-4~o 541 T~TAL® 62S 543 Ti-4.5AI-3V-2~o-2Fe 544 IMI367 549 IMI550 549 550 IMI 55l. Ti-6-22-22S 551 Ti-5AI-2.5Fe 556 Ti-5AI-5Sn-2Zr-2~o-0.25Si 557 Beta and Near-Beta Alloys 559 Ti-ll.5~o-6Zr-4.5Sn . . . . . . . . . . .. 559 Ti-5AI-2Sn-2Zr-4~o-4Cr
Ti-3AI-8V-6Cr-4~o-4Zr
(Beta C) . . . . . . . . . . . . . . . . . . .. Ti-lOV-2Fe-3Al Ti-13V-llCr-3Al Ti-15V-3Cr-3AI-3Sn T~TAL® 21S Ti-5AI-2Sn-4Zr-4~o-2Cr-IFe Ti-8~o-8V-2Fe-3Al Ti-15~o-5Zr.
Ti-15~o-5Zr-3Al.
Ti-ll.5V-2AI-2Sn-llZr Ti-12V-2.5AI-2Sn-6Zr Ti-13V-2.7AI-7Sn-2Zr Ti-8V-5Fe-IAI Ti-16V-2.5Al. . . . . . . . . . . . . . . . . .. Heat Treating Cast and PIM Titanium. .. Modifying Microstructure . . . . . . . . Hot Isostatic Pressing Weld Repair . . . . . . . . . . . . . . . . . . .
563 566 572 577 582 584 586 589 591 594 595 597 599 601 602 602 602 602
Zinc Alloys . . . . . . . . . . . . . . . . . . . . . . . .. Heat Treating Zinc Alloys . . . . . . . . . . . . Heat Treatment of Zamak and ZA Alloys . . . . . . . . . . . . . . . . . . Reasons for Heat Treating . . . . . . . . Supporting Documentation . . . . . .. Conventional Zinc Die Casting Alloys AC43A AG40A AC41A AG40B Zinc-Aluminum Casting Alloys ZA-8 ZA-12 ZA-27
607 609
Lead Alloys Heat Treating Lead and Lead Alloys Solid-Solution Hardening Solution Treating and Aging .. . . .. Dispersion Hardening Fabrication . . . . . . . . . . . . . . . . . . .. Cold Storage. . . . . . . . . . . . . . . . . . . Service Temperatures . . . . . . . . . . . .
619
Refractory Metals and Alloys . . . . . . . . . .. Heat Treating Refractory Metals and Alloys General Annealing Treatments. . . .. Molybdenum and Tungsten Annealing Practice
609 609 609 615 615 615 616 616 617 617 617 618
621 621 621 621 622 622 622 625 627 627 627
Tantalum and Niobium Annealing Practice . . . . . . . . . . . . . . . . . . .. 628 Tin-Rich Alloys. . . . . . . . . . . . . . . . . . . . .. 631
Heat Treating Tin-Rich Alloys , Binary Alloys. . . . . . . . . . . . . . . . .. Ternary Alloys , Pewter
viii
633 633 633 633
Glossary
635
Conversion Tables
647
Cross Reference
651
PREFACE Heat Treater's Guide, Practices and Procedures for Nonferrous Metals/Alloys, features quick access to some 450 or more authoritative datasheets on the subject, namely: • • • • • • •
Superalloys Nickels Aluminum Copper Magnesium Titanium Zinc
In addition, brief overview articles provide information on the heat treatment of: • • • • • •
Aluminum PIM alloys Beryllium-copper alloys Lead and lead alloys Refractory metals and alloys Tin-rich alloys and Sintering of copper-base materials
Information is organized by material group, and is provided on an alloy-by-alloy basis. Each datasheet includes information such as: composition, trade names and common names, specifications (both U.S. and foreign), typical applications, mechanical and chemical properties, fabrication characteristics, and, of course, the reconunended heat treating practice. These datasheets are designed to follow a similar format to that established in the popular Heat Treater s Guide, Procedures and Practices for Irons and Steels. Access to this data is facilitated by the cross reference provided at the end of the book. For further convenience to the reader, we have included a Glossry of terms related to the heat treating of nonferrous materials. We are interested in receiving datasheet contributions you might have that could be included in this book, as well as your conunents or suggestions.
Materials Park, OH September 1996
iii
Introduction The principles which govern heat treatment of metals and alloys are applicable to both ferrous and nonferrous alloys. However, in practice there are sufficient differences to make it convenient to emphasize as separate topics the peculiarities of the alloys of each class in their response to heat treatment. For example, in nonferrous alloys, eutectoid transformations, which play such a prominent role in steels, are seldom encountered, so there is less concern with principles associated with time-temperaturetransformation diagrams and with martensite formation. On the other hand, the principles associated with chemical homogenization of cast structures are applicable to many alloys in both classes.
The diffusion process is involved in nearly all heat treatments for nonferrous alloys. Common treatments include: • • • •
Annealing after cold working Homogenization of castings Precipitation hardening treatments Development of two-phase structures
Diffusion Process In the heat treatment of metals and alloys, the rate of structural change usually is controlled by the rate at which atoms in the lattice change positions. For example, when cold-worked copper is annealed and softens, or an aluminum-base alloy is aged, it is important to know how the atoms move relative to each other so as to bring about the observed changes in properties. This movement of atoms is called diffusion. Two different diffusion mechanisms are shown in Fig. 1.
Fig. 1 Schematic representation of two possible diffusion mechanisms. (a) Two atoms move simultaneously to exchange positions. (b) Four atoms move cooperatively to rotate simultaneously to move to new positions
.... .... .... ••••••• ••••••• " ••••••• ••••••• ••••••• ~
(a)
........ ••••••• • •••••• • •• W •• ••••••• ••••••• ••••••• (b)
Annealing Cold-Worked Metals Cold working increases hardness, yield strength, and tensile strength, and lowers ductility. Also, electrical resistivity is improved because increasing density of dislocations scatters the electrons. The effects of cold working on several properties are shown in Fig. 2. Role of Annealing. In shaping metals by cold working, there is a limit to the amount of plastic deformation possible without fracture. Annealing restores the metal to a structural condition similar to that prior to deformation, making further cold working possible. Changes in strength that take place during annealing are indicated by the hardness data in Fig. 3(a). In this instance, data are for a fixed temperature. A similar result is obtained by annealing for a fixed time at increasing temperatures (Fig. 3b). Recovery, recrystallization, and grain growth are stages in annealing. The stage for short times at low temperatures in which hardness remains constant, or increases slightly, is called the recovery region. Dislocations undergo movement by thermal activation, being rearranged into arrays somewhat more stable and more difficult to move than in the cold worked, unannealed condition. A slight increase in hardness results. Some properties regain values they had prior to cold working. Hence the
term recovery. Electrical conductivity is one of the properties involved (see. Fig. 4). Recrystallization. With longer times or at higher temperatures, the structure undergoes a more radical change. Small crystals appear which contain a low dislocation density (of a magnitude similar to that prior to cold working) and are relatively soft. Crystals nucleate in regions of high dislocation density, and in the microstructure appear at or near deformation bands. With time, the nuclei grow, and more nuclei form in the remaining cold-worked matrix. Eventually, grains contact each other (at that time the original cold-worked material has disappeared). The formation of grains is referred to as recrystallization. At this time, strength drops drastically (see Fig. 3 and 4). Growth in grain size. Microstructural changes that occur during annealing are illustrated in Fig. 5. During recovery, the density of deformation bands drops, but the change is not marked. When crystallization commences, small, equiaxed grains begin to appear (see micrograph 2 in Fig. 5, and a recrystallized nucleus shown in Fig. 6). Grains continue to form and to grow until the cold-worked matrix is consumed, which marks the end of the recrystallization period and the beginning of grain growth.
2/ Heat Treater's Guide: Nonferrous Alloys
Fig. 2 Effect of cold working (by rolling at 25°C, or 77 ° F) on the tensile mechanical properties and hardness of oxygen-free, high-conductivity (OFHC) copper
120 .-------.------,---.--------,
.~
§ 100 \----+-------11----+-------1
LIVE GRAPH
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80 f - - - - / - - + - - - - - I - - - - + - - - - - - - I
-SOl c: ~
t> 60 If----+-yield strength, ksi --+:=~---1
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.~
g> 40 \-----,,,L-----Y'--------I----+-------I
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Fig.3 (a) Effect of annealing time at fixed temperature (400°C, or 750 OF) on hardness of a Cu-5Zn solid-solution alloy cold worked 60%. (b) Effect of annealing temperature at fixed time (15 min) on hardness of a Cu-5Zn solid-solution alloy cold worked 60%
140
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Annealing temperature, of 750 390 1110 1470 60
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Introduction /3 With further annealing, grain size continues to grow (see micrographs 3, 4, and 5 in Fig. 5). Because annealing of cold-worked metals usually is carried out to soften the material, the temperature and time needed to complete recrystallization must be known to determine the proper heat treatment. The recrystallization temperature is commonly referred to as an indicator of the temperature at which metal must be annealed for softening.
As a rule of thumb, the recrystallization temperature is approximately 0.3 to 0.6 of the absolute melting point. In the case ofCu-Zn solid solution alloys, the addition of zinc to copper lowers the melting point, and the recrystallization temperature will decrease for high zinc contents (20 to 30%, for example), see Fig. 7.
Fig. 5 Microstructure of a CU-5Zn alloy, cold rolled to 60%, then annealed for different times at 400°C (750 OF). The numbers refer to the different annealing times shown in Fig.3(a)
127 Rockwell B Recrystallization just beginning
128 Rockwell B No recrystallization yet; still in recovery
OM 100 urn 63 Rockwell B Recrystallization essentially complete; grain growth beginning
I
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60 Rockwell B
OM
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OM
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4/ Heat Treater's Guide: Nonferrous Alloys
recrystallized grain
deformation bonds
Fig. 6 High-magnification scanning electron micrograph showing a small recrystallized nucleus. Cu-5Zn alloy, cold worked by rolling 20°C (68 OF) to a reduction in thickness of 60%; annealed 60 min at 350°C (660 OF)
annealing
Iwins
Fig. 7 Illustration of effect of zinc content of Cu-Zn solid-solution alloys on the annealing process. The alloys were originally cold rolled at 25°C (77 OF) to 60%
Annealing temperature. of 390
200
750
1110
1470
I
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Alloy
Cu-20Zn
o
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160
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220°C (493 K) 410°C (683 K) 320°C (593 K)
0.36 0.51 0.47
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Annealing temperature, °C
Homogenization of Castings This treatment is applied prior to the mechanical processing of cast ingot and is often used even when an object is cast essentially to its final shape. Temperatures and times used in this process depend on the diffusion rate and the starting structure. In chemical homogenization annealing, chemical gradients in a dendritically cored structure can be reduced at a sufficiently high temperature
for a sufficient time. The rate of diffusion is given by an appropriate solution to Fick's law. As a conservative approximation, the required time is x 2 "" Dt, where x is the distance between regions of low and of high concentration in the dendrite cell, which is one-half of cell size.
Introduction I 5
Precipitation Hardening Treatments In designing alloys for strength, an approach often taken is to develop an alloy in which the structure consists of particles which impede dislocation motion dispersed in a ductile matrix. The fmer the dispersion, for the same amount of particles, the stronger the material. Such a dispersion can be obtained by choosing an alloy that, at elevated temperature, is single phase, but that on cooling will precipitate another phase in the matrix. A heat treatment is then developed to give the desired distribution of the precipitate in the matrix. If hardening occurs from this structure, then the process is called precipitation hardening or age hardening. However, not all alloys in which such a dispersion can be developed will harden. Solution Heat Treatment. A prerequisite to precipitation hardening is the ability to heat the alloy to a temperature range wherein all of the solute is dissolved, so that a single-phase structure is attained. This is shown schematically in Fig. 8 for a 10% B alloy in a hypothetical system A-B. Heating above the solvus temperature T2 for this alloy and holding in the a range for sufficient time will form the single phase a. This is the required solution heat treatment.
The Process of Precipitation. After quenching from the a region (Fig. 8), precipitation is achieved by reheating the alloy below the solvus (T2 in Fig. 8) at a suitable temperature for a suitable time. Precipitation Hardening. The high strength is produced by the fmely dispersed precipitates that form during precipitation treatments (which may include either natural room-temperature aging, or artificial aging at elevated temperatures). The effect of temperature and time on aging is illustrated by the data in Fig. 9. As pointed out previously, the higher the precipitation temperature, the lower the maximum hardness, because less precipitate forms as the solvus temperature is approached. However, the higher the temperature, the higher the rate of precipitation, and hence the maximum hardness is attained in less time. In most commercial precipitation-hardenable alloys, the rate of precipitation is low at ambient temperature, although sufficiently rapid to bring about measurable hardness changes in a reasonable time, as shown in Fig. 9 for aging at 30°C (85 "F), If hardening occurs at or near ambient temperature, it is termed age hardening; aging at other temperatures is called precipitation hardening.
Fig. 8 Hypothetical phase diagram of system A-B. The decreasingsolubilityof B ina with decreasing temperature allowsan alloy containing 10% B to be single-phase at high temperature (that is, above 7;) but two-phase at lowtemperature (1;)
o1
10
50
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10 Time, days
L...-
100
-'-
1000
----'
10,000
Fig. 9 Hardness as a function of aging time for an AI-4Cu alloy. The alloy
was solution annealedfor at least 48 h at 520°C (970 OF), then cooled quickly (waterquenched) to 25°C (77 OF)
6/ Heat Treater's Guide: Nonferrous Alloys
Developing Two-Phase Structures the region of ex and Pphase stability. The Pphase is a body-centered cubic, with the copper and zinc atoms located at random on the lattice sites. On cooling to temperatures below the dashed line (about 450°C, or 840 "F), the copper and zinc atoms take specific relative position on the sites, forming an ordered structure, or a superlattice. This phase is denoted Win Fig. 10. If the composition is exactly 50 at.% Zn, then the ordered structure is based on a body-centered cubic cell with zinc atoms at the center and copper atoms on the comers (or vice versa). See Fig. 11 for typical microstructure of Muntz metal (Cu-40Zn), Fig. 12 for microstructure of Cu-42Zn quenched from beta region, then reheated to develop an alpha precipitate structure.
In some nonferrous alloys (for example, titanium-base alloys and high-zinc Cu-Zn alloys), the desired structure consists of a mixture of two phases of comparable quantity (unlike the two-phase structures developed in precipitation hardening, where the precipitate is in the minority). The morphology and amount of each are varied by control of the high temperature used and the cooling rate from that temperature. The preferred microstructure can be quite complex, and the required treatment differs considerably for different systems, so that a systematic treatment of the principles involved is difficult. In the Cu-Zn system, alloys containing about 40% Zn serve as the basis for some commercial alloys (for example, Muntz metal and naval brass). The Cu-Zn phase diagram (Fig. 10) shows that the alloys of interest are in
Fig. 10 The cu-zn diagram. The p phase is body-centered cubic; the Wphase is an ordered structure based on this arrangement
Zinc, at.%
1100
1000
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10
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20
30
50
60
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80
90
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800
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300
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20
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40
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70
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400 Zn
Zinc, wt%
Fig. 11 Typical microstructure of annealed Muntz metal (Cu40Zn). The clear, white regions are the W, and the dark and gray regions showing annealing twins are ex. Optical micrograph. 250x
OM
250X
Introduction /7
Fig. 12 Microstructures of Cu-42Zn alloy quenched from the
p region, then reheated to develop an a precipitate structure. The higher reheating temperature gives a coarser structure and thus a softer material AII{3'
OM Quenched from 800
°e
wax
(a)
White ex in {3'
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OM Quenched from 800 "C. reheated for 30 min at 400 -c (b) White ex in {3'
OM Quenched from 800 reheated for 30 min at 600 -c (e)
°e,
wax
Superalloys
Heat Treating Superalloys Superalloys are heat-resistant alloys based on nickel, iron-nickel, and cobalt-nickel that exhibit a good combination of mechanical strength and
resistance to surface degradation. Compositions of wrought and cast superalloys are listed in Tables 1 and 2, respectively.
Characteristics The high-temperature strength of all superalloys is based on the principle of a stable face-centered cubic (fcc) matrix combined with either precipitation strengthening and/or solid-solution hardening. In age-hardenable nickel-base alloys the t' intermetallic (NhAI,Ti) is generally present for strengthening, while the non-hardenable nickel-, cobalt-, and iron-base alloys rely on solid-solution strengthening of the fcc (y) matrix.
Table
Iron-base and nickel-iron superalloys may also develop, in addition to y', second-phase strengthening from the y" (NhNb) intermetallic and perhaps 11 (NirTi). Cobalt-base superalloys may develop some precipitation strengthening from carbides (Cr7C3,M23C6), but no intermetallic-phase strengthening equal to the y' strengthening in nickel-base alloys has been discovered in cobalt-base superalloys.
1 Nominal compositions of wrought superalloys UNS
Alloy
Composition, %
Number
Cr
Ni
Co
Mo
W
Nb
R30155 R30556 S63198
21.0 22.0 19.0
20.0 21.0 9.0
20.0 20.0
3.00 3.0 1.25
2.5 2.5 1.25
1.0 0.1 0.4
N06230 N06617 N06625 N06333 Nl000l Nl0003 N06635 NlOOO4 N06002 NI0276 N06075
16.0 22.0 22.0 21.5 25.0 LOmax 7.0 15.5 5.0 22.0 15.5 19.5 25.0
76.5 55.0 55.0 61.0 45.0 63.0 72.0 67.0 61.0 49.0 59.0 75.0 65.0
20.0 22.0 20.0 20.0 19.0
10.0 22.0 20.0 35.0 25.0
15.0 14.0 0.1 max 0.1 max 20.5 14.8 13.5
26.0 26.0 38.0 37.7 38.4 38.0 44.0 27.0 26.0
15.0 21.0 8.0 10.0 15.0
56.5 61.0 62.5 60.0 67.0
TI
AI
F.
C
Other
0.3
32.2 29.0 66.8
0.15 0.10 0.30
0.15 N,0.2 La, 0.02 Zr 0.50Ta, 0.02 La, 0.002Zr 1.10Mn,O.60Si
3.0 3.0max
0.03 0.10 0.07 0.05 0.05 0.05 max 0.06 0.02max 0.12max 0.15 0.02max 0.12 0.05
Solid-solution alloys
Iron/nickel-base AlloyN-155(Multimet) Haynes556 19-9DL
0.3
Nickel-base Haynes214 Haynes230 Inconel617 Alloy625 RA333 HastelloyB HastelloyN HastelloyS HastelloyW HastelloyX Hastelloy C-276 Nimonic75 Nimonic86
5.0 max 12.5 3.0 2.5 max 2.5 max 1.5max
2.0 9.0 9.0 3.0 28.0 16.0 15.5 24.5 9.0 16.0
14.0 3.6
0.2
4.5 0.35 1.0 0.2
3.0 0.5 max 0.2 0.6 3.7
2.0 0.4
0.15
2.5 18.0 5.0 5.0max 1.0 5.5 15.8 5.0 2.5
10.0
0.Q15 max B,0.02 La
omv 0.02 La 0.6V 0.25maxCu 0.03 Ce, 0.015Mg
Cobalt-base Haynes25(L605) R30605 R30l88 Haynes188 R30816 AlloyS-816 R30035 MP35-N MPI59 R30159 Precipitation-hardening alloys
50.0 37.0 42.0 35.0 36.0
4.0 10.0 7.0
15.0 14.5 4.0
3.0 3.0max 4.0
4.0 0.6
0.10 0.10 0.38
3.0
0.2
9.0
2.0 1.7 1.4 1.7 1.5 1.5 2.1 3.0 2.85
0.2 0.25 0.7 1.0 0.03 0.03 0.2 0.25 0.2
55.2 55.0 41.0 39.0 42.0 42.0 29 48.6 55.8
0.04 0.06 0.04 0.03 0.01 0.01 0.01 0.08 max 0.08max
3.4
3.5 1.3
2.9
4.7 0.5
4.4 0.2 0.5 max 5.5 0.5
<0.3 5.0 2.0 max <0.6 7.0
0.06 0.01 0.10 max 0.15 0.06
1.5Mn 0.90 La
Iron-base A-286 Discaloy Incoloy903 PyrornetCTX-I Incoloy907 Incoloy909 Incoloy925 V-57 W-545
S66286 S66220 NI9903 NI9907 N19909 N09925 S66545
15.0 16.0 13.0 13.0
1.25 3.0 0.1 0.1
3.0 3.0 4.7 4.7
2.8 1.25 1.5
0.005B, 0.3 V
0.15Si O.4Si 1.8Cu 0.D1 B, 0.5 maxV 0.05B
Nickel-base Astroloy CustomAge625PLUS Haynes242 InconellOO Inconell02
N13017 N07716 N13I00 N06102
15.0 2.5 max 15.0
5.25 8.0 25.0 3.0 2.9
3.0 (continued)
0.03 B,0.06 Zr 0.006maxB 1.0V, 0.06 Zr, 0.D15 B 0.005B,0.02Mg,0.03 Zr
12/ Heat Treater's Guide: Nonferrous Alloys
Table 1 (continued) Alloy
Incoloy901 Inconel702 Inconel706 Inconel718 Inconel721 Incone\722 Inconel725 Incone1751 InconelX-750 M252 Nimonic80A Nimonic90 Nimonic95 Nimonic100 Nimonic 105 Nimonicll5 C-263 Pyrornet860 Pyromet31 Refractaloy 26 Rem! 41 Rem! 95 Rene100 Udnnet500 Udimet520 Udimet630 Udimet700 Udimet710 UnilempAF2-lDA Waspaloy
UNS Number
N09901 N07702 N09706 N07718 N07721 N07722 N07725 N0775I N07750 N07252 N07080 N07090
N07263 N07031 N07041 N07500
N07012 N07OO1
Cr
Ni
12.5 15.5 16.0 19.0 16.0 15.5 21.0 15.5 15.5 19.0 19.5 19.5 19.5 11.0 15.0 15.0 20.0 13.0 22.7 18.0 19.0 14.0 9.5 19.0 19.0 17.0 15.0 18.0 12.0 19.5
42.5 79.5 41.5 52.5 71.0 75.0 57.0 72.5 73.0 56.5 73.0 55.5 53.5 56.0 54.0 55.0 51.0 44.0 55.5 38.0 55.0 61.0 61.0 48.0 57.0 50.0 53.0 55.0 59.0 57.0
Co
Mo
W
Nb
6.0
10.0 1.0 18.0 18.0 20.0 20.0 15.0 20.0 4.0 20.0 11.0 8.0 15.0 19.0 12.0 18.5 14.8 10.0 13.5
3.0
5.1
8.0
3.5 1.0 1.0
10.0
5.0 5.0 4.0 5.9 6.0 2.0 3.2 10.0 3.5 3.0 4.0 6.0 3.0 5.0 3.0 3.0 4.3
ComposlUoD, % Ti
2.7 0.6 1.75 0.9 3.0 2.4 1.5 2.3 2.5 2.6 2.25 2.4 2.9 1.5
1.1 3.5
3.5
1.0 3.0
6.5
1.5 6.0
1.2 4.0 2.1 3.0 2.5 2.6 3.1 2.5 4.2 3.0 3.0 1.0 3.4 5.0 3.0 3.0
AI
3.2 0.2 0.5 0.7 0.35max 1.2 0.7 1.0 1.4 1.4 2.0 5.0 4.7 5.0 0.45 1.0 1.5 0.2 1.5
3.5 5.5 3.0 2.0 0.7 4.3 2.5 4.6 1.4
Fe
C
36.2 1.0 37.5 18.5 6.5 7.0 9.0 7.0 7.0 <0.75 1.5 1.5 5.0 max 2.0 max
0.10max 0.05 0.03 0.08max 0.04 0.04 0.03max 0.05 0.04 0.15 0.05 0.06 0.15max 0.30max 0.08 0.20 0.06 0.05 0.04 0.03 0.09 0.16 0.16 0.08 0.08 0.04 0.07 0.07 0.35 0.07
1.0 0.7 max 28.9 14.5 16.0 <0.3 <0.3 LOmax 4.0 max 18.0 <1.0 <0.5 2.0max
Other
0.5 Mo, 0.2 Cu,0.4 81 2.9 (Nb + Th),0.15 maxCu 0.15maxCu 2.2Mn, 0.1Cu 0.5 Mo, 0.2 Cu,0.4 81 0.25maxCu O.25maxCu 0.005B 0.10 maxCu +B,+Zr +B,+Zr 0.005B O.04Zr O.OIB 0.005B 0.015B O.oIB 0.01 B,0.05Zr 0.015B, 0.06Zr, 1.0V O.OO5B 0.005B O.OO4B 0.03B O.OIB 1.5Th,0.015B,0.1 Zr 0.006B, 0.09Zr
Heat Treating Practice Stress relieving. This treatment frequently entails a compromise between maximum relief of residual stress and effects deleterious to hightemperature properties and/or corrosion resistance. True stress relieving of wrought material is usually, but not always, confined to non-age-hardenable alloys because a full-solution treatment is useful prior to age-hardening. In addition, the stress-relieving temperature would typically fall within the upper temperature range for age-hardening. Time and temperature cycles vary considerably, depending on the metallurgical characteristics of the alloy and on the type and magnitude of the residual stresses developed in the prior fabrication processes. Stress-relieving temperatures are usually below the annealing or recrystallization temperatures. Annealing. When applied to superalloys, annealing implies full annealing, that is, complete recrystallization and attaining maximum softness. The practice is usually applied to non-hardening wrought alloys. For most of the age-hardenable alloys, the annealing cycles are the same as for solution treating. However, the two treatments serve different purposes. Annealing is used mainly to reduce hardness and increase ductility to facilitate forming or machining, prepare for welding, relieve stresses after welding, produce specific microstructures, or soften age-hardened structures by resolution of second phases. Solution treating is intended to dissolve second phases to produce maximum corrosion resistance or to prepare for age hardening.
Most wrought superalloys can be cold formed but are more difficult to form than austenitic stainless steels. Severe cold-forming operations may require several intermediate annealing operations. Full annealing must be followed by fast cooling. . Annealing should be conducted after welding the age-hardenable alloys if highly restrained jointsare involved. For alloys sensitive to strain age cracking, heating rates must be rapid. If the configuration of the weldment does not permit annealing, aging may be used for stress relieving in alloys not prone to strain age cracking. Reheating for hot working is similar to annealing in that the aim is to promote adequate formability of the metal being deformed. Control of temperature can be critical to resultant properties, as varying degrees of recrystallization and control of grain growth may be desired. In most standard operations, heating or reheating for hot working is a full annealing step with recrystallization and dissolution of all or most secondary phases. Solution Treating. The first step in heat treating superalloys is usually solution treatment. In some wrought alloys, the solution-treating temperature will depend on the properties desired. A higher temperature is specified for optimum creep-rupture properties; a lower temperature is used for optimum short-time tensile properties at elevated temperature, improved fatigue resistance (via finer grain size), or improved resistance to notch rupture sensitivity. The higher solution-treating temperature will result in some grain growth and more extensive dissolving of carbides. The principal objective
Superalloys /13
is to put hardening phases into solution and dissolve some carbides. After aging, the resulting microstructure of these wrought alloys consists of large grains that contain the principal aging phases (y', y", 11) and a heavy concentration of carbides in the grain boundaries. The lower solution-treating temperature dissolves the principal aging phases without grain growth or significant carbide solution. For some wrought superalloys (such as Nimonic BOA and Nimonic 90), an intermediate solution-treating temperature is selected to produce a compromise of the properties. For other alloys (such as Udimet 500 and Udimet 700), the intermediate-temperature aging treatment is used to tailor the grain boundaries for improved creep-rupture properties. Quenching. The purpose of quenching after solution treating is to maintain, at room temperature, the supersaturated solid solution obtained during solution treating. Quenching permits a finer age-hardening precipitate size. Cooling methods commonly used include oil and water quenching as well as various forms of air or inert gas cooling. Internal stress resulting from quenching can also accelerate overaging in some age-hardenable alloys. Aging treatments strengthen age-hardenable alloys by causing the precipitation of additional quantities of one or more phases from the
supersaturated matrix that is developed by solution treating. Factors that influence the selection and number of aging steps and aging temperature include: • • • •
Type and number of precipitating phases available Anticipated service temperature Precipitate size The combination of strength and ductility desired and heat treatment of similar alloys
Typical heat treatments of wrought age-hardenable superalloys are given in Table 3. Because dimensional changes can occur during aging, it is recommended that finish machining be done after aging. Thermomechanical Processing. In recent years there has been more interest in the interdependence of hot working and heat-treating operations. In many critical applications the desired final properties are not attainable via heat treatment if the hot working operation has not been conducted under controlled temperature and deformation parameters. This requires a study of hot working and heat treating, known as thermomechanical processing. One application of thermomechanical process-
Table 2 Nominal compositions of cast superalloys Alloy designation
C
Ni
Cr
Co
Mo
Fe
Nomloal composition, % B A!
'Ii
111
Other
W
Nickel-base B-I900 CMSX-2 HastelloyX Inconell00 Inconel713C Inconel713LC Inconel738 Inconel792 Inconel718 X-750 M-252 MAR-M200 MAR-M246 MAR-M247 PWA1480 Ren~41 Ren~77
Ren~80 Ren~80Hf Ren~l00 Ren~N4
Udimet500 UdiJret700 Udimet710 Waspaloy WAX-20(DS)
0.10 0.10 0.18 0.12 0.05 0.17 0.20 0.04 0.04 0.15 0.15 0.15 0.15 0.09 0.07 0.17 0.08 0.18 0.06 0.10 0.10 0.13 0.07 0.20
64
66.2 50 60.5 74 75 61.5 60 53 73 56 59 60 59 bal 55 58 60 60 61 62 53 53.5 55 57.5
8 8 21 10 12.5 12 16 13 19 15 20 9 9 8.25 10 19 15 14 14 9.5 9.8 18 15 18 19.5
10 4.6 1 15
8.5 9
10 10 10 10 5.0 11.0 15 9.5 9.5 15 7.5 17 18.5 15 13.5
6 0.6 9 3 4.2 4.5 1.75 2.0 3
6 56
10.0 4.2 4 4 3 1.5 4 5.25 3 4.2
4(a) 6
18
18 7
10 2.5 0.7
0.Ql5
0.5
2
72
5.5 6 6 3.4 3.2 0.5 0.7 1 5 5.5 5.5 5.0 1.5 4.3 3 3 5.5 4.2 3 4.25 2.5 1.2 6.5
0.01 0.012 0.01 0.01 0.02
0.005 0.Ql5 0.Ql5 0.Ql5 0.01 0.Ql5 0.Ql5 0.Ql5 0.Ql5 0.004 0.03 0.005
5 0.8 0.6 3.4 4.2 0.9 2.5 2.6 2 1.5 L 1.5 3.1 3.3 5 4.8 4.2 3.5 3 3.5 5 3
8 1
1.75 4 2.6 4
1.5 3 12
12.5 10 10 4.0
4 4 4.8
0.10 6 0.06 0.1 0.1 0.1 0.1
IV 0.9Nb
0.05 0.05 0.05
INb(b)
0.04 0.03 0.02 0.06
6
1.5 20
2Nb 2Nb 0.1 Cu,5Nb 0.25 Cu,O.9Nb
1.5Hf
0.75Hf IV 0.5Nb, 0.15 Hf
0.08 0.09 1.5
Cobalt-base AiResist 13 AiResist213 AiResist215 FSX-414 Haynes 21 Haynes 25; lr605 J-1650 MAR-M302 MAR-M322 MAR-M509 MAR-M918 NASACo-W-Re S-816 V-36 WI-52 X-40 (Stellitealloy3L)
0.45 0.20 0.35 0.25 0.25 0.10 0.20 0.85 1.00 0.60 0.05 0.40 0.40 0.27 0.45 0.50
0.5 0.5 10 3 10 27
10 20 20 20 10
21 20 19 29 27 20 19 21.5 21.5 23.5 20 3 20 25 21 22
62 64
63 52.5 64
54 36 58 60.5 54.5 52 67.5 42 42 63.5 57.5
(a) B-I900 + Hf also contains 1.5% Hf. (b)MAR-M 200 + Hf also contains 1.5% Hf
0.5 0.5 1 1 1 0.5 0.5
4 3 2 1.5
2 6.5 7.5
3.4 3.5 4.3 0.010
11 4.5 4.5 7.5
0.1 0.1
O.LY 0.1 Y O.lY 5Mo
0.02 0.005
3.8 0.75 0.2
2 9 4.5 3.5 7.5
15 12 10 9 7 25 4 2 11 7.5
0.2 2 0.5 0.1 1
2Re 4Mo,4Nb,1.2Mn,O.4Si 4 Mo, 2 Nb, 1Mn, 0.4 Si 2Nb+Ta 0.5 Mn, 0.5 Si
14/ Heat Treater's Guide: Nonferrous Alloys ing is the development of direct aged Inconel718 for turbine disk applications. Proper heating temperatures and forging operations also influence the microstructure and distribution of phases in alloys such as 718. Grain Size Control. An important objective of thermomechanical processing is grain size control. For example, grain structure may be controlled by thermomechanical processing in several iron-nickel-base alloys that have two precipitates present, such as the primary strengthening precipitate (y" NbNb in Incone1 718 and t' Nij'I'i in Inconel 901) and a secondary precipitate (0 in Inconel 718 and 11 Nij'I'i in InconeI901). The secondary precipitate is produced first, by an appropriate heat treatment (8 h at 900 "C, or 1650 OF, for 901), followed by working at about 950 "C (1740 oF),
below the 11 solvus. Final working is carried out below the recrystallization temperature, and the alloy is subsequently recrystallized below the 11 solvus. Finally, the alloy is aged by standard procedures. The result is a fine-grain alloy with higher tensile strength and improved fatigue resistance. Other thermomechanical working schedules are used to produce a double necklace structure of fine grains surrounding the large grains formed during high-temperature recrystallization. Reductions of25 to 50% are needed in the [mal working operations at 1080 to 1110 "C (1975 to 2030 "F) to produce the small recrystallized grains in cast/wrought Rene 95. Further information on heat treatment is found on pp 15-16.
Table 3 Typical solution-treating and agingcycles forwrought superalloys SolutiontreaUng Thmperature
Aging
TIme,
Cooling
"C
OF
h
procedure
980 1010
1800 1850
1 2
Oilquench Oilquench
N-155 Incoloy903
1165-1190 845
2125-2175 1550
Waterquench Waterquench
Incoloy907
980
1800
Air cool
Incoloy909
980
1800
Air cool
Incoloy925
1010
1850
Air cool
2150 1975 1900
4 4
CustomAge625PLUS
1175 1080 1038
I
Air cool Air cool Aircool
Inconel901
1095
2000
2
Waterquench
Inconel625 Inconel706
1150 925-1010
2100 1700-1850
2
(b)
InconeI706(c)
980
1800
Aircool
Inconel718
980
1800
Air cool
Inconel725
1040
1900
Air cool
InconelX-750
1150
2100
2
Air cool
Nimonic80A Nimonic90
1080 1080 1065 1080
1975 1975 1950 1975
8 8
Air cool
1175 1080 1080
2150 1975 1975
1175
2150
Alloy
Thmperalure °C
TIme, OF
h
Cooling procedure
Iron-base alloys A-286 Dlscaloy
720 730 650 815 720 620 775 620 720 620 730(a) 620
1325 1350 1200 1500 1325 1150 1425 1150 1325 1150 1350(a) 1150
16 20 20 4 8 8 12 8 8 8 8 8
Furnacecool Air cool Furnacecool Aircool Furnacecool Air cool Furnacecool Air cool
845 760 720 620 790 720
1550 1400 1325 1150 1450 1325
24 16 8 8 2 24
Air cool Aircool Furnacecool Air cool Air cool Aircool
845 720 620 730 620 720 620 730(a) 620 845 705 705 705 760 845 760 845 760 845 760
1550 1325 1150 1350 1150 1325 1150 1350 1150 1550 1300 1300 1300 1400 1550 1400 1550 1400 1550 1400
3 8 8 8 8 8 8 8 8 24 20 16 16 16 24 16 24 16 24 16
Air cool Furnacecool Aircool Furnacecool Air cool Furnacecool Air cool Furnacecool Aircool Air cool Air cool Air cool Aircool Aircool Air cool Air cool Air cool Aircool Air cool Air cool
760
1400
12
Air cool
Air cool Air cool
Aircool Air cool
Nickel-base alloys Astroloy
Ren~41
Udimet500 Udimet700 Waspaloy
4
Aircool Air cool Air cool
4 4 4
Air cool Air cool Air cool
\12
Cobalt-base alloys S816
(b)
Note:Alternatetreatments may be used to improvespecificproperties. (a) If furnace size/loadprohibitsfast heatup to initialage temperature, a controlledramp up from590 to 730°C (1100to 1350oF) is recommended. (b) Toprovideadequatequenchingaftersolutiontreating, it is necessaryto cool belowabout540°C (1000oF) rapidlyenoughtopreventprecipitation in theintennediatetemperature range. For sheetmetalpansofmostalloys,rapidaircoolingwillsuffice. Oilor waterquenchingisfrequently requiredforheaviersectionsthatare notsubjecttocracking. (c)HeattreatmentofInconel706to enhance tensilepropertiesinsteadof creepresistancefor tensile-limited applications
SuperaUoys /15 Table 4 Constituents observed in superalloys Phase
y'
Crystal sInIcture
fcc (ordered Lh)
Lattke pal'IIII1e1er. DID
Formula
0.3561for pureNhAI to 0.3568 for
NhAl Nh(AI,TI)
Principal strengthening phasein manynickel-andnickel-iron-basesuperalloys; crystallattice
NhTI(nosolubilityfor otherelements)
varies sligbtlyin size(0to0.5%)fromthatofaustenite matrix;shapevariesfromspherical to cubic;sizevarieswithexposuretimeandtemperature. Gammaprime is spherical in ironnickel-base and insomeoftheoldernickel-base alloys, suchasNirnonicSOA andWaspaloy. In themorereeentlydeveloped nickel-base alloys,y' is generally cuboidal. Experiments have shownthatvariations inmolybdenum contentandin thea1uminumltitaniumrntiocan change themorphology ofy.Withincreasingyly'mismatch, theshapechangesin thefollowing order: spherical, globular, blocky,cuboidal. Whentheyly' latticemismatch is high,extended exposureabove700"C (1290"F) causesundesirablen(NiJTI) or li(Ni]Nb)phases to form. Foundin iron-,cobalt-, andnickel-base superalloys withhigbtitaniumlaluminumratios after extendedexposure; mayformintergranularly in a cellularformor lntragranularly asacicular
Ni3(A1051105)
a., = 0.5093
Co = 0.8276
Commeols
~~~tsinaWidmansm~n~~
bet(ordered DOn)
ao=0.3624 eo= 0.7406
NiJNb(li)
Onhorhombic (ordered Cu3TI)
MC
Cubic
ao=0.5106-0.511 bo=0.421-0.4251 Co = 0.452-0.4556 ao= 0.430-0.470
MZJQ;
fcc
M6C
fcc
ao= 1.050-1.070 (varieswith composition) ao= 1.085-1.175
Hexagonal
ao= 1.398 Co = 0.4523 ao= 0.560-0.620 Co = 0.300-0.330
Tetragonal
MN
Cubic
ao=0.424O
Rhombohedral
ao= 0.475 Co =2.577 ao= 0.475-0.495 Co = 0.770-0.815
Laves
Hexagonal
(J
'Ietragonal
Principal strengthening phasein Incone1718: y" precipitates arecoherentdisk-shapedparticles thatformonthe (100I planes(avgdiamapproximately 600 A, thickness approximately 50to 90 A); Bright-field TEMexamination isunsatisfactory forresolvingy" due to thehigbdensity of theprecipitates andthestrongcontrastfromthecoherency strainfieldaroundthe precipitates. However, dark-field TEMexarnination provides excellentimagingofthey" by selective imagingofprecipitates thatproducespecific superlattice reflections. In addition, t" can beseparated fromt' usingthedark-field mode,hecausethey" dark-field imageis substantially brigbterthanthatofy ', Observed in overaged Incone1718; has an acicularshapewhenformedbetween815and980°C NiJNb (1500and 1800oF); formsbycellularreactionat lowagingtemperatures andby intragranular precipitation at higbagingtemperatures TIC TItanium carbidehas somesolubility fornitrogen, zirconium, andmolybdenum; composition is NbC variable; appearsasglobular, irregularly shapedparticles thataregrayto lavender; "M" HfC elements canbe titanium, tantalum, niobium, hafnium, thorium, or zirconium Cr23Q; (Cr,Fe,W,Mo)nQ; Fonn ofprecipitation is important; it canprecipitate asfilms,globules, platelets.lamellae, and cells;usuallyformsat grainboundaries; 'M" elementis usually chromium, but nickel-cobalt, iron,molybdenum, andtungsten cansubstitute Randomly distributed carbide;mayappearpinkish;"M"elements aregenerally molybdenum or FeJM03C tungsten; Ihereissomesolubility forchromium, nickel-niobium, tantalum, andcobalt FC:JW3C-FelW2C Fe.JNb3C Nb3Co3C Ta3CoJC o-c, Generally observedas ablockyintergranular shape;observed onlyin alloyssuchasNirnonic 80Aafterexposureabove1000°C(1830oF), andinsomecobalt-base alloys Observed in iron-nickel- andnickel-base alloyswilhabout0.03%B orgreater;boridesappear Th3B2 similartocarbides, butarenotallackedbypreferential carbideetchants; "M' elementscanbe V3B2 molybdenum, tantalum, niobium, nickel,iron,orvanadium Nb3B2 (Mo,TI,Cr,Ni,Fe)JB2 M02FeB2 TIN Nitrides areobservedin alloyscontaining titanium, niobium, orzirconium; theyareinsoluble at (Ti,Nb,Zr)N temperatures belowIhemeltingpoint;easilyrecognized as-polished, havingsquareto m,Nb,Zr) (C,N) rectangular shapesandrangingfromyellowtoorange ZrN NbN Generally observed inalloyswilhhighlevelsofmolybdenum ortungsten; appearsascoarse, ColW6 (Fe,Co)J(Mo,Wl6 irregularWidmanstii~n platelets; formsat higbtemperatures Mostcommonin iron-base andcobalt-base superalloys; usuallyappears asirregularly shaped Fe.JNb Feill globules, oftenelongated, or asplatelets afterextended high-temperature exposure Fe2Mo C02Ta NhNb
ColTi
ao= 0.880-0.910 Co = 0.450-0.480
FeCr FeCrMo CrFeMoNi
oce
Mostoftenobservedin iron-and cobalt-base superalloys,less commonly in nickel-base alloys; appears as irregularly shapedglobules, oftenelongatedtforms afterextendedexposure between 540and980°C(1000to 1795 OF)
CrNiMo
Table 5 Typical effects of aging on room-temperature mechanical properties of solution-treated heat-resisting alloys Yield strength (0.2% olf..O Alloy A-286 Ren~41
X-750 Haynesalloy25
Notaged MPa ksI 240 620 410 480
35 90 60 69
Aged MPa
ksi
760
110
1100
160 92 70
650 480
Elongation in 50 mm(2ln.l, % Notaged Aged 52 45 45 55
33 15 24 45
Table 6 Minimum mill annealing temperatures for solid-solution-strengthened alloys Approximate minimum temperature formillllDIlOllling Alloy HastelloyX HastelIoyS AUoy625 RA333 Inconel617 Haynes230 Haynes188 AUoyL-605 AlloyN-155 Haynes556
·C
1010 955 925 1035 1035 1120 1120 1120 1035 1035
OF
1850 1750 1700 1900 1900 2050 2050 2050 1900 1900
16/ Heat Treater's Guide: Nonferrous Alloys
Table 7 Typicalsolution annealing temperatures for solid-solution-strengthened alloys '!)pioal solulionannealing temperatures
Alloy
HastelloyX Hastelloy S AIIoy625 RA333 Inconel617 Haynes230 Hayoes188 AIIoyL-605 AIIoyN-155 Hayoes556
1165-1190 1050-1135 1095-1205 1175-1205 1165-1190 1165-1245 1165-1190 1175-1230 1165-1190 1165-1190
2125-2175 1925-2075 2000-2200 2150-2200 2125-2175 2125-2275 2125-2175 2150-2250 2125-2175 2125-2175
Table 8 Cooling rate effects on time to 0.5% creep at 870°C (1600 OF) with 48 MPa (7 ksi) load Solutionlreal al1175 "C (2150oF) and 0001 al the rate indiealed
'IbneloO.51l> ereep,h Haynes HastelJoyX 188
Waterquench. Aircool Furnacecool 10650°C (1200oF)andthenaircool
8 7 6
148 97 48
lnconel 617
302 15 9
Table 9 Typical heat treatments for precipitation-strengthened cast superalloys Alloy
Heal treatmenl (temperature/duration In bJ<:ooHng)(a)
PolycrystalUne (conventional) castings B-19OO1B-I900+Hf IN-l00 1N-7l3 1N-7l8 1N-718 withHIP
1080°C (1975°F)/4/AC + 900°C (1650°F)/lO/AC 1080°C (1975°F)/41AC + 870°C (1600°F)/I21AC
as-cast 1095°C (2000°F)/l/AC +955°C (1750°F)/l/AC +720°C (1325°F)/81FC+ 620°C (1150°F)/8/AC 1150°C (2100°F)/41FC+ 1190°C(2175°F)/4115 ksi (HIP) + 870°C(16OO °F)/I01AC+955 °C(1750°F)/l/AC+ 730°C (13500F)/8/FC + 665°C (1225°F)/81AC 1120°C (2050°F)/2/AC + 845°C (1550°F)/24/AC 1120°C (2050°F)/4/RAC + 1080°C (1975°F)/4/AC+ 845°C (1550°F)/241AC 1160°C (2120°F)/4/RAC + 1000°C (1830°F)/6IRAC + 900°C (1650°F)/241AC + 700°C(1290°F)/I61AC 1220°C (2230°F)/2/AC + 870°C (1600°F)l24/AC 1080°C (1975°F)/4/AC+ 870°C (16OO°F)l2O/AC 1065°C (1950°F)/3/AC + 1120°C (2050°F)/1.5/AC + 900°C (1650°F)/4/AC 1163°C(2125°F)/41AC+ 1080°C(1975°F)/4/AC + 925°C(1700°F)l24/AC+760°C (1400°F)/I61AC 1220°C (2225°F)/2/GFQ + 1095°C (WOO °F)/41GFQ + 1050°C(1925°F)/41AC + 845°C (1550°F)/I61AC 1150°C(2100°F)/4/AC + 1080°C(1975°F)/4/AC+ 760 °C(1400°F)/l6IAC 1175°C (2150°F)/41AC + 1080°C(1975°F)/4/AC+845°C(1550°F)/24/AC+760°C (1400°F)/I61AC 1080°C (1975°F)/41AC + 845°C (1550°F)/4/AC+760°C (1400°F)/l6IAC
1N-738 1N-792 1N-939 MAR-M246+Hf MAR-M247 Rene! 41 Rene! 77 Rene! 80 Udimet500 Udirnet700 Waspaloy Directionally-solidified (DS)castings DSMAR-M247 DSMAR-M200+Hf DSRene!80H Single-crystal castings CMSX-2 PWA1480 Rene!N4
1230°C (2250°F)/2/GFQ +980 °C (1800°F)/5/AC + 870°C (1600°F)/20/AC 1230°C (2250°F)/4/GFQ + 1080°C (1975°F)/4/AC+ 870°C (1600°F)/321AC 1190°C (2175°F)/2/GFQ+1080°C (1975°F)/4/AC+ 870°C (1600°F)/I61AC 1315°C (2400°F)/3/GFQ + 980°C (1800°F)/5/AC + 870°C (1600°F)/20/AC 1290°C (2350°F)/41GFQ+ 1080°C (1975°F)/41AC + 870°C(1600°F)/321AC 1270°C (2320°F)/2/GFQ + 1080°C (1975°F)/4/AC+ 900°C (1650°F)/l6IAC
(a) AC.aircooling; Fe. furnace cooling;GFQ.gas furnacequench.; RAC.rapidaircooling
Table 10 Typical heat treatments for solid-solution-strengthened cast superalloys Alloy
HastelloyC HastelloyS HastelloyX Inconel6OO Incone1625 FSX-414 MAR-MS09 Wi-52 X-40
HeallrealmeDl
1220°C(2225°F)/O.5 Wair cool 1050°C(1925°F)/1h. aircool As-cast As-cast 1190°C(2175°F)/1Waircool 1150°C(2100°F)/4/h. furnacecool+980 °C(1800°F)/4h.lfumace cool As-cast As-cast As-cast
Nickel·Base Alloys Astroloy Chemical Composition. Astroloy (nominal). 15.00 Cr, 56.50 Ni, 15.00 Co, 5.25 Mo, 3.50 Ti, 4.40 AI, <0.30 Fe, 0.06 C, 0,03 B, 0.06 Zr
1. Aging. Treatment is at 845°C (1555 oF) for 24 h; aircooling is used 2. Aging. Treatment is at 760°C (1400"F) for 16h; aircooling is used
Characteristics A nickel-base, precipitation-hardeningalloy
Recommended Heat Treating Practice In solution heat treating and in aging, alternative treatments areavailable:
1. Solution Heat Treating. Treatment is at 1175 °C (2145 "F) for 4 h; air cooling is used 2. Solution Heat Treating. Treatment is at 1080 °C (1975 "F) for 4 h; air cooling is used
Stress Relieving. Full annealing is recommended because intermediate temperatures cause aging Annealing. Treatment is at 1135 °C (2075 OF). Holding time is 4 h per inch of section Astroloy: Microstructure. Forging, solution annealed 4 h at 1150 -c (2100 OF), air cooled, aged 4 h at 1080 °e (1975 OF), oil quenched, aged 4 h at 845 "O (1555 OF), air cooled, aged 16.h at 760 °e (1400 OF), and air cooled. Kalling's reagent 2. 100x
Astroloy: Microstructure. Forging, solution annealed 1 h at 1150 "O (2100 OF) and air cooled, showing grain boundaries and fine Me carbides in a y-phase matrix. Kalling's reagent 2. 100x
Astroloy: Microstructure. Forging, solution annealed 1 h at 1150 "O (2100 OF) and air cooled, showing a clean grain boundary (diagonal). t' precipitate is visible in the y matrix. Electrolytic: H2S04 , H3P04 , and HN03 • 10,OOOx
Astroloy: Microstructure. Forging, solution annealed 4 h at 1150 -c (2100 OF), air cooled, aged 4 h at 1080 -c (1975 OF), oil quenched, aged 4 h at 845 "C (1555 OF), air cooled, aged 16 h at 760 "C (1400 OF), and air cooled. Me carbides are precipitated at grain boundaries; the solid-solution matrix contains y' particles. Kalling's reagent 2. 1000x
Next Page 18/ Heat Treater's Guide: Nonferrous Alloys
Astroloy: Microstructure. Forging, solution annealed 4 h at 1150 °C (2100 OF), air cooled, aged 4 h at 1080 °C (1975 OF), oil quenched, aged 4 h at 845°C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Microstructure shows intergranulary' precipitated at 1080 °C (1975 OF) as well as fine y' precipitated at 845°C (1555 OF) and 760 °C (1400 OF). Carbide particles are visible at grain boundaries. Electrolytic: H2S0 4 , Ha P0 4 , and HNO a. 10,OOOx
Astroloy: Microstructure. Forging, solution annealed 4 h at 1115 °C (2040 OF), air cooled, aged 8 h at 870°C (1600 OF), air cooled, aged 4 h at 980°C (1795 OF), air cooled, aged 8 h at 650 °C (1200 OF), air cooled, aged 8 hat 760°C (1400 OF), and air cooled. The y matrix contains some undissolved y'. High magnification delineates MC carbides (large, white particles) and undissolved y' (small, white particles). Kalling's reagent 2. 1000x
Astroloy: Microstructure. Forging, solution annealed 4 h at 1115 °C (2040 OF), air cooled, aged 8 h at 870°C (1600 OF), air cooled, aged 4 h at 980°C (1795 OF), air cooled, aged 8 h at 650 °C (1200 OF), air cooled, aged 8 h at 760°C (1400 OF), and air cooled. The y matrix contains some undissolved y'. Kalling's reagent 2. 100x
Astroloy: Microstructure. Forging, solution annealed 4 h at 1115 °C (2040 OF), air cooled, aged 8 h at 870°C (1600 OF), air cooled, aged 4 h at 980°C (1795 OF), air cooled, aged 8 h at 650 °C (1200 OF), air cooled, aged 8 h at 760°C (1400 OF), and air cooled. The y matrix contains some undissolved t' and shows M2aC s carbides (white, irregular) and t' precipitates. Electrolytic: H2 S0 4 , HaP0 4 , and HNOa. 10,000x
Previous Page
Nickel-Base Superalloys /19
D.. 979 Chemical Composition D·979 (UNS N09979) (nominal). 15.00 Cr, 45.00 Ni, 4.00 Mo, 3.00 Ti, 1.00 Ti, 27.00 Fe, 0.05 C, 0.01 B
Characteristics A nickel-base, precipitation-hardening alloy
Similar Alloys (U.S. and/or Foreign). UNS N09979
In 100 Chemical Composition. IN 100 (UNS N13100) (nominal). 10.00 Cr, 60.00 Ni, 15.00 Co, 3.00 Mo, 4.70 Ti, 5.50 AI, <0.6 Fe, 0.15 C, 1.00 V, 0.06 Zr, 0.Q15 B
Characteristics A nickel-base, precipitation-hardening alloy
Similar Alloys (U.S. and/or Foreign). UNS N13100
IN 100: Microstructure. As cast. Small, white islands are primary (eutectic) y'; peppery gray constituent is precipitated y'; black constituent is probably perovskite, a complex carbide. Ni3(AI,Ti)C; matrix is nickel-rich y. Marble's reagent. 100x
IN 100: Microstructure. As cast. Shown at higher magnification. Light constituent (A) is primary (eutectic) t'. dark (8), probably perovskite, Ni3(AI,Ti)C. Dispersed carbide particles are shown at C. Gamma matrix contains precipitated (D). Marble's reagent.
IN 100: Microstructure. As cast. The white islands are primary, or eutectic, y'. Precipitated t' is barely visible in the y matrix. Marble's reagent. 100x
20 I Heat Treater's Guide: Nonferrous Alloys
IN 100: Microstructure. As cast. Shown at higher magnification and a replica electron micrograph showing islands of primary t' (A), a large particle of primary carbide (8), and dispersed particles of precipitated t' in ymatrix. Marble's reagent. 5000x IN 100: Microstructure. As cast. Shown at higher magnification. Island of primary (eutectic) 't' (A), dispersed carbide (8), and precipitated t' in y matrix. Marble's reagent. 500x
IN 100: Microstructure. Casting, held at 760°C (1400 OF) for 5000 h. Replica electron micrograph. Platelets of o and primary and precipitated t' in y matrix. HCI, ethanol, and H20 2. 4500x
IN 100: Microstructure. Casting, held at 815°C (1500 OF) for 5000 h. Structure consists of massive MC particles, platelets of o phase, and primary and precipitated y' in the y matrix. HCI, ethanol, and HP2· 500x
Nickel-Base Superalloys /21
IN 100: Microstructure. Casting, held at 815°C (1500 OF) for 5000 h. Replica electron shows a massive particle of MC, Widrnanstatten platelets of (J phase, and t' in the y matrix. HCI, ethanol, and H20 2. 4500x
IN 100: Microstructure. Casting, held at 925°C (1695 OF) for 36 h. Replica electron micrograph. No (J formed at this temperature. The structure is grain-boundary carbide and t' in the y matrix. HCI, ethanol, CuCI2, and HP2' 4500x
IN 100: Microstructure. Casting, held at 925°C (1695 OF) for 5000 h. Replica electron micrograph. No o formed at this temperature. The structure is grain-boundary M23C a and y' in the y matrix. HCI, ethanol, and H20 2. 4500x
IN 100: Microstructure. Casting, held at 1040 °C (1905 OF) for 16 h. A replica transmission electron micrograph. Note the absence of (J phase in this structure and the presence of coarsened y' in the y matrix. HCI, ethanol, CuCI2, and H20 2. 4500x
IN 100: Microstructure. Casting, creep-rupture tested at 815°C (1500 OF) for 1113.6 h at 276 MPa (40 ksi). The structure consists of WidmansW.tten (J phase (A), primary (eutectic) t' (8), precipitated y' (C), and particles of carbide (D), in the y matrix. Glyceregia. 500x
22/ Heat Treater's Guide: Nonferrous Alloys
IN 100: Microstructure. Casting, held at 1040 °C (1905 OF) for 5000 h. A replica transmission electron micrograph. Structure consists of blocky y' and fine precipitated t' in a matrix of y solid solution. HCI, ethanol, and H202. 4500x
IN 100: Microstructure. Casting, held at 1095 °C (2000 OF) for 5000 h. Optical micrograph shows random dispersion of large and small islands ofy' in theymatrix. HCI, ethanol, and HP2' 500x
IN 100: Microstructure. Casting, creep-rupture tested at 815°C (1500 OF) for 1113.6 h at 276 MPa (40 ksi). The structure consists of Widmanstatten 0' phase (A), primary (eutectic) t' (8), precipitated y' (C), and particles of carbide (D), in the ymatrix. Higher magnification and a replica electron micrograph shows platelets of 0' emerging from carbide and precipitated t' in the y matrix. Electrolytic etch: H2S0 4 and methanol. 10,OOOx
IN 100: Time-temperature-oxidation diagram. Summary of main stages of oxidation. Nominal composition: Ni - 15% Co - 10% Cr - 5.5% AI 4.7% Ti - 3% Mo - 0.95% V
NI-15Co-1OCr-5.5Al-4. 75TI-3Mo-0. 95V AS CAST NUMERATOR DENOMINATOR
= =
PHASES PRESENT IN SCALE PHASES PRESENT IN SUBSCALE
LIVE GRAPH Click here to view
-
-1-- _ _
-... ....... -,
1600 -
NiO + T102
I
\. (Nl, Co)O+(NICo)C r204+NITI0~
\
I
I
Air + TI02 + TiN
1400 ' - - - -.......---~:----~--~~---'-':-"--~ 103 10 4 10 5 10 1 TIME - MIN
Nickel-Base Superalloys /23
IN 100: Time-temperature diagram. Minor phase concentration as a function of aging temperature. Composition: Ni - 0.17 C - 10.30% Cr -14.30% Co - 2.89% Mo - 4.73% Tl - 5.79% AI0.016% B - 0.076% Zr - 0.93% V. Treatment: Solution treated as cast, aged at 760 to 1205 °C (1400 to 2200 OF) for varying times
VA NI-15Co-1OCr-5. 5AI-4. 75T1-3Mo-0. 95V AS CAST + AGE AS INDICATED
MC
--
M23C6
<,
-----
A
VR - VERY RARE M
f--
R-RARE M- MEDIUM A -ABUNDANT VA - VERY ABUNDANT
/
R
."..-
\ \
\
,
\
'M3Bz <,
1400F 96HR
1500F 72HR
1600F 4811R
"
1700F 36HR
I
1800F 24HR
2000F 8HR
1900F 16HR
2100F 6HR
2200F 2HR
AGING TIME AND TEMPERATURE
Nl-15Co-10Cr-6. 5A1-4. 76TI-3Mo-0. 96V AS CAST. Nv. 2.60 (AV ELECTRON VACANCY DENSITY) EXPOSED 5000 HR AT TEMP INDICATED
VR - VERY RARE M - MEDIUM V A - VERY ABUNDANT R - RARE A -ABUNDANT
VA
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1600 1800 EXPOSURE TEMP - F
2000
IN 100: Time-temperature diagram. Minor phase concentration as a function of temperature for long exposure times. Composition: Ni 0.17% C - 10.30% Cr - 15.00% Co - 2.93% Mo 4.68% Ti - 5.53% AI - 0.016% B - 0.082% Zr 0.94% V. Treatment: Solution treated as cast, aged in air at 760 to 1095 °C (1400 to 2000 OF) at 38°C (100 OF) intervals for 5000 h, and at 1150 °C (2100 OF) for 2000 h
24/ Heat Treater's Guide: Nonferrous Alloys
IN 100: Time-temperature-transformation diagram. Transformation to sigma phase for as-cast and forged alloy for two levels of electron vacancy concentration. Nominal composition: Ni 15% Co-10% Cr- 5.5%AI- 4.7% li -3% Mo - 0.95% V Nl-15Co-1OCr-5. 5Al- •• 75T1-3Mo-0. 95V (NOMINAL) ACTUAL COMPOSITION FOR 2 LEVELS OF NY MED NV (2••9):Nl-lS.3Co-l0.UCr-5.5Al-f.29T13. 55Mo-O. B6V IIIGH Nv (2.65)INl-lS.3Co-l0.12Cr-5.W-f.69 3.51Mo-O.97V ALL ALLOYS MADE FROM SAME KASTER HEAT. ADDmONS OF Al AND T1 MADE DURING CASTING TO ACIUEVE DESIRED LEVEL OF ELECTRON VACANCY CONCENTRATION (Nv) TESTED AS CAST OR FORGED TO PANCAKE IN FOLLOWING STEPSI 1. EXTRUSION AT 2050F FROM 5 IN DIA INGOT TO 3 1/9 IN STEEL PIPE 2. FLATTENED AT 2050F TO 13/. IN DIA PANCAKE 3. FLATTENED AT 2050F TO 1 IN DIA PANCA •• FLATTENED AT 2050F TO 5/8 IN DIA PANCAKE TEST SPECIMEN 1/. IN DIA BAR x 1 1/. IN GAGE LENGTH EXPOSED WITHOur STRESS FOR TIMES AND TEMP SHOWN
IN 100: Time-temperature-precipitation diagram. Relation for the onset of sigma phase precipitation for medium and high electron vacancy compositions, and in fine and coarse-grain size structure. Nominal composition: Ni - 15% Co -10% Cr - 5.5% AI - 4.7% TI· 3% Mo - 0.95% V
LIVE GRAPH
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----FORGED
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Nl-15Co-1OCr-5. 5Al- •• 7T1-3Mo-o. 95V(NOMINAL) ACTUAL COMPOSITION FOR TWO "LEVELS OFNv MEDIUM l'lv(2••9)1 Nl-13.3Co-l0.UCr5.5Al-•• 29T1-3. 55Mo-0. B6V mGH NV(2.65): Nl-13.3Co-l0.12Cr-5.6Al.. 69'1'1-3. G1Mo-0. 97V ALL ALLOYS MADE FROM SAME MASTER HEAT. ADDIT.IONS OF AlIoTl MADE DURING CASTING TO ACHIEVE DESIRED LEVEL OF ELECTRON VACANCY CONCENTRATION Rv COARSE GRAIN ALLOYS PREPARED BY . NORMAL INVESTMENT CASTING PlIOOEDUREll; FINE GRAIN ALLOYS PREPARED BY MOLD DlNOCULATION 'rE;T SPECIMEN 1/. IN DIA x 11/. IN GAGE LENGTH EXPOSED WITHOUT STRESS FOR TIMES AND TEMPERATURES INDICATED ~GHNV _ ~ MEDIUMNv
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1000 TIME - HR
10,000
IN 100 (Modified): Time-temperature-precipitation diagram. Start of sigma phase. PM modified versions of IN 100 (Alloy 3) and AF-2IDA (Alloy 5) vs. conventional wrought. IN 100 Nb-modified (PM), composition: Ni - 11.9% Cr - 17.7% Co - 3.3% Mo - 5.2% AI- 4.2% Ti - 1.4% Nb - 0.24% B - 0.06% Zr - 0.09% C. IN 100 Nb-modified (CE), composition: Ni -12.1% Cr-17.4% Co - 3.2% Mo - 5.3% AI4.4%Ti - 1.5% Nb - 0.028% B - 0.06% Zr - 0.08% C. AF-2-1 DA NbC-modified (PM), composition: Ni -12.1%Cr-10.0%Co- 5.7% W -2.9% Mo-4.8%AI-3.1% Ti-1.5% Nb-1.5% Ta-0.018% B-0.08% Zr - 0.09% C. AF-2-1DA Nb-C-modified (CE), composition: Ni12.0% Cr - 10.3% Co - 5.5% W - 2.9% Mo - 4.7% AI- 2.9% Tl - 1.4% Nb - 1.6% Ta - 0.020% B - 0.11% Zr - 0.09% C. PM, powder metallurgy; CE, cast and extruded. Treatment: Both PM and CE materials were given identical heat treatments, which consisted of a partial gamma prime solution treatment at temperatures 20 °C (70 OF) below the gamma prime solvus for 2 h, followed by cooling in air, a carbide-stabilizing heat treatment at 980 °C (1795 OF) for 8 h, followed by an air cool, and a gamma prime precipitation cycle of 760 °C (1400 OF) for 8 h. To observe the formation of sigma phase the heattreated specimens were exposed to temperatures from 708 to 980 °C (1300 to 1795 OF) for various times in argon
Next Page
Nickel-Base Superalloys /25
IN 100: Time-temperature-transformation diagram. Shows start of sigma phase formation. Composition: Ni - 0.18% C -14.26% Co10.26% Cr - 2.97% Mo - 5.35% Ti - 5.60% AI - 0.30% Fe - 0.92% V - 0.012% B - 0.05% Zr
1800
1----------;
/700
1------------11700'F/20,oOO P.S.I. 2056.1 HOURS
t
1600
I--------,L----l------------I------------l
/500
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Compilation of phaaes found in IN-IOO
Phases present
TIC (J
M23C6 M6C M6C'
Ascast
4.30A Strong N.D.(a)
1O.67A Veryweak II.OIA Veryweak 1O.92A Very weak
/0.000 TIME (HOURS I -
As-cast + 1800°F/13,OOO psi, 1592.7b
As-east + 1700°F/20,OOO psl 2056.1b
As-east + 1500°F/50,OOO psl, 769.3b
As-east + 1350°F/70,OOO psi, 1827.1b
4.31A Weaktomoderate weak c=4.62A a=8.84A da=O.S2 Very weak 1O.71A Strong N.D.
4.31A Moderate c=4.60A a=8.8SA da=O.S2 Weak 1O.71A Strong N.D.
4.31A Strong c=4.59A a=8.8SA da=O.52 Moderate strong 1O.71A Moderate strong 11.06A Very weak 1O.98A Weak
4.31A Strong c=4.S8A a=8.83A da=O.S2 Moderate 1O.68A Moderate
?(b)
?
(a)Not detected. (b)Presenceor absencequestionable.
IN 102 Chemical Composition. IN 102 (UNS N06102) (nominal). 15.00 Cr, 67.00Ni, 2.90 Mo, 3.00 W, 2.90 Nb, 0.50Ti, 0.50 AI, 7.00 Fe, 0.06 C, 0.0005 B, 0.02 Mg, 0.03 Zr
Similar Alloys (U.S. and/or Foreign). UNS N06102
Characteristics A nickel-base, precipitation-hardening alloy
Previous Page 26/ Heat Treater's Guide: Nonferrous Alloys
Incoloy 901 and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from solid treating or annealing temperatures does not suppress the aging treatment for some alloys, such as Astroloy. They become harder and stronger
Chemical Composition.lncoloy 901 (UNS N09901) (nominal). 12.50 Cr, 42.50 Ni, 6.00 Mo, 2.70 Ti, 36.20 Fe, 0.10 C max
Similar Alloys (U.S. and/or Foreign). UNS N09901
Characteristics A nickel-base, precipitation-hardening alloy
Incoloy 901: Effectof grain size on the high-cycle fatigue properties at 455°C (850 OF)
Recommended Heat Treating Practice
455°C(850 oF) Fatigue strength (10'cycles)
Stress Relieving. Full annealing is recommended, because intermediate Incoloy901
temperatures cause aging
Annealing. Treatment is at 1095 °C (2000 OF). Holding time is 2 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperatures to prevent precipitation ofhardening phases; water quenching is preferred; and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching is adequate
Fatigue ratio (FS!UTS)(a)
gralnsize
MPa
ksl
AS1M2 AS1M5 AS1M12
315 439 624
64
46
0.32 0.42 0.55
91
(a) FSIlITS. fatiguestrengthto ultimatetensilestrength
Incoloy 901: Effectof stabilization on typical properties Elongation in
Thsted at 20 °C (70 oF) No intennediateaging(a): HeatA HeatB Withintennediateaging(b): HeatA HeatB Thsted at 650°C (1200 oF) No intermediate aging(a): HeatA HeatB Withintermediate aging(b): HeatA HeatB
Yield strength
Ullimate tensile strength MPa ksi
MPa
ksi
(2 In.), %
Reduction in area, %
1050 1080
152 157
790 790
115 114
12 17
13 16
1040 1040
151 151
730 710
106 103
12 12
15 13
SOmm
Creep-rupture Iire,h
1.0
76 118
1.5
11 7
45 54
(a) Heat treatment:1120°C (2050 "P) for 2 h. waterquench;745°C (1375 oF) for 24 h, air cool.(b) Heat treatment: 1120°C (2050 "P) for 24 h, waterquench;815°C (1500 oF), 4 h; air cool;745°C (1375 "F), 24 h; air cool
Incoloy 901 : Tensile properties at 540°C (1000 OF) at various locations in disk forgings in two heat-treated conditions Conditlon
'lestlocation
Yield strength ksi MPa
Ultimate tensile strength
Elongalion in SO Reduction in
MPa
ksi
mm (2 In.), %
area,%
1095°C (2000"F) for2 h, waterquench+790°C (1455"F) for2 h, water quench+ 730°C (1345 OF)for 24 h. aircool
Rim-radial-top Rim-tangent-middle Web-radial-top Web-tangent-middle Bore-radial-top Bore-tangent-middle
772 772 781 772 782 772
112.0 112.0 113.2 112.0 113.4 112.0
1037 1048 1049 1041 1045 1027
150.4 152.0 152.1 151.0 151.6 149.0
13 12 13 14 13 14
18 18 21 21 20 22
1010°C (1850oF) for 2 h. waterquench+ 730°C (1345 oF) for20 h, water quench+650 °C (1200 oF) for 20 h, aircool
Rim-radial-top Rim-tangent-middle Web-radial-top Web-tangent-middle Bore-radial-top Bore-tangent-middle
832 910 853 876 855 876
120.6 132.0 123.7 127.0 124.0 127.0
1066 1117 1091 1089 1069 1105
154.6 162.0 158.2 158.0 155.0 160.2
14 17 20 19
27 38 39 39 30 38
17 17
Nickel-Base Superalloys /27
210
30
Temperature, ·F 570 750
390
1110
930
Incoloy 901: Effects of temperature and grain size on tensile properties of forgings in the solution-treated, stabilized, and aged condition. AC, air cooled
1290
1500 0955 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC 1400 ~-- .980 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC l> 1095 ·C/1 h/AC + 720 ·C/4 h/AC + 650 ·C/12 h/AC 1300
ASTM grain size 12 5
-----1200
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200
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Incoloy 901 : Tensile properties at various locations in disk forgings in two heat-treated conditions Condition 1095°C (2000·f) for 2 h. waterquench+ 790°C (1445of) for 2 h.water quench + 730°C (1345of) for 24 h. aircool
1010°C(1850 °f)for2h. waterquench+ 730"C (1345Of)for 20 h. water quench + 650°C (1200of) for20 h. aircool
ThsItocation
Yield strength MPa ksi
Ultimate tensile streng1h MPa ksi
Rim-radial-top Rim-radial-boltom Rim-radial-middle Rim-axial-middle Rim-tangent-middle Bore-radial-top Bore-radial-bottom Bore-radial-middle Bore-axial-middle Bore-tangent-middle
859 907 880 858 883 874 889 869 840 859
124.6 131.6 127.6 124.4 128.0 126.8 129.0 126.0 121.8 124.6
1178 1168 1179 1054 1175 1200 1131 1172 1154 1167
170.8 169.4 171.0 152.9 170.4 174.0 164.0 170.0 167.4 169.2
Rim-radial-top Rim-radial-bottom Rim-radial-middle Rim-axial-middle Rim-tangent-middle Bore-radial-top Bore-radial-bottom Bore-radial-middle Bore-axial-middle Bore-tangent-middle
924 952 980 972 986 978 976 968 940 965
134.0 138.0 142.0 141.0 143.0 141.9 141.6 140.4 136.4 140.0
1234 1240 1258 1255 1274 1248 1255 1252 1081 i253
179.0 179.8 182.4 182.0 184.8 181.0 182.0 181.6 156.8 181.8
Elongation in SO Reduction in area, % mm(2 In), % 15 13 15
16 14 17
13 14
17 17
16
20
15
17
17 17 19 21 18 18 20 21 5 20
20 21 29 31 25 24 31 34
9 31
28/ Heat Treater's Guide: Nonferrous Alloys
Incoloy 901: Microstructure. Solution annealed 2 h at 1065 °C (1950 OF), water quenched, aged 2 h at 800°C (1470 OF), air cooled, aged 24 h at 730°C (1345 OF), and air cooled. The grainboundary constituents (MC, Ma82 , or both) contributed to low ductility, Note the grain-boundary depleted zone, The y matrix contains t' precipitate. Electrolytic: H2S04 , HaP04 , and HNOa. 10,OOOx
Incoloy 901: Microstructure. Negative replica electron micrograph, creep tested to.rupture at 138 MPa (20 ksi) for 7380 h at 730°C (1345 OF). The needlelike constituent is 11 phase (Niali); the remainder of the structure is y' in a y matrix, Glyceregia, 15,000x
Incoloy 901: Microstructure. Solution annealed 2 h at 1065 °C (1950 OF), water quenched, aged 2 h at 800°C (1470 OF), air cooled, aged 24 h at 730°C (1345 OF), and air cooled. Structure is grain-boundary envelope and MC carbide (large particle) in a y matrix. 1:1 HCI and Hp. 1000x
Incoloy 901: Effect of revision in aging treatment on creep-rupture properties Creeprupture(a) No
Originaltreotment(b) Life, Elongation, h %
Life,h
Elongation inSOmm(2in.), %
I 2 3 4 5 6 7
72 126 161 III 127 76 127
74 115 160 110 84 84 98
13 12 13 9 9 8 9
Thst
Revised treatment(c)
4 4 4 4 4 4 4
(a) At 650°C (1200 oF) and 552 MPa (80 ksi) specified minimum: life, 23 h; elongation, 5'70. (b) Solution treatedat 1085°C (1985 "F) for 2 h, cooled;aged at 720 °C (1325 "F) for 24 h, air cooled. (c)Sameconditionsas in (b) except that temperatureof first aging was 810 °C (1490 "F)
Incoloy 901: Effect of single and double aging on room-temperature properties Ultimate tensile strength MPa ksi
Incoloy 901: Effectof grain size on the low-cycle fatigue properties at 455°C (850 OF) lncoloy901
Stress
Temperature
grain sire
MPa
ksi
°C
OF
AS1M2 AS1M5 AS1M12 AS1M2 AS1M5 AS1M12
205±448 205±448 205±448 205±530 205±530 205±530
30±65 30±65 30±65 30±77 30±77 30±77
455 455 455 455 455 455
850 850 850 850 850 850
(a) Averageof 8 tests at 455 °C (850 "F)
Cycles to foilure(a) 9,000 26,000 200,000+ 5,000 16,000 137,000
Specification Singleaging(a) Doubleaging(b)
1140 1150·1160 1190·1210
165 167·169 173·175
Yield strength ksi MPa 827 800·810 830·890
120 116·118 121·129
Elongation in SO rom Reduction in (2in.), % area, % 12 2()"23 18·22
15 24-29 24·29
Singleand doubleaging datareflecttheresultsof fourtests.(a)Solutiontreatedat 1085°C (1985"F) for2 h, waterquenched;aged at770°C (1420 "F) for 2 h, air cooled;aged at 720°C (1325 oF) for 24 h, air cooled. (b)Re-aged at 650 °C (1200 oF) for 12 hand air cooled
Nickel-Base Superalloys /29
Inconel706 Aging. Alternative temperatures, times, and cooling procedures in this instance are:
Chemical Composition. Inconel 706 (UNS N09706) (nominal). 16.00Cr, 41.50Ni, 1.75Ti, 0.20 AI, 37.50 Fe, 0.03 C, 2.90 (Nb+Ta), 0.15 Cumax
• 845°C (1555 OF) for 3 h; air cool • 720°C (1325 OF) for 8 h; furnace cool • 620°C (1150 OF) for 8 h; air cool
Similar Alloys (U.S. and/or Foreign). UNS N09706
Characteristics Nickel-base, precipitation-hardening alloy
Solution Treating. Range of temperatures is 925 to 1010 °C (1695 to 1850 OF)
Recommended Heat Treating Practice Alternative solution treating and aging temperaturesare available
Aging. Alternative temperatures, time, and cooling procedures in this instance are:
Solution Treating. Range of temperatures is 925 to 1010 °C (1695 to 1850 oF).
• 730°C (1350 "F) for 8 h; furnace cool • 620°C (1150 OF) for 8 h; air cool
2000
10·00
v 900
0
1800
~
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1600
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Inconel 706: Time-temperature-precipitatioh diagram. Nominal composition: Ni- 37% Fe - 16% Cr - 2.9% Nb - 1.8% Ti. Treatment: Solution annealed at 1095 °C (2000 OF) 1 h, air cooled and aged at various times and temperatures
700
III
III
c 'iil1200
c
'iiI
oC
oC
600 1000
SOO 800 1.0
0.1
A2B
= Laves
10.0 Aging Time, h,
100.0
1 7 0 0 , . . . . - - - - - - - - - - - - - - - - - - - - - - - -... 900 26 RC
1600
o
o
i
z 800
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0.1
0.2
0.4 0.6
1.0 2.0 4.0 Aging Time. h
6.0
10.0
20.0
40.0 60.0
Inconel 706: Time-temperaturehardness diagram. Nominal composition: Ni - 37% Fe - 16% Cr 2.9% Nb - 1.8% Ti. Treatment: Annealed at 1040 °C (1900 OF) for 30 min, air cooled
LIVE GRAPH Click here to view
30 I Heat Treater's Guide: Nonferrous Alloys
Inconel X 750 Chemical Composition. lnconel X 750 (UNS N07750) (nominal). 15.50Cr, 73.00 Ni, 1.00 Nb,2.50Ti, 0.70 AI, 7.00 Fe, 0.04C, 0.25 Cu max Similar Alloys (U.S. and/or Foreign). UNS N07750; AMS 5667
Characteristics A nickel-base, precipitation-hardening alloy
preferred, and usually is necessary for heavy sections; for complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from strip or sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy. They become harder and stronger; air cooling is preferred for heavy sections ofInconel X-750, because water quenching causes cracking
Recommended Heat Treating Practice Two versions of this alloy are available: Inconel X-750 (AMS 5667), Inconel X-750 (AMS 5668). Their parameters for solution treating and aging are different:
Solution Treating per AMS 5667. Temperatures, 855°C (1570 oF) for 24 h; air cool Aging per AMS 5667. Temperature, 705°C (1300 OF) for 20 h; air cool
Inconel X 750: Microstructure. Replica electron micrograph of alloy solution annealed 2 h at 1150 °C (2100 OF) and air cooled, then aged 24 h at 815°C (1500 OF). Structure is small, uniformly dispersed t' precipitate and large, discontinuous M23CS carbide at the grain boundary. Glyceregia. 15,OOOx
Solution Treating per AMS 5668. Temperature, 1150 °C (2100 oF) for 2 h; air cool Aging per AMS 5668. Temperature, 845°C (1555 OF) for 24 h: air cool Stress Relieving. Treatment is at 880°C (1615 "F), It is used only for stress equalizing of warm worked grades Annealing. Treatment is at 1035 °C (1895 OF) for 30 min Minimum hardness is obtained by cooling rapidly from annealing temperatures, to prevent precipitation of hardening phases; water quenching is
Inconel X·750: Typicalthermal treatments for precipitation hardening of products Form
Desiredproperty
Rods,bars,andforgings Strengthandoptimum ductilityup to595°C (1100oF) Optimumtensilestrength up to 595°C (1100oF)
Maximumcreepstrength above595°C(lI00°F)
Sheet,strip,and plate
Highstrengthat high temperatures Highstrengthandhigher tensileproperties to705 °C(1300°F)
Thbing
Highstrengthat high temperatures
No.1 temperwire
Serviceupto540°C (lDOO°F) Serviceupt0370°C (700°F) Serviceat480-650°C (900-1200 oF)
Springtemperwire
Thermal treatment
Equalize: 885°C (1625oF), 24 b, aircool Precipitation: 705°C (1300oF),20 h, air cool Solution: 980°C (1795"F), aircool Fumace-cool, precipitation: 730°C (1345 "F), 8 h, furnacecoolto 620°C (1150oF), hold8 h, aircool Fullsolution: 1150°C (2100"P), 24 h. air cool Stabilize: 845°C (1555"F), 24 h, aircool Precipitation: 705°C (1300OF), 20 h, air cool Annealed+ Precipitation: 705°C (1300"F), 20 h, air cool Annealed + Furnace-cool, precipitation: 730°C (1345 oF), 8 h, furnacecoolto 620°C (1150oF), hold8 h, aircool(a) Annealed+ Precipitation: 705°C (1300"F), 20 h, air cool Solutiontreated+ cold drawn(15-20%) + 730°C (1345"F), 16h, aircool Solutiontreated+ cold drawn(30-65%)+ 650°C (1200"F), 4 h, aircool Colddrawn(30-65%)+ 1150°C (2100oF), 2h, aircool + 845 °C(1555 "F), 24h, air cool + 705°C (1300oF),20h, aircool
(a)Equivalentpropertiesin a shortertimecanbedevelopedby thefollowingprecipitation treatment: 760 °C (1400 "P) for I h, furnacecool(FC)to 620°C (1150 "F), hold 3 h, air cool (AC)
Inconel X 750: Microstructure. Replica electron micrograph of alloy, solution annealed 2 h at 1150 °C (2100 OF) and air cooled, then aged 24 h at 815°C (1500 OF), then 24 h at 705°C (1300 OF). Grain-boundary M23CS carbide is stabilized, and precipitation of fine t' particles has increased. Glyceregia. 15,000x
Nickel-Base Superalloys /31
lnconel X. 750: Microstructures. The effects of different etch ants on solution-annealed and aged alloy. (a) Tint etched in 50 mL HCI, 50 mL Hp, and 1 g K2S20 S ' (b) Etched using Kalling's reagent 2. (c) Etched using glyceregia. All 1OOx
lnconel X. 750: Microstructures. Different etchants used to delineate the structure of solution-annealed and aged alloy. (a) Etched using Marble's reagent. (b) Etched using aqua regia. (c) Etched using HCI + 1% NaP2' All 1OOx
(a)
(b)
(c)
32/ Heat Treater's Guide: Nonferrous Alloys
Inconel X 750: Time-temperature-sensitization diagram. Indicated by corrosion rate in inches per month (ipm). Composition: 73.19% Ni - 0.03% C - 0.56% Mn - 6.51% Fe - 0.007% S - 0.27% Si - 0.06% Cu - 15.24% Cr - 0.76% AI- 2.50% Ti - 0.85% Nb+Ta. Treatment: All but one specimen were solution treated at 1150 °C (2100 OF), aged for temperatures and times shown in the diagram. then aged at 705°C (1300 OF) for 20 h. The one other specimen was direct-aged at 705°C (1300 OF) for 20 h ~
LIVE GRAPH
1700
Click here to view
~
0~8
~
~ 1600
ffi
0.016
Q.
~
1500
C>
>0.015 ipm
Z
(51400
w
~
so 1300
0.0901pm (Direct-Ailed Sample'
w ~
~ 1200 ~
0.20
0.40
100 2.00 6.00 10.0 20.0 INTERMEDIATE AGING TIME, HOUR
AO.O
100.0
Inconel X 750: Time-temperature-precipitation diagram. Composition: 72.02% Ni - 0.06% C - 0.19% Mn -7.82% Fe - 0.001% S0.40% Si - 0.37% Cu - 14.82% Cr - 0.85% AI - 2.49% Ti - 0.98% Nb+Ta. Treatment: Solution annealed at 1075 °C (1965 OF) for 2 h, water quenched, and aged
LIVE GRAPH Click here to view
.-
., MC
, ,
-TIME (HfI.l
I .. I
\
r;y"
MC-tMuC,-t yl
..
-:
'0
Nickel-Base superanovs I 33
Inconel751 Chemical Composition. lnconel 751 (nominal). 15.50 Cr, 72.50 Ni, 1.00 Nb, 2.30 Ti, 1.20 AI, 7.00 Fe, 0.05 C, 0.25 Cu max
Characteristics A nickel-base, precipitation-hardening alloy
Hastelloy B Chemical Composition. Hastelloy B (UNS N10001) (nominal). 1.0 Cr max, 63.0 Ni, 2.5 Co max, 28.0 Mo, 5.00 Fe, 0.05 C max, 0.03 V
Similar Alloys (U.S. andlor Foreign). UNS NOOOOl
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treat at 1175 °C (2145 "F) for 30 min. To get an
temperature range. Rapid air cooling suffices for sheet metal parts of most alloys. Oil or water frequently is required for heavier sections not subject to cracking
Aging. This phenomenon occurs in service at elevated temperatures Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging Annealing. Treatment is at 1175 °C (2145 "F); holding time is 1 h per inch of section
adequate quench after solution treating, it is necessary to cool below about 540°C (1000 OF) rapidly to prevent precipitation in the intermediate
Hastelloy B: Microstructure. As-cast. Structure consists of MaC at grain boundariesand as islands in the 'Y matrix. Electrolytic etch: HCI and Cr0 3 • 300x
Hastelloy B: Microstructure. Casting, annealed at 1175 °C (2145 OF) for 2 h and water quenched. MaC islands in the matrix. Electrolytic etch: HCI and cr03 • 300x
Hastelloy Chemical Composition. Hastelloy B-2 (UNS N10665) (nominal). 1.00 Cr max, 69.00 Ni, 1.00 Co max, 18:00 Mo, 2.00 Fe max
Similar Alloys (u.s, Andlor Foreign). UNS N10665
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1065 °C (1950 oF) for 30 min; a rapid quench is used. To get an adequate quench, it is necessary to cool down to about 540°C (1000 OF) rapidly enough to prevent precipitation in the intermediate temperature range. Rapid air cooling suffices for sheet metal parts of most alloys. Oil or water quenching frequently is required for heavier sections not subject to cracking
Aging. Aging occurs in service at elevated temperatures
34/ Heat Treater's Guide: Nonferrous Alloys
Hastelloy 8-2 vs. Hastelloy 8-282: Time Temperature Corrosion Diagrams. Corrosion tests in boiling 21% HC), or at 185 °G (365 OF). Hastelloy 8-2, nominal composition: Ni - 1.00% max Co - 1.00% max Cr - 26.00%-30.00% Mo - 2.00% max Fe - 0.10% max Si - 1.00% max Mn - 0.02% max C - 0.040% max P - 0.030% max S vs. Hastelloy 8-282, nominal composition: Ni - 0.40% Cr - 4.80% Fe - 0.02% C - 0.31 % Si - 0.52% Mn - 37.50% Mo - 0.33% V Ni-No
Ni-No-V
1100 .----rCh--r-r---"T"'"".----..,-,
~ ~
LEGEND:
o ~
No Intergranular Corrosion
()
Intergranular Corrosion Under ZO /-l Deep
•
Intergranular Corrosion Over ZO /-l Deep
900
-
::J
ca
-,
j
700
500
..- +
.........:
1-
CD
a. E ~
o
~~~ +
/ ,~
"
""
-
+ Brittle Range
L -_ _.l.--L.....L....l.-_-'-J........:"""".......
Time, Min.
Hastelloy B-2 vs. Hastelloy 8-282: Time Temperature Precipitation Diagrams. Corrosion tests in boiling 21% HCI, or at 185°C (365 OF). Hastelloy 8-2, nominal composition: Ni - 1.00% max Co - 1.00% max Cr - 26.00%-30.00% Mo - 2.00% max Fe - 0.10% max Si 1.00% max Mn - 0.02% max C - 0.040% max P - 0.030% max S vs. Hastelloy 8-282, nominal composition: Ni - 0.40% Cr - 4.80% Fe 0.02% C - 0.31% Si - 0.52% Mn - 37.50% Mo - 0.33% V ~
1100
o ~
-
900
/
::J
lii
~ ~
(])
a. E ~
~
" "
700
,
~
F-,
1-01-h~
~
-~
....
I~l
""'i
Ni 4No+[MlZCtN 6C) ~
~~
rv
~< r~ ~E'llllI::;,
,
500
"'""-- .---~
~NllNo+[)-t12C+NGC] I~
~~ [\.bo-..
~
1- ~Ni;No+
10
Time. Min.
~
[NllC + N~]
I'~-rt-i
~~-[M 12C+ ' ...... N()CJ
10
,..
o
N6C Inside Grains
~
MlZC Along Grain Boundaries
Nickel-Base Superalloys /35
Hastelloy B-2: Time Temperature Intergranular Corrosion Diagram. Composition: Ni - 1.00% max Co - 1.00% max Cr - 26.00%30.00% Mo - 2.00% max Fe - 0.10% max Si - 1.00% max Mn - 0.02% max C - 0.040% max P - 0.030% max S
MP 1300
1
1
2
1200
o
o 1100 10
30
50
10
30
50
Exposure Time, min Ni - 27% Mo - 3.5% Fe and 0.015-0.02% C vs 0.04% C
LIVE GRAPH Click here to view
Ni - 27% Mo - 0.2% Fe and 0.015-0.02% C vs 0.04% C
LEGEND: LIVE GRAPH 1 = 0.016-0.02% C Click here to view 2 0.04% C o No intergranular corrosion Intergranular corrosion ov 20 r" deep
=
= •=
Hastelloy C Chemical Composition. Hastelloy C (UNS N10002) (nominal). 16.50 Cr, 56.00 Ni, 17.00 Mo, 6.00 Fe, 0.15 C max Similar Alloys (U.S. and/or Foreign). UNS NlO002
Characteristics A nickel-base, solid-solution alloy
Annealing. Treatment is at 1215 °C (2220 oF); holding time is 1 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections; for complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from sheet or strip rapid air cooling usually is adequate
Recommended Heat Treating Practice Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging Hastelloy C: Microstructure. As-cast. Structure consists of MaC at grain boundaries and as islands in the y matrix. Electrolytic etch: c-o, 300x
.of
Hastelloy C: Microstructure. Casting, annealed at 1230 "O (2250 ° F) for 2 h and water quenched. MaC in y matrix. Electrolytic etch: c-o, 300x
36/ Heat Treater's Guide: Nonferrous Alloys
C 1200
1000
----lifI '00
.J,.......:.
0.001
0.0)
0.1
Hastelloy C: Time Temperature Precipitation Diagram. Treatment: Aged from 540 to 1230 °C (1 000 to 2250 °F) for 1.5 to 96 h. Composition: Ni - 14.9416.46% Cr - 15.47-16.47% Mo - 3.384.02% W -5.05-6.77% Fe - 0.74-1.86% Co - 0.42-0.69% Mn - 0.42-0.73% Si -
0.22-0.32% V - 0.04-0.08% C - 0.0040.012% P - 0.005-0.011% S
LIVE GRAPH Click here to view
1
HOLDING TIME, HR
Hastelloy C·4 Chemical Composition. Hastelloy C4 (UNS N06455) (nominal). 16.00 Cr, 63.00 Ni, 2.00 Co max, 15.50Mo, 0.70 Ti max, 3.00Fe max, 0.015 C max Similar Alloys (U.S. and/or Foreign). UNS N06455
Recommended Heat Treating Practice Solution Treating. Treatment is at 1065 °C (1950"F) for 30min. Rapid quench is used
Characteristics A nickel-base, solid-solution alloy
.~
1000
o
215
• ..!.!!...
.-!!!...210
900
280
o
2:" ::l 800
f
~ ~
Hastelloy C-4: TIme Temperature Precipitation Corrosion Diagram. Corrosion test solution: 10% HCI test and the ferric sulfate test (50% sulfuric acid plus 42 giL ferric SUlfate). Nominal composition: Ni -16% Cr- 0.15% W - 0.3% Fe<0.01% C - 0.03% Si - 0.1% Co - 0.05% Mn - 0.03% V -15% Mo - 0.45% Ti. Treatment: Solution annealed at 1065 °C
Solution Annealed Matrix
~.
Secondary Carbides
..!.!.!!...
300
LIVE GRAPH
300
Click here to view
TOO
.~
800
• .!!!.. 450
300
0.1
(1950 OF)
~C
10
1.0
Time,h
100
1000
Nickel-Base Superalloys /37
Hastelloy C·276 Chemical Composition. Hastelloy C-276 (UNS N10276) (nominal). 15.50 Cr, 59.00 Ni, 16.00 Mo, 3.70 W, 5.00 Fe, 0.02 C max Similar Alloys (U.S. and/or Foreign). UNS N10276
Recommended Heat Treating Practice Solution Treating. Treatment is at 1065 °C (1950 "P) for 30 min. Rapid quench is used
Characteristics A nickel-base, solid-solution alloy
.~
• .!.!!!!.. 430
1000
••0
Secondary Carbides and Mu Phase
o o ~.
j
;.
TOO
Hastelloy C-276: Time Temperature Precipitation Corrosion Diagram. Corrosion test solution: 10% HCItest and the ferric sulfate test (50% sulfuric acid plus 42 giL ferric sulfate). Nominal Composition: Ni - 16% Cr - 3.4% W6% Fe - 0.01% C - 0.02% Si - 1% Co0.45% Mn - 0.2% V - 16% Mo. Treatment: Solution annealed at 1125 °C (2045 OF)
.~ aoo
• !!!!!!. 1020
Solution Annealed Matrix
LIVE GRAPH Click here to view
MPY Fe2(SO..)S Test
eoo
.-!!!!..,.
...!!!!. •
284...
2eo
MPYHCI
O.t
1.0
Time,h
to
too
tooo
Hastelloy N Chemical Composition. Hastelloy N (UNS N10003) (nominal). 7.00 Cr, 72.00 Ni, 16.00 Mo, 0.5 Ti max, 5.00 Fe max, 0.06 C
Similar Alloys (u.s. and/or Foreign). UNS N10003
Recommended Heat Treating Practice Solution Treating. Treatment is at 1175 °C (2145 oF) for 30 min. Rapid quench is used
Characteristics A nickel-base, solid-solution alloy
Hastelloy 5 Chemical Composition. Hastelloy S (nominal). 15.50 Cr, 67.00 Ni, 15.50 Mo, 0.20 AI, 1.00 Fe, 0.02 C max, 0.02 La
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1065 °C (1950 "F) for 30 min. Rapid quench is used
38/ Heat Treater's Guide: Nonferrous Alloys
Hastelloy W Chemical Composition. Hastelloy W (UNS N10004) (nominal). 5.00 Cr, 61.00 Ni, 2.50 Co max, 24.50 Mo, 5.50 Fe, 0.12 C max, 0.06 V
of most alloys, rapid air cooling will suffice. For heavier sections not subject to cracking, oil or water quenching frequently is required
Similar Alloys (U.S. and/or Foreign). UNS NlO004
Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1175 °C (2145 OF) for 1 h. Rapid quench is used. To provide adequate quench after solution treatment, it is necessary to cool below about 540°C (1000 "F) rapidly enough to prevent precipitation in the intermediate temperature range. For sheet metal parts
Annealing. Treatment is at 1175 °C (2145 "F), Holding time is 1 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature to prevent precipitation of hardening phases. Water quenching is preferred and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy; they become harder and stronger
Hastelloy X Chemical Composition. Hastelloy X (UNS N06002) (nominal). 22.00 Cr, 49.00 Ni, LSO Co max, 9.00 Mo, 0.06 W, 2.00 AI, 15.80Fe, 0.15 C
Characteristics A nickel-base, solid-solution alloy
Similar Alloys (U.S. and/or Foreign). UNS N06002
Recommended Heat Treating Practice
Hastelloy X: Oxidation resistance. (a) In dry air for Haynes 188 vs. Hastelloy X and L-605 alloys showing continuous penetration from original thickness. (b) Static values at 1100 °C (2010 OF) in air with 5% water vapor
Aging. Heat to 760°C (1400 OF); hold 3 h; cool in air; reheat to 595°C (1100 OF); hold 3 h; cool in air
Temperature, 'F 1700 1800 1900
1600
2000
~ 75
~
~ 64 ~ 50
.,..,
g 38
.~ 25
~
8:-
13
V"
0 870
I-"'"
925
2100 3.0 ~
V' ~a~1I0YX
-L-605........
2.5 ~ 2.0
I
980 1035 1095 Temperature, 'C
LIVE GRAPH Click here to view
0.25
160
Incoloy MA 956
s: o gJ -0.50
al -160 g'
"
\
l:
::E -0.75
llJ
Hastellov X
s: o
-320 gJ
\
llJ
"c
~ E
1\-- ~ -,
llJ
::E -485
\ Haynes 1BB(UNS R301BB)
-1
I
o Ib)
I
I
600 1200 1800 Exposure time, h
Annealing. Treatment is at 1175 °C (2145 OF). Holding time is 1 h per inch of section
o 8:-
320
llJ
g
Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging
1150
0.50
~ E g -0.25
E
1.5 J,.I.....~ I vHay~es 1BB 1.0 .~ 0.5 ~
(8)
"E
Solution Treating. Treatment is at 1175 °C (2145 °F)for 1 h. To provide an adequate quench after solution treating, it is necessary to cool below about 540°C (1000 OF) rapidly enough to prevent precipitation in the intermediate temperature range. For sheet metal parts of most alloys, rapid air cooling suffices. For heavier sections not subject to cracking, oil or water quenching frequently is required for heavier sections not subject to cracking
-645 2400
LIVE GRAPH Click here to view
Hastelloy X: Microstructure. Solution annealed at 1065 °C (1950 OF) and aged 100 h at 760°C (1400 OF). The structure is mixed carbide particles in a y matrix. Electrolytic: oxalic acid. 500x
Next Page
Nickel-Base Superalloys /39
Hastelloy X: Microstructure. Solution annealed at 1065 °C (1950 OF) and aged 100 h at 760°C (1400 OF). The structure is mixed carbide particles in a 'Y matrix. Electrolytic oxalic acid. 1000x
Hastetloy X: Microstructure. Thin-foil transmission electron micrograph, solution annealed 1 hat 1175 °C (2145 OF), water quenched, and aged 500 h at 705°C (1300 OF). The structure is primary MsC and needlelike M23C s carbides that have precipitated at dislocations generated around primary carbide. The matrix is 'Y solid solution. Not polished, not etched. 11 ,000x
Hasteltoy X: Microstructure. Thin-foil transmission electron micrograph, solution annealed 1 hat 1175 °C (2145 OF), water quenched, deformed 2% by reduction at room temperature, and aged 144 h at 705°C (1300 OF). Structure is a band of high dislocation density and precipitated M23C s carbide at sites of high dislocation density and adjacent locations. Not polished, not etched. 40,000x
Haynes 214 Chemical Composition. Haynes 214 (nominal). 16.00 Cr, 76.50 Ni, 4.50 AI, 3.00Fe,0.03 C
Characteristics A nickel-base, solid-solution alloy
Previous Page 40 I Heat Treater's Guide: Nonferrous Alloys
Haynes 230 Chemical Composition. Haynes 230 (UNS N06230) (nominal). 22.00 Cr, 55.00 Ni, 5.00 Co max, 2.00 Mo, 14.00 W, 0.35 AI, 3.00 Fe max, 0.10 C, 0.015 B, 0.02 La
Recommended Heat Treating Practice Annealing. Treatment is at set temperature in range of 1175 to 1245 °C (2150 to 2275 "F); water quench or room air cool
Similar Alloys (U.S. and/or Foreign). UNS N06230
Stress Relieving. Annealing serves this purpose
Nimonic 86 Chemical Composition. Nimonic 86 (nominal). 25.00 Ni, 10.00 Mo, 0.25 C, 0.03 Ce, 0.Ql5 Mg
Characteristics
Cr, 65.00
A nickel-base, solid-solution alloy
Custom Age 625 PLUS Chemical Composition. Custom Age 625 PLUS (UNS N07716) (nominal). 21.00 Cr, 61.00 Ni, 8.00 Mo, 3.40 Nb, 1.30 Ti, 0.20 AI, 5.00 Fe, 0.01 C
Similar Alloys (U.S. and/or Foreign). UNS N-07716
Characteristics A nickel-base, precipitation-hardening alloy
1500
Aging Temperature (F)
~
~
~ 1>:9
1450
i"-c ~9
1400
-
-
':~ ~3
...-
~a-1- I-C
( 31(
(
2
V
1>3 - ,. ~( )3
(
r-,~ ~ t'
1350 ---_. - - f--
r--... I"-
1300 Solu Ion reete
9P
-~O~~F:tt:
L""R
~ ~-3
~ ~ ~~ ~ N <, "- i'.
(1038C /2h AC p 1<1 r t
~R~ *81 I
.
·83 ~- - ' -
1
,
-
~3 ~---
st Ingle
10
a~
Ing
I
760
I
03~
1250
0.1
34
788
·_0- __
-0-
I
HiB91' 1,
Custom Age 625 PLUS: Time-temperature-hardness on aging diagram. Nominal composition: 61% Ni • 0.01% C 21% Cr - 8% Mo - 3.4% Nb - 1.3% 1i0.2% AI • 5% Fe. Treatment: Solution treated at 1040 -c (1900 OF) for 2 h, air cooled prior to single aging
LIVE GRAPH Click here to view
732
704
100
Aging Time (hours)
Haynes 242 Chemical Composition. Haynes 242 (nominal). 8.00 Cr, 62.50 Ni, 2.50 Co max, 25.00 Mo, 0.50 Al max, 2.00 Fe max, 0.10 C max, 0.006 B max
Characteristics A nickel-base, precipitation-hardening alloy
Nickel-Base Superalloys /41
Inconel702 Characteristics
Chemical Composition. Inconel 702 (UNS N07702) (nominal). 15.50 Cr, 79.50 Ni, 0.60 Ti, 3.20 AI, 1.00 Fe, 0.05 C, 0.50 Mn, 0.20 Cu, 0.40 Si
A nickel-base, precipitation-hardening alloy
Similar Alloys (U.S. and/or Foreign). UNS N07702
Inconel 702: Precipitation diagram. Nominal composition: Ni 0.08% C - 0.6% Ti - 3.2% AI- 15.5% Cr1.0% max Fe. Treatment: Specimens were heat treated at 2200 of for 2 h, ice brine quenched, aged as noted on diagram, water quenched
N'."'.·· ••••• STAaNGTMENIMG .....AlfIC Cr.,C~,Cr&,C6· EM8AITn'NO PMA•• Ti le,NJ· ••••••• LITT\.& I."~CT
AMOUNT
OF PMMe;
L~~~-----------"''''-.''' C.. ~'!.C6) _ _
es- 1300S: t400F SOl. 100MClS IOOI4RS
1550F 46 MRS
1800F 2414R5
1975F eMIlS
Precipitation of phaees and relative amounts
Inconel718 Chemical Composition.lnconel718 (UNS N07718) (nominal). 19.00 Cr, 52.50 Ni, 3.00 Mo, 0.90 Ti, 0.50 AI, 18.50 Fe, 0.08 C max, 0.15 Curnax
Recommended Heat Treating Practice Solution Treating. Treatment (per AMS 5662) is at 980°C (1795 oF) for 1 h; cooling is in air. An alternative procedure per AMS 5664: treat at 1065 °C (1950 "F) for 1 h; cool in air
Similar Alloys (U.S. and/or Foreign). UNS N07718, AMS 5662, AMS5664
Aging. Four alternative procedures are available:
Characteristics
• Treat at 720°C (1325 "P) for 8 h; furnace cool • Treat at 620°C (1150 oF); air cool • Heat to 720°C (1325 OF); hold 8 h; furnace cool to 620°C (1150 "F); hold until furnace time equals 18 h; cool in air (per AMS 5662)
A nickel-base, precipitation-hardening alloy
Inconel718: Propertiesasfunction of heat treatment Room-temperaturetensile propertles 0.2% yield
Stressrupture al6S0 OC (1200OF) with690MPa (100....J
Ultimatete",ne
SolutiontrealmeDl(a)
MPa
....1
MPa
....1
Elongation,%
Reductionin area, %
Llre,h
Elongation,%
None (direct aged) 940 °C (1725oF). 1 h. aircooled 955°C(1750°F).1 h.aircooled 970°C(1775 OF). 1 h. aircooled 980°C (1795oF).1 h. aircooled
1330 1240 1180 1145 1172 1185 1165
193 180 171 166 170 172 169
1525 1460 1420 1405 1405 1390 1365
221 212 206 204 204 202 198
19 18 20 23 24 22 25
34 34 38 41 43 46 48
95 194 122 218 200 270 225
24
strength
1010°C(l850 oF).1h.air cooled 1040°C(l905 OF). 1h.air cooled
strength
All aged 720 °C (1325oF)for 8 h. cool 55 0C/h(130°FIb)to 620°C (l150 oF).hold for 8 h. air cool (AC).
11
14 13 6 6 2
Reduclionin ........'.Ii
31 16 19 15 10 12 8
42/ Heat Treater's Guide: Nonferl'ous Alloys • Heat to 760°C (1400 "F); hold 10 h; furnace cool to 650°C (1200 "F); hold until furnace time for entire age hardening cycle equals 20 h; cool in air
Stress Relieving. Full annealing is recommended, because intermediate temperature causes aging
annealing temperature to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from strip or sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys such as Astroloy. They become harder and stronger
Annealing. Treatment is at 955°C (1750 OF); holding time is 1 h per inch of section. Minimum hardness is obtained by cooling rapidly from the
Inconel 718: Tensile properties in longitudinal orientations of hot-rolled rounds of several sizes and in various heat-treated conditions Diameter
Ullimale tensile strength
Yield strength
mm
in.
16
0.625
25
38
1.5
100
4
Condition
MPa
As-rolled 955°C (1750 OF) I h. air cool 1065°C (1950 oF)1 h, air cool 955°C (1750 "P) 1 h, air cool + age(a) 1065°C (1950 "F) I h. air cool + age(b) As-rolled 955°C (1750 "F) I h, air cool 1065°C (1950 oF) 1h, air cool 955°C (1750oF) I h, air cool + age(a) 1065°C(l950°F) 1 h, air cool + age(b) As-rolled 955°C (1750 oF) I h, air cool 1065°C (1950 oF) I h, air cool 955°C (1750 "F) I h. air cool + age(a) 1065°C (1950oF) I h. air cool +age(b) 955 °C (1750 oF) 1h, air cool 1065°C (1950oF) 1 h, air cool 955°C (1750 "P) I h, air cool + age(a) 1065°C (1950 oF) 1h, air cool + age(b)
ksi
82.1 79.2 48.2 179.8 157.5 65.0 64.5 52.0 175.0 152.0 105.5 72.5 55.0 167.5 153.0 55.0 48.0 165.0 165.0
566 546 332 1239 1086 448 445 359 1206 1048 727 500 379 1155 1055 379 331 1138 1138
MPa
ksi
962 958 803 1435 1339 896 889 776 1389 1296 1013 976 827 1413 1316 810 776 1323 1348
139.5 139.0 116.5 2082 194.2 130.0 129.0 112.5 201.5 188.0 147.0 141.5 120.0 205.0 191.0 117.5 112.5 192.0 195.5
Elongation in50 mm(2in.l,%
Reduclionin
46 50 61 21 22 54 55
60 49 66 39 30 67 61 68 36 34 52 45 60 28 36 52 63 24 34
64
20 21 40 46 58 20 24 53 60 17 21
area,%
(a) Age720°C (1325"F) for 8 h, furnacecool 10 620°C (1150 "F), hold for a totalageof 18h, aircool. (b)Age 760°C (1400 "F) for 10h. furnacecool to 650°C (1200"F), holdfor a totalage of20 h, aircool.
Inconel 718: Tensile properties of pancake forgings of various sizes in different heat-treated conditions Forging size 200 romdiam(8 in.)x 63.5 rom (2.5in.)
175romdiam (7 in.)x 25 rom(I in.) 140romdiam(5.5 in.) x 25 rom (I in.)
Condition
Orienlalion
Solutioned925°C (1695 "F) for I hand aircooled + age(a)
Solutioned 1065°C (1950oF)for 0.5 h and air cooled + age(b) Solutioned980°C (1795 oF)for I h, water quenched+ age(a) Solutioned 1065°C (1950oF)for I h, water quenched+ age(b)
Uhimate tensile strength MPa ksl
Yield strength ksl MPa
Radial: Topedge Center Bottornedge Tangential: Topedge Bottornedge Radial Tangential Radial Radial
Elongation in 50mm(2In), %
Reducilonin area,%
1096 1103 1100
159.0 160.0 159.5
1255 1351 1286
182.0 196.0 186.5
10 24 16
10.5 33.0 19.0
1248 1234 1055 1056 1189
181.0 179.0 153.0 153.2 172.5
1441 1448 1307 1277 1398
209.0 210.0 189.5 185.2 202.8
19 18 19 19 19
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(a)Age 720°C (1325 "P) for 8 h, furnacecool to 620°C (1150 "F), hold for total age of 18h. (b) Age 760°C (1400oF)for 10h, furnacecool to650°C (1200 "F), hold for total age of20h
Inconel718 Effect of heat treatment on typical room-temperature properties Heattreatment Solutionanneal:1025°C (1875oF)for 1h, waterquench; Age:790 °C (1455oF)for 6-8 h,aircool Solutionanneal:1050°C (1925OF) for 1 h,waterquench; Age:760 °C (1400 "P) for 6 h. aircool Solutionanneal:955°C (1750oF)for2 h, waterquenchor aircool; Age:720°C (1325oF)for 8 h, cool55 0C/h (100°FIb) to620°C (1150"F), hold8 h, aircool SolutionanneaI:1050°C (1925OF) for I h, aircool; Age:760°C (1400"P) for 6 h, furnacecool55 0C/h (100°FIb) to650°C (1200oF),hold 8h, aircool Solutionanneal:1065°C (1950OF) for I h, aircool
Yield strength (0.2 %olTset) tsl MPa
Thnsile strength MPa ksi
Elongation, %
area, %
Hardness, HRC
Reduction in
Fracturetoughness b, psi. in. MPa·m
855
124
1200
174
28
51
35
334
1908
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124
1205
175
27
42
38
286
1631
1130
164
1330
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100
572
1255
182
1415
205
17
41
44
84
480
1110
161
1310
190
19
40
96
546
Nickel-Base Superalloys I 43
Inconel718: Typical properties of Inconel718 as a function of processing. (a) Ultimate tensile strength. (b) Rupture stress. (c) Fatigue at 540°C (1000 OF).
8?
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Inconel718: Transformation diagram for vacuum-melted and hot-forged bar 1100
105
0
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-
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Inconel718: Microstructure. Vacuum cast, solution annealed 2 hat 1095 °C (2000 OF), air cooled, reannealed 1 hat 980°C (1795 OF), air cooled, aged 16 h at 720°C (1325 OF), air cooled. Structure: chainlike precipitate of MiCb,Ti). Laves phase in the y matrix. HCI, methanol, and FeCla • 250x
44/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Microstructure. Vacuum cast, solution annealed 1 hat 1095 °C (2000 OF), air cooled; reannealed 1 hat 980 °C (1795 OF), air cooled; aged 16 h at 720 °C (1325 OF), air cooled. All furnace heating was done under a protective atmosphere of argon. Laves phase (white islands) has precipitated at dendrites in the y matrix. HCI, methanol, and FeCla. 250x
/
/
.
Inconel718: Microstructure. Alloy 718 (89 HRS), solution annealed 1 h at 955 °C (1750 OF) and air cooled. Large particles are MC carbides. Glyceregia. 100x
Inconel 718: Microstructure. Alloy 718 (89 HRS) solution annealed 1 hat 955 °C (1750 OF) and air cooled. Structure is large MC carbides and fine 0 phase (NiaNb)at the austenite grain boundaries. Glyceregia. 1000x
Inconel 718: Microstructure. Alloy 718 (37 HRC), solution annealed 1 hat 955 °C (1750 OF), air cooled, aged 8 h at 720 °C (1325 OF), and air cooled. Structure is MC carbides in an austenite matrix. Glyceregia. 100x
Nickel-Base Superalloys I 45
Inconel718: Microstructure. Alloy 718 (37 HRC) solution annealed 1 h at 955°C (1750 OF), air cooled, aged 8 h at 720°C (1325 OF), and air cooled. Structure is cube-shaped nitride, large MC carbides, and fine 0 phase at the austenite grain boundaries. Glyceregia. 1000x
.
Inconel718: Microstructure. Alloy 718 (40 HRC), solution annealed 1 h at 955°C (1750 OF), air cooled, aged 8 h at 720°C (1325 OF), cooled 55° per h to 620°C (1150 OF), held 8 h, and air cooled. Structure is carbides in an austenite matrix. Glyceregia. 100x
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lnconel 718: Microstructure. Alloy 718 (40 HRC), solution annealed 1 hat 955°C (1750 OF), air cooled, aged 8 h at 720°C (1325 OF), cooled 55° per h to 620°C (1150 OF), held 8 h, and air cooled. Structure is MC carbides and fine 0 phase at the austenite grain boundaries. Glyceregia. 1000x
Inconel 718: Microstructure. Alloy 718 (80 HRB), solution annealed 2 h at 1065 °C (1950 OF) and air cooled. Nitrides and MC carbides are visible. Glyceregia. 100x
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.
.
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46/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Microstructure. Alloy 718 (29 HRC), solution annealed 2 h at 1065 °C (1950 OF), air cooled, aged 8 h at 720°C (1325 OF), and air cooled. Glyceregia. 100x
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Inconel 718: Microstructure. Solution annealed 1 hat 955°C (1750 OF), air cooled, and aged 100 h at 870°C (1600 OF) to form coarse 0 (NiaNb) needles. Glyceregia. 200x
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Inconel 718: Microstructure. Solution annealed 1 h at 955°C (1750 OF), air cooled, and aged 100 h at 870°C (1600 OF) to form coarse 0 (NiaNb) needles. Glyceregia. 400x
Inconel 718: Microstructure. Solution annealed 1 h at 955°C (1750 OF), air cooled, and aged 100 h at 870°C (1600 OF) to form coarse 0 (NiaNb) needles. Shown using differential interference contrast. Delta needles are recessed, MC carbides stand in relief, and nitrides (lower right) are flush with the matrix. As-polished. 400x
Nickel-Base Superalloys I 47
lnconel 718: Microstructure. Alloy 718 (21.5 HRC), solution annealed 1 hat 1150 °C (2100 OF), air cooled, and aged 100 h at 870°C (1600 OF) to form coarse needles of 0 phase (NiaNb). Glyceregia.100x
Inconel 718: Microstructure. Alloy 718 (21.5 HRC), solution annealed 1 h at 1150 °C (2100 OF), air cooled, and aged 100 h at 870°C (1600 OF) to form coarse needles of 0 phase (NiaNb). Shown using differential interference contrast illumination to show 0 phase in four austenite grains. Hard MC carbide is in relief. As-polished. 400x
Inconel718: Microstructure. Alloy 718, solution annealed 1 hat 955°C (1750 OF), air cooled, aged 8 h at 720°C (1325 OF), and furnace cooled in 10 h to 620°C (1150 OF). Structure is 0 phase (NiaNb) in a ymatrix. Electrolytic: H2S04 , HaP04 , and H2Cr04 • 1000x
Inconel 718: Microstructure. Alloy 718, solution annealed 1 hat 955°C (1750 OF), air cooled, and aged 10 h at 760°C (1400 OF) and at 650 °C (1200 OF). Structure is Laves phase (light gray particles), MC carbide (dark), and needlelike o. The matrix is y phase. Electrolytic: H2S04 , HaP04 , and H2Cr04 • 1000x
48/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Microstructure. Alloy 718, solution annealed 1 h at 955°C (1750 OF), air cooled, and aged 10 h at 760°C (1400 OF) and at 650 °C (1200 OF). Structure is Laves phase (light gray particles), MC carbide (dark), and needlelike 0, as well as y' in the y matrix. Electrolytic: H2S04 , HaP0 4 , and HNO a. 10,000x
Inconel718: Microstructure. Alloy 718, solution annealed 1 h at 955°C (1750 OF), air cooled, aged 8 h at 720°C (1325 OF), and furnace cooled in 10 h to 620°C (1150 OF). Structure is 0 phase (NiaNb) in a ymatrix, and details of o-phase crystals. t' precipitate is visible in the y matrix. Electrolytic: H2S04 , HaP04 , and HNOa. 10,000x
1100
2010
1,1 I I I
Inconel 718: Transformation diagram. Vacuum-melted and hotforged Inconel718 bar
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Inconel 718: Precipitation phases. Composition: Fe - 53% Ni - 0.05% C - 1.0% Ti - 0.7% AI 19.0% Cr - 3.0% Mo - 5.3% Nb+Ta - 0.006% B 0.03% Zr - 0.2% Mn - 0.3% Si. Treatment: 1230 °C (2250 OF) for 2 h, ice brine quench + 705°C (1300 OF) for 100 h, water quench, aged at temperatures and times indicated
Nickel-Base Superalloys I 49
Inconel718: Time-temperature diagram. Composition: Ni - 0.06% C -18.86% Cr - 2.99% Mo - 0.93% Ti - 0.57% AI- 5.25% Nb -17.48% Fe. Treatment: Solution treated at 980°C (1795 OF) for 1 h, aged in air at 760 to 1095°C (1400 to 2000 OF) at 40°C (100 OF) intervals for 5000 h, and at 1149 °C (2100 OF) for 2000 h Very Abundant
h
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1700 1600 1800 Temperature, of
1600
1900
2000
2100
Inconel718: CCT diagram. Note: cooling rate °C/h, and resultant hardness, HV. Composition: Ni -17.4% Cr-18.7% Fe - 5.16% Nb2.96% Mo - 0.99% Ti - 0.48% AI - 0.06% C - 0.07% Mn - 0.10% Si - <0.01% B - 0.003% S. Treatment - solid circle: Annealed at 950°C (1740 OF) for 1 h. Treatment - open circle: Annealed at 1050 °C (1920 OF) for 1 h ·C 1200
Allo" Inconel718
1100
~
T
CCl
DIAGRAM
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17.4 111.7 5.16\2.960.990.48 0.OS!0.07!0.10kO.01!o.oo:l
Anne.llng 1000 ttt+++-1--+---'f----+++++-HI-t-t-----+H++-HH---~-+H_H+_I__1---+___16omln at 950·C • 60m;" at" 1050·C 0 900 "800 700 600 500 400
,
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300 200 100
• n-' 185
183
205
211
210
0
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315
378
370
345
HV
10
50 I Heat Treater's Guide: Nonferrous Alloys
Inconel718: Time-temperature-precipitation diagram. Delta phase NiaNbstart only. Composition: 53.1-53.2% Ni -17.8-19.1% Fe0.03-0.05% C - 0.21-1.12% Si - 17.9-18.3% Cr - 3.0-3.06% Mo - 5.11-5.17% Nb+Ta - 0.96-1.0% Ti - 0.42-0.47% AI. Treatment: Solution treated at 1030, 1065, and 1080 °C (1885, 1950, and 1985 OF)
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TIME (HOURS) LEGEND:
1032°C ST 1066°C ST 0C 1080 ST
lnconel 718: Time-temperature-precipitation diagram. Delta phase start only. Composition 718 (solid line): Ni - 0.95% Ti 0.46% AI - 5.26% Nb - 18.25% Fe - 3.05% Mo - 18.00% Cr 0.031 % C - 0.003% B - 0.001% Mg. Composition alloy 4 (dashed line): Ni - 1.34% Ti - 0.63% AI- 5.28% Nb - 18.30% Fe 3.05% Mo - 17.80% Cr - 0.028% C - 0.004% B - 0.001% Mg. Treatment: Solutionized at 1110 °C (2030 OF) for 6 hand quenched
LIVE GRAPH
Inconel718: Time-temperature-precipitation diagram. Delta phase start only. Composition alloy 9 (solid line): Ni - 0.96% Ti - 0.53% AI - 4.32% Nb - 18.30% Fe - 3.02% Mo - 18.15% Cr 0.031% C - 0.003% B - 0.004% Mg. Composition alloy 11 (dashed line): Ni - 0.96% Ti - 0.87% AI- 5.42% Nb - 18.00% Fe 3.02% Mo - 17.80% Cr - 0.031% C - 0.004% B - 0.001% Mg. Treatment: Solutionized at 1110 "C (2030 OF) for 6 hand quenched
LIVE GRAPH
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11100
1800
1700
1700
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1600
Q:
1500
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TIME (hours)
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TIME (hours)
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100
Nickel-Base Superalloys /51
=
Inconel718: Time-temperature-precipitation diagram for Ni 3Nb (bet) gamma *, gamma prime, delta, and alpha-chromium. Composition: Ni -17.58% Fe -18.83% Cr- 0.98% Ti -2.97% Mo - 5.13% Nb - 0.53%AI- 0.05% Ta- 0.30% Co - 0.09% Mn - 0.04% C - 0.004% S - 0.01% P - 0.17% Si - 0.09% Cu. Treatment: Solution treated between 955 and 1200 °C (1750 and 2190 OF) followed by either water quench, air cool, or furnace cool
LIVE GRAPH
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900
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'''800
;
i
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600
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10 Time in hours100
1000
'0,000
Inconel718: Time-temperature-precipitation diagram for delta and gamma double prime. Nominal composition: Fe - 0.08% max C - 0.35% max Mn - 0.35% max Si - 0.015% max P - 0.Q15% max S - 17.0-21.0% Cr - 1.0% max Co - 2.80-3.30% Mo - 4.75-5.50% Nb+Ta - 0.65-1.15% Ti - 0.20-0.80% AI - 0.30% max Cu - 50.0-55.0 Ni+Co - 0.006% max B. Treatment: Solution treated at 1090 °C (1995 OF), isothermally aged at temperatures between 500 and 1050 °C (930 and 1920 OF) for times varying from 15 min to 250 h 1100
1000
900
800
ee .a
l!!
8-
700
E
~
600
500
400
Time (h)
52/ Heat Treater's Guide: Nonferrous Alloys
Inconel718. TIT diagram. A composite of past work. Composition: Fe- 52.5% NI- 0.04% C -19.0% Cr- 0.90% TI- 0.50% AI- 0.005% B - 3.05% Mo - 5.30% Nb. Treatment: Annealed in the range 1150 to 1095 °C (2100 to 1995 OF) for 1 h, water quenched
1050 1000 950 900 850
°C
800 750 700 1200
650 600 550
1000
0.5 1.0
5
10
50 100
LIVE GRAPH
TIME, HOURS
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Inconel 718: Time-temperature-precipitation diagram.
LAVES
1000
1800
w 1600
0:: 0:: W o,
,/
900
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°C
N' Nb
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600 0.1
0.5 1.0
5 10
TIME(h)
50 100 5001000
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Nickel-Base Superalloys I 53
Inconel718: Time-temperature-precipitation diagram. For appearance of gamma double prime phase and highest temperature TM for homogeneous precipitation in alloys 1, 2, 3, and 4. On this diagram curves showing the gamma prime size before appearance of gamma double prime are indicated for alloys 2, 3, and 4. Alloy 1 composition: 52.51% Ni - 18.16% Cr - 19.5% Fe - 2.96% Mo - 0.82% 1i - 0.70% AI- 5.18% Nb. Alloy 2 composition: 51.98% Ni -18.59%Cr-21% Fe-2.85% Mo- 0.72% 1i - 0.63%AI- 3.99% Nb. Alloy 3 composition: 51.98% Ni -18.97% Cr-17% Fe -7.03% Mo- 0.59% Ti - 0.63%AI- 3.41% Nb. Alloy 4 composition: 52.09% Ni -18.90% Cr-16.4% Fe7.00% Mo - 0.90% Ti- 0.74%AI- 3.85% Nb. Treatment: Annealed at 1200 °C (2190°F) for 30 min, water quenched, aged at650t0820°C (1200 to 1510 OF) under vacuum in vycor capsules
LIVE GRAPH Click here to view
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Aging Time , hours
Inconel718: Composite time-temperature-precipitation diagram. Composition: Ni - 0.04% C - 0.20% Mn - 0.30% Si - 18.6% Cr3.1% Mo - 5.0% Nb - 18.5% Fe - 0.9% Ti - 0.4% AI
LIVE GRAPH Click here to view
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54/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Time-temperature-precipitation diagram of Ni3Nb. Composition: Fe - 53.8% Ni - 18.0% Cr - 3.00% Mo - 5.24% Nb+Ta1.00% Ti - 0.59% AI- 0.05% C - 0.003% S - 0.004% B. Treatment: Solution treated at 1065 °C (1950 OF) for 4 h, air cooled
LIVE GRAPH
2000
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NF 0
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0.5
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50
100
500
1000
TIME, HOURS
Inconel718: Time-temperature-precipitation diagram for Ni 3Nb compared to Eiselstein data. Composition: Fe - 53.8% Ni -18.0% Cr - 3;00% Mo - 5.24% Nb+Ta- 1.00% Ti - 0.59% AI- 0.05% C - 0.003% S - 0.004% B. Treatment: Solution treated at 1065 °C (1950 OF) for 4 h, air cooled 2000
LIVE GRAPH Click here to view
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100
500 1000
Nickel-Base Superalloys I 55
Inconel718: Time-temperature-precipitation diagram. At this time the strengthening phase was thought to be gamma prime; later it was shown to be gamma double prime. Nominal composition: Ni - 19% Cr - 18% Fe - 5% Nb - 3% Mo - 0.15% Si - 0.10% Cu - 0.20% Mn - 1.0% Ti - 0.4% AI- 0.04% C - 0.007% S. Treatment: Solution annealed at 1150 °C (2100 OF) for 1 h, and water quenched 2000
LIVE GRAPH Click here to view
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56/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Time-temperature-precipitation diagram. Occurrence of grain boundary carbide film and needles. Nominal composition: Ni -19% Cr -18% Fe - 5% Nb - 3% Mo - 0.15% Si - 0.10% Cu - 0.20% Mn -1.0% Ti - 0.4% AI- 0.04% C - 0.007% S. Treatment: Solution annealed at 925°C (1700 OF), aged at various times and temperatures indicated
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Nickel-Base Superalloys I 57
Inconel718: Time-temperature-precipitation diagram. Occurrence of grain boundary carbide film and needles. Nominal composition: Ni -19% Cr-18% Fe - 5% Nb - 3% Mo - 0.15%Si - 0.1 0% Cu - 0.20%Mn -1.0% Ti - 0.4%AI- 0.04%C - 0.007% S. Treatment: Solution
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Next Page 58/ Heat Treater's Guide: Nonferrous Alloys
Inconel718: Time-temperature-hardness diagram. (Strengthening phase thought to be gamma prime). Composition: Ni - 18.49% Cr -16.79% Fe-5.07% Nb+Ta-3.11% Mo- 0.95% Ti -0.51%AI-0.30% Si -0.28% Mn-0.05%Cu-0.04%C- 0.011% P-0.007% S-0.0023% B. Treatment: Solution treated at 1040 °C (1900 OF) for 30 min, water quenched to room temperature within 1 min 1600
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Nickel-Base Superalloys I 59
Inconel721 Chemical Composition. Inconel721 (UNS N07721) (nominal). 16.00 Cr, 71.00 Ni, 3.00 Ti, 0.04 C, 2.20 Mn, 0.10 Cu
Characteristics A nickel-base, precipitation-hardening alloy
Similar Alloys (U.S. and/or Foreign). UNS N07721
Inconel722 Chemical Composition. Inconel722 (UNS N07722) (nominal). 15.50 Cr, 75.00 Ni, 2.40 Ti, 0.70 AI, 7.00 Fe, 0.04 C, 0.50 Mn, 0.20 Cu, 0.40 Si
Similar Alloys (U.S. and/or Foreign). UNS N07722
Characteristics
Recommended Heat Treating Practice Solution Treating. Treat at set temperature of980 °C (1800 "F); hold 1 h per 25 mm (1 in.) of thickness. Minimum time is 10 min
Precipitation Heat Treating. Treat at set temperature of 705 °C (1300 OF) for 16 h min; air cool
A nickel-base, precipitation-hardening alloy
C...263 Chemical Composition. C·263 (UNS N07263) (nominal). 20.00 Cr, 51.00 Ni, 20.00 Co, 5.90 Mo, 2.10 Ti, 0.45 AI, 0.70 Fe max, 0.06 C
Characteristics A nickel-base, precipitation-hardening alloy
Similar Alloys (U.S. and/or Foreign). UNS N-07263
pyromet 31 Chemical Composition. Pyromet 31 (UNS N07031) (nominal). 22.70 Cr, 55.50 Ni, 2.00 Mo, 1.10 Nb, 2.50 Ti, 14.50 Fe, 0.04 C, 0.005 B
Similar Alloys (U.S. and/or Foreign). UNS N07031
Pyromet 31: Microstructure. Pyromet 31 alloy (325 HV), heat treated 1500 h at 815°C (1500 OF) to form coarse needles of 11 (NiaTi) phase. Glyceregia. 400x
Characteristics A nickel-base, solid-solution alloy
pyromet 31: Microstructure. Pyromet 31 alloy (325 HV), heat treated 1500 h at 815°C (1500 OF) to form coarse needles of 11 (NiaTi) phase. Parts of only a few grains are visible. Glyceregia. 1000x.
60 I Heat Treater's Guide: Nonferrous Alloys
pyromet 31: Microstructure. Pyromet 31 alloy (260 HV), heat treated 4 h at 955°C (1750 OF) to form needles of 11 (Ni3Ti) phase. Glyceregia. 1000x
pyromet 31: Microstructure. Pyromet 31 (40 HRC), solution annealed and aged. The specimen was tint etched with 66 mL HCI, 33 mL H20 , and 1 g K2 S 20 5 • 100x
Pyromet 31: Microstructure. Pyromet 31 (260 HV), heat treated 4 h at 955°C (1750 OF) to form needles of 11 (Ni3 li) phase, shown with dark-field illumination. Glyceregia. 1000x
pyromet 31: Microstructure. Pyromet31 (40 HRC), solution annealed and aged. The specimen was etched using Kalling's reagent 2 (''waterless'' Kallings). 100x
Nimonic 80A Chemical Composition. Nimonic BOA (UNS N070BO) (nominal). 19.50Cr, 73.00Ni, 1.00Co, 2.25Ti, 1.40 AI, 1.50Fe, 0.05C, 0.10 Cu max Similar Alloys (U.S. and/or Foreign). UNS N07080
Characteristics A nickel-base, precipitation-hardening alloys
Recommended Heat Treating Practice Solution Treating. Treatment is at 1080 °C (1975 "F) for 8 h. Cooling is in air Aging. Treatment is at 705°C (1300 "F) for 16 h. Cooling is in air Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging
Nickel-Base Superalloys /61 adequate and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy. They become harder and stronger
Annealing. Treatment is at 1080 °C (1975 "F), holding time is 2 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is
Nirnonic BOA: Time-temperature-precipitation diagram for carbides after various heat treatments. Nominal composition: Ni0.08% C - 20% Cr - 2.4% Ti -1.4% AI Treatment: Heat treated at 1080 0 C (1976 0 F ) for 8 h, water quench
Treatment: Heat treated at l0800 C (1976 0 F) for 8 h, air cool
Reaction time, h
Reaction time, h
5
10
50 100
1000 500
5
1100 1000
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10
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Treatment: Heat treated at l0800 C (1976 0 F ) for 8 h, air cool + 850 0 C (1562~) for 24 h, air cool
Treatment: Heat treated at 1200 0 C (2192 0 F) for 2 h, air cool
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LIVE GRAPH 500
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62/ Heat Treater's Guide: Nonferrous Alloys
Nimonic 80A: Hardness. Hardness changes on aging at various temperatures. Prior treatment: solution 10aO °C (1975 OF) for h, water quenched
a
Nimonic 80A: Aging. Effect of increasing intermediate aging on rupture properties of wrought Nimonic aOA. AC (air cooled)
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Nimonic 90 Chemical Composition. Nimonic 90 (UNS N07090) (nominal). 19.50 Cr, 55.50 Ni, 18.00 Co, 2040 ri lAO AI, 1.50 Fe, 0.06 C
treating temperature does not suppress the aging reaction of some alloys, such as Astroloy; they become harder and stronger
Similar Alloys (U.S. and/or Foreign). UNS N07090
Characteristics
Nimonic 90: Effect of cold work and annealing on grain size for Nimonic 90 sheet cold rolled in steps from 1.a to 0.9 mm (0.072 to 0.036 in.) thick and annealed at five temperatures
A nickel-base, precipitation-hardening alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1080 °C (1975 OF) for 8 h; cooling is in air Aging. Treatment is at 705°C (1300 OF) for 16 h; cooling is in air Stress Relieving. Full ami.ealing is recommended, because intermediate temperatures cause aging Annealing. Treat at 1080 °C (1975 OF); holding time is 2 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation of hardening phases; water quenching is preferred and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution
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pyromet 860 Chemical Composition. Pyromet 860 (nominal). 13.00 4.00 Cr, 6.00 Mo, 3.00 Ti, 1.00 AI, 28.90 Fe, 0.05 C, 0.01 B
o,
44.00 Ni,
Recommended Heat Treating Practice Solution Treating. Treat at 1095 °C (2000 "F) for 2 h; water quench
Characteristics
High Temperature Aging. Treat at 830°C (1525 OF) for 2 h; air cool
A nickel-base, precipitation-hardening alloy
Low Temperature Aging. Treat at 760°C (1400 OF) for 24 h; air cool
Nickel-Base Superalloys /63
Refractory 26 Chemical Composition. Refractory 26 (nominal). 18.00 Cr, 38.00 Ni, 20.00 Co, 3.20 Mo, 2.60 Ti, 0.20 AI, 16.00 Fe, 0,03 C, 0.015 B
Characteristics A nickel-base, precipitation-hardening alloy
Rene 41 Chemical Composition. Rene 41 (UNS N07041) (nominal). 19.00 Cr, 55.00 Ni, 11.00 Co, 10.00 Mo, 3.10 Ti, 1.50 AI, <0.3 Fe, 0.09 C, 0.01 B
Similar Alloys (U.S. and/or Foreign). UNS N07041
Characteristics A nickel-base, precipitation-hardening alloy
Recommended Heat Treating Practice
Annealing. Treatment is at 1080 °C (1975 "F); holding time is 2 h per inch of section. Minimum hardness is obtained by rapid cooling from the annealing temperature, to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavier sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from strip or sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, and as Astroloy, they become harder and stronger
Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging
Rene 41: Microstructure. Solution annealed 4 h at 1065 °C (1950 OF) and air cooled. Structure consists of stringers of carbide in a y solid-solution matrix. Kalling's reagent 2. 100x
Rene 41: Microstructure. Solution annealed 4 h at 1065 °C (1950 OF) and air cooled. Structure consists of stringers of carbide in a y solid-solution matrix. Light, globular particles are MaC; gray particles are MC carbide; grain-boundary envelopes are MaC or M23C a. Kalling's reagent 2. 500x
Rene 41: Microstructure. Solution annealed 4 h at 1065 °C (1950 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Particles of mixed carbides are present in the y solid-solution matrix, which was darkened by the formation of y I at 760°C (1400 OF). Kalling's reagent 2. 11 Ox
64/ Heat Treater's Guide: Nonferrous Alloys
Rene 41: Microstructure. Solution annealed 4 h at 1065 °C (1950 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Particles of mixed carbides are present in the y solid-solution matrix, which was darkened by the formation of y I at 760°C (1400 OF). High magnification, shows particles of MaC (white), MC (gray), and M23Ca (at grain boundaries). Grain-boundary borders are darkened by y/. Kalling's reagent 2. 540x
Rene 41: Aging. Relative amounts of precipitates resulting from aging Rene 41 at various times and temperatures after solution treating at 1205 °C (2200 OF) and water quenching
Time at temperature, h 100
48
24
I
I
I
1400
Aging temperature, 'JF 1600 1800 2000
1200
1200
Rene 41: Minor phase concentration as a function of the aging temperature. Composition: Ni - 0.08% C - 19.31% Cr - 10.82% Co 9.77% Mo - 2.34% Fe - 3.23% Ti - 1.51% AI0.006% B. Treatment: Bar stock specimens were solution treated at 1205 °C (2200 OF) for 2 h, aged at 760 to 1205 °C (1400 to 2200 OF) at varying times
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Nickel-Base Superalloys /65
Rene 41: Time-temperature-precipitation of phases. Isothermalphase reactions after aging at the times and temperaturesindicated. Typical composition: Ni - 0.08% C - 0.50% Fe - 19.00%Cr - 11.00% Co - 9.75% Mo - 3.15% Ti -1.50% AI- 0.006% B. Treatment: Bar stock specimenswere initiallytreated at 1205 °C (2200 OF), water quenched, and aged VERY ABUNDANT
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Rene 41: Minor phase concentration as a function of temperature for long exposure times. Composition: Ni - 0.08% C - 19.31 % Cr - 10.82%Co - 9.77% Mo - 3.23%Ti - 1.51 % AI- 0.006% B - 2.34% Fe.Treatment: Solutiontreated at 1175°C (2150 OF) for 2 h, aged in air at 760 to 1095 °C (1400to 2000 OF) at 38°C (100 OF) intervalsfor 5000 h, and at 1150°C (2100 OF) for 2000 h Very Abundant
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66/ Heat Treater's Guide: Nonferrous Alloys
Rene 41: Postweld thermal cycles used for developing strain-age cracking C-curves in next 5 diagrams. Composition: Ni 20.10% Cr - 2.03% Fe - 0.089% C - 0.25% Si - 11.55%Co - 0.05% Mn - 10.17% Mo - 1.60%AI- 3.17% Ti - 0.0056% B - 0.016% S 2000
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Rene 41: Time-temperature-cracking diagram. Crack susceptibility C-curve as generated using the postweld heat treating procedure in prior figure. Indicated cracking occurred either during isothermal aging, or during cooling. Composition: Ni - 20.105 Cr 2.03% Fe - 0.89% C - 0.25% Si -11.55% Co - 0.05% Mn - 10.17% Mo - 1.60% AI - 3.17% Ti - 0.0056% B 0.016% S. Treatment: Mill annealed prior to welding
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Nickel·Base Superalloys /67
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Rene 41: Time-temperature-cracking diagram. Crack susceptibility C-curve. Composition: Ni - 18.64% Cr 0.20% Fe - 0.075% C - 0.05% SI - 10.76% Co - 0.05% Mn - 9.76% Mo -1.62% AI- 3.13% Ti - 0.009% B - 0.008% P - 0.007% S. Treatment: Mill annealed prior to welding
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1100
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2000
100.0
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Ra ~e I:..posure Time In Minutes
-
Rene 41: Time-temperature-cracking diagram. Crack susceptibility C-curve. Composition: Ni - 19.02% Cr 0.30% Fe - 0.07% C - 0.06% SI - 10.84% Co - 0.04% Mn - 9.84% Mo - 1.45% AI- 3.18% TI - 0.0056% B - 0.005% P - 0.005% S. Treatment: Mill annealed prior to welding
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Rene 41: Time-temperature-cracking diagram. Comparison of the crack susceptibilities of high Fe-Si-Mn-S and low Fe-Si-Mn-S heats. High Fe-Si-Mn-S composition: Ni 19.73% Cr- 2.03% Fe - 0.067% C - 0.18% Si -11.12% Co0.05% Mn - 10.09% Mo - 1.60% AI - 3.10% Ti - 0.0045% B 0.020% S. Low Fe-Si-Mn-S composition: NI - 18.64% Cr0.20% Fe - 0.075% C - 0.05% Si - 10.76% Co - 0.05% Mn
1300 1200 1100
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68/ Heat Treater's Guide: Nonferrous Alloys
Rene 41: Time-temperature-cracking diagram. Annealed vs. overaged crack susceptibility C-curve. The dotted curve, shown for comparison, is for the mill annealed alloy. The test data are for the overaged specimens. Composition: Ni - 19.02% Cr - 0.30% Fe - 0.07% C 0.06% Si - 10.84% Co - 0.04% Mn - 9.84% Mo -1.45% AI- 3.18% Ti - 0.0056% B - 0.005% P - 0.005% S. Overage treatment: Aged at 1080 "C (1975 OF) for 30 min, cooled at -2 to 5°C/min to 960°C (1800 OF), held for 4 h, cool at -2 to 5°C/min to 870°C (1600 OF), held for 4 h, cool at -2 to 5°C/min to 760°C (1400 OF) held for 16 h, air cool to room temperature
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\
o
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.... ,
uncraoked
0
0
-------- ---------0
....
,I 10.0 1\l0.() I...oth...... al A1I101f 1\an1lG Exposure TaG 10 lI1nutee
.,1 1000."
Rene 95 Chemical Composition. Rene 95 (nominal). 9.50 Cr, 61.00 Ni, 15.00Co, 3.00 Mo, 4.20 Ti, 5.50 AI, 1.00Fe max, 0.6 C, 0,015B, 0.06Zr, 1.00V
Characteristics A nickel-base, precipitation-hardening alloy
Rene 95: Microstructure. Powder-made Rene 95, hot isostatically pressed. Structure includes large, coarse y ', Prior particle boundaries are also visible. Glyceregia. 200x
Nickel-Base superauoys I 69
Rene 95: Microstructures. Powder-made Rene 95, hot isostatically pressed. Structure includes large, coarse t'. Prior particle boundaries are also visible. Different illumination modes to delineate structure. Some carbide networks are visible at this magnification. Glyceregia.1000x
Rene 100 Chemical Composition. Rene 100 (nominal). 9.50 Cr, 61.00 Ni, 15.00 Co, 3.00 Mo, 4.20 Ti, 5.50 AI, 1.00 Fe max, 0.16 C, 0.Ql5 B, 0.06 Zr, 1.00 V
Characteristics A nickel-base, precipitation-hardening alloy
Udimet 500 Chemical Composition. Udimet 500 (UNS N07500) (nominal). 19.00 Cr, 48.00 Ni, 19.00 Co, 4.00 Mo, 3.00 Ti, 3.00 AI, 4.00 Fe max, 0.08 C, 0.005 B
Similar Alloys (U.S. and/or Foreign). UNS N07500
Characteristics A nickel-base, precipitation-hardening alloy
sections; but air cooling is preferred for heavy sections of Udimet 500 because water quenching causes cracking. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts shaped from strip or sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys. They become harder and stronger
Recommended Heat Treating Practice Solution Treating. Treatment is at 1080 °C (1975 OF) for 4 h; cooling is in air
Udimet 500: Effectof eliminating intermediate aging on typical room-temperature mechanical properties Uhlmate tensile
Aging. Two different procedures are available: ED ED
Aging at 845°C (1555 OF) for 24 h; cooling is in air Aging at 760°C (1400 OF) forlf h; cooling is in air
Specified min
Elongation in
MPa
ksi
Yield strength (0.2% offset) MPa ksi
1030
150
690
100
10
15
830 810
120 118
7 4
11
800 850
116 123
14.5 14
17
strength
SOrnm (2in.), %
Reduction in area, %
Obtained with intermedinte aging(a)
Stress Relieving. Full annealing is recommended, because intermediate
Test 1 Test 2
temperatures cause aging
Obtained without intermediate aging(b)
Annealing. Treatment is at 1080 °C (1975 OF); holding time is 4 h per inch of cross section. Minimum hardness is obtained by cooling rapidly from the annealing temperature to prevent precipitation of hardening phases. Water quenching is preferred, and is usually necessary for heavier
Test 1 Test 2
1030 970 1170 1230
149 141 170 179
5
16
(a) Heat treatment: 4hat 1080°C(1975 "F), air cool; 24hat 845 °C(I445 "F), air cool (intermediate aging); 16 h at 760°C (1400 OF),air cool. (b) Same as (a), but without intermediate aging
70 I Heat Treater's Guide: Nonferrous Alloys
Udimet 520 Chemical Composition. Udimet 520 (nominal). 19.00 Cr, 57.00 Ni, 12.00 Co, 6.00 Mo, 1.00 W, 3.00 Ti, 2.00 AI, 0.08 C, 0.005 B
o cs free
ED
(c) Udimet 520
Characteristics A nickel-base, precipitation-hardening alloy
Udimet 520: Time-temperature-precipitation diagram. Showing sigma phase formation. U-520 composition: Ni - 0.03% C -18.8% Cr -11.8 Co - 6.0% Mo - 0.9% W - 2.9% Ti - 2.1%AI- 0.02% B
<5 prone
N v = 2.40
9 50 i
1850
K>-Q'i'W+f+t'-N-H-t'-H-f-h"""''-I+f-hf-H'-f+jH
~ 750 Ki>ood-~'-.ld-HHf+f+HH-H-H-H-H~
::;,
] (lJ
a.
E QI
-;;950 Kl~o--~>----<>-------<:H c
:g 900 K--
-::::::::;::;:~'77"i'/,~>m,..."..ffl97mH ~
850 t-(Jt--,fItHo-H-r+fIhl-r+f-f-:f-h.....'-H'-H'-H'-H'-He..,o..-j
o
1000
h
10000
Udimet 700 Chemical Composition. Udimet 700 (nominal). 18.00 Cr, 55.00 Ni, 14.80 Co, 3.00 Mo, 1.50 W, 5.00 Ti, 2.50 AI, 0.D7C, 0.01 B
Characteristics A nickel-base, precipitation-hardening alloy
Recommended Heat Treating Practice Alternative solution treating and aging procedures are available.
Solution Treating. lD lD
Treatment is at 1175 °C (2150 OF) for 4 h; cooling is in air Treatment is at 1080 °C (1975 OF) for 4 h; cooling is in air
Aging. lD lD
Treatment is at 845°C (1555 OF) for 24 h; cooling is in air Treatment is at 760°C (1400 OF) for 16 h; cooling is in air
Stress Relieving. Full annealing is recommended because intermediate temperatures cause aging Annealing. Treatment is at 1135 °C (2075 OF); holding time is 4 h per inch of section. Minimum hardness is obtained by rapid cooling from the annealing temperature, to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections, but air cooling is preferred for heavy sections of Udirnet 700, because water quenching causes cracking. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts
formed from strip and sheet, rapid air cooling usually is adequate. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy, they become harder and stronger
Udimet 700: Microstructure. Fully heat-treated, showing cubical r'. 6800x
Nickel-Sase Superalloys /71
Udimet 700: Time-temperature diagram. Gamma prime particle size vs. temperature and time. From 760 to 1095 °C (1400 to 2000 OF). Volume fraction of gamma prime from 38 to 14%. Composition: Ni - 14.5% Cr - 17.5% Co - 5.1% Mo - 3.7% Ti - 4.1% AI- 0.015% B - 0.08% C. Treatment: Specimens were annealed above the gamma prime solvus temperature at 1175 °C (2150 OF) for 4 h, followed by a fast air cool
LIVE GRAPH Click here to view
2000°F 19S0 oF 1900 0F 18S0 oF 1800 0F 17S0 oF 1700 0F 16S0 oF 1600 0F lHooF IS000F USooF
1000
500
14'10 22'10 27'10 30'10 33,"0 35'10 36'10 38'10 38'10 38'10 38'10 38'10
UOooF 38'10
5
10
TIME (HOURS)
SO
100
500
Udimet 700: Time-temperature-oxidation diagram. Isoreactivity plots for constant amount of subscale damage. Note: complete reversal of behavior at 1040 °C (1900 OF) and absence of internal oxidation atthis temperature. Composition: Ni -15.0% Cr- 0.15% Fe -19.0% Co - 5.15% Mo· 3.49% Ti - 4.45% AI - 0.10% Si - 0.10% Mn - 0.028% B • 0.06% C. Treatment: 0.5-in. diam rod, solution annealed at 1177 °C (2150 OF) for 4 h, aged at 1080 °C (1975 OF) for 4 h + at 845°C (1550 OF) for 24 h and at 870°C (1600 OF) for 16 h
LIVE GRAPH
Click here to view 2200
2000
1.0A.D. ______
~----========1800
c~-~
1.0 A.D.
................
A.D.-ALLOY DEPLETION MIl/SIDE X.O. INTERNAL OXI DATION MILISIDE 1600
\0
T1M~
HOURS
100
----1000
72/ Heat Treater's Guide: Nonferrous Alloys
Udimet 700: Time-temperature-oxidation diagram. Simplified summary of the four main stages of oxidation. Composition: Ni - 15.0% Cr - 0.15% Fe - 19.0% Co - 5.15% Mo - 3.49% Ti - 4.45% AI - 0.10% Si - 0.10% Mn - 0.028% B - 0.06% C. Treatment: 0.5-in. diam rod. solution annealed at 1175 °C (2150 OF) for4 h, aged at 1080 °C (1975 OF) for4 h + 845°C (1550 OF) for 24 hand at 870 °C (1600 oF)for16 h
LIVE GRAPH Click here to view
CrZ03+ Ni Crz04 + Ni0
2000
--- --- -
A1z03+ Ti N
LEGEND: (1) = linear growth rate (2) and (3) = parabolic growth rate (4) where weight gain reaches a constant value in some 1000 min Numerator = the scale constituents present Denominator = the products of internal oxidation
=
CD 1800
1600'---------L-----....I---.l....----.L.--....:....----' 10,000 10 1000 100 MINUTES
Udimet 700: Time-temperature diagram. Minor phase concentration as a function of aging temperature. Nominal composition: Ni 0.08% C - 15.0% Cr - 18.5% Co - 5.2% Mo - 3.5% Ti - 4.3% AI- 0.030% B. Treatment: Bar stock specimens were solution treated at 1175 °C (2150 OF) for 6 h, aged at 760 to 1150 °C (1400 to 2100 OF) for varying times Very Abundant
r - -.........- - , . - - - - - , , . - - - . - - , - - - - - , - - - - r - - , - - - - - - ,
Abundant d
o
~...
~
Medium
o
o ~ ..
g
Rare
~ Very Rare
1400
1600
1600
1700
1800
1900
2000
2100
2200
Temperature, OF 96
72
48
36
24 Time,h
16
8
6
2
NickelBBase Superalloys /73
Udimet 700: Time-temperature diagram. Minor phase concentration as a function of temperature for long exposure times. Composition: Ni - 0.07% C -15.1 0% Cr - 18.30% Co - 5.33% Mo - 3.34% Ti - 4.29% AI- 0.024% B. Treatment: Solution treated at 1175 °C (2150 OF) for 4 h, aged in air at 760 to 1095 °C (1400 to 2000 OF) at 38°C (100 OF) intervals for 5000 h, and at 1150 °C (2100 OF) for 2000 h
Very Abundant
I
t::=
.5l Abundant
f
1 ~ ..c::
Medium
Il.
~
~
M
C 23 •
\
.....--0
o
o
r>;
:k~c~\
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/
Very Rare
\
°
I
\
Sigma
I>~\ 0, \
\
Me
'\
I I MgB2 \\ rrr::__. \, I --+.__.__ 8-L._ _ I I 1400
\ I 1500
1600
1700
1800 Temperature, of
/
1900
l
2000
2100
Udimet 700: Microstructures. (a) Solution annealed at 1175 °C (2150 OF) for 4 to 6 h and then aged 5000 h at 760°C (1400 OF). Replica electron micrograph shows large particle of MC at grain-boundary intersection and t' in grains of y matrix. 4500x. (b) Solution annealed as for (a) and aged for 5000 h at 815°C (1500 OF). Replica electron micrograph shows acicular sigma, carbide (M23C6) at grain boundary, and t' within grains of the y' matrix. 4700x
(a)
(b)
74/ Heat Treater's Guide: Nonferrous Alloys
Udimet 710 Chemical Composition. Udimet710 (nominal). 18.00 Cr. 55.00 Ni. 14.80 Co. 3.00 Mo. 1.50 W. 5.00 rt, 2.50 AI. 0.07 C. 1.50 Ta. 0.Ql5 B. O.lOZr
Characteristics
Udimet710: Time-temperature-precipitation diagram. Showing sigma phase formation. U-710 composition: Ni - 0.06% C17.7% Cr - 15.1% Co - 3.0% Mo - 1.4% W - 4.8% Tl - 2.4% AI0.02%8
A nickel-base. precipitation-hardening alloy
o
cs free
(0) Udimet 520
•
(3
prone
N v = 2.40
..
Unitemp AF2-1 DA ChemicalComposition. UnitempAF2-1 DA (nominal). 12.00 Cr. 59.00 Ni. 10.00 Co. 3.00 Mo. 6.00 W. 3.00 Ti. 4.60 AI, <0.50 Fe, 0.35 C. 1.50 Ta, 0.015 B, 0.010 Zr
Characteristics A nickel-base, precipitation-hardening alloy
Recommended Heat Treating Practice Solution Treating. Treated at 1230 °C (2250 "F) for 2 h, aged in air at 760 to 1095 °C (1400 to 2000 OF) at 38°C (100 OF) intervals for 5000 h, and at 1150 °C (2100 OF) for 2000 h
Next Page Nickel-Base Superalloys /75
Unitemp AF2-1 0: Transformation diagram. Minor phase concentration as a function of aging temperature. Composition: Ni - 0.35% C - 11.92% Cr - 14.05% Co - 4.94% Mo - 4.87% W - 3.02% Ti - 4.60% AI- 0.013% B - 0.10% Zr - 1.56% Ta. Treatment: Bar stock specimens were solution treated at 1230 °C (2250 OF) for 2 h, aged at 760 to 1205 °C (1400 to 2200 OF) at varying times MC
Very Abundant
Abundant
M6 C
I:l 0
....
~
I:l Qj u I:l
Medium
0
0
Qj
~ ..<:
,
..
I,"
~
Rare
0
I:l
J J
~
I I
M23 C6
I
Very Rare
" 1400
1600
1600
96
72
48
1900 1700 1800 Temperature of 16 36 24
2000
2100
2200
8
6
2
Time,h
Unitemp AF2-1 0: Transformation diagram. Minor phase concentration as a function of temperature for long exposure times. Composition: Ni - 0.33% C - 11.93% Cr - 14.20% Co - 5.05% Mo - 3.04% Tl - 4.60% AI- 4.93% W - 0.014% B - 0.10% Zr - 1.48% Ta. Treatment: Solution treated at 1230 °C (2250 OF) for 2 h, aged in air at 760 to 1095 °C (1400 to 2000 OF) at 38°C (100 OF) intervals for 5000 h, and at 1150 °C (2100 OF) for 2000 h
Very Abundant
,
° ~
,,, ,,
I I I
I
Rare
Very Rare 1300
I I I I I I I I
D
o
1400
1600
\
, \
I
I I I I MaC-i I
I I - M23 C6 I
~
j
,
\
I
f-- MaC
Medium
,\
'
,
M23 C6 ,
1 o ~ ..cI
MC
I I
Abundant
\Me ,
\
,
I:l
~--8~
O~O--Q~8""'-::::::::::, MC / 0 ,
\ \ \ \ \ \ , ,
1600 1700 1800 Temperature, of
I
I I
I I
I I
I I I
I
I I I
1900
I
I 2000
2100
Previous Page
76/ Heat Treater's Guide: Nonferrous Alloys
AF-2-1 DA (Modified): Time-temperature-precipitation diagram. Start of sigma phase. PM modified versions of IN-1 00 (Alloy3) and AF2-IDA (Alloy 5) vs. conventional wrought.IN-100 Nb-modified (PM) _composition: Ni -11.9% Cr -17.7% Co - 3.3% Mo - 5.2% AI- 4.2% li - 1.4% Nb - 0.024% B - 0.06% Zr - 0.09% C.IN-100 Nb-modified (CE) - composition: Ni - 12.1% Cr - 17.4% Co - 3.2% Mo - 5.3% AI4.4% Ti ~ 1.5% Nb - 0.028% B - 0.06% Zr - 0.08% C. AF-2-1 DA Nb-C-modified (CE) _composition: Ni - 12.0% Cr - 10.3% Co - 5.5% W 2.95% Mo - 4.7% AI- 2.9% Tl - 1.4% Nb -1.6% Ta - 0.020% B - 0.11 % Zr - 0.09% C. PM: powder metallurgy. CE: case and extruded. Treat.ment: Both PM and CE materials were given identical heat treatments, which consisted of a partial gamma prime solution treatment at temperatures 20°C (70 OF) below the gamma prime solvus for 2 h, followed by cooling in air, a carbide-stabilizing heattreatment at 980°C (1795 OF) for 8 h, followed by an air cool, and a gamma prime precipitation cycle of 760°C (1400 OF) for 8 h. To observe the formation of sigma phase the heat-treated specimens were exposed to temperatures from 710 to 980°C (1300 to 1795 OF) for various times in argon atmosphere
Alloy 5 PM and C
»:
E.-- -
............
_.- - - -
---- - -
Waspaloy Chemical Composition. Waspaloy (UNS N 07001) (nominal). 19.50 Cr, 57.00 Ni, 13.50 Co, 4.30 Mo, 3.00 Ti, 1.40 AI, 2.00 Fe max, 0.07 C, 0.006 B, 0.09 Zr Similar Alloys (U.S. and/or Foreign). UNS N07001
Waspaloy: Microstructure. Waspaloy (265 HV), solution annealed 4 h at 1010 °C (1850 OF) and water quenched. Glyceregia. 200x
Characteristics A nickel-base, precipitation-hardening alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1080 °C (1975 OF) for 4 h; cooling is in air Aging. Alternative procedures are available: CD CD
Treatment at 845°C (1550 OF) for 24 h; cool in air Treatment at 760°C (1400 OF) for 16 h; cool in ail'
Stress Relieving. Full annealing is recommended because intermediate temperatures cause aging Annealing. Treatment is at 1010 °C (1850 OF); holding time is 4 h pel' inch of section. Minimum hardness is obtained by cooling rapidly from annealing temperature, to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections; ail' cooling is preferred for heavy sections of Waspaloy, because water quenching causes cracking. For complex shapes subject to excessive distortion, oil. Quenching often is adequate and more practical. For parts formed from strip or sheet, rapid ail' cooling usually is adequate, Rapid
cooling from the annealing or solution treating temperature does not suppress the aging reaction for some alloys, such as Astroloy. They become harder and stronger
Nickel-Base Superalloys /77
Waspaloy: Influence of different treatments. (a) The tensile properties of Waspaloy and (b) The Larson-Miller plot 1000
145
""
r-," " _1_ \
RT
LIVE GRAPH
390
Temperature, of 750 1110
' \ \\
1470
Treatment for turbine disks • Treatment for turbine blades
1500
72.5
500
217.5
\
\
co
D.. ~
D.. ~
'iii
co
"'"
145 vJ Ul
1000
~
vJ
00
Ul
...~
c:0
Cl
60 50
-
40
iii
30 20
- - Elongation - - - Reduction in area
--
c 0
a:
29 70 I
~
60
.il
50
Ii
/
40
,1 ~ ~
~
co
c
20
./
10
.~
:::l "0 Q)
a:
10 RT
200 400 600 Ternperature.vc
100
800
20
(a)
li e Q)
43.5
3
15. :::l
a:
\
\~
'"
.s 0
- - ./ IJ
30
\
~ 1il
\ \ \ \
200
?ft.
58
\\
15. :::l
72.5
200 70
.~
300
:::l
500
?ft.
400
~ 1il ~
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Treatment for turbine blades
o
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LIVE GRAPH
LIVE GRAPH
Treatlent for turbine disks
22 24 p= K (20 + log t)
29
14.5
26
(b)
Waspaloy: Time-temperature cracking diagram. Post-weld heat treatment cracking tendency as a function of aging time and temperature. Nominal composition: Ni - 20% Cr - 14% Co - 4% Mo - 3% TI- 1% AI
1900
LIVE GRAPH
Waspaloy
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1800 LL 1»' :;,
.....
1700
lIS
I»
1600
...
1500
a. E I»
~
/
(
Post-Weld Heat Treatment Cracking
<,
~
No Cracking
1400 1300 0 10
10'
---------10 2
Aging Time, min
105
78/ Heat Treater's Guide: Nonferrous Alloys
Waspaloy: Time-temperature diagram. Minor phase concentration as a function of temperature for long exposure times. Composition: Ni - 0.06% C -19.30% Cr-14.60% Co - 4.39% Mo - 3.08% Tl -1.42% AI- 0.051% Zr. Treatment: Solution treated at 1080 °C (1975 OF) for 4 h, aged in air at 760 to 1095 °C (1400 to 2000 OF) at 38°C (100 OF) intervals for 5000 h, and at 1150 °C (2100 OF) for 2000 h Very Abundant
Abundant
~
~lJ
Medium
f-
Q
~
~
~~23C6
(
\
o
..c: p.,
...o
Rare
\
Me
I-
1300
1400
\-X'_O_I
~ Very Rare
-
~O~
§
o_o_oJ \
1600
0
1600
I
I
1700
1800
,
I
1900
2000
2100
Temperature, of
Waspaloy: Microstructure. Waspaloy (265 HV) solution annealed 4 h at 1035 °C (1895 OF) and water quenched. 223 HV. Glyceregia. 100x
Waspaloy: Microstructure. Waspaloy, solution annealed 4 h at 1065 °C (1950 OF) and water quenched. Higher temperatures caused increased grain size, complete solutioning, and decreased hardness. Glyceregia. 100x
Nickel-Base Superalloys /79
Waspaloy: Microstructure. Waspaloy (42 HRC), solution annealed 4 h at 1010 °C (1850 OF), water quenched, aged 4 h at 845 °C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Glyceregia. 200x
Waspaloy: Microstructure. Waspaloy (42 HRC), solution annealed 4 h at 1010 °C (1850 OF), water quenched, aged 4 h at 845 °C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Tint etched to color matrix phase. 50 mL HCI, 50 mL Hp, and 1 9 K2 SP 5' 100x
Waspaloy: Microstructure. Waspaloy (42 HRC), solution annealed 4 h at 1010 °C (1850 OF), water quenched, aged 4 h at 845 °C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Higher magnification shows residual t' from hot working that was not dissolved. Glyceregia. 1000x
Waspaloy: Microstructure. Fully heat-treated Waspaloy showing MC and M23C5 carbides. 3400x
80 I Heat Treater's ~uide: Nonferrous Alloys
r------------------------------------------------, Waspaloy: Microstructure. Waspaloy (37 HRC), solution annealed 4 h at 1035 °C (1900 OF), water quenched, aged 4 h at 845°C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Left microstructure: etched in glyceregia. Right microstructure: tint etched in 50 mL HCI, 50 mL H20 , and 1 g K2Sp s' Both 100x
Waspaloy: Microstructure. Waspaloy (35 to 36 HRC), solution annealed 4 h at 1065 °C (1950 OF), water quenched, aged 4 hat 845°C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Left microstructure: etched in glyceregia. Right microstructure: tint etched using 50 mL HCI, 50 mL H20 , 3 g NH 4F . HF, and 1.5 g K2S20 S ' Both 100x
Waspaloy: Microstructures. Waspaloy (37 HRC), solution annealed 4 h at 1035 °C (1900 OF), water quenched, aged 4 h at 845°C (1555 OF), air cooled, aged 16 h at 760°C (1400 OF), and air cooled. Left microstructure: bright-field illumination. Middle microstructure: dark-field illumination. Right microstructure: differential interference contrast. Glyceregia. 100x
Nickel-Base Superalloys /81
Nimonic PE16 Chemical Composition. Nimonic PE16 (nominal). 16.50Cr, 43.00 Ni, 1.00 Co, 1.10 MO,1.20 AI, 33.00 Fe, 0.05 C, 0.10 Mn, 0.10 Si, 0.020 B
Characteristics A nickel-base alloy
Recommended Heat Treating Practice Solution Treating. Rapidly heat to 1100 °C (2010 "F) and maintain at temperature for 1 h; rapidly cool to an aging temperature between 625 and 950°C (1160 and 1740 "F); maintain at desired aging temperature for times varying between 15 and 3600 s, followed by rapid cooling to ambient temperatures
Nimonic PE.16: Time-temperature-precipitation diagram for carbides. Composition: Fe - 17.1 % Cr - 42.5% Ni - 3.1 % Mo - 1.2% Ti 1.3% AI - 0.03% Zr - 0.05% Mn - 0.0003% B - 0.08% C. Treatment: Specimens were rapidly heated to 1100 °C (2010 OF) and maintained at temperature for 1 h, then rapidly cooled to an aging temperature between 625 and 950°C (1160 and 1740 OF) and maintained at the desired aging temperature for times varying between 15 and 3600 s, followed by rapid cooling to ambient temperatures
LIVE GRAPH Click here to view
1100 u 0 ..
1000
w
~ 900 ~ a:::
x o
•e
no carbides identified TiC identified M23CS identified TiC and M23C6 identified ....
....
w
~ 0
?t=
c, ~
W
o 0
0
0
00
~
o
o o
e
~~-
I-
10
100 TIME, s
1000
Nimonic PK33 Chemical Composition. Nimonic PK33 (nominal). 18.50 Cr, 56.00 Ni, 14.00 Co, 7.00 Mo, 2.00 Ti, 2.00 AI, 0.30 Fe, 0.05 C, 0.10 Mn, 0.10 Si, 0.030 B
Characteristics A nickel-base alloy
Inconel600 Chemical Composition. Inconel 600 (UNS N06600) (nominal). 15.50 Cr, 76.00 Ni, 8.00 Fe, 0.08 C, 0.25 Cu max
Recommended Heat Treating Practice
Similar Alloys (U.S. and/or Foreign). UNS N0660
Solution Treating. Treatment is at 1120 °C (2050 "P) for 2 h. Cooling is in air
Characteristics
Stress Relieving. Treatment is at 900°C (1650 "F), Holding time is 1 h per inch of section
A nickel-base, solid-solution alloy
82/ Heat Treater's Guide: Nonferrous Alloys
distortion, oil quenchingoften is adequate andmore practical.For formed strip or sheet parts, rapid air cooling usually is necessary. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, such asAstroloy, they becomeharderand stronger
Annealing. Treatmentis at 1010°C (1850 OF). Holding time (15 min per inch of section) is to prevent grain coarsening. Minimal hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation of hardening phase. Waterquenchingis preferredandusually is necessary for heavy sections. For complex shapes subject to excessive
=
Inconel 600: Time-temperature grain boundary microstructure. LEGEND: Dotted lines minor grain boundary segregation or chromium depletion. Solid bars = maximum improvement in caustic SCC resistance. Composition: 73.66% Ni - 0.04% C - 15.36% Cr - 9.98% Fe - 0.40% Mn - 0.17% Si - 0.38% Cu - 0.17% AI- 0.20% Ti - 0.05% Co - 0.Q11 % S. Treatment: Annealed in a flowing hydrogen environment, followed by a thermal treatment in the temperature range 595 to 870°C (1100 to 1600 OF). Note: The grain-boundary carbide precipitate morphology was divided into four classes: fine discrete particles, semicontinuous precipitate, coarse semicontinuous precipitate, and large discrete precipitates. A floating time scale was used for each thermal treatment temperature so that a precipitate morphology could be assigned to each thermal treatment. The presence of a chromium-depleted layer and grain-boundary phosphorus segregation is also represented
1
1600lf
V/
5 hrs. '//////J
LEGEND: Dotted lines minor grain boundary segregation or chromium depletion Solid bars maximum improvement in caustic sec resistance
=
1
13DOlf
10
24 hrs.
=
V///-////// V / / / ///1_ Phosphorus Segregation
Chromium Depletion --§
1
12000f
10
100
24
hrs.
IZ ' l // /,////////1 li:iiii~~,i:ik=·"'---:.J
----
1
UDOlf
l.~_ ~-'", .!.
Fine Discrete Precioitates
10
24
•
hrs.
100
L/ ,;-t/>'///////) Semi-Continuous Precinitates
Coarse Semi-Continuou s Precioitates
2200 2100
1200 2l00°F
" -, ,
2000 1900 ~
° QI
'" B <'Il
large Discrete Precioitates
1100
,
1000 u °
1800
-
1700
QI
900
...;3
1600
I-l
'~"
1500
QI
I-<
1400
QI
QI
<'Il
...
800
e
QI
I-<
1300
700
1200 600
1100 1000 0.01
0..
0.1
1
Time, hr
10
100
Inconel 600: Time-temperature-carbide-precipitation diagram for material having various carbon contents. Broken line curves show time below solution temperature at the center of a 510 mm (20 in.) diameter round during air cooling from the indicated temperatures. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe - 0.25% Cu - 15.5% Cr. Treatment: Solution treated at 1150 -c (2100 OF) for 30 min, before exposure to precipitation temperatures.
LIVE GRAPH Click here to view
Nickel-Base Superalloys I 83
Inconel 600: Time-temperature-carbide-precipitation diagram for material having various carbon contents. Broken line curves show time below solutiontemperature at the center of a 250 mm (10 in.) diameterroundduring air coolingfrom the indicatedtemperatures. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe - 0.25% Cu - 15.5% Cr. Treatment: Solutiontreated at 1150 °C (2100 OF) for 30 min, before exposureto precipitation temperatures
2200
LIVE GRAPH
1200
2100
Click here to view
2000
1100
1900 I&<
° " I-<
GI
::I
u
III
1000
1800 1700
GI
900
1600
GI
H
H
;:J
u
III H
I-<
~ GI
u
°.
GI
1500
800
0-
S
GI
Eo-<
1400 1300
700
1200 600
1100 1000 0.01
0.1
10
1
100
Time, hr
Inconel 600: Time-temperature-sensitization diagram in two conditions. The curves enclose areas of high corrosion rates in boiling
70% nitric acid. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe - 0.25% Cu - 15.5% Cr. Treatment: Solutiontreated at 1095 °C (2000 OF) 2100
LIVE GRAPH Click here to view
1100
2000
< 0.01 ipm (3.0 mm/yr)
1900
I&<
° "
GI
I-<
;:l
u
co
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H
1000
SOlutio
1800
~ 0.10
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u
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900
1600
°. GI
H ;:J
SOl Pll.isl.it:/'Oll
1500
800
<5'/( 'l'~e
1400
• COldi1ted
1200
700
> 0.10 ipm (30 mm/yr)
600
1000 500
900 0.1
1 Time, hr
'"
0-
1100
0.01
III GI
WO~1c
1300
u
10
100
eClI
Eo-<
84/ Heat Treater's Guide: Nonferrous Alloys
Inconel 600: Time-temperature-sensitization diagram. Contour lines, corrosion rates in milligrams/dm 2/day, mils per year in boiling 65% nitric acid. No specimens failed the copper-copper sulfate-sulfuric acid test. Composition: Ni -7.92% Fe - 0.15% Cu • 0.06% C • 0.17% Mn - 0.007% S - 0.22% Si - 15.40% Cr. Treatment: Solution heat treated in argon at 1120 °C (2050 OF) for 2 h, water quenched, aged, and rapidly water cooled
Inconel 600: Time-temperature diagram. Light microscope evaluation of heat treated specimens. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti - 0.03% Mo - 0.03% N - 0.03% Cu - 0.16% AI - 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Etchant: 10% Br-ChaOH
LIVE GRAPH Click here to view
I
\
,-" , ,, , ,
1000
I I
10'00r--""'T--~--.,.--......,r----r--.....,
,-"'-',,I 90''l---f
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700
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,
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,
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0)
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600 \
\
1.0
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Time atTemperature, h
7001----
i 60011--~
1---1L1-~
1---411II
~
1---- 1-----4. ~-.....,...-__t
i ~
f
~
~
500
~
550
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~-
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\ \
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100
400t----1--....(
350_ _-::-~_ _~ _ - - : ~_ _~ _ ~ " " " '_ _-' 0,1 1000 10000 .100
Heat treatment time, h
LIVE GRAPH Click here to view
LEGEND: No precipitate ~ Fine GB particles t> Massive GB particles Specimen identification ~ GB and ITB particles • GB, ITB and TB particles
o
o
GB = Grain boundary ITB Incoherent twin boundary TB Coherent twin boundary
= =
Nickel-Base Superalloys I 85
Inconel 600: Time-temperature diagram. Scanning electron microscope evaluation of heat treated specimens. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti - 0.03% Mo - 0.03% N - 0.03% Cu - 0.16% AI - 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Etchant: 10% Br-Ch 30H
Inconel 600: Time-temperature diagram. Intercrystalline corrosion susceptibility. Test conditions: 45 h boiling in solution of 21 g Fe2(S04)3 + 100 mL H2S04 + 400 mL H20, followed by bend test and SEM. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti 0.03% Mo - 0.03% N - 0.03% Cu - 0.16% AI- 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF)
1000 1000 900
.
4 ..
0
fj< ~- 700
i . ..
600
j
3
2
900
1'\ V 800
,.
.lII 1'\ V .lII 1'\ ,,,,",
. "'
a.lll 1'\
1"...
0
0
i
~cu
~
'\ .J
cu
E-o 600
...
~
"lil
... ~
..
=
6.l11 1'\ I'"
"lil
500
700
::l
9 .. ~
IS ..
... II'
..
"lilcu
1'\
E-o
'Il II'
"lilcu
500
= 350
121'~'\
51''''
400
"
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,.,
400
0,1
10
100
Heat treatment time, h
1000
t---+----{
10000 350'---~--~---~--...J.~-~~-~_ 0,1 1000 10000
LEGEND:
o No precipitate ~ Fine GB particles () Massive GB particles e GB and ITB particles • GB, ITB and TB particles
GB ITB TB
= Grain boundary = Incoherent twin boundary = Coherent twin boundary LIVE GRAPH Click here to view
LEGEND:
o No attack ~
GB etching GB fissuring II GB cracking • Disintegration
e
GB = Grain boundary ITB Incoherent twin boundary TB Coherent twin boundary
= =
86/ Heat Treater's Guide: Nonferrous Alloys
1000
Inconel 600: Time-temperature diagram. Transmission electron microscope evaluation of heat treated specimens. Composition: Ni - 15.6% Cr - 8.1% Fe - 0.2% Ti - 0.03% Mo - 0.03% N - 0.03% Cu 0.16% AI - 0.040% C - 0.27% Si - 0.13% Mn. Grain size: ASTM 6-7. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Carbon-extraction replicas of Br-methanol etched transverse cross sections of tube specimens
4~ 00
00
t"\ ...V
... 1"\1.1
3 ....
2~
8 ....
....
.,1"\
1'\
,~
6.
.....
400
350
13....
'"
"\
16 .t1111 "\
,,,. '\
I 'I
100
5
0,1
.... .,
1'\
"
10
1000
10000
Heat treatment time, h
LEGEND:
e> Very fine GB particles ()
Coarse or dendritic GB particles No precipitate except globular MC x or M(C, N) particles Q GB and ITB particles
o
GB ITB TB
= Grain boundary = Incoherent twin
boundary
= Coherent twin boundary
2200 ,--------r--------r-------r-----.....,.. 1200
Inconel 600: Time-temperature-carbideprecipitation diagram. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe 0.25% Cu - 15.5% Cr. Treatment: Solution treated at 1150 °C (2100 OF) for 30 min, before exposure to precipitation temperatures
2100 ~_-----11100
2000 1900 ~
woo u
1800
°
0
Ql
1700 900
I-< ~
u
1600
Ql
P-
eQl f-4
III I-<
1500
800
~
e
Ql
1400
f-4
700
1300 1200 1100 WOO
0.01
~
u
llJ
I-<
~
0.1
1 Time, hr
10
100
LIVE GRAPH Click here to view
Nickel-Base Superalloys I 87
Incoloy 600: Time-temperature-carbide-precipitation diagram. Nominal composition: Ni - 0.08% C - 0.5% Mn - 8% Fe - 0.25% Cu 15.5% Cr. Treatment: Solution treated at 1150 °C (2100 OF) for 30 min, and cold worked 25% before exposure to precipitation temperatures
2200
LIVE GRAPH Click here to view
1200
2100 1100
2000 1900 ~
°
1700
'"'
1600
;:J I-J
1000 u
1800
°
900
I'll
I'll
'
0-
S
E-<
'"'
;:J I-J
'0-"'
1500
800
S
1400
E-<
1300
700
1200 600
1100 1000 0.01
10
1
0.1
100
Time, hr
Alloy 600: Time-temperature-sensitization diagram. Composition: 74.5% Ni - 0.029% C - 0.211% Mn - 8.05% Fe - 0.003% S - 0.180% Si - 0.219% Cu - 14.09% Cr - 0.464% AI- 0.259% Ti - 0.034% Co - 0.007% P - 0.002% B - 0.026% Mg. Treatment: Mill annealed and thermally aged at temperatures ranging from 300 to 600°C (570 to 1110 OF) for times ranging from 1 to 10,000 h. Corrosion tests were conducted in accordance with a modification of ASTM A-262 Practice C (Huey) Samples were immersed in a boiling 25% nitric acid solution for 48 h. Corrosion values in mg/cm 2/day are listed below each symbol. PartiallGA, attack which is 1 grain or less deep
LIVE GRAPH
NO IGA
Click here to view
700
"
• D...
u lJJ
a:
600
::J
e
0.~2
•
e e 0,'5 0.50
e 0.520.610.510.55 e
e
e 0.550.590 .• 5
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e
"
a
0.5' 0.100.76
&
:.
PARTIAL IGA
e
-
IGA
•
0.51
~
a:
a:
lJJ Q...
500
"
0 .• 3
z;
A
O. EJ
I. 10
•
".11
•
0.37
~
e
e
e
"
A
1.271.272.30
lJJ
t-
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Z
~oo
0.29
"
L:l
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A
0.7.
a::
•
300
10 0
10 1
TIME
•
"
"
...
0,'0
0.HO.52
0."1"1 1.3&
102
10 3
10'
(HOURS)
88/ Heat Treater's Guide: Nonferrous Alloys
Inconel601 Chemical Composition. Inconel 601 (UNS N06601) (nominal). 23.00 Cr, 60.50 Ni, 1.35 AI, 14.10 Fe, 0.05 C, 0.5 Cu max Similar Alloys (U.S. and/or Foreign). UNS N06601
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice
Annealing. Treatment is at 980°C (1795 "F), Minimum hardness is obtained by rapid cooling from the annealing temperature. Water quenching is preferred, and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quench often is adequate and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid cooling from annealing or solution treating temperature does not suppress the aging reaction of some alloys, such as Astroloy. These alloys become harder and stronger
Solution Treating. Treatment is at 1150 °C (2100 OF) for 1 h. Cooling is in air
Inconel604 Chemical Compositlon.lnconel604 (nominal). 16.00 Cr, 74.00 Ni, 2.25 Nb, 7.50 Fe, 0.02 C, 0.03 Cu max
Characteristics A nickel-base, solid-solution alloy
Inconel617 Chemical Composition.lnconel617 (nominal). 22.00 Cr, 55.00 Ni, 12.50 Co, 9.00 Mo, 1.00 AI, 0.07 C
Characteristics A nickel-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1175 °C (2145 OF) for 2 h. To get an adequate quench after solution treating, it is necessary to cool below about 540°C (1000 OF) rapidly enough to prevent precipitation in the intermediate temperature range. For sheet metal parts of most alloys, rapid air cooling suffices. Oil or water quenching frequently is required for heavier sections not subject to cracking
Inconel625 Chemical Composition. Inconel 625 (UNS N06625) (nominal). 21.50 Cr, 61.00 Ni, 9.00 Mo, 3.60 Nb, 0.20 Ti, 0.20 AI, 2.50 Fe, 0.05 C
cooling suffices. Oil or water quenching frequently is required for heavier sections not subject to cracking
Similar Alloys (U.S. and/or Foreign). UNS N06625
Stress Relieving. Treatment is at 870°C (1600 "F) for 1 h per inch of section
Characteristics A nickel-base, solid solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1150 °C (2100 oF) for 2 h. To get an adequate quench after solution treating, it is necessary to cool below about 540°C (1000 "F) rapidly enough to prevent precipitation in the intermediate temperature range. For sheet metal parts of most alloys, rapid air
Annealing. Treatment is at 980°C (1795 OF). Holding time is 1 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature to prevent precipitation of hardening phases. Water quenching is preferred, and usually is necessary for heavy sections; for complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from sheet or strip, rapid air cooling usually is adequate. Rapid air cooling does not suppress the aging reaction of some alloys, such as Astroloy; they become harder and stronger
Nickel-Base Superalloys I 89
Inconel 625: Time-temperature-precipitation diagram. Composition: Ni - 0.03% C - 0.10% Mn - 0.25% Si - 0.008% S 0.011% P -22.1% Cr-1.89% Fe - 0.20% AI - 0.22% Ti - 9.1% Mo - 3.35% Nb+Ta 0.20% W - 40 ppm B - 50 ppm 0 - 480 ppm
900
800 t-------<:>----li!/
o :£
N
+
LIVE GRAPH
~
100 t---o-\:--+-O-~:>---O---O~~"---~~
":3
Click here to view
!J
600 t---4:r---+--o-;llo",()o---<>------O-----{ o
no incoherent phases NiS(Nb Mo) needles and rods
•
SOD,
IlJ rods
10
100
10000
1000
Aging Time, h
t
20'
600
Sh20'
M 2SC6 (1)
o
\\
~
~
~
700
"",<,
~""I
J
I
\ . NiS(NbMo)
f
~
\
_\
<,
\ '.
I'
.........
j
i""'--.
....
10 1
"
NiS(NbX)/'''''
--
-'I""-
800
-.
I
, \
Inconel625: Time-temperature-precipitation diagram. (1) For short aging times, M2aCais precipitated at grain boundaries, dislocations and twin boundaries. (2) M2aCaprecipitates within the grains and grow slowly (for t >50 h, needle and plate-shaped carbides are formed). Composition: Ni 0.016% C - 0.3% Si - 0.05% Mn - 0.005% P - 0.006% S 21.8% Cr - 0.027% Co - 9.05% Mo - 0.2% Ti - 0.1% AI- 2.4% Fe - 0.023% Cu - 3.7% Nb-Ta - 1 ppm B. Treatment: Solution annealed at 1150 °C (2100 OF) for 3 h, water quenched. Aging done in a vacuum
166h40' 450h 1000h
M2SC6 (2)
rr
600
::s
60h
I
o
t
16h40'
LIVE GRAPH
'\
Click here to view
'\
r>
I lOS
Aging time, t, min
1150 1100 1050
o o
~-
/'
1000 950 I"""T
900
f8. aso
~ ~~
i
J
"
--
150
100
650
.....
"""-..
-
~
'~
..........
............... r---
--............
..... .............
M~
r----........
600 Q33
r-c
---- ...
.........
:.- ~
~ I
"
'" I'-....
-«: r-........ ~
"'-- t--.
............
=
~ 0..;::"'000.
Alloy: Inconel 625: Time-temperature-precipitation diagram. Gamma double prime - NiaNb is tetragonal = gamma double prime. Nia(Nb,Mo) - orthorhombic delta phase. Composition: Ni 0.029% C - 0.34% Si - 0.38% Mn - 0.009% P 0.004% S - 22.67% Cr - 1.33% Fe - 8.75% Mo0.17% li-3.72% Nb-0.15%AI-0.0071%N. Treatment: Solution treated at 1150 °C (2100 OF) for 3 h, water quenched, followed by a precipitation anneal at temperatures between 600 and 1100 °C (1110 and 2010 OF) for 5 min to 3000 h. Note: During aging, carbides M2aCa and MaC, carbonitrides of type MX, the intermetallic phase gamma+-NbNi a, (Mo,Nb)Nia and, to a small extent, eta-Nl.Tl precipitated out. A phase was also observed, which could not be identified exactly. It is presumably a niobium carbonitride of type M2X but could also possibly be AIN
--
-
AIN/M2X _
!,-"M2SC6 (end)'
I'"
l .....
r--... ~
f:::: ~.
~ ..... ~
(Mo, Nb) NiS
~?~Nir
10 3 30 SO Annealing Time, h
100 l!i43 300SOO 1000
3000
90 I Heat Treater's Guide: Nonferrous Alloys
Inconel 625: Time-temperature-sensitization diagram. Nominal composition: 61.0% Ni+Co - 21.5% Cr - 9.0% Mo - 3.65% Nb+Ta 2.5% Fe - 0.05% C - 0.25% Mn - 0.008% S - 0.25% Si - 0.2% AI- 0.2% Ti. Treatment: annealed at 980°C (1795 OF) for 30 min, water quenched, subjected to sensitizing heat treatments of 540 to 870 °C (1000 to 1600 OF) for 1 h, and air cooled. Specimens were then subjected to the ASTM A262 boiling 65% nitric acid test 1800 (982)
LIVE GRAPH Click here to view
1700 (927)
u "" •.....
.'"
1600 (871)
OJ"
...
1500 (816)
;:l
.u
...OJ
l\l
1400 (760)
~ I-<
< 40
mpy
1300 (704)
IlO
t=
~
N
~
.u
1200 (649)
.,
~
eOJ
II)
1100 (593) 1000 (538) 0.01
0.1
1
10
100
1000
Time at Temperature, hr
Inconel625: Time-temperature-sensitization diagram. Nominal composition: 61.0% Ni+Co - 21.5% Cr - 9.0% Mo - 3.65% Nb+Ta2.5% Fe - 0.05% C - 0.25% Mn - 0.008% S - 0.25% Si - 0.2% AI - 0.2% Ti. Treatment: Annealed at 1150 °C (2100 OF) for 30 min, water quenched, subjected to sensitizing heat treatments of 540 to 870°C (1000 to 1600 OF) for 1 h, and air cooled. Specimens were then subjected to the ASTM A262 boiling 65% nitric acid test 1800 (982)
LIVE GRAPH Click here to view
u-
e,
.....
1700 (927)
1600 (871)
,j
...;:l
...
1500 (816)
0.
1400 (760)
l\l
...OJ e
OJ I-<
00
....Nc
....u .... III
c
< 40
ropy
1300 (704) 1200 (649)
CI
II)
1100 (593) 1000 (538) 0.01
0.1
L
LO
Time at Temperature, hr
100
1000
Nickel-Base Superalloys /91
Inconel 625: Time-temperature-sensitization diagram. Correlation of sensitization with carbide precipitation MaCis the predominant carbide. Labels, %Cr in extracted carbide residues. Broken-line curves enclose areas of moderate sensitization. Nominal composition: 61.0% Ni+Co - 21.5% Cr - 9.0% Mo - 3.65% Nb+Ta - 2.5% Fe - 0.05% C - 0.25% Mn - 0.008% S - 0.25% Si - 0.2% AI- 0.2% li. Treatment: Annealed at 980°C (1795 OF) for 30 min, water quenched, subjected to sensitizing heat treatments of 540 to 870 °C (1000 to 1600 OF) for 1 h, and air cooled. Specimens were then subjected to the ASTM A262 boiling 65% nitric acid test
11100 (982)
LIVE GRAPH Click here to view
.....
4
J
1700 (927)
U
0
...oi
a..
1500 (816)
Gl
1400 (760)
...
~
1300 (704)
16
1200 (649)
6
\
N
""u ""•c:: " I II
}-
.
6
fo4
1lO
~
,,
Gl
~
3
')
6
1600 (871)
1&0 0
... ........
1100 (593) 1000 (538) 0.0'1
10
1
0.1
1000
100
Time at Temperature, hr LEGEND: Labels %Cr in extracted carbide residues Broken-line curves enclose areas of moderate sensitization and excessive sensitization from prior diagram
=
Inconel 625 Relativeamounts and compositions o~hases present after anneal at 980°C (1795 OF) for 1 h, water quench an age treatments listed below 'Thmperature OC (oF)
649(1200)
704(1300)
760(1400)
816(1500)
871(1600)
927(1700)
Timeat 'Thmperature, h
1 10 100 1000 1 10 100 1000 1 10 100 1000 1 10 100 1000 1 10 100 1000 1 10 100 1000
Cb(C,Nl M M M M M M
Phase.present(a) M.C' M.C A A A A A A A
R
R A
MR M M
M MR
M R
M
A A A A A MR MR A A MR R A A
A VA
M
R A A R
4 A
Mt£1i
M A A MR
Ni
18 17 25 40 18 21 40 26 19 23 28 31 21 24 38 39 17 38 36 36 18 29 40 35
(a)A, abundant; R, rare;M, medium; VA,very abundant. (b) Iron and titanium
Residue analysis, % Cr Cb Mo
6 8 10 17 6 9 14 21 6 9 7 7 7 8 5 4 6 5 3 3 7 5 3 4
40
38 32 19 40
35 19 18 40
32 23 17
37 30 21 21 39 31 27 31 39 34 32 30
30 29 26 19 30 27 21 31 29 30 40
43 30 33 33 34 30 27 32 27 29 28 23 26
Otber(b)
6 8 7 5 6 9 6 4 6 6 2 2 5 5 3 2 8 4 2 3 7 4 2 5
92/ Heat Treater's
GUid~:
Nonferrous Alloys
Inconel625: Time-temperature-sensitization diagram. Correlation of sensitization with carbide precipitation. Labels, %Cr in extracted carbide residues. Broken-line curves enclose areas of moderate sensitization. Nominal composition: 61.0% Ni+Co - 21.5% Cr - 9.0% Mo - 3.65% Nb+Ta - 2.5% Fe - 0.05% C - 0.25% Mn - 0.008% S - 0.25% Si - 0.2% AI- 0.2% Tl, Treatment: Annealed at 1204 °C (2200 OF) for 1 h, water quenched, subjected to sensitizing heat treatments of 540 to 870°C (1000 to 1600 OF) for 1 h, and air cooled. Specimens were then subjected to the ASTM A262 boiling 65% nitric acid test 1800 (982)
LIVE GRAPH Click here to view
,.., o
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5
1700 (927)
. I-.
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...
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... 0)
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.... III
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5
1600 (871) 1500 (816)
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.... ....
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---
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10
12 14
,
1400 (760)
I
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1300 (704)
" " "-
18 "-
33
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10
1200 (649)
--
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II)
1100 (593)
--
1000 (538) 0.01
1
0.1
1000
100
10
Time at Temperature, hr
Inconel 625 Relative amounts and compositions of phases present after anneal at 1205 °C (2200 OF) for 1 h, water quench and age treatments listed below Thmperature ·C (OF)
649(1200) 704(1300) 760(1400)
816(1500)
871 (1600)
827(1700)
Timeat Thmperature,h Ch(C,N)
100 100 1000 10 100 1000 10 100 1000 1 10 100 1000 1 10 100 1000
A A A A A A A M A A
A M
Ph.... present(a) MoC ALC' Moen M,aC.
R
R M A
R
R R R R
A
M R
R A 4 M A A A A A A A
R A
R A
Nl
Residueanalysis, % Cr Ch Mo
12 7 10 9 7 13 9 16 21 10 11 21 19 7 15 19 16
10 18 33 13 18 14 12 10 12 13 6 8 4 5 5 8 4
(a)A, abundant; R, rare; M, medium; VA, very abundant. (b) Iron and titanium
49 48 27 44 48 32 48 41 24 52 54 37 33 61 47 36 44
13 9 13 9 9 29 12 20 34 11 19 28 39 15 23 32 32
Olher(h)
16 18 17 25 18 12 19 13 7 14 10 6 4 13 10 5 4
Nickel-Base Superalloys /93
Inconel625: Time-temperature-precipitation diagram. Composition: 60.95%Ni - 22.21 % Cr - 3.61 % Fe - 8.97%Mo - 3.50% Nb+Ta0.19%AI- 0.27% Ti - 0.26%Si - 0.05% Mn - 0.006%P - 0.004%S - 0.08%Cu - 0.03%C. Treatment: Solutionannealed materialobtained by heattreating millannealedmaterialat 1150 °C (2100OF) for 1 h, aircooled.(a) Databasedon solution-annealed material. (b) Databased on mill-annealed material
r
'"{fin
• y" PRESENT ~ H6C(2) PRESENT • 6 PRESENT ... \I PRESENT OAcv PHASES NOT PRESENT
1600
1500
........ u::-
1~00
«:
S ... :c ...... D.
'" :!: a
..J
1300.
1200.
0
:z:
1100
1000
900 \0
LIVE GRAPH
\00
10,000
1000
(a) data based on solution-annealed material (b) data based on mill-annealed material
Click here to view
Inconel625: Time-temperature-aging diagram. Contoursof equalyield strength(ksi).Composition: 60.64%Ni - 0.02%C - 0.09% Mn - 0.19%Si - 22.14%Cr- 4.06%Fe- 9.0% Mo - 3.39%Nb+Ta- 0.22%AI- 0.24%Ti - 0.001 % B - 0.05%Co.Treatment: Hot-rolled, nucleated at 650°C (1200OF) for 10 h, then aged as shown
x - OBSERVED YIELD
STRENGTH (CALCULATED YIELD STRENGTHI 6- CALCULATED MAXIMUM YIELD STRENGTH
LIVE GRAPH Click here to view
------
.... II.
I 1300
a:
:> t-
el
...a:
4.
2 ~ 1200
"<;z el
124.8 X 1123.11
90
100
110
120
130
94/ Heat Treater's Guide: Nonferrous Alloys
1200 . - - - - - - - - - - - - - - - - - - - , 1100 1000
Alloy 625: Time-temperature-precipitation diagram. Composition: Ni - 20.5% Cr - 8.2% Mo - 4.3% Fe - 3.6% I---F==========~ Nb - 0.1% Co - 0.1% AI- 0.1% Ti - 0.1% Si - 0.1% Mn0.03% C. Treatment: Solution annealed at 1150 °C 1---F'~~~~""""'-:::~------1 (2100 OF), then aged at 600 to 1075 °C (1110 to 1965 OF)
• • • •
<:> 900 t----+O---.......... o
-
~
--..;;::=_ _::::--~"""'-ii::::~--l
LIVE GRAPH Click here to view
800 I------_....,;:;::=""'-=--~_-_Io___~
.a m700 t----------Ml--~IIlollro::::---_t C.
.....
E 600 1---------~ -__4~---I
~
500 2 10·
0
10 10 Time (hr.)
LEGEND:
•
MC
a
MeC
•
M2S C6
X
gamma double prime
A
delta
1
x- OBSERVED YIELD
STRENGTH ICALCULA'TED YIELD STRENGTH A-CALCULATED MAIlIMIIM YIELD STRENIITH
1400
Inconel 625: Time-temperature-aging diagram. Contours of equal yield strength (ksi). Composition: 60.64% Ni - 0.02% C - 0.09% Mn - 0.19% Si 22.14% Cr - 4.06% Fe - 9.0% Mo - 3.39% Nb+Ta - 0.22% AI - 0.24% Ti - 0.001 % B 0.05% Co. Treatment: Hot-rolled, millannealed, then aged as shown
~_ _- - - - - - 94.9 ~ 1:500 I
'"cr
lC 1107.01 105.8
_ _- - - - - -
:l
l-
e
LIVE GRAPH
cr
'"
~ 1200
I-
Click here to view
127.1 lC 1125.81
ll.
A 1128.:51
CI
Z
<; e
118.8 1120.11
..".~ ~------~---------~ :=; "
o
10
20
:50
40
I
I
I
90
100
110
120
1:50
Alloy 625 (Nicrofer 6020 hMo): Time-temperature-toughness diagram. Iso-notched impacts tests (iso-impact strength curves) at room temperature. Composition: Ni - 22.25% Cr - 9.27% Mo - 2.05% Fe - 0.1% Mn - 0.04% Si - 0.3% Ti - 3.42% Nb+Ta - 0.14% AI- 0.011 % C. Treatment: Annealed at 1120 °C (2050 OF) for 50 min and aged as shown
LIVE GRAPH Click here to view
100 0
o
"ai... 90 0
~ .........
e800 :l
Ql
a.
sE 70 0
~
~OO
!lll",,~
150 J cm 2
III
.!: 60 0
. r-..... r-- -. ...
50
"""
~ e--....
t""'--. I""-
'iij
Ql
~ 500
ca
40
-
1
10
100 tlme,h
1000
Nickel-Base Superalloys /95
Inconel625: Time-temperature-aging diagram. Contours of equal yield strength (ksi). Composition: 60.64% Ni - 0.02% C - 0.09% Mn - 0.19% Si - 22.14% Cr - 4.06% Fe - 9.0% Mo - 3.39% Nb+Ta - 0.22% AI- 0.24% Ti - 0.001% B - 0.05% Co. Treatment: Hot-rolled, then aged as shown
x-
OBSERVED YIELD STRENGTH ICALCULATED YIELD STRENGTHI A - CALCULATED MAXIMUM YIELD STRENGTH
LIVE GRAPH Click here to view
98.0
...~ 1300 III
a:
1112.51
~
112.5
tC(
a:
III
Go
~
t-
12B.1 X 1128.01
112B.61 A
1200
110
el
z
el C(
1118.81 X 118.7
~-----------------
1100
90.4
GO 60 70 80 AGING TIME - HOURS
90
I
I
100
110
I 120
1 130
Inconel625: Time-temperature-aging diagram. Contours of equal yield strength (ksi). Composition: 60.96% Ni - 0.02% C - 0.12% Mn - 0.31% Si - 21.94% Cr - 3.82% Fe - 8.94% Mo - 3.47% Nb+Ta - 0.21% AI- 0.20% Ti - 0.06% Co - 0.001% B. Treatment: Hot-rolled, aged as shown OBSERVED YIELD STRENGTH ICALCULATED YIELD STRENGTHI A - CALCULATED MAXIMUM YIELD STRENGTH
I( -
LIVE GRAPH Click here to view
1400
.
_---------X9ii::6------- __ X 98.6
=__=====__---·---~::::::==================:=::-:::::::=-:
0, 1300Ej~::=--------
III
a:
------=::: === II 10. 71
::>
t-
C(
a: ~
:I ~ 1200
I(
109.8
133.1 1132.211( A 1133.91
el
z
G C(
124.5 X 1124.51
10
20
30
40
50
60 70 80 AGING TIME - HOURS
90
100
110
120
130
96/ Heat Treater's Guide: Nonferrous Alloys
Inconel625: Time-temperature-aging diagram. Contours of equal yield strength (ksi). Composition: 60.96% Ni - 0.02% C - 0.12% Mn - 0.31% Si - 21.94% Cr - 3.82% Fe - 8.94% Mo - 3.47% Nb+Ta - 0.21% AI- 0.20% Ti - 0.06% Co - 0.001% B. Treatment: Hot-rolled, aged as shown
x- OBSERVED YIELD
STRENGTH ICALCULATED YIELD STRENGTH1 ll. - CALCULATED MAXIMUM YIELD STRENGTH
LIVE GRAPH Click here to view
_.-------X~6-----II 98.6
__
... ". 1300 tal II:
••
...="
~ ~1128.11
~
tal
~
~
:::: =
--"ljjjI05i6.UO~IJx~I~06~.9!:======:;;:;~~~~====:::::::: 1110.71 X 109.8 X
1200
1"~·761 II...
\!)
z
l
129.0 X 12~.8 127.0 130.7 130
120
111~X==-
iii c(
20
30
40
so
60
70
lI.
1133.91
_
124.~ X 1124.51
--.:~~~
114.2
10
133.1 X 1132.21
80
110
100
110
120
130
AGING TIME - HOURS
Inconel 625: Time-temperature-precipitation diagram. Lower gamma double prime limit determined by hardness measurements. Nominal composition: Ni - 0.06% C - 3% Fe - 21.5% Cr - 9% Mo - 4% Nb. Treatment: Solution annealed, then aged 2000
LIVE GRAPH
-- ---
~---~ ,. Cb(C.NI ce IC.N) Rare
Click here to view
1800
1100 (M6C 2
1000
/
I
, I
fa<
0
1600
i
::s -:;; 1400
. Q)
0.
8 ~ 1200
900
Film (M6C)
I
0
0
\ \ \
,,
800 i::s
e
... ....
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700
Q)
f-<
600 1000 500
800 0.1
~
1.0
10
Time,h
100
1000
10,000
Nickel-Base Superalloys /97
Alloy 625 (Nicrofer 6022 hMo): Time-temperature-toughness diagram. Iso-notched impacts tests (iso-impact strength curves) at room temperature. Composition: Ni - 21.9% Cr- 8.94% Mo -1.4% Fe - 0.03% Mn - 0.04% Si - 0.18% Ti - 3.74% Nb+Ta - 0.16% AI- 0.03% C. Treatment: Annealed at 980°C (1795 OF) for 50 min and aged as shown
LIVE GRAPH Click here to view
1000
o
""""
"€900
1< "'"
e800 :::l
l""'l-..
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E 700
.!
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400
1
10
100 tlme,h
1000
Nimonic 75 Chemical Composition. Nimonic 75 (nominal). 19.50 Cr, 75.00 Ni, 0.40 Ti, 0.15 AI, 2.50 Fe, 0.12 C, 0.25 Cu max
Recommended Heat Treating Practice
Characteristics
Annealing. Treat at set temperature of 1050 °C (1920 "F); soak time is between 15 minutes min and 3 h max. Cooling rate is not critical
A nickel-base, solid-solution alloy
Stress Relieving. Annealing serves this purpose
RA·333 Chemical Composition. RA-333 (UNS N06333) (nominal). 25.00 Cr, 45.00 Ni, 3.00 Co, 3.00 Mo, 3.00 W, 18.00 Fe, 0.05 C
Characteristics A nickel-base, solid-solution alloy
NA·224 Chemical Composition. NA-224 (nominal). 27.00 Cr, 48.00 Ni, 6.00 W, 18.50 Fe, 0.50 C
Characteristics A nickel-base, solid-solution alloy
5 ..81 Chemical Composition. Alloy S-816 (UNS R30816) (nominal). 20.00 Cr, 20.00 Ni, 42.00 Co, 4.00 Mo, 4.00 W, 4.00 Nb, 4.00 Fe, 0.38 C Similar Alloys (U.S. and/or Foreign). UNS R30816
°C (1000 OF) rapidly enough to prevent precipitation in the intermediate temperature range. For most alloys, rapid air cooling is adequate. For heavier sections not subject to cracking, oil or water quenching frequently is required
Characteristics
Stress Relieving. See annealing
A cobalt-base alloy
Annealing. Treatment is at 1205 °C (2200 OF); holding time is 1 h per inch of section. Full annealing is recommended if further fabrication is performed. Otherwise, the alloy can be stress relieved at about 55°C (l00 OF) below the annealing temperature
Recommended Heat Treating Practice Solution Treating. Treatment is at 1175 °C (2145 OF) for 1 h. To provide adequate quench after solution treating, it is necessary to cool, below 540
5tellite Chemical Composition. Stellite 68 (nominal). 30.00 Cr, 1.00 Ni, 61.5 Co, 4.50 W, 1.00 Fe, 1.00 C
Stellite 68: Microstructure. Solution annealed at 1230 °C (2250 OF) and aged 8 h at 900°C (1650 OF). Structure is M7C3 and M23C6 carbides in a fcc matrix. Electrolytic: HCI and H202. 500x
Characteristics A cobalt-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1230 °C (2250 OF) for 1 h; parts are air-cooled
Stellite 68: Microstructure. Solution annealed at 1230 °C (2250 OF) and aged 8 h at 900°C (1650 OF). M7C3 and M23C6 carbides in a predominantly fcc matrix with some hcp crystals. Electrolytic: HCI and HP2' 500x
Stellite 68: Microstructure. Solution annealed at 1230 °C (2250 OF) and aged 8 h at 1150 °C (2100 OF). Dark areas around primary MP3 show it changing to M23C6 • Matrix is fcc. Electrolytic: 2% H2Cr04 ; KMn04 stain. 500x
Cobalt-Base Superalloys /99
Haynes 25; L·605 Chemical Composition. Haynes 25 (L-605), UNS R30605 (nominal). 20.00 Cr, 10.00 Ni, 50.00 Co, 15.00 W, 3.00 Fe, 0.10 C, 1.50 Mn Similar Alloys (U.S. and/or Foreign). UNS R30605
Characteristics A cobalt-base, solid-solution alloy
Recommended Heat Treating Practice Solution Treating. Treatment is at 1230 °C (2250 OF) for 1 h; parts are rapid air-cooled Aging, Occurs at elevated temperatures in service
Stress Relieving. Full annealing is recommended; otherwise, material can be stress relieved at approximately 55 °C (100 "F) below annealing temperature Annealing. Parts are annealed at 1230 °C (2250 OF), and held at temperature for 1 h per inch of section. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation hardening phases. Water quenching is preferred and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. Rapid air cooling usually is adequate for parts formed from strip or sheet. Rapid cooling from annealing or solution treating temperature does not suppress aging reaction of some alloys, such as astroloy. They become harder and stronger
Haynes 25 (L-605): Stress rupture curves. 1ODD-h stress-rupture curves of wrought cobalt-base (Haynes 188 and L-6D5) and wrought iron-base superalloys
1380
1560
Temperature, of 1740
1920
LIVE GRAPH Click here to view 550 f - - - - - - - - - + - - - - - t - - - - - + - - - - - - - - - - - l - - - - - - - - t 79.8
'\
tt--------t-----t------+------f--------------l72.5
450 I\--_\__ ,,-----+-----+------+---------1f----------1 65.3 \ . \ Incoloy 901
400 f--\-\.\-,-\\ - - - + - - - - - - - + - - - - - + - - - - - t - - - - - - - - - J 58.0
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750
850
950 Ternperature.vc
1050
'-
7.3
100 I Heat Treater's Guide: Nonferrous Alloys
Haynes 25 (L-605): Microstructures. Microstructures of Haynes 25 and 188 after various heat treatments. (a) Haynes 25, solution annealed at 1205 °C (2200 OF) and aged for 3400 h at 815°C (1500 OF). Structure is made up of precipitates of MsCand C02W intermetallic compound in an fcc matrix. (b) Haynes 25, solution annealed at 1205 °C (2200 OF) and aged for 3400 h at 870°C (1600 OF). Structure is same as (a). (c) Haynes 25, solution annealed at 1205 °C (2200 OF) and aged for 3400 h at 925°C (1695 OF). Structure is same as (a), but MsC is considered primary, while C0 2W is considered secondary. All at 50Ox
(a)
(b)
Haynes 25 (L-605): Microstructure. Solution annealed at 1205 °C (2200 OF) and aged 3400 h at 650°C (1200 OF). Structure is MsC and M23CS carbides in a mixed fcc and hcp matrix. Electrolytic: HCI and H20 2 • 500x
(c)
Haynes 25 (L-605): Oxidation resistance. (a) In dry air for Haynes 188 versus Hastelloy X and L·605 alloys showing continuous penetration from original thickness. (b) Static values at 1100 °C (2010 OF) in air with 5% water vapor
LIVE GRAPH Click here to view 1600 ~ 75 :i!! 64 ~ 50
g 38
1800
13
V
&0
870
1900
2000
..J
L-605"",
,/'"
-V
.~ 25
~
Temperature. OF
1700
925
~
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2100 3.0 ~ 2.5 ~ 2.0
E
g
1.5 J.,.v. I V Hay~es 188- 1.0 .~ 0.5 ~
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9BO
1035
1095
o
1150
&
Ternperature.v'C
(0)
0.50
320
0.25
160
N
Incoloy MA 956
E
Haynes 25 (L-605): Microstructure. Solution annealed at 1205 °C (2200 OF) and aged 3400 h at 815°C (1500 OF). Structure is precipitates of MsC and IC02W" intermetallic in a fcc matrix. Electrolytic: HCI and H20 2 • 500x
~ E
~ -0.25
c: ro s: o fI) fI)
\
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ro
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--.......
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C
~ E
~
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ai
go
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-320 ~ ro ::2 -485
\ Haynes 188 (UNS R30188)
-1
o
I
I
I
600
1200
1BOO
Exposure time. h (b)
-645 2400
LIVE GRAPH Click here to view
Cobalt-Base Superalloys /101
Haynes 25 (L-G05): Microstructure. Solution annealed at 1205 °C (2200 OF) and aged 3400 h at 870°C (1600 OF). Structure is precipitates of MaC and lC02W" intermetallic in an fcc matrix. Electrolytic: HCI and H202. 500x
Haynes 25 (L-G05): Microstructure. Solution annealed at 1205 °C (2200 OF) and aged 3400 h at 925°C (1695 OF). Structure consists of MaC (primary) and lC02W" intermetallic (secondary) in a fcc matrix. Electrolytic: HCI and HP2' 500x
Haynes 25 (L-G05): Microstructure. Solution annealed and cold worked to 35% reduction. Longitudinal section. (a) Bright-field illumination. (b) Dark-field illumination. (c) Differential interference contrast. All etched with 15 mL HCI, 10 mL acetic acid, 5 mL HN03 , and 2 drops olvcerol. 100x
(a)
(b)
(c)
1021 Heat Treater's Guide: Nonferrous Alloys
Haynes 25 (L-G05): Microstructures. Cold worked to 35% reduction and given different solution-annealing treatments. Grain size increases with increasing annealing temperature and time. (a) Solution annealed 2.5 min at 1150 °C (2100 OF); 261 HV. (b) Solution annealed 4.25 min at 1150 °C (2100 OF); 254 HV. (c) Solution annealed 2.5 min at 1205 °C (2200 OF); 246 HV. 15 mL HCI, 10 mL acetic acid, 5 mL HN03 , and 2 drops glycerol. 100x
(a)
(b)
(c)
Haynes 188 Chemical Composition. Haynes 188 (UNS R30188) (nominal). 22.00 Cr, 22.00 Ni, 37.00 Co, 14.50 W, 3.00 Fe max, 0.10 C, 0.90 La Similar Alloys (U.S. and/or Foreign). UNS R30188
Recommended Heat Treating Practice Solution Treating. Treatmentis at 1175 °C (2145 OF) for 30 min; parts arerapid air cooled
Characteristics A cobalt-base, solid-solution alloy
Haynes 188: TIme-temperature-precipitation diagram on aging. Nominal composition: Co - 20-24% Cr - 20-24% Ni - 13-16% W - 0.05-
0.15% C - 0.03-0.15% La - 0.20-0.50% Si - up to 3% Fe - up to 1.25% Mn
LIVE GRAPH Click here to view
1800 1----+
M
6C
i I
uo
u.i 16001-------t-I-t-H-----j---f
L.U IX
IX
;:)
;:)
I-
I-
-c IX
-< IX
L.U
a.
L.U
L.U
700 ~
a.
~
~
I-
600 : I
10000 TIME, hours
Cobalt-Base Superalloys 1103
Haynes 188: Microstructures. (a) Haynes 188, cold rolled, 20% solution annealed at 1175 °C (2145 OF) for 10 min before water quenching. Fully annealed structure is MaCparticles in an fcc matrix. (b) Haynes 188, solution annealed at 1175 °C (2145 OF) and aged at 650°C (1200 OF) for 3400 h. Microstructure is particles of MaCand M23Ca in an fcc matrix. (c) Haynes 188, solution annealed at 1175 °C (2145 OF) and aged at 870°C (1600 OF) for 6244 h. Structure is M23Ca, Laves phase, and probably MaCin an fcc matrix. All 50Ox o
o
o o
0"
o
(a)
(b)
(c)
Haynes 188: Microstructure. Cold rolled 50%, heated to 815°C (1500 OF) for 1 h and water quenched. The partly recrystallized structure contains MaCand M23Cacarbides in a fcc matrix. Electrolytic: HCI and HP2' 1000x
Haynes 188: Microstructure. Cold rolled 20% and solution annealed at 1175 °C (2145 OF) for 10 min, then water quenched. The fully annealed structure consists of MaC particles in a fcc matrix. Electrolytic: HCI and HP2' 50Ox :J
0
°
0
0
~
"
0
'
...
..',' 0
~
1041 Heat Treater's Guide: Nonferrous Alloys
Temperature. 'F 1380
1560
1740
Haynes 188: Stress rupture curves. 1000h stress-rupture curves of wrought cobaltbase (Haynes 188 and L-605) and wrought iron-base superalloys
1920
5501-----+-----1------1-------1------179.8
LIVE GRAPH Click here to view f r - - - - - - + - - - - - + - - - - - + - - - - - I - - - - - - I 72.5
'"~
4501\-\__----1-------+-----+------1------165.3
\\lnCOIOY901 f--\__-\-----+------+----__+-----t__-~--_l
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\
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\
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li 00l'!
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650
750
--'-
---I.
850
""""-,-'"
950
.l--
1050
---J
0
1150
Temperature. 'C
Haynes 188: Microstructure. Solution annealed at 1175 °C (2145 OF) and aged 3400 hat 650°C (1200 OF). Structure is MsC and M23Cs particles in a fcc matrix. Electrolytic: HCI and H20 2. 500x
Haynes 188: Microstructure. Solution annealed at 1175 °C (2145 OF) and aged 6244 h at 870°C (1600 OF). Structure is M23Cs, Laves phase, and probably MsC in a fcc matrix. Electrolytic: HCI and HP2' 500x
Cobalt-Base Superalloys /105
Haynes 188: Oxidation resistance. (a) In dry air for Haynes 188 versus Hastelloy X and L-605 alloys showing continuous penetration from original thickness. (b) Static values at 1100 °C (2010 OF) in air with 5% water vapor
Temperature, 'F
1600 ~ 75 :Q! 84 [ 50
.g, 38 ~
~
1700
1800
I I L-605........
~ 0 870
"......
- --
25 ......... 13
...v I 925
2100 3.0 ~ ...l 2.5 ~ /1 /Ha~elloyX 2.0 'E 1.5
1900
980
2000
J,.V
I
g
Ha~es 188
I 1035
1095
1,0 .~
0.5
~
o
~
1150
Temperature, 'C
(e)
320
0.50
180
0.25 N
Incoloy MA 956
E
..§
Cl
E
g -0.25
c: <0 s:
N.
c:
's
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-160
~ -0.50
<0
-0.75
g> <0
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:2
E ai'
s: o
-320 :il <0 :2 -485
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o
I
I
I
600
1200
1800
-645 2400
Exposure time, h (b)
LIVE GRAPH Click here to view
Haynes 188: Microstructure. Solution annealed at 1175 °C (2145 OF), aged 6244 h at 980°C (1795 OF). Structure consists of MsCand M23Cs, and probably Laves phase, in a fcc matrix. Electrolytic: HCI and HP2' 500x
MP35 Chemical Composition. MP35·N (UNS R30035) (nominal). 20.00 Cr, 35.00 Ni, 35.00 Co, 10.00 Mo
Similar Alloys (U.S. and/or Foreign). UNS R30035
Characteristics A cobalt-base, precipitation-hardening alloy
Recommended Heat Treating Practice Precipitation Treating. Treat at set temperature in range of 540 to 650 °C (1000 to 1200 OF); hold 4 to 4.5 h; air cool
1061 Heat Treater's Guide: Nonferrous Alloys
MP35N: Microstructure. Solution annealed 1 h at 1065 °C (1950 OF), air cooled, and cold worked to 51 % reduction. Longitudinal section. 15 mL HCI, 10 mL acetic acid, 5 mL HN0 3 , and 2 drops glycerol. 100x
MP35N: Microstructure. Solution annealed 1 h at 1065 °C (1950 OF), then aged 4 h at 535°C (995 OF) to increase hardness. Longitudinal section. 15 mL HCI, 10 mL acetic acid, 5 mL HN03 , and 2 drops glycerol. 100x
MP159 Chemical Composition. MP159 (nominal). 19.00 Cr, 25.00 Ni, 36.00 Co, 7.00 Mo, 0.60 Nb, 3.00 Ti, 0.02 AI, 9.00 Fe
Characteristics
Recommended Heat Treating Practice Precipitation Treating. Treat at set temperature in range of 650 to 675 °C (1200 to 1250 OF); hold for 4 to 4.5 h; air cool
A cobalt-base, precipitation-hardening alloy
Air..Resist 213 Chemical Composition. Air-Resist 213 (nominal). 19.00 Cr, 0.50 Ni max, 65.00 Co, 4.50 W, 3.50 AI, 0.050 Fe max, 0.17 C, 6.50 Ta, 0.15 Zr, O.lOY
Characteristics A cobalt-base, precipitation-hardening alloy
Eigiloy Chemical Composition. Elgiloy (nominal). 20.00 40.00 Co, 7.00 Mo, 0.10 C, 2.00 Mn, 0.04 Be, bal Fe
Characteristics A cobalt-base alloy
Cr, 15.00 Ni,
Recommended Heat Treating Practice Annealing. Solution annealed 1 hat 1230 °C (2250 OF) and air cooled
Cobalt-Base superanoys /107
Eigiloy: Microstructure. Cold drawn to 50 to 55% reduction, showing grains and dispersed stringers of carbide elongated in the rolling direction. HCI, HN03 , and FeCI3 • 250x
Eigiloy: Microstructure. Cold drawn to 50 to 55% reduction, solution annealed 1 hat 1230 °C (2250 OF) and air cooled. The coldworked grains have been fully recrystallized. HCI, HN03 , and FeC13·250x
V..36 Chemical Composition. V-36 (nominal). 25.00 Cr, 20.00 Ni, 4.00 Mo, 2.30 Nb, 2.40 Fe, 0.32 C, 1.00 Mn, bal Co
Characteristics A cobalt-base, precipitation-hardening alloy
UMCo..50 Chemical Composition. UMCo-50 (nominal). 28.00 o, 49.00 Co, 21.00· Fe, 0.12 C max
Characteristics A cobalt-base, solid-solution alloy
Iron-Base Alloys A·286 Chemical Composition. A-286 (UNS K66286) (nominal). 15.00 Cr, 26.00 Ni, 1.30 Mo, 2.00 Ti, 0.2 AI, 54.0 Fe, 0.05 C, 0.015 B Similar Alloys (U.S. and/or Foreign). UNS K66286
Characteristics An iron-base, precipitation-hardening alloy. Aging increases room temperature yield strength (0.2% offset) of solution treatedparts from 240 MPa (35 ksi) in the non-aged condition to 760 MPa (110 ksi). Elongation in 50 mm (2 in.), is reduced from 52% in non-aged condition to 33%
Aging. Treat at 720 (1325 OF) for 16 h, cool in air Stress Relieving. Full annealing is recommended because intermediate temperatures cause aging Annealing. Treat at 980°C (1800 OF), and hold 1 h per inch of cross section. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation hardening of phases. Water quenching is preferred, and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. Rapid air cooling usually is adequate for parts made from sheet or strip
Recommended Heat Treating Practice Solution Treating. Treat at 980°C (1800 OF) for I h, quench in oil
A 286: Time-temperature-precipitation diagram. 11M vs. PIM, near start of precipitation. Transformation to 1 nm precipitates as derived from peak resistance changes. Composition: Fe - 24.7% Ni- 14.4% Cr - 2.2% Ti - 1.1% Mo - 0.26% AI.Treatment: Powder samples were produced by Inert Gas Atomization and the properties of conventional Ingot Metallurgy material were used as a baseline for determination of the effects of IGApowder metallurgy processing. 11M material was solution treated at 900°C (1650 OF) for 2 h and water quenched. PIM material was held at 1100 °C (2010 OF) for 1 h and water quenched
LIVE GRAPH Click here to view
A 286: Effectsof alternative aging treatments on rupture properties 'Ireatment
Life, h
Originat heat treatment(b) 900°C (1650oF),2 h, oilquench; 720°C(1325°F),16h,aircool Revised heat treatments(c) Originalplusadditionalageat 650°C (1200oF),12h, aircool 900°C (1650oF),2 h, oilquench; 730°C (1345oF),16h, aircool
Creep rupture(a) Elongationin Locationor so mm (1in.), II. ralIure
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(a) Specificationrequirementsfor creep-ruptureat 650°C (1200 "P) and 450 MPa (65 ksi):life,23 h min; no failurein notchpermitted.(b)Thnspecimenstested.(c)Fivespecimensforeach treatment
800
750
A 286: Effect of cold work and aging on diamond pyramid hardness of A-286
11M
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Iron-Base SuperaUoys /109
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A 286 (AISI 680): Microstructure. (195 HV), solution annealed 2 h at 900°C (1650 OF) and oil quenched. Specimen has a very fine austenite grain size. Glyceregia. 100x
A 286 (AISI680): Microstructure. (195 HV), solution annealed 2 hat 900°C (1650 OF) and oil quenched. Specimen showing the very fine austenite matrix grains. Tint etch: 20 mL HCI, 100 mL H2 0 , 1 g NH4F . HF,0.5 g K2S 20 S ' 200x
A 286 (AISI 680): Microstructure. (195 HV), solution annealed 2 h at 900°C (1650 OF) and oil quenched. Showing an area near the surface of the specimen with a duplex grain structure. Tint etch: 20 mL HCI, 100 mL H20 , 2.4 g NH4F . HF, and 0.8 g K2S20 S ' 100x
A 286 (AISI 680): Microstructure. (357 HV), solution annealed 2 h at 900°C (1650 OF), oil quenched, and held 16 h at 720°C (1325 OF). Glyceregia. 100x
1101 Heat Treater's Guide: Nonferrous Alloys
A 286 (AISI 660): Microstructure. (357 HV), solution annealed 2 h at 900°C (1650 OF), oil quenched, and held 16 h at 720°C (1325 OF). Showing a region near the surface ofthe specimen with a fine grain structure. Tint etched. 100x
A 286 (AISI 660): Microstructure. (357 HV), solution annealed 2 h at 900°C (1650 OF), oil quenched, and held 16 h at 720°C (1325 OF). Showing the very fine matrix grain structure. lint etched. 100x
A 286 (AISI660): Microstructure. (150 HV), solution annealed 1 h at 980°C (1795 OF) and oil quenched, showing a coarser grain structure due to the higher solutionizing temperature. Glyceregia. 100x
A 286 (AISI 660): Microstructure. (150 HV), solution annealed 1 hat 980°C (1795 OF) and oil quenched. Tint etched using 20 mL HCI, 100 mL H20 , 1 g NH 4F . HF, and 0.5 g K2S20 5 • 100x
A 286 (AISI660): Microstructure. (318 HV), solution annealed 1 h at 980°C (1795 OF), oil quenched, aged 16 h at 720°C (1325 OF), and air cooled. Glyceregia. 100x
Iron-Base SuperaUoys /111
A 286 (AISI 660): Microstructure. Showing lamellar or cellular precipitation of 11 phase (NiaTi)caused by overaging or by insufficient boron. Cold working accelerates the response to aging. 15 mL HCI, 10 mL HNO al and 10 mL acetic acid. 1000x
A 286 (AISI660): Microstructure. (318 HV), solution annealed 1 hat 980°C (1795 OF), oil quenched, aged 16 h at 720°C (1325 OF), and air cooled. Tint etched. Only the matrix phase has been colored. 20 mL HCI, 100 mL Hp, 1 g NH 4F . HF, and 0.5 g K2SP5' 100x
A286 (AISI660): Microstructures. Solution annealed 1 h at 980 °C (1795 OF) and aged 16 h at 720 °C (1325 OF), then air cooled and creep tested to rupture. (a) Tested 7131 h at 650 °C (1200 OF). Matrix and grain-boundary precipitates have coalesced. 31.5 HRC. (b) Tested 1232 h at 730°C (1345 OF). Grain-boundary precipitates have coalesced; the matrix is darkened by y I precipitation. HRC 25.5. (c) Tested 546 h at 815°C (1500 OF). Grain-boundary precipitates have coalesced, and the overaged matrix contains needlelike 11 phase (NiaTi). HRB 88.5. 15 mL HCI, 10 mL HNO al and 10 mL acetic acid. 1000x
(a)
(b)
(c)
A286: Effectof heat treatment on properties
Heattreatment
0.2% YIeld strength MFa ksi
980°C (1800 OF) for 1 h, oil quench (OQ) + no°c (1325 OF)for 16h,aircool 900°C (1650 oF) for 2 h, 00+ rzo-c (1325 OF)for 16h, air cool
690 740
100 108
Tensile Propertiesat 21°C (70 oF) UUimate tensilestrength Elongation, MFa % ksi 1070 1100
156 160
24 25
Reduction inarca, %
46 46
Stressrupture at 650°C (1200oF) with450MFa (65ksJ) Life, Elongation, Reduction h % in area, % 85 64
10 15
15 20
112/ Heat Treater's Guide: Nonferrous Alloys
W..545 Chemical Composition. W-545 (UNS K66545) (nominal). 13.50 Cr, 26.00 Ni, 1.50Mo, 2.85 Ti, 0.20 AI, 55.80 Fe, 0.08 Cr, 0.05 B Similar Alloys (U.S. and/or Foreign). UNS K66545
Characteristics An iron-base, precipitation-hardening alloy
V..57 Chemical Composition. V-57 (UNS K66545) (nominal). 14.80 Cr, 27.00 Ni, 1.25 Mo, 3.00 Ti, 0.25 AI, 48.60 Fe, 0.08 C max, 0.01 B, 0.05 V max
Characteristics An iron-base, precipitation-hardeningalloy
Similar Alloys (U.S. and/or Foreign). UNS K66545
Incoloy 800 Chemical Composition. Incoloy 800 (UNS N08800) (nominal). 21.00 Cr, 32.5 Ni, 0.38 Ti, 0.38 AI, 45.70 Fe, 0.05 C Similar Alloys (U.S. and/or Foreign). UNS N08800
complex shapes subject to excessive distortion, oil quenching often is adequate andmorepractical. Rapid air cooling usual1y is adequate for parts formed from sheet or strip
Characteristics An iron-base, precipitation-hardeningalloy
Recommended Heat Treating Practice Stress Relieving. Treatment is at 870°C (1600 OF). Holding time per inch of section: 1.5 h Annealing. Treatment is at 980°C (1795 OF). Holding time is 0.25 h per inch of section. Minimum hardness is obtained by rapid cooling from the annealing temperature to prevent precipitation of hardeningphases. Water quenching is preferred, and usually is necessary for heavy sections. For
Incoloy 800: Time-temperature-sensitization diagram. Composition: Fe - 31.85% Ni - 0.23% Cu - 0.06% C - 0.81% Mn 0.007% S - 0.32% Si - 21.81% Cr. Treatment: Solution heat treated in argon at 1093 °C (2000 OF) for 1 h, water quenched, aged, and rapidly water cooled. Key: Contour lines, corrosion rates in rnilllqrams/dmvday, mils per year in boiling 65% nitric acid; X, specimens which failed the copper-copper sulfate-sulfuric acid tests (ASTM A262-68) LIVE GRAPH Click here to view
1000 850 Incoloy 800: Microstructure. Strip, in the mill-annealed condition. The microstructure consists of a solid-solution matrix in which some grains are delineated by precipitated carbide particles at the boundaries and by twinning lines. Glyceregia. 250x
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Iron-Base Superalloys /113
Incoloy 800: Intercrystalline corrosion susceptibility. Test conditions: 45 h boiling in solution of 250 mL H2S04 + 100 g CuS04 + 750 mL H20, followed by bend test and SEM evaluation. Composition: Fe - 31.1% Ni - 21.4% Cr - 0.90% Mn - 0.28% Si 0.037% C - 0.02% N - 0.01% P - 0.007% S - 0.5% AI - 0.3% Ti. Grain size: ASTM 7-8. Treatment: Mill annealed specimens . aged at 400 to 800°C (750 to 1470 OF)
Incoloy 800: Transmission electron microscope evaluation of heat treated specimens. Composition: Fe - 31.1% Ni 21.4% Cr - 0.90% Mn - 0.28% Si - 0.037% C - 0.02% N - 0.01% P - 0.007% S - 0.5% AI- 0.3% Ti. Grain size: ASTM 7-8.Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Carbon-extraction replicas of Sr-methanol etched transverse cross sections of tube specimens 1000
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Next Page 114/ Heat Treater's Guide: Nonferrous Alloys
Incoloy 800: Scanning electron microscope evaluation of heat treated specimens. Composition: Fe - 31.1% Ni - 21.4% Cr - 0.90% Mn - 0.28% Si - 0.037% C - 0.02% N - 0.01% P 0.007% S - 0.5% AI- 0.3% li. Grain size: ASTM 7-8. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Etchant: 10% Br-CH30H
Incoloy 800: Light microscope evaluation of heat treated specimens. Composition: Fe-31.1% Ni - 21.4% Cr-0.90% Mn 0.28% Si - 0.037% C - 0.02% N - 0.01% P - 0.007% S - 0.5% AI0.3% li. Grain size: ASTM 7-8. Treatment: Mill annealed specimens aged at 400 to 800°C (750 to 1470 OF). Etchant: 10% BrCH30H
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=
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No precipitate Fine GB particles Massive GB particles Specimen identification GB and ITB particles GB, ITB ad TB particles
GB = Grain boundary ITB = Incoherent twin boundary TB = Coherent twin boundary
Incoloy 801 Chemical Composition.lncoloy 801 (UNS N08801) (nominal). 20.50 Cr, 32.00 Ni, 1.13Ti, 46.30Fe, 0.05 C Similar Alloys (U.S. and/or Foreign). UNS N08801
Characteristics An iron-base, precipitation-hardening alloy
Previous Page Iron-Base Superalloys /115
Incoloy 802 Chemical Composition.lncoloy 802 (nominal). 21.00 Cr, 32.50 Ni, 0.75 Ti, 0.58 AI, 44.80 Fe, 0.35 C
Characteristics An iron-base, precipitation-hardening alloy
Incoloy 807 Chemical Composition. Incoloy 807 (nominal). 20.50 Cr, 40.00 Ni, 8.00 Co, 0.10 Mo. 5.00 W, 0.20 AI, 0.30 Ti, 25.00 Fe, 0.50 Mn, 0040 Si, 0.05 C
Characteristics An iron-base, precipitation-hardening alloy
Incoloy 825 Chemical Composition. Incoloy 825 (nominal). 19.50 to 23.50 Cr. 38.00 to 46.00 Ni, 2.50 to 3.50 Mo, 0.20 AI, 0.60 to 1.20 Ti, 22.00 Fe, 1.00 Mn, 0.50 Si, 0.05 C
Characteristics An iron-base, precipitation-hardening alloy
Recommended Heat Treating Practice Annealing. Treatment is at 980°C (1795 "F). Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent the precipitation of hardening phases. Water quenching is preferred, and is usually necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. For parts formed from sheet or strip. rapid air cooling usually is adequate.
Incoloy 825: Time-temperature-sensitization diagram. Composition: Ni - 0.03% C - 0.65% Mn - 29.59% Fe - 0.27% Si - 1.71% Cu21.18% Cr - 0.11% AI- 0.99% Ti - 2.61 % Mo. Treatment: Annealed at 1093 °C (2000 OF) for 1 h prior to aging
LIVE GRAPH Click here to view
<12mpy 1000
0.1
116/ Heat Treater's Guide: Nonferrous Alloys
Incoloy 825: Time-temperature-sensitization diagram. Composition: Ni - 0.03% C - 0.65% Mn - 29.59% Fe - 0.27% Si - 1.71% Cu21.18% Cr - 0.11 % AI- 0.99% Ti - 2.61% Mo. Treatment: Annealed at 941°C (1725 OF) for 1 h prior to aging
LIVE GRAPH Click here to view
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Incoloy 825: Time-temperature-precipitation diagram for M23Ce. The amount of M23C e is indicated by the chromium content of the carbide residue. Composition: Ni - 0.05% C - 0.57% Mn - 6.56% Fe - 0.25% Si - 0.05% Cu - 15.66% Cr - 0.70% AI- 2.35% Ti - 0.92% Nb
LIVE GRAPH Click here to view
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0.2
2
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6
10
20
40
60
100
Time, hr
Incoloy 825: Time-temperature-precipitation diagram for M23C e• Numbers show the Cr and Ti contents of the residue (77Cr, 13Ti for as-annealed material). Composition: Ni - 0.03% C - 0.65% Mn - 29.59% Fe - 0.27% Si - 1.71% Cu - 21.18% Cr0.11% AI- 0.99% Ti - 2.61% Mo. Treatment: Annealed at 941°C (1725 OF) for 1 h
1800
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. 0.2
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1
2
4 Time, h
6
10
20
40 60
100
Iron-Base Superalloys /117
Incoloy 903 Chemical Composition.lncoloy 903 (UNS N19903) (nominal). O.lOCrmax, 38.00Ni, 15'()()Co, O.lOMo, 3.00Nb, 1.40Ti, 0.70 AI, 41.00 Fe,O.04C Similar Alloys (U.S. and/or Foreign). UNS N19903
Recommended Heat Treating Practice Solution Treating. Treated at 845°C (1555 "F) for 1 h, and water quenched Aging. Treatment is at 720°C (1325 "F) for 8 h, then furnace cooled
Characteristics An iron-base, precipitation-hardening alloy
Incoloy 907 Chemical Composition.lncoloy 907 (UNS N19907) (nominal). 38.00 Ni, 13.00 Co, 4.70 Nb, 0.03 AI, 1.50 Ti, 42.00 Fe, 0.15 Si Similar Alloys (U.S. and/or Foreign). UNS N19907
Recommended Heat Treating Practice Solution Treating. Treating at 980°C (1795 oF) for 1 h, then air cooled Aging. Treated at 775°C (1425 "F) for 12 h, then furnace cooled
Characteristics. An iron-base, precipitation-hardening alloy
Incoloy 909 Chemical Composition. Incoloy 909 (UNS N19909) (nominal). 38.00 Ni, 13.00 Co, 4.70 Nb, 1.50 Ti, 42.00 Fe, 0.40 Si, 0.01 C, 0.001 B Similar Alloys (U.S. and/or Foreign). UNS N19909
Recommended Heat Treating Practice Solution Treating. Treatment is at 980°C (1795 OF) for 1 h, then air cooled Aging. Treatment is at 720°C (1325 OF) for 8 h, then furnace cooled
Characteristics An iron-base, precipitation-hardening alloy
1040
Incoloy 909: Time-temperature-precipitation diagram. Composition: Fe - 38.3% Ni - 12.9% Co - 4.70% Nb - 1.58% Ti - 0.35% Si0.04% AI - 0.01% C - 0.01% Cr. Treatment: Solution annealed at 1038 °c (1900 OF) for 1 h, air cooled, and isothermally aged between 540 and 1038 °c (1000 and 1900 OF) for 0.1 to 1000 h
984 928
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0.1
1.0 10.0 100.0 1000.0 Time (Hours)
118/ Heat Treater's Guide: Nonferrous Alloys
Incoloy 925 Chemical Composition. Incoloy 925 (UNS W09925) (nominal). 20.50 Cr, 44.00 Ni, 2.80 Mo, 2.10 Ti, 0.20 AI, 29.00 Fe, 0.01 C, 1.80 Cu
Recommended Heat Treating Practice
Similar Alloys (U.S. and/or Foreign). UNS N09925
Solution Treating. Treatment is at 1010 °C (1850 OF) for 1 h; parts are air cooled
Characteristics An iron-base, precipitation-hardening alloy
Aging. Treatment is at 730°C (1345 OF) for 8 h; parts are furnace cooled. Alternate treatments may be used to improve specific properties. If furnace size or load prohibits fast heat up to the initial age temperature, a controlled ramp up from 595 to 730°C (1l00 to 1345 "F) is recommended
16..25",6 Chemical Composition. 16-25-6 (nominal). 16.00 Cr, 25.00 Ni, 6.00 Mo, 50.70 % Fe, 0.06 C, 1.35 Mn, 0.70 Si, 0.15 N
Characteristics An iron-base, solid-solution alloy
16-25-6 (AISI650): Microstructure. After forging between 650 and 705°C (1200 and 1300 OF) and stress relieving. The solid-solution matrix exhibits banding because of carbide segregation. Marble's reagent. 100x
16·25·6 (AISI650): Microstructure. After forging between 650 and 705°C (1200 and 1300 OF) and stress relieving. Higher magnification reveals the carbide segregation in banding. The matrix is austenitic solid solution. Marble's reagent. 500x
16-25-6 (AISI650): Microstructure. After forging between 650 and 705°C (1200 and 1300 OF) and stress relieving. Here the carbide segregation is dispersed, not banded, in the solid-solution matrix. Marble's reagent. 100x
Iron-Base Superalloys /119
Chemical Composition. 17-14-CuMo (nominal). 16.00 Cr, 14.00 Ni, 2.50 Mo, 0.40 Nb, 0.30 Ti, 62.40 Fe, 0.12 C, 0.75 Mn, 0.50 Si, 3.00 Cu
Characteristics An iron-base, solid-solution alloy
19..9DL Chemical Composition. 19-9DL (UNS K63198) (nominal). 19.00 Cu, 9.00 Ni, 1.25 Mo, 1.25 W, 0.4 Nb, 0.3 Ti, 66.80 Fe, 0.30 C, 1.10 Mn, 0.60 Si Similar Alloys (U.S. and/or Foreign). UNS K63198
Characteristics An iron-base, solid-solution alloy
Recommended Heat Treating Practice Stress Relieving. Nominal temperature of 650 to 705°C (1200 to 1300 OF) is permitted. Holding time is 4 h per inch of section Annealing. Minimum hardness is obtained by cooling rapidly from the annealing temperature (980°C or 1795 OF), to prevent precipitation of hardening phases. Holding time is 1 h per inch of section. Water quenching is preferred and usually is necessary for heavy sections. For complex shapes subject to excessive distortion; oil quenching often is adequate and more practical. Rapid air cooling usually is adequate for formed sheet or strip parts.
N..155 Chemical Composition. N·155 (UNS R30155) (nominal). 21.00 Cr, 20.00 Ni, 20.00 Co, 3.00 Mo, 2.50 W, 1.00 Nb, 32.2 Fe, 0.15 C, 0.15 N, 0.60 Si, 0.02 Zr Similar Alloys (U.S. and/or Foreign). UNS R30155
Recommended Heat Treating Practice Solution Treating. Treat at 1165 to 1190 °C (2125 to 2175 "F) for 1 h, quench in water Aging. Treat at 815°C (1500 OF) for 4 h, air cool
Characteristics An iron-base, solid solution alloy
N155 (AISI661): Microstructure. Solution annealed 1 hat 1150 °C (2100 OF) and water quenched. Primary carbide particles are mostly dispersed within grains; some are at grain boundaries. 1:1 HCI and H2 0 . 500x
N155 (AISI661): Microstructure. Solution annealed 1 hat 1150 °C (2100 OF), then aged 5 h at 760°C (1400 OF) and air cooled. Precipitated secondary carbide (MaC or M23C a) at grain boundaries and within grains. 20% HCI, methanol, and 1% H2 0 2 , 5 S. 500x
120 I Heat Treater's Guide: Nonferrous Alloys
RA..330 Chemical Composition. RA-330 (UNS N08330) (nominal). 19.00 Cr, 36.00 Ni, 45.10 Fe, 0.05 C Similar Alloys (U.S. and/or Foreign). UNS N08330
Characteristics An iron-base, solid-solution alloy
Recommended Heat Treating Practice Stress Relieving. Treat at 900°C (1650 "F), Holding time is 1 h per inch of section. Time given is minimum, Some plants hold as much as 3 h per inch
Annealing. Treatment time is 1110 °C (2030 OF), although nominal temperatures of 1035 to 1175 °C (1895 to 2145 "F) are commonly used. Holding time is 0.25 h per inch of section because of the need to prevent grain coarsening. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation of hardening phase. Water quenching is preferred and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. Rapid air cooling usually is adequate for parts formed from sheet or strip. Rapid cooling from the annealing or solution treating temperature does not suppress the aging reaction of some alloys, they become harder and stronger
Discaloy Chemical Composition. Discaloy (UNS K66220) (nominal). 14.00 Cr, 26,00 Ni, 3.00 Mo, 1.70 Ti, 0.25 AI, 55.00 Fe, 0.06 C
Stress Relieving. Full annealing is recommended, because intermediate temperatures cause aging
Similar Alloys (U.S. and/or Foreign). UNS K66220
Annealing. Treat at 1035 °C (1895 OF) for 1 h per inch of cross section. Minimum hardness is obtained by cooling rapidly from the annealing temperature, to prevent precipitation hardening ofphases. Water quenching is preferred, and usually is necessary for heavy sections. For complex shapes subject to excessive distortion, oil quenching often is adequate and more practical. Rapid air cooling usually is adequate for parts formed from sheet or strip
Characteristics An iron-base, precipitation-hardening alloy
Recommended Heat Treating Practice Solution Treating. Treat at 1010 °C (1850 OF) for 2 h, quench in oil Aging. Treat at 730°C (1350 "F) for 20 h, air cool
Discaloy (AISI 662): Microstructures. Solution annealed 1 h at 1065 °C (1950 OF), showing the effects of different aging processes. (a) Oil quenched; 139 HV. (b) Aged 64 h at 650°C (1200 OF); 249 HV. (c) Aged 512 h at 650°C (1200 OF); 315 HV. Glyceregia. 500x
I' •
~ /. ~r~ ?' . ~,~ I.
/'
(a)
(b)
(c)
Iron-Base Superalloys /121
Discaloy (AISI662): Microstructures. Solution annealed 1 hat 1065 °C (1950 OF). (a) Aged 2 hat 705°C (1300 OF); 223 HV. (b) Aged 64 hat 705°C (1300 OF); 292 HV. (c) Aged 272 h at 705°C (1300 OF); 295 HV. Glyceregia. 500x
(a)
(c)
(b)
Discaloy (AISI662): Microstructures. Solution annealed 1 hat 1065 °C (1950 OF). (a) Aged 1 hat 760°C (1400 OF); 248 HV. (b) Aged 8 hat 760°C (1400 OF); 258 HV. (c) Aged 128 h at 760°C (1400 OF); 253 HV. Glyceregia. 500x
(a)
(b)
Haynes 556 Chemical Composition. Haynes 556 (nominal). 22.00 Cr, 21.00 Ni, 20.00 Co, 3.00 Mo, 2.50 W, 0.1 Nb, 0.3 AI, 29.00 Fe, 0.10 C, 0.50 Ta, 0.02 La, 0.002 Zr
Characteristics An iron-base, solid-solution alloy
Recommended Heat Treating Practice Annealing. Treat at set temperature of 1175 °C (2150 OF); water quench or room air cool Stress Relieving. Annealing serves this purpose
(c)
55~ AI!oy: Effectof cold reduction and annealing temperature on gram size Coldreduction,
5-minsubseguent.nnealing temperature
%
°C
OF
0 10 20 30 40 50 10 20 30 40 50 10 20 30 40 50 10 20 30 40 50
None 1010 1010 1010 1010 1010 1065 1065 1065 1065 1065 1120 1120 1120 1120 1120 1175 1175 1175 1175 1175
None 1850 1850 1850 1850 1850 1950 1950 1950 1950 1950 2050 2050 2050 2050 2050 2150 2150 2150 2150 2150
Degreeof
ASTM
recrystallization
grain size
5.0-6.0 Incomplete Incomplete Partial Partial
Full
7.5-9.5 9.0-10.0
Incomplete Incomplete
Full Full Full Full Full Full Full Full Full Full Full Full Full
7.5-9.5 8.0-9.5 8.5-10.0 5.0-5.5 7.5-8.5 7.0-7.5 7.5-9.0 8.0-9.5 5.0-5.5 6.0-6.5 4.5-6.5 4.5-6.5 5.5-6.0
122/ Heat Treater's Guide: Nonferrous Alloys
Pyromet CTX..1 Chemical Composition. Pyromet CTX·1 (nominal). 0.10% Cr max, 37.70 Ni, 16.00 Co, 0.10 Mo, 3.00 Nb, 1.70 Ti, 1.00 AI, 39.00 Fe, 0.03 C
Characteristics An iron-base, precipitation-hardening alloy
Recommended Heat Treating Practice Solution Treating. Warm worked stock is typically heat treated at 845 to 870°C (1550 to 1600 OF) for 1 h and air cooled. For large section sizes, water or oil quenching is suggested. Time at temperature varies with section size to ensure thorough heating. Aging. Treatment is at 720°C (1325 "F) for 8 h; cooling is at 55°C (100 OF) per hour to 620°C (1150 OF); holding 8 h at heat is followed by air cooling
Pyromet CTX·1: Time-temperature-precipitation diagram. Composition: Fe - 37.7% Ni - 16.0% Co - 3.0% Nb - 1.75% Ti - 1.0% AI 0.008% B - 0.03% C. Treatment: Annealed at 913°C (1675 OF) for 1 h, oil quenched
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1600 ! - - - 4 - - - - - - - - - - l -....,...
,,1500 I&.
o
•..
I --;---------11----.....
,\---+----I
= "•..
1400
a-
t:
Gamma Prime
I'
~ 1300
~
\
<,
1200 1 - - - 4 - - - - - . . . ; ; 0.1
Pyromet CTX",3 Chemical Composition. Pyromet CTX·3 (nominal). 0.20 Cr, 38.30 Ni, 13.60 Mo, 4.90 Nb, 0.10 AI, 1.60 Ti, 0.15 st. 0.05 C, 0,007 B, Fe bal
Recommended Heat Treating Practice
Characteristics
Solution Treating. Warm worked material is treated at 980°C (1800 OF) for 1 h; air cooled
An iron-base precipitation hardening alloy
Aging. Treatment is at 775°C (1425 OF) for 12 h; furnace cooled at 55°C (100 OF) per hour to 620°C (1150 OF) for 8 h; air cooled
Nickel
Heat Treating Nickel In some ways nickel is easier to heat treat than many of the iron-base alloys that depend on carbon-related microstructural changes to achieve desired properties. Nickel is an austenite former, and no allotropic phase transformations occur. See Table I for compositions. Because nickel is found in nature as nickel sulfide and nickel oxide ores, it has a natural tendency to combine with sulfur and/or oxygen. One of the most important factors to consider when heat-treating nickel is to minimize exposure to sulfur, whether in solid form (such as lubricants, grease, or temperature-indicating sticks) or in gaseous form (such as S02 or H2S). When embrittlement by sulfur occurs, there are no techniques that can be used to reclaim the affected material; the contaminated area must be either removed, such as by grinding, or scrapped. Because nickel has a very low solubility for carbon in the solid state, it does not readily carburize. Almost all heat treatment methods used with nickel are employed either to soften it, such as annealing, or to increase its strength, such as age hardening.
Fig. 1 Effects on room-temperature properties of cold-drawn Monel 400 rod held for 3 h at various temperatures Heat-treating temperature, OF 100
al
a:
v
400
800
r-.
J:
li 01 l:
1200 I
80
r-"
'E co
J:
-, 100
co
-ECl
60
l:
c
~
40
US
~
US
20
'if. cO
Stress Relieving
0 100
0
.~
In stress relieving, careful regulation of time and temperature is required. These variables are usually determined experimentally for each application; some typical ranges are given in Table 2. Figure I shows the effect of stress relief, at temperatures from about 400 to about 600 °C (750 to 1100 "F), on the room-temperature properties of Mone1400.
Cl
Ni
C
Mn
Fe
Si
99.5 99.5 66.0 66.0 65.0
0.06 0.01 0.12 0.18 0.15
0.25 0.20 0.90 0.90 0.60
0.15 0.15 1.35 1.35 1.00
0.05 0.05 0.15 0.15 0.15
50
l:
0
UJ
0 0
Table 1 Nominal compositions of nickels
Nickel200 Nickel201 Monel400 MonelR-405 MoneIK-500
1i -ECl
:2
The annealing of nickel consists of heating the metal at a predetermined temperature for a definite time and then slowly or rapidly cooling it to produce a change in mechanical properties, usually a complete softening, as the result of recrystallization. Nickel that has been hardened by cold-working operations, such as rolling, deep drawing, spinning, or severe bending, requires softening before cold working can be continued. See Table 3 for annealing atmospheres.
Material
80
D..
Annealing
800 200 400 600 Heat-treating temperature, °C
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Composition. wi % Cr Cu 0.05 0.05 31.5 31.5 29.5
TI
AI
0.50
2.80
Mo
Co
O.04S
Table 3 Prepared atmospheres suitable for annealing nickel Atmospheres 2 through 7 can be used for bright annealing of nickel, modified nickels, and nickel-copper alloys; atmosphere 4 or atmosphere 7 must be used for bright annealing of nickel alloys that contain chromium, molybdenum, or both. Ah-Io-gas Composition, vol% Dew point (appro:dmate) Atmosphere
I 2 3 4 5 6 7
Completelyburnedfuel,leanatmosphere Paritallyburnedfuel, medium-rich atmosphere Reactedfuel,richatmosphere Dissociatedammonia(completedissociation) Dissociatedammonia,partiallyburned Dissociatedammonia, completelyburned Electrolytic hydrogen,dried(d)
mlio(a)
10:1 6:1 3:1 No air 1.25:I(c) 1.8:I(c) No air
IL
co
Co,
0.5 15.0 38.0 75.0 15.0 1.0 100.0
0.5 10.0 19.0 0.0 0.0 0.0 0.0
10.0 5.0 1.0 0.0 0.0 0.0 0.0
CIL
0.0 1.0 2.0 0.0 0.0 0.0 0.0
0,
N,
-c
OF
0.0 0.0 0.0 0.0 0.0 0.0 0.0
89.0 69.0 40.0 25.0 85.0 99.0 0.0
Saturated(b) Saturated(b) 20 -5510-75 Saturated(b) Saturated(b) -5510-75
Saturated(b) Saturated(b) 70 -7010-100 Saturated(b) Saturated(b) -7010-100
(a)Basedon use of naturalgascontainingnearly 100%methaneandratedot37 MJ/m 3 (1000Btulft\ Forhigh-hydrogenmanufacturedgas (20 MJ/m 3, or 550 Btulft~, ratiosare about 50% of valueslisted. For manufactured gas with lowerhydrogenandhigh carbonmonoxidecontents(17 MJ/m 3, or 450 Btulft\ ratiosare about40% ofvalues listed.For propane,ratios are abouttwice thoselisted.For butane, multiplylistedvaluesby three.(b) Whenatmosphereis cooledby tap waterheatexchangers,dew point will be about6to 8°C (10to 15 "F) abovethe temperatureof the tap water.Dewpoint may be reduced to about 5 DC (40 OF)by refrigerationequipmentand to-55°C (-70 "F) or lowerby activated-absorption equipment.(c)Ratioof air to dissociatedammonia.(d) Driedto a dew pointof -5510 -75°C (-70 to -100 "F) by aluminaplus molecularsieve
126/ Heat Treater's Guide: Nonferrous Alloys
Table 2 Annealing, stress-relieving, andstress-equalizing schedules fornickels Soft!l!l!!08llng
Batch
Continuous
TIm.(al,
1300-1400 1300-1400 1400-1500 1400-1500 1600-1900
2-6 2-6 1-3 1-3 1-3
AC AC AC AC WQ
TIme,
h
CooUng method
1-2 1-2 1-3
AC AC AC
of
min
815-925 760-870 870-980 870-980 870-1040
1500-1700 1400-1600 1600-1800 1600-1800 1600-1900
0.5-5 0.5-5 0.5-15 0.5-15 0.5-20
ACorWQ ACorWQ ACorWQ ACorWQ WQ
TIme,
OC
OF
260-480 260-480 230-315
500-900 500-900 450-600
Material
NickelWO Nickel201 Monel400 MonelR-405 MoneIK-500
TIm., h
Cooling
of
OC
Cooling method(hl
Thmperature
Thmperalure
-c
705-760 705-760 760-815 760-815 870-1040
StressegnaHzing
Streso relieying
OC
OF
min
Cooling method
480-705 480-705 540-650
900-1300 900-1300 1000-1200
0.5-120 0.5-120 0.5-120
AC AC AC
Thmperature
Material
Nickel200 Nickel201 Monel400 MonelR-405 MoneIK-500
method
Thmpernture
(a)Tunesgivenrepresentactualrangesthat thin sheet/stripproductsandheavycrosssectionswouldreceivein continuous furnaces. (b) AC,aircool;WQ, waterquench
Nickel 200 ChemicalComposition (nominal). 99.50 Ni, 0.06 C, 0.25 Mn, 0.15 Fe, 0.05 Si, 0.5 Cu
Characteristics Commercially pure wrought nickel, with good mechanical properties and excellent resistance to many corrosives. Uses include food processing equipment, caustic handling equipment and piping, electronic, aerospace, and missile components
• Annealing temperatures in continuous furnaces range from 815 to 925 °C (1500 to 1695 OF). Times (actual) for treating thin sheet and strip products and those with heavy cross sections range from 0,5 to 5 min. Parts are air cooled or water quenched • Annealing temperatures in batch furnaces range from 705 to 760°C (1300 to 1400 "F), Time at temperature ranges from 2 to 6 h. Parts are air cooled
Stress Relieving. Temperatures range from 480 to 705°C (900 to 1300
Recommended Heat Treating Practice
"F), Times range from 30 sec to 120 min, Parts are air cooled
Soft Annealing. Procedures differ for continuous and batch annealing:
Stress Equalizing. Temperatures range from 260 to 480 °C (500 to 900 "F). Times range from 1 to 2 h. Parts are air cooled
Nickel 201 Chemical Composition (nominal). 99.50 Ni, 0.01 C, 0.20 Mn, 0.15 Fe, 0.05 Si, 0.05 Cu
Characteristics Commercially pure wrought alloy has low carbon (0.02% max) for service at temperatures above 315°C (600 "F), Has good mechanical properties and excellent resistance to many corrosives. Uses include food processing equipment, caustic handling equipment and piping, plus electronic, aerospace, and missile components
Recommended Heat Treating Practice Soft Annealing. Nickel 201 is annealed in continuous and batch furnaces. Temperatures, times at temperature, and cooling method depend on type of furnace: • In continuous furnaces, parts are annealed at 760 to 870°C (1400 to 1600 "F) for 30 sec to 5 min, and air cooled or water quenched • In batch furnaces, parts are annealed at 705 to 760 °C (1300 to 1400 OF) for 2 to 6 h, and air cooled Stress Relieving. Parts are treated at 480 to 705°C (900 to 1300 OF) for 30 sec to 120 min, and air cooled Stress Equalizing. Parts are treated at 260 to 480 °C (500 to 900 oF)
Nickel/127
Monel400
Monel 400: Effects on room-temperature properties of colddrawn Monel 400 rod held for 3 h at various temperatures
Chemical Composition (nominal). 66.00 Ni, 0.12 C, 0.90 Mn, 1.35 Fe, 0.15 Si, 31.50 Cu
Characteristics A nickel-copper alloy with high strength and excellent resistance to corrosion in a range of media, including seawater, hydrofluoric acid, sulfuric acid, and alkalies. Used in marine engineering, chemical and hydrocarbon processing equipment, valves, pumps, shafts, fittings, fasteners, and heat exchangers
Heat-treating temperature, OF
al
J:
~
c
• In continuous furnaces, parts are' annealed at 870 to 980°C (1600 to 1800 "F) for 30 sec to 15 min, and cooled in air or water • In batch furnaces, parts are annealed at 760 to 815 °C (1400 to 1500 "F) for 1 to 3 h, and air cooled
Stress Relieving. Parts are treated at 540 to 650°C (1000 to 1200 "F) for 30 sec to 120 min, and air cooled Stress Equalizing. Parts are treated at 230 to 315 °C (450 to 600 OF) for 1 to 3 h, and air cooled
-
400
800
1200
r-.
80
I
\
'E co
J:
Recommended Heat Treating Practice Soft Annealing. Monel 400 is annealed in continuous and batch furnaces. Temperatures, times at temperature, and cooling method depend on type of furnace used:
100
a:
-.
60 80°I:=:::i===::rr-111 100
co
600
80
D..
:2:
-EC>
400 1----7"4---t-='k--++-----=J 60
c
~
40
Ul Yield strength (0.00% offset)
0 100
C>
50
c 0
iii
o o
200
--
400
-EC> c e
Ul
20
I
I
e0
.~
'iii
.><
.>:
600
800
Heat-treating temperature, °C
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Monel R·405 Chemical Composition (nominal). 66.00 Ni, 0.8 C, 0.90 Mn, 1.35 Fe, 0.15 Si, 31.5 Cu, 0.04 S
Characteristics Free machining version of alloy 400. Sulfide inclusions act as chip breakers in machining. Applications include meter and meter valve parts, fasteners, and screw machine products. Alloy is not stress relieved or stress equalized
Recommended Heat Treating Practice Soft Annealing. R-405 is annealed in continuous and batch furnaces. Temperatures, times at temperature, and cooling methods vary by type of furnace: • In continuous furnaces, parts are annealed at 870 to 980°C (1600 to 1795 "F) for 30 sec to 15 min, and cooled in air or water • In batch furnaces, parts are annealed at 760 to 815 °C (1400 to 1500 "F) for 1 to 3 h, and water quenched
Monel K·500 Chemical Composition (nominal). 65.00 Ni, 0.15 C, 0.60 Mn, 1.00 Fe, 0.15 Si, 29.5 Cu, 0.50 Ti, 2.80 Al
Characteristics A precipitation-hardenable, nickel-copper alloy that combines corrosion resistance of alloy 400 with greater strength and hardness. Also has low permeability and is nonmagnetic under -100°C (-150 OF). Applications: Pump shafts, oil well tools and instruments, doctor blades and scrapers, springs, valve trim, fasteners, and marine propeller shafts
Recommended Heat Treating Practice Solution Heat Treating. Alloy is treated at 980 °C (1795 "F) for 30 min to 1 h, and water quenched Age Hardening Treatment. Parts are heated to 595°C (1100 oF), held for 16 h; furnace cooled to 540°C (1000 "F), held 6 h; furnace cooled to 480°C (900 "F), held 8 h; and air cooled
Aluminum Alloys
Heat Treating Aluminum Alloys Not all aluminum alloys are heat treatable. Generally, only the precipitation hardenable wrought and cast alloys are heat treated (to increase strength and hardness). The strength of the nonheat treatable alloys is upgraded primarily via cold work. Heating and cooling do little to increase their strength. Both types of alloys are annealed (to reduce strength and to increase ductility). Typical practices are summarized in the graphics that follow: • Fig. I, an aluminum-copper phase diagram. identifies temperature ranges for annealing, precipitation hardening, and solution treating • Table l(a) provides information on typical solution and precipitation heat treatments for commercial mill products with copper alloying, namely:
1. 2. 3. 4.
Aluminum-copper alloys without magnesium alloying Aluminum-copper-magnesiumalloys Aluminum-copper-magnesium-silicon alloys Aluminum-copper-lithiumalloys
• Table I (b) provides typical solution and precipitation heat treatments for magnesium-silicon alloys (6xxx series) • Table 1(c) provides typical solution and precipitation heat treatments for zinc-magnesium alloys from 7xxx series • Table 2 provides soak times and maximum quench delays for the solution treatment of wrought alloys • Table 3 provides typical heat treatments for sand and permanent mold alloy die castings
Tablela Typical solution and precipitation heat treatments for commercial heat-treatable aluminum alloy mill products with copper alloying
Alloy
Product form
Solutionheallrealment(.) Thmper Melllliempemlure(h) OF -c designation
1're
Thmpor designation
AI-Cu alloys without magnesium aUoying 2011
2025 2219(f)
Rolled or cold finished rod and bar
525
975
Die forgings Flat sheet
515 535
960 995
Plate
535
995
T3(d) T4 T451(e) T4 T31(d) T37(d) T42 T31(d) T37(d)
160
320
14
T8(d)
170 175 165 190 175 175
340 350 325 375 350 350
10 18 24 36 18 18
T6 T81(d) T87(d) T62 T8 I(d) T87(d)
T351(e) T42 T351(e) 1'3 I(d) T3510(e) T3511(e) T42 T4 T4 T352(f)
175 190 190 190 190 190 190 190 190 175
350 375 375 375 375 375 375 375 375 350
18 36 18 18 18 18 36 26 26 18
T851(e) T62 T851(e) T81(d) T8510(e) T8511(e) T62 T6 T6 T852(f)
170 190 190 190 190
340 375 375 375 375
10 12 8 9 16
T61 T81(d) T861(d) T62 T72
190 190 190 190 190 190 190 190 190 190 190 190 190
375 375 375 375 375 375 375 375 375 375 375 375 375
9 16 12 8 9 12 12 8 16 12 12 12 16
T62 T72 T851(e) T861(d) T62 T6 T851(e) T86(d) T62 T81 T8510(e) T851l(e) T62
205
400
2
T6
Rolled or cold finished wire. rod, and bar Extruded rod, bar, shapes, and tube
535 535
995 995
Die forgings and rolled rings Hand forgings
535 535
995 995
2018 2024(h)
Die forgings Flat sheet
51O(g) 495
950(g) 920
T4 T3(d) T361(d) T42
2024(h)
Coiled sheet
495
920
T4 T42
2219(f)
AI-Cu-Mg aUoys
2036 2038
Plate
495
920
Rolled or cold finished wire. rod, and bar
495
920
Extruded rod. bar. shapes. and tube
495
920
1'3 T3510(e) T351l(e) T42 T3(d) T42 T4 T4
Drawn tube
495
920
Sheet Sheet
500 540
930 1000 (continued)
T351(e) T361(d) T42 T4 T351(e) T36(d) T42
132/ Heat Treater's Guide: Nonferrous Alloys Table1a (continued) Precipitation heattreatment 'I1me(C), Melallemperoture(bj OF h "C
Solution heallrealment(o) Melallemperoture(h) 'fimper OF deolgnotion "C
'fimper designation
Alloy
Product Corm
2218
Oleforgings
510(g) 51O(i)
950(g) 950(i)
T4 T41
170 240
340 460
10 6
T61 112
Sheet Flatsheet
510 500
950 935
Coiledsheet
500
935
Plate
500
935
Rolledorcoldfmished wire,rod, andbar
500
935
Extrudedrod, bar,shapes,andtube
500
935
Drawntube
500
935
Dieforgings Rolledorcoldfmishedwire,rod,andbar
5000) 500
9350) 935
205 160 160 160 160 160 160 16O(k) l6O(k) 16O(k) 16O(k) 16O(k) 16O(k) 16O(k) 16O(k) 170
400 320 320 320 320 320 320 320(k) 320(k) 320(k) 32O(k) 32O(k) 320(k) 320(k) 320(k) 340
I 18 18 18 18 18 18 18 18 18 18 18 18 18 18 10
T62(e) T62 T6 T6 T62 T62 T651(e) T6 T62 T651(e) T6 T62 T6510(e) T6 T62 T6
2017 2117
Rolledor coldfmishedwireand rod
500
935
Forgings androlledrings Oleforgings
530 510(h)
985 950(h)
T4(d)O) D(d) T42 T4 T42 T42 T451(e) T4 T42 T451(e) T4 T42 T4510(e) T4 T42 T4 T4 T42 T4 T42 T4 T4
200 170
390 340
20
10
T61 T6
Sheet Sheet Extruded bar Extruded bar Extruded bar
540 530 530 530 540
1000 990 990 990 1000
D(d) D(d) D(d) D(d) D(d)
165 120 190 190 190
325 250 375 375 375
24 24 12 12 12-15
T83(d) T84(d) Peakaged(d) Peakaged(d) Peakaged(d)
Al.Cu-Mg-Si alloys 2008 2014(11)
2618 4032 Al-Cu-Llalloys 2090
2091 8090 CP276
(a)Material shouldbequenched fromthesolution-treating temperature asrapidlyaspossibleandwithminimum delayafterremovalfromthefurnace. Whenmaterial isquenchedbytotalimmersion In water, unlessotherwiseIndicated, thewatershouldbeatroomtemperature, andshouldbesuitably cooledsothatitremalnsbelow38°C (100oF)duringthequenchingcycle.Useofhigh-velocity, high-volume jets of coldwateralsoiseffective forsomematerials. (h)Thenominaltemperatures listedshouldbeattained asrapidlyaspossibleandmaintained within±6 °C (±IOoF)ofnominalduringthetimeat temperature. (c)Approximate time attemperature. The specific timewilldependonthetimerequired fortheloadtoreachtemperature. The timesshownarebasedonrapidheating,withsoaktimemeasured fromthetime theloadreachesa temperature within6 °C(10oF)of the applicable temperature. (d)Coldworking subsequent tosolutionheattreatment andpriortoanyprecipitation heattreatment Is necessary to attainthe specified properties forthistemper. (e)Stressrelievedbystretchingtoproducea specified amountofpermanent setsubsequent tosolutionheattreatment andpriortoanyprecipitation heattreatment. (I) Stress relievedby Ito 5%coldreductionaftersolutiontreatmentandpriortoprecipitation heattreatment. (g)Quenched Inwaterat 100°C (212 "F), (h)Theseheattreatments alsoapplytoalcladsheetandplateof thesealloys.(i)Quenched withroom-temperature air blast.0)See U.S.Patent4,840.852. (k)Analternative heattreatment of8 h at 177°C (350"F) mayalsobeused.0) Quenched Inwaterat 60to 80°C (140 to 180°F)
800 (a)
(b)
I
I
L
600 AI + L
i
----- Temperature range for solution heat treating
U
°
Fig. 1 Portion of aluminum-copper binary phase diagram. Temperature ranges for annealing, precipitation heat treating, and solution heat treating are indicated. The range for solution treating is below the eutectic melting point of 548°C (1018 OF) at 5.65 wt% Cu
1400
1000 u,
°oj
~
:;
~ ~
...
J
Q.
E
...
I-
OJ
, Temperature range for annealing 0 0
Q;
Q.
E
600
I
}
Temperature range for precipitation heat treating
! 200
AI + CuAI;
0 0
2
12
4 Copper. %
...
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Aluminum /133
Table 1b Typical solution and precipitation heattreatments forMg-Si aluminum alloys(6xxx seriesalloys> Alloy
6005 6009(e) 6010 6053 6061(f)
Product rorm
Solullon heatlrealment(a) Thmper Melallempemlure(b) OF designation -c
Extrudedrod,bar, shapes.and tube Sheet Sheet Dieforgings Sheet
530(d) 555 565 520 530
985(d) 1030 1050 970 985
Plate
530
985
Rolledorcold finishedwire,rod. and bar
530
985
Extrudedrod. bar,shapes,andtube
530(d)
985(d)
Drawn tube
530 530
985 985
Dieandhandforgings Rolledrings
530 530
985 985
Extrudedrod,bar,shapes.andtube
Drawntube
(d) 520(d) 520 520
(d) 970(d) 970 970
Sheet Plate Extrudedrod.bar.shapes.andtube
570 570 530
1055 1055 990
Drawntube
530
990
Ole forgings Extrudedrod.bar,shapes.and tube
530 545(d)
990 1015(d)
6111 6151
Sheet Dieforgings Rolledrings
560 515 515
1040 960 960
6262
Rolledorcoldfmishedwire. rod,and bar
540
1000
6061(f)
6063
6013(0) 6066
6070
6262
Extrudedrod.bar,shapes,andtube
54O(d)
lOOO(d)
Drawntube
540 540
1000 1000
(d) 520(d) 520 530
(d) 97O(d) 970 985
6463
Extrudedrod.bar,shapes.andtube
6951
Sheet
T1 T4 T4 T4 T4 T42 T4(g) T42 T451(h) T4
T42 T451(h) T4 T451O(h) T4511(h) T42 T4 T42 T4 T4 T4520) Tl
T4 T42 T4
T42 W(P) W(P) T4 T42 T451O(h) T4511(h) T4 1'42 T4 T4 T42 T4 T4 T4 T452(1) T4 T451 T42 T4 T451O(h) T42 T4 T42 T1 T4 T42 T4 T42
Preclpllalion heallreatment Melallempomlure(b) 11me(e). OF -c h 175 205 205 170 160 160 160 160 160 160(1) 160(1) 160(1) 160(1) 160(1) 160(1) 16O(i) 175 175 175 175 160(1) 160(i) 175 175 175 205(m) 175(n) 175(n) 175 175 175 175 175 190 190 175 175 175 175 175 175 175 160 160 175 170 170 170 170 170 170 170 175 175 175 170 170 170 205(m) 175(n) 175(n) 160 160
350 400 400 340 320 320 320 320 320 320(i) 320(1) 320(1) 320(1) 320(1) 320(i) 320(i) 350 350 350 350 320(1) 320(1) 350 350 350 400(m) 350(n) 350(n) 350 350 350 350 350 375 375 350 350 350 350 350 350 350 320 320 350 340 340 340 340 340 340 340 350 350 350 340 340 340 400(m) 350(n) 350(n) 320 320
8 I 1 10 18 18 18 18 18 18 18 18 18 18 18 18 8 8 8 8 18 18 8 8 8 I 8 8 8 8 8 8 8 4 4 8 8 8 8 8 8 8 18 18 8 10 10 10 8 12 8 8 12 12 12 8 8 8 I 8 8 18 18
Thmper designation T5 T6(e) T6(e) T6 T6 T62 T6(g) T62 T651(h) T6 T89ij) T93(k) T913(k) T94(k) T62 T651(h) T6 T651O(h) T6511(h) T62 T6 T62 T6 T6 T6520) T5 T6 T62 T6 T83ij)(d) T83Iij)(d) T832ij)(d) T62 T6 T651 T6 T62 T651O(h) T6511(h) T6 T62 T6 T6 T62 T6(q) T6 T6 T6520) T6 T9(k) T651(h) T62 T6 T651O(h) T62 T6 T9(k) T62 T5 T6 T62 T6 T62
(a) Materialshouldbequenched from !he solution-treating temperatureas rapidlyas possibleandwithminimumdelayafterremovalfromthefurnace.When materialisquenchedby totalimmersioninwater, unlessotherwiseindicated.the watershouldbe at roomtemperature, andshouldbe suitablycooledso thatItremainsbelow38°C (100"P) duringthe quenchingcycle.Use of high-velocity. high-volumejets of coldwateralsoIseffectiveforsomematerials.(b) The nominaltemperatures listedshouldbeattainedas rapidlyas possibleandmaintainedwithin±6 °C (±10 "P) of nominalduringthetimeat temperature. (c) Approximatetimeat temperature. The specifictimewill dependon the timerequiredfor theloadto reachtemperature. The timesshownare basedonrapidheating,withsoak timemeasuredfromthetime theloadreachesa temperaturewithin6 °C (10 "F) of the applicabletemperature. (d)By suitablecontrolofextrusiontemperature, productmay bequencheddirectlyfromextrusionpress to providespecified propertiesfor this temper.Some productsmay be adequatelyquenched In room-temperature air blast.(e) Alternateheat treatmentsof 4 h at 190°C (375 "F) or 8 h at 175°C (350 oF) mayalso be used.See U.S.Patent4.082.578.(f)Theseheat treatments alsoapplyto alcladsheetandplateInthesealloys.(g)Applicabletotreadplateonly.(b) Stressrelivedby stretchingtoproducea specifiedamountofpermanent set priortopreclpllalionheat treatment. (I)An alternativeheat treatmentof 8 h at 170°C (340 oF) alsomay be used.ij) Coldworkingaftersolutiontreatmentis necessaryto attainspecifiedpropertiesduring precipitationheat treatments. (k) ColdworkingafterprecipitationheattreatmentIs necessary to attainspecifiedproperties. 0) Stressrelievedby Ito 5% cold reductionsubsequentto solutionheat treatment and priorto precipitationheat treatment. (m) An alternativetreatmentofJ hat 182°C (360 "F) alsomay be used. (n) An altemativetreatmentof6 h at 182°C (360 "F) alsomay beused. (0)See U.S. Patent 4,589,932.(P)1\vo weeksof naturalagingto a T4 condition.(q)ArtIficiallyagedinlaboratoryfromT4 toT6
134/ Heat Treater's Guide: Nonferrous Alloys
Table lc Typical solution and precipitation heattreatments forheat-treatable Zn-Mg aluminum alloysfrom the 7 xxx series Alloy
Product form
7001
Extrudedrod, bar,shapes,and tube
Solution heat \realmenl(a) Melal temperature(b) Thmper of "C designation
465
870
W W510(d) W511(d)
7005 7050
7075(i)
Extrudedrod, bar,and shapes Plate
890
Extrusions
475
890
Die andhandforgings
475
890
Sheet
480
900
Plate
7075(i)
475
Rolledorcoldfinishedwire,rod, and bar
480
490
900
915
W51(d) W510(d) W511(d) W W52(d) W
W W51(d) W W51(d)
Extrudedrod, bar,shapes,and tube
465
870
W
W510(d) W511(d) Drawntube
465
870
W
Dieforgings
470(m)
880(h)
W
880(h)
W52(n) W
Handforgings
470(m)
W52(n) 7175
Rolledrings Die forgings Handforgings
7475
Sheet Plate
Alclad 7475
Sheet
470
880
(0) (0) (0) (0) (0)
(0) (0) (0) (0) (0)
515(P)
960(p)
510(P) 495
950(P) 920
W W W W52(n) W W52(n) W W51(d) W
Predpitollon heat _ e n t 11me(e), MelaItemperature(bJ of h "C
120 120 120 120
250 250 250 250
24 24
24 24
(f)
(f)
(f)
(h)
(h)
(h)
(f) (f)
(f) (f)
(f) (f)
(h) (h) 1200) 1200)
(h) (h) 25O(j) 25O(j)
(h) (h) 24
(f)
(f)
(f)
(h)(k) 1200) (h)(k) 1200)
(h)(k) 25O(j) (h)(k) 25O(j)
(h)(k) 24 (h)(k)
(f)
(f)
(f)
120 120 (h)(k) 120 (b)(k) 120(1) 120(1) (h)(k)
250 250 (h)(k) 250 (h)(k) 250(1) 250(1) (h)(k)
24 24 (h)(k)
24
24
24 (h)(k)
24 24 (h)(k)
(f)
(f)
(f)
120(1) (h)(k)
250(1) (h)(k)
24
(f)
(f)
(f)
120(1) (h)(k)
250(1) (h)(k)
24
(f)
(f)
(f)
120 120 (h)(k) • 120 (h) (h) 120 (h) 120 (h) 120
250 250 (h)(k) 250 (h) (h) 250 (h) 250 (h) 250
24 24 (h)(k) 24
(0) (0) (0) (0) (0)
(0) (0) (0) (0) (0)
(0) (0) (0) (0) (0)
120 plus 155
250 315
3 3
(f)
(f)
(f)
120
250
24
(f)
(f)
(f)
(h) 120 plus 155
(h) 250 315
(h) 3 3
(f)
(f)
(f)
(h)(k) (h)(k)
(b)
(h) 24 (h) 24 (b)
24
Thmper designotioo
16 T62 T6510(d) T6511(d) T53(e) 17651(g) 17451(g) 176510(g) 176511(g) 174(g) 17452(g) T6 T62 176(g) 173(g) T62 17351(d)(g) T651(d) 17651(g) T6 T62 173(g) T651(d) 17351(d)(g) T6 T62 173(g) 176(g) T6510(d) 173510(d)(g) 176510(g) T6511(d) 173511(d)(g) 176511(g) T6 T62 173(g) T6 173(g) 17352(n)(g) T6 173(g) T652(n) 17352(n)(g) T6 T66(o) 174(g)(o) 17452(n)(g)(o) 174(g)(o) 17452(n)(g)(o) T61(P) 1761(g)(P) T651(P) 17651(g)(P) 17351(g)(P) T61(P) 1761(g)(P)
(a)Materialshouldbequenchedfromthesolution-treatingtemperatureasrapidlyaspossibleandwithminimumdelayafterremovalfromthefurnace.Whenmaterialisquenchedby totalimmersioninwater, unlessotherwiseindicated,thewatershouldbe atroom temperature, andshouldbe suitablycooledso thatit remainsbelow 38°C (100 "F) duringthequenchingcycle.Use ofhigh-velocity,high-volumejets of coldwateralsois effectiveforsomematerials.(b) The nominaltemperatures listedshouldbe attainedas rapidlyas possibleandmaintainedwithin±6 °C (±10 "F) of nominalduring the timeat temperature. (c)Approximatetimeat temperature. The specifictimewiu dependon the timerequiredfor theload toreach temperature. The timesshownare basedon rapidheating,withsoak timemeasuredfromthe time the loadreachesa temperaturewithin6 °C (10"F) ofthe applicabletemperature. (d)Stressrelivedby stretchingtoproducea specifiedamountof permanentsetaftersolutiontreatmentandpriortoprecipitation heat treatment.(e)No solutionheat treatment;72 h at room temperaturefollowingpressquench,followedby two-stageprecipitationheat treatmentcomprisedof8 h at 107°C (225 oF) plus 16h at 149°C (300 "F), (f) Agingpracticevarieswithproduct.size,natureofequipment,loadingprocedures,andfurnace-controlcapabilities. The optimumpracticefor a specificitemcanbe ascertained onlyby actualtrial treatmentof the itemunder specificconditions.Typicalproceduresinvolvea two-stagetreatmentcomprisedof3 to 30 hat 121°C (250 oF) followedby 15 to 18 hat 163°C (325 oF) for extrusions.An alternativetwo-stagetreatmentof 8 h at 99 ~C (210 oF) followedby24 to 28 h at 163°C (325 "F) alsomay be used. (g) Agingof aluminumalloys7050, 7075,7175, and 7475from any temperto the173 to 176 temperseries requirescloser-than-normal controlson agingvariables such as time,temperature, heatuprate,and so forth,for any givenitem In addition,whenmaterialin a T6-type temperis re-agedto a173- or176-type temper,thespecificconditionof theT6 material(suchaspropertylevelsandothereffectsof processingvariables)isextremelyimportantandwillaffectthecapabUity of there-agedmaterial to conformto therequirementsspecifiedfor the applicable173- or176-type temper. (h)Two-stagetreatmentcomprisedof6to 8 h at 107°C (225 "P) followedby:24 to 30 h at 163°C (325 "F) for sheetand plate; 8 to 10 h at 177°C (350 "P) for rolledor cold finishedrod and bar;6to 8 h at 177°C (350 "P) for extrusionsand tube;8 to 10h at 177°C (350 "F) for forgingsin tbe173 temper;and 6 to 8 h at 177°C (350 oF) for forgingsin the17352 temper. (i)Theseheat treatmentsalsoapplyto alcladsheetand plateof thesealloys.0) An alternativetwo-stagetreatmentcomprisedof 4 h at 96°C (205 "F) followedby 8 hat 157°C (315 oF) alsomay be used.(k) For sheet,plate, tube,andextrusions,an alternativetwo-stagetreatmentcomprisedfor6 to 8 h at 107°C (225 "F) followedby 14to 18 h at 168°C (335 oF) may be used, provided that a heatup rate of approximately 14 0C/h(25 °FIh)is employed.For rolled or cold finishedrod and bar, the alternativetreatmentis 10 hat 177°C (350 "F). (1) An alternativethree-stage treatmentcomprisedof 5 h at 99°C (210 "F), 4 h at 121°C (250 "P), andthen4 h at 149°C (300 "F) may also be used.(m)Quenchedin waterat 60 to 80°C (140to 180"F), (n)Stressrelievedby 1to 5% cold reductionaftersolutiontreatmentand priortoprecipitationheattreatments. (0) 7175-174 and-17452 heattreatmentsare directedto specificresults,mayvary fromsupplierto supplierand areeitherproprietory or patented.(P)Must be precededby soak at 466 to477 °C (870to 890 "F), SeeU.S.Patent3,791,880
Aluminum /135
Strengthening by Heat Treatment Heat treatment to increase strength of aluminum alloys is a three-step process: • Solution heat treatment: dissolution of soluble phases • Quenching: development of supersaturation • Age hardening: precipitation of solute atoms either at room temperature (natural aging) or elevated temperature (artificial aging or precipitation heat treatment)
Solution Heat Treating To take advantage of the precipitation-hardening reaction, it is necessary first to produce a solid solution. The process is called solution heat treating, and its objective is to take into solid solution the maximum practical amounts of the soluble hardening elements in alloy. The process consists of soaking the alloy at a temperature sufficiently high and for a time long enough to achieve a nearly homogeneous solid solution. Nominal commercial, solution heat-treating temperature is determined by the composition limits of the alloy and an allowance for unintentional temperature variations. Although ranges normally listed allow variations of ±6 °C (±10 OF) from the nominal, some highly alloyed, controlledtoughness, high-strength alloys require that temperature be controlled within more restrictive limits. Broader ranges may be allowable for alloys with greater intervals of temperature between their solvus and eutectic melting temperatures. Overheating. Care must be exercised to avoid exceeding the initial eutectic melting temperature. If appreciable eutectic melting occurs as a result of overheating, properties such as tensile strength, ductility, and fracture toughness may be degraded. Materials that exhibit microstructural evidence of overheating are generally categorized as unacceptable by specification. Evidence of grain-boundary melting that occurs above the eutectic melting temperature of the alloy usually is not detectable by either visual examination or nondestructive testing. Although maximum temperature must be restricted to avoid melting, the lower limit should, when possible, be above the temperature at which complete solution occurs (solvus). In the alloy represented by line (a) in Fig. 1, these temperatures would be about 575 and 515°C (1065 and 960 OF), respectively. However, under production conditions, the temperature interval for solution treatment (shown in Fig. 1 for typical 2xxx or 2xx.x) alloys provides a margin to safeguard against eutectic melting and a cushion on the low side for increased solution and diffusion rates. For alloys containing more than 5.65% Cu, complete solution can never occur. For these alloys, such as alloy 2219 (which has 5.8 to 6.8% Cu), the minimum solution heat-treating temperature is established so that it is as close as practical to the eutectic temperature while providing a margin of safety commensurate with the capability of the equipment. Line (b) in Fig. 1 is another example of a composition above 5.65% Cu that does not allow complete dissolution of aluminum-copper precipitates. For more complex ternary and quaternary systems, solution treatments are modified according to the effect of new elements on the solid solubility and/or the eutectic melting points of the basic binary system. In aluminumlithium alloys, for example, magnesium reduces the solubility oflithium in aluminum. In the aluminum-copper system, magnesium also lowers the eutectic melting point. The proximity of typical solution-treating temperature ranges to eutectic melting temperatures for three common alurninumcopper-magnesium alloys is shown in the following table:
Solutlon-treating
Eutectic
melting
Similar considerations apply to other age-hardenable alloy systems such as aluminum-magnesium-silicon alloys. For example, according to Fig. 2(a), a 1.08% Mg2Si alloy would be soaked at a temperature in excess of 500°C (930 oF) but below the solidus of 595 °C (1100 oF) to avoid incipient melting. However, because some alloy constituents may form complex eutectics that melt at temperatures below the equilibrium eutectic temperature, the upper limit for solution treatment of aluminum-magnesium-silicon alloys is in the range of 515 to 540°C (960 to 1000 "F). At 540 °C (1000 "F), about 0.6% Mg can be placed in solution (Fig. 2b). Underheating. When the temperatures attained by parts being heat treated are appreciably below the normal range, solution is incomplete, and strength somewhat lower than normal is expected. In the aluminum-copper system (Fig. 1), the shallow slope of the solvus at its intersection with the composition line indicates that a slight decrease in temperature will result in a large reduction in the concentration of the solid solution and a correspondingly significant decrease in final strength. The effect of solution-treating temperature on the strength of two aluminum alloys is illustrated by the following table: Solution-treating temperature DC
OF
6061-T6 sheet 1.6 mm (0.064in.) thick 493 920 504 940 516 960 527 980 2024-T4 sheet 0.8 mm (0.032in.) thick 488 910 491 915 493 920 496 925
Tensile strength
Ylelds!Tength
MPa
bj
MPa
ksj
301 316 333 348
43.7 45.8 48.3 50.5
272 288 305 315
39.4 41.7 44.3 45.7
419 422 433 441
60.8 61.2 62.8 63.9
255 259 269 271
37.0 37.5 39.0 39.3
Table 2 Soak times and maximum quench delays for solution treatment of wrought aluminum alloys See Table 1 for solution-treating temperatures. Soaktime, minutes Thickness(.), rom (in,)
Air tumace(b) min mox(d)
S:O.41 (0.016) 0.51(0.020) 0.64(0.025) 0.81(0.032) 1.02(0.040) 1.27(0.050) 1.35(0.053) 1.80(0.071) 2.03(0.080) 2.29(0.090) 2.54(0.100) 3.18(0.125) 4.06(0.160) 4.57(0.180) 6.35(0.250) >6.35(0.250)-12.7 (0.500) Foreachadditional12.7(0.50)orfraction Rivets (all)
20 20 25 25 30 30 30 35 35 35 40 40 50 50 55 65 +30 60
25 30 35 35 40 40 40 45 45 45 55 55 60 60 65 75 +30
Maldmum
Salt bath(c) mox{d) min
10 10 15 15 20 20 20 25 25 25 30 30 35 35 35 45 +20 . 30
15 20 25 25 30 30 30
35 35 35 45 45 45 45 45 55 +20
queo<:b
delay,.
5 7 7 7 10 10 10 10 10 10 15 15 15 15 15 15 (e) 5
temperature
tempemture Alloy
°C
OF
OC
OF
2014 2017 2024
496-507 496-507 488-499
925-945 925-945 910-930
510 513 502
950 955 935
(a)Minimumdimensionoflhickest section.(b) Soak timebeginswhen all pyrornetricinstruments recoverto originaloperatingtemperature. (c)Soak timebeginsat time of immersionexceptwhena heavy chargecauses bath ternpemture to drop below specifiedminimum. in which case soak time begins when bath regains minimum temperature, (d) Applicableto alclad materialsonly. (e) Increases in lhicknessabove 12.7 rnrn (~ in.) do not affect rnaxirnurn quench delay,which remains constantat 15s
136/ Heat Treater's Guide: Nonferrous Alloys
Table 3 Typical heattreatments foraluminum alloy sand and permanent mold castings Typeor Alloy
201.0(d)
'Thmper
castIog(a)
T4
SorP
Solutionheat treatment(b) 'Thmpomture(c) of °C
490-500(e) +5~-530
T6
S
TI
S
T43(f) TIl 204.O(d)
206.O(d)
208.0 222.0
242.0
T4 T4 T6(g) T4
SorP SorP SorP SorP
T6
SorP
TI
SorP
TI2
SorP
T55 O(h) T61 T551 T65
S S S P
0(1)
S S P S SorP S S S S P P P S S
T571
295.0
296.0
319.0
TI7 T61 T4 T6 T62 TI T4 T6 TI T5 T6
P 328.0 332.0 333.0
336.0 354.0 355.0
T6 T5 T5 T6 TI T551 T65 T51 T6 T62 TI TIl
C355.0
T6 T61
356.0
T51 T6 TI TIl
A356.0
T6 T61
357.0
T6 T61
A357.0 359.0 A444.0
T4
S P P P P P P (k) SorP S P P S P S P S P
510-515(e) +525-530 510-515(e) +525-530 525 490-500(e) +525-530 530 520 530 490-500(e) +525-530 490-500(e) +525-530 490-500(e) +525-530 490-500(e) +525-530
'910-930(e) +980-990 950-96O(e) +980-990 950-96O(e) +980-990 980 910-930(e) +980-990 985 970 985 910-930(e) +980-990 910-930(e) +980-990 910-930(e) +980-m 910-930(e) +980-990
11me,h
2 14-20 2 14-20 2 14-20 20 2 14-20 12 10 12 2 14-20 2 14-20 2 14-20 2 14-20
510
950
12
510
950
4-12
515 515 515 515 515 515 510 510 510
960 960 960 960 960 960 950 950 950
5(j) 4-12(j) 12 12 12 12 8 8 8
505 505 515
940 940 960
12 4-12 12
505 505
940 940
6-12 6-12
515 525-535
960 980-995
8 10-12
525 525 525 525 525 525 525 525 525
980 980 980 980 980 980 980 980 980
12 4-12 4-12 12 4-12 12 4-12 12 6-12
SorP S P S P S P S P
540 540 540 540 540 540 540 540
1000 1000 1000 1000 1000 1000 1000 1000
12 4-12 12 4-12 10-12 4-12 12 6-12
P S (k) (k) P
540 540 540 540 540
1000 1000 1000 1000 1000
8 10-12 8-12 10-14 8-12
(continued)
AgIng treatment 'Thmpomture(c) OF °C
Time,h
Minimwnof5 days atroomtemperature 155
310
20
370 190 5 24 h at roomlempel1lture + 0.50 to 1 hat 160°C 390 4 200 Minimum of 5 days at room temperature (g)
(g)
Minimum of 5 days at room temperature 155
310
12-24
200
390
4
243-248 155 315 155 170 170 345 205 165-170 330-355 205-230
470.480 310 600 310 340 340 650 400 330-340 625-675 400.450
16 3 11 16-22 7-9 3 8 22-26 2 (minimum) 3-5
155 155 260
310 310 500
3-6 12-24 4-6
155 310 500 260 400 205 155 310 310 155 155 310 205 400 205 400 155 310 260 500 400 205 400 205 (h) (h) 225 440 155 310 155 310 170 340 225 440 225 440 245 475 245 475 310 155 Room temperature 155 310 225 440 155 310 155 310 205 400 225 440 475 245 245 475 310 155 Room temperature 155 310 175 350 155 310 (h) (h) (h) (h)
1-8 4-6 8 2-5 2-5 2-5 7-9 7-9 2-5 4-6 7-9 7-9 (I)
7-9 3-5 2-5 14-18 3-5 3-9 4-6 3-6 3-5 8 (minimum) 10-12 7-9 3-5 2-5 3-5 7-9 3 3-6 3-5 8 (minimum) 6-12 6 10-12 (h) (h)
Aluminum /137
Table 3 (continued) Solullon heal !realmenl(b) 'Iempemlure(c)
'l)peof Alloy
'Thmper
castlng(a)
°C
OF
1ime,h
520.0 535.0 705.0
T4 T5(i1) T5
S S S
430 400
810 750
18(m) 5
P
707.0
T5
S P
17
710.0 711.0 712.0
T5 Tl T5
S P S P S
713.0
T5
SorP
771.0
T53(i1) T5 T51 T52 T6 171 T5 T5 T6 T5
S S S S S S SorP SorP P SorP
850.0 851.0 852.0
530 530
990 990
8-16 4-8
415(n)
775(n)
5(n)
59O(n) 590(1)
1090(n) 1090(1)
6(n) 6(1)
480
900
6
Aging lreatment 'Iempemture(c) of °C
Roomtemperature 100 210 Roomtemperature 100 210 155 310 Roomtemperature, or 100 210 175 350 175 350 Roomtemperature Roomtemperature Roomtemperature, or 155 315 Roomtemperature, or 120 250 36O(n) 180(n) 180(n) 355(n) 205 405
1ime,h
21 days 8 21 days 10 3-5 21 days 8 4-10 4-10 21 days 21 days 21 days 6-8 21 days 16 4(n) 3-5(n) 6
(h)
(h)
(iI)
130 140 220 220 220 220
265 285 430 430 430 430
3 15 7-9 7-9 4 7-9
(a)S, sand;P, permanentmold. (b) Unlessotherwiseindicated, solutiontreatingIs followed by quenchingin waterat 65-100°C(150-212"F), (c) Exceptwhererangesaregiven,listedtemperatures are±6 °C or ±10 oF.(d) Castingwall thickness, solidification rate, and grain refinement affectthesolutionheat-treatment cycle in alloys201.0,204.0,and 206.0,and care must be takenin approaching thefinal solutiontemperature. Toorapidan approachcan resultin theoccurrence of incipientmelting.(e)Forcastingswiththickor otherslowlysolldifiedsections,a pre-solution heattreatmentrangingfromabout 490 to515°C (910to960 "P) maybe neededto avoidtoorapidatemperature riseto ihesolutiontemperature andthemeltingofCuAh. (f) ThmperT43 for201.0wasdeveloped forimprovedimpactresistance withsomedecreasein othermechanical properties.Typical Charpyvalueis20J (15 ft ·Ib). (g) The Frenchprecipitation treatment technology fortheheat treatmentof204.0 alloyrequires12h at temperature. The agingtemperatures of 140,160.or 180°C(285.320,or 355 "P) areselectedto meet therequiredcombination ofproperties. (h) Stressrelievefordimensionalstabilityasfollows:hold5 h at 413 ± 14°C (775± 25 oF); furnacecoolto 345°C (650oF) overa periodof2 h ormore;furnacecool 10230°C (450 "F) overa periodofnot morethan0.50h; furnacecoolto 120°C(250 oF) overaperiodofapproximately 2 h;coolto roomtemperaturein still airoutsidethe furnace.(i)Noquenchrequired; coolin stillair outsidethefurnace. (j) Air-blastquenchfromsolution-treating temperature. (k) Castingprocessvaries(sand, permanentmold. or composite)dependingon desired mechanical properties. 0) Solutionheat treatas indicated, ihen artificially age by healinguniformly at the temperature and for the timenecessaryto develop the desiredmechanicalproperties. (m)Quenchin waterat65-1oo °C (150-212oF) for 10-20s only.(n)Coolto roomtemperature in still air outsidethefurnace
Solution-Treating Time. The time at the nominal solution heat-treating temperature (soak time) required to effect a satisfactory degree of solution of the undissolved or precipitated soluble phase constituents and to achieve good homogeneity of the solid solution is a function of microstructure before heat treatment. This time requirement can vary from less than a minute for thin sheet to as much as 20 h for large sand or plastermold castings. Guideline information for soak times required for wrought products of various section thicknesses is given in Table 2. Similar guidelines for castings are presented in Table 3. The time required to heat a load to the treatment temperature in furnace heat treatment also increases with section thickness and furnace loading, and thus total cycle time increases with these factors. Precipitation HeatTreating withoutPrior Solution HeatTreatment. Certain alloys that are relatively insensitive to cooling rate during quenching can be either air cooled or water quenched directly from a final hot-working operation. In either condition, these alloys respond strongly to precipitation heat treatment. This practice is widely used in producing thin extruded shapes of alloys 6061, 6063, 6463, and 7005. Upon precipitation heat treating after quenching at the extrusion press, these alloys develop strengths nearly equal to those obtained by adding a separate solution heat treating operation. Changes in properties occurring during the precipitation treatment follow the principles outlined in the discussion of solution heat-treated alloys.
Quenching In most instances, to avoid precipitation detrimental to mechanical properties or to corrosion resistance, the solid solution formed during solution heat treatment must be quenched rapidly enough (and without interruption) to produce a supersaturated solution at room temperature-
the optimum condition for precipitation hardening. The resistance to stresscorrosion cracking of certain copper-free aluminum-zinc-magnesium alloys, however, is improved by slow quenching. Most frequently, parts are quenched by immersion in cold water or, in continuous heat treating of sheet, plate, or extrusions in primary fabricating mills, by progressive flooding or high-velocity spraying with cold water. However, parts of complex shape, often with both thin and thick sections (such as die forgings, most castings, impact extrusions, and components formed from sheet) are commonly quenched in a medium that provides somewhat slower cooling. This medium may be water at 65 to 80 °C (150 to 180 "F), boiling water, an aqueous solution of polyalkylene glycol, or some other fluid medium such as forced air or mist. Effectof Quench Rate on Properties. As a broad generalization, the highest strengths attainable and the best combinations of strength and toughness are those associated with the most rapid quenching rates. Resistance to corrosion and stress-corrosion cracking are other characteristics that are generally improved by maximum rapidity of quenching. Some of the alloys used in artificially aged tempers, and in particular the copper-free Txxx alloys, are exceptions to this rule. Delay in Quenching. Whether the transfer of parts from the furnace to the quench is performed manually or mechanically, it must be completed in less than the specified maximum time. The maximum allowable transfer time or "quench delay" varies with the temperature and velocity of the ambient air and the mass and emissivity of the parts. From cooling curves such as those illustrated in Fig. 3, maximum quench delays (see table accompanying Fig. 3) can be determined that will ensure complete immersion before the parts cool below 400°C (750 OF). Quench delay is conservatively defined as commencing "when the furnace door begins to open or the first corner of a load emerges from a salt bath" and ending "when the
138/ Heat Treater's Guide: Nonferrous Alloys
Fig. 2 Equilibrium solubility as function of temperature for (a) M92Si in aluminum with an Mg-Si ratio of 1.73-to-1 and (b) magnesium and silicon in solid aluminum when both Mg2Si and silicon are present
LIVE GRAPH Click here to view
Fig. 3 Cooling curves for Alclad and nonclad aluminum products cooled from 495°C (920 oF) in forced air. Air temperature, 25°C (80 OF); air velocity, 2.3 m1s (450 fVmin).Tabulated values of quench delay (maximum delay before the material being quenched has cooled below 400°C, or 750 OF) were determined from cooling curves shown
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last corner of the load is immersed in the water quench tank." Recommended maximum quench-delay times are listed in Table 2. However, exceeding the maximum delay time is permitted if temperature measurements of the load prove that all parts are above 415°C (775 "F) when quenched. The C-curves used in quench-factor analysis can also assist in determining a maximum allowable delay. Water-immersion quenching normally is controlled in practice by stipulating maximum quench-delay time and maximum water temperature. The first requirement controls the cooling rate during transfer and, for high-strength alloys, often is based on the criterion of complete immersion before the metal cools below 415°C (775 OF). This speciftcationof 415°C (775 OF) is based on a critical temperature for alloy 7075, which has one of the more severe C-curves (Fig. 4). Therefore, the criterion for complete immersion of other alloys might be based on a temperature lower than the 415°C (775 OF) specification, depending on the characteristics of the particular C-curve. The second requirement controls the cooling rate during immersion. MlL-H-6088 speciftes that for water-immersion quenching, except quenching of forgings and castings, the temperature of the water shall not exceed 38°C (110 "F) upon completion of quenching. This requirement controls both the temperature of the quench water prior to immersion and the ratio of the combined mass of load and rack to the volume of water. However, to ensure adequate quenching effectiveness, it is necessary also
that the cooling fluid flow past all surfaces of each part during the first few seconds after immersion. Before parts enter the furnace, their placement in racks or baskets should be compatible with this requirement. During the first few seconds of quenching, agitation of the parts or the water should be sufficient to prevent local increases in temperature due to the formation of steam pockets. Spray Quenching. For spray quenching, the quench rate is controlled by the velocity of the water and by volume of water per unit area per unit time of impingement of the water on the workpiece. Rate of travel of the workpiece through the sprays is an important variable. Forming and Straightening after Quenching. Immediately after being quenched, most aluminum alloys are nearly as ductile as they are in the annealed condition. Consequently, it is often advantageous to form or straighten parts in this temper. Moreover, at the mill level, controlled mechanical deformation is the most common method of reducing residual quenching stresses. Because precipitation hardening will occur at room temperature, forming or straightening usually follows as soon after quenching as possible. In addition, maximum effectiveness in stress relief is obtained by working the metal immediately after quenching.
Age Hardening After solution treatment and quenching, hardening is achieved either at room temperature (natural aging) or with a precipitation heat treatment (artificial aging). In some alloys, sufficient precipitation occurs in a few days at room temperature to yield stable products with properties that are adequate for many applications. These alloys sometimes are precipitation heat treated to provide increased strength and hardness in wrought or cast products. Other alloys with slow precipitation reactions at room temperature are always precipitation heat treated before being used. In some alloys, notably those of the 2xxx series, cold working of freshly quenched material greatly increases its response to later precipitation heat treatment. Mills take advantage of this phenomenon by applying a controlled amount ofrolling (sheet and plate) or stretching (extrusion, bar, and plate) to produce higher mechanical properties. However, if the higher properties are used in design, reheat treatment must be avoided.
Aluminum /139
Fig. 4 Time-temperature-property curves at 95% of maximum tensile stress for various alloys . 1110
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Natural Aging. The more highly alloyed members of the 6xxxwrought series, the copper-containing alloys of the Txxx group, and all of the 2xxx alloys are almost always solution heat treated and quenched. For some of these alloys-particularly the 2xxxalloys-the precipitation hardening that results from natural aging alone produces useful tempers (1'3 and T4 types) that are characterized by high ratios of tensile to yield strength and high fracture toughness and resistance to fatigue. For the alloys that are used in these tempers, the relatively high supersaturation of atoms and vacancies retained by rapid quenching causes rapid formation of GP zones, and strength increases rapidly, attaining nearly maximum stable values in four or five days. Tensile-property specifications for products in 1'3- and T4type tempers are based on a nominal natural aging time of four days. In alloys for which 1'3- or T4-type tempers are standard, the changes that occur on further natural aging are of relatively minor magnitude, and products of these combinations of alloy and temper are regarded as essentially stable after about one week. In contrast to the relatively stable condition reached in a few days by 2xxx alloys that are used in 1'3- or T4-type tempers, the 6xxx alloys and to an even greater degree the 7xxx alloys are considerably less stable at room temperature and continue to exhibit significant changes in mechanical properties for many years.
Temperature control and uniformity present essentially the same problems in precipitation heat treating as they do in solution heat treating. Good temperature control and uniformity throughout the furnace and load are required for all precipitation heat treating. Recommended temperatures are generally those that are least critical and that can be used with practical time cycles. Except for 7xxx alloys in TIx tempers, these temperatures generally allow some latitude and should have a high probability of meeting property specification requirements. Furnace radiation effects seldom are troublesome except in those few furnaces that are used for both solution and precipitation heat treating. Generally, such situations should be avoided, because the high heat capacity needed for the higher temperatures may be difficult to control at normal aging temperatures. Soak time in precipitation heat treating is not difficult to control; the specified times carry rather broad tolerances. Heavier loads with parts racked closer together, and even nested, are not abnormal. The principal hazard is undersoaking due to gross excesses in loading practices. Some regions of the load may reach soak temperature long after soak time has been called. Placement of load thermocouples is critical, and limiting the size and spacing of a load may be necessary for aging to the TI3 and TI6 tempers. Soak time is not as critical for peak-aged (T6 and TB) tempers.
140 I Heat Treater's Guide: Nonferrous Alloys
Hardening of Cast Alloys In general, the principles and procedures for heat treating wrought and cast alloys are similar. The major differences between solution-treating conditions for castings and those for wrought products are found in soak times and quenching media. Solution of the relatively large microconstituents present in castings requires longer soaking periods than those used for wrought products (fable 3). When heat treatment of castings must be repeated, solution times become similar to those for wrought products, because gross solution and homogenization have been completed and are irreversible under normal conditions. Reduction of stresses and distortion from quenching is also important, because castings generally are complex shapes with variations in section thickness. Quenchants. Quenching of castings is often in boiling water or a milder medium to reduce quenching stresses in complex shapes. A commercially important variety is a mixture of polyalkylene glycol and water, which has no detrimental effect on properties for thicknesses under ap-
proximately 3.2 mm (0.125 in.). Quenchant additions can be made for the following purposes: • To promote stable vapor film boiling by the deposition of compounds on the surface of parts as they are submerged in the quench solution • To suppress variations in heat flux by increasing vapor ftlm boiling stability through chemically decreased quench solution surface tension • To moderate quench rate for a given water temperature Tempers. Cast products of heat-treatable alloys have the highest combinations of strength, ductility, and toughness when produced in T6-type tempers. Developing T6-type tempers in cast products requires the same sequence of operations employed in developing tempers of the same type in wrought products-solution heat treating, quenching, and precipitation heat treating. Premium-quality casting specifications such as MlL-A-21180 can require different strengths and ductility levels in the same casting.
Stress Relief Immediately after being quenched, most aluminum alloys are nearly as ductile as they are in the annealed condition. Consequently, it is often advantageous to stress relieve parts by working the metal immediately after quenching. Numerous attempts also have been made to develop a thermal treatment that will remove, or appreciably reduce, quenching stresses. Normal precipitation heat-treating temperatures are generally too low to provide appreciable stress relief. Exposure to higher temperatures (at which stresses are relieved more effectively) results in lower properties. However, such treatments are sometimes utilized when even moderate reduction of residual stress levels is important enough so that some sacrifice in mechanical properties can be accepted. The T7 temper for castings is a typical example of this kind of treatment. Mechanical Stress Relief. Deformation consists of stretching (bar, extrusions, and plate) or compressing (forgings) the product sufficiently to achieve a small but controlled amount (l to 3%) of plastic deformation. If the benefits of mechanical stress relieving are needed, the user should refrain from reheat treating. Specific combinations of the supplemental digits are used to denote the tempers produced when mechanical deformation is used primarily to relieve residual stresses induced during the quenching operation. For products stress relieved by stretching, the digits 51 follow the basic Tx designation (f451, for example). For products stress relieved by compressive deformation, the supplementary digits are 52. An additional digit is added to designations for extrusions: an added zero specifies that the product has not been straightened after final stretching; an added one indicates that straightening may have been performed after fmal stretching.
Effect of Precipitation Heat Treating on Residual Stress. The stresses developed during quenching from solution heat treatment are reduced during subsequent precipitation heat treatment. The degree of relaxation of stresses is highly dependent upon the time and temperature of the precipitation treatment and the alloy composition. In general, the precipitation treatments used to obtain the T6 tempers provide only modest reduction in stresses, ranging from about 10 to 35%. To achieve a substantial lowering of quenching stresses by thermal stress relaxation, highertemperature treatments of the T7 type are required. These treatments are used when the lower strengths resulting from overaging are acceptable. Other thermal stress-relief treatments, known as subzero treatment and cold stabilization, involve cycling ofparts above and below room temperature. The temperatures chosen are those that can be readily obtained with boiling water and mixtures of dry ice and alcohol-namely, 100 and-73°C (212 and-loo °F)-and the number of cycles ranges from one to five. The maximum reduction in residual stress that can be effected by these techniques is about 25%. The maximum effect can be obtained only if the subzero step is performed first, and immediately after quenching from the solution-treating temperature while yield strength is low. No benefit is gained from more than one cycle. A 25% reduction in residual stress is sometimes sufficient to permit fabrication of a part that could not be made without this reduction. However, if a general reduction is needed, as much as 83% relief of residual stress is possible by increasing the severity of the uphill quench-that is, more closely approximating the reverse of the cooling-rate differential during the original quench.
Effects of Reheating The precipitation characteristics of aluminum alloys must be considered frequently during evaluation of the effects ofreheating on mechanical properties and corrosion resistance. Such evaluations are necessary for determining standard practices for manufacturing operations, such as hot forming and straightening, adhesive bonding, and paint and dry-film lubricant curing, and for evaluation the effects of both short-term and long-term exposure in elevated temperatures in service.
The stage of precipitation that exists in an alloy at the time ofreheating plays a significant role in the effects of reheating. Consequently, it is extremely dangerous to reheat material in a solution heat-treated temper without first carefully testing the effects of such reheating. In one such test, 2024-T4 sheet was found to be very susceptible to intergranular corrosion when subjected to a 15-min drying operation at 150°C (300 OF) during the first 8 h after quenching; no susceptibility was evident when the same drying operation was performed more than 16 h after quenching.
Aluminum /141
Annealing Annealing treatments are of several types that differ in objective. Annealing times and temperatures depend on alloy type as well as on initial structure and temper. Full Annealing. The softest, most ductile, and most workable condition of both nonheat-treatable and heat-treatable wrought alloys is produced by full annealing to the temper designated "0." For both heat-treatable and non-heat-treatable aluminum alloys, reduction or elimination of the strengthening effects of cold working is accomplished by heating at a temperature from about 260 to about 440°C (500 to 825 "F). The rate of softening is strongly temperature-dependent; the time required to soften a given material by a given amount can vary from hours at low temperatures to seconds at high temperatures. If the purpose of annealing is merely to remove the effects of strain hardening, heating to about 345°C (650 oF) will usually suffice. If it is necessary to remove the hardening effects of a heat treatment or of cooling from hot-working temperatures, a treatment designed to produce a coarse,
widely spaced precipitate is employed. This usually consists of soaking at 415 to 440°C (775 to 825 "F) followed by slow cooling (28 °CIh, or 50 °FIh, max) to about 260°C (500 oF). The high diffusion rates that exist during soaking and slow cooling permit maximum coalescence of precipitate particles and result in minimum hardness. In annealing, it is important to ensure that the proper temperature is reached in all portions of the load; it is common to specify a soaking period of at least 1 h. The maximum annealing temperature is moderately critical;
Table 4b Typical full annealingtreatments for some common wrought aluminumalloys These treatments, which anneal the material to the 0 temper, are typical for various sizes and methods of manufacture and may not exactly describe optimum treatments for specific items. Metaltempemture Alloy
Table 4a Typical annealingtreatments for aluminum alloymill products Alloy
1060 1100 1145 1235 1345 1350 2014 2017 2024 2117 2219 3003 3004 3005 3105 5005 5050 5052 5056 5083 5086 5154 5254 5454 5456 5457 5652 6005 6053 6061 6063 6066 7072 7075 7175 7178 7475 Brazing Sheet: Nos. 11& 12 Nos. 23&24
MetaJ tempemture OF
Approximate timeat Iempemture bours
deslgoalion
Thmper
650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 775 650 775 650 650 650 650 650 650 650 650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 650 775(c) 775(c) 775(c) 775(c)
(a) (a) (a) (a) (a) (a) (b)(c) (b)(c) (b)(c) (b)(c) (b)(c) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (b)(c) (b)(c) (b)(c) (b)(c) (b)(c) (a) (b)(c) (b)(c) (b)(c) (b)(c)
0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0
650 650
(a) (a)
0 0
(a)TImein the furnaceneednot be longerthan necessarytobring allpartsofload to annealingtemperature.Rateof coolingis unimportant.(b)These treatmentsare intendedto removeeffectsof solutionheattreatmentandincludecoolingat rateof about50 OF perhourfromtheannealingtemperature to 500 oF-The rate of subsequentcooling is unimportant. Treatmentat 650 OF, followed by uncontrolledcooling,may be usedto removetheeffectsof cold work,or topartiallyremovethe effectsof heattreatment.(c)ThIstreatmentisintendedto removetheeffectsofsolutionheatlreatment and includescoolingat an uncontrolledrateto 400 OF or less, followedbyreheatingto 450 OF for 4 h. Treatmentat 650 OF, followedby uncontrolledcooling,may be usedto removetheeffectsof cold work, or to partiallyremovethe effectsof heattreatment.
1060 1100 1350 2014 2017 2024 2036 2117 2124 2219 3003 3004 3105 5005 5050 5052 5056 5083 5086 5154 5182 5254 5454 5456 5457 5652 6005 6009 6010 6053 6061 6063 6066 7001 7005 7049 7050 7075 7079 7178 7475 Brazing sheet No. Hand 12 No.21 and22 No.23 and24
OC
OF
Appromnate tbneat Iempemture, b
345 345 345 415(b) 415(b) 415(b) 385(b) 415(b) 415(b) 415(b) 415 345 345 345 345 345 345 345 345 345 345 345 345 345 345 345 415(b) 415(b) 415(b) 415(b) 415(b) 415(b) 415(b) 415(c) 345(d) 415(c) 415(c) 415(c) 415(c) 415(c) 415(c)
650 650 650 775(b) 775(b) 775(b) 725(b) 775(b) 775(b) 775(b) 775 650 650 650 650 650 650 650 650 650 650 650 650 650 650 650 775(b) 775(b) 775(b) 775(b) 775(b) 775(b) 775(b) 775(c) 650(d) 775(c) 775(c) 775(c) 775(c) 775(c) 775(c)
(a) (a) (a) 2-3 2-3 2-3 2-3 2-3 2-3 2-3 (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) (a) 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3
345 345 345
650 650 650
(a) (a) (a)
(a) 'lime in the furnaceneed not be longerthan necessaryto bring alI parts of the load to annealing temperature. Coolingrate isunimportant. (b)These treatments areintendedtoremovetheeffectsof solutiontreatmentand includecoolingat a rate of aboUl300C/h (50°FIb)from the annealingtemperatureto 260 "C (500 oF). Rate of subsequentcooling is unimportant. Treatmentat 345°C (650 oF), followedby uncontrolled cooling,may be used toremove the effectsof cold work or to partly removetheeffectsof heat treatment. (c)Thesetreatmentsareintendedto removetheeffectsof solution treatmentand includecoolingat an uncontrolledrateto205°C (400 oF) or less,followedbyreheatingto 230°C (450 oF) for 4 h. Treatmentat 345 "C(650 oF), followedby uncontrolledcooling, maybe usedtoremovethe effectsof cold workor to partlyremovetheeffectsof heattreatment. (d) Coolingrate to205 DC (400 OF) or belowis less than orequal to 30 0C/h (50 °FIb)
142/ Heat Treater's Guide: Nonferrous Alloys
it is advisable not to exceed 415°C (775°F), because of oxidation and grain growth. The heating rate can be critical, especially for alloy 3003, which usually requires rapid heating for prevention of grain growth. Relatively slow cooling, in still air or in the furnace, is recommended for all alloys to minimize distortion. Typical annealing conditions used for some alloys in common use are listed in Tables 4a and b. Partial Annealing. Annealing of cold-worked non-heat-treatable wrought alloys to obtain intermediate mechanical properties (H2-type tempers) is referred to as partial annealing or recovery annealing. Bendability and formability of an alloy annealed to an H2-type temper generally are significantly higher than those of the same alloy in which an equal strength level is developed by a final cold-working operation (HI-type temper). Treatments to produce H2-type tempers require close control of temperature to achieve uniform and consistent mechanical properties. Stress-Relief Annealing. For cold-worked wrought alloys, annealing merely to remove the effects of strain hardening is referred to as stress-relief annealing. Such treatments employ temperatures up to about 345°C (650 "F), or up to 400 ± 8°C (750 ± 15 "F) for 3003 alloy, and cooling to room temperature. No appreciable holding time is required. Such treatment may result in simple recovery, partial recrystallization, or full recrystallization. Age hardening may follow stress-relief annealing of heat-treatable alloys, however, because a concentration of soluble alloying
elements sufficient to cause natural aging remains in solid solution after such treatments. Controlled-Atmosphere Annealing and Stabilizing. Aluminum alloys that contain even very small amounts of magnesium will form a surface magnesium oxide unless the atmosphere in the annealing furnace is free ofmoisture and oxygen. Examples include alloy 3004, which is used for cooking utensils, and alloys of the 5xxx series. Another problem that control of the annealing atmosphere helps to overcome or avoid is oil staining by oil-base roll lubricants that do not burn off at lower annealing temperatures. If the oxygen content of the furnace atmosphere is kept very low during such annealing, the oil will not oxidize and stain the work. Temperature control for full and partial annealing is somewhat more critical than for stress-relief annealing; the temperatures and times specified are selected to produce recrystallization and, in the case of heat-treatable alloys, a precipitate of maximum size; for this the cooling rate must be closely controlled. Annealing of castings for 2 to 4 h at temperatures 315 to 345°C (600 to 650 OF) provides the most complete relief of residual stresses and precipitation of the phases formed by the excess solute retained in solid solution in the as-cast condition. Such annealing treatments provide maximum dimensional stability for service at elevated temperatures. The annealed temper is designated "0."
Grain Growth Many aluminum alloys in common use are subject to grain growth during solution treatment or annealing. This phenomenon can occur during or after recrystallization of material that has been subjected to a small critical amount of prior cold work. It is usually manifested by surface roughening during subsequent fabrication operations and frequently results in rejections for appearance or functional reasons. Less frequently, some deterioration of mechanical properties is encountered, and this is undesirable regardless of surface-roughening effects. When a grain-growth problem is discovered, it is too late to change the condition of the parts in question, but several methods are available for preventing recurrence of the difficulty. The simplest of these is relieving
the causative stress by interjecting a stress-relief anneal into the manufacturing sequence immediately prior to the solution-treating or full-annealing cycle in which the grain growth occurred. This approach is usually successful and practical. Another possibility is to adjust the amount of stress present in the part immediately prior to the critical heat treatment so that the stress level is outside the critical range. This may be done by adding a cold-working operation before forming, such as prestretching of blanks, or by forming in multiple stages with a stress-relief anneal before each stage. A third method that is sometimes successful consists of increasing the heating rate during the critical heat treatment by reducing the size of furnace loads or by changing from an air furnace to a salt bath.
Dimensional Changes during Heat Treatment Distortion as a result of creep during solution heat treatment should be avoided by proper loading of parts in baskets, racks, or fixtures, or by provision of adequate support for long pieces of plate, rod, bar, and extrusions heat treated in horizontal roller hearth furnaces. Sheet is provided with air-pressure support in continuous heat-treating furnaces to avoid scratching, gouging, and distortion. If parts are to be solution heat treated in fixtures or racks made of materials (such as steel) with coeffi-
cients of thermal expansion lower than that of the aluminum being treated, allowance should be made for this differential expansion to ensure that expansion of the aluminum is not restricted. Straightening immediately after solution heat treating may be preferable to fixturing, Solution of phases formed by major alloying elements causes volumetric expansion or contraction, depending on the alloy system, and this may have to be taken into account in heat treatment of long pieces.
Quality Assurance Tensile Tests. In general, the relatively constant relationships among various properties allow the use of tensile properties alone as acceptance criteria. The minimum guaranteed strength is ordinarily that value above which it has been statistically predicted with 95% probability that 99% or
more of the material will pass. The inherent variability within lots and among specimens from a given piece is shown in Fig. 5. Hardness. Tests are less valuable for acceptance and rejection of heat-treated aluminum alloys than they are for steel. Nevertheless, hard-
Aluminum /143 ness tests have some utility for process control. Typical hardness values for various alloys and tempers are given in Table 5. Figure 6 shows the general relationship between longitudinal tensile strength and hardness for aluminum alloys. Electrical Conductivity. For control of the corrosion and stress-corrosion characteristics of certain tempers, notably the 1'73 and 1'76 types, the material must meet combination criteria of yield strength plus electrical conductivity. Low tensile strengths may be accompanied by high levels of electrical conductivity, so electrical conductivity is sometimes used as a quality-assurance diagnostic tool. However, because the correlation between strength and electrical conductivity is strongly a function of chemical composition and fabricating practice, use of electrical conductivity is not recommended except for rough screening, which must be followed by hardness testing, and then by tensile testing if the hardness tests indicate that the heat treatment was suspect. Fracture Toughness Indices. Fracture toughness is rarely, if ever, a design consideration in the 1000,3000,4000,5000, and 6000 series alloys. The fracture toughness of these alloys is sufficiently high that thicknesses beyond those commonly produced would be required to obtain a valid test.
Fracture toughness quality control and material procurement minimums are appropriate for controlled-toughness, high-strength alloys. The alloys and tempers currently identified as controlled-toughness, highstrength products include: AnDy
Condltlon
Product rorm
2048 2124 2419 7049 7050 7150 7175 7475
T8 13.T8 T8 T7 T7 T6 T6,T7 T6,T7
Sheetandplate Sheetandplate Sheet,plate,extrusions, andforgings Plate,forgings, andextrusions Sheet,plate,forgings, andextrusions Sheetandplate Sheet,plate,forgings,andextrusions Sheetand plate
The fracture toughness of these alloys and tempers range in measured Klc values from about 20 MPa'.lnl (18 ksi"ln.) upward. Controlled-toughness alloys are often derivatives of conventional alloys.For example, 7475 alloy is a derivative of 7075 with maximum compositional limits on some elements that were found to decrease toughness.
Table 5 Typical acceptable hardness values for wrought aluminum alloys Acceptable hardness does not guarantee acceptable properties; acceptance should be based on acceptable hardness plus written evidence of compliance with specified heat-treating procedures. Hardness values higher than the listed maximums are acceptable provided that the material is positively identified as the correct alloy. Hardness Alloy lindtemper
2014-13,-T4,-T42 2014-T6,-T62,-T65 2014-T61 2024-13 2024-136 2024-T4,-T42(d) 2024-T6,-T62 2024-TSI 2024-TS6 6053-T6 6061-T4(d) 6061-T6 6063-T5 6063-T6 6151-T6 7075-T6,-T65
7079-T6,-T65 7178-T6
Product rorm(o)
HRB
HRE
All
65-70 80-90 81-90
87-95 103-110 104-110 100-109 97-106 91-100 93-102 100-110 97-106 91-100 93-102 99-106 99-106 99-106 105-110 79-87 60-75 70-81
Sheet{b) All others All
Notclad(c) Clad, ~1.60 mm(0.063in.) Clad,>1.60mm(0.063in.) All
Notclad Clad, ~1.60 mm (0.063in.) Clad,>1.60mm (0.063in.) All
Notclad Clad All All
Sheet Extrusions;bar Notclad,0.41 mm (0.016in.) Notclad,~.51 mm (OmOin.) Clad
69-83 52-71 52-71 76-90 69-83 52-71 52-71 74.5-83.5 74.5-83.5 83-90
HR15T
111-118 109-116 109-116
82.5-87.5 80-84.5
111-118 109-116 109-116
85-90 82.5-87.5 80-84.5 84-88 84-88
88-100 82-103
87.5-90 74.5-78.5 64-75 67-78 75-84 78-84
89-97
62.5-70
85-94
85-97 84-96 55-70 70-85 91-102 106-114
78-90 76-90 76-90 73-90 81-93 85 min
102-110 104-110 104-110 102-110 102-110 104-114 105min
87.5-92 88min
102min
86 min
47-72
All All All
Notclad(e) Clad: ~.91 mm (O.036 in.) >0.91s 1.27mm (>0.036s 0.050in.) >1.27~ 1.57mm (>0.050~ 0.062 in.) >1.57s 1.78mm (>0.062~0.070 in.) >1.78mm (0.070in.) All(e) Notclad(t) Clad: ~.91 mm (0.036in.) >0.91 s 1.57mm (>0.036~ 0.062in.) >1.57mm (0.062in.)
HRH
87.5-92 86-90
85 min 88min
(a)Minimumhardnessvaluesshownforcladproductsarevalidforthicknesses up to and including2.31mm(0.091in.);forheavier-gage material,claddingshouldbe locallyremovedforhardnesstestingor test should be perfonnedon edge of sheet. (b) 126to 158HB (lO mm bal, 500kg load).(c) 100to 130HB (10mm ball,500kg load).(d)Alloys2024-T4,2024-T42 and6061-T4shouldnot be rejectedfor lowhardnessuntil theyhaveremainedatroom temperature for at least three daysfollowingsolutiontreatment. (e) 136to 164HB (10 mmball,500kg load).(t) 136HBmin(lOmmball, 500kgload)
144/ Heat Treater's Guide: Nonferrous Alloys
600
Fig. 6 Tensile strength versus hardness for various aluminum alloysandtempers
85
550
LIVE GRAPH
75
'"
Q.
500
:;; f5'
70
en
c
e
. .'"
to
.
c I-
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~ tc:
e 65 :;:
450
.. ..
~
60 400
c:
I-
55 350
50 45 70 80 Hardness. HRB
90
100
Temper Designations for Heat-Treatable Aluminum Alloys Basictemperdesignations for heat-treated conditions include the codes 0, W, and T. Other basic temper designations are F (as fabricated) and H (strain hardened). • 0, annealed. Applies to wrought products that are annealed to obtain lowest strength temper and to cast products that are annealed to improve ductility and dimensional stability. The 0 may be followed by a digit other than zero. • W, solution heat treated. An unstable temper applicable to any alloy that naturally ages (spontaneously ages at room temperature) after solution heat treatment. This designation is specific only when the period of natural aging is indicated-for example, W 1;2 h. (See discussion of the Tx51, Tx52, and Tx54 tempers, in the section below on subdivision of the T temper.) • T, heat treated to produce stable tempers other than O. Applies to products that are thermally treated, with or without supplementary strain hardening, to produce stable tempers. The T is always followed by one or more digits.
MajorSubdivisions of T Temper. In T-type designations, the T is followed by a number from I to 10; each number denotes a specific sequence of basic treatments: • TI, cooled from an elevated-temperature shaping process and naturally aged to a substantially stable condition. Applies to products that are not cold worked after an elevated-temperature shaping process such as casting or extrusion, and for which mechanical properties have been stabilized by room-temperature aging. If the products are flattened or straightened after cooling from the shaping process, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • TI, cooled from an elevated-temperature shaping process, cold worked, and naturally aged to a substantially stable condition. Applies to products that are cold worked specifically to improve strength after cooling from a hot-working process such as rolling or extrusion, and for which mechanical properties have been stabilized by room-temperature aging. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits.
• TI, solution heat treated, cold worked, and naturally aged to a substantially stable condition. Applies to products that are cold worked specifically to improve strength after solution heat treatment, and for which mechanical properties have been stabilized by room-temperature aging. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits. • T4, solution heat treated and naturally aged to a substantially stable condition. Applies to products that are not cold worked after solution heat treatment, and for which mechanical properties have been stabilized by room-temperature aging. If the products are flattened or straightened, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • T5, cooled from an elevated-temperature shaping process and artificially aged. Applies to products that are not cold worked after an elevated-temperature shaping process such as casting or extrusion, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. If the products are flattened or straightened after cooling from the shaping process, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • T6, solution heat treated and artificially aged. Applies to products that are not cold worked after solution heat treatment, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. If the products are flattened or straightened, the effects of the cold work imparted by flattening or straightening are not recognized in specified property limits. • 11, solution heat treated and stabilized. Applies to products that have been precipitation heat treated to the extent that they are overaged. Stabilization heat treatment carries the mechanical properties beyond the point of maximum strength to provide some special characteristic, such as enhanced resistance to stress-corrosion cracking or to exfoliation corrosion. • T8, solution heat treated, cold worked, and artificially aged. Applies to products that are cold worked specifically to improve strength after solution heat treatment, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. The effects of cold work, including any cold work
Aluminum /145 imparted by flattening or straightening, are recognized in specified property limits. • 1'9, solution heat treated, artificially aged, and cold worked. Applies to products that are cold worked specifically to improve strength after they have been precipitation heat treated. • TlO, cooled from an elevated-temperature shaping process, cold worked, and artificially aged. Applies to products that are cold worked specifically to improve strength after cooling from a hot-working process such as rolling or extrusion, and for which mechanical properties or dimensional stability, or both, have been substantially improved by precipitation heat treatment. The effects of cold work, including any cold work imparted by flattening or straightening, are recognized in specified property limits.
Other Subdivisions T Temper Codes for Stress-Relieved Products. When it is desirable to identify a variation of one of the ten major T tempers described above, additional digits, the first (x) of which cannot be zero, may be added to the designation. The following specific sets of additional digits have been assigned to stress-relieved wrought products:
• Tx51, stress relieved by stretching. Applies to the following products when stretched to the indicated amounts after solution heat treatment or after cooling from an elevated-temperature shaping process: Tx51 applies directly to plate and to rolled or cold finished rod and bar. These products receive no further straightening after stretching. Tx51 also applies to extruded rod, bar, shapes, and tubing, and to drawn tubing, when designated as follows: Product Corm
Plate Rod, bar.shapes.extrudedtube Drawntube
Permanent set, %
1.5-3 1-3 0.5-3
• Tx5lO. Products that receive no further straightening after stretching • Tx511. Products that may receive minor straightening after stretching to comply with standard tolerances • Tx52. Stress relieved by compressing. Applies to products that are stress relieved by compressing after solution heat treatment, or after cooling from a hot-working process to produce a permanent set of 1 to 5% • Tx54. Stress relieved by combining stretching and compressing. Applies to die forgings that are stress relieved by restriking cold in the finish die. (These same digits-and 51, 52, and 54-may be added to the designation W to indicate unstable solution heat-treated and stress-relieved tempers) Temper designations T42 and T62 apply to wrought products heat treated from the 0 or the F temper to demonstrate response from the heat treatment described below. Temper designations T42 and T62 also may be applied to wrought products heat treated from any temper by the user when such heat treatment results in the mechanical properties applicable to these tempers. • T42. Solution heat treated from the 0 or the F temper to demonstrate response to heat treatment and naturally aged to a substantially stable condition • T62. Solution heat treated from the 0 or the F temper to demonstrate response to heat treatment and artificially aged
Subdivision of the 0 Temper. In temper designations for annealed products, a digit following the 0 indicates special characteristics. For example, 01 denotes that a product has been heat treated according to a time/temperature schedule approximately the same as that used for solution heat treatment, and then air cooled to room temperature, to accentuate ultrasonic response and provide dimensional stability; this designation applies to products that are to be machined prior to solution heat treatment by the user.
Properties of Wrought Aluminum and Wrought Aluminum Alloys Aluminum mill products have been subjected to plastic deformation by hot- and cold-working mill processes (such as rolling, extruding, and drawing, either singly or in combination), so as to transform cast ingot into the desired product form, Microstructural changes associated with the working and with any accompanying thermal treatments are used to control certain properties and characteristics of the worked, or wrought, product or alloy.
Typical mill products include plate or sheet (which is subsequently formed or machined into products such as aircraft or building components), household foil, and extruded shapes such as storm window frames. A vast difference in the mechanical and physical properties of mill products can be obtained through the control of the chemistry, processing, and thermal treatment. Examples of corrosion and fabrication properties that are available, per alloy and temper, are found in the Table that follows.
Comparative characteristics and applications Weldabilil}'(Q Resistance spotand
Resistance tocorrosion St.....General(a)
crackiDg(b)
Workabitity (cold)(e)
Machlnability(e)
A A A A ,A A A A A A A A A A A A A A A A A A A A A A A A A A D(c) D(c) D
A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D B
A A A B B A A A B B A A A B C A A A B B A A A B B A A A B B C B D
E E
D(c) D
C C
C D
corrosion
Alloy temper 10500 Hl2 HI4 HI6 Hl8 10600 HI2 HI4 HI6 HI8 11000 HI2 HI4 HI6 HI8 11450 HI2 HI4 Hl6 HI8 11990 HI2 HI4 HI6 HI8 13500 H12,H1l1 H14,H24 HI6,H26 HI8 2011TI T4, T451 T8 20140 TI,T4,T451 T6, T651,T651O. T6511
D D D E E D D D E E D D D E E
D D D E E
D D
D E E D D D A A A D B
B
Gas
An:
seam
ability(l)
Solderabilil}'(g)
A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D D D
A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D B B
B A A A A B A A A A B A A A A B A A A A B A A A A B A A A A D D D B B B
A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A D D D D D D
A A A A A A A A A A A A A A A A A A A A A A A A A A A A A A C C C C C C
Braze-
Some lypicaI applications ofalloys Chemicalequipment, railroadtankcars
Chemicalequipment, railroadtankcars
Sheet-metalwork,spunhollowware, fin stock
Foil.fin stock
Electrolytic capacitorfoil,chemical equipment,railroadtankcars
Electricalconductors
Screw-machine products
Truckframes, aircraftstructures
(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittent spraying or immersion. Alloys with A and B ratings can be used in industrialand seacoast atmosphereswithout protection. Alloyswith C. D, and Eratings generallyshould be protected at least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratorytests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A = No known instance of failure in service or in laboratory tests. B = No known instance of failure in service;limited failures in laboratory tests of short transversespecimens. C = Service failures with sustained tension stress acting in short transverse direction relative to grain structure: limited failures in laboratory tests of long transverse specimens.D = Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would be E. (d) This rating may be different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasingorder of merit. (f) Ratings A through D for weldabilityand brazeabilityare relative ratings defined as follows:A = Generally weldableby all commercial proceduresand methods. B = Weldablewith special techniquesor for specificapplications;requirespreliminarytrials or testing to develop welding procedure and weld performance.C = Limited weldabilitybecause of crack sensitivityor loss in resistance to corrosion and mechanicalproperties.D = No commonlyused welding methods have been developed. (g) Ratings A through D and NA for solderabilityare relative ratings defined as follows:A = Excellent.B =Good. C = Fair. D = Poor.NA = Not applicable (continued)
Wrought Aluminum and Aluminum Alloys /147 Comparative characteristics andapplications (continued) WeldabilitylO Resistance spoland
Resistance 10 corrosion
StressGenerat(a)
cmcking(b)
Workability (cold)(e)
D(c) D(c) D 0
C C B B
C D C D
C D D D
B C C
D(c) D(c) 0 D 0 A A A A A A A A A A A A A A A A A C B A A A A A A A A A A A A A A A A A A A A(d) A(d) A(d) A(d) A(d) B(d) B(d)
C C B B C A A A A A A A A A A A A A A A A A B A A A A A A A A A A A A A A A A A A A A B(d) B(d) B(d) B(d) C(d) Oed) D(d)
corrosion
Alloy temper 20240 T4, TI, TI51, TI51O,TI511 TI61 T6 T861, T81,T851,T851O, T8511 172 2036T4 2124T851 2218T61 172 22190 TIl, TI51, TI51O,TI511 TI7 T81, T851,T851O, T8511 T87 2618T61 30030 HI2 H14 HI6 HI8 H25 30040 H32 H34 H36 H38 31050 H12 H14 H16 H18 H25 4032T6 4043 50050 HI2 HI4 HI6 HI8 H32 H34 H36 H38 50500 H32 H34 H36 H38 50520 H32 H34 H36 H38 50560 HIll H12,H32 HI4,H34 HI8,H38 H192 H392
B D
C D D D A A B C C B A B B C C A B B C C B NA A A B C C B C C A A B C C A B B C C A A B B C D D
Machinability(e)
Gas
Arc
seam
abilily(1)
Solderability(g)
D B B B B B C B
D C 0 D D
D B C C C
D B B B B
D D D D D
C C C C C
Truckwheels,screw-machine products,aircraftstructures
D
B C
0 D
D D A A A A D A A A A A A B B B B B B B B B B B D NA A A A A A A A A A A A A A A A A A A A C C C C C C C
C A A A A A C A A A A A A A A A A A A A A A A A B NA A A A A A A A A A A A A A A A A A A A A A A A A A A
C C C
Military supersonic aircraft
B
B B C B B A A A A B B A A A A A B A A A A B A A A A A C NA B A A A A A A A A B A A A A B A A A A B A A A A A A
B B B B B E E D D 0 0 0 D C C C E E D D D D B C E E 0 0 D E D D D E D 0 C C D D C C C D D D C C B
B
Braze-
D D D D D D D A A A A A A B B B B B B B B B B B 0 NA B B B
Auto-bodypanelsheet
NA
B B B
NA A A A A A A B B B B B B B B B B B NA NA B B B B B B B B
B
B
B B B B B C C C C C 0 D D D D D D
C C C C C D D D D D 0 0 0 0 0 0 D
B B
Some typical applications oralloys
Jet engineimpellers andrings Strucmralusesathigh temperatures (to 315°C, or 600 "P) high-strength weldments
Aircraftengines Cookingutensils, chemicalequipment, pressurevessels,sheet-metalwork, builder's hardware,storage tanks
Sheet-metalwork,storagetanks
Residential siding,mobilehomes, rain-carryinggoods,sheet-metal work
Pistons Weldingelectrode Appliances, utensils,architectura1, electricalconductors
Builders'hardware, refrigerator trim, coiled tubes
Sheet-metal work,hydraulictube, appliances
Cablesheathing, rivetsfor magnesium, screenwire, zippers
(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittentspraying or immersion. Alloys with A and B ratings can be used in industrialand seacoast atmosphereswithout protection.Alloys with C, D, and E ratings generally should be protected at least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A =No known instance of failure in service or in laboratory tests. B =No known instance of failure in service; limited failures in laboratory tests of short transversespecimens. C =Service failures with sustained tension stress acting in short transverse direction relative to grain structure: limited failures in laboratory tests of long transverse specimens. 0 =Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would be E. (d) This rating may be different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasing order of merit. (f) Ratings A through 0 for weldabilityand brazeability are relative ratings defined as follows: A =Generally weldableby all commercial proceduresand methods. B =Weldablewith special techniquesor for specific applications;requires preliminarytrials or testing to develop welding procedureand weld performance.C =Limited weldablllty because of crack sensitivity or loss in resistance to corrosion and mechanicalproperties.D =No commonly used welding methods have been developed. (g) Ratings A through 0 and NA for solderabilityare relative ratings defined as follows: A =Excellent. B =Good. C =Fair. D =Poor.NA =Not applicable (continued)
148 I Heat Treater's Guide: Nonferrous Alloys Comparative characteristics andapplications (continued) Resistance tocorrosion StressWorkabitity (co!d)(e)
Machinability(e)
Gas
An:
seam
abillly(f)
A(d) A(d) B(d) A(d) A(d) B(d) B(d) B(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A A A A(d) A(d) A(d) A(d) A(d) A A A A A B(d) B(d) B(d) A A A A A A A A A A A
B C C A B B C C B A B B C C A D B B C A B B C C NA A B B B B C C A A B B C C A B B
D D D D D C C C D D D C C C D B D C C D D C C C B D D C D D D D E D D C C C D D D D C
C C C C C C C C C C C C C C C C A A A C C C C C NA C C C C C C C A A A A A A A A A A A
A A A A A A A A A A A A A A A A A A A A A A A A NA A A A A A A A A A A A A A A A A A A
B A A B A A A A A B A A A A B A A A A B A A A A NA B A A A B A A B B A A A A A A A A A
D D D D D D D D D D D D D D D D C C C D D D D D NA D D D D D D D B C C C C C B B B B A
D D D D D D D D D D D D D D D D D D D D D D D D NA
A A A B A A A A A A A B B B B A A
A B A B C B B B C C B C
C C D C C D D C C C D C B C C C D
A A A A A A A A A A D D D A A A A
A A A A A A A A A A B B B A A A A
A A B A A A A A A A B B B A A A A
A A A A A A A A A A D D D B B A A
B B B B B B B B B B
corroslon
Alloy temper 50830 H32l,H1l6 H11l 50860 H32,H116 H34 H36 H38 H11l 51540 H32 H34 H36 H38 51820 HI9 5252H24 H25 H28 52540 H32 H34 H36 H38 5356 54540 H32 H34 HlII 54560 H11l H321,HlI5 54570 56520 H32 H34 H36 H38 5657H241 H25 H26 H28 6005T5 6009T4 6010T4 60610 T4,T45l, T451O, T4511 T6, T65l, T652,T651O, T6511 6063T1 T4 T5,T52 T6 T83,T831,T832 60660 T4,T451O, T4511 T6, T651O, T65l1 6070T4,T4511 T6 61OIT6,T63 T6I,T64
General(a)
rracking(b)
A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A(d) A A A A A A(d) A(d) A(d) A(d) A(d) A A A A A A(d) A(d) A(d) A A A A A A A A A A B A A B B B A A A A A C
C C B B A A
Weldabillty(l) Resislance spoland
C
C
C
B C C B
Braze-
Solderabillly(g)
Some lyplcalappUralions oralloys Unfired,weldedpressurevessels, marine,auto aircraftcryogenics,TV towers,drillingrigs, transportation equipment,missilecomponents
Weldedstructures, storagetanks, pressurevessels,salt-waterservice
Automobilebodysheet,canends Automotiveandappliancetrim
Hydrogenperoxideandchemical storagevessels
Welding electrode Weldedstructures, pressurevessels, marineservice
NA
NA B D D D D D
High-strength weldedstructures, storagetanks,pressurevessels, marineapplications Hydrogenperoxideandchemical storagevessels
Anodizedautoandappliance trim NA
NA
NA NA NA
Heavy-dutystructuresrequiringgoodcorrosionresistanceapplications, truckandmarine,railroad cars,furniture, pipelines Automobilebodysheet Automobilebodysheet Heavy-dutystructuresrequiringgood corrosionresistance,truckand marine,railroadcars,furniture,pipelines Piperailing,furniture, architectural extrusions
Forgingsandextrusionsfor welded structures Heavy-dutyweldedstructures, pipelines High-strength busconductors
(a) Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittentspraying or immersion. Alloys with A and B ratings can he used in industrialand seacoast atmosphereswithout protection.Alloys with C, D, and E ratings generallyshould be protectedat least on faying surfaces. (b) Stress-corrosioncracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test. A =No known instance of failure in service or in laboratory tests. B =No known instance of failure in service; limited failures in laboratory tests of short transversespecimens. C =Service failures with sustained tension stress acting in short transverse direction relative to grain structure; limited failures in laboratory tests of long transverse specimens.D =Limited service failures with sustained longitudinal or long transverse stress. (c) In relatively thick sections the rating would he E. (d) This rating may he different for material held at elevated temperaturefor long periods. (e) Ratings A through D for workability (cold), and A through E for machinabilityare relative ratings in decreasing order of merit. (f) Ratings A through D for weldabilityand brazeabilityare relative ratings defined as follows:A =Generally weldableby all commercialprocedures and methods.B =Weldablewith special techniquesor for specific applications;requirespreliminarytrials or testing to develop welding procedureand weld performance.C =Limited weldabllitybecause of crack sensitivity or loss in resistance to corrosion and mechanicalproperties. D =No commonlyused welding methodshave been developed. (g) Ratings A through D and NA for solderabilityare relative ratings defined as follows: A =Excellent. B =Good. C =Fair. D =Poor. NA =Not applicable (continued)
Wrought Aluminum and Aluminum Alloys /149 Comparative characteristics and applications (continued) Weldability(f)
Resista_to corrosion Stress-
corrosion
Alloy temper
Generalla)
cracking(b)
Workabilily (cold)(e)
Machin-
ability(e)
Gas
Resistance spotand
Braze-
seam
ability(!)
Arc
Solde" ability(g)
6151T6.T652
B
6201T81 6262T6,T651,T6510.T6511 1'9 6351.T5.T6
A B B B
A A A A
6463T1 T5 T6 7005T53
A A A
A A A
B
B
7049T73.T7351. T7352 T76.T7651 7050T74.T7451.T7452 T76.T761 7072 70750 T6,T651.T652.T651O, T6511 T73.T7351 7175.T74.T7452 71780 T6,T651.T651O. T6511 7475T6,T651 T73.T7351.T7352 T76,T765l
C C C C A
B B B B
C(c) C C C(c) C C C
A C B B
C C B B
C C D C
B B
B B
D C C A
C C D D D D A
C
B B B B
D D
D D D
B B B
D D D D
B B B B
NA NA
A A A A
A A A A
A A A A
A A A A
A A A
A A A
A A A
A A A
NA
B
B
B
B
B
D D D D A D D D D D D D D D
C C C C A C C C C C C C C C
B B B B
D D D D A D D D D D D D D D
D D D D A D D D D D D D D D
A B B B B B B B B B
B
Some typical appticatlons oralloys Moderate-strength, intricate forgings formachineand autoparts High-strength electric conductor wire Screw-machineproducts Heavy-duty structures requiring goodcorrosion resistance. truckandtractorextrusions Extruded architectural and trim sections Heavy-duty structures requiring goodcorrosion resistance. trucks.trailers, dumpbodies Aircraft andolherstructures Aircraftandolherstructures Finstock,cladding alloy Aircraftandotherstructures Aircraft andolherstructures. forgings Aircraftandolherstructures Aircraftandotherstructures
(a)RatingsAIhrough E arerelativeratingsindecreasing orderof merit.basedon exposures to sodiumchloridesolutionby intermittent spraying or immersion. AlloyswithA and B ratingscan be usedin industrial andseacoastatmospheres withoutprotection. AlloyswilhC. D. and E ratingsgenerally shouldbeprotectedat least on fayingsurfaces. (b) Stress-corrosion crackingratingsarebasedon service experience andon laboratory testsof specimens exposedto the3.5%sodiumchloridealternate inunersion test.A = No knowninstanceof failurein serviceor in laboratory tests.B = No knowninstance of failureinservice; limitedfailures inlaboratory testsof shorttransverse specimens. C=Servicefailures wilhsustained tensionstressactinginshorttransverse directionrelativetograinstructure; lintitedfailures in laboratory testsof longtransverse specimens. D = Limitedservicefailures withsustainedlongitudinal or longtransverse stress.(c)In relatively thicksectionstheratingwould be E. (d)Thisratingmay be different forrnaterial heldatelevatedtemperature forlongperiods.(e)RatingsAIhrough Dforworkability (cold),andAIhrough Eformachinability arerelativeratingsindecreasing orderofrnerit.(f) Ratings A IhroughD for weldability andbrazeability arerelativeratingsdefmedas follows: A= Generally weldableby allcommercial procedures andmelhods. B= Weldable wilhspeclaltechniques or forspecific applications; requires preliminary trialsor testingto developweldingprocedure andweldperformance. C = Limitedweldability becauseofcracksensitivity orlossin resistance tocorrosion andmechanical properties. D = No commonly usedweldingmethodshavebeendeveloped. (g) RatingsA Ihrough D andNAforsolderability arerelativeratingsdefinedas follows: A= Excellent. B = Good.C = Fair.D = Poor. NA= Notapplicable
1050 Chemical Composition. Composition Limits. 99.50 Al min, 0.25 Si max, 0.05 Cu max, 0.05 Mn max, 0.05 Mg max, 0.05 V max, 0.03 others max (each)
Aluminum content: 99.5 Al min
Specifications (U.S. and/or Foreign). ASTM. B491; UNS. A91050;
Typical Uses. Extruded coiled tubing for equipment and containers for food, chemical, and brewing industries; collapsible tubing
(Canada) CSA 9950; (France) NF A5; (United Kingdom) B5 IB; (Germany) DIN A199.5
Available Product Forms. Extruded pyrotechnic powder
Characteristics
Recommended Heat Treating Practice Annealing. Temperature 345°C (650 oF)
1050 Aluminum: Typical mechanical properties 'Iemper
0 H14 H16 HI8
1enslJe strength MPa ksl 76 110 131 159
11 16 19 23
Yield strength MPa ksl 28
103 124 145
4 15 18 21
Elongation,
....
39 10 8 7
Shearstrength MPa ksl 62 69 76 83
9 10 11 12
150 I Heat Treater's Guide: Nonferrous Alloys
1060 Chemical Composition. Composition Limits. 99.60 AI min, 0.25 Si max, 0.35 Fe max, 0.05 Cu max, 0.03 Mn max, 0.03 Mg max, 0.05 Zn max, 0.05 V max, 0.03 Ti max, 0.03 others max (each) Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4000; ASME. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A91060
ASME and ASTMspecifications Specification number
Mill fonn and condition
ASME
AS1M
Sheetand plate Wire, rod, and bar (rolledor coldfinished) Wire, rod. bar.shapes.and tube (extruded) Pipe (gas and oil transmission) Tube (condenser) Tube (condenserwithintegralfins) Tube (drawn) Tube (drawn.seamless) Tube (extruded, seamless)
SB209
B209 B211 B221 B345 B234 B404 B483 B210 B241
SB221 SB234
SB210 SB241
Available Product Forms. Sheet, plate, drawn tubing, extruded tubing, heat exchanger tubing. Available tempers: H12, H14, HI6, HI8
Characteristics Aluminum content: 99.60 Al min
Typical Uses. Chemical equipment and railroad tank cars. Has very good resistance to corrosion and good formability. For more information on resistance to corrosion, cold formability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Application" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Temperature is 345 °C (650 OF). Time in furnace need not be longer than necessary to bring all parts of load to annealing temperature. Rate of cooling is not important .
1060 Aluminum: Typical mechanical properties Thnsilestrength MPa ksi
Elongatlon(a),
Hardness,
Thmper
MPa
ksi
%
HB(b)
0 H12 HI4 H16 H18
69 83 97 110 131
28 76 90 103 124
4 11 13 15 18
43 16 12 8 6
19 23 26 30 35
10 12 14 16 19
Yieldstrength
Shear strength MPa ksi
48 55 62 69 76
7 8 9 10 11
Fatigue Iimll(c) MPa ksi
21 28 34 45 45
3 4 5 6.5 6.5
(a) 1.6 rom (0.0625 in.) thick specimens.(b)500 kg load: 10 romdiam ball. (c)AI5 x 108 cycles; RR Moore type test
1060 Aluminum: Tensile-property limits Thnsileslrength Minimum Thmper
Maximum
MPa
ksi
MPa
ksi
55 75 83 110
8.0 11.0 12.0 16.0
95 110
115
14.0 16.0 17.0
75 70 62
11.0 10.0 9.0
58 70 83 110 58
8.5 10.0 12.0 16.0 8.5
58 58
8.5 8.5
95 95(b)
14.0 14.O(b)
83
12.0
Sheet and plate
o HI2 H14
HI8 H112 0.250-0.499 in. thick 0.500-1.000 in. thick 1.001-3.000in. thick Drawn lube (0.010-0.500 in. wall thickness)
o HI2 H14
HI8 H112 Extruded tube
o H112 Beat-exchanger tube (0.010-0.200 in. wall thickness) H14
(a) In 50 rom (2 in.) or 4d, where d is diameter of reduced section of tensile test specimen.Where a range of values appears in this column, specified minimum elongation varies with thickness of the mill product. (b) Applicableonly 10tube25.410 114.3 rom (1.000104.500 in.) diam by 1.27104.29 rom(0.050 100.169 in.) wall thickness
Wrought Aluminum and Aluminum Alloys /151
1100 Chemical Composition. Composition Limits. 99.00 Al min, 1.00 Si max + Fe, 0.05 to 0.20 Cu, 0.05 Mn max, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total). 0.0008 Be max (for welding electrode and filler rod only)
Characteristics A 99.00 Al (min)-0.12 Cu grade. Typically used where requirements call for combination of good formability and high resistance to corrosion, but where high strength is not necessary. For example: Food and chemical handling and storage equipment, sheet metal work, drawn or spun hollowware, welded assemblies, heat exchangers, lithoplate, nameplates, and light reflectors.
Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASME. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A9l100; Government. (See adjoining Table); (Canada) CSA 990C; (France) N A45; ISO. A199.0 Cu
For additional information on resistance to corrosion, cold formability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Available Product Forms. Sheet; plate; wire, rod, and bar (rolled or cold finished); wire. rod, bar, shapes and tubing (extruded); tubing (extruded, seamless; extruded coiled; drawn; seamless; and welded); rivet wire and rod; spray gun wire; forgings and forging stock; impacts; and foil
Recommended Heat Treating Practice Annealing. Temperature is 345°C (650 OF). Time in furnace need not be any longer than necessary to bring all parts of load to annealing temperature. Rate of cooling is not important
1100-0 sheet, cold rolled and annealed. Recrystallized, equiaxed grains and insoluble particles of FeAla (black). Size and distribution of Fe-Al, in the worked structure were unaffected by annealing. 0.5% HF. 500x
1100 Aluminum: Microstructures. 1100-H18 sheet, cold rolled. Note metal flow around insoluble particles of FeAla (black). Particles are remnants of scriptlike constituents in the ingot that have been fragmented by working. 0.5% HF. 500x
..--. .- .
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". • '-
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._---_._-------------------'
1100 Aluminum. Representative isothermal annealing curves for 1100-H18 200
LIVE GRAPH Click here to view
1100'.H18
150
~ ~
100
I °
~r-,
'0
~
>-
50
o o
\\ <, """"'-
/
1o
1~5 C (35~ F)
-
"-....2r °c (45
'"'-
/260 °c (500 OF)
20 ]
"205°C (400 of)
I
I oF)
1
1
"288 ° and 316°C (550 and 600 OF)
0.5
1.5
2.5 Time. h
3.5
o 4.5
5
152 I Heat Treater's Guide: Nonferrous Alloys 1100 Aluminum: Tensile-property limits EllDgation
'IlmsiJe strength
Minimum ksi
'Thmper
Sheet and plate 0 H12 H14 H16 HIB H112 0.25()"().499 in. thick 0.500-2.000in. thick 2.001-3.000in. thick Wire, rod, and bar (rolled or cold finished) 0 H112 H12(b) Hl4(b) H16(b) H18(b) Wire, rod, bar, and shapes (extruded) 0 H112 Wire and rod (rivet and cold heading gmde) O(c) HI4(c) Dmwn tube (0.014to 0.500 in. wall thickness) 0 H12 H14 H16 H18 Extruded tube 0 H112
YIeldotrength (min) MPa ksi
Maximum lui
MPa
MPa
(min),
-"(a)
25 75 95 115
3.5 11.0 14.0 17.0
15-28 3-12 1-10 1-4 1-4
50 35 30
7.0 5.0 4.0
9 14 20
15.5
20 20
3.0 3.0
25
105
15.5
20 20
3.0 3.0
25
105 145
15.5 21.0
105
15.5
105
15.5
20 20
3.0 3.0
25 25
75 95 110 130 150
11.0 14.0 16.0 19.0 22.0
105 130 145 165
90 83 80
13.0 12.0 11.5
75 75 95 110 130 150
11.0 11.0 14.0 16.0 19.0 22.0
105
75 75
11.0 11.0
110
16.0
95 110 130 150
14.0 16.0 19.0 22.0
75 75
11.0 11.0
15.5 19.0 21.0 24.0
(a)In 50 rom(2 in.)or 4d, whereiis diameterof reducedsectionof tensiletestspecimen.Wherea rangeof valuesappearsin this column.thespecifiedminimumelongationvaries with thicknessof the mil product.(b)Nominalthicknessup througl19.5 rom(0.374 in.), (c)Nominaldiameterup through25.4rom(1.000in.)
1100 Aluminum: Standard specifications
1100 Aluminum: Typical room-temperature mechanical properties Elongation, -..
Spedllcatlon number Mill form and condltlon
AMS
Sheetand plate 4001,4003 Wrre, rod, andbar(rolledorcoldfinished) 4102 Wrre, rod,bar,shapes,and tube(extruded) ThOO (extruded, seamless) ThOO (extruded, coiled) ThOO (drawn) ThOO (drawn,seamless) 4062 ThOO (welded) Rivet wireandrod Spraygun wire 4180 Forgingsandforgingstock Welding rodandelectrodes(bare) Impacts Foil
ASME
SB209
ASTM
'Thmper
MPa
lui
YIeld s1Nngth MPa lui
0 H12 H14 H16 H18
90 110 124 145 165
13 16 18 21 24
34 103 117 138 152
'Th1lS1Ie strength
Government
B209 QQ-A-250/1 B211 QQ-A-22S/l SB221 B221 SB241 B241 B491 B483 B210 WW-T-7ooll B313,B547 QQ-A-430 B316 MIL-W-6712 B247 QQ-R-566, MIL-E-16053 MIL-A-12545 QQ-A-1876.
5 15 17 20 22
\16 In.
Shear ~In. otrength thick thick Hardness, specimens specimens HB(a) MPa lui
35 12 9 6 5
45 25 20 17 15
23 28 32 38 44
(a)500 kg load; 10romball.(b) At5 x 108 cycles;R.R.Mooretype test
62 69 76 83 90
9 10 11 12 13
FalIgue 1imII{h)
MPa
lui
34 41 48 62 62
5 6 7 9 9
Wrought Aluminum and Aluminum Alloys J 153
1145 Chemical Composition. Composition Limits. 99.45 AI min, 0.55 Si max + Fe, 0.05 Cu max, 0.05 Mn max, 0.05 Mg max, 0.05 Zn max, 0.05 V max, 0.03 'n max, 0.03 others max (each)
1145 Aluminum: Tensile properties of 1145 aluminumfoil
Specifications (U.S. and/or Foreign). AMS. 4011; ASTM. B 373; Government. QQ-A-1876
Ylekhtrength MPa koI
'ThDJile strength ksl
MPa
'Thmper
EloogalioD,
""
Typical properties
o
Available Product Form. Foil
75 145
11 21
95max 140 min
14max 20 min
HI8 Tensilestrength Iimits(B)
Characteristics
o
34 117
Aluminum content: 99.45 AI min
HI9
Typical Uses. Foil for packaging, insulating, and heat exchangers
(a) Unmounted foil 0.02 to 0.15 mm (0.0007 100.0059 in.) thick
5 17
40
5
Recommended Heat Treating Practice Annealing. Temperature: 345°C (650 OF)
1199 Chemical Composition. Composition Limits. 99.9 AI min, 0.006 Si max, 0.006 Fe max, 0.006 Cu max, 0.002 Mn max, 0.006 Mg max, 0.006 Zn max, 0.002 Ti max, 0.005 V max, 0.005 Ga max, 0.002 other max. See adjoining Figure for effect of purity on strength of unalloyed aluminum
Typical Uses. Electrolytic capacitor. Foil, vapor deposited coatings for optically reflective surfaces
Tradenames. Super-purity aluminum, Raffinal
1199 Aluminum: Typical tensile properties
Common Name. Super-purity aluminum, refined aluminum Available Product Form. Foil
Aluminum content: 99.9 AI min
MPa
6.5 8.6 11.1 13.9 15.9 17.5
10 57 75 91 105 113
MPa
o(annealed)
45 59 77 96 110 120
10 20 40 60 75
Characteristics
V..ldst.rength ksi
'ThoslJe strength ksI
Reduction by
1199 Aluminum. Effectof purity on strength and hardnessof unalloyedaluminum 150
~
100
ic:
TenSileSI~
~
50
~
v ./
Yleldslreng~~
99.999
99.99
99.9
o
99.0
Purity, %
250
5:
200
~
c:
"E
~
- 20
-----
150
/
/
/
100 99.999
99.99
99.9 Purity, %
99.0
1.5 8.2 10.8 13.2 15.1 16.4
EIoogalioD,
"" 50 40 15 11 6 5
154 I Heat Treater's Guide: Nonferrous Alloys
1350 Chemical Composition. Composition Limits. 99.50 AI, 0.10 Si max, 0.40 Fe max, 0.05 Cu max, 0.01 Mn max, 0.01 Cr max, 0.05 Zn max, 0.03 Ga max, 0.02 V max + Ti, 0.05 B max, 0.03 others max (each), 0.10 others max (total). See Figure below for effect of purity on strength and hardness of unalloyed aluminum 150
i
100
1 ~
Temileltr~
50
.>
2
V
1
~
Yi.ldSl,ength~ .",. 9U9S
9U9
0
99.0
9U
Specifications (U.S. and/or Foreign). ASTM. Aluminum conductor, steel reinforced: B 232, B 401. Bus conductors: B 236. Communication wire: B 230, B 609. Wire, rectangular and square: B 324. Round, solid conductors: B 544. Stranded conductors: B 231, B 400. (France) NF A51L; (Spain) UNE Al 99.5E; (United Kingdom) BSIE; (Germany) DIN EA199.5 Available Product Forms. Sheet, plate, extruded tubing, pipe, structural shapes; extruded wire, rod, bar and shapes; rolled or cold-finished rod, bar, and wire. Available tempers include H12, H14, H16, and H18, H19, HI 12, HIll, H2, H24, and H26
Common Name. Electrical conductor grade (BC)
Characteristics Aluminum content: 99.50 Al min.
Purity, "
Typical uses. Wire, stranded conductors, bus conductors, and trans260
~
I ~
200
---
150
/
former strip.
V
/
For information on resistance to corrosion, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Application" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Temperature is 345°C (650 OF). Time in furnace need be no longer than necessary to bring all parts of load up to annealing temperature. Rate of cooling is not important
100 99.99S
98.99
98.9
99.0
Purity, "
1350 Aluminum: Tensile-property limits Thnsilestrength Maximum Minlmum Thmper
MPa
ksi
MPa
ksi
Yield
Elongation
strength (min)
(min),
MPa
% (a)
ksl
1350 Aluminum: Tensile-property limits for 1350 aluminum wire, H19temper Minbnum tensile strength Wire dlameter.In,
Individual(a) MPa ksi
Average(b) MPa ksl
0.0105-0.0500 0.0501-0.0600 0.0601-0.0700 0.0701-0.0800 0.0801-0.0900 0.0901-0.1000 0.1001-0.1100 0.1101-0.1200 0.1201-0.1400 0.1401-0.1500 0.1501-0.1800 0.1801-0.2100 0.2101-0.2600
160 185 185 183 180 175 170 165 162 162 160 160 155
172 200 195 193 190 185 180 175 172 170 165 165 162
Minbnum etongation!.), % Individual!a) Avemge(h)
Sheet and plate
o H12 H14 H16 H18
55 83 9.5 110 125
8.0 12.0 14.0 16.0 18.0
75 70 62
11.0 10.0 9.0
58 83 105 115
8.5 12.0 15.0 17.0
58
8.5
83
12.0
95 115 130 145
14.0 17.0 19.0 21.0
15-28 3-12 1-10 1-4 1-4
HlI2
0.250-0.499in. thick 0.500-1.000in. thick l.oo1-1.500in.lbick Wire(b) and redraw rod(c)
o H12andH22 H14andH24 H16andH26 Extrusions(d) Hlll Rolled bar(e) H12 Sawed-plate bar
10 16 22
0.125-0.499in. thick 0.500-1.000in. thick 1.001-1.500in. thick
75 70 62
11.0 10.0 9.0
(0) In 50 nun (2 in.) or 4d, where d is diameterof reduced sectionof tensiletestspecimen.Where 0 range of values appears in Ibiscolumn,specifiedminimumelongationvarieswith thicknessof the mill product. (b) Up Ihrough9.50 nun (0.374 in.) diam. (c)9.52 nun (0.375in.) diam.(d) Bar, rod, tubularproducts,and structuralshapes.(e)3to 25 nun (0.125to 1.0in.) thick
25.0 29.0 28.5 28.0 27.5 27.0 26.0 25.5 25.0 24.5 24.0 24.0 23.5
1.2
1.4 1.5 1.6 1.6 1.6 1.6 1.7 1.8 1.9 2.0 2.1 2.3
1.3
1.4 1.5 1.5 1.5 1.6 1.7 1.8 1.9 2.0 2.2
(a)Minimumvaluefor anytest in 0 givenlot. (b) Minimumvaluefor averageof all testsfor a given lot. (c) In 250nun (10 in.)
1350 Aluminum: Typical mechanical properties Thmper
MPa
ksi
Yield strength ksi MPa
0 HI2 H14 H16 H19
83 97 110 124 186
12 14 16 18 27
28 83 97 110 165
ThIlSUestrength
HlI2
23.0 27.0 27.0 26.5 26.0 25.5 24.5 24.0 23.5 23.5 23.0 23.0 22.5
(0) In 250 nun (10in.),valueapplicableto wire only
4 12 14 16 24
Elongation(a),
Shearstrength
%
MPa
ksi
23
55 62 69 76 103
8 9 10 11 15
1.5
Wrought Aluminum and Aluminum Alloys /155
2011 Chemical Composition. Composition Limits. 0.40 Si max, 0.7 Fe max, 5.0 to 6.0 Cu, 0.30 Zn max, 0.20 to 0.60 Pb, 0.05 others (each), 0.15 total, bal Al Specifications (U.S. and/or Foreign). ASTM. Drawn seamless tubing: B21O. Rolled or cold finished wire, rod, and bar: B 211; SAE. J454; UNS. A92011; Government. Rolled or cold finished wire, rod, and bar: QQ-A-22513; (Canada) CSNCB60; (France) NFA-U4Pb; (United Kingdom) BSFCI; (Germany) DIN AICuBiPb Available Product Forms. Rod, bar (rolled or cold finished), and wire
Characteristics An Al-Cu alloy without Mg alloying Typical Uses. Screw machine products are typical applications-where good machinability and good strength are required. For information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
sequent to solution heat treatment and prior to precipitation heat treatment is necessary to obtain desired properties of T3 temper. To obtain desired properties for the T451 temper it is necessary to stress relieve parts by stretching to produce permanent set subsequent to solution treatment and prior to precipitation treatment Precipitation Heat Treating (Artificial Aging). Treatment temperature for the T8 temper, 160°C (320 OF), is held for approximately 14 h. The nominal treatment temperature should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) during time at temperature. Specific time depends on time needed for load to reach temperature. Time given in this instance is based on rapid heating, with soak time measured from time load reaches a temperature within 6 °C (10°F) of the applicable temperature. To obtain properties ofT8 temper, parts are cold worked subsequent to solution treatment and prior to precipitation heat treatment Annealing. This alloy is annealed at 415°C (775 oF) 2011-T3 Aluminum: Typical tensile properties
Recommended Heat Treating Practice
'Iemperature
°C
Solution Heat Treating. Treatment temperatures for T3, T4, and T451 tempers are 525°C (975 OF). Material should be quenched as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature, and cooled so that it remains below 38°C (100 OF) during the quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Nominal treatment temperatures should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) during time at temperature. Cold working sub-
24 100 150 205 260 315 370
OF 75 212 300 400 500 600 700
Yieldstrength (0.2% offset) MPa ks1
Thnsilestrength MPa ksi
379 324 193
llO 45 21 16
55 47 28 16 6.5 3.1 2.3
296 234 131 76 26 12
10
E1ongalion, %
43 34 19 11 3.8 1.8 1.4
15 16 25 35 45 90 125
Note: Lowest strength for exposures up to 10000 h at temperature. no load; test loading applied at 35 MPaimin (6 ksilmin) to yield strength and then at strain rate of5%/min to fracture
2014, Alclad 2014 Chemical Composition. Composition Limits (2014). 3.9 to 5.0 Cu, 0.50 to 1.2 Si, 0.7 Fe max, 0.40 to 1.2 Mn, 0.20 to 0.8 Mg, 0.25 Zn max, 0.10 Cr max, 0.15 Ti max, 0.05 other max (each), 0.15 max other (total), bal Al Composition Limits (AIclad 2014). 6006 cladding-Q.20 to 0.6 Si, 0.35 Fe max, 0.15 to 0.30 Cu, 0.05 to 0.20 Mn, 0.45 to 0.9 Mg, 0.10 Cr max, 0.10 Zr max, 0.10 Ti max, 0.05 other max (each), 0.15 other max (total), bal Al Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASME. Rolled or cold fmished wire, rod, and bar: SB 211. Forgings; SB 247; ASTM. (See adjoining Table); UNS. A92014; Government. (See adjoining T~ble); (Canada) CSA C541N; (France) NF A-U4SG; (Germany) DIN AICuSiMn; ISO. AICu4SiMg; (United Kingdom) BS HI5 Available Product Forms. (See adjoining Table)
Alloy 2014: Standard specifications Specificationnumber Miueorm
AMS
AS1M
Sheet and plate
40 14
B209
Rolled or cold fmished wire, rod, and bar Extruded wire, rod, bar, shapes, and tube Extruded seamless tube Drawn, seamless tube Forgings
Forging stock
4028 4029 4121 4153
4133 4134 4135 4134 4133 4135
B 211 B 221 B241 B210 B 247
QQ-A-225/4 QQ-A-20012
QQ-A-365 MlL-A-2277I QQ-A-367
Impacts Sheet and plate (Alclad)
Government
B 209
MlL-A-12545 QQ-A-25013
156 I Heat Treater's Guide: Nonferrous Alloys some materials. Nominal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature
Characteristics An AI-Cu-Mg-Si alloy
Typical Uses. For parts that require high strength and hardness, including service at high temperatures, i.e., heavy duty forgings, plate, and extrusions for aircraft wheels, wheels, and major structural components, space booster tankage and structures, frame, and suspension parts for trucks. For information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Precipitation Heat Treating (Artificial Aging). With one exception, all mill products named in section on solution treating have a treatment temperature of 160°C (320 "F), Exception: temperature for die forgings is 170 °C (340 oF). Tempers involved are T6, T62, T651, T651O. An alternative treatment, 8 h at 177 °C (350 "F), is available in processing rolled or cold finished wire, rod, and bar (to T6, T62, or T651 tempers); extruded rod, bar, shapes, tubing (to T6, T62, or T6510 tempers); and drawn tubing (to T6 and T62 tempers).
Recommended Heat Treating Practice Treatments discussed here also apply to Alclad sheet and plate
Plate, rolled or cold finished wire, rod, and bar in the 651 temper, and extruded rod, bar, shapes, and tubing in the 6510 temper are stressed relieved by stretching to produce a specified amount of permanent set subsequent to solution treatment and prior to precipitation treatment
Solution Heat Treating. Treatment temperatures (500°C, or 930 oF) apply to all of the following mill products and tempers: flat sheet; coiled sheet; plate; rolled or cold finished wire, rod, and bar; extruded rod, bar, shapes, and tubing; drawn tubing; and die forgings in these tempers: TI, T4, T42, T451, and T4510
Annealing. Treatment temperature is 415°C (775 OF)
2014 Alloy: Typical tensile properties of 2014-T6 or 2014-T651 at various temperatures
Special considerations include: • In treating flat sheet to the TI temper, cold working subsequent to solution treatment and prior to precipitation treatment is necessary to obtain properties provided by this temper • In treating plate to T42 and T451 tempers; rolled or cold finished wire, rod, and bar to T451 temper; and extruded rod, bar, shapes, and tubing to T4510 temper, parts are stress relieved by stretching to produce a specified amount of set subsequent to solution treatment and prior to precipitation treatment
Lowest strengthfor exposuresup to 10000 h at temperature under no load; test loading applied at 35 MPa/min (5 ksVmin) to yield strength and then at strain rate of 5%/min to fracture Thmpemture ThmUe strengtb Yieldstrengtb(.) Elongation, °C OF MP. ksi MP. IIsI If, -196 -ll0 -28 24 100 150 205 260 315 370
In all instances, material should be quenched from the solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled in some manner so that it remains below 38°C (l 00 "F) during the quenching cycle. Use of high-velocity, high-volume jets of water also is effective for 400
-320 -112 -18 75 212 300 400 500 600 700
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--a: tal
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496 448 427 414 393 241 90 52 34 24
72 65 62 60 57 35 13 7.5 5 3.5
14 13 13 13 15 20 38 52 65 72
2014 Aluminum. Rotating beam fatigue data of 7039 plate compared with fatigue characteristics of 2014 and 2219. Data for 7039 are based on least-of-four results in the longitudinal direction with a 7.5 mm (0.3 in.) diam smooth specimen. Curves for 2014 and 2219 are mean values from published literature
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Wrought Aluminum and Aluminum Alloys /157
2014 Aluminum: Microstructures. (a) 2014-T4 closed die forging, solution heat treated at 500°C (930 OF) for 2 h and quenchedin water at 60 to 70°C (140 to 160 OF). Longitudinal section. Structure contains particles of CuAI2 (white, outlined) and insoluble (Fe,Mn)3SiAI12 (dark). Keller's reagent. 1OOx (b) 2014-T6closed-dieforging, solution heat treated,then aged at 170°C (340 OF) for 10 h. Longitudinal section. Fragmented grain structure. Veryfine particlesof CuAI2have precipitatedin the matrix.Keller's reagent. 100x (c) 2014-T6closed-die forging, overaged. Solution heat treatment was sufficient, but specimen was overaged. Fragmented grain structure. More CuAI2has precipitated. Note lackof graincontrast.Keller's reagent. 1OOx (d) 2014-T4 closed-dieforgingthat receivedinsufficientsolutionheattreatment. Longitudinalsection. More CuAI2is visible, because less is in solution. Keller's reagent. 250x (e) 2014-T6 closed-dieforging, showing rosettes formed by eutectic melting. Solidus temperature (510°C, or 950 OF) was exceeded during solution heat treating. Keller's reagent. 500x (f) 2014-T6 closed-dieforging. Hydrogenporosity(black),and particlesof (Fe,Mn)3SiAI12 (gray)and CuAI2(gray, speckled)are visible. As-polished.250x
(d)
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~
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Next Page 158 I Heat Treater's Guide: Nonferrous Alloys
2014 Aluminum. Aging characteristics of aluminum sheet 2014 at room temperature, at 0 °C (32 OF), and at -18°C (0 OF) 2014
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2014 Aluminum: Microstructure. 2014-T61 closed-die forging. Blister on surface is associated with hydrogen porosity.As-polished. 50x
Previous Page
Wrought Aluminum and Aluminum Alloys /159
2017 Chemical Composition. Composition Limits. 0.20 to 0.80 st, 0.70 Fe max, 3.50 to 4.5 Cu, 0.40 to 0.80 Mg, 0.40 to 1.00 Mn, 0.10 Cr max, 0.15 Ti max, 0.25 Zn max, 0.05 other (each), 0.15 others (total), bal Al Specifications (U.S. and/or Foreign). ASTM. B 211 and B 316; SAE. J454; ANSI. H38.4 and H38.12; UNS. A92017; Government. QQ-A222/5, QQ-A-430, MIL-R-430; (France) A-U46; (Germany) AICuMgl and 3.1325; (Great Britain) LI8 and 150A; (Canada) CM41; (Austria) AICuMg1. 150: AICuMgSi Available Product Forms. Forgings, extrusions, bar, rod wire, shapes, rivets
Characteristics First alloy developed in AI-Cu-Mg series is now in limited use
Typical Uses. Chiefly for rivets. Used in components for general engineering purposes, structural applications in construction and transportation, screw machine products, and fittings. Alloy is age hardenable with medium strength and ductility, good machinability, and formability, and fair resistance to atmosphere corrosion. Welding is not recommended unless heat treatment after welding is practical. Service temperature is below 100°C (212 OF). For more information, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Rolled or cold finished wire, rod, and bar are treated to obtain T4 and T42 tempers at 500 to 510 °C (930 to 950 "F),
Material should be quenched as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature, and cooled in some manner so that it remains below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Nominal treatment temperatures should be attained as rapidly as possible and maintained with ±6 °C (±1O "F) during time at temperature
Natural Aging. Occurs at room temperature Annealing. A heat-treated anneal is obtained at 415°C (775 OF); a cold work anneal is obtained at 340 to 350 °C (645 to 660 OF)
2017 Aluminum: Typicaltensile properties of 2017 (T4 and T451 tempers) at various temperatures lOst temperalure(a) OF -c
-196 -80 -28 24 100 150 205 260 315 370
- - -_"':=-
400
550 448 440 427 393 275 110 62 40 30
80 65 64 62 57 40 16 9 6 4.3
Yieldstrength (0.2% oft'se!) MPa ksi
365 290 283 275 270 207 90 52 35 24
53 42 41 40 39 30 13 7.5 5 3.5
Elongationin SOmm (2in.l,%
28 24 23 22 18 15 35 45 65 70
(a)Tested afterholding10000h attemperature
600,....--------------------, 500
-320 -112 -18 75 212 300 400 50 600 700
Thnsile strength MPa ksl
2017 Aluminum: Time temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A =7075. B =2017. C =6061. D =6063
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2024, Alclad 2024 Chemical Composition. Composition Limits (2024). 0.50 Si max, 0.50 Fe max, 3.8 to 4.9 Cu, 0.30 to 0.90 Mn, 1.2 to 6.8 Mg, 0.10 Cr max, 0.25 Zn max, 0.15 Ti max, 0.05 other max (each), 0.15 other max (total), bal AI Composition Limits (Alclad 2024). 1230 c1adding-99.30 Al min, 0.70 Si max + Fe, 0.10 Cu max, 0.05 Mn max, 0.05 Mg max, 0.10 Zn max, 0.05 V max, 0.03 Ti max, 0.03 other max (each)
Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASME. Rolled or drawn coil, rod, and bar: SB 211. Extrusions: SB 221; ASTM. (See adjoining Table); SAE. J 454; UNS. A92024; Government. (See adjoining Table); (Austria) Onom AICuMg2; (Canada) CSA CE42; (France) NFA-U4G1; (Italy) UNI P-AICu4.5MgMn, Alclad 2024, P-AICu4.5MgMn place; (Spain) UNE L-314; (Germany) DIN AICuMg2 Available Product Forms. (See adjoining Table)
160 I Heat Treater's Guide: Nonferrous Alloys Precipitation Heat Treating (Artificial Aging). Approximate metal temperatureof 190°C (375°F) is maintained in treating flat sheet; coiled sheet; plate; rolled or cold finished wire, rod, and bar; extruded rod, bar, shapes, and tubing to the T6, T62, T81, T86, T851, T861, T851O, and T8511 tempers. Nominal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature. Times at temperature listed are approximate. Specific times are based on time required for load to reach temperature. Times given here are based on rapid heating, with soak time measured from time load reaches a temperature within 6 °C (10 OF) of applicable temperature.
Characteristics An AI-Cu-Mg alloy Typical Uses. Applications include aircraft structures, rivets, hardware, truck wheels, screw machine products, and other structural applications. For information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Treatments also apply to Alclad flat sheet and coiled sheet in T3, T4, T42, and TI61 tempers
Times at temperature can vary with product:
Treatment temperatures are 495°C (920 OF) for flat sheet to obtain TI, T4, T42, and T461 tempers; for coiled sheet to obtain T4 and T42 tempers; for plate to obtain T42, T351, and TI61 tempers; for cold or cold finished coil, rod, and bar to obtain T4, T42, TI51, and TI61 tempers; for extruded rod, bar, shapes, and tubing to obtain TI, T42, TI51O, and TI51 tempers; for drawn tubing to obtain TI and T42 tempers.
Temper
Product
1'861 T62 1'81 172 T62 T62 T6and1'851 1'861 1'851 1'86 T81. T8510, 1'8511
Aatsheet
Coiledsheet Plate
Material should be quenched as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled in some manner so that it remains below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume.jets of cold water is effective for some materials. Nominal treatment temperature should be attained as rapidly as possible and maintained at ±6 °C (±10°F) during time at temperature.
Rolledor coldfinishedwJre, rod,andbar Extrudedrod,wire,shapes,andtubes
nmesat Temperature (hl
8 9 12 16 9 9 12 8 12 8 12
Special considerations include: • In treating flat sheet and plate, to the T81, T86 and T861 tempers, cold working is necessary and subsequent to solution treatment, and prior to any precipitation treatment.to obtain desired properties. • In treating plate, rolled, or cold finished wire, rod, and bar to T851; and extruded rod, wire, shapes or tubing to T8l, T8510, and T8511, the parts are stress relieved by stretching to produce a specified amount of permanent set, subsequent to solution treatment and prior to any precipitation treatment.
Special considerations include: • In treating flat sheet to TI and TI61 tempers and treating rolled or cold finished wire, rod, and bar to TI6 temper, and treating plate to TI61 temper ... cold working subsequent to solution-treatment and prior to precipitation treatment is necessary to obtain properties provided by these tempers • In treating plate and rolled or cold finished wire rod and bar to TI51 temper, parts are stress relieved by stretching to produce a specified amount of set subsequent to solution treatment and prior to precipitation treatment
Annealing. This alloy is annealed at 415°C (775 OF)
2024 Aluminum. Type and depth of attack on 2024-T4 sheet versus quench factor 0.20
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Wrought Aluminum and Aluminum Alloys /161
2024 Aluminum. Effect of temperature on tensile properties of Alclad 2024-T3. Sheet was 1.0 mm (0.04 in.) thick
Tasting temperature, OF
Testing temperature, OF
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100
600
200
300
100
600
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200
300
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500
400
--...:
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-
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- 60 - 50
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80
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20
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100
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o
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500
70 34°C (94 OF)
400
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190°C (376 OF) - 20
100 - 1
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10
100
1000
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10000
Ruptura time, h
2024 Aluminum. Fatigue characteristics of 1 mm (0.04 in.) Alclad 2024-T4 sheet after
400 . - - - - - - - - - - - - - , - - - - - - - - - - , - - - - - - - - - - - - , Curve
Bend radius Not bent
3.2mm 3.2mm 3.2mm 1.6mm
300
Condition during flattening Not applicable Annealed As-quenched + 3 days storage As-quenched + 14 days storage As-quenched + 3 days storage
50
a.
:2
90° bending in the annealed condition and subsequent flattening as indicated. Flattening (unbending) was done either in the annealed condition (curve 2), or in the solutiontreated and quenched condition (curves 3, 4, 5) with indicated storage times at -18 to -12 °C (0 to 10 OF)
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Stress ratio. 0.1
20 100'------------'-----------'------------' 10 0.01 0.1 Millions of cycles to failure
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162 I Heat Treater's Guide: Nonferrous Alloys
2024 Aluminum: Microstructures. (a) 2024-T3 sheet, solution heat treated at 495°C (920 OF) and quenched in cold water. Longitudinal section. Dark particles are CuMgAI 2 , Cu 2MnA12o ' and Cu 2FeAI 7 • Keller's reagent. 50Ox (b) 2024-T3 sheet, solution heat treated at 495°C (920 OF) and quenched in boiling water. The lower quenching rate resulted in precipitation of CuMgAI 2 at grain boundaries. Keller's reagent. 500x (c) 2024-T3 sheet, solution treated at 495°C (920 OF), quenched in cold water and cooled in an air blast. The lower cooling rate resulted in increased precipitation of CuMgAI 2 at grain boundaries. Keller's reagent. 50Ox (d) 2024-T3 sheet, solution treated at 495°C (920 OF), quenched in cold water and cooled in still air. The slow cooling resulted in intragranular and grain-boundary precipitation of CuMgAI?. Keller's reagent. 50Ox(e) 2024-T3 sheet clad with alloy 1230 (5% per side), solution heat treated. Normal amount of copper and magnesium diffusion from base metal into cladding (top). Keller's reagent. 1OOx (f) 2024-T6 sheet, 6.4 mm (0.25 in.) thick (reduced from 406-mm, or 16-in. thick ingot), stretched 2%. Longitudinal section. Note absence of strain lines in structure. Keller's reagent. 100x (g) 2024-T6 sheet, 6.4 mm (0.25 in.) thick (reduced from 406 mm, or 16 in. thick ingot) stretched 6%. Longitudinal section. Some faint strain lines have formed. Keller's reagent. 100x (h) 2024- T6 sheet, 6.4 mm (0.25 in.) thick (reduced from 406 mm, or 16 in. thick ingot) stretched 20%. Longitudinal section. Many strain lines have formed. Keller's reagent. 1OOx (a)
(d)
(f)
(g)
(h)
Wrought Aluminum and Aluminum Alloys /163
2024 Aluminum: Microstructures. (a) 2024-T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. Section was taken in the rolling plane (long transverse) from an area near the surface showing elongated grains. Keller's reagent. 200x (b) 2024- T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. Longitudinal section showing the edge view of an area near the surface of the plate. Grains are flattened and elongated in the direction of rolling. Keller's reagent. 200x (c) 2024- T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. A short transverse section showing the end view of an area near the surface of the plate. Grains are flattened. Keller's reagent. 200x (d) 2024-T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. Specimen was from the center of the plate thickness, which received less cold working than the surface. Keller's reagent. 200x (e) 2024- T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. Specimen was from the center of the plate thickness. There is less flattening and elongation of the grains. Keller's reagent. 200x (f) 2024- T851 plate, 150 mm (6 in.) thick, cold rolled, solution heat treated, stretched and artificially aged. Specimen was taken from the center of the plate thickness. Less coldworking resulted in less deformation. Keller's reagent. 200x (g) 2024-T851 plate, 100 mm (4 in.) thick, hot rolled, solution heat treated, stretched, and artificially aged. Fragmented grain structure; one small recrystallized grain. High rolling temperature limited strain and recrystallization. 10% H3P04 • 500x (h) 2024-0 plate, 13 mm (0.5 in.) thick, hot rolled and annealed. Longitudinal section. Elongated recrystallized grains and unrecrystallized stringers resulting from polygonization that occurred during the hot water working. KMn0 4 , Na 2C03 • 100x (i) 2024-0 sheet. Structure consists of light gray particles of insoluble (Cu,Fe,Mn)Al e, large black particles of undissolved CuMgAI 2 , and fine particles of CuMgAI 2 that precipitated during annealing. 25% HNO a• 500x
(b)
(e)
(g)
(h)
(i)
164 I Heat Treater's Guide: Nonferrous Alloys
2024 Aluminum. Effect of stretching and aging on the toughness and yield strength of 2024 sheet
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2024 Aluminum. Quench curves for 2024-T4 sheet, to eliminate susceptibility to intergranular corrosion LIVE GRAPH
Transverse yield strength, ksi
500
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300
350
400
2000 500
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2024 Aluminum. Effects of cold work after quenching and before aging on tensile properties of 2024 sheet
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00 .~ E
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... \ --
00
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220°C (425 OF) 0
0
12 Aging time, h
16
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,
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00
/
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30 16
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Aging time, h
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40 200
12
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-205°C ---'::::-1 (400 OF)
300
o
16
Aging time, h
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00
-"
e,
300 0
w'"
190°C (375 OF) 175°C (350 OF)
" :;;
';;;
c:
300
e:'
600
19~ °c (375 ~F)
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2024,T36 (cold worked 5 to 6%)
2024,T3 (cold worked 1 to 2%)
600
600
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:;:
Wrought Aluminum and Aluminum Alloys /165
2024 Aluminum. c-curve indicating type of corrosion attack on 2024-T4 sheet
LIVE GRAPH
2024 Aluminum. Aging characteristics of 2024 aluminum sheet alloy at room temperature, at 0 °C (32 OF), and at -18 °C (0 OF)
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l;.l 500
~ 400
:::J
~ 300 Q)
g-
200
j! 100 0.1
900 lI~
-= 700
c....
predomi~
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pitting
10 Critical time,
I 100
--
2024
600
:::J
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80
Q.
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-
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300 40
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I-
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2024 Aluminum: Standard specifications
f
1 year
MiUrormand
condition
Bare 2024 Sheetandplate
WIre,rod,andbar (roUed orcoldfinished)
WIre,rod,bar,shapes,andtube(extruded)
Tube (extruded, seamless) Tube(drawn,seamless)
Thbe(hydraulic) Rivet wireandrod Foil Alclad2024 Sheetandplate
AMS
30 ~in
Specification number AS1M Government
\WCek 21~onlhs1 20
1 ~ay
100 0.1
10 Elapsed time after quenching, h
4033 4035 4037 4097 4098 4099 4103 4104 4105 4106 4192 4193 4112 4119 4120 4152 4164 4165 4087 4088 4086
B209
QQ-A-250/4 500
400
~
;,: B211
I
v
QQ-A-22516
B221
QQ-A-20013
I
o B241 B210
B316
0.1
o "c (32 "FI
.1 (Q -FI
,-
-18 'C
QQ-A-250/5
J
20
1 veer'" 10 \ week 2 ~onlhS
I
1
10
40 .~
H
N
1;
3D
E E
B209
60
Elapsed time after quenching, h
WW-T-70013 MIL-T-50777 QQ-A-430 MIL-A-81596
1 ~ay
-
---=
;-
V-
.:
30 min
70
-
100
4007 4034 4040 4041 4042 4060 4061 4072 4073 4074 4075 4194 4195
--
;-
200
-
_18°C (O°F)
'" ~
'°"
o °c (32 OF)
/"
0
AT
20
~.
.~
c 0 iii
10 1 yea I
30 min
1 day
1 week 2 months
o 0.1
I
10 Elapsed time after quenching. h
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166 I Heat Treater's Guide: Nonferrous Alloys
2024 Aluminum. Aging characteristics of 2024 sheet
550
:1..
175 "c
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r
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/~
«
450 <0
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400
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-
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YI
I
II
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~
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50
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.. ~
>-
"
1 day 1 week 2 months I yea, I
60
E:
205 "c, 260 "c 1400 "F) 1500 "F)
250
70
II
-
40
30
Wrought Aluminum and Aluminum Alloys /167
2024 Aluminum. Effect ofuphill quenching ondeflection oftines. Six-tine specimen wasmachined from 50 by50 mm(2 by2 in.)bar. Similarspecimens machined from 25 by25 mm (1 by 1 in.)and75 by75 mm(3 by3 in.)bars hadfour andeight tines, respectively
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2600
+ 100
25-by-25-mm 11-by-l,in.1 bar
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:>.
C
a0
-1300
c'
-g
~
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d c'
I
-100
-2600
0
-3900'P-+--+---+------+-l 7075 o Control specimen
• Quenched from - 75°C (-100 of) \0 steam Quenched from liquid
-200
nitrogen to steam
-6500 L --~--'--~--~ 1 Tine number
+1300,-------,..-----.-----.----=---.., +50
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123 456
E "- -1300
.~
-50
a
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0
d
0
.~
c'
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-100
0
7075 -3900
.s
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a Control specimen
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6
-200 Tine number
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2600
100 75,by,75-mm (3.by,3·in.) bar
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+50 .~
E
"-
a
c'
d
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.~
c'
.s
~
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0
u
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0
7075 o Control specimen
0
-100 0
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10
steam
6 Quenched from liquid nitrogen to steam
Tine number
168 I Heat Treater's Guide: Nonferrous Alloys
500
I..
. .... /' ......•. B -"'A
•••••
2024 Aluminum: Time-temperature-property diagram.
..•.•
=
------ ----
.:
-_..-:------
.....
.... LOO
- - AA202L-T851 - - - AA202L -T351 .......... AA2219 - T87 .
II>
:::>
E II>
Q.
E
II>
.... 300
Treatment: Sequence A Specimens were quenched directly into a salt bath at 250 to 475°C (480 to 890 OF); Sequence B = Specimens were first quenched to room temperature, then heated in the salt bath. All specimens were quenched in cold water to complete the sequences after hold times of 2 s to 1 h. stretched to 5% plastic strain, and then aged for 16 h at 170°C (340 OF) Comparison of yield strength (0.2% offset) C-curves for sequence Aand B treatments of 2024-T851, 2024-T351, and 2219-787. Corresponding yield strengths are 90% of values obtained from direct quench; 415 MN m-2 for 2024-T851 , 345 MN m-2 for 2024-T351, and 345 MN m-2 for 2219-T-87
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10
102
10]
Critical time,s
600,..--.-----r-----.----.----,r--,---,----,---, S at grain boundaries
500 ~
8 at dispersoids
2024 Aluminum: Time-temperature-nucleation curves.
=
Treatment: Sequence A Specimens were quenched directly into a salt bath at 250 to 475°C (480 to 890 OF) Schematic representation of nucleation curves for sequence A
LIVE GRAPH
400
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...'" :::>
~
300
a. '" E
~ 200
100 10 4 10 5 Time,s
600,..--.-----r--.....,....--..,..--,..--.----:-----r--~
2024 Aluminum: Time-temperature-nucleation curves.
=
500 ~
400
...'"
- 300 :::>
~
S at grain boundaries
Treatment: Sequence B Specimens were first quenched to room temperature, then heated in the salt bath. All specimens were quenched in cold water to complete the sequences after hold times of 2 s to 1 h. stretched to 5% plastic strain, and then aged for 16 h at 170°C (340 OF) Schematic representation of nucleation curves for sequence B treatment
a.
E
....'" 200 100
LIVE GRAPH Click here to view
Wrought Aluminum and Aluminum Alloys /169
2024 Aluminum: Time-temperature-corrosion diagram. Effect of temperature and time in interruptedquenching experiments on type of corrosion attack developed in 2024-T4 sheet by an accelerated corrosiontest
900 e
o
800 u,
700
Q)
.... 600 ::J
....
0
Q)
a. E
Type of corrosion attack I - - - f ----iH,... 0 - Pi "ing 0- Pilling plus slighl inlergronulor I - - - - - - " r " " d - - A - Pilling plus inlergranulor • -Inlergranular
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500
~ 400 o
300
o
200 0.1
100
10
1.0
1000
Time, sec
2048 Chemical Composition. Composition Limits. 0.15 Si max, 0.20 Fe max, 2.8 to 3.8 Cu, 0.20 to 0.60 Mn, 1.20 to 1.80 Mg, 0.25 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al
Typical Uses. ill structural components for aerospace and military equipment
Specifications (U.S. and/or Foreign). UNS. A92048 Available Product Forms. Sheet and plate
Characteristics Major alloying elements: 3.3Cu-1.5Mg-OAOMn
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2048 Aluminum. Typical tensile properties of 2048-T851 plate Temperature. OF
100
500
200
300
Temperature. OF
400
500
20
70
::2 400
0..
'"
60
~
50 t5> <::
~ 300
g 15
0
50
Ol
5
iii
10
30 250 300
100 150 200 Temperature. °C
300
5
Temperature. OF
400
500
r-, I,
V ./
~
40 (j)
200
200
-J!.
"(;;
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(j)
100
,/
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80
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70
100
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300
400
500
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60
9
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250 300
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50
100 150 200 Temperature. °C
250
300
o
100 150 200 Temperature. °C
50
2048 Aluminum. Typical compressive properties of 2048"T851 plate Temperature, OF
100
600
s:
200
300
--
::;:
.c
bo 400 e
~.,
--
>
.~
300
0.
Temperature, OF
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8
o
60
100
150
<:
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200
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260
40
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o 30 300
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200
100
80
70
E
200
600
400
70
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60
300
400
600
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60
100
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200
200
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260
300
~
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Next Page 170 I Heat Treater's Guide: Nonferrous Alloys
2048 Aluminum. Axial fatiguecurves for unnotchedspecimens of 2048-T851 plate 5 0 0 . . . - - - - - - - -........- - - - - - - - , - - - - - - - - - r - - - - - - - - - - - ,
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60
400 1 - - - - - - - - l - - - - - o l
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~ 1ii E ::J E
ui
50
•
V>
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1ii 300 t-------t-------"~:_-_:_f"'__=_--O==""--==I=o:::i:::.=====~ E ::J 40 E
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30 200 1--------+----------"i-iI~---------(J=1',.......-~~==~
a
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100
0
/j.
Longitudinal Long transverse
L-
:2
R=-1.0 /
---'-
-'---
----'-
20
/j.
----J
10 7
10 3
2048 Aluminum. ModifiedGoodman diagramfor axial fatigue of unnotched specimensof 2048-T851 plate Minimum stress,ksi
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s:
50
:;;
Ii
e
t:
t:
E
"E
'x
~
~
300
E
"E
..
200
'x
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-300
-200
-100
+100
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2048 Aluminum. Creep-rupturecurves for 2048-T851 plate, longitudinalorientation 1000 ,-----,----.-,--,--,------,---,----,,-,,
Rupture
1000
0.2% deformation
100
100
120°C (260 of) 120°C (260°F) 176°C (360 of) 176°C (260 of) ~
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1
10
10 L 10
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Previous Page
2061 Heat Treater's Guide: Nonferrous Alloys
6063 Chemical Composition. Composition Limits. 0.20 to 0.60 Si, 0.35 Fe max, 0.10 Cu max, 0.10 Mn max, 0.45 to 0.90 Mg, 0.10 Cr max, 0.10 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), balAl Specifications (U.S. and/or Foreign). AMS. Extruded wire, rod, bar, shapes, and tubing: 4156; ASME. Extruded wire, rod, bar, shapes, and tubing: SB221. Pipe: SB241; ASTM. (See adjoining Table); SAE. J454; UNSA96063
Available Product Forms. Extruded wire, rod, bar, shapes, and tubing; drawn tubing. Tempers include TI, T4, T5, T52, T6, T83, T831, T832
General Considerations. Temperatures given here are nominal and should be attained as rapidly as possible and maintained with ±6 °C (±l0 OF) of nominal during time at temperature. Times at temperature are approximate. Specific times are based on time required for load to reach temperature. Times given here are based on rapid heating, with soak times measured from time load reaches within 6 °C (10 "F) of applicable temperature
Annealing. Treat at 415°C (775 "F); hold 2 to 3 h at temperature; cool at 28°C (50 oF) per hour from 415°C (775 oF) to 260 °C (500 oF)
Characteristics Major alloying elements: 0.7Mg-0.4Si
Typical Uses. Pipe, railing, furniture, architectural extrusions, truck and
6063 Aluminum: Typical tensile properties at various temperatures
trailer flooring, doors, windows, irrigation pipe. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing may be treated to TI temper by quenching directly from the extrusion press with suitable control of extrusion temperature. T42 temper is obtained by treating product at 520°C (965 "F), Drawn tubing is treated to T4 and T42 tempers at 520°C (965 OF). Sheet and plate are solution treated at 570 °C (1060 OF). T4 temper is obtained with natural aging of two weeks
General Considerations. Unless otherwise indicated, product should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective in treating some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1OOF) of nominal during time at temperature Precipitation Heat Treating (Artificial Aging). Extruded rod, bar, shapes, and tubing are treated to T5 temper at 205°C (400 OF) for I h. Alternate treatment: 3 h at 180°C (355 "F). Same products are treated to T6 and T62 tempers by treating at 175°C (345 OF) for 8 h. Alternate treatment: 6 h at 180°C (355 "F), In treating drawn tubing to T83, T831, and T832 tempers, cold working after solution treatment is necessary to get desired properties. Nominal treatment temperatures for these alloys and T62 are 175°C (345 "F) for 8 h. Alternative for treating to T83, T831, and T832 tempers: quench directly from extrusion press if it has suitable temperature control
-c
Temperature OF
YIeldstrength (0.2c;{, offset) ksI MPa
'Iensile strength(a) ksI MPa
Elongation, c;{,
Tl temper(b) -320 -112 -18 75 212 300 400 500 600 700
-196 -80 -28 24 100 150 205 260 315 370
234 179 165 152 152 145 62 31 23 16
34 26 24 22 22 21 9 4.5 3.2 2.3
110 103
103 45 24 17 14
16 15 14 13 14 15 6.5 3.5 2.5 2
255 200 193 186 165 138 62 31 23 16
37 29 28 27 24 20 9 4.5 3.2 2.3
165 152 152 145 138 124 45 24 17 14
24 22 22 21 20 18 6.5 3.5 2.5 2
324 262 248 241 214 145 62 31 23 16
47 38 36 35 31 21 9 4.5 3.3 2.3
248 228 221 214 193 133 45 24 17 14
36 33 32 31 28 20 6.5 3.5 2.5 2
97 90
97
44 36 34 33 18 20
40 75 80 105
TStemper -196 -80 -28 24 100 150 205
-320 -112 -18 75 212 300 400 500 600 700
260 315 370
28 24 23 22 18 20
40 75 80 105
T6temper -320 -121 -18 75 212 300 400 500
-196 -80 -28 24 100 150 205 260 315 370
600 700
24 20 19 18 15 20
40 75 80 105
(a) Lowest strength for exposures up to 10 000 h at temperature, no load; testloading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture. (b) Tl temper fonnerlyT42
6063 Aluminum: Typical mechanical properties 'Thmper
0 Tl(c) T4 T5 T6 T83 T831 T832
Tensilestrength MPa ksi
YIeldstrength MPa ksI
90 152 172 186 241 255 207 290
48 90 90 145 214 241 186 269
13 22 25 27 35 37 30 42
7 13 13 21 31 35 27 39
(a) 500 kg load: 10 rnm diam ball. (b) At 5 X 108 cycles: R.R. Moore type test. (c) Formerly T42 temper
Elongation, c;{,
20 22 12 12 9 10 12
Hanlness(a), HB
Shear strength MPa ksI
Fatigue streogth!b) MPa ksI
25 42
69 97
10 14
55 62
8 9
60 73 82 70 95
117 152 152 124 186
17 22 22 18 27
69 69
10 10
Wrought Aluminum and Aluminum Alloys /207
6063 Aluminum. 6063-T5 extrusion. Transverse section. Grains at surface of extrusion have recrystallized because of more working and heating. Grains in the interior of the extrusion are unrecrystalIized. Tucker's reagent. Actual size
6063 Aluminum: Time-temperature property diagram. Composition: AI-0.60% Mg-0.30% Si-0.02% Mn-0.16% Fe-O.Q1 % Zn-0.02% Ti. Treatment: Solution heat-treated at 540°C (1000 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 25.9 ksi (178 MPa) Iso-yield curve is 90% of quenched and aged yield strength
I
800 (4211
90% of T6 YS
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400 (:Ill4'
~
100
1000
Time of Isothermal Hold, s
6063 Aluminum: Time-temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A= 7075; B = 2017; C = 6061; D = 6063
600
---..-- :----- ---
500 400
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A
U
0.300
I-
200 100 0
1
100
10
t.s
1000
2081 Heat Treater's Guide: Nonferrous Alloys ASTMspecifications Mill form andoondltlon
WIre. rod.bar.shapes.WId tube(extruded) Tube(extruded, seamless); pipe Tube(extruded, coiled) 'Iube (drawn) Tubejdrawn,seamless) Pipe(gasWId oilttansmission) Structural pipeWId nibe(extruded)
ASTMNo.
B221 B241 B491 B483 B2LO B345 B429
6066 Chemical Composition. Composition Limits. 0.90 to 1.80 Si, 0.50 Fe max, 0.70 to 1.20 Cu, 0.60 to 1.10 Mn, 0.80 to 1.40 Mg, 0.40 Cr max. 0.25 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Extruded wire, rod, bar, shapes, and tubing: B 221; SAB. J454; UNS. A96066; Government. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/1O. Forgings: QQ-A-367; (United Kingdom) BS H11 Available Product Forms. Extruded wire, rod, bar, shapes, and tubing; die forgings. Available tempers: T4, T6, T450, T4511, T651O, T65l1
Characteristics Major alloying elements: 1.4Si-l.1Mg-1.0Cu-0.8Mn Typical Uses. Forgings and extrusions for welded structures. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Precipitation Heat Treating (Artificial Aging). Extruded rod, bar, shapes, and tubing; drawn tubing, and die forgings are treated to T6, T62, T651O,T6511 tempers at 175°C (345 oF) for 8 h. Parts scheduled for T6510 and T6511 tempers are stress relieved by stretching to produce specified amount of permanent set prior to precipitation heat treatment General Considerations. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 OF) of nominal during time at temperature. Time at temperature is approximate. Specific times are based on time needed for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature Annealing. Temperature of 415°C (775 "F) is held for 2 to 3 h 6066 Aluminum: Tensile properties
Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing; drawn tubing; and die forgings are treated at 530°C (985 OF) to T4, T42, T451O, and T4511 tempers. Product in T4510 and T45ll tempers are stress relieved by stretching to produce specified amount of permanent set prior to precipitation heat treatment General Considerations. Product should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (l00 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) during time at temperature
Thmper
'Iypleal properties 0 T4.T451 T6.T651 Property limits (extrusions) 0 T4. T4510.T4511 T42 T6.T6510.T6511 T62 Property limits (die forgings) T6
Thnslle strength ksl MPH
YIeld strength (0.2% olrsel) MPH ksl
150 360 395
22 52 57
83 207 359
12 30 52
18 18 12
200 max 275 min 275 min 345 min 345 min
29 max 40 min 40 min 50 min 50 min
125max l70min 165min 310min 290 min
18 max 25 min 24 min 45 min 42 min
16min 14min 14min 8 min 8 min
345 min
50 min
310min
45 min
FJongatlon(H), %
(a) In 50 mrn(2 in.) or 4d. where d is diameterof reducedsectionof tensiletestspecimen
6070 Chemical Composition. Composition Limits. 1.00 to 1.70 Si, 0.50 Fe max, 0.15 toO.4OCu,0.40 to 1.00Mn, 0.50 to 1.20Mg, 0.10Crmax, 0.25 Zn max, 0.15 Ti max, 0.5 others max (each), 0.15 others max (tota!),bal AI
Specifications (U.S. and/or Foreign). ASTM. Gas and oil transmission pipe: B 345; SAB. J454; Government. Extruded rod, bar, shapes, and tubing: MIL-A-46104. Impacts: MlL-A-12545
Wrought Aluminum and Aluminum Alloys 1209
Available Product Forms. Extruded rod, bar, shapes, and tubing. Tempers include T4, T6, and T4511
Characteristics Major alloying elements: 1.45Si-0.8Mg-0.7Mn-0.3Cu
Typical Uses. Heavy duty welded structures, pipelines, extruded structural parts for autos. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Extruded bar, rod, shapes, and tubing are treated to T4 and T42 tempers at 545°C (1015 "F), With suitable control of extrusion temperatures, product may be directly quenched from extrusion press.
General Considerations. Material should be quenched as rapidly as possible from solution treating temperature and with minimum delay after removal from furnace. When quenching is by total immersion in' water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible within ±6 °C (±IO "F) during time at temperature Precipitation Heat Treating (Artificial Aging). Product is treated to T6 temper at a metal temperature of 160°C (320 "F) for 18 h. Time at temperature is approximate. Specific times depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature Annealing. Temperature for T4 temper is 545°C (1015 "F)
6101 Chemical Composition. Composition Limits. 0.30 to 0.70 si, 0.50 Fe max, 0.10 Cu max, 0.03 Mn max, 0.35 to 0.80 Mg, 0.03 Cr max, 0.10 Zn max, 0.06 B max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Bus conductor: B 317; SAE. J454; UNS. A96101; (Austria) Onorm E-AlMgSi; (France) NF A-G5IL; (Italy) UNI P-AlSiO; (Switzerland) USM AI-Mg-Si; (United Kingdom) BS 9IE; (Germany) E-AlMgSiO.5; Werkstoff-Nr-3.3207 Available Product Forms. Extruded rod, bar, tubing, pipe, and structural shapes. Available tempers: T4, T6, T61, T63, T64, T65
Characteristics
6101 Aluminum: Typical tensile properties of 6101-T6 at various temperatures Tempemture -196 -80 -28 24 100 150 205 260 315 370
OF
-320 -112 -18 75 212 300 400 500 600 700
296 248 234 221 193 145 69 33 24 17
43 36 34 32 28 21 10 4.8 3 2.5
Recommended Heat Treating Practice Solution Heat Treating. Heat to 510 °C (950 "F); hold at temperature for 1 h Precipitation Heat Treating (Artificial Aging). Heat to 175°C (345 OF); hold at temperature for 6 to 8 h
(0.2% off.. l)(o) MPo ksI
228 207 200 193 172 131 48 23 16 12
33 30 29 28 25 19 7 3.3 2.3 1.8
6101 Aluminum: Property limits for 6101 extrusions Eleelrleal
Temper
Yield strength Teosil's1reogth(o) MPo ksl
For information on corrosion resistance, cold workability, machinability, braze ability , and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
Major alloying elements: 0.6Mg-0.55Si
·C
Typical Uses. High strength bus bars, electrical conductors, and heat sinks.
Tensile slrength(o) MPo ksl
YIeld s1reogth(o) MPo ksi
oondU
ElongoUon(h). %
24 20 19 19 20 20 40
80 100 105
(a)Loweststrengthforexposuresup to 10000 h at temperature, no load; testloadingappliedat35 MPalmin(5 ksilmin)to yieldstrengthand thenat strainrate of 5%/minto fracture, (b) In 50 rom(2 in.)
HIll
T6 T61 0.125-0.749 in. thick 0.750-1.499 in. thick 1.500-2.000 in. thick T63 T64 T65
83 200
12 29
138 20 124 18 103 15 186 27 103 15 172-221 25-32
(a)Singleentries areminimumvalues
55 172
8 25
103 15 11 76 55 8 152 22 55 8 138-186 2()'27
59 55 57 57 57 56 59.5 56.5
2101 Heat Treater's Guide: Nonferrous Alloys
6151 General Considerations. Material should be quenched from solution. treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated. water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. High-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 "F) ofnominal during time at temperature
Chemical Composition. Composition Limits. 0.60 to 1.20 Si, 1.00 Fe max, 0.35 Cu max, 0.20 Mn max, 0.45 to 0.80 Mg, 0.15 to 0.35 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total) Specifications (U.S. and/or Foreign). AMS. Forgings: 4125; SAE. J454; UNS. A96151; Government. Forgings and forging stock: QQ-A367, MIL-A-22771; (Canada) C~A SGUP Available Product Forms. Sheet, die forgings, forging stock, and rolled rings. Tempers include T6 and T652
Precipitation Heat Treating (Artificial Aging). Die forgings and rolled rings are treated to 6T tempers at 170°C (340 oF) and held at temperature for 10 h.
Characteristics Major alloying elements: 0.9Si-0.6Mg-0.25Cr
Rolled rings being treated to T652 temper should be stress relieved by 1 to 5% cold reduction subsequent to solution treatment and prior to precipitation treatment
Typical Uses. Applications require combination of good forgeability, good strength, and resistance to corrosion. Examples: Die forgings and rolled rings for crank cases, fuses, and machine parts
General Considerations. Temperatures for precipitation treatment given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 OF) of nominal during time at temperatureand those given here are approximate. Specific times depend on .time required for load to reach temperature. Times given are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature
Recommended Heat Treating Practice Solution Heat Treating. Die forgings and rolled rings are treated to T4 temper at 515°C (960 OF). Rolled rings being treated to T452 temper should be stress relieved by 1 to 5% cold reduction subsequent to solution treatment and prior to precipitation treatment.
6151 Aluminum: Typical tensile properties 6151 Aluminum: Tensile-property limits °C
Thmper
ThllSile strength ksi MPa
Yieldstrength MPa ksi
Eiongatioo(a). %
Thmperalure OF
-196
-SO Die forgings, T6 Axisparalleltograin flow AxisnOI parallel10grainflow Rolled rings, T6 and T6S2 Tangential AxiaI
Radial
-28 303
44
255
37
303
44
255
37
14(coupon) 10(forging) 6 (forging)
303 303 290
44 44
255 241 241
37 35 35
5 4 2
42
24 100 150 205 260 315 370
-321 -112 -18 76 212 300 400 500 600 700
Thnsilestrength(o) ksl MPa
57 50 49 48 43 28 14 6.5 5 4
395 345 340 330 295 195 95 45 34 28
6151 Aluminum. Effectof quenchingfrom 540°C (1000 OF) on residual stressesin solid cylinders Cross section of solid cylindrical
Cross section of solid cylindrical
specimen, in. 2
t
100
30
specimen, in. 2
40
40
t
10 0c
c
~
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:;;
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.;;;
50
~
5
~
~
-o c 0
-'
c
C.
E 0
0
5
.~
C.
'0
.een c
0
E -'
50
o
~
5
'"
c
0
.~
10 o° 100 0
10
20
30
Cross section of solid cylindrical specimen, 10 3 mm 2
l
t c
o
.~
.,.c .,.
~
.een
10
~
I-
'"
345 315 310 298 275 185 85 34 27 22
50 46
45 43 40 27 12 5 3.9 3.2
Elongation, %
20 17 17 17 17 20 30 50 43 35
(a)Loweststrengthforexposuresup to 10 000 h at temperature, no load;testloadingappliedat35 MPalmin(5ksilmin)to yieldstrengthand then atstrainrateof 5%/minto fracture
(a) In 50 mm (2 in.)or 4d. where d is diameterofreducedsectionof tensiletestspecimen
0
Yieldstrength (0.2% offset)(o) MPa ksi
.=: '0
.~
.3
~
~
~
:;; c 0
c
.~
.~
~
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o
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100 '----_---'-_ _--'--------'----' o 10 20 30 Cross section of solid cylindrical specimen, 10 3 mm 2
~
Wrought Aluminum and Aluminum Alloys /211
6151 Aluminum. 6151-T6 closed-die forging showing large particles of Mg2Si (rounded) and (Fe,Mn)3SiAI12 (angular or scriptlike), and a fine, banded dispersion of extremely small particles of a chromium intermetallic phase. Keller's reagent. 250x
6201 Chemical Composition. Composition Limits. 0.60 to 1.20 Si, 1.00 Fe max, 0.35 Cu max, 0.20 Mn max, 0.45 to 0.80 Mg, 0.15 to 0.35 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0,15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Wire: B 398. Stranded conductor, T81 temper, B 399; SAE. J454; UNS. A96201 Available Product Forms. Rod and wire
Characteristics Major alloying elements: 0.7Si-0.8Mg
Typical Uses. High strength electrical conductors For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Temperature is 510 °C (950 OF) Precipitation Heat Treating (Artificial Aging). Product is treated at 150°C (300 OF), and held at that temperature approximately 4 h
6205 Chemical Composition. Composition Limits. 0.60 to 0.90 Si, 0.70 Fe max, 0.20 Cu max, 0.05 to 0.15 Mn, 0.40 to 0.60 Mg, 0.5 to 0.15 Cr, 0.25 Zn max, 0.05 to 0.15 Zr, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al
Typical Uses. High impact strength in service
Specifications (U.S. and/or Foreign). UNS. A96205
Precipitation Heat Treating (Artificial Aging). Temperature is 175 °C (345 OF). Parts are at temperature approximately 6 h
Available Product Forms. Plate, tread plate, and extrusions
Characteristics Major alloying elements: 0.8Si-0.5Mg-0.l OMn-O.lOCr, O.lOZr
Recommended Heat Treating Practice Solution Heat Treating. Temperature is 525°C (970 OF)
212/ Heat Treater's Guide: Nonferrous Alloys
6205 Aluminum: Time-temperature-property diagram. Composition: AI-0.53% Mg-0.76% Si-0.12% Cr-0.1 09% Zr-0.11 % Mn-0.13B% Fe-0.04% Zn-0.01 % li. Treatment: Solution heat-treated at 540 °C (1000 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 37.2 ksi (256 MPa). Iso-yield curve is 90% of quenched and aged yield strength
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ltOO
14
eoo
141r
S
90% ofT6 YS
~ ~
0
..~ f
Ql
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.00
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11041
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6262 Chemical Composition. Composition Limits. 0.40 to 0.80 Si, 0.70 Fe max, 0.15 to 0.40 Cu, 0.15 Mn max, 0.80 to 1.20 Mg, 0.04 to 0.14 Cr, 0.40 to 0.70 Bi, 0.40 to 0.70 Pb, 0.05 others max (each), 0.15 others max (total), bal AI Specifications (U.S. and/or Foreign). ASTM. Rolled or cold finished wire, rod, and bar: B 211. Extruded wire, rod, bars, shapes, and tubing: B 221. Drawn, seamless tubing: B 210. Drawn tubing: B 483; SAE. J454; Government. Rolled or cold fmished wire, rod, and bar: QQ-A255/10 Available Product Forms. Cold or cold finished wire, rod, and bar; extruded wire, rod. bar, shapes, and tubing; drawn, seamless tubing, and drawn tubing
Characteristics Major alloying elements: 1.0Mg-0.6Si-0.3Cu-0.09Cr-0.6Pb
In treating extruded rod, bar, shapes, and tubing to T4 temper, product may be quenched directly from extrusion press when extrusion temperature is suitably controlled. In treating extruded rod, bar, shapes, and tubing to T4510 temper, parts are stress relieved by stretching to produce specified amount of permanent set prior to precipitation treatment General Considerations. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise advised, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (± 10°F) ofnominal during time at temperature
Typical Uses. High-stress screw machine products requiring more resistance to corrosion than alloys 2011 and 2017.
Precipitation Heat Treating (Artificial Aging). Rolled or cold finished wire, rod, and bar; and drawn tubing are treated at a metal temperature of 170°C (340 OF).
For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Extruded rod, bar, shapes, and tubing are treated at a metal temperature of 175 °C (345 oF). Times at temperature vary per product and teinperatures, as follows:
Recommended Heat Treating Practice Solution Heat Treating. A metal temperature of 540°C (1000 OF) is used in treating rolled or cold finished wire, rod, and bar; extruded rod, bar, shapes, and tubing; and drawn tubing to T4, T42, T451, and T4510 tempers.
• Rolled or cold finished wire, rod, and bar treated to T6, T651, and T62, tempers are held for 8 h at solution treating temperature. Parts being treated to T9 temper are held at temperature 12 h. Solution treated parts to be treated to T9 temper are cold worked following solution treating. Parts destined for T651 temper are stress relieved by stretching to
Wrought Aluminum and Aluminum Alloys /213
III
produce specified amount of permanent set prior to precipitation heat treating Drawn tubing in T6, T9, and T62 tempers are held at the precipitation treatment temperature for 8 h. Parts in T9 temper are cold worked after precipitation treatment to obtain desired properties
General Considerations. III
III
Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1O"F) of nominal during time at temperature Times at temperature are approximate. Specific times depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature with 6 °C (10 OF) of applicable temperature
Annealing. Metal is heated to 415°C (775 OF); holding time is 2 to 3 h
6262 Aluminum: Typical tensile propertiesat varioustemperatures 'Iemperature OF "C
T651 temper -196 -320 -112 -80 -28 -18 24 75 100 212 150 300 T9temper -196 -320 -112 -80 -28 -18 24 75 100 212 150 300 205 400 260 500 600 315 370 700
'Iensllestrength(a) MPa ksI
Yieldstrength (0.2% oliset)(a) MPa ksI
414 338 324 310 290 234
60 49 47 45 42 34
324 290 283 276 262 214
47 42 41
510 427 414 400 365 262 103 59 32 24
74 62 60 58 53 38 15 8.5 4.6 3
462 400 386 379 359 255 90 41 19 12
67 58 56 55 52 37
40
38 31
13
6 2.7 1.8
Elongation, %
22 18 17 17 18 20 14 10 10 10 10 14 34 48 85 95
(a)Loweststrengthforexposures up to 10000 h at temperature, no load;testloadingappliedat 35 MPalmin(5ksilmin)toyieldstrength andthenat strainrateof 5%/minto fracture
6351 Chemical Composition. Composition Limits. 0.70 to 1.30 Si, 0.50 Fe max, 0.10 Cu max, 0.40 to 0~80 Mn, 0.40 to 0.80 Mg, 0.20 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Gas and oil transmission pipe: B 345. Extruded wire, rod, bar, shapes, and tubing: B 221; UNS. A9635 1 Available Product Forms. Extruded shapes, structurals, pipe, and tubing
Characteristics Major alloying elements: I.OSi-0.6Mg-0.6Mn
Typical Uses. Extruded structures for road vehicles and railroad stock; tubing and pipe that carries water, oil, or gasoline. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Parts are heated to 505°C (940 OF) Precipitation Heat Treating (Artificial Aging). Treatment is at 170 °C (340 "F); treatment temperature is held 6 h Annealing. Treatment temperature is 350°C (660 OF), which is held for about 4 h
6351 Aluminum. 6351-T6 extruded tube, 1.5-mm (0.06-in.) wall. Longitudinal section. Polarized light. Coarse, recrystallized grains at top are near surface; polygonized subgrains are in unrecrystallized interior. Barker's reagent. 100x
214/ Heat Treater's Guide: Nonferrous Alloys
6463 Chemical Composition. Composition Limits. 0.20 to 0.60 Si, 0.15 Fe max, 0.20 Cu max, 0.05 Mn max, 0.45 to 0.90 Mg, 0.05 Zn max, 0.05 others (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Extruded wire, bar, shapes, and tubing: B 221; SAE. J454; UNS. A96463; (United Kingdom) B5E6
Available Product Forms. Extruded rod, bar, shapes, and tubing
Characteristics Major alloying elements: OAOSi-0.7Mg
Typical Uses. Extruded architectural and trim sections, appliance parts, and bright anodized automotive extrusions. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. Temperature used to treat parts to T4 and T42 tempers is 520°C (965 OF). In addition, parts may be treated to T1 temper by quenching them directly from the extrusion press when extrusion
temperature is properly controlled. Same practice may be used in treating to T4 temper
General Considerations. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Metal temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±IO "F) of nominal during time at temperature
Precipitation Heat Treating (Artificial Aging). Parts are treated to T5 temper at a temperature of 205°C (400 "F) for 1 h. An alternate treatment: 3 h at 180°C (355 oF) General Considerations. • Metal temperatures given are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1O "F) during time at temperature • Times given for time at temperature are approximate, specific times depend on time required for load to reach temperature. Times are based on rapid heating with soak time measured from time load reaches temperature within 6 °C (10 OF) of applicable temperature
7005 Chemical Composition. Composition Limits. 0.10 Cu max, 1.00 to 1.80 Mg, 0.20 to 0.70 Mn, 0.35 Si max, 0040 Fe max, 0.06 to 0.20 Cr, 0.01 to 0.06 Ti, 4.00 to 5.00 Zn, 0.08 to 0.20 Zr, 0.05 others max (each), 0.15 others max (total), bal Al
Specifications (U.S. and/or Foreign). ASTM. Extruded wire, rod, bar, shapes, and tubing: B 221; UNS. A97005 Available Product Forms. Extruded rod, bar, and shapes
lytic solution potentials; alternately, joint surfaces should be protected or insulated
Recommended Heat Treating Practice Parts are treated to T53 temper by press quenching from hot working temperature, naturally aging 82 h at room temperature, then two-stage artificial aging 8 h at 100 to 110 °C (212 to 230 OF), plus 16 h at 145 to 155 °C (290 to 310 oF)
Characteristics
Solution Heat Treating. Temperature is 400°C (750 oF)
Major alloying elements: 4.6Zn-1AMg-0.5Mn-0.1Cr-0.1Zn-0.03Ti
Annealing. Temperature is 345 °C (650 OF)
Typical Uses. Extruded structural members such as frame rails, cross
7005 Aluminum: Typicaltensile properties at various temperatures for 7005-T53
members, comer posts, side posts, and stiffeners for trucks, trailers, cargo containers, and rapid transit cars. Welded or brazed assemblies requiring moderately high strength and high fracture toughness, such as large heat exchangers, especially where solution heat treatment after joining is impractical. Sports equipment such as tennis racquets and softball bats
Precautions in Use. To avoid stress-corrosion cracking, stresses in the transverse direction should be avoided at exposed machined or sawed surfaces. Parts should be cold formed in 0 temper, then heat treated; alternatively, parts may be cold formed in W temper, followed by artificial aging. In parts intended for service in aggressive electrolytes such as seawater, selective attack along the heat-affected zone in a weldment or torch-brazed assembly can be avoided by postweld aging. When the service environment is conducive to galvanic corrosion, 7005 should be coupled or joined only to aluminum alloy components having similar electro-
"C
Thmperature OF
-269 -196 -80
-28 24 100 150 205 260
-452 -320 -112 -18 75 212 300 400 500
'Iensilestrengtb(a) MPa ksi
641 538 441 421 392 303 165 97 76
93 78 64 61 57 44 24 14 11
YIeldstreogth(a) MPa ksI
483 421 379 359 345 283 145 83 66
70 61 55 52 50 41 21 12 9.5
Elongation, %
16 16
13 14 15 20 35 60 80
(a) Lowest strength for exposures up to 10000 h at temperature, no load; lest loading applied at35 MFa/min (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture
Wrought Aluminum and Aluminum Alloys /215 7005 Aluminum: Minimum mechanical properties ThmU. strength ksI
%
MPH
Compressive yield strength ksi
MPH
10
296
43
193
28
172
42
303
44
38
269
39
186
27
152
YIeld strength MPo ksi
Thmpec
MPH
Extrusions T53 Ldirection
345
50
303
44
331
48
290
324
47
262
L-T direction Sbeet 80d plate T6(d),T63(e),T6351(e)
Eiongatlon(o),
Shear strength ksI
Shear yield strength MPo ksi
Beoriog yield strength MPo ksI
Bearingstrength MPo
ksi
25
655(b) 496(c)
95(b) 72(c)
503(b) 407(c)
73(b) 59(c)
22
634(b) 483(c)
92(b) 70(c)
448(b) 365(c)
65(b) 53(c)
(a) In 50 mm (2 in.) or4d. where d is diameterof reducedsection of tensiletest specimen.(b) e/d =2.0. where e is edge distance and d is pindiameter.(c) e/d = 1.5.(d) Up to 6.35 mm (0.250in.) thick. (e) 6.35 to 75 mm (0.250 to 3.00 in.) thick
7039 Chemical Composition. Composition Limits. 2.30 to 3.30 Mg, 3.50 to 4.50 Zn, 0.10 to 0.40 Mn, 0.15 to 0.25 Cr, 0.30 Si max, 0.10 Cu max, 0.40 Fe max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI
Specifications (U.S. and/or Foreign). Military. MIL-A-22771, MILA-45225, MIL-A-46063; UNS. A97039
sium alloys as 5052, 5086, and 5083. Resistance to general corrosion is very much superior to that of most heat-treatable alloys. Under standard 6% NaCl immersion test for 6 mo or 5% NaCl salt fog, the alloy evidenced a slight superficial staining and a mild and shallow pitting attack with no measurable loss in strength. In a sodium chloride-hydrogen peroxide test, no evidence of intergranular corrosion was observed
Available Product Forms. Sheet (limited) plate, forgings, extrusions
Recommended Heat Treating Practice
Characteristics
Solution Heat Treating. Heat metal to 460 to 500°C (860 to 930 OF), soak 2 h, quench in cold water. Sheet stock should be quenched from 490 to 500°C (910 to 930 "F); extruded stock should be quenched from 460 to 470 °C (860 to 880 oF)
Major alloying elements: 4Zn-2.8Mg-0.25Mn-0.20Cr
Typical Uses. Cryogenic storage tanks, unfired pressure vessels, ordnance tanks, armor plate, missile structures, low temperature processing equipment. and storage tanks
Weldability. Readily weldable by the direct-current inert-gas tungstenarc (TIG) and by the metal-arc-insert-gas (MIG) process, using a weldfiller alloy of aluminum X5039 or 5183 rod. Has considerably better weld strength and ductility than 5083. Readily welded over a wide range of thicknesses with no decrease in weld ductility. Shows very good crack resistance in restrained plate weldments when joined with X5039 filler wire. Room temperature weld strength averages 360 MPa (52 ksi) and increases to 448 MPa (65 ksi) at -195°C (-320 OF). No special pre-weld or post-weld heat treatment is required
Precipitation HeatTreating (Artificial Aging). In treatingto T6 temper: reheat to 120°C (250 OF); hold at temperature 20 to 24 h; air cool Annealing. For 0 temper, heat to 415 to 455°C (775 to 850 OF); soak 2 to 3 h; air cool; reheat to 230°C (450 OF); hold at temperature 4 h; air cool. Or heat to 355 to 370°C (670 to 700 "F); air cool Stress Relief Anneal. Heat to 355 to 370 °C (670 to 700 oF); soak 2 h; air cool to room temperature
7039 Aluminum: Typical mechanical properties
Machinability. Good machinability in the annealed state. Soluble oil emulsions, kerosene, and kerosene-lard oil mixtures are recommended for most machining operations, but high viscosity lubricants are recommended for tapping operations
Workability. Best formed in its freshly quenched condition. In the soft temper, the alloy can be successfully formed on all types of equipment. Because ofits higher strength. a greater allowance for springback will have to be made than when working with other aluminum alloys. Use of heat up to 120°C (250 "F) during forming in the annealed condition is beneficial in certain swaging, spinning, and drop hammer operations. In the solution treated condition the properties are intermediate between those of 0 and T6 temper, but definitely higher than 0 temper condition during the first few hours after quenching. The formability gradually lessens as age-hardening increases. In the solution treated and aged T6 temper condition, the material exhibits very poor forming qualities. Due to the elaborate annealing and stabilizing treatment required. severe forming in the annealed 0 temper condition would be impractical. Rubber forming is usually conducted at 120 to 230°C (250 to 450 OF)
Corrosion Resistance. The general corrosion resistance characteristics of 7039-T64 are comparable to such highly resistant aluminum-magne-
Property
Tensilestrength,MPa (ksi) Longitudinal Transverse 0.25%tensileyieldstrength,MPa (ksi) Longitudinal Transverse Elongationin 50 mm (2in.), % Longitudinal Transverse 0.2% compressiveyieldstrength,MPa (ksi) Longitudinal Transverse Sheerstrength.MPa (ksi) Longitudinal Transverse Bearingstrength(b),MPa (ksi) Longitudinal Transverse Brinellhardness(1500 kg).HB
1'64
Property volue(o) at temper: T61
0
450(65) 450(65)
400(58) 400(58)
227(33) 227(33)
380(55) 380(55)
330(48) 330(48)
103 (15) 103 (15)
13 13
14 14
22 22
400(58) 415(60)
380(55) 407(59)
270(39) 255 (37)
235(34)
910(132) 910(132) 133
827(120) 123
61
(a)Propertyvaluesfor 6 to 75 mm (O.25t03.0in.) thick plate.(b) eld=2, wheree is theedge distance and d is the pin diameter
216/ Heat Treater's Guide: Nonferrous Alloys
7039 Aluminum: Microstructures. (a) 7039 ingot 305 mm (12 in.) thick. Polarized light. Structure shows equiaxed grains with interdendritic areas of M92Si and Fea-SiAI 12 • Barker's reagent. 50x. (b) 7039-F plate, 150 mm (6 in.) thick, as hot rolled (50% reduction). Polarized light. Grains are elongated and thinned by working. Barker's reagent. 50x. (c) 7039-F plate, 50 mm (2 in.) thick, as hot rolled (83% reduction). Polarized light. Grains are greatly elongated and thinned. Barker's reagent. 50x
(b)
(a)
400
(c)
I
I
Rotating beam lests 350
300
250
ro
n,
:2 • 200
~ \).
\" K, , , ~ ~.~
7039-T61
j
1'-. "
It <,
~ I.e <,
<,
<,
150
-,
,
:a
.....
/--
~
o
0
00---
-- ., ~€ ~ ---- ---- r-.::J--.....
..... ... .....
50 I - - -
o T64 36 mm plate It T61 19 mm plate
I 10 8 Cycles
7039 Aluminum: Transverse impact toughness of 7039-T64 plate
1.50
20
/
2014-T6
38
40
........... ...................
100
1.75
-
70;e-T64 00
2219-T81
45
50
'Thst temperature OF "C
24 -195 24 -195
75 -320 75 -320
Elongationin SOmm (2in.), %
12 12 11 11
LIVE GRAPH Click here to view
"'-..~ , -
Plate thkkness mm in.
-
7039 Aluminum. Rotating beam fatigue data of 7039 plate compared with fatigue characteristics of 2014 and 2219. Data for 7039 are based on least-of-four results in the longitudinal direction with a 7.5 mm (0.3 in.) diam smooth specimen. Curves for 2014 and 2219 are mean values from published literature
Unnotchedimpact toughness J II ·Ihe
66.2 87.5 75.3 96.7
48.8 64.5 55.5 71.3
Notchedimpact toughness J II ·llif
7.6 6.5 7.5 8.3
5.6 4.8 5.5 6.1
-
10
Wrought Aluminum and Aluminum Alloys /217
7039 Aluminum: Microstructures. (a) 7039 ingot, 305 mm (12 in.) thick. Dendritic cells show precipitate formed during homogenization. 10% H3 P0 4 • 1OOx. (b) 7039-F plate, 150 mm (6 in.) thick, as hot rolled (50% reduction). Dendritic cells are elongated and thinned by working. 10% H3 P0 4 • 1OOx. (c) 7039-F plate, 50 mm (2 in.) thick, as hot rolled (83% reduction). Dendritic cells are elongated and thinned by working. 10% H3 P0 4 • 100x
(a)
(b)
(c)
7049 Chemical Composition. Composition Limits. 1.20 to 1.90 Cu, 2,00 to 2.90 Mg, 0.20 Mn max, 0.25 Si max, 0.35 Fe max, 0.10 to 0.22 Cr, 7.20 to 8.2 Zn, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al
General Considerations. CIl
Specifications (U.S. and/or Foreign). AMS, Extrusions: 4157,4159, Forgings: 4111; UNS. A97049; Government. Forgings: QQ-A-367; MILH-6088 Available Product Forms. Die and hand forgings
CIl
Characteristics Major alloying elements: 7.6Zn-2.5Mg-1.5Cu-0.15Cr. Used where static strength is approximately same as that of forged 7079-T6 and high resistance to stress corrosion cracking is required. Fatigue characteristics are about equal to those of 7075-T6 products; toughness is somewhat higher. General resistance to corrosion is poor Typical Uses.•Forged aircraft and missile fittings, landing gear cylinders, and extruded sections.
Precipitation Heat Treating (Artificial Aging). CIl
CIl
For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Solution Heat Treating. CIl
CIl CIl
Both die and hand forgings are treated to W and W52 tempers at 470°C (880 oF) W temper parts are quenched in water at 60 to 80°C (140 to 180 OF) W52 temper parts are stress relieved by 1 to 5% cold reduction after solution treatment and prior to precipitation treatment
Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When material is quenched by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled to below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water is effective for some materials Nominal metal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±10 OF) of nominal during time at temperature
To obtain T73 tempers, solution treated parts are held at room temperature for minimum of 48 h, followed by a two-stage treatment: 24 hat 120 °C (250 OF), then 10 to 16 h at 165°C (330 "F) To obtain T7352 temper, parts are stress relieved by 1 to 5% cold reduction subsequent to solution treatment and prior to precipitation treatment
General Considerations. CIl
liD
Nominal metal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) of nominal during time at temperature Time at temperature depends on time needed for load to reach temperature. Times shown are based on rapid heating, with soaking time measured from time load reaches within 6 °C (10 "F) of applicable temperature
218/ Heat Treater's Guide: Nonferrous Alloys
7049 Aluminum: Mechanical properties Tensile Sizeand dlrectlon
slnmgth(a) ksi MPa
Die forgings (AMS4111),1'73 temper Parallel tograinflow Up to 2 in., include 496 Over 2-4 in., include 490 Over 4-5 in., include 483 Acrossgrainflow Up to 1 ln., include 490 Over 1-4in., include 483 Over 4-5 in., include 469 Extrusions (AMS4157),1'73511temper Up to2.999in.,incl Longitudinal 510 Long transverse 483 Over2.999-5.000 in.,incl Longitudinal 496 Long transverse 469 Extrusions (AMS4159),1'75511temper Upto2.999in.•incl Longitudinal 538 Long transverse 524 Over2.999-5.000 in.•incl Longitudinal 524 Long transverse 510
YI.1dstrength (0.2% olfset)(a) ks\ MPa
%
Comp .....iv. yield strength ksI MPa
Shearstrength MPa ksi
MPa
k!i
MPa
ks\
Eloogatlon(a)(b),
Bearing slnmgth(
Bearing yield streogth(a)
72 71 70
427 421 414
62 61 60
7 7 7
441 434 427
64 63 62
283 276 269
41 40 39
917 903 890
133 131 129
662 655 641
96 95 93
71 70 68
421 414 400
61 60 58
3 3-2 2
434 427 414
63 62 60
283 276 269
41 40 39
917 903 890
133 131 129
662 655 641
96 95 93
74 70
441 414
64 60
7 5
448 420
65 61
276 276
40 40
758 993
110 144
72 68
427 400
62 58
7 5
435 407
63 59
269 269
39 39
738 965
107 140
78 76
483 469
70 68
7 5
490 475
71 69
290 290
42 42
586 724
85 105
76 74
469 455
68 66
7 5
475 462
69 67
283 283
41 41
572 696
83 101
(a) Singlevaluesare minimumvalues.(b) In 50 mrn(2 in.)or 4d, whered is diameter of reducedsectionof tensiletestspecimen. Wherea rangeappearsin this column,thespecifiedminimumelongation varieswiththickness of mill product. (c) e/d = 2.0,where e isedgedistance andd is pindiameter
7050 Chemical Composition. Composition Limits. 2.00 to 2.60 Cu, 1.90 to 2.60 Mg, 0.10 Mn max, 0.12 Si max, 0.15 Fe max, 0.04 Cr max, 0.08 to 0.15 Zr, 5.70 to 6.70 Zn, 0.06 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI
Specifications (U.S. and/orForeign). AMS. 4050, 4107, 4108; UNS. A97050
Available Product Forms. Plate, rolled or cold ftnished wire and rod; extruded rod, bar, and shapes; die forgings, hand forgings
Characteristics Major alloying elements: 6.2Zn-2.3Mg-2.3Cu-0.12Zr
Typical Uses. Structural applications in aircraft (plate, extrusion, hand and die forgings) take advantage of a combination of properties: very high strength coupled with resistance to exfoliation corrosion, stress corrosion, and fatigue, plus high fracture toughness. For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice SolutionHeat Treating. Plate, extrusions, die and hand forgings are treated to W, W51, W52, WSW, and W511 tempers at metal temperatures of 475°C (890 OF). In treating to W51, W52, WSW, and W511 tempers, parts may be quenched directly from extrusion press if extrusion temperatures are properly controlled
General Considerations. • Material should be quenched from solution treating temperature as rapidly as possible, and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials • Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1OOF) ofnominal during time at temperature
Precipitation Heat Treating (ArtificialAging). • Plate is subjected to two-stage treatment for T7451 temper: 3 to 6 hat 120°C (250 OF), followed by 24 to 30 h at 165°C (330 OF). Also, parts are stress relieved by stretching to produce a specifted amount of set subsequent to solution treatment and prior to precipitation treatment • Plate is subjected to a different treatment for the T7651'temper: 3 to 6 h at 120°C (250 OF), followed by 12 to 15 h at 165°C (330 OF). Also, parts are stress relieved by stretching to produce a specifted amount of permanent set subsequent to solution treatment and prior to solution treatment • Rolled or cold ftnished wire and rod are treated to a T7 temper by subjecting them to a two-stage treatment: 4 h at 120°C (250 "F), followed by 6 to 10 h at 180°C (355 "F) • Extruded rod, bar, and shapes are treated to T73510 and T73511 tempers in a two-stage treatment: 24 h at 120°C (250 OF), followed by 10 to 14 hat 175°C (345 OF) • Extruded rod, bar, and shapes are treated to T74510 and T74511 tempers in a two-stage treatment: 24 h at 120°C (250 OF), followed by 8 to 12 h at 175°C (345 oF)
Wrought Aluminum and Aluminum Alloys /219 LIVE GRAPH LIVE GRAPH LIVE GRAPH Click here to view
• Extruded rod, bar, and shapes are treated to 176510 and 176511 tempers in a two-stage treatment: 3 to 6 h at 120°C (250 OF), followed by 12 to 15 h at 165°C (330 oF) • All extruded rod, bar, and shapes are stress relieved by stretching to produce a specified amount of permanent set subsequent to solution treatment and prior to precipitation treatment • Die forgings are heated to 174 temper and hand forgings to 17452 temper in a multistage treatment: 8 h at 105°C (225 "F), followed by 8 hat 120°C (250 oF), then 4 to 10 hat 175°C (345 OF). Hand forgings are stress relieved by 1 to 5% cold reduction subsequent solution treating and prior to precipitation treatment General Considerations.
Click here to view
7050 Aluminum. Aging characteristics at room temperature, at 0 °C (32 OF), and at -18°C (0 OF)
7050 600
v . .V 500
--
~
• Nominal metal temperatures should be reached as soon as possible and maintained at ±6 °C (±10 OF) during time at temperature • Time at temperature depends on time for load to reach temperature. Times given are based on rapid heating, with soaking time measured from time load reaches temperature within 6 °C (10 OF) of applicable temperature
Click here to view
~ 300
80
~T
/ ,-
70
i .~
60
50
~ ~
40
I-
.~ I-
200
30 1 year
30 100 0.1
[";7
1 day
I wfek
2 months
t
20
1()4
10 Elapsed lime quenching, h
7050 Aluminum: Plane-strain fracture toughness Thmperand orientation
500
MPa.,r,n
70
Average
Minimum
MPa.,r,n
ksIVlIL
ksiVlIL ~
Plate 173651 L-T T-L S-L Extrusions 17651X L-T T-L S-L 17351X L-T T-L S-L
Q.
./'
::< ~ 300
26.4 24.2 22.0
24 22 20
35.2 29.7 28.6
32 27 26
~
'0
// 200
Die forgings 1736 L-T T-L,S-L
28 24 19
45.1 31.9 26.4
41 29 24
/
100
60
-
f
;,:
1 year
o
40
30 ~
11 ~ay
30 min I
50 ~
£
, / RT
---
.~
>-
30.8 26.4 20.9
.....
400
I
1 i~ek 2
mlo~'hs
10
Io
104
10 Elapsed lime after quenching, h
0.1
20
40
.£
27.5 20.9
Hand forgings 173652 L-T T-L S-L
25 19
36.3 25.3
33 23
o
"'c 29.7 18.7 17.6
27 17 16
36.3 23.1 22.0
33 21 20
30
1'- ...............
E E o
~ 10
o iii
I Vl'ar
30,m'7
o 0.1
Aging temperature, OF 320 330 340 I I II
co
e,
:2: £ C, c:
e
50
-......
-
<,
0
-
<,
<,
'iii "C
Qi
'> c:
-50
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~ -100
:j:
w
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Compared for standard conditions of 29 h at 165·C
-150 150
I
I
10
5
o
r-, I
-
~
155 160 165 170 Aging temperature, °C
1 week
2 months
10
7050 Aluminum. Actual versus predicted yield strengths for 7050 extrusions
Click here to view 310 100
1 day
Elapsed lime after quenching, h
7050 Aluminum. Effect of aging temperature on yield strength of 7050-T736
LIVE GRAPH
--- --
RT
20
-
-5 -10
LIVE GRAPH
-EOl c: ~
'iii "C
Qi
's
g
tJ
-15 ~ w -20
175
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'0;
.><
700 r--~--r--r.----,--r-,......., 100
'"
n,
:2: £c, 600
~~E=t~~o::::+1f-++-=1
90 80
c: ~
'iii~0 ~
~
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'iii
70
~
400
-EOl ~
~ '--_....L...--l.--l--l._ _l.-.--L....L-I
2
4 6 8 10 20 30 40 60 Equivalent aging time at 165°C (325 OF), h
60
Next Page 220 I Heat Treater's Guide: Nonferrous Alloys 7050 Aluminum: Typical mechanical properties Thmperature OF "C
1'73651 plate 24 75 100 212
150
300
175
350
205
400
1'73652 forgings -196 -320 -SO -112 -28 -18 24 75 100 212
150
175
205
300
350
400
'Ibneat lemp,h
0.1-10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000
0.1-10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000
ThosDe strength MPa ksl
510 441
448 441 441 393 393 393 359 290 221 359 352 324 248 193 159 303 290 221 165 131 117 662 586 552 524 462 469 462 462 414 414
407 365 290 221 379 365 324 248 193 159 324 296 221 165 131 117
Allndkaled temperature YIeldstrength ksi MPa
74 64 65 64 64 57 57 57 52 42 32 52 51 47 36 28 23 44 42 32 24 19 17
455 427 434 427 421 386 386 386 332 276 193 345 345 310 234 172 124 290 276 207 152 110 90
96 85 80 76 67 68 67 67 60 60 59 53 42 32 55 53 47 36 28 23 47 43 32 24 19 17
572 503 476 455 427 434 427 421 386 386 386 352 276 193 345 345 310 234 172 124 290 276 207 152 110 90
66 62 63 62 61 56 56 56 51 40 28 50 50 45 34
25 18 42 40 30 22 16 13 83 73 69
66 62 63 62 61 56 56 56 51 40 28 50 50 45 34
25 18 42 40 30 22 16 13
'ThnsiIe 8lreogth ksi MPa
EIongadon(a), I'.
Al roomlemperature after beating EIongadon(a), Yieldstrength I'. MPa ksi
11 13 13 14 15 16 17 18 19 21 29 19 20 22 25 31 40 22 23 27 32 45 54
510 510 510 510 510 510 510 503 483 407 331 510 496 469 386 317 248 490 469 386 317 262 234
74 74 74 74 74 74 74 74 70 59 48 74 72 68 56 46 36 71 68 56 46 38 34
455 455 462 455 441 455 448 441 407 317 228 448 441 400 296 214 152 434 421 283 200 138 117
66 66 64 66 65 64 59 46 33 65 64 58 43 31 22 63 61 41 29 20 17
11 11 12 12 12 11 12 12 13 13 14 12 12 13 13 14 15 12 12 13 14 16 19
13 14 15 15 16 16 17 . 17 17 17 18 20 23 29 19 20 22 25 31 40 22 23 27 32 45 54
524 524 524 524 517 517 510 503 483 407 331 510 496 469 386 317 248 503 483 386 317 262 234
76 76 76 76 75 75 74 73 70 59 48 74 72 68 56 46 36 73 70 56 46 38 34
455 455 462 524 517 455 448 441
66 66 67 76 75 66 65 64 59 46 33 65 64 58 43 31 22 63 61 41 29 20 17
15 15 15 16 16 15 15 16 16 17 17 15 15 16 17 17 18 15 15 16 17 19 22
407 317 228 448 441 400 296 214 152 434 421 283 200 138 117
67
66
(a) In 50 mm (2 in.)
7050 Aluminum: Creep and rupture properties of 7050-13651 plate Thmperature OF °C
24
100
150
75
212
300
'Ibne under stress,h
0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000
Rupture stress MPa ksi
510 503 490 476 469 441 427
407 379 359 372 345 310 262 179
74 73 71 69 68 64 62 59 55 52 54 50 45 38 26
Stressfor creep of: 1.0%
0.1%
0.1%
0.5%
MPa
ksi
MPa
ksi
MPa
ksi
MPa
496 483 469 455 448 434 414 393 372 352 365 338 303 255 179
72 70 68 66 65 63 60 57 54 51 53 49 44 37 26
476 462 455 448 441 427 407 386 365 345 359 324 290 241 165
69 67 66 65 64 62 59 56 53 50 52 47 42 35 24
455 448 441 441
66
448
65
65
441 441 434
64 64
421 400 372 345 317 345 303 269 193 145
61 58 54 50 46 50 44 39 28 21
414 386 359 331
60 56 52 48
324 290 228 152 124
47 42 33 22 18
64 64
ksi
63
Previous Page
Wrought Aluminum and Aluminum Alloys /171
2124 Chemical Composition. Composition Limits. 0.20 Si max, 0.30 Fe max, 3.80 to 4.90 Cu, 0.30 to 0.90 Mn, 1.20 to 1.80 Mg, O.IOCrmax, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total),bal AI. Note: fracture toughness is degraded when impurity limits exceed specifications
Typical Uses. Plate 40 to 150 rom (1.5 to 6.0 in.) thick for aircraft structures
Recommended Heat Treating Practice
Characteristics
Solution Heat Treating. Parts are treated 495°C (920 "F) to TI51 temper. Parts are stress relieved by stretching. The requirement is based on the need to produce a specified amount of permanent set subsequent to solution treatment, and, where applicable, prior to any precipitation heat treatment (artificial aging). To obtain T851 temper, a metal temperature of 190°C (375 OF) is required. Approximate time at temperature is 12 h. As in solution treating, stress relief by stretching is required
Major alloying elements: 4.4Cu-1.5Mg-0.6Mn
Annealing. Temperature is 415°C (775 OF)
Specifications (U.S. and/or Foreign). AMS. 4101; ASTM. B 209; UNS. A92124; Government. QQ-A-250/29 Available Product Forms. Plate
2124 Aluminum: Creep-rupture properties of 2124-T851 plate, 70 mm (2.75 in.) thick 'Thmperature of °C
24
75
100
212
150
300
175
350
205
400
230
450
260
500
315
600
TIme under st""',b 0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000 10.000 100.000 0.1 1 10 100 1000 10,000 100.000 0.1 1 10 100 1000 10,000 100,000 0.1 1 10 100 1000 10,000 100,000 0.1 1 10 100 1000 10,000 100,000 0.1 1 10 100 1000
StressCorcreepof Rupture stress
1.0%
0.5%
0.1%
0.2% MPa
ksi
MPa
ksi
57 55 52 54 50 47 44 39
420 405 380 360 340 360 330 310 290 235
61 59 55 52 49 52 48 45 42 34
415 395 370 345 325 345 310 285 250 205
60 57 54 50 47 50 45 41 36 30
340 310 275 240 170
49 45 40 35 25
325 290 255 205 140
47 42 37 30 20
305 260 230 170 105
44
45 40 35 27 18 10
295 270 235 180 115 59
43 39 34 26 17 8.5
285 250 205 150 90
41 36 30 22 13
260 220 170 115 52
38 32 25 17 7.5
260 235 185 125
38 34 27 18
250 220 180 115
36 32 26 17
235 205 150
34 30 22
215 170 115
31 25 17
205 180 130 76
30 26 19 11
200 170 125 69
29
180 150 97
26 22 14
170 130 76
25 19 11
110 90 55 34 20
16 13 8 5 2.9
105 83 52 30 18
97 69 45 25
14 10 6.5 3.6
90 59 38 21
13 8.5 5.5 3
MPa
ksi
MPa
ksi
MPa
ksi
485 475 475 470 470 455 435 420 400 380 400 370 345 315 290 235 170 365 340 305 270 205 145 90 325 . 290 255 200 130 83 52 275 240 195 130 76 48 34 215 185 140 83 48 32 23 110 97 59 34 21
70 69 69 68 68 66 63 61 58 55 58 54 50 46 42 34 25 53 49 44 39 30 21 13 47 42 37 29 19 12 7.5 40 35 28 19 11 7 4.9 31 27 20 12 7 4.7 3.4 16 14 8.5 5 3
470 460 455
68 67 66
455 450
66 65
435 420 405 385 370 380 360 340 310 285
63 61 59 56 54 55 52 49 45 41
425 415 395 380 360 370 345 325 305 270
345 325 290 255 195
50 47 42 37 28
310 275 240 185 125 69
62
60
25 18 10
15 12 7.5 4.4 2.6
38 33 25 15
172 I Heat Treater's Guide: Nonferrous Alloys 2124 Aluminum: Mechanical properties of 2124-T851 plate, 70 mm (2.75 in.) thick 'Iemperature
-c
of
-269 -195 -80 -28 24 100
-452 -320 -112 -18 75 212
150
300
175
350
205
400
230
260
315
370
450
500
600
700
425
800
480 535
900 1000
TImeat temperature,h
0.1-10,000 100.000 0.1-10 100 10011 10,000 100,000 0.1 0.5 10 100 1000 10,000 100,000 0.1 0.5 10 100 1000 10,000 100.000 0.1 0.5 10 100 1000 10,000 100,000 0.1 0.5 10 100 1000 10,000 100.000 0.1 0.5 10 100 1000 10.000 100.000 0.1 0.5 10 100 1000 10.000 100,000 0.1 0.5
Tensile strength ksi MPa
AtlndicaledtempemluN Yieldstrength Elongation, MPa ksl 'I
705 595 525 505 485 455 450 415 405 400 370 345 397 385 380 360 330 295 220 365 360 330 305 260 185 125 325 310 275 235 170 110 83 270 255 205 150 105 76 62 160 140 83 69 62 52 45 76 59 48 41 38 34 34 34 30 16 2
620 545 490 470 450 420 415 395 395 380 330 295 370 365 360 340 305 250 180 340 330 310 270 220 140 90 295 285 250 200 125 76 59 240 230 185 125 76 55 45 145 115 69 55 45 41 38 69 45 34 31 28 28 28 28 24 12 2
102 86 76 73 70 66 65 60 59 58 54 50 57 56 55 52 48 43 32 53 52 48 44 38 27 18 47 45 40 34 25 16 12 39 37 30 22 15 11 9 23 20 12 10 9 7.5 6.5 11 8.5 7 6 5.5 5 5 5 4.4 2.3 0.3
90 79 71 68 65 61 60 57 57 55 48 43 54 53 52 49 44 36 26 49 48 45 39 32 20 13 43 41 36 29 18 11 8.5 35 33 27 18 11 8 6.5 21 17 10 8 6.5 6 5.5 10 6.5 5 4.5 4.1 4.1 4.1 4.1 3.5 1.8 0.3
2124 Aluminum: Typical tensile properties of 2124-T851 Spe
Tensile strength ksI MPa
Yieldstrength MPa ksi
Elongation, 'I
1.500-2.000 in. thick Longitudinal Long transverse Short transverse
490 490 470
71 71 68
440 435 420
64 63 61
9 9 5
480 470 465
70 68 67
440 435 420
64 63 61
9 8 4
2.000-3.000 in. thick Longitudinal Long transverse Short transverse
10 9 8 8 8 9 9 10 10 11 13 15 12 12 12 12 14 16 23 13 13 14 15 19 28 40 15 15 17 20 30 45 55 17 17 20 29 45 60 65 23 26 40 50 65 75 80 35 50 75 85
90 95 100 65 85 65 2
Modulusofelastkily lO'psi GPa
81 76 74 72 71 71 68 68 68 68 68 66 66 66 66 66 66 66 63 63 63 63 63 63 63 61 61 61 61 61 61 61 59 59 59 59 59 59 59 53 53 53 53 53 53 53 45 45 45 45 45 45 45
11.8 11.0 10.7 10.5 10.3 10.3 9.9 9.9 9.9 9.9 9.9 9.6 9.6 9.6 9.6 9.6 9.6 9.6 9.2 9.2 9.2 9.2 9.2 9.2 9.2 8.9 8.9 8.9 8.9 8.9 8.9 8.9 8.5 8.5 8.5 8.5 8.5 8.5 8.5 7.7 7.7 7.7 7.7 7.7 7.7 7.7 6.5 6.5 6.5 6.5 6.5 6.5 6.5
Tensile strwgth MPa ksI
At roomtemperaluN after heaIlng YIeld strmgth MPa ksi
Elongation, 'I
485 485
70 70
450 450
65 65
8 8
485 485 475 460
70 70 69 67
450 440 435 405
65 64 63 59
8 8 8 8
485 485 485 470 455 405
70 70 70 68 66 59
450 450 435 420 400 305
65 65 63 61 58 44
8 8 8 8 8 10
475 460 435 395 290
69 67 63 57 42
435 405 370 305 165
63 59 54 44 24
8 8 8 9 12
470 425 370 290 215
68 62 54 42 31
425 360 275 170 90
62 52 40 25 13
8 8 10 12 18
455 385 290 235 195
66 56 42 34 28
400 295 170 110 83
58 43 25 16 12
9 10 12 17 22
340 270 240 215 185
49 39 35 31 27
230 130 105 83 76
33 19 15 12 11
10 13 17 22 22
275 255 235 205 185
40 37 34 30 27
130 105
19 15 13 12 11
13 18 22 22 22
90 83 76
Wrought Aluminum and Aluminum Alloys /173
2218 Chemical Composition. Composition Limits. 0.90 Si max, 1.00 Fe max, 3.50 to 4.50 cu. 0.20 Mn max, 1.2 to 1.8 Mg, 0.10 Cr max, 1.70 to 2.30 Ni, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al
temperature as rapidly as possible and with minimum delay after removal from furnace. Nominal metal temperatures listed should be attained as rapidly as possible, and maintained within ±6 °C (±1O OF) of nominal during time at temperature. Quenching is in 100°C (212 OF) water
Specifications (U.S. and/or Foreign). AMS. Forgings and forging stock: 4142; SAE. 1454; UNS. A92218; Government. Forgings and forging stock: QQ-A-367; (France) NFA-U4N; (Spain) UNEL-315; (Switzerland) USM AI-Cu-Ni
Precipitation Heat Treating (Artificial Aging). Forgings are treated at a nominal metal temperature of 170°C (340 "F) for approximately 10 h to obtain T61 temper. The T72 temper is obtained in 6 h at.a metal temperature of240 °C (460 OF). Nominal treatment temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O OF) of nominal during time at temperature
Available Product Forms. Die forgings
Characteristics An Al-Cu-Mg alloy
Typical Uses. Pistons for aircraft and diesel engines; cylinder heads for aircraft engines; impellers for jet engines; compressor rings
Recommended Heat Treating Practice Solution Heat Treating. Forgings are treated to T4 at a metal temperature of 510 °C (950 OF). Material should be quenched from solution treating
2218 Aluminum. 2218-T61 closed-die forging, solution heat treated and artificially aged. Fine, recrystallized structure. The dark particles of insoluble FeNiAlg phase show banding, which resulted from the working during forging. Keller's reagent. 100x
2218 Aluminum: Tensile properties of 2218-T61 Temperature OF
°C
-195 -80 -30 25 100 150 205 260 315 370
Tensile strength(a) MPa ksi
-320 -112 -18 75 212 300 400 500 600 700
495 420 405 405 385 285 150 70 40 30
Yield strength(a) MPa ksi
72.0 61.0 59.0 59.0 56.0 41.0 22.0 10.0 5.5 4.0
360 310 305 305 290 240 110 40 20 17
52.0 45.0 44.0 44.0 42.0 35.0 16.0 6.0 3.0 2.5
Elongation, %
15 14 13 13
15 17 30 70 85 100
(a)Loweststrengthdetermined forrepresentative lotduring10 000hexposureat temperature under no load
2218 Aluminum: Creep-rupture properties of 2218·T61 plate Temperature
'TIme under
OF
stress,h
100 150
212 300
205
400
315
600
Up to 1000 0.1 1 10 100 1000 0.1 1 10 100 1000 0.1
°C
I
10 100
Stress forcreepof Rupture stress MPa ksl
MPa
ksi
MPa
ksi
MPa
ksl
MPa
ksi
385 360 350 350 330 290 325 310 255 185 115 55 48 45 27
350 345 340 325 290 315 305 250 180 110 52 48 41 23
51.0 50.0 49.0 47.0 42.0 46.0 44.0 36.0 26.0 16.0 7.5 7.0 6.0 3.4
330 325 315 310 290 290 275 240 170 105 48 45 47 21
48.0 47.0 46.0 45.0 42.0 42.0 40.0 35.0 25.0 15.0 7.0 6.5 6.9 3.0
315 310 305 295 270 275 260 220 140 105 45 41 34 14
46.0 45.0 44.0 43.0 39.0 40.0 38.0 32.0 20.0 15.0 6.5 6.0 5.0 2.1
290 285 275 230 140 255 235 160 105
42.0 41.0 40.0 33.0 20.0 37.0 34.0 23.0 15.0
41 38 21
6 5.5 3.0
56.0 52.0 51.0 51.0 48.0 42.0 47.0 45.0 37.0 27.0 17.0 8.0 7.0 6.5 3.9
0.5%
1.0%
0.1%
0.2%
174 I Heat Treater's Guide: Nonferrous Alloys
2219, Alclad 2219 Chemical Composition. Composition Limits (2219). 0.20 Si max, 0.30 Fe max, 5.6 to 6.8 Cu, 0.20 to 0.40 Mn, 0.02 Mg max, 0.10 Zn max, 0.05 to 0.15 V, 0.02 to 0.10 Ti, 0.10 to 0.25 Zr, 0.05 others max (each), 0.15 others max (total), bal AI Composition Limits (Alclad 2219). 7072 cladding-0.l0 Cu max, 0.10 Mn max, 0.70 Si max + Fe, 0.80 to 1.3 Zn, 0.10 Mg max, 0.05 others max (each), 0.15 others max (total) Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4031. Extruded wire, rod, bar, shapes, and tubing: 4162, 4163. Forgings: 4143, 4144. Alclad 2219, sheet and plate: 4094,4095,4096; ASTM. Sheet and Plate: B 209. Rolled or cold fmished wire, rod, and bar: B 211. Extruded wire, rod, bar, shapes, and tubing: B 221. Extruded, seamless tubing: B 241. Forgings: B 247. Alclad 2219, sheet and plate: B 209; SAE. J474; UNS. A92219; Government. Sheet and plate: QQ-A-250/30. Forgings: QQ-A-367, MIL-A-22771. Armor plate: MIL-A-46118. Rivet wire and rod: QQ-A-430; (France) NFA-U6MT; (United Kingdom) DTD 5004 Available Product Forms. Flat sheet; plate; forgings; rolled or cold finished wire, rod and bar; extruded rod, bar, shapes, and tubing; Alclad sheet and plate; die and hand forgings, and rolled rings
Characteristics An AlCu alloy without Mg alloying Typical Uses. Useful at service temperatures ranging from -270 to +300 °C (-450 to +570 "F); has high fracture toughness; T8 temper is highly resistant to stress corrosion cracking; is readily weldable. Applications include welded space booster oxidizer and fuel tanks; skin and structural components for supersonic aircraft.
For more information on resistance to corrosion, machinability, brazeability, and weldability see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Precipitation Heat Treating. Nominal metal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±IO OF) of nominal during time at temperature.
Approximate times at temperature, per product and temper, are as follows: • Flat sheet to T62 temper, 36 h, at 190°C (375 "F) • Plate to T81, T87, T851 tempers, 18 h, 175°C (345 "F) plate to T62 temper, 36 h, at 190°C (375 oF) • Rolled or cold fmished wire, rod, and bar to T851 temper, 18 h, at 190 °C (375 OF) • Extruded rod, bar. shapes, and tubing: For 851, T81, T851O, and T8511 tempers, 18 h, at 190°C (375 OF); For T62 temper, 36 h, at 190°C (375 OF) • Die forgings and rolled rings to T6 temper, 26 h, at 190°C (375 "F) CD Hand forgings to T6 temper, 26 h, at 190°C (375 "F); Hand forgings to T852 temper, 18 h, at 175°C (345 OF) Special considerations include:
• Some products and tempers require cold working subsequent to solution treating and prior to precipitation treatment to get the properties provided by a given temper. They include: Flat sheet for T81 and T87 tempers; plate for T81 and T87 tempers; and extruded rod, bar, shapes, and tubing for T81 temper • Some products and tempers must be stress relieved by stretching to produce a specified amount of permanent set subsequent to solution treating and prior to precipitation treatment. They include: Plate for T851 temper; rolled or cold finished wire, rod, and bar for T81 and T87 tempers; and extruded rod, bar, shapes, and tubing forT851, T851O,and T8511 tempers
Recommended Heat Treating Practice
In addition, hand forgings must be stress relieved by 1 to 5% cold reduction after solution treatment and prior to precipitation treatment to obtain T852 temper
All heat treatments that follow apply to Alclad sheet and plates
Annealing. Parts are annealed at 415°C (775 OF)
Solution Heat rreating. Flat sheet; plate; rolled or cold finished wire, rod, and bar; extruded rod, bar, shapes and tubing; die forgings; rolled ring; and hand forgings are treated toT4, T31, TI7, T42, T351, T352, andT3510 tempers at a nominal metal temperature of 525°C (970 OF).
2219 Aluminum: Typical tensile properties at varioustemperatures
Material should be quenched from solution treating temperature as rapidly as possible with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled in a manner so its temperature remains below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here for solution treatment are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±IO "F) during time at temperature.
Thmpemture 'Iemper
762
OF
-196
-320 -112 -18 75 212 300 400 500 600 700 -320 -112 -18 75 212 300 400 500 600 700
~O
Special considerations include:
• Cold working subsequent to solution treating and prior to any precipitation treatment is necessary to obtain desired properties for a given temper for the following: Flat sheet for TIl and T37 tempers; Plate for T37 temper; Rolled or cold finished wire, rod, and bar for TIl temper; Hand forgings for TI52 temper • Stress relief by stretching is necessary to produce a specified amount of permanent set subsequent to solution treating and prior to precipitation treatment to obtain desired properties for a given temper for the following: Plate for TI51 temper; Rolled or cold finished wire, rod, and bar for T temper; Extruded rod, bar, shapes, and tubing for 3510 and TI511 tempers; Hand forgings for T352 temper
°C
T81,T851
-28 24 100 149 204 260 316 371 -196 ~O
-28 24 100 149 204 260 316 371
ThIlSUe strength(a) MPa ksi 503 434 414 400 372 310 234 186 69 30 572 490 476 455 414 338 248 200 48 30
73 63 60 58 54 45 34 27 10 4.4 83 71 69 66 60 49 36 29 7 4.4
Yield strength (0.2 % offset)(a) MPa ksi 338 303 290 276 255 227 172 133 55 26 421 372 359 345 324 276 200 159 41 26
49 44
42 40
37 33 25 20 8 3.7 61 54 52 50 47 40 29 23 6 3.7
Eloogatioo, %
16 13 12 12 14 17 20 21 40 75 15 13 12 12 15 17
20 21 55 75
(a)Loweststrengthforexposuresup 10 10 000h atternperatureundernoload; testloadappliedat35 MPalmin(5 ksi/min) 10 yield strengthand thenat strainrate of 5%/minto fracture
Wrought Aluminum and Aluminum Alloys /175 2219 Aluminum: Tensile-property limits 'finsile slreogtb (min) MPa lui
'fimper
Sheet and plate 0 AlcladO 1'31(h) 0.020-0.039 in.thick 0.040-0.249 in.thick Alc1ad1'31(h) 0.040-0.099 in. thick 0.100-0.249 in.thick 1'351(c) 0.250-2.000 in.thick 2.100-3.000 in.thick 3.100-4.000in. thick 4.100-5.000 in.thick 5.001-6.000 in.thick Alc1ad1'351(c) 1'37 0.020-0.039 in.thick 0.040-2.500 in.thick 2.501-3.000 in.thick 3.001-4.000in.thick 4.001-5.000 in. thick Alc1ad1'37 0.040-0.099 in.thick 0.100-0.499 in.thick T62 AlcladT62 0.020-0.039 in.thick 0.040-0.099 in. thick 0.100-0.499 in.thick 0.500-2.000in. thick(c) 1'8I(h) Alclad1'81(h) 0.020-0.039 in. thick 0.040-0.099in. thick 0.100-0.249 in. thick T851(d) 0.250-2.000in. thick 2.001-3.000 in. thick 3.001-4.000 in.thick 4.001-5.000 in.thick 5.001-6.000in. thick Alclad 1'85l(d) T87 0.020-0.249 in. thick 0.250-3.000in. thick 3.001-4.000in. thick 4.001-5.000in.thick Alclad1'87 0.040-0.099 in. thick
220(max) 32 (max) 220(max) 32 (max)
Yield.treogtb(min) lui MPa
Elongation (a), '.l>
110(max) 16(max) 110(max) 16(max)
12 12
315 315
46 46
200 195
29 28
8 10
290 305
42
170 180
25 26
10 10
315 305 290 275 270 305
46 44
44
195 195 185 180 170 180
28 28 27 26 25 26
10 10 9 9 8 10
340 340 325 310 295
49 49 47 45 43
260 255 250 240 235
38 37 36 35 34
6 6 6 5 4
310 325 370
45 47 54
235 240 250
34 35 36
6 6 6-8
305 340 350 370 425
44
49 51 54 62
200 220 235 250 315
29 32 34 36 46
6 7 7-8 7-8 6-7
340 380 400
49 55 58
255 285 295
37 41 43
6 7 7
425 425 415 405 395 400
62 62 60 59 57 58
315 310 305 295 290 290
46 45 43 42 42
7-8 6 5 5 4 8
440 440 425 420
64 64 62 61
360 350 345 340
52 51 50 49
5-6 6-7 4 3
395
57
315
46
6
44
42 40 39
44
'fiosUe.lreogtb(min) Temper
MPa
ksi
60 0.100-0.499 in. thick 415 Wire, rod, and bar (rolled or cold finished) 1'851 58 0.500-2.000in.thick 400 orindiam 2.001-4.000 in. thick 395 57 orindiam Wire, rod, bar, and sbapes (extruded) 0 221 (max) 32 (max) 1'31,1'3510,1'3511 42 Up thru 0.499in. thick 290 orindiam 0.500-2.999 in. thick 310 45 orindiam T62 54 370 1'81,1'8510,1'8511 58 400 Extruded tube 0 220 (max) 32 (max) 1'31,1'3510,1'3511 42 290 Up thru 0.499 in.thick orindiam 0.500-2.999 in. thick 45 310 or in diam T62 54 370 1'81,1'8510,1'8511 58 400 Die forgings T6 58 Specimenaxis parallel 400 10grainflow 56 Specimenaxis not 385 parallelto grainflow Hand forgings(g) T6 58 Longitudinal axis 400 380 55 Longtransverseaxis Shorttransverseaxis 365 53 Mechanical property limits 1'852 62 Longitudinal axis 425 62 Longtransverseaxis 425 Shorttransverseaxis 415 60 Rolled rings(h) T6 Tangential axis 385 56 55 Axialaxis 380 Radialaxis 365 53
YieldstreDglb (min)
MPa
Elongation (a),
ksi
'.l>
330
48
6-7
275
40
4
270
39
4
125(max) 18(max)
12
180
26
14
185
27
14
250 290
36 42
6 6
125(max) 18(max)
12
180
26
14
185
27
14
250 290
36 42
6 6
260
38
8(e)(0
250
36
4(e)
275 255 240
40 37 35
6 4 2
345 340 315
50 49 46
6 4 3
275 255 240
40 37 35
6 4 2
(a) In 50 mm (2 in.) or 4d, where d is diameterof reducedsectionof tensiletestspecimen. Wherea range of valuesappearsin thiscolumn,specified minimumelongation varieswiththickness of the mill product.(h)Sheetonly.(c)Forplate 12.7mm(0.500in.)orgreaterinthickness, property limitsapplytocorematerialonly.Tensileandyieldstrengthsofcomposite~Iateslightly lowerdependingonthickness ofcladding.(d)Plateonly.(e)Specimentakenfromforging. (0 10%forspecimentakenfromseparately forgedcoupon.(g)Maximumcross-sectional area1650cm (256in.\ Theseproperties notapplicable to upsetbiscuitforgings orrolled rings.(h) Onlyapplicableto ringshavingratioof outsidediameterto wallthickness equal to or greaterthan 10
2219 Aluminum: Typical tensile properties 'Iensile
Yield
Temper
strengtb MPa ksi
strengtb ksi MPa
0 T42 1'31,1'351 1'37 T62 1'81,1'851 1'87
172 359 359 393 414 455 476
76 186 248 317 290 352 393
25 52 52 57 60 66 69
11 27 36 46
42 51 57
Elongation, '.l>
18 20 17 11 10 10 10
176 I Heat Treater's Guide: Nonferrous Alloys
2219 Aluminum: Time-temperature-property diagram. Treatment: SequenceA = Specimenswere quenched directly into a salt bath at 250 to 475°C (480 to 885 OF); Sequence B = Specimenswere first quenchedto room temperature, then heated in the salt bath. All speclmens were quenched in cold water to complete the sequencesafter hold times of 2 s to 1 h, stretched to.5% plastic strain, and then aged for 16 h at 170°C (340 OF). C-curve for 2219-T87 of 370 MN m-2 yield strength
500 ,-------.-"7""""--=----r----,-------.
LIVE GRAPH Click here to view
,-,400 o
-
'"=>
.." 0'" E '" t - 300
200 L.-_ _---l.. 10 1
~------l-:-----=:.----..:b:-----I
10 2 Critical time, S
2219 Aluminum. Rotating beam fatigue data of 7039 plate compared with fatigue characteristics of 2014 and 2219. Data for 7039 are
based on least-of-four results in the longitudinal direction with a 7.5 mm (0.3 in.) diam smooth specimen. Curves for 2014 and 2219 are mean values from publishedliterature 400
LIVE GRAPH
I
I
Rotating beam tests
Click here to view 350
300
~ \). \
250
.. ~"-
, X1"-.,.~ " • ~ "-
III
a.
::i: - 200
7039-T61
~
-,
'-..:,:::: ............... ......
150
. -- ---
o 0 ~ I-h..r. - ..........-
2219-T81 100
............
.....
"1 ~
...... ....
-~
--.~-
~
.....
~::l./
o
T64 36 mm plate • T61 19 mm plate
I Cycles
40
00-0
20
-
2014-T6 50 f - - - -
-
-
00
....
/~
50
70?-T64
la
-,
"- "-
-
_
10
Wrought Aluminum and Aluminum Alloys 11n 2219 Aluminum: Creep-rupture properties of 2219-T87 plate Temperature °C
OF
Time under stress,h
24
75
100
212
0.1 1 10 100 1000 0.1
300
10 100 1000 0.1
I
150
I
205
400
230
450
260
500
315
600
10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10. 100 1000 0.1 I
370
700
10 100 1000 0.1 1 10 100 1000
SlressCor creepoC 0.1%
Rupturestress MPa ksi
MPa
ksi
MPa
ksl
MPa
ksl
MPa
ksl
460 455 450 435 420 400 380 350 330 315 345 315 290 260 235 255 230 205 180 150 206 185 170 150 130 170 160 145 125 105 115 105 90 62 34 59 48 34 23 17
450 425 405 395 380 365 345 330 315 305 315 295 275 250 230 240 215 185 165 145 195 170 160 140 125 160 145 130 115 105 110 105 83 55 31 55 45 30 20 13
65 62 59 57 55 53 50 48 46 44 46 43 40 36 33 35 31 27 24 21 28 25 23 20 18 23 21 19 17 15 16 15 12 8 4.5 8 6.5 4.4 2.9 1.9
420 400 385 380 370 350 340 325 310 295 310 290 260 235 205 230 200 170 145 130 180 165 145 125 115 150 140 125 110 97 105 97 76 52 28 52 41 26 17
61 58 56 55 54 51 49 47 45 43 45 42 38 34 30 33 29 25 21 19 26 24 21 18 17 22 20 18 16 14 15 14 11 7.5 4 7.5 6 3.8 2.5 1.6
385 380 370 365 360 340 325 305 290 260 290 260 235 200 165 200 165 140 115 97 165 140 115 105 83 140 125 105 90 69 97 83 62 45 26 48 32 17
56 55 54 53 52 49 47 44 42 38 42 38 34 29 24 29 24 20 17 14 24 20 17 15 12 20 18 15 13 10 14 12 9 6.5 3.8 7 4.7 2.4 1.6 1.2
370 365 360 350 345 325 310 290 260 240 270 240 205 165 140 165 140 110 97 83 140 115 97 83 69 125 105 83 69 59 83
54 53 52 51 50 47 45 42 38 35 39 35 30 24 20 24 20 16 14 12 20 17 14 i2 10 18 15 12 10 8.5 12 9.5 7.5 5 3.3 5 2.6 1.7 1.2 0.9
67 66 65 63 61 58 55 51 48 46 50 46 42 38 34 37 33 30 26 22 30 27 25 22 19 25 23 21 18 15 17 15 13 9 5 8.5 7 5 3.4 2.4
1.0%
0.5%
II
0.2%
II
8
66
52 34 23 34 18 12 8 6
2219 Aluminum: Microstructures. (a) 2219-T6 closed-die forging, solution heat treated and artificially aged. Longitudinal section. Worked structure contains some recrystallized grains. See adjoining figure for a totally unrecrystallized structure. Keller's reagent. 100x (b) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled 2219-T6 closed die forging, solution heat treated and artificially aged. Longitudinal section shows no recrystallization of the worked structure. Note the large amount of slip (light parallel lines) that has occurred on two sets of slip planes. Keller's reagent. 100x
(a)
(b)
178 I Heat Treater's Guide: Nonferrous Alloys
2219 Aluminum: Creep-rupture properties of 2219-T851 plate 'Il>mperature
TUne under
of
stress,h
24
75
100
212
0.1 1 lO 100 lOoo 0.1 1 10 100 lOoo 0.1 1 10 100 lOoo lO,ooo 100,000 0.1 1 10 100 1000 lO,ooo 100,000 0.1 1 100 1000
°C
150
175
205
300
350
400
mooo
230
260
315
370
450
500
600
700
100,000 0.1 1 lO 100 1000 lO,ooo 100,000 0.1 1 10 100 1000 lO,ooo 100,000 0.1 1 lO 100 1000 lO,ooo 0.1 1 10 100 1000
Stressfor creep of Ruplurestress MPa ksi
455 450 435 425 420 395 370 350 330 315 340 315 290 260 235 205 170 305 275 250 220 185 160 130 270 235 180 150 125 97 230 200 170 150 125 97 66, 180 165 150 130 lO5 69 45 130 lt5 lO5 69 41 22 69 62 32 22 14
-
0.2%
0.5%
1.0%
0.1%
MPa
ksi
MPa
ksi
MPa
ksI
MPa
ksi
66 65 63 62 61 57 54 51 48 46 49 46 42 38 34 30 25
435 420 400 380 365 360 340 325 3lO 295 305 290 270 250 220
63 61 58 55 53 52 49 47 45 43
60 56 53 52 51 49 47 45 43 41 43 40 37 34 29
365 360 345 340 330 315 305 290 275 270 275 255 235 200 165
53 52 50 49 48 46 42 40 39 40 37 34 29 24
350 345 330 325 315 305 285 275 270 260 260 235 205 170 150
51 50 48 47 46
42 39 36 32
415 385 365 360 350 340 325 3lO 295 285 295 275 255 235 200
44
275 255 230 200 170
40 37 33 29 25
260 240 215 185 160
38 35 31 27 23
250 220 195 160 140
36 32 28 23 20
230 200 165 130 lO5
33 29 24 19 15
240 220 165 140 125
35 32 24 20 18
235 205 150 125
34 30 22 18
215 180 130 lt5
31 26 19 17
195 160 ltO
28 23 16 13
205 185 160 140 lt5
200 170 150 130 ltO
26 22 19 16 13
165 140 ltO
97
29 25 22 19 16 14
180 150 130 ltO 90
97
30 27 23 20 17 14
170 160 140 125 97 69
25 23 20 18 14 10
165 150 130 110 83
24 22 19 16 12
160 140 ltO 90 69
23 20 16 13 lO
145 115
125 115 97 69 41
18 17 14 lO 6
125 110 90 62 38
18 16 13 9 5.5
lt5 lO5 76 52 28
17 15
ltO
It
62 38 23
16 13 9 5.5 3.4
lO 9 4.3 2.9 1.9
69 59 27 18
lO 8.5 3.9 2.6 1.6
66 45 23 13
66 32 18
9.5 4.7 2.6
40 36 32 27 23 19 39 34 26 22 18 14 33 29 25 22 18 14 9.5 26 24 22 19 15 lO 6.5 19 17 15 lO 6 3.2 10 9 4.7 3.2 2.1
69 62 30 20
13
44
It
44
7.5 4.1 9.5 6.5 3.3 1.9
2319 Chemical Composition. Composition Limits. 5.80 to 6.80 Cu, 0.20 to 0040 Mn, 0.10 to 0.25 zr, 0.10 to 0.20 Ti, 0.05 to 0.15 V, 0.20 Si max, 0.30 Fe max, 0.02 Mg max, 0.10 Zn max, 0.0008 Be max, 0.05 others max (each), 0.15 others max (total)
Specifications (U.S. and/or Foreign). UNS. A92319. Government. QQ-A-566. MIL-E-16053
Characteristics Major alloying elements: 5.3Cu-0.3Mn-0.18Zr-0.lOV
Typical Uses. Electrode and filler rod for welding 2219
Recommended Heat Treating Practice Annealing.Temperature is 415°C (775 OF)
90
90 69
90 69 59
90
44 41 40 39 38 38 34 30 25 22
24 20 16 13 lO
21 17 13 lO 8.5
Wrought Aluminum and Aluminum Alloys /179
2618 Chemical Composition. Composition Limits. 0.10 to 0.25 Si, 0.90
Forgings and rolled rings are treated to T61 temper by heating them to 200 °C (390 OF) and maintaining that temperature for 20 h
to 1.30 Fe, 1.90 to 2.70 Cu, 1.30 to 1.80 Mg, 0.90 to 1.20 Ni, 0.10 Zn max, 0.040 to 0.10 Ti, 0.05 others max (each), 0.15 others max (total), bal Al
Specifications (U.S. and/or Foreign). AMS. Forgings and forging stock: 4132; ASTM. Forgings: B 247; SAE. J454; Government. Forgings: QQ-A-367; MIL-A-22771; (France) NFA-U2GN; (United Kingdom) BS H12
2618 Aluminum: Tensile properties of 2618-T61
Available Product Forms. Forgings and rolled rings
Characteristics
'IYpical Allproducts Property limits Dieforgings.thickness91 in.(c) Axis parallelto grainflow Axisnotparalleltograinflow Handforgings Thickness$2.000 in.(c)(O Longitudinal Long transverse Short Iransverse 2.001-3.000 in. Longitudinal Long transverse Short transverse 3.001-4.000in. Longitudinal Long transverse Short transverse Rolledrings.thicknessg.5oo in.(g) Tangential Axial
An AI-Cu-Mg-Si alloy
Typical Uses. For elevated temperature service, such as die and hand forgings for pistons and rotating, aircraft engine parts, tire molds, and rolled rings
Recommended Heat Treating Practice Solution Heat Treating. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. Quenching is by total immersion in water, unless otherwise indicated. Water should be at room temperature and cooled so that its temperature remains below 38°C (100 OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here for solution treatment are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±1OOF) during time at temperature. To obtain T4 temper, parts are treated at 530°C (985 OF)
y.,ld strength MPa ksI
'Ienslle strength MPa ksi
Product andorientation
E1ongation(a), %
440
64
372
54
1O(b)
400 380
58 55
310 290
45 42
4(d)(e) 4(d)
400 380 360
58 55 52
325 290 290
47 42 42
7 5 4
395 380 360
57 55 52
315 290 290
46 42 42
7 5 4
385 365 350
56 53 51
310 275 270
45 40 39
7 5 4
380 380
55 55
285 285
41 41
6 5
(a) In 50 rnm (2 in.) or4 d. where d is diameterof reducedsectionof tensiletest specimen. (b) 12.5 nun (0.5 in.) diameter specimen.(c) Propertiesalso apply to forgingsmachined prior 10 heat treatment, providedmachinedthicknessis notless than half of original(as-forged)thickness.(d) Specimen takenfrom forgings.(e)Elongation6% minforspecimentakenfromseparatelyforgedcoupon. (0 Maximum cross-sectional area 930 cm2 (I fe). Not applicable to upset biscuit forgings or to rolled rings. (g) Applicableonly to rings having ratio of outsidediameter 10 wall thicknessequal to or greaterthan 10
Precipitation Heat Treating (Artificial Aging). Temperatures given here are nominal and time at temperature is approximate. Specific times depend on time needed for load to reach temperature. Soak times are measured from time load reaches a temperature of 6 °C (10 OF) of applicable temperature.
2618 Aluminum: Creep-rupture properties 'Iemperature
°C
OF
150
300
177
350
205
400
260
500
315
600
Stressforcreepof
Time under stress.h
Rupture.tress MPa ksi
MPa
ksi
MPa
ksi
MPa
ksi
MPa
ksi
0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000 0.1 I 10 100 1000
380 360 340 305 255 340 310 285 250 205 290 260 230 195 160 185 165 140 105 62 97 69 52 32 20
345 340 325 305 255 325 305 275 240 200 285 255 220 185 150 170 150 130 97 62 83 62 45 28 17
50 49 47 44 37 47 44 40 35 29 41 37 32 27 22 25 22 19 14 9 12 9 6.5 4.1 2.5
345 330 315 290 250 315 295 260 235 195 270 250 215 180 145 165 145 125 90 55 69 55 41 26 14
50 48 46 42 36 46 43 38 34 28 39 36 31 26 21 24 21 18 13 8 10 8 6 3.7 2.1
330 315 295 270 240 295 275 250 220 185 255 235 200 165 130 160 140 110 69 48 55 45 38 19
48 46 43 39 35 43 40 36 32 27 37 34 29 24 19 23 20 16 10 7 8 6.5 5.5 2.8
315 290 270 240 205 285 255 220 185 150 240 205 170 140 90 145 115 83 52
46 42 39 35 30 41 37 32 27 22 35 30 25 20 13 21 17 12 7.5
48 41 26 15
7 6 3.8 2.2
55 52 49 44 37 49 45 41 36 30 42 38 33 28 23 27 24 20 15 9 14 10 7.5 4.6 2.9
1.0%
0.5%
0.1%
0.2%
180 I Heat Treater's Guide: Nonferrous Alloys
2618 Aluminum: Microstructures. (a) 2618-T4 closed-die forging, solution heat treated at 530°C (985 OF) for 2 h, quenched in boiling water. Small particles of CuMgAI2 precipitated at grain boundaries; larger particles are insoluble FeNiAlg phase. 0.5% HF. 500x. (b) 2618-T4 forging, solution heat treated at 530°C (985 OF) for 2 h and cooled in still air. Slower cooling resulted in an increase of CuMgAI2 at grain boundaries and within grains. 0.5% HF. 500x. (c) 2618-T61 forging, solution heat treated, quenched in boiling water, aged at 200°C (390 OF) for20 h, stabilized at230 °C (450 OF) for? h. CuMgAI2 has also precipitated in grains. 0.5% HF.500x. (d) 2618-T61 forging, solution heat treated, cooled in still air, aged. Note increase in precipitation and alloy depletion near light grain boundaries. 0.5% HF. 500x
(b)
(a)
(c)
(d)
2618 Aluminum: Typical tensile properties of 2618-T61 at various temperatures Yieldstrength Temperature of -c
Tensile strength MPa ksi
(0.2 % offset) MPa ksi
-196 -80 -28 24 100 149 204 260 316 371
538 462 441 441 427 345 221
421 379 372 372 372 303 179 62 31 24
-320
-112 -18 75 212 300 400 500 600 700
90 52 34
78.0 67.0 64.0 64.0 62.0 50.0 32.0 13.0 7.5 5.0
61.0 55.0 54.0 54.0 54.0 44.0 26.0 9.0 4.5 3.5
Elongation,
%
12 11 10 10 10 14 24 50 80 120
3003, Alclad 3003 Chemical Composition. Composition Limits (3003). 0.60 Si max, 0.70 Fe max, 0.05 to 0.20 Cu, 1.00 to 1.50 Mn, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total) Composition Limits (Alclad 3003). 7072 cladding-O.lO Cu max, 0.10 Mg max, 0.10 Mn max + Si, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total) Specifications (U.S. and/or Foreign). AMS. (See adjoining table); ASME. (See adjoining table); ASTM. (See adjoining table); SAE. J454; UNS. 3003: A93003; Government. (See adjoining table); (Canada) CSA MClO; (France) NFA-Ml; (United Kingdom) BS N3; (Germany) DIN AIMn.lSO: AIMnlCu Available Product Forms. Include sheet, plate, drawn and extruded tubing, pipe, extruded wire, rod, bar, and shapes, rolled or cold-finished rod, bar, wire, rivets, forgings and forging stock, foil, and fin stock
Characteristics Major alloying elements: 1.2Mn-0.12Cu
Typical Uses. Used mainly where good formability, very good resistance to corrosion, or good weldability (or all three) are required. Also has more strength than unalloyed aluminum. Applications include cooking utensils, food and chemical handling, and storage equipment, tanks, trim for transportation equipment, lithographic sheet pressure vessels, and piping. Tempers include 0, H12, H14, H16, H18, and H25. Farm roofing and siding are typical uses for Alclad 3003. For more information on resistance to corrosion, machinability, brazeability, and weldability per alloy and temper see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Commercial practice is to treat at 400 to 600 °C (750 to 1110 OF). Higher temperatures are only used for flash annealing
Wrought Aluminum and Aluminum Alloys /181
3003 Aluminum: Mechanical properties
Thmper
'lYpica\ properties 0 H12 H14 H\6 H18 Property limits 0(0.006-3.000 in. thick) H12(0.017-2.000 in. thick) H14(0.009-1.000 in. thick) HI6 (0.006-{).162 in. thick) H18(0.006-0.128 in. thick) H1l2 (0.250-0.499in. thick) (0.500-2.000in. thick) (2.000-3.000in. thick) Property limits, AI.lad 3003(.) 0(0.006-0.499 in. thick) (0.500-3.000in. thick) H12 (0.017-0.499in. thick) (0.500-2.000in. thick) H14 (0.009-0.499in. thick) (0.500-2.000in. thick) H16 (0.006-0.162 in. thick) H18(0.006-0.128 in. thick) HI12 (0.250-0.499in. thick) (0.500-2.000in. thick) (2.000-3.000in. thick)
MPa
ThnsUe strength Iosl MPa
Yieldstrength ksI MPa
Elongation,
42 6 18 125 145 21 25 175 27 185 Minimum
30-40 10-20 8-16 5-14 4-10
27
83 115 145 165
5 12 17 21 24
14-25 3-10 1-10 1-4 1-4
17 15 14.5
69 41 41
10 6 6
8 12 18
110 16 19 130 150 22 175 25 200 29 Minimum 97 115 140 165 . 185 115 105 100
14 17 20
24
ksI
Maximum 130 160 180 205
19 23 26 30
34
90 97
13 14
125 130
18 19
31 34
110 115
16 17
150 160
22 23
83
11 12
4-9 10
130 140 160 180
19 20 23 26
170 180 200
25 26 29
110 115 140
16 17 20
1-8 10 1-4 1-4
110 105 100
16 15 14.5
62 41 41
9 6 6
8 12 18
n
4.5 5.0
~
Hanlneoo RB(a) HR
28 35 40 47 55
45-65 55-75 70-90 75-92 84-95 Minimum
Shear streugtb MPa IIsI
76 83
97 105 110
11 12 14 15 16
FatIgue I!reD&Ih(b) MPa IIsI
48 55 62 69 69
7 8 9 10 10
14-25 23
(a)500 kg load, 10mm ball, 30 s durationofloading. (b) At5 x 108 cycles.RR Moore type test.(c) Mechanicalpropertiesof 3003clad with7072 are practicallythe same as for bare material, except that hardnessand fatigueresistancetend to be slightly lowerfor the cladproduct
182 I Heat Treater's Guide: Nonferrous Alloys
3003 Aluminum: Microstructures. (a) 3003-0 sheet, annealed. Longitudinal section shows recrystallized grains. Grain elongation indicates rolling direction, but not the crystallographic orientation within each grain. Polarized light. Barker's reagent. 100x. (b) 3003-0 sheet, annealed. Same as adjoining microstructure, but shown at a higher magnification. Dispersion of insoluble particles of (Fe,Mn)Al s (large) and aluminum-manganese-silicon (both large and small) was not changed by annealing. 0.5% HF.750x
(a)
(b)
3003 Aluminum: Microstructures. 3003-F sheet, hot rolled. Longitudinal section shows stringer of oxide from an inclusion in the cast ingot and particles of phases that contain manganese, both primary (large, angular) and eutectic (small). As-polished. 500x
3004, Alclad 3004 Chemical Composition. Composition Limits (3004). 0.25 Cu max, 0.30 Si max, 0.70 Fe max, 1.00 to 1.50 Mn, 0.80 to 1.30 Mg, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Composition Limits (Alclad 3004). 7072 cladding-Q.lO Cu max, 0.10 Mg max, 0.10 Mn max, 0.7 Fe max + Si, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. 3004: sheet and plate, B 209; extruded tubing, B 221; welded tubing, B 313, B 547. Alclad 3004: sheet and plate, B 209; welded tubing, B 313; culvert pipe, B 547; SAE. J 454; UNS. A93004; Government: culvert pipe. WW-P-402; (Australia) A 3004; (France) NFA-MIG; (Germany) DIN AIMnlMgl Available Product Forms. Sheet, plate, drawn tubing. Alclad: sheet and plate
Characteristics Major alloying elements: 1.2Mn-l.0Mg. Provides combination of good formability and higher strength than alloy 3003.
Typical Uses. Drawn and ironed rigid containers (cans). Chemical-handling and storage equipment, sheet metal work, builders' hardware, incandescent and fluorescent lamp bases. Alclad: siding, culvert pipe, industrial roofing. For more information on resistance to corrosion, cold workability, machining, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Product is treated at 415°C (775 OF)
Wrought Aluminum and Aluminum Alloys /183
3004 Aluminum: Mechanical properties Thmper
MPa
'IYpical properties 0 H32 H34 H36 H38 Property limits 0(0.006-3.000 in. thick) H32 (0.017-2.000 in. thick) H34 (0.009-1.000 in. thick) H36 (0.006-0.162 in. thick) H38 (0.006-0.128 in. thick) H112(0.250-3.000 in. thick) Property limits, Alclad 3004(c) 0 (0.006-0.499in. thick) (0.500-3.000in. thick) H32 (0.017-0.499in. thick) (0.500-2.000in. thick) H34 (0.009-0.499in. thick) (0.500-1.000in. thick) H36(0.006-0.162 in. thick) H38 (0.006-0.128 in. thick) H112 (0.250-0.499in. thick) (0.500-3.000in. thick)
ThnslJe strength MPa ksi
180 26 215 31 240 35 260 38 285 41 Minimum
ElongaUon,
ksi
Yield strength MPa ksi
20-25 10-17 9-12 5-9 4-6
Maximum
69 10 170 25 200 29 230 33 250 36 Minimum
%
150 195 220 240 260 160
22 28 32 35 38 23
200 240 260 285
29 35 38 41
59 145 170 195 215 62
8.5 21 25 28 31 9
10-18 1-6 1-5 1-4 1-4 7
145 150
21 22
195 200
28 29
55 59
8 8.5
10-18 16
185 195
27 28
235 240
34 35
140 145
20 21
1-6 6
215 220 235 255
31 32 34 37
255 260 275
37 38 40
165 170 185
24 25 27
1-5 5 1-4 1-4
150 160
22
59 62
8.5 9
7 7
23
Hardness, HB(a)
45 52 63 70 77
Fatigue strength(b)
Shearstrength MPa ksl
MPa
ksi
110 115 125 140 145
97 105 105 110 110
14 15 15 16 16
16 17 18 20 21
(a) 500 kg load, 10mm ball,30 s durationofloading. (b) At5 x 108 cycles,R.R.Moore type test.(c)Mechanicalpropertiesof 3004 clad with7072 are practicallythe sameas for bare material,exceptthat hardnessandfatigueresistancetend tobe slightlylowerfor the clad product
3004 Aluminum: Typical mechanical properties at various temperatures °C
Thmperalure OF
o temper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752 H34temper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752 H38lemper -200 -328 -100 -148 -30 -22 25 77 100 212 200 392 300 572 400 752
ThnslJestreogth(a) MPa ksi
Yield strength(a) MPa
Elongation,
ksi
%
290 200 180 180 180 96 50 30
42.5 29 26 26 26 14 7.2 4.4
90 80 69 69 69 65 34 9
13.2 11.5 10 10 10 9.5 4.9 2.8
38 31 26 25 25 55 80 90
360 270 245 240 240 145 50 30
52 39 36 35 35 21 7.2 4.4
235 212 200 200 200 105 34 19
34 31 29 29 29 15 4.9 2.8
26 17 13 12 12 35 80 90
400
58 45 42 41 40 22 7.2 4.4
295 267 245 245 245 105 34 19
43 39 36 36 36 15 4.9 2.8
20 10 7 6 7 30 80 90
310 290 280 275 150 50 30
(a) Loweststrengthsfor exposuresup to 10000 h at temperature, no load;test loadingappliedat 35 MPa/min(5 ksi/min) 10 yieldstrengthand thenat strainrate of 5%/minto fracture
184 I Heat Treater's Guide: Nonferrous Alloys
3105 Chemical Composition. Composition Limits. 0.60 Si max, 0.70 Fe max, 0.30 Cu max, 0.20 to 0.80 Mn, 0.20 to 0.80 Mg, 0.20 Cr max, 0.40 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. B 209; SAE. J 454 Available Product Forms. Sheet, in 0, H12, H14, H16, H18, and H25
Typical Uses. Residential siding, mobile home sheet, gutters and downspouts, sheet metal work, bottle caps, and closures. For information on resistance to corrosion, machinability, brazeability, and weldability see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
tempers
Recommended Heat Treating Practice
Characteristics
Annealing. Treatment temperature is 345°C (650 "F)
Major alloying elements: 0.55Mn-0.50Mg
3105 Aluminum: Mechanical properties of 3105 sheet Thmper
MPa
ThosUe strength ksi MPa
Shear strength ksI
Yieldstrength ksI
Elongation, %
MPa
55 8 19 130 150 22 25 170 195 28 23 160 Minimum
24 7 5 4 3 8
83 97 105 110 115 105
MPa
ksi
'Iypical properties
0 Hl2 H14 H16 Hl8 H25 Property limits
17 115 22 150 25 170 195 28 31 215 26 180 Minimum
0(0.013-0.080 in.thick) HI2 (0.017-0.080 in.thick) Hl4 (0.013-0.080 in.thick) HI6 (0.013-0.080 in.thick) HI8 (0.013-0.080 in.thick) H25(0.013-0.080 in.thick)
97 130 150 170 195 160
14 19 22 25 28 23
Maximum 145 180 200 220
34 105 125 145 165 130
21 26 29 32
12 14 15 16 17 15
16-20 1-3 1-2 1-2 1-2 2-6
5 15 18 21 24 19
4032 Chemical Composition. Composition Limits. 11.00 to 13.50 Si, 1.00 Fe max, 0.50 to 1.30 Cu, 0.80 to 1.30 Mg, 0.10 Cr max, 0.50 to 1.30 Ni, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al
Specifications (U.S. and/or Foreign). AMS. Forgings and forging stock: 4145; ASTM. Forgings: B247; SAE. J454; Government. Forgings: QQ-A-367; Foreign. (Canada) CSA SG121; (France) NF A-SI2UN; (Italy) UNI P-AISi12MgCuNi
4032 Aluminum: Fatigue strength of 4032-16 at various temperatures "C
Thmperature OF
24
75
150
300
Available Product Forms. Forgings and forging stock
Characteristics An Al-Cu-Mg-Si alloy for high temperature service
Typical Uses. Pistons and other parts that see high temperatures. For information on resistance to corrosion, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice
205
260
Solution Heat Treating. Heat to 500 to 515°C (930 to 960 OF), hold for 4 min at temperature, then quench in cold water. Quench heavy or complicated forgings in water at 65 to 100 °C (150 to 212 "F) Precipitation Heat Treating (Artificial Aging). Die forgings are heated to 170 to 175°C (340 to 345 OF), and held 8 to 12 h at temperature Annealing. Metal is heated to 415°C (775 "F); held for 2 to 3 h at temperature, then furnace cooled to 260°C (500 "F) at 25°C (50 OF) per hour max
400
500
No.of cycles
4
10 105 106 107 108 5x 108 105 106 108 8 sx 10 105 106 107 108 sx 108 105 106 107 108 sx 108
Stress(a)
MPa
lui
359 262 207 165 124 114 207 165
52 38 30 24 18 16.5 30 24 13 11.5
90
79 186 138 90
55 48 131
83 55 34 34
27 20
13 8 7 19 12 8 5 5
(a)Basedon rotatingbeamtestsat roomtemperatureandcantileverbeamtestsatelevatedtemperatures
Wrought Aluminum and Aluminum Alloys /185
4032 Aluminum: Creep-rupture properties StressCor creepoC: 'Thmperature OF °C
TImeunder stress,h
Rupture stress MPa ksi
MPa
lui
MPa
lui
100
0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000
331 317 303 296 296 290 276 269 248 207 234 214 186 138 83
283 283 283 276 276 276 269 255 241 200 228 207 179 131 76
41 41 41 40 40 40 39 37 35 29 33 30 26 19 11
269 262 262 262 255 248 241 234 221 186 221 200 165 124 69
39 38 38 38 37 36 35 34 32 27 32 29 24 18 10
212
150
300
205
400
48
46
44 43 43 42 40 39 36 30 34 31 27 20 12
0.2%
0.5%
1.0%
lui
MPa
138 131 103 59
20 19 15 8.5
4032 Aluminum: Typical mechanical properties of 4032-T6 at various temperatures -c
'Thmperature of
-200 -100 -30 25 100 200 300 400
'Thwile strength ksi MPa
-328 -148 -22 77 212 392 572 752
460 415 385 380 345 90 38 21
67
60 56 55 50 13 5.5 3.1
Yieldstrength MPa ksi
337 325 315 315 300 62 24 12
49 47
46 46 44 9 3.5 1.8
Elongation, 'lo
11 10 9 9 9 30 70 90
4043 Chemical Composition. Composition Limits. 4.50 to 6.00 Si, 0.80 Fe max, 0.30 Cu max, 0.05 Mn max, 0.05 Mg max, 0.10 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), 0.0008 Be max (welding electrode only), bal Al
Available Product Forms. Welding rod and electrodes
Major alloying element: 5.2 Si
Specifications (U.S. and/or Foreign). AMS. Bare welding rod and
Typical Uses. General purpose weld filler alloy (rod or wire) for welding
electrodes: 4190; SAE. J454; Government. Bare welding rod and electrodes: QQ-R-566, MIL-E-16053; spray gun wire: MIL-W-6712; (Australia) B 4043; (Canada)CSA S5; (France) NF A-S5; (United Kingdom) BS N21; (Germany) DIN AISi5, Werstoff-Nr. 3.2245
all wrought and foundry alloys (except those rich in magnesium)
Characteristics
Recommended Heat Treating Practice Annealing. Product is annealed at 350°C (660 "F)
5005 Chemical Composition. Composition Limits. 0.30 Si max, 0.70 Fe max, 0.20 Cu max, 0.20 Mn max, 0.50 to 1.10 Mg, 0.10 Cr max, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al
clearer and lighter than anodized 3003, and color match with 6063 architectural extrusions is better
Typical Uses. Electrical conductor wire, cooking utensils, appliances,
Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Wire, HI9 temper; B 396. Stranded conductor: B 397. Rivet wire and rod: B 316. Rolled rod: B 531. Drawn tubing: B 483; SAE. J 454; UNS. A95005; Government. Rivet wire and rod: QQ-A-430; (France) NFA00.6; (United Kingdom) B5 N41; (Germany) DIN AIMg1. ISO: AIMgI
Available Product Forms. Sheet, plate, wire and rod, conductor, tubing. Tempers include 0, H12, H14, H16, H18, H32, H34, H36, H38
Characteristics Major alloying element: 0.8 Mg. Medium strength and good resistance to corrosion are properties similar to those of Alloy 3003. Anodized 5005 is
and architectural uses. o
For more information on resistance to corrosion, cold workability, machinability, brazeability, and weldability see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Product is treated at 345°C (650 OF); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 "F)
186/ Heat Treater's Guide: Nonferrous Alloys
5005 Aluminum: Mechanical property limitsfor sheet and plate Y;eld
Thnsilestrength
Minimum
Maximum
strength (min) ksi MPa
Thmper
MPa
ksi
MPa
ksi
0
105 125 145 165 185 120 140 160 180
15 18 21 24 27 17 20 23 26
145 165 185 205
21 24 27 30
35 95 115 135
5 14 17 18
160 180 200
23 26 29
85 105 125
12 15 18
115 105 100
17 15 15
H12 H14 H16 H18 H32 H34 H36 H38 H1I2 0.250-0.492 in. thick 0.492-1.60in. thick 1.60-3.20in. thick
5005 Aluminum: Typical mechanicalproperties
Elongation (min)!a), %
12-22 2-9 1-8 1-3 1-3 3-10 2-8 1-4 1-4 8 10 16
Thmper
0 Hl2 Hl4 H16 H18 832 834 836 838
Thnsile strength(a) ksi MPa
124 138 159 179 200 138 159 179 200
18 20 23 26 29 20 23 26 29
Yield strength(a) MPa ksi
41 131 152 172 193 117 138 165 186
6 19 22 25 28 17
20 24 27
E1ongation(a)(b),
Hardness(c),
%
DB
25 10 6 5 4 11 8 6 5
28
Shear strength ksi MPa
76 97 97 103 110 97 97 103 110
36 41 46 51
11 14 14 15 16 14 14 15 16
(a) Strengths and elongationsunchanged or improved at low temperatures.(b) 1.6nun (0.0625 in.) thickspecimen. (c) 500 kg load; 10nun diam ball
(a) In 50 nun (2 in.) or 5d, where d is diameter or reduced section of tensiletest specimen.Where a range of values appears in this colunm, the specified minimum elongation varies with thicknessof the mill product
5050 Chemical Composition. Composition Limits. 0040 Si max, 0.70 Fe max, 0.20 Cu max, 0.10 Mn max, 1.10 to 1.80 Mg, 0.10 Cr max, 0.25 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASlM. Sheet and plate: B 209. Drawn, seamless tubing: B 210. Drawn tubing: B 483. Welded tubing: B 313, B 547; SAE. J454; UNS. A95050; (France) NFA-G1; (Italy) P-AlMg1.5; (Switzerland) AI1.5Mg; (United Kingdom) BS 3L44. ISO: AlMg1.5
Hot Working Temperature. Product is heated in range of260 to 510 °C (500 to 950 oF)
5050 Aluminum: Typical tensile properties Thmperalure
Available Product Forms. Sheet, plate, tubing, pipe, rod, bar, wire
"C
Characteristics
-196
-SO -28
Major alloying element: 1.4 Mg
Typical Uses. Builder's hardware, refrigerator trim, coiled tubes, tubing for auto gas and oil lines, welded irrigation pipe. For information on resistance to corrosion, cold workability, machinability, braze ability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
-SO
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 OF); holding at temperature is not required
5050 Aluminum: Tensile-property limits Thnsile strwgth (min) Thmper
MPa
ksl
o
125 150 170 185 200
18 22 25 27 29
H32 H34 836 838
Yield strength (min) MPa ksi
41 110 138 151
6 16 20 22
24 100 150 205 260 315 370 -196
Elongation (min)!a), %
16-20 4-6 3-5 2-4 2-4
(a) Wherea range of valuesappearsinthiscolunm,specified minimumelongation varieswith thickness of the mill product
-28 24 100 150 205 260 315 370 -196
-SO -28 24 100 150 205 260 315 370
OF
-320 -112 -18 75 212 300 400 500 600 700 -320 -112 -18 75 212 300 400 500 600 700 -320 -112 -18 75 212 300 400 500 600 700
Thnsilestrength(a) MPa ksi
Yield strength (0.2 % offset)!a) ksi MPa
255 150 145 145 145 130 95 60 41 27 305 205 195 195 195 170 95 60 41 27 315 235 220 220 215 185 95 60 41 27
70 60 55 55 55 55 50 41 29 18 205 170 165 165 165 150 50 41 29 18 250 205 200 200 200 170 50 41 29 18
37 22 21 21 21 19 14 9 6 3.9
44 30
28 28 28 25 14 9 6 3.9 46 34 32 32 31 27 14 9 6 3.9
10 8.5 8 8 8 8 7.5 6 4.2 2.6 30 25 24 24 24 22 7.5 6 4.2 2.6 36 30 29 29 29 25 7.5 6 4.2 2.6
(a) Lowest strengthsfor exposuresup to 10 000 h at temperature;no load; test loading applied at35 MFa/min (5 ksi/min) to yield strength and then at strainrate of 5%/min to fracture
Wrought Aluminum and Aluminum Alloys /187 5050 Aluminum: Typical mechanical properties
Thmper
Thmlle strength(a) MPa ksi
Yield streng!h(a) ksf MPa
0 H32 H34 H36 H38
145 170 190 205 220
55 145 165 180 200
21 25 28 30 32
Eiongation(a)(b), %
Hardnesste),
HB
Shearstrength MPa ksl
24 9 8 7 6
36 46 53 58 63
105 115 123 130 138
8 21 24 26 29
Fatigue strength(d) ksi MPa
15 17 18 19 20
83 90 90 97 97
12 13 13 14 14
8
(8) Strengths andelongationgenerally unchanged or improvedat lowtempemtures. (b) 1.6mrn(0.625in.) thicksheetspecimen. (c)500kg load;10mrndiamball.(d)At5 x 10 cycles;R.R.Mooretypetest
5052 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.10 Mn max, 2.20 to 2.80 Mg, 0.15 to 0.35 Cr,O.lO Zn max, 0.05 others max (each), 0.15 others max (total), bal Al
Characteristics Major alloying elements: 2.5Mg-0.25Cr. Applied when a combination of good workability, good resistance to corrosion, high fatigue strength, weldability, and moderate static strength is required
Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASTM. (See adjoining Table); SAE. J454; UNS. A95052; Government. Sheet and plate: QQ-A-250/8. Foil: MIL-A-81596. Rolled or cold finished wire, rod, and bar: QQ-A-22517. Drawn, seamless tubing: WW-T-700/4. Rivet wire and rod: QQ-A430. Rivets: MIL-R-24243; (Canada) CSA GR20; (France) NF A-G2.5C; (Italy) ON.l P-AlMg2.5; (Germany) DIN AIMg2.5. ISO: AIMg2.5
Typical Uses. Sheet metal work, hydraulic tubing, appliances, street light standards, rivets, and wire. Tempers include 0, H32, H34, H36, and H38. For more information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Available Product Forms. Sheet; plate; bar and shapes (extruded); wire, rod, and bar (rolled or cold fmished); tubing; rivet wire and rod; foil
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
5052Aluminum. Representative isothermal annealing curves for 5052-H18 350
50
LIVE GRAPH Click here to view
505d.H18 300
250 ~
Q.
:;: • 200
t
~
~
150
:;
100
~
/175 °c (350 OF)
"\-
-. -, -
",I
/205 °c (400 OF)
40
"230°C (450 ° F)
'I
260°C (500 OF)
"'--
--
.L2 90 °c
r--2
(550°F)1
\315 °c (600 OF) 1
50
o
o
0.5
1.5
2.5 Time, h
3.5
4.5
188/ Heat Treater's Guide: Nonferrous Alloys 5052 Aluminum: Typical mechanical properties Elongation, ...(a) 'ThnslJe
YleId
'IOmper
lI!mIgth(a) MPa bi
0 H32 H34 H36 H38
195 230 260 '1J5 290
strength(a) MPa bi
28
90 195 215 240 255
33 38 40 42
U.5mm (0.51u.)
Bard......
dlam
HB(b)
25 12 10 8 7
'1J 16 12 9 7
47 60 68 73 77
13 28 31 35 37
Fatlgue
Shear
l.6mm (o.0625Iu.) thkk
strength MPa bi
MPa
bi
125 140 145 160 165
110 115 125 130 140
16 17 18 19 20
Itreogtb(cl
18 20 21 23 24
(a) Strengthsandelongationsunchangedor improvedat low temperatures. (b) 500kg load; 10mm warn ball.(c) At5 x loBcycles;RR Moore type test
5052 Aluminum: Typicaltensile properties at various temperatures Temperature 'IOmper
0
H34
H38
OC
-196
OF
-320 -SO -1l2 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 370 700 -196 -320 -SO -1l2 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 370 700 -196 -320 -80 -112 -28 -18 24 75 100 212 150 300
ThnsiJe strength MPa ksi 303 200 193 193 193 159 117 83 52 34 379 276 262 262 262 207 165 83 52 34 414 303 290 290 '1J6 234
44 29
28 28
28 23 17 12 7.5 5 55 40 38 38 38 30 24 12 7.5 5 60 44 42 42 40 34
YIeld Itreogth (0.2'" otr..,1) MPa bi
110 90 90 90 90 90 76 52 38 21 248 221 214 214 214 186 103 52 38 21 303 262 255 255 248 193
16 13 13 13 13 13 II
7.5 5.5 3 36 32 31 31 31 27 15 7.5 5.5 3 44 38 37 37 36 28
5052 Aluminum: Standard specifications SpecUkationNo.
Elongation,
...
46 35 32 30 36 50 60 80 110 130 28 21 18 16 18 27 45 80 110 130 25 18 15 14 16 24
MID Conn
Sheetandplate Sheet,plate.bar.andshapes(extruded) Wire. rod.and bar(rolledor cold finished) 1\100 Drawn Drawn. seamless Hydraulic Extruded Extruded. seamless Condenser Condenserwith integral fins Welded Rivetwireandrod Foil
AMS
ASTM
4015 4016.4017 4114
B209 B221 B211
4069 4070 4071
B483 B210 B221 B241 B234 B404 B313,B547 B316
4004
5056, Alclad 5056 Chemical Composition. Composition Limits (5056). 0.30 Si max, 0.40 Fe max, 0.10 Cu max, 0.05 to 0.20 Mn, 4.50 to 5.60 Mg, 0.20 Cr max, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al Composition Limits (Alclad 5056). 6253 cladding-Si, 45 to 65% of Mg content, 0.50 Fe max, 0.10 Cu max, 1.00 to 1.50 Mg, 0.15 to 0.35 Cr, 1.60 to 2.40 Zn, 0.05 others max (each), 0.15 others max (total), bal AI Specifications (U.S. and/or Foreign). AMS. Rolled or cold fmished wire, rod, and bar: 4182. Foil: 4005; ASTM. Rivet wire and rod: B 316. Rolled or cold fmished wire, rod, and bar: B 211. Alclad, rolled or cold finished wire, rod, and bar: B 211; SAE. J 454; UNS. A95056; Government. Rivet wire and rod: QQ-A430, foil: MIL-A-8l596; (Austria) AlMg5; (Canada) CSA-GM50R; (United Kingdom) BS N6 2L.58; (Germany) DIN AlMg5. ISO: AlMg5
Available Product Forms. Rolled or cold finished wire, rod, and bar; rivet wire and rod
Characteristics Major alloying elements: 5.0Mg-0.1Mn-0.lCr
Typical Uses. Rivets for use with magnesium alloy and cable sheathing, zipper stock, and nails. Alclad wire is used exclusively in the fabrication of insect screens and other instances where wire products require good resistance to corrosion. For more information on resistance to corrosion, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treatment is at 415°C (775 "F); holding attemperature is not required
Hot Working Temperature. Range is 315 to 480°C (600 to 900 oF)
Wrought Aluminum and Aluminum Alloys /189
5056 Aluminum: Typical mechanical properties 'ThnslJe strength(a) MPa ksl
'Thmper
0 H18 H38
290 434 414
Yieldstrength(a) MPa ksl
42 63 60
152 407 345
22 59 50
Eiongallon(a)(h), %
Hanlness(c), HB
35 10 15
65 105 100
Fatigue otrength(d) MPa ksi
Shearstrength MPa ksi
179 234 221
138 152 152
26
34 32
20 22 22
8 (8) Strengthsand elongationare unchangedor improvedat low temperatures. (b) 12.5rom(0.50in.) dlam;roundspecimen.(c) 500 kg load; 10 romdiam ball.(d)At 5 X 10 cycles; R.R Moore type test
5056 Aluminum: Typical tensileproperties 'Iemperamre
'Thmper
-c
OF
0
24 150 205 260 315 370 24 150 205 260 315 370
75 300 400 500
H38
'ThnslJe strength(a) ksl MPa
y,.ld strength(a) ksJ MPa
Elongation, %
5056 Aluminum: Mechanical-property limits for rolled or cold finished wire,rod, andbar 'Thnslle s!mlgth(mia) MPa ksl
Thmper
600
700 75 300 400 500 600
700
290 214 152 110 76 41 414 262 179 110 76 41
42 31 22 16 11 6 60 38 26 16 11 6
150 117 90 69 48 28 345 214 124 69 48 28
22 17 13 10 7 4 50 .31 18 10 7 4
35 55 65 80 100 130 15 30 50 80 100 130
(8) Loweststrengthsfor exposuresup to 10000 h at temperature, no load;testloadingappliedat 35 MPalmin (5 ksilmin)to yieldstrengthand then at strainrate of5%/min to fracture
BareSOS6 0 Hlll H12 H32 H14 H34 H18 H38 H192 H392 AicladSOS6 H192 H392 H393
315 (max) 305 315 305 360 345 400 380 415 400 360 345 370(a)
46 (max)
44 46
44 52 50 58 55 60 58 52 50 54
(a)Yieldstrength (min), 325 MPa (47 ksi)
5083 Chemical Composition. Composition Limits. 0040 Si max, 0040 Fe max, 0.10 Cu max, 0040 to 1.00 Mn, 4.00 to 4.90 Mg; 0.05 to 0.25 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 othersmax (each), 0.15 others max (total),bal AI Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4056, 4057,4058,4059; ASTM. Sheet and plate: B 209. Extruded wire, bar, rods, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn seamless tubing: B 210. Welded tubing: B 547. Forgings: B 247. Gas and oil transmission pipe: B 245; SAE. J454; Government. Sheet and plate: QQ-A-250/6. Extruded wire, rod, bar, shapes and tubing: QQ-A-200/4. Forgings: QQ-A-367. Armor plate: MIL-A-46027. Extruded armor: MILA-46083. Forged armor: MIL-A-45225; (Canada) CSA GM4l; (United Kingdom) BS H8; (Germany) DIN AIMg4.5Mn, Werstoff-Nr. 3.3457, ISO: AIMg4.5Mn Available Product Forms. Sheet; plate; extruded wire, rod, bars, shapes, and tubing; extruded seamless tubing; drawn seamless tubing; welded tubing; forgings; gas and oil transmission pipe
Characteristics
For information on resistance to corrosion, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treatment is at 415°C (775 "F); holding at temperature is not required Hot Working Temperature. Range is 315 to 480 °C (600 to 900 oF)
5083 Aluminum: Typical tensile properties 'Thmper
'Thnsll.strength(a) MPa ksi
YIeldsIreDgtb MPa ksi
Eiongatlon(a)(h), %
Major alloying elements: 4.4Mg-0.7Mn-0.15Cr. Suitable for applications requiring weidability, moderate high strength, and good resistance to corrosion
0 8112 H116 H321 H323,H32 H343,H34
Typical Uses. Marine, auto, and aircraft parts; unfired pressure vessels; cryogenics; TV towers; drilling rigs, transportation equipment, missile components, and armor plate. Tempers include H32l, H1I6, HIll.
(a)Strengthsand elongationsare unchangedor improvedatlow temperatures, (b) 1.6rom(0.0625 in.) thickspecimens
290 303 317 317 324 345
42
44 46 46 47 50
145 193 228 228 248 283
21 28 33 33 36 41
22 16 16 16 10 9
190 I Heat Treater's Guide: Nonferrous Alloys 5083 Aluminum: Mechanical-property limits Tensile strength Minimum MPa ksi
Temper
Yield strength Maximum MPa ksl
Minimum ksi MPa
350 345
125 lI5 lIO 105 95
18 17 16 15 14
Maximum MPa ksi
Elongation (min)(a),%
0 0.051-1.5000in. thick 1.501-3.000in. thick 3.001-5.000in. thick 5.001-7.000in. thick 7.001-8.000in. thick HlI2 0.250-1.500in. thick 1.501-3.000in. thick H1l6 0.063-1.500in. thick 1.501-3.000in. thick H321 0.188-1.500in. thick 1.501-3.000in. thick H323 H343
16 16 14-16 14 12
40 39 38 37 36
275 270
40 39
125 lI5
18 17
12 12
305 285
44 41
215 200
31 29
12 12
305 285 310 345
44 41 45 50
215 200 235 270
31 29 34 39
385 385 370 405
51 50
56 56 54 59
200 200
29 29
275 270 260 255 250
295 295 305 340
43 43 44 49
12 12 8-10 6-8
(a) In 50 nun (2 in.) or 4d, where d is diameterof reduced sectionof tensiletestspecimen.Wherea range of valuesappearsin thiscolumn, the specifiedminimumelongationvaries with thicknessof the mill product
5083 Aluminum: Microstructures. (a) 5083-H112 plate, cold rolled. Longitudinal section shows particles of primary MnAl a (gray, outlined). Small, dark areas may be particles of insoluble phases, such as phases that contain magnesium (for example, M92Si) or that contain manganese. Keller's reagent. 50x. (b) 5083 plate, cold rolled. The coarse, gray areas are particles of insoluble (Fe,Mn)aSiAI,2; adjacent black areas are voids caused by breakup of the brittle (Fe,Mn)aSiAI'2 particles during cold rolling. Separate black areas may be insoluble particles of M9 2Si. As-polished. 500x
(a)
(b)
5083 Aluminum: Typical tensile properties at various temperatures 'Thmperature OF -c
-195
-80 -30 25 100 150 205 260 315 370
-315 -lI2 -22 80 212 302 400 500 600 698
'Iensile strength(a) MPa ksl
405 295 290 290 275 215 150 115
75 41
59 43 42 42 40 31 22 17 II 6
Yield strength (0.2% offset)(a) MPa ksl
165 145 145 145 145 130 115 75 50 29
24 21 21 21 21 19 17 II 7.5 4.2
Elongation, %
36 30 27 25 36 50 60 80 lIO 130
(a) Loweststrengthfor exposures up to 10 000 h at temperature, no load; test loadingappliedat 35 MPalmin(5 ksilmin)to yield strengthand then at strainrate of IO%/min to fracture
Wrought Aluminum and Aluminum Alloys /191
5086, Alclad 5086 Chemical Composition. Composition Limits. 0040 Si max, 0.50 Fe max, 0.20 to 0.70 Mn, 3.50 to 4.50 Mg, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded bar, wire, rod, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn seamless tubing: B 313, B 547. Gas and ore transmission pipe: B 345. Alclad 5086. Sheet and plate: B 209; SAE. J454; UNS. A95086; Government. Sheet and Plate: QQ-A-250/7, QQ-A-250/19. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/5. Drawn, seamless tubing: WW-T-700/5; Foreign. (France) NFA-G4MC; (Germany) DIN AlMg4. ISO: AlMg4 Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing; welded tubing; gas and oil transmission pipe. Alclad, sheet and plate
Characteristics Major alloying elements; 4.0Mg-OAMn-0.15Cu. Applications include those requiring a weldable, moderate strength alloy with comparatively good resistance to corrosion
Typical Uses. Marine, auto, and aircraft parts, cryogenics, TV towers, drilling rigs, transportation equipment, missile components, armor plate, and unfired, welded pressure vessels.
5086 Aluminum: Microstructure. 5086-H34 plate, 13-mm (0.5in.) thick, cold rolled and stabilized at 120 to 175 0p (250to 350 OF) to prevent age softening. Undesirable continuous network of M92Al a particles precipitated at grain boundaries; large particles are insoluble phases. 25% HNOa• 250x
For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. The range is 315 to 480 °C (600 to 900 OF)
5086 Aluminum: Typical tensile properties of 5086-0 at various temperatures Temperature
-c
-196 -80 -28 24 100 149 204 260 316 371
OF
-320 -112 -18 75 212 300 400 500 600 700
Tensile strength(a) ksi MPa 379 269 262 262 262 200 152 117 76 41
Yield strength (0.2 % ofl'set)(a) MPa ksi 131 117 117 117 117 110 103 76 52 29
55 39 38 38 38 29 22 17 11 6
Elongation, %
46 35 32 30 36 50 60 80 110 130
19 17 17 17 17 16 15 11 7.5 4.2
(a)Lowest strengthsfor exposuresup to 10 000 h at temperature, no load; test loadingappliedat 35 MPalmin(5 ksilmin)to yieldstrengthand thenat strainrate of 5%/minto fracture
5086 Aluminum: Tensile properties Temper Typical properties 0 H32,H1l6 H34 H112 Property limits 0(0.020-2.000 in. thick) H32 (0.020-2.000in.thick) H34(0.009-1.000in. thick) H36(0.006-0.162in. thick) H38(0.006-0.020in. thick) H112 (0.188-0.499in. thick) (0.500-1.000 in. thick) (1.001-3.000in. thick) (2.001-3.000in. thick) H116(0.063-2.000in. thick)
MPa
Tensile strength ksi MPa
260 38 42 290 47 325 270 39 Minimum 240 275 305 325 345
35 40 44 47 50
250 240 240 235 275
36 35 35 34 40
ksi
Maximum 305 325 350 370
44 47 51 54
Yield strength Elongation(a), MPa ksi %
115 17 205 30 255 37 130 19 Minimum
22 12 10 14 Minimum
95 195 235 260 285
14 28 34 38 41
15-18 6-12 4-10 3-6 3
125 110 95 95 195
18 16 14 14 28
8 10 14 14 8-10
(a) In 50 rom (2 in.) or 4d,where d is diameterof reduced sectionof tensile test specimen.Wherea range of values appearsin this column,specifiedminimumelongationvaries with thicknessof the millproduct
51 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.10 Mn max, 3.10 to 3.90 Mg, 0.15 to 0.35 Cr, 0.20 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total),bal AI
seamless tubing: B 210. Welded tubing: B 313, B 547; SAE. J454; UNS. A95154; (Canada) CSA GR40; (France) NF A-GC3; (United Kingdom) BS N5. ISO: AIMg3.5
Specifications (U.S. and/or Foreign). AMS. Sheet and plate: 4018, 4019; ASTM. Sheet and plate: B 209. Rolled or cold finished wire, rod, and bar: B 211. Extruded wire, rod, bar, shapes, and tubing: B 221. Drawn,
Available Product Forms. Sheet and plate; rolled or cold finished wire, rod, and bar; extruded wire, rod, bar, shapes, and tubing; drawn seamless tubing; and welded tubing
192/ Heat Treater's Guide: Nonferrous Alloys 5154 Aluminum: Typicaltensile properties of 5154-0 at various temperatures
Characteristics Major alloying elements: 3.5Mg-0.25Cr
Typical Uses. Welded structures, storage tanks, pressure vessels, marine structures, and transportation trailer tanks. For additional information on corrosion resistance, cold workability, machinability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
-1%
--so -28 24 100 150 205
Recommended Heat Treating Practice Annealing. Treatmentis at 345°C (650 OF); holding at temperature is not
260
required
315 370
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 OF)
YIeld strength !O.2%oft'.gel) MPa ksi
'lOruile strength MPa ksI
'Iemperamre OF "C
-320 -112 -18 75 212 300 400 500 600 700
360 250 240 240 240 200 150 115 75 41
130 115 115 115 115 110 105 75 50 29
52 36 35 35 35 29 22 17 11 6
19 17 17 17 17 16 15 11 7.5 4.2
FJongation!a),
...
46 35 32 30 30 50 60 80 110 130
(a)In 50mm (2 in.) or 4d.whered is diameterof reducedsectionoftensiletestspecimen
5154 Aluminum: Mechanical properties Thmper
'JYpicalproperties 0 H32 H34
H36 H38 Hll2 Property limits 0(0.020-3.000 in. thick) H32(0.020-2.000 in. thick) H34 (0.009-1.000 in. thick) H36 (0.006-0.162 in. thick) H38(0.006-0.128 in. thick) Hll2 (0.250-0.499in. thick) (0.500-3.000in. thick)
MPa
Yieldstrength ks\ MPa
EIongation!a),
ksi
...
1Iardness(h). HB
27 15 13 12 10 25
58 67 73 78 80 63
Maximum
117 17 207 30 33 228 248 36 39 269 117 17 Minimum
'lO...itestrength ksi MPa
240 35 270 39 42 290 310 45 330 48 240 35 Minimum 205 250 270 290 310
30 36 39 42 45
220 205
32 30
285 295 315 340
41 43 46 49
75 180 200 220 240
11 26 29 32 35
12to 18 5to 12 41010 3105 3105
125 75
18 11
8 11to 15
Shear strengtb MPa
ksI
152 152 165 179 193
22 22 24 26
28
Fatigue strength!e) ksi MPa
117 124 131 138 145 117
17 18 19 20 21 17
(a) In 50 mm (2 in.) or4d. where d is diameterof tensileteslspecimen. Wherea rangeof valuesappearsin thiscolumn.specifiedminimumelongationvarieswith thickness of themillproduct. (h) 500 kg load;10mmball.(c)At 5 X 108 cyclesof completely reversedstress;R.R.Mooretypetest
5182 Chemical Composition. Composition Limits. 0.20 Si max, 0.35 Fe
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 "F)
max, 0.15 Cu max, 0.20 to 0.50 Mn, 4.00 to 5.00 Mg, 0.10 Cr max, 0.25 Zn max, 0.10 Ti max. 0.05 others max (each), 0.15 others max (total), bal AI
Specifications (U.S. and/or Foreign). UNS. J95182 Available Product Form. Sheet
Characteristics Major alloying elements: 4.5Mg-0.35Mn
Typical Uses. Container ends, auto body panels and reinforcement members. brackets, and parts
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 oF)
5182 Aluminum: Typicaltensile properties 'Iemper
o H32 H34 HI9(c)
'lOmitestrengthCa) MPa ksi
276 317 338 421
40 46 49 61
Yieldstrength!a) MPa ksi
138 234
283 393
19 34 41 57
Elongalion!a)(h),
...
25 12 10 4
(a) Strengths and elongations are unchanged or increasedat low temperatures. (h) 1.6mm (0.0625 in.) thickspecimen. (c)Propertiesof thistemperareforcontainerendstock0.25to 0.38mm(0.010 100.015in.) thick
Next Page Wrought Aluminum and Aluminum Alloys
/193
5252 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.10 Cu max, 0.10 Mn max, 2.20 to 2.80 Mg, 0.05 Zn max, 0.05 V max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet: B 209; SAE. J454;lnNS.A95252
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
Available Product Forms. Sheet 5252 Aluminum: Tensile properties
Characteristics
YIeld strength MPa Ilsi
'l\",.1Ie strength
Major alloying element: 2.5Mg. Can be bright dipped or anodized to give a bright. clear finish Typical Uses. Sheet metal work, hydraulic tubing, automotive and appliance trim, where more strength than that provided by other trim alloys is needed. Available tempers include 0, H32, H34, H36, H38. For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
MPa
Thmper
Ilsi
MPa
Ilsi
'IYPicalproperties H25 235 34 170 H28,H38 283 41 240 Property limits for 0.75-2.3 mm (0.030-0.090in.) thick sheet Minimum Maximum 205 215 260
H24 H25 H28
30 31 38
260 270
EIoogatloo(a).
...
l1(a) 5(a)
25 35
Minimum 10 9 3
38 39
(a) 1.6 mm(0.0625in.) thickspecimen
5254 Chemical Composition. Composition Limits. 0.45 Si max + Fe, 0.05 Cu max, 0.01 Mn max, 3.10 to 3.90 Mg, 0.15 to 0.35 Cr, 0.20 Zn max, 0.05 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded seamless tubing: B 241; SAE. J454; UNS. A95254; (Canada) CSA GR40 Available Product Forms. Sheet and plate
Typical Uses. Storage vessels for hydrogen peroxide and other chemicals. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice
Characteristics
Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required
Major alloying elements: 3.5Mg-0.25Cr
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
5254 Aluminum: Mechanical properties Thnsile strength Thmper
MPa
ksi
MPa
ksi
YIeld strength MPa kst
Elongation,
115 17 205 30 23G 33 250 36 270 39 115 17 Minimum(d)
27 15 13 12 10 25
...
H~(a).
Shear strength Ilsi
HB
MPa
58 67 73 78 80 63
150 150 165 180 195
Fa!igue strengthlb) Ilsi MPa
'Iypleal properties(c)
o H32 H34 H36 H38 H112 Property limits
o H32 H34 H36 H38 H112 6-12.5 mm(0.250-0.499in.) thick 13-75mm (0.500-3.000in.)thick
240 35 270 39 290 42 310 45 330 48 240 35 Minimum 205 250 270 290 310
30 36 39 42 45
220 205
32 30
Maximum 285 295 315 340
41 43 46 49
75 180 200 220 240
11 26 29 32 35
12-18 5-12 4-10 3-5 3-5
125 75
18 11
8 11-15
22 22
24 26 28
115 125 130 140 145 115
17 18 19 20 21 17
(a) 500kgload; 10mm ball, (b) At5 X 108cycles;R.R. Mooretypetest.(c)Strengthsandelongationsareunchangedor Increasedatlow tempemtures. (d)In 50 mm (2 in.) or 41. whered isdiameterof reduced sectionof testspecimen.Wherea rangeof valuesappearsin thiscolumn,specifiedminimumelongationvarieswith thicknessof the millproduct
Previous Page
194/ Heat Treater's Guide: Nonferrous Alloys 5254 Aluminum: Typical tensile properties of 5254-0 at various temperatures °C
Thmperature of
-196 -80 -28 24 100 ISO 205 260 315 370
'Iensile strength(a) MPa ksi
-320
-112 -18 75 212 300 400 500 600 700
360 250 240 240 240 200 150 ll5 75 41
52 36 35 35 35 29 22
17 II 6
Yield strengthla) MPa ksi
130 ll5 ll5 ll5 ll5 llO 105 75 50 29
19 17 17 17 17 16 IS II 7.5 4.2
Elongation,
%
46 35 32 30 36 50 60 80 llO 130
(a) Loweststrengthsfor exposure up to 10 000 h at temperature, no load; testloadingappliedat 35 MPa/min(5 ksi/min)to yieldstrengthand then at strainrate of 5%/min to fracture
5356 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.05 to 0.20 Mn, 4.50 to 5.5 Mg, 0.05 to 0.20 Cr, 0.10 Zn max, 0.06 to 0.20 Ti, 0.05 others max (each), 0.15 others max (total), balAI
Characteristics Major alloying elements: 5.0Mg-0.12Mn-0.12Cr Typical Uses. Welding base metals high (73%) in magnesium
Specifications (U.S. and/or Foreign). UNS. A95356; Government. QQ-R-566, MIL-E-16053; (Canada) CSA GM50P; (France) NF A-GS
Recommended Heat Treating Practice
Available Product Forms. Welding electrodes and filler wire
Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
5454 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.50 to 1.00 Mn, 2.40 to 3.00 Mg, 0.05 to 0.20 Cr, 0.25 Zn max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al
Hot Working Temperatures. Range is 260 to 510 °C (500 to 950 "F)
Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded wire, rod, bar, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Condenser tubing: B 234. Condenser tubing with integral fins: B 404. Welded tubing: B 547; SAE. J454; UNS. A95454; Government. Sheet and plate: QQ-2501l0. Extruded wire, rod, bar, shapes, and tubing: QQ-A-2oo/6; (Canada) CSA GM31N; (France) NF A-G2.5MC; (United Kingdom) B5 N51; (Germany) DIN AIMg2.7Mn. ISO: AIMg3Mn
5454 Aluminum: Microstructure. 5454, hot-rolled slab, longitudinal section. Oxide stringer from an inclusion in the cast ingot. The structure also shows some particles of (Fe,Mn)Al a (light gray). As-polished. 50 Ox
Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing
Characteristics Major alloying elements: 2.7Mg-0.8Mn-0.12Cr Typical Uses. Welded structures, pressure vessels, and tubing for marine service. Available in 0, H32, H34, and HIll tempers. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treating is at 345°C (650 OF); holding at temperature is not required
Wrought Aluminum and Aluminum Alloys /195
5454 Aluminum: Typical tensile properties of 5454 at various temperatures
5454 Aluminum: Mechanical properties Yield Temper
Tensile strength MPa ksi MPa ksI
strength MPa ksi
Elongatloo,%
250 275 305
22 10 10 8 8 14 18 18
Shear Hardness strength (a),HB MPa ksi
H32 H34 H36 H38 Hlll H112 H311 Property limits
0 H32 H34 H112 6-12.5mm (0.250-0.499 in.) thick 13-75mm (0.500-3.00 in.) thick
OF
Teosile strength(a) MPa ksi
Yield strength(a) MPa ksi
Eloogalioo, %
o temper
'IYpical properties
0
Thmperature °C
36 40
49 54 260 38 250 36 38 260 Minimum
Maximum
117 17 207 30 241 35 276 40 310 45 179 26 124 18 26 179 Minimum
215 250 270
31 36 39
285 305 325
85 180 200
12 26 29
12-18(b) 5-12(b) 4-10(b)
220
32
125
18
8
215
31
85
12
11-15(b)
44
340 370
41
44 47
62 73 81
159 165 179
23 24 26
70 62 70
159 159 159
23 23 23
-196 -80 -28
24
(a) 500 kg load; 10 mm ball. (b) Range of values indicates that specified minimum elongation varies with thickness of mill product
100 150 205 260 315 370
-320 -112 -18 75 212 300
400 500 600 700
370 255 250 250 250 200 150 115 75 41
54 37 36 36 36 29 22 17 11 6
130 115 115 115 115 110 105 75 50 29
19 17 17 17 17 16 15 11 7.5 4.2
39 30 27 25 31 50 60 80 110 130
405 290 285 275 270 220 170 115 75 41
59 42 41 40 39 32 25 17 11 6
250 215 205 205 200 180 130 75 50 29
36 31 30 30 29 26 19 11 7.5 4.2
32 23 20 18 20 37 45 80 110 130
63
285 250 240 240 235 195 130 75 50 29
41 36 35 35 34 28 29 11 7.5 4.2
30 21 18 16 18 32 45 80 110 130
H32temper -196 -80 -28 24 100 150 205
-320 -112 -18 75 212 300
260
500
315 370
700
400 600
H34temper -196 -80 -28 24 100 150 205 260 315 370
-320 -112 -18 75 212 300
400 500 600 700
435 315 305 305 295 235 180 115 75 41
46
44 44 43 34 26 17 11 6
(a) Lowest strengths for exposures up to 10 000 h at temperature, no load, test loading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture
5456 Chemical Composition. Composition Limits. 0.25 Si max, 0.40 Fe max, 0.10 Cu max, 0.50 to 1.00 Mn, 4.70 to 5.50 Mg, 0.05 to 0.20 Cr, 0.25 Cr max, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal A1 Specifications (U.S. and/or Foreign). ASTM. Sheet and plate: B 209. Extruded wire, rod, bar, shapes, and tubing: B 221. Extruded seamless tubing: B 241. Drawn, seamless tubing: B 210; SAE. J454; UNS. A95456; Government. Sheet and plate: QQ-A-250/9, QQ-A-250/20. Extruded wire, rod, bar, shapes, and tubing: QQ-A-200/7. Armor plate: MIL-A-46027. Extruded armor: Mll..-A-46083. Forged armor: Mll..-A-45225
Available Product Forms. Sheet; plate; extruded wire, rod, bar, shapes, and tubing, armor plate
Characteristics Major alloying elements: 5.IMg-0.8Mn-0.12Cr
Typical Uses. High strength welded structures, pressure vessels, marine applications, storage tanks, armor plate. Available in 0, H32l, and Hl16 tempers, For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 "F); holding at temperature is not required
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
196/ Heat Treater's Guide: Nonferrous Alloys 5456 Aluminum: Tensile properties 'Iemper
MFa
ThnsiIe strength k.si MPa
Typical properties 0 H111 H112 H321(b), H116(c)
310 324 310 352
45 47 45 51
ksl
MPa
YIeld strength k.si MPa
159 228 165 255
23 33 24 37
Elongation, %
k.si
24(a) 18(a) 22(a) 16(a) Mlnlmum(d)
Property 1Imlts
Mlnlmum
Maximum
Mlnlmum
InSOmm
Maximum
In5d(S.6S.,pt)
0 1.20-6.30 mmthick 6.30-80.00 mmthick 80.00-120.00 mmthick 120.00-160.00 mmthick 160.00-200.00 mmthick H1I2 6.30-40.00 mmthick 40.00-80.00 mmthick H116(c)(e) 1.60-30.00 mmthick 30.00-40.00 mmthick 40.00-80.00 mmthick 80.00-110.00 mmthick H321 4.00-12.50 mmthick 12.50-40.00 mmthick 40.00-80.00 mmthick H323 1.20-6.30 mmthick H343 1.20-6.30 mm thick
130 125 120 115 105
19 18 17 17 15
42 41
130 125
19 18
12
10 10
46
230 215 200 170
33 31 29 25
10
10 10 10 10
290 285 275 270 265
42 41 40 39 38
290 285 315 305 285 275
365 360
53 52
44
41 40
315 305 285
46 44
205 205
30 30
16 16
12
41
405 385 385
59 56 56
230 215 200
33 31 29
315 305 295
43
330
48
400
58
250
36
315
46
6t08
365
53
435
63
285
41
350
51
6t08
46 44
14 12 12 10
10 10
(a) 12.5(0.5 in.) diam specimen. (b)Material in thistempernotrecommended forapplications requiring exposuretoseawater. (c)Hl16 designation alsoappliesto thecondition previously designated H117. (d) Elongations in 50 mm(2 in.) applyto thicknesses through12.5mm(0.5 in.); elongations in 5d (5.65.,pt), whered is diameter andAis cross-sectional areaof tensiletestspecimen, applyto material over 12.5mm(0.5 in.) thick.(e)Materialin thistemperrequired to passanexfoliation corrosiontestadministered by thepurchaser
5456Aluminum: Microstructures. (a) 5456plate, hot rolled.Longitudinal section, Polarized light. Partial recrystallization occurred immediatelyafter hot rollingfrom residual heat. This type of recrystallization is frequently referred to as "dynamic recrystallization." Barker's reagent. 100x. (b) 5456 plate, 6.4 mm (0.25 in.) thick, cold rolled and stress relieved below the solvus at 245°C (475 OF). Particles are (Fe,Mn)Ala (gray), M92Si (black), andM92AI3 (fineprecipitate). Thereis nocontinuous networkof precipitate at grainboundaries. 25%HN03 • 500x. (c) 5456-0 plate, 13 mm(0.5in.) thick, hot rolled, and annealed abovethe solvus. Rapidcoolingresulted in retention of M92AI3 in solid solution. The light, outlinedparticlesare insoluble(Fe,Mn)Al a; the dark particles are insolubleM92Si. 25% HN0 3 • 500x
(a)
(b)
(c)
Wrought Aluminum and Aluminum Alloys /197
5457 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.20 Cu max, 0.15 to 0.45 Mn, 0.08 to 1.20 Mg, 0.05 Zn max, 0.05 V max, 0.03 others max (each), 0.10 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Sheet: B 209; UNS. A95457 Available Product Forms. Sheet
Typical Uses. Brightened and anodized trim for autos and appliances. Is readily formed in both annealed and H25 tempers.
For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice
Characteris.tics
Annealing. Treat at 345°C (650 "F); holding at temperature is not required
Major alloying elements: 1.0Mg-0.30Mn. Fine grain size is required in most applications
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
5457 Aluminum: Microstructures. (a) 5457-F extrusion. A transverse section, photographed with polarized light. Surface grains (top) show random reflection, indicating random crystallographic orientation; interior grains show uniform reflection indicating a high degree of preferred orientation. Barker's reagent. 1OOx. (b) 5457-F plate 6.4-mm (0.25-in.) thick, hot rolled. Fine particles of M92Si precipitated during the rolling. If carried through to final sheet, this amount of precipitate would cause an objectionable milky appearance in a subsequently applied anodic coating. 0.5% HF. 500x. (c)5457-0 plate 1O-mm (O.4-in.) thick, longitudinal section. Annealed at 345°C (650 OF). Polarized light. The grains are equiaxed. Barker's reagent. 100x
(a)
(b)
(c)
5457 Aluminum: Microstructures. (a) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 10% reduction. Barker's reagent. 100x. (b) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 40% reduction. Barker's reagent. 100x. (c) Effect of cold rolling on 5457-0 plate, originally 10 mm (0.4 in.) thick, annealed at 345°C (650 OF). Polarized light. 80% reduction. Barker's reagent. 100x
(a)
(b)
(c)
198/ Heat Treater's Guide: Nonferrous Alloys 5457 Aluminum: Typical mechanical properties 'Thnslle strength!.)
Yield
strength!.)
Eiongation!.)(b),
Hardnesslc),
'Thmper
MPa
ksI
MP.
ksi
~
HB
MP.
ksi
0 H25 H38.H28
130 180 205
19 26 30
50 160 185
7 23 27
22 12 6
32 48 55
85 110 125
12 16 18
Shearstrength
(a) Strengths andelongations areunchanged or improved at lowertemperatures. (b) 1.6 mm (0.625 in.) thickspecimen. (c) 500 kgload; lOmmdiam ball
5652 Chemical Composition. Composition Limits. 0.40 Si max + Fe, 0.04 Cu max, 0.01 Mn max, 2.20 to 2.80 Mg, 0.15 to 0.35 Cr, 0.10 Zn max, 0.05 others max (each), 0.15 others max (total), bal Al
Typical Uses. Storage vessels for hydrogen peroxide and other chemicals. Available in 0, H32. H34, H36, H38 tempers.
Specifications (U.S.and/or Foreign). ASTM. Sheet and plate: B 209. Extruded seamless tubing: B 241; SAE. J454; UNS. A95652
For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Available Product Forms. Sheet, plate, extruded tubing
Recommended Heat Treating Practice
Characteristics
required
Major alloying elements: 2.5Mg-0.25Cr
Hot Working Temperature. Range is 260 to 510 °C (500 to 950 oF)
Annealing. Treatment is at 345°C (650 "F); holding at temperature is not
5652 Aluminum: Mechanical properties FIIIigue
'Thmper
'Iypleal properties 0 H32 H34 H36 H38 Property limits 0 H32 H34 H36 H38 H112 (0.250-0.499in. thick) !0.5OO-3.000 in. thick)
MP.
'ThnsIIe strength ksi MP.
195 28 230 33 260 38 275 40 290 42 Minimum 170 215 235 255 270
25 31 34 37 39
195 170
28 25
Yield strength ksl
Maximum 215 260 285 305
31 38 41 44
MP.
ksl
90 13 195 28 215 31 240 35 255 37 Minimum
EJong.Uon!.),
Hardness(b),
~
DB
MP.
ksi
MPa
ksi
25 12 10 8 7 Minimum
47 60 68 73 77
124 138 145 158 265
18 20 21 23 24
110 117 124 131 138
16
65 160 180 200 220
9.5 23 26 29 32
14-18 4-12 3-10 2-4 2-4
110 65
16 9.5
7 12-16
Shearstrength
strength!c)
17
18 19 20
(a) In 50 mm(2 in.) or4d. whered isdiameter ofreducedsectiouof tension-test specimen. Wherearangeofvaluesappears in thiscolumn,thespecified minimumelongation varieswiththickness of the mill product. (b) 500 kgload; 10 mmball.(c)At 5 x 108 cycles;RR Mooretypetest
5657 Chemical Composition. Composition Limits. 0.08 Si max, 0.10 Fe max, 0.10 Cu max, 0.03 Mn max, 0.60 to 1.00 Mg, 0.05 Zn max, 0.03 Ga max, 0.05 V max, 0.02 others max (each), 0.05 others max (total), bal AI
Characteristics Major alloying element: 0.8Mg. Fine grain size is essential for almost all applications
Specifications (U.S. and/or Foreign). ASTM. B 209; UNS. A95657;
Typical Uses. Brightened and anodized auto and appliance trim. Avail-
(Italy) B-AlMgO.9
able in 0, H32, H34, H36, and H38 tempers.
Available Product Forms. Sheet
Wrought Aluminum and Aluminum Alloys /199 For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Annealing. Treatment is at 345°C (650 OF); holding at temperature is not required Hot Working Temperature. Range is 260 to 510 °C (500 to 950 OF)
5657 Aluminum: Tensile properties MPa
Temper
Typical properlies(b) H25 H28,H38 Properly limits H241(e) H25 H26 H28
Tensilestrength ksi MPa ksi
160 23 195 28 Minimum 125 140 150 170
18 20 22 25
Yield strength MPa ksi
140 165 Maximum 180 195 205
26 28 30
20
24
Elongation(a), %
12 7 Minimum 13 8 7 5
(a) In 50 mm (2 in.) or 4d, where d is diameterofredueed sectionof tension-test specimen. (b) Strengths and elongations are unchanged or increasedat lowtemperatures. (e)Materialin this tempersubjectto somerecrystallization andattendantlossof brightness
5657 Aluminum: Microstructures. (a) 5657-F sheet, cold rolled (85% reduction). Longitudinal section. Polarized light. Grains are greatly elongated and contribute to high strength, but ductility is lower than for specimen annealed at 315°C (600 OF). Barker's reagent. 100x. (b) 5657-F sheet, 85% reduction, stress relieved at 300°C (570 OF) for 1 h. Polarized light. Structure shows onset of recrystallization, which improves formability. Barker's reagent. 1OOx. (c) 5657-F sheet, 85% reduction, annealed at 315°C (600 OF) for 1 h. Polarized light. Recrystallized grains and bands of unrecrystallized grains. Barker's reagent. 100x
(b)
(a)
(c)
5657 Aluminum: Microstructures. (a) 5657 ingot. Dendritic segregation (coring) of titanium. Black spots are etch pits. Anodized coating from Barker's reagent was stripped with 10% H3 P0 4 at 80°C (175 OF). 200x. (b) 5657 sheet. Banding from dendritic segregation (coring) of titanium in the ingot in accompanying figure. Anodized coating from Barker's reagent was stripped with 10% H3 P0 4 at 80°C (175 OF). 200x
(a)
(b)
200 I Heat Treater's Guide: Nonferrous Alloys
6005 Chemical Composition. Composition Limits. 0.6 to 0.9 Si, 0.35 Fe max, O.lOCu max, O.lOMn max, 0.40 to 0.60 Mg, 0.10 Cr max, O.lOZn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). ASTM. Extrudedrod,bar,shapes, and tubing: B 221; SAE. J451; UNS. A96005 Available Product Forms. Extruded wire, rod, bars, shapes, and tubing
Characteristics Major alloying elements: 0.8Si-0.5Mg Typical Uses. Extruded shapes and tubing for commercial applications requiring greater strength than that of alloy 6063. More common products are ladders and TV antennas. Caveat: Alloy is not recommended for applications requiring resistance to impact loading. Available in T1 and T5 tempers. Alloy is generally brazeable and weldable by all commercial procedures and methods
General Considerations. Material should be quenched from solution treating temperature as rapidly as possible with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature and cooled to keep to temperature below 38°C (lOO "F) during the quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here for solution treatment are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO OF) during time at temperature. Note: By suitable control extrusion temperature, product may be quenched directly from the extrusion press to provide specified properties for this temper Precipitation Heat Treating (Artificial Aging). Product is heated to metal temperature of 175°C (345 "F) and held for 8 h to obtain T5 temper. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO "F) during time at temperature Annealing. Treatment is at415 °C (775 OF); timeattemperatureis 2 to3 h
Recommended Heat Treating Practice Solution Heat Treating. Extruded rod, bar, shapes, and tubing are treated at a metal temperature of 530°C (985 "F) for a T1 temper.
6009 Chemical Composition. Composition Limits.0.60 to 1.00 Si, 0.50 Fe max, 0.15 to 0.60 Cu, 0.20 to 0.80 Mn, 0.40 to 0.80 Mg, 0.10 Cr max, 0.25 Zn max, 0.10Ti max, 0.05 others max (each), 0.15 others max (total), balAI Specifications (U.S. and/or Foreign). UNS. A96009 Available Product Forms. Sheet
Characteristics Major Alloying Elements. 0.80Si-0.60Mg-0.50Mn-0.35Cu Typical Uses. Auto body sheet Formability Requirements. For sheet in T4 temper, 1t radius required for 90° bending. It for flanging material 0.80 to 1.30 mm (0.032 to 0.050 in.) thick. Only roped hems, "made by bending 180° or 2t interface thickness, can be made in sheet 0.80 to 1.30 mm (0.315 to 0.05 in.) thick. Olsen cup height typically is 9.1 mm (0.36 in.) when tested using 25 mm (1 in.) diam top die at 15 MPa (2200 psi) hold-down pressure and polyethylene film lubricant. Strain hardening exponent (n) typically is 0.22; plastic strain ratio (r) typically is 0.70
maintained at a temperature below 38°C (lOO OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±lO "F) of nominal during time at temperature Precipitation Heat Treating (Artificial Aging). Sheet is treated to T6 temper at 205°C (400 OF) for I h. This time at temperature is approximate. Specific times depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (lO OF) of applicable temperature. Alternative treatments are available: 4 hat 190°C (375 OF) or 8 h at 175 °C (345 OF) Annealing.Treatment is 415°C (775 OF)
6009 Aluminum: Typical tensile properties of 6009 automobile body sheet
Recommended Heat Treating Practice Solution Heat Treating. Sheet is treated to T4 temper at a metal temperature of 555°C (1030 OF). Alternative treatments: 4 h at 190°C (375 oF) or 8 h at 175°C (345 OF). General Considerations.Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and
Orientation
Thnsile strength ksl MPH
Yieldstrength ksl
MPH
EJongHIIon, %
T4temper Longitudinal Transverse and 45°
234 228
34 33
131 124
19 18
24 25
345 338
50 49
324 296
47 43
13
T6temper longitudinal Transverse and 45·
12
Wrought Aluminum and Aluminum Alloys 1201
6010 Chemical Composition. Composition Limits. 0.80 to 1.20 Si, 0.50 Fe max, 0.15 to 0.60 Cu, 0.20 to 0.80 Mn, 0.60 to 1.00 Mg, 0.10 Cr max, 0.25 Zn max, 0.10 Ti max, 0.05 others max (each), 0.15 others max (total), balAl Specifications (U.S. and/or Foreign). UNS. A96010 Available Product Forms. Auto body sheet
removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 oF) during quenching cycle. Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal and should be maintained within ±6 °C (±1OOF) of nominal during time at temperature
Precipitation Heat Treating (Artificial Aging). Sheet is treated to T6 temper at 205°C (400 OF) for I h. This time at temperature is approximate. Specific types depend on time required for load to reach temperature. Times are based on rapid heating, with soak time measured from time load reaches temperature within 6 °C (10 "F) of applicable temperature.
Characteristics Major alloying elements: 1.00Si-0.80Mg-0.5Mn-0.35Cu
Typical Uses. Auto body sheet Formability Requirements. For sheet in T4 temper, It radius required to 90° bending, It for flanging material 0.80 to 1.30 Mn (0.032 to 0.050 in.) thick. Only roped seams, made by bending 180° or 2t interface thickness, can be made in sheet 0.80 to 1.30 mm (0.315 to 0.05 in.) thick. Olsen cup height typically is 9.1 m min (0.36 in.) when tested using 25 mm (1 in.) diam top die at 15 MPa (2200 psi) hold-down pressure and polyethylene film lubricant. Strain hardening exponent (n) typically is 0.22; Plastic strain ratio (r) typically is 0.70
Recommended Heat Treating Practice Solution Heat Treating. Sheet is treated to T4 temper at metal temperature of 565°C (1050 oF) General Considerations. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after
Alternative treatments are available: 4 h at 190°C (375 "F), or 8 h at 175 °C (345 oF)
6010 Aluminum: Typical tensile properties of 6010 automobile body sheet 'IOnsIIe otrength lis; MPa
Orientallon
T4temper Longitudinal Transverse and45° T6temper Longitudinal Transverse and45°
YIdd strength lis;
MPa
EIougalion, II
296 290
43 42
186 112
21 25
23 24
386 319
56 55
312 352
54 51
12
11
6010 Aluminum: Time-temperature property diagram. Effectof aging time and temperature on longitudinalyield strength of 6010-T4 500~-----..--------r----------,
6010-14
234 MPa (34 ksl) 262 MPa (38 ksi) 290 MPa (42 ksl) 317 MPa (46 ksi)
250 225 u
331 MPa (48 ksl) 175 338 MPa (49 ksl) 345 MPa (50 ksi) 200 338 MPa (49 ksl) 300 207 MPa (30 ksi)+--~.---_~~~~=t'-oII~ 331 MPa (48 ksi) 150 234 MPa (34 ksi) 317 MPa (46 ksl) 290 MPa (42 ksi) 262 _ MPa (38 ksi)_ _....L.250 '----'-_ --= 125 10 1 102 ~
_
0
...e~
:::J
Q)
a. E
~
~
Time,h
6061, Alclad 6061 Chemical Composition. Composition Limits (6061). 0.40 to 0.80 Si, 0.70 Fe max, 0.15 to 0.40 Cu, 0.15 Mn max, 0.80 to 1.20 Mg, 0.04 to 0.35 Cr, 0.25 Zn max, 0.15 Ti max, 0.05 others max (each), 0.15 others max (total), bal AI
Composition Limits (Alclad 6061). 7072 cladding-O.70 Si max + Fe, 0.10 Cu max, 0.10 Mn max, 0.10 Mg, max, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total), bal Al
2021 Heat Treater's Guide: Nonferrous Alloys Specifications (U.S. and/or Foreign). AMS. (See adjoining Table); ASTM. (See adjoining Table); UNS. A96061; Government. (See adjoining Table); (Canada) CSA GSI1N; (France) NF A-GSUC; (United Kingdom) BS H20. ISO: AIMgSiCu
Use of high-velocity, high-volume jets of cold water also is effective for some materials. Temperatures given here are nominal, and should be attained as rapidly as possible and maintained within ±6 °C (±100F) of nominal during time at temperature
Available Product Forms. Sheet; plate; rolled or cold-finished wire, rod, and bar; extruded rod, bar, shapes, and tubing; structural shapes; pipe; drawn pipe; die and hand forgings; rolled rings
Precipitation Heat Treating (Artificial Aging). The following products (sheet; plate; rolled or cold finished wire, rod, and bar; and drawn tubing) are heated to a metal temperature of 160°C (320 oF) and held for 18 h.
Characteristics Major alloying elements: 1.0Mg-0.6Si-0.30Cu-0.2OCr
Typical Uses. Provides combination of strength, weldability, and corrosion resistance needed for structural applications; trucks, towers, canoes, railroad cars, furniture, pipelines. Tempers include T4, T451, T451O, T4511, T6, T651, T652, T651 1. For more information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
The following products (extruded rod, bar, shapes, and tubing; die and hand forgings; and rolled rings) are heated to a metal temperature of 175 °C (345 OF) and held for 8 h
Special considerations: 8
8
8
Recommended Heat Treating Practice 8
Solution Heat Treating. All products are treated to T4, T42, T45, T45l, T451O, and T4511 tempers at 530°C (985 OF). Special considerations: 8 8 8
8
Only tread plate is treated to T4 temper at 530°C (985 OF) Plate, rolled or cold finished rod, bar, shapes and tubing in T451 temper; extruded rod, bar, shapes, and tubing in T4510 and T4511 tempers are all stress relieved by stretching to produce specified amount of set prior to precipitation heat treatment Rolled rings in T452 temper are stress relieved by 1 to 5% cold reduction subsequent to solution heat treatment and prior to precipitation heat treatment
General Information. Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching by total immersion in water, unless otherwise indicated, water should be at room temperature and maintained at a temperature below 38°C (100 "F) during quenching cycle.
8
Only tread plate is treated at 160°C (320 "F) and held at temperature for 18 h to obtain T6 temper Plate and rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature for 18 h to obtain T651 temper Extruded rod, bar, shapes, and tubing are treated at 175°C (345 OF) and held at temperature for 8 h Rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature of 18 h to obtain T89 temper. Cold working after solution treating is necessary to get desired properties in precipitation treating Rolled or cold finished wire, rod, and bar are treated at 160°C (320 OF) and held at temperature for 18 h to obtain T93, T94, and T913 tempers Rolled rings are treated at 175°C (345 OF) and held at temperature 8 h to obtain T652 temper. Parts are stress relieved by 1 to 5% cold reduction subsequent to solution treating and prior to precipitation treating
Alternative treatment for rolled or cold finished wire, rod, and bar in T6, T62, T89, T93, T94, T651, T913 tempers; and drawn tubing in T6 and T62 tempers: 8 h at 170°C (340 OF) versus standard 18 h at 160°C (320 OF)
General Information. Temperatures given here are nominal and should be attained as rapidly as possible and maintained within ±6 °C (±10 "F) of nominal during time at temperature annealing. See Table titled "Typical Annealing Treatments for Aluminum Alloy Mill Products" in introduction titled "Heat Treating Aluminum Alloys"
6061 Aluminum: Microstructures. (a) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled (71% reduction).' Longitudinal section from center of plate thickness. Particles are Fe3SiAI,2 (gray, scriptlike) and M92Si (black). 0.5% HF.250x. (b) 6061-F plate, 38 mm (1.5 in.) thick, as hot rolled (91% reduction). Longitudinal section from near plate surface. HF. 250x. (c) 6061-F 6.4-mm (0.25-in.) sheet, hot rolled (reduced 98%); midthickness longitudinal section. Most M92Si will dissolve during solution treating. 0.5% HF.250x
...
-
.
-(a)
(b)
(c)
.'
Wrought Aluminum and Aluminum Alloys 1203
6061 Aluminum. Effect of quenching medium on strength of 6061-T6 sheet. Water-immersion quench equals 100%. Control of coolant flow will minimize decrease in mechanical properties
Mill form and condition
Bar 6061 Sheetand plate
LIVE GRAPH Click here to view
Thickness, 0.001 in.
150
100
100
Standard specifications
-.............. t---
r-. '\
200
250
II V Water ~
-,
-,
60
Treadplate Wire.rod.andbar (rolledorcoldftnished)
spray
~ Rod,bar.shapes.andtube(extruded) VAirblast
-,
Structuralshapes Thbe(drawn) Thbe(seamless)
2500
3150
Click here to view
c: ~
200
'"
E
QQ-A-2501ll
B632 B211
MIL-F-17132
B221
QQ-A-200/8
B808 B241 B483 B210
QQ-A-200/8
4115 4116 4117 4128 4129 4150 4160 4161 4172 4173 4113
Tube(condenser) Tube(condenser withintegralftns) Thbe(welded)
250
II
Pipe Pipe(gasandoil transmission) Forgings Forgingstock
~irblast
10
Rivet wire Impacts Structural pipeandtube(extruded) Aiclad6061 Sheetandplate
;j1
6061·Tt sheet
60 1250
2500
3150
5000
6250
1500
Th ickness, JIm
QQ-A-22518
WW-T-700/6
MIL-T-7081 B234 B404 B313 B549
Tube(waveguide)
t\.
80
'x '0
Tube(hydraulic)
~
90
~
E :> E
150
B209
V Water spray
.;;;
~
1500
0 '\ """,
s: l5>
:;;
6250
J,lrn
Thickness, 0.001 in. 100
100
5000
Thickness,
LIVE GRAPH
4025 4026 4027 4043 4053
4079 4080 4082 4081 4083
50 1250
ASTM
Tube(extruded. seamless)
6061.Tt sheet
Specification No. Government
AMS
4127 4127 4146
B241 B345 B247
B316 B429 4020 4021 4022 4023
MIL-W-85 MIL-W-23068 MIL-W-23351 MIL-P-25995 QQ-A-367.MIL-A-22771 QQ-A-367 QQ-A-430 MIL-A-12545 MIL-P-25995
B209
6061 Aluminum: Time-temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys. A = 7075; B = 2017; C = 6061; D =6063
600
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500
-:.-:-,:,,--==.~.
400
A
U
0.300
I-
200 100 0
1
100
10
t,s
1000
2041 Heat Treater's Guide: Nonferrous Alloys
6061 Aluminum. Aging characteristics of 6061 sheet
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LIVE GRAPH
LIVE GRAPH
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Click here to view
Click here to view
6061 Aluminum. Aging characteristics of aluminum sheet alloys at room temperature, at 0 °C (32 OF), and at -18°C (0 OF)
LIVE GRAPH Click here to view
6061
350..---..---,...---,...----,----,-·---.---.----,50
600
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104
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30
500
70
-
400 105
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300 40
'C
250
"
m 40 200
--
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35
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Duration of precipitation heat treatment, h
AT .;;;
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_205'C _ 170°C _'50'C 3011---+- 230°C 1340 of) 1300 'FI----i-----if----; 1450 ° FI 1400 'Ft
I yea,
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30 mll~
10
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103
Elapsed lime after qucnchmq, h
If. c"
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6061 Aluminum: Typical tensile properties of 6061-T6 or T651 at various temperatures
0
iii 0 0
0.01
0.1
10
104
100
Duration of precipitation heat treatment, h
LIVE GRAPH Click here to view
LIVE GRAPH Click here to view
105
'Thmperalure of "C
-196 -80 -28 24 100 150 205 260 315 370
-320 -112 -18 75 212 300 400 500 600 700
'ThnsUestrength(a) MPa ksi
414 338 324 310 290 234 131 51 32 24
60 49 47 45 42 34 19 7.5 4.6 3
rleld strength (0.2% oll"set)(a) ksl MPa
324 290 283 276 262 214 103 34 19 12
47 42 41
40 38 31 15 5 2.7 1.8
Elongation, %
22 18 17 17 18 20 28 60 85 95
(a) Lowest strength for exposures up 10 10 000 h at temperature, no load; testloading applied at 35 MPalmin (5 ksilmin) to yield strength and then at strain rate of 5%/min to fracture
Next Page
Wrought Aluminum and Aluminum Alloys 1205
-
6061 Aluminum: Time-temperature property diagrams. Composition: AI-0.55% Mg-0.6B% Si-0.01% Cr-0.014% Mn-O.ll% Fe-0.036% Cu-O.Ol% li0.002% B. Treatment: Solution heat-treated at 550°C (1020 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 3B.4 ksl (264 MPa) Iso-yield curve is 90% of quenched and aged yield strength
1 411'
90% ofT6 YS
100 141
6'
~ ~
'00
(nn
0
Qj
~
~
...
100 (1111
Qj
~
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Qj
Eo<
100
(1101
400 1104
100
10
1000
Time of Isothermal Hold. s
6061 Aluminum: Time-temperature property diagrams. Composition: AI-0.9B% Mg-0.66% Si-0.12% Cr-0.12% Mn-0.3B% Fe-0.23% Cu-0.07% Zn-0.Q14% li-O.OOl % B. Treatment: Solution heat-treated at 540°C (1000 OF) for 1 to 1.5 h, down quenched to various temperatures into molten salt, held at temperature for varying times, water quenched, and aged. Maximum quenched and aged yield strength 40.5 ksi (2BO MPa) Iso-yield curve is 90% of quenched and aged yield strength
LIVE GRAPH Click here to view tIOO (4121
90% ofT6 YS
6'
o......... (41" 100
fr Qj
~
II"" e:8
'00
100
UIII
!lOO
l2IOl
100
10
11)00
Time of Isothermal Hold, s
6061 Aluminum: Typical mechanical properties
Temper
Elongation, % 1.6 nun (0.0625 In.) 13 nun (0.5 In.) thkk specimen diam specimen
ThnsUe strength MPa k.si
y,.ld slrength MPa ksl
124 241 310
18 35 45
55 145 276
8 21
40
25 22 12
117 228 290
17 33 42
48 131 255
7 19 37
25 22 12
Shearlllrength
MPa
ksi
83 165 207
12 24 30
76 152 186
22 27
Bar 6061
0 T4,T451 T6, T651
30 25 17
AIc1ad 6061
0 T4,T451 T6,T651
11
Previous Page Wrought Aluminum and Aluminum Alloys / 221 7050 Aluminum: Typical axial fatigue strength at lo7cycles Fntipues t r e d (mar stm)
Product and temper
Stress ho,R
Smmrbspeeimens
ma
kri
Plate, 25-150 m m (1lo 6 in.) thick 2842 T6typelemPers 0.0 190-290 T73m tempers 0.0 170-300 2444 Extrusionsr,295m m (1.16in.) thick T76511temper 0.5 320-340 46-50 0.0 180-210 26-30 -1.0 130-150 19-22 Die forgings, 25-150 mm (1 to 6 in.) thick 0.0 210-275 3040 "736 temper Hand forgings,144 x 559 x 2130 m m (4.5 x 22 x 84 in.) "73652 temper Longiiudinal 0.5 325 47 0.o 225 33 -1.0 145 21 Long transverse 0.5 275 40 0.0 170 25 -1.0 125 18 Short transverse 0.5 260 38 0.0 170 25 -1.0 115 17
Notched speeimem(n) kd
MPn
...
...
50-90
7.5-13
110-125 70-80 35-50
16-18 10-12 5-7
75-115
11-17
145 90 50 115 90 50 115 60
21 13 7 17 13 7 17 9 7
50
(a)Notch fatigue factor, 4, of 3.0
Chemical Composition. Composition Limits. 0.10 Cu max, 0.10 Mgmax,0.10Mnmax,0.70Simax+Fe, 0.80 to 1.30Zn,0.05 othersmax (each), 0.15 others rnax (total), bal A1 Specifications (US. andlor Foreign). ASTM. B 209; SAE.J454; UNS. A97072
Characteristics Major alloying element: 1.0 Zn.
Typical Uses. Fin stock and cladding alloy for Alclad plate, sheet, and tube products with following core alloys: 2219, 3003, 3004, 5050, 5052, 5154,6061,7075,7475,7178
7072 Aluminum: Mechanicalproperty limits for 7072 fin stock
mper
'lkmllestrength MLnimum Madmum Mpn hi Mpn hi
0 H14 H18 H19 H25 H111.HZ11
97 131 145 107 62
55
8.0 14.0 19.0 21.0 15.5 9.0
90 131
13.0 19.0
Yleld
Elongation (min),
MPa
ksi
%(n)
21 83
3 12
15-20 1-3
......
...... ......
148 97
83 41
......
21.5 14.0
12 6.0
102 1
2-3 12
(a)In5Omm(2in.).~e~a~geofvaluesap~~~~~lu~,s~~~~ume varies with thicknessof the mill product
Recommended Heat Treating Practice Annealing. Temperature is 345 "C (650 OF)
7075, Alclad 7075 Chemical Composition. Composition Limits (7075). 1.20 to 2.00 Cu,2.10to2.90Mg,0.30Mnmax,0.40Simax,0.50Femax,0.18 to0.28 Cr, 5.10 to 6.10 Zn, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal A1 Composition Limits (Alclad 7075). 7072 cladding-0.10 Cu max, 0.10Mgmax,0.10Mnmax,0.70Simax+Fe,0.80to 1.30Zn,0.05 others rnax (each), 0.15 others max (total), bal A1 Specifications (US. and/or Foreign). AMS. (See adjoining Table); ASTM. ( S e e adjoining Table); SAE. 5454; UNS. A97075; Government. (See adjoining Table); (Aushia) Onorm AlZnMg-Cul.5; (Canada) CSA ZG62, ZG62 Alclad; (Switzerland) VSM Al-Zn-Mg-Cu: Alclad, Al-Zn-
Mg-Cu-Al; (United Kingdom) BSL.95, L96; (Germany) DIN AlZnMgCul.5; Werkstoff-Nr'3.4365. ISO: AlZn6MgCu
Available Product Forms. Sheet, plate, rolled or cold finished wire, rod, and bar; extruded rod, bar, and shapes; extruded tubing; drawn tubing; die forgings, hand forgings; rolled rings
Characteristics Major alloying elements: 5.6Zn-2.5Mg-1.6Cu-0.23Cr
Typical Uses. Structural aircraft parts and other highly stressed structural applications requiring very high strength and good resistance to corrosion.
222 / Heat Treater's Guide: Nonferrous Alloys
Standard specifications
7075 Aluminum: Typical plane-strain fracture toughness Speei6eathn No.
Mlll form andcouditmn
AM!3
m
4038
B 209
Minimum
Government
Bare pmducts Sheetand plate
4078 4122 4123 4124 4154 4167 4168 4169
'hk(extruded, seamlw) nbe (drawn, seamless)
... ...
... ... ... B211 ... ... B 221 ... ... ...
Forgings and forging stock
4139
B 241 B 210 B 247
4045
WE,rod,and bar (rolled or cold finished)
Rod bar. shapes,and tube (extruded)
Impacts Rivets
Alclad pmducts Sheet and plate
... 4110 ...
Tapered sheet and plate
4039 4048 4049 4047
Alclad oneside products Sheet and plate
4046
...
... ... QQ-A-2299 ... ... QQ-A-200/1 ... ... ... ... ...
B316
QQ-A-361 IVIIGA-2217 1 =A-12545 QQ-A430
B 209
QQ-A-250/13
... ...
...
...
... ...
B 209
MPaGhi&
Aversge
MW-hikYK
hlaximum MPaGksiG
GTorientation Plate
QQ-A-250l2 4044
h d u c t and temper
... ...
QQ-A-250118
T65 1 T7351 Extruded shapes T6510.1 T73 10,l Forgings T652 T7352 T-Lorientation
28.6 33.0
26
30
29.1
21
......
28.6 34.1
26 31
30.8 36.3
28 33
35.2 31.4
32 34
26.4 29.7
2A 21
28.6 34.1
26 31
30.8 38.5
28 35
22.0 21.5
20 25
24.2 31.9
22 29
25.3 36.3
23 33
m.9 24.2
19 22
24.2 26.4
22 24
28.6 30.8
26
......
28
......
25.3
23
25.3 21.5
23 25
28.6
26
16.5 20.9
15 19
11.6 22.0
16 20
19.8 23.1
18 21
19.8
18
20.9 22.0
19 20
24.2
22
......
18.1 23.1
17 21
21.5
25
Plate T651 T7351 Extludedshapes T65 10,l T73 10.1 Forgings T65 1 T7351
......
20.9
19
...... ......
Die and hand forgings are treated to W and W52 tempers at temperature of 470 "C (880 O F ) . After solution treatment parts are quenched in water at a temperature ranging from 60 to 80 "C (140 to 180 OF). Also after solution treatment and prior to precipitation treatment, parts are stress relieved by stretching to produce a specified amount of permanent set
General Considerations.
Recommended Heat Treating Practice
Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching in water by total immersion, unless otherwise indicated, water should be at room temperature andmaintained at a temperature below 38 "C (100 O F ) during quenching cycle. Use of high-velocity, high-volumejets of cold water also is effective in treating some materials Temperatures given here are nominal and should be attained as rapidly as possible and maintained within f 6 "C (f10 "F) during time at temperature
Solution Heat Treating. Sheet is treated to W temper at temperature of 480 "C (900 OF). With optimum homogenization, temperatures up to 495 "C (920 OF) are sometimes acceptable Plate is treated to W and W51 tempers at temperature of 480 "C (900 OF). With optimum homogenization,temperaturesup to 495 "C (920 OF) are acceptable. When plate thickness is over 100 mm (4 in. and rod diameter or bar thickness exceed 100 mm (4 in.), a maximum temperature of 450 "C (840 O F ) is recommended to avoid eutectic melting. Subsequent to solution treating and prior to precipitation treating, parts are stress relieved by stretching to produce a specified amount of permanent set Rolled or cold fmished wire, rod, and bar are treated to W and W51 tempers at 490 "C (910 OF). With optimum homogenization, temperatures up to 495 "C (920 O F ) are sometimes acceptable. When rod diameters or bar thicknesses exceed 100 mm (4 in.), a maximum temperature of 450 "C (840 "F)is recommended to avoid eutectic melting. Subsequent to solution treating and prior to precipitation treating, parts in W51 tempers are stress relieved by stretching to produce or specified amount of permanent set Extruded rod, bar, and shapes and tubing, are treated to W, W510, and W511 tempers at 465 "C (870 OF). Subsequent to solution treating and prior to precipitation treatingparts in W510 and W5 11tempers are stress relieved by stretching to produce a specified amount of permanent set Drawn tubing is treated to W temper at 465 "C (870 OF)
25
......
Plate T65 1 T7351 Extrudedshapes T6510,l T7310,l Forgings T652 n352 S-Lorientation
Caveat: caution should be exercised in T6 temper applications where sustained tensile stresses are encountered, either residual or applied, particularly in the transverse grain direction. Alternative: consider173 temper even though there is some sacrifice in strength. For additional information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristicsand Applications" in introduction to this chapter
21.5
Precipitation Heat Treating (Artificial Aging). General Considerations.
0
Nominal metal temperatures should be reached as rapidly as possible and maintained within f 6 "C (&lo O F ) of nominal during time at temperature Time at temperaturedepends on time required for load to reach temperature. Times given here are based on rapid heating, with soaking time measured from time load reaches within 6 "C (10 "F) of applicable temperature
For detailed information on the treatment of specificproducts and tempers, see adjoining Table titled, 'Typical Precipitation Heat Treatments for Aluminum Alloy 7075" Annealing. See table titled 'Typical Annealing Treatments for Aluminum Alloy Mill Products," in introduction titled "Heat Treating Aluminum Alloys." Check footnotes (a), (b), and (c)
Wrought Aluminum and Aluminum Alloys / 223 7075 Aluminum: Tensile properties 'lkndlertmqth b p e r
Yield m g t h
Uongathn(a),
ma
LEi
ma
kd
96
228 572 503 221 524
33 83 73 32 76
103 503 434 97 462
15 73 63 14 67
17 11
mica1properties 0 T6,T651 T73 &lad 0 T6. T651 Pmperty Limits Sheet and plate 0 Sheet T6, T62 0.008-0.011 in. thick 0.012-0.039 in. thick 0.040-0.125 in. thick 0.126-0.249 in. thick T73 T76 Plate T62.T651 0.250-0.499 in. thick 0.500-1.000in. thick 1.001-2.000in thick 2.001-2.500 in thick 2.501-3.000in. thick 3.001-3.500in. thick 3.5014.000 in. thick T7351 0.250-2.000in. thick 2.001-2.500in. thick 2.501-3.000in. thick T765 1 0.250-0.499 in. thick 0.500-1.000 in. thick Alelad sheet and plate 0 0.008-0.062in. thick 0.063-0.187 in. thick 0.188-0.499in. thick 0.500-1.000in.thick Alclad sheet T6, T62 0.008-0.011 in. thick 0.012-0.039 in. thick 0.040-0.062 in. thick 0.063-0.187 in. thick 0.188-0.249 in. thick T73 0.040-0.062 in. thick 0.063-0.187 in. thick 0.188-0.249 in. thick T76 0.125-0.187h thick 0.188-0.249 in. thick Alclad plate T62,T651 0.250-0.499 in. thick 0.500-1.000 in. thick 1.001-2.000 in. thick 2.001-2.500in. thick 2.501-3.000in. thick 3.001-3.500in.thick 3.5014.000in. thick T7351 0.250-0.499 in. thick 0.500-1.000in.thick T7651 0.250-0.499 in. thick 0.500-1.000in. thick
17 11
Minimum
Minimum
Minimum
...
145 (max)
21 (rnax)
10
74 76 78 78 67 73
434 462 469 476 386 427
63 67 68 69 56 62
5 7 8 8 8 8
78 78 77 76 72 71 67
462 469 462 441 42 1 400 372
67 68 67 64 61 58 54
9 7 6 5 5 5 3
476 455 441
69 66
64
393 359 338
57 52 49
6-7 6 6
496 490
72 71
421 414
61 60
8 6
248 (max) 262 (max) 269 (max) 276 (max)
36 (max) 38 (max) 39 (max)
138 (rnax) 138(rnax) 145 (max)
20 (max)
9-10 10 10 10
469 483 4%
68 70 72 73 75
400
58 60 62 63
434 441 455
63
276 (max)
510 524 538 538 462 503
538 538 531
524 496 490 462
40 (m)
40 @ax)
...
20 @ax) 21 (max)
...
64
5 7 8 8 8
66
352 359 372
51 52 54
8 8 8
469 483
68 70
393 407
57 59
8 8
517 538@) 531@) 52W) 496@) 4W) 462@)
75 78@) 77@) 76@) 72@) 71@) 67@)
448 469@) 462@) 421W 4wb) 372@)
65 68@) 67@) 64@) 61@) 58@) 54@)
9 7 6 5 5 5 3
455 476
66 69
372 393
54 57
8 7
476 4W)
69 710
400 4140~)
58 @J(b)
8 6
503 517
64
414 427 434 441
(a) In 50 mm (2 in.) or 4d,w h a e dis diameter of reduced section of tensile test specimen. Where a range appears in this column,the specifiedminimum elongationvaries with thickness of the mill product. @)Forplate 13mm (0.500in.) or over in hickness, listed properties apply to core material only. Tensile and yield strengths of compositeplate are slightly lower lhanlisted value, dependingon thickness of cladding
224 / Heat Treater's Guide: Nonferrous Alloys
Testing temperature, O F
100
600
7075 Aluminum. Effect of temperature on tensile properties of Alclad 7075-T6
Testing temperature, O F
300
200
80 600
70
400
60
c
I
60
C
40
6 300 e 6 200
30 20
100 10 0
0
50
160
100
0 200
Testing temperature, O C
Testing temperature, O C
LIVE GRAPH
LIVE GRAPH
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Click here to view
600 I
I
I
I
I
I
80
500 '
70
400
60
c
s
60
300
3
40 In
In
200
30 20
100 10
0.1
I
I
1
10
I
I0 10000
1000
100
Rupture time, h
7075 Aluminum: Typical tensile properties at various temperatures
7075 Aluminum. Cooling curves for 7075-T6 sheet
LIVE GRAPH Click here to view 500
T6,T651tempers -196
40
-320 -112 -18
-28 24 15 100 212 150 300 205 400 260 500 315 600 270 700 "73, T7351 tempers -1% -320 -80 -112 -28 -I8 24 75 100 212 150 300 400 205 260 500
703 621 593 572 483 214
102
110
16 11 8 6
76 55
41
90 86 83 70 31
634 545 511 503
448 186 87 62 45 32
92 19 75 73 65 27 13 9 6.5 4.6
9 11 11 11 14 30 55 65 70 70
72 67 65 63 58 27 13 9 6.5 4.6
14 14 13 13
900 800
400 0
700 , u
?600
I
Z
300
I
E
500
I-"
I-" 400
200
300
634 545 524 503 434 214 110 76
315
600
55
370
700
41
92 19 76 73 63 31 16 11 8 6
496 462 448 434
400 186
90 62 45 32
15
30 55
65 70 70
(a) Lowest smngth for exposures up to 10 OOO h at lemperarUre, no load; test loading applied at 35 W m i n (5 ksiimin) to yield smgth and hen at shainrate of 5%/min to fracture.(b)In5Omm (2 in.)
i
2
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0
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10
20
15
Time, I
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30
35
Wrought Aluminum and Aluminum Alloys / 225
700
600
OIh
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75
500
a
I i' 400
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._ 300 -
v)
v)
F
7075 Aluminum. Effect of strain rate and temperature on tensile strength of 7075-T6
100
F 200
25
100
0 (
1
0.1
0
10 ioo Strain rate, mmlm s 1
103
.
7075 Aluminum. Effect of surface conditions on the midplane cooling of a 13 mm (0.5 in.) thick plate of 7075 from quenching in (a) 20 "C (70 O F ) water and (b) boiling water
500 8oo 400
' ?i c e
f
F
600
300
3
c
e
200
100
Black oxide etched coating
As-rolled surface
Sanded surface
0 0
1
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4
3
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6
Time, s
400
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100
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0 10
20
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40 Time. s
50
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80
226 / Heat Treater's Guide: NonferrousAlloys 7075 Aluminum: Typical Precipitationheat treatments Me(al tempemtum(a) &Y
7075(g)
PmdUd
Sheet
Plate
Rolled or c o l d f ~ s h e d wire, rod, and bar
Extrudedrcd, barand shapes
Extruded tube
Drawntube Die forgings
OF
Appmrtheat tempemturn@) Hours
7075 Aluminum. C-curve for 99.5% maximum yield strength of 7075-T6sheet
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hper desiion
T6 T73(e) T7W T62 T651(c) T7351(c)(e) T7651(c)(e) T62 T6 T73(e) T62 T651(c) T7351(c)(e) T6 T73(e) T76(e) T62 T651qc) T73510(c)(e) T76510(c)(e) T6511(c) T73511(c)(e) 'I765 1l(c)(e) T6 T73(e) T62 T651qc) T73510(c)(e) T6511(c) T73511(c)(e) T6 T73W T62 T6
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.f m
d
900
400
Y
700
+E
E
500
E
r-"
200
300 100 0.1
10
1
100
10 000
1000
Critical lime. I
7075 Aluminum. Through-thickness property variations due to quench rate and temperature-rise effects in 7075-T62 plate 75 rnm (3 in.) thick
LIVE GRAPH Click here to view Depth, in.
I
60
1
,
- 0 Control specimen
1
1
Quenched from side A only A Quenched from side 8 , inlempled after 3 s
T652(d) T7352(d)(e) T6
(a) The nominal metal temperature should be anained as rapidly as possible and maintained f10"F of nominal during the time at temperature. (b)The time at temperaturewill depend on time required for load to reach temperature.The timesshown are based on rapid heating, with soaking time measuredfromthetimethelcadreacheswithin10"Foftheapplicabletemperamre.(c)Sms-relieved by sktching. muired 10produce a specified amount of permanent set subsequent to solution heat matmentand,whereapplicable. priortoany precipitation heat treatment. (d)S!xess-relievedby 1to 59bcoldreductionsubsquenttosolution heattreatmentandpriortoprecipitationheattreatment.(e) Thisagingofaluminumalloys7075and7178fromany tempertotheT73(applicableto7075only) or 'I76 temper series required closer than normal conaols on aging practice variables such as time, temperature. heating-up rates, etc.,for any given item. In addition to the above, when re-aging malerialintheT6ternperseriestothe'I73orT76temperseries,thespecificconditionoftheT6temper material (such as its property level and other effect of processing variables) is extremely important and will afSect thecapabilityof there-aged material toconfom to the requirementsspecified for the applicableT13orT76temperseries.(f)Theagingpr~ticewillv~ withtheprcduct,size,natureof equipment. 1oadingproceduresandfurnaceconaolcapabilities.Theoptimumpracticefor aspecific item can be ascertained only by actualtrial treatment of the itemunder specific conditions. %ical p d u r e s i n v o l v e a two-stage&eamentcomprisedof3to30hat 12OoC(25O0F)followedby15 to 18 hat 165 "C(325 OF) forextrusions.An alternatetwo-stage treatment of 8 hat 100"C (210 OF) followed by 24 lo 28 h at 165 "C (325 OF) may be used. (g)An alternate two-stage treahmnt comprisedof4hat95"C(205"F)followedby8hatl~oC(3lSo~~omaybeused. QAnaltemate three-stage treatment comprised of 5 h at 100 "C (210 "F)followed by 4 h at 120 "C (250 O F ) followed by 4 h at 150"C (300 "F)also may be used. (i) 'ho-stage treatment comprised of 6 to 8 h at 105 "C (225 OF) followed by a second stage of: 1) 24 to 30 hat 165 "C (325 "F)for sheet and plate, 2) 8 to 10hat 175"C(350 "F)for rolled or cold-f~shed rod and bar. 3) 6 to 8 hat 175'C (350 OF) for extrusions and tube,and 4) 8 to 10hat 175"C (350 T )for forgings in T73 temper and 6 to 8 hat 175 "C (350 "F)for forgings in "7352 temper. 0) An alternatetwo-stage treatmentfor sheet. plate, tube,andextrusionscomprisedof6to8 hat 105"C(225"F)followedbyasecondstageof1410 18 h at 170 "C (335 OF) may be used providing a heating-uprate of-5 "C (25 "F)h is used. For rolled or cold-finished rodand bar the alternate treatment is 10hat 175 "C (350 "F)
c
i
300
Hand forgings
Rolledrings
@
0
1
I
50
1
1
1 Side 8
Deplh. mm
Side A
Deplh. in.
2
0
I .o
0.5
1.5
2.5
2.0
3.0
-
600
5 c
; 500
-. a
a
5
400
s
D
5
300 Side 8
Depth. mm
Side A
Depth. In.
0
I .o
0.5
15
20
3.0
25
550
0"
;
70
D C
60
?
-=-
50
350
5
-5 -
5
5
40
-
30
5
250
D
C m
-I
150 0
2 f
450
1 10
20
30
40 Depth, rnrn
Side A
50
MI
10
80 Side 8
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Wrought Aluminum and Aluminum Alloys / 227
7075 Aluminum. Aging characteristics of 7075 sheet at room temperature, at 0 "C (32 OF), and at -1 8 "C (0"F)
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7075Aluminum. Effect of uphill quenching on deflectionof tines. Six-tine specimen was machined from 50 by 50 mm (2 by 2 in.) bar. Similar specimens machined from 25 by 25 mm (1 by 1 in.) and 75 by 75 mm (3 by 3 in.) bars had four and eight tines, respectively
LIVE GRAPH Click here to view 2600
+I300
0
E
-1300
c
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-0
c
0.1
1
10
102
103
0"
104
-2600
Elapsed time after quenching, h
-3900
-5200
J A
Quenched from liquid nitrogen to steam
2
-6500
3
4
Tine number
+50
+1300
0
0 0. I
1
10
102
103
104
E
Elapsed lime alter quenching, h
-1300
-50
-2600
-100
-3900
-150
x
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A -5200
Quenched from liquid nilrosen 10 steam I
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-I -200 6
Tine number
Elapsed time alter quenching. h
t50
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9
0 C
-50
-2
+
al
a -100 Quenched from -75 "C (-100 O F ) to steam AQuenched from liquid nitrogen to steam
-3900 1
2
3
4
5
6
7
-150 8
Tine number
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228 / Heat Treater’s Guide: NonferrousAlloys
Yield strength. kri
7075 Aluminum. Comparison of distribution of yield strength in heat-treated 7075-T6 clad sheet product with distribution in a single sheet. A is 95% probabilitythat not more than 1% of all material will fall below this value: B is 95% probability that not more than 10% of all material will fall below this value. (A and B refer only to curve representing 4290 routine mill tests.)
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I
Yield strength, MPa
7075 Aluminum. Iso-yieldstrength curves 225
LIVE GRAPH Click here to view
400 200
!+
9 E!
E!
2 L
2 175
350
0.
s 300
E
P
E 150
c ~
.P
.-C
P 125
250
100 0.01
0.1
1
10
100
1000
Aging time, h
7075 Aluminum: Timetemperature-property diagram. Effect of time and temperature in interrupted quenching experiments on tensile and yield strength of alloy 7075, expressed as percentages of strengths obtained by quenching without interruption
900
800 L
700 LIVE GRAPH
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t
500
E
I-” 400 300 200 0.I
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I .o
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Tensile strenglh strength
- -Yield
10 Time, sec
I I 1 1111
I00
I
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I I I 1
1000
Wrought Aluminum and Aluminum Alloys / 229 ~
~~
~~
7075 Aluminum: Time-temperature-property diagram. Curves at 95% of maximum tensile stress for various alloys
6
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500
5
300
I-
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.
'O0I 100
01
I
1
10
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1 0
100
t.s
7075 Aluminum: Time-temperature-property diagram, Effectsof precipitationtreatment time and temperature on strength of 7075 plate quenched directly to the precipitationtreatment temperature
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35c
I
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U
3
Q
LL W
I
1 1 1 1 1 1
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OUENCHED FROM SOLUTION TREATMENT TEMPERATURE INTO WOOD'S METAL AT 200.F (94'Cl TO 350.F (177.C) CURVES ARE LOCI OF YIELD STRENGTH K S I AND ( K g / m m Z l
325
I-
I
150
300
a I 275
a
z
125 250
2
w
3
225
0
100 I
200 0.2
I I 0.5
I l l 1
I
2
5
10
20
100
50
HOURS AT QUENCH-AGING TEMPERATURE
7075 Aluminum: Yield-strength values for 7075-T6sheet predicted from cooling curves using average quench rate and quench factor Yieldstrength
M
Average quench rate for4W l o 290°C
Cold water DeMturedalcoholt0290"C(55OoF),thencold water Boilingwaterto315 oC(600°F),thencold water Still air to 370 "C (700 OF), then cold water
935
50
1680 90
30
55
5
9
Mepcwpd yield
0.464 8.539 15.327 21.334
506 476 458 468
73.4 69.1 66.4 67.9
Ykld rtreqgth
fromawrage
499 463 443 242
72.4 67.2 64.2 35.1
498 478 463 449
72.3 69.4 67.1 65.1
230 / Heat Treater's Guide: Nonferrous Alloys
7075 Aluminum: Time-temperature-property diagram. Effects of precipitationtreatment time and temperatureon strength of 7075 + Ag plate quenched directly to the precipitation treatment temperature 375
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W
5
325
l-
a a W
5
300
225
200 HOURS AT QUENCH-AGING TEMPERATURE
7075 Aluminum: Time-temperature-property diagram. Is0 yield strength curves
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200
100
7075 Aluminum: Effects of annealing treatments on ductility of 7075-0 sheet Anwaliog treatment
Tkatment I(d) Treabnent2(e) Treatment3(f)
EInnpationin tension(n), % in 50 m m (2 in.) for thickness of: 0.5mm 1.6 mrn 2.61~ (0.020 h) (0.064 in.) (0.lCnln)
12 14 16
12 14 16
12 14
...
Bendangle@),degms,forthieknesoE 1.6mm 2.61~ (0.064 h) (0.lCnin.)
82 91 92.5
Elongationin bending(c), %in501010 (2 h)forthielmest& 1.61~ 2.6 m m
(0.064in.)
(0.lrnh)
73 76
48 58
50 57
84
56
60
(a)Uniformelongationofgridded tension specimens. @)Bend angleatfustfrachue.(c)Elongation in bend testfor 1.3 mm(0.05in.)gagespanning frachue.(d) Soak2 hat415 f 14°C (775f25OF); fiunace coolto260aC~5000~at300C/h(500F/h~;aircool. (e)Soak2hat425°C(795"D,aicool;soak2hat 230"C(450"F),aircool. (f)Soak 1 hat425°C(795"F);fumacecoolto2300C(4500F)at300Ch (50"F/h);soak6 h at 230 "C(450 OF), air cool
roperty diagram. Comparison of yield strength C-curves for 7050-T76 and 7075-T6 sheet
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K
800
100
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....
.*---
100
I g
600
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ka BL w
c w
400
300
icrostructures.(a) 7075-0 sheet, annealed. The fine particles of MgZn, (dark) were precipitatedat lower temperatures during heating to or cooling from the annealing temperature. The insoluble particles of FeAI, (light gray, outlined) were not affected by the annealingtreatment. 25% HNO,. 500x. (b) 7075-0 sheet, annealed, cooled slowly from annealingtemperature. Platelets of MgZn, precipitated at grain boundariesduring slow cooling. 25% HNO,. 500x. (c) 7075-T7352forgings, solution heat treated, cold reduced, and artificially aged. Particles are insoluble (Fe,Mn)Al, (dark gray). Some unresolved Mg,Si may be present.This is a normal structure. Keller’s reagent. 250x. (d) 7075-T7352forging, solution heat treated, cold reduced, and artificially aged. Eutectic meltingtemperature was exceeded during solution heat treatment. Fusion voids (black areas) and agglomeration of insoluble phases (dark gray). Keller’s reagent. 250x
icrostr~ctures. 7075-T6sheet clad with 0.07 mm (0.0027 in.) of alloy 7072 for 1.6-mm (0.064-in.) total thickness. Particles in cladding (top) are Fe,SiAl,,; those in core are Cr,Mg,Al,, and (Fe,Mn)Al,. Keller’s reagent. 350x
.
707 inum: (a) Patting-plane fracture in 7075-T6 forging that contained a bushing in a machined hole. Fracture . Parting plane fracture in a 7075T6 forging that contained a bushing was caused by excessiveassembly stress. Keller’s reagent. 1 . 5 ~(b) in a machined hole. The fracture started at the machined hole and progressedparallel to the flow lines of the forging. Keller’s reagent. 8x. (c) Patting plane fracture in a 7075-T6 forging that contained a bushing in a machinedhole (machined hole at bottom). Woody, brittle fracture pattern is typical of garting-planefracture in this alloy. Not polished, not etched. 4x
s.(a)Typical ductile fracture 7075T6 Alclad sheet, showing the deformedgrains and neckingat the fracture. Keller’s reagent. 200x. (b) Brittle fracture in overheated 7075T6 Alclad sheet, caused by solid-solution melting at the grain boundaries. Keller’s reagent. 200x. (c) Typical branched intergranularstress-corrosioncracks in 7075-T6 extruded bar. Transverse section. Keller’s reagent. 200x
inu
inu
c ~ o s ~ r u ~ ~(a) u rFold, e ~ .or lap, at a machinedfillet in a 7075-T6 forging. Defectwas co nuous before machining. See etails of a small area of the portion of the defect at lower right. Keller’s reagent. 8x. (b) larged view of an area of the fold, or lap, at lower right in adjoining figure. Defect contains nonmetallic particles, oxides, and voids, which prevented it from welding, or healing, during forging. Keller’s reagent, 200x
s. (a) Surface appearance of a lap (at trough, center) in an alloy 7075-T6 forging. Forging flow lines bend in the vicinity of the lap, indicating that the defect occurred during forging. Not polished, not etched. lox. (b) Section through the forging lap shown in surface view in adjoining figure. The trough at the surface is at the left. The grains near the lap are deformed, which indicates that the defect occurred during forging. Keller’s reagent. 500x
icrostructures. (a) Fracturedlug of a 7075-T6 forging. Arrows illustrate sites at machined hole where stress-corrosion cracks originatedbecause of stress acting across the short transverse grain direction. Keller’s reagent. 2.75~.(b) Higher magnificationview of area of the fractured lug in figure that contains intergranularcracks caused by stress corrosion, which resulted when assembly of a pin in the machined hole produced excessive residual hoop stress in the lug. Keller’s reagent. 200x
rou
luminu
s. (a) Band of shrinkage cavities and internal cracks in an alloy 7075-T6 forging. The cracks developed from the cavities, which were produced during solidificationof the ingot and which remainedduring forging because of inadequatecropping. Keller’s reagent. 9x. (b) Area of the forging in figure above that contains rows of unhealedshrinkage cavities (black), shown at higher magnification. No cracks have developed from the cavities in this particular area. Keller’s reagent. 200x. (c) Area of the forging in figure above that contains intergranularand connecting transgranular cracks shown at a higher magnification.The cracks developed from shrinkage cavities. Keller’s reagent. 200x
ui
.
(a) Exfoliation-typecorrosion in an alloy 7075-T6 extrusion. Rapid attack was parallel to the surface of the extrusion and alongthe grain boundariesor along striations within elongated grains. Keller's reagent.20x. (b) Higher magnificationview of figure above (rotated go"), showing how the corrosion product caused the uncorroded, recrystallized skin of the extrusion to split away, resulting in a leafing action. Keller's reagent. 200x
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lurninurn
s. (a) Brittle fracture surfaces in a tension-test specimen machinedfrom 7075-T6 forging that contained a defect. (Shrinkagecavities and internal cracks.) Not polished, not etched. 3x. (b) Fracture in 7075T6 extrusion, showing segregation of chromium particles (light gray, fractured). Segregation originated in the ingot and persisted through to the final product. Keller's reagent. 200x. (c) Fracture in 7075-T6extrusion, showing a spongy inclusion of dross (center) and some segregation of chromium particles (left) at fracture surface, both of which originated in the ingot. Keller's reagent. 200x
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238/ Heat Treater's Guide: Nonferrous Alloys
7075 Aluminum: Microstructures. (a) Intergranular corrosion in 7075-T6 plate. Grain boundaries were attacked, causing the grains to separate. Keller's reagent. 200x. (b) Pitting-type corrosion (dark area) in the surface of an aircraft-wing plank machined from 7075-T6 extrusion. Keller's reagent. 200x
(a)
b
7175 Chemical Composition. Composition Limits. 1.2 to 2.0 Cu, 2.1 to 2.9 Mg, 0.10 Mn max, 0.15 Si max, 0.20 Fe max, 0.18 to 0.28 Cr, 5.1 to 6.1 Zn, 0.10 Ti max, 0.05 max other (each), 0.15 max others (total) Consequence of Exceeding Impurity Limits. Degraded fracture toughness Specifications (U.S. and/or Foreign). AMS. 4109, 4148, 4149, 4179; UNS. A97175
Annealing. Temperature, 415°C (775 OF) Aging. Temperature, 120 to 175°C (250 to 350 OF)
7175 Aluminum: Plane-strain fracture toughness of 7175-1736 forgings Plane-strain fracture toughness Minimum Average
Characteristics
Temperand orientation
Typical Uses. Die and hand forgings for structural parts requiring very high strength, such as aircraft components. T736 tempers supply high strength, resistance to exfoliation corrosion and stress-corrosion cracking, high fracture toughness, and good fatigue resistance
Recommended Heat Treating Practice Solution Heat Treating. Temperature, 515°C (960 OF); must be preceded by soak at 477 to 485 °C (890 to 905 OF). Quench from lower temperature
MPa,r,n
ks~
MPa,r,n
~
1736 L·T T·L,S·L
29.7 23.1
27 21
33.0 28.6
30 26
Hand forgings 1736 L·T T·L S·L
33.0 27.5 23.1
30 25 21
37.4 29.7 26.4
34 27 24
Die forgings
Wrought Aluminum and Aluminum Alloys /239
7175 Aluminum: Typical mechanical properties of 7175-T736 die forgings up to 75 mm (3 in.) thick -c
Temperature
-253 -196
OF
24 100
-423 -320 -112 -18 75 212
150
300
175
350
205
400
230
450
--SO
-28
'lime at temperature, h
0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000
Tensilestrength MPa ksi
876 731 621 600 552 490 490 496 503 503 496 427 427 427 393 310 241 365 379 338 262 200 165 324 310 228 165 124 124 262 228 159 117 97
90
127 106 90 87 80 71 71 72 73 73 72 62 62 62 57 45 35 53 55 49 38 29 24 47 45 33 24 18 18 38 33 23 17 14 13
At indkaled temperature Y",ld strength MPa ksI
745 676 572 552 503 476 462 476 483 483 476 414 414 414 372 296 214 345 345 324 241 179 131 303 283 214 221 103 90 241 214 145 103 83 76
EIongation(al, %
108 98 83 80 73 69 67 69 70 70 69 60 60 60 54 43 31 50 50 47 35 26 19 44 41 31 32 15 13 35 31 21 15 12 11
12 13 14 16 14 14 15 16 16 17 17 20 18 20 25 30 30 20 25 25 25 35 55 20 30 35 35 45 65 20 25 35 40 45 50
Thnsilesln:ngth ksI MPa
552 552 552 552 558 565 558 552 552 552 524 441 352 538 538 496 421 331 262 524 503 393 317 255 234 510 448 338 269 234 221
80 80 80 80 81 82 81 80 80 80 76 64 51 78 78 72 61 48 38 76 73 57 46 37 34 74 65 49 39 34 32
At room temperature after beating Yield sl",ngth Eiongation(al, MPa ksi %
503 503 503 510 510 517 503 503 503 496 462 359 248 490 483 427 331 228 152 469 427 296 207 138 110 441 359 228 145 103 97
73 73 73 74 74 75 73 73 73 72 67 52 36 71 70 62 48 33 22 68 62 43 30 20 16 64 52 33 21 15 14
14 14 14 14 14 14 14 15 15 15 16 17 18 14 14 16 16 18 20 16 14 16 18 20 25 16 16 17 19 25 25
(a) In 50 nun (2 in.)
7178, Alelad 7178 Chemical Composition. Composition Limits (7178). 1.60 to 2.40 Cu. 2.40 to 3.10 Mg, 0.30 Mnmax, 0.40 Si max, 0.50 Fe max, 0.18 to 0.35 Cr. 6.30 to 7.30 Zn, 0.20 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Composition Limits (Alclad 7178). 7011 cladding--o.05 Cu max, 1.00 to 1.60 Mg, 0.10 to 0.30 Mn, 0.15 Si max, 0.20 Fe max, 0.08 to 0.20 Cr. 4.00 to 5.50 Zn, 0.05 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al. 7072 cladding-i-Odtl Cu max, 0.10 Mg max, 0.70 Si max + Fe, 0.80 to 1.30 Zn, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). AMS. Extruded wire, rod, bar, shapes, and tubing: 4158. Alclad 7178, sheet and plate: 4051, 4052; ASTM. (See adjoining Table); SAE. J454; UNS. A97178; Government. (See adjoining Table)
Standard specifications MiUformand condition
Sheetandplate
B209
WIre,rod, bar,shapes,andtube(extruded)
B221
Rivet wire
B316 B241 B209
Alcladsheetandplate
Characteristics Major alloying elements: 6.8Zn-2.7Mg-2.0Cu-0.3Cr Typical Uses. Aircraft and aerospace vehicles where high compressive yield strength is required. Caveat: the T6 temper is highly susceptible to exfoliation corrosion. Improved resistance is obtained with T76 temper, which has mechanical properties similar to those of7075-T6. For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice Specillcation number ASTM Government
Tube (extruded, seamless)
Available Product Forms. Sheet and plate; extruded wire, rod, bar, shapes, and tubing; rivet wire; extruded and seamless tubing; Alclad sheet and plate
QQ-A-250114 QQ-A-250121 QQ-A-2ooll3 QQ-A-2oo/14
QQ-A-250/15 QQ-A-250122 QQ-A-250128
Solution Heat Treating. • Sheet is treated to W temper at 470°C (875 "F) • Plate is treated to W temper at 470°C (875 "F), In treating plate to W51 temper, parts are stress relieved by stretching to produce specified amount of permanent set after solution treatment and prior to precipitation treatment • Rolled or cold finished wire and rod are treated to W temper at 465°C (870 OF)
240 I Heat Treater's Guide: Nonferrous Alloys material, such as property levels, is extremely important and will affect capability of the re-aged material to conform to requirements of the 173 or 176 temper series • Nominal metal temperatures should be attained as rapidly as possible and maintained at ±6 °C (±1O "F) during time at temperature • Time at temperature depends on time needed for load to reach temperature. Times given here are based on rapid heating, with soaking time measured from time load reaches within 6 °C (10 "F) of the applicable temperature
• Extruded rod, bar, and shapes are treated to W temper at 465°C (870 "F), Product treated to W510 and W511 tempers is stress relieved by stretching to produce specified amount of permanent set after solution treatment and prior to precipitation treatment
General Considerations. • Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. Unless otherwise indicated, when material is quenched by total immersion in water, water should be at room temperature and suitably cooled to remain below 38°C (100 "F) during quenching cycle. Use ofhigh-velocity, high-volume jets of cold water also is effective for some materials. For additional details see MIL-H-6088 or ASTM B 597 • Nominal metal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature. Times given here are based on rapid heating with soaking measured from time load reaches within 6 °C (10 OF) of applicable temperature
7178 Aluminum: Typicaltensile properties -c
OF
T6, T651 tempers -196 -320 -112 --110 -18 -28 24 75 100 212 149 300 204 400 260 500 316 600 371 700 T76, T7651tempers -196 -320 -112 --110 -18 -28 24 75 100 212 149 300 204 400 260 500 316 600 371 700
Precipitation Heat Treating (Artificial Aging). • Sheet is treated to T6 and T62 tempers at 120°C (250 OF). In treating to 176 temper a two-stage treatment is used: 6 to 8 hat 105°C (225 OF) is followed by 24 to 30 h at 165°C (325 "F) • Rolled or cold finished wire and rod are treated to T6 temper at 120°C (250 oF) for 24 h • Extruded rod, bar, and shapes are treated to T6, T62, and T6510 tempers at 120°C (250 OF) for 24 h. Product treated T6510 temper is stress relieved by stretching to produce specified amount of permanent set after solution treatment and, where applicable, prior to precipitation treatment. Product in 17610 and 176511 temper is subjected to twostage treatment: 3 to 5 h at 120°C (250 OF), followed by 18 to 21 hat 160°C (320 "P), Both tempers are also stress relieved by stretching like those in T6510 temper
General Considerations. • In aging 7178 from any temper up to 176 series, closer than normal controls on aging practice are required, for such variables as time, temperature and heating rates. In addition, when re-aging material in T6 temper series to the 173 or 176 series, the specific condition of the T6
Yieldsln!ngth (0.2% oflid)(a) MPa ksi
Thnslle5\rengtb(a) MPa ksi
Thmperature
EIoogatIoD(b). %
730 650 625 605 505 215 105 76 59 45
106 94 91 88 73 31 15 11 8.5 6.5
650 580 560 540 470 185 83 62 48 38
94 84 81 78 68 27 12 9 7 5.5
5 8 9 11 14 40 70 76 80 80
730 625 605 570 475 215 105 76 59 45
106 91 88 83 69 31 15 11 8.5 6.5
615 540 525 505 440 185 83 62 48 38
89 78 76 73
10 10 10 11 17 40 70 76 80 80
64
27 12 9 7 5.5
(a)Loweststrength for exposures up to 10000 h at temperature, no load;testloading applied at 35 MPalmin (5ksVmin) toyieldstrength andthenat strain rateof5%/min to fracture. (b) In 50rom(2in.)
7178 Aluminum: Creep-rupture properties of 7178-T6
-c 150
205
260
315
Thmperature
OF
300
400
500
600
TIme under stress,b
0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000
Stress fortreep of: Rupture stress MPa ksi
440 415 370 285 180 275 215 150 105 69 110 97
69 55 41 62 52 41 34
28
64
60 54
41 26
40 31 22 15 10 16 14 10 8 6 9 7.5 6 5 4
1.0%
0.2%
0.5%
0.1%
MPa
ksi
MPa
ksi
MPa
ksi
MPH
ksi
420 395 345 270 180 260 205 145
61 57 50 39 26 38 30 21 14 10 16 14 10 7.5 5 7.5 6.5 5.5 4.3 3.4
415 380 340 255 170 255 200 145 97 69 110 90 66 45 29 48 41 34 26
60 55 49 37 25 37 29 21 14 10 16 13 9.5 6.5 4.2 7 6 4.9 3.8
395 360 310 235 150 235 180 130 83 59 105 83 55 34
57 52 45 34 22 34 26 19 12 8.5 15 12 8 5
365 315 250 185 130 205 145
53
45 34 26
6.5 5 3.8
97
69 110 97
69 52 34 52 45 38 30 23
97
76 55 97 66
41
38 26
46
36 27 19 30 21 14 11 8 14 9.5 6 5.5 3.7
Wrought Aluminum and Aluminum Alloys /241
7178 Aluminum: Microstructures. (a) Alloy 7178-T76 sheet, 3.2 mm (0.125 in.) thick, exposed in a test chamber containing a fog of 5% NaCI for two weeks. Note exfoliation of the sheet. Keller's reagent. 75x. (b) 7178-T76 sheet, 3.2 mm (0.125 ln.) thick, clad with 0.127 mm (0.005 in.) of 7072 (3.2 mm, or 0.125 in. total thickness), in a test chamber containing a fog of 5% NaCI for two weeks. Sacrificial corrosion of cladding prevented exfoliation of sheet during testing. Keller's reagent. 75x
(a)
Chemical Composition. Composition Limits. 1.20 to 1.90 Cu, 1.90 to 2.60 Mg, 0.06 Mn max, 0.18 to 0.25 Cr, 0.12 Fe max, 5.20 to 6.20 Zn, 0.06 Ti max, 0.05 others max (each), 0.15 others max (total), bal Al Specifications (U.S. and/or Foreign). AMS. 4084, 4085, 4089, 4090; UNS.A97475 Available Product Forms. Sheet, plate, and rod
(b
Precipitation Heat Treating (Artificial Aging). GIl
GIl
GIl GIl
Characteristics Major alloying elements: 5.7Zn-2.30Mg-1.5Cu-0.22Cr Typical Uses. Bar and Alclad sheet and plate for aircraft fuselage and wing skins, spars, and bulkheads. Alloy provides combination of high strength and high fracture toughness.
GIl
General Considerations. GIl
For information on corrosion resistance, cold workability, machinability, brazeability, and weldability, see Table titled "Comparative Characteristics and Applications" in introduction to this chapter
Recommended Heat Treating Practice
Sheet is treated to T61 temper in a two-stage treatment: 120°C (250 OF) for 3 h, followed by 3 hat 160°C (320 "F) Sheet is treated to T761 temper by two-stage treatment: 120°C (250 OF) for 3 h, followed by 10 h at 165°C (330 OF) Plate is treated to T651 temper at 115°C (240 "F) for 24 h Plate is treated to T7351 temper in a two-stage treatment of 4 to 8 h at 100°C (210 OF), followed by 24 to 30 h at 160°C (320 oF) Rod is treated to T62 temper in a two-stage treatment: 3 h at 120°C (250 "F), followed by 3 h at 165°C (330 oF)
Nominal metal temperatures should be attained as rapidly as possible and maintained at ±6 °C (±1O OF) during time at temperature
Time at temperature depends on time.needed for load to reach temperature. Times given here are based on rapid heating, with soaking time measured from time load reaches within 6 °C (10 "F) of the applicable temperature
Solution Heat Treating. GIl
GIl
GIl
Sheet is treated to W temper at 480°C (900 "F), a temperature at which temperature melting may occur if thermal pretreatment is not adequate Plate treated at 480°C (900 OF) is also subject to melting if thermal pretreatment is not adequate. Product treated to W51 temper is stress relieved by stretching to produce specified amount of permanent set subsequent to solution treatment, and, where applicable, before solution treating Rod is treated to W temper at 480°C (900 OF)
General Considerations. GIl
GIl
Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. Unless otherwise indicated, when parts are quenched by total immersion in water, water should be at room temperature and suitably cooled to remain below 38°C (l00 OF) during quenching cycle. Use of high-velocity, high-volume jets of cold water is also effective for some materials Nominal metal temperatures should be attained as rapidly as possible and maintained within ±6 °C (±1O OF) of nominal during time at temperature. Times given here are based on rapid heating with soaking time measured from time load reaches within 6 °C (10 OF) of applicable temperature
7475 Aluminum: Typical fracture-toughness values L-T
T-L MPa", ~
Temper
8-L MParm ~
High-strength plate (Klc)(a) T651 T7651 T7351
42.9 47.3 52.7
39 43 48
High-strength sheet (Kc)(b) 1.2 rom(0.047 in.)thick,roomtemperature -54°C (--{)5 oF) 1.4 rom (0.055 in.)thick, roomtemperature -54°C (--{)5 oF) 1.6 rom(0.063 in.)thick,roomtemperature -54°C (--{)5 oF) 1.6 rom (0.063 in.) thick, roomtemperature -54°C (--{)5 oF) 1.6 rom(0.063 in.) thick,roomtemperature -54°C (--{)5 oF) 1.8 rom (0.071 in.)thick, roomtemperature -54°C (--{)5 oF)
37.4 38.5 41.8
143 90 136 87 122 102 150
111 147 109 149 125
34 35 38
29.7 30.8 35.2
27 28 32
130 82 123 79 112 93 137 101 134 99 136 114
(a)Determined usingstandard compacttensionspecimen. (b) Determined using400x 1120rom(16 x 44 in.) centercrackedpanelwithantibuck1ing guides
242/ Heat Treater's Guide: Nonferrous Alloys 7475 Aluminum Typical tensile properties at various temperatures Thmpemture OF °C
Timeat temperature, h
'Thnsile strength MPa ksl
At indi
At room temperature after heating
EIougation(a). %
Thnsile stm!gIh ksI MPa
Yieldstrength
Elougation(a), %
MPa
ksI
72 54 43 34 30 71 61 44 35 31 28 59 49 37 33 30 27 46 39 35 32 30 27 40
496 496 496 503 510 490 496 490 434 310 207 490 483 414 290 193 124 469 427 276 186 117 97 414 331 193 124 97 76 310 221 131 97 83 69 193 131 90 83 76 69 117
72 72 72 73 74 71 72 71 63 45 30 71 70 60 42 28 18 68 62 40 27 17 14 60 48 28 18 14 11 45 32 19 14 12 10 28 19 13 12 11 10 17
12 12 12 12 12 13 12 12 12 13 14 12 12 12 12 14 15 12 12 12 13 15 18 12 12 13 14 18 22 12 12 15 19 21 22 13 15 19 20 21
76 76 77 76 76 76 71 58 45 75 75 68 55 44 34 73 70
462 462 469 462 462 455 421 303 207 455 455 393 283 193 124 434 414
67 67 68 67 67 66 61 44 30 66 66 57 41 28 18 63 60
12 12 12 13 12 12 12 13 14 12 12 12 12 14 15 12 12
T61 sheet, to 6.35 mm (0.040.{I.249In.) thick -196 --SO -28 24 100
-320 -112 -18 75 212
683
607
579 552 O.I.{1.5 496 10 496 100 503 1000 503 10000 483 0.1-0.5 150 300 434 10 434 100 379 1000 262 10000 207 0.1 175 350 386 0.5 379 10 324 100 228 172 1000 10000 131 205 0.1 331 400 0.5 296 10 200 145 100 1000 110 97 10000 230 0.1 234 450 200 0.5 10 138 97 100 83 1000 10000 83 260 500 0.1 159 131 0.5 10 90 100 76 1000 69 10000 66 315 0.1 76 600 0.5 69 10 48 100 45 1000 45 10000 45 370 700 0.1 41 0.5 38 10-10000 34 425 0.1 800 24 0.5 23 480 18 900 540 1000 11 T761 sheet, 1 to 6.35 mm (0.040 to 0.249 ln.) thick -196 -320 655 --SO -112 579 -28 -18 552 24 75 524 100 212 0.1-10 455 100-1000 455 10000 441 150 300 0.1-0.5 400 10 393 100 359 1000 362 10000 207 175 350 0.1 352 0.5 352 10 303 100 228 1000 172 10000 131 205 0.1 290 400 0.5 276
600
99 88 84 80 72 72 73 73 70 63 63 55 38 30 56 55 47 33 25 19 48 43 29 21 16 14 34 29 20 14 12 12 23 19 13 11 10 9.5 11 10 7 6.5 6.5 6.5 6 5.5 5 3.5 3.3 2.6 1.6
545 517 496 462 462 469 476 448 414 414 372 255 179 365 365 310 221 159 110 317 283 193 138 97 76 221 186 131 90 76 62 152 124 83 69 59 48 69 62 41 38 38 38 34 32 27 20 19 15 9
87 79 75 72 67 67 68 69 65 60 60 54 37 26 53 53 45 32 23 16 46 41 28 20 14 11 32 27 19 13 11 9 22 18 12 10 8.5 7 10 9 6 5.5 5.5 5.5 5 4.7 3.8 2.8 2.7 2.2 1.3
10 12 12 12 14 14 13 13 14 18 17 19 23 28 19 19 21 23 30 40 17 19 26 35 45 55 19 21 30 45 60 65 20 25 45 60 70 70 35 45 65 75 80 80 70 70 85 85 85 50 3
95 84 80 76 66 66 64 58 57 52 38 30 51 51 44 33 25 19 42 40
565 503 483 462 434 434 421 386 379 345 255 179 338 331 290 221 159 110 269 262
82 73 70 67 63 63 61 56 55 50 37 26 49 48 42 32 23 16 39 38
11 12 12 12 14 13 14 18 17 19 23 28 19 19 21 23 30 40 17 19
(continued)
552 552 558 558 565 552 552 545 510
400 310 545 538 490 386 303 234 531 496 372 296 234 207 490 421 303 241 214 193 407 338 255 228 207 186 317 269 241 221 207 186 276
524 524 531 524 524 524 490
400 310 517 517 469 379 303 234 503 483
80 80 81 81 82 80 80 79 74 58 45 79 78 71 56 44 34
77
17
Wrought Aluminum and Aluminum Alloys /243 7475 Aluminum (continued) Thmpemture
OF
°C
230
450
260
500
315
600
370
700
'!ensilestrengtb MPa ksl
Time at temperature, b
10 100 1000 10000 O.l 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100 1000 10000 0.1 0.5 10 100-10000
200 145 110 97 221 193 138 97 83 83 159 131 90 76 69 66 76 69 48 45 45 45 41 38 34 34
29 21 16 14 32 28 20 14 12 12 23 19 13 11 10 9.5 11 10 7 6.5 6.5 6.5 6 5.5 5 5
Al indlcatedtempemture Yieldstrengtb MPa ksl
Eiongation!a),
%
MPa
ksi
At room temperature after beating Yield strength ksl MPa
193 138 97 76 207 179 131 90 76 62 152 124 83 69 59 48 69 62 41 38 38 38 34 32 27 27
26 35 45 55 19 21 30 45 60 65 20 25 45 60 70 70 35 45 65 75 80 80 70 70 80 85
372 296 234 207 462 414 303 241 214 193 386 338 255 228 207 186 310 269 241 221 207 186 276
54 43 34 30 67 60 44 35 31 28 56 49 37 33 30 27 45 39 35 32 30 27 40
276 186 117 97 386 324 193 124 97 76 283 221 131 97 83 69 186 131 90 83 76 69 117
28 20 14 11 30 26 19 13 11 9 22 18 12 10 8.5 7 10 9 6 5.5 5.5 5.5 5 4.7 3.9 3.8
'Ienslle strengtb
Elongatlon!a),
%
12 13 15 18 12 12 13 14 18 22 12 12 15 19 21 22 13 15 19 20 21
40 27 17 14 56 47 28 18 14 11 41 32 19 14 12 10 27 19 13 12 11 10 17
17
(a) In 50 rom (2 in.)
7475 Aluminum: Creep-rupture properties of 7475 sheet 1 to 6.35 mm (0.040 to 0.25 in.) thick 'Thmperature
OF
°C
Time under stress,b
St..... Corcreep oC: Rupture stre .. MPa ksi
0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000
552 545 545 538 524 490 476 455 427 386 414 386 352 262 186
0.1 1 10 100 1000 0.1 1 10 100 1000 0.1 1 10 100 1000
524 517 510 496 490 441 421
1.0%
0.2%
0.5%
0.1%
MPa
ksi
MPa
ksi
MPa
ksi
MPa
ksi
80 79 79 78 76 71 69 66 62 56 60 56 51 38 27
538 531 517 510 503 476 455 434 414 379 400 372 338 248 179
78 77 75 74 73 69 66 63 60 55 58 54 49 39 26
524 517 510 503 496 469 448 427
76 75 74 73 72 68 65 62 58 53 57 53 46 35 26
517 510 503 496
75 74 73 72
510 503 496
74 73 72
455 434 414 386 352 379 345 283 214 165
66
448 421 393 365
65 61 57 53
365 310 241 193 159
53 45 35 28 23
76 75 74 72 71 64 61 58 55 52 54 50 45 36 27
503 490 483 476 462 421 407 386 372 352 365 338 303 234 179
73 71 70 69 67 61 59 56 54 51 53 49 44 34 26
70 69 68 68 67 60 58 56 53 50 53 48 42 33 26
476 469 462 462 455 414 393 372 352 324 352 310 255 207 165
469 462 462 455 448 400 379 359 324
68 67 67 66 65 58 55 52 47
324 276 234 193 159
47 40 34 28 23
T61sbeet 24
75
100
212
150
300
400 365 393 365 317 241 179
63 60 56 51 55 50 41 31 24
T761sbeet 24
75
100
212
150
300
400 379 359 372 345 310 248 186
483 476 469 469 462 414
400 386 365 345 365 331 290 228 179
69 68 67 67
66 60 57 54 51 47 51 45 37 30 24
Aluminum Casting Alloys 201.0 (4.6Cu-O.7Ag-O.35Mn-O.35Mg:-O.251i) Commercial Names. Trade name. KO-l
Creep Rupture Properties
Specifications U.S. and/or Foreign. Fonner ASTM. CQ 51A; SAB.
See Table
382; UNS number. A0201O;AMS. 4228 and 4229
Fabrication Characteristics
Chemical Composition. Composition Limits. 4.0 to 5.2 Cu,0.15 to 0.55 Mg, 0.20 to 0.50 Mn, 0.10 Si max, 0.15 Fe max, 0.15 to 0.35 Ti, 0040
Machinability. Rating is excellent. Moderate to fast speeds and feeds are
to 1.0 Ag, 0.05 others (each) max, 0.10 others (total) max, bal Al
recommended
Consequence of Exceeding Impurity Limits. High iron or silicon de-
Weldability. Very good results can be obtained when joining castings of
creases tensile properties
alloy 201.0 to components of similar composition, using arc or resistance welding methods. Weld repair methods are not simple and require close control of the temperature of the casting during welding to prevent hot tearing and solidification cracking
Applications Typical Uses. Sand castings, permanent mold and investment castings. Structural casting members, aerospace housings, electrical transmission line fittings, insulator caps, truck and trailer castings, other applications requiring highest tensile and yield strengths with moderate elongation. Gasoline engine cylinder heads and pistons, turbine and supercharger impellers, rocker arms, connecting rods, missile fins, other applications where strength at elevated temperatures is important. Structural gear housings, aircraft landing gear castings, ordnance castings, pump housings, otherapplicationswherehigh strengthand high energy-absorptioncapacityare required
Finishing. Electroplating imparts an excellent finish to this alloy. Mechanical polishing also gives excellent results. Anodizing produces very good appearance and good protection
Precautions in Use. 201.0 castings should be specified in the 17 temper wherever resistance to stress-corrosion cracking is an important consideration (exceeds requirement of 60 days alternate immersion exposure-lO min/h to 3.5% NaCl and stressed to 75% of yield strength). T6 temper unsuitable for such applications
Alloy 201.0: Tensile properties
Mechanical Properties Tensile Properties. See Table Hardness. T4 temper, 95 lIB; T6 temper, 135 HB; 17 temper, 130 HB (500 kg load, 10 mm ball)
Alloy 201.0, 206.0: Heat treatment practices Temper desigoation
T4 T6 T7 T43(d)
Solutlon treatment
510-515°C (950-960"P) for2 h followedby 525-530°C (980-990°F)(a)for 14-20h(b) anda waterquench(c) SarneasT4
Aging treatment None
Roomtemperature for 12-24h, or ISO-ISS °C (305-315 oF)for20 h Roomtemperature for 12-24h, or Sarneas T4 185-190°C (365-375 oF)for5 h 525°C (980oF)for 20 h andwalerquenched(c) 24h at roomtemperature plus0.5101 h at 160°C(320 oF)
(a)Carefulcompositionandtemperaturecontrolmust be maintainedduringsolutionheat treatment in order10attainboth adequatesolutionand to prevent incipientmelting.(b)Soakingtimeperiods requiredfor averagesandcastingsafterload hasreached specifiedtemperature. Timechangesmay be required.Permanentmold and thin wall castings,in general,lake less time.(c) Al 65 10100°C (ISO10212"F), (d)ThmperT43developedforalloy201.0for improvedimpactresistancewithsome decreasein otherproperties
Recommended Heat Treating Practice Solution Temperature. See Table Aging Temperature. See Table
E!JlOsure Condltlon
OC
OF
Exposure time, h
TensUe strength MPa
ksi
YIeld strength(a) MPa
'Iypical propertles(c) 215 365 53 T4 435 70 485 T6 415 67 460 T7 Short-lime elevaled-temperature propertles(c) 55 360 380 T7 150 300 0.5-100 52 345 360 1000 275 10,000 315 46 47 310 325 205 400 0.5 285 41 270 100 230 250 36 1000 10,000 185 27 150 195 28 185 260 500 0.5 22 140 100 150 125 18 110 1000 140 20 130 315 600 0.5 12 75 100 85 60 1000 70 10 10,000 60 9 55 Average (avg) and minimum (min) values forT43 tempered) 416(avg) 60.3(avg) 257(avg) Integraltest 372(f) 54{min)(f) 220(f) bars(e) 393(g) 57(min)(g) 235(g) 391(avg) 56.7(avg) 241(avg) Teslbarscut 193(f) 338{f) 49(min)(f) fromcast360(g) 52(min)(g) 215(g) ings(b)
ksi
E1ongation(h), '.{,
31 63 60
20 7 4.5
52 50 40 45 39 33 22 27 20 16 19 11 9 8
6-8.5 8 7 9 10 9 14 14 17 18 12 30 39 43
37.3(avg) 17.4(avg) 32(min)(f) 34(min)(g) 35.0{avg) 15.2{avg) 28{min)(f) 31(min)(g)
(a)0.2%offset.(b)In 50 nun or2 in.Wherearangeappearsin thiscolumn,specifiedelongationvarieswithexposurelime.(c)Propertiesof'separately sandcast testbars.{d)TheT431emperwasdeveloped to provideincreasedimpactresistancewith somedecrease in other mechanicalproperties.(e) Propertyvaluesfrom210 tests,(f)Minimumvalueabovewhich99% of thepopulationvaluesisexpected10fall with a 95% confidencelevel.(g)Minimumvalueabove which90% of the population valuesis expectedto fallwith a 95% confidencelevel. (h) Propertyvaluesfrom 117tests
Aluminum Casting Alloys /245 Alloy 201.0: Creep-rupture properties of separately sand cast test bars -c
Thmperature
150
175(a)
OF
300
350
205
400
230
450
260
290
315
500
550
600
TIme under stress,h 10 100 1000 10,000 10 100 1000 10,000 10 100 1000 10,000 10 100 1000 10,000 10 100 1000 10,000 10 100 1000 10,000 10 100 1000 10,000
Rupturest..... MPa ksI Aboveyield Aboveyield 270 39 195 28 Aboveyield 250 36 26 180 19 130 250 36 26 180 19 130 14 95 185 27 20 140 95 14 70 10 140 20 95 14 70 10 50 7.5 90 13 66 9.5 48 7.0 34 5.0 59 8.6 43 6.2 31 4.5 23 3.3
Mlnlmumcreep rateat rupture stress, %perh
St..... (orcreep or,
1.0%
0.5%
0.25%
MPa
ksi
MPa
ksI
MPa
ksi
0.00013 0.000023
260 195
38 28
250 185
36 27
250 180
36 76
0.00095 0.000175
250 180 130 240 180 130 95 185 140 95 70 140 95 70 50 83 63 46 33 55 39 29 21
36 26 19 35 26 19 14 27
235 170 125 230 170 125 90 170 130 90 65 125 95 70 50 83 58 42 30 51 37 27 20
34 25 18 33 24 18 13 25 19 13 9.5 18 14 9.8 7.2 12 8.4 6.1 4.4 7.4 5.4 3.9 2.9
230 170 125 220 170 110 85 170 115 85
33 24 18 32 24 16 12 24 17 12 9 16 12 8.6 6.3 10 7.8 5.7 4.2 6.8 4.9 3.5 2.6
0.ססOO35
0.0145 0.0024 0.00046 0.ססOO88
0.028 0.0048 0.00083 0.000175 0.047 0.0080 0.00130 0.00028 0.062 0.0118 0.0022 0.00037 0.073 0.0126 0.0023 0.00043
20
14 10 20 14 10 7.5 12 9.2 6.7 4.8 8.0 5.7 4.2 3.0
60
110 85 60
45 69 54
39 29 47 34 24 18
(a)For thistemperature, properties areinterpolations
Alloy 201.0: Creep rates at various temperatures M1nimumcreep rate,%/h
150-c (300 oF) ksi MPa
1 X 10-5 1 X 10-4 1 X 10-3 0.01 0.1 1.0
165 255 (a) (a) (a) (a)
24.0 37.5 (a) (a) (a) (a)
St..... to produ"", minlmum ereeprate at: 260 -c (500 oF) 205 °C(400 oF) ksi ksi MPa MPa 64
98 155 234 (a) (a)
9.3 14.2 22.5 34.0 (a) (a)
28 43 66 103 155 241
4.0 6.2 9.5 15 22.5 35.0
315OC (600 oF) MPa ksi 11 17 26
41 62 97
1.6 2.5 3.8 6.0 9.0 14.0
(a)Abovethe minimum yieldstrengthspecification valueof345 MPa(50ksi)
204.0 (4.6Cu-O.25Mg-O.17Fe-O.17Ti) Commercial Names. A-U5GT (Pechiney). ELT-204 (French AFNOR)
Mechanical Properties
Applications
Tensile Properties. See Table
Typical Uses. Extensively used in France for high-performance sand and permanent mold castings
Recommended Heat Treating Practice
Permanent Mold. Break calipers in Bendix brakes for European cars 1958 through early 1980s (many million castings produced and used without problems)
Sand and Permanent Mold. Light- and heavy-duty impellers, structural parts for aerospace and auto industry. Ordnance parts for tanks, off-the-highway trucks and other equipment, light-weight, high-strength hand tools, light-weight power-train castings in auto and truck industry
The effects of solution treatment time depend to a considerable extent on the rate of solidification of the casting. A casting that has solidified rapidly permits a short solution treatment, whereas one that has solidified slowly requires a longer solution treatment time. The graphs in the Figure compare mechanical property test results of permanent mold test specimens with sand cast test specimens as related to the solidification rate. Note the much longer times at the solution time required for the slowly solidified sand cast bars as compared with the rapidly solidified penn anent mold test pieces. This difference is most pronounced in 204.0-type alloys. However, some degree of these solution heat-treatment effects on mechanical properties occurs in all aluminum casting alloys
246/ Heat Treater's Guide: Nonferrous Alloys
Alloy 204.0: Tensile properties and heat treatment Mean property valuesand estimatedstandard deviation
At least 5 days al20 °C (68 oF) 12 h at 140 °C (285 oF) 12hat 160 °C (320°F) 12hat 180 °C (355 oF)
110 105 115 125
400± 10 395±10 405±20 420±20
58±1.5 57 ± 1.5 59±3 6l±3
250± 10 230± 10 290±20 380±20
36±1.5 33±1.5 42±3 55±3
21±2 20±2 16±1 8±1
At least S days at 20 °C (68 oF) 12hat 140 °C (285 oF) 12 h at 160 °C (320 oF) 12 h at 180 °C (355 "P)
110 105 115 125
4OO±10 395±10 4OO±10 420±1O
58± 1.5 57± 1.5 58± 1.5 6l± 1.5
265± 10 250± 10 300±20 395±20
38.5± 1.5 36±1.5 43.5±3 57±3
14±1 13.5±1 9±1 3±0.5
Condition
Thnsllestrength MPa ksi
0.2% yield strength MPa ksi
Eiongationin
Precipilalion(realmenl(a)
Hardness, lIB
SOmm (2 in.). %
Permanent molds Y34(f4) Y33(f6)
Sand castings Y24(f4) Y23(f6)
(a) Precipitation treatment preceded by a ~olution treatment of 12 h at 530°C (985 oF) and a water quench
450
Ultimate tensile strength
,,- .....
400
'"
350
n,
:2; 300
I
I
58
/
'~" '/ ~-
0.2% yield strength
Alloy 204.0: Effect of solution treatment time on tensile properties. An AFNOR testpiece was cast in a permanent mold (solidification time 15 to 20 s). An Aluminium Pechiney testpiece was cast in sand (solidification time 2 min). Solution treatment at 530 °C (985 OF) followed by cold water quench and natural aging.
250
~
Permanent mold casl testpiece with solidification time of 15-20 s 150 '-- I- _ _ Sandcaslteslplece with solidificalion time of 2 min
200
I-
100
29
14.5
25
*'
20
JV
.g, 15 'g"> 10 1/ o
iii
5
,.,..-
-
I- 1--
....
-
o 3
6
12
24 48 96 192 400
Solution treatment time, h
206.0, A206.0 (4.5Cu-O.30Mn-O.25Mg-O.22Ti) Specifications U.S. and/or Foreign. AMS. 4235,4236,4237 Chemical Composition. Composition Limits. 4.2 to 5.0 Cu, 0.15 to 0.35 Mg, 0.20 to 0.50 Mn, 0.10 Si max, 0.15 Fe max, 0.10 Zn max, 0.15 to 0.30 Ti, 0.05 Ni max, 0.05 Sn max, 0.05 others (each) max, 0.15 others (total) max, bal AI. A206.0: 4.2 to 5.0 Cu, 0.15 to 0.35 Mg, 0.20 to 0.50 Mn, 0.05 Si max, 0.10 Fe max, 0.10 Zn max, 0.15 to 0.30Ti, 0.05 Ni max, 0.05 Sn max, 0.05 others (each) max, 0.15 others (total) max, bal Al
Applications Typical Uses. Structural castings in heat-treated temper for automotive, aerospace, and other applications where high tensile and yield strength and moderate elongation are needed. Gear housings, truck spring hanger castings, and other applications where high fracture toughness is required. Cylinder heads for gasoline and diesel motors, turbine and supercharger impellers, other applications where high strength at elevated temperatures and special aging treatment are required Precautions in Use. Subject to corrosion problems due to copper content of alloy. T4 and TI heat treatments qualify and meet federal test
requirements for stress-corrosion cracking. T6 temper should not be used where stress-corrosion cracking could be a problem
Mechanical Properties Tensile Properties. Separately cast test bars. Tensile strength and yield strength, see Table and Figure. Elongation in 50 mm or 2 in. (typical for A206.0-TI): 11.7% at room temperature, 14.0% at 120°C (250 oF), 17.7% at 175°C (350 OF). Reduction in area (typical for A206.0-TI): 26.0% at room temperature, 40.4% at 120°C (250 OF), 53.7% at 175°C (350 OF) Hardness. T4 temper, 118 HV; TI temper, 137 HV
Chemical Properties General Corrosion Behavior. Comparable to other wrought or cast aluminum alloys containing equivalent amounts of copper
Fabrication Characteristics Weldability. Fair repair welding characteristics
Aluminum Casting Alloys /247
Recommended Heat Treating Practice • T7 temper, 200°C (390 "F), hold at temperature for 8 h • T6 temper, 155°C (310 "F), hold at temperature for 8 h • T4 temper, room temperature
Solution Temperature. See Table Aging Temperature. See Table, or use the following:
A206.0-T7: Effect of temperature on strength. (a) Tensile properties. (b) Shear strength. (c) Compressive properties. (d) Bearing strengths. (e) Unnotched fatigue limits. (f) Notched fatigue limits.
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248/ Heat Treater's Guide: Nonferrous Alloys Alloy206.0-T7: Typicalmechanical properties for separately cast test bars Strengthatlndlcated temperature Room Property
Tensilestrength Tensileyieldstrength Shearstrength Compressive yieldstrength Bearingultimatestrength(BUS) e/d= 1.5(a) e/d=2.O(a) Bearingyieldstrength(BYS) e/d= 1.5(a) e1d=2.O(a) Axialfatiguestrength Unnotched,R = 0.1 100cycles loScycles 1 10 cycles NOlChed.K,=3.0.R=0.1 10' cycles loScycles 101 cycles
temperature MPa ksl
UOOC (250oF) MPa ksi
Click here to view 175 -c (350oF) MPa ksl
436 347 257 372
63 50 37 54
384 316 232 347
56 46 34 50
333 302 208 318
48 44 30 46
692 960
100
632 784
92 114
545 635
79 92
73 91
477 566
544 658
131
79 95
507 628
Alloy A206.0: Variation in plain strain-fracture toughness with yield strength LIVE GRAPH
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370 115 90
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208.0 (4Cu-3Si) Commercial Names. Former designation. 108
Mechanical Properties
Specifications U.S. and/or Foreign. Fonner SAE. 380; Fonner ASTM.
Tensile Properties. Typical for separately cast test bars. F temper; ten-
CS43A; UNS number. A 02080; Government. QQ-A-601, class 8
Chemical Composition. Composition Limits. 3.5 to 4.5 Cu, 0.10 Mg
sile strength, 145 MPa (21 ksi); yield strength, 95 MPa (14 ksi); elongation, in 50 mm or 2 in., 2.5%
max, 0.5 Mn max, 2.5 to 3.5 Si, 1.2 Fe max, 1.0 Zn max, 0.35 Ni max, 0.25 Ti max, 0.50 others (total) max, bal AI
Hardness. 55 HB (500 kg load, 10mm ball)
Consequence of Exceeding Impurity Limits. High iron decreases me-
Fabrication Characteristics
chanical properties, especially ductility. Zinc Of tin decreases mechanical properties. Magnesium reduces ductility
Joining. Rivet compositions: 2117-T4, 2017-T4. Soft solder with Alcoa
Applications Typical Uses. Manifolds, valve bodies, and similar castings requiring pressure tightness. Other applications where good casting characteristics, good weldability, pressure tightness, and moderate strength are required
No. 802; no flux. Rub-tin with Alcoa No. 33 flux: flame either reducing oxyacetylene or reducing oxyhydrogen. Metal-arc weld with 4043 alloy: Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy: Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Thngsten-arc argon-atmosphere weld with 4043 alloy: no flux. Resistance welding: spot, seam, and flash methods
Recommended Heat Treating Practice Aging Temperature. T55 temper: 150 to 160°C (300 to 320 oF) for 16 h
238.0 (10.0%Cu-4.0%Si-O.3%Mg) Commercial Names. 138
Applications
Specifications U.S. and/or Foreign. Fonner. CS104A, 138
Where combination of high hardness in the as-cast condition, good casting characteristics, and good machinability is required
Aluminum Casting Alloys /249
242.0 (4Cu-2Ni-2.5Mg) Commercial Names. Fonner designation. 142
Mechanical Properties
Specifications U.S. and/or Foreign. AMS. 4220,4222; Fonner ASTM,
Tensile Properties. See Tables
CN42A; Fonner SAE. 39; UNS number. A02420; Government. QQ-A601. class 6 (sand); QQ-A-596, class 3 (permanent mold); Foreign. Canada: CSA CN42. France: NF A-U4NT. ISO: AICu4Ni2Mg2
Hardness. See Table
Fabrication Characteristics
Chemical Composition. Composition Limits. 3.5 to 4.5 Cu, 1.2 to
Joining. Rivet compositions: 2117-T4, 2017-T4. Soft solder with Alcoa
1.8 Mg, 0.35 Mn max. 0.7 Si max, 1.0 Fe max, 0.25 Cr max, 0.35 Zn max, 0.25 Ti max, 1.7 to 2.3 Ni, 0.05 others (each) max, 0.15 others (total) max, balAI
No. 802; no flux. Rub-tin with Alcoa No. 802. Metal-arc weld with 4043 alloy: Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy: Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Tungsten-arc argon-atmosphere weld with 4043 alloy: no flux. Resistance welding: spot. seam, and flash welds
Consequence of exceeding Impurity Limits. High iron may cause shrinkage difficulties. High silicon decreases mechanical properties. Chromium decreases thermal conductivity
Recommended Heat Treating Practice
Applications
Annealing Temperature. See Table
Typical Uses. Motorcycle, diesel, and aircraft pistons, air-cooled cylin-
Solution Temperature. See Table
der heads, aircraft generator housings, other applications where excellent high-temperature strength is required
Aging Temperature. See Table
Alloy 242.0: Typcial mechanical properties of separately cast test bars 'lemper Sand cast TIl T571 T77 Permanent mold cast T571 T61
Thnslle strength(a) IIsI MPa
Thnslle yield strength!a) ksi MPa
185 220 205
27 32 30
125 205 160
275 325
40 47
235 290
Shearstrength MPa ksi
Compressive yieldstrengthCa) MPa ksi
Faliguestrength!.) MPa ksl
Elongatlon!a), %
Hardnesstb), HB
18 30 23
1.0 0.5 2.0
70 85 75
145 180 165
21 26 24
55 75 70
8.0 11.0 10.5
125 235 165
18 34 24
34 42
1.0 0.5
105 110
205 240
30 35
70 65
10.5 9.5
235 305
34 44
(a) Strengths and elongations remain unchanged or improve at low temperatures. (b) 500 kg load; 10 mm baIl.(c) At 5 X108cycles; R.R. Moore type test
Alloy 242.0-T571: Typical tensile properties of separately cast test bars at elevated temperatures Thmperalure OF ·C
Thnslle strength MPa ksi
Yieldstrength MPa ksl
ElongaUon!a). %
Sand cast 75 24 150 300 205 400 260 500 600 315 Permanent mold cast 24 150 205 260 315
75 300 400 500 600
(a) In 50 mm or 2 in.
220 205 180 90 55
32 30 26 13 8
205 195 145 55 30
30 28 21 8 4
0.5 0.5 1.0 8.0 20.0
275 255 195 90 55
40 37 28 13 8
235 230 150 55 30
34 33 22 8 4
1.0 1.0 2.0 15.0 35.0
Alloy 242.0-T77: Tensile properties at various temperatures 'IOmperature OF
"C
Sand castings -195 -320 -80 -112 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 371 700 Permanent mold casting -195 -320 -112 -80 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 371 700 (a) 0.2% offset
Thnslle strength MPa ksI
YIeld streog1h(a) MPa' ksi
Elongation, %
255 220 220 207 207 186 138 90 55 35
37 32 32 30 30 27 20 13 8 5
193 172 158 158 158 145 103 55 28 21
28 25 23 23 23 21 15 8 4 3
2 2 2 2 2 2 3 6 20 40
290 275 275 275 275 255 193 90 55 35
42 40 40 40 40 37 28 13 8 5
270 248 235 235 235 227 152 55 28 21
39 36 34 34 34 33 22 8 4 3
1 1 1 1 1 1 2 15 35 60
250 I Heat Treater's Guide: Nonferrous Alloys Alloy 242.0: Heat treatments for separately cast test bars 'Thmperature °C
of
Time, h
340-345 170-175 520-525 340-345
645-655 335-345 965-975 645-655
2-4 40-48 6(b)(c) 1-3
170-175 515-520 200-205
335-345 955-965 395-405
40-48 4(b)(1) 3-5
Purpose (andresulting temper) Sand castings Annealing, TIl Aging,T571(a) Solutionheattreatment Aging,T77(d)(e) Permanent mold castings Aging,T571(b) Solution heattreatment Aging,T61(e)
(a)Nosolutionheat treatment. (b)Soaking-time periodsrequiredfor averagecastingsafterloadhas reachedspecifiedtemperature. Timecan be decreasedor may haveto be increased, depending on experiencewithparticularcastings.(c)Still-aircooling.(d) Startwithsolutionheat-treated material. (e) U.S.Patent 1,822,877. (I) Coolin waterat 65 to 100°C (\50t0212 "F)
295.0 (4.5Cu-1.1 Si) Commercial Names. Fonner designation. 195
Applications
Specifications U.S. and/or Foreign. AMS. 4230, 4231; Fonner ASlM. C4A; SAB. 38; UNS number. A02950; Government. QQ-A-601, class 4; Foreign. Canada: CSA-C4. ISO: AICu4Si
Typical Uses. Flywheel housings, rear-axle housings, bus wheels, aircraft wheels, fittings, crankcases and other applications where a combination of high tensile properties and good machinability is required, but pressure tightness is not needed
Chemical Composition. Composition Limits. 4.0 to 5.0 Cu, 0.03 Mg max, 0.35 Mn max, 0.7 to 1.5 Si, 1.0 Fe max, 0.35 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al Consequence of Exceeding Impurity Limits. High iron or silicon decreases tensile properties, especially ductility. Manganese or magnesium decreases ductility. Tin reduces strength, hardness, and resistance to corrosion
Mechanical Properties Tensile Properties. Typical for separatelycast testbars. Tensilestrength:T4 temper, 220 MPa (32 ksi); T6 temper, 250 MPa (36 ksi); T62 temper, 285 MPa (41 ksi). Yield strength: T4 temper, 110 MPa (16 ksi); T6 temper, 165 MPa (24 ksi); T62 temper, 220 MPa (32 ksi). Elongation in 50 rom or 2 in.: T4 temper, 8.5%; T6 temper, 5.0%; T62 temper, 2.0%. Strengths and elongations remain unchanged or improve at low temperatures. See Table Hardness. T4 temper, 60 HB; T6 temper, 75 HB; T62 temper, 90 HB (500 kg load, 10 rom ball)
Alloy 295.0: Typical tensile properties for separately cast test bars at elevated temperatures Temperature °C
T4temper 24 150 205 260 315 T6temper 24 150 205 260 315
OF
Tell-'ilestrength MPa ksi
Yield strength MPa ksi
Elongation(a), %
75 300 400 500 600
220 195 105 60 30
32 28 15 9 4
110 105 60 40 20
16 15 9 6 3
8.5 5.0 15.0 25.0 75.0
75 300 400 500 600
250 195 105 60 30
36 28 15 9 4
165 140 60 40 20
24 20 9 6 3
5.0 5.0 15.0 25.0 75.0
Fabrication Characteristics Joining. Rivet compositions: 2117-T4, 2017-T4. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Atomic-hydrogen weld with 4043 alloy; Alcoa No. 22 flux. Oxyacetylene weld with 4043 alloy; Alcoa No. 22 flux; flame neutral. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Thngsten-arc argon-atmosphere weld with 4043 alloy; no flux. Resistance welding: spot, seam, and flash methods
Recommended Heat Treating Practice
(a) In 50mm or 2 in.
Solution Temperature. 515 to 520 °C (955 to 965 "F); hold at temperature for 12 h; cool in water at 65 to 100°C (150 to 212 "F) Aging Temperature. 150 to 155°C (305 t0315 OF). ToobtainT6 temper from solution heat-treated material, hold at temperature for 3 to 5 h; for T62 temper, hold at temperature for 12 to 16 h
Aluminum Casting Alloys /251
296.0 (4.5Cu-2.5Si) Commercial Names. Fonner designations. B 295.0, B 195
Recommended Heat Treating Practice
Specifications U.S. and/or Foreign. AMS. 4282, 4283; SAE. 380;
Solution Temperature. 505 to 515°C (945 to 955 "F); hold at tempera-
UNS number. A-22950; Government. QQ-A-596, class 4
ture for 8 h; cool in water at 65 to 100°C (150 to 212 "F)
Chemical Composition. Composition Limits. 4.0 to 5.0 Cu, 0.05 Mg
Aging Temperature. To obtain T6 temper from solution heat-treated material, 150 to 155°C (305 to 315 "F) and hold at temperature 5 to 7 h; for T7 temper (U.S. Patent 1,822,877) 255 to 265°C (495 to 505 OF) and hold at temperature 4 to 6 h
max, 0.35 Mn max, 2.0 to 3.0 Si, 1.2 Fe max, 0.50 Zn max, 0.25 Ti max, 0.35 Ni max, 0.35 others (total) max, bal Al
Consequence of Exceeding Impurity Limits. High iron decreases tensile properties, especially ductility. Zinc or tin decreases tensile properties. Manganese or magnesium reduces ductility
Applications Typical Uses. Aircraft fittings, aircraft gun control parts, aircraft wheels, railroad car seat frames, compressor connecting rods, full pump bodies, other applications requiring a combination of high-tensile properties and good machinability
Mechanical Properties Tensile Properties. Typical for separately cast test bars. Tensile strength: T4 temper, 255 MPa (37 ksi); T6 temper, 275 MPa (40 ksi); T7 temper, 270 MPa (39 ksi). Yield strength: T4 temper, 130 MPa (19 ksi); T6 temper, 180 MPa (26 ksi); T7 temper, 140 MPa (20 ksi). Elongation, in 50 rum or 2 in.: T4 temper, 9%; T6 temper, 5%; T7 temper, 4.5%. Strengths and elongations remain unchanged or improve at low temperatures. See Table
Hardness. T4 temper: 75 HB; T6 temper: 90 HB; T7 temper: 80 HB (500 kg load, 10 rum ball)
Fabrication Characteristics
Alloy 296.0: Typicaltensile properties of separately permanent mold cast test bars at elevated temperature Eiongalion(a), %
'ThnsUe strength ksi MPa
Yieldstrength ksi MPa
75 300 400 500 600
255 200 115 50 25
37 29 17 7 3.5
130 160 75 30 15
19 23 11 4 2.5
9 5 15 25 75
75 300 400 500 600
275 200 115 50 25
40 29 17 7 3.5
180 160 75 30 15
26 23 11 4 2.5
5 5 15 25 75
'Iemperature OF °C
T4temper 24 150 205 260 315
T6temper 24 150 205 260 315
(a)In 50 mmor 2 in.
Joining. Same as alloy 295.0
308.0 (5.5Si-4.5Cu) Commercial Names. Fonner designation. A108
Mechanical Properties
Specifications U.S. and/or Foreign. Fonner ASTM. SC64A; SAE. 330; UNS number. A03080; Government. QQ-A-596, class 6
Tensile Properties. Typical for separately cast test bars. F temper: ten-
Chemical Composition. Composition Limits. 4.0 to 5.0 Cu, 0.10 Mgmax, 0.50 Mnmax, 5.0 to 6.0Si, I.OFemax,l.0Znmax, 0.25 Ti max, 0.50 others (total) max, bal Al
Consequence of Exceeding Impurity Limits. High iron, zinc, or tin decreases mechanical properties. Magnesium decreases ductility
Applications Typical Uses. Ornamental grills, reflectors, general-purpose castings, and other applications where good casting characteristics, good weldability, pressure tightness, and moderate strength are required
sile strength, 195 MPa (28 ksi); yield strength, 110 MPa (16 ksi); elongation in 50 rum or 2 in., 2.0%
Hardness. 70 HB (500 kg load, 10 rum ball)
Fabrication Characteristics Joining. Rivet compositions: 2117-T4, 2017-T4. Soft solder with Alcoa No. 802. Braze with Alcoa No. 717; Alcoa No. 33 flux; flame either reducing oxyacetylene or reducing oxyhydrogen. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Thngsten-arc argon-atmosphere weld with 4043 alloy, no flux. Resistance welding: spot, seam, and flash
252/ Heat Treater's Guide: Nonferrous Alloys
319.0 (6Si-3.5Cu) Commercial Names. Former designations. 319, Allcast Specifications U.S. and/or Foreign. Former ASTM. SC64D; SAE. 326; UNS number. A03190; Foreign. ISO: AISi6Cu4 Chemical Composition. Composition Limits. 3.0 to 4.0 Cu, 0.10 Mg max, 0.50 Mn max, 5.5 to 6.5 Si, 1.0 Fe max, 1.0 Zn max, 0.25 Ti max, 0.35 Ni max, 0.50 others (total) max, bal Al Consequence of Exceeding Impurity Limits. Mechanical properties are relatively insensitive to impurities
Applications Typical Uses. Automotive cylinder heads, internal combustion engine crankcases, typewriter frames, piano plates, and other applications where good casting characteristics and weldability, pressure tightness, and moderate strength are required
Alloy 319.0: Typical mechanical properties for separately cast test bars TeIlS"e st",ngth(a) Temper MPa ksI
TeIUUe yield Shear 51reogth(a) Elongation Hardness strength MPa ksI (a)(h).~ (c).HB MPa IIsI
Fatigue 51",ngth@ MPa ksi
Compressive yield s!TeDgth(a) MPa ksI
Sandeast As-cast 185 27 T6 250 36 Permanent mold As-cast 235 34 T6 280 40
125 18 165 24
2.0 2.0
70 80
150 22 200 29
70 75
10 11
130 19 170 25
130 19 185 27
2.5 3.0
85 95
165 24 185 27
70
10
130
19
(a)Strengthsand elongationsare unchan~d or improvedat low temperatures.(b) In 50 nun or 2 in. (e) 500kg load: 10nun ball. (d) At5 x 10 cycles; R.R.Moore type test
Mechanical Properties
Recommended Heat Treating Practice
Tensile Properties. See Table
Solution Temperature. 500 to 505°C (935 to 945 "F); hold at temperature 12 h (sand), 8 h (permanent mold); cool in water at 65 to 100°C (150 to 212 oF)
Hardness. See Table
Fabrication Characteristics Joining. Same as for alloy 208.0
Aging Temperature. To obtain T6 temper from solution-treated material. 150 to 155°C (305 to 315 "F) and hold at temperature 2 to 5 h
332.0 (9.5%Si-3.0%Cu-1.0%Mg) Commercial Names. F332, FI32 Specifications U.S. and/or Foreign. Former ASTM. SC103A; Former SAE 332; UNS number. A03320
Applications Typical Uses. Applications where good high-temperature strength, low coefficient of thermal expansion, and good resistance to wear are required (for example, automotive and diesel pistons, pulleys, sheaves)
Mechanical Properties
Alloy 332.0-T5: Tensile properties of permanent mold alloy at various temperatures Temperature OF °C
'ThnsUe strength MPa IIsI
24 100 150 205 260 315 371
248 227 215 172 130 83 55
75 212 300 400 500 600 700
36 33 31 25 19 12 8
Yield5II1!ngth(a) MPa IIsI
193 185 165 110 83 55 41
28 27 24 16 12 8 6
Elongation, ~
1 1 2 3 6 15 25
Tensile Properties. See Table (a)0.2% offset
336.0 (12Si-2.5Ni-1 Mg-1 Cu) Commercial Names. Former designations. A332.0, A132. Specifications U.S. and/or Foreign. Former ASTM. SNI22A; SAE. 321; UNS number. A13320; Government. QQ-A-596, class 9; Foreign. Canada: CSASNI22; France: NF A-SI2N2G
Chemical Composition. Composition Limits. 0.5 to 1.5 Cu, 1.3Mg max, 0.35 Mn max, 11.0 to 13.0 Sit 1.2 Fe max. 0.35 Zn max, 0.25 Ti max, 0.05 other (each) max, 0.15 others (total) max, bal Al Consequence of Exceeding Impurity Limits. High iron or chromium promotesshrinkagedifficulties
Aluminum Casting Alloys /253
Applications Typical Uses. Automotive and diesel pistons, pulleys, sheaves, and other applications where good high-temperature strength, low coefficient of thermal expansion, and good resistance to wear are required
Mechanical Properties Tensile Properties. Typical for separately cast test bars. Tensile strength: T551 temper, 248 MPa (36 ksi); T65 temper, 324 MPa (47 ksi). Yield strength: T551 temper, 193 MPa (28 ksi); T65 temper, 296 MPa (43 ksi). Elongation, in 50mmor2 in.: T55l and T65 tempers, 0.5%. Strengths and elongations remain unchanged or improve at low temperatures. See Tables
Alloy 336.0: Typical tensile properties for separately cast test bars at elevated temperature 'Thmpemture OF °C
'ThwD. strength MPa ks!
Y\eIdstrength MPa ksi
25 150 205 260 315
250 215 180 125 70
195 150 105 70 30
75 300 400 500 600
36 31 26 18
10
EJoogatloo(a),
"
28 22 15 10 4
0.5
1.0 2.0 5.0 10.0
(a) In 50 rnmor 2 in.
Hardness. T551 temper, 105 HB; T65 temper, 125 HB (500 kg load, 10 rnm ball)
Fabrication Characteristics Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic); Alcoa No. 27 flux (manual). Tungsten-arc argon-atmosphere weld with 4043 alloys; no flux. Resistance welding: spot, seam, and flash methods
Recommended Heat Treating Practice Solution Temperature. 515 to 520°C (955 to 965 oF); hold 8 h at temperature; cool in water at 65 to 100°C (150 to 212 OF) Aging Temperature. 170 to 175 -c (335 to 345 OF); hold at temperature 14 to 18 h to obtain T5 temper from as-cast material; 12 to 26 h to obtain T6 temper from solution heat-treated material
Alloy 336.0: Tensile properties of sand cast alloy at various temperatures 'Iemperature
°C
OF
-195
-320 -112 -18 75 212 300 400 500 600 700
~o
-28 24 100 150 205 260 315 371
'Thosile strength MPa ks!
310 275 262 248 240 215 180 125 70 35
45 40 38 36 35 31 26 18 10 5
YIelds1rength(o) ksi MPa
270 235 215 193 172 152 103 70 28 21
39 34 31 28 25 22 15 10 4 3
Eloogatloo,
"
1 1 1 0.5 1 1 2 5
10 45
(a) 0.2% offset
339.0 (12.0%Si-1.0%Ni-1.0%Mg-2.25%Cu) Commercial Names. Z332.0, Z132
Applications A lower cost alloy quite similar to 336.0 alloy. Applications similar to those for 336.0 alloy and not needing the higher elevated-temperature property available in 336.0 alloy
354.0 (9Si-1.8Cu-O.5Mg) Commercial Names. 354
Mechanical Properties
Specifications U.S. and/or Foreign. FormerASTM.SC92A;UNSnumber. AC3540;Government. MIL-A-2ll80
Tensile Properties. See Tables
Chemical Composition. Composition Limits. 1.6 to 2.0 Cu, 0.4 to 0.6 Mg, 0.10 Mn max, 8.6 to 9.5 Si, 0.2 Fe max, 0.1 Zn max, 0.2 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al
Creep Rupture Properties See Table
Recommended Heat Treating Practice Applications Typical Uses. Permanent mold castings used in applications requiring high strengths and heat treatability
Solution Temperature. 525°C (980 oF); hold at temperature 10 to 12 h; quench in hot water 60 to 80°C (140 to 176 oF) Aging Temperature. To obtain T61 temper from solution heat-treated material, room temperaturefor 8 to 16 h; 155°C (310 oF); hold attempemture for 10 to 12 h
254/ Heat Treater's Guide: Nonferrous Alloys
Alloy 354.0-161: 1ypical mechanical properties for separately cast test bars at various temperatures 'Thmperature OF "C -196 -80,-28 24 100
-320 -112,-18 75 212
150
300
175
350
205
400
230
450
260
500
600
315
At indicated temperature Yieldstrength MPa ksi
ThnsiJe strength MPa \lsi
11meat temperature, h
470 400 380 345 350 360 370 415 325 345 350 340 290 310 325 295 230 130 290 270 205 130 105 255 195 125 95 80 195 115 80 65 60 90 60 40
0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5
10 100 1000 10000
340 290 285 285 285 290 310 340 275 295 315 305 240 270 290 260 195 95 270 250 180 105 75 240 170 95 75 60 170 105 65 50 40 80 50 35
68 58 55 50 51 52 54 60 47 50 51 49 42 45 47 43 33 19 42 39 30 19 15 37 28 18 14 12 28 17 12 9.5 8.5 13 8.5 6
Elongation(a), %
49 42 41 41 41 42 45 49 40 43
Thnslle strength MPa ksl
5 5 6 6 6 6 6 6 6 6 6 6 6 6 6 8 13 24 6 9 17 30 45 9 15 25 40 55 16 22 35 50 65 29 60 85
46 44 35 39 42 38 28 14 39 36 26 15 11 35 25 14 11 8.5 25 15 9.5 7.5 6 12 7 5
380 380 385 400 420 435 380 395 425 405 340 380 405 405 325 205 405 400 330 220 185 400 315 240 195 170 360 250 205 185 165 260 205 185 170 160
At room temperatureafter beating Yieldstrength \lsi MPa
55 55 56 58 61 63 55 57 62 59 49 55 59 59 47 30 59 58 48 32 27 58 46 35 28 25 52 36 30 27 24 38 30 27 25 23
285 285 290 295 310 350 290 305 345 360 275 295 340 350 255 115 340 340 255 125 90 345 250 140 95 75 290 150 105 80 70 145 90 75 65 60
Eloogalion(a), %
41 41 42 43 45 51 42
6 6 6 6 6 5 6 5 5 4 6 6 4 5 8 16 5 5 7 14 20 5 8 11 17 22 6 11 15 19 11 13 17 19 21
44 50 52 40 43 49 51 37 17 49 49 37 18 13 50 36 20 14 11 42 22 15
12 10 21 13 11 9.5 8.5
23
(a) In 50 mm, 2 in. or 4d, where d is diameter of reduced section of'tensile-test specimen
Alloy 354.0-161: Fatigue strengths for separately cast test bars Cyeles
'Thmperature OF "C 24 150 205 260 315
75 300 400 500 600
10'
10'
10'
10'
5x10'
10'
MPa
ksl
MPa
\lsi
MPa
ksi
MPa
\lsi
MPa
\lsi
MPa
\lsi
345
50
195
28
275 255 215 140 75
40 37 31 20.5 11
215 200 150 96 55
31 29 22 14 8
175 150 105 60 40
25.5 21.5 15 9 6
145 115 70 40 30
21 17 10 6 4
135 110 60 40 30
19,5 16 9 6 4
Note: R.R.Moore type lest
Alloy 354.0-161: Creep-rupture properties for separately cast test bars StressIor creepoC: Temperature OF DC 177
205
350
400
11meunder ot...... h 0.1 1.0 10 100 1000 0.1 1.0 10 100 1000
Rupturest ..... MPa ksl 305 295 285 240 170 285 255 220 160 90
44 43 41 35 25 41 37 32 23 13
1%
0.5%
0.1%
0.2%
MPa
\lsi
MPa
ksi
MPa
ksi
MPa
ksi
295 290 285 235 165 275 250 215 160 90
43 42 41 34 24 40 36 31 23 13
285 285 275 230 165 270 250 205 150 83
41 41 40 33 24 39 36 30 22 12
290 290 255 205 138 255 235 180 125 83
39 39 37 30 20 37 34 26 18 12
255 255 240 115 76 240 215 125 69 48
37 37 35 17 11 35 31 18 10 7
Aluminum Casting Alloys /255 Alloy 354.0-T61: Minimum mechanical properties for castings CIass(a) 1 2 10 11
'Iensllestrengthfb) ksi MPa
324 345 324 296
47 50 47 43
'Ienslle yield strength(b) (c) ksi MPa 248 290 248 227
%
Compressive yield strength(e) MPa ksi
3 2 3 2
248 290 248 227
Elongation(b)(d),
36 42 36 33
36 42 36 33
(a) Classes 1 and 2 (levelsof properties)obtainableonly at designatedareasof casting;classes 10 and 11 may be obtainedat any locationin casting.(b) Specifiedin MIL-A-21180. (c)0.2% offset. (d) In 50 mm,2 in. or4d, whered is diameterof reducedsectionof tensile-testspecimen.(e)Design values;not specified
355.0, C355.0 (5Si-1.3Cu-O.5Mg) Specifications U.S. and/or Foreign. AMS. 4210, 4212, 4214, 4280, 4281; Fonner ASTM. 355.0: SC51A. C355.0: SC51B; SAE. 322; UNS number. A03550; Government. 355.0: sand castings, QQ-A-601, class 10; permanent mold castings, QQ-A-596, class 6. C355.0: MlL-A-21180; Foreign. Canada: CSA SC51
Chemical Composition. Composition Limits. 355.0: 1.0 to 1.5 Cu, 0040 to 0.60 Mg, 0.50 Mn max, 4.5 to 5.5 Si, 0.6 Fe max, 0.25 Cr max, 0.35 Zn max, 0.25 Ti max, 0.05 other (each) max. 0.15 others (total) max, bal AI. (If Fe exceeds 0045, Mn content may not be less than 0.5 Fe content.) C355.0: 1.0 to 1.5 Cu, 0040 to 0.60 Mg, 0.10 Mn max, 4.5 to 5.5 Si, 0.20 Fe max, 0.10 Zn max, 0.20 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al Consequence of Exceeding Impurity Limits. High irondecreasesductility. Nickel decreases resistance to corrosion. Tin reduces mechanical properties
Applications Typical Uses. Aircraft supercharger covers, fuel-pump bodies, air-compressor pistons, liquid-cooled cylinder heads, liquid-cooled aircraft engine crankcases, water jackets, and blower· housings. Other applications where good castability, weldability, and pressure tightness are required. The presence of copper in 355.0 increases strength but reduces corrosion resistance and ductility
Mechanical Properties Tensile Properties. See Table
Creep Rupture Properties See Table
Fabrication Characteristics Joining. Same as alloy 514.0
Recommended Heat Treating Practice Solution Temperature. See Table Aging Temperature. See Table
Alloy 355.0: Typicaltensile properties of separately cast test bars at elevated temperatures 10mperature "C
OF
'Ienslle strength(a) MPa ksi
T6 temper, sand cast 25 75 240 150 300 230 400 205 115 260 500 65 315 600 40 T6 temper, permanent mold cast 75 25 290 150 300 220 205 400 130 260 500 65 315 600 40 TSI temper, sand cast 25 75 195 150 300 165 400 205 95 260 500 65 600 315 40
Yield strength(a) ksi MPa
E1ongation(a)(b), %
Alloy 355.0: Heat treatments for separately cast test bars Purpose (and
35 33 17 9.5 6
170 170 90 35 20
25 25 13 5 3
3 1.5 8 16 36
42 32 19 9.5 6
185 170 90 35 20
27 25 13 5 3
4 10 20 40 50
28 24 14 9.5 6
160 130 70 35 20
23 19 10 5 3
1.5 3 8 16 36
(a) Strengthsand elongationsremainunchangedor improveat low temperatures. (b)In 50 rrunor 2 in.
resulting temper) Sand castings Solution Aging T51(c) T6(d) T61(d) T7(d)(e) T71(d)(e) Permanent mold castings Solution Aging(1) T62(d)
11meat
'Iemperature
-c
OF
temperature, h
520-530
970-990
12(a)(b)
225-230 150-155 150-160 225-230 245-250
435-445 300-315 300-320 435-445 470-480
7-9 3-5 8-10 7-9 4-6
520-530
970-980
8(a)(b)
170-175
335-345
14-18
(a)Soaking-timeperiodsrequiredfor averagecastingsafterloadbasreachedspecifiedtemperature. Timecan be decreasedor may have to he increased,dependingon experiencewithparticularcastings.(b) Cool in waterat65 to 100°C (150to 212 "F). (c) No solutionheat treatment.(d)Start with solutionheat-treatedmaterial,(e) U.S.Patent 1,822,877. (I) Exceptfortemperlistedunderthishead, temperaturevaluesfor all tempersare thesameas for sandcastings
256/ Heat Treater's Guide: Nonferrous Alloys
Alloy 355.0: Typical mechanical properties for separately cast test bars 'Thmper
'Ilmslle strength ksI MPa
'Thosile yield strength MPa ksl
195 240 270 260 240
28 35 39 38 35
160 170 240 250 200
205 290 310 275 250
30 42 45 40 36
165 185 275 205 215
Compressive yieldstrength ksi MPa
Elongation, %
Hardness(a),
HB
Shear strength MPa ksI
Fatigue strength(h) MPa ksI
23 25 35 36 29
1.5 3.0 1.0 0.5 1.5
65 80 90 85 75
150 195 215 195 180
22 28 31 28 26
55 62 66 69 69
8.0 9.0 9.5 10.0 10.0
165 180 255 260 205
24 26 37 38 30
24 27 40 30 31
2.0 4.0 1.5 2.0 3.0
75 90 105 85 85
165 235 250 205 185
24 34 36 30 27
69 69 69 69
10 10 10 10
165 185 275 205 215
24 27 40 30 31
Sand cast T51 T6 T61
TI TIl Permanent mold cast T51 T6 T62
TI TIl
8
(a) 500 kg load; 10 mm ball. (b) At5 x 10 cycles; R.R. Moore type test
Alloy 355.0-T51: Tensile properties at various temperatures 'Thmpemture OF
'Thosile strength MPa ksi
"C
Yieldstrength!a) MPa ksI
Alloy 355.0-T71: Tensile properties at various temperatures
Elongation, %
Sand castings -195 -80 -28 24 100 150 205 260 315 371
'Thnsile strength MPa ksi
YIeld strength!a) MPa ksI
Elongation, %
Sand castings
-320 -112 -18 75 212 300 400 500 600 700
227 193 193 193 165 95 67 40 25
33 29 28 28 28 24 14 9.5 6 3.5
185 165 160 160 152 130 70 35 21 14
27 24 23 23 22 19 10 5 3 2
1.5 1.5 1.5 1.5 2 3 8 16 36 50
255 240 215 207 193 160 103 67 41 25
37 35 31 30 28 23 15 9.5 6 3.5
185 172 165 165 165 138 70 35 21 14
27 25
1 1.5 1.5 2 3 4 19 33 38 60
200
-195 -80 -28 24 100 150 205 260 315 371
Permanent mold -195 -80 -28 24 100 150 205 260 315 371
'Thmpemture OF °C
-320 -112 -18 75 212 300 400 500 600 700
282 255 248 240 235 207 117 67 41 25
41 37 36 35 34 30 17 9.5 6 3.5
235 220 215 193 180 90 35 21 14
34 32 31 29 28 26 13 5 3 2
1.5 1.5 1.5 1.5 2 3 8 16 36 50
317 345 262 248 227 200 130 67 41 25
46 50 38 36 33 29 19 9.5 6 3.5
262 235 227 215 200 180 90 35 21 14
38 34 33 31 29 26 13 5 3 2
1.5 2 2.5 3 4 8 20 40 50 60
200
Permanent mold
-320 -112 -18 75 212 300 400 500 600 700
24 24 24 20 10 5 3 2
(a) 0.2% offset
-195 -80 -28 24 100 150 205 260 315 371
-320 -112 -18 75 212 300 400 500 600 700
(a) 0.2% offset
Alloy 355.0-T61: Creep-rupture properties for separately cast test bars StressCorcreep DC: 'Thmpemlure OF -c
150
300
205
400
nmeunder stress, h
0.1 I 10 100 1000 0.1 1
to
260
500
100 1000 0.1 1 10 100 1000
Rupture stress MPa ksi
MPa
ksI
MPa
ksi
MPa
ksi
MPa
ksi
285 285 275 260 220 250 230 180 130 97 165 125 90 62 45
275 270 260 250 215 250 220 120 130 90 145 110 83 62 45
40 39 38 36 31 36 32 25 19 13 21 16 12 9 6.5
270 260 250 235 206 240 205 160 125 83 130 97 76 55 41
39 38 36 34 30 35 30 23 18 12 19 14 11 8 6
240 235 230 215 185 230 170 130 97
35 34 33 31 27 33 25 19 14
230 220 205 170 140 170 140 110
33 32 30 25 20 25 20 16
105 83 59 41
15 12 8.5 6
41 41 40 38 32 36 33 26 19 14 24 18 13 9 6.5
1%
0,5%
0.2%
0.1%
83 59 41
12 8.5 6
Aluminum Casting Alloys /257 Alloy 355.0-T61: Minimum mechanical properties of castings 'llmsileyleld strength(b)Cc) MPa ksi
ThnsUe strength ·CIassCo) 1 2 3 10
11 12
MPa
ksi
285 305 345 285 255 240
41 44 50 41 37 35
215 230 275 215 205 195
ElongationCd), %
31 33 40 31 30 28
3 3 2 3 1 1
Alloy C 355.0-T61: Fatigue properties for separately cast test bars
Compressive yield strengthCe) MPa ksI 215 230 275 215 205 195
31 33 40 31 30 28
(a)Classes1,2, and3(levelsofproperties) obtainableonlyatdesignated areasofcasting;classes 10, 11,and 12maybeobtainedfromany locationincasting.(b) SpecifiedinMIL-A-21180.Highpropertiesareobtainedby advancedfoundrytechniques andbycarefulcontrolof traceelementsat lower levels than specifiedfor alloy 355.0 castings. (c) 0.2% offset.(d) In 4d, where d is diameterof reducedsectionof tensile-test specimen. (e)Designvalues;notspecified
Thmperature OF
Faligue streogth(o)
Numheror cycles
"C
24
75
260
500
5
10 106 7 10 108 5 X 108 105 6 10 7 10 108 5x108
MPa
ksI
195 130 110 100 95 125 80 50 40 35
28.0 19.0 16.0 14.5 14.0 18.0 11.5 7.5 5.5 5.0
(a)Basedonrotating-beam testsat room temperature andcantileverbeam (rotatingload)testsatelevated temperature
356.0, A356.0 (7Si-O.3Mg) Specifications U.S. and/or Foreign. AMS. 356.0: 4217,4260,4261, 4284,4285,4286. A356.0: 4218; Fonner ASTM. 356.0, SG70A; A356.0, SG70B; SAE. 356.0: J452, 323; UNS number. 356.0: A03560. A356.0: A13560; Government. 356.0: QQ-A-601, QQ-A-596. A356.0: MIL-C21180 (class 12); Foreign. ISO: AISi7Mg
Consequence of Exceeding Impurity Limits. High copper or nickel
Chemical Composition. Composition Limits. 356.0: 0.25 Cu max,
Typical Uses. 356.0: aircraft pump parts, automotive transmission cases,
0.20 to 0.45 Mg, 0.35 Mn max, 6.5 to 7.5 Si, 0.6 Fe max, 0.35 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal AI. A356.0: 0.20 Cu max, 0.25 to 0.45 Mg, 0.10 Mn max, 6.5 to 7.5 Si, 0.20 Fe max, 0.10 Zn max, 0.20 Ti max, 0.05 others (each) max, 0.15 others (total) max, balAI
aircraft fittings and control parts, water-cooled cylinder blocks. Other applications where excellent castability and good weldability, pressure tightness, and good resistance to corrosion are required. A356.0: aircraft structures and engine controls, nuclear energy installations, and other applications where high-strength permanent mold or investment castings are required
decreasesductility and resistance to corrosion. High iron decreases strength and ductility
Applications
Mechanical Properties Alloy 356.0-T6: Typical tensile properties of separately cast test bars Thmperature OF -c 24 150 205 260 315
Thnsile strengthCo) MPa ksi
75 300 400 500 600
230 160 85 50 30
33 23 12 7.5 4.0
Yield strengthCo) MPa ksi 165 140 60 35 20
24 20 8.5 5.0 3.0
ElongotlonCo)(b),
Tensile Properties. See Tables
Creep Rupture Properties
%
See Table
3.5 6.0 18 35 60
Joining. Same as alloy 514.0
(a)Strengthsandelongationsremainunchanged or improveat low temperatures. (b) In 50 mm or 2 in.
Fabrication Characteristics Recommended Heat Treating Practice Solution Temperature. See Table Aging Temperature. See Table
Alloy 356.0: Typical mechanical properties for separately cast test bars Thmper Sandcasl T51 T6 TI TIl Permanent mold T6 TI
Thnsile strength MPa ksi
YIeld strength MPa ksl
172 228 234 193
25 33 34 28
140 165 205 145
262 221
38 32
185 165
Compressive
FJongalionCo),
Hardness(b),
%
HB
Shearstrength MPa ksl
20 24 30 21
2.0 3.5 2.0 3.5
60 70 75 60
140 180 165 140
20 26 24 20
55 60 62 60
27 24
5.0 6.0
80 70
205 170
30 25
75
(a) In 50 mmor 2 in. (b) 500kg load; 10 mm ball.(c)At5 x 108 cycles;R.R.Mooretypetest
Faligue streogthCc) MPa
90
ksI
8.0 8.5 9.0 8.5 13 11
yield strength
MPa
ksI
145 170 215 150
21 25 31 22
185 165
27 24
258/ Heat Treater's Guide: Nonferrous Alloys Alloy 356.0-T7: Tensile properties at various temperatures 'Iemperature OF °C
Sand castings -195 -320 -80 -112 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 371 700 Permanent mold castings -195 -320 -80 -112 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 371 700
Thnsile strength MPa ksl
y.,ldstrength(a) MPa ksl
283 248 235 235 207 160 83 53 28 17
41 36 34 30 23 12 7.5 4 2.5
275 248 165 220 185 160 83 50 28 17
40 36 34 32 27 23 12 7 4 2.5
240 220 215 207 193 138 58
34
Alloy 356.0-T6: Tensile properties at various temperatures
Elongation,
21 14
35 32 31 30 28 20 8.5 5 3 2
2 2 2 2 2 6 18 35 60 80
207 180 172 165 160 138 58 34 21 14
30 26 25 24 23 20 8.5 5 3 2
6 6 6 6 10 20 40 55 70 80
34
Thmpemture
%
DC
Yield strength(a)
ThnsiJe strength MPa ksl
OF
Sand castings -195 -320 -112 -80 -28 -18 24 75 100 212 150 300 205 400 260 500 315 600 371 700 Permanent mold castings -195 -320 -80 -112 -28 -18 24 75 100 212 150 300 205 400 260 500 600 315 371 700
Elongation,
MPo
ksI
%
275 240 227 227 2W 160 83 53 28 17
40 35 33 33 32 23 12 7.5 4 2.5
193 172 165 165 165 138 58 35 21 14
28 25 24 24 24 W 8.5 5 3 2
3.5 3.5 3.5 3.5 4 6 18 35 60 80
330 275 270 262 207 145 83 53 28 17
48 40 39 38 30 21 12 7.5 4 2.5
2W 193 185 185 172 117 58 34 21 14
32 28 27 27 25 17 8.5 5 3 2
5 5 5 5 6 10 30 55 70 80
(a) 0.2%offset
(a)0.2% offset
Alloy 356.0-T61: Creep-rupture properties for separately cast test bars
Alloy A356.0-T61: Effect of neutron radiation on 'tensile properties Thnsile strength MPa ksl
Fast neutron Dux.
D/cm2
Stress forcreep oC: Temperature TIme under Rupture stress stress,h MPa ksi °C OF 150 300
0.1 I
10 100 1000
235 235 230 200 165
34 34 33 29 24
1%
MPa ks\
0.5% MPa ksl
0.2% MPa ksi
MPa ks\
215 215 205 195 165
205 200 195 185 160
195 185 180 170
185 180 170 165
31 31 30 28 24
30 29 28 27 23
resulting lemper)
Thmperature °C
28 27 26 25
27 26 25 24
%
180 200 230 290 360
33 37 42 46 54
26 29 33 42 52
4 6 6 6 3
Note:Separatelycast testbars;irradiation temperature, 50°C (120 "F)
Alloy A356.0-T61: Minimum mechanical properties for alloy castmgs
temperature, b
CIoss(a) Sand castings Solution Aging T51(c) T6(d) TI(d)(e) TII(d) Permanent mold castings Solution Aging(f) T6(d)
230 255 290 315 375
Controlsample 2.0x 1019 1.2x loW 5.6x 1020 9.8x loW
TIme at OF
Eiongallon,
0.1%
Alloys 356.0 and A 356.0: Heat Treatments for separately cast test bars Purpose (and
Yield strength MPa ksl
535-540
995-1005
12(a)(b)
225-230 150-155 225-230 245-250
435-445 305-315 435-445 470-480
7-9 2-5 7-9 2-4
535-540
995-1005
8(a)(b)
150-155
305-315
3-5
(a) Soaking-time periodsrequiredforaveragecastingafterloadhas reachedspecifiedtemperature. Timecan be decreased or mayhaveto be increased,dependingon experiencewithparticularcastings. (b) Coolin wateral65 to 100°C (150to212 "F), (c) No solutionheat treatment. (d)Stan with sclutionheat-treated material.(e)U.S.Patent1,822,877. (f)Exceptfortemperlistedunderthishead, temperature valuesfor all tempersare thesanne as for sand castings
I
2 3 10 11 12
ThnsiJe streogth(b) MPa ksl 260 275 310 260 230 220
38 40 45 38 33 32
Thnsile yield strength(b)(c) MPa ksl 195 205 235 195 185 150
28 30 34 28 27 22
Eiongallon(d),
Compreosive yield strength(e)
%
MPo
ksl
5 3 3 5 3 2
195 205 235 195 185 150
28 30 34 28 27 22
(a)ClassesI, 2, and3 (levelsofproperties) obtainableonlyat designated areasofcasting;classes10, 11,and 12may be specifiedat anylocationin casting.(b) Specifiedin Mll..-A-2I 180.(c)0.2%offset.(d) In 4d, whered is diameterofreducedsectionoftensile-testspecimen.(e)Designvalues;not specified
Aluminum Casting Alloys /259
357.0, A357.0 (7Si-O.5Mg) Specifications U.S. and/or Foreign. UNS number. 357.0: A03570. A357.0: A13570; Government. A357.0: MIL-A-21180 Chemical Composition. Composition Limits. 357.0: 0.05 Cu max; 0.45 to 0.6 Mg, 0.03 Mn max, 6.5 to 7.5 Si, 0.15 Fe max, 0.05 Zn max, 0.20 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal AI. A357.0: 0.20 Cu max, 0.40 to 0.7 Mg, 0.10 Mn max, 6.5 to 7.5 Si, 0.20 Fe max, O.lOZn max, 0.10 to 0.20Ti, 0.04 to 0.07 Be, 0.05 others (each) max, 0.15 others (total) max, bal AI
Recommended Heat Treating Practice Solution Temperature. 540°C (1005 OF); hold at temperature for 8 h; hot water quench
Aging Temperature. T6 temper: 170°C (340 "F); hold at temperature 3 to 5 h
Applications Typical Uses. Critical aerospace applications and other uses requiring heat-treatable permanent mold casting that combines ready weldability with high strength and good toughness
Mechanical Properties Tensile Properties. See Tables Hardness. A357.0, T61 temper: 100 HB
Alloy 357.0-T62: Typical mechanical properties of separately cast bars at various temperatures Thmpemlure OF -c -196 -80 -28 24 100
-320 -112 -18 75 212
150
300
175
350
205
400
230
450
260
500
315
600
Fabrication Characteristics Joining. Because of the beryllium content, care should be taken not to inhale fumes during welding
Alloy A357.0: Minimum mechanical properties of castings Class(a)
Thnsile strengtb(b) ksI MPH
ThnsiIe yieldstrengtb(b)(c) MPH ksi
EIoogaUon(b)(d), %
Compressive yieldstrengtb(e) MPa ksi
T61, permanent mold castings 1 10
46
317 283
41
248 214
36 31
3 3
310 345 262 283
45 50 38 41
241 276 193 214
35 40 28 31
3 5 5 3
T62 castings 1 2 10 11
241 276 193 214
35 40 28 31
(a) Classes 1 and 2 (levels of properties obtainable only at designated areas of casting); classes 10 and 11may be obtained from any location in castings. (b) Specified inMIL-a-21180. (c) 0.2% offset. (d) In 4d. where d is diameter of reduced section of tensile-test specimen. (e) Design values; not specified
1imeat temperature. b
0.5-100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 0.5 10 100 0.5
Thnsl1e strength ksI MPa 425 380 370 360 315 315 330 270 285 290 260 160 255 275 240 150 90 250 205 160 85 70 215 130 95 160 85 55 70
62 55 54 52 46 46 48 39 41 42 38 23 37 40 35 22 13 36 30 23 12 10 31 19 14 23 12 8 10
YIeld strengtb ksi MPH 330 310 305 290 270 275 310 240 255 275 250 145 235 260 230 140 75 240 195 145 70 50 205 125 90 150 75 50 65
48 45
44 42 39 49 45 35 37 40 36 21 34 38 33 20 11 35 28 21 10 7.5 30 18 13 22 11 7 9.5
E1ongation(a) %
6 6 6 8 10 8 6 10 9 7 7 20 7 6 7 19 35 6 7 23 40 50 9 13 45 16 23 55 35
(a) In 4d. where d is diameter of reduced section oftensile-test specimen
359.0 (9Si-O.6Mg) Specifications U.S. and/or Foreign. Former ASTM. SG91A; UNS number. A03590; Government. MIL-A-21180 Chemical Composition. Composition Limits. 0.20 Cu max, 0.50 to 0.7 Mg, 0.10 Mn max, 8.5 to 9.5 Si, 0.20 Fe max, 0.10 Zn max, 0.20 Ti max, 0.05 other (each) max, 0.15 others (total) max, hal Al
Applications Typical Uses. A moderately high-strength permanent mold casting alloy having superior casting characteristics
Mechanical Properties Tensile Properties. See Tables
Recommended Heat Treating Practice Solution Temperature. 540°C (1000 "F); hold at temperature 10 to 14 h; hot water quench 60 to 80°C (140 to 175 OF) Aging Temperature. Room temperature for 8 to 16 h after solution treatment, then 155°C (310 "F) for 10 to 12 h (T61 temper), or 170°C (340 OF) for 6 to 10 h (T62 temper)
260 I Heat Treater's Guide: Nonferrous Alloys Alloy 359.0-T61: Minimum mechanical properties
CIass!a)
1 2 10 11
ThIlSiJe streDB!b(b) lui MPu
310 324 310 276
45 47 45 40
ThllSiJe y\e/dstreogtb(b)!c) MPa ksI
241 262 234 207
35 38 34 30
~
Comp.....lve yieldstrengtb!.) ksl MPa
4 3 4 3
241 262 234 207
Eloogatlon(b)!d),
35 38 34 30
(a)Gasses 1and2 (levelsofproperties) obtainable onlyfromdesignated areasofcasting;classes10 and 11maybe obtainedfromanylocationincasting.(b) SpecifiedinMlL·A·21180.(c)0.2%offset. (d) In 4d. where d is diameter of reduced sectionof tensile-test specimen. (e) Designvalues;not specified
Alloy 359.0-T6: Typical tensile properties of separately cast test bars 'Iemperature of -c
-196 -320 -80 -112 -28 -18 150 300 260
315 370
500
600
700
TIm. at temperature, b
100 1000 10000 0.5 10 100 1000 10000 0.5 10 100 0.5
ThIISU. strengtb MPa ksl
435 380 360 290 250 125 125 65 60 50 50 50 40 40
30
YIeld strengtb MPu lui
63 55 52 42 36 18 18 9.5 8.5 7.5 7 7.5 6 5.5 4.4
325 325 310 260 235 95 115
60 50 40
35 45 40
30 28
EIongatlon!a), ~
47 47 45 38 34 14 17 8.5 7 6 5 6.5 5.5 4.4 4
4 5 6 10 11
30 25 40
50 55 60 50 60 65 55
(a) In 4d. whered is diameter ofreducedsectionoftensile-test specimen
360.0, A360.0 (9.5Si-O.5Mg) Specifications u.s. and/or Foreign. AMS.360.0:4290F;Fonner ASTM. 360.0: SGlOOB. A360.0: SGlOOA;SAE. A360.0: J452, 309; UNS number. 360.0: A03600. A360.0: AI3600; Government. 360.0: QQ-A-591 Chemical Composition. Composition Limits. 360.0: 0.6 Cu max, 0.40 to 0.6 Mg, 0.35 Mn max, 9.0 to 10.0 Si, 2.0 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal AI. A360.0: 0.6 Cu max, 0040 to 0.6 Mg, 0.35 Mn max, 9.0 to 10.0 Si, 1.3 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal Al Consequence of Exceeding Impurity Limits. Increasing copper limits lowers resistance to corrosion; increasing iron lowers ductility. Decreasing silicon reduces castability
Applications Typical Uses. Die castings requmng improved corrosion resistance compared to 3800. Other applications where excellent castability, pressure tightness. resistance to hot cracking, strength at elevated temperatures, and ability to be electroplated are required. Poor weldability and brazeability. General-purpose casting alloy for such items as cover plates and instrument cases
Alloy 360.0-F and A360.0-F: Typical tensile properties for separately cast test bars at elevated temperature Thmperature OF -c
360.0aluminum 24 75 100 212 150 300 205 400 250 500 315 600 370 700 A36O.0 aluminum 24 75 100 212 150 300 205 400 250 500 315 600 370 700
Thnsile strengtb MPa ksI
Tensile Properties. Typical for separately cast test bars, as-cast. 360.0: tensile strength, 305 MPa (44 ksi); yield strength, 170 MPa (25 ksi); elongation, 2.5% in 50 mm or 2 in. A360.0: tensile strength, 320 MPa (46 ksi); yield strength, 170 MPa (25 ksi); elongation, 3.5% in 50 mm or 2 in. See Table
Fabrication Characteristics Joining. Same as alloys 413.0 and A413.0
E1ongation(b), ~
325 305 240 150 85 50 30
47 44 35 22 12 7 4.5
170 170 165 95 50 30 20
25 25 24 14 7.5 4.5 3
40
315 295 235 145 75 45 30
46
165 165 160
24 24 23 13 6.5 4 2.5
5 3 5 14 30 45 45
(a)0.2%offset.(b) In 50 mmor2 in.
Mechanical Properties
Yieldstrengtb!a) MPa ksi
43 34 21 11 6.5 4
90
45 28 15
3 2 4 8 20 35
Aluminum Casting Alloys /261
380.0, A380.0 (8.5Si-3.5Cu) Specifications U.S.and/or Foreign. AMS. A380.0: 4291; Fonner ASTM. 380.0: SC84B. A380.0: SC84A; SAE. 380.0: 308. A380.0: 306; UNS number. 380.0: A03800. A380.0: A13800; Government. A380.0: QQ-A591; Foreign. 380.0: Canada, CSASC84 Chemical Composition. Composition Limits. 380.0: 3.0 to 4.0 Cu, 0.10 Mg max, 0.50 Mn max, 7.5 to 9.5 Si, 2.0 Fe max, 0.50 Ni max, 3.0 Zn max, 0.35 Sn max, 0.50 others (total) max, bal AI. A380.0: 3.0 to 4.0 Cu, 0.10 Mg max, 0.50 Mn max, 7.5 to 9.5 Si, 1.3 Fe max, 0.50 Ni max, 3.0 Zn max, 0.35 Sn max, 0.50 others (total) max, bal Al
Consequence of Exceeding Impurity Limits. Increasing iron will lower
aluminum die casting alloy. Poor weld ability and brazeability; fair strength at elevated temperatures
Mechanical Properties Tensile Properties. Typical for separately cast test bars, as-cast. 380.0: tensile strength, 330 MPa (48 ksi); yield strength, 165 MPa (24 ksi); elongation, 3% in 50 rom or 2 in. A380.0: tensile strength, 325 MPa (47 ksi); yield strength, 160 MPa (23 ksi)
Fabrication Characteristics Joining. Same as alloy 413.0 and A413.0
ductility. Relatively large quantities of impurities may be present before serious effects are detected
Recommended Heat Treating Practice
Applications
Annealing Temperature. For increased ductility, 260 to 370°C (500 to 700 "F); hold at temperature 4 to 6 h; furnace cool or cool in still air
Typical Uses. Vacuum cleaners, floor polishers, parts for automotive and
Stress Relief Temperature. 175 to 260°C (350 to 500 "F); hold at
electrical industries such as motor frames and housings. Most widely used
temperature 4 to 6 h; cool in still air
Alloy 380.0-F: Typical tensile properties for separately cast test bars at elevated temperature
Alloy 380.0-F: Tensile properties of die cast alloy at various temperatures
Temperature OF °C
24 100 150 205 260 315 370
75 212 300 400 500 600 700
'Thnslle strength ksi MPH
330 310 235 165 90 50 30
48 45 34 24 13 7 4
Yieldstrength MPa ksI
165 165 150 110 55 30 15
24 24 22 16 8 4 2.5
Elongation, %
3 4 5 8 20 30 35
'Thmperalure OF °C
-195 -80 -26 24 100 150 205 260 315 371
-320 -112 -18 75 212 300 400 500 600 700
'Thmu.strength ksI MPa
407 338 338 330 310 235 165 90 49 28
59 49 49 48 45 34 24 13 7 4
YIeldstrength!a) MPa ksI
207 165 165 165 165 152 110 55 28 17
30 24 24 24 24 22 16 8 4 2.5
Elongation, %
2.5 2.5 3 3 4 5 8 20 30 35
(a) 0.2% offset
383.0 (10.5Si-2.5Cu) Specifications U.S. and/or Foreign. Former ASTM. SCI02A; SAE. 383; UNS number. A03830
Mechanical Properties Tensile Properties. Typical for separately cast test bars, as-cast: tensile
Chemical Composition. Composition Limits. 2.0 to 3.0 Cu, 0.10 Mg max, 0.50 Mn max, 9.5 to 11.5 si, 1.3 Fe max, 0.30 Ni max, 3.0 Zn
strength, 310 MPa (45 ksi); yield strength, 150 MPa (22 ksi); elongation, 3.5% in 50 rom or 2 in.
max, 0.15 Sn max, 0.50 others (total) max, bal Al
Hardness. 75 HB (500 kg load, 10 rom ball)
Applications
Recommended Heat Treating Practice
Typical Uses. Applications requiring good die filling capacity, fair pres-
Stress Relief Temperature. 175 to 260°C (350 to 500 oF); hold at temperature 4 to 6 h; cool in still air
sure tightness I electroplating and machining characteristics, and strength at elevated temperature, poor weldability, and brazeability; anodizing quality is poor
Annealing Temperature. For increased ductility, 260 to 370°C (500 to 700 "F); hold at temperature 4 to 6 h; furnace cool or cool in still air
262/ Heat Treater's Guide: Nonferrous Alloys
384.0, A384.0 (11.2Si-3.8Cu) Specifications U.S. and/or Foreign. Fonner ASTM. SC114A; SAE. 303; UNS number. 384.0: A03840. A384.0: A13840; Government. 384.0: QQ-A-591
Chemical Composition. Composition Limits. 384.0: 3.0 to 4.5 Cu, 0.10 Mg max, 0.5 Mn max, 10.5 to 12.0 si, 1.3 Fe max, 0.50 Ni max, 3.0 Zn max, 0.35 Sn max, 0.50 others (total) max, bal AI. A384.0: 3.0 to 4.5 Cu, 0.10 Mg max, 0.50 Mn max, 10.5 to 12.0 Si, 1.3 Fe max, 0.50 Ni max, 1.0 Zn max, 0.35 Sn max, 0.50 others (total) max, bal Al Consequence of Exceeding Impurity Limits. Generally insensitive to minor variations in composition, but resistance to corrosion is reduced and lowers as copper increases
Mechanical Properties Tensile Properties. Typical for separately cast test bars, as-east, 384.0 and A384.0: tensile strength, 330 MPa (48 ksi); yield strength, 165 MPa (24 ksi); elongation, 2.5% in 50 mm or 2 in. Hardness. 384.0 and A384.0: 85 HB (500 kg load, 10 mm ball)
Recommended Heat Treating Practice Stress Relief Temperature. 175 to 260°C (350 to 500 "F); hold at temperature 4 to 6 h; cool in still air Annealing Temperature. For increased ductility, 260 to 370°C (500 to 700 OF); hold at temperature 4 to 6 h; furnace cool or cool in still air
Applications Typical Uses. Die casting applications where fair pressure tightness and fair strength at elevated temperatures are required. Better die filling than 380.0. Poor weldability and brazeability
390.0, A390.0 (17.0Si-4.5Cu-O.6Mg) Specifications U.S. and/or Foreign. UNS number. 390.0 die cast-
Alloy 390.0: Typicalelevated-temperature tensile yield strength for separately cast test bars
ings, A03900. A390.0; sand and permanent mold castings, A13900 Thmperalure
Chemical Composition. Composition Limits. 390.0: 4.0 to 5.0 Cu,
Temper
0.45 to 0.65 Mg, 0.10 Mn max, 16.0 to 18.0 Si, 1.3 Fe max, 0.10 Zn max, 0.20 Ti max, 0.10 others (each) max, 0.20 others (total) max, bal AI. A390.0: 4.0 to 5.0 Cu, 0.45 to 0.65 Mg, 0.10 Mn max, 16.0 to 18.0 Si, 0.5 Fe max, 0.10 Zn max, 0.20 Ti max, 0.10 others (each) max, 0.20 others (total) max, bal Al
F
T5
Typical Uses. Automotive cylinder blocks, four cycle air-cooled en-
Mechanical Properties
T6
T7
Tensile Properties. See Tables Hardness. See Table
Recommended Heat Treating Practice
38 95 150 205 260 38 95 150 205 260 38 95 150 205 260 38 95 150 205 260
100 200 300 400 500 100 200 300 400 500 100 200 300 400 500 100 200 300 400 500
195 195 180 155 100 210 225 195 160 85 365 335 305 235 70 280 270 245 195 70
34 10 40 39 35 28 10
38 95 150 205 260
100 200 300 400 500
260 285 265 210 125
37 41 38 30 18
Aging Temperature. T5 and T7 tempers: 230°C (450 "F), T6 temper: 175°C (350 "F); hold at temperature for 8 h
28 28 26 22 14 30 32 28 23 12 52 48 44
Die castings F
Solution Temperature. 495°C (925 oF)
OF
Acurad castings
Applications gines, air compressors, Freon compressors, pumps requiring abrasive resistance, pulleys, and brake shoes. Other applications where high wear resistance, low coefficient of thermal expansion, good elevated-temperature strength, and good fluidity are required
Yield streogth(o) MPo ksi
-c
(a) Based on cast-to-size test specimens tested after 1000 h holding at test temperature
Aluminum Casting Alloys /263 Alloys 390.0 and A390.0: Typical room-temperature mechanical properties for separately cast test bars Temper
Yield strength(h) MPa lIsi
TeIl5iJe strength(a) MPa lIsi
>\390.0,sand castings 26 F.T5 180 T6 40 275 T7 36 250 A390.0, permanent mold castings F,T5 29 200 45 T6 310 T7 260 38 390.0, conventional die castings 40.5 F 280 T5 43 295 390.0, Acurad castings F 30 205 T5 205 30 T6 53 365 40 T7 275
Hardness(a)(c), HB
180 275 250
26 40 36
100 140 115
200 310 260
29 45 38
110 145 120
240 260
35 38
195 200 365 275
28 29 53 40
Fatigue strength(d) MPa ksi
105
15
115 100
17 14.5
120 125
140
20
110 110 150 125
90 95
13 14 17 16
115
110
(a)Tensilepropertiesand hardnessaredetennined from standardcast-to-sizetensilespecimens 12.7 mm(0.5in.)diameterforsand,pennanentmold,andAcuradcastingsand6.4rrun(0.25 in.)diameter for die castings and tested without machining the surface. (b) 0.2% offset. For 390.0 and A39O.0 castings,yield strength normallyequals tensilestrength because0.2% offsetis not reachedprior to fracture.(c) 500 kg load; 10mm ball. (d)At 5 x 108 cycles;R.R.Moore type test
413.0, A413.0 (12Si) Commercial Names. Fonner designation. 413.0: 13. A413.0: A13 Specifications U.S.and/or Foreign. Fonner ASTM. 413.0: S12B. B85 SI2A; SAE. A413.0: J453, 305; UNS number. 413.0: A04130. A413.0: A14130; Government. A413.0: QQ-A-591 (class 2); Foreign. Canada: A413.0, CSA SI2P; France: NF A-S13. ISO: AlSi12
Chemical Composition. Composition Limits. 413.0: 1.0 Cu max, 0.10 Mg max, 0.35 Mn max, 11.0 to 13.0 Si, 2.0 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal AI. A413.0: 1.0 Cu max, 0.10 Mg max, 0.35 Mn max, 11.0 to 13.0 Si, 1.3 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max, 0.25 others (total) max, bal AI
Consequence of Exceeding Impurity Limits. Content of impurities may be quite high before serious effects are detected. Increasing copper lowers corrosion resistance; increasing iron and magnesium lowers ductility; increasing silicon content may lead to machining problems
Applications Typical Uses. Miscellaneous thin-walled and intricately designed castings. Other applications where excellent castability, resistance to corrosion, and pressure tightness are required
Mechanical Properties Tensile Properties. Typical for separately cast test bars, as-cast. 413.0: tensile strength, 300 MPa (43 ksi); yield strength, 145 MPa (21 ksi); elongation, 2.5% in 50 mrn or 2 in. A413.0: tensile strength, 290 MPa (42
ksi); yield strength, 130 MPa (19 ksi); elongation, 3.5% in 50 mrn or 2 in. See Table
Fabrication Characteristics Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder: After copper plating, then use methods applicable to copper-base alloys. Resistance welding: flash method
Alloy413.0-F: Typicaltensile properties for separately cast test bars at elevated temperature Temperature OF
-c
-195 ~O
-28 24 100 150 205 260 315 370
-320 -112 -18 75 212 300 400 500 600 700
Tensile strength MPa ksi 360 310 303 295 255 220 165 90 50 30
(a)0.2% offset. (b) In 50mmor2 in.
52 45 44 43 37 32 24 13 7 4.5
Yield strength(a) ksi MPa 160 145 145 145 140 130 105 60 30 15
23 21 21 21 20
19 15 9 4.5 2.5
Eiongation(h). %
1.5 2 2 2.5 5 8 15 30 35 40
264/ Heat Treater's Guide: Nonferrous Alloys
443.0, A443.0, 8443.0, C443.0 (5.2Si) Commercial Names. Fonner designation. 43
Fabrication Characteristics
Specifications U.S.and/or Foreign. Fonner ASTM.443.0:S5B. B443.0: S5A. C443.0: S5C; SAE. C443.0: 304; UNS number. 443.0: A04430. A443.0: Al4430. B443.0: A24430. C443.0: A34430; Government. B443.0: QQ-A-601 (class 2). C443.0: QQ-A-591; Foreign. Canada: CSA S5
Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder with copper plate and use methods applicable to copper-base alloys for die castings. Use Alcoa No. 802, no flux or rub-tin with Alcoa No. 802 for sand and permanent mold castings. Sand and pennanent mold casting alloys (unless otherwise noted): braze with Alcoa No. 717; Alcoa No. 33 flux; flame either reducing oxyacetylene or reducing oxyhydrogen. Atomic-hydrogen weld with 4043 alloy; Alcoa No. 22 flux. Oxyacetylene weld with 4043 alloy; Alcoa No. 22 flux; neutral flame. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa No. 27 flux (manual). Tungsten-arc argon-atmosphere weld 4043 alloy; no flux. Resistance weld: flash method for die cast alloys; spot, seam, and flash methods for sand and pennanent mold cast alloys
Chemical Composition. Composition Limits. 443.0: 0.6 Cu max, 0.05 Mg max. 0.50 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.25 Cr max, 0.50 Zn max, 0.25 Ti max, 0.35 others (total) max, bal AI. A443.0: 0.30 Cu max, 0.05 Mg max, 0.50 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.25 Cr max, 0.50 Zn max. 0.25 Ti max, 0.35 others (total) max, bal AI. B443.0: 0.15 Cu max, 0.05 Mg max. 0.35 Mn max, 4.5 to 6.0 Si, 0.8 Fe max, 0.35 Zn max, 0.25 Ti max, 0.25 others (total) max, bal AI. C443.0: 0.6 Cu max, 0.10 Mg max, 0.35 Mn max, 4.5 to 6.0 si, 2.0 Fe max, 0.50 Ni max, 0.50 Zn max, 0.15 Sn max. 0.25 others (total) max, bal Al Consequence of Exceeding Impurity Limits. For die cast alloy, relatively large quantities of impurities may be present before serious effects are detected. Increasing copper tends to lower resistance to corrosion; increasing iron and magnesium tends to lower ductility. For sand and permanent mold cast alloys, high copper. iron, or nickel decreases ductility and resistance to corrosion. Increasing magnesium reduces ductility
Applications Typical Uses. Cooking utensils, food-handling equipment, marine fittings, miscellaneous thin-section castings. Die castings: applications where good pressure tightness, above-average ductility, and excellent resistance to corrosion are required. Sand and permanent mold castings: applications where very good castability and resistance to corrosion with moderate strength are required
Mechanical Properties Tensile Properties. See Table Hardness. F temper: 443.0 (sand castings): 40 HB. B443.0 (permanent mold castings): 45 HB. C443.0 (die castings): 65 HB (500 kg load, 10 rom ball)
Alloy 443.0, 443.0-F, 8443.0-F, C443.0-F: Typical tensile properties for separately cast test bars Temperature OF OC
'IensUestrengtb MP. ksl
443.0-F sand castings 24 130 75 B443.0-F permanent mold castings 24 160 75 C443.0-F die castings 24 230 75 100 195 212 150 150 300 205 400 110 260 500 60 315 600 35 370 700 25
Yieldstrengtb!.) MP. ksi
Elong8lion(b), 'I
19
55
8
8
23
60
9
10
33 28 22 16 9 5 3.5
110 110 105 85 40 25 15
16 16 15 12 6 3.5 2.5
9 9 10 25 30 35 35
(a) 0.2% offset. (b)In50mmor2in.
514.0 (4Mg) Commercial Names. Fonner designation. 214
Applications
Specifications U.S. and/or Foreign. Fonner ASTM. G4A; SAE. 320; UNS number. A05140; Government. QQ-A-60l (class 5); Foreign. Canada: CSA G4. United Kingdom: DID 165. ISO: AIMg3
Typical Uses. Dairy and food-handling applications. cooking utensils. fittings for chemical and sewage use. Other applications where excellent resistance to corrosion and tarnish are required
Chemical Composition. Composition Limits. 0.15 Cu max, 3.5 to 4.5 Mg, 0.35 Mn max, 0.35 Si max, 0.50 Fe max. 0.15 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al
Mechanical Properties
Consequence of EXceeding Impurity Limits. High copper or nickel greatly decreases resistance to corrosion and decreases ductility. High iron, silicon, or manganese decreases strength and ductility. Tin reduces resistance to corrosion
Tensile Properties. Typical, F temper. Tensile strength, 145 MPa (21 ksi); yield strength, 95 MPa (14 ksi); elongation, 3.0%. See Table Hardness. 50 HB (500 kg load, 10 rom ball)
Fabrication Characteristics Joining. Rivet compositions: 6053-T4. 6053-T6, 6053-T61. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Braze with Alcoa
Aluminum Casting Alloys /265 No. 717; Alcoa No. 33 flux; flame either reducing oxyacetylene or reducing oxyhydrogen. Atomic-hydrogen weld with 4043 alloy; Alcoa No. 22 flux. Oxyacetylene weld with 4043 alloy; Alcoa No. 22 flux; flame neutral. Metal-arc weld with 4043 alloy; Alcoa No. 27 flux. Carbon-arc weld with 4043 alloy; Alcoa No. 24 flux (automatic), Alcoa 27 flux (manual). Tungsten-arc argon-atmosphere weld with 4043; no flux. Resistance welding: spot, seam, and flash welds
Alloy 514.0-F: Typical tensile properties for separately cast test bars 'Thmperature OF
°C
24 150 205 260 315
75 300 400 500 600
'Thnsile strength lis; MP.
170 150 125 90 60
25 22 18 13 9
YieldS\ftngth(.) MP. ksi
85 85 85 55 30
12 12 12 8 4
Elongation, II>
9 7 9 12 17
(a) 0.2% offset
518.0 (8Mg) Commercial Names. Former designation. 218 Specifications U.S. and/or Foreign. Former AS'IM. G8A; UNS number. A05180; Government.QQ-A-591 Chemical Composition. Composition Limits. 0.25 Cu max, 7.5 to 8.5 Mg, 0.35 Mnmax, 0.35 Si max, 1.8Femax,0.15Nimax, 0.15 Zn max, 0.15 Sn max, 0.25 others (total) max, bal Al
Applications Typical Uses. Alloy has excellent corrosion resistance and machinability; high ductility; poor castability (is hot short). Takes a high polish;
difficult to attain a uniform appearance after anodizing. Non-heat treatable. Poor weldability and brazeability. Used for die cast marine fittings, ornamental hardware, ornamental automotive parts, and other applications requiring the highest corrosion resistance
Mechanical Properties Tensile Properties. Typical, F temper. Tensile strength, 310 MPa (45 ksi); yield strength, 190 MPa (28 ksi); elongation, 5 to 8% in 50 rnm or 2 in. Hardness. 80 HB (500 kg, 10 rnm load)
520.0 (10Mg) Commercial Names. Former designation. 220 Specifications U.S. and/or Foreign. AMS. 4240; Former AS'IM. GIOA; SAE. 324; UNS number. A05200; Government. QQ-A-60l (class 16); Foreign. Canada: CSAGIO. France: NF A-GIO. ISO: AIMglO Chemical Composition. Composition Limits. 0.25 Cu max, 9.5 to 10.6 Mg, 0.15 Mn max, 0.25 Si max, 0.30 Fe max, 0.15 Zn max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal Al
Hardness. 75 HB (500 kg load, 10 rnm ball)
Fabrication Characteristics Joining. Rivet compositions: 6053-T4, 6053-T6, 6053-T61. Soft solder with Alcoa No. 802; no flux. Rub-tin with Alcoa No. 802. Resistance welding: spot, seam, and flash methods
Consequence of Exceeding Impurity Limits. High copper or nickel greatly decreases resistance to corrosion. High iron, silicon, or manganese contents adversely affect mechanical properties
Applications Typical Uses. Aircraft fittings, railroad passenger-car frames, miscellaneous castings requiring strength and shock resistance. Other applications where excellent machinability and resistance to corrosion with highest strength and elongation of any aluminum sand casting alloy are desired
Mechanical Properties Tensile Properties. Typical. T4 temper: tensile strength, 330 MPa (48 ksi); yield strength, 180 MPa (26 ksi); elongation in 50 mm or 2 in., 16%. See Table
Alloy 520.0-F: Typical tensile properties for separately cast test bars at elevated temperature 'Thmperalure OF -c
24 150 205 260 315
75 300 400 500 600
(a) In 50mmor2 in.
'IImsIJe strenglh MP. ksl
315 240 150 105 70
46 35 22 15 10.5
0.211> yleldstrength ksI MPa
170 130 80 50 25
25 19
11.5 7.5 3.5
EIongatlon(.), II>
14 16 40 55 70
266/ Heat Treater's Guide: Nonferrous Alloys
535.0, A535.0, B535.0 (7Mg) Commercial Names. Former designations. 535.0: Almag35. A535.0: A218. B535.0: B218
Specifications U.S.and/or Foreign. Fonner AMS. 4238A, 4239; Former ASTM. 535.0: GM70B; UNS number. 535.0: A05350. A535.0: A15350. B535.0: A25350; Government. 535.0: QQ-A-601, QQ-A-371 Chemical Composition. Composition Limits. 535.0: 0.05 Cu max, 6.2 to 7.5 Mg, 0.10 to 0.25 Mn, 0.15 Si max, 0.15 Fe max, 0.10 to 0.25 Ti, 0.003 to 0.007 Be, 0.002 B max, bal AI. A535.0: 0.10 Cu max, 6.5 to 7.5 Mg, 0.10 to 0.25 Mn, 0.20 Si max, 0.20 Fe max, 0.25 Ti max, 0.05 others (each) max, 0.15 others (total) max, bal AI. B535.0: 0.10 Cu max, 6.5 to 7.5 Mg, 0.05 Mn max, 0.15 Si max, 0.15 Fe max, 0.10 to 0.25 Ti, 0.05 others (each) max, 0.15 others (total) max, bal Al
Applications Typical Uses. Maximum properties are available immediately after casting without the aid of heat treatment or natural aging. Used in parts in computing devices, aircraft and missile guidance systems, and electric equipment where dimensional stability is essential. Highly useful in marine and other corrosive-prone applications
speeds. 535.0 takes a very high mirror polish. Normally this alloy is used for sand and permanent mold castings, but it can also be used for die castings. Where high dimensional tolerance is required, the following procedure should be used: rough machine parts; heat at 200°C (400 "F) for 14 h; cycle between -73 to 100 °C (100 to 212 "F) five times (30 h/cycle); finish machine; heat 10 h at 200°C (400 OF); cycle between -73 to 100°C (-100 to 212 "F) 25 times (30 h/cycle). 535.0 may be stress relieved at approximately 370°C (700 OF) for 5 h; air cool. Creep resistance at 370°C (700 OF) is very low, permitting plastic flow under the load of locked-up stresses and resulting in stress-free castings. On air cooling from 370 °C (700 OF), 535.0 will have full hard and physical properties and will be stable. After being stress relieved, most castings from 535.0, A535.0, and B535.0 can be rough and finish machined without breaking into the machining sequence
Weldability. Can be welded by any inert gas shielded-arc systems using filler material of 5356 or 535.0 aluminum. Welding fluxes should be avoided if possible. Because of the beryllium content in alloy 535.0, care should be taken not to inhale fumes during welding Anodizing. Use sulfuric acid process to produce a pure satin white finish capable of being dyed to brilliant pastel colors
Mechanical Properties Tensile Properties. F and T5 tempers: 535.0: Tensile strength: typical, 275 MPa (40 ksi); minimum, 240 MPa (35 ksi). Yield strength: typical, 140 MPa (20 ksi); minimum, 125 MPa (18 ksi). Elongation in 50 mm or 2 in.: typical, 13%; minimum, 8.0%. See Table
Hardness. Typical: 60 HB. Minimum: 70 HB
Chemical Properties General Corrosion Behavior. 535.0 has the highest resistance to corrosion of any of the common aluminum casting alloys
Fabrication Characteristics Machinability. Superior, can be milled at speeds four times faster than other aluminum casting alloys. High microfinishes can be achieved at high
Alloy 535.0-F: Typical tensile properties for separately cast test bars at elevated temperature Thmpernlure OF °C
150 175 205 260 315 370
300 350 400 500 600 700
Thmile strength list MPa
260 235 220 180 140 105
37.5 34 32 26.5 20.5 15.5
EIoogation(a),
"
11 14 14
13 13 12
(a) In 50 nun or 2 in.
712.0 (5.8Zn-O.6Mg-O.5Cr-O.2Ti) Commercial Names. Former designations. D712.0, D612, 40E Specifications U.S. and/or Foreign. Fonner ASTM. ZG61A; SAE. 310; UNS number. A47120; Government. QQ-A-601 (class 17)
Applications Typical Uses. Applications where a good combination of mechanical
Chemical Composition. Composition Limits. 0.25 Cu max, 0.50 to
properties is required without heat treatment: shock and corrosion resistance, machinability, dimensional stability, no distortion in heat treating
0.65 Mg, 0.10 Mn max, 0.30 Si max, 0.50 Fe max, 0.40 to 0.6 Cr, 5.0 to 6.5 Zn, 0.15 to 0.25 Ti, 0.05 others (each) max, 0.20 others (total) max, bal Al
Mechanical Properties Tensile Properties. F or T5 temper. Typical tensile strength, 240 MPa (35 ksi); yield strength, 170 MPa (25 ksi); elongation, 5%. Low-temperature strength after 24 h at -70°C (-94 oF): tensile strength, 265 MPa (38.4 ksi); elongation in 50 mm or 2 in., 5%. See Table
Aluminum Casting Alloys /267 Hardness. 70 HB (500 kg load, 10 mm ball)
Recommended Heat Treating Practice Aging Temperature. T5 temper: room temperature for 21 days or at 157 °C (315 "F) for 6 to 8 h
Alloy 712.0-F: Typical tensile properties for separately cast test bars at elevated temperature Thmperature 0C
OF
79 120 175
175 250 350
'Thnsile strength MPa ksi
235 205 135
0.2 % yleldstrength MPa ksi
34 29.5 19.5
210 175 115
30.5 25 17
E1ongation(a), %
3 2 6
(a)In50mmor2in.
713.0 (7.5Zn-O.7Cu-O.35Mg) Commercial Names. Former designation. 613, Tenzaloy Specifications U.S. and/or Foreign. Former ASTM. Sand castings, B26 ZC81A. Permanent mold castings, B108 ZC8lB; Former SAE. 315; UNS number. A07130; Government. Sand castings, QQ-A-601 (class 22). Permanent mold castings: QQ-A-596 (class 12) Chemical Composition. Composition Limits. 0.40 to 1.0 Cu, 0.20 to 0.50 Mg, 0.6 Mn max, 0.25 Si max, 1.1 Fe max, 0.35 Cr max, 0.15 Ni max, 7.0 to 8.0 Zn, 0.25 Ti max, 0.10 others (each) max, 0.25 others (total) max, balAI
Applications Typical Uses. Cast aluminum furniture and other very large casting applications that require high strength without heat treatment. 713.0 ages at room temperature to produce mechanical properties equivalent to those of common heat-treated aluminum cast alloys. These properties develop in 10 to 14 days at room temperature or in 12 h at 120°C (250 "F)
Mechanical Properties Tensile Properties. Typical for T5 temper, aged at room temperature for 21 days or artificially aged at 120 ± 5.5 °C (250 ± 10 OF) for 16 h. Sand casting: tensile strength, 205 MPa (30 ksi); yield strength: ISO MPa (22 ksi); elongation, 4.0% in 50 mm or 2 in. Permanent mold casting: tensile
strength, 220 MPa (32 ksi); yield strength: ISO MPa (22 ksi); elongation, 3.0% in 50 mm or 2 in.
Chemical Properties General Corrosion Behavior. Good resistance to corrosion, equivalent to aluminum-silicon alloys. A typical corrosion test showed no loss in mechanical properties after immersion for 90 days in aerated 3% salt-water solution. Not subject to acceleration of corrosion by stress or to stress-corrosion cracking as determined by the standard test of exposure for 14 days to the corrosive medium while under a continuous load of 75% of yield strength
Fabrication Characteristics Machinability. Good machinability and polishing characteristics. Very good dimensional stability. Fully aged material shows a decrease in length of less than 0.1 min/in. of length. If713.0 is given a stress-relief treatment of 6 h at 450°C (850 "F) and air cooled, it ages naturally. The resulting product is a stress-free, full-strength casting. This is not possible with any heat-treatable aluminum alloy Weldability. For high-strength welds, shielded-arc methods can be used with filler alloys 5154 and 5356 Brazeability. Readily brazed at 540 to 595°C (1000 to 1100 "P) using any of the common brazing methods
771.0 (7ln-O.9Mg-O.13Cr) Commercial Names. Former designation. Precedent 71A
Mechanical Properties
Specifications U.S. and/or Foreign. Former ASTM. 771.0: ZG71B; UNS number. A07710; Government. 771.0: QQ-A-60lE
Tensile Properties. See Table
Chemical Composition. Composition Limits. 0.10 Cu max, 0.8 to 1.0 Mg, 0.10 Mn max, 0.15 Si max, 0.15 Fe max, 0.06 to 0.20 Cr, 6.5 to 7.5 Zn, 0.10 to 0.20 Ti, 0.05 others (each) max, 0.15 others (total), bal Al
Applications Typical Uses. Applications where dimension stability is important. Polishes to a high luster; anodizes with good clean appearance. Good corrosion resistance
Fabrication Characteristics Machinability. 771.0-T5 has good stability and machinability. It can be milled five times faster and hole worked at twice the speed of alloys such as 356.0 and 319.0. It can be finished machined in one clamping operation to flatness tolerance of 0.001 in. This reduces total cost of machining over most casting alloys, which require two clamping operations to obtain this type of flatness tolerance Weldability. Can be welded by either gas tungsten-arc or gas metal-arc welding using 5356 rod or wire. Special procedure should be followed in welding to ensure good results.
268/ Heat Treater's Guide: Nonferrous Alloys If parts are to be welded, the operation should be made part of the heat-treating cycle. If welding is to be done on T6 or 17 I parts, the castings are heated to 580°C (1080 "F), removed from the heat-treating furnace, and welded while hot. The parts are then returned to the furnace and the T6 and 171 heat treatments continued. If the parts are to be used in the T52 or T2 temper, they are heated to 415°C (775 OF), taken from the furnace, welded hot, then returned to the furnace and the heat treatment continued. Items to be used in the T51 temper are heated to 205°C (405 "F), taken from the furnace, welded hot, then returned to the furnace and T51 treatment continued. Repair weld parts should be heated and welded as described above
The T5 temper should not be welded but can be welded if the procedure for T51 is used
Recommended Heat Treating Practice See Table
Alloy 771.0: Heat treatments
T2
Alloy 771.0: Minimum mechanical properties for separately cast test bars
T5 T6
'Iemper
T5 T51 T52 T6 TIl
ThosiIe strength (min) ksI MPa
290 220 250 290 330
42 32 36 42 48
YlOId strength (Min)(a) MPa ksI
260 185 205 240 310
38 1:1 30 35 45
E1ongatlon(b),
...
Hardness(c). DB
1.5 3.0 1.5 5.0 2.0
100 85 85 90 120
(a) 0.2%offset, (b) In 50mmor2 in. (c)500 kg load. 10mrnbaIl
'frealmeDl
'Iemper
T51 T52
TIl
Holdat415± 14°C (775±25 OF) for5 h; cooloutsidefurnacein stillair toroom temperature; hardenbyreheatingto 180±3 °C(36O±5 OF) for4 h;cool in air Holdat 180± 3 °C (355± 5 oF)for 3 to 5 h; cooloutsidefurnacein still air to room temperature Hold8t580 to 595°C (1080to 1100oF)for6 h;cooloutsidefurnace to roomtemperature in stillair;agebyholdingfor 3 h at 130°C (265oF)followed bycoolingin stillair Agebyholding8t205 °C (405oF)for6 h; cool in still air Holdat415 °C(775±25 oF)for5 h; coolfrom415 to 345°C (775t0650°F)in2hor more;coolfrom345to230°C (650to 450 "P) innotmorethan0.5h (20 mindesirable); coolfrom230 to 120°C (450to250 oF)inapproximately 2 h;coolfrom 120°C (250oF) to roomtemperature instill air outsideoffurnace;hardenbyreheatingto 165°C (330"P) for6to 16h andcoolingoutsideoffurnace in still air Holdat 580to 595°C (1080to 1100oF)for6 h;cooloutsidefurnace ioroomtemperature in stillair;agebyholdingat 140°C (285oF)for IS h followed bycoolingin stillair. Similarproperties can be obtainedbyagingat ISS°C (310°F) for3 h
850.0 (6.28n-1Cu-1 Ni) Commercial Names. Former designation. 750
Applications
Specifications U.S. and/or Foreign. AMS. Permanent mold casting: 4275; UNS number. A08500; Government. QQ-A-596 (class 15)
Typical Uses. Applications where excellent bearing qualities are required
Chemical Composition. Composition Limits. 0.7 to 1.3 Cu, 0.10 Mg max, 0.10 Mn max, 0.7 Si max, 0.7 Fe max, 5.5 to 7.0 Sn, 0.7 to 1.3 Ni, 0.20 Ti max, 0.30 others (total) max, bal Al Consequence of Exceeding Impurity Limits. High iron, manganese, or magnesium decreases ductility and increases hardness. High silicon modifies bearing characteristics
Mechanical Properties Tensile Properties. Typical for T5 temper: tensile strength, 160 MPa (23 ksi); yield strength, 75 MPa (11 ksi); elongation in 50 rom or2 in., 10% Hardness. T5 temper: 45 HB (500 kg load. 10 mm ball)
Recommended Heat Treating Practice Aging Temperature. 230°C (450 OF); hold at temperature for 8 h
Heat Treating Aluminum-Lithium Alloys Commercial aluminum-lithium alloys are targeted as advanced materials for aerospace technology primarily because of their low density, high specific modulus, and excellent fatigue and cryogenic toughness properties. Superior fatigue crack propagation resistance in comparison with that of traditional2xxx and 7xxx alloys, is primarily due to high levels of crack tip shielding, meandering crack paths, and the resultant roughness-induced crack closure. However, the fact that these alloys derive their superior properties extrinsically from the above mechanisms has certain implications with respect to small-crack and variable-amplitude behavior. For example, aluminum-lithium alloys lose their fatigue advantage over conventional aluminum alloys in compression-dominated variable-amplitude
fatigue spectra tests. However, in tension-dominated spectra, aluminumlithium alloys show greater retardations on the application of single-peak tensile overloads. The principal disadvantages of peak-strength aluminum-lithium alloys are reduced ductility and fracture toughness in the short-transverse direction, anisotropy of in-plane propeties, the need for cold work to attain peak properties, and accelerated fatigue crack extension rates when cracks are microstructurally small. These limitations have precluded the direct substitution of aluminum airframe alloys. However, certain aluminum-lithium alloys exhibit more damage tolerance, strength, and corrosion resistance than other aluminum-lithium alloys.
Weldalite 049 an AI-Cu-Li alloy Chemical Composition. Nominal. 5.4 Cu, 1.3 u, 0.4 Ag, 0.4 Mg, 0.14 Zr, Other, each: 0.4 Ag, bal Al
Product Forms. The alloy is available as sheet, plate, forgings, and extrusions
Applications. A weldable alloy for aerospace applications, such as propellant tanks for cryogenic service, Weldalite 049 was designed to replace major aluminum alloys such as 2219 and 2014 in launch system applications
In high strength plate and forging applications, Weldalite 049 is compared with 7075-T651 In welding applications for sheet, plate, forgings, and extrusions, it is compared with 2219
Characteristics Joining. Weldalite 049 has very good weldability; for example, it displays no discernible hot cracking in highly restrained weldments made by gas tungsten arc, gas metal arc, and variable polarity plasma arc (VPPA) welding. Extremely high weldment strengths have been reported using conventional 2319 filler, and even higher weldment strengths have been obtained with the use of a proprietary Weldalite filler (see adjoining Table). A mean VPPA weldment strength of 370 MPa (54 ksi) has been obtained by welding Weldalite 049 with 049 filler. High strengths (310 MPa, or 45 ksi, ultimate tensile strength) have also been attained with tungsten inertgas welds Forging. The ability of Weldalite 049 to attain high strength without cold work is particularly beneficial for forgings, where the uniform introduction of cold work is often impractical. Weldalite 049 small-scale forgings and commercial Boeing hook forgings have displayed tensile strengths of greater than 700 MPa (100 ksi). See Table for tensile properties in various tempers and product forms
Mechanical Properties Fracture Toughness. See Table for plain strain fracture toughness of Weldalite 049 extruded bar
Yield Strength, See Figure for the yield strengths of Weldalite 049 and another aluminum-lithium alloy, 2219 in the T87 temper, at cryogenic temperatures
Recommended Heat Treating Practice Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thennomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging Weldalite 049 shows high strength in a variety ofproducts and tempers (see adjoining Table). Its natural aging response is extremely strong with cold work (temper TI), and even stronger without cold work (1'4); in fact, it has a stronger natural aging response than that of any other known aluminum alloy. Weldalite 049 undergoes reversion during the early stages of artificial aging, and its ductility increases significantly up to 24%. Tensile strengths of 700 MPa (100 ksi) have been attained in both T6 and T8 tempers produced in the laboratory. As shown in adjoining Figure, specimens of Weldalite 049 in the peak-aged condition all have essentially the same level of hardness despite varying degrees (from 0.5 to 9%) of cold work prior to aging; the yield strength of Weldalite 049 is also relatively unaffected by prior cold work The ability of Weldalite 049 to attain high strength without cold work is particularly beneficial for forgings, where the uniform introduction ofcold work is often impractical (see adjoining Table). Weldalite 049 small-scale forgings and commercial Boeing hook forgings have displayed tensile strengths of greater than 700 MPa (100 ksi)
270 I Heat Treater's Guide: Nonferrous Alloys
Weldalite049: Aging. Aging response of Weldalite 049 with various amounts of deformation prior to aging. Approximate aging temperature, 170°C (340 OF) 100
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Weldalite 049: Plane-strain fracture toughness (Kid of extruded bar Thmperature OF
°C 21 21
21 21 21 -195 -195
70 70 70 70 70 -320 -320
'Iemper
Orientation(a)
1'3 1'3 1'3
L-T T-L T-L L-T L-T T-L T-L
T6E4 T6E4
1'3 1'3
Tensile strength MPa ksi
Kr<
designation
MPaw
ksl'llii:'
33.6 28.1 27.1 27.3 26.4 28.9 28.1
36.9 30.9 29.8 30 29 31.8 30.9
77
530 485 485 650 650 615 615
70 70 94 94 89 89
y,.1d strength MPa
ksi
405 350 350 605 605 455 455
59 51 51 88 88
66 66
(a) L-T. crack plane perpendicular to extrusion direction; T-L, crack plane parallel to extrusion direction
Weldalite 049: Mean longitudinal tensile properties of Weldalite 049 in various tempers and product forms Data for 2219-T8 provided for comparison. Uhanate
Descriptionand/or temper
Elongationin 50
Yieldstrength ksi MPa
tensilestrength ksl MPa
407 438 331 680 692
59.0 63.5 48.0 98.7 100.4
529 591 484 720 713
76.7 85.7 70.2 104.4 103.5
16.6 15.7 24.2 3.7 5.3
303 352
44.0 51.0
420 455
61.0 66.0
6.0 10.0
643 625 642 662 671 668 650
93.3 90.7 93.1 96.0 97.3 96.7 94.3
664 660 665 686 700 692 672
96.3 95.8 96.5 99.5 101.6 100.3
97.4
5.7 5.2 5.2 3.7 5.3 5.6 5.1
392 658
56.9 95.5
559 702
81.1 101.8
18.5 5.0
IDID (2 in.).
Extruded products(a)
T3 T4 Reversion T6 TS 2219-TSI Minimum Typical Rolled products(b) TS,5 mm (0.2 in.) thick(c) T6,5 mm (0.2 in.) thick(c) T6A. 5 (0.2 in.) mm thick T6B, 5 (0.2 in.) mm thick T6A, 6.35 mm (0.25 in.) thick T6B, 6.35 mm (0.25 in.) thick T6A. 9.5 mm (0.38 in.) thick Forging(d) T4. naturally aged for lOOOh Slightly underaged (l70°C, or 340 of. for 20 h)
(a) Most are 100 x 9.5 mm (4x 0.375 in.) extruded plate. (b) Rolled from 180 kg (400 lb) pilot commercial ingots. (c) For tankage. (d) Commercial hook forging
II>
Aluminum-Lithium Alloys /271 Weldalite 049: Mean tensile properties of Weldalite 049, 2090, and 2219 weldments with conventional and Weldalite filler Thlckness
Base
'Thmperature(a)
metal/filler
VPPAsquore butt weldments(b) 2219/2319 RT 22191049 RT 22191049 RT 209012319 RT 20901049 RT 049/2319 RT 0491049 RT 0491049 RT VPPAweldments of extruded plote(c) 175°C (350 oF) 0491049 0491049 RT -195°C (-320 oF) 0491049 -253 °C (-423 oF) 0491049
mm
in.
PoSlWeld temper
Weldposllion
9.5 9.5 5.8 13 6.5 9.5 9.5 9.5
0.375 0.375 0.230 0.500 0.255 0.375 0.375 0.375
As-welded As-welded As-welded As-welded As-welded As-welded As-welded Naturallyagedfor 800 h
60· borizontal 60· horizontal 60° horizontal Venical 60· horizontal Vertical 60° horizontal 60· horizontal
9.5 9.5 9.5 9.5
0.375 0.375 0.375 0.375
As-welded As-welded As-welded As-welded
Ultimate tensilestrength MPa ksi
Yieldstrength MPa ksi
Elongation, %, in 25 mm (1 in.) 50 mm (2 in.)
273 283 325 252 285 274 315 372
39.6 41.1 47.1 36.5 41.3 39.8 45.7 54.0
140 154 161 156 147 248 249 290
20.4 22.3 23.4 22.7 21.3 36.0 36.1 42.1
7.9 7.1 9.0 8.6 7.1 1.5 1.5 3.0
287 372 413 505
41.6 54.0 59.9 73.2
188 290 360 427
27.3 42.0 52.2 61.9
5.4 3.0 1.9 1.7
4.6 4.7 5.0 4.7 3.8 1.0 1.5
(a) RT,room temperature. (b) Allfractures occurredin theheat-affected zone.(e) 100 x 9.5 mm (4 x 0.375 in.)plate
Weldalite 049: Yield strength. Yield strengths of two aluminum-lithium candidate alloys for cryogenic tankage applications. Strain rate, 4 x 10-4/swith a 0.5 h hold at temperature Temperature, OF
-400
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700
~
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-100
1000 900
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-200
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200 100 -250
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2090 Chemical Composition. Registered Limits. 0.10 Si, 0.12 Fe, 2.40 to 3.00 ce, 0.05 Mn, 0.25 Mg, 0.05 Cr, 0.10 Zn, 1.90 to 2.60 Li, 0.08 to 0.15 Zr, 0.15 Ti, 0.05 others (each), 0.15 others (total), Al bal
Product Forms. The alloy is available as sheet, plate, and extrusions Applications. A high strength alloy with 8% lower density and 10% higher elastic modulus than 7075 T6. Is intended to compete where medium-strength sheet, plate, and extrusions are used in aerospace structures. A combination of weldability and cryogenic properties make it suitable for superplastic forming applications
Characteristics In general, the engineering characteristics of aluminum-lithium alloys are similar to those of the current 2.xxx and 7xxx high-strength alloys used by the aerospace industry. However, some material features vary somewhat
from those of the conventional aluminum alloys and should be considered during the design and material selection phase Two examples: • Elevated-temperature exposures of the peak-aged tempers (T86, T81, and T83) show good stability within 10% of original properties. However the underaged temper (T84) requires significant additional aging • Cold work is needed to obtain optimum properties. In this instance the alloy is similar to 2219 and 2024 Alloy 2090 and its tempers are relatively new and in different phases of registration and characterization. As a result, data for some forms may be incomplete. Current mechanical property limits (tensile and toughness) in sheet, plate, and extrusion forms are given in adjoining Table Tempers and their characteristics in various product forms are given in an adjoining Table. Behavior is similar to that of other 2.xxx and 7xxx alloys,
272/ Heat Treater's Guide: Nonferrous Alloys variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thermomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging
but the Alloy 2090 tempers exhibit higher strength than other alloys at elevated temperatures. Changes in strength and toughness at cryogenic temperatures are more pronounced in 2090 than in conventional aluminum alloys; alloy 2090 has a substantially higher toughness at cryogenic temperatures
Properties Corrosion. Alloy 2090 sheet and plate, and T86 extrusions have demonstrated excellent resistance to exfoliation corrosion in extensive seacoast exposure tests. Resistance is superior to that of 7075-T6, which, in some product forms, can suffer very severe exfoliation during a two year seacoast exposure
Solution Heat Treating. Sheet is treated at 540°C (1000 "P) to obtain
The stress-corrosion cracking (SCC) resistance of 2090 is strongly influenced by artificial aging. Tempers that are underaged, such as T84, may be more susceptible to SCC than the near-peak-aged T83, T81, and T86 tempers
the TI temper Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated water should be at room temperature, and suitably cooled so it stays below 38°C (100 OF) during quench cycle
Forming. In tests of 2090-0, -TIl, -TI, and T-83 sheet in the binding, stretch-bending, and the biaxial stretching modes, results were compared with those for 2024-TI and 7075-T6. Example: In down flange minimum bend tests, the 0, TIl, and TI tempers of Alloy 2090 and the T6 temper of 7075 outperformed 2090 in the T83 temper
Nominal temperatures listed should be reached as rapidly as possible and maintained with ±6 "C (±IO "F) of nominal during time at temperature
Machinability. Test indicate that the machinability of plate is comparable to that of B-rated aerospace alloys, 2024-TI51, 7075-T651, and 7075T651
Cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (T3)
Weldability. Gas metal are, gas tungsten arc, and electron beam welding
h to obtain T83 temper
Precipitation Heat Treating. Sheet is treated at 165°C (325 "F) for 24
have "good" ratings
Time at temperature in precipitation heat treating is approximate. Actual time depends on time required for load to reach temperature, with soak time measured from time load reaches temperature within ±6 °C (±IO "F)
Recommended Heat Treating Practice Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing
Cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (T3)
2090: Tentative mechanical property limits Typical values are given in parentheses. Data for alloy 7075-T6 are included for comparison. Thnsileproperties Ultimatetensile
streogth
Thickness
2090temper
Yletd strength
mm
In.
Specification
Dlrection(a)
MPa
ksi
MPa
ksi
Shfet 1'83
0.8-3.175
0.032-0.125
AMS4351
1'83
3.2-6.32
0.126-0.249
AMS4351
1'84
0.8-6.32
0.032-0.249
AMSOraft 089
L LT 45° L LT 45° L LT 45° LT LT L
530(550) 505 440 483 455 385 495(525) 475 427 317 min 213 max (570)
77(80) 73 64 70 66 56 72(76) 69 62 46 min 31 max (83)
517 (517) 503 440 483 455 385 455 (470) 415 345 214 min 193max (517)
75 (75) 73 64 70 66 56 66(68) 60 50 31min 28 max (75)
L L L LT
517 545 550 525
75 79 80 76
470 510 517 483
68 74 75 70
L L LT
(565) 517 (550) 517
(82) 75(80) 75
(510) 483 (517) 470
(74) 70(75) 68
TI(e) 0 7075-T6 Extrusions 1'86(g)
Plate 7075-T6 '1'81
(t) (t)
0.0-3.15(h) 0.000-0.1 24(h) AMSOraft 3.175-6.32(h) 0.125-0.249(h) 088BE 6.35-12.65(h) 0.25lUl,499(h)
13-38
0.50-1.50
AMS4346
Elongation in SO min (210.),%
Direction(b) and(K,) or
3 (6) 5
L-T(Kc)
(44)(d)
(40)(d)
L-T(Kc) T-L(Kc)
49 (71)(d) 49(d)
45 (65)(d) 45(d)
L-T(Kc)
(71)(d)
(65)(d)
L-T(XIc) L-T(KIc) L-T(KIc)
(27) ~7(7l)
(25) :m(65) ;"20
(K,,)(.)
Toughness
KlcorKc MPaViil ksrI'iiL
4 5 3(5) 5 7 6 min 11 min (11)
4 4 5
(11)
4(8) 3
~2
(a)L, longitudinal; LT,longtransverse. (b) L-T,crackplaneanddirection perpendicular to theprincipaldirectionofmetalworking (rollingorextruslon);T-L,crackplaneanddirectionparallelto thedirection of metalworking. (c)Xc,plane-stress fracturetoughness; XIc, plane-strain fracturetoughness. (d)Toughness limitsbasedon limiteddata and typical values(in parentheses) for 405 x 1120mm (16x44 in.) sheetpanel.(e)TheTI tempercanbe agedto the1'83or T84 temper. (f)No enduserspecification. (g)Temperregistration requestmadetotheAluminum Association. (h)Nominaldiameteror leastthickness (bars, rod, wire.shapes)or nominalwallthickness (tube)
Aluminum-lithium Alloys /213
2090: Quench sensitivity. Comparative quench sensitivity of 2090 and other aluminum alloys as a function of quench rates
100 ~
.<:' 80 15>
Furnace cooling Forced air cooling
c: ~
LIVE GRAPH
'til "0 a;
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';;:'
d ~
....0
Alloy and condition (Source: Ref 1) o 8090, peak aged 41 2090, peak aged A 7150, aged 24 h at 120°C .& 7475, aged 24 h at 120°C
c 0
'g
e
u..
0 0.01
0.1
10
WQ
Average cooling rate, aCts
2090: Unrecrystallized microstructures. (a) 45 mm (1.75 in.) thick 2090 plate. (b) 1.6 mm (0.063 in.) thick 2090 sheet
L--I
800
um L--'
50 IJm (0)
(b)
2090: Effectof average quench rate on tensile properties Tensile
strength(a) MPa ksi
slrength(a) MPa ksi
162 448 128 338
24 65 19 49
334 513 312 476
48 75 45 69
2 5 12 6
As-quenched 138 6%stretch+ aged8 h at 190°C 530
20 77
331 570
48 83
16 9
As-quenched 139 6%stretch+ aged8 h at 190°C 526
20 76
331 570
48 84
17 7
As-quenched 135 6%stretch+ aged8 h at 190°C 535
20 78
349 575
51 83
19 7
Averagequenchrateat center orplate
0.5 °Cls (13romplate, air cooled) 36°Cls (38romplate, quenched inroomtemperature water) 46 °Cls (13romplate, quenched inboiling water) 48 aCts(13romplate, quenchedin room temperature water) 85 °Cls (13romplate, quenchedinice brine)
2090: Tempers and corresponding products forms
Yield Condltlon
As-quenched 6%stretch+ aged8 h at 190"C As-quenched 6% stretch+ aged8 h at 190"C
(a) Dataareaverages from4 specimens
Elongatlonta), %
Temper
Characteristics
Product forms
0 1'3I(a)
Annealed, loweststrength, maximum fonnability Goodformability, willapproachT83 orT84 properties afteragingby user Moderate formability, can be agedtoT83 andT84 properties bycustomer Strengths similartothoseof7075-T6511 Strengthssimilartothoseof7075-T6 Strengths similartothoseof7075-T651 Strengthandtoughness similartothoseof7075-T76 Solutionheattreatedandaged byuser
Sheet,plate Sheet,extrusions
D(a) T86 T83(a) T8I(a) T84(a) T6(a)
(a)Registered withAluminum Association
Sheet,extrusions Extrusions Sheet Plate Sheet,plate Sheet,plate
274/ Heat Treater's Guide: Nonferrous Alloys
2091 Chemical Composition. Registered Limits. 0.20 si, 0.30 Fe, 1.80 to 2.50 Cu, 0.10 Mn, 1.10 to 1.90 Mg, 0.10 Cr, 0.25 Zn, 1.70 to 2.30 0.04 to 0.16 Zr, 0.10 Ti, 0.05 others (each), 0.15 others (total), bal Al
u,
Product Forms. Sheet and extruded bar are available Applications. Alloy 2091 was developed to be a damage-tolerant alloy with 8% lower density and 7% higher modulus than 2024-TI, a major high-toughness damage-tolerant alloy currently used for most aircraft structures. Alloy 2091 is also suitable for use in secondary structures where high strength is not critical
The microstructural relationship for stress-corrosion cracking in sheet products is the converse of that for exfoliation. As the microstructure becomes more fibrous, the SCC threshold increases. For thicker unrecrystallized structures and thinner elongated recrystallized structures, it is possible to attain an sec threshold of 240 MPa (35 ksi), which is quite good compared to that of 2024-TI
Forming. Generally, aluminum-lithium alloys have the best forming properties in the as-quenched condition. In this condition,2091 recrystallizedsheets have better formability than that of 2024
Recommended Heat Treating Practice
Characteristics A variety of tempers is being developed to offer useful combinations of strength, corrosion resistance, damage tolerance. and fabricability. Because alloy 2091 and its tempers are relatively new and in different phases of registration and characterization, data may be incomplete for some forms. In general, the behavior of 2091 is similar to that of other 2xxx and Txxx alloys. Material characteristics that have been cause for concern in other aluminum-lithium alloys are of less concern in 2091. Alloy 2091 depends less on cold work to attain its properties than does 2024. The properties of 2091 after elevated-temperature (:=;;125 °C, or 260 "F) exposure are relatively stable in that changes in properties during the lifetime of a component are acceptable for most commercial applications
Structures. The microstructure of 2091 varies according to product thickness and producer; in general, gages above 3.5 mm (0.140 in.) have an unrecrystallized microstructure, and lighter gages feature an elongated recrystallized grain structure
Corrosion. The exfoliation resistance of 2091-T84. like that of 2024, varies depending on the microstructure of the product and its quench rate. The more unrecrystallized the structure, the more even the exfoliation attack. However, the exfoliation resistance of2091 is generally comparable to that of similar gages of 2024-TI
Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys. aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number ofthermomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging
Solution Heat Treating. Sheet and extruded bar are treated to the TI temper at 530°C (990 OF) Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated, water should be at room temperature, and suitably cooled so it stays below 38°C (100 "F) during quench cycle Nominal temperatures listed should be reached as rapidly as possible and maintained with ±6 °C (±1O OF) of nominal during time at cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (T3)
Precipitation Heat Treating. Sheet is treated to the T84 temper at 120
2091: Tensile strength + yield strength. Variation in room-temperature ultimate tensile strength and yield strength for aluminum-lithium alloy 2091 after holding at 130°C (265 OF) at indicated times. Data for aluminum alloys 2024 and 7010 are included for comparison
-c (250 OF) for 24 h
Extruded bar is peak aged at 190°C (375 "F) for 12 h Time at temperature in precipitation heat treating is approximate. Actual time depends on time required for load to reach temperature, with soak time measured from time load reaches temperature within ±6 "C (±1O"F)
LIVE GRAPH Click here to view
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2091: Registered temper designations of bare and aluminum-dad sheet Temper
a TI(a) T8,T84(a) T851 T8X51
Characteristlcs
Forms
Annealed,lowest strength.maximum formability Solutionheattreatedand stretched;can be aged toT84 temper Underagedtemper;has thebest combinationof strength.toughness.and corrosionresistancefor damage-tolerant applications Medium-strengthproduct Underageddamage-tolerantproduct
Sheet.plate
Holding time, h (a)OnlyT84 is registeredwith the AluminumAssociationat thistime
Sheet,plate Sheet Plate Thick sheetand plate
Aluminum-Lithium Alloys /275 2091: Preliminary European Normale (prEN) specifications for minimum tensile properties of bare and aluminum-clad sheet and light-gage plate 0.2% yield
strength MPa ksi
Productthlclmess mm
in.
Longitudinal properties Ultimate tensile strength Elongation, MPa %(0) ksi
tensile strength Elongation, %(0) MPo ksl
strength MPo ksi
45°properties Ultimate tensile strength MPo ksi
Long-transverse proper1ies 0.2% yield Ultimate
strength MPo ksl
0.2% yield
Elongation, %(0)
Aluminum-clad products (prEN 60(3)(b) 0.79-3.45 3.45-6.0
0.031-0.136 0.136-0.236
265 334
38.5 48.5
364 418
52.8 60.7
10 8
265 290
38.5 42.1
384 418
55.7 60.7
10 10
236 34.2 256 37.1
350 364
50.7 52.8
15 15
290 359 359 354
42.1 52.1 52.1 51.4
394 448 448 438
57.1 65 65 63.5
10 8 8 7
295 325 325 320
42.8 47.1 47.1 46.4
408 359 359 423
59.2 52.1 52.1 61.4
10 10 10 8
265 285 285 275
379 398 398 394
55 57.8 57.8 57.2
15 15 15 13
Bare products (prEN 6OOS)(b) 0.81-3.3 3.3-6.0 6.0-12 12-40
0.032-0.130 0.130-0.236 0.236-0.472 0.472-1.575
38.5 41.4 41.4 40
(a) Elongation in 50 mm (2 in.). (b) prEN specifications issued by the AECMA standards organization in Europe
2091: Exfoliation from seacoast exposure and EXCO testing Thmper
Plane
EXCOtesting(o) 4-<1ay exColiation roting(h)
T8 T3 T8 T8 T8 T3 T8
T/2 T/2 T/2 T/2 T/2 TIIO T/2 T/2
EA (superficial) EB (moderate) EB (moderate) EB (moderate) EA (superficial) EA (superficial) P(pitting) EA (superficial)
Goge Product
mm
in.
Sheeted) Sheet(e) Sheet(e) Sheet(e) Sheet(e)
1.0-3.5 6.3 3.2 3.2 4.8
0.04-0.14 0.25 0.125 0.125 0.19
Sheet(g) Plate(e)
1.2 12.7
0.047 0.5
Seacoast exposure(c) Month. ExColiotion rotlng(h)
EB (moderate)(f) P(pitting) EB (moderate)
6 12 12
(a) Exfolialioncorrosion (EXCO)teslingper AS1M G 34. (b) Exfoliation rating perAS1M G 34: P, pitting; EA(superficial).tiny blisters. thin slivers. flakes. or powders with only slight separatlcn of metal; EB (moderate). notable layering and penetration into metal. (c) Seacoast exposure at Point Judith. Tl, (d) Pechiney data. (e) Sheet and plate fabricated at Davenport. JA facility. (f) Exfoliation more advanced on Point Judith panel than on EXCO panel. (g) Fokker data
2091: Aging. Natural aging of 2091 and 2024 aluminum alloy. Aging done at room temperature (22 °C, or 71 OF) except where indicated
LIVE GRAPH
2091: Tensile Properties. Longitudinal tensile properties of alloys 2091 and 2024 as a function of cold working prior to aging. Aluminum alloy 2024 is naturally aged; aluminum-lithium alloy 2091 is aged to temper TaX
LIVE GRAPH
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140 ~ 130
- - As-quenched - - - As-quenched + 2%slrelch
~ 120 ~ 110
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276/ Heat Treater's Guide: Nonferrous Alloys
2091: Resllonse of aluminum-lithium alloys 2090 and2091 to chemical milling Respo.... cbarac:leriolk
2090
Standard chemical millIng solution (NaOH + Na2S) Roughness, 11m Qiin.) 3.4-3.8 (135-150) 38-46 (1.5-1.8) Elchmte perside,lIm1min (milslrnin) TEA-modified chemical milling solutlon(a) Roughness,11M Qiio.) 2.25-2.35(89-93) Elchrateperside,lIm1min(mils/min) 43-50 (1.7-2.0)
AIIoy .... ponse 201Af/075
2091
0.9-1.0 (36-41) 40 (1.6)
1.8(70) 63.5 (2.5)
0.80-0.85(31-34) 40 (1.6)
1.65(65) 66 (2.6)
(a) Sodiumhydroxide,triethanolamine(I'EA), and sodiumsulfide
8090 Chemical Composition. Registered Limits. 0.20 Si, 0.30 Fe, 1.00 to 1.60 Cu, 0.10 Mn, 0.60 to 1.30 Mg, 0.10 Cr, 0.25 Zn, 2.20 to 2.70 u, 0.04 to 0.16 Zr, 0.10 Ti, others 0.05 (each), others 0.15 (total), bal Al Product Forms. Product forms include plate, extrusions, and forgings. Welded products also are available Applications. Aerospace applications are based on two critical requirements: damage tolerance and lowest possible density
Characteristics Alloy 8090 was developed to be a damage-tolerant medium-strength alloy with about 10% lower density and 11% higher modulus than 2024 and 2014, two commonly used aluminum alloys The chemical composition of 8090 has been registered with the Aluminum Association. And a variety of tempers have been developed that offer useful combinations of strength, corrosion resistance, damage tolerance, and fabricability, but there has been no official registration in the United States for any of these tempers or for any of the product forms. Descriptions of commonly used unofficial temper designations are given in an adjoining Table Strength and Toughness. Because alloy 8090 and its tempers and product forms are relatively new and unregistered, property data are incomplete. Available data for the current capabilities of 8090 products and tempers are given in an adjoining Table. The medium-strength products of alloy 8090 are aged to near-peak strength and show small changes in properties after elevated temperature exposure (see Table). The very underaged (damage-tolerant) products will undergo additional aging upon exposure to elevated temperatures. Changes in strength and toughness at cryogenic temperatures are more pronounced in 8090 than in conventional aluminum alloys; 8090 has a substantially higher strength and toughness at cryogenic temperatures (see Table) Microstructure. Plate, extrusions, and forgings have an unrecrystallized microstructure; damage-tolerant sheet has a recrystallized microstructure. Higher-strength sheet is available with a recrystallized or unrecrystallized microstructure (see Figure) Other considerations:
• The in-plane anisotropy of tensile properties for unrecrystallized products (plate, extrusions, forgings, and some medium-strength sheet) is higher in 8090 than in conventional alloys, placing more importance on 45° and shear properties
• Recrystallized damage-tolerant sheet and recrystallized mediumstrength sheet show much less anisotropy of tensile properties than do the unrecrystallized products Corrosion Properties. Performance is a strong function of the degree of artificial aging and the microstructure. Corrosion performance by product and temper for various types of corrosion tests is summarized in an adjoining Table
Alloy 8090 has displayed generally good exfoliation resistance in atmospheric exposure. For thick products, short-transverse SCC resistance is best in the peaked-aged temper. Thick products with unrecrystallized microstructures have good SCC resistance in the long-transverse direction, whereas those with recrystallized structures have a lower SCC threshold Forming. Bend tests indicate that 8090 has a lower material springback than that associated with conventional aluminum alloys Welding. The alloy is commercially weldable with the gas metal arc, gas tungsten arc, and electron beam processes
Recommended Heat Treating Practice Like other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thermomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging Solution Heat Treating. Alloy 8090 extruded bar is treated to the T3 temper at 540°C (1000 oF)
Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated water should be at room temperature, and suitably cooled so it stays below 38°C (100 OF) during quench cycle
Aluminum-Lithium Alloys /277 Nominal temperatures should be reached as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature
Precipitation Heat Treating. Alloy 8090 extruded bar is peak aged at 190°C (375 oF) for 12 h
Cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (f3)
Time at temperature is approximate, Actual time depends on time required for load to reach temperature, with soak time measured from time load reaches temperature within ±6 °C (±l0 OF)
8090: Tensile properties and fracture toughness MInImum and Ifill
Groin
Thmper 8090-1'81 (underaged) 8090-1'8X (peakaged)
Product form
stmeture(a)
Dlreetkm
Damage-tolerant bare sheet<3.55mm (0,140in.) thick Medium-strength sheet
R
Longitudinal Long transverse 45· Longitudinal Long transverse 45· Longitudinal Long transverse 45· Longitudinal Long transverse Short transverse 45· Longitudinal Long transverse 45· Longitudinal Long transverse 45· Longitudinal
UR
8090-78X
Medium-strength sheet
R
8090-T8771, 8090-T65I (peakaged)
Medium-strength plate
UR
8090-1'8151 (underaged)
Damage-tolerant plate
UR
8090-1'852
Die forgingswith cold work,or hand forgings Extrusions
UR
8090-1'8511, 8090-T6511
UR
345440 385-450 380-435 470-490 450-485 380-415 420-455 420-440 420-425 460-515 435 min 465typ 420 min 435-450 435 min 425 min 425-495 405-475 405-450 460-510
50-64 56-65 55-63 68-71 65-70 55-60 61-66 61-64 61-62 67-75 63 min 67typ 61 min 63-65 63 min 61.5 min 62-72 59-69 59-65 67-74
295-350 290-325 265-340 380-425 350-440 305-345 325-385 325-360 325-340 380-450 365 min 360typ 340 min 345-370 325 min 275 min 340-415 325-395 305-395 395-450
43-51 42-47 38,5-49 55-62 51-64 44-50 47-56 47-52 47-49 55-65 53 min 52typ 49 min 50-54 47 min 40 min 49-60 47-57 44-57 57-65
Fracture
Elongation InSOmm
orientotlon!!!!d
(11n, ),%
(KkorK.,)(e)
8-lOtyp 10-12 14typ 4-5 4-7 4-11 4-8 4-8 4-10 4-6 min 4 min
I.rT(KC> T-L(Kc) S-L(Kc)
94-165 85 min
86-150 77 min
I.rT(Kc)
75typ
68typ
20-35 13-30 16 type
18-32 12-27 14,5typ
35-49 30-44 25typ 30typ 20typ 15typ
32-45 27-40 23typ 27typ 18typ 14typ
1-1.5min 5 min 5 min 8 min 6-8 3-6 2-6 3-6
toughness \file
T-L(Kc) S-L(Kc) I.rT(KC> T-L(Kc) S-L(Kc) I.rT(KIc) T-L(K",) S-L(KIc) I.rT(KIc) T-L(KIc) S-L(KIc) I.rT(KIc)
T-L(KIc) S-L(KIc)
'Ibnghness voJuWf! MPa{,D ksilll.
(a) R, recrystallized; UR, unreerystallized. (b) Unlessotherwisespecifiedas onlya minimum(min)or a typical(typ)value, the two valuesgivenfor a propertyrepresentits minimumand typicalvalue.The minimumvaluesareproposedbyvariouscustomerand nationalspecifications and do notreflecta uniformregistration,(c) K c, plane-stressfracturetoughness;KIc,plane-strainfracturetoughness
8090: Cryogenic tensile and toughness properties of 8090·T3 ThnsiJe properties
Thst
temperature, K 295 76 20 4
Direction Longitudinal Transverse Longitudinal Transverse Longitudinal Transverse Longitudinal Transverse
Yield strength ksl MPa
ThnsUe strength MPa lui
217 208 248 241 272 268 280 270
326 348 458 450 609 592 605 597
31.5 30 36 35 39,5 39 41 39
Eiongalion 1n38mm
Reduetlon
(l.51n.). %
In area, %
12 14 22 20 28 25 26 24
18 26 27 37 28 27 28 29
47 50,5 66,5 65 88.3 86 88 86.5
'Ibugbness MPa{,D ~
97(a) 6O(b)
88(a) 55(b)
74(a) 5O(b)
67(a) 45(b)
(a)Toughnesswithan I.rTcrack orientation(crackplaneand growthdirectionperpendicularto therollingdirection),(b)Toughnesswitha T-Lcrackorientation(crackplaneand growthdirectionparallelto the rollingdirection)
8090: Exfoliation ratings and SCCthresholds Exfoliation rating(a) Product
Mierostruelure
EXCO lest(b)
lest(e)
Atmospherie exposure
Sheet Sheet Extrusions Plate Plate Sheet Forgings
Recrystallized Recrystallized Unrecrysta11ized Unrecrystallized Unrecrysta11ized Unrecrystallized Unrecrystallized
EA ED
EA EA
P,EA P
MASTMAASIS
Thmper 8090-1'81 (underaged) 8090-1'8 (peakaged) 8090-1'8510111 (peakaged) 8090-T877I,8090-T65I (peakaged) 8090-1'851 8090-1'8(peakaged) 8090 (peak aged)
SurfaceP EC(d) EC
EB(d) EB
SurfaceP P,EA
SCCthreshold
60% of yieldstrengthin the L-T direction 75% of yieldstrengthin the L-T direction 105-140MPa (15-W ksi)short-transverse threshold 75% of yieldstrengthin theI.rT direction 140MPa (20 ksi) short-transverse threshold
(a) Bxfoliarion ratingper ASTM G 34: P,pining; EA, superficial-tiny blisters,thinslivers,flakesor powderswith onlyslight separationofmetal;EB, moderate,notablelayeringand penetrationinmeta1; ED, very severe-penetration to a considerabledepth and loss of melal, (b) Exfoliationcorrosiontestper ASTMG 34. (c)MASTMAASIS,modifiedASTMaceticacidsalt intermittentspmy.(d)Ratingat a plane locationofTl2, whereT is a platethickness
278/ Heat Treater's Guide: Nonferrous Alloys
8090: Microstructure of 8090 sheet. (a) Recrystallized grain structure. (b) Unrecrystallized grain structure
/---1
(a)
(b)
100 11m
8090: Quench sensitivity. Quench sensitivity of alloy 8090 and other alloys as a function of average quench rates. (a) Yield strength after aging of four wrought alloys. (b) Tensile strength after aging of eight wrought alloys. (c) Relative quench sensitivity of two aluminum-lithium alloys (2090 and 8090, both solution treated for 1 hat 520°C, or 965 OF) and two Zn-Mg-Cu aluminum alloys (7150 and 7475, both solution treated for 40 min at 480°C, or 900 OF)
LIVE GRAPH
LIVE GRAPH
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Average cooling rate from 750-550 of, °F/s
Average quenching rate from 750-550 of, °F/s
10
10 2
10 3
~ 600 80 Xi ~. 500 --+::;;-"""'-.,.-----1-s 0, 400 1-----"""---'-----+---~:7'"1f='" 60 g> c ~ ~ 300 40 tl tl "0 a; "0 200 a; 100 L -_ _L - _ - - - J L - _ - - - '_ _--' 20 >= >= 2 3 4 1 10 10 10 10 Average quenching rate from 400-290 DC, °C/s
10 2 1
10 1
700
~'" 600
-SOJ c
~
tl
I-?
.,/
h
400
'iii
r
c 300 ~ 200
I
10 5 1- 100
607'0-T6~ 60 I
10 2
10 3
10 4
-
40
10 5
Average cooling rate from 400-290 DC, °C/s (b)
100
LIVE GRAPH
Click here to view a'<
-SOJ
Furnace cooling
80
c
~
tl
"0
a; ':;'
o 5 .... 0
Alloy and condition (Source: Ref 1)
a
8090, peak aged • 2090, peak aged '" 7150, aged 24 h at 120°C II. 7475, aged 24 h at 120°C
c 0
.~
e
u..
0 0,01
0.1
10 Average cooling rate, °C/s
(e)
'iii
""-S c e
OJ
tl
~
'iii
6061-T6
I 10
1
(a)
p-
r/ .>
~
10 4 1
7178-T6 7075-T6 7050-T73 ~ 80 7075-T73_ 2014-T6 2024-T4
.:
...-
500
10 3 1
wo
c ~
Aluminum-Lithium Alloys /279
8090: The effect of quench rate on the mechanical properties of age-hardened aluminum-lithium alloy 8090 Ultimate tensile
CooUngfrom
solution .trealment(a)
AIIoycomposllion AJ-2.8Li-0.86Cu-0.90Mg-0.13Zr-0.13Fe-0.06Si
Air cool (-0.25 °Cls) Polymer quench (-18 °Cls) Water quench
AJ-2.58Li-l.36Cu-0.89Mg-0.13Zr-0.17Fe-0.04Si
Air cool (-0.25 °Cls) Polymer quench (-18 °Cls) Water quench (-120 °Cls)
Stretch, %
Aging treatment
2 4 2 4 2 4 2 4 2 4 2 4
190°Cfor 16h 170°C for 24 h 190 °C for 16h 170°Cfor24h 190°Cfor 16h 170°C for 24 h 190°C forl6 h 170°C for 24 h 190°Cfor 16h 170°C for 24 h 190°Cfor16h 170°C for 24 h
Yieldstrength(b) MPa ksi
strength(b) MPa ksl
380 401 415 415 428 417 417 442 448 448 464 448
465 481 481 492 483 485 503 524 519 535 517
55 58 60 60 62 60 60 64 65 65 67 65
446
64.5 67.5 70 70 71.4 70 70.3 73 76 75 77.5 75
Elongation in SOmm
(2in.)(b),% 7.7 6.0 8.0 7.2 8.1 7.5 6.5 4.5 6.8 5.0 8.2 6.3
(a) Solution treatment of 550°C 0020 "F) for I h. (b) Data are averages from two specimens
8090: temper designations Temper(a) 1'8,1'8X T81 1'8771, T651, TIE20 1'8151,1'8ES7 T651l,1'8511110 1'8771. 1'852
Characteristics
Forms
Near-peak-aged medium-strength sheet product Underaged damage-tolerant sheet Near-peak-aged plate Underaged damage-tolerant plate Medium-to-high-strength peak-aged extrusions Medium-strenglh. peak-aged forgings
Sheet Sheet Plate Plate Extrusions Forgings
(a) Temper designations are not registered; this listing is a recap of designations used by producers and users
CP276 Chemical Composition. Nominal. 2.7 Cu, 2.2 u, 0.5 Mg, 0.12 Zr Product Form. Extruded bars
Recommended Heat Treating Practice Aluminum-Lithium Alloys. As with other age-hardened aluminum alloys, aluminum-lithium alloys achieve precipitation strengthening by thermal aging after a solution heat treatment. The precipitate structure is sensitive to a number of processing variables, including, but not limited to, the quenching rate following the solution heat treatment, the degree of cold deformation prior to aging, and the aging time and temperature. Minor alloying elements can also have a significant effect on the aging process by changing the interface energy of the precipitate, by increasing the vacancy concentration, and/or by raising the critical temperature for homogeneous precipitation. Like some other age-hardened 2xxx aluminum alloys, aluminum-lithium-base alloys also gain increased strength and toughness from deformation prior to aging. This unusual phenomenon has given rise to a number of thermomechanical processing steps for aluminum-lithium alloys aimed at optimizing mechanical properties after artificial aging
Solution Heat Treating. Extruded bar is treated to 1'3 temper at 540°C (1000 oF) Material should be quenched from solution treating temperature as rapidly as possible and with minimum delay after removal from furnace. When quenching is by total immersion in water, unless otherwise indicated water should be at room temperature, and suitably cooled so it stays below 38°C (100 OF) during quench cycle Nominal temperatures listed should be reached as rapidly as possible and maintained within ±6 °C (±1O "F) of nominal during time at temperature Cold working after solution treatment and before precipitation hardening is necessary to get specified properties in this temper (T3)
Precipitation Heat Treating. Extruded bar is treated to peak aged temperature at 190°C (375 oF) for 12 to 15 h· Time at temperature is approximate. Actual time depends on time required for load to reach temperature, with soak time measured from time load reaches temperature within ±6 °C (±1O OF)
Heat Treating Aluminum P/M Parts Commercially available aluminum powder alloy compositions consist of blends of atomized aluminum powders mixed with powders of various
alloying elements such as zinc, copper, magnesium, and silicon (see Table for compositions).
Heat Treatable Grades These grades are comparable to the 2xxx and 6xxx series wrought aluminum alloys. Alloys 201AB and MD-24 are most similar to wrought alloy 2014. They develop high strength and offer moderate corrosion resistance. Alloys 601AB and MD-69 are similar to wrought alloy 6061. These alloys have high strength, good ductility, corrosion resistance, and can be specified for anodized parts. Alloy 601AC is the same as 601AB,
but does not contain an ad-mixed lubricant. It is used for isostatic and die-wall-lubricated compaction. When high conductivity is require1 alloy 602AB often is used. Conductivity of 602AB ranges from 24 x 10 to 28 6 X 10 Slm (42.0 to 49% lACS), depending on the type of heat treatment selected.
Applications Alloys 60 lAB, 602AB, 201AB, and 202AB are designed for forgings. Alloy 202AB is especially well suited for cold forging. Forging of PIM preforms is a well established technology. A sintered compact is coated with a graphite lubricant to permit proper metal flow during forging. The part is either hot or cold forged; hot forging at 300 to 450°C (575 to 850 "F) is recommended for parts requiring critical die fill. Forging pressure usually does not exceed 345 MPa (50 ksi). Forging
normally is in a confined die so that no flash is produced and only densification and lateral flow result from the forging step. Scrap loss is less than 10% compared to conventional forging, which approaches 50%. Forged aluminum PIM parts have densities of over 99.5% of theoretical density. Strengths are higher than those of nonforged PIM parts, and in many ways, are similar to conventional forging. Fatigue endurance limit is doubled over that of nonforged PIM parts.
Heat Treating Technology All of the aluminum powder alloys respond to strain hardening and precipitation hardening, providing a wide range of properties. For example, hot forging of alloy 601AB-T4 at 425°C (800 oF) followed by heat treatment gives ultimate tensile strengths of221 to 262 MPa (32 to 38 ksi), and a yield strength of 138 MPa (20 ksi), with 6 to 16% elongation in 25 mm (1 in.), Heat treated to the T6 condition, 601AB has ultimate tensile strengths of 303 to 345 MPa (44 to 50 ksi). Yield strength is 303 to 317 MPa (44 to 46 ksi), with up to 8% elongation. Forming pressure and percentage of reduction during forging influence final properties. Ultimate tensile strengths of 358 to 400 MPa (52 to 58 ksi), and yield strengths of255 to 262 MPa (37 to 38 ksi), with 8 to 18% elongation, are possible with 201AB heat treated to the T4 condition. When heat treated to the T6 condition, the tensile strength of 201AB increases from 393 to 434 MPa (57 to 63 ksi). Yield strength for this condition is 386 to 414 MPa (56 to 60 ksi), and elongation ranges from 0.5 to 8%. Properties of cold-formed aluminum PIM alloys are increased by a combination of strain-hardened densification and improved interparticle bonding. Alloy 601AB achieves 257 MPa (37.3 ksi) tensile strength and 241 MPa (34.9 ksi) yield strength after forming to 28% upset. Properties for the T4 and T6 conditions do not change notably between 3 and 28% upset. Alloy 602AB has moderate properties with good elongation. Strain hardening (28% upset) results in 221 MPa (32 ksi) tensile and 203 MPa
(29.4 ksi) yield strength. The T6 temper parts achieve 255 MPa (37 ksi) tensile strength and 227 MPa (33 ksi) yield strength. Highest cold-formed properties are achieved by 201AB. In the as-formed condition, yield strength increases from 209 MPa (30.3 ksi) for 92.5% density, to 281 MPa (40.7 ksi) for 96.8% density. Alloy 202AB is best suited for cold forming. Treating to the T2 condition, or as-cold formed, increases the yield strength significantly. In the T8 condition, 202AB develops 280 MPa (40.6 ksi) tensile strength and 250 MPa (36.2 ksi) yield strength, with 3% elongation at the 19% upset level.
Compositions of typical aluminum P1M alloy powders Grade
Cu
Mg
ComposItion, % Si
60IAB 201AB 602AB 202AB MO-22 MO-24 MO-69 MO-76
0.25 4.4
1.0 0.5 0.6
0.6 0.8 0.4
1.0 0.5 1.0 2.5
0.3 0.9 0.6
4.0 2.0 4.4 0.25 1.6
AI
Lubricant
bal bal bal bal bal bal bal bal
1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5
Aluminum P/M Parts /281
Parts in the T2 temper have been cooled from an elevated temper shaping process, cold worked and naturally aged. In the T4 condition, parts have been solution treated and naturally aged. In the T6 condition, parts have been solution treated, quenched, and artificially aged.
Solution treating and aging procedures for MD-22, MD-24, MD-69, and MD-76 are set forth in a Table. The information includes procedures for heat treating these alloys to the T6 temper, plus the mechanical properties obtained.
Typical heat-treated properties of nitrogen-sintered aluminum P/M parts Heat-tmded
Gmdes
variablesand properties Solution treatment Temperature, °C (oF) Time. min Atmosphere Quench medium Aging Temperature. °C (oF) Tirne,h Atmosphere Heat-treated (T6) properties(a) Transverse-rupture strength. MPa (ksi) Yield strength. MPa (ksi) Tensile strength, MPa (ksi) Elongation, % Rockwell hardness, HRE Electrical conductivity, %IACS
MD-22
MD-24
MD-69
MD-76
520(970) 30 Air H2O
500(930) 60 Air H2O
520(970) 30 Air H2O
475 (890) 60
150(300) 18 Air
150(300) 18 Air
150(300) 18 Air
125 (257) 18 Air
550(80) 200(29) 260(38) 3 74 36
495(72) 195(28) 240(35) 3 72 32
435 (63) 195 (28) 205 (30) 2 71 39
435 (63) 275 (40) 310(45) 2 80 25
Air H2O
(a) T6, solution heat treated, quenched. and artificially age hardened
Typical properties of nitrogen-sintered aluminum P/M alloys Compacting
pressure Alloy 601AB
MPa
lsi
96
7
Green d.nsit~ % glcm 85
2.29
Greenstrengtb psi MPa 3.1
450
Sintereddensity glcm' % 91.1
2.45
Thmper
TI T4 T6
165
602AB
12
90
2.42
345
25
95
2.55
165
12
90
2.42
6.55 950
10.4
1500
6.55 950
93.7
2.52
96.0
2.58
93.0
2.55
345
25
95
2.55
10.4
1500
96.0
2.58
110
8
85
2.36
4.2
600
91.0
2.53
180
13
90
2.50
8.3
1200
92.9
2.58
413
30
95
2.64
13.8
2000
97.0
2.70
202AB Compacts
180
13
90
2.49
5.4
780
92.4
2.56
Cold-fonned parts (19% strain)
180
13
90
2.49
5.4
780
92.4
2.56
201AB
TI T4 T6 T1 T4 T6 T1 T4 T6 T1 T4 T6 T1 T4 T6 T1 T4 T6 T1 T4 T6 T1 T4 T6 T2 T4 T6 T8
ThosU. strengtb!a) MPa ksi 110 141 183 139 172 232 145 . 176 238 121 121 179 131 134 186 169 210 248 201 245 323 209 262 332 160 194 227 238 236 274 280
(a) Tensile properties determined using powder metal flat tension bar (MPIF standard 10-63), sintered 15min at 620 °C (1150 "F) in nitrogen
16 20.5 26.5 20.1 24.9 33.6 21 25.6 34.5 17.5 17.5 26 19 19.5 27 24.5 30.5 36 29.2 35.6 46.8 30.3 38 48.1 23.2 28.2 33 33.9 34.3 39.8 40.6
Yield strength(a) MPa ksi 48 96 176 88 114 224 94 117 230 59 62 169 62 65 172 145 179 248 170 205 322 181 214 327 75 119 147 216 148 173 250
7 14 25.5 12.7 16.6 32.5 13.7 17 33.4 8.5 9 24.5 9 9.5 25 24 26 36 24.6 29.8 46.7 26.2 31 47.5 10.9 17.2 21.3 31.4 21.5 25.1 36.2
Elongation, %
Hardness
6 5 1 5 5 2 6 6 2
55-60HRH 80-85HRH 70-75HRE 6O-65HRH 80-85HRH 75-80HRE 65-70HRH 85-9OHRH 80-85HRE 55-60HRH 65-70HRH 55-60HRE 55-60HRH 70-75HRH 65-70HRE 6O-65HRE 70-75HRE 80-85HRE 70-75HRE 75-80HRE 85-9OHRE 70-75HRE 80-85HRE 90-95HRE 55-60HRH 70-75HRH 45-50HRE 80HRE 70HRE 85HRE 87HRE
Ii 7 2 9 10 3 2 3 0 3 3.5 0.53 5 2 10 8 7.3 2.3 8 8.7 3
Copper Alloys
Heat Treating Copper Alloys Heat-treating processes for copper and copper alloys include homogenizing, annealing, stress relieving, solution treating, precipitation (age) hardening, and quench hardening and tempering.
Homogenizing In this process, prolonged high-temperature soaking is used to reduce chemical or metallurgical segregation commonly known as coring, which occurs as a natural result of solidification in some alloys. Homogenizing is
applied to copper alloys to improve the hot and cold ductility of cast billets for mill processing, and occasionally is applied to castings to meet specified hardness, ductility, or toughness requirements.
Annealing Annealing softens and increases the ductility and/or toughness of metals and alloys. It is applied to wrought products, during and after mill processing, and to castings. The process includes heating, holding, and cooling, and a proper process description should include heating rate, temperature, time at temperature, atmosphere, and cooling rate where each may affect results. Cold-worked metal is annealed by heating to a temperature that produces recrystallization and, if desirable, by heating beyond the recrystallization temperature to initiate grain growth. Temperatures commonly used for annealing cold-worked coppers and copper alloys are given in Table I. Annealing is primarily a function of metal temperature and time at temperature. Except for multiphase alloys, including certain precipitationhardening alloys and alloys susceptible to fire cracking, rates of heating
and cooling are relatively unimportant. On the other hand, the source and application of heat, furnace design, furnace atmosphere, and shape of the workpiece are important because they affect fmish, cost of annealing, and uniformity ofresults obtained. Castings. Annealing is applied to castings of some duplex alloys, such as manganese bronzes and aluminum bronzes, to correct the effects ofmold cooling. The extremely slow cooling of sand and plaster castings, or the rapid cooling of permanent mold or die castings, can produce microstructures resulting in high hardness and/or low ductility and occasionally inferior corrosion resistance. Typical annealing treatments are in the range of 580 to 700°C (1075 to 1300 OF) for I h at temperature. For aluminum bronzes, rapid cooling by water quenching or high-velocity air is advisable.
Table 1 Annealing temperatures for widely used cold-worked copper and copper alloys AnnealIngtemperature Alloy
Commonname
-c
OF
375-650 475-750 375-650 25().650 475-750 400-475 375-650 375-650 400-650 425-650 425-650 475-525
7llO-1200
425-750 775-925(a) 700-800 375-650
800-1400 1425-1700(a) 13llO-1500 700-1200
Wrought coppers C10100-C10300 CI0400-CI0700 CI0800
CllOOO ClllOO Cl1300, CI1400, CII500, C1l600 CI2000 C12200 C12500, CI2700, CI3000 C14500 C14700 C15500
Oxygen-free copper Oxygen-free silver-bearing copper Oxygen-free low-phosphorus copper Electrolytic tough-pitch copper Electrolytic tough-pitch, anneal-resistant copper Silver-bearing toughpitchcopper Phosphorus-deoxidized copper. lowresidual phosphorus Phosphorus-deoxidized copper, highresidual phosphorus Pire-refined.tough-pitch copperwithsilver Phosphorus-deoxidized, tellurium-bearing copper Sulfurcopper
9llO-14OO 7llO-1200 5llO-1200
9llO-14OO 75()'900 7llO-1200 7llO-1200 75()' I200 800-1200 8llO-1200
9llO-IOOO
Wrought copper alloys C16200 C17000, Cl7200, C17500 C19200
Cl9400
Cadmiumcopper Beryllium copper
(continued) (a)Solution-treating temperature; seeTable4 for temperatures forspecificalloys.(b) Coolrapidly(cooling methodimportantin determining resultof annealing). (c)Air cool(coolingmethodimportantin determining resultof annealing)
286/ Heat Treater's Guide: Nonferrous Alloys
Table 1 (continued> Annealing temperatnre
Alloy
Common name
C19500
cztooo C22000 C22600 C23000 C24000 C26000 C26800,czrooo, C27400 C28000 C314OO, C31600 cnceo, C33500 C33200,C34200,C35300 C34000,C35000 C35600 C36000 C36500,C36600,C36700,C36800 C37000 C37700 C38500 C41100 C41300 C42500 C443OO, C44400,C44500 C46200,C46400-C467OO C48200,C48500 C50500 C5looo,C521oo,C524OO C53200,C534OO, C54400 C60600,C60800 C61000 C613OO, C61400 C61800,C62300-C625OO C61900 C63000 C63200 C64200 C63800 C65100 C65500 C66700 C67OOO, C674OO, C67500 C68700 C68800 C70600
cnooo.cnsoo C72500 C74500,C75200 C754OO, C75700,C77000 C78200 Cast copper alloys C95300-C95800
Gildingmetal Commercial bronze Jewelrybronze Red brass Low brass Cartridgebrass Yellowbrass Muntzmetal Leadedcommercial bronzes Low-leaded brass High-leaded brass Medium-leaded brass Extra-high-leaded brass Free-cutting brass LeadedMuntzmetal Free-cutting Muntzmetal Forgingbrass Architectural bronze
Inhibitedadmiralty brasses Navalbrass Leadednavalbrass Phosphorbronze Phosphorbronze Free-cutting phosphorbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Low-silicon bronze High-silicon bronze Manganesebrass Manganesebronze Aluminumbrass Coppernickel, 10% Coppernickel, 20%,Coppernickel,30% Nickelsilver Nickelsilver Leadednickelsilver Aluminumbronzecastings
°C
OF
375-600 425-800 425-800 425-750 425-725 425-700 425-750 425-700 425-600 425-650 425-650 425-650 425-650 425-650 425-600 425-600 425-650 425-600 425-600 425-600 425-750 475-750 425-600 425-600 425-600 475-650 475-675 475-675 550-650 615-900 750-875 600-650(b) 550-800 6oo-700(c) 625-700(c) 600-700 400-600 475-675 475-700 500-700 425-600 425-600 4llO-600 600-825 650-825 675-800 600-750 600-815 500-620
750-1100 800-1450 800-1450 800-1400 800-1350 800-1300 800-1400 800-1300 800-1100 800-1200 800-1200 800-1200 800-1200 800-1200 800-1100 800-1100 800-1200 800-1100 800-1100 800-1100 800-1400 900-1400 800-1100 800-1100 800-1100 900-1200 900-1250 900-1250 1000-1200 1125-1650 1400-1600 l1oo-1200(b) 1000-1450 l100-1300(c) 1150-1300(c) 1100-1300 750-1100 900-1250 900-1300 930-1300 800-1100 800-1100 750-1100 1100-1500 1200-1500 1250-1475 1100-1400 1100-1500 930-1150
620-670
1150-1225
(a) Solution-treating temperature;seeTable4 for temperatures for specificalloys.(b) Cool rapidly(coolingmethodimportantin determining result of annealing),(c) Air cool (coolingmethodimportantin determiningresultof annealing)
Stress Relieving This process relieves internal stress in materials or parts without appreciably affecting their properties, Treatments are applied to wrought or cast copper and copper alloys. During the processing or fabrication of copper or copper alloys by cold working, strength and hardness increase as a result of plastic strain. Because plastic strain is accompanied by elastic strain, residual stresses remain in the product and can result in stress-corrosion cracking ofmaterial
in storage or service. unpredictable distortion during cutting or machining, and hot cracking during processing, brazing, or welding. In brasses that contain more than 15% Zn, stress-corrosion cracking, or "season cracking," can occur if sufficient amounts of residual tensile stress and trace amounts of atmospheric ammonia are present. Other copper alloys, such as cold-worked aluminum bronzes and silicon bronzes, may stress-corrosion crack in more severe environments.
Copper Alloys I 287
Table 2 Typical stress-relieving temperatures for wrought coppersandcopper alloys St...ss-...llen.mpemture ror Sheeland strip Rod andwire
Flat
Copperor copper alloy number Coppers Cl1000 C12000 C12200 C14200 Copper alloys C21000 C22000,C22600 C23000 C26000 C27000 C31400 C33000,C33200 C33500 C34000.C35000 C353oo.C356OO, C36000.C37700 C43000 C43400 C44300-C445OO C46200.C46400-C467OO C51000 C52100 C54400 C651OO. C65500 C68700 C69700 C70600 C71500 C73500 C74500 C75200 C75400 C75700 C77000
product.(a) °C(OF)
Electrolytic tough-pitch Phosphorus deoxidizedDLP Phosphorus deoxidizedDHP Phosphorus deoxidizedDPA
180(335)
Gilding,95% Commercial bronzeandjewelrybronze Redbrass,low brass Cartridgebrass Yellow brass,65% Leadedcommercialbronze High-andlow-leadedbrasses Low-leaded brasses Medium-leaded brasses Leaded.free-cutting, andforgingbrasses
275(525) 275 (525) 275 (525) 260(500) 260(500)
Nam.
Admiraltybrasses Navalbrasses PhosphorbronzeA PhosphorbronzeC PhosphorbronzeB-2 Siliconbronzes Aluminum brass.arsenical Coppernickel.10% Coppernickel,30% Nickelsilver.65-10 Nickelsilver.65-18 Nickelsilver.65-15 Nickelsilver,65-12 Nickelsilver.55-18
OC(OF)
Wire(c) °C(OF)
°C(°F)
180(335)
180(355)
180(355)
180(355)
275 (525) 275 (525) 275 (525) 260(500) 260(500)
260(500)
260(500)
275(525) 275(525)
275 (525) 275 (525)
275 (525)
275 (525)
420(790) 460(860) 380(715)
420(790) 460(860) 380(715)
380(715)
380(715)
340(645)
'Thbe(d)
OC (OF)
Part.
Rod(b)
'Thhe(.) °C(OF)
°C(OF)
220(430) 240(465) 260(500)
200(390) 220(430) 240(465)
330(625) 320(610) 290(555)
275(525) 260(500) 260(500)
320(610)
260(500)
320(610)
260(500)
330(625)
290(555)
480(895) 520(970)
420(790) 460(860)
Part.
300(570) 300(570) 290(555) 290(555) 300(570)
260(500) 260(500) 250(480) 250(480) 260(500)
275 (525) 275 (525) 260(500) 260(500) 275 (525)
290(555)
250(480)
260(500)
290(555) 300(570)
250(480) 260(500)
260(500) 275(525)
290(555) 300(570) 300(570) 300(570) 300(570)
250(480) 260(500) 260(500) 275(525)
260(500) 275 (525) 275 (525) 275 (525) 275 (525)
360(680)
360(680)
360(680)
400(750) 340(645)
350(660) 290(555)
380 (715) 320(610)
400(750) 350(660)
350(660) 300(570)
380 (715) 340(645)
Parts
340(645)
Note: Annealingtime is 1h with the exceptionoftube. (a)Extrahard. (b) Halfhard.(c)Spring.(d) Annealingtime for tube is 20 min.(e)Harddrawn
Stress-relief heat treatments are carried out at temperatures below those normally used for annealing. Typical temperatures for selected coppers and copper alloys are given in Table 2 (wrought products) and Table 3 (cast products).
Table 3 Typical stress-relieving temperatures for cast copperalloys Copperalloy number
°C
OF
CB1300-C82200 C82400-C82800 C83300-C84800 C95200-C95800 C96600-C978oo C99300
260 200 260 315 260 510
500 390 500 600 500 950
Thmpemture
Note:Time is 1 h per 25 mm (I in.) of sectionthicknessexceptfor copperalloy C99300;timefor it is 4 h per 25 mm (l in.)
Hardening Copper alloys that are hardened by heat treatment are of two general types; those that are softened by high-temperature quenching and hardened by lower-temperature precipitation heat treatments, and those that are hardened by quenching from high temperatures through martensitic-type reactions. Alloys that harden during low-to-intermediate-temperature treatments following solution quenching include precipitation-hardening, spinodal-hardening, and order-hardening types. Quench-hardening alloys comprise aluminum bronzes, nickel-aluminum bronzes, and a few special
copper-zinc alloys. Usually quench-hardened alloys are tempered to improve toughness and ductility and reduce hardness in a manner similar to that used for alloy steels. Low-Temperature-Hardening Alloys. For purposes of comparison, Table 4 lists examples of the various types of low-temperature-hardening alloys, as well as typical heat treatments (precipitation hardening and spinodal hardening) and attainable property levels for these alloys.
288/ Heat Treater's Guide: Nonferrous Alloys Table 4 Typicalheat treatments and resulting properties for severallow-temperature-hardening alloys Aging treatment °C
of
°C
of
Time,b
Hardneu
Eledrlcal conductivity, %IACS(b)
980 760-800 900-950 980-1000 775-800 885
1795 1400-1475 1650-1740 1795-1830 1425-1475 1625
500-550 300-350 455-490 425-500 305-325 482
930-1025 575-660 850-915 800-930 580-620 900
3 1-3 1-4 2-4 5 I
30HRB 35-44HRC 95-98HRB 68HRB 180HB 170HB
87-95 22 48 80 15 17
900-950 815-845
1650-1740 1500-1550
425-7fIJ 35Q.3fIJ
800-1400 6f1J-680
1-2 4
86HRC 32HRC
4-4
Solullon-trealing temperature(a) Alloy
Precipitation hardening C15000 C17000.CI72oo, C17300 C175OO. CI7600 CI8000(c),CI8400.CI85oo.C815oo C94700 C99400 Spinodal hardening C71900 C72800
Temperature
(a)Solutiontreatingisfollowedby waterquenching.(b) International AnnealedCopperStandard. (c) AlloyC18000(81540)mustbe doubleaged, typically3 h at 540 °C (1000 oF) followedby 3 h at 425°C (800 "P) (U.S. Patent 4.191.flJl) in orderto developthe higherlevelsofelectricalconduclivityandhardness
Order-Hardening Alloys. Certain alloys, generally those that are nearly saturated with an alloying element dissolved in the a phase, undergo an ordering reaction when highly cold worked material is annealed at a relatively low temperature. C61500, C63800, C68800, and C69000 are examples of copper alloys that exhibit this behavior. Strengthening is attributed to the short-range ordering of the dissolved atoms within the copper matrix, which greatly impedes the motion of dislocations through the crystals. The low-temperature order-annealing treatment also acts as a stressrelieving treatment, which raises yield strength by reducing stress concentrations in the lattice at the focuses of dislocation pileups.
Quench Hardening and Tempering. Quench hardening and tempering (also referred to as quench and temper hardening) are used primarily for aluminum bronze and nickel-aluminum bronze alloys, and occasionally for some cast manganese bronze alloys with zinc equivalents of37 to 41%. Aluminum bronzes with 9 to 11.5% AI, as well as nickel-aluminum bronzes with 8.5 to 11.5% AI, respond in a practical way to quench hardening by a martensitic-type reaction. Generally alloys higher in aluminum content are too susceptible to quench cracking for this treatment, and those with lower aluminum contents do not contain enough high-temperature ~ phase to respond properly.
Copper-Beryllium Alloys Because the solid solubility of beryllium in an a-copper matrix decreases as the temperature is lowered, beryllium-copper alloys are precipitation hardenable. Heat treatment typically consists of solution annealing, followed by precipitation hardening. Table 5 gives recommended schedules for the solution treating and precipitation hardening of the five major copper-beryllium alloys that are produced in wrought form. Optimum mechanical and physical properties for specific applications can be attained by varying these schedules, but the temperatures and times given in the adjoining Table constitute the most conventional practice and typically provide maximum tensile strength. In addition, better age hardening characteristics can be obtained if the material is cold worked after the solution anneal. Solution Treating. Wrought copper-beryllium alloy mill products are generally supplied solution treated or solution treated and cold worked
(Table 6). Material in these conditions can be fabricated without further heat treatment. Thus, solution treating is not typically a part of the fabricating process unless it is necessitated by a special requirement such as softening of the material for additional forming or is used as a salvage operation for parts that have been incorrectly heated for precipitation hardening. Precipitation Hardening. The cold working of solution-treated copper-beryllium alloys influences the strength attainable through subsequent aging; the greatest response to aging occurs in material in the cold-rolled hard temper. In general, work hardening offers no advantage beyond the hard temper because formability is poor and control of the precipitationhardening treatment for maximum strength is critical. For some applications, however, wire is drawn to higher levels of cold work prior to precipitation hardening. Table 7 lists the properties typically specified for mill products of the common copper-beryllium alloys.
Table 5 Solution treating and precipitation hardening of copper-beryllium alloys
Alloy
C17000 CI7200 C17300 C17500 C17510
Solution treatmenna) Thmperature 'llme(b). OF °C b 775-800 775-800 775-800 900-925 900-925
1425-1475 1425-1475 1425-1475 1650-1700 1650-1700
0.5-3 0.5-3 0.5-3 0.5-3 0.5-3
Aging treatment Temperature Time, °C
OF
b
300-330 300-330 300-330 455-480 455-480
575-625 575-625 575-625 850-900 850-900
1-3 1-3 1-3 1-3 1-3
(a) All alloysare cooled immediatelyandrapidlyfromthe solution-treating temperature. Thin sections such as stripcan be cooled in circulatingatmosphere;heaviersectionsrequirewaterquenching. (b) Shortertimesmaybe desirableto minimizegrain growth,particularlyfor thinsections
Table 6 Typical conditions of copper-beryllium mill products Tensile strengtb before aging Temper
Description
MPa
ksI
TBOO
Solutiontreated Solutiontreatedand cold workedto quarterhard Solutiontreatedandcold worked 10half hard Solutiontreatedandcold workedto hard
480 550 625 7fIJ
70 80 91 110
TOOl
TD02 TD04
Copper Alloys /289
Table 7 Properties and precipitation treatments usually specified for copper-beryllium alloys E1ongation(b). II>
Hardness(c)
Electri lACS
Standard agingtreatmeDl TIme,
initial oondiwn
Cl7200 Flatproducts Annealed Quarterhard Halfhard Hard Annealed(d) Annealed Quarterhard(d) Quarterhard Halfhard(d) Halfhard Hard(d) Hard Rod,bar,plate Annealed Hard Annealed(d) Hard(d) Wire(e) Annealed Quarterhard Ha1fhard Threequarterhard Annealed(d) Annealed Quarterhard(d) Quarterhard Halfhard(d) Half hard Three quarterhard(d) Three quarterhard C17000 Flatproducts Annealed Quarterhard Half hard Hard Annealed Annealed(d) Quarterhard Quarterhard(d) Half hard Halfhard(d) Hard Hard(d) Rod,bar Annealed Hard Annealed Annealed(d) Hard Hard(d) C17500,C17510 Rod.bar,plate.flatprod-
h
None None None None 3 0.5 2 0,33 2 0.25 2 0.25 None None 3 2 None None None None 3 0.5 2 0.25 1.5 0.25 1 0.25
None None None None 3 3 2 3 2 2 2 2 None None 3 3 2 2
Temperature
OC
315 370 315 370 315 370 315 370
315 315
315 370 315 370 315 370 315 370
315 345 315 330 315 330 315 330
315 345 315 345
of
ThosUe strength MPa ksi
Yieldstrength!a) ksi MPa
600 700 600 700 600 700 600 700
415-540 515-605 585-690 690-825 1140-1345 1105-1310 1205-1415 1170-1380 1275-1485 1240-1450 1310-1575 1275-1480
60-78 75-88 85-100 100-120 165-195 160-190 175-205 170-200 185-215 180-210 190-220 185-215
195-380 415-550 515-655 620-770 965-1205 895-1205 1035-1275 965-1275 1105-1345 1070-1345 1140-1415 1105-1415
28-55 60-80 75-95 90-112 140-175 130-175 150-185 140-185 160-195 155-195 165-205 160-205
35-60 1040 10-25 2-8 4-10 3-10 3-6 2-6 2-5 2-5 1-4 1-4
45-78HRB 68-9OHRB 88-96HRB 96-102HRB 35-40HRC 34-40HRC 37-42HRC 36-42HRC 39-44HRC 38-44HRC 4o-45HRC 39-45HRC
17-19 16-18 15-17 15-17 22-25 22-25 22-25 22-25 22-25 22-25 22-25 22-25
600 600
415-585 585-895 1140-1345 1205-1550
60-85 85-130 165-200 175-225
185-205 515-725 1000-1205 1035-1380
20-30 75-105 145-175 150-200
35-60 10-20 3-10 2-5
45-85HRB 88-103HRB 36-4IHRC 39-45HRC
17-19 15-17 22-25 22-25
600 700 600 700 600 700 600 700
450-590 620-795 760-930 895-1070 1140-1310 1105-1310 1205-1415 1170-1415 1310-1480 1275-1480 1345-1585 1310-1585
65-85 90-115 110-135 130-155 165-190 160-190 175-205 170-205 190-215 185-215 195-230 190-230
185-240 485-655 620-760 760-930 1000-1205 930-1205 1105-1310 1035-1310 1205-1380 1170-1380 1245-1415 1205-1415
20-35 70,95 90-110 110-135 145-175 135-175 160-190 150-190 175-200 170-200 180-205 175-205
35-55 10-35 4-10 2-8 3-8 3-8 2-5 2-5 1-3 1-3 1-3 1-3
600 650 600 625 600 625 600 625
415-540 515-605 585-690 690-825 1035-1240 1105-1275 1105-1310 1170-1345 1170-1380 1240-1380 1240-1450 1275-1415
60-78 75-88 85-100 100-120 150-180 160-185 160-190 170-195 170-200 180-200 180-210 185-205
170-365 310-515 450-620 550-760 895-1105 860-1140 860-1140 895-1170 895-1170 965-1240 965-1240 1070-1345
25-55 45-75 65-90 80-110 130-165 125-165 135-170 130-170 145-175 140-180 155-180 155-195
35-60 1040 10-25 2-8 4-10 4-10 3-6 3-6 2-5 2-5 2-5 2-5
47-78HRB 68-9OHRB 88-96HRB 96-102HRB 33-39HRC 34-4OHRC 34-4OHRC 36-41HRC 36-41HRC 38-42HRC 38-42HRC 39-43HRC
17-19 16-18 15-17 15-17 22-25 22-25 22-25 22-25 22-25 22-25 22-25 22-25
600 650 600 650
415-585 585-895 1035-1240 1105-1275 1140-1380 1205-1415
60-85 85-130 150-180 160-185 165-200 175-205
185-205 515-725 860-1070 930-1140 930-1140 965-1170
20-30 75-105 125-155 135-165 135-165 140-170
35-60 10-20 4-10 4-10 2-5 2-5
45-85HRB 88-103HRB 32-39HRC 34-40HRC 36-41HRC 38-42HRC
17-19 15-17 22-25 22-25 22-25 22-25
900 850 900 850
240-380 515-585 690-760 725-825 760-860 795-930
35-55 75-85 100-120 105-120 110-130 115-135
185-205 380-550 550-690 550-725 690-825 725-860
20-30 55-80 80-100 80-105 100-120 105-125
20-35 3-10 10-20 8-12 8-15 5-8
20-43HRB 78-88HRB 92-1OOHRB 93-1OOHRB 95-103HRB 97-104HRB
25-30 20-30 45-60 45-52 45-60 45-52
17-19 15-17 15-17 15-17 22-25 22-25 22-i5 22-25 22-25 22-25 22-25 22-25
ucts
Annealed Hard Annealed Annealed(d) Hard Hard(d)
None None 3 3 2 2
480 455 480 455
(a)At 0.2%offset. (h) In 50 mrn(2 in.).(c)Rockwell B and C hardnessvaluesare accurate onlyif metalis at least 1 mm (0.040in.) thick.(d) Heat treatmentthatprovidesoptimumstrength. (e)For wire diameters greaterthan 1.3mrn(0.050in.)
290 I Heat Treater's Guide: Nonferrous Alloys
Copper-Chromium Alloys After being solution treated, the material may be aged for several hours at 400 to 500 °C (750 to 930 OF) to produce special mechanical and physical properties. A typical aging cycle is 4 h or more at 455°C (850 OF). Typical effects of heat treatment and cold work on the properties of chromium-copper are shown in Table 8.
Copper-chromium alloys with 0.5 to 1.0% Cr are solution treated in molten salt or in controlled-atmosphere furnaces (to avoid scaling) at 980 to 1010 °C (1800 to 1850 OF) and rapidly quenched. Solution-treated chromium copper is soft and ductile; therefore, it can be cold worked in a manner similar to that for unalloyed copper.
Table 8 Typical effects of heat treatment and cold work on properties of Cu-l % Cr alloys
Condition
%
Hardness
Electrical conduclivlly, % lAC
15 40 45 56 62
42 15 15 18 18
50HRF 90HB(c) 65HRB 68-75HRB 75-80HRB
3542 75-82 40 80 80
40
17
105HB(c)
75-80
Ultimate leoslle strength MPa ks!
Yield strengthCa) MPa ksi
240 350 415 435 480
35 51 60 63 70
105 275 310 385 425
350
51
275
AlloyC18200 Solutiontreated Solutiontreatedand aged Solutiontreatedand drawn40% Solutiontreated,harddrawn,and aged Solutiontreated,aged,anddrawn30% AlloyC81500 Cast,solutiontreated,and aged
Eiongalion(b),
(a) AIO.5%extensionunder load. (b) In 50 nun (2 in.). (c) 500 kg load
Copper-Zirconium Alloys Temperature
The solution treatment of zirconium-copper containing 99.7% Cu (min) and 0.13 to 0.30% Zr consists of heating to 900 to 980°C (1650 to 1795 OF) and quenching in water. The material may then be precipitation hardened for 1 to 4 h at 500 to 550°C (930 to 1020 OF). If cold working is done prior to aging, the aging temperature is reduced to the range of 370 to 480°C (700 to 900 OF)for 1 to 4 h. Normally, as the solution temperature is increased from 900 to 980°C (1650 to 1795 "F), the aging temperature should also be increased to maintain high electrical conductivity. Aging treatments that produce the best combination of mechanical properties and electrical conductivity are:
Time, h
Condhlon
Solutiontreated At 900 °C (1650 OF) At 900 °C (1650 oF) and cold worked At 980°C (1795 OF) At 980 °C (1795 oF) and cold worked
3 3 3 3
930 750 1020 840
500 400 550 450
The increase in the strength of zirconium-copper depends primarily on cold working. Although aging results in some increase in strength, its chief effect is to increase electrical conductivity. The properties developed by various combinations of heat treatment and cold working are given in Table 9.
Table 9 Effect of heat treatment and cold work on properties of copper-zirconium alloy C15000 Solution_ling lempemlure(a) OF ·C 900 900 980 980 980 980 980 980 980 980 980
1650 1650 1795 1795 1795 1795 1795 1795 1795 1795 1795
Amount orcold work, % 20 80 None 20 80 None None 20 20 85 85
Aging
'Thmperature
-c
OF
475 425
885 795
500 550 400 450 400 450
930 1025 750 840 750 840
Time.h
3 3 3 3 3 3
(a) Hold 30 min. water quench. (b) In 50 nun (2 in.). (c) 0.5% extensionunderload
'Thoslle strength MPa ksi 310 425 200 270 440 205 205 330 330 495 470
45 62 29 39 64 30 30 48 48 72 68
FJectrical
Yield strength MPa ksI 260 380 41(c) 250(c) 420(c) 90 90 260 275 440 425
38 55 6(c) 36(c) 61(c) 13 13 38 40 64 62
Baroness
Eiongalion(h), %
HRB
25 12 54 26 19 51 49 31 28 24 23
48 64 37 73
50 57 79 74
conductivily, % lACS 85 min 85 min 64 64 64 87 95 80 92 85 91
Copper Alloys /291
Miscellaneous Precipitation-Hardening Alloys Other alloys that can be age hardened are the nickel-tin bronze alloys C94700 and C94800, copper-nickel-beryllium alloy C96600, and the com-
plex, special alloys C99400 and 99500. The solution-treating and precipitation-hardening treatments for these alloys are shown in Table 10.
Table 10 Typical heat-treating schedules and resulting properties for precipitation-hardening miscellaneous alloys
Alloy
C94700 C94800 C96600
C99400 C99500
Solution treatment Thmperature OF OC Time,mio
775-800
1425-1475
120
995 885 885
1825 1625 1625
60 60 60
Thmpering treatment Thmperature OF OC Time.min
305-325 305-325 510 480 480
580-620 580-620 950 900 900
300 360-1000 180 60 60
Thosilestrength MPa ksi
Yield strength(a) MPa ksl
585 415 760 545 595
415 205 485 370 425
85 60 110 79 86
Eloogation(h),
%
10 8 7
60 30 70 54 62
8
Hardness HB(c)
180 120 230 170 196
(a) At 0.2%extensionunderload for C966OO; at 0.5% extenslon underload forall other alloys. (h) In 50 nun (2 in.),(c) 3000 kg load
Spinodal-Hardening Alloys Spinodal structures are composed of a fine, homogeneous mixture of two phases that form by the growth of composition waves in a solid solution during a suitable heat treatment. The phases of the spinodal product differ in composition from each other and from the parent phase
but have the same crystal structure as the parent phase. The fineness of spinodal structures is characterized by the distance between regions of identical composition, which is of the order 50 to 100 A.
Copper-Aluminum (Aluminum Bronze) Alloys The microstructures and consequent heat treatabilities of aluminum bronzes vary with aluminum content in much the same manner as steels do with carbon contents. Unlike steels, aluminum bronzes are tempered above the normal transformation temperature, typically in the range of 565 to 675 °C (1050 to 1250 "F). In the selection of tempering temperatures, consideration must be given to both required properties and the hardness obtained upon quenching. Normal tempering time is 2 h at temperature. Moreover, heavy or complex sections should be heated slowly to avoid cracking. After
the tempering cycle has been completed, it is important that aluminum bronzes be cooled rapidly using water quenching, spray cooling, or fan cooling. Slow cooling through the range of 565 to 275°C (1050 to 530 OF) can cause the residual tempered martensitic ~ phase to decompose, forming the embrittling a-~ eutectoid. Table 11 gives typical tensile properties and hardnesses of a-~ aluminum bronzes after various stages of heat treatment.
Table 11 Typical heat treatments and resulting properties for complex (a-p> aluminum bronzes 'JYpical
Alloy
C62400 C63000 C95300 C95400
condition(a)
As-forgedor extruded Solutiontreatedat 870°C (1600 "P) andquenched.tempered2 h at 620°C (1150"P) As-forgedor extruded Solutiontreatedat 855°C (1575 "P) andquenched,tempered2 h at 650 °C (1200"F) As-cast Solutiontreatedat 855°C (1575 oF) andquenched,tempered2 h at 620 °C (1150"F) As-cast
Solutiontreatedat 870°C (1600 "P) andquenched,tempered2 h at 620°C (1150"P) C95500
As-cast
Solutiontreatedat 855°C (1575 oF) andquenched.tempered2 h at 650°C (1200"F)
Thosile strength MPa ksl
620-690 675-725 730 760 495-530 585 585-690 655-725 640-710 775-800
90-100 98-105 106 110 72-77 85 85-100 95-105 93-103 112-116
Yield sirength(b) MPa ksi
240-260 345-385 365 425 185-205 290 240-260 330-370 290-310 440-470
35-38 50-56 53 62 27-30 42 35-38 48-54 42-45 64-68
E1ongation(c)
%
Hardness HB
14-16 8-14 13 13 27-30 14-16 14-18 8-14 10-14 10-14
163-183 187-202 187 212 137-140 159-179 156-179 187-202 183-192 217-234
(a) As-cast condition is typical for moderatesectionsshaken out at temperatures above 540 °C (1000 "F) and fan cooled or mold cooled. annealedat 620°C (1150 "F), and fan (rapid)cooled. (h) AtO.5% extension underload. (c) In 50 mm (2 in.)
292/ Heat Treater's Guide: Nonferrous Alloys
Copper Casting Alloys Copper alloy castings require superior corrosion resistance, high thermal or electrical conductivity, good bearing surface qualities, or other special properties. Casting makes it possible to produce parts with shapes that cannot be easily obtained by fabrication methods such as forming or machining. Often, it is more economical to produce a part as a casting than to fabricate it by other means. Because pure copper is extremely difficult to cast and is prone to surface cracking, porosity problems, and the formation of internal cavities, small amounts of alloying elements (such as beryllium, silicon, nickel, tin, zinc, and chromium) are used to improve the casting characteristics of copper. Larger amounts of alloying elements are added for property improvement. The copper-base castings are designated in the Unified Numbering System (UNS) with numbers ranging from C80000 to C99999. Also, copper alloys in the cast form are sometimes classified according to their freezing range (that is, the temperature range between the liquidus and solidus temperatures).
Compositions of copper casting alloys (Table 12) may differ from those of their wrought counterparts for various reasons. Generally, casting permits greater latitude in the use of alloying elements because the effects of composition on hot- or cold-working properties are not important. However, imbalances among certain elements, and trace amounts of certain impurities in some alloys, will diminish castability and can result in castings of lower quality. Certain cast alloys may also be unsuitable for wrought products. For example, several alloys listed in Table 12 have lead contents of 5% or more. Alloys containing such high percentages oflead are not suited to hot working, but they are ideal for low- or medium-speed bearings, where the lead prevents galling (and excessive wear if a lubricant is not present). The tolerance for impurities is normally greater in castings than in their wrought counterparts because of the adverse effects certain impurities have on hot or cold workability. On the other hand, impurities that inhibit response to heat treatment must be avoided both in castings and in wrought products. The choice of an alloy for any casting usually depends on five factors: metal cost, castability, machinability, properties, and final cost.
Table 12 Nominal compositions of principal copper casting alloys UNS number
ASTMB22 C86300 C90500 C91100 C91300 ASTMB61 C92200 ASTMB62 C83600 ASTMB66 C93800 C94300 C94400 C94500 ASTMB67 C94100 ASTMB148 C95200 C95300 C95400 C95410 C95500 C95600 C95700 C95800 ASTMB176 C85700 C85800 C86500 C87800 C87900 C99700 C99750 ASTMBS84 C83450 C83600 C83800 C84400 C84800 C85200 C85400 C85700
Common name
PreviousASTM designation
Cu
Sn
B22-E B22-0 B22-B B22-A
62 88 84 81
10 16 19
Valvebronze
88
6
Leadedredbrass
85
5
High-lead tin bronze High-leadtin bronze Leadedphosphorbronze High-leadtinbronze
78 70 81 73
7 5 8 7
High-leadtinbronze
bal
5.5
Manganesebronze Tin bronze Tin bronze Tin bronze
Aluminumbronze Aluminumbronze Aluminumbronze Aluminumbronze Nickel-aluminum bronze Silicon-aluminum bronze Aluminumbronze Nickel-aluminum bronze Yellow brass Yellowbrass Manganesebronze Siliconbrass Siliconyellowbrass Whitemanganese bronze Whitemanganese bronze Leadedredbrass Leadedredbrass Leadedredbrass Leadedsemiredbrass Leadedsemiredbrass Leadedyellowbrass Leadedyellowbrass Leadednavalbrass
B 148-9A B 148-9B B 148-9C B 148-90 B 148-9E
Z30A ZSI44A . ZS331A
B 145-4A B 145-4B B 145-5A B 145-5B B 146-6A B 146-6B B 146-6C
88 89 85.5 84 81 91 75 81.5 61 58 58 82 65 58 58 88 85 83 81 76 72 67 61 (continued)
2.5 5 4 3 3 I I I
Pb
Composition Zn
Fe
AI
Otber
24
3
6
3Mn
2
Copper Alloys /293 Table12 (continued) UNS number
Common name
C86200 C86300 C86400 C86500 C86700 C87300 C87400 C87500 C87600 C87610 C90300 C90500 C92200 C92300 C92500 C93200 C93500 C93700 C93800 C94300 C94700 C94800 C94900 C96800 C97300 C97600 C97800
High-strength manganese bronze High-strength manganese bronze Leadedmanganesebronze Manganesebronze Leadedmanganesebronze Siliconbronze Leadedsiliconbrass Siliconbrass Siliconbronze Siliconbronze ModifiedG bronze Gbronze NavyM Leadedtin bronze Leadedtinbronze High-leadtinbronze High-leadtin bronze High-leadtin bronze High-leadtin bronze High-leadtinbronze Nickel-tinbronze Leadednickel-tin bronze Leadednickel-tinbronze Spinodalalloy Leadednickel-silver Leadednickel-silver Leadednickel-silver
PrevIous ASlM designation
Cu
B 147-8B B 147-8C B 147-7A B 147-SA B 132-B B 198-12A B 198-13A B 198-13B B 198-13C B 198-12A B 143-1B B 143-1A B 143-2A B 143-2B
63 62 58 58 58 95 82 82 91 92 88 88 88 87 87 83 85 80 78 70 88 87 80 82 56 64 66
BI44-3B BI44-3C B 144-3A B 144-30 B 144-3E B292-A B292-B
B 149-IOA B 149-11A B 149-11B
Pb
Sn
Composition Zn
Fe
A!
27 26 38 39 34
3 3 1 1 2
4 6 0.5 1 2
0.5
8 10 6 8 10 7 5 10 7 5 5 5 5 8 2 4 5
14 14 5 4 4 2 3.5 4 2 3 1
1.5 1 1 7 9 10 15 25 1 5
2 2 5
10 4 2
20 8 2
Oiber
3Mn 3Mn O.5Mn lMn 2Mn lMn,4S1 3.5S1 4S1 4S1 4S1
5NI 5NI 5NI IONI,O.2Nb 12NI 20NI 25NI
Table13 Typical properties of coppercasting alloys UNSnumber
ASTMB22 C86300 C90500 C91100 C91300 ASTMB61 C92200 ASTMB62 C83600 ASTMB66 C93800 C94300 C94400 C94500 ASTMB67 C94100 ASTMB148 C95200 C95300 C95400 C95400(Hf)(e) C95410 C95410(Hf)(e) C95500 C95500(Hf)(e) C95600 C95700 C95800 ASTMB176 C85700 C85800 C86500 C87800 C87900
Elongation, %
Hardness, HB(e)
Electricalconductivity, % lACS
18min 24 min
18 30 2 0.5
225(d) 75 135(d) 170(d)
8.0 10.9 8.5 7.0
105
15
45
64
14.3
15
100
14
32
62
15.0
110 90 110 83
16 13 16 12
83 76
12 11
20 15 18 12
58 48 55 50
11.6 9.0 10.0 10.0
20
97
14
15
44
552 517 620 758 620 793 703 848 517 655 662
80 75 90 110 90 116 102 123 75 95 96.
200 186 255 317 255 400 303 545 234 310 255
29 27 37 46 37 58 44 79 34 45 37
38 25 17 15 17 12 12 5 18 26 25
120(d) 14O(d) 170(d) 195(d) 170(d) 225(d) 200(d) 248(d) 14O(d) 180(d) 160(d)
380
55
205(t)
30(t)
15
22.0
620 400
90 58
205(t) 205(t)
30(t) 30(t)
25 15
6.5
Compressiveyieldstrength(b) MPa ksI
'Thll'lUe strength MPa ksI
Yieldstrength(a) MPa ksl
820 317 241 241
119 46 35 35
468 152 172 207
68 22 25 30
490
71
125min 165min
280
41
110
16
240
35
105
221 186 221 172
32 27 32 25
138
207 138
30 20
241
35
12.2 15.3 13.0 12.4 13.0 10.2 8.8 8.4 8.5 3.1 7.0
(continued) Note: HT indicatesalloy Inheat-treatedcondition.(a)At 0.5%extensionunderload. (b) At a permanentset of 0.025 mm (0.001 in.). (c) 500 kgf (1100Ibf)load. (d) 3000 kgf (6600Ibt) load.(e)Heat treated at 900 °C (1650 "F), waterquenched.temperedat 590 °C (1100 "F), waterquenched.(t) At 0.2% offset.(g) Solutionannealof760 °C (1400 oF) for4 h, waterquench,andthen age at315 °C (600 "P) for5 h and air cool
294/ Heat Treater's Guide: Nonferrous Alloys Table 13
Compressive yield slrength(h) MP. ksi
Yield strength(.)
UNSnumher
MP.
ksi
MP.
ks!
C99700 C99750
415
60
180
26
255 241 241 234 262 262 234 352 662 820 448 489 586 400 379 469 456 400 310 317 283 290 303 262 221 269 221 186 345 620 310 262 min 862 min 248 324 379
37 35 35 34 38 38 34 51 96 119 65 71 85 58 55 68 66 58 45 46 41 42 44 38 32 39 32 27 50 90 45 38 min 125 min 36 47 55
103 103 110 97 103 90 83 124 331 469 166 179 290 172 165 207 221 172 138 152 110 138 138 117 110 124 110 90 159 483 159 97 min 689min(1) 117 179 214
15 15 16 14 15 13 12 18 48 68 24 26 42 25 24 30 32 25 20 22 16 20 20 17· 16 18 16 13 23 70 23 14 min 100min(1) 17 26 31
Elongation, %
Hardness, HB(c)
E1ecIricaI concluclivily, % lACS
15
120(d)
3.0
34 32 28 28 37 40 37 43 20 18 20 40 20 35 30 17 20 35 30 30 45 32 30 30 20 30 20 15 35 10 35 15 min 3 min 25 22 16
62 62 60 55 59 46 53 76 180(d) 225(d) 108(d) 130(d) 155(d) 85 70 115 135(d) 85 70 75 70 72 67 60 67 58 48 85 21O(d) 80
20.0 15.1 15.3 16.8 16.4 18.6 19.6 21.8 7.4 8.0 19.3 20.5 16.7 6.1 6.7 6.1 8.0 6.1 12.4 10.9 14.3 12.3 10.0 12.4 15.0 10.1 11.6 9.0 11.5 14.8 12.0
60 85 130(d)
5.9 4.8 4.5
ASTMBS84 C83450 C83600 C83800 C84400 C84800 CS5200 CS5400 C85700 C86200 CS6300 C86400 C86500 C86700 CS7300 CS7400 C87500 C87600 C87610 C90300 C90500 C92200 C92300 C92600 C93200 C93500 C93700 C93800 C94300 C94700 C94700(H1)(g) C94800 C94900 C96800 C97300 C97600 C97800
69 97 83
10 14 12
90 62 62
13 9 9
352 489 159 166
51 71 23 24
131
19
179
26
131 90 103 103 69 83
19 13 15 15 10 12
124 83 76
18 12 11
159
23
64
Note: H'l'Indicates alloy in heat-treated condition. (a) At 0.5% extension under load. (b) At a permanent set of 0.025 rom (0.001 in.). (c) 500 kgf(1100 lbf) load. (d) 3000 kgf(6600 lbf) load, (e) Heat treated at 900 °C (1650 "F), water quenched, tempered at 590 °C (1100 "F), water quenched. (I) At 0.2% offset. (g) Solution anneal of760 °C (1400 "F) for 4h. water quench, and then age at315 °C (600 oF) for 5 h and air cool
Table 14 Composition andtypicalproperties of heat-treated coppercasting alloysof highstrength andconductivity MP.
ksi
MP.
ksl
%
Hardness
E1ecIricaI conductivity, % lACS
365 350 705 660 655 1105 1140
53 51 102 96 95 160 165
250 275 515 515 515 1035 1070
36 40 75 75 75 150 155
11 17 8 6 7 1 1
69HRB 105HB 96HRB 96HRB 96HRB 43HRC 46HRC
70 85 48 48 48 20 18
Yield strength
Thnsile strength UNSnumher
Nomlnal composition
CSI400 CS1500 CS1800 CS2000 CS2200 CS2500 CS2800
99Cu-0.8Cr-0.06Be 99Cu-1Cr 97Cu-1.5Co-IAg-0.4Be 97Cu-2.5Co-O.5Be 98Cu-1.5Ni-0.5Be 97Cu-2Be-0.5Co-O.3Si 96.6Cu-2.6Be-O.5Co-O.3Si
Elongalion,
Wrought Coppers and Copper Alloys C10100 and C10200 Commercial Names. Previous trade names. ClOl00: Oxygen-free,
Joining. Readily soldered, brazed, gas tungsten arc welded, gas metal arc
electronic copper. C10200: Oxygen-free copper; Common name. Oxygenfree copper
welded, or upset welded. Results in oxyfuel gas welding are fair. Shielded metal arc and most resistance welding methods are not recommended
Designations. ClOl: OFE. C10200: OF
Recommended Heat Treating Practice
Chemical Composition. Composition Limits (C10100). 99.99 Cu min. (specific limits in ppm for 17 other elements are named in ASTM B
Annealing. Temperature range is 375 to 650°C (710 to 1200 "F)
170, or Copper Handbook published by Copper Development Association)
Hot Working. Temperature range is 750 to 850 °C (1380 to 1560 oF)
Composition Limits (C10200). 99.95 Cu + Ag min Specifications (U.S. and/or Foreign). ASTM (C 10100). Flat products: B 48, B 133, B 152, B 187, B 272, B 432, F 68. Pipe: B 42, B 188, F 68. Rod: B 12, B 49, B 133, B 187, F 68. Shapes: B 133, B 187, F 68. tubing: B 372, B 68, B 75, B 188, B 280, F 68. Wire: B I, B 2, B 3, F 68; ASTM (CI0200). Flat products: B 48, B 133, B 187, B 272, B 370, B 432. Pipe: B 42, B 188. Rod: B 12, B 49, B 124, B 133, B 187. Tubing: B 68, B 75, B 88, B lll, B 188, B 280, B 359, B 372, B 395, B 447. Wire: B I, B 2, B 3, B 33, B 47, B 116, B 189, B 246, B 286, B 298, B 355. Shapes: B 124, B 133, B 187; Govemmentspecifications (CIOIOO). Rod: QQ-C-502; Government specifications (C10200). Flat products: QQ-C-576. Rod and shapes: QQ-C-502. Tubing: WW-T-575. Wire: QQ-C-502, QQ-W-343, MIL-W-3318
C10100, C10200: Mechanical properties. Low-temperature mechanical properties of C1 01 00 or C1 0200 bar
LIVE GRAPH Click here to view
Temperature, OF
-400 -300 -200 -100 600 n--..,,--,,--,---r---r-,---,
80 500 t--~---t-------t-------r---j--------:::J 70
Characteristics Machinability. 20% that of C36000 (free-cutting brass) Forgeability. 65% of C37700 (forging brass) Formability. Readily formed by variety of hot and cold methods. Easily stamped, bent, coined, sheared, spun, upset, swaged, forged, roll threaded, and knurled
Tensile strength, 061 temper 0.2% yield strength, 061 temper 100
20
k-=~+---t----t----t-----t-----j
10
0'--_-'--_-'-_----'-_--'-_--'
,
80 r"T1'---.-..----r--r-,-,.--,--,-,
C10100: Microstructure. OFE copper bar, electron beam welded without filler metal. Columnar grains in fusion zone (middle) and original equiaxed grains in base metal. The scattered back dots along the edge of the fusion zone are gas porosity. Etchant 1 g (Fe(NOs)s, 100 mL Hp. 35x
*c
60
'iii
40
r-.._.~ .. ..
o
OJ
c:
o
'ol1 t~Jer~
....-;::-i_7'"
. . . . . .:--: - - - - - -
""-:--j------t-----(-------t----j
<,
' -_
W
/ ' HSO temper
0'--_-'--_-'-_----'-_--'-_--'
~1~
~
:B
'"
V- '" I
125 V""""""
I
c::
HS10temper-
100
~ ~
--- 40 -200
-150 -100 -50 Ternperature.X;
o
LIVE GRAPH
LIVE GRAPH
Click here to view
Click here to view
296/ Heat Treater's Guide: Nonferrous Alloys
C10100 and C10200: Typical mechanical properties Thnsile strengtb MPa ksl
Temper Flat products, 1 mm (0.04 ln.) thick M20 05025 05050 HOO HOI H02 H04 H08 HI0 Flat products, 6 mm (0.25 in.) thick M20 05050 HOO HOI H04 Flat products, 25 mm (1 in.) thick H04 Rod, 6 mm (0.25 ln.) in diameter H80(40'1o) Rod, 25 mm (1 ln.) in diameter M20 05050 H80(35'1o) Rod, 50 mm (2 In.) in diameter H80(l6'1o) Wire,2 mm (0.08 in.) in diameter 05050 H04 H08
Elongation in SO mm
Yield strenglb(a) ksl MPa
(210.),%
HRF
160 160 150 170 170 180 195 200 200
23 23 22 25 25 26 28 29 29
90
10 25 50
150 150 170 170 195
22 22 25 25 28
20
85
45
180
26
50
10
94
80
200
29
10 10
44
55(c) 55(c) 16(d)
40 40 87
47
150 150 185
22 22 27
40
20
85
45
180
26
35(e) 1.5(f) 1.5(f)
45
165 200 230
24 29 33
11 10 32 50
45 45 25 8
45 40 77 95
160 150 180 200
23 22 26 29
10 10 10 32
50 50 50 30
45 45 45
150 150 150 180
22 22 22 26
235 235 220 250 260 240 345 380 395
34 34 32 36 38 42 50 55 57
69 76 69 195 205 250 310 345 360
10 11 10 28 30 36 45 50 53
45 45 45 30 25 14 6 4 4
45 45 40 60 70 84 90 94 95
220 220 250 260 345
32 32 36 38 50
69 69 195 205 310
10 10 28 30 45
50 50 40 35 12
40 40 60 70
310
45
275
40
380
55
345
220 220 330
32 32 48
69 69 305
310
45
275
240 380 455
35 55 66
Thhing, 25 mm (1 in.) outside diameter x 1.65 mm (0.065 ln.) wall thickness OS025 235 34 76 05050 220 32 69 H55(l5%) 275 40 220 H80(4O'1o) 380 55 345 Shapes, 13 mm (0.50 In.) in diameter M20 220 32 69 M30 220 32 69 OS050 220 32 69 H80(l5'1o) 275 40 220
10 25 40 50 60 62
35 60
Fatigue strengtb(b) MPa lui
Sbearstrength MPa ksi
Hardness HRB HR30T
25 36 50 57 63 64
45 63
35
76
11
90 90 95
13 13 14
115
17
(a) At 0.5'10 extensionunderload. (b) Al 108cycles.(c)70'10 reductionin area.(d) 55'10 reductionin area. (e) Elongationin 254mm (10 in.). (f) Elongation in 1500mm (60 in.)
C10100 and C10200: Creep properties Thst
Stress(a) forcreeprateof
temperature
Condltlon andgrainsize
°C
OF
OS025(b)
43 120 150 205 260 370 480 43 120 150 370 480 650 150 205
110 250 300 400 500 700 900 110 250 300 700
Cold drawn4O%(c)
Cold drawn84'1o(d)
10"%[h MPa ksi
11 3 0.7
1.6 0.5 0.1
10"'%[h MPa ksi
25 10 3
3.6 1.5 0.4
10"'%[h
MPa
55 33 12
ksl
8.0 4.8 1.7
(4.5)
(0.65)
55 12
8.0 1.7
10·1%[h ksi
MPa
185 150 130
27 22 19
200 165 150
29 24 22
21 9.9 330 270 235 26 8.3 3
3.1 1.45 48 39 34 3.8 1.2 0.5
(40) (23)
(5.8) (3.3)
(s95) 250 (39) (17) 6
(43) 36 (5.6) (2.4) 0.9
ksi
MPa
170 125 110
25 18 16
45 35 29 1.6
310 240 200 11
900
1200 300 400
10-"%[h
MPa
10-'%/b lui
89.6 13.0 35 5.0
(a) Parentheses indicateextrapolated values.(b)Tensilestrength. 220MPa(31.9ksi)8121 °C (70 oF). (e)Tensile strength, 352 MPa(51.1ksi)at21 °C (70 oF). (d)Thnsile strength,376 MPa(54.5ksi)8121 °C(70 oF)
Wrought Copper I 297
C10100: Microstructure. OFE copper, 10-mm (0.375-in.) diam rod, rolled to 1.3-mm (0.052 in.) strip and annealed. Crack formed at the intersection of shearing grain boundary and the surface. The specimen was tested at 550°C (1020 OF) with an extension rate of 0.03 mm/s (0.001 in.ls). Etchant 20 mL NH40H, 0-20 mL Hp mL 3% HP2' 91Ox
C10100, C10200: Tensile properties. Elevated-temperature tensile properties of C10100 or C10200 rod, 1180temper
LIVE GRAPH
LIVE GRAPH Click here to view
Temperature, of
200
500
a.
300
0.2% yield strength~
1400
1200
c
200
,
70
-
60
-
50
o
100
200
300
40
- 30
....
60
400
~
:J
Q)
0
'\.
---
500
600
20 10
o
800
100
200
Temperature,OC
C10200: Microstructure. OF copper, hot-rolled bar. Large, equiaxed, twinned grains. Etchant 20 mL NHpH, 0-20 mL H20, 8"20 mL 3% H20 2 • 100x
l.--'
»-::
In area
---
.....-
V
~ -......J
/
1400
I
Elongation
.>
o
o 700
1200
~eductlon
\
40
1000
....-
-5 .Ii
20
~;:::- -
Click here to view
800
600
400
I
-.
80
~
200
'" c tj
~
100
100
-
-
~
t!.
o
1000
"""" ~ength
.s;:.'
~
800
600
~
400
'" ::;:
400
Temperature, of
300
400
500
600
800
700
Temperature,OC
C10100 and C10200: Stress-rupture properties Stress(a)for rupture in Temperor condition
OS025(b) Cold drawn 40%(e) H80(d)
Testtempemture 'C 'F 150 200 120 150 450 650
300 380 250 300 840 1200
lOOb
lOb
MPa
33 9.7
ksi
4.8 1.4
lOOOb
ksi
MPa
ksi
MPa
161 130 272 241
23.4 18.9 39.4 35.0 2.4 0.75
147 21.3 106 15.3 (245) (35.6) (215) (31.2)
17 5.2
(a) Parentheses indicate extrapolated values. (b) Tensile strength. 238 MPa (34.5 ksi) at 21 'C (70 'F). (e) Tensile strength, 352 MPa (51.1 ksi) at 21 'C (70 'F). (d) Tensile strength, 426 MPa (61.8 ksi)at21 'C(70'F)
298/ Heat Treater's Guide: Nonferrous Alloys
C10300 Common Name. Oxygen free, extra-low phosphorus copper
Characteristics
Designation. OFXLP
Typical Uses. Busbars, electrical conductors and terminals, commutators, tubular busbars, clad product, wave guide tubing, thermostatic control tubing
Chemical Composition. Composition Limits. 99.95 Cu + Pmin, 0.001 to 0.005 P min, 0.05 others max (total)
Machinability. 20% of C36000 (free-cutting brass)
Specifications (U.S. and/or Foreign). ASTM. Flat products: B 133, B 152, B 157, B 272, B 432. Pipe: B 42, B 188, B 302. Rod: B 12, B 133, B 187. Shapes: B 133, B 187. Thbing: B 68, B 75, B 88, BIll, B 188, B 251, B 280, B 306, B 359, B 372, B 395, B 447
Other Fabrication Characteristics. Same as those of ClOlOO and C10200
Recommended Heat Treating Practice Annealing. Temperature range is 375 to 650°C (710 to 1200 "F) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 oF) C10300: Typical mechanical properties Thmper
ElongHtion in SOmm(2ln.l,%
Hardness
Thnslle strength MPH ksi
Yieldstrengthfa) MPH ksi
220 235 250 260 290 345
32 34 36 38 42 50
69 76 195 205 250 310
10 11 28 30 36 45
45 45 30 25 14 6
40
220 250 345 220
32 36 50 32
69 195 310 69
10 28 45 10
50 40 12 50
40
310
45
275
40
20
85
380 330 310
55 48 45
345 305 275
50 44 40
20 16 20
85
10 11 32 50
45 45 25 8
40
55
69 76 220 345
345
50
310
45
220 275
32
40
69 220
10 32
Shear strength HRJOT
MPH
ksi
25 36 50 57
150 160 170 170 180 195
22 23 25 25 26 28
10 50
150 170 195 150
22 25 28 22
45
180
26
94
60
87
47 45
200 185 180
29 27 26
45 77 95
35 60
150 160 180 200
22 23 26 29
10
90
50
195
28
50 30
40 35
150 180
22 26
HRF
HRB
Flal products, 1 mm (0.04 ln.) thick OS050 OS025 HOD HOl H02 H04
45 60 70
10 25
84
40
90
50
Flat products, 6 mm (0.25 ln.) thick OS050 HOD H04 M20
60 90
40
FllIt products, 25 mm (1 in.) thick H04 Rod,6 mm (0.25 ln.) in diameter H80(4O%) H80(35%) H80(l6%)
Thbing, 25 mm (1 in.) outside diameter x 1.65 mm (0.65 in.) wall thickness OS050 OS025 H80(l5%) H80(4O%)
220 235 275 380
32 34
40
45 63
Pipe,J;..SPS H80(30%) Shapes, 13 mm (0.50 in.) section size OS050 H80(15%) (0) At 0.5% extension under load
C10400,C10500,C10700 Commercial Names. Trade name. AMSIL copper; Common name. Oxygen-free, silver copper
Characteristics
Composition Limits (C10500). 99.95 Cu + Ag min, 0.034 Ag min
Typical Uses. Busbars, conductivity wire, contacts, radio parts, winding, switches, commutator segments, automotive gaskets and radiators, chemical plant equipment, printing rolls, printed circuit foil. Many applications are based on good creep strength at elevated temperatures and the high softening temperature of these alloys
Composition Limits: (C10700). 99.95 Cu + Ag min, 0.085 Ag min
Machinability. 20% that of C36000 (free-cutting brass)
Specifications (U.S. and/or Foreign). See adjoining Table for ASTM specifications
Other Fabrication Characteristics. Same as those of ClOlOO and C10200
Chemical Composition. Composition Limits (C10400). 99.95 Cu
+ Ag min, 0.027 Agmin
Wrought Copper I 299
Recommended Heat Treating Practice
C10400, C10500, C10700: Softening characteristics. Softening characteristics of oxygen-free copper containing various amounts of silver. Data are for copper wire cold worked 90% to a diameter of 2 mm (0.08 in.) and then annealed 0.5 h at various temperatures
Annealing. Temperature rangeis 475 to 750°C (890 to 1380 OF). Also see adjoining Figure Hot Working. Temperature rangeis 750 to 875°C (1380 to 1610OF)
LIVE GRAPH
Cl0400, Cl 0500, and Cl 0700: Summary of ASTM and government specifications ClOOlO
CIOSOO
CI0700
600
B 48, B 133, B 152, B 187,B272 B42,B 188 B 12,B49, B 133,B 187 B 133,B 187 B 188 B I,B2, B3
B 152, B 187, B 272
B 152, B 187. B 272
400
B 188 B 12, B49, B 133, B 187 B 187 B 188 B I,B2,B3
B 188 B 12,B49, B 133,B 187 B 187 B 188 B \,B 2,B 3
MWproduct
Click here to view
Temperature, of
300
600
900
700
70
ASTMnumbers Flat products
Pipe Rod
Shapes 1\100 Wrre Government numbers Flat products Rod Shapes
1\Ibe
Wrre
60 Silver-free
60
If. :;;
.=
40 b>
b> c:
~
.. -e
c
0.044 Ag 30
200
QQ-C-502, QQ-C-576
QQ-C-576
QQ-C-502 QQ-C-502
QQ-C-502 QQ-B-825, MIL-B-19231 QQ-B-825 QQ-W-343. MIL-W-3318
~
.". >=
>=
QQ-C-502, QQ-C-576 QQ-C-502 QQ-C-502, QQ-B-825 QQ-B-825 QQ-W-343, MIL-W-3318
Xi
.=
300
20 100
QQ-B-825 QQ-W-343, MIL-W-3318
10 0 As drawn
200
400 300 Temperature,OC
0 600
Cl0400, Cl0500, and Cl0700: Typical mechanical properties Temper
Flat products, 1 mm (0.04 ln.) thick OS025 HOO HOI H02 H04 H08 HIO M20 Flat products, 6 mm (0,25 in.) thick OS050 HOO HOI H04 M20 Flat products, 25 rom (l ln.) thick H04 Rod, 6 mm (0.25 m.) in diameter H80(4O%) Rod, 25 mm (1 in.) in diameter OS050 H80(35%) M20 Rod, 50 mm (2 in.) in diameter H80(16%) Wire,2 mm (0.08 ln.) in diameter OS050 H04 H08 Shapes, 13 rom (0.50 in.) section size OSOSO H80(15%) M20
M3a
Tensilestrength MPo ksi
Yieldstreng1h(a) MPo ksi
235 250 260 290 345 380 395 235
34 36 38 42 50 55 57 34
76 195 205 250 310 345 365 69
220 250 260 345 220
32 36 38 50 32
310
Hardu ess HRB HR30T
Elongation in SOmm (1 iIL), %
HRF
11 28 30 36 45 50 53 10
45 30 25 14 6 4 4 45
45 60 70 84 90 94 95 45
10 25 40 50 60 62
69 195 205 310 69
10 28 30 45 10
50 40 35 12 50
40 60 70 90 40
10 25 50
45
275
40
20
85
380
55
345
50
10
220 330 220
32 48 32
69 305 69
10
44
310
45
275
240 380 455
35 55 66
220 275 220 220
32 40 32 32
Thbing, 25 mm (1.0 in.) diameter x 1.65 rom (0.065 in.) wall thickness OS050 32 220 OS025 235 34 H80(l5%) 275 40 H80(50%) 380 55
Shear strenglh ksi MPo
160 170 170 180 195 200 200 160
23 25 25 26 28 29 29 23
150 170 170 195 150
22 25 25 28
45
180
26
94
60
200
29
40 87 40
47
10
55 16 55
150 185 150
22 27 22
40
20
85
45
180
26
165 200 230
24 29 33 22 26 22 22 22 23 26 29
25 36 50 57 63 64
35(b) l.5(c) 1.5(c) 69 220 69 69
10 32 10 10
50 30 50 50
40 40 40
150 180 150 150
69 76 220 345
10 11 32 50
45 45 25 8
40 45 77 95
150 160 180 200
(a) AtO.5% extension underload. (b) Elongation in 25 nun (10 in.). (c) Elongation in 1500 nun (60 in.)
35
35 60
45 62
22
300 I Heat Treater's Guide: Nonferrous Alloys
C10800 Commercial Names. Trade name. AMAX-LP copper; Common name. Oxygen-free, low phosphorus copper
Chemical Composition. Composition Limits. 99.95 Cu + Ag + P, 0.005 to 0.012 P min
Specifications (U.S. and/or Foreign). ASTM. Flat products: B 113, B 152, B 187, B 432. Pipe: B 42, B 302. Rod: B 12, B 133. Shapes: B 133. Tubing: B 68, B 75, B 88, B lll, B 188, B 251, B 280, B 306, B 357, B 360, B 372, B 395, B 447, B 543
Characteristics Typical Uses. Refrigerator and air conditioning tubing and terminals, clad products, gas and burner lines and units, oil burner tubes, condenser and heat exchanger tubes, pulp and paper lines, steam and water lines, tank gage lines, plumbing pipe and tubing, thermostatic control tubing, plate for welded continuous casting molds, tanks, kettles, and rotating bands
Fabrication Characteristics. Same as those ofC10100
Recommended Heat Treating Practice Annealing. Temperature range is 375 to 650°C (710 to 1200 oF) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "P) Cl0800: Typical mechanical properties .'!ensilestrength MPa ksi
'Iemper
Yield s1reoglh(a) MPa ksl
ElongaUon In SOmm(2 In.), %
HRF
Flat products, 1 mm (0.04 in.) thick 05025 HOO HOI H02 H04 H08
235 250 260 290 345 380
34 36 38 42 50 55
76 195 205 250 310 345
11 28 30 36 45 50
45 30 25 14 6 4
45 60 70 84 90 94
Flat products, 6 mm (0.25 in.) thick 05050 HOO H04 M20
220 250 345 220
32 36 50 32
69 195 310 69
10 28 45 10
50 40 12 50
40 60 90 40
Flat products, 25 mm (1 in.) thick H04
310
45
275
40
20
Rod, 6 mm (0.25 ln.) in diameter H80(4O%)
380
55
345
50
Rod, 25 mm (1 ln.) in diameter H80(35%)
330
48
305
Rod, 50 mm (2 in.) in diameter H80(16%)
310
45
275
Thbing, 25 mm (l in.) outside diameter x 1.65 mm (0.065 OS050 220 OS025 235 H55(l5%) 275 H80(4O%) 380
Hardness HRB HRJOT
Shear strength MPa ksi
160 170 170 180 195 200
23 25 25 26 28 29
10 50
150 170 195 150
22 25 28 22
85
45
180
26
20
94
60
200
29
44
16
87
47
185
27
40
20
85
45
180
26
150 160 180 200
22 23 26 29
195
28
10 25 40 50 60
25 36 50 57 63
Fa!lgue streogth(h) MPa ksl
76
11
90 90 97
13 13 14
115
17
ln.) wall thickness 32 34 40 55
69 76 220 345
10 11 32 50
45 45 25 8
40 45 77 95
35 60
50
310
45
10
90
50
45 63
Pipe,3/4 SPS H80(30%)
345 8
(a) Al 0.5% extension under load. (b) Al 10 cycles
C11000 (99.95Cu-0.040) Common Name. Electrolytic, tough pitch copper Designation. ETP Chemical Composition. Composition Limits. 99.90 Cu min (silver counted as copper) Silver has little or no effect on mechanical and electrical properties, but does raise recrystallization temperature and tends to produce fine grain copper Iron in commercial copper has no effect on mechanical properties, but traces can cause C11000 to be slightly ferromagnetic
Sulfur causes spewing and unsoundness; is kept below 0.003% in ordinary refining practice
Specifications (U.S. and/or Foreign). AMS. Sheet and strip: 4500. Wire: 470; ASME. Plate for locomotive fire boxes: SB11. Rod for locomotive stay bolts: SBI2; ASTM. See adjoining Table; SAE. J463; Government. Federal specifications: see adjoining Table. Military specifications: Rod: MIL-C-12166. Wire: MIL-W-3318, MIL-W-6712
Characteristics Typical Uses. C11000 is produced in all forms except pipe. Typical uses: downspouts, flashing, gutters, roofing, screening, gaskets, radiators, bus-
Wrought Copper 1301 Joining. Soldering properties are excellent; brazing and resistance butt
bars, electrical wire, stranded conductors, contacts, radio parts, switches, ball floats, butts, cotter pins. nails, rivets, soldering copper, tacks, chemical processing equipment, kettles, pans, printing rolls, rotating bands, roadbed expansion plates
welding properties are good. Gas shielded, arc welding properties are rated fair. Not recommended: oxyfuel gas, shielded metal are, resistance spot and resistance seam welding Caveat: Cll00 is subject to embrittlement when heated to 370°C (700 "F) or above in a reducing atmosphere, as in annealing, brazing, or welding. Embrittlement can be rapid if hydrogen or carbon monoxide is present in reducing atmosphere
General Corrosion Behavior. Copper often is used where resistance to corrosion is of prime importance. Sometimes it is better to use a copper alloy instead of an unalloyed copper. Tough pitch copper is considered to be immune in stress corrosion cracking in ammonia and other agents that induce such cracking of brasses. But tough pitch copper is susceptible to embrittlement in reducing atmospheres, especially those containing hydrogen
Recommended Heat Treating Practice Annealing. Temperature range is 475 to 750°C (890 to 1380 "F). Also see adjoining Figures concerning variations in tensile properties and grain size also time-temperature relationships in annealing
Machinability. 20% that ofC36000 (free-cutting brass) Forgeability. 65% that of C37700 (forging brass)
Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)
Formability. Cold working and hot forming properties are excellent
'IYpical Softening Temperature is 360°C (680 oF)
C11000: Tensile properties. Variation of tensile properties and grain size of electrolytictough pitchcopper and similarcoppers
400
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400 500 600 Annealing temperature, °C
700
800
900
3021 Heat Treater's Guide: Nonferrous Alloys
Cll000: Typical mechanical properties Tensile strength ksi MPa
Temper
Yield strength(a) ksi MPa
Elongation in SOmm (2 In.), %
HRF
45 45 30 25 14 6 4 4 45
40 45 60 70 84 90 94 95 45 40 60 70
Shear strength MPa ksi
Hardness HRB HRJOT
Fatigue strength(b) MPa ksi
Flat products,l mm (0.04 in.) thick OS050 OS025 HOO HOI H02 H04 H08 HIO M20
10 11 28 30 36 45 50 53
150 160 170 170 180 195 200 200 160
22 23 25 25 26 28 29 29 23
150 170 170 195 150
22 25 25 28 22
45
180
26
94
60
200
29
55 16 55
40 87 40
47
150 185 150
22 27 22
20
85
45
180
26
165 200 230
24 29 33
150 160 180 200
22 23 26 29
150 180 150 150
22 26 22 22
220 235 250 260 290 345 380 395 235
32 34 36 38 42 50 55 57 34
69 76 195 205 250 310 345 365 69
220 250 260 345 220
32 36 38 50 32
69 195 205 310 69
28 30 45 10
50 40 35 12 50
40
310
45
275
40
20
85
380
55
345
50
10
220 330 220
32 48 32
69 305 69
10 44 10
310
45
275
40
240 380 455
35 55
10
10 25 40 50 60 62
25 36 50 57 63 64
76
11
90
90
13 13
97
14
115(c)
17(c)
Flat products, 6 mm (0.25 in.) thick OS050 HOO HOI H04 M20
10
10
25 50
90
Flat products, 25 mm (1.0 ln.) thick H04 Rod, 6 mm (0.251n.) in diameter H80(4O%) Rod, 25 mm (1.0 in.) in diameter OS050 H80(35%) M20 Rod, 50 mm (2.0 in.) in diameter H80(l6%) Wire,2 mm (0.08 in.) in diameter OS050 H04 H08
35(d) 1.5(e) 1.5(e)
66
Thbe, 25 mm (1.0 in.) diameter x 1.65 mm (0.065 in.) wall thickness OS050 OS025 H55(l5%) H80(4O%)
220 235 275 380
32 34 40 55
69 76 220 345
10 11 32 50
45 45 25 8
40 45 77 95
220 275 220 220
32 40 32 32
69 220 69 69
10 32 10 10
50 30 50 50
40
35 60
45 63
Shapes, 13 mm (0.50 in.) in diameter OS050 H80(15%) M20 M30
35 40 40
(a) At 0.5% extension under load. (b) At 10Kcycles in a reversed bending test. (c) At3 x 10K cycles in a rotating beam test. (d) Elongation in 250 nun (lOin.). (e) Elongation in 1500 nun (60 in.)
C11000: Tensileproperties. Short-time elevated-temperature tensile properties
LIVE GRAPH
LIVE GRAPH 200
400
,f
400
--
600
800
I
I
1000
1200 80
-
300
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100
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100
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300
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600
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Temperature, OF
o o
100
200
300
400
Temperature,OC
500
600
700
Wrought Copper I 303
C11000: Tensile properties. Variation of tensile properties with amount of cold reduction by rolling
LIVE GRAPH Click here to view
400
Cll000: ASTMand federal specifications
50 300 40
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200
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40
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r. r-,
00
20 40 60 Reduction of thickness, %
80
Cll000: Typical impact strength Impact strength Product and condition
J
ft·lhC
96
71
11 43
8 32
52 35
38 26
54 45
40
52 53(a) 39(b) 26(a) 12(b)
38 39(a) 29(b) 19(a) 9(b)
Charpy V-notch Hot rolled,annealed Charpy keyhole-notch As-cast As-hotrolled Rod Annealed Commercial temper
bod Rod Annealed and drawn 30% Drawn 30% Plate As-hot rolled Annealed Cold rolled 50%
33
(a) Parallelto rollingdirection.(b)Transverseto rollingdirection
Flat products Generalrequirements forcopperand copperalloyplate,sheet,strip,androlledbar Sheet,strip,plate,androlledbar Sheet,leadcoated Sheetandstripfor buildingconstruction Stripand flatwire Foil,strip,andsheetfor printedcircuits Rod, bar, and shapes Generalrequirements for copperand copperalloyrod,bar,andshapes Rod,bar,andshapes Rod,hotrolled Rod,bar,andshapesfor forging Busbars, rods,and shapes Wire Generalrequirements forcopperand copperalloywire Harddrawn Tinned Medium-hard drawn Tinned Soft Lead alloy coated Nickel coated Rectangularand square Tinned Silvercoated Trolley Conductors Bunchstranded Concentric-lay stranded Conductors forelecironicequipment Rope-laystranded Compositeconductors (copperpluscopper-clad steel) Tubular products Bus pipeandtube Pipe Weldedcopperrube Miscellaneous Standardclassification of coppers Electrolytic Cu wirebars, cakes,slabs, billets,ingots,andingotbars Anodes Dieforgings
B248 B 152 BIOI B370 B272 B451
QQ-C-576
QQ-C-502
B249
B 133 B49 B 124 B 187
QQ-C-502,QQ-C-576 QQ-C-5Ol QQ-B-825
B250 Bl B246 B2 B246 B3 B 189 8355 B48,B272 B33 B298 B47,B 116
QQ-W-343 QQ-W-343 QQ-W-343
B 174 B 8,B226,B496 B286,B470 B 172,B 173 B229
B 188
QQ-B-825 WW-P-377
B447 B224 B5 QQ-A-673 B283
200
C11000: Stress relaxation curves. Data
150
are for H80 temper wire, 2 mm (0.08 ln.) in diameter, and represent the time-temperature combination necessary to produce a 5% reduction in tensile strength
300 LL
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304/ Heat Treater's Guide: Nonferrous Alloys
C11000: Tensile properties. Low-temperature tensile properties
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C11000: Optical properties at 21 °C (70 oF)
0.3
----
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V
-
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0.4 0.5 0.6 0.7 Wavelength, urn
0,8
0.9
C11000: Fatigue strength. Rotating-beam fatigue strength of C11000 wire, 2 mm (0.08 in.) in diameter, H80 temper
V
V o
10
30 40 50 20 Reduction in thickness, %
60
70
C11000: Microstructure. ETP copper, static cast. Excellentdefinition of dendritic structure. 5x
10' Stress cycles
10'
LIVE GRAPH Click here to view
C11000: Microstructure. ETP copper, hot-rolled rod. Transverse section shows equiaxed grains and dispersion of Cup particles.250x
Wrought Copper I 305
C11000: Thermal expansion. (a) Total thermal expansion from -190°C (-310 OF). (b) Enthalpy (heat content) above 0 °C (32 OF) Temperature, of 800 1200
400
1600
400
2000
800
Temperature, of 1200 1600
2000
2400
800
»> 600
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10 100 Duration of heating, min
C11000: Microstructure. ETP copper, cold-rolled bar, annealed approximately 1 h by holding at 375°C (710°F), then tungsten arc welded in two passes using straight-polarity direct current and copper 11000 filler metal. 2x
1200
1400
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C11000: Annealing. lime-temperature relationships
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CHOOO: Microstructure. ETP copper, 16-mm (0.625-in.) diam bar, tested at 350°C (660 OF) at an extension rate of 0.03 mm/s (0.00114 in./s). W-type void formation. Etchant 20 mL NHpH, 020 mL Hp, 3-20 mL 3% HP2' 160x
3061 Heat Treater's Guide: Nonferrous Alloys
8.96
8.94
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8.88
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C11000: Density. Variation of density with amount of cold reduction by rolling. A, vacuum annealed 12 h at 880°C (1615 OF) and cold drawn. S, vacuum annealed 12 h at 970°C (1775 OF) and flat rolled. C, vacuum annealed 12 h at 995°C (1825 OF) and cold drawn. D, hot rolled, vacuum annealed 4 hat 600°C (1110 OF), and drawn
LIVE GRAPH
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20
40
60
80
100
Amount of reduction, %
C11100 (99.95Cu-0.040-0.01 Cd) Commercial Names. Previous trade name. Electrolytic, tough pitch copper, anneal resistant; Common name. Anneal-resistant, electrolytic copper
Typical softening temperature is 355°C (670 OF)
Chemical Composition. Composition Limits. 99.90 Cu min. Limits on 0 and Cd or other elements making this copper anneal resistant are established by conductivity tests and/or stress relaxation tests, rather than by chemical analysis
Cl1100: Specifications
Specifications (U.S. and/or Foreign). ASTM. See adjoining Table; SAE. Bar, plate, sheet, strip: J461, J463; Government. See adjoining Table
Characteristics TYpical Uses. Mainly for electrical power transmission wire where resistance to softening under overload is needed Fabrication Characteristics. Same as those for CIOWO Machinability. 20% that of C36000 (free-cutting brass) Forgeability. 65% that of C37700 (forging brass) Formability. Excellent for cold working and hot forming, i.e., drawing, stamping, stranding Joining. Excellent solderability. Brazing and resistance butt welding: good. Gas-shielded, arc welding: fair. Not recommended: oxyacetylene coated, metal arc and resistance spot and seam welding
Recommended Heat Treating Practice
Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)
Product
Bar Bar,bus Pipe, bus Plate Rod Rod,bus Shapes Shapes,bus Sheet Strip Tubing.bus
Wire,coated With tin With lead alloy With nickel With silver Wlre,flat Wife, harddrawn Wire,medium-hard drawn Wife, stranded Wire, rod
Wire,trolley
Federal
QQ-C-502, QQ-C-576 QQ-B-865 QQ-B-825 QQ-C-576 QQ-B-502 QQ-B-825 QQ-C-502 QQ-B-825 QQ-C-576 QQ-C-502, QQ-C-576 QQ-B-825
ASIM
B49, B 133
B246 B334 B 159 B355 B298 QQ-C-502 QQ-W-343
Bl B2 B8,B 172,B 173,B 174, B 226, B 228, B 229, B 286 B47 B 116
Annealing. Temperature range is 475 to 750°C (890 to 1380 OF)
C11300, C11400, C11500, C11600 (99.96Cu + Ag - 0.40) Commercial Names. Previous trade name. Tough pitch copper with silver; Common name. Silver-bearing, tough pitch copper Designation. STP
Chemical Composition. Composition Limits. Copper limits: 99.00 to 99.90 Cu; Oxygen limit: 0.04% 0 max; Silver limits: Cl1300, 0.027 Ag max; C11400, 0.034 Ag max; CU500, 0.054 Ag max; Cl1600; 0.085 Ag max. These coppers may be low resistance lake coppers or electrolytic copper to which Ag has been intentionally added
Wrought Copper I 307 Specifications (U.S. and/or Foreign). AMS. Soft wire (all alloys)
Cl1300, Cl1400, Cl1500, and Cl1600: Specifications
and trolley wire (C113OOonly):4701; ASME. Strip (C11300only): SB152; ASTM. See adjoining Table; SAE. Bar, sheet, strip (C11300, C 11400, and C11600) and plate (C113OO and C11400): J463; Federal. See adjoining Table; Military. Soft wire (all alloys) and trolley wire (11300 only): MILW-3381. Commutator bar (11600 only): MIL-B-19231
Product
Annealing. Temperature range is 475 to 750°C (890 to 1380 "F)
Bar Bar.bus Pipe.bus Plate Rod Rod.bus Shapes Shapes,bus Sheet Sheet,c1ad Strip Strip,c1ad Tube.bus Wrre, coaled with Tin Lead alloy Nickel Silver Wrre.f1at Wire, hard drawn Wire, medium-hard drawn Wrre,rod Wrre,soft Wrre, stranded
Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 OF)
Wrre,trolley
Characteristics Typical Uses. All product forms except pipe and tubing. Examples: gaskets, radiators, busbars, conductivity wire, contacts, radio parts, windings. switches, terminals, commuter segments, chemical processing equipment, printing rolls, clad metals, printed circuit foil
Machinability. 20% that of C36000 (free-cutting brass) Forgeability. 65% that of C37700 (forging brass) Formability. Cold working and hot forming rated excellent Joining. Soldering: excellent. Brazing and resistance butt welding: good. Gas-shielded, arc welding: fair. Not recommended: oxyacetylene coated metal arc and resistance spot and seam welding
Recommended Heat Treating Practice
ASTM
Federal
B 152(a) B 181(a) B 188(a) B 152(a) B49(e) B 181(a)
QQ-C-516(a), QQ-C-502(b) QQ-B-825(a) QQ-B-825(a) QQ-B-825(a) QQ-C-502(0 QQ-B-825(0 QQ-C-502(0 QQ-B-825(0 QQ-C-516(0 QQ-C-502(e) QQ-C-502(b), QQ-C-516(0
B 181(a) B 152(a) B506(a) B 152(a), B 272(e) B 506(a) B 188(a)
QQ-B-825(t)
B 246, B 334(e) B 189(e) B355(e) B298(e) B 272(e) B l(e) B2(e) B49(e) B 3(a), B 48(e) B 8, B 112, B 113, B 1143, B 226, B 228, B 229, B 286(e) B41,B 116(e)
QQ-C-502(a) QQ-W-343(e) QQ-W-343(e) QQ-W-343(e)
QQ-W-343(g)
(a) CI1300, Cl1400, and C11600. (b) C11600 only. (c) Cl1400 only. (d) Cl1400 and CI1600. (e) C11300, CII400, C11500, and CI1600. (0 C11300 only
C11300, C11400, Cl1500, and Cl1600: Typical mechanical properties 'Thnslle strength 'Thmper
Elongation In SOmm!21n.),%
HRF
11 28 30 36 45 50 53 10
45 30 25 14 6 4 4 45
45 60 10 84 90 94 95 45
69 195 205 310 69
10 28 30 45 10
50 40 35 12 50
40 60 10 90 40
45
215
40
20
380
55
345
50
220 330 220
32 48 32
69 305 69
310
45
215
240 380 455
35 55 66
220 215 220 220
32 40 32 32
MPa
ksi
Yieldstrength!a) MPa ksi
235 250 260· 290 345 380 395 235
34 36 38 42 50 55 51 34
15 195 205 250 310 345 365 69
220 250 260 345 220
32 36 38 50 32
310
Hardness HRB
HR30T
Shear strength ksl MPa
Flat products, 1 mm (0.04 in.) thick 08025 HOO HOI H02 H04 H08 HIO M20
160 110 110 180 195 200 200 160
29 29 23
10 25 50
150 110 110 195 150
22 25 25 28 22
85
45
180
26
10
94
60
200
29
10 44 10
55 16 55
40 81 40
41
150 185 150
22 21 22
40
20
85
45
180
26
165 200 230
24 29 33
150 180 150 150
22 26 22 22
10 25 40 50 60 62
25 36 50 51 63
64
23 25 25 26
28
Flat products, 6 mm (0.25 In.) thick 08050 HOO HOI H04 M20 Flat products, 25 mm (l in.) thick H04 Rod,6 mm (0.25 In.) in diameter H80(4O%) Rod, 25 mm (1.0 in.) diameter 08050 H80(35%) M20 Rod, 51 mm (2.0 la.) diameter H8O(16%) Wire. 2 mm (0.08 ln.) diameter OS050 H04 H08
35(b) 1.5(e) 1.5(e)
Shapes,13 mm (0.50 in.) diameter 08050 H80(15%) M20 M30
69 220 69 69
10 32 10 10
(a) At 0.5% extension under load. (b) Elongation in 250 mm (10 in.), (c) Elongation in 1500 mm (60 in.)
50 30 50 50
40 35
40 40
3081 Heat Treater's Guide: Nonferrous Alloys
12800,C12900,C13000
C12500, C12700,
Commercial Names. Previous trade name. Fire-refined, tough-pitch copper (12500); fire-refined, tough-pitch copper with silver (C12700, C12800, C12900, CI3000); Common name. Fire-refined copper Designation. C12500; FRTP. Others: FRTSP Chemical Composition. Composition Limits. (per ASTM B 216): 99.88 Cu + Ag min (may be specified by agreement), 0.012 As max, 0.003 Sb max, 0.025 + Te max, 0.05 Ni max, 0.003 Bi max, 0.004 Pb max
(700 "F) or above. If hydrogen or carbon monoxide is present, embrittlement can be rapid
Recommended Heat Treating Practice Annealing. Temperature range is 400 to 650°C (750 to 1200 "F) Hot Working. Temperature range is 750 to 950 °C (1380 to 1740 "F)
Note: Bi and Pb can cause hot workability problems if composition limits are exceeded. Se and Te greatly affect recrystallization and grain growth Specifications (U.S. and/or Foreign). ASTM. Flat products: B 11, B 124, B 133, B 152, B 272. Rod: B 12, B 124, B 133. Shapes: B 124, B 133, B 216. Lake copper wirebar, coke, slab, billet, and ingot: B 4; Government. MlL-W-3318
C12500: Microstructure. FRTP copper, hot-rolled strip 12.7 mm (0.5 in.) thick. Structure consists of twinned grains of copper, with stringers of Cup particles resulting from segregation of the oxide in the ingot during casting. 200x
Characteristics Typical Uses. Architectural: building fronts, downspouts, flashing, gutters, roofing, screen, spouting. Automotive: gaskets, radiators. Electrical: busbars, contacts, radio parts, commutator segments, switches, terminals. Miscellaneous: anodes, chemical process equipment, kettles, and pans Machinability. 20% that of C36000 (free-cutting brass) Formability. Hot or cold forming excellent, but should not be heated for forming or annealing in a reducing atmosphere Joining. Riveting: use copper rivets. Pressure welding: use roll weld proprietary method. Soldering: soft solder with all grades of solder, commercial solder fluxes, or rosin. Silver braze with all types of flame, using copper-phosphorus, silver, or copper-zinc (see ASTM B 260). Satisfactory fluxes are commercially available. Use gas shielded arc welding processes with recommended filler metals, depending on application. Generally other welding methods are not recommended. Caveat: this copper is subject to embrittlement when heated in a reducing atmosphere, as in annealing, brazing, or welding at temperatures of 370°C
C12500, C12700, C12800, C12900, and C13000: Typical mechanical properties
Thmper
Thnsile strength ksi MPa
Yieldstrength At0.5% extension underload At 0.2% offset MPa MPa ksi ksi
ElongationIn 50 mm (2IlL), %
HRF
45 30 14 6 4 4 45
45 60 84 90 94 95 45
55 16 55
40 87 40
Hardness
Shear strength
HRB
HR30T
10 40
25 50 57 63
MPa
ks1
160 170 180 195 200 200 160
23 25 26 28 29 29 23
ISO ISO
22 27 22
165 200 230
24 29 33
150 180
22 26 22 22
Flat products,l mm (0.04 ln.) thick OS025 HOO H02 H04 H08 HIO M20
11
235 250 290 345 380 395 235
34 36 42 50 55 57 34
76 195 250 310 345 365 69
28 36 45 50 53 10
220 330 220
32 48 32
69 305 69
10 44 10
240 380 455
35 55 66
220 275 220 220
32 40 32 32
235 270 327 360 370
34 39 47.5 52 54
50 60 62
64
Rod, 25 mill (1 in.) in diameter OS050 H80(35'7o) M20
47
185
Wire, 2 mm (0.08 in.) in diameter OS050 H04 H08
35(a) l.5(b) 1.5(b)
Shapes, 13 mm (0.50 ln.) In diameter OS050 H80 (I 5'70) M20 M30
(a) Elongation in 250 mm (10 in.). (b) Elongation in 1500mm (60 in.)
69 220 69 69
10 32 10 10
50 30 50 50
40 35
40 40
ISO ISO
Wrought Copper 1309
C14300, C1431 0 (99.90Cu-O.1 Cd; 99.8Cu-O.2Cd) Commercial Names. Previous trade names. C14300: Cadmium-copper, deoxidized
Chemical Composition. Composition Limits. Copper: 99.80 to 99.90
Recommended Heat Treating Practice Annealing. Temperature range is 535 to 750°C (995 to 1380 "P)
Cu; Cadmium: C14300, 0.05 to 0.15 Cd. C1431O, 0.1 to 0.3 Cd
Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)
Characteristics
C14300and C14310: Typical mechanical properties
Machinability. 20% that of C36000 (free-cutting brass) Thnsile strength
Yield strength
FlongaIIonIn
at 0.2 '.Iiolrlet
SO mm.(2 in.),
Forgeability. 65% that of C37700 (forging brass)
'Thmper
MPo
ksi
MPo
ksl
'.Ii
Formability. Cold working and hot forming: excellent
05025 H04 H08 HI0
220 310 350 400
32 45 51 58
75 275 330 385
11 40 48 56
42 14 7 3
Joining. Soldering, brazing, and gas-shielded, metal arc welding: excellent. Oxyacetylene welding and resistance butt welding: good. Not recommended: coated metal arc and resistance, seam and spot welding
Note:Values forstrip,0.3 to 1mm(0.01to0.04 in.) diameter
C14500 (99.5Cu-O.Te) Commercial Names. Previous trade name. Phosphorus deoxidized, tellurium-bearing copper; Common name. Free-machining copper Designation. DPTE Chemical Composition. Composition Limits. 99.90 Cu + Ag + Te min; 0.004 to 0.012 P, 0.40 to 0.60 Te
Specifications (U.S. and/or Foreign). ASTM. Flat products and rod: B 124, B 301. Shapes: B 124, B 283
Characteristics Typical Uses. Forgings and screw machine products requiring high conductivity, extensive machining, corrosion resistance, and copper color, or combinations thereof. Typical parts: electrical connectors, motor parts, switch parts, plumbing fixtures, soldering tips, welding torch tips, transistor bases, and parts assembled by furnace brazing
Machinability. 85% that of C36000 (free-cutting brass). Carbide-tipped tools should be used
Formability. Cold working (usually drawing, rolling or swaging): good. Hot forming (generally extrusion, forging, or rolling): excellent Joining. Soldering and brazing: excellent. Not recommended: arc welding, oxyfuel gas welding, and most resistance processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 650°C (795 to 1200 "F) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 oF) C14500: Typical mechanical properties of rod 'Thnsile strength 'Thmper
MPa
ksi
6 mm (0.25ln.) diameter H02 295 43 H04 365 53 13 mm (0.50in.) diameter 05015 230 33 H02 295 43 H04 330 48 25 mm (1 in.) diameter 05050 220 32 H02 290 42 H04 330 48 SO mm (2 ln.) diameter H02 290 42
Yield strength(a) Eiongalion In MPa ksl SO mm(2in.), '.Ii
275 340
40 49
76 275 305
Hardness, HRB
Shear strength MPo ksi
18 10
43 54
180 200
26 29
11
46
40
W 15
43HRF 43 48
150 180 185
22 26 27
40HRF 42 48
150 170 185
22 25 27
42
170
25
44
69 275 305
10 40 44
50 25 20
270
39
35
(a)Al 0.5%extensionunderload
C14700 (99.6Cu-O.45) Commercial Names. Previous trade name. Sulfur bearing copper; Common name. Free-machining copper, sulfur copper Chemical Composition. Composition Limits. 0.20 to 0.50 S, 0.10 others max (total), bal Cu + Ag
Specifications (U.S. and/or Foreign). ASTM. Flat products and rod: B 301
310 I Heat Treater's Guide: Nonferrous Alloys
Characteristics
Machinability. 85% of C36000 (free-cutting brass)
Typical Uses. Screw machine products and parts requiring high conductivity, extensive machining, resistance to corrosion, or a combination thereof. Other applications include electrical connectors; motors, and switching components, plumbing fittings, furnace brazed components, soldering coppers, rivets, and welding torch tips
Recommended Heat Treating Practice
C14700: Microstructure. Sulfur-bearing copper rod, cold worked to 50% reduction. Transverse section shows dispersion of round particles of CuS, which improves machinability. 200x
Annealing. Temperature range is 425 to 650°C (795 to 1200 "F) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)
C14700: Typical mechanical properties of rod Temper
Tensilestrength ksl MPa
Yieldstrength(a) MPa ksi
Elongation in
Hardness,
50mID (2 ln.), %
HRB
Shear strength MPa ksi
6 mm (0.25 in.) diameter H02 H04
43 53
295 365
275 340
40 49
18 10
43 54
180 200
26 29
76 275 305
11 40 44
46 20 15
43HRF 43 48
150 180 185
22 26 27
69 275 305
10
40 44
50 25 20
40HRF 42 48
150 170 185
22 25 27
270
39
35
42
170
25
13 mm (0.50 in.) diameter OS015 H02 H04
230 295 330
33 43 48
25 mm (1 in.) diameter OS050 H02 H04
32 42 48
220 290 330
50 mm (2 ln.) diameter H02
42
290
(a) At 0.5% extension under load
C15000 (991185Cu..OIl15Zr) Commercial Names. Trade name. Amzire Brand copper; N-4 alloy; Common name. Zirconium copper Chemical Composition. Composition Limits. 99.5 Cu + Ag + Zr min, 0.13 to 0.20 Zr
Recommended Heat Treating Practice Solution Heat Treating. Solution treat 5 to 30 min at temperature (900 to 925°C, or 1650 to 1695 OF); then age 1 to 4 h. Aging time and temperature are based on section size and amount of previous cold work Annealing. Temperature range is 600 to 700°C (1110 to 1290 OF)
Characteristics Zirconium copper is best treatable and retains much of its room temperature strength up to 450°C (840 OF)
Aging. Aged only, temperature range is 500 to 550 °C (930 to 1020 OF); cold worked and aged, 375 to 475°C (710 to 890 OF) Hot Working. Temperature range is 900 to 950 °C (1650 to 1740 "F)
Typical Uses. Steel bases for power transmitters and rectifiers, switches and circuit breakers for high temperature service, commutators, resistance welding tips and wheels, solderless wrapped connectors Machinability. 20% that of C36000 (free-cutting brass)
C15000: Stress-rupture properties. Stress-rupture properties, TH08 temper. Material was solution treated 1 hat 950°C (1740 OF), quenched, cold worked 85%, and aged 1 hat 425°C (795 OF) 400
Formability. Cold working and hot forming: excellent. Generally fabricated by swaging, bending, heading, or forging. Caveat: forging should be discontinued if temperature falls below 800°C (1400 OF). Part must be reheated to at least 900 °C (1650 OF) before forging can be resumed Joining. Soldering: excellent. Brazing or resistance butt welding: good. Not recommended: other welding processes
LIVE GRAPH Click here to view
55 350
50
iii 300
45
If
:;;
e
Ii)
40
250
35 30 1000 Rupture time. h
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Next Page Wrought Copper /311 C15000: Typical low-temperature mechanical properties 'IOst.emperature
°C 22 -78 -197 -253 -269
'IOnsile stnmgtb
OF 72
-108 -323 -423 -452
No/cbed tensile strengtb(a) MPa ksi
MPa
ksi
445 463 534 587 591
64.5 67.2 77.4 85.2 85.7
Yield strengtblbl MPa ksl
97.6 103.1 1I2.4 119.0 121.6
673 711 775 820 838
411 423 453 458 446
59.6 61.3 65.7 66.4 64.7
Eiongallon(c),
Reduclion
%
inares, %
16
62 66 71
20
26 37 36
Impact strengtb(d) J ft·lbr
121 142 155 155
72
89 105 114 114
69
Note: Dataare forTH04 tempermaterialssolutiontreatedat 950 °C(174OOF), cold worked85 to 90%, and aged I h at 450 °C (840 "F), (a) For K, of5.0. (b) At 0.2% offset.(c) In 2 diameters. (d) Charpy Vnotch, standard10mm (0.39in.)squarespecimen
500
e 400
Test temperature, OF 400 600 800
--- -- ,
200 ~
........
:2
-E300 0)
..
r-- .....
c
lii 200
~
c
o
-
co
.S c
'fl
60
"a::
40
o
......
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100
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'iii
20
c
OJ
I-
0
I
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100
* 100 ....... cO ... l!! 80
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- - THoa temper - TH03 temper
'iii
f'!.
60
......... -,
e
C15000: Tensile properties. Short-time elevated-temperature tensile properties. Material was solution treated 15 min at 900°C (1650 OF), quenched, cold worked, and aged. The TH03 temper material was cold worked 54%, then aged 1 hat 400°C (750 OF); the TH08 temper material was cold worked 84%. then aged 1 hat 375°C (710°F)
1000
-
500 200 300 400 Test temperature, °C
600
C15000: Typical creep strength lOst tempersture OF -c
l000b ksi MPa
THOltemper(17% cold work) 300 570 277 350 660 217 400 750 150 450 840 98 500 930 88 600 1Il0 28 TH02 temper (43 % cold work) 250 480 343 300 570 325 350 660 247 400 750 176 450 840 100 500 930 74 600 IIlO 18 TH04 temper (82 % cold work) 250 480 321 300 570 305 350 660 257 400 750 201 450 840 77 500 930 63 600 lliO 5.2 650 1200 3.0
C15000: Typical mechanical properties Stress for1% creepin 10000b MPa ksi
l00000b MPa ksi
40.2 31.5 21.7 14.2 12.7 4.1
241 166 123 70 39 15
35.0 24.0 17.9 10.2 5.6 2.2
208 185 102 51 16 7.5
30.2 26.8 14.8 7.4 2.3 Ll
49.7 47.2 35.8 25.6 14.5 10.7 2.6
330 297 212 142 74 53 12
47.8 43.1 30.7 20.6 10.7 7.7 1.8
317 272 181 1I4 51 39 8.3
46.0 39.5 26.2 16.5 7.4 5.6 1.2
46.5 44.2 37.3 29.2 ILl 9.2 0.75 0.44
312 271 238 161 53 41 2.8 1.7
45.2 39.3 34.5 23.4 7.7 6.0 0.41 0.25
303 240 219 139 44 28 1.5 1.0
44.0 34.8 31.8 20.2 6.4 4.0 0.22 0.14
Seellonsize rom
Rod 5 6 9.5 13 16 19 22 25 32 Wire I 2.3
0.20 0.25 0.37 0.50 0.62 0.75 0.87 1.0 1.25
76 10(d) 80 56 61 50 48 48 32
44 47 31 34 52 47 17 98(e) 62(e)
0.04 0.09 0
0 6
Note: Data arefor materialssolutiontreated,coldworkedthe indicatedamount.thenaged I hat 425 °C(795 oF)
in.
Coldwork,%, after Thnsile strength Solulion trealing(a) Aging(b) MPa ksi
13
0.25 0.50
O(d)(f) 30(d)
430 285 470 460 440
435 430 430 413 525 495 200 205 255 365
62 41 68 67 64 63 62 62 60 76 72
29 30 37 53
Yield strengtb(c) ksi MPa
385 250 440
435 430 420 415 415 400
495 470 40 90 75 340
Elongation in SO mm(2in.), %
56 36 64 63 62 61 60 60 58
8 34
72
1.5 3 54 49 50 23
68 6 13 II
49
II
15 15 15 15 15 18
(a) At 900 10925°C (1650101695 oF). (b) For I h or more at 400 10425°C (750to 795 oF). (c)At 0.5% extensionunder load.(d) Mill annealed. (e) Solutiontreated.cold workedthe statedamount, thenaged.(f)OS025temper
Previous Page
312/ Heat Treater's Guide: Nonferrous Alloys
C15100 (99.9Cu-0.1 Zr) Trade Name. ZHC copper
Characteristics
Chemical Composition. Composition Limits. 0.05 to 0.15 Zr, 0.005
Typical Uses. Typically used for combination of properties: high con-
Al max, 0.005 Mn max, 0.005 Fe max, 0.01 Al + Mn + Fe max, bal Cu
ductivity, moderate strength, good bendability, good resistance to stress relaxation. Applications include lead frame for high-power electronic circuits, connectors, and switch blade pieces
C15100: Nominal mechanical properties of rolled strip Tensile
MP,
ksi
MP,
ksi
Elengation in SOmm (2 ln), %
Hardness,
Temper
HOI H02 H03 H04 HOO H08
295 325 360 400 430 470
43 47 52 58 62 68
240 295 345 385 415 455
35 43 50 56 60 66
22 10 5 3 2 2
32 38 48 57 60 62
strength
Yield strength
HRB
Machinability. 20% that of C36000 (free-cutting brass) Fotigue strength(,) MP, ksi
Formability. Hot forming and cold working: excellent Joining. Solderability: excellent. Brazing and resistance butt welding: good. Not recommended: other welding processes
Recommended Heat Treating Practice 95
14
Annealing. Temperature range is 450 to 550 °C (840 to 1020 "F) Hot Working. Temperature range is 750 to 875°C (1380 to 1610 "F)
(a) At 108 cycles
C15500 (99.75Cu-0.11 Mg-0.06P) Chemical Composition. Composition Limits. 99.75 Cu min, 0.027
Formability. Cold working and hot forming: excellent
to 0.10 Ag, 0.04 to 0.080 P, 0.08 to 0.13 Mg
Hot Forgeability. 65% that of C37700 (forging brass)
Characteristics
Joining. Resistance spot welding only. Other welding processes not recommended. Solderability: excellent. Brazing: excellent
Typical Uses. High conductivity, light duty springs, electrical contacts,
Recommended Heat Treating Practice
resistance welding electrodes, electrical fittings, clamps, connectors, diaphragms, electronic components
Annealing. Temperature range is 485 to 540°C (905 to 1000 "F)
Machinability. 20% that ofC36000 (free-cutting brass)
Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 oF)
C15500: Mechanical properties of flat products
'Iemper
Thnsilestrength MP, ksi
Yietd strength Ato.s% extension under load MP, ksi
At 0.2% olTset ksi
MP,
EIong,tion in 50 mm (2 In.), %
Hardness HRF HRB
Fatigue strength
MP,
ksl
103
15.0
162 155
23.5 22.5
Section size, 1.0 mm (0.040 ln.) thick Light anneal (050) Quarter hard (HO1) Half hard (H02) Hard(H04) Spring (H08) Extra spring (HIO) Super spring Special spring
275 310 365 425 460 495 515 550
40 45 53 62 67 75 80
125 250 325 393 450 470 480 495
275 310
40 45
125 248
72
18 36 47 57 65 68 70
72
123 247 324 394 462 490 503 517
17.8 35.8 47.0 57.2 67.0 71.0 73.0 75.0
34 25 13 5 4 3 3 3
18 36
122 246
17.7 35.7
40 28
70 89
92 97 100 80 82 84
Section size, 5.0 mm (0.200 in.) thick Light anneal Quarter hard
70 89
Wrought Copper I 313
Chemical Composition. Composition Limits. 99.69 to 99.85 Cu, 0.15
C15710: Typical mechanical properties
to 0.25 Ah03, 0.01 Fe max, 0.01 Pb max, 0.04 0 max
Characteristics Typical Uses. Rolled strip, rolled flat wire, rod and wire for electrical connectors, light-duty, current carrying springs, inorganic insulated wire, thermocouple wire.Iead wire, resistance welding electrodes for aluminum, heat sinks Formability. Cold working: excellent. Hot forming: poor Joining. Soldering: excellent. Brazing: good. Resistance butt welding: fair. Resistance spot and seam welding: poor. Not recommended: oxyacetylene, gas shielded are, and coated metal arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 875°C (1200 to 1610 OF)
Diameter mm 10.
Rod 24
22 19 16 10 6
Amountorcold workingor temper designation
0.94 0.88 0.75 0.63 0.38 0.25
Yieldstrengtbat 0,211i olrset(a) MPa ksl
'Thnsile streogtb(a) ksi MPa
0% 13% 39% 56% 82% 93% 061
325 345 415 450 510 530 325
47 50
270 330
60
400
65 74 47
425 470 485 275
39 48 58 62 68 70 40
98.5% 99.5% 061 99.8% 65% 99.9% 85% 061
565 650 325 685 455 725 475 345
82 94 47 99 66 105 69 50
540 620 275 650 420 690 450 290
78 90 40 94 61 100 65 42
77
Elongationin IIardoess, SOmm(21o.),iii BRB
20 18 16 12 10 10 20
60 65
70 70 72 74 60
Wire
2 1
0.09 0.05
0.8
0.03
0.5
0.02
(a) Properties will vary,depending onextrusion rallo and temperature
C15720 (99.6Cu-O.4AI 2 0 3 ) Chemical Composition. Composition Limits. 99.49 to 99.60 Cu, 0.35
C15720: Typical mechanical properties
to 0.45 Al203, 0.01 POmax, 0.01 Fe max, 0.04 0 max
Characteristics Typical Uses. Where parts require combination of high strength and conductivity, particularly after exposure to high manufacturing or service temperatures. Applications include rolled and drawn strip, rolled flat wire; drawn bar, rod, wire, and shapes for relay and switch springs; lead frames; contact supports; heat sinks; circuit breaker parts; rotor bars; resistance welding electrodes and wheels; and connectors
Formability. Cold working: excellent. Hot forming: poor Joining. Soldering: excellent. Brazing: good. Resistance butt welding: fair. Resistance spot and seam welding: poor. Not recommended: oxyacetylene, gas-shielded are, and coated metal arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 925°C (1200 to 1695 OF)
Size
Flat products 0.76 nun (0.03 in.) thick 0.51 nun (0.02 in.) thick 0.25 nun (0.01 in.) thick 0.152mm (0.006 in.) thick
Rod 24 nun (0.94 in.) diameter 21 nun (0.81 in.) diameter 18 nun (0.72 in.) diameter 16 nun (0.63 in.) diameter 13 nun (0.50 in.) diameter 10nun (0.38 in.) diameter 76nun (3.0 in.) diameter 102 nun (4.0 in.) diameter
Amountoroold 'Thoslle worklngor temper slreogtb(a) deslgoatlon ksl MPa
Yleldstrengtb 8tO,2% olfset(a) ElongationIn HanIness, ksl SOmm (210.),iii BRB MPa
91%
570
83
545
79
7
95%
585
85
565
82
6
97%
605
88
580
84
5
98%
615
89
585
85
3.5
061 .
485
70
380
55
13
0%
470
68
365
53
19
74
26%
495
72
470
68
16
77
42%
410
74
485
70
14
78
56%
530
77
495
72
13
79
72%
540
78
505
73
11
79
82%
550
80
510
74
10
80
M30
525
76
510
74
13
78
M30
460
67
395
57
20
68
(a) Properties will vary,depending onextrusion ratio and temperature
314/ Heat Treater's Guide: Nonferrous Alloys
Chemical Composition. Composition Limits. 99.19 to 99.35 Cu, 0.65 to 0.75 Ah03, 0.01 Fe max, om Pb max, 0.04 0 max
Characteristics Typical Uses. Where parts must retain high strength and conductivity after exposure to high temperatures. Applications include rod for resistance welding electrodes, circuit breakers, feed-through conductors, seat sinks, motor parts
Formability. Cold working: excellent. Hot forming: poor Joining. Soldering: excellent. Brazing: good. Resistance butt welding: fair. Resistance spot and seam welding: poor. Not recommended: oxyacetylene, gas shielded are, and coated metal arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 925°C (1200 to 1695 OF)
C15735: Typicalmechanical properties of rod Diameter mm in.
24 19 16 64 76 102
0.94 0.75 0.63 2.5 3.0 4.0
Amount of cold workingor temper designation
0% 39% 56% M30 M30 M30
Thnsile strength!.) MP. ksl
485 550 585 490 565 515
70 80 85 71 82 75
Yieldstrength at Elong.tion In 0.2% offset!.) MP. ksi 5Omm(2in.), %
420 540 565 415 540 485
61 78 82 60 78 70
Hardness,
HRB
16
77
13
13
80 83 76 78 75
Elong.lion In 50 mm (2 Ia), %
Hardness
10 16 11
(a)Properties will vary.depending on extrusion ratio and temperature
C16200 (99Cu-1 Cd) Commercial Names. Previous trade name. Cadmium copper Chemical Composition. Composition Limits. 98.78 to 99.3 Cu, 0.7
C16200: Typicalmechanical properties 'Iensile strength MP. ksl
to 1.2 Cd, 0.02 Fe max
Temper
Specifications (U.S.and/or Foreign). ASTM. Wire: B 9, B 105; SAE.
Flat pmduets. I mm (0.04 In.) thick 35 240 OS025 anneal (0.025 mm grainsize) 415 60 Hard 440 64 Spring 72 495 Extraspring Rod, 13 mm (0.50 in.) diameter 240 35 OS050 anneal (0.050mm grainsize) OS025 anneal 250 36 (0.025mm grainsize) Half hard(25%) 400 58 Hard 505 73 Wire, 0.25 mm (0.01 ln.) diameter Drawn(>99%) 690 100 Wire, 2 mm (0.08 ln.) diameter 38 OS025 anneal 260 (0.025mm grainsize) 485 70 Hard Spring 550 80 Drawn(>96%) 88 605
J463
Characteristics Typical Uses. Rolled strip, rod, and wire for trolley wire, heating pad and electric blanket elements, spring contacts, rail bands, high-strength transmission lines, connectors, cable wrap, switch gear components, waveguide cavities
Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold working: excellent. Hot forming: good Joining. Soldering and brazing: excellent. Oxyfuel gas, gas shielded are, and resistance butt welding: good. Not recommended: shielded metal are, resistance spot and resistance seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 750°C (795 to 1380 OF) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 OF)
Yieldstrength(.) MP. ksi
76
11
52
54HRF
310
45
405
59
5 3 1
64HRB 73HRB 75HRB
48
7
56
46HRF
83
12
57
46HRF
310 474
45 68.7
12 9
65HRB 73HRB
1.0{b) 83
12
50
380 455
55 66
6 2 1.5{b)
(a)At 0.5% extension underload. (b) In 1.5 mm(60in.)
C17000 (98Cu-1.7Be-O.3Co) Commercial Names. Trade name. Berylco 165; Common name. Beryl-
Specifications (U.S. and/or Foreign). ASTM. Flat products: B 194.
lium copper, 165 alloy
Rod, bar: B 196. Forgings and extrusions: B 570; SAE. J463; Government. QQ-C-533: Resistance Welding Manufactures' Association. Class IV
Chemical Composition. Composition Limits. 1.60 to 1.79 Be, 0.21 Ni + Co min, 0.6 Ni + Fe + Co max, bal Cu
Characteristics Typical Uses. Bellows, Bourdon tubing; diaphragms, fuse clips, fasteners, lock washers, springs, switch and relay parts, electrical and electronic
Wrought Copper I 315
components, retaining rings, roll pins, valves, pumps, spline shafts, rolling mill parts, welding equipment, nonsparking safety tools
C17000: Approximate corrosion resistance Good
Formability. Can be formed, drawn, blanked, pierced, and machined in unhardened condition Joining. Soldering, brazing, gas shielded arc welding, shielded metal arc welding, and resistance spot welding: good. Resistance seam and resistance butt welding: fair. Not recommended: oxyfuel gas welding General Corrosion Behavior. Basically same as pure copper. Resistance to specific corrosive agents: see adjoining Table Caveat: contains beryllium, a potential hazard to health. Ventilation must be provided for dry sectioning and grinding, machining, melting, welding, and any other process that produces metal dust or fumes
Recommended Heat Treating Practice Annealing. Strip, thin rod, wire: temperature range is 775 to 800°C (1425 to 1475 OF) for 10 min; water quench. Larger sections: 1 h for each 25 mm (I in.) of thickness Solution Heat Treating. Temperature range is 760 to 790°C (1400 to 1455 "F), Note: all annealing of this material is a solution treatment Aging. Temperature range is 260 to 425°C (500 to 795 OF). Maximum strength is obtained by aging 1 to 3 hat 315 to 345°C (600 to 650 "F), depending on amount of cold work preceding aging Hot Working. Temperature range is 650 to 825 °C (1200 to 1520 OF) Hot-shortness temperature: 845°C (1555 OF)
PoorreslslOllCe(c)
Fairreslslaoce(b)
reslslan<e(a)
Machinability. 20% that of C36000 (free-cutting brass) Acetatesolvents Aceticacid,cold, unaerated Alcohols Ammonia,dry Atmosphere, rural,industrial, marine Benzene Borax Boricacid Brine Butane Carbondioxide Carbontetrachloride Chlorine, dry Freon Gasoline Hydrogen Nitrogen Oxalicacid Potassiumchloride Potassiumsulfate Propane Rosin Sodiumbicarbonate Sodiumchloride Sodiumsulfate Sulfurdioxide Sulfurtrioxide Water, freshor saIt
Aceticacid,hot Aceticacid,cold, aerated Ammonia,moist Aceticanhydride Ammoniumhydroxide Acetylene Ammoniumnitrate Ammoniumchloride Bromine,aeratedor hot Ammoniumsulfate Chlorine,moistor warm Aniline Chromicacid Bromine,dry Carbonicacid Ferricchloride Ferricsulfate Coppernitrate fluorine, moistor warm Ferrous chloride Hydrochloric acid,over0.1% Ferroussulfate fluorine, dry Hydrocyanic acid Hydrochloric acid,up to 0.1% Hydrofluoricacid,concentrate Hydrogensulfide,moist Hydrofluoricacid,dilute Lacticacid,hot or aerated Hydrofluosilicic acid Mercuricchloride Hydrogenperoxide Mercury Nitricacid,up to 0.1% Mercurysalts Phenol Nitricacid,over0.1% Phosphoricacid,unaerated Phosphoricacid,aerated Potassiumhydroxide Sodium hydroxide Picricacid Potassiumcyanide Sodiumhypochlorite Silverchloride Sodium peroxide Sodiumsulfide Sodiumcyanide Stannicchloride Sulfur Sulfuricacid,aerated Sulfurchloride Sulfurousacid Sulfuricacid, unaerated Tartaricacid,hot or aerated Zincchloride
(a)<0.25mm1year (0.01in./year)penetration.(b)0.025-2.5mm1year (0.001-0.10 in./year)penetration.(c)>0.25mmlyear(O.OI in.lyear)penetration
C17000: Typical mechanical properties and electrical conductivity of strip Tensile strength MPa ksi
'Iemper
raoo TOOl TD02 TD04 TFOO(b)
THOI(c) TH02(c) TH04{c) TMOO(d) TMOI(d) TM02(d) TM04(d) TM06(d) TM08(d)
410-540 520-610 590-690 690-825 1030-1240 1100-1280 1170-1340 1240-1380 690-760 760-825 825-930 930-1030 1030-1100 1100-1210
60-78 75-88 85-100 100-120 150-180 160-185 170-195 180-200 100-110 110-120 120-135 135-150 150-160 160-175
PropoI1ional Umit at 0.002 % offset ksi MPa 100-140 280410 380480 480-590 550-760 620-795 660-860 690-930 480-590 520-660 550-690 590-725 590-760 620-795
15-20 40-60 55-70 70-85 80-110 90-115 95-125 100-135 70-85 75-95 80-100 85-105 85-110 90-115
YIeld strenglh at 0.2 % offset MPa ksl 190-370 310-520 450-620 550-760 895-1140 930-1170 1000-1210 1070-1240 520-620 620-760 690-860 760-930 860-965 965-1140
28-53 45-75 65-90 80-110 130-165 135-170 145-175 155-180 75-90 90-110 100-125 110-135 125-140 140-165
Elongation in
Electrical conductivity,
50 mm (2 in.), %
%IACS
35-60 10-35 5-25 2-8 4-10 3-6 2-5 1-4 18-22 15-19 12-16 9-13 9-12 3-7
17-19 16-18 15-17 15-17 22-25 22-25 22-25 22-25 20-33 20-33 20-33 20-33 20-33 20-33
Fatigue strength(a) ksi MPa 190-230 200-235 220-260 240-270 240-270 250-280 250-290 260-310 230-255 230-260 240-270 250-280 255-290 230-310
28-33 29-34 32-38 35-39 35-39 3641 3642 3845 33-37 34-38 35-39 3640 3742 3345
(a) Rotatingbeam at 108 cycles.(b) Aged3 h at 315°C (600 "F), (c)Aged2hat315 °C (600 "F), (d)Proprietary millheat treatmentintendedtoproducethe statedtensileproperties
C17000: Typical mechanical properties and electrical conductivities of rod, bar, plate, tubing, billets, and forgings Productform Rod, bar,plate.tubing All sizes <10 mm «0.375 in.) 10-25 mm (0.375-1 in.) >25 mm (>I in.) Billet
'Iemper
rnoo TFOO(a) TD04 TH04(b) TD04 TH04(b) TD04 TH04(b) As-cast Castandaged(a)
rsoo
TFOO(a) Forgings
TBoo TFOO(a)
'Iensde strength MPa ksl 415-585 1035-1240 655-895 1205-1380 620-825 1170-1345 585-795 1140-1310 515-585 655-690 415-515 965-1170 415-585 1035-1240
(a) Aged3 h at 350°C (660 oF). (b) Aged2 to 3 h at 330°C (625 oF)
60-85 150-180 95-130 175-200 90-120 170-195 85-115 165-190 75-85 95-100 60-75 140-170 60-85 150-180
Yield strength at 0.2% offset MPa ksi 140-205 860-1070 515-725 930-1140 515-725 930-1140 515-725 930-1140 275-345 485-515 170-205 725-930 140-205 860-1070
20-30 125-155 75-105 135-165 75-105 135-165 75-105 135-165 40-50 70-75" 25-30 105-135 20-30 125-155
Electrical conductivity,
Elongationin SOmm(2in.),%
Hardness
%lACS
35-60 4-10 10-20 2-5 10-20 2-5 10-20 2-5 15-30 10-25 25-45 1-4 35-60 4-10
45-85HRB 32-39HRC 92-I03HRB 364IHRC 91-102HRB 35-4OHRC 88-101HRB 34-39HRC 80-85HRB 18-25HRC 65-75HRB 30-38HRC 45-85HRB 32-39HRC
17-19 22-25 15-17 22-25 15-17 22-25 15-17 22-25 16-22 18-23 13-18 18-25 17-19 22-25
316/ Heat Treater's Guide: Nonferrous Alloys C17000: Typicalhardness of strip 'Iemper
HV
Standanl RockweU
SuperlldoJRockwen
TBOO
90-160 150-190 185-225 200-260 320 min 343 min 360 min 370 min 200-235 230-265 260-295 290-325 320-350 434-375
45-78HRB 68-9OHRB 88-96HRB 96-102HRB 33-38HRC 35-39HRC 37-40HRC 39-41HRC 18-23HRC 21-26HRC 25-30HRC 30-35HRC 31-37HRC 32-38HRC
45-67HR30T 62-75HR30T 74-79HR3OT 79-83HR3OT 55-58HR30N 55-59HR30N 56-80HR30N 58-61HR30N 37-42HR30N 42-46HR30N 46-50HR30N 50-54HR30N 52-56HR30N 55-58HR30N
TOOl
TD02 TD04
TFOO TIIOI TII02 TII04 1M00 1MOI
1M02 1M04
1M06 1M08
C17200,C17300 Commercial Names. Previous trade names. CI7200: 25 alloy, alloy 25.
General Corrosion Behavior. Basically same as that of pure copper.
C 17300: Alloy M25; Common name. Beryllium copper
Resistance to specific corrosive agents: see adjoining Figure
Chemical Composition. Composition Limits. 1.80 to 2.00 Be, 0.20
Machinability. CI7200: 20% that of C36000 (free-cutting brass). C17300: 50% that of C36000 (free-cutting brass). Both alloys are readily machined by all conventional methods. Machining parameters depend on shapes, machining method, and temper or condition of metal. C17300, which contains lead, is especially intended for machining parts, other properties are not changed by the presence of lead
Ni + Co min, 0.6 Ni +Co + Fe max (CI7200) or 0.20 to 0.60 Pb (CI7300), 0.5 others max (total) bal Cu. Caveat: excessive P and Si decrease electrical conductivity. Excessive Sn and Pb cause hot shortness
Specifications (U.S. and/or Foreign). AMS. Flat products: 4530, 4532. Rod, bar, and forgings: 4650. Wire: 4725; ASTM. Flat products: B 194 (CI7200 only), B 196. Rod and bar: B 196. Wire: B 197 (CI7200 only). Forgings and extrusions: B 570 (CI7200 only); SAE. J463 (CI7200); Government. Strip: QQ-C-533 (CI7200 only). Rod and bar: MIL-C-21657, QQ-C-530. Resistance Welding Manufacturers' Association: Class IV
Recommended Heat Treating Practice Annealing. For strip, thin rod, and wire: temperature range is 760 to 790 °C (1400 to 1455 OF) for 10 min; water quench. Larger sections: hold 1 h per 25 mm (1 in.) or fraction of a mm (in.) per cross section Solution Heat Treating. Temperature range is 760 to 790°C (1400 to
Characteristics
1455 OF). All annealing of this material is a solution treatment
Microstructure. Conventional metallographic techniques may be used.
Aging. Temperature range is 260 to 425 °C (500 to 795 "F). Maximum strength is obtained by aging 1 to 3 hat 315 to 345°C (600 to 650 "F), depending on amount of cold work
Drip sectioning and grinding should be done in a ventilated area One of the common etchants for immersion etching is ammonium persulfate. This etchant reveals general details of microstructure, matrix is stained blue to deep lavender, depending on the state of heat treatment, etchant concentration, and etching time. Etchant should be freshly made A common etchant for swabbing is potassium dichromate. This etchant emphasizes grain boundaries, particularly when heavily decorated with discontinuous precipitate. An effective procedure: first etch with ammonium persulfate, then remove stain with single wipe of the dichromate etchant
Hot Working. Temperature range is 650 to 800 °C (1200 to 1470 OF). Cl7300 cannot be hot rolled or forged but can be hot extruded Recrystallization temperature is approximately 730°C (1345 OF) Hot shortness temperature is 845 °C (1555 OF)
C17200: Hardness. Effect of solution-treating temperature on hardnessafter aging LIVE GRAPH Click here to view Solution-treating temperature. OF
Typical Uses. Both alloys are used for parts subjected to severe forming and have a combination of requirements: high strength, anelasticity, and resistance to fatigue and creep. Examples: a wide variety of springs, flexible metal hose, Bourdon tubing, bellows, clips, washers, retaining ring In other applications, parts require high strength or wear resistance, along with good electrical conductivity and/or magnetic characteristics. Examples: navigational instruments, nonsparking safety tools, firing pins, bushings, valves, pumps, shafts, and rolling mill parts Still other applications require high strength, combined with good electrical conductivity and resistance to corrosion. Examples: electrochemical springs, diaphragms, contact bridges, bolts, and screws Caveat: beryllium content presents potential hazard to health. Adequate ventilation should be provided for dry sectioning, melting, grinding, machining, welding, or any other fabrication or testing process that produces dust or fumes
80
1000
1200
I
I
1400
I
I
I
1600 I
Cu-1.9BB-O.25Co, aged
z
lil
lC
60
:x:
m
c:
~ 40 :x: 20 500
(
J)
600 700 800 900 Solution-treating temperature, °C
Wrought Copper /317 Cl7200 and C17300: Tensile property ranges forstrip of various tempers ThmBe st",ngth MPa ksl
Thmper TBOO TOOl TD02
415-540 515-605 585-690 690-825 1140-1310 1205-1380 1275-1450 1310-1480 690-760 760-825 825-930 930-1035 1035-1105 1105-1205 1205-1310
TD04
TRlO(a) lHOl(b) lH02(b) lH04(b) TMOO(c) TMOI(c) TM02(c) TM04(c) (c) TMOO(c) TM08(c)
Yield stnmgth at0.1~ offset MPa ksl
Propol1lonal Omitat 0.002 ~ off..t MPa ksl
60-78 75-88 85-100 100-120 165-190 175-200 185·210 190-215 100-110 110-120 120-135 135-150 150-160 160-175 175-190
105-140 275-415 380-485 485-585 690-860 760-930 825-1000 860-1070 450-585 515-655 585·725 655-795 725-825 760-860 795-895
195-380 415-605 515-655 620-770 965-1205 1035-1275 1105-1345 1140-1415 515-620 620-760 690-860 795-930 860-965 1000-1170 1070-1240
15-20 40-60 55·70 70-85 100-125 110-135 120-145 125-155 65-85 75·95 85-105 95-115 105-120 110-125 115-130
J!jongatlon In 50_(210.), ~
28-55 60-88 75-95 90-112 140-175 150-185 160-195 165-205 75-90 90-110 100-125 115-135 125-140 145-170 155-180
35-60 10-36 5-25 2-8 4-10 3-6 2-5 1-4 18-23 15-20 12-18 9-15 9-14 4-10 3-9
(a)Soluliontreatedandaged3 h 31315°C (600 "P), (b)Coldrolledand aged2 h at315 °C (600 "F). (c)Proprietarymilltrealmenttoproducetheindicatedtensileproperties
Cl7200 and Cl7300: Property ranges forvarious mill products Thmper
ThIckness ordiameter
Rod, bar, plate, and tubing TBOO All sizes TD04 <9.5mm (0.38in.) 9.5-25mm (0.38-1in.) >25 mm (l in.) TRlO(a) All sizes lH04(b) <9.5mm (0.38in.) 9.5-25mm (0.38-1in.) >25 mm (l in.) Wire TBOO All sizes TD04 <2 mm (0.08in.) 2-9.5mm (0.08-0.38 in.) >9.5mm (0.38in.) TRlO(a) All sizes lH04(c) <2 rnm(0.08 in.) lH04(d) 2-9.5 rnm(0.08-0.38in.) >9.5mm (0.38in.) Billets Ascast Castandaged(a) TBOO TFOO(a) Forgings TBOO TFOO(a)
ThnsBe stre ogth MPa ksi
Yield st",ngthal0.1~ offset MPa ksI
EIectricalcondU
Elongation in SO mm(2 In.), ~
~IACS
415-585 655-900 620-825 585-790 1140-1310 1280-1480 1240-1450 1210-1410
60-85 95-130 90-120 85-115 165-190 185-215 180-210 175-205
140-205 515-725 515-725 515-725 1000-1210 1140-1380 1140-1380 1030-1340
20-30 75"105 75·105 75-105 145-175 165-200 165·200 150-194
35-60 10-20 10-20 10-20 3-10 2-5 2-5 2-5
45-85HRB 92-103HRB 91·102HRB 88-102HRB 36-40HRC 39-45HRC 38-44HRC 37-43HRC
17-19 15·17 15-17 15-17 22-25 22-25 22·25 22-25
400-540 895-1070 655-900 620-825 1140-1310 1.310-1590 1280-1480 1240-1450
58-78 130-155 95-130 90-120 165-190 190·230 185-215 180-210
140-240 760-930 515-725 515-725 1000-1210 1240-1410 1210-1380 1140-1380
20-35 110-135 75-105 75-105 145-175 180-205 175-200 165-200
35-55 2-8 10-35 10-35 3-8 1-3 2-5 2-5
515-585 725-760 415-515 1070-1210
75-85 105-110 60-75 155-175
275-345 515-550 170-205 860-1030
40-50 75-80 25-30 125·150
15-30 10-20 25-45 1-3
80-85HRB 20-25HRC 65-75HRB 36-42HRC
16-22 18-23 13-18 18-25
415·585 1140-1310
60-85 165-190
140-205 1000-1210
20-30 145-175
35-60 3-10
45-85HRB 36-41HRC
17-19 22-25
17-19 15-17 15-17 15-17 22-25 22-25 22-25 22-25
(a) Aged3h at330 °C (625 oF). (b)Aged2t03hat330°C(625 oF). (c)Aged 1hat330°C(625 oF). (d)Aged 1.5t03 hat330°C(625 oF)
Cl7200 and C17300: Hardness, conductivity, and fatigue strength forstrip of various tempers Elec:trkal conductivity,
Hardness
Fatigue .....ngth
Thmper
HV
HRC
HRJON
~IACS
MPa
ksI
TBOO TOOl T002 TD04 TFOO
90-160 150-190 185·225 200-260 343 min 370 min 380 min 385 min 200-235 230-265 260-295 290-325 320-350 343-375 370-400
45-78HRB 68-90HRB 88-96HRB 96-102HRB 31-41 38-42 39-44 40-45 18-23 21-26 25-30 30-35 31-37 32-38 33-42
45·67HR3OT 62-75HR30T 74-79HR30T 79-83HR3OT 56-61 58-63 59-65 60-65 37-42 42-47 45-51 50-55 52-56 55-58 56-63
17-19 16-18 15-17 15·17 22-25 22-25 22-25 22-25 20-28 20-28 20-28 20-28 20-28 20-28 20-28
205-240 215-250 220-260 240-270 240-260 240-270 270-295 285-315 230-255 235-260 240-295 260-310 260-310 260-310 275-330
30-35 31·36 32-38 35-39 35-38 35-39 39-43 41-46 33-37 34-38 35-43 38-45 38-45 38-45 40-48
rnoi lH02 lH04 TMOO TMOI TM02 TM04 (a) TMOO TM08
(a) Proprietary millheat treatmentto producetensilestrengthof 1030-1100 MPa(150to 160ksi)
318/ Heat Treater's Guide: Nonferrous Alloys
C17200: Aging. Effect of metal thickness and heating medium on aging time required to develop maximum strength in strip
LIVE GRAPH Click here to view 0
Thickness of strip, 0.001 in. 20
40
60
C17200: Microstructure. Strip, solution annealed at 790°C (1455 OF) and cold rolled at 37% to full hard temper. Longitudinal section shows elongated grains of ex phase and cobalt beryllides. 400x
80
80
60 c
'E
."E'" 40 c:
~
20
0.5
1.0 1.5 Thickness of strip, mm
2.0
2.5
Cl7200 and C17300: Approximate corrosion resistance Good resistanceta)
Fairresistancetb)
Acetatesolvents Aceticacid,cold,aerated Aceticacid,cold,unaerated Aceticanhydride Alcohols Acetylene Ammonia, dry Ammonium chloride Atmosphere, rural, indusAmmonium sulfate trial, marine Benzene Aniline Borax Bromine,dry Boricacid Carbonicacid Brine Coppernitrate Butane Ferrouschloride Carbondioxide Ferroussulfate Carbontetrachloride Fluorine,dry Chlorine, dry Hydrochloric acid,up to0.1% Freon Hydrofluoric acid,dilute Gasoline Hydrofluosilicic acid Hydrogen Hydrogenperoxide Nitrogen Nitricacid,up to 0.1% Oxalicacid Phenol Potassium chloride Phosphoric acid,unaerated Potassium sulfate Potassium hydroxide Propane Sodiumhydroxide Rosin Sodiumhypochlorite Sodiumbicarbonate Sodiumperoxide Sodiumchloride Sodiumsulfide Sodiumsulfate Sulfur Sulfurdioxide Sulfurchloride Sulfurtrioxide Sulfuricacid,unaerated Water, freshorsalt Zincchloride
Poorresistance(c) Aceticacid,hot Ammonia, moist Ammonium hydroxide Ammonium nitrate Bromine, aeratedorhot
C17200: Microstructure. Strip, mill hardened to XHMS (TM08) temper for high strength and limited formability. Longitudinal section shows elongated grains of the ex phase and cobalt beryllides. Striations result from precipitation of metastable phases not resolved by optical microscopy. 400x
Chlorine, moistor warm Chromicacid Ferricchloride Ferricsulfate Fluorine, moistor warm Hydrochloric acid,overO.l% Hydrocyanic acid Hydrofluoric acid,concentrated Hydrogen sulfide, moist Lacticacid,hotoraerated Mercuricchloride Mercury Mercurysalts Nitricacid,over0.1% Phosphoric acid,aerated Picricacid Potassium cyanide Silverchloride Sodiumcyanide Stannicchloride Sulfuricacid,aerated Sulfurousacid
(a) <0.25 mmfyear(0.01 inJyear) attack.(b) 0.025-2.5 mmfyear (0.001-0.10 in.lyear) attack.(c) >0.25mmfyear (0.01 in.lyear) attack
C17200: Microstructure. Strip, solution annealed, cold rolled full hard and precipitation hardened at 315°C (600 OF) for 2 h to achieve maximum hardness. Longitudinal section shows elongated grains of ex phase and cobalt beryllides. Striations are caused by metastable precipitates not resolved by optical microscopy.400x
Wrought Copper I 319
400.------.......----r-------r-----r-----r-------, C17200 strip
~
700
Ii-
350 1------->.;~.......- - - " " - _ . . . : : _ l _ _ : , < _ - - _ + - - - - _ + _ - - - _ _ _ I - - - - _ _ 1
~
a m
:::l
~
:;;
CD
a. E
a.
2l
....... ....... .......
Cl
c:
--
~
250 L..-
....L.
.L-
o
.......L
-'-
----J'--
4
5
2
E 600 s
C17200: Time-temperature relationships. Time-temperature relationships in aging of C17200 strip, showing aging time required for the development of maximum strength in annealed, quarter hard, half hard, and hard C17200 strip aged at various temperatures in a recirculating-air furnace
LIVE GRAPH Click here to view
Cl
c: '0.
«
...J
500
6
C17200: Tensile strength. Variation in tensile strength of hard C17200 strip after aging. The strip was 0.17 to 0.19 mm (0.0065 to 0.0075 in.) thick and was aged 3 h at 315°C (600 OF). The number of tests of each group was 200 Tensile strength, ksi 100
150
120
110
190
200
120 1----/------1........----+------+----+--
'" 1il ....2l 0
wwwl As-received ~Aged
90
:;;
.0
E :::l
60
Z
30
0
1520 Tensile strength, MPa •
C17200: Hardness. Variation in hardness for 50 batches of aged spring contact receptacles stamped from quarter hard C17200 strip 15 C17200
Aim
'"
CD J::
sm
r« ~
10
.0
....0
0.0131 0.0121
:;;
E :::l
z
0.765
l
.0
5
0 75
76
77
Hardness, HR15N
78
79
Spring contact receptacle
320 I Heat Treater's Guide: Nonferrous Alloys
C17200: Microstructure. Strip, solution annealed and aged at 370°C (700 OF) for 6 h to attain an overaged condition. The structure shows y precipitates in the grain boundaries, which appear as dark nodules in a light matrix. 400x
C.17200: Microstructure. Beryllium copper, solution treated 10 min at 790°C (1455 OF) and water quenched. Typical hardness is 62 HRB. Structure is equiaxed grains of supersaturated solid solution of beryllium in copper. 300x
C17200: Microstructure. Strip heated to 885°C (1625 OF) and water quenched. The microstructure shows "burned metal" caused by solution annealing at too high a temperature. Partial melting at the grain boundaries, caused by extreme temperatures, resolidifies as p phase. 700x
C1
10 (99..2Cu",0..3Be",0..5Co)
Chemical Composition. Composition limits. 0.15 to 0.5 Be, 0.35 to 0.60 Co, 0.20 Al max, 0.20 Si max, 0.20 Fe max, 99.5 Cu min + Ag + named elements
Characteristics
Formability. Cold and hot forming capability are rated excellent. Joining by soldering, brazing, and resistance spot welding is rated good. Other welding processes are rated fair. Not recommended: oxyacetylene welding
Recommended Heat Treating Practice Annealing. Temperature range is 450 to 550°C (840 to 1020 "F)
Typical Uses. Strip and wire, fuse clips, fasteners, springs, diaphragms, lead frames, switch parts, and electrical connectors. Rod and plate go into resistance spot welding tips, die casting plunger tips, tooling for plastic molding. Caveat: the alloy contains beryllium, a potential health hazard. Safety precautions are mandatory for all melting, welding, grinding, and machining operations Machinability. 25% that of C36000 (free-cutting brass)
Hot Working. Temperature range is 650 to 925 °C (1200 to 1695 "F)
C17410: Nominal mechanical properties of mill-hardened strip Temper
0.5HT HT
Thnsllestrength MPa ksI
725 830
105 120
YIeldstrength MPa ksi
620 760
90 110
Elongation in SOmm(2 in.),%
Hardness,
15 12
95 95 min
HRB
Fatigue strength MPa ksI
300
43
Wrought Copper /321
C17500 (97Cu..O.50Be..2.5Co) Commercial Names. 10 alloy, alloy 10, Berylco 10; Common name. Low beryllium copper Chemical Composition. Composition Limits. 0.40 to 0.70 Be, 2.40 to 2.70 Co, 0.10 Fe max, 0.50 other max (total), bal Cu Specifications (U.S. and/or Foreign). ASTM. Flat products: B 534. Rod, bar: B 441; SAE. J463; Government. Rod, bar: MIL-C-46087. Strip: MIL-C-81021. Resistance Welding Manufacturers' Association. Class III
Ordinary metallographic techniques are used with one exception: OSHA requirements should be strictly observed, i.e., grinding must be done in a vented area
Machinability. C17500 is readily machinable by all common methods. Recommended machining conditions depend greatly on part shape, its prior heat treatment, and type of machining operation. OHSArequirements must be strictly observed-normally those involving flooding and/or special ventilation to prevent the inhaling or ingesting of metal dust
Recommended Heat Treating Practice
Characteristics
Annealing. All annealing of this alloy is a solution treatment. Crystal Structure. The alpha copper solid solution is face-centered cubic. The beryllide (Cu,Co) Be, is ordered body centered cubic of the CsCl (B2) type.
Solution Heat Treating. For strip, rod, bar, tubing, wire: 10 min at 900 to 955°C (1650 to 1750 "F); water quench. For large sections: 1 h perinch or fraction of an inch at 900 to 925°C (1650 to 1695 OF); water quench
Microstructure. Alpha copper with beryllium in solid solution and with (Cu,CO) Be beryllide inclusions. Appearance of the matrix of the beryllides depends on the extent of deformation and the state of heat treatment. The microstructure of strip and rod is fine-grain, equiaxed alpha copper, with small, mainly spherical, uniformly dispersed beryllides. Regardless of product type there is little difference in microstructure between the annealed and aged conditions.
Aging. For maximum strength: 3 to 6 h at 425°C (795 oF), depending on degree of cold work. Commercial practice: 2 to 3 h at 470 to 495°C (890 to 900 OF). Provides combination of high strength and electrical conductivity. Cooling rate after aging is not critical (see adjoining Figure) Hot Working. Temperature range is 700 to 925°C (1290 to 1695 oF) Hot shortness temperature: 980 °C (1795 oF)
C17500: Microstructure. Strip, solution annealed at 900 °C (1650 OF), quenched rapidly to room temperature and precipitation hardened at 480 °C (900 OF) for 3 h to achieve maximum hardness. Microstructure shows equiaxed grains of supersaturated solution of beryllium and cobalt in copper. The cobalt-beryllide phase is uniformly distributed, and metastable hardening precipitates are not resolved. 400x
C17500: Typical mechanical properties and electrical conductivity
Temper
Strip TBOO H04 TFOO
TH04 HTR(b) HTC(c) Rod, bar, plate, tubing TBOO H04 TFOO TH04 Forged products TBOO TFOO
'Thnsile strength ksi MPa
240-380 35-55 485-585 70-85 690-825 100-120 760-895 1!Q.130 825-1035120-150 515-585 75-85 240-380 450-550 690-825 760-895
35-55 65-80 100-120 1!Q.130
240-380 35-55 690-825 100-120
ProportiollJlllimit at 0.002% offset ksi MPa
69-140 240450 380-515 485-655 550-760 205415
10-20 35-65 55-75 7Q.95 8Q.1!0 30-60
Yieldstrength at 0.2% offset MPa ksl
Elongation inSOmm (2 in.), %
Hardness, HRB
ElectricnJ conductivity, %lACS
Fatiguestrength(a) MPa ksi
205 30 205 30 240 35 24Q.26O 35-38 205-240 30-35
140-205 380-550 550-690 690-825 760-965 345-515
20-30 55-80 80-100 100-120 1!Q.14O 50-75
20-35 3-10 10-20 8-15 1-4 8-15
28-50 70-80 92-100 98-102 98-103 79-88
2Q.30 2Q.30 45-60 5Q.6O 45-60 60 min
140-205 380-515 550-690 690-825
20-30 55-75 80-100 1OQ.120
20-35 lQ.15 10-25 10-20
20-50 60-80 92-100 95-102
2Q.30 2Q.30 45-60 5Q.6O
140-205 20-30 550-690 80-100
20-35 10-25
20-50 92-100
2Q.30 45-60
(a) Reversed bendingat 108 cycles.(b)Proprietary millhardening formaximum strength. (c)Proprietary millhardening maximum electrical conductivity
322/ Heat Treater's Guide: Nonferrous Alloys
C17500: Aging curves. (a) T800 temper. (b) T002 temper 1000 , . . - - - , - - - - - . - - - , - - - ,
LIVE GRAPH
1000
140
Click here to view
480 ·C J
co
0-
~
co BOO
BOO
0~
.c
e
I:
e
600
2!
-0:-:-::.
370 ·C
\540·C--
2!
'0;
I:
f--
BOO
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--
ti
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III
C,
I:
ti
, I.... ---_
.c
C,
LIVE GRAPH
/425 ·C
--_.......
..../
I:
400
~ 400 40
200 30
200 20
*-1:'
..0,
co
..•.
*-
C
0
20
.~
Cl I:
Cl I:
0
540·C..........
W
15
o
10 60
~
40
r/
1'i
:I
w
/··t~·~
----~25.C
.....
g '~
-- t·C--
o
.
_~ -----370 ·C
y
Click here to view 1600
I
I
1800
I
Cu-o.6Be-2.5Co, aged
m I:
'E co ::c 80
60 700
V
V
»:
800
s :J.
"0
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I:
o
30
f .. .' ..1/ v ...-
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-
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,
40
0
roo
/'
540
1·C
.£-t-./480J~ .....
---- --1--------::::425·C"370 ·C I
/:315·C-:
V-
20 As-rolled
4 6 Aging time. h
(b)
Solution-treating temperature, OF
al100 a: ::c
>
Q)
C17500: Aging. Effect of solution-treating temperature on hardness of C17500 after aging LIVE GRAPH
I
50
,~
m
(e)
1400
~
'~
30 I , /
20 l..===::r::=-----.L_......l_ _ o 2 4 6 Aging time. h
120
'.
"
en
/540
50 I------,A--=----+_- 480 ·C
:f (
"""'I"
60
....-
y
42JC
~
0
W
*....
370·C
/ .....,..:.,. -- --:,:,.. ....":1::. .... :ifF~-~.....• 480·C 10 V \ ....................... 15
25
900
Solution-treating temperature, °C
1000
C17500: Microstructure. Strip, solution annealed, cold rolled, and precipitation hardened at 480°C (900 OF) for 2 h to achieve maximum hardness. Structure consists of the <X phase and a uniform distribution of the beryllide phase. Elongated grains are the result of cold work, and metastable hardening precipitates are not resolved. 400x
Wrought Copper /323
C17600 Commercial Names. Previoustrade name. 50 alloy, alloy 50; Common name. Beryllium-copper Chemical Composition. Composition Limits. 99.50 Cu + Be + additives min 0.25 to 0.50 Be, 1.40 to 1.70Co, 0.90 to 1.10 Ag, 1.40 Co + Ni min, 1.90 Co + Ni + Fe max Specifications (U.S. and/or Foreign). SAE. J463 (CAI76). Resistance WeldingManufacturers'Association. Class ill
Characteristics Crystal Structure. Alpha copper solid solution is face-centered cubic; the beryIIide, (Cu.Co) Be, is ordered,body-centeredcubic of the CsCI (B2) type Microstructure. Matrix is alpha copper; large and sharply angular bluegray beryIIide inclusions in grain boundaries of cast product, smaller Widmanstlitten beryllide in the grain. In wrought products with large amounts of deformation, beryllides are small, mainly spherical, and uniformly distributed Conventional metallographic techniquesare used. In dry grinding, OHSA requires ventilation. Common etchants for inunersion etching are 3 part concentrateNH40H, I part 3% H202,2 parts 10% (NH4)S203, and 7 to 10 parts H20. Common etchants for swabbing are 3 g K2Cr207, 1.5 g NaCl, 8 mL H2S04, and 100 mL H20
Typical Uses. This high conductivity alloy is designed especially for resistanceweldingelectrodesfor spot, seam,flash, and projectionwelding methods; electrical connectors, clip. Caveat: OHSA requires ventilation during melting, welding, grinding, and all machining operations Machinability. The alloy is machinableby all conventionalmethods
Recommended Heat Treating Practice Annealing. Temperature range for treating strip, wire, rod, and bar is from 900 to 950°C (1650 to 1740 "F) for 10 min; quenching is in water. Larger sections are annealed I h per inch or fraction of an inch at 900 to 925°C (1650 to 1695 OF); quenching is in water Solution Heat Treating. All annealing of this alloy is a solution treatment Aging. Maximum strength is obtained with 3 to 6 h at 425°C (795 "F), Commercial practice:2 to 3 hat 480°C (900 "F). Result is combinationof high strength and electrical conductivity Hot Working. Temperature range is from 750 to 925 °C (1380 to 1695 OF) Hot shortness temperatureis 975°C (1785 OF)
C17600: Typical mechanical properties and electrical conductivity heat treated to various tempers 'Thmper(a) Rod, bar, wire, tubing, plate TBOO H04 TRIO lH04 Billet As-cast Cast andaged TBOO TRIO Forged products TBOO TRXl
'Thnsile strength MPa ksi
Yield streogtb at 0.2% offset MPa lui
Electriall condnctMty,
Elongation in50 mm(2iu.),%
Hardness, HRB
%IACS
240-380 45().550 690-825 76().9OO
35-55 65-80 10().120 110-130
140-205 38()'515 550-690 690-825
20-30 55-75 80-100 100-120
20-35 1()'15 10-25 10-20
20-50 60-80 92-100 95-102
20-30 20-30 45-60 50-60
31()'415 415-515 275-345 655-760
45-60 6().75 40-50 95-110
105-240 205-380 69-115 515-550
15-35 30-55 10-17 75-80
15-25 10-20 20-40 3-15
60-65 65-90 10-45 92-100
32-37 40-50 22-28 50-60
140-205 20-30 550-690 80-100
20-35 10-25
25-45 92-100
20-30 50-60
240-380 35-55 69()'825 10().120
(a)ForTBOO temper:solutiontreatstrip,bar, rod, andtubing 10 min at 900 to 955°C (1650 to 1750 "F) andwaterquench:solutiontreatthicker productssuch as billet 1h for each 25 mrn (1 in.)of thickness or fractionthereofat 900 to 925°C (1650 to 1695 "F) andwaterquench.For agingcast billetsor producingTFOO temper,age 3 h at 470 to 500 °C (880 to 930 oF). For producinglH04 temper,age 2h at 470 to 500 °C (880 to 930 oF)
C18100 (99Cu-0.8Cr-0.16Zr-0.04Mg) Chemical Composition. Composition Limits. 0.40to 1.20Cr,0.050to 0.30 Zr, 0.030 to 0.060 Mg
Characteristics Typical Uses. Resistance welding electrodes and wheels, switches, circuit breakers,high-temperature wire, semiconductorbases, heat sinks, and continuous casting molds
Formability. Rating for both cold and hot forming is excellent Joining. Solderabilityis excellent; brazeabilityand weldabilitywith gasshielded arc method are rated good. Butt resistance welding is fair. Not recommended: oxyacetylene,spot, and seam resistance welding
Recommended Heat Treating Practice Annealing. Temperature range is 600 to 700°C (1110to 1290 OF)
324/ Heat Treater's Guide: Nonferrous Alloys Solution Heat Treating. Temperature range is 900 to 975°C (1650 to 1785 "F) for 1 h
C18l00: Nominal mechanical properties of strip and wire
Aging. Temperature range is 400 to 500°C (750 to 930 OF) for 1 h
'Thmper
Hot Working. Temperature range is 790 to 925°C (1455 to 1695 "F)
Strip
10wIIe st",ngth ksi MPa
Yleldst_gth MPa ksi
Elongation in (Zin.), 'J>
Cold worked (40% reduction) Cold worked (40% reduction), aged
460 495
67 72
430 455
62 66
6 10
WIre Cold worked (60% reduction) Cold worked (60% reduction), aged Cold worked (75% reduction) Cold worked (75% reduction), aged Cold worked (90% reduction) Cold worked (90% reduction), aged
480 515 495 550 500 585
70 75 72 80 73 85
435 470 455 475 455 515
63 68
11
6
66
5 12 4
75
13
66
69
Hardness, HRB
80
C18200,C18400,C18500(99Cu·1C~ Commercial Names. Previous trade name, CA182, CA184, CA185; Chrome copper 999 (CI8200); Common name. Chromium-copper
Aging. Temperature range is 425 to 500°C (795 to 930 "F) for 2 to 4 h Hot Working. Temperature range is 800 to 925°C (1470 to 1695 "F)
Chemical Composition. Composition Limits (C18200). 0.60 to 1.20 Cr, 0.10 Fe max, 0.10 Si max, 0.05 Pb max, 0.50 others max (total), bal Cu +Ag Composition Limits (C18400). 0.40 to 1.20 Cr, 0.7 Zn max, 0.15 Fe max, 0.10 Si max, 0.05 Pmax, 0.05 Li max, 0.005 As max, 0.005 Ca max, 0.20 others max (total), bal Cu + Ag Composition Limits (C18500). 0.40 to 1.00 Cr, 0.08 to 0.12 Ag, 0.04 P max, 0.04 Li max, 0.015 Pb max, bal Cu + Ag Specifications (U.S. and/or Foreign). ASTM. Wire: F9; SAE. J463 (C18400 only); Government. Bar, forgings, rod, strip: MIL-C-19311 (CI8400, C18500)
C18200, C18400, and C18500: Typical mechanical properties 'Iemper
10nsilest",ngth MPa ksl
Yieldst",ngth(a) ksi MPa
Elongation in SO mm(Zin.). 'J>
Banlness, HRB
16 59
Flat products,l mm (0.04 ln.) thick
TBoo
235 350 365 460-
34 51 53 67
130 250 350 405
19 36 51 59
40 22 6 14
79
400
58
290
42
25
70
385
56
275
40
30
68
510 595 Rod,13 mm (0.50 In.) diameter
74 86
505 530
73
77
5 14
TBoo
45 70 57 77 77
97 380 385 450 460
14 55 56 65 67
40 21
16 19
70 65 82 83
72
450
65
18
80
TFOO
485 Rod, 75 mm (3.0 ln.) diameter
70
450
65
18
75
TFOO
450 Rod,l00 mm (4.0 in.) diameter
65
380
55
18
70
TFOO
55
295
43
25
68
TFOO(b) 1D04 lH04(c)
66
Plate, 50 mm (2.0 in.) thick
Characteristics Typical Uses. For applications requiring combination of excellent cold workability and good hot workability, coupled with medium-to-high conductivity. Uses include resistance welding electrodes, seam welding wheels, switch gears, electrode holders, cable connectors, current carrying arms and shafts, circuit breaker parts, molds, spot welding tips, flash welding tips, electrical and thermal conductors requiring more strength than that provided by unalloyed coppers, and switch contacts Machinability. 20% that of C36000 (free-cutting brass) Formability. Suited for hot working by extrusion, and forging (subsequent solution treatment required), and suited for cold working (in soft, solution annealed or drawn temper) by drawing, rolling, impacting, heading, bending, or swaging Joining. Properties developed in heat treatment are lowered by welding and brazing temperatures; such processes normally applied to material in soft condition, followed by necessary heat treatment. Soldering properties are good. Not recommended: oxyfuel gas, shielded metal arc, resistance spot, and resistance seam welding
TFOO Plate,75 mm (3.0 ln.) thick
TFOO
Rod: 4 mm (0.156 In.) diameter
mos
lH08
TFOO(b) 1D04 lH04(c) lH03, cold worked 6%
310 485 395 530 530
11
Rod,25 mm (1.0 ln.) diameter
TFOO
495
Rod, 50 mm (2.0 in.) diameter
380
Thbe, 9.5 mm (0.375 in.) outside dlameter x 2.4 mm (0.09410.) wallthickoess
060
275
40
105
15
50
59HRF
Thbe, 31.8 mm (1.25 in.) outside dlameter x 5.4 mm (0.212 fn.) wallthlekness
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 980 to 1000 °C (1795 to 1830 "F) for 10 to 30 min; quenching is in water
T004 lH04, cold-worked 28%
405 475
59 69
395 435
57 63
21 26
67 84
(a) At 0.5% extension under load. (b) Aged 3 h at 500 °C (930 oF). (e) Aged 3 h at 450°C (840 oF)
Wrought Copper /325
C18200: Microstructure. Chromium copper, 0.8% Cr, solutionized 5 min at 1010 °C (1850 OF). Solutionizing increases solubility of chromium, which gives higher hardness after quenching and aging. However, if all chromium goes into solid solution, uncontrolled grain growth results, starting where there is the most cold work before heat treatment (right). Excessive grain growth embritties grain boundaries; temperature, chromium content, cold work, and time at temperature must be controlled to prevent complete solution of chromium and uncontrolled grain growth. 0.45x
0.46
0.58 ~ 0
E
::I
·s.
0.75
0
.c::
(J
0.95
1.18 0.5
10
15
20
30
Percent reduction before heat treatment
C18700 (99Cu",1 Pb) Commercial Names. Previous trade name. Leaded copper; Common name. Free-machining copper
Joining. Solderability is excellent; brazing is good. Not recommended: most arc, gas, and resistance welding processes
Chemical Composition. Composition Limits. 0.80 to 1.50 Pb, 0.10 other max (total), bal Cu. Oxygen-free grades are those containing deoxidizers (such as P, B, or Li) may be specified
Recommended Heat Treating Practice
Specifications (U.S. and/or Foreign). ASTM. Flat product, rod: B 301; SAE. Rod J463
Annealing. Temperaturerange is 425 to 650°C (795 to 1200 "F) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 "F)
Characteristics Typical Uses. Electrical connectors, motor parts, switch parts, and screw machine parts requiring high conductivity. Caveats: unless specifically deoxidized, alloy is subject to embrittlement when heated in a reducing atmosphere (as in annealing or brazing) at temperatures of350 °C (660 "F) or above. If hydrogen or carbon monoxide is present, embrittlement can be rapid Machinability. 85% that ofC36000 (free-cutting brass) Formability. Cold working properties are good; those for hot forming, poor
C18700: Typical mechanical properties of rod, H04 temper Diameter mm
in.
6 13 19 25
0.25 0.50 0.75 1.0
Tensilestrength MPa ksi
415 380 365 350
60 55 53 51
Yieldstrength MPa ksi
380 345 330 315
55 50 48 46
Elongotion in 50mm (2 ln.), %
Hardness, HRB
10 11 12 14
55 50 50 50
Shear strength MPa ksi
200 205 200 195
32 30 29 28
C19200 (98..97Cu",1 ..0Fe",O..03P) Chemical Composition. Composition Limits. 98.70 to 99.19 Cu, 0.80 to 1.20 Fe, om to 0.04 P Specifications (U.S. and/or Foreign). ASTM. Tubing: Bill, B 359, B 395, B 469
Characteristics TYpical Uses. Rolled strip and tubing for air conditioning and heat exchanger tubing, applications requiring resistance to softening and stress corrosion, automotive hydraulic brake lines cable wrap, circuit breaker components, contact springs, electrical connectors and terminals, eyelets, flexible hose, fuse clips, gift hollowware, lead fumes Machinability. 20% that of C3600Q (free-cutting brass)
326/ Heat Treater's Guide: Nonferrous Alloys Forgeability. 65% that of C37700 (forging brass)
C19200: Typicalmechanical properties
Joining. Soldering, brazing, and gas-shielded arc welding properties are excellent. Oxyacetylene welding properties are rated good. Not recommended: coated metal are, resistance seam, spot, and butt welding
Recommended Heat Treating Practice Annealing. Temperature range is from 700 to 815°C (1290 to 1500 OF) Hot Working. Temperature range is from 825 to 950°C (1520 to 1740 oF)
Temper
Yieldstrength Al 0.5% exleusion At 0.2% offsel under load MPa ksl MPa ksi
Tensile strength MPa ksi
Eiongalion in SOmm (Z ta), %
Hardness,
25 min 20 9 7 3 2min 2 min
38 55 55 72 75 76 77
HRB
Strip, 1 mm (0.04 in.) diameter
060 082 H02 H04 H06 H08 HI0
310 395 395 450 485 510 530
45 57 57 65 70 74 77
140 min 20 min 305 44 44 305 60 415 460 67 490 71 510 74
...
Thblng, 48 mm (1.88 ln.) outside diameter x 3 mm (0.12 ln.) wall thickness 050 290 42 160 23 150 22 30 060 255 37 83 12 76 11 40 H80(4O%) 385 56 360 52 360 52 7 Thbing,5 mm (0.19 in.) outside diameter x 0.8 mm (0.03 in.) wall thickness
H55
290
42
215
31
205
30
35
C19210 (99.87Cu-O.1 Fe-O.03P) Chemical Composition. Composition Limits. 0.05 to 0.15 Fe, 0.025 to 0.04 P, bal Cu
Characteristics
Recommended Heat Treating Practice Annealing. Temperature range is 450 to 550°C (840 to 1020 "F) Hot Working. Temperature range is 700 to 900 °C (1290 to 1650 "F)
Typical Uses. Air conditioning and heat exchanger tubing, lead frames, electrical connectors, and terminals
Machinability. 20% that of C36000 (free-cutting brass)
C19210: Nominal tensile properties of sheet
Formability. Both cold and hot forming properties are excellent
Temper
Tensilestrength ksi MPa
Yield51rength ksi MPa
Joining. Soldering, brazing, and coated metal arc welding properties are rated excellent. Butt, resistance and oxyacetylene welding properties are good. Not Recommended: gas shielded are, spot and seam resistance welding
HOI H02 H04 H08
345 390 440 490
330 385 435 480
50 57 64 71
48 56 63 70
Elongation in SOmm(Zln), %
13 6 4 2
C19400 (Cu-2.35Fe-O.03P-O.12Zn) Commercial Names. Previous trade name. High-strength, modified copper, HSM copper
rivets; welded condenser tubes; semiconductor lead frames, and cable shielding
Chemical Composition. Composition Limits. 2.10 to 2.60 Fe, 0.05
Machinability. 20% that of C36000 (free-cutting brass)
to 0.20 Zn, 0.015 to 0.15 P, 0.03 Pb max, 0.03 Sn max, 0.15 others max (total), bal Cu
Specifications (U.S. and/or Foreign). ASME. Weldedtubing:SB543; ASTM. Flat products: B 465, welded tubing: B 543, B 586
Characteristics Typical Uses. Where requirement calls for excellent cold and hot workability, plus high strength and conductivity. Applications include circuit breaker components, contact springs, electrical clamps, springs, and terminals; flexible hose, fuse clips, gaskets; gift hollowware, plug contacts;
Formability. Alloy may be formed by blanking, coining, coppersrnithing, drawing, bending, heading, and upsetting; hot forging and pressing; piercing and punching; roll threading and knurling; shearing, spinning, squeezing, and stamping Joining. Soldering, brazing, and gas tungsten arc welding properties are excellent
Recommended Heat Treating Practice Annealing. Appropriate temperatures are found in adjoining Table
Wrought Copper I 327 C19400: Typical mechanical properties Yield strenglb at 0.2% olfset MPa ...1
Tensilestrength Temper
MPa
ksi
Flat products, 0.64 mm (0.025 In.) thick 060 310 050 345 082 400 Flat products, 1 mm (0.04 in.) thick H02 400 H04 450 H06 485 H08 505 Hl0 530 H14 550 min
Elongafion in SO mm (2 In.), %
HRB
45 50 58
150 max 160 255
22 max 23 37
29 min 28 15
38 45
58 65 70 73 77 80 min
315(d) 380 465 486 507 530 min
46(d) 55 67.5 70.5 73.5 77 min
18 7 3 3 2 max 2 max
68 73 74 75 77
165 205 365 435 465 486 505 380 455
24 30 53 63 67.5 70.5 73 55 66
28 16 9 4 3 2 1 9 2
Thbing, 25 mm (1 in.) outside diameter x 0.9 mm (0.035 in.) wall thickness 060 310 45 050 345 50 WM02 400 58 WM04 450 65 WM06 485 70 WMOB 505 73 WMlO 525 76 H55(15%) 400 58 H80(35%) 470 68
Faligue strengtb(a) MPa ksi
HR30T
66 69 71 72 74 >73
38 45 61 73 74 75 76 61 73
110
16
145
21
148 141
21.5 20.5
60 66 68 69 69 60 66
8
(a) At 10 cycles as detennined by therotating-beamtest
C19400: Typical elevated-temperature properties of annealed strip Testlempernture OF °C
Te... iIe strength, min MPa ksi
Ambient 65 95 120 150 175 205 230 260 290 315
341 324 313 300 289 276 266 253 235 219 203
150 200 250 300 350 400 450 500 550 600
49.5 47.0 45.4 43.5 41.9 40.1 38.6 36.8 34.1 31.8 29.5
Yieldstrengtb at 0.2%olfset, min MPa
ksi
150 144 144 144 139 135 131 131 127 123 116
22.0 20.9 20.9 20.9 20.2 19.6 19.0 19.0 18.4 17.8 16.8
Stress-rupture stress, mln(b) MPa ksl
Creep strengtb, mln(a) MPa ksi
190 171 143 124 110 96 84 74
27.6 24.8 20.8 18.0 16.0 13.9 12.2 10.8
171 148 125 105 82 65 47
24.9 21.4 18.1 15.2 11.9 9.4 6.8
(a) Stresscausingsecondarycreep of0.01% per 1000h in a 10,OllO-h test. (b) Stresscausingrupture in 100,000h (extrapolatedfrom 10,000h)
C19400: Typical room-temperature and low-temperature (cryogenic) properties Temper
Tensile strengtb ksi MPa
Room-temperature properties 061 47 325 H02 405 59 H04 66 455 Cryogenic properties: -196°C (-320°F) 061 475 69 H02 570 83 H04 615 89
YIeld strength at 0.2%olfset MPa ksi
Elongation In SOmm(21n.), %
170 360 405
25 52 59
28 15 10
195 425 485
28 62 70
38 30 23
C19400: Annealing response of strip Annealing
temperature OF OC
H04temper 100 212 205 400 315 600 370 700 425 800 480 900 540 1000 595 1100 650 1200 705 1300 760 1400 815 1500 HI0temper 100 212 205 400 315 600 370 700 425 800 480 900 540 1000 595 1100 650 1200 705 1300 760 1400 815 1500
Tensllestrength MPa ksi
YIeld strength at Elongation In 0.2%olfset SOmm(21n.), % MPa ksi
Electrical
conductlvily, %IACS
460 450 440 415 415 400 385 350 315 310 305 305
67 65 64 60 60 59 56 51 46 45 44 44
450 435 415 385 360 345 310 220 140 115 110 110
65 63 60 56 52 50 45 32 20 17 16 16
3 5 9 12 14 16 17 23 33 34 36 36
64(a) 52 51 49 48 48
510 495 485 330 325 315 315 310 305 295 290 285
74 72 70 48 47 46 46 45 44 43 42 41
490 460 415 170 145 140 140 130 130 115 110 105
71
3 5 8 25 27 28 31 33 34 34 35 35
65 66 67 71 74 69 64(a) 58 52 49 48 48
67 60 25 21 20 20 19 19 17 16 15
66 67 68 68 72 71
(a) Conductivitymaybe restoredto about70% lACS by holdingat 500 °C (930 "F) for I h
328/ Heat Treater's Guide: Nonferrous Alloys
C19500 (97Cu-1.5Fe-0.1 P-0.8Co-0.6Sn) Trade Name. Strescon
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 1.30 to 1.70 Fe, 0.6
Annealing. Temperature range is from 375 to 600°C (710 to 1110 OF)
to 1.00 Co, 0.08 to 0.12 P, 0.40 to 0.70 Sn, 0.20 Zn max, 0.02 AI max, 0.02 Pb max, 0.05 others max (each), 0.10 others max (total), bal Cu
Characteristics
C19500: Typical mechanical properties Yieldstrength
Typical Uses. Applications are in two categories: (1) Parts requiring a combination of strength and exceptional resistance to softening, such as electrical springs, sockets, terminals, connectors, clips, and other currentcarrying parts. (2) Parts requiring excellent cold and hot workability, high strength, and high conductivity .
Machinability. 20% that of C36000 (free-cutting brass)
ThnsUe strength 1<51 MPa
Thmper
061 050 H02 H08 HIO
360 min 520-590 565-620 605-670 670 min
MPa
ksl
ElongationIn 50 mm (1 IlL), '.{,
Hardness, HRB
170min 395-530 505-605 585-650 650 min
25 min 57-77 73-88 85-94 94 min
25 min 11-17 3-13 2-5 2 max
81-89 85-88 87-90 90 min
atO.1'.{,0&1
52min 75-85 82-90 88-97 97 min
Formability. Alloy is suited to forming by bending, drawing, coining, and stamping
C19700 (99.15Cu-0.6Fe-0.2P-0.05Mg) Chemical Composition. Composition Limits. 0.30 to 1.20 Fe, 0.10 to 0.40 P,0.2 Sn and Zn (each, max), 0.05 Co, Mn, Ni, and lead (each, max), 99.8 Cu + named elements min
Characteristics
Recommended Heat Treating Practice Annealing. Temperature range is from 450 to 600°C (840 to 1110 "F) HotWorking. Temperature range is from 750 to 950 °C (1380 to 1740 oF)
Typical Uses. Generally suited for parts requiring excellent formability, combined with high strength and conductivity. Examples: electrical and electronic connectors, circuit breaker components, fuse clips, cable sheathing, and lead frames
C19700: Nominal mechanical properties of strip
Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold and hot forming properties are excellent Joining. Soldering and brazing properties are excellent
Elongation in 50 mm
'Iemper
ThnsUe strength MPa 1<51
MPa
1<51
(:!ilL). '.{,
Hardn.... HRB
H02 H04 H06 H08
380 450 480 500
315 415 470 490
46 60 68 71
10 6 3 2
68 70 73 75
55 65 70 73
YIeld strength
C21000 (95Cu-5Zn) Commercial Names. Previous trade name. Gilding metal, 95%; CA210
Crystal Structure. Face centered, cubic alpha
ChemicalComposition. Composition Limits. 94.00 to 96.00 Cu, 0.05 Pb max, 0.05 Fe max, bal Zn. (See adjoining Figure for effect of Zn content on properties.)
Machinability. 20% that of C36000 (free-cutting brass)
Specifications (U.S. and/or Foreign). ASTM. Rolled bar, plate, sheet, and strip: B 36. Wire: B 134; SAE. J463; Government. Wire: QQ-W-321. Sheet and strip: MIL-C-21768
Recrystallization. Temperature is 370°C (700 oF) for 50% reduction and 0.015 to 0.070 mm initial grain size. (See adjoining Figure showing variation in tensile strength with annealing temperature.)
Characteristics Typical Uses. Coins, metals, tokens, bullet jackets, ftring pin supports, shells, fuse caps and primers, emblems, jewelry plaques, base for gold plate, base for vitreous enamel
Recommended Heat Treating Practice
Annealing. Temperature range is from 425 to 800°C (795 to 1470 "F) HotWorking. Temperature range is from 750 to 875 °C (1380 to 1610 oF)
Wrought Copper /329
C21000: Typicalmechanical properties 'IIm,lIestrength MPa ksi
Thmper
05050 anneal (0.050mrngrainsize) 05035 anneal (0.035mrn grainsize) 05015 anneal (0.015mrn grainsize) Quarterhard Halfhard Hard Extrahard Spring
34 35 38 42 48 56 61 64
235 240
260 290 330 385 420 440
69 76 97 220 275 345 380 400
46HRF 52HRF 60HRF 38 :;2 64 70 73
45 45 42 25 12 5 4 4
10 11 14 32 40 50 55 58
Shear strength MPa ksI
Hardoeu HRB HR30T
ElongationIn 50mm!% In.). '.l>
Yieldstrength!a) MPa ksI
4 15 44 54 60 64 66
28 30 32 34 37 39 40
195 205 220 235 255 270 275
Note: Values for flatproducts.1 mrn(0.04 in.)thick.(a)At 0.5% extensionunderload
LIVE GRAPH Click here to view
C21000: Properties. Variation of propertieswith zinc contentfor wroughtcopper-zincalloys
LIVE GRAPH Click here to view
700
.
45
80
100 90
600
40
70 80
Q.
~
£500 C,
70
c:
o
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;g Cl
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E
E
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'iii c:
< ~
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60
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-g 0
:I:
50 {!!.
{!!.
(/)
30
U
50 25
300 40 200 80
40 100
30
60 40 20 80 Reduction of area by drawing, %
Hardness, cold drawn tempers
Elongation
100
22
060 temper 90
12.0 ~
~
;J!.
c0
~::l.
00
~
a: 80
Cl
:I:
0
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21
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c:
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u>
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u>
19
10.5
0
c
40
20 30 Zinc content, %
c:
.
tl 18
10.0 1ii
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E
LIVE GRAPH Click here to view 50 Cu 9.0
4.0
8.8
3.8
'"E
.!:! Cl
i-
'iii c: Q) 0
::>
8.6
3.6
0
~ 0
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8.4 \
Density and velocity of sound 8.2 Cu
10
30 20 Zinc content, %
40
3.4 ..Q Q) \
>
\
3.2 50
30
Cu
40
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40
330 I Heat Treater's Guide: Nonferrous Alloys
Annealing temperature, OF
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400
600
800
1000
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C21000: Tensile strength. Variation of tensile strength with annealing temperature. Data are for 1 mm (0.04 in.) thick ready-to-finish strip that was cold rolled 50% then annealed 1 h at the indicatedtemperature. Recrystallization temperature, 370 °C (700 OF) for initial grain sizes of 0.015 to 0.070 mm
400
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Annealing temperature, °C
C22000 (90Cu-10Zn) Commercial Names. Previous trade name. Commercial bronze, 90%;
Characteristics
CA220
Typical Uses. Architectural: etching bronze, grillwork, screen cloth,
Chemical Composition. Composition Limits. 89.00 to 91.00 Cu,
weather stripping. Hardware: escutcheons, kickplates, line clamps, marine hardware, rivets, screws, screw shells. Munitions: primer caps, rotating bands. Miscellaneous: compacts, lipstick cases, costume jewelry, ornamental trim, screen wire, base for vitreous enamel, waveguides
0.05 Pb max, 0.05 Fe max, bal Zn. Note: see comments on consequences of impurity limits (for lead, aluminum, arsenic, cadmium, chromium, iron, nickel, and phosphorus in article on C26000.) For effect of zinc content on properties, see Figure in article on C21000
Machinability. 20% that of C36000 (free-cutting brass)
Specifications (U.S. and/or Foreign). ASTM. Rolled bar, plate, and
Crystal Structure. Face-centered, cubic alpha
sheet: B 36. Strip: B 36 and B 130. Cups, bullet jackets: B 131. Tube, rectangular waveguide: B 372. Seamless tube: B 135. Wire: B 134; SAE. Rolled bar; plate, sheet, strip, and seamless tube: J463 (CA220); Government. Wire: QQ-W-321; MIL-W-6712. Bands, rotatingprojectile: MIL-B18907. Blanks, rotating bands for projectiles: MIL-B-20292. Cups, bullet jackets: MIL-C-3383. Sheet and strip: MIL-C-21768. Tubing, rectangular waveguides: MIL-W-85. Seamless tubing for microwave usage: MIL-T52069
Recommended Heat Treating Practice Recrystallization. Temperature is 370 °C (700 oF) for 37% reduction and 0.050 mm (0.002 in.) initial grain size. (See adjoining Figure concerning variations in tensile strength and grain size with annealing temperature.) Annealing. Temperature range is 425 to 800 °C (795 to 1470 oF) Hot Working. Temperature range is 750 to 875 °C (1380 to 1610 oF)
Annealing temperature, OF
500 (721
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C22000: Tensile strength. Variation of tensile strength and grain size with annealing temperature. Data are for rod less than 25 mm (1 in.) in diameter that was cold drawn to a 37% reduction in area and then annealed 1 h at the indicated temperature. Grain size before annealing was 0.050 mm
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Next Page
Wrought Copper /331
C22000: Typical mechanical properties
Thmper
Yield
ThMiIe strength MPa ksi
strengthen) MPa ksl
255 260 270 280 310 360 420 460 495 270
37 38 39 41 45 52 61 67 72 39
69 83 97 105 240 310 370 400 425 97
10 12 14 15 35 45 54 58 62 14
45 45 44 42 25 11 5 4 3 44
53 57 60 65 42HRB 58HRB 70HRB 75HRB 78HRB 60
260 360 255
38 52 37
83 310 69
12 45 10
50 15 45
57 58HRB 53
275 290 305 345 415 510 570 620
40 42 44 50 60 74 83 90
Hardness IIRF HRJOT
Eioogalion in SOmm(210.), %
Shear strength MPa ksi
Flat products,l mm (0.040 ln.) thick 05050 05035 05025 05015 HOI H02 H04 H06 H08 M20
19~
6 12 16 26 44 56 63 67 69
205 215 220 230 240 260 275 290 215
28 30 31 32 33 35 38 40 42 31
205 240 195
30 35 28
205 220 230 235 255 290
30 32 33 34 37 42
220 230
32 33
Flat products, 6 mm (0.250 ln.) thick 05035 H02 M20 Wire,2 mm (0.080 in.) diameter 05035 05015 HOO HOI H02 H04 H06 H08
50 48 27 13 6 4 3 3
Thbing, 25 mm (1 in.) outside diameter x 1.65 mm (0.065 in.) wall thickness 05025 H8O(b)
260 415
38 60
275 310
40 45
83 365
12 53
50 6
57 69HRB
50 25
55 42HRB
12 62
Rod, n.7 mm (0.500 in.) diameter 05035 HOO
(a) AtO.5% extension underload. (b) Drawn35%
C22600 (87.5Cu-12.5Zn) Commercial Names. Previous trade name. Jewelry bronze, 87.5%; CA226; Common name. Jewelry bronze
C22600: Typicalmechanical properties
Chemical Composition. Composition Limits. 86.00 to 89.00 Cu,
'Iemper
Thnslle strenglh ksl MPa
Yieldstrengthen) MPa ksi
Eiongnlion in SOmm(21o.),%
Hardness
55HRF 59HRF 64HRF 68HRF 47HRB 61HRB 73HRB 78HRB 82HRB
200 205 215 220 235 250 275 290 305
29 30 31 32 34 36 40 42 44
70HRB
200 205 215 220 235 250 275
29 30 31 32 34 36 40
Shear strength MPa ksI
0.05 Pb max, 0.005 Fe max, bal Zn Flat products, 1 mm (0.04 in.) thick
Characteristics Typical Uses. Architectural: angles, channels. Hardware: chain, eyelets, fasteners, slide fasteners. Novelties: compacts, costume jewelry, emblems, etched articles, lipstick containers, plaques, base for gold plates Machinability. 30% that of C36000 (free-cutting brass)
Recommended Heat Treating Practice Recrystallization. Temperature is about 330°C (625 OF) for 1 mm (0.04 in.) strip rolled to six Brown and Sharpe numbers hard from a 0.035 mm (0.001 in.) grain size. (Also see adjoining Figure.)
Annealing. Temperature range is 425 to 750°C (795 to 1380 OF) Hot Working. Temperature range is 750 to 900 °C (1380 to 1650 OF)
05050 05035 05025 05015 HOI H02 H04 H06 H08
270 275 290 305 325 370 455 495 545
39 40 42 44 47 54 66 72 79
76 90 105 110 255 325 385 415 425
11 13 15 16 37 47 56 60 62
46 45 44 42 25 12 5 4 4
90 105 115 125 240 360 415 440 450 455
13 15 17 18 35 52 60 64 65 66
44 42 40 38 26 12 7 5 4 3
Wire, 2 mm (0.08 in.) diameter 05050 05035 05025 05015 HOO HOI H02 H04 H06 H08
275 285 295 310 325 385 470 570 615 670
40 41 43 45 47 56 68 83 89 97
(a) At 0.5% extensionunderload
Previous Page 332/ Heat Treater's Guide: Nonferrous Alloys
Annealing temperature, OF
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C22600: Annealing characteristics. Data are for jewelry bronze strip with an initial grain size of 0.035 mm that was cold rolled 50% to a thickness of 1 mm (0.04 in.) and annealed 1 h at various temperatures
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C23000 (85Cu-15Zn) Commercial Names. Previous trade name. Red brass, 85%; CA230; Common name. Red brass Chemical Composition. Composition Limits. 84.00 to 86.00 Cu, 0.06 Pb max, 0.05 Fe max, bal Zn. (See comments in article on C26000 for consequences of exceeding impurity limits. See article on C22000 for Figure showing variance in properties due to.zinc content.) Specifications (U.S. and/or Foreign). ASME. Pipe: SB43. Condenser tubing: SBlll. Finned tubing: SB359. U-bend tubing: SB395; ASTM. Plate, sheet, strip, hot-rolled bar: B 36. Pipe: B 43. Condenser tubing: B 111. Finned tubing: B 359. Seamless tubing: B 135. U-bend tubing: B 395. Wire: B 134; SAE. Sheet, strip, seamless tubing: J463 (CA230); Government. Bar, forgings, rod, shapes, strip: QQ-B-626. Plate, sheet, strip, hot-rolled bar: QQ-B-613. Pipe: WW-B-351. Seamless tubing: WW-T-791;MIL-T-20168. Wire: QQ-W-321
Characteristics Typical Uses. Architectural: etching parts, trim, weather strip. Electrical: conduit, screw shells, sockets. Hardware: eyelets, fasteners, fire extinguishers. Industrial: condenser and heat exchanger tube, flexible hose, pickling crates, pump lines, radiator core. Plumbing: plumbing pipe, Jbends, service lines, traps. Miscellaneous: badges, compacts, costume jewelry, dials, etched articles, lipstick containers, nameplates, tags Machinability. 30% that of C36000 (free-cutting brass)
Recommended Heat Treating Practice Recrystallization. Temperature is about 350°C (660 OF) for I mm (0.04 in.) sheet rolled six Brown and Sharpe numbers hard with a 50% reduction and 0.035 mm (0.001 in.) initial grain size Annealing. Temperature range is 425 to 725°C (795 to 1335 OF). See adjoining Figure on annealing characteristics Hot Working. Temperature range is 800 to 900 °C (1470 to 1650 OF)
C23000: Typical mechanical properties Thnsile Thmper
stnmgth MPa ksl
YIeld strength(a) MPa ksl
Flat products, 1 mm (0.040 In.) thick 270 39 69 10 275 40 83 12 285 41 97 14 295 43 110 16 310 45 125 18 345 50 270 39 340 49 395 57 485 70 395 57 420 61 540 78 580 84 435 63 (0.08 in.) diameter 285 41 43 295 310 45 345 50 405 59 495 72 605 88 725 105
05070 05050 05035 05025 05015 HOI H02 H04 H06 H08 Wire, 2 mm 05035 05025 05015 HOO HOI H02 H04 H08
Elongation in SO mm (210.),'Jp
48 47 46 44 42 25 12 5 4 3
HanIneso HRF IIR30T
56 59 63 66
10 14 22
28
71
38
55HRB 65HRB 77HRB 83HRB 86HRB
54 60 68 72 74
48
25 11 8 6
Thbing, 25 mm (1 ln.) outside diameter x 1.65 mm (0.065 in.) wall tbickness 05050 275 40 83 12 60 15 55 05015 305 44 125 18 45 71 38 H55(15%) 345 50 55HRB 54 275 40 30 H80(35%) 485 70 365 53 8 77HRB 68 Pipe, 19 mm (0.75ln.) SPS 05015 305 44 125 18 71 45 (a) At 0.5% extension under load
Shearlilrength MPa ksl
215 215 215 220 230 240 255 290 305 315
31 31 31 32 33 35 37 42 44 46
215 220 230 240 260 295 330 370
31 32 33 35 38 43 48 54
Wrought Copper /333
C23000: Annealing characteristics. Data are for 1 mm (0.04 in.) thick red brass sheet, H06 temper, annealed 1 h at various temperatures
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C23000: Creep rates. Minimum creep rates for C23000 wire. Data are for red brass wire, 3.2 mm (0.125 in.) in diameter, that was cold drawn to size, then tested in the as-drawn or annealed condition
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334/ Heat Treater's Guide: Nonferrous Alloys
C24000 (80Cu-20Zn) Commercial Names. Trade name. Low brass, 80%; CA240; Common name. Low brass
C24000: Typical mechanical properties
Chemical Composition. Composition Limits. 78.50 to 81.50 Cu, 0.05 Pb max, 0.05 Fe max, bal Zn
Thmper
Specifications (U.S. and/or Foreign). ASTM. Flat products: B 36. Wire: B 134; SAE. Sheet, strip: J463 (CA240); Government. Finished edge bar and strip, forgings, rod, and shapes: QQ-B-626. Rolled bar, plate, sheet, strip: QQ-B-613. Wire: QQ-W-321. Brazing alloy wire: QQ-B-650
Yield strength!u) MPu ksi
ThD5ile strength ksi MPu
E1ongution in 50rom!2 ln.), %
Hardness HRF HRJOT
Shearstrength ksi MPu
FIat products, 1 mm (0.040 in.) thick OS070 OS050 OS035 OS025 OS015 HOI H02 H04 H08
Characteristics Typical Uses. Ornamental metal work, medallions, spandrels, electrical battery caps, bellows and musical instruments, clock dials, flexible hose, pump lines, tokens
290 305 315 330 345 365 420 510 625
42 44 46 48 50 53 61 14 91
83 91 105 115 140 215 345 405 450
12 14 15 11 20 40 50 59 65
52 50 48 41 46 30 18 1 3
51 61 66 69 15 55HRB 10HRB 82HRB 91HRB
8 16 28 32 42 54 64 11 11
220
32
230 250 210 295 330
33 36 39 43 48
220
32
230 255 290 325 365
33 31 42 41 53
415
60
Wire, 2 mm (0.08 in.) diameter
Crystal Structure. Face-centered, cubic alpha
OS050 OS035 OS015 HOO HOI H02 H04 H06 H08
Machinability. 30% that of C36000 (free-cutting brass)
Recommended Heat Treating Practice Recrystallization. Temperature is about 400°C (750 OF) for 37% reduction and 0.060 mm (0.002 in.) initial grain size Annealing. Temperature range is 425 to 700°C (795 to 1290 OF). See adjoining Figure on tensile strength and grain size versus annealing temperatures
44 46 50 56 68 82 107 116 125
305 315 345 385 410 565 140 800 860
55 50 41 21 12 8 5 4 3
(a) AtO.5% extension under load
Hot Working. Temperature range is 825 to 900 "C (1520 to 1650 OF)
Annealing temperature, OF
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C24000:Tensile strength. Tensile strength and grain size versus annealing temperature for C24000 annealed from HC2 temper. Data are for low brass with an initial grain size of 0.060 mm that was cold drawn 37% to a diameter of less than 25 mm (1 in.) and annealed 1 h at the indicated temperature
700
0.040
o
800
Annealing temperature, °c
C26000 (70Cu-30Zn) Commercial Names. Previous trade name. Cartridge brass, 70%; CA260; Common name. Cartridge brass, 70-30 brass, spinning brass, spring brass, extra-quality brass
Chemical Composition. Composition Limits. 68.50 to 71.50 Cu, 0.07 Ph max, 0.05 Fe max, 0.15 others max (total), bal Zn (See article on C21000 for Figure showing effect of zinc content on variations in properties.)
Wrought Copper I 335 Magnetic Properties. Iron above 0.03% can precipitate from alloy during suitable, low temperature anneals. Precipitation is slow and occurs chiefly in nonmagnetic form, which is converted to ferromagnetic structure on subsequent cold working
Effects of other elements on properties are as follows:
• Lead. Content should be kept under 0.01 % for hot rolling. Additions up to 4% improves machinability of copper processed by extrusion and by cold working. Lead lowers room temperature ductility of brass, and it leads to hot shortness at temperature above 315°C (600 OF) • Aluminum. Levels as high as 2% have no adverse effect on cold or hot working properties, but annealing and grain size are affected • Arsenic. Does not affect cold or hot working, but tends to refme grain size, which lowers ductility • Cadmium. Effects not universally agreed upon. Some say as much as 0.10% has little effect. Others believe content should be held under 0.05% • Chromium. Affects annealing temperature and grain size. Condition is aggravated by presence of iron • Iron. Chiefly affects annealing and magnetic properties • Nickel. Restrains grain growth • Phosphorus. Has no adverse effect up to 0.04%; does restrain grain growth, increases tensile strength, and lowers ductility to some extent
General Corrosion Behavior. Resists corrosion in wide variety of coaters and chemical solutions; can undergo dezincification in slowly moving salt solutions. Susceptible to stress corrosion cracking, especially in ammonial environments Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working and forming properties are excellent, but only fair for hot forming. Directionality in brass is more readily developed with high zinc content. Earing usually occurs 45° to direction of rolling, and is aggravated by heavy final reductions, low ready-to-finish annealing temperatures, and high finish annealing temperatures Joining. Soldering and brazing properties are excellent, welding properties are good for oxyfuel gas, resistance spot, and resistance butt processes. Not recommended: other welding processes
Specifications (U.S. and/or Foreign). AMS. Flat products: 4505, 4507. Thbing: 4555; ASTM. .Flat products: B 19, B 36, B 569. Cups for cartridge cases: B 129. Thbing: B 135, B 587. Wire: B 134; SAE. J463; Government. Flat products: QQ-B-613, QQ-B-626, MIL-C-50. Rod, bar, shapes, forging: QQ-B-626. Thbing: MIL-T-6949, MlL-T-20219. Wire: QQ-W-321, QQ-B-650. Shim stock, laminated: MlL-S-22499. Cups for cartridge cases: MIL-C-10375
Annealing. Temperature range is 425 to 750°C (795 to 1380 "F)
Characteristics
Hot Working. Temperature range is 725 to 850 °C (1355 to 1560 oF)
Recommended Heat Treating Practice Recrystallization. Temperature is about 300°C (570 "F) for 0.045 mm (0.001 in.) initial grain size and a cold reduction of 50%
Typical Uses. Architectural: grillwork. Automotive: radiator cores and tanks. Electrical: lead chain, flashlight shells, reflectors, lamp fixtures, socket shells, screw shells. Hardware: eyelets, fasteners, pins, hinges, kickplates, locks, rivets, springs, starnpings, tubing, etched articles. Munitions: ammunition components, particularly cartridge cases. Plumbing: accessories, fittings. Industrial: pump andpower cylinders, cylinder liners. Caveat: alloy is highly susceptible to stress corrosion cracking in ammonial environments
C26000: Typicaltensile properties of cold-rolled and annealed sheet 1Onsil. strength MPH ksi
Direction In sbeet
ParallelloRD
330 305 325
45° to RD
48 44 47
EloogHUoo,
%
59 66 61
Crystal Structure. Face-centered cubic
90°to RD
Microstructure. Single phase alpha, with extensive pattern of annealing
Note:Approximatevaluesfor materialgivena ready-to-finish annealat 400 °C (750 "F), thencold rolled70% and annealed 1h at 575°C (1070oF). RD,rollingdirection
twins
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C26000: Tensile strength. Tensile strength and grain size as a function of annealing temperature for rod. Data are for cartridge brass rod less than 25 mm (1 in.) in diameter that was cold drawn 50% (from starting material having a grain size of 0.045 mm), then annealed 1 hat the indicated temperature
LIVE GRAPH Click here to view
336/ Heat Treater's Guide: Nonferrous Alloys
C26000: Tensile properties. Low-temperature tensile properties of C26000 rod, 061 temper
LIVE GRAPH
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C26000: Tensile properties. Typical distribution of tensile properties and hardness for C26000 strip, H01 temper. Data are for cartridge brass strip 0.5 to 1 mm (0.020 to 0.040 in.) thick
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Wrought Copper /337
C26000: Annealing data. Finish rolling reduction 40.6%
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400
500
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LIVE GRAPH 1000
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Temperature, °C
,/Tensile strength
Yield strength (2% offset)
Yield strength (1% offset)
~
1400
I
~6000
400
Temperature, of 600
800
1000
1200
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1200
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LIVE GRAPH 400
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Temperature, "C
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600
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Temperature, "C
C26000: Microstructure. Cartridge brass, annealed. Polarized light illumination was used to increase contrast of the microstructure.55x
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100
200
300
400
500
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600
700
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Temperature, "C
C26000: Microstructure. Cartridge brass, drawn cup. Because grains are small, cup has a smooth surface
338/ Heat Treater's Guide: Nonferrous Alloys
C26000.: Microstructure. Cartridge brass tube, drawn, annealed and cold-reduced 5%. Typical intergranular stress-corrosion crack, with some branching. NH 40H + H202 • 150x
C26000: Microstructure. Cartridge brass, showing a transgranular corrosion crack. Note the lack of branching in the inner (fatigue) section of the crack. 130x
C26000: Microstructure. Cartridge brass hot rolled to 10 mm (0.4 in.) thick, annealed to a grain size of 15 J.1m, cold rolled to 40% to 6 mm (0.24 in.) thick, and annealed to a grain size of 120 J.1m. Diagram in lower left corner of each micrograph indicates the view relative to the rolling plane of the sheet. Nominal tensile strength of 296 MPa (43000 psi). 75x
C26000: Microstructures. Cartridge brass, processed to obtain various grain sizes. Preliminary processing: hot rolled, annealed, cold rolled, annealed to a grain size of 25 urn, cold rolled to 70% reduction. Final anneal temperature gives difference in grain sizes. (a) Grain size is 5 J.1m; final annealed at 330°C (625 OF). (b) Grain size is 10 J.1m; final annealed at 370°C (700 OF). (c) Grain size is 15 J.1m; final annealed at 405°C (760 OF). (d) Grain size is 20 J.1m; final annealed at 425°C (795 OF). 75x
(a)
(b)
(c)
(d)
Wrought Copper I 339
C26000: Microstructure. Local plug-type dezincification (dark, at specimen surface) consists of a spongy mass of copper that resulted from the selective removal of zinc. 150x
C26000: Microstructure. Cartridge brass, cast, slowly cooled, and quenched. Primary dendrites aligned in <100> crystallographic directions. The fine, quenched structure has the same orientation as the coarse dendrites. 30x
C26800, C27000 (65Cu..35Zn) Commercial Name. Previous trade name. C26800: Yellow brass, 66%. C27000: Yellow brass, 65; Common name. Yellow brass
eyelets, fasteners, grommets, kickplates, push plates, stencils, plumbing accessories, sink strainers, wire, pins, rivets, screws, springs
Chemical Composition. Composition Limits (C26800). 64.00 to 68.50 ce, 0.15 Pb max, 0.05 Fe max, bal Zn
Crystal Structure. Face-centered cubic alpha
Composition Limits (C27000). 63,00 to 68.50 Cu, 0.10 Pb max, 0.07 Fe max, bal Zn. (See Figure in article on C21000 showing effect of zinc content on properties.)
Machinability. 30% that of C36000 (free-cutting brass)
Specifications (U.S. and/or Foreign). AMS. Wire: 4710,4712; ASlM. Flat products: B 26 (C26800). Tubing: B 135 (C27000), B 587 (C26800, C27000). Wire: B 134; SAE. J463; Government. Flat products: QQ-B-613. Bar, rod, forgings, shapes: QQ-B-626. Wire: QQ-W-321, MIL-W-6712
Characteristics Typical Uses. Architectural grillwork, radiator cores and tanks, reflectors, flashlight shells, lamp fixtures, screw shells, socket shells, bead chain,
Microstructure. Single phase alpha
Recommended Heat Treating Practice Recrystallization. Temperature is 290°C (555 OF) for strip rolled 50% to 1 mm (0.04 in.) thickness and having an initial grain size of 0.035 mm (0,002 in.) Annealing. Temperature range is 425 to 700°C (795 to 1290 OF). Maximum cold reduction between anneals is 90% Hot Working. Temperature range is 700 to 820 °C (1290 to 1510 "F)
340 I Heat Treater's Guide: Nonferrous Alloys
400
1000
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800
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600
800
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1200
~
700
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Annealing temperature, °C
Annealing temperature, of
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C27000: Effects of annealing temperature. Effects of annealing temperature and time on characteristics of C27000 wire and strip. Effects of annealing temperature (annealing time. 1 h) on (a) tensile strength, (b) grain size, and (c) elongation of C27000 wire hard drawn 63%. (d) Effect of annealing time on grain size of C27000 strip 1.3 mm (0.050 in.) thick
Annealing temperature, of
Annealing temperature, of
10
1
600 1000
100
c: c:
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Duration of annealing, min
LIVE GRAPH
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LIVE GRAPH Click here to view
C26800 and C27000: Typical mechanical properties 'Thnslle strength ksi
Yieldstrength!a) ksi
Elongation in 50mm!2Ia), %
Hardness HRF HR30T
'Thmper
MPa
Flat products, 1 mm (0.040 in.) thick 05070 05050 05035 05025 05015 HOI H02 H04 H06 H08 HIO
315 325 340 350 365 370 420 510 585 625 675
46 47 49 51 53 54 61 74 85 91 98
97 105 115 130 150 275 345 415 425 425 435
14 15 17 19 22 40 50 60 62 62 63
65 62 57 55 54 43 23 8 5 3 3
58 64 68 72 78 55HRB 70HRB 80HRB 87HRB 90HRB 91HRB
330 380
48 55
110 275
16 40
65(b) 48(e)
65
330 345 360 370 400 485 605 760 825 885
48 50 52 54 58 70 88 110 120 128
110 125 145 160 315 395 420
16 18 21 23 46 57 61
64 60 58 55 35 20 15 8 4 3
MPa
15 26 31 36 43 54 65 70 74 76 77
Shearrtreogth MPa
ksi
220 230 235
32 33 34 35 36 36 40 43 45 47
240 250 250 275 295 310 325
Rod, 2S mm (1.0 in.) diameter 05050 HOO!6%) Wire,2 mm (0.08 In.) diameter 05050 05035 05025 05015 HOO HOI H02 H04 H06 H08
(a) At 0.5% extension under load. (b) 75% reduction in area. (e) 70% reduction in area
...
235
34 36
230 235 240 250 290
33 34 35 36 38 42
380
55
415
60
55
260
Wrought Copper I 341
C28000 (60Cu..40Zn) Commercial Names. Previous trade name. Muntz metal, 60%; CA280; Common name. Muntz metal
ammonia peroxide; is dark when etched with ferric chloride. In grain size determination, beta phase should be ignored
Chemical Composition. Composition Limits. 59.00 to 63.00 Cu, 0.30 Pb max, 0.07 Fe max, bal Zn. (See Figure in article on C21000 showing effect of zinc content on properties.)
General Corrosion Behavior. Typically good. Has better resistance to sulfur-bearing compounds than that of higher copper alloys
Specifications (U.S. and/or Foreign). ASME. Condenser tubing:SB111; ASTM. Thbing: BIll, B 135; Government. Flat products: QQ-B-613. Bar, rod, forgings, shapes: QQ-B-626. Seamless tubing: WW-T-791
Forgeability. 90% that of C37700 (forging brass)
Machinability. 40% that of C36000 (free-cutting brass)
Characteristics
Formability. Cold working properties are fair. Hot forming properties are excellent
Typical Uses. Architectural panel sheets; structurals, such as heavy plate; bolting and valve stems; tubing for heat exchangers; brazing rod for copper alloys and cast iron; hot forgings
Joining. Soldering and brazing properties are excellent. Welding properties of three processes are rated good (oxyfuel gas welding, resistance spot welding, and resistance butt welding). Gas shielded arc welding is rated fair
C28000 has poor cold drawing and forming properties in comparison with those of higher copper alloys. Hot working properties are excellent. Is strongest of copper-zinc alloys but less ductile than higher copper alloys. Is subject to dezincification and stress corrosion cracking under certain conditions
Microstructure. Two-phase: face-centered cubic alpha plus body-centered cubic beta. Beta phase appears lemon yellow when etched with
LIVE GRAPH
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to 1110 "F) Hot Working. Temperature range is 625 to 800 °C (1155 to 1470 OF) C28000: Microstructure. Muntz metal ingot, as-cast. Structure is dendrites of a phase in a matrix of ~ phase. 21Ox
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C28000: Mechanical properties. Typical mechanical properties of extruded and drawn C28000. Data are for Muntz metal rod less than 25 mm (1 in.) in diameter that was extruded and then cold drawn to various percentages of reduction in area 700 600 ~
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-
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C28000: Microstructure. Muntz metal ingot, as-cast, showing a feathers that formed at ~ grain boundaries during quenching of the all-~ structure. 105x
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20
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Amount of cold work, %
60
342/ Heat Treater's Guide: Nonferrous Alloys C28000: Typical mechanical properties Tensilestrength ksl MPa
Temper
Yieldstrength(a) ksl MPa
Elongation In 50mm (2 In.), %
Hardness, HRF
Shear strength MPa ksi
Flat products, 1 mm (0.04 ln.) thick
M20 061 HOD H02
370 370 415 485
54 54 60 70
145 145 240 345
21 21 35 50
45 45 30 10
85 80 55HRB 75HRB
275 275 290 305
40 40 42 44
140 145 345
20 21 50
52 50 25
78 80 78
270 275 310
39 40 45
Rod, 25 mm (1 in.) diameter
M30 061 HOI
360 370 495
52 54 72
(a) At 0.5% exteosion under load
C28000: Annealing curves. Data are for Muntz metal rod less than 25 mm (1 in.) in diameter that was extruded, cold drawn 30%, and annealed 1 h at various temperatures
LIVE GRAPH
LIVE GRAPH
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100
200
300
400
500
600
700
Annealing temperature, 'C
C28000: Microstructure. Muntz metal ingot, drawn and annealed tube. Uniform dezincification, with ex grains in the corroded area (dark at the surface). 250x
Wrought Copper /343
C31400
(89Cu-9~1Zn-1.9Pb)
Commercial Names. Previous trade name. Leaded commercial bronze; CA3l4
Machinability. 80% that of C36000 (free-cutting brass) Formability. Cold working properties are good; hot forming properties,
Chemical Composition. Composition Limits. 87.50 to 90.50 Cu, 1.30 to 2.50 Ph max, 0.10 Fe max, 0.7 Ni max, 0.5 others max (total), bal Zn
poor
Joining. Soldering properties are excellent; brazing properties good; resistance butt welding properties are fair. Not recommended: all other welding processes
Specifications (U.S. and/or Foreign). ASTM. B 140
Characteristics Typical Uses. Screws, screw machine parts, pickling racks and fixtures,
Recommended Heat Treating Practice Temperature range is 425 to 650°C (795 to 1200 oF)
electrical, plug-type connectors, builders' hardware
C31600 (89Cu-8.1 Zn-1.9Pb-1 Ni) Commercial Names. Previous trade name. Leaded commercial bronzenickel bearing; CA3l6
Chemical Composition. Composition Limits. 87.50 to 90.50 Cu,
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 650°C (795 to 1200 "F)
1.30 to 2.50 Pb, 0.70 to 1.20 Ni, 0.1 Fe max, 0.040 to 0.10 P,0.5 others max (total), bal Zn
C31600: Typicalmechanical properties
Specifications (U.S. and/or Foreign). ASTM. B 140
Temper
Characteristics
TensUeslreog1b MPa ksI
Yieldslrengtb(a) MPa ksI
Elongation in SOmm (2 in.), %
Hardness, HRF
Sbearstrength MPa ksi
Drawn bar, 6 mm (0.25 ln.) diameter
Typical Uses. Electrical connectors, fasteners, hardware, nuts, screws,
H04
screw machine parts. Most commonly used as rod or drawn bar
Rod, 13 mm (0.50 in.) diameter
Machinability. 80% that of C36000 (free-cutting brass)
Rod, 25 mm (1 ln.) diameter
Formability. Cold working properties are good; hot forming properties
05050 H04
H04
are poor
Joining. Soldering properties are excellent; brazing properties good; re-
435 460 255 450
63 67 37 65
385
56
12
70
405
59
13
72
275
40
83 395
12 57
45 15
55HRF 70
165 270
24 39
(a) At 0.5% extension under load
sistance butt welding properties are fair. Not recommended: all other welding processes
C33000 (66Cu-33.5Zn-O.5Pb) Commercial Names. Previous trade name. Low leaded brass (tube); Common name. High brass, yellow brass Chemical Composition. Composition Limits. 65.00 to 68.00 Cu,
Characteristics Typical Uses. Alloy is for general purpose usage where a combination of
0.2 to 0.8 Pb, 0.07 Fe max, 0.5 others max (total), bal Zn. Note: Pb content may be less than 0.2% for tubing with an OD greater than 125 mm (5 in.)
some degree of machinability and moderate cold working properties are required, i.e., primers for munitions. Plumbing applications include J-bend, pump, and trap lines
Specifications (U.S. and/or Foreign). AMS. 4555; ASTM. B 135; SAE. J463; Government. WW-T-79l; MlL-T-46072
Machinability. 60% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties are poor
C33000: Typical mechanical properties oftubing 'Iemper
Tensile "reog1b MPa lIsi
OS050 OS025 H58 H80
325 360 450 515
47 52 65 75
YIeld "reog1b(a) MPa IIsl
105 135 345 415
15 20 50 60
Elongation in SOmm (2 ln.), %
60 50 32 7
Hardness HRF
HRB
HR30T
70 85
26 36 66 76
64 75
lOll
Note: Values for tubing, 25 men(1.0 in.) outside diameter x 1.65 mm (0.065 in.) wall thickness. (a) 0.5% extension under load
Joining. Soldering properties are excellent; brazing properties good. Joining properties of three welding processes are good (oxyfuel gas, gas-shielded are, and butt welding methods). Not recommended: all other welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 650°C (795 to 1200 "F) Recrystallization. Temperature is 290 °C (555 oF)
344/ Heat Treater's Guide: Nonferrous Alloys
C33200 (66Cu-32.4Zn-1.6Pb) Commercial Names. High leader brass (tube); Common name. Free-
Recommended Heat Treating Practice
cutting tube brass
Chemical Composition. Composition Limits. 65.00 to 68.00 Cu, 1.30
Annealing. Temperature range is 425 to 650°C (795 to 1200 "F) Recrystallization. Temperature is 288 °C (550 oF)
to 2.00 Pb, 0.07 Fe max, 0.5 others max (total), bal Zn
Specifications (U.S. and/or Foreign). AMS 4558; ASTM B 135; (Government) Mll..-T-460n
C33200: Typical mechanical properties of cold drawn tubing
LIVE GRAPH
Characteristics
Click here to view
Typical Uses. General purpose, screw machine products
8!.
600
Machinability. 80% that of C36000 (free-cutting brass)
::2
Formability. Cold working, fair; hot forming, poor
C> c
Joining. Soldering, excellent; brazing, good; resistance butt welding, fair.
~ 300
i
Not recommended: all other welding processes
400
.2'- 40 n;~
C33200: Typical mechanical properties of C33200 tubing
Thmper
08050 OS025 H58 H80
ThnsUestrength MPa ks!
325 360 450 515
105 135 345 415
47 52 65 75
Elongation In 50 mm (1 In.), %
15 20 50 60
~
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YIeld strength(a) MPa ksi
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Hardness HRF HRB HRJOT
64 75 100
60 50 32 7
70 85
26 36 66 76
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0
l;
100
:I:
80
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60
12
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I1l
:I:
Note: Values for tubing, 25 nun (1.0 in.) outside diameter x 1.65 nun (0.065 in.) waUthickness. (a) 0.5% extension under load
-
20
40
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Amount of cold work, %
C33500 (65Cu-34.5Zn-O.5Pb) Commercial Names. Previous trade name. Low leaded brass Chemical Composition. Composition Limits. 62.50 to 66.50 Cu, 0.30 to 0.80 Pb, 0.1 Fe max, 0.5 others max (total), bal Zn
Specifications (U.S.and/or Foreign). (ASTM) Flat products: B 121, Rod: B 453; (Government) Flat products: QQ-B-613. Bar, forgings, rod, shapes, strip: QQ-B-626
Characteristics Typical Uses. Hardware such as butts and hinges; also watch backs
C33500: Typical mechanical properties
Thmper
08070 08050 OS035 OS025 HOI H02 H04
H06
Thnsile strength MPa ks!
Yield streogth(a) ksi MPa
315 325 340 350 370 420 510 580
97 105
14 15
115
17
130 275 345 415
19 40 50 60
46 47 49 51 54 61 74 84
Elongallon in SO mm (1 In.), %
65 62 57 55 43 23 8
Machinability. 60% that of C36000 (free-cutting brass) Hardness HRJOT HRF
58 64 68 72 55HRB 70HRB 80HRB 86HRB
15 26 31 36 54 65 69 74
Note: Values for flat products, 1 nun (0.04 in.) thick. (a) 0.5% extension under load
Shear strength MPa ks!
Formability. Cold working properties are good; hot forming, poor. Commonly fabricated by blanking, drawing, machining, piercing, punching, and stamping processes
220
32
Joining. Soldering properties are excellent; brazing, good. Four welding
235
34
250 275 295
36 40 43
methods are rated fair (oxyfuel gas, gas shielded are, resistance spot and butt welding). Not recommended: shielded metal arc and resistance seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 700°C (795 to 1300 oF)
Wrought Copper /345
C34000 (65Cu-34Zn-1 Pb) Commercial Name. Previous trade name. Medium leaded brass, 64.5%
C34000 Typical mechanical properties
Chemical Composition. Composition Limits. 62.50 to 66.50 Cu, 0.80 to 1.40 Pb, 0.10 Fe max, 0.50 others max (total). bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 121. Rod: B 453; (Government) Flat products: QQ-B-6B. Bar, forgings, rod, shapes, strip: QQ-B-626
Characteristics Typical Uses. Flat products: butts, disc, engravings, gears, instrument plate, nuts, or drawn shells all involving piercing, threading, or machining. Rod, bar, and wire: couplings, free-machining screws and rivets, gears, nuts. tire valve stems, screw machine products involving severe knurling and roll threading or moderate cold heading, spinning or swaging Machinability. 60% that of C36000 (free-cutting brass) Formability. Cold working properties are good: properties for hot forming are poor Joining. Soldering properties are excellent; brazing properties, good; resist butt welding, fair. Not recommended: all other welding properties
Thmper
Th",Ue strength MPa lIsi
Yield streogth(a) MPa lIsi
Elongation in50mm
(2in.), %
Hardness HRB BR30T
Sheantreogth MPa ksi
Flat products, 1 mm (0.04 in.) thick OS035 OS025 HOI H02 H04 H06
340 49 115 51 350 130 370 54 275 420 61 345 74 415 510 585 85 425 Rod, 2S mm (1.0 in.) diameter
17 19 40 50 60 62
54 53 41 21 7 5
68HRF 72HRF 55 70 80 87
OS025 H03 H02
20
60 40 30
70HRF 60 68
345 50 135 380 55 290 63 330 435 Wire, 2 mm (0.08 ln.) diameter
OS025 HOO HOI H02
345 400 485 605
42 48
31 36 54 63 70 73
50 30 13 7
50 58 70 88
225 235 250 275 295 310
33 34 36 40 43 45
235 250 275
34 36 40
235 260 290 315
34 38 42 46
(a) 0.5% extension under load
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 650°C (795 to 1200 OF) Recrystallization. Temperature is 288 °C (550 OF)
C34200 (62Cu-36.2Zn-2Pb) C35300 (62Cu-36.2Zn-1.8Pb) Commercial Name. Previous trade name. High leaded brass; Common name. Clock brass. engraver's brass, heavy-leaded brass Chemical Composition. Composition Limits (C34200). 62.50 to 66.50 Cu. 1.50 to 2.50 Pb, 0.1 Fe max, 0.5 others max (total), bal Zn; Composition Limits (C35300). 59.00 to 64.50 Cu. 1.30 to 2.30 Pb, 0.1 Fe max, 0.5 others max (total), bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 121. Rod: B 453; SAE J463; UNS number C34200, C35300; (Government) Flat products: QQ-B-613. Bar, forgings, rod, shapes, strip: QQ-B-626
Characteristics Typical Uses. Flat products: gears, wheels. nuts, plates for clocks, keys, bearing cages, engraver's plates. Rod: gears, pinions, valve stems, automotive screw machine parts that need more severe cold working than can be tolerated by free-cutting brass, i.e., processes such as knurling and moderate staking
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to 1100 OF) Recrystallization. Temperature is 320 °C (610 oF) Hot Working. Temperature range is 785 to 815°C (1445 to 1500 "F)
C34200 Typical mechanical properties Thmper
Thmile strength MPa ksl
Yield strength(a) MPa lIsi
Elongation in 50 mm
(210.), %
Hardness HRB BRJOT
Shear strength MPa ksl
Flat products, 1 mm (0.04 in.] thick 24 20 17 15 40 50 60 62
45 48 52 55 38 20 7 5
78HRF 76HRF 68HRF 66HRF 55 70 80 87
18 39 45
50(b) 28(e) 23(d)
66HRF 65 72
OS015 OS025 OS035 OS050 HOI H02 H04 H06
370 360 340 325 370 420 510 585
54 52 49 47 54 61 74 85
Machinability. 90% that ofC36000 (free-cutting brass)
165 140 115 105 275 345 415 425 Rod, 2S mm (1.0 in.) diameter
Formability. Cold working properties are fair; hot forming properties, poor
050 H55 H02
325 400 450
47 58 65
Joining. Soldering properties are excellent; brazing properties good; resistance butt welding properties, fair. Not recommended: all other welding processes
(a) 0.5% extension under load. (b) Reduction in area 65%. (e) Reduction in area 50%. (d) Reduction in area 35%
Crystal Structure. Face-centered cubic alpha Microstructure. 1\\'0 phase: alpha and lead
125 270 310
41 37 32 28 54 63 71 75
255 250 235 225 250 275 295 310
37 36 34 33 36 40 43 45
Next Page 346/ Heat Treater's Guide: Nonferrous Alloys
Annealing temperature, OF
400
600
700
800
1000
1200
1400
I
1
I
1
C34200: Annealing behavior of C34200. Curves are for 1 mm (0.04 in.) thick strip cold rolled from 08035 temper starting stock 100
LIVE GRAPH Ol a. 600
:2
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400 600 Annealingtemperature, °C
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C34900 (62Cu-37.5Zn-O.3Pb) Chemical Composition. Composition Limits. 61.00 to 64.00 Cu, 0.10 to 0.50 Pb, 0.1 Fe max, 0.5 others max (total), bal Zn
C34900: Typical mechanical properties
Characteristics
Thmper
Typical Uses. Builders' hardware, drilled and tapped rivets, plumbing goods, saw nuts, and parts requiring moderate cold working and some machining
Tensilestrength ksi MPa
OS035
365
53
HOI
Wire, 6 mm (0.25 in.) diameter
Recommended Heat Treating Practice Hot Working. Temperature range is 675 to 800 °C (1245 to 1470 OF)
Hardness
Shear strength MPa ksi
165
24
50
75HRF
235
34
290
42
42
70HRB
250
36
150 380
22 55
48 18
70HRF 72HRB
240 285
35 410
110
16
72
67HRF
220
32
Rod, 25 mm (l.O in.) diameter
Formability. Cold working properties are good; hot forming properties, poor
Annealing. Temperature range is 425 to 650°C (795 to 1200 OF)
Elongation in SO mm (2in.), %
Rod, 6 mm (O.25ln.) diameter
Machinability. 50% that of C36000 (free-cutting brass)
Joining. Soldering properties are excellent; brazing properties, good; welding with oxyfuel gas, gas-shielded are, and resistance spot and butt welding methods is rated fair. Not recommended: shielded metal arc and resistance seam welding
Yield strength(a) MPa ksi
OS015 HOI
385 380 470
56 55 68
Wire, 19 mm (O.75ln.) diameter OS050
330
48
(a) At 0.5% extension under load
Previous Page
Wrought Copper /347
C35000 (65.5Cu-36.4Zn-1.1 Pb) Commercial Names. Previous trade name. Medium-leaded brass, 62%
C35000: Typical mechanical properties
Chemical Composition. Composition Limits. 59.00 to 64.00 Cu, 0.80 to 1.40 Pb, 0.10 Fe max, 0.5 others max (total), bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 121. Rod: B 453; SAE J463; (Government) Flat products: QQ-B-613. Bar, forgings, rod, shapes, strip: QQ-B-626
Characteristics Typical Uses. Bearing cages, book dies, clock plates, engraving plates, gears, hinges, hose couplings, keys, lock parts, lock tumblers, meter parts, sink strainers, strike plates, templates, nuts, type characters, washers, and wear plates Machinability. 70% that of C36000 (free-cutting brass) Forgeability. 50% that of C37700 (forging brass) Formability. Cold working and hot forming properties are fair Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties, fair. Not recommended: all other welding processes
Thmper
ThnsUe streog1h MPa ksl
Yieldstreog1h Elongation 0.5%euenslon 0.2%otTset in SOrom underload (21n.), % MPa ksI ksI MPa
Hardness HRB
HR30T
57 54 50 46 43 29 17 10 5
61HRF 67HRF 70HRF 74HRF 66 75 80 86
52 60 68 71 75
56 46 42 22
65HRF 85HRF 60 80
25 50 57 70
Shear strength MPa ksi
FIat products, 1 mm (0.04 ln.) thick
OS050 OS035 OS025 OSOl5 HOI H02 H03 H04 H06
310 325 330 350 370 415 460 505 580
45 47 48 51 54 60 67 73 84
90 110 135 170 220 310 365 415 450 Rod, 12 mm (O.S ln.) diameter OS050 330 48 110 OS0I5 380 55 170 HOI 400 58 305 H02 485 70 360
13 16 20 25 32 45 53 60 65
90 110 135 170 235 310 380 415 475
13 16 20 25 34 45 55 60 69
16 25 44 52
235 250 260 290
34 36 38 42
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600 °C (795 to 1110 OF) Hot Working. Temperature ranges from 760 to 800°C (1400 to 1470 oF)
C35600 (62Cu-35.5Zn-2.5Pb) Commercial Names. Previous trade name. extra-high-leaded brass
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 59.00 to 64.50 ce, 2.00 to 3.00 Pb, 0.1 Fe max, 0.5 others max (total), bal Zn
Annealing. Temperature range is 425 to 600°C (795 to 1110 "F) Hot Working. Temperature range is 700 to 800°C (1290 to 1470 "F)
Specifications (U.S. and/or Foreign). (ASTM) Flat products: BI21. Rod: B 453; (Government) Flat products: QQ-B-613. Bar, rod, shapes, strip: QQ-B-626
Characteristics Typical Uses. Hardware: clock plates and nuts, clock and watch backs, clock gears and wheels. Industrial: channel plate Machinability. 100% that of C36000 (free-cutting brass) Formability. Cold working properties are poor; hot working properties, fair Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties, fair. Not recommended: all other welding processes
C35600: Typical mechanical properties of 1 mm (0.04 in.) thick C35600 sheet and strip 'Iemper
OS035 HOI H02 H04
Thnslle strength MPa ksI
340 370 420 510
49 54 61 74
Yieldstrength!a) MPa ksi
115 275 345 415
17 40 50 60
Elongationin 50rom (2 in.), %
50 35 20 7
Hardness HRB HRJOT
68HRF 55 70 80
31 54 65 69
(a) At 0.5% extension under load
C36000 (61.5Cu-35.5Zn-3Pb) Commercial Names. Previous trade name (free-cutting brass); Common name. Free-turning brass, free-cutting yellow brass, high-leaded brass Chemical Composition. Composition Limits. 60.00 to 63.00 Cu, 2.50 to 3.70 Pb, 0.35 Fe max, 0.5 others max (total), bal Zn
Specifications (U.S. and/or Foreign). AMS 4610; (ASTM) B16; SAE J463; (Government) Flat products: QQ-B-613. Bar, forgings, rod, shapes, strip: QQ-B-626
348/ Heat Treater's Guide: Nonferrous Alloys
Characteristics
C36000 Typical mechanical properties
Typical Uses. Hardware: gears, pinions. Industrial: automatic, highspeed screw machine parts
Thnsile strength MPa ksi
Temper
Yield strength(a) MPa ksl
Elongation in50mm (2 In), %
Reduction in ares, %
Hardness, HRB
Shear strength MPa ksl
Microstructure. Usually is three phase: alpha, beta, and lead Machinability. 100%-the standard for the machinability of all other copper alloys Formability. Cold working properties are poor; hot forming properties, fair Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties, fair. Not recommended: all other types of welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to 1110 OF). Also see annealing curves in adjoining Figure
Rod, 6 mm (0.25 ln.) diameter H02(b) 470 68 360 Rod, 25 mm (1 ln.) diameter
52
18
48
80
260
38
340 49 125 310 400 58 Rod, 50 mm (2 ln.) diameter
18 45
53 25
58 50
68HRF 78
205 235
30 34
H02(d)
52
75
220
32
68HRF 62
205 230
30 33
061 H02(c)
380
55
305
44
32
340 385
49 56
125 310
18 45
50 20
Shapes M30 H01(e)
(a) 0.5% extension under load. (b) Cold drawn 25%. (c) Cold drawn 20%. (d) Cold drawn 18%. (e) Cold drawn 15%
Hot Working. Temperature range is 700 to 800 °C (1290 to 1470 OF) Recrystallization. Temperature is 330°C (625 OF)
C36000: Microstructure. Free-cutting brass, as-cast. Solid-state transformation makes this structure appear unlike an as-cast structure. Etchant; 20 mL NHpH, 0-20 mL H20, 8-20 mL 3% H20 2·50x
C36000: Microstructure. Free cutting brass semi-solid processed plumbing fitting. The large particles (white, light gray) are solid that was present before casting; the matrix was rapidly solidified to produce the structure shown. NHpH + HP2 + Hp. 310x
C36000: Annealing curves. Data are for free-cutting brass rod, cold drawn 30% to 19 mm (0.75 in.) in diameter from M30 temper (as-extruded) starting stock, then annealed 1 h at temperature
LIVE GRAPH
LIVE GRAPH
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Click here to view Annealing temperature. OF
600
800
1000
1200
1400
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Wrought Copper /349
C36500, C36600, C36700, C36800 (60Cu-39.4Zn-O.6Pb) Commercial Names. Previous trade names. C36500, uninhibited leaded muntz metal; C36600, arsenical leaded muntz metal; C36700, antimonial leaded muntz metal; C36800, phosphorized leaded muntz metal; Common name. Leaded muntz metal; inhibited leaded muntz metal
Chemical Composition. Composition Limits. 58.00 to 61.00 Cu, 0.40 to 0.90 Pb, 0.15 Fe max, 0.25 Sn max; As, Sb, P (see below): 0.1 others max
(total), bal Zn. Antimony or phosphorus limits, C36500, none specified; C36600, 0.02 to 0.10 As; C36700, 0.02 to 0.10 Sb; C36800, 0.02 to 0.10 P
Specifications (U.S. and/or Foreign). (ASME) Plate, condenser tubing: SBI71; (ASTM) Plate, condenser tubing: B 171. Clad plate: B 432
ferric chloride etch. Lead appears as insoluble gray particles randomly distributed throughout structure
General Corrosion Behavior. Alloys have good resistance to corrosion in fresh and salt water. C36500 is an uninhibited alloy and is subject to dezincification. Each inhibited alloy contains 0.02 to 0.10% of an inhibitor element (arsenic, antimony, or phosphorus), which provides high resistance to dezincification
Machinability. 60% of C36600 (free-cutting brass) Formability. Cold working properties are fair; hot working properties, excellent
Joining. Soldering properties are excellent; brazing properties, good.
Characteristics Typical Uses. Main tube sheets for condensers and heat exchangers; support sheets; baffles
Welding properties with three processes are rated fair (oxyfuel gas, gas shielded are, resistance butt welding). Not recommended: all other welding processes
Recommended Heat Treating Practice
Crystal Structure. Face-centered cubic Microstructure. Alpha and beta with undissolved lead. Beta phase appears lemon yellow with ammonia peroxide-etch; may be darkened with
Annealing. Temperature range is 425 to 600 °C (795 to llIO "F) Hot Working. Temperature range is 625 to 800°C (1155 to 1470 oF)
C37000 (60Cu-39Zn-1 Pb) Commercial Names. Previous trade name. Free-cutting muntz metal Chemical Composition. Composition Limits. 59.00 to 62.00 Cu, 0.90 to 1.40 Pb, 0.15 Fe max, 0.5 others max (total), bal Zn
Specifications (U.S. and/or Foreign). (ASTM)Thbing: B 135;(Government) Flat products: QQ-B-613. Bar, forgings. rod, strip: QQ-B-626. Thbing: MIL-T-46072
Characteristics Typical Uses. Automatic screw machine parts
C37000: Typical mechanical properties Thnsile strength
Temper
MPa
ksi
Yield strength(.) MPa ksi
Machinability. 70% that of C36000 (free-cutting brass) Hardness
Elongollon In SO mm (2 fn.), %
Thbe, 38 mm (1.5 in.) outside diameter x 3 mm (0.125 in.) wall thickness 050 370 54 140 20 40 H8O{b) 550 80 415 60 6
HRB
HRJOT
80HRF 85
43 74
Thbe, 50 mm (2 In.) outside diameter x 6 mm (0.25 in.) wall thickness H80(c) 485 70 310 45 10
Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties, fair. Not recommended: all other welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to llIO "F)
75
67
Hot Working. Temperature range is 625 to 800°C (1155 to 1470 "F)
(a) At 0.5% extension underload. (b) Cold drawn35%. (c) Cold drawn25%
C37700 (60Cu-38Zn-2Pb) Commercial Name. Previous trade name. Forging brass
Crystal Structure. Face-centered cubic
Chemical Composition. Composition Limits. 58.00 to 62.00 Cu, 1.50
Microstructure. Two phase: alpha and beta, with undissolved lead. Beta phase appears lemon yellow with ammonia peroxide etch. Ferric chloride darkens beta phase. Lead appears as gray particles
to 2.50 Pb, 0.3 Fe max, 0.50 others max (total), bal Zn
Specifications (U.S. and/or Foreign). (AMS) Die forgings, forging rod: 4614; (ASME) Die forgings: SB283; (ASTM) Bar, forgings, rod, shapes: B 124. Die forgings: B 283; (Government) QQ-B-626. Die forgings: MIL-C-13351
Characteristics Typical Uses. Forgings and pressings of an kinds
Alloy is nonmagnetic
Machinability. 80% that of C36000 (free-cutting brass) Forgeability Rating. 100%-the standard to which other copper alloys are compared
350 I Heat Treater's Guide: Nonferrous Alloys Formability. Cold working properties are poor; hot forming properties, excellent Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties, fair. Not recommended: all other welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to 111 0 "F), Also see adjoining Figure on annealing curves Hot Working. Temperature range is 650 to 825 °C (1200 to 1500 oF)
LIVE GRAPH
LIVE GRAPH
Click here to view
Click here to view
C37700: Typical mechanical properties. Typical mechanical properties of extruded and drawn C37700. Data are for forging brass rod less than 25 mm (1 in.) in diameter that was extruded, then cold drawn to various percentages of reduction in area
C37700: Annealing curves. Typical data are for forging brass rod less than 25 mm (1 in.) in diameter that was extruded, cold drawn 18%, and annealed 1 h at various temperatures Annealing temperature, OF
600 Tensile strength
80
500
200
400 600 800 1000 1200
500
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C38500 (57Cu-40Zn-3Pb) Commercial Name. Previous trade name. Architectural bronze Chemical Composition. Composition Limits. 55.00 to 60.00 Cu. 2.00 to 3.80 Pb, 0.35 Fe max, 0.5 others max (total). bal Zn Specifications (U.S. and/or Foreign). (ASTM) Shapes: B 455
Characteristics Typical Uses. Architectural: extrusions, storefronts, thresholds, and trim. Hardware: butts, hinges, lock bodies. Industrial: forgings Machinability. 90% that of C36000 (free-cutting brass)
Formability. Cold working properties are poor. Hot forming properties, excellent Joining. Soldering properties are excellent; brazing properties, good; resistance butt welding properties; fair. Not recommended: all other welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 600°C (795 to 1110 oF) Hot Working. Temperature range is 625 to 725°C (1155 to 1335 OF)
Wrought Copper /351
C40500 (95Cu-4Zn-1 Sn) Commercial Names. Trade name: High conductivity bronze; Common name. Penny bronze
Specifications (U.S. and/or Foreign). ASTM B 591
Characteristics
Chemical Composition. Composition Limits. 94.00 to 96.00 Cu, 0.70 to 1.30 Sn, 0.05 Pb max, 0.05 Fe max, bal Zn
Typical Uses. Meter clips, terminals, fuse chips, contact springs, relay springs, washers from rolled strip, rolled bar, sheet
Machinability. 20% that of C36000 (free-cutting brass) C40500: Typical mechanical properties
'lemper
ThnsIIe strength MPa lIsi
Formability. Cold working properties are excellent; hot forming proper-
Y,.1d strength Elongation At 0.5% extension underload At0.2% offset IoSOmm MPa IIsI MPa ksl (210.), %
ties, good Shear IIardoess ~ HRB HR30T MPa ksi
Flat products,1 mm (0.04in.)thick OS035 OS025 OS015 HOI H02 H03 H04 H06 H08 HlO
270 280 290 325 360 400 440 475 510 540
39 41 42 47 52 58 64 69 74 78
83 83 90 250 295 340 380 415 435 485
12 12 13 36 43 49 55 60 63 70
69 76 97 250 345 385 425 460 495 525
10 11 14 36 50 56 62 67 72 76
49 48 47 30 15 12 10 7 4 3
55HRF 58HRF 64HRF 46 60 67 72 76 79 82
10 13 24 47 56 62 65 69 71 72
215 230 230 240 255 260 270 280 295 310
31 33 33 35 37 38 39 41 43 45
Joining. Soldering and brazing properties are excellent; welding properties are good for three processes: gas-shielded are, resistance spot and butt welding. Oxyacetylene and resistance seam welding properties are fair. Not recommended: coated metal arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 510 to 670 °C (950 to 1240 "F) Hot Working. Temperature range is 830 to 890°C (1525 to 1635 oF)
C40800 (95Cu-2Sn-3Zn) Chemical Composition. Composition Limits. 94.00 to 96.00 ce, 1.80 to 2.20 Sn, 0.05 Pb max, 0.05 Fe max, bal Zn
C40800: Typical mechanical properties
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 591
'leoslle strength MPa ksi
Characteristics
'Iemper
Typical Uses. Rolled strip for electrical connectors
05035 290 42 05025 305 44 05015 310 45 HOi 345 50 H02 370 54 H03 425 62 H04 460 67 H06 73 505 H08 545 79 HlO 545(a) 79(a)
Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, fair
Joining. Solder and brazing properties are excellent. Properties for oxyacetylene, gas shielded arc, and resistance butt welding are good. Not recommended: resistance spot and seam welding
Yieldstrength At 0.5% extension Elongation underload At 0.2% offset 1050nun (210.),% MPa ksl MPa ksi
90 97 105 270 315 360 395 420 455 515
13 14 15 39 46 52 57 61 66 75
310 380 415 485 540 565 580
45 55 60 70 78 82 84
43 43 42 24 12 6 5 4 3 3
Hardn ess
HRB HR30T
60HRF 22 65HRF 26 69HRF 31 50 54 62 65 72 67 76 70 82 73 85 77 84(a) 75(a)
Shear ~ MPa ks!
230 235 235 250 260 280 295 310 330 340
33 34 34 36 38 41 43 45 48 49
Recommended Heat Treating Practice Annealing. Temperature range is 450 to 675°C (840 to 1245 OF)
Note: Values for flat products. 1 rrun (0.04 in.) thick. (a) min
Hot Working. Temperature range is 830 to 890 °C (1525 to 1635 OF)
C41100 (91 Cu-8.5Zn-0.5Sn) Commercial Name. Previous trade name. Lubaloy
Characteristics
Chemical Composition. Composition Limits. 89.00 to 93.00 Cu, 0.30
Typical Uses. Rolled strip, rolled bar, rod, and sheet for bushings, bear-
to 0.70 Sn, 0.1 Pb max, 0.05 Fe max, bal Zn
ing sleeves, thrust washers, terminals, connectors, flexible metal hose, and electrical connectors
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 508, B 591. Wire: B 105
Machinability. 20% that of C36000 (free-cutting brass)
352/ Heat Treater's Guide: Nonferrous Alloys Formability. Cold working properties are excellent; hot forming proper-
C41100: Typicalmechanical properties
ties, good
Joining. Soldering properties are excellent. Properties for gas-shielded arc and resistance butt welding, good. Brazing, oxyacetylene, and resistance spot welding properties are fair. Not recommended: coated metal arc and resistance seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 500 to 700 °C (930 to 1290 OF) Hot Working. Temperature range is 830 to 890°C (1525 to 1635 OF)
'Thnsile strength MPa ksl
'Thmper
Yieldstnmgth At 0.2% Elongation underload oll'set inSOmm MPa ksl MPa ksl (2 In.), %
0.5% extension
Flat products,l mm (0.04 In.) thick 260 38 76 270 39 76 280 41 83 290 42 83 330 48 260 325 380 55 415 60 360 380 455 66 495 72 415 540 78 485 495 550 80 (0.25 ln.) diameter
08050 08035 08025 08015 HOI H02 H03 H04 H06 H08 HIO Wire, 6 mm
11 11 12 12 38 47 52 55 60 70
62 83 97 105 280 365 400 440 485 515 525
72
9 12 14 15 41 53 58 64 70 75 76
Shear
HIII'IIness ~ HRB lIR30T MPa ksl
58HRF 60HRF 68HRF 7lHRF 52 62 70 76 78 81 83
44 43 41 40 23 14 6 5 4 3 2
220 32 230 33 235 34 58 60 66 69 71
250 36 275 40
72
73
2(a)
H80(70%) 560 81 Wire, 3 mm (0.10 ln.) diameter R80(95%) 705 102 WIre, 1 mm (0.05 in.) diameter H80(98.7%) 730 106
1(b) 0.9(b)
(a) Elongation In 254 mm (10 in.), (b) Elongation in 1500 rom (60 in.)
C41500 (91 Cu-7 .2Zn-1.85n) Chemical Composition. Composition Limits. 89.00 to 93.00 Cu, 1.50
C41500: Typicalmechanical properties
to 2.20 Sn, 0.1 Pb max, 0.05 Fe max, bal Zn
Specifications (U.S. and/or Foreign). ASTM B 591
'Thnsile strength MPa ksi
Characteristics
'Thmper
Typical Uses. Rolled strip for spring applications in electrical switches
08035 315 46 08025 08015 345 50 HOI 345 50 H02 385 56 H03 435 63 H04 485 70 H06 525 76 H08 560 81 560(a) 81(a) HIO
Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, fair
Joining. Soldering and brazing properties are excellent. Properties for three welding methods are good (oxyacetylene, gas-shielded arc, and resistance butt welding). Resistance spot welding processes are fair. Not recommended: coated metal arc and resistance seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 400 to 705°C (750 to 1300 "F) Hot Working. Temperature range is 730 to 845 °C (1345 to 1555 "F)
Yield strength At 0.2% Elongation underload olrset inSOmm MPa ksi MPa ksl (2 In.), %
0.5% extension
115
17
125
18
44
180 280 365
26 41 53
185
27
370
54
42 28 16
450 490 505 515
65 71 73 75
455 515 570 605
66 75 83 88
5 4 3 2
Note: Valuesfor flat products. 1 rom (0.04 In.) thick. (a) min
Fatigue Hardness HRB lIR30T
64HRF 24 68HRF 29 74HRF 36 62 58 74 65 78 68 72 83 86 73 90 75 89(a) 74(a)
strength
MPa
ksl
240
35
250
36
280 290 305 305 345 360
41 42 44 44 50 52
Wrought Copper /353
C41900 (90.5Cu-4.35Zn-5.15Sn) Commercial Names. Previous trade name. CA419; Common name. Tin brass
~41900:
Typicalmechanical properties of C41900 strip
Chemical Composition. Composition Limits. 89.00 to 92.00 Cu, 4.80 to 5.50 Sn, 0.10 Pb max, 0.05 Fe max, bal Zn
Thmper
Characteristics
061 HOI H02 H03 H04 H06 H08
Typical Uses. Electrical connectors
Recommended Heat Treating Practice Annealing. Temperature range is 480 to 680°C (900 to 1250 OF)
Yieldstrength 010.2% orr.et ,MPa ksl
Thmlleslrength ksl MPa
340
130 315 395 450 510 530 550
49 58 68 75 82 93 102
400 470 515 565 640 705
FJongalion ln50mm (2 In.),%
67HRF 64 73 78 87
42 25 14 5 4 3 2
19 46 57 65 74 77 80
HardDess, HRB
92 95
C42200 (87.5Cu-11.4Zn-1.1 Sn) Commercial Names. Previous trade name. Lubronze
Hot Working. Temperature range is 830 to 890 °C (1525 to 1635 oF)
Chemical Composition. Composition Limits. 86.00 to 89.00 Cu, 0.80 to 1.40 Sn, 0.35 Pmax, 0.05 Pb max, 0.05 Fe max, bal Zn
Specifications (U.S. and/or Foreign). ASTM B 591
C42200: Typicalmechanical properties
Characteristics Typical Uses. Rolled strip, rolled bar and sheet for sash chains, terminals, fuse clips. spring washers, contact springs, and electric connectors
Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, good
Joining. Soldering and gas-shielded arc welding properties are excellent. Resistance spot and butt welding properties are good. Resistance seam welding and brazing properties are fair. Not recommended: oxyacetylene welding
Thmper
Thmilestrength ksI MPH
OS035 OS025 OS015 HOI H02 H03 H04 H06 H08 HlO
295 305 315 360 415 455 505 550 600 605(a)
43
44 46 52 60 66 73 80 87 88(a)
YIeldstrength At At 0.5'.I> extension 0.2'.1> ol&el underload ksI MPa ksi MPa
15 16 17 40 51 55 65 68 73 75
105 110 115 275 350 380 450 470 505 515
14 15 19 39 57 64 70 76 81 84
97 105 130 270 395 440 485 525 560 580
Elongation ln50mm IIanIness (2 In.), '.I> HRB HR30T
46 45
44 30 12 6 4 3 2 2
65HRF 27 70HRF 31 75HRF 40 54 56 70 64 77 68 81 70 72 84 87 73 86(a) 74(a)
Note: Values forflatproducts, 1 mm (0.04 in.) thick.(a) min
Recommended Heat Treating Practice Annealing. Temperature range is 500 to 675°C (930 to 1245 OF)
C42500 (88.5Cu-9.5Zn-2Sn) Chemical Composition. Composition Limits. 87.00 to 90.00 Cu, 1.50
Hot Working. Temperature range is 790 to 840°C (1455 to 1545 oF)
to 3.00 Sn, 0.35 P max, 0.05 Pb max, 0.05 Fe max, bal Zn
Specifications (U.S. and/or Foreign). ASTM B 591
Characteristics
C42500: Typicalmechanical properties
Typical Uses. Rolled strip, rolled bar and sheet for electrical switch springs, terminals, connectors, fuse clips, pen clips, and weather stripping
Thmper
Thmllestrength MPa ksl
OS035 OS025 OS015 HOl H02 H03 H04 H06 H08 HIO
310 315 325 370 435 470 525 565 615 635(a)
YIeldstrength AI0.5% exlemlon At 0.2'.1> olJset underload MPa ks! MPa ksi
Elongation ln50mm (2 In.), %
IIanIness HRB HR30T
Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, fair
Joining. Soldering and brazing properties are excellent. Three welding processes are rated good (oxyacetylene, gas-shielded arc, and resistance butt welding). Not recommended: coated metal arc and resistance spot and seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 425 to 700 °C (795 to 1290 OF)
45 46 47 54 63 68 76 82 89 92(a)
125 125 135 310 345 395 435 485 515 525
18 18 20 45 50 57 63 70 75 76
105 125 130 315 405 450 505 545 585 615
Note:Values forflatproducts, 1 mm (0,04 in.) thick.(a) min
15 18 19 46 59 65 73 79 85 89
49 48 47 35 20 15 9 7 4 2
70HRF 72HRF 79HRF 60 75 80 86 90 92 92(a)
32 36 45 56 68 70 73 74 76 76(a)
354/ Heat Treater's Guide: Nonferrous Alloys
C43000 (87Cu-10.8Zn-2.25n) Chemical Composition. Composition Limits. 84.00 to 87.00 Cu, 1.70 to 2.70 Sn, 0.10 Pb max, 0.05 Fe max, bal Zn
Hot Working. Temperature range is 790 to 840°C (1455 to 1545 oF)
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 951
C43000: Typical mechanical properties
Characteristics Typical Uses. Rolled strip and sheet for electrical switches, spring, fuse and pen clips, and weather stripping Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, good Joining. Soldering and brazing properties are excellent; three welding methods are rated good (oxyacetylene, gas-shielded are, and resistance butt welding). Resistance spot welding has a fair rating. Not recommended: coated metal arc and resistance seam welding
Recommended Heat Treating Practice
Thmper
05035 05025 05015 HOI H02 H03 H04 H06 H08 HIO
'Ienslle strength MPa ksI
315
Yield
Elongation
strength(a) ksl MPa
in50mm (2io.),%
125
46
18
HRF
Hardness lIRB lIR30T
69
55
30 34 39 57 73 79 84 81 91 9O(b)
72 77 53 62
365 425 495 540 605 650 620(b)
TI5 380 450 460 485 495 505
72 78 88 94 9O(b)
40 55 65 67 70
44 25 13 10 5 4 3
72 73
57 65 69 73 75 77 75(b)
Note: Values for flat products. 1 rom (0.04 in.) thick. (a) At 0.5% extension underload. (b) min
Annealing. Temperature range is 425 to 700 °C (795 to 1290 oF)
C43400 (85Cu-14.3Zn-O.75n) Chemical Composition. Composition Limits. 84.00 to 87.00 Cu, 0.40 to 1.00 Sn, 0.05 Pb max, 0.05 Fe max, bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 591
Hot Working. Temperature range is 790 to 840 °C (1455 to 1545 "F)
C43400 Typical mechanical properties
Char:acteristics Typical Uses. Rolled strip for electrical applications: switch parts, blades, relay springs, contacts Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, good Joining. Soldering and brazing properties are excellent. Four welding processes have good ratings (oxyacetylene, gas-shielded are, resistance spot and butt welding). Not recommended: resistance seam welding
Recommended Heat Treating Practice
Thmper
05035 05025 05015 HOI H02 H03 H04 H06 H08 HIO
Thuslle
Yield
Elongation
strength ksI MPa
strength(a) MPa ksl
IoSOmm (210.), %
310 315 330 360 405 470 510 580 620 605(b)
45 46 48 52 59 68 74 84 90 88(b)
105 110 115 280 350 405 460 490 510 515
15 16 17 41 51 59 67 71 74 75
49 48 47 28 18
10 7 5 4 3
Hardness lIRB HRJOT
64HRF 65HRF 70HRF 54 66 73 80 83 86 84(b)
22 26 30 55 63 68
71 74 76 74(b)
Shear strength MPa ksi
250 255 255 275 290 310 340 360 370 385
36 37 37 40 42 45 49 52 54 56
Note: Values for flat products, I rom (0.04 in.) thick. (a) 0.5% extension under load. (b) min
Annealing. Temperature range is 425 to 625°C (795 to 1155 "F)
C44300, C44400, C44500 (71Cu-28Zn-15n) Commercial Names. Previous trade names. C44300. arsenical admiralty metal; C44400: Antimonial admiralty metal; C44500: Phosphorized admiralty metal; Common name. Inhibited admiralty metal; admiralty brass Chemical Composition. Composition Limits. 70.00 to 73.00 Cu, 0.07 Pb max. 0.06 Fe max, 0.90 to 1.20 Sn (or 0.80 to 1.20 Sn for flat-rolled products): As, Sb, or P (see below). bal Zn. Limits for As, Sb, and P, C44300: 0.02 to 0.10 As; C44400: 0.02 to 0.10 Sb; C44500: 0.02 to 0.10 P
Specifications (U.S. and/or Foreign). (ASME) Condenserplate: SB171. Tubing: SB1II, SB359, SB543; (ASTM) Condenser plate: B 171. Tubing: BIll, B 359, B 395, B 543
Characteristics Typical Uses. Condenser, distiller, and heat exchanger tubing: ferrules. strainers, and condenser tube plates. Caveat: all three alloys are susceptible to stress corrosion cracking. When possible. they should be used in annealed condition. When fabrication results in residual stresses, parts should be stress relieved
Wrought Copper /355 General Corrosion Behavior. Alloys have good resistance to salt and fresh water at low velocities. Water velocities above 1.8 mls (6 ft/s) cause impingement attack. A different inhibitor is added to each alloy to protect against dezincification
welding, and flash welding. Not recommended: shielded metal arc welding and resistance seam welding
Recommended Heat Treating Practice
Machinability. 30% that of C36000 (free-cutting brass)
Annealing. Temperature range is 425 to 600 °C (795 to 1110 "F)
Formability. Cold working properties are excellent; hot fanning proper-
Hot Working. Temperature range is 650 to 800°C (1200 to 1470 "F)
ties, fair for the following: silver alloy brazing, oxyfuel gas welding, resistance spot
Recrystallization. Temperature is 300 °C (570 OF) for 1 mm (0.04 in.) strip cold rolled hard (50% reduction) from grain size of 0.015 mm (0.0006 in.)
C44300: Microstructure. Arsenical admiralty tube, drawn stress
C44300: Microstructure. Arsenical admiralty tube, drawn and
relieved. and bent 180 0 • Transgranular stress-corrosion crack. Etchant; 20 mL NHpH, 0-20 mL Hp, 8-20 mL 3% HP2' 200x
annealed. Uniform dezincification, with a grains in corroded area (dark at the surface). Etchant; 20 mL NHpH, 0-20 mL H20. 8-20 mL 3% H202 • 250x
Joining. Soft soldering properties are excellent. Properties are rated good
C44300, C44400, C44500: Typical mechanical properties
'Iemper
Thnsile strength MPa ksi
Yield strength(a) MPa ksi
C44300, C44400, C44500: Typical Charpy impact strength data
Elongation
inSOmm (2 ln.), %
Thsttempemlure
Hardness HRF HRIST HR30T
Thbing, 25 mm (1 in.) outside diameter x 1.65 mm (0.065ln.) wall thickness 08025 365 53 152 22 65 75 HOI 434 63 45 86.5 H02 503 73 29 90 H03 565 82 15 90 H04 669 97 4 92 Plate, 25 mm (1 in.) dinmeter M20 330 48 124 18 65 70 Strip. 1 mm (0.04ln.) diameter 060(0.080mm) 310 45 90 13 69 59 9 060(0.015mm) 330 48 62 60 97 14 9 H04 607 88 109 496 72 4 90
37 78 81 84
°C 20 3 -18 -30 -50
-SO -115
OF
J
68 38
o
-25 -60 -110 -175
Impact strength D·llif
82.4 82.2 79.7 82.4 79.9 83.4 80.3
60.8 60.6 58.8 60.8 58.9 61.5 59.2
Annealedspecimens, cut from 19 mm (0.75 in.)diamrodintokeyhole-notch bars.Values areaveragesof datafromthreetests(specimens didDOt fracture). Tensilestrengthat 20 °C (68 "F), 320 MPa (46.5 ksi); yieldstrength, 92 MPa (13.3 ksi);elongation, 83.5%; hardness, 64 HRF 20 20 76
(a) At 0.5% extensionunderload.Apparentelasticlimit(tubing), 125 MPa (18 ksi)
C44300, C44400, C44500: Typical creep datar',
------------------'.\.~""'-'-._._------
Values for rod, hot rolledto 22.2 mm (0.875 in.), thencold drawn to 19.0 mm (0.750 in.).(a) No measurable flow.(b) Nearlyzero
356/ Heat Treater's Guide: Nonferrous Alloys
C44300, C44400, C44500: Properties vs. grain size and annealing temperature. Data for inhibited admiralty metal tubing (71Cu-28Zn1Sn), cold drawn 50% and annealed 1 h at temperature
LIVE GRAPH
LIVE GRAPH
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Annealing temperature, °C
Annealing temperature, °C
C46400, C46500, C46600, C46700 (60Cu-39.2Zn-O.8Sn) Commercial Names. Previous trade names. C46400: Uninhibited naval brass; C46500, arsenical naval brass; C46600, antimonial naval brass; C46700, phosphorized naval brass; Common names: Naval brass; inhibited naval brass Chemical Composition. Composition Limits. 59.00 to 62.00 Cu, 0.50 to 1.00 Sn, 0.20 Pb max, 0.10 Fe max, bal Zn. As, Sb, and P content: C46400, none specified; C46500, 0.02 to 0.10 As; C46600, 0.02 to 0.10 Sb; C46700, 0.20 to 0.10 P Specifications (U.S. and/or Foreign). (AMS) Bar and rod (C46400 only): 4611, 4612; (ASME) Condenser plate: SBI71; (ASlM) Bar, rod, and shapes (C46400 only): B 21, B 124. Forgings (C46400 only): B 283. Condenser plate: B 171; (SAE) Bar, rod and shapes (C46400 only): J461, J463; (Government) QQ-B-626. Bar, rod, shapes, forgings and wire (C46400 only): QQ-B-637. Bar and flat products (C46400 only): QQ-B639. Thbing (C46400 only): MlL-T-6945
Characteristics Typical Uses. Condenser plates, welding rod, marine hardware, propeller shafts, valve stems, airplane turnbuckle barrels, balls, nuts, bolts, rivets, fittings Crystal Structure. Face-centered cubic alpha and body centered cubic beta Microstructure. Generally two phases-alpha and beta General Corrosion Resistance. Has good resistance to corrosion in fresh and salt water. Different inhibitor elements are added to C46500, C46600, and C46700 to protect against dezincification Machinability. 30% that of C36000 (free-cutting brass) Forgeability. 90% that of C37700 (forging brass) Formability. Hot forming properties are excellent; cold forming properties, fair Joining. Soft soldering and silver soldering properties are excellent. Properties of three welding methods are rated good (oxyfuel gas welding,
Wrought Copper I 357 resistance spot welding, and flash welding). In the fair category are gasshielded arc welding and resistance seam welding. Not recommended: shielded arc welding
Recrystallization. Temperature is about 350°C (660 OF) for 19 mm (0.75 in.) diam rod cold drawn 30%. Also see adjoining figure showing variations in properties with annealing temperatures
Recommended Heat Treating Practice
Cold Reduction. Maximum between anneals is 30%
Annealing. Temperature range is 425 to 600 °C (795 to 1110 OF) Hot Working. Temperature range is 650 to 825°C (1200 to 1520 OF)
C46400,C46500,C46600,orC46700: Typical mechanical properties 'Thnslle strength ksi MPa
'Iemper
C46400: Microstructure. Uninhibited naval brass extruded, drawn, and annealed. Structure shows twinned grains resulting from annealing. Etchant; 59 g FeCla and 96 mL ethanol. 300x
Elongation inSOmm (2m), %
Yield
strength(a) MPa ksi
Flat products, 1 mm (0.04 in.) thick 207 30 050 427 62 HOI 58 483 70 400 Flat products, 6 mm (0.25 ln.) thick 060 25 400 58 172 050 414 193 28 60 Flat products, 25 mm (1.0 in.) thick M20 172 25 379 55 Rod and bar, 6 mm (0.25 ln.) diameter
060
400 58 186 27 207 30 050 434 63 HOI (10%) 482 70 331 48 H02(20%) 552 80 393 57 Rod and bar, 25 mm (1.0 ln.) diameter 060 393 57 172 25 207 050 434 63 30 HOI (8%) 476 69 317 46 H02(20%) 517 75 365 53 Rod and bar, 51 mm (2.0 ln.) diameter 060 386 56 172 25 050 427 62 193 28 HOI (8%) 462 40 67 276
Hardness, BRB
Reduction in area,%
Shear strength ksi MPa
40 17
60 75
283 296
41 43
49 45
56 58
275 283
40 41
50
55
275
40
45 40 25 20
60 55 50 45
56 60 80 85
275 290 296 310
40 42 43 45
47 40 27 20
60 55 50 45
55 60 78 82
275 290 296 303
40 42 43
47 43 35
60 55 50
55 60 75
275 290 296
40 42 43
275
40
Thbing,9 mm (0.375 in.) outside diameter x 2.5 mm (0.097 ln.) wall thickness 18 H80(35%) 607 66 40 95 88 455 061 427 62 207 30 45 25 Extruded shapes M30 400 58 40 170 25
44
(a) 0.5% extension under load
C46400, C46500, C46600, C46700: Variation of properties in strength, ductility, and grain size with annealing temperature. Data for 19 mm (0.75 in.) diam naval brass rod (60Cu-39.2Zn-0.8Sn), cold drawn 30% and annealed 1 h attemperature. Grain size before cold drawing, 0.025 mm
LIVE GRAPH
LIVE GRAPH
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Annealingtemperature, °C
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800
358/ Heat Treater's Guide: Nonferrous Alloys
C46400: Microstructure. Uninhibited naval brass, as-cast. Transverse macrosection showing the columnar structure of the outer edges of the casting that results from more rapid cooling near the surface of the casting. Various concentrations HNO a • 1.5x
C46400: Microstructure. Uninhibited naval brass, as-cast. Transverse macrosection showing the columnar structure of the outer edges of the casting that result from more rapid cooling near the surface of the casting. Higher magnification reveals dendritic microstructure. Etchant; 20 mL NHpH, 0-20 mL Hp, 8-20 mL 3% HP2' then 59 9 FeCla and 96 mL ethanol. 30x
C48200 (60..5Cu..38Zn..O..8Sn..O..7Pb) Commercial Names. Previous trade names. Naval brass, medium leaded: CA482; Common name. Leaded naval brass
C48200: Typical mechanical properties
Chemical Composition. Composition Limits. 59.00 to 62.00 Cu, 0.40 to 1.00 Pb, 0.10 Fe max, 0.50 to 1.00 Sn, bal Zn
Specifications (U.S. and/or Foreign). (ASTM) Rod, bar, and shapes: B 21 (CA482). B 124 (C48200). (Government) QQ-B-626. Bar, rod, forgings, shapes, wire: QQ-B-637. Bar and plate: QQ-B-639
Characteristics Typical Uses. Marine hardware, screw machine products, valve stems Microstructure. Generally is three phase: alpha, beta, and lead General Corrosion Behavior. Good resistance to seawater and marine atmosphere
Machinability. 50% that of C36000 (free-cutting brass)
Temper
Tensile strength MPa ksl
395 435 475 515
57 63 69 75
060 050 HOI (8%) H02(15%)
385 425 460 485
56 62 67 70
55 60 78 82
260 270 275 285
37 30 17
55 60 75 78
260 270 275 285
38 39
33
43
78
275
40
230
33
34
60
270
39
275
40
32
75
275
40
170 205 315 365
25 30 46 53
170 195 275 360
25 28 40 52
40
230
40
35 20 15
38 39 40
41
40
41
435
63
Bar, 10 mm (0.38 in.) diameter Bar, 38 mm (1.5 in.) diameter
poor
HOI
Joining. Soft soldering properties are excellent; silver brazing properties, good. Flash welding properties, fair. Not recommended: oxyfuel gas welding, arc welding, and most resistance welding processes
(a) At 0.5% extension under load
Recrystallization. Temperature is about 360 °C (680 OF) for 19 mm (0.75 in.) diamrod cold drawn 30%
Shenr strength MPa ksl
Rod, 76 mm (3.0 in.) diameter HOI (4%) M30
Hot Working. Temperature range is 650 to 760°C (1200 to 1400 OF)
Hardness, HRB
Rod, 51 mm (2.0 in.) diameter
Formability. Hot working properties are good; cold working properties,
Recommended Heat Treating Practice
Elongation in SO mm !2in.),%
Rod, 25 mm (1.0 ln.) diameter 060 050 HOI (8%) H02(20%)
Forgeability. 90% that of C37700 (forging brass)
Annealing. Temperature range is 425 to 600 °C (795 to 1110 OF)
Yield strength!a) MPa ksl
435 455
63 66
Wrought Copper /359
C48500 (60Cu-37.5Zn-1.8Pb-O.75n) Joining. Soft soldering properties are excellent; silver alloy brazing, good. Flash welding, fair. Not recommended: oxyfuel gas welding, arc welding, and most resistance welding processes
Commercial Names. Previous trade names. High-leaded naval brass; CA485; Common name. Leaded naval brass Chemical Composition. Composition Limits. 59.00 to 62.00 Cu, 1.30 to 2.20 Pb, 0.10 Fe max, 0.50 to 1.00 Sn, bal Zn
Recommended Heat Treating Practice
Specifications (U.S. and/or Foreign). (ASTM) Rod, bar, and shapes: B 21 (CA482), B 124 (C485OO). Forgings: B 283 (CA485). (Government) QQ-B-626. Bar, rod, shapes, forgings, and wire: QQ-B-637. Bar and plate products: QQ-B-639
Annealing. Temperature range is 425 to 600°C (795 to 1110 "F) Hot Working. Temperature range is 650 to 760 °C (1200 to 1400 oF) Recrystallization. Temperature is about 360°C (680 "F) for 19 mm (0.75 in.) diam rod cold drawn 30%. Also see adjoining Figure showing variation in properties with annealing temperature
Characteristics Typical Uses. Marine hardware, screw machine products, valve stems
Cold Reduction. Maximum between anneals is 20%
Microstructure. Usually is three-phase: alpha, beta, and lead C48500: Typical mechanical properties
General Corrosion Behavior. Good resistance to seawater and marine atmospheres Machinability. 70% that of C36000 (free-cutting brass) Forgeability. 90% that of C37700 (forging brass) Formability. Hot working properties are good; cold working properties, poor
Yield
Elongation
s1reogth(a) MPa ksi
JnSOmm (2in.), %
Hardness,
Thmper
Thosile s1renglh MPa ksi
060 HOI (8%) H02(20%)
393 476 517
172 317 365
40 20 15
55 78 82
57 69 75
25 46 53
Shear streogth MPa ksl
HRB
248 269 276
36 39 40
(a) Values for rod. 25 mm (1.0 in.) diameter
C48500: Variation of strength. Variation of properties in ductility,and grain size with annealing temperature. Data for 19 mm (0.75 in.) diam high-leaded naval brass (60Cu-37.5Zn-1.8Pb-0.7Sn) rod that was cold drawn 30% and annealed 1 h at temperature. Grain size before cold drawing, 0.025 mm
LIVE GRAPH
LIVE GRAPH
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Annealing temperature, °C
C50500 (98.7Cu-1.35n) Commercial Names. Previous names. Phosphor bronze, 1.25% E; CA505; Common name. Phosphor bronze (1.25% Sn)
Specifications (U.S. and/or Foreign). (ASTM) Strip: B 105. Wire: B 105
Chemical Composition. Composition Limits. 1.00 to 1.70 Sn, 0.05 Pb max, 0.10 Fe max; 0.35 P max, bal Cu; 99.50 Cu + Sn + P min
Characteristics Typical Uses. Electrical contacts, flexible hose, pole line hardware
360 I Heat Treater's Guide: Nonferrous Alloys Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold forming properties are excellent; hot forming properties, good. Parts commonly are fabricated blanking, forming, bending, upsetting, shearing, squeezing, and swaging Joining. Flash welding, soldering, and brazing properties are rated excellent; gas metal arc welding properties, fair. Not recommended: other welding processes
Recommended Heat Treating Practice Annealing. Temperature range is 475 to 650°C (890 to 1200 OF) Hot Working. Temperature range is 800 to 875°C (1470 to 1610 OF)
C50500: Typical mechanical properties Thnslle 'Iemper
05035 05075 H02 H04 H06 H08 HIO
Grain slze.mm
0.035 0.Q15 0.035 0.Q15 0.035 0.Q15 0.035 0.Q15 0.035 0.Q15 0.035 0.015
strength MPa ksi
Yield strength(a) ksI MPa
276 290 365 372 421 441 462 483 483 510 510 524
76 90 352 359 414 434 455 476 476 503 503 517
40 42 53 54 61
64 67 70 70 74 74 76
Elongation in so rom (2 ln), %
11 13 51 52 60 63 66 69 69 73 73 75
HRll
Fatigue strength(h) MPa ksI
59.0 60.0 67.0 69.0 73.0 75.0 76.0 78.0 69.0 BO.O
114 121 162 172 179 190 172 193 197 203 197 210
Hardness,
47.0 47.0 12.0 13.0 5.0 5.0 3.0 3.0 3.0 3.0 3.0 3.0
16.5 17.5 23.5 25 26 27.5 25 28 28.5 29 28.5 30.5
Note: Values for flat products 1 mm (0.040 in.) thick.Data in this table were interpolated from A5lM 5TP I. (a) At 0.2% offset.(b) At 108 cyclesoffully reversedstress
CS1000 (94..8Cu..SSn..0 ..2P) Commercial Names. Previous trade name. Phosphor bronze, 5% A Chemical Composition. Composition Limits. 93.60 to 95.60 Cu, 4.20 to 5.80 Sn, 0.03 to 0.35 P, 0.05 Pb max, 0.10 Fe max, 0.3 Zn max Specifications (U.S. and/or Foreign). (AMS) Flat products: 4510. Bar, rod, tubing: 4625. Wire: 4720; (ASTM) Flat products: B 100, B 103. Bar: B 103, B 139. Rod, shapes: B 139. Wire: B 159; SAE J463; (Government) Flat products: bar, shapes: QQ-B-750. Rod: QQ-B-750, MIL-B-13501. Bearings: MIL-B-13501. Wire: QQ-B-750, QQ-W-321, MIL-W-6712
Characteristics Typical Uses. Architectural: bridge bearing plates. Hardware: beater bars, bellows, bourdon tubing, clutch discs, cotter pins, diaphragms, fuse clips, fasteners, lock washers, sleeve bushings, springs, switch parts, truss
wire, wire brushes. Industrial: chemical hardware, perforated sheets, textile machining, welding rods Machinability. 20% that of C36000 (free-cutting brass) Formability. Excellent properties for cold working by blanking, drawing, forming, bending, roll threading, knurling, shearing, stamping. Hot forming properties are poor Joining. Soldering, brazing, and resistance butt welding properties are excellent; gas metal arc and resistance spot welding are rated good. These processes have fair ratings: oxyfuel gas, shielded metal arc, and resistance seam welding
Recommended Heat Treating Practice Annealing. Temperature range is 475 to 675°C (890 to 1245 "F) C51000: Typical mechanical properties Thnslle strength
C51000: Microstructure. Phosphor bronze, 5% A, rod, extruded, cold drawn, and annealed 30 min at 565°C (1050 OF). Structure consists of recrystallized ex grains with annealing twins. Etchant; 2 g K2C rP 7' 8 mL H2 S0 4 , 4 mL NaCI (saturated solution), 100 mL Hp. 500x
'Iemper
MPa
ksI
Flat products,1 mm (0.04 in.) thick 05050 325 47 05035 340 49 05025 345 50 05015 365 53 H02 470 68 H04 560 81 H06 635 92 H08 690 100 HIO 740 107 Rod, 13 mm (0.05 m.) diameter H02 515 75 Rod, 25 mm (1 ln.) diameter H02 480 70 Wire,2 mm (0.08 m.) diameter 05035 345 50 HOI 470 68 H02 585 85 H04 760 110 H06 895 130 H08 965 140 (a) At 0.5% extensionunder load
Yield strength(a) MPa ksl
Elongation in SO rom (2 In.), %
Hardness,
64 58 52 50 28 10 6 4 3
26 28 30 34 78 87 93 95 97
nan
130 140 145 150 380 515 550
19 20 21 22 55 75 80
450
65
25
80
400
58
25
78
140 415 550
20 60 80
58 24 8 5 3 2
Wrought Copper /361
C51100 (95.6Cu-4.2Sn-0.2P) Chemical Composition. Composition Limits. 94.50 to 96.30 Cu, 3.50
Recommended Heat Treating Practice
to 4.90 Sn, 0.003 to 0.35 P, 0.05 Pb max, 0.10 Fe max, 0.30 Zn max
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 100, B 103
Characteristics
Annealing. Temperature range is 475 to 675°C (890 to 1245 "F)
C51100: Typical mechanical properties of 1 mm (0.04 in.) thick strip
Typical Uses. Architectural: bridge, bearing plates. Hardware: beater bars, bellows, clutch disks, connectors, diaphragms, fuse clips, fasteners, lock washers, sleeve bushings, springs, switch parts, terminals. Industrial: chemical hardware, perforated sheets, textile machining
Machinability. 20% that of C36000 (free-cutting brass) Formability. Excellent capacity for cold working by blanking, drawing, forming, bending, roll threading, knurling, shearing and stamping. Hot forming properties are poor Joining. Soldering, brazing, and resistance butt welding properties are excellent. Gas metal arc and resistance spot welding properties are good. Oxyfuel gas, shielded metal are, and seam welding properties are fair
b.
YIeldlllreogth aIO.2~ offset MPa ksi
46 48 50 51 55 62 74 80 92 98 103
110 130 145 160 295 385 495 530 615 655 675
Thmper
'IensDe strength MPa
08050 08035 08025 08015 HOI H02 H03 H04 H06 H08 H10
315 330 345 350 380 425 510 550 635 675 710
EIoDglltioo in SO (110.). ~
16 19 21 23 43 56 72 77 89 95 98
48 47 46 46 36 19 11 7 4 3 2
IIardoera HRB IIR30T
70HRF 73HRF 75HRF 76HRF 48 70 84 86 91 93 95
45 65 72 74 78 79 80
C521 00 (92Cu-8Sn) Commercial Names. Previous trade names. Phosphor bronze, 8% C
C52100: Typicalmechanical properties
Chemical Composition. Composition Limits. 90.50 to 92.8 Cu, 7.00 to 9.00 Sn, 0.03 to 0.35 P, 0.05 Pb max, 0.10 Fe max, 0.20 Zn max
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 103. Bar: B 103, B 139. Rod, shapes: B 139. Wire: B 159. SAE J463. (Government) MIL-E-23765
Characteristics Typical Uses. For more severe service than that tolerated by C51100 alloy. Architectural: bridge bearing plates. Hardware: beater bars, bellows, bourdon tubing, clutch discs, cotter pins, diaphragms, fuse clips, fasteners, lock washers, sleeve bushings, springs, switch parts, tress wire, wire brushes. Industrial: chemical hardware, perforated sheets, textile machining, welding rods
Machinability. 20% that of C36000 (free-cutting brass) Formability. Good capacity for cold working by blanking, drawing, forming, bending, shearing, and stamping. Hot forming properties are poor
Joining. Soldering, brazing, and resistance butt welding properties are excellent. Gas metal arc and resistance spot welding properties are good. Properties for oxyfuel gas, shielded metal are, and resistance seam welding are fair
Recommended Heat Treating Practice Annealing. Temperature range is 475 to 675°C (890 to 1245 OF)
Thmper
ThosIJe strength ksi MPa
Yield strength(a) ksi MPa
FJODglltioo inSOmm (110.). ~
HRF
Hardoeso IIR30T HRB
Flat products, 1 mm (0.04 In.) thick 55 08050 380 08035 58 400 08025 415 60 08015 62 425 H02 525 76 93 H04 640 H06 106 730 H08 770 112 HIO 120 825 Rod, 13 mm (0.5 ln.) diameter H02 Wire, 2 mm 08035 HOI H02 H04 H06
80 550 (0.08 ln.) diameter 415 560 725 895 965
60 81 105 130 140
(0) At 0.5% extension under load
70 65 63 60 32 10 4 3 2
165
24
380 495 550
55 72 80
450
65
33
165
24
65
75 80 82 85
50
84 93 96 98 100 85
73 78 80 81 82
362/ Heat Treater's Guide: Nonferrous Alloys
C52100: Annealing temperature. Effect of annealing temperature on the mechanical properties of an alloy C521 00 slab. Annealingtime,4 h
Temperature, of 930
750 450 (65)
1110
1290
1470
1650 70
(
400 (58)
350 (51)
-5
V
"-..., I
~
I
~
e:2:
I 300 (44)
01
~
I
v--:
--
•
~ 60
50
~
40
I
c:
.0, '" 01 c: 0
l!!
iii
iii
o
Elongation • Ultimate tensile strength 6. 1% yield strength '" 0.2% yield strength
250 (36)
200 (29)
150 (22)
....,
fro-
....
............
100 (15) 400
r-------
20 6. 6.
.
~
500
30
600
700
10
o 800
900
Temperature, °C
C52400 (90Cu-10Sn) Commercial Names. Previous trade name. Phosphor bronze, 10% D
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 83.30 to 90.07 Cu, 9.00
Annealing. Temperature range is 475 to 675°C (890 to 1245 "P)
to 11.00 Sn, 0.03 to 0.35 P, 0.05 Pb max, 0.10 Fe max, 0.20 Zn max
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 103. Bar: B 139. Rod, shapes: B 139. Wire: B 159; (Government) Flat products. Wire: QQ-B-750
C52400: Typical mechanical properties
Characteristics Typical Uses. Heavy bars and plates for severe compression loads, requiring good resistance to wear and corrosion; bridge and expansion plates and fittings. Also for products requiring extra spring qualities and optimum resiliency, particularly in fatigue
Machinability. 20% that of C36000 (free-cutting brass) Formability. Alloy has good capacity for cold working by blanking, forming, bending, and shearing. Hot forming properties are poor Joining. Soldering, brazing, and resistance butt welding properties are excellent. Properties for gas metal arc and resistance spot welding are good. Oxyfuel gas, shielded metal are, and resistance seam welding properties are rated fair
ThllSlJestrength Thmper
MPa
Flat products,! mm (0.04 ln.) thick 05035 455 H02 570 H04 690 H06 795 H08 840 H10 885 Wire, 2 rom (0.08in.) diameter 05035 455 HOI 650 H02 815 H04 1013
Elongation in 50 rom (1ial, %
Hardness, HRB
66 83 100 115122 128
68 32 13 7 4 3
55 92 97 100 101 103
66 93 118 147
70
ksi
Wrought Copper I 363
CS4400 (88Cu-4Pb-4Sn-4Zn) Commercial Names. Previous trade name. Phosphor bronze B-2; Common names: Free-cutting phosphor bronze; 444 bronze; bearing bronze
C54400: Typical mechanical properties
Chemical Composition. Composition Limits. 3.50 to 4.50 Pb, 3.50 to 4.50 Sn, 1.50 to 4.50 Zn, 0.10 Fe max, 0.01 to 0.50 P, bal Cu 99.5 Cu + Pb + Sn + Zn + P min
Temper
Specifications (U.S. and/or Foreign). (AMS) Strip: 4520; ASTM B 103, B 139; SAE J463. Bearing alloy: J460 (791); (Government) Bar and rod: QQ-B-750
Characteristics Typical Uses. Bearings (sleeve and thrust), bushings, gears, pinions, screw machine products, shafts, thrust washers, valve parts
Machinability. 80% that of C36000 (free-cutting brass)
Tensile streogtb MPa ksi
YIeld slrength(a) MPa ksi
Elongation in 50 mm (210.),...
Hardness,
48 47 46 46 19 7 4 3 2
70HRF 73HRF 75HRF 76HRF 70 86 91 93 95 70
HRB .
Sheet and strip, 1 mm (0.04 in.) thick 05050 05035 05025 05015 H02 H04 H06 H08 HlO
315 330 345 350 425 550 635 675 710
46 48 50 51 62 80 92 98 103
370 510
54 74
550
80
Flat products, 8 mm (0.38 in.) thick H04 415 60 Flat products, 19 mm (0.75 ln.) thick
310
45
20
Formability. Has good cold working properties; is commonly fabricated by machining, shearing, blanking, drawing, forming, bending. Not recommended: hot working and hot forming
H04
240
35
25
Rod, 13 mm (0.50 in.) diameter H04 75 515 Rod, 25 mm (1.0 in.) diameter
435
63
15
83
H04
395
57
20
80
Joining. Soldering properties are excellent; brazing properties, good; flash welding properties, fair. Not recommended: other welding processes
Recommended Heat Treating Practice
380
470
55
68
(a) At 0.5% extension under load
Annealing. Temperature range is 475 to 675°C (890 to 1245 OF) Stress Relieving. Temperature for treating rod is 300 °C (570 OF); for treating parts, 275°C (530 OF)
C60600 (95Cu-SAI) Commercial Names. Previous trade name. Aluminum bronze A; CA606; Common name. Aluminum bronze, 5% Chemical Composition. Composition Limits. 92.00 to 96.00 Cu, 4.00 to 7.00 AI, 0.50 Fe max, 0.50 others max (total). Caveat: excessive amounts of Pb, Zn, and P will cause hot shortness and problems in welding
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 169; (Government) Bar, rod, forgings, shapes: QQ-C-645. Sheet and plate: QQ-C-450. Strip: QQ-C-450, QQ-C-465
Characteristics Typical Uses. Alloy is produced as sheet, strip, and rolled bar; uses include fasteners, deep drawn, "gold" decoration, and parts requiring resistance to corrosion. Caveat: alloy is not suitable for use in oxidizing acids
Microstructure. Has alpha structure, face-centered cubic
General Corrosion Resistance. For discussion of general corrosion resistance, see article on C61400. Alloy has been used in sulfuric acid pickling applications where oxygen content is low. Has been used in anhydrous NH40H applications, but presence of moisture causes stress corrosion cracking. Not suitable for nitric acid application. Oxidizing salts such as chromates and metal salts such as ferric chloride generally are corrosive to C60600 Machinability. 20% that of C36000 (free-cutting brass). Alloy tends to form tough, stringy chips. Good lubrication and cooling are essential to a good finish. Carbide or tool steel cutters are used
Recommended Heat Treating Practice Annealing. Temperature range is 550 to 650°C (1020 to 1200 OF) Hot Working. Temperature range is 815 to 870 °C (1500 to 1600 "P) Recrystallization. Temperature is 350°C (660 "F) at 44% reduction and 0.075 mm (0.003 in.) initial grain size
C60800 (95Cu-SAI) Commercial Name. 5% aluminum bronze; Common name. Aluminum bronze, 5%
Chemical Composition. Composition Limits. 92.50 to 94.80 Cu, 5.00 to 6.50 AI, 0.02 to 0.35 As, 0.10 Pb max, 0.10 Fe max. Caveat: excessive Pb, Zn, and P causes problems in welding and hot working
Specifications (U.S.and/or Foreign). (ASME) Tubing: SBlll, SB359, SB395; (ASTM) Tubing: B 111, B 359, B 395
Next Page 364/ Heat Treater's Guide: Nonferrous Alloys
Characteristics Typical Uses. Alloy is produced as seamless tubing and ferrule stock for
Machinability. 20% that of C36000 (free-cutting brass). Chips tend to be tough and stringy. Good fmishes required adequate lubrication and cooling. Carbide or tool steel cutters are used
heat exchanger tubing, condenser tubing, and other applications requiring corrosion-resistant seamless tubing. Caveat: not suitable for use in oxidizing acids
fair
Microstructure. Has alpha structure, face-centered cubic
ties are fair. Not recommended: soldering and oxyfuel gas welding
GeneralCorrosion Resistance. For discussion of general corrosion resistance, see article on C61400. Has been used in sulfuric acid pickling operations where oxygen content is low. In anhydrous NH40H application, presence of moisture can cause stress corrosion cracking. Not suitable for use with nitric acid. Oxidizing salts such as chromates and metal salts such as ferric chloride generally are corrosive
Recommended Heat Treating Practice
Formability. Cold working properties are good; hot forming properties, Joining. Arc and resistance welding have good ratings. Brazing proper-
Annealing. Temperature range is 550 to 650°C (1020 to 1200 "F) Hot Working. Temperature range is 800 to 875 °C (1470 to 1610 "F) Recrystallization. Temperature is 350°C (660 "F) at 44% reduction and 0.Q75 mm (0.003 in.) initial grain size
C61000 (92Cu-SAI) Commercial Names. Common name. 8% aluminum bronze
Forgeability. 70% that of C37700 (forging brass)
ChemicalComposition. Composition Limits. 6.00 to 8.50 AI, 0.50 Fe max; 0.02 Pb max, 0.20 Zn max, 0.10 Si max, 0.50 others max (total), balCu
Formability. Has good capacity for both hot forming and cold working. Common processes include blanking, drawing, forming, bending, cold heading, and roll threading
Specifications (U.S. and/orForeign). (ASME) SB169; ASTM B 169;
Joining. Properties for arc welding, resistance spot welding, and resis-
(Government) QQ-C-450; MIL-E-23765
Characteristics
tance butt welding are rated good; soldering and resistance seam welding properties, fair. Not recommended: brazing and oxyfuel gas welding
Typical Uses. Produced as rod or wire and used to make bolts, shafts, tie
Recommended Heat Treating Practice
rods, and pump parts. Also used as a welded overlay on steel to improve resistance to wear
Annealing. Temperature range is 600 to 675°C (1110 to 1245 oF)
Machinability. 20% that of C36000 (free-cutting brass)
Hot Working. Temperature range is 760 to 875 °C (1400 to 1610 "F)
C61300 (90Cu-7 AI-0.3Sn) Commercial Name. Aluminum bronze, 7% Chemical Composition. Composition Limits. 88.50 to 91.50 Cu, 6.00 to 7.5 AI, 0.02 to 0.50 Sn, 2.00 to 3.00 Fe, 0.10 Mn max, 0.15 Ni (+ Co) max, 0.01 Pb max, 0.05 Zn max, 0.05 max others. Caveat: excessive Pb, Zn, P, or Si can cause problems in hot working and welding Specifications (U.S. and/or Foreign). (Government) Flat products: QQ-C-450
Characteristics Typical Uses. Alloy is produced in a number of forms: rod, bar, sheet, plate, seamless tubing, pipe, and welded pipe. Applications include tube sheets, heat exchanger tubing, acid resistant piping, columns, water boxes, and corrosion resistant vessels Microstructure. Alloy has alpha structure, single phase, with iron rich precipitates
General Corrosion Resistance. See article on C61400 for discussion of general corrosion resistance The alloy is very resistant to neutral and nonoxidizing salts. Examples include:
• Extended service in potash solutions of potassium chloride, sodium chloride, magnesium chloride, and calcium chloride The alloy resists nonoxidizing mineral acids. Examples: • Has been used in tanks containing hydrofluoric acid in glass etching applications • In organic acid service, it has been used to make acetic acid distillation columns The alloy is highly resistant to dealloying and to stress corrosion cracking (SCC) in steam and hot oxidizing aqueous solutions and vapors. Presence of tin in 7% aluminum bronze evidently renders the alloy immune to SCC in these environments. However, C61300 is susceptible to SCC in moist ammonia and mercurous nitrate solutions. But it is highly resistant to SCC in anhydrous ammonia, especially when moisture content is below 500 ppm and temperature is below 85°C (180 "F) Because of its high resistance to corrosion in salt water, the alloy is used in a variety of components for marine and desalting plant service • Examples include tube sheets for condensers in nuclear and fossil fuel power stations; cooling tower transfer piping, seawater piping for sec-
Previous Page Wrought Copper /365 ondary cooling systems in nuclear power plants, and piping for geothermal heat transfer systems
Joining. Arc and resistance welding properties are good; brazing properties, fair. Not recommended: soldering and oxyfuel gas welding
Recommended Heat Treating Practice
Machinability. Fair to poor. Chips tend to be stringy and gummy. Good lubrication and cooling are essential. Practice for tool steel cutters: roughing speed 90/min (300 ftImin) with feed of 0.3 mm1rev (0.011 in.lrev); finishing speed is 350 mlmin (1150 ftImin) with feed of 0.3 mm1rev(0.011 in.lrev)
Annealing. Temperature range is 600 to 875°C (1110 to 1610 "F)
Forgeability. 50% that of C37700 (forging brass)
Recrystallization. Temperature range is 785 to 870°C (1445 to 1600 "F)
Formability. Cold working and hot working properties are rated good
Hot shortness temperature is 1010 °C (1850 oF)
C61300: Charpy V-notch. Variation in Charpy V-notch impact strength with temperature for C61300 and C61400
LIVE GRAPH Click here to view
Hot Working. Temperature range is 800 to 925 °C (1470 to 1695 oF)
C61300: Typical mechanical properties of C61300 and C61400 rod at various temperatures ThnsiIe 'IOmperalure OF "C
I\reogtb
YIeld otreogtb(a)
FJongalion InSOmm Redudlon (2in.)," Inarea,"
ModIWsof ~
GPa~poi
IIardneso, HB(b)
MPH
ksi
MPa
ksI
718 611 606 590 532 432 170 88
104.1 88.6 87.9 85.5 77.2 62.6 24.6 12.8
397 335 339 318 298 271 105 71
57.6 48.7 49.2 46.1 43.3 39.3 15.2 10.3
50 45 44 42 35 22 52 27
49 55 58 59 32 24 41 26
156 149 172 126 128 88 48 45
22.7 21.6 25.0 18.3 18.5 12.8 6.9 6.6
186 170 162 157 144 137 83 49
707 102.6 610 88.4 600 87.1 583 84.6 522 75.7 427 62.0 174 25.3 92 13.3
347 305 303 288 276 256 123 68
50.3 44.3 43.9 41.8 40.1 37.1 17.8 9.9
52 47 44 45 34 30 60 36
51 57 56 56 32 27 55 33
139 176.5 172 136.5 130 81 67 45
20.2 25.6 24.9 19.8 18.8 11.7 9.7 6.5
185 162 161 155 142 134 84
Temperalure, OF
Cold finished 80
.0
f-----l-~"L--+-~~-+-----=l60 :;;
40
~ "c t"l a .§
20 20 L.-_---'-_ _--'-_ _.L-_----' -200 200 400 600 Temperature,OC
-182 -295 --60 -75 -29 -20 20 70 205 400 315 600 425 800 540 1000 Annealed -182 -295 --60 -75 -29 -20 20 70 205 400 315 600 425 800 540 1000
50
(a)AI0.5%exlensionunderload. (b)3000kg(66151b)load
C61400 (91Cu-7AI-2Fe) Commercial Names. Previous trade name. Aluminum bronze D; Common name. Aluminum bronze, 7% Chemical Composition. Composition Limits. 88.00 to 92.50 Cu, 6.00 to 8.00 AI, 1.50 to 3.50 Fe, 1.00 Mn max, 0.20 Zn max, 0.01 Pb max, 0.015 P max, 0.5 others max (total). Excessive Pb, Zn, Si, or P causes hot shortness and cracking during hot working and welding Specifications (U.S. and/or Foreign). (ASME) Flat products: SB169, SBI7l, Bar, rod, shapes: SB150; (ASTM) Flat products: B 169,B 171. Bar, rod, shapes: B 150; SAE J463; (Government) Flat products: QQ-C-450, QQ-C-465. Bar, rod, shapes, forgings: QQ-C-465. Flat wire: QQ-C-465
Characteristics Typical Uses. Alloy is produced as seamless tubing, welded and seamless pipe, sheet, plate, rod, and bar. Applications include condenser and heat exchanger tubing, fasteners, tube sheets, and corrosion resistant vessels. Caveat: not suitable for use in oxidizing acids. Susceptible to stress corrosion cracking in moist ammonia or in steam environments, especially when stress levels are high Microstructure. Structure is alpha solid solution, with precipitates of iron-rich phase
Aluminum bronzes resist nonoxidizing mineral acids, such as sulfuric, hydrochloric, and phosphoric acids. Resistance tends to decrease with increasing concentration of dissolved oxygen or oxidizing agents, especially as temperatures increase above 55°C (130 "F) Aluminum bronzes are generally suited for service in alkalies, neutral salts, nonoxidizing acid salts and many organic acids and compounds. Oxidizing acids, oxidizing salts, and heavy metal salts are corrosive. Aluminum bronzes resist dealloying, but to different degrees, depending on alloy composition General Corrosion Resistance. In general, corrosion resistance is mostly influenced by solution concentration, aeration, temperature, velocity, and amount of any impurities in the solution Aluminum bronzes are susceptible to stress corrosion cracking in moist ammonia and mercury compounds. When stress levels are high, the alloys also may be susceptible to stress corrosion cracking in purified steam or in steam containing acidic or salt vapors Applications include systems that contain mineral acids, alkalies such as sodium or potassium hydroxide, neutral salts such as sodium chloride, and organic acids such as acetic, lactic, or oxalic. The alloy also resists anhydrous ammonia, but care must be taken to exclude moisture to avoid stress corrosion cracking. In addition, the alloy resists anhydrous, chlorinated
366/ Heat Treater's Guide: Nonferrous Alloys hydrocarbons, such as carbon tetrachloride, but the presence of moisture makes these chemicals corrosive Machinability. 20% that of C36000 (free-cutting brass). Alloy has tendency to form continuous, stringy chips. Good lubrication and cooling are essential. Tool steel or carbide cutters may be used. Typical practice for tool steels cutters: roughing speed, 90 mlmin (300 ftlmin) with feed of 0.3 mmlrev (0.011 in.lrev); finishing speed, 350 mlmin (1150 ftlmin) with feed of 0.3 mmlrev (0.011 in.lrev) Formability. Cold working properties are fair; hot forming properties, good Joining. Properties for gas-shielded are, coated metal are, and resistance welding are good; brazing properties, fair. Not recommended: soldering, oxyacetylene, and carbon arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 600 to 900 °C (1110 to 1650 OF) Hot Working. Temperature range is 800 to 925°C (1470 to 1695 OF) Recrystallization. Temperature range is 785 to 870 °C (1445 to 1600 oF) Hot shortness temperature is 1010 °C (1850 oF)
C61400: Charpy V-notch. Variation in Charpy V-notch impact strength with temperature for C61300 and C61400
LIVE GRAPH Click here to view
C61400: Typical mechanical properties of C61300 and C61400 rod at various temperatures Thnsile strength MPa ksi
Yield strength(a) MPa ksi
718 611 606 590 532 432 170 88
104.1 88.6 87.9 85.5 77.2 62.6 24.6 12.8
397 335 339 318 298 271 105 71
-182 -295 --(i() -75
707 610
102.6 88.4
-29 20
-20 70
600
205 315 425 540
400 600
522 427 174
Thmperalure
OC
OF
Elongation
inSOmm (2in.),1I>
Reduction in area, II>
57.6 48.7 49.2 46.1 43.3 39.3 15.2 10.3
50 45 44 42 35 22 52 27
49 55 58 59 32
347 305
50.3 44.3
87.1 84.6
303 288
75.7 62.0 25.3 13.3
276 256 123 68
Modulus or elastici\t GPa 10
Psi
Hardness, HB(b)
Cold finished -182 -295 --(i() -75 -29 -20 20 70 400 205 315 600 425 800 540 WOO
41 26
156 149 172 126 128 88 48 45
22.7 21.6 25.0 18.3 18.5 12.8 6.9 6.6
186 170 162 157 144 137 83 49
52 47
51 57
139 20.2 176.5 25.6
185 162
43.9 41.8
44 45
56 56
172 24.9 136.5 19.8
161 155
40.1 37.1 17.8 9.9
34 30
32 27 55 33
130 81 67 45
18.8 11.7 9.7 6.5
142 134 84 50
24
Annealed
800 1000
583
92
60 36
(a) At 0.5% extension underload. (b) 3000 kg (66151b) load
C61400: Typicalmechanical properties
Temperature, OF
Size
Thnsilestrength MPa ksi
Yield strength(a) Elongation in MPa ksf SOmm(2in.), II>
Shear strength MPa ksi
80
Flat products, 060 temper
.0
t----1f--."L---+~*-t----=I 60
J;
~
c:
g" 40
c.
E
3 mm (0.12 in.) thick 8 mm (0.31 in.) thick 13 mm (0.50 in.) thick 25 mm (1.00 in.) thick
565 550 535 525
82 80 78 76
310 275 240 230
45 40 35 33
40 40 42 45
615 585 550 535
89 85 80 78
415 370 310
60 58 54 45
32 35 38 40
585 565 550
85 82 80
310 275 240
45 40 35
35 35 35
310 290 275 275
45 42 40 40
330 310 275
48 45 40
Flat products, H04 temper 3 mm (0.12 in.) thick 8 mm (0.3l in.) thick 13mm (0.50 in.) thick 25 mm (1.00 in.) thick
400
Rod, H04 temper 20 20'--_-----'_ _--'-_ _-'--_ _-' -200 200 400 600 Temperature,OC
13 mm (0.50 in.) diameter 25 mm(1.00 in.) diameter 51 mm(2.00in.)diameter (a) At 0.5% extension under load
C61500 (90Cu.8AI.2Ni) Commercial Name. Previous trade name. Lusterloy
Machinability. 30% that of C36000 (free-cutting brass)
Chemical Composition. Composition Limits. 89.00 to 90.50 Cu, 7.70 to 8.30 AI, 1.80 to 2.20 Ni, O.oI5Pb max
Forgeability. 50% that of C37700 (forging brass)
Characteristics
Formability. Cold working and hot forming properties are excellent. Suitable forming processes include bending, drawing, deep drawing, forging, extrusion, blanking, and stamping. Slight directionality in bending
Typical Uses. Hardware, decorative metal trim, interior furnishings, giftware, springs, fasteners, architectural panels and structural sections, deep drawn articles, tarnish-resistant articles General Corrosion Resistance. Excellent-Similar to that of other aluminum bronzes
Joining. Properties for gas-shielded arc welding, shielded metal are, and resistance welding are excellent; soldering and brazing properties, good (with use of mildly aggressive fluxes). Not recommended: Oxyfuel gas welding
Wrought Copper /367
Recommended Heat Treating Practice
C61500: Typical mechanical properties of 1 mm (0.04 in.) thick sheet and strfp
Annealing. Temperature range is 620 to 675°C (1150 to 1245 OF) Aging Temperature. Order strengthening, 300°C (570 OF) for I h (a low temperature annealing treat that permits short range ordering of solute atoms within a matrix, which greatly impedes dislocation motion.) Hot Working. Temperature range is 815 to 870°C (1500 to 1600 OF)
Thmper
ThlL'lUestrength MPa ksl
060
485 050 585 H02 725 H04 860 H06 930 H08 965 HR06(a) 1000
70 85 105 125 135 140 145
Yieldstrength at 0.211> ollset MPa ksi
150 345 515
6W 690 725 965
Elongation In
SOmm(21o.),1I>
22 50 75 90 100 105 140
IIardneu, HR30T
42 70 81 83 84 84.5 86.5
55 36 15 5 4 3 1
Fatigue strength at II/ cY£1es ksi MPa
260
38
270
39
275
40
(a) Cold worked 50%. then stress relieved for 1 h a1300 °C (570 "P)
C62300 (87Cu-10AI-3Fe) Commercial Name. Aluminum bronze, 9% Chemical Composition. Composition Limits. 88.20 to 89.50 Cu, 8.50 to 11.00 AI, 2.00 to 4.00 Fe, 1.00 Ni (+ Co) max, 0.6 Sn max, 0.50 Mn max, 0.25 Si max, 0.5 others max (total).Caveat: Excessive P causes hot shortness; excessive Si causes loss in ductility. Excessive AI reduces ductility and resistance to corrosion Specifications (U.S. and/or Foreign). (ASME) Bar, rod, shapes: SB150; (ASTM) Bar, rod, shapes: B 150. Forgings: B 283; SAE J463; (Government) Forgings: MIL-B-16166
Characteristics Typical Uses. Produced in rod and bar forms. Applications include bearings, bushings, nuts, bolts, gears, valve guides, pumps, cams, and products
Thmperature OF
Yield strength(a) MPa ksl
778 682 663 652 550 465 196 103
112.8 98.9 96.2 94.5 79.8 67.5 28.5 15.0
390 340 326 320 296 296 138 92
56.5 49.3 47.3 46.4 43.0 43.0 20.0 13.3
37 34 34 34 22 10 32 18
41 41 44 44 22 13 33 29
127 108 114
-60 -29 20 205 315 425 540
-295 -75 -20 70 400
600 800 1000
762 664 647 620 534 448 210 94
110.5 96.3 93.8 90.0 77.5 65.0 30.5 13.6
377 330 323 294 302 288 153 84
54.7 47.9 46.9 42.6 43.8 41.8 22.2 12.2
35 33 31 32 20 10 46 27
38 39 38 39 21 13 39 32
Alloy resists nonoxidizing mineral acids, but hydrochloric is more corrosive than other acids of this type. Also, alloy resists dealloying, but to lesser extent than C61300 and C61400. In addition, C62300 cannot be used in oxidizing acid such as nitric Machinability. Fair, and good finish is possible. Carbide and tool steel cutters are used. Typical practice with steel cutters: roughing speed, 107 m1min (350 ft/min) with feed of 0.3 mmlrev (0.011 in.lrev); fmishing speed, 350 m1min (1150 ft/min) with feed of 0.15 mm1rev(0.006 in.lrev)
Joining. Properties are good for gas-shielded are, shielded metal are, and all types of resistance welding; brazing properties are fair. Not recommended: soldering and oxyfuel gas welding
Recommended Heat Treating Practice
Cold finished -182
General Corrosion Resistance. For general corrosion behavior, see article on C61400
Formability. Cold and hot working properties are good
Modulus or Elongation elasticity In 50 mm Reduction intension Hardness, (210.),% In area, II> GPa 10· psi HB(b)
ThmUe strength MPa ksi
Microstructure. Has duplex structures of face-centered cubic alpha plus metastable, body-centered cubic beta with iron-rich precipitates
Forgeability. 75% that of C37700 (forging brass)
C62300: Typical mechanical properties of rod at various temperatures
-c
requiring resistance to corrosion. Caveat: not suitable for use in oxidizing acids
114 85 54 41
18.4 15.7 16.5 16.1 16.5 12.4 7.9 5.9
193 170 168 165 152 148 98 54
125 121 124 120 138 79 73 51
18.1 17.5 18.0 17.4 20.0 11.5 10.6 7.4
195 171 168 161 151 146 97 46
111
Annealing. Temperature range is 600 to 650°C (1110 to 1200 "F) Hot Working. Temperature range is 700 to 875 °C (1290 to 1610 "F) Hot shortness temperature is 1010 °C (1850 OF)
Annealed -182
-60 -29 20 205 315 425 540
-295 -75 -20 70 400
600 800 1000
(a) At 0.5% extension under load. (b) 3000 kg (6615Ib) load
C62300: Typical compressive properties for rod, H50 temper
Rod diameter
0.111> MPa ksI
g5 nun (:!>1 in.) 25-50 nun (1-2 in.) 50-75 nun (2-3 in.)
360 345 315
52 50 46
Compressivestrength at pennanent ..t or 1% lOll> MPa ksi MPa ksl
485 450 415
70 65 60
825 675
6W
120 98 90
2011> MPa ksi
965 930 895
140 135 130
368/ Heat Treater's Guide: Nonferrous Alloys
C62300: Charpy V-notch. Variation in Charpy V-notch impact strength with temperature
Temperature. of -200
80
0
200 400 600
800 1000
LIVE GRAPH Click here to view
-,
f
60 I----+----+---+------j ~ jCOld finished 40 ~ 40
/'
'\
1
j
20
/
/
'
I~i""ealed
o
-200
0
200
~~ 400
0
600
Temperature.YO
C62400 (86Cu-11AI-3Fe) Common name. Aluminum bronze, 11% Chemical Composition. Composition Limits. 82.80 to 88.00 Cu, 10.00 to 11.50 AI, 2.00 to 4.50 Fe, 0.30 Mn max, 0.25 Si max, 0.20 Sn max, 0.50 others max (total). Caveat: excessive Si and Al reduce ductility
Specifications (U.S. and/or Foreign). SAE J463
(0.011 in.lrev); fmishing speed, 290 mlmin (950 ftlmin) with feed of 0.1 mm1rev (0.004 in.lrev) Practice with carbide cutters at rate of 2.3 to 6.4 mrn (0.09 to 0.25 in.) cut: roughing speed, 53 mlmin (175 ftlmin) with feed of 0.3 mm1rev (0.011 in.lrev); finishing speed, 38 to 45 mlmin (125 to 150 ftlmin) with feed of 0.3 mm1rev (0.011 in.lmin)
Characteristics
Weldability. Similar to that of C62300
Duplex microstructure consists of alpha plus metastable beta phases and iron-rich precipitates
Recommended Heat Treating Practice
Typical Uses. Produced as rod and bar which are used in gears, wear
Annealing. Temperature range is 600 to 700 °C (1110 to 1290 "F)
plates, cams, bushings. nuts, drift pins, tie rods. Caveat: Parts can lose ductility with prolonged heating in range of 370 to 565°C (700 to 1050 "F), Also, alloy isn't suitable for use in oxidizing acids
General Corrosion Resistance. For general corrosion behavior, see article on C61400. Alloy resists nonoxidizing mineral acids, but hydrochloric is more corrosive than other acids of its type. Also, alloy is susceptible to dealloying, but heat treatment provides relief. In addition, alloy can't be used in presence of oxidizing acid like nitric
Machinability. 50% that of C36000 (free-cutting brass). Chips break readily. Carbide and tool steel cutters are used. Typical practice for tool steel cutters: roughing speed, 90 mlmin (300 ftlmin) with feed of 0.3 mlrev
Hot Working. Temperature range is 760 to 925°C (1400 to 1700 oF)
C62400: Typicalcompressive properties for rod, H50 temper Compressive strengthat pennanenl oel of
Ulllmale
Rod diameter
MPa
ksl
MPa
ksi
MPa
ksi
oompresslve strength MPa ksi
525 mm (SI in.) 25-50mm (1-2 in.) 50-75mm(2-3 in.)
290 220 175
42 32 25
470
68 58 48
885 825 795
128 120 115
1140 1090 1090
O.l~
l~
400
330
10~
16S 158 158
C62500 (82.7Cu-4.3Fe-13AI) Commercial Name. Trade names: AMPCO 21, Wearite 4-13
Typical Uses. Include guide bushings, wear strip, cams, sheet metal
Chemical Composition. Composition Limits. 12.50 to 13.50 AI, 3.50
forming dies, and forming rolls
to 5.00 Fe, 2.00 Mn max, 0.50 others max (total), bal Cu. Caveat: presence of elements such as Pb, Zn, P, and Si in more than trace amounts can cause hot shortness, reduced wear resistance, and increase tendency to spall
Microstructure. Primarily body-centered cubic beta phase with small crystals of ordered, close-packed, hexagonal gamma phase
Characteristics
ambient moisture and industrial atmospheres. But the alloy rarely is used in strongly corrosive environments. General corrosion properties are inferior to those of C62400 and C62300
Low ductility and low resistance to impact make it advisable to provide adequate structural support for C62500 components subjected to shock loads or high stress. Also, alloy's resistance to corrosion is inferior to that of aluminum bronzes containing less aluminum
General Corrosion Resistance. Corrosion resistance is adequate in
Machinability. 20% that of C36000 (free-cutting brass)
Wrought Copper /369 Formability. Hot forming properties are excellent. Cold working is not recommended
Recommended Heat Treating Practice Annealing. Temperature range is 600 to 650°C (1110 to 1200 "F)
Joining. Gas-shielded arc and shielded metal arc welding properties are good; brazing and resistance welding properties, fair. Not recommended: oxyfuel gas welding and soldering
Hot Working. Temperature range is 745 to 850 °C (1375 to 1560 "P)
C63800 (95Cu-2.8AI-1.8Si-O.40Co) Commercial Name. Trade name: Coronze
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 2.50 to 3.10 AI, 1.50
Annealing. Temperature range is 400 to 600°C (750 to 1110 "F). Also
to 2.10 Si, 0.25 to 0.55 Co, 0.80 Zn max, 0.10 Ni max, 0.05 Pb max, 0.10 Fe max, 0.10 Mn min, bal Cu
see adjoining figure on anneal resistance
Characteristics Typical Uses. Springs, switch parts, contacts, relay springs, glass sealing, porcelain enameling
C63800: Typical mechanical propertiesofsheet and strip
General Corrosion Resistance. C63800 is more resistant to stress corrosion than the nickel silvers, and are close to phosphor bronzes in performance. Resistance to crevice corrosion is far superior to that ofmost other copper alloys. At elevated temperatures, oxidation resistance is excellent. On the basis of weight gain after heating 2 to 24 h in air at temperatures of600 to 800 °C (1100 to 1300 OF), the alloy was consistently superior to Nickel 270, Nichrome (80Ni-20Cr), type 301 stainless steel, Incoloy 800 (ASTM B 408), C60600. Superiority was especially evident at 800°C (1300 OF)
Formability. Cold working and hot forming properties are excellent. Parts are formed by blanking, drawing, bending, shearing, and stamping Joining. Soldering usually is done with standard fluxes. Commonly used joining processes are brazing, gas-shielded arc welding, and all forms of resistance welding
Thmper
061 HOI H02 H03 H04 H06 H08 HIO
82 96 106 111 120 124 130 130(a)
565 660 730 765 825 855 895 895(a)
FJongatioo 105Omm (110.),'h
YIeldslreogth at 0.2'h offset MPa ksI
'Iensilestrength ksi MPa
56 82 93 99 109
385 565 640 680 750 780 800 820(a)
33 17 10 8 5 4 3 2(b)
113 116 119(a)
94 97 98 99 100 100 lOO(a)
C63800: Tensile properties. Typical short-time tensile properties of H02 temper Click here to view
C63800:Tensile properties. Annealresistanceof C63BOO strip, HOB temper. Typical room-temperature tensile properties for material annealed 1 h at varioustemperatures Click here to view
400
1000 BOO III
n,
:2
.£ ~
~
600
-
600
BOO I
-- l'\
\\ j
-
~ <:
I
Tinsile strength
I ....
I Yield strength
r--- t-.....
..... r-- . . . 30
Yield
I"ensile strergth
strengt~\\
" I~
250
Q)
I
"#.
200
~
E E
150
.!; <:
30 ~
o
I
lo
.~
1100
I
- 90
II
Il)
l----
/
h
100
0
ii Ol <: 0
V
As- 200 300 400 500 600 rolled Annealing temperature, °C
,,\
900
,
-, ,
400
200
700
0
I
r
500
'...........
o
"6> <:
(f)
o
o f---
~
90 ~ £ 60
200
V- f-
600
Testtemperature. OF
300
:2
120
\
400
III
1000 1200 I
BOO
n,
Annealing temperature, OF
iii 700
74 78 80 81 82 82 83 83(a)
(a) min. (b) max
LIVE GRAPH
LIVE GRAPH
Hardneos HRB IIRJOT
J
50
o 100
l-----'
V
200 300 400 500 Testtemperature. °C
600
370 I Heat Treater's Guide: Nonferrous Alloys
C65100 (98.5Cu-1.5Si) Commercial Names. Previous trade name. Low-silicon bronze B; Common name. Low silicon bronze Chemical Composition. Composition Limits. 0.80 to 2.00 Si, 0.05 Pb max, 0.80 Fe max, 1.50 Zn max, 0.70 Mn max, bal Cu Specifications {U.S. and/or Foreign}. (ASME) Bar, rod, shapes: SB98. Thbular products: SB315; (ASTM) Flat products: B 97. Bar, rod, shapes: B 98. Tubular products: B 315. Wire: B 99; (Government) QQ-C-591
Characteristics Typical Uses. Aircraft: hydraulic pressure lines. Hardware: anchor screws, bolts, cable clamps, cap screws, machine screws, marine hardware, nuts, pole line hardware, rivets, U-bolts. Industrial: electrical conduits, heat exchanger tubes, welding rod
C65100: Typicalmechanical properties ThnsIJe Temper
275 485 620
40 70 90
Wire, 2 mm (0.08 in.) diameter ~ _ ~
Shear strength Bardeess MPa ksI
105 380 460
15 55 67
50 15 12
55 HRF 80HRB 310 90HRB 345
45 50
%
ill
40
40
~
~
mew
~
~
ill
H02 H04 H06
550 690 725
63 70 71
15 11 10
310 345 365
80 100 105
Wire, 11 mm (0.44 ln.) diameter
Formability. Cold working and hot forming properties are excellent
HOO(21%) H02(37%) H04(60%)
Recommended Heat Treating Practice
Elongation inSOmm (2in.),%
Rod, 25 mm (1 ln.) thick
05035 H04(36%) H06(50%)
Machinability. 30% that of C36000 (free-cutting brass)
Joining. Properties for soldering, brazing, gas-shielded arc, resistance spot and resistance butt welding are excellent; oxyfuel gas and resistance seam welding properties are good; shielded metal arc welding properties, fair
Yield strength(a) MPa ksi
strength MPa ksi
435 550 655
435 485 490
63 80 95
40 45 50 53
30 20 12
Thbing,25 mm (1.0 ln.) outside diameter x 1.65 mm (0.065 in.) waU thickness
05015 ~~~
310
45
m
140
e
ill
20 40
55
68HRF
W
~HRB
(a)At0.5%extensionunderload
Annealing. Temperature range is 475 to 675°C (890 to 1245 OF) Hot Working. Temperature range is 700 to 875 °C (1290 to 1610 OF)
C65400 (95.4Cu-3.0Si-1.5Sn-O.1 Cr) Chemical Composition. Composition Limits. 2.70 to 3.40 Si, 1.20 to 1.90 Sn, 0.010 to 0.12 Cr, 0.50 Zn max, 0.05 Pb max, bal Cu
C65400: Nominal mechanical properties of C65400 strip
Characteristics Typical Uses. Provides high strength and good formability in combination with good resistance to stress relaxation. Uses include contact springs, connectors, and wiring devices Machinability. 30% that of C36000 (free-cutting brass) Formability. Cold working and hot forming properties are excellent Joining. Soldering and brazing properties are good; welding properties are rated excellent for all forms of resistance welding and gas-shielded arc welding; coated metal arc welding has fair rating
Temper
HOI H02 H03 H04 H06 H08 HI0
Tensile strength MPa ksI
570 655 725 790 825 890 930
83 95 105 115
lW 129 135
Yield strength MPa ksi
415 585 635 700 760 815 860
60 85 92
102 110 118 125
Elongation in 5Omm(2in.), %
Hardness,
30 W 13 6 5 3 2
82 92 95 97 99 100 101
HRB
Fatigue strength a110' cycles MPa ksI
235
34
255
37
Recommended Heat Treating Practice Annealing. Temperature range is 400 to 600 °C (750 to 1110 OF)
C65500 (97Cu-3Si) Commercial Names. Previous trade name. High silicon bronze A; Common name. High silicon bronze
Chemical Composition. Composition Limits. 2.80 to 3.80 Si, 0.50 Pb max, 0.80 Fe max, 1.50 Zn max, 1.50 Mn max, 0.60 Ni max, bal Cu
Wrought Copper /371 Specifications (U.S. and/or Foreign). (AMS) Bar, rod: 4615. Tubing: 4655; (ASME) Flat products: SB96. Bar, rod, shapes: SB98. Tubular products: SB315; (ASTM) Flat products: B 96, B 97, B 100. Bar, rod, shapes: B 98, B124. Forgings: B 283. Tubular products: B 315. Wire: B 99; SAE J463; (Government) QQ-C-591. Tubing: MlL-T-8231
C65500: Typicalmechanical properties ThllSile Thmper
strength MPa ksl
Yield strength(a) MPa ksi
Shear strength MPa ksl
Elongation inSOmm (2 In.), 'I
Flat products,l mm (0.04 in.) thick
Characteristics Typical Uses. Aircraft: hydraulic pressure lines. Hardware: bolts, burrs, butts, clamps, cotter pins, hinges, marine hardware, nails, nuts, pole line hardware, screws. Industrial: bearing plates, bushing, cable, channels, chemical equipment, heat exchanger tubing, kettles, piston rings, tanks, rivets, screen cloth and wire, screen plates, shafting. Marine: propeller shafts
Machinability. 30% that of C36000 (free-cutting brass) Forgeability. 40% that of C37700 (forging brass) Formability. Cold working and hot forming properties are excellent Joining. Properties are excellent for brazing, gas-shielded arc, and all forms of resistance welding. Soldering and oxyfuel gas welding properties are good; shielded metal arc welding properties, fair
Recommended Heat Treating Practice Annealing. Temperature range is 475 to 700 °C (890 to 1290 OF) Hot Working. Temperature range is 700 to 875°C (1290 to 1610 OF)
08070 08035 08015 HOI H02 H04 H06 H08
385 415 435 470 540 650 715 760
56 60 63 68 78 94 104 110
145 170 205 240 310 400 415 427
21 25 30 35 45 58 60 62
63 60 55 30 17 8 6 4
40 62 66 75 87 93 96 97
290 295 310 325 345 390 415 435
42 43 45 47 50 57 60 63
150 310 380 415
22 45 55 60
60 35 22 13
60 85 90 95
295 360 400 425
43 52 58 62
170 275 330 395 450 485
25 40 48 57 65 70
60 35 20 8 5 3
295 330 360 400 450 485
43 48 52 58 65 70
Rod, 25 mm (1.0 ln.) diameter 08050 H02(20%) H04(36%) H06(50%)
400 540 635 745
58 78 92 108
Wire, 2 mm (0.08 in.) diameter 08035 HOO HOI H02 H04 H08(80%)
415 485 550 675 860 1000
60 70 80 98 125 145
Thbing, 25 mm (1.0 ln.) outside diameter x 1.65 mm (0.065 in.) wall thickness 08050 H80(35%)
395 640
57 93
70 22
45 92
(a) At 0.5% extension under load
C68800 (73.5Cu-22.7Zn-3.4AI-O.4Co) Commercial Name. Tradename: Alcoloy
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 72.30 to 74.70 Cu, 3.00
Annealing. Temperature range is 400 to 600°C (750 to 1110 "F)
to 3.80 AI, 0.25 to 0.55 Co, 0.05 Pb max, 0.010 others max (total), bal Zn (25.10 to 27.10 Al + Zn)
Order Strengthening. Temper rolled C68800 when heated to 220°C
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 592
Characteristics Typical Uses. Springs, switches, contacts, relays, terminal, plug receptacles. connectors
General.Corrosion Resistance. Alloy is more resistant than C26000 to corrosion and stress corrosion cracking
Formability. Cold working and hot forming properties are excellent. Suitable forming processes include blanking, drawing, bending, shearing, and stamping. Bending characteristics are nearly nondirectional for all annealed and rolled tempers Joining. Is soldered with mildly activated commercial fluxes. Tarnish resistance is substantially better than that of most alloys. Is also joined by brazing and resistance welding processes
(430 OF) undergoes an ordering reaction that increases strength (see adjoining Table). Parts should be given this treatment after forming because ductility is reduced. Specific times and temperatures for the treatment may vary, depending on the cold-worked temper. Caveat: susceptibility to stress corrosion cracking increases dramatically with an increase in the degree of ordering
Stabilization. The purpose of this treatment is to enhance stress relaxation. There is little change in 0.2% offset yield strength. Times and temperatures for the treatment vary, depending on cold worked temper; the ranges are 280 to 320 °C (540 to 610 OF) and 10 min to 2 h, respectively. To gain maximum benefit for stabilization, parts should be stabilized after forming. No increase in susceptibility to stress corrosion cracking results from the treatment
372/ Heat Treater's Guide: Nonferrous Alloys C68800: Typical mechanical properties of 1 mm (0.04 in.) thick strip
C68800: Typicalmechanical properties after low-temperature thermal treatment As-rolled ThIisllestrength
Yield strength .t 0.2 % offset
Thmper
MP.
ksi
MP.
ksi
H02(b) H04 H06 H08 HlO
695 750
101 109 122 129 13O(e)
640
93 97 110 114 117(e)
840 890 895(e)
670 760 785 805(e)
Stablllzation treated(.) Yieldstrength ThnsB. strength .to.2% offset MP. ksi MP. ksi
725 780 910 960 965
105 113 132 139 140
690 740 895 925 945
100 107 130 134 137
(a) Heated 1h at 205 to 230°C (400 to 450 "P), (b) Stabilization treatment is not effective on HOO or HOltemper material. (e) min
Thmper
Thnsllestrength ksl MP.
06O(a) 050 HOI H02 H04 H06 H08 HlO
565 615 650 725 780 825 885 895(b)
82 89 94 105 113 120 128 130(b)
Yield strength .to.2% offoel MP. ksi
365 475 525 635 705 750 785 805(b)
53 69 76 92 102 109 114 117(b)
FJongation inSOmm (210.), %
35 30 20 9 5 3 2 2(e)
IIon1nes!I HRB HR30T
78
69
90.5 95
78 81 82.5 83 83.5 84(b)
97 98 99 99(e)
(a) Annealed C68800 usually has a very fine grainsize (OmO mm or less). (b) min. (e) max
C69000 (73.3Cu-22.7Zn-3.4AI-O.6Ni) Chemical Composition. Composition Limits. 72.00 to 74.50 Cu, 3.30 to 3.50 AI, 0.50 to 0.70 Ni, 0.05 Fe max, 0.025 Pb max, bal Zn
Recommended Heat Treating Practice
Characteristics
Annealing. Temperature range is 400 to 600 °C (750 to 1110 "F); stress relief annealing is carried out at 225°C (440 "F) for 1 h
Typical Uses. Electrical parts, contacts, connectors, switches, relays,
Hot Working. Temperature range is 790 to 840°C (1455 to 1545 "F)
springs, high strength shells
General Corrosion Resistance. Provides significantly better resistance to corrosion than C26000, in terms of uniform rate of corrosion and resistance to stress corrosion
Formability. Similar in behavior to C26000 in blanking, drawing, bending, stamping, and other cold forming operations, but directionability is lower in bending cold worked tempers. Cold working and hot forming properties are excellent
Joining. Resistance welding properties are good; soldering and brazing properties, fair-if an active flux is used. Not recommended: oxyfuel gas and arc welding
C69000: Typical mechanical properties
Thmper
OS025 HOI H02 H04 H06 H08 HlO EHT(a)
Thnsilestrength MPo ksl
565 650 715 780 825 870 895(b) 930
82 94 105 113 120 126 130(b) 135
Yield strength .to.2%off""t ksi MPo
360 525 635 700 750 785 805 875
52 76 92 102 109 114 117 127
Elongation inSOmm (210.), %
35 19.5 9 4.5 2.5 1.5 2(e) I
IIardne5s HRB HR30T
69 90.5 95 97 98 96 99(b) 84.5
(a) Cold rolled 50% and stress relief annealed I hat 220°C (430 oF). (b) min. (e) max
C69400 (81.5Cu-14.5Zn-4Si) Commercial Name. Previous trade name. Silicon red brass, CA691 Chemical Composition. Composition Limits. 80.00 to 83.00 Cu, 0.30 Pb max, 0.20 Fe max, 3.50 to 4.50 Si, bal Zn
Specifications (U.S. and/or Foreign). (ASTM) Rod: B 371 (CA694)
Characteristics Typical Uses. Valve stems requiring a combination of corrosion resistance and high strength; forged or screw machine parts
Machinability. 30% that of C36000 (free-cutting brass) Forgeability. 80% that of C37700 (forging brass)
Wrought Copper /373
Formability. Hot forming properties are excellent; cold working properties are poor
C69400: Typicalmechanical properties of copper alloy C69400 rod
Joining. Soldering and silver brazing properties are excellent; oxyfuel gas welding and resistance welding properties, good. Not recommended: arc welding
Thmper
Recommended Heat Treating Practice
060
YIeldstreoglh
HOO
621 586 550 689
0.5 1.0 2.0 0.75
13 25 51 19
Annealing. Temperature range is 425 to 650°C (795 to 1200 OF) Hot Working. Temperature range is 650 to 875 °C (1200 to 1610 OF)
'ThosIJe olrength MPa ksi
Section size mm 10.
90
85 80 100
(0.5.... exleDsioo
Ebogation
underload) ksi MPo
IoSOmm
Bardoeoo,
(110.),....
BRB
20
85 85 85 95
310 296 276 393
45 43 40 57
25 25 21
C70400 (92.4Cu-5.5Ni-1.5Fe-O.6Mn) Chemical Composition. Composition Limits. 91.20 Cu min, 4.80 to 6.20 Ni, 1.30 to 1.70 Fe, 0.30 to 0.80 Mn, 1.00 Zn max, 0.05 Pb max Specifications (U.S. and/or Foreign). (ASTM) Pipe: B 466. Tubing: B 111, B 359, B 395, B 543
Recommended Heat Treating Practice Annealing. Temperature range is 565 to 815°C (1050 to 1500 "F) Hot Working. Temperature range is 815 to 950 °C (1500 to 1740 oF)
Characteristics Typical Uses. Rolled strip, sheet, and tubing for industrial applications, condensers, condenser plates, evaporator and heat exchanger tubing, ferrules, salt water pipe, lithium bromide absorption system tubing, shipboard condenser intake systems Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, good Joining. Properties for soldering, brazing, and gas-shielded arc welding are excellent; properties for coated metal arc and resistance spot, seam, and butt welding are good; oxyacetylene properties, fair
C70400: Typicalmechanical properties
Thmper
Thnsile strength MPa lui
Strip 061 HOI H02 H04 H06 H08
260 350 395 440 485 530
Yieldstrength At 0.5"" At 0.1....otrJel extensionUDder load MPa list MPa lui
38 51 57 64 70 77
83
12 275 280 435 475 525
40 55 63 69 76
Ebogalioo
1050mm (110.),....
Hardoeoa BRB HRJOT
41 21 11 5 3 2{a)
8 54 57 67 65 72 68 75 69 76{a) 70{a)
Thbing,25 mm (l.0 in.)outside diameter x 1.65mm (O.065 in.) waUthickness 08015 285 41 97 14 46 58 HRF H55 330 48 250 36 18 67 HRF (a) min
C70600 (90Cu-10Ni) Commercial Names. Previous trade names. Copper-nickel 10%; CA706; Common name. 90-10 cupronickel Chemical Composition. Composition Limits. 0.05 Pb max, 1.00 to 1.80 Fe, 1.00 Zn max, 9.00 to 11.00 Ni, 1.00 Mn max, 0.05 others max (total), bal Cu Specifications (U.S. and/or Foreign). (ASME) Flat products: SBI71, SB402. Pipe: SB466, SB467. Tubing: SBlll, SB359, SB395, SB466, SB467, SB543; (ASTM) Flat products: B 122, B 171, B 402, B 432. Pipe:
B 466, B 467. Rod: B 151. Tubing: B 111, B 359, B 395, B 466, B 467, B 543, B 552; (SAE) Plate and tubing: J463; (Government) Bar, flat products, forgings, rod: MIL-C-15726 E(2). Tubing: MIL-C-I6420, MIL-T1638 C(2), MIL-T-23520 A(4). Condenser tubing: MIL-T-15OO5 F
Characteristics Typical Uses. Condensers, condenser plates, distiller tubes, evaporator and heat exchanger tubing, ferrules, salt water piping, boat hulls
374/ Heat Treater's Guide: Nonferrous Alloys
LIVE GRAPH Click here to view
General Corrosion Resistance. Alloy has excellent resistance to seawater Machinability. 20% that ofC36000 (free-cutting brass) Formability. Properties for cold working and hot forming are good
C70600: Mechanical properties. Mechanical properties of cold drawn C70600 tubing. Data for variation in mechanical properties with amount of cold reduction for tubing with a diameter of 60 mm (2.375 in.) and a wall thickness of 4.8 mm (0.1875 in.) wall
Joining. Properties for soldering, brazing, gas-shielded arc and resistance butt welding are excellent; properties for shielded metal arc and resistance spot and seam welding, good; properties for oxyfuel gas welding, fair
500
I
Tensile strenglh
..V ~ V ...-
.:
400
Recommended Heat Treating Practice
III
a.. ::;;
Annealing. Temperature range is 600 to 825°C (1110 to 1520 OF)
,5 300 c
~
Tensile
strength MPa ksi
Flat products, 1 mm (0.04 in.) tbick 05050 350 51 90 05035 358 52 98 05025 365 53 110 HOI 415 60 330 H02 468 68 425 H04 518 75 490 H06 540 78 518 H08 565 82 540 HIO 585 85 540
13 14 16 48 62 71 75 78 78
90 98 110 338 435 500 525 545 545
13 14 16 49 63 72
76 79 79
'w -'" ,5 0)
40
c
~
(j)
/ 200
Temper
Yield strength at 0,05°(°_ extension under load
/
1/
C70600: Typical mechanical properties of C70600 and C71000 Yield strength At0.5% extensionunderload At0.2%offset MPa ksi MPa ksI
60
/\
V ;'
0)
Hot Working. Temperature range is 850 to 950 (1560 to 1740 "F)
~
I
- 20
Elongation in SO DlDl
Hardness
(2in.),%
HRF
HRB
35 35 35 20 8 5 4 3 3
72
25 27 30 58 75 80 82 84 86
Thbing, 25 mm (1 in.) outside diameter x 1.65 mm (0.065 in.) wall tbickness 05025 338 49 125 18 40 H55 468 68 430 62 14 Wire, 2 mm (0.080 in.) diameter HIO 655 95 585 85 5
73 75 92 100
1\
I----
<J) <J)
80
V
Q)
c
...- ..-
1:'
25 76
I
I-
~ <, Rockwell F
/ /;
III
72
<,
-7
Rockwell B
/
40
/ /
o
o
20
40
60
80
Cold reduction, %
C70600: Microstructure. Copper-nickel, 10% Ni, semicontinuous cast. Microstructure shows the distinct segregation of the copper-rich phase (dark) and the nickel-rich phase (light). Etchant; 169 c-o, 1.8 g NH4CI, 10 mL HN03 , 200 mL Hp. 50x
C70600: Microstructure. Copper nickel, 10% Ni, 2.3 mm (0.090 in.) thick. Laser welded to 1020 steel base. Weld made with 2.0 kW of laser input energy at travel speed of 17 to 25.4 mm/s (40 to 60 in.lmin). No melting of the steel base occurred. Etchant; 1 part acetic acid, 1 part HN03 , 2 parts acetone. 15x
Wrought Copper I 375
C70600: Microstructure. Copper nickel, 10% Ni, showing the grain-boundary cracks (dark areas) typical of stress-rupture failure. Etchant; 2 g K2CrP7' 8 mL H2 S0 4 , 4 mL NaCl, 100 mL Hp. 300x
C71000 (80Cu..20Ni) Commercial Name. Previous trade names. Copper-nickel, 20%; CA71O; Common names: 8020 cupronickel
Machinability. 20% that of C36000 (free-cutting brass) Formability. Properties for cold working by blanking, forming, and bending are good, as are properties for hot forming
Chemical Composition. Composition Limits. 0.05 Pb max, 1.00 Fe max, 1.00 Zn max, 19.00 to 23.00 Ni, 1.00 Mn max, 0.50 others max (total), bal Cu
Joining. Properties for soldering, brazing, gas-shielded arc welding, and
Specifications (U.S. and/or Foreign). (ASME) Pipe: SB466, SB467.
all types of resistance welding are excellent. Properties for shielded metal arc welding are good; properties for oxyfuel gas welding, fair
Tubing: SBIIl, SB359, SB395, SB466, SB467; (ASTM) Bar and flat products: B 122. Pipe: B 466, B 467. Tubing: BIll, B 359, B 395, B 466, B 467. Wire: B 206; (SAE) Bar, flat products, tubing: J463
Annealing. Temperature range is 650 to 825°C (1200 to 1520 OF)
Recommended Heat Treating Practice Hot Working. Temperature range is 875 to 1050 °C (1610 to 1920 OF)
Characteristics Typical Uses. Communication relays, condensers, condenser plates, electrical springs, evaporator and heat exchanger tubing, ferrules, resistors
C71000: Typical mechanical properties of C70600 and C71000 Yieldstrength 'Iensile strength 'Iemper
MPa
ksi
At 0.5% extensionunder load MPa ksi
350 358 365 415 468 518 540 565 585
51 52 53 60 68 75 78 82 85
90 98 110 330 425 490 518 540 540
13 14 16 48 62 7l 75 78 78
At 0.2% offset ksi MPa
Elongation in SO nun (210.),%
Hardness HRF
HRB
72
25 27 30 58 75 80 82 84 86
FIat products, 1 mm (0.04 in.) thick 08050 08035 08025 HOI H02 H04 H06 H08 HIO
90 98
no 338 435 500 525 545 545
13 14 16 49 63 72
76 79 79
35 35 35 20 8 5 4 3 3
73 75 92 100
Thbing, 25 mm (1 ln.) outside diameter x 1.65 mm (0.065 in.) wall thickness 08025 H55
338 468
49 68
125 430
18 62
40 14
655
95
585
85
5
Wire,2 mm (0.080 ln.) diameter HIO
72
25 76
376/ Heat Treater's Guide: Nonferrous Alloys
C71500 (70Cu..30Ni) Commercial Names. Previous trade names. Copper-nickel, 30%: CA715; Common name. 70-30 cupronickel Chemical Composition. Composition Limits. 0.05 Pb max, 0.40 to 0.70 Fe, 1.00 Zn max, 29.00 to 33.00 Ni, 1.00 Mn max, 0.5 others max (total), bal Cu Specifications (U.S. and/or Foreign). (ASME) Flat products: SB171, SB402. Pipe: SB466, SB467. Tubing: SBll1, SB359, SB395, SB466, SB467, SB543; (ASTM) Flat products: B 122, B 151, B 171, B 402. Pipe: B 466, B 467. Rod: B 151. Tubing: B 111, B 359, B 395, B 466, B 467, B 552; (SAE) Bar, flat products, tubing: J463; (Government) Bar, flat products, forgings, rod, wire: MIL-C-15726. Tubing: MIL-T-19005, MIL-T16420, MIL-T-22214
Characteristics Typical Uses. Condensers, condenser plates, distiller tube, evaporator and heat exchanger tubing, ferrules, salt water piping Machinability. 20% that of C36000 (free-cutting brass) Formability. Has good properties for cold working and hot forming by bending and forming Joining. Properties are excellent for soldering, brazing, all forms of resistance welding; properties for oxyfuel gas welding are good. Caveat: stress relieving or full annealing should precede exposure to solders of all kinds
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 825°C (1200 to 1520 "F) Hot Working. Temperature range is 925 to 1050 °C (1695 to 1920 OF)
C71500: Typical mechanical properties size Flat products 25 mm (I in.)plate I mm (0.04in.)strip
Rod <25mm(l in.)diameter 25 mm(1 in.)diameter Thbing 29 mm (0.75 in.) outsidediameterx 1.25mm (0.049in.) wallthickness 25 mm (I in.) outsidediameterx 1.65mm(0.065in.) wall thickness 114mm(4.5in.)outsidediameterx 2.75mm(0.109 in.) wallthickness
Tensile strength ksi
Thmper
MPa
M20temper 061temper(b) H80temper
380 380 580
55 55 84
061temper(c) H80 temper(d) H02 temper(e)
380 585 515
55 85 75
061 temper(b) H80temper OS025temper OS035temper
340 580 415 370
49 84
Yieldstrength(a) MPa ksi
140 125 545
140 540 485
170
60
20 18 79
45 36 3
36
20 78 70
45 15
15
37 81 80
50 4 45 45
45 36
25
54
Elongation in 50 mm(21n.), %
40 86
(a)0.5%extensionunderload. (b)Annealedat705 °C (1300 "P). (c)Annealedat760 °C (1400 "F), (d) Colddrawn50%.(e) Colddrawn20%
C71500: Microstructure. Copper nickel, 30% Ni, as-cast. Longitudinal section showing columnar structure near the surface of the billet. The grains are inclined upward from horizontal by up to 30° due to convection in the initial state of freezing. Etchant; 5 parts HN03 , 5 parts acetic acid, 1 part H3P04 , then 59 g FeCI3 , 96 mL ethanol. 0.3x
C71500: TypicalCharpy impact strengths Thsting temperature "C OF
-115 -18 3 20 65 120 205
-175
o
38 68 150 250 400
Charpy Impact strength(a) J R·!bf
81 81 87 89 72 72 68
60 60 64 66
53 53 50
(a) For 10 mm (0.39 in.) square keyholespecimensmachined fromannealedrod
Wrought Copper /377
C71500: Tensile and yield strengths. Typical properties of C71500 rod
LIVE GRAPH
LIVE GRAPH Click here to view 700
Click here to view
Testing temperature, of
--400
T400
700
100
600
Testing temperature, of
o
--400
<,
600
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~ <,
80 500
500
If
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If
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60
400
t;, e
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300
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400
t:
-e
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300
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ci
Cold drawn 40%
.... Cold drawn 70%
100
•
-5
N
• Cold drawn 26%
200
400
200
20
o Cold drawn 25% and annealed
100
~~
800
400
600
800
0 1000
o
-400
-200
o
Testing temperature, °c
I
100
80
~'\ 1\ ~\ ~
-
\
~
• Cold drawn 40% and annealed
+200
1600
I
-,
20
-a....:
v Cold drawn 70% and annealed
0 -400
1200
'200
400
~ ~.ri
600
800
o 1000
Testing temperature, °c
C71900 (67.2Cu-30Ni-2.8Cr) Commercial Name. Previous trade names. Copper-nickel, chromiumbearing; CA719; Common name. Cupronickel with Cr Chemical Composition. Composition Limits. 28.00 to 32.00 Ni, 2.40 to 3.20 Cr, 0.5 Fe max, 0.20 to 1.00 Mn, 0.10 to 0.20 Ti, 0.02 to 0.25 Zr, 0.04 C max, 0.25 Si max, 0.50 others max (total), bal Cu
ing is not recommended. Material thick enough to require multipass welds develops a minimum yield strength of 345 MPa (50 ksi), as-welded. Single pass welds develop a minimum yield strength of 275 MPa (40 ksi) aswelded. This value can be raised to 345 MPa (50 ksi) by a postweld heat treatment: 1 h at 480°C (900 OF)
Characteristics
Recommended Heat Treating Practice
Typical Uses. Heat exchange tubing, tube sheets, water boxes, ferrules, seawater pipe
Full properties of the spinodally decomposed condition can he obtained by furnace or still air cooling through the temperature range of 760 to 425°C (1400 to 795 "F) from a soaking temperature of 900 to 1065 °C (1650 to 1950 OF)
General Corrosion Resistance. In seawater, C71900 resists both general and localized attack. Corrosion rate is low-generally less than 0.1 mm/yr, or less than 4 mils/yrin seawater flowing at velocity around 1.8 mls (6 ftls). Welding does not have an adverse effect on corrosion resistance; and the alloy appears to be immune to stress-corrosion cracking in seawater Formability. C71900 can be cold worked in a manner similar to that for C71500, although C71900 has higher tensile and yield strengths at any given reduction. C71900 is readily hot worked from a starting temperature of 1040 to 1065 °C (1905 to 1950 OF), but hot working should not be continued below 840°C (1545 "F) because ofreduced ductility. About 25 % more extrusion pressure is required in comparison with practice for C71500. Because of microsegregation, cast billets should be homogenized 3 to 4 h at 1040 to 1065 °C (1905 to 1950 OF) before being extruded Joining. Properties for soldering, brazing, and all forms of arc welding are excellent. Resistance welding normally is not used. Oxyfuel gas weld-
C71900: Typical mechanical properties Yield strength
Condllion
MPa
ksi
at 0.2% offset MPa ksI
Heattreated(a) Half-hard temper(b) Hardtemper(c) Springtemper(d)
600 730 780 835
87 106 113 121
365 685 740 800
'Thll'lile strength
53
99 107 116
so mm (2 in.), %
EIongalionln
Hardness, HRB
32 14 8 6
87 100 100 101
(a)Spinodallydecomposedby air coolingfrom 900 °C (1650 "F). (b) Spinodallydecomposed.then cold rolled 20%. (c) Spinoda1ly decomposed.then cold rolled 37%. (d) Spinodally decomposed. thencold rolled60%
378/ Heat Treater's Guide: Nonferrous Alloys
C72200 (83Cu-16.5Ni-O.5Cr) Commercial Names. Previous trade names. Copper-nickel, chromiumbearings; CA722; Common name. Cupronickel with Cr Chemical Composition. Composition Limits. 15.00 to 18.00 Ni, 0.30 to 0.70 Cr, 0.50 to 1.00 Fe, 0.40 to 0.90 Mn, 0.03 Si max, 0.03 Ti max, 0.03 C max, 0.5 others max (total), bal Cu
Formability. Has good properties for cold working and hot forming Joining. Properties for gas-shielded arc welding are excellent. Properties are good for soldering, brazing, shielded metal arc welding. and all types of resistance welding; oxyfuel gas welding properties are fair
Recommended Heat Treating Practice
Characteristics
Annealing. Temperature range is 730 to 815°C (1345 to 1500 OF)
Typical Uses. Condenser and heat exchanger tubing, saltwater pipe
Hot Working. Temperature range is 900 to 1040 °C (1650 to 1905 OF)
C72500 (88.2Cu-9.5Ni-2.3Sn) Commercial Name. Previous trade names. Copper-nickel. tin-bearing; CA725; Common name. Cupronickel with Sn
Chemical Composition. Composition Limits. 0.05 Pb max, 0.6 Fe max, 0.2 Mn max. 8.50 to 10.50 Ni, 1.80 to 2.80 Zn, 0.2 others max (total), balCu
Characteristics
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 800°C (1200 to 1470 "F) Hot Working. Temperature range is 850 to 950 °C (1560 to 1740 "F)
C72500: Typical mechanical properties Yield strength 0.5 % extension
Typical Uses. Relay and switch springs, connectors. lead frames, control and sensing bellows, brazing alloy
General Corrosion Resistance. Alloy has excellent resistance to corrosion in seawater
Machinability. 20% that of C36000 (free-cutting brass) Formability. Has excellent capacity for cold working and hot forming by blanking, coining, drawing, forming, bending, heading, upsetting, roll threading, knurling, shearing, spinning. squeezing, stamping, and swaging Joining. Properties are excellent for soldering. brazing, and resistance spot and butt welding. Properties are good for gas-shielded are, shielded metal are, and resistance seam welding; properties for oxyfuel gas welding are fair
Temper
Thnsllestrength MPa ksl
under load MPa ks\
Elongation
0.2% offset MPa ks\
in SOmID (2 In.). %
Hardness, HRB
35 18 6 3 2 1 1
42 71 78 85 88 90 99
Flat products, 1 mm (0.04 In.) thick Annealed(a) Quarter hard Halfhard Hard Extrahard Spring Superspring
380 450 490 570
600 625 770
55 65 71 83 87 91 112
Wire, 2 mm (0.08 in.) diameter Annealed(a) . 415 60
150 365 450 515 555 570 570
22 53 65 75 81 83 83
170
25
150 400 475 555 590 620 740
22 58 69 81 86 90 108
(a) Grain size. 0.015 mm
C74500 (65Cu-25Zn-10Ni) Commercial Name. Nickel silver. 65-10
Machinability. 20% that of C36000 (free-cutting brass)
Chemical Composition. Composition Limits. 63.50 to 68.50 Cu. 9.00 to 11.00 Ni, 0.10 Pb max, 0.25 Fe max, 0.5 Mn max. 0.5 others max (total). balZn
ties are poor
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; (Government) Flat products: QQ-C-585. Bar: QQ-C-585. Rod, shapes, flat wire: QQ-C-586. Wire: QQ-W-321
Characteristics Typical Uses. Hardware. rivets. screws, slide fasteners, optical, optical parts. Miscellaneous: etching stock, hollowware. name plates, plater's bars
Formability. Cold working properties are excellent; hot forming properJoining. Soldering and brazing properties are excellent. Properties are good for oxyfuel gas. resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding
Recommended Heat Treating Practice Annealing. Temperature range is 600 to 750°C (1110 to 1380 "F)
Wrought Copper /379
C74500: Typical mechanical properties Temper
Tensile strength MPa k.sI
Yield streugthta) MPa k.sI
Elongation in SOmm!2ln.), %
HRF
Hardness HRB
HR30T
Shear strength MPa ksi
Flat products, 1 mm (0.04 in.) thick 05070 05050 05035 05025 05015 Hoo HOI H02 H04 H06 Wire,2 mm (0.08 in.) diameter
340 350 365 385 415 415 450 505 590 655
49 51 53 56 60 60 65 73 86 95
05070 05050 05035 05025 05015 Hoo(IO%) HOI (20%) H02(37%) H04(6O%) H06(75%) H08(84%)
345 360 385 400 435 450 495 585 725 825 895
50 52 56 58 63 65 72 85 105 120 130
125 130 140 160 195 240 310 415 515 525
18 19 20 23 28 35 45 60 75 76
49 46 43 40 36 34 25 12 4 3
67 71 76 80 85
22 28 35 42 52 60 70 80 89 92
30 34 38 44 51 55 63 70 76 78
285
41
295 310 345 380 405
43 45 50 55 59
50 48 45 40 35 25 10 7 5 3 1
(a) At 0.5% extensionunderload
C74500: Microstructure. Cold-rolled sheet, 2.5 mm (0.10 in.) thick, annealed at 650 to 700°C (1200 to 1290 OF). Longitudinal section shows equiaxed crystallized grains of a solid solution containing twin bands. Etchant; 60 g FeCls' 20 g Fe(NOs)s, 2000 mL Hp.100x
C75200 (65Cu..18Ni..17Zn) Common Name. Nickel-silver 65-18 Chemical Composition. Composition Limits. 63.00 to 66.50 Cu, 16.50 to 19.50 Ni, 0.1 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; SAE J463; Government QQ-C-585. Bar: QQ-C-585, QQ-C-586. Rod, shapes, flatwire: QQ-C-586. Wire: QQ-W-321
Characteristics Typical Uses. Hardware, rivets, screws, table flatware, truss wire, zippers, optical goods, camera parts, core bars, templates. Miscellaneous: base for silver plate, costume jewelry, etching stock, hollowware, nameplates, radio dials Machinability. 20% that of C36000 (free-cutting brass) Formability. Cold working properties are excellent; hot forming properties, poor
380 I Heat Treater's Guide: Nonferrous Alloys Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties, fair. Not recommended: shielded metal arc welding
C75200: Typical mechanical properties
'Thmper
Recommended Heat Treating Practice
'ThnslJe strength ksI MPa
Yield strength(a) MPa IIsI
Eiongationin SO mm(11o.), ...
IIardneos
HRF
ORB IIR30T
Flat products. 1 mm (0.04 in.) thick 08035 08015 HOI H02 H04
Annealing. Temperature range is 600 to 750°C (1110 to 1380 OF)
400 415 450 510 585
58 60 65 74 85
170 205 345 427 510
25 30 50 62 74
40 32 20 8 3
170 415
25 60
42 20
170 205 450 550 620
25 30 65 80 90
45 35 16 7 3
85
09
40 55 73 83 87
65 72 75
Rod. 13 mm (O.Sln.) diameter 08035 H02(20%)
385 485
56 70
78
Wires,2 mm (0.08 in.) diameter 08035 08015 HOI H02 H04
400 415 505 590 710
58 60 73 86 103
(a) At 0.5% extension under load
C75400 (65Cu-20Zn-15Ni) knurling, shearing, spinning, squeezing, swaging. Hot forming properties are poor
Common Name. Nickel-silver, 65-15 Chemical Composition. Composition Limits. 63.50 to 66.50 Cu, 14.00
Joining. Soldering and brazing properties are excellent; properties are
to 16.00 Ni, 0.10 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn
good for oxyfuel gas resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding
Characteristics Typical Uses. Camera parts, optical equipment, etching stock, jewelry
Recommended Heat Treating Practice
Machinability. 20% that of C36000 (free-cutting brass)
Annealing. Temperature range is 600 to 815°C (1110 to 1500 "F)
Formability. Cold working properties are excellent-Processes include blanking, drawing, forming, bending, heading, upsetting, roll threading,
C75400: Typical mechanical properties of sheet or strip, 1 mm (0.04 ln.) thick 'ThnslJe 'Iemper
MPa
ks1
Yield strength(a) lIsi MPa
08070 08050 08035 08025 08015 HOO HOI H02 H04 H06
365 380 395 405 420 425 450 510 585 635
53 55 57 59 61 62 65 74 85 92
125 130 145 165 195 240 340 425 515 545
strength
(a) At 0.5% extension under load
18 19 21 24 28 35 49 62 75 79
Elongation in SOmm (1 In.)....
43 42 40 37 34 30 21 10 3 2
Hordness HRF HR30T
69 73 79 82 89 60HRB 70HRB 80HRB 87HRB 90HRB
27 33 41 46 53 55 63 70 75
77
Shear strength MPa ksi
285
295 305 325 360 370
41
43
44 47 52
54
Wrought Copper I 381
C75700 (65Cu-23Zn-12Ni) Common Name. Nickel-silver, 65-12 Chemical Composition. Composition Limits. 63.50 to 66.50 Cu, 11.00 to 13.00 Ni, 0.05 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn
Formability. Cold working properties are excellent-processes include blanking, drawing, forming, bending, etching, heading, upsetting, roll threading, knurling, shearing, spinning, squeezing, swaging. Hot forming properties are poor
Characteristics
Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding. Gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding
Typical Uses. Slide fasteners, camera parts, optical parts, etching stock, nameplates
Recommended Heat Treating Practice
Machinability. 20% that of C36000 (free-cutting brass)
Annealing. Temperature range is 600 to 825°C (1110 to 1520 "F)
Specifications (U.S.and/or Foreign). (ASTM) Bar, rod: B 151. WIre:B 206; (Government) Wire: QQ-W-321
C75700: Typical mechanical properties of sheet or strip, 1 mm (0.04 in.) thick 'Iensllestrength 'Iemper
MPa
ksi
YIeldst">ngth(a) MPa ksi
OS070 OS050 OS035 OS025 OS015 HOO HOI H02 H04 H06
360 370 385 405 420 415 450 505 585 640
52 54 56 59 61 60 65 73 85 93
125 130 145 165 195 240 310 415 515 545
Elongation ln
18 19 21 24 28 35 45 60 75 79
50 IDDl (2 ln.), Ili
HRF
48 45 42 38 35 32 23 11
69 73 78 82 88
4 2
Shoarstrength ksi
Hardness HRB HRJOT
22 30 37 45 55 60 70 80 89 92
MPa
27 33 38 44 51 55 63 70 75 77
285
41
295 305 325 360 385
43 44 47 52 56
(a) At 0.5% extension under load
C77000 (55Cu-27Zn-18Ni) Common name. Nickel-silver, 55-18
Recommended Heat Treating Practice
Chemical Composition. Composition Limits. 53.50 to 56.50 Cu, 16.50 to 19.50 Ni, 0.10 Pb max, 0.25 Fe max, 0.50 Mn max, 0.50 others max (total), bal Zn
Annealing. Temperature range is 600 to 825°C (1110 to 1520 OF)
Specifications (U.S. and/or Foreign). (ASTM) Flat products: B 122. Bar: B 122, B 151. Rod: B 151. Wire: B 206; SAE J463; (Government) Flat products: QQ-C-585. Bar: QQ-C-585, QQ-C-586. Rod, shapes, flat wire: QQ-C-586. Wire: QQ-W-321
C77000: Typical mechanical properties Thnsilestrength MPa ksi
Yield strength(a)
Characteristics
'Iemper
Typical Uses. Optical goods, springs, resistance wire
Flat products,1 mm (0.04 In.) thick OS035 415 60 185 H04 690 100 585 H06 745 108 620 H08 795 115 Wire, 2 mm (0.08 in.) diameter OS035 415 60 H08 (68%) 1000 145
Machinability. 30% that ofC36000 (free-cutting brass) Formability. Properties are good for cold working by blanking, forming, bending, shearing; hot forming properties are poor Joining. Soldering and brazing properties are excellent; properties are good for oxyfuel gas, resistance spot and resistance butt welding; gas metal arc and resistance seam welding properties are fair. Not recommended: shielded metal arc welding
(a}At 0.5% extension under load
MPa
ksi
27 85 90
Elongation ln 50 IDDl (210.), Ili
HRF
40
90
3 2.5
2.5 40 2
Hardness HRB HRJOT
55 91 % 99
77 80 81
382/ Heat Treater's Guide: Nonferrous Alloys
C78200 (65Cu-25Zn-8Ni-2Pb) Chemical Composition. Composition Limits. 63.00 to 67.00 Cu, 1.50 to 2.50 Pb, 7.00 to 9.00 Ni, 0.35 Fe max, 0.50 Mn max, 0.10 others max (total), bal Zn
Characteristics Typical Uses. Key blanks, watch plates, watch parts Machinability. 60% that of C36000 (free-cutting brass) Formability. Cold working properties are good; hot forming properties, poor. Commonly fabricated by blanking, milling, drilling Joining. Soldering properties are excellent; brazing properties, good. Generally not recommended: oxyfuel gas, are, and resistance welding
Recommended Heat Treating Practice Annealing. Temperature range is 500 to 620°C (930 to 1150 "F)
C78200: Typical mechanical properties of 1 mm (0.04 in.) thick sheet
Thmper
Thnsile strength MP. lui
Yield strength(.) MP. lui
05035 05015 HOI H02 H03 H04 H06
365 405 425 475 540 585 625
160 185 290 400 435 505 525
53 59 62 69 78 85 91
(a>At 0.5% extension under load
23 27 42 58 63 73 76
Ekmgatkm inSOmm (2in.), %
40 32 24 12 5 4 3
Hardness, HRB
78HRF 85HRF 65 78 84 87 90
Shear strength MP. Ioii
275 295 305 325 350 370 400
40 43 44 47 51 54 58
Copper Casting Alloys C81300 Commercial Names. Previous trade name. CA813; Common name. Beryl-
Applications
Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involing beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Typical Uses. Higher-hardness electrical and thermal conductors
Recommended Heat Treating Practice
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease.
Solution Heat Treating. Temperature range is 980 to 1010 °C (1800 to
lium-copper
ChemicalComposition. Composition Limits. 98.5 Cu min, 0.10 to 0.20 Be, 0.6 to 1.0 Co. (Cu + sum of named elements shall be 99.5% minimum.)
1850 oF)
Aging. Temperature is 480°C (900 "P) Stress-Relieving. Temperature is 260 °C (500 OF)
C81400 Commercial Names. Previous trade name. Beryllium-eopper 7OC,CA814; Common name. Be-modified chrome copper
ChemicalComposition. Composition Limits. 98.5 Cu min, 0.6 to 1.0 Cr, 0.02 to 0.10 Be
Specifications (U.S. and/or Foreign). RWMA Class 11
Applications Typical Uses. Electrical parts that meet RWMA Class 11 standards. The beryllium content of this alloy ensures that the chromium content will be kept under control during melting and casting, thus allowing the production of chrome copper castings of consistently high quality
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-
lium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 1000 to 1010 °C (1830 to 1850 OF)
Aging. Temperature is 480°C (900 oF)
C81500 Commercial Names. Previous trade names. Chromium-copper, CA815; Common name. Chrome copper Chemical Composition. Composition Limits. 98.0 to 99.6 Cu, 0040 to 1.50 Cr, 0.015 Pb max, 0.04 P max, 0.15 max other (total)
Consequence of Exceeding Impurity Limits. Elements that contribute to hot shortness must be avoided. Because of the high solution temperatures
necessary to develop the desired mechanical properties, elements that enter into solid solution must be held to close limits
Applications
buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Typical Uses. Electrical and/or thermal conductors used as structural
Recommended Heat Treating Practice
members in applications requiring greater strength and hardness than that of cast coppers C80100 to C81100
Solution Heat Treating. Temperature range is 1000 to 1010 °C (1830 to
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and
1850 OF)
Aging. Temperature is 480°C (900 oF)
384/ Heat Treater's Guide: Nonferrous Alloys
C81800 (97Cu-1.5Co-1 Ag-0.4Be) Commercial Names. Previous trade name. Beryllium-copper alloy SOC, CA818 Chemical Composition. Composition Limits. 0.30 to 0.55 Be, 1.4 to 1.7 Co, 0.8 to 0.12 Ag, 0.15 Si max, 0.20 Ni max, 0.10 Fe max, 0.10 Al max, 0.10 Sn max, 0.002 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications. RWMA Class III
Typical Uses. The silver content of C81800 provides an improved surface conductivity over other RWMA Class III alloys. Typical uses are resistance welding electrode tips and holders and arms Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with
300
Q)
<::
200
<1l
I
150
100
I r/
o
2
As-cast Cast and aged(c) TBOO(c) TFOO(c)
345 450 310 705
50 65 45 102
YIeldstrength(a) MPa 1<51
140 275 83 515
20 40 12 75
Elooga,ion(h), %
Hardness, HRB
20 15 25 8
50 70 40 96
(a) At 0.2% offset. (b) In 50mm(2 in.). (c) Aged 3 hat480·C(900°Fj
\
(/ ""./'
:r:
Thnslle strength MPa 1<51
Thmper
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\
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C81800: Typical mechanical properties
LIVE GRAPH
400-425 ·C
::f
Solution Heat Treating. Temperature range is 900 to 925°C (1650 to 1700 oF)
C81800: Aging curves for cast and solution-treated C81800
I
250 lD
Recommended Heat Treating Practice
Aging. Temperature is 480 °C (900 oF). See adjoining figure
Applications
:r:
these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
--I 540 ·C
370°C
-
- r--
f---
I 3
4
5
6
7
8
Aging lime, h
C82000 (97Cu-2.5Co-0.5Be) Commercial Names. Previous trade name. Beryllium-copper alloy lOC, CA820; Common name. Beryllium-copper casting alloy lOC Chemical Composition. Composition Limits. 0.45 to 0.8 Be, 2.4 to 2.7 Co, 0.15 Si max, 0.20 Ni max, 0.10 Fe max, 0.10 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S. and/or Foreign). GovernmentQQ-C-390 (CA820), MIL-C-19464 (Class I)
Applications Typical Uses. C82000 castings are used when a combination of high conductivity and high strength is required. Applications include resistance
welding tips, holders and arms, circuit-breaker parts, switch gear parts, plunger tips for die casting, concasting molds, for continuous casting installations, soldering-iron tips, brake drums, and whenever RWMAClass III properties are required
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Copper Casting Alloys /385
Recommended Heat Treating Practice
C82000: Typicalmechanical properties
Solution Heat Treating. Temperature range is 900 to 925°C (1650 to 1700 oF)
Thmper
ThmUe strengtb MPa Iud
Aging. Temperature is 480 °C (900 OF)
As-cast Castandaged(c) TBOO(d) TFOO(d)(e)
345 450 325 660
50 65 47 %
Yieldstrengtb(a) MPa IIsI
140 255 105 515
20 37 15 75
EIoogaoon(b). 'J>
lIBrdnes8, HRB
20
52 70 40 96
12 25
6
(a)At 0.2%offset. (h) In 50 mm (2 In.). (c)Aged2 h at 480 °C (900oF).(d)Solutiontreated at 900 to 950°C (1650to 1750oF).(e) Aged3 h at 480 °C (900°F)
300
250 al :I:
~
c:
200
~
r r>
150
100
/
/
1/ /
:I:
C82000: Aging curves for cast and solution-treated C82000
I
425-480°C
o
1/
/400°C
LIVE GRAPH Click here to view
~
V
/
V
370°C/
/ 540°C
/
/ 1/
2
3
4
5
6
7
8
Aging lime, h
C82200 (98Cu-1.5Ni-O.5Be) Commercial Names. Previous trade name. Beryllium-copper alloy 3OC, CA822; Common name. Beryllium-copper casting alloy 30C, 35C, or 53B
Chemical Composition. Composition Limits. 0.35 to 0.8 Be, 1.0 to 2.0 Ni, 0.15 Si max, 0.20 Co max, 0.10 Fe max, 0.10 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 900 to 955°C (1650 to 1750 oF)
Aging. Temperature range is 445 to 455 °C (835 to 850 oF)
Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening
Specifications (U.S. and/or Foreign). RWMA Class III
Applications Typical Uses. Seam welder electrodes,projection welder dies, spot welding tips, beam welder shapes: water-cooled holders, arms bushings for resistance welding, clutch rings, brake drums
Precautions In Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffmg under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
C82200: Typicalmechanical properties Thmper
As-cast Castandaged(c) TBOO(d) TFOO(d)(c)
'Iensilestrengtb MPa ksi
345 450 310 655
50 65 45 95
YIeldstrengtb(a) lis; MPa
170 275 85 515
25 40 12 75
E1oogaoon(b). 'J>
Hardness, HRB
20 15 30 7
55 75 30 %
(a)Al 0.2% offset.(h) In 50 mm (2 In.). (c)Aged 3 h al480 °C (900 "P), (d)Solutiontreatedat 900 to 955°C (1650to 1750oF)
386/ Heat Treater's Guide: Nonferrous Alloys
C82400 (98Cu-1.7Be-O.3Co) Commercial Names. Previous trade name. Beryllium-copperalloy 165C, CA824; Common name. Beryllium-copper casting alloy 165C Chemical Composition. Composition Limits. 1.65 to 1.75 Be, 0.20 to 0.40 Co, 0.10 Ni max, 0.20 Fe max, 0.15 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of Exceeding Impurity Limits. Generally, electricalconductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening
lium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Specifications (U.S.and/or Foreign). Government QQ-C-390 (CA824)
Recommended Heat Treating Practice
Applications
Solution Heat Treating. Temperature range is 790 to 815°C (1450 to 1500 oF)
Typical Uses. C82400 was developed for use in marine service as a corrosion-resistant. pressure-tight casting material. Its lower beryllium content compared to C82500 makes this alloy the least expensive of the commercial high-strength beryllium-copper alloys. When its hardness is relatively low, C82400 exhibits greater-than-normal toughness. Typical uses include various parts for the submarine telephone cable repeater system and hydrophone, molds for forming plastics, safety tools, plunger tips for die casting, cams, bushings, bearings, valves, pump parts, and gears Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-
Aging. Temperature is 345 °C (650 oF)
C82400: Typical mechanical properties Temper
Tensile strength MPa ksi
Yield streogth(a) MPa ksi
As-cast Castandaged(c) TBOO(d) 1FOO(d)(c)
485 690 415 1070
275 550 140 1000
70 100 60 155
E1ongation(b), %
Hardness
15 3 40 1
78HRB 21HRC 59HRB 38HRC
40 80 20 145
(a)At 0.2% offset. (b) In 50 mm(2 in.). (c) Aged 3 h at 345°C (650 oF). (d) Solution treatedat 800 to 815 °C (1475 to 1500 oF)
C82500 (97.2Cu-2Be-O.5Co-O.25Si) Commercial Names. Previous trade name. Beryllium-copper 2OC, CA825; Common name. Standard beryllium-copper casting alloy Chemical Composition. Composition Limits. 95.5 Cu min, 1.90 to 2.15 Be, 0.35 to 0.7 Co, 0.20 to 0.35 Si, 0.20Ni max, 0.25 Fe max, 0.15 AI max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max. Available with or without 0.02 to 0.10% Ti added as a grain refiner Consequence of EXceedingImpurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S. and/or Foreign). (AMS) Investment castings: 4890; (Government) Sand castings: QQ-C-390, MIL-C-19464 (class 2); centrifugal castings: QQ-C-390; precision castings: MIL-C-1l866 (composition 17), MIL-C-17324; investment castings: MIL-C-22087; (Other) ICI-Cu-2-10780
Applications Typical Uses. Molds for forming plastics, die casting plunger tips, safety tools, cams, bushings, bearings, gears, sleeves, valves, wear parts, structural parts, resistance welding electrodes and inserts, holders, and structural members Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryl-
Iium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF) Aging. Temperature is 345 °C (650 oF)
C82500: Typical mechanical properties Temper
Tensile strength MPa ksi
As-cast Castandaged(c) TBOO(d) 1FOO(d)(c)
515 825 415 1105
75 120 60 160
Yield streogth(a) MPa ksi 275 725 170 1035
40 105 25 150
Eiongaoon(b), %
Hardness
15 2 35 1
81HRB 30HRC 63HRB 43HRC
(a) At 0.2% offset. (b) In 50 nun (2 in.), (c) Aged 3 h at 345°C (650 "F), (d) Solution treatedat 790 to 800 °C (1450 to 1475 oF)
Copper Casting Alloys /387
C82500 (beryllium-copper alloy 21C): Agingcurves for solution-treated alloy
LIVE GRAPH
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316°C
400
350
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300
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34loc
-. ....... --=:;;;;"
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I
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I
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250
200
150
100
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2
3
4
5
6
7
8
Aging time, h
C82600 (97Cu-2.4Be-O.5Co) Commercial Names. Previous trade name. Beryllium-copper 245C; Common name. Beryllium-copper casting alloy 245C Chemical Composition. Composition Limits. 2.25 to 2.45 Be, 0.35 to 0.7 Co, 0.20 to 0.35 Si, 0.20 Ni max, 0.25 Fe max, 0.15 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max, bal Cu Consequence of EXceedingImpurity Limits. Generally, electricalconductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S. and/or Foreign). Government QQ-C-390
Applications Typical Uses. C82600 is intermediate in beryllium content between C82500 and C82800. It exhibits better fluidity, castability, and hardness than C82500 and better toughness and lower cost than C82800. C82600 is used primarily to produce molds for plastic parts. In pressure castings, the lower pouring temperature results in longer tool life than for similar castings of C82500 Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with
these limits. is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF) Aging. Temperature is 345 °C (650 "F)
C82600: Typical mechanical properties Temper
Tensile strength MPa ksi
As-cast Castand aged(e) TBoo(e) TFOO(d)(e)
550 825 485 1140
80 120 70 165
Yield strength(a) MPa ksi
345 725 205 1070
50 105 30 155
EIongalioo(b), %
Hardness
10 2 12 I
86HRB 31HRC 75HRB 45HRC
(a) At 0.2% offset. (b) In 50 mm (2 in.).(c) Aged 3 h at 345°C (650 "F), (d) Solution treated at 790 to 800 °C (1450 to 1475 oF)
388/ Heat Treater's Guide: Nonferrous Alloys
C82800 (96.6Cu-2.6Be-O.5Co-O.3Si) Commercial Names. Previous trade name. Beryllium-copper alloy 275C, CA828; Common name. Beryllium-copper casting alloy 275C
Chemical Composition. Composition Limits. 94.8 Cu min, 2.50 to 2.75 Be, 0.37 to 0.7 Co, 0.20 to 0.35 Si, 0.20 Ni max, 0.25 Fe max, 0.15 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max Consequence of Exceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening Specifications (U.S.and/or Foreign). (Government) QQ-C-390, MILT-16243, MIL-C-19464 (Class IV); Other ICI-Cu-2-10785
a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF)
Aging. Temperature is 345 °C (650 "F), See adjoining figure
.Applications Typical Uses. C82800 is a special-purpose, high-fluidity casting alloy developed for molds for forming plastics and other applications where the casting process should replicate finest detail with maximum fidelity and the resultant part must exhibit maximum hardness and wear resistance for a cast beryllium-copper alloy. Typical uses are molds for forming plastics, cams, bushings, bearings, valves, pump parts, sleeves, and precision cast parts for the communications, textile, aerospace, business machine, firearm, instrument, ordnance, and other industries Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating
C82800: Typical mechanical properties of sand cast test bars Thmper
Thnslle strength MPo ksI
Yieldstrength!o) MPo ksi
As-cast Cast and aged(c) TBOO{d) TFOO(d)(c)
550 860 550 1140
345 760 240 1070
80 125 80 165
50 110 35 155
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450
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~
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345°C
400
7 -I----
370°C
'I
350
I
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--1/ ---- -----r-, -
300
.......
29o-\15°C
~
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---
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250
II 200
150
o
2
3
IIordne5s
10 2
88HRB 31HRC 85HRB 46HRC
10 1
(a) At 0.2% offset. (b) In 50 mm(2 in.), (c) Aged 3 h at 345 °C (650 "F). (d) Solution Ireatedat790 to 800 °C (1450 to 1475 oF)
C82800: Aging curves for solution-treated alloy
LIVE GRAPH
EIongotion(b), %
4 Aging time, h
6
8
Copper Casting Alloys /389
C82800: Typical tenslle properties, TFOO temper. Sand cast test bars were solutiontreated, then aged at 345°C (650 OF)
Temperature, of
200
1400
400
600 I
-
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ti
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300
400
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Temperature, °c
C83300 Commercial Names. Previous trade name. CA833; Common name. Contact metal
ChemicalComposition. Composition Limits. 92.0 to 94.0 Cu, 1.0 to 2.0 Pb, 1.0 to 2.0 Sn, 2.0 to 6.0 Zn
Specifications (U.S. and/or Foreign). Ingot code number 131
Applications Typical Uses. Terminal ends for electrical cables
CopperSpecification. In reporting chemical analyses by the use of instru-
Recommended Heat Treating Practice
ments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses obtained by wet methods, zinc may be indicated as balance for alloys with over 2% Zn
Stress-Relieving. Temperature is 260°C (500 "F)
C861 00, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) Commercial Names. Common names. Manganese bronze (90,000 psi); High-strength yellow brass; CA861; CA862 Chemical Composition. Composition Limits. C86100: 66.0 to 68 Cu, 4.5 to 5.5 AI, 2.0 to 4.0 Fe, 2.5 to 5.0 Mn, 1.0 Ni max, 0.2 Sn max, 0.2 Pb max, bal Zn. C86200; 60.0 to 68.0 Cu, 3.0 to 7.5 AI, 2.0 to 4.0 Fe, 2.5 to 5.0 Mn, 1.0 Ni max, 0.2 Sn max, 0.2 Pb max, bal Zn
MIL-C-22229 (composition 10). C86200: investment castings, MIL-C22087 (composition 9); precision castings, MIL-C-11866 (composition 20); sand castings, MIL-C-22229 (composition 9); Ingot code number 423
Applications Typical Uses. Marine castings, gears, gun mounts, bushings, and bear-
Specifications (U.S. and/or Foreign). ASTM C86100: none. C86200:
ings
Ingot, B 30; centrifugal castings, B 271; sand castings, B 584; continuous castings, B 505; SAE J462. (Former alloy number: 430A); (Government) QQ-C-390, QQ-C-523. C86100: centrifugal castings, MIL-C-15345 (Alloy 5); investment castings, MIL-C-22087 (composition 7); sand castings,
Recommended Heat Treating Practice Annealing. Temperature is 260°C (500 "F)
390 I Heat Treater's Guide: Nonferrous Alloys
C86300 (64Cu-26Zn-3Fe-3AI-4Mn) Commercial Names. Common names. Manganese bronze (110,000 psi), High-strength yellow brass, CA863 Chemical Composition. Composition Limits. 60.0 to 68.0 Cu, 2.5 to 5.0 Mn, 3.0 to 7.5 AI, 2.0 to 4.0 Fe, 0.2 Pb max, 0.2 Sn max, bal Zn
(composition 9); precision castings, MIL-C-1l866 (composition 21); sand castings, MIL-C-22229 (composition 8); Ingot code number 424
Applications Typical Uses. Extra-heavy duty, high-strength alloy for gears, cams, bear-
Consequence of Exceeding Impurity Limits. Excessive Sn causes
ings, screw-down nuts, bridge parts, hydraulic cylinder parts
brittleness; excessive Pb or Ni decreases elongation
Precautions in Use. Not to be used in marine atmospheres, ammonia, or highly corrosive atmospheres
Specifications (U.S.and/or Foreign). AMS 4862; (ASTM) Sand castings: B 22, B 584; centrifugal castings: B 271; continuous castings: B 505, ingot: B 30; SAE J462; (Government) QQ-C-390, QQ-C-523. Centrifugal castings, MIL-~-15345 (Alloy 6); investment castings, MIL-C-22087
Recommended Heat Treating Practice Annealing. Temperature is 260°C (500 "F)
C86400 (59Cu-0.755n-0.75Pb-37Zn-1.25Fe-0.75AI-0.5Mn) Commercial Names. Previous trade name. Leaded high-strength yellow brass, stem manganese bronze; Common name. Manganese bronze (60,000 psi) Chemical Composition. Composition Limits. 56.0 to 62.0 Cu, 1.5 Sn max, 0.5 to 1.5 Pb, 2.0 Fe max, 1.5 Al max, 1.5 Mn max, 1.0 Ni max, balZn
Applications Typical Uses. Free-machining manganese bronze for valve stems, marine castings and fittings, pump bodies
Recommended Heat Treating Practice Annealing. Temperature is 260°C (500 oF)
Specifications (U.S.and/or Foreign). (ASTM) Sand castings: B 584; centrifugal castings: B 271; ingot: B 30; (Government) QQ-C-390, QQ-C523; Ingot code number 420
C86500 (58Cu-39Zn-1.3Fe-1 AI-0.5Mn) Commercial Names. Previous trade name. High-strength yellow brass; Common name. Manganese bronze (65,000 psi) Chemical Composition. Composition Limits. 55.0 to 60.0 Cu, 0.4 to 2.0 Fe, 0.5 to 1.5 AI, 1.5 Mn max, 0.4 Pb max, 1.0 Sn max, 1.0 Ni max, bal Zn
C86500: Typical Brinell Hardness
LIVE GRAPH Click here to view Temperature, ° F
Specifications (U.S. and/or Foreign). AMS 4860A; (ASTM) Sand
100
castings: B 584; centrifugal castings: B 271, ingot: B 30; SAE J462; (Government) QQ-C-390. Sand castings, MIL-C-22229 (composition 7); centrifugal castings, MIL-C-15345 (Alloy 4); investment castings, MIL-C22087 (composition 5); Ingot code number 421
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Applications
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Typical Uses. Propeller hubs, blades, and other parts in contact with salt and fresh water, gears, liners
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Copper Casting Alloys I 391
C86500: Typical tensile properties
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C86700 Commercial Names. Previous trade name. CA867; Common names. Leaded high-strength yellow brass; 80,000 psi tensile manganese bronze Chemical Composition. Composition Limits. 55.0 to 60.0 Cu, 1.0 to 3.0 AI, 1.0 to 3.0 Fe, 0.5 to 1.5 Pb, 1.0 to 3.5 Mn, 1.0 Ni max, 1.5 Sn max, 30.0 to 38.0 Zn. Ingot for remelting specifications may vary from the ranges shown Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses ob-
tained by wet methods, zinc may be indicated as balance on those alloys with over 2% Zn Specifications (U.S. ancIJor Foreign). ASTM Centrifugal, B 271; ingot, B 30; sand, B 584, B 763
Applications Typical Uses. High-strengthfree-machiningmanganese bronze valve stems
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
C86800 Commercial Names. Previous trade name. CA868; Common name. Nickel-manganese bronze
max, bal Zn. Ingot for remelting specifications may vary from the ranges shown
Chemical Composition. Composition Limits. 53.5 to 57.0 Cu, 2.0 Al max, 1.0 to 2.5 Fe, 0.20 Pb max, 2.5 to 4.0 Mn, 2.5 to 4.0 Ni, 1.0 Sn
Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption,
392/ Heat Treater's Guide: Nonferrous Alloys copper may be indicated as balance. In reporting chemical analyses obtained by wet methods, zinc may be indicated as balance on those alloys with over 2% Zn
Typical Uses. Marine fittings and propellers
Specifications (U.S. and/or Foreign). (ASTM) Die, B 176; (Govern-
Recommended Heat Treating Practice
ment) Sand, QQ-C-390; valves, WW-V-1967
Applications
Stress-Relieving. Temperature is 260°C (500 oF)
C87300 (formerly C87200) Commercial Names. Trade name. Everdur, Herculor, Navy Tombasi1; Common name. Silicon bronze, 95-1-4, 92-4-4,89-6-5
Applications Typical Uses. As a substitute for tin bronze where good physical and
max, 0.25 Zn max, 0.20 Fe max, 3.5 to 4.5 Si, 0.8 to 1.5 Mn
corrosion resistance are required. Bearings, bells, impellers, pump and valve components, marine fittings, statuary and art castings
Cu + Sum of Named Elements. 99.5 min
Recommended Heat Treating Practice
Specifications (U.S.and/orForeign). (ASTM) Centrifugal, B 271; ingot, B 30; sand, B 585, B 763; SAE J 461, J 462; Government QQ-e-390, WW-V-1967; Military MIL-C-1l866 (composition 19); MIL-C-22229; (Other) Ingot code number 50DA
Stress-Relieving. Temperature is 260°C (500 oF)
Chemical'Composition. Composition Limits. 94.0 Cu min, 0.20 Pb
C87600 Commercial Names. Common names. Low-zinc silicon brass, CA876
Applications
ChemicalComposition. Composition Limits. 88.0 Cu min, 0.50 Pb
Typical Uses. Valve stems
max, 4.0 to 7.0 Zn, 0.20 Fe max, 3.5 to 5.5 Si, 0.25 Mn max
Cu + Sum of Named Elements. 99.5 min
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)
Specifications (U.S. and/or Foreign). (ASTM) Ingot, B 30; sand, B 584, B 763; (Other) Ingot code number 500D
C8761 0 Commercial Names. Common name. Silicon bronze
Applications
Chemical Composition. Composition Limits. 90.0 Cu min, 0.20 Pb
Typical Uses. Bearings, bells, impellers, pump and valve components,
max, 3.0 to 5.0 Zn, 0.20 Fe max, 3.0 to 5.0 Si, 0.25 Mn max
Cu + Sum of Named Elements. 99.5 min Specifications (U.S. and/or Foreign). (ASTM) Ingot: B 30; (Other) Ingot code number 500E
marine fittings, corrosion-resistant castings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
Copper Casting Alloys /393
C87500, C87800 (82Cu-4Si-14Zn) Commercial Names. Trade name. Tombasil; Common name. Silicon brass, 82-4-14
Chemical Composition. Composition Limits. C87500: 79.0 min Cu, 0.50 Pb max, 12.0 to 16.0 Zn, 0.50 Al max, 3.0 to 5.0 Si. C87800: 80.0 to 83.0 Cu, 0.25 Sn max, 0.15 Pb max, 0.15 Fe max, 0.15 Mn max, 0.15 Al max, 3.75 to 4.25 Si, 0.01 Mg max, 0.25 max others (total), bal Zn, but As, Sb, and S not to exceed 0.05 each, and P not to exceed 0.01 Specifications (U.S. and/orForeign). (ASTM) C87500: ingots, B 30; centrifugal castings, B 271; sand castings, B 584. C87800: die castings, B 176; SAE J 462; Government C 87500: sand castings, QQ-C-390; invest-
ment castings, MlL-C-22087 (composition 4). C87800: die castings, MILB-15894 (class 3); (Other) Ingot code number 500T
Applications 'TYpical Uses. Bearings, gears, impellers, rocker arms, valve stems, brush holders, bearing races, small boat propellers
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)
C87900 Commercial Names. Common names. Silicon yellow brass, CA879 ChemicalComposition. Composition Limits. 63.0 Cu min, 0.25 Sn max, 0.25 Pb max, 30.0 to 36.0 Zn, 0.40 Fe max, 0.15 Al max, 0.8 to 1.2 Si, 0.15 Mn max, 0.50 Ni (including Co) max, 0.05 S max, 0.01 P max, 0.05 As max, 0.05 Sb max. Total named elements shall be 99.5% minimum Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses obtained by wet methods, zinc may be indicated as balance on those alloys
with over 2% zinc. In determining Cu min, copper may be calculated as Cu +Ni
Specifications (U.S. and/or Foreign). (ASTM) Ingot: B 30; die: B 176; Government MlL-B-15894; SAE J461, J462; Ingot code number 5000
Applications 'TYpical Uses. General-purpose die-easting alloy having moderate strength
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
C92200 (88Cu-6Sn-1.5Pb-4.5Zn) Commercial Names. Common name. Navy "M" bronze, steam bronze, 88-6-1.5-4.5
Chemical Composition. Composition Limits. 86.0 to 90.0 Cu, 5.5 to 6.5 Sn, 1.0 to 2.0Pb, 3.0to 5.0Zn, 1.0Nimax, 0.25 Fe max, 0.05 Pmax. (1.5 P max for continuous castings), 0.05 S max, 0.005 Si max, 0.25 Sb max
Specifications (U.S.amI/or Foreign). ASTMB 584, B 61, B 271, B 505, B 30; SAE J462 (C92200); Government CA922, QQ-B-225 (Alloy number I), MlL-B-1654I, MIL-B-15345; (Other) Ingot code number 245
Applications Typical Uses. Component castings of valves, flanges and fittings, oil pumps, gears, bushings, bearings, backing for babbitt-lined bearings, pressure-containing parts at temperatures up to 290°C (550 "F), and stresses up to 20 MPa (3 ksi)
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
C92200: BrinellHardness
LIVE GRAPH Click here to view 75 In
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394/ Heat Treater's Guide: Nonferrous Alloys
C92200: Tensile properties
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C92300 (87Cu-8Sn-1 Pb-4Zn) Commercial Names. Common names. Leaded tin bronze, leaded Navy "G" -bronze, 87-8-1-4
ChemicalComposition. Composition Limits. 85.0 to 89.0 Cu, 7.0 to 9.0 Sn, 1.0 Pb max, 2.5 to 5.0 Zn, 1.0 Ni max, 0.25 Fe max, 0.05 P max (1.5 P max for continuous castings), 0.25 Sb max, 0.05 S max, 0.005 Si max, 0.005 Al max
Specifications (U.S.and/or Foreign). (ASTM) Sand castings: B 584; centrifugal castings: B 271; continuous castings: B 505; ingot: B 30; SAE
J462; Government QQ-C-390. Centrifugal castings: MlL-C-15345 (Alloy 10); (Other) Ingot code number 230
Applications Typical Uses. Strong general-utility structural bronze for use under severe conditions; valves, expansion joints, special high-pressure pipe fittings, steam pressure castings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 "F)
C92500 (87Cu-11 Sn-1 Pb-1 Ni) Commercial Names. Common name. Leaded tin bronze, 640; 87-11-10-1
ChemicalComposition. Composition Limits. 85.0 to 88.0 Cu, 10.0 to 12.0 Sn, 1.0 to 1.5 Pb, 0.5 Zn max, 0.8 to 1.5 Ni, 0.15 Fe max, 0.20 to 0.30 P, 0.005 Al max
Specifications (U.S. and/or Foreign). (ASTM) Continuous castings: B505; ingot: B 30; SAE J462; (Other) Ingot code number 250
Applications Typical Uses. Gears, automotive synchronizer rings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
Copper Casting Alloys /395
C92600 (87Cu-1 05n-1 Pb-2Zn) Commercial Names. Common name. Leaded tin bronze Chemical Composition. Composition Limits. 86.0 to 88.5 Cu, 9.3 to 10.5 Sn, 0.8 to 1.2 Pb, 1.3 to 2.5 Zn, 0.75 Ni max, 0.15 Fe max. 0.25 Sb max, 0.05 S max, 0.005 Si max, 0.03 P max, 0.005 Al max Specifications (U.S. and/or Foreign). Ingot code number 215
Applications
severe conditions; bolts. nuts, gears; heavy-pressure bearings and bushings to use against hardened steel; valves, expansion joints. special high-pressure pipe fittings; pump pistons; elevator components; steam pressure castings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 "F)
Typical Uses. Commercial bronze for high-duty bearings where wear resistance is essential; strong general-utility structural bronze for use under
C92700 (88Cu-105n-2Pb) Commercial Names. Common name. Leaded tin bronze, 88-10-2-0
Applications
Chemical Composition. Composition Limits. 86.0 to 89.0 Cu, 9.0 to 11.0 se.r.ore 2.5 Pb. 0.7 Znmax, 1.0Ni max, 0.15 Fe max, 0.25 Prnax, 0.005 Al max
Typical Uses. Bearings, bushings, pump impellers. piston rings, valve components, steam fittings, gears
Specifications (U.S. and/or Foreign). (ASTM) Continuous castings: B 505; ingot: B 30; SAE J462; (Other) Ingot code number 206
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
C92900 (84Cu-105n-2.5Pb-3.5Ni) Commercial Names. Common name. Leaded nickel-tin bronze, 84-102.5-0-3.5 Chemical Composition. Composition Limits. 81.0 to 85.5 Cu, 9.0 to 11.0 Sn, 2.0 to 3.2 Pb, 2.8 to 4.0 Ni, 0.50 P max, 0.50 max other (total)
Applications Typical Uses. Gears, wear plates and guides, cams
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)
Specifications (U.S. and/or Foreign). (ASTM) Sand and centrifugal castings: B 427; continuous castings: B 505; ingot: B 30; SAE J462
C93200. (83Cu-75n-7Pb-3Zn) Commercial Names. Common name. High-leaded tin bronze; bearing bronze 660; 83-7-7-3 Chemical Composition. Composition Limits. 81.0 to 85.0 Cu, 6.3 to 7.5 Sn, 6.0 to 8.0 Pb, 2.0 to 4.0 Zn, 0.50 N max, 0.20 Fe max, 0.15 P max, 0.35 Sb max, 0.08 S max, 0.003 Si max. In determining Cu, minimum may be calculated as Cu + Ni Other Phosphorus Specifications. 1.5 P max for continuous castings; 0.50 P max for permanent mold castings Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 584; centrifugal castings, B 271; continuous castings: B 505; ingot: B 30; SAE
J462; Government QQ-C-390; QQ-C-525; QQ-L-225 (Alloy 12); MIL-C15345 (Alloy 17); MIL-C-1l553 (Alloy 12); MIL-B-16261 (Alloy vn, (Other) Ingot code number 315
Applications Typical Uses. General-utility bearings and bushings, automobile fittings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
396/ Heat Treater's Guide: Nonferrous Alloys
C93400 Commercial Names. Common name. High-leaded tin bronze, CA934, 84-8-8-0
ChemicalComposition. Composition Limits. 82.0 to 85.0 Cu, 7.0 to 9.0 Sn, 7.0 to 9.0 Pb, 0.8 Zn max, 0.20 Fe max, 0.50 Sb max, Ni (including Co) 1.0 max, 0.08 S max, 0.50 P max (for continuous castings, phosphorus shall be 1.5% maximum), 0.005 Al max, 0.005 Si max. Ingot for remelting specifications vary from the ranges given
Copper and Zinc Specifications. In reporting chemical analyses by the use of instruments such as spectrograph, x-ray, and atomic absorption, copper may be indicated as balance. In reporting chemical analyses ob-
tained by wet methods, zinc may be indicated as balance on those alloys with over 2% zinc
Specifications (U.S. and/or Foreign). (ASTM) Continuous, B 505; ingot, B 30; Government QQ-C-390; Mll.-C-22087; Mll.-C-22229; (Other) Ingot code number 310
Applications Typical Uses. Bearings and bushings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
C93500 (85Cu-5Sn-9Pb-1 Zn) Commercial Names. Common name. High-leaded tin bronze, 85-5-9-1 ChemicalComposition. Composition Limits. 83.0 to 86.0 Cu, 4.5 to 6.0 se, 8.0 to 10.0 Pb, 2.0 Zn max, 0.50 Ni max, 0.20 Fe max, 0.02 P max (1.5 P max for continuous castings), 0.30 Sb max, 0.08 S max, 0.003 Si max. In determining Cu, minimum may be calculated as Cu + Ni
Specifications (U.S. and/orForeign). (ASTM) Sand castings: B 584; centrifugal castings, B 271; continuous castings, B 505; ingot, B 30; SAB
J462; Government QQ-C-390;QQ-L-225 (Alloy 14); Mll.-B-11553B (Alloy 14); (Other) Ingot code number 326
Applications Typical Uses. Small bearings and bushings, bronze backings for babbittlined automotive bearings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)
C93700 (80Cu-10Sn-10Pb) Commercial Names. CDA and UNS number. C93700; Common names. High-leaded tin bronze, bushing and bearing bronze, 80-10-10 .
Chemical Composition. Composition Limits. 78.0 to 82.0 Cu, 9.0 to 11.0 sn, 8.0 to 11.0 Pb, 0.70 Zn max, 0.70 Ni max, 0.15 Fe max, 0.05 P max, 0.50 Sb max, 0.08 S max, 0.003 Si max
Specifications (U.S. and/or Foreign). (AMS) Sand and centrifugal castings: 4842; (ASTM) Sand castings: B 22, B 584; centrifugal castings: B 271; continuous castings: B 505; ingot: B 30; SAB J462; Government QQ-C-390; Mll.-B-13506 (Alloy A2); (Other) Ingot code number 305
Applications Typical Uses. Bearings for high speed and heavy pressure, pumps, impellers, applications requiring corrosion resistance, pressure-tight castings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 oF)
Copper Casting Alloys /397
C93700: Tensile properties. Typical tensile properties at various temperatures 50 45 40 "-
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C93800 (78Cu-7Sn-15Pb) Commercial Names. Common name. High-leaded tin bronze, anti-acid metal,78-7-15
(Alloys 19 and 7); MIL-B-16261 (Alloy IV); (Other) Ingot code number 319
Chemical Composition. Composition Limits. 75.0 to 79.0 Cu, 6.3 to 7.5 Sn, 13.0 to 16.0 Pb, 0.70 Znmax, 0.70 Nimax, 0.15 Fe max, 0.05 P max, 0.70 Sb max, 0.08 S max, 0.003 Si max, 0.005 Al max. In determining Cu, minimum may be calculated as Cu + Ni
Applications
Consequence of Exceeding Impurity Limits. Aluminum or silicon causes lead sweating during solidification and may cause a substantial portion of castings to be unsound Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 66, B 584; centrifugal castings: B 271; continuous castings: B 505; ingot: B 30; SAE J462; Government QQ-C-390; QQ-C-525 (Alloy 7); QQ-L-225
Typical Uses. Locomotive engine castings and general-service bearings for moderate pressure; general-purpose wearing metal for rod bushings, shoes, and wedges; freight car bearings; backs for lined journal bearings for locomotive tenders and passenger cars; pump impellers. and bodies for use in acid mine water
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
398/ Heat Treater's Guide: Nonferrous Alloys
C95200 (88Cu-3Fe-9AI) Commercial Names. Previous trade name. Ampco AI; Common name. Aluminum bronze 9A, 88-3-9 Chemical Composition. Composition Limits. 86 Cu min, 8.5 to 9.5 AI, 2.5 to 4.0 Fe, 1.0 max other (total)
C95200: Tensileproperties. Typical short-time tensile properties of C95200, as-cast
LIVE GRAPH Click here to view
Consequence of Exceeding Impurity Limits. Possible hot shortness and/or hot cracking, embrittlement, and reduced soundness of castings
700
Specifications (U.S. and/orForeign). (ASME) Sand castings: SB148;
600
centrifugal castings: SB271; (ASTM) Sand castings: B 148; centrifugal castings: B 271; continuous castings: B 505; ingot: B 30; SAE J462; (Government) Centrifugal, sand, and continuous castings: QQ-C-390; sand castings: MIL-C-22229; (Other) Ingot code number 415
Applications
Temperature. OF
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C95300 (89Cu-1 Fe-1 OA1) Commercial Names. Trade name. Ampco B2; Common names. Aluminum bronze 9B, 89-1-10
Chemical Composition. Composition Limits. 86 Cu min, 9.0 to 11.0 AI, 0.8 to 1.5 Fe, 1.0 max other (total
Consequence of EXceeding Impurity Limits. Possible hot shortness, loss of casting soundness, embrittlement, reduced response to heat treatment
Specifications (U.S. and/or Foreign). (ASTM) Sand Castings: B 148; centrifugal castings: B 271; continuous castings: B 505; ingots: B 30; SAE J462; (Government) Centrifugal and sand castings: QQ-C-390; pre-
cision castings: MIL-C-11866, composition 22; (Other) Ingot code number 415
Applications Typical Uses. Pickling baskets, nuts, gears, steel mill slippers, marine equipment, welding jaws, nonsparking hardware
Precautions in Use. Not suitable for exposure to oxidizing acids. Prolonged heating in the 320 to 565°C (610 to 1050 "F) range can result in a loss of ductility and notch toughness
Recommended Heat Treating Practice Annealing. Temperature range is 595 to 650 °C (1100 to 1200 "F)
Copper Casting Alloys /399
C95400 (85Cu-4Fe-11 AI) and C9541 0 Commercial Names. Trade name. Ampco C3; Common names. Aluminum bronze 9C, G5, 85-4-11
ChemicalComposition. Composition limits of C95400. 83 min Cu, 10.0 to 11.5 AI, 3.0 to 5.0 Fe, 0.50 Mn max, 2.5 Ni max (+ Co), 0.5 max other (total)
C95400: Tensile properties. Typicalshort-time tensile properties of C95400,as-cast
LIVE GRAPH
Composition Limitsof C95410. 83.0 Cu min, 3.0 to 5.0 Fe, 1.5 to 2.5 Ni (including Co), 10.0 to 11.5 AI, 0.50 Mn max Cu + Sum of Named Elements. 99.5 min Consequence of EXceeding Impurity Limits. Possible hot shortness, reduced casting soundness, embrittlement and loss of heat treating response Specifications (U.S. and/or Foreign). (ASME) Sand castings: SB148; (ASTM) Sand castings: B 148; centrifugal castings: B 271; continuous castings: B 505; ingots: B 30; Government QQ-C-390; Sand castings, MIL-C-22229 (composition 6); investment castings, MIL-C-15345 (Alloy 13); centrifugal castings, MIL-C-22087 (composition 8). (Other) Ingot code number 415
600
8!.
500
tc
400 t-----t--t-----t--t--+-+---=J
::<
~
300
t-----t-~I_
100 '--'-_"'--'-_-'----'-_..1.--1 30 r-"TT'"--,rr---r-.,,--rr-TT-'
#. 20 I---__+_.~
Applications
g
Typical Uses. Pump impellers, bearings, gears, worms, bushings, valve
Cl
seats and guides, rolling mill slippers, slides, nonsparking hardware
Temperature, OF
Click here to view
101---9"--
O'--'-_.L..--'-_.L.---'-_-'----'
o
Precautions in Use. Not suitable for use in oxidizing acids. Prolonged
50
100 150 200 250 300 350 Temperature. °C
heating in the 320 to 565°C (610 to 1050 "F) range can result in loss of ductility and notch toughness
Recommended Heat Treating Practice Annealing. Temperature is 620 °C (1150 oF)
C95500 (81Cu-4Fe-4Ni-11AI) Commercial Names. Previous trade name. Arnpco 04; Common names. Aluminum bronze 9D, 415,81-4-4-11 ChemicalComposition. Composition Limits. 78 Cu min, 10.0 to
MIL-C-15345 (Alloy 14); sand castings, MIL-C-22229 (composition 6); investment castings, MIL-C-22087 (composition 8); (Other) Ingot code number 415
11.5 AI, 3.0 to 5.0 Fe, 3.5 Mn max, 3.0 to 5.5 Ni (+ Co), 0.5 max other (total)
Applications
Consequence of EXceeding Impurity Limits. Possible hot shortnessin
Typical Uses. Valve guides and seats in aircraft engines, corrosion-resis-
welding, embrittlement, increased quench-cracking susceptibility, possible loss of heat-treating response. Excessive Si can cause machining difficulties
tant parts, bushings, gears, worms, pickling hooks and baskets, agitators
Specifications (U.S. and/orForeign). AMS 4880; (ASTM) Sand castings: B 148; centrifugal castings: B 271; continuous castings: B 505; ingots: B 30; SAE J462; Government QQ-C-390; centrifugal castings,
Recommended Heat Treating Practice
Precautions in Use. Not suitable for use in strong oxidizing acids
Annealing. Temperature range is 620 to 705°C (1150 to 1300 "F)
C95600 (91Cu-2Si-7AI) Commercial Names. Common name. Aluminum-silicon bronze
Cu + Sum of Named Elements. 99.0% min
Chemical Composition. Composition Limits. 88.0 Cu min, 0.25 Ni
Specifications (U.S.and/or Foreign). (ASTM) Ingot: B 30; sand castings: B 148, B 763; Government QQ-B-675, MIL-V-11-87; (Other) Ingot code number 415E
(including Co) max, 6.0 to 8.0 AI, 1.8 to 3.3 Si
400 I Heat Treater's Guide: Nonferrous Alloys
Applications
Recommended Heat Treating Practice
Typical Uses. Cable connectors, terminals, valve stems, marine hardware, gears, worms, pole-line hardware
Stress-Relieving. Temperature is 260°C (500 oF)
C95700 (75Cu-3Fe-8AI-2Ni-12Mn) Commercial Names. Previous trade name. Superstone 40, Novoston, Ampcoloy 495; Common name. Manganese-aluminum bronze, 75-3-8-212 Chemical Composition. Composition Limits. 71.0 Cu min, 11.0 to 14.0 Mn, 7.0 to 8.5 AI, 2.0 to 4.0 Fe, 1.5 to 3.0 Ni, 0.10 Si max, 0.03 Pb max, 0.5 max others (total) Consequence of Exceeding Impurity Limits. Possible hot shortness and reduced cast strength Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 148; ingot: B 30; (Government) Sand castings: MIL-B-24480
Applications Typical Uses. Propellers, impellers, stator clamp segments, safety tools, welding rods, valves, pump casings, marine fittings Precautions in Use. Slow cooling or prolonged heating in the 350 to 565°C (660 to 1050 "F) range may cause embrittlement. Not suitable for use in oxidizing acids
Recommended Heat Treating Practice Annealing. Temperature is 620°C (1150 OF)
C95800 (82Cu-4Fe-9AI-4Ni-1 Mn) Commercial Names. Common names. Alpha nickel-aluminum bronze, propeller bronze
B-24480: centrifugal castings only: MIL-C-15345, Alloy 28; (Other) Ingot code number 415
Chemical Composition. Composition Limits. 79.0 Cu min, 0.03 Pb max, 3.5 to 4.5 Fe, 4.0 to 5.0 Ni (+ Co), 0.8 to 1.5 Mn, 8.5 to 9.5 AI, 0.10 Simax
Applications Typical Uses. Propeller blades and hubs for fresh- and salt-water service, fittings, gears, worm wheels, valve guides and seals, structural applications
Consequence of Exceeding Impurity Limits. Hard spots, embrittlement, possible hot shortness, possible weld cracking
Precautions in Use. Not suitable for use in oxidizing acids or strong alkalies
Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 148; centrifugal castings: B 271; continuous castings: B 505; ingots: B 30; SAE 1462; (Government) Sand and centrifugal castings: QQ-C-390; MIL-
Recommended Heat Treating Practice Annealing. Temperature range is 650 to 705°C (1200 to 1300 "F)
C96600 (69.5Cu-30Ni-O.5Be) Commercial Names. Previous trade name. Beryllium cupro-nickel alloy 71C, CA966; Common name. Beryllium cupro-nickel Chemical Composition. Composition Limits. 0.40 to 0.7 Be, 29.0 to 33.0 Ni, 0.8 to 1.1 Fe, 1.0 Mn max, 0.15 Si max, 0.01 Pb max, bal Cu Consequence of Exceeding Impurity Limits. An excessive amount of Si will increase as-cast hardness and lower ductility. High Pb will cause hot shortness Specifications (U.S. and/or Foreign). (Government) ,Sand castings: MIL-C-81519
Applications Typical Uses. C96600 is a high-strength version of the well-known cupro-nickel alloy C96400, possessing twice the strength. Like C96400, C96600 exhibits excellent corrosion resistance to seawater. Typical uses
are high-strength constructional parts for marine service; pressure housings for long, unattended submergence; pump bodies; valve bodies; seawater line fittings; marine low-tide hardware; gimbal assemblies; and release mechanisms Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis. a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Copper Casting Alloys I 401
Recommended Heat Treating Practice
Aging. Temperature is 510 °C (950 oF). Typical aging time, 3 h
Solution Heat Treating. Temperature is 995°C (1825 OF)
C97300 (56Cu-2Sn-10Pb-20Zn-12Ni) Commercial Names. Previous trade name. 12% nickel silver; Common name. Leaded nickel brass, 56-2-10-20-12 Chemical Composition. Composition Limits. 53.0 to 58.0 Cu, 1.5 to 3.0 Sn, 8.0 to 11.0 Pb, 17.0 to 25.0 Zn, 11.0 to 14.0 Ni, 1.5 Fe max, 0.50 Mn max, 0.35 Sb max, 0.15 Si max, 0.08 S max, 0.05 P max, 0.005 Al max Specifications (U.S. and/or Foreign). (ASTM) Centrifugal castings: B 271; sand castings: B 584; ingot: B 30
Applications Typical Uses. Investment, centrifugal, permanent mold, and sand castings for hardware fittings; valves and valve trim; statuary, and ornamental castings
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 "F), 1 h for each 25 mm (1 in.) of section thickness
C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) Commercial Names. Previous trade name. 20% nickel silver; Common name. Dairy metal, leaded nickel bronze, 64-4-4-8-20 Chemical Composition. Composition Limits. 63.0 to 67.0 Cu, 3.5 to 4.5 Sn, 3.0 to 5.0 Pb, 3.0 to 9.0 Zn, 19.0 to 21.5 Ni, 1.5 Fe max, 1.0 Mn max, 0.25 Sb max, 0.15 Si max, 0.08 S max, 0.05 P max, 0.005 Al max
Applications Typical Uses. Centrifugal, investment, and sand castings for marine castings; sanitary fittings; ornamental hardware; valves, and pumps
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 "F), I h for each 25 mm
Specifications (U.S. and/or Foreign). (ASME) Sand castings: SB584; (ASTM) Centrifugal castings: B 271; sand castings: B 584; ingot: B 30; (Government) Sand castings: MIL-C-17112; (Other) Ingot code number 412
(1 in.) of section thickness
C97800 (66.5Cu-5Sn-1.5Pb-2Zn-25Ni) Commercial Names. Previous trade name. 25% nickel silver; Common name. Leaded nickel bronze, 66-5-2-2-25 Chemical Composition. Composition Limits. 64.0 to 67.0 Cu, 4.0 to 5.5 Sn, 1.0 to 2.5 Pb, 1.0 to 4.0 Zn, 24.0 to 27.0 Ni, 1.5 Fe max, 1.0 Mn max, 0.20 Sb max, 0.15 Si max, 0.08 S max, 0.05 P max, 0.005 Al max Specifications (U.S. and/or Foreign). (ASTM) Centrifugal castings: B 271; sand castings: B 584; ingot: B 30
Applications Typical Uses. Investment, permanent mold, and sand castings for ornamental castings; sanitary fittings; valve bodies; valve seats; and musical instrument components
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 "F)
C99400 (90.4Cu-2.2Ni-2.0Fe-1.2AI-1.2Si-3.0Zn) Commercial Names. Common name. Nondezincification alloy, NDZ
Applications
Chemical Composition. Composition Limits. 0.25 Pb max, 1.0 to 3.5 Ni, 1.0 to 3.0 Fe, 0.50 to 2.0 AI, 0.50 to 2.0 Si, 0.50 to 5.0 Zn, 0.50 Mn max, bal Cu
Typical Uses. Centrifugal, continuous, investment, and sand castings for valve stems; propeller wheels; electrical parts; gears for mining equipment; outboard motor parts; marine hardware; and other environmental uses where resistance to dezincification and dealuminification is required
402/ Heat Treater's Guide: Nonferrous Alloys
Recommended Heat Treating Practice Solution Heat Treating. Temperature is 885°C (1625 OF), 1 h for each 25 mm (1 in.) of section thickness
Aging. Temperature is 480°C (900 oF), 1 h at temperature Stress-Relieving. Temperature is 315°C (600 "F), 1 h for each 25 mm (1 in.) of section thickness
C99500 Commercial Names. Trade name. NDZ-S
Applications
Chemical Composition. Composition Limits. 0.25 Pb max, 3.5 to
Typical Uses. Valve stems, marine, and other environmental uses where
5.5 Ni, 3.0 to 5.0 Fe, 0.50 to 2.0 AI, 0.50 to 2.0 Si, 0.50 Mn max, 0.50 to 2.0 Zn, bal Cu
Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 763
resistance to dezincification and dealuminification is required, propeller wheels, electrical parts, gears for mining equipment and outboard marine industry; same as C99400 but used where higher yield strength is required
Recommended Heat Treating Practice Stress-Relieving. Temperature is 315°C (600 OF)
C99750 Chemical Composition. Composition Limits. 0.25 to 3.0 AI, 55.0 to 61.0 Cu, 0.50 to 2.5 Pb, 17.0 to 23.0 Mn, 5.0 Ni max, 17.0 to 23.0 Zn, 1.0 Fe max (iron content shall not exceed nickel content)
Recommended Heat Treating Practice Stress-Relieving. Temperature is 260°C (500 OF)
Specifications (U.S. and/or Foreign). (ASTM) Die castings: B 176
Beryllium copper 21C (97Cu-2Be-1Co) Commercial Names. Common name. Grain-refined beryllium-copper casting alloy 21C
Chemical Composition. Composition Limits. 2.00 to 2.25 Be, 1.0 to 1.2 Co, 0.20 to 0.40 Si, 0.20 Ni max, 0.25 Fe max, 0.15 Al max, 0.10 Sn max, 0.02 Pb max, 0.10 Zn max, 0.10 Cr max
Consequence of EXceeding Impurity Limits. Generally, electrical conductivity is lowered. High Fe raises magnetic susceptibility. High Sn, Zn, or Pb causes hot shortness. High Cr diminishes response to precipitation hardening
Applications
beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Recommended Heat Treating Practice Solution Heat Treating. Temperature range is 790 to 800°C (1450 to 1475 OF)
Aging. Temperature is 340 °C (650 "F)
Typical Uses. The 1%Co content is a strong grain refiner, and as a result, this alloy is used instead of beryllium-copper alloys C82500 and C82400 when thin sections must be cast at high temperatures or when thick and thin sections are present within the same casting in order to achieve a uniform fine-grained structure. The higher cobalt content imparts better wear resistance but less desirable polishability and machinability. Typical uses are comparable to those of beryllium-copper alloys C82400 and C82500
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffing under improper conditions may raise the concentration of beryllium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving
Berylliumcopper 21C: Typical mechanical properties Thmper
MPa
ksi
Yield strength MPa ksi
As-cast Castand aged(a) Solutiontreated(b) Solutiontrealed(b) andaged(a)
515 825 415 1105
75 120 60 160
275 725 170 1035
Thnsilestrength
40 105 25 150
(a) Aged 3 hat345 °C(650°F). (b) At790 to 800 °C (1450 to 1475oF)
EIongalion in SO mm (2 in.), %
25 5 40 1
75HRB 30HRC 63HRB 42HRC
Copper Casting Alloys I 403
Beryllium copper nickel 72C (68.8Cu-30Ni-1.2Be)
as-cast hardness and lower ductility. High lead will cause hot shortness. High carbon will result in undesirable carbides
lium in the air to levels above the limits prescribed by OSHA, thus creating a potential for personnel to contract berylliosis, a chronic lung disease. Exhaust ventilation, the principal means of achieving compliance with these limits, is a specific OSHA requirement for processes involving beryllium alloys. Careful attention to the exhaust-ventilation requirements of these and any other effluent-producing operations is essential. Actual exposure of workers should be continually monitored using prescribed air-sampling and calculation methods to determine compliance or noncompliance with OSHA limits
Applications
Recommended Heat Treating Practice
Commercial Names. Common name. Modified beryllium cupro-nickel alloy 72C
Chemical Composition. Composition Limits. 1.1 to 1.2 Be, 29.0 to 33.0 Ni, 0.7 to 1.0 Fe, 0.10 to 0.20 Zr, 0.10 to 0.20 Ti, 0.7 Mn max, 0.15 Si max, 0.1 Pb max, bal Cu
Consequence of Exceeding Impurity Limits. High silicon will raise
Typical Uses. Alloy 72C is a modified version of beryllium cupro-nickel alloy 71C, its increased beryllium content providing improved castability. Its field of application is the plastic tooling industry. Alloy 72C generally is ceramic mold cast into tooling used for molding flame-retardant plastics containing bromine, bromine-boron, chlorinated paraffins and phosphates, and other halogens. Additionally, alloy 72C tooling is resistant to corrosion by the foaming agents used.in structural plastics that generate ammonia at elevated temperatures, as well as to decompositional products of PVC that contain HCI. The good castability of 72C allows it to be cast into tooling of fine detail
Precautions in Use. Melting, casting, abrasive-wheel operations, abrasive blasting, welding, arc cutting, flame cutting, grinding, polishing, and buffmg under improper conditions may raise the concentration of beryl-
Solution Heat Treating. Temperature is 995°C (1825 "F) Aging. Temperature is 510 °C (950 oF) Beryllium copper nickel 72C: Typical mechanical properties of cast beryllium cupro-nickel alloy 72C Thmper
As-castandaged(a) Solutionlreaied(b)andaged(a)
ThnsUestrength MPa ksi
555 860
81 125
YIeldstrength MPa ksi
310 550
Elongation in 50 mm (1 In.),% Hardness
45 80
(a) Aged3 h at510 °C (950 oF). (b) Waterquenched from995°C (1825 oF)
15 70
90HRB 26HRC
Heat Treating Beryllium Copper Alloys Solution Annealing This treatment is performed by heating the alloy to a temperature slightly below the solidus to dissolve a maximum amount of beryllium, then rapidly quenching the material to room temperature to retain the beryllium in a supersaturated solid solution. Users of beryllium-copper alloys are seldom required to solution anneal; this operation is almost always done by the supplier. Typical annealing temperature ranges are 760 to 800°C (1400 to 1475 OF) forthe high-strength alloys and 900 to 955°C (1650 to 1750 "F) forthe high-conductivity alloys. Temperatures below the minimum can result in incomplete recrystallization. Too Iowa temperature can also result in the dissolution of an insufficient amount of beryllium for satisfactory age hardening. Annealing at temperatures above the maximum can cause excessive grain growth or induce incipient melting. Once the set temperature is reached, it is not necessary to hold the metal at the annealing temperature for more than a few minutes to accomplish solution treatment. In general, thin strip or wire can be annealed in less than 2 min; heavy-section products usually are held at the annealing
temperature for 30 min or less. It is important to be sure to reach the set temperature; as a guide, heat-up time is usually estimated as 0.5 to 1 h per inch of thickness. The use of thermal measurement equipment is helpful in establishing these parameters because they depend on the size and quantity of parts being treated. Prolonged annealing time does not increase the solution of beryllium at a given annealing temperature. At the high end of the annealing temperature range, extended dwell time can promote undesirable secondary grain growth. Interrupted or slow quenching rates should be avoided because they permit precipitation of beryllium during cooling, resulting in an unacceptably high level of as-quenched hardness and an inadequate final age-hardening response. This is caused by the annealing out of quenched-in vacancies at these lower quenching rates. The annealing practice for beryllium-copper is in distinct contrast to that for many copper alloys that do not strengthen by heat treatment. These alloys are typically subjected to lower-temperature and longer-time annealing for recovery ofcold-working strains and control of recrystallized grain size.
Age Hardening The treatment involves reheating the solution-annealed material to a temperature below the equilibrium solvus for a time sufficient to nucleate and grow the beryllium-rich precipitates responsible for hardening. For the high-strength alloys, age hardening is typically at temperatures of 260 to 400 DC (500 to 750 OF) for 0.1 to 4 h. The high-conductivity alloys are age hardened at 425 to 565°C (800 to 1050 "P) for 0.5 to 8 h. Within limits, cold working the alloy between solution annealing and age hardening increases both the rate and the magnitude of the age-hard-
ening response in wrought products. As cold work increases to about a 40% reduction in area, the maximum peak-age hardness increases. Further cold work beyond this point is nonproductive and results in decreased hardness after age hardening and diminished ductility in the unaged condition. Commercial alloys intended for user age hardening are limited to a maximum of about 37% cold work in strip (H temper). For wire, the maximum amount of cold work is commonly somewhat greater.
Underaging, Peak Aging, and Overaging Treatments Material that has been aged for an insufficient amount of time to attain the maximum possible hardness at a particular temperature is said to be underaged. Material aged at time-temperature combinations resulting in maximum attainable hardness is said to be peak aged. Material aged beyond the relative maximum in the aging response curve is said to be overaged. Underaged material retains the capacity to increase in hardness through additional age hardening; overaged material does not. Considerable latitude exists for obtaining target strength levels with combinations of cold work and age-hardening temperature and time. When strength less than maximum is desired, for example. for increased ductility, cold work can be reduced and underaging (lower-temperature/longer-time,
higher-temperaturelshorter-time) or overaging (higher-temperaturellongertime) heat treatments can be used to attain the desired properties. If parts are inadvertently overaged to lower-than-desired hardness, they require re-solution annealing to restore the age-hardening response. In this case, the strengthening contribution of any cold work imparted before the original age-hardening treatment is erased, and the maximum strength attainable in the salvaged components is that available from solution-annealed and peak-aged material. From a process control standpoint, peak aging at intermediate temperatures is relatively insensitive to minor fluctuations in temperature. Appreciable extension in time beyond that to attain the aging response
Beryllium Copper Alloys /405
plateau is tolerable. The low sensitivity of final strength to aging conditions once this plateau has been attained accounts for the recommendation of age-hardening temperatures of 315°C (600 OF) for the high-strength alloys and 480 °C (900 OF) for the high-conductivity alloys. Peak-aging treatments are ideally suited for hardening large lots of components on reels or in baskets or trays. Greater precision is needed to select the correct temperature and time to achieve the desired properties when using (in order of increasing need for precision) overaging, low-temperature underaging, high-temperature underaging, and aging to the relative maximum hardness at higher temperatures. Age-hardening treatments involving precise temperature and time combinations pose problems for batch-type heat-treating processes. Furnace loads must be evenly distributed to ensure uniform heating rates and soaking times in all components for a consistent part-to-part aging response. The use of vacuum furnaces for age-hardening necessitates the shielding of parts from direct radiation. The furnace should be backfilled
with an inert gas to provide a more uniform convective heat transfer to the load than that which can be achieved by radiation alone. For further information see the following Tables and Figures accompanying this article:
Beryllium-copper mill products: Typical conditions
In addition, microstructures of a C82500 alloy casting and a CI7200 alloy strip are provided.
nesc:ripllon
'Iemper
TBOO TOOl TD02 TD04
Thoslle strength beCore aging MPa ksi 70 80 91 110
480 550 625 760
Solutiontreated Solutiontreatedandcold worked10quarter-hard Solutiontreatedandcold worked10half-hard Solutiontreatedand cold worked10hard
Beryllium-copper alloys: Solution treating and precipitation hardening
Alloy
C17000 CI7200 CI7300 CI7500 C17510
Solution trealmentla) Thmperature Time(h). OF OC h 775-800 775-800 775-800 900-925 900-925
1425-1475 1425-1475 1425-1475 1650-1700 1650-1700
0.5-3 0.5-3 0.5-3 0.5-3 0.5-3
Aging treatment Thmperalure OF -c
300-330 300-330 300-330 455-480 455·480
Time,
h 1-3 1-3 1-3 1-3 1-3
575-625 575-625 575-625
sso-soo sso-soo
(a)All alloysare cooledimmediatelyandrapidlyfrom the solution-treating temperature. Thin sections such as stripcan be cooled in circulatingatmosphere;heaviersectionsrequirewaterquenching. (b) Shortertimesmay be desirableto minimizegrain growth.particularlyfor thin sections
• • • • • • • • • • •
Compositions of commercial beryllium-copper alloys Phase diagrams for beryllium-copper alloys Solution treatments and aging treatments Typical tempers of mill products Properties obtained in precipitation treatments Influence of cold reduction and age hardening on mechanical properties Age hardening response curves for tensile strength, yield strength. and elongation Age hardening response of annealed C17510 in TBOO temper Temper designations for beryllium-copper strip Properties obtained in precipitation treatment of CI7200, CI7000, C17500, and C17510 in various product forms Effects of special precipitation hardening treatments on mechanical properties and electrical conductivity of CI7200 and C17500 strip in various conditions
Compositions of commercial beryllium-copper alloys UNS number
Be
Co
NI
Composition, WI~ Co+Ni Co+Ni+Fe
Si
Cn
Pb
Wrought alloys 0.20 min 0.6 max C17200 1.80-2.00 0.2ll-O.6 0.20 min 0.6 max CI7300 1.80-2.00 0.20 min 0.6 max C17000 1.60-1.79 CI7510 0.2-0.6 1.4-2.2 2.4-2.7 C17500 0.4·0.7 C17410 0.15-0.50 0.35-0.60 Cast alloys 2.40-2.70 C82000 0.45-0.80 1.ll-2.0 C82200 0.35-0.80 0.2ll-0.65 C82400 1.60-1.85 0.2ll-O.35 C82500 1.90-2.25 0.35-0.70 0.2ll-O.35 1.00-1.20 C82510 1.90-2.15 0.2ll-O.35 C82600 2.25-2.55 0.35-0.65 0.2ll-O.35 0.35-0.70 C82800 2.5ll-2.85
bal bal bal bal bal bal bal bal bal bal bal bal bal
Note:Copperplus additions. 99.5%min
Beryllium-Copper Wire: Mechanical and electrical properties Electrical Wire diameter
Temper deslguations AS'IM
Commercial
Aging treatment
mm
in.
3hat315-330°C 2hat315-330°C 1.5h at 315-330·C I hat315-330°C IhaI315-330·C
1.3-12.7 1.3-12.7 1.3-12.7 1.3-2.0 1.3-2.0 1.3-12.7 1.3-12.7 1.3-12.7 1.3-2.0 1.3-2.0
0.05-0.5 0.05-0.5 0.05-0.5 0.05-0.08 0.05-0.08 0.05-0.5 0.05-0.5 0.05-0.5 0.05-0.08 0.05-0.08
3 h a148ll-495 °C 2 h at 48ll-495°C
1.3-12.7 1.3-12.7 1.3-12.7 1.3-12.7
0.05-0.5 0.05-0.5 0.05-0.5 0.05-0.5
ThnsUestreogth MPa ksi
Yield strength ksi MPa
Elongation,
conductivity,
~
~IACS
Cl72ooandC17300
'raoo
A
TOOl TD02 Too3 TD04
Quarter-H Half-H 'Three quarter-H H
TRlO
xr
THOI Quarter-HT TH02 Half-HT TH03 Threequarter-HT TH04 HT C17510 and C17500 TBOO A TD04 H TFOO xr TH04 HT
75ll-94O 890-1070 960-1140 1100-1380 1200-1450 127ll-1490 131ll-1590 134ll-159O
59-78 90-116 110-136 130-155 140·165 160-200 175-210 184-216 190-230 194-230
130-210 51ll-730 620-870 790-1040 89O-1110 990-1250 1130-1380 1170-1450 1200-1520 124O-15W
19-30 74-106 9ll-126 115-151 129-161 144-181 164-200 17ll-21O 174-2W 18ll-2W
3ll-6O 3-25 2-15 2-8 1-6 3 min 2 min 2 min 2 min I min
15-19 15-19 15·19 15-19 15-19 22-28 22-28 22-28 22-28 22-28
24ll-380 44ll-56O 68ll-900 75ll-970
35-55 64-81 99-130 109-140
60-210 370-520 550-760 650-870
8.7-30 54-75 80-110 94-126
2ll-6O
2ll-30 2ll-30 45-60 48-60
41ll-54O
ezo-soo
2-W
10min 10min
4061 Heat Treater's Guide: Nonferrous Alloys
Beryllium-copper strip: Temper designationsand properties forvarious conditions Temperdesignnlloos ASIMB601 Commercial
Ioltial
cODditIoD(a)
Agiog treatmentfb)
TellSile strength MPa ksi
Yieldstrength atO.2%offset
FlectricaI ksi
Eloogatloo, %
Rockwell hardness
conductivity,
MPa
%IACS
C17000 (97.9Cu-l.7Be) TBoo TOOl T002 TD04 TRlO(c)
A A{planish) Quarter-H Half-H H AT
Annealed Annealed Quarter-hard Half-hard Hard Annealed
THOl(c)
Quarter-HT
Quarter-hard
TH02(c)
Half-HT
Half-hard
TH04(c)
HT
Hard
AM Quarter-HM Half-HM HM SHM XHM
Annealed Quarter-hard Half-hard Hard Hard Hard
'raoo
lMoo lMOI lM02 lM04 lM05 lM06
3hat315°C 3hat345°C 2hat315°C 3hat330°C 2hat315°C 2hat330°C 2hat315°C 2hat330°C M M M M M M
410-530 410-540 510-610 580-690 680-830 1030-1250 1105-1275 1100-1320 1170-1345 1170-1380 1240-1380 1240-1380 1275-1415 680-760 750-830 820-940 930-1040 1030-1110 1060-1210
59-77 59-78 74-88 84-100 99-120 149-181 160-185 160-191 170-195 170-200 180-200 180-200 185-205 99-110 109-120 119-136 135-151 149-161 154-175
190-250 200-380 410-560 510-660 620-800 890-1140 860-1140 930-1210 895-1170 1030-1250 965-1240 1060-1250 1070-1345 480-660 550-760 650-870 750-940 860-970 930-1140
28-36 29-55 59-81 74-96 90-116 129-165 125-165 135-175 130-170 149-181 140-180 154-181 155-195 70-96 80-110 94-126 109-136 125-141 135-165
35-65 35-60 20-45 12-30 2-10 3-20 4-10 3-15 3-6 1-10 2-5 1-6 2-5 18-30 15-25 12-22 9-20 9-18 3-10
45-78HRB 45-78HRB 68-9OHRB 88-96HRB 96-102HRB 33-38HRB 34-4OHRC 35-40HRC 36-41HRC 37-42HRC 38-42HRC 38-44HRC 39-43HRC 98HRB-23HRC 20-26HRC 24-30HRC 28-35HRC 31-37HRC 32-38HRC
15-19 15-19 15-19 15-19 15-19 22-28 22-28 22-28 22-28 22-28 22-28 22-28 22-28 18-33 18-33 18-33 18-33 18-33 18-33
3hat315°C 0_5h31370 °C 2hat315°C 0.25 h at 370°C 2hat315°C 0.25 h at 370°C 2hat315°C 0.25 h at 370°C M M M M M M M
410-530 410-540 510-610 580-690 680-830 1130-1350 1105-1310 1200-1420 1170-1380 1270-1490 1240-1450 1310-1520 1275-1480 680-760 750-830 820-940 930-1040 1030-1110 1060-1210 1200-1320
59-77 59-78 74-88 84-100 99-120 164-195 160-190 174-206 170-200 184-216 180-210 190-220 185-215 99-110 109-120 119-136 135-150 149-160 154-175 174-191
190-250 200-380 410-560 510-660 620-800 960-1205 895-1205 1030-1275 965-1275 1100-1350 1035-1345 1130-1420 1105-1415 480-660 550-760 650-870 750-940 860-970 930-1180 1030-1250
28-36 29-55 59-81 74-95 90-116 139-175 130-175 149-185 140-185 159-196 150-195 164-206 160-205 70-96 80-110 94-126 109-136 125-140 135-171 149-181
35-65 35-60 20-45 12-30 2-18 3-15 3-10 3-10 2-6 1-8 2-5 1-6 1-4 16-30 15-25 12-22 9-20 9-18 4-15 3-12
45-78HRB 45-78HRB 68-9OHRB 88-%HRB 96-102HRB 36-42HRC 34-40HRC 36-43HRC 36-42HRC 38-44HRC 38-44HRC 38-45HRC 39-45HRC 95 HRB-23 HRC 20-26HRC 23-30HRC 28-35HRC 31-37HRC 32-38HRC 33-42HRC
15-19 15-19 15-19 15-19 15-19 22-28 22-28 22-28 22-28 22-28 22-28 22-28 22-28 17-28 17-28 17-28 17-28 17-28 17-28 17-28
750-900
109-130
650-870
94-126
7-17
95 HRB-27 HRC
45-55
240-380 240-380 480-590 725-825 680-900 680-900 792-950 750-940 750-940 820-1040 510-590
35-55 35-55 70-85 105-120 99-130 99-130 115-138 109-136 109-136 119-150 74-85
130-210 170-320 370-560 550-725 550-690 550-690 725-860 650-830 650-830 750-970 340-520
19-30 25-46 54-81 80-105 80-100 80-100 105-125 94-120 94-120 109-140 49-75
20-40 20-40 2-10 8-12 10-25 10-25 5-8 8-20 8-20 1-5 8-20
20-45HRB 20-45HRB 78-88HRB 93-looHRB 92-1OOHRB 92-1OOHRB 97-104HRB 95-I02HRB 95-102HRB 98-I03HRB 79-88HRB
20-30 20-30 20-30 45-60 45-60 45-60 45-52 48-60 48-60 48-60 60 min
Cl7200 (98.1Cu-l.9Be) TBoo TBoo TOOl T002 TD04 TRlO(c)
A A (planish) Quarter-H Half-H H AT
Annealed Annealed Quarter-hard Half-hard Hard Annealed
THOI(c)
Quarter-HT
Quarter-hard
TH02(c)
Half-HT
Half-hard
TH04(c)
HT
Hard
AM Quarter-HM Half-HM HM SHM XHM XHMS
Annealed Quarter-hard Half-hard Hard Hard Hard Hard
lMoo lMOI lM02 lM04 lM05 lM06 lM08
C17400 (99'sCu(rninHI.30Be-O.2SCo) and C17410 (99.5 Cu(rnin)-0.3Be-O.SCo) HT
Hard
M
C17SOO (96.9Cu-o.SSBe-2.SSCo) and C17S10 (97.8Cu-o.4Be-l.8Ni) TBoo TBoo TD04 TRlO(c)
A A (planish) H AT
Annealed Annealed Hard Annealed
lMoo TH04(c)
AM HT
Annealed Hard
HM
Hard Hard Hard
lM04
HTR HTC
3hat455°C 3hat480°C M 2hat455°C 2hat480°C M M M
(a) All annealing is solution treating, and all alloys are annealed prior to roll hardening and/or heat treatment where applicable. (b) M. mill hardened with special mill processing and precipitation treatment. (c) Two heat treatments given for comparison
Beryllium Copper Alloys 1407
Beryllium-copper alloys: Properties and precipitation treatments usually specified
Initialcondition C17200 Flatproducts Annealed Quarter-hard Half-hard Hard Annealed(d) Annealed Quaner-hard(d) Quarter-hard Half-hard(d) Half-hard Hard(d) Hard Rod,bar,plate Annealed Hard Annealed(d) Hard(d) Wrre(e) Annealed Quarter-hard Half-hard Threequarter-hard Annealed(d) Annealed Quarter-hard(d) Quarter-herd Half-hard(d) Half-hard Threequaner-hard(d) Threequarter-hard C17000 Flatproducts Annealed Quarter-hard Half-hard Hard Annealed Annealed(d) Quarter-hard Quaner-hard(d) Half-hard Half-hard(d) Hard Hard(d) Rod,bar Annealed Hard Annealed Annealed(d) Hard Hard(d) Cl7SOO, Cl7S10 Rod,bar,plate.flatproducts Annealed Hard Annealed Annealed(d) Hard Hard(d)
Standard aging treatment Thmpemture TIme, OF h OC
None None None None 3 0.5 2 0,33 2 0.25 2 0.25 None None 3 2 None None None None 3 0.5 2 0.25 1.5 0.25 I 0.25
None None None None 3 3 2 3 2 2 2 2 None None 3 3 2 2
None None 3 3 2 2
315 370 315 370 315 370 315 370
315 315
315 370 315 370 315 370 315 370
315 345 315 330 315 330 315 330
315 345 315 345
480 455 480 455
Electrical
Thnsile strength MPa ksi
Yield strength!a) ksi MPa
conductivlty,
Elongatlon(h), %
llanlness(c)
% lACS
600 700 600 700 600 700 600 700
415-540 515-605 585-690 690-825 1140-1345 1105-1310 1205-1415 1170-1380 1275-1485 1240-1450 1310-1575 1275-1480
60-78 75-88 85-100 100-120 165-195 160-190 175-205 170-200 185-215 180-210 190-220 185-215
195-380 415-550 515-655 620-770 965-1205 895-1205 1035-1275 965-1275 1105-1345 1070-1345 1140-1415 1105-1415
28-55 60-80 75-95 90-112 140-175 130-175 150-185 140-185 160-195 155-195 165-205 160-205
35-60 10-40 10-25 2-8 4-10 3-10 3-6 2-6 2-5 2-5 1-4 1-4
45-78HRB 68-9OHRB 88-96HRB 96-I02HRB 35-4OHRC 34-4OHRC 37-42HRC 36-42HRC 39-44HRC 38-44HRC 4O-45HRC 39-45HRC
17-19 16-18 15-17 15-17 22-25 22-25 22-25 22-25 22-25 22-25 22-25 22-25
600 600
415-585 585-895 1140-1345 1205-1550
60-85 85-130 165-200 175-225
185-205 515-725 1000-1205 1035-1380
20-30 75-105 145-175 150-200
35-60 10-20 3-10 2-5
45-85HRB 88-103HRB 36-41HRC 39-45HRC
17-19 15-17 22-25 22-25
600 700 600 700 600 700 600 700
450-590 620-795 760-930 895-1070 1140-1310 1105-1310 1205-1415 1170-1415 1310-1480 1275-1480 1345-1585 1310-1585
65-85 90-115 110-135 130-155 165-190 160-190 175-205 170-205 190-215 185-215 195-230 190-230
185-240 485-655 620-760 760-930 1000-1205 930-1205 1105-1310 1035-1310 1205-1380 1170-1380 1245-1415 1205-1415
20-35 70-95 90-110 110-135 145-175 135-175 160-190 150-190 175-200 170-200 180-205 175-205
35-55 10-35 4-10 2-8 3-8 3-8 2-5 2-5 1-3 1-3 1-3 1-3
600 650 600 625 600 625 600 625
415-540 515-605 585-690 690-825 1035-1240 1105-1275 1105-1310 1170-1345 1170-1380 1240-1380 1240-1450 1275-1415
60-78 75-88 85-100 100-120 150-180 160-185 160-190 170-195 170-200 180-200 180-210 185-205
170-365 310-515 450-620 550-760 895-1105 860-1140 860-1140 895-1170 895-1170 965-1240 965-1240 1070-1345
25-55 45-75 65-90 80-110 130-165 125-165 135-170 130-170 145-175 140-180 155-180 155-195
35-60 10-40 10-25 2-8 4-10 4-10 3-6 3-6 2-5 2-5 2-5 2-5
47-78HRB 68-9OHRB 88-96HRB 96-I02HRB 33-39HRC 34-4OHRC 34-4OHRC 36-41HRC 36-41HRC 38-42HRC 38-42HRC 39-43HRC
17-19 16-18 15-17 15-17 22-25 22-25 '22-25 22-25 22-25 22-25 22-25 22-25
600 650 600 650
415-585 585-895 1035-1240 1105-1275 1140-1380 1205-1415
60-85 85-130 150-180 160-185 165-200 175-205
185-205 515-725 860-1070 930-1140 930-1140 965-1170
20-30 75-105 125-155 135-165 135-165 140-170
35-60 10-20 4-10 4-10 2-5 2-5
45-85HRB 88-103HRB 32-39HRC 34-4OHRC 36-41HRC 38-42HRC
17-19 15-17 22-25 22-25 22-25 22-25
900 850 900 850
240-380 515-585 690-760 725-825 760-860 795-930
35-55 75-85 100-120 105-120 110-130 115-135
185-205 380-550 550-690 550-725 690-825 725-860
20-30 55-80 80-100 80-105 100-120 105-125
20-35 3-10 10-20 8-12 8-15 5-8
20-43HRB 78-88HRB 92-IOOHRB 93-IOOHRB 95-103HRB 97-I04HRB
25-30 20-30 45-60 45-52 45-60 45-52
17-19 15-17 15-17 15-17 22-25 22-25 22-25 22-25 22-25 22-25 22-25 22-25
(a) At 0.2% offset. (b) In 50 nun (2 in.), (e) RockwellBand C hardnessvalues are accurateonly if metalis at least I nun (0.040 in.) thick. (d) Heat treatmentthatprovidesoptimumstrength.(e) For wire diametersgreaterthan 1.3nun (0.050in.)
4081 Heal Treater's Guide: Nonferrous Alloys Cu-Be strip: Effectsof special precipitation-hardening treatments on mechanical properties and electrical conductivity Initial condition
AlloyCl7200 Annealed
Quarterhard
Halfhard
Hard
AlloyCl7500 Annealed
Hard
Aging treatment TIme, Temperalure min
None 5 15 30 60 120 240 None 5 15 30 60 120 240 None 3 5 15 30 60 120 240 420 None 5 15 30 60 120 240 None 120 120 120 120 None 120 120 120 120
°C
of
370 370 370 370 370 370
700 700 700 700 700 700
370 370 370 370 370 370
700 700 700 700 700 700
370 370 370 370 370 370 370 370
700 700 700 700 700 700 700 700
370 370 370 370 370 370
700 700 700 700 700 700
425 455 480 510
800 850 900 950
425 455 480 510
800 850 900 950
Tensile slreogth
Yield strength!a)
MPa
ksI
MPa
465 855 1195 1260 1240 1195 1150 570 1115 1250 1290 1230 1185 1155 605 1010 1280 1310 1325 1280 1200 1185 1010 730 1300 1360 1310 1295 1240 1215
67.5 124 173 182.5 180 173.5 167 82.5 162 181 187 178.5 172 167.5 87.5 146.5 186 190 192.5 185.5 174 172 146.5 106 188.5 197 190 188 180 176
250 695 1055 1060 1055 1040 980 485 945 1115 1125 1060 1000 970 555 885 1110 1175 1180 1105 1040 1035 860 690 1125 1195 1170 1105 1090 1055
350 805 835 805 795 440 985 915 850 800
51 117 121 116.5 115 63.5 142.5 133 123 116
170 625 675 625 600 425 860 800 760 705
Elongalion(h), conducllvlty,
Modulus or elasticity
Fatigue
EIecIJical strength!c)
%
%IACS
MPa
ksI
GPo
lOOps;
36 101 153 153.5 153 151 142 70.5 137 162 163.5 154 145 141 80.5 128 161 170.5 171 160 150.5 150 125 100 163 173 170 160 158 153
49 18 10 6 5 6 6 21 9 6 4 3 4 6 17 11 3 2 2 2 3 3 10 5 3 2 1 1 2 2
18.0 19.5 22.0 23.0 25.5 26.0 26.5 17.0 18.5 W.5 23.5 25.5 26.5 27.0 16.0 18.0 21.0 23.0 24.5 25.0 26.0 27.0 27.0 15.0 18.0 21.0 24.5 26.5 27.5 27.5
205
30
255
37
2W
32
290
42
230 230 295 305 305 295 275 275 200 270
33 33 43 44 44 43
315
46
115 120 125 125 130 130 130 115 125 130 130 130 130 130 115 125 125 130 130 130 130 130 130 120 125 130 130 130 130 130
16.5 17.5 18.0 18.0 18.5 18.5 19.0 17.0 18.0 18.5 18.5 18.5 19.0 19.0 17.0 18.0 18.0 18.5 18.5 18.5 18.5 19.0 19.0 17.5 18.0 18.5 19.0 19.0 19.0 19.0
25 91 98 91 87 61.5 125 116 110.5 102
30 14 14 14 16 2 11 13 13 12
25 44 48 48 48.5 27.8 44.0 45.0 47.5 49.0
110 135 140 140 140 125 140 140 140 140
16.3 19.3 20.0 20.0 W.O 18.3 20.0 20.0 20.0 20.0
ksi
40 40
29 39
215
31
250
36
(a)At 0.2%offset.(b) In 50 mm(2 in.), (c) 107 cycles
C82500 Alloy Casting: Microstructure. Solution annealed at 790 DC (1450 OF) and aged to peak hardness at 315 DC (600 OF) for 3 h. Microstructure consists of Chinese-script beryllides in a copper-rich a solid-solution matrix, with angular ~ phase transformed to a lamellar aggregate of a and y phases. Striations are the result of metastable precipitation in the alloy. 400x
LIVE GRAPH
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Beryllium Copper Alloys I 409
Phase diagram for beryllium-copper alloy. Binary composI-
Phase diagram for Beryllium-copper alloy. Pseudobinary
tion for high-strength alloyssuch as C17200
composition for a high-conductivity alloy, C17510
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Beryllium, wt%
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Beryllium-Copper Alloy C17510: Age Hardening. Age-hardening response curvesfor annealed(TBOO temper)
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Copper-Beryllium Alloys: Mechanical Properties. Influence of cold reduction and age hardening on the mechanical properties of beryllium-copper alloys. (a) C17510 aged at 480°C (895 OF) for 2 or 3 h. (b) C17200 aged at 315°C (600 OF) for 20r3h
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C17200 Alloy Strip: Microstructure.. Solution annealed at 790 °C (1450 OF) and cold rolled at 37% to full hard temper. Longitudinal section shows elongated grains of ex phase and cobalt berylIides.400x
Beryllium Copper Alloys /411
Copper-Beryllium Alloy C17200: Age Hardening. Age-hardening response curves for the tensile strength, yield strength, and elongation. (a) Annealed (TBOO) temper. (b) Roll-hardened (TD04)temper
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Production Sintering of Bronze
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Sintering Time and Temperature. Typical sintering furnace temperatures for bronze range from 815 to 860°C (1500 to 1580 "F); total sintering time within the hot zone may range from 15 to 30 min, depending on the furnace temperature selected. required dimensional change. and most importantly. the presence of an optimum alpha grain structure. Sintering atmospheres should be protective and reducing to facilitate sintering. Reduction of the copper oxides that may surround each copper powder particle and reduction of tin oxide formation allow for increased diffusion rates. Consequently, faster sintering rates and more homogeneous structures can be obtained. Dimensional Change. Effective sintering is essential. because the homogeneity of the sintered structure affects the resultant secondary forming and operational characteristics of the finished part. A typical sintering/dimensional change pattern is shown in an adjoining Figure. which illustrates the relationship of a "medium growth" copper-tin system as a function of total time in the furnace hot zone. Absolute sintered dimensional characteristics typically are unique to a specific source of copper and tin powders. For example. sintered dimensional consistency may be obtained by blending two or more base copper powders that exhibit different growth characteristics and/or by use of tin powders that also exhibit different growth characteristics. Generally, copper-tin blends composed of relatively coarse powder sinter to higher growth values than a blend composed of finer powders. After powder blends have been tested and adjusted to provide an approximation of target dimensions. final adjustments are made during production sintering to obtain dimensional precision. Factors affecting the ultimate. or peak, dimensional values include physical characteristics of the constituents and compacted density. Control of sintered dimensions in premix systems is achieved by manipulating sintering time and/or temperature.
Dimensional change in an elemental bronze blend (90Cu10Sn) as a function of time and temperature. Sintered in hot zone at 845°C (1555 OF) in dissociated ammonia atmosphere +3.0
Green density. g/cm 3
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20
Total time. min
Production Sintering of Brass and Nickel Silvers Sintering temperatures for standard brasses range from 760 to 925 °C (1400 to 1700 "F), Temperature selection depends on the brass alloy being sintered and the mechanical properties desired after sintering. Lower brasses with higher zinc contents and lower melting points are sintered at the lower temperature. Generally. a starting temperature of 100°C (180 "F) below the solidus temperature (as determined from any copper-zinc binary alloy constitutional diagram) is suitable. Nickel silver may be sintered at 870 to 980°C (1600 to 1800 "F), Currently. only one base alloy is used for the manufacture ofPIM structural parts; it has nominal composition of 64Cu-18Ni-18Zn. The leaded alloy composition contains 1.5% Pb. Sintering characteristics are similar to those of the brasses; therefore. responses to sintering parameters that affect dimensional and mechanical properties of brass are equally applicable to nickel silver. Sintered Properties. Dimensional and mechanical properties of brasses and nickel silvers are primarily affected by compact density and the
amount of time at temperature, as well as the sintering temperature itself. As mentioned above, other elements that affect dimensional and mechanical properties usually are not added to powders. However. sintered properties, especially dimensional change. may be effectively controlled by manipulation of sintering time at the appropriate temperature. Each alloy exhibits unique dimensional characteristics-a 90Cu-IOZn brass compacted at 414 MPa (30 tsi) and sintered for 30 min at 870°C (1600 oF) may shrink 0.5%, while a 70Cu-30Zn brass similarly treated may shrink 2.5%. Figures show typical property relationships that can be controlled through manipulation of time at temperature. The leaded brasses shown in Figures (80Cu-20Zn and 70Cu-30Zn) are commonly used for structural parts fabrication. Densities shown are "average" for compacting lubricated prealloyed powders containing 0.375% lithium stearate and 0.375% zinc stearate at 414 MPa (30 tsi). As shown, close dimensional control may be obtained with a minimum reduction in mechanical properties after 15 min at temperature. Ductility is increased for subsequent forming operations,
Sintering Copper-Based Materials /413 such as sizing, cold re-pressing for densification, or coining, by increasing sintering time. Atmosphere protection is required for sintering brasses and nickel silvers to prevent oxidation and to ensure effective sintering. Use ofIithium stearate as the base lubricant allows the use of most common sintering atmospheres over a wide range of dew points. Although dry hydrogen or dissociated ammonia provides the best sintering atmosphere, comparable properties can be obtained with nitrogen-based or partially combusted hydrocarbon gas atmospheres. When sintering, compacts should be protected from direct impingement of furnace flame curtains and atmosphere gases by partially or fully covering loaded trays to minimize zinc loss. Because it has a high vapor pressure at standard sintering temperature (boiling point of pure zinc is 906 "C, or 1663 OF), zinc may be lost to the atmosphere as it diffuses through to the particle surfaces. Loss of excessive surface zinc results in a change in surface composition. In the case of brasses, pink copper or zinc-depleted areas are apparent. Although superficial zinc losses do not adversely affect sintered properties, surface finish is diminished; finished parts may be rejected because of color differences. Q)
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Magnesium Alloys
Heat Treating Magnesium Alloys Magnesium alloys usually are heat treated either to improve mechanical properties or as a means of conditioning for specific fabricating operations. The type of heat treatment selected depends on alloy composition and form (cast or wrought), and on anticipated service conditions. Solution heat treatment improves strength and results in maximum toughness and shock resistance. Artificial aging (precipitation heat treatment) after solution treatment gives maximum hardness and yield strength, but with some sacrifice oftoughness. As applied to castings, artificial aging without prior solution treatment or annealing is a stress-relieving treatment that also somewhat increases tensile properties. Annealing of products lowers tensile properties considerably and increases ductility, thereby facilitating some types offabrication. Modifications of these basic treatments have been developed for specific alloys, to obtain the most desirable combinations of properties. For example, increasing the aging time for some magnesium alloy castings considerably increases yield strength (although with some sacrifice of ductility). Also, combinations of solution treating, strain hardening, and artificial aging are applied to alloy HM2lA sheet to improve mechanical properties over those attainable by solution treating and artificial aging alone. For certain magnesium alloys, development of properties depends almost entirely on heat treatment. In magnesium-zirconium alloys, however, the extremely pronounced grain-refining effect of the zirconium also plays a very important role in improving mechanical properties. The mechanical properties of most magnesium casting alloys can be improved by heat treatment. Casting alloys can be grouped into seven general classes of commercial importance on the basis of composition:
• • • • •
Magnesium-aluminum-manganese (example: AMl00A) Magnesium-aluminum-zinc(examples:AZ63A, AZ81A, AZ91C, AZ92A) Magnesium-zinc-zirconium (examples: ZK51A, ZK61A) Magnesium-rare earth metal-zinc-zirconium (examples:EZ33A, ZFAIA) Magnesium-rare earth metal-silver-zirconium, with or without thorium (examples: QE22A, QH21A) • Magnesium-thorium-zirconium, with or without zinc (examples: HK31A, ZH62A, HZ32A) • Magnesium-zinc-copper (example: ZC63A)
In most wrought alloys, maximum mechanical properties are developed through strain hardening, and generally they are either used without subsequent heat treatment or merely aged to a T5 temper. Occasionally, however, solution treatment, or a combination of solution treatment with strain hardening and artificial aging, will substantially improve mechanical properties. Wrought alloys that can be strengthened by heat treatment are grouped into five general classes according to composition:
• • • • •
Magnesium-aluminum-zinc (example: AZ80A) Magnesium-thorium-zirconium (example: HK31A) Magnesium-thorium-manganese (examples: HM21A, HM31A) Magnesium-zinc-zirconium (example: ZK60A) Magnesium-zinc-copper (example: ZC71A)
Types of Heat Treatment Commonly used heat treatments for wrought and cast alloys and the tempers on which they are based are listed in Table 1 and Table 2. Individual datasheet articles on each ofthe alloys named in Table 1 follow this introduction. Annealing. Wrought magnesium alloys in various conditions of strain hardening or temper can be annealed by being heated at 290 to 455°C (550 to 850 OF), depending on alloy, for one or more hours (Table 3). This procedure usually will provide a product with the maximum anneal that is practical. Because most forming operations on magnesium are at elevated temperature, the need for fully annealed wrought material is less than with many other metals. Stress Relieving of Wrought Alloys. Stress relieving is used to remove or reduce residual stresses created in cold and hot working, shaping and forming, straightening, and welding. Table 4 gives recommended stress-relieving times and temperatures. When extrusions are welded to hard-rolled sheet, the lower stress-relieving temperature and longer time should be used to minimize distortion; for example, use 150°C (300 "F) for 60 min rather than 260 °C (500 "F) for 15 min. Stress Relieving of Castings. Machining of castings to close dimensionallimits, the necessity of avoiding warpage and distortion, and the desirability of preventing stress-corrosion cracking in welded magnesiumaluminum casting alloys make it mandatory that castings be substantially free from residual stresses. Although magnesium castings do not normally contain high residual stresses, the low modulus of elasticity of magnesium alloys means that comparatively low stresses can produce appreciable elastic strains.
Table1 Heat treatments commonly applied to magnesium alloys Alloy
Heal lrealmenl(a)
Casting alloys AMlOOA
1\l.63A AZSIA AZ9lC AZ92A EZ33A EQ2lA HK3IA HZ32A QE22A QH2lA
WFA3A WE54A ZC63A ZE4IA ZE63A ZH62A ZK5IA ZK6lA
T4. T5. T6. T61(b) T4.T5.T6 T4 T4.T6 T4.T6 TS T6 T6 T5 T6 T6 T6 T6 T6 TS T6(c) TS TS T4,T6
Wrought alloys AZSOA HM2IA HM3IA ZC7IA
ZK60A
T5 TS, 1'8.1'81(d) TS F,T5.T6 TS
(a) Indicated by temper designations (see Table), (b) Same as T6 except aged for longer time to increase yield strength. (e) Thermal treatment must include hydriding. (d) Mill modification of1'8 to
improve mechanical properties
418/ Heat Treater's Guide: Nonferrous Alloys Residual stresses may arise from contraction due to mold restraint during solidification, from nonuniform cooling after heat treatment, or from quenching. Machining operations also can result in residual stress and require intermediate stress relieving prior to final machining. Weld repairs may introduce severe stresses and should be followed by some type ofheat treatment to prevent subsequent movement and cracking. See Table 5 for postweld heat treatments. The following heat treatments for castings will provide stress relief without significantly affecting mechanical properties:
Table 2 Basic temper designations for magnesium alloys ElqIlanation
Designation
As-fabricated Annealed,recrystallized(wroughtproductsonly) Strainhardened(wroughtproductsonly) Strainhardenedonly Strainhardenedand partiallyannealed Strainhardenedand stabilized Solutionheat treated;unstabletemper Heat treatedto producestabletempersother thanF, 0, or H Annealed(castproductsonly) Solutionheat treatedand cold worked Solutionheat treated Artificiallyaged only Solutionheat treatedand artificiallyaged Solutionheat treatedand stabilized Solutionheat treated,cold worked,and artificiallyaged Solutionheat treated,artificiallyaged,and coldworked Artificiallyaged and cold worked
F
o H
HI H2 H3 W
T 1'2
Solution Treating and Aging. Schedules for solution treating and aging of magnesium alloys are summarized in Table 6. In solution treating of magnesium-aluminum-zinc alloys, parts should be loaded into the furnace at approximately 260°C (500 OF) and then raised to the appropriate solution-treating temperature slowly, to avoid fusion of eutectic compounds and resultant formation of voids. The time required to bring the load from 260 °C (500 "F) to the solution-treating temperature is determined by the size of the load and by the composition, size. weight, and section thickness of the parts, but 2 h is a typical time. All other heat-treatable magnesium alloys can be loaded into the furnace at the solution-treating temperature. For alloy HK3IA, it is important to bring the load to temperature as rapidly as possible to avoid grain coarsening. During aging, magnesium alloy parts should be loaded into the furnace at the treatment temperature, held for the appropriate period. and then cooled in still air. As indicated in Table 6, there is a choice ofartificial aging treatments for some alloys; results are closely similar for the alternative treatments given.
Table 3 Annealing temperatures for wrought magnesium alloys Annealingtemperafureta) Alloy
AZ31B AZ3IC AZ6IA AZSOA HIGIA HM2IA HM3IA ZK60A
Original temper
F,HIO.HII,H23,H24,H26
345 345 345 385 400 455 455 290
F F
F,T5,T6 H24 T5,T8,T81 T5 F,T5,T6
650 650 650 725 750 850 850 555
1'3 T4 TS T6 T7 1'8 1'9 TIO
Note: For moreinformationon the designationsoutlinedhere, seeVolume2 oftheASM Handbook series
Table 4 Recommended stress-relieving treatments for wrought magnesium alloys Sbeet
Alloy
AZ31B AZ3IB-F AZ6IA AZ6IA-F AZSOA-F AZSOA-T5 HK3IA HM2IA-T5 HM2IA-TB HM2IA-TBI HM3IA-T5 ZC7IA-T5 ZK60A-F ZK60A-T5
Annealed Thmperature TIme, OF min OC
Bard rolled Thmpemture 'lime, OF -c min
345
650
120
150
300
60
345
650
120
205
400
60
345
230
650
450
60
290
555
30
370 400
700 750
30 30
180
Extrusionsand forgings Thmperature 'lime, OF OC min
260
500
15
260 260 205
500
500 400
15 15 60
370
700
30
430 330 260 150
800 625 500 300
60 60 15 60
Note: Stressrelievingafterwelding, to prevent stress-corrosion cracking,is necessaryonly for alloys thatcontainmorethan 1.5%aluminum
(a) Tune at temperature. I h or more
Table 5 Postweld heat treatments for magnesium alloy castings Alloy
Weldingrod
AZ63A
AZ63Aor AZ92A(a)
AZSIA AZ91C
AZ92AorAZIOI AZ92Aor AZI OJ
AZ92A
AZ92A
EQ21A EZ33A HIGIA HZ32A QE22A QH21A WE43A WE54A ZC63A ZE4IA ZH62A ZK5IA
EQ21A EZ33A HK3IA(g) HZ32A(g) QE22A QH21A WE43A WE54A ZC63A ZE4IA(g) ZH62A(g) ZK5IA(g)
Thmperbeforeweldlng
F F T4 T40rT6 T4
Desiredtemper after welding
T4
T4 T6 T4 T6 T4 T4
T40rT6 T4 T40rT6 T40rT6 ForT5 T40rT6 ForT5 T40rT6 T40rT6 T40rT6 T40rT6 T40rT6 ForT5 ForT5 ForT5
T4 T6 T6 T5 T6 T5 T6 T6 T6 T6 T6 T5 T5 T5
T6
Postweklbeat treatment
12h at385 ±6 °C (725± 100F)(b) 12hat385 ±6 °C (725± 100F)(b), plus5 hat220 °C (430°F) 0.5 h at 385± 6 °C (725± 10oF) 0.5h at 385± 6 °C (725± 10oF),plus5 hat 220°C (430oF) 0.5h at415 ±6 °C (775± 10°F)(c) 0.5 hat415±6°C(775± IO°F)(c) 0.5 hat415±6°C(775 ±1O°F)(c),plus4hat215°C(420°F)or 16hatI70°C(340°F) 0.5hat41O±6°C(765± IO°F)(c) 0.5hat41O±6 °C(765 ± IO°F)(c),plus4 h at 260°C (500°F) or5 h at220°C (430°F) I h at 505± 6 °C (940± 10oF),quench,16h at 205°C (400oF) 2 h at 345°C (6500F)(d), and/or5 h at215 °C (420oF),or 24 h at 220 °C (430oF) 16hat205°C(4OO°F)(e) 16hat315°C(600°F) I hat51O±6°C(950± 10°F), quench,16hat205 °C(4OO°F) I hat51O±6°C (950± IO°F),quench, 16hat205°C(4OO°F) I hat510±6°C(950± IO°F),quench,16hat205 °C (400°F) I hat51O±6°C(950± 10°F), quench,16h at 205°C(4OO°F) I hat425±6°C(795± 10°F), quench,16h at 205°C (400°F) 2 hat330 °C (6250F)(f) 12h at 250°C(480 0F)(f) 2 h at 330°C (625oF), plus 16h at 175°C (350oF)
(a) AZ63Arod must be usedfor weldingAZ63Ain theF temperbecause12h at385 °C (725 "F) causesgermination in welds madewith AZ92Arod:AZ92A rod normallyis usedfor weldingAZ63Ain the T4 orT6 conditionunlessAZ63Arod is requiredby specifications. (b)Preheatto260°C (500°F); heat to specifiedtemperatureat no more than83 0C/h(150 °FIb).(c) Usecarbon dioxideor sulfurdioxide atmosphere.(d) Heatingfor2 h at 345°C (650 "F) resultsin slightlossofcreepstrength.(e) Alternativetreatment: I h at315 °C (600oF),plus 16h at 205°C (400 "F). (f)Alternativetreatment: 2 h at 330°C (625 oF),plus 16 It at 175°C (350 oF).(g) Or EZ33A
Magnesium Alloys /419 Reheat Treating. Under normal circumstances, when mechanical properties are within expected ranges and the prescribed heat treatment has been carried out, reheat treating is seldom necessary. However, if the microstructures of heat-treated castings indicate too high a compound rating, or if the castings have been aged excessively by slow cooling after solution treating, reheat treating is called for. Most magnesium alloys can
be reheat treated with little danger of germination (excessive grain growth). When reheat treating of alloy HK31A is necessary, however, the castings should be checked carefully for evidence of germination. To prevent germination in Mg-AI-Zn alloys, solution reheat-treating time should be limited to 30 min (assuming proper solution treatment of thick sections during prior heat treatment).
Table 6 Recommended solution-treating and aging schedules for magnesium alloy castings and wrought alloy ZC71A For castings up to 50 mm (2 in.) in section thickness; heavier sections may require longer times at temperature. Solutiontreallng!c) Maximum temperature
Aging!a) Alloy
Final temper
Temperature
Temperature
°C,±6(b)
Magnesium-aluminum-zinc castings(d) AM100A T5 230 T4 T6 T61 26O(f) AZ63A T5 T4 T6 AZS1A T4 AZ91C T5 168(g) T4 T6 AZ92A T5 260 T4 T6 Magnesium-zinc-mpper castings ZC63A(k) T6 Magnesium-zirconium castings EQ21A(k) T6 EZ33A T5 175 HK3IA(m) T6 HZ32A T5 315 QE22A(k) T6 QH21A(k) T6 WE43A(k) T6 WE54A(k) T6 ZE41A T5 330(n) ZE63A(P) T6 ZH62A T5 330 plus: 177 ZKS1A T5 177(q) ZK61A T5 150 T6 Wrought products ZC71A(k) T5 180 ZC7IA(k) T6
°F,±10(b)
'Dme,b
450
5
500(f)
335(g)
500
·C,±6(b)
°F,±10(b)
Time,b
°C
425(e) 425(e) 425(e)
795(e) 795(e) 795(e)
16-24(e) 16-24(e) 16-24(e)
435 435 435
810 810 810
385 385 415(e)
725 725 775(e)
10-14 10-14 16-24(e)
390 390 418
735 735 785
415(e) 415(e)
775(e) 775(e)
16-24(e) 16-24(e)
418 418
785 785
168(h)
335(h)
16(h)
410(j) 41O(j)
765(j) 765(j)
16-24(j) 16-24(j)
415 415
775 775
218
425
5
440
820
4-8
445
830
200
390
16
520
965
4-8
530
985
200
390
16
565
1050
2
570
1060
205
400
16
525 525 525 527
970 970 970 970
4-8 4-8 4-8 4-8
540 540 535 535
1000 1000 995 995
205 205 250 250
400 400 480 480
8 8 16 16
480
900
10-72
490
910
140
285
48
500(r)
930(r)
2(r)
500
930
130
265
48
430
800
4-8
435
810
180
355
16
°C,±6(b)
°F,±1O(b)
'Dme,b
230 218
450 425
5 25
218(f)
425(f)
5(f)
4(f)
16(g)
4
350
16
600
16
625(n)
2(n)
625 350 350(q) 300
2 16 12(q) 48
355
Aging after solutiontreating 'fimperature
OF
16
(a) Agingto theT5temperis done fromtheas-fabricated(I) condition.(b) Exceptwherequoteddifferently. (c) Aftersolutiontreatmentand beforesubsequentaging.castingsare cooledto roomtemperature by fast fan cooling,except where otherwiseindicated.Use carbon dioxide,sulfurdioxide,or 0.5 to 1.5%sulfurhexafluoridein carbon dioxideas a protectiveatmosphereabove 400 °C (750 "F), (d) For solutiontreating,Mg-AI-Znalloys areloadedinto !he furnaceat 260 °C (500 "P) and broughtto temperatureovera 2-hperiodat a uniformrateof temperatureincrease.(e) Alternativetreatrnenr, to prevent germination(excessivegraingrowth):6 h at415 ±6 °C (775± 10°F), 2 h at352±6 °C (665± 10oF),lOh at415 ±6 °C (775± 10oF).(f) Alternative treatment: 5 hat230±6 °C (450± 10°F).(g)Alternative treatment:4 h at 215±6 °C (420± 10"F), (b) Alternativetreatment: 5 to6 h at215 ±6 °C (420± 10 "F), (j)Alternativetreatment, to preventgermination(excessivegraingrowth):6 h at41O±6 °C (765± 10 "F), 2 h at 352 ± 6 °C (665± 10 "F), 10h at 410 ± 6 °C (765± 10 "F), (k) Quenchfromsolution-treating temperatureeitherin waterat 65°C (150oF)or in other suitablemedium.(m)AlloyHK31Acastings must beloadedinto!hefurnacealreadyat temperatureand broughtbackto temperature as quicklyas possible.(n)Thistreatmentisadequatefor developmentof satisfactoryproperties;it may be followedby 16 h at 177± 6 °C (350± 10oF)to providevery slightimprovements inmechanicalproperties.(p) AlloyZE63Amustbe solutiontreatedin a specialhydrogenatmospherebecauseits mechanicalproperties are developedlhroughhydridingofsomeofits alloyingelements.Hydridingtimedependsonsectionthickness;asaguide, 6.4mm(0.25in.)sectionsrequireapproximatelylOb, and 19mm (0.75in.)sections requireabaut72 h. Followingsolutiontreatment, ZE63Ashouldbequenchedin oil, waterspray,or air blast.(q)Alternativetreatment: 8 h at 218± 6 °C (425± 10oF).(r)Alternativetreatment: 10 h at480 ± 6 °C (900± 10oF)
420 I Heat Treater's Guide: Nonferrous Alloys
Effects of Major Variables Casting size and section thickness, relation of casting size to volume capacity of the furnace, and arrangement of castings in the furnace are mechanical considerations that can affect heat-treating schedules for all metals. Section Size and Heating Time. No general rule exists for estimating time of heating per unit of thickness for magnesium alloys. However, because of the high thermal conductivity of these alloys, combined with their low specific heat per unit volume, parts reach soaking temperature quite rapidly. The usual procedure is to load the furnace and to begin the soaking period when the loaded furnace reaches the desired temperature. The heat-treating times given in Table 5 have been found to be satisfactory for normal furnace loads and for castings of moderate section thickness. In the heat treating of magnesium alloy castings with thick sections (occasionally as low as 25 mm, or 1 in., but usually over 50 mm, or 2 in.), a good rule is to double the time at the solution-treating temperature. For example, the usual solution treatment for AZ63A castings is 12 h at about 385°C (725 "F), while 25 h at about 385°C is suggested for castings with section thicknesses greater than 50 mm (2 in.). The best way to determine whether additional solution-treating time is required is to cut a section through the thickest portion of a scrap casting and examine the center of the section microscopically: if heat treatment is complete, this examination will reveal a low compound rating. Heat-Treating Time and Temperature. As demonstrated by the data in Fig. 1 to 4, the mechanical properties of magnesium alloys can be varied within wide limits by varying the heat-treating times and tempera-
tures. The effect ofquenching media on properties is an example of another important consideration. See Table 7.
Solution-treating temperature. OF
Fig. 1 Tensile properties as function of solution treating temperature. Tensile properties as functions of solution-treating temperature. Data were obtained from test bars of casting alloy QE22A-T6 machined from 25 mm (1 in.) diam cast specimens. The bars were held at temperature for 4 h
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Sources Information in this introduction and in the 24 datasheet articles that follow is from three volumes in ASM International's Handbook Series: • Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, Vol 2, 10th ed. • Heat Treating, Vol 4, 10th ed. • Metallography and Microstructures, Vol 9, 10th ed.
Table 7 Effectof quenching medium on average tensile properties ofQE22A-T6 Queochlogmedlum
Stillair(c) Airblast(c) Waterat65°C (150°F)(c) 30%glycolatroomtemperature(d)
Thnslle strength ksI MPa
232 250 270 269
33.6 36.2 39.2 39.0
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22.9 26.4 27.5 27.5
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Magnesium Alloys /421
Fig. 2 Tensile properties as functions of aging time and temperature. Tensile properties of alloy QE22A- T6 as functions of aging time and temperature. Data were obtained from test bars of casting alloy QE22A-T6 machined from 25 mm (1 in.) diam cast specimens
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422/ Heat Treater's Guide: Nonferrous Alloys
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Cast Magnesium Alloys AM100A A magnesium-aluminum-zinc alloy Chemical Composition. Composition Limits. 9.3 to to.7 AI, 0.10 Mn min, 0.30 Zn max, 0.30 Si max, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. Corrosion resistance decreases with increasing amounts of Cu, Ni, and Fe. Increased amounts ofZn decrease pressure tightness. More than 0.5% Si decreases elongation Specifications (U.S. and/or Foreign). (AMS) Permanent mold castings: 4482. Investment castings: 4455; (ASTM) Sand castings: B 80. Ingot for sand, permanent mold, and die castings: B 93. Permanent mold castings: B 199. Investment castings: B 403; SAE J465. Former SAE alloy number: 502; UNS Mto100; (Government) Permanent mold castings: QQ-M-55
Characteristics Product Forms. Permanent mold castings, investment castings, sand castings, and die castings ApplicationslTypical Uses. Pressure-tight sand and permanent mold castings with good combinations of tensile strength, yield strength, and elongation
Mechanical Properties See Tables for typical mechanical properties of sand castings, and for typical tensile properties of sand castings at elevated and subzero temperatures
Fabrication Properties Weldability. Gas-shielded, metal arc process with AM 1OOA rod has "very good" rating
Recommended Heat Treating Practice Tempering Treatments. Commonly used treatments are for T4 condition (solution heat treated), T5 condition (artificially aged only), T6 condition (solution treated and artificially aged), and T61 condition (same as T6 except aged longer for higher yield strength) Solution Heat Treating. For solution treating, Mg-AI-Zn alloys are loaded into furnace at 260°C (500 OF) and brought to temperature over 2 h period, at a uniform rate of temperature increase. Solution Treating for T4 Condition. Heating is at 425°C (795 oF) for 16 to 24 h. Maximum temperature is 430°C (810 OF) Alternate treatment to prevent germination (excessive grain growth): Heat 6 h at 415 ± 6°C (775 ± 10 OF), 2 h at 352 ± 6 °C (665 ± 10 OF), 10 h at 415 ± 6°C (775 ± 10 OF)
Solution Treating for T6 Condition. Heat at 425°C (795 "F) for 16 to 24 h, maximum temperature is 435°C (810 OF) Alternative treatment to prevent germination (excessive grain growth): Heat 6 h at 415 ± 6°C (775 ± 10 OF), 2 h at 350 ± 6°C (665 ± 10 OF), 10 hat 415 ± 6°C (775 ± 10 OF)
Aging. For T5 condition: alloy is in F condition. Heating is at 230°C (450 OF) for 5 h Aging after Solution Treating. For T6 condition: 230°C (450 oF) for 5 h Solution Treating. For T61 condition: heat at 425°C (795 OF) for 16 to 24 h. Maximum temperature is 435°C (810 "F)
AM100A-F: Microstructure. As-cast. Massive M917A1 12 compound containing globular magnesium solid solution and surrounded by lamellar M917AI,2 precipitate. Normal air cooling produces this type of segregated eutectic. 500x
Alternative treatment to prevent germination (excessive grain growth): heat 6 h at 415 ± 6 °C (775 ± 10 OF), 2 h at 350 ± 6 °C (665 ± 10 OF), to h at 415 ± 6°C (775 ± to OF)
Aging after Solution Treating. For T61 condition: heat at 220°C (430 OF) for 24 h Before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as protective atmosphere above 400°C (750 OF)
AM100A: Typical mechanical properties of sand castings at room temperature
Temper F T4 T61 T5 T7
Tensile strength MPa ksi 150 275 275 150 260
22 40 40 22 38
Tensile or compressive yieldstrength(a) ksi MPa 83 90 150 110 125
12 13 22 16 18
Elongation in SO mm(2In.), %
HB
HRE
2 10 1 2 1
53 52 69 58 67
61 62 80 70 78
(a) Values are the same for tensile and compressive yield strengths
Hardness
Shearstrength MPa ksi 125 140 145
18 20 21
Cast Magnesium Alloys I 433 AM1OOA: Typical tensile properties of sand castings at elevated and subzero temperatures Testing temperature OF °C
Thnsile strength MPa ksi
Ftemper -78
-108
150
22
125
18.0
T4temper -78 -108 93 200 150 300 260 500 T6 temper(a)
260 235 160 83
38 34 23 12
125
18.0
270 165 115 83 59 38
39 24 17 12 8.5 5.5
180 62 45 28 17 10
26.0 9.0 6.5 4.0 2.5 1.5
-78 150 205 260 315 370
-108 300 400 500 600 700
'Iensileyieldstrength MPa ksi
Elongatlonin 50mm (2in.), %
7 1.5 9 22 2 4 25 45 60 100
(a) Elevated-temperature properties were determined after prolonged heating
AZ63A A magnesium-aluminum-zinc alloy Chemical Composition. Composition Limits. 5.3 to 6.7 AI, 2.5 to 3.5 Zn, 0.15 Mn min, 0.30 Si max, 0.25 Cu max, 0.01 Ni max, 0.30 other (total), bal Mg Consequence of Exceeding Impurity Limits. Excessive Si causes brittleness. Excessive Cu degrades mechanical properties and corrosion resistance. Excessive Ni degrades corrosion resistance Specifications (U.S. and/or Foreign). (AMS) Sand castings: F temper, 4420; T4 temper, 4422; T5 temper, 4424; (ASTM) Ingot: B 93. Sand castings: B 80; SAE J465. Former SAE alloy number: 50; UNS Ml1630; (Government) Sand castings: QQ-M-56. Permanent mold castings: QQ-M55; (Foreign) Elektron AZG
Characteristics Product Forms. Sand and permanent mold castings ApplicationslTypical Uses. Sand castings with good strength, ductility, and toughness
Mechanical Properties See Table for typicaltensilepropertiesof sand castings at elevatedtemperatures
Fabrication Properties Weldable casting alloys. Weldability rating is "Fair." Gas-shielded metal arc welding with AZ63A or AZ92A rod. Former is preferred
Recommended Heat Treating Practice Tempering Treatments. T4 (solution heat treated), T5 (artificially aged only), and T6 (solution treated and artificially aged) are the commonly used heat treatments for this alloy Solution Heat Treating. In solution treating, Mg-AI-Zn alloys are loaded into furnace at 260°C (500 OF) and brought to temperature over 2 h period at a uniform rate of temperature increase To obtain T4 condition, heat to 385°C (725 "F) for 10 to 14 h. Maximum temperature is 390°C (735 oF) To obtain T6 condition, heat to 385°C (725 "F) for 10 to 14 h. Maximum temperature is 390°C (735 OF)
Aging After Solution Treating. Note: Before aging in this instance, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as protective atmosphere above 400 °C (750 OF) T6 is heated to 218°C (425 OF) for 5 h in aging after solution heat treatment An alternative aging treatment: 5 h at 230 ± 6°C (450
± 10 OF)
Aging. AZ63A in the F condition is heated at 260°C (500 OF) for 4 h to obtain the T5 condition An alternative aging treatment: Heat 5 hat 230 ± 6 °C (450 ± 10 "F)
Note: See Table for postweld heat treatments of AZ63A
AZ63A: Microstructure. Alloy AZ63A-T6 sand casting. Lamellar M932(AI,Zn)49 discontinuous precipitate (dark) near some grain boundaries; some particles of Mg2Si and manganese-aluminum compounds. 250x
434/ Heat Treater's Guide: Nonferrous Alloys AZ63A: Postweld heat treatments for magnesium alloy castings
Alloy
Weldingrod
AZ63A
AZ63Aor AZ92A(a)
AZSIA AZ91C
AZ92Aor AZIOI AZ92Aor AZIOI
Temper Desired before temper after welding welding
Tested as soon as specimens reached testing temperature Postweldheat treatment
F
T4
12 h at 385 ± 6 °C (725 ± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12 h at 385 ± 6 °C (725 ± 10 0F)(b), plus 5 hat220°C(430°F) 30 min at 385 ± 6 °C (725 ± 10 oF) 30 min at 385 ± 6 °C (725 ± 10 "F), plus 5 h at 220 °C (430 oF) 30minat415±6°C(775± 1O°F)(c)
T4
T4
30minat415±6 °C(775± 1O°F)(c)
T4 or T6
T6
30minat415 ±6 °C(775± 1O°F)(c), plus4h at 215°C (420 "P) or 16h at 170°C (340 oF) 30 min at41O±6 °C (765 ± 1O°F)(c) 30minat41O±6 °C(765± 10 °F)(c),plus4h at 260 °C (500 "P) or 5 h at 220°C (430 oF) I h at 505 ± 6 °C (940 ± 10 oF),quench, 16 h at 205°C (400 oF) 2 h at 345°C (650 °F)(d), and/or 5 h at215 °C (420 oF),or 24 h at 220°C (430°F) 16hat 205 °C(4OO°F)(e) 16hat315 °C (600°F) I hat51O±6 °C(950± 10 °F),quench, 16h at 205°C (400 oF) I hat51O±6 °C(950± 10°F), quench, 16h at 205°C (400 oF) 1 hat51O±6°C(950± 1O°F),quench, 16h at 205°C (400 oF) I hat 51O±6 °C(950± 10 °F),quench, 16h at 205°C (400 oF) I hat425±6°C(795± 1O°F),quench, 16h at 205°C (400 oF) 2 h at 330°C (625 0F)(I) 12h at 250°C (480 0F)(I) 2 h at 330°C (625 oF),plus 16 h at 175°C (345 "P)
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HZ32A QE22A
HK3IA(g) HZ32A(g) QE22A
T40rT6 ForT5 T4 or T6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ZE4IA ZH62A ZKSIA
ZE4IA(g) ZH62A(g) ZKSIA(g)
ForT5 ForT5 ForT5
T5 T5 T5
AZ63A: Typical tensile properties of sand castings at elevated temperatures
(a) AZ63A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63Ain the T4 orT6 condition unless AZ63Arod is required by specifications. (b) Preheat to 260 °C (500 "F); heat to specified temperature at no more than 83 0C/h (150 °FIh). (c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 oF) results in slight loss of creep strength. (e) Alternative treatment: 1hat 315°C (600 oF), plus 16 h at 205°C (400 "F), (I) Alternative treatment: 2 h at 330°C (625 "F), plus 16 h at 175°C (345 OF). (g) Or EZ33A
Testingtemperature of
-c
Tensilestrength MPa ksi
YIeldstrength ksi MPa
Elongation in 50 mm (210.), %
Ftemper 24 65 93 120 150 205 260
75 150 200 250 300 400 500
197 210 208 191 166 105 71
28.6 30.5 30.1 27.7 24.1 15.3 10.3
94
13.7
4.5 3.0 4.5 7.5 20.5 50.5 38.0
75 150 200 250 300 400 500
254 253 236 207 154 101 75
36.8 36.7 34.3 30.0 22.4 14.6 10.9
94
13.6
10.0 9.0 7.0 9.0 33.2 38.0 26.0
95 200 250 300 400 500 600
232 248 223 169 121 83 57
33.7 36.0 32.4 24.5 17.5 12.0 8.2
122 119 114 103 83 61 39
17.7 17.3 16.5 15.0 12.0 8.8 5.6
5.5 11.0 11.0 15.0 17.0 15.0 20.0
T4temper 24 65 93 120 150 205 260 T6temper 35 93 120 150 205 260 315
AZ63A: Microstructure. Massive Mg32(AI,Zn)49 (white) in ascast specimen etched with 50% picral to protect M9 2Si (hexagonal particle) from HF, then with 5% HF to blacken Mg 17A112 and distinguish it from M9 32(AI,Zn)49' then with 10% picral to darken the matrix. 500x
Cast Magnesium Alloys I 435
AZ81A A magnesium-aluminum-zinc alloy Chemical Composition. Composition Limits. 7.0 to 8.1 AI, 0.4 to 1.0 Zn, 0.13 Mn min, 0.30 Si max, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. Excessive Si causes brittleness. Excessive Cu degrades mechanical properties and corrosion resistance. Excessive Ni degrades corrosion resistance Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80. Ingot: B 93. Permanent mold castings: B 199. Investment castings: B 403; SAE J465. Former SAE alloy number: 505; UNS M1181O;(Government) Sand castings: QQ-M-56. Permanent mold castings: QQ-M-55; (Foreign) Elektron A8. (British) BS 2970 MAGI. (German) DIN 1729 3.5812. (French) AIR 3380 G-A9
Characteristics Product Forms. Sand and permanent mold castings
ApplicationsITypical Uses. Sand and permanent mold casting, which have good strength combined with excellent ductility and toughness. are used in the solution treated condition (T4 temper)
Mechanical Properties See Tables for typical tensile properties of sand castings at elevated temperatures, and for typical creep properties of AZ81A-T6 sand castings
Fabrication Properties A castable, weldable alloy. Gas-shielded, metal arc welding with AZ92A rod has "very good" rating
Recommended Heat Treating Practice Solution treating to the T4 temper is the most commonly used heat treatment
Solution Heat Treating. A281Ais treatedat415 °C (775 F) for 16 to 24 h. Maximum treatment temperature is 420°C (785 OF) Alternative solution treatment: purpose is to prevent germination (excessive grain growth). Materialis treated 6 h at 415 ± 6 °C (775 ± 10 "F), 2 h at 352 ± 6°C (665 ± 10 OF), 10 h at 415 ± 6 °C (775 ± 10 "F)
AZ81A-T6: Postweld heat treatments for magnesium alloy castings Desired berm.. temperafter welding welding
'Iemper Alloy
Welding rod
AZ63A
AZ63Aor AZ92A(a)
AZSIA AZ91C
AZ92A
AZ92Aor AZ101 AZ92Aor AZI01
AZ92A
F
T4
12hat385±6 °C(725 ± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12ha1385±6 °C(725 ± 10 0F)(b), plus 5 hal220 °C (430 oF) 30 min al385 ± 6 °C (725 ± 10 oF) 30 min al385 ± 6°C (725 ± 10 oF), plus 5 h al220 °C (430 oF) 30 min al415 ± 6 °C (775 ± 10 °F)(c)
T4
T4
30 minal415 ±6 °C (775 ± 1O°F)(c)
T40rT6
T6
T4 T40rT6
T4 T6
30 min at415 ±6 °C (775 ± 1O°F)(c),plus4h al215 °C (420 oF) or 16hal170°C(34O°F) 30 min al410 ± 6°C (765 ± 10 °F)(c) 30 min al410 ± 6 °C (765 ± 10 °F)(c), plus 4 h al260 °C (500 oF) or 5 h al220 °C (430 oF) I h at 505 ± 6 °C (940 ± 10 "F), quench, 16 h al205 0C(4OOoF) 2h al345 °C (650°F)(d), and/or 5 hal215 °C (420 oF),or 24 h at 220 °C (430 oF) 16 h at 205°C (400 °F)(e) 16 hal315 °C(600°F) I hat51O±6 °C(950± 10 oF).quench, 16h al205 0C(4OOoF) I hat 510 ± 6 °C(950 ± 10 oF), quench, 16 h al205 -cr400 oF) I hat51O±6°C(950±1O°F),quench,16h at205°C(4OO°F) I ha151O±6 °C(950± 1O°F),quench, 16h at205°C(4OO°F) I h al425 ± 6°C (795 ± 10 oF), quench, 16 h al205 °C (400 oF) 2 h at 330°C (625 0F)(f) 12 hat250 °C(480 0F)(f) 2 hat330°C (625 oF), plus 16hal175 °C(345 oF)
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HIOIA HIO I A(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T4 or T6
T6 T5 T6
QH21A
T6
QH21A
Postweld heat treatment
T40rT6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T4orT6
T6
ZE4IA ZH62A ZK5IA
ZE4IA(g) ZH62A(g) ZK5IA(g)
ForT5 ForT5 ForT5
T5 T5 T5
(a) AZ63Arod must be used for welding AZ63Ain the Ptemper because 12h al385 °C (725 oF) causes germination in welds made wilh AZ92A rod: AZ92A rod normally is used for welding AZ63Ain the T4 orT6 condition unless AZ63Arod is required by specifications. (b) Preheat 10260 °C (500 "F); hearto specified rernperanireat no more than 83 0C/h(150 °FIh). (c) Use carbon dioxide or sulfur dioxide atmosphere, (d) Healing for 2 h al345 °C (650 oF) results in slight loss of creep strength. (e) Alternative treatment: 1hat315 °C(600°F), plus 16hal205 0C(4OO 0F). (f) Alternative treatment: 2 hat 330°C(625 oF), plus 16h al175 °C(345 oF). (g) OrEZ33A
See Table for postweld heat treatment of AZ81A In solution treating, Mg-AI-Zn alloys are loaded into furnace at 260°C (500 "F) and brought to temperature over 2 h period, at a uniform rate of temperature increase
AZ81A-T6: Typical tensile properties of sand castings at elevated temperatures Properties determined using separately cast test bars 'ThsIing temperature OF
21 93 150
205 260
YIeld strength MPa ksi
'Thnsile strength MPa ksi
0C
70 200 300 400 500
275 260
190 140 97
12.0 12.0 11.5 11.0 10.5
83 83 80 76
40.0 37.5 27.5 20.0 14.0
ElongationIn 50 mm (2 in), %
72
15.0 20.0 24.5 29.0 35.0
AZ81A-T6: Typical creep properties of sand castings Properties determined using separately cast test bars 'Thnsile stressresultingIn tola!extension(a) or TImeunder Ioad,h
0.5%
0.2%
0.1%
MPa
ksi
MPa
ksi
MPa
ksi
39 37 36
5.6 5.4 5.2
58 55 51
8.4 8.0 7.4
86 83 81
12.5 12.0 11.8
1 37 10 28 100 15 At 20S °C (400 oF)
5.4 4.0 2.2
53 45 24
7.7 6.5 3.5
62 46
9.0 6.6
1 10 100
3.4 1.7 1.0
41 21 12
6.0 3.1 1.7
21
3.0
At 93°C (200 oF) I 10 100 At lSOoC (300°F)
23 12 7
(a) Total extension equals initial extension plus creep extension
436/ Heat Treater's Guide: Nonferrous Alloys
AZ91A,AZ91B,AZ91C,AZ91D,AZ91E A magnesium-aluminum-zinc alloy Chemical Composition. Composition Limits of AZ91 A. 8.3 to 9.7 AI, 0.13 Mn min, 0.35 to 1.0 Zn, 0.50 Si max, 0.10 Cu max, 0.03 Ni max, 0.30 max other, bal Mg Composition Limits of AZ91B. 8.3 to 9.7 AI,O.13 Mnmin, 0.35 to 1.0 Zn, 0.50 Si max, 0.35 Cu max, 0.03 Ni max, 0.30 max other, bal Mg Composition Limits of AZ91 C. 8.1 to 9.3 AI, 0.13 Mn min, 0.40 to 1.0 Zn, 0.30 Si max, 0.10 Cu max, 0.01 Ni max, 0.3 max other (total), bal Mg Composition Limits of AZ91 D. 8.3 to 9.7 AI, 0.15 Mn min, 0.35 to 1.0 Zn, 0.10 Si max, 0.005 Fe max, 0.030 Cu max, 0.002 Ni max, 0.02 max other (each), bal Mg Composition Limits of AZ91 E. 8.1 to 9.3 AI, 0.17 to 0.35 Mn, 0.4 to 1.0 Zn, 0.20 Si max, 0.005 Fe max, 0.015 Cu max, 0.0010 Ni max, 0.01 max other (each), 0.30 max other (total) Consequence of Exceeding Impurity Limits. Corrosion resistance decreases with increasing Fe, Cu, or Ni content. More than 0.5% Si decreases elongation. If Fe content exceeds 0.005% in AZ9lD or AZ9lE, the permissible Fe-Mn ratio will not exceed 0.032, and corrosion resistance will rapidly decrease. Specifications (U.S. and/or Foreign). (AMS) Die castings: AZ9lA, 4490. Sand castings: AZ9lC, 4437; AZ9lE, 4446; (ASTM) Die Castings: AZ9lA, AZ9IB, and AZ9ID, B 94. Sand castings: AZ9lC and AZ9lE, B 80. Permanent mold castings: AZ9lC and AZ9lE, B 199. Investment castings: AZ9lC and AZ9lE, B 403. Ingot: B 93; SAE J465. Former SAE alloy numbers: AZ9lA, 501; AZ9IB, SOIA; AZ9lC, 504; UNS AZ9lA: M1191O. AZ9lB: M119l2. AZ9lC: M119l4. AZ9ID: M119l6. AZ9lE: M1192l; (Government) Die castings: AZ9lA, QQ-M-38. Permanent mold castings: AZ92C, QQ-M-55 and MIL-M-46062. Sand castings: AZ9lC, QQ-M-56, and MIL-M-46062; (Foreign) Elektron AZ91. (British) BS 2970 MAG3. (French) AIR 3380 G-AZ91. (German) DIN 17293.5912
Characteristics Product Forms. Products include die castings, sand castings, permanent mold castings, and investment castings ApplicationslTypical Uses. AZ9lA, AZ9IB, and AZ91D (which have the same nominal composition except for iron, copper, and nickel contents)
are die casting alloys used in the as-cast condition (F temper). AZ9lDis a high-purity alloy which has excellent corrosion resistance; it is the most commonly used magnesium die casting alloy. AZ9lA and AZ91B can be made from secondary metal, reducing the cost of the alloy; they must be used when maximum corrosion resistance is not required. AZ9lE is a high-purity alloy with excellent corrosion resistance used in pressure-tight sand and permanent mold castings with high tensile strength and moderate yield strength. AZ9lC is used in sand and permanent mold castings when maximum corrosion resistance is not required
Corrosion Properties For excellent corrosion resistance: AZ91D and AZ91E. For less than maximum corrosion resistance: AZ91A, AZ9IB, AZ9lC
Mechanical Properties See Table for typical room-temperature properties of AZ91A, AZ9IB, AZ91C, AZ91D, AZ9lE castings See Table for typical tensile properties of A29l sand castings at elevated temperatures
Fabrication Properties Weldability. AZ9lC and AZ9lE can be readily welded by the gasshielded arc process using AZ9lC or AZ91A rod; stress relief required. AZ9lA, AZ9IB, and AZ91D not weldable Hot-Shortness Temperature. 400°C (750 OF)
Recommended Heat Treating Practice A29lC is commonly solution treated to T4 temper or solution treated and artificially aged to T6 temper Solution Heat Treating. AZ9lC-FtoT4 temper: 415°C (775 OF) for 16 to 24 h. Maximum treating temperature is 418°C (785 "F) Alternative treatment for AZ9l-C-F to T4 temper: purpose is to prevent germination (excessive grain growth): 6 h at 415 ± 6°C (775 ± 10 OF), 2 h at 352 ± 6 °C (665 ± 10 OF), 10 h at 415 ± 6 °C (775 ± 10 "F) Note: In solution treating, Mg-Al-Zn alloys are loaded into furnace at 260 °C (500 "F) and brought to temperature over 2 h period at a uniform rate of temperature increase Aging. AZ9lC in F temper is aged toTS temper by heating to 168°C (335 OF) for 16 h Alternative treatment for AZ91C-F to T5 temper: 4 hat 215 ± 6°C (420 ± 10°F) Solution Treating AZ91-C-F to T6 Temper and Subsequent Aging:
AZ91: Typical room-temperature mechanical properties of AZ91A, AZ91 H,AZ91 C, AZ91 D, and AZ91 Ecastings AZ91A, AZ9IB. and AZ91D
AZ91Cand AZ91E
Property
Flemper
Flemper
T4lemper
T6lemper
Tensilestrength.MPa (ksi) Tensileyieldstrength.MPa (ksi) Elongation in 50 rom(2 in.), % Compressive yieldstrengthat 0.2%offset,MPa(ksi) Ultimatebearingstrength.MPa (ksi) Bearingyieldstrength.MPa (ksi) Hardness
230(33) 150(22) 3 165(24)
165(24) 97 (14) 2.5 97 (14)
275 (40) 90(13) 15 90(13)
275 (40) 145(21) 6 130(19)
415(60) 275(40)
415 (60) 305 (44)
515 (75) 360(52)
60 66 0.79 (0.58)
55 62 4.1 (3.0)
70 77 1.4 (1.0)
HB lIRE
OJarpyV-notch impact strength.J (ft . Ibf)
63 75 2.7(2.0)
• For solution treating: Treat at 415°C (775 OF) for 16 to 24 h. Maximum treatment temperature is 418°C (785 OF) • For aging: Treat at 168 °C (335 oF) for 16 h • Alternative solution treatment. Purpose is to avoid germination (excessive grain growth): 6 h at 415 ± 6 °C (775 ± 10 "F), 2 h at 352 ± 6 °C (665 ± 10 "F), 10 h at 415 ± 6°C (775 ± 10 "F) • Alternative aging treatment: 5 to 6 h at 215 ± 6 °C (420 ± 10 "F) Note: After solution treatment and before subsequent aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as protective atmosphere at temperature above 400 °C (750 OF) See Table for postweld heat treatment of AZ9lA-T4 and T6 castings
Cast Magnesium Alloys I 437
AZ91A·F: Microstructure. AZ91A-Fdie casting. Massive M917A112 compound at the boundaries of small, cored grains. Segregation (coring) in the grains and absence of precipitated discontinuous M9 17A112 are results of the rapid cooling rate of die castings. 500x
AZ91C-T6: Typical tensile properties of sand castings at elevated temperatures Thnsile strength
Thstingtempernture 0C OF
150 205
300 400
Thnsile yield strength
Elongation in
MPa
ksi
MPa
ksi
50 mm (2 in), %
185 115
27 17
97 83
14 12
40 40
AZ91: Postweld heat treatments for magnesium alloy castings Temper
Alloy
A263A AZ63Aor A292A(a)
AZ8IA
AZ91 A-F: Microstructure. Hot tear in an AZ91A-F die casting. Tear occurred in an area of compound segregation that was last to solidify and least resistant to stress caused by mold restriction during solidification shrinkage. 75x
AZ91A-F: Microstructure. Segregation of thin oxide skin in an AZ91 A-F die casting. This type of skin forms whenever molten metal surfaces are exposed to the atmosphere for a few seconds. 250x
A291C
Desired
hefore temperafter Welding rod welding welding
AZ92Aor A2101 A292Aor A2101
Postweld beattreatment
F
T4
12hat385±6 °C(725± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385±6 °C (725± 100F)(b), plus5h at 220 °C(430 oF) 30 min at 385± 6 °C (725± 10oF) 30 min at 385± 6 °C (725± 10oF). plus5 h at 220°C (430oF) 30 minat415 ±6 °C (775± 1O°F)(c)
T4
T4
30minat415±6°C (775± 1O°F)(c)
T40rT6
T6
30minat415 ±6 °C(775 ± 1O°F)(c), plus4h at215 °C (420OF) or 16hat 170°C (340oF) 30minat41O±6°C (765± 1O°F)(c) 30 min at41O± 6 °C (765±10 °F)(c),plus4h at 260°C (500oF)or5 h at 220°C (430oF) 1h at 505± 6 °C (940± 10"F), quench, 16h at 205°C (400oF) 2hat 345°C (650°F)(d),and/or5 hat215 °C(420 oF),or24h at220°C(430 oF) 16hat205 °C (4OO°F)(e) 16hat315 °C (600oF) 1hat51O±6°C(950± 10°F), quench,16h at 205°C (400oF) 1hat 510 ± 6 °C (950± 10"F), quench,16h at 205°C (400oF) 1hat51O±6°C(950± 1O°F),quench,16h at 205°C (400oF) I hat51O±6°C(950± 10°F),quench,16h at 205°C (400oF) 1hat 425 ± 6 °C (795± 10 "F), quench,16h at 205°C (400oF) 2 h at 330°C (6250F)(t) 12hat 250°C (4800F)(t) 2h at 330°C (625oF), plus 16hat 175°C(345 oF)
A292A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
QH21A
QH21A T40rT6
T6
WE43A WE43A T40rT6
T6
WE54A WE54A T4orT6
T6
ZC63A
ZC63A T40rT6
T6
ZE4IA ZE4IA(g) For T5 ZH62A ZH62A(g) ForT5 ZK51A ZK5IA(g) ForT5
T5 T5 T5
(a) AZ63Arod must be used for weldingAZ63A in the F temperbecause 12 h at 385°C (725 "F) causes germination in welds made with A292A rod: A292A rod normally is used for welding A263A in the T4 orT6 conditionunlessA263Arod is requiredby specifications. (b)Preheatto 260 °C (500"F); heatto specifiedtemperatureatno morethan830C/h(150°FIh).(c)Usecarbondioxide or sulfur dioxideatmosphere. (d) Heatingfor 2 h at 345°C (650 oF)results in slight loss of creep strength.(e)Alternativetreatment: I hat 315°C (600"F), plus 16h at205°C (400"F). (t)Alternative treatment: 2 h at 330 °C (625oF),plus 16h at 175°C (345 "P), (g) Or EZ33A
438/ Heat Treater's Guide: Nonferrous Alloys
AZ92A A magnesium-aluminum-zinc alloy Chemical Composition. Composition Limits. 8.3 to 9.7 AI, 0.10 Mn min, 1.6 to 2.4 Zn, 0.30 Si max, 0.25 Cu max, other (total), bal Mg
om Ni max, 0.30 max
Consequence of Exceeding Impurity Limits. Excessive Cu or Ni degrades corrosion resistance. More than 0.5% Si decreases elongation
Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4434. Investment castings: 4453. Permanent mold castings: 4484; (ASTM) Ingot: B 93. Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; SAE J465. Former SAE alloy number: 500; UNS M11920; (Government) Sand castings: QQ-M-56 and MIL-M-46062. Permanent mold castings: QQ-M-55 and MIL-M-46062
Characteristics Product Forms. Sand Castings, permanent mold castings, investment castings
ApplicationsfTypical Uses. Pressure-tight sand and permanent mold
Solution Treating to T6 Temper Followed by Aging: • Solution treating is at 410 °C (765 OF) for 16 to 24 h. Maximum treatment temperature is 415°C (775 OF) • Aging is at 218 °C (425 OF) for 5 h • An alternative solution treating procedure is designed to prevent germination (excessive grain growth). It consists of treating 6 h at 410 ± 6°C (765 ± 10 "F), 2 h at 352 ± 6 °C (665 ± 10 "F), 10 h at 410 ± 6°C (765 ± 10 oF)
Note: After solution treating and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide at temperatures above 400°C (750 "F) See Table for postweld heat treatments for AZ92A castings in T4 and T6 tempers
castings with high tensile strength and good yield strength
AZ92A: Typical tensile properties of sand castings at elevated temperatures Typical tensile properties of AZ92A sand castings
TIme at 'Iestlna °C
Properties determined using separately cast test bars. ThnsUe strength Temper
F
T4 T5 1'6 T7
MPa 170 275 170 275 275
ksi 25 40 25 40 40
Yield strength MPa ksi 97 97 115
150 145
14 14 17 22 21
Elongation, %(a) 2 10 1 3 3
(a) In 50 mm (2 in.)
Mechanical Properties See Table for typical tensile properties of AZ92A sand castings at elevated temperatures
Hardness. F temper: 65 HB or 76 HRE. T4 temper: 63 HB or 75 HRE. T5 temper: 69 HB or 80 HRE. T6 temper: 81 HB or 88 HRE. T7 temper: 78 HB or 86 HRE
tempemture(a)
F'temper 93 150 205 260 T41emper 93 150 205 260 T61emper 93 150 205 260
OF
Elongation in
temperature,
50 rom (2 Ia) %
days(b)
16 12
2 3 36 34
80 160 160 40
'Ienslle strength MPa ksI
25
200 300 400 500
170 150 110 83
200 300 400 500
275 180 115 76
40 26 17 11
8 40 41 52
160 160 160 40
200 300 400 500
260 170 115 76
38 25 17 12
7 40 43 47
160 160 160 40
22
(a)Testedafterprolongedheatingat testingtemperature. (b) Prior to testing
Fabrication Properties A weldable casting alloy. Gas-shielded, arc welding with AZ92A rod is rated "Good." Stress relief after welding is required
Recommended Heat Treating Practice Common heat treatments are for solution treated T4 temper and for solution treated and artificially aged T6 temper
Solution Heat Treating. To obtain T4 temper, material is treated at 410 °C (765 OF) for 16 to 24 h. Maximum treatment temperature is 415°C (775 OF) Alternative treatment for T4 temper. Purpose is to prevent germination (excessive grain growth): Treat 6 h at 410 ± 6 °C (765 ± 10 "F), 2 h at 352 ± 6°C (665 ± 10 "F), 10 h at 410 ± 6°C (765 ± 10 OF)
Note: In solution treating, Mg-AI-Zn alloys are loaded into furnace at 260 °C (500 OF) and brought to temperature over 2 h period, at uniform rate of temperature increase.
Aging. Aging to T5 temper is done in the as-fabricated F condition. Material is aged at 260°C (500 "F) for 4 h
AZ92A: Microstructure. Permanent mold casting. M917A1 12 compound: Massive (outlined) at grain boundaries; precipitated (dark) near grain boundaries. Slower cooling rate than that of die castings has resulted in larger grains. 250x
Cast Magnesium Alloys I 439
AZ92A: Postweld heat treatments for magnesium alloy castings
Alloy
Welding rod
NZ63A
NZ63Aor AZ92A(a)
AZ8IA AZ91C
AZ92Aor AZIOI AZ92Aor AZIOI
Desired
Temper before welding
temper after welding
F
T4
12hat385 ±6 °C (725 ± 100F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385±6 °C(725 ± 100F)(b), plus 5 h at 220°C (430 oF) 30 min at 385 ± 6 °C (725 ± 10 "F) 30 min at 385 ± 6°C (725 ± 10 oF),plus 5 h at 220 °C (430 oF) 30minat415±6 °C (775 ± 1O°F)(c)
T4
T4
30minat415±6°C(775± 1O°F)(c)
T40rT6
T6
30minat415±6 °C (775 ± 10 °F)(c),plus4h at 215°C (420°F) or 16h at 170°C (340 oF) 30minat41O±6 °C (765 ± 1O°F)(c) 30minat41O±6°C(765± 1O°F)(c),plus4h at 260 °C (500 oF)or 5 h at 220°C (430 oF) I hat505±6 °C (940 ± 10°F), quench, 16h at 205°C (400 OF) 2h at 345 °C (650 °F)(d), and/or 5 hat215 °C (420°F), or24h at220°C (430°F) 16hat205°C(4OO°F)(e) 16h at315 °C(600°F) I h at51O±6 °C(950± 10°F), quench, 16h at 205°C (400 oF) I hat51O±6°C(950± 1O°F),quench,16h at 205°C (400 oF) I hat51O±6 °C (950 ± 1O°F),quench, 16h at 205°C (400 oF) I hat 510±6 °C (950± 1O°F),quench, 16h at205°C(4OO°F) I hat425±6 °C(795 ± 10°F), quench, 16h at 205°C (400 oF) 2 h at 330°C (625 0F)(I) 12h at 250°C (480 °F)(I) 2h at 330°C (625 °F),plus 16hat 175 °C(345 oF)
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HZ32A QE22A
HK31A(g) HZ32A(g) QE22A
T40rT6 ForT5 T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ZE41A ZH62A ZKSIA
ZE4 IA(g) ZH62A(g) ZKSIA(g)
ForT5 ForT5 ForT5
T5 T5 T5
Postweld heat treatment
AZ92A-F: Microstructure. AZ92A-F sand casting. The appearance of the interdendritic eutectic, a mixture of magnesium solid solution and M9 17AI 12 , was retained in this form by a rapid quench from above the eutectic temperature. 1500x
AZ92A-F: Microstructure. AZ92A-F, as-cast. Massive M917AI 12 compound surrounded by lamellar M9 17AI 12 precipitate. Normal air cooling of zinc-containing magnesium-aluminum alloys produces this type of completely divorced eutectic. 500x
(a) AZ63A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 OF) causes germination in welds made with AZ92A rod: AZ92A rod nonna11y is used for welding AZ63A in the T4 or T6 condition unless AZ63A rod is required by specifications. (b) Preheat to 260°C (500 OF);heat to specified temperature at no more than 83 °C/h (150 °F/h). (c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 OF) results in slight loss ofcreep strength. (e) Alternative treatment: I hat315 °C(600 "F), plus l6h at 205 °C (400°F). (I) Alternative treatment: 2 hat330°C(625 oF), plus l6h at 175°C (345 oF). (g) Or EZ33A
EQ21 A magnesium-zirconium-alloy Chemical Composition. Composition Limits. 1.3 to 1.7 Ag, 1.75 to 2.5 Nd-rich rare earths, 0.4 to 1.0 Zr, 0.05 to 0.10 Cu, 0.01 Ni max, 0.3 max other (total), bal Mg Consequence of Exceeding Impurity Limits. Zr content below 0.5% may result in somewhat coarser as-cast grains and lower mechanical properties
Specifications (U.S. and/or Foreign). AMS 4417; (ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; UNS M16330; (Government) Sand and permanent mold castings: MIL-M46062; (Foreign) (British) BS 2970 MAGl3
Next Page 440 I Heat Treater's Guide: Nonferrous Alloys
Characteristics Product Forms. Sand castings, permanent mod castings, and investment castings ApplicationslTypical Uses. Sand and permanent mold castings used in the solution-treated and artificially aged condition (1'6 temper), with high yield strengths at service temperatures up to 200°C (390 OF). Castings have excellent short-time elevated-temperature mechanical properties and are pressure tight and weldable. Mechanical Properties Tensile Properties. In T6 temper, tensile strength is 235 MPa (34 ksi); yield strength is 170 MPa (25 ksi); elongation is 2% in 50 mm (2 in.)
EQ21A: Postweld heat treatments for magnesium alloy castings
Alloy
Weldingrod
A'ZfJ3A
A'ZfJ3Aor AZ92A(a)
AZS1A AZ92Aor AZl0l AZ91C AZ92Aor AZ101
Hardness. 65 to 85 lIB
'Thmper before welding
Desired temper after welding
F
T4
12hat385±6°C(725± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12 hat 385 ±6°C(725 ± 10°F)(b),plus5 h at 220°C (430oF) 30 minat385± 6 °C (725± 10oF) 30 minat 385± 6 °C (725± 10oF),plus5 h at 220°C (430oF) 30minat415±6 °C (775± lO°F)(e)
T4
T4
30 minat415 ± 6 °C (775± 10°F)(e)
T40rT6
T6
30minat415 ±6 °C(775 ± lO°F)(e),plus4h at215 °C (420oF)or 16hat170°C(335 OF) 30minat41O±6 °C(765± lO°F)(e) 30minat410±6 °C(765± 10°F)(e),plus4h at 260°C (500oF)or 5 h at 220°C (430°F) 1 hat505±6°C(940± 10°F),queneh,16h at 205°C (400oF) 2 h at 345°C (650°F)(d),and/or5 hat215 °C (420oF),or 24 h at220°C (430oF) 16hat205 °C (400°F)(e) 16hat315 °C (600oF) 1hat51O±6°C (950± 10°F),quench,16h at 205°C (400oF) 1 hat510±6°C(950±10°F),quench,16h at 205°C (400oF) 1hat510±6°C(950± 10°F),quench,16h at 205°C (400oF) 1 hat51O±6°C (950± 10°F),quench,16h at 205°C (400oF) 1 hat 425 ± 6 °C (795± 10oF),quench,16h at 205°C (400oF) 2 h at 330°C (6250F)(t) 12h at 250°C (4800F)(t) 2 h at 330°C (625oF),plus16h at 175°C(345oF)
Fabrication Properties
AZ92A
AZ92A
T4 T40rT6
T4 T6
A castable, weldable alloy. Welding is with gas-shielded arc process, using A292A rod. Stress relief is required after welding
EQ21A
EQ21A
T40rT6
T6
Recommended Heat Treating Practice
EZ33A
EZ33A
ForT5
T5
EQ2lA is commonly solution treated and artificially aged to T6 condition
HK31A HK31A(g) HZ32A HZ32A(g) QE22A QE22A
T4orT6 ForT5 T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
Solution Heat Treating. EQ21A is solution treated at 525°C (970 "P) for 4 to 8 h. Maximum treatment temperature is 530°C (985 OF). Quenching from solution treating temperature is either in water at 65°C (150 "F) or in some other suitable medium Aging After Solution Treating. The alloy is artificially aged at 200°C (390 OF) for 16 h
ZE41A ZE41A(g) ZH62A ZH62A(g) ZKSIA ZKSIA(g)
PostweldbeatImltmeot
(a) AZ63Arod must be usedfor weldingAZ63A in the F temperbecause 12h at 385°C (725 oF) causes germination in welds made with AZ92A rod: AZ92A rod nonnaUy is used for welding AZ63Ain theT4 or T6 conditionunless A'ZfJ3A rod is requiredby specifications. (b)Preheatto 260 °C (500°F);heattospecifiedtemperature at nomorethan83 0C/h(l50°FIb). (c)Usecarbondioxide or sulfur dioxideatmosphere. (d) Heating for 2 hat 345°C (650 "F) results in slight loss of creep strength.(e) Alternative treatment: 1 h at315 °C (600 "P), plus 16 h at 205°C (400 "P), (t) Alternative treatment: 2 h at 330°C (625oF),plus 16 h at 175°C (345 oF).(g)Or EZ33A
EZ33A A magnesium-chromium alloy Chemical Composition. Composition Limits. 2.5 to 4.0 rare earths, 2.0 to 3.1 Zn, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4442; (ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; SAE J465. Former SAE alloy number: 506; UNS M12330; (Government) Sand castings: QQ-M-56. Permanent mold castings: QQ-M-55. Welding rod: MIL-R-6944; (Foreign) Elektron ZRE1. (British) BS 2970 MAG6. (German) DIN 1729 3.5103. (French) AIR 3380 ZREI
ApplicationslTypical Uses. Pressure-tight sand and permanent mold castings relatively free from microporosity, used in T5 condition for applications requiring good strength properties up to 260°C (500 "F) Mechanical Properties Tensile Properties. T5 temper, tensile strength is 160 MPa (23 ksi); yield strength is 110 MPa (16 ksi); elongation is 3% in 50 mm (2 in.) Hardness. 50 HB or 59 HRE Fabrication Properties
Characteristics Product Forms. Sand castings, permanent mold castings, investment casting
A castable, weldable alloy. Welding properties (gas-shielded metal arc process, using EZ33A rod) are excellent. Preheating may be used, but it isn't necessary. Postweld heat treatment is required
Wrought Magnesium Alloys AZ31B,AZ31C Chemical Composition. Composition limits of AZ31B. 2.5 to 3.5 AI, 0.20 Mn min, 0.60 to 1.4 Zn, 0.04 Ca max, 0.10 Si max, 0.05 Cu max, 0.005 Ni max, 0.005 Fe max, 0.30 max other (total); bal Mg
Mechanical Properties See Tables for room temperature mechanical properties, and for typical tensile properties at various temperatures
Composition limits of AZ31C. 2.4 to 3.6 AI, 0.15 Mn min, 0.50 to 1.5 Zn, 0.10 Cu max, 0.03 Ni max, 0.10 Si max, bal Mg
fabrication Properties
Consequence of Exceeding Impurity limits. Excessive Cu, Ni, or Fe degrades corrosion resistance
AZ31B only: Sheet and plate with good formability and strength, high resistance to corrosion, and good weldability. AZ31Band AZ31C are used in the as-fabricated (F), annealed (0), and hard-rolled (H24) tempers
Specifications (U.S. and/or Foreign). (AMS) AZ31B sheet: 0 temper, 4357; H24 temper, 4376; (ASTM) Sheet: B 90. Extruded rod, bar, shapes, tubing, and wire: B 107. AZ31B forgings: B 91; (SAE) AZ31B: J 466. Former SAE alloy number: 510; UNS AZ3IB: MI13ll. AZ31C: M1l312; (Government) AZ3IB: Forgings, sheet, and plate, QQ-M-40; extruded bar, rod, and shapes, QQ-M-31B; extruded tubing, WW-T-825B; (Foreign) Elektron AZ31 (extruded bar and tubing). (British) Sheet, BS 3370 MAG1l1; extruded bar and tubing, BS 3373 MAGIll. (German) DIN 97153.5312. (French) AFNOR G-A37 1
Weldability. Gas-shielded arc welding with AZ61A or AZ92A rod (AZ61A preferred), excellent; stress relief required. Resistance welding, excellent
Characteristics
Hard rolled, AZ31B sheet is treated at 150°C (300 OF) for 1 hr
ApplicationslTypical Uses. AZ31B and AZ31C: Forgings and extruded bar, rod, shapes, structural sections, and tubing with moderate mechanical properties and high elongation; AZ31C is the commercial grade, with the same properties as AZ31B but higher impurity limits
AZ31B-H24: Microstructure. Alloy AZ31 B-H24 sheet. Longitudinal edge view of worked structure, showing elongated grains, and mechanical twins, which resulted from warm rolling of the sheet. 250x
Recommended Heat Treating Practice Annealing. AZ31B in the F, HIO, HIl, H23, H24, and H26 conditions and AZ31C in F condition are annealed at 345°C (650 OF) for 1 h or more Stress Relieving Treatments. AZ31B sheet in annealed condition is treated at 345°C (650 OF) for 2 h AZ31B-F extrusions and forgings are treated at 260°C (500 OF) for 0.25 h
Recrystallization. Takes place after 1 hat 205°C (400 OF), following 15% cold work Hot Working Temperature. 230 to 430°C (450 to 800 OF)
AZ31B: Typicaltensile properties at various temperatures Testingtemperature OF ·C
Sheet, hard rolled ,<;0 -112 -27 -18 21 70 100 212 150 300 205 400 260 500 315 600 370 700 Extrusions, as fabricated -185 -300 -130 -200 -73 -100 -18 0 21 70 93 200 120 250 150 300
Tensile strength ksi
MPa
331 310 290 207 152 103 76 41 28
48.0 45.0 42.0 30.0 22.0 15.0 11.0 6.0 4.0
234 234 221 145 90 59 31 21 14
34.0 34.0 32.0 21.0 13.0 8.5 4.5 3.0 2.0
15 30 45 55 75 125 140
434 359 314 283 262 238 217 179
63.0 52.0 45.5 41.0 38.0 34.5 31.5 26.0
338 303 262 228 200 148 117 100
49.0 44.0 38.0 33.0 29.0 21.5 17.0 14.5
6.0 7.5 9.5 12.5 15.0 23.5 29.5 37.5
MPa
Yieldstrength ksi
Elongationin 50 mm(2 in.), %
424/ Heat Treater's Guide: Nonferrous Alloys AZ31B: Typical room-temperature mechanical properties
Produet form
'Ienslle strength MFa ksi
Thnsile yield strength(a) MFa ksl
Sheet,annealed Sheet,hardrolled Extrudedbar,rod,andsolidshapes Extrudedhollowshapesandtubing Forgings
255 290 255 241 260
150 220 200 165 170
37 42 37 35 38
22 32 29 24 25
Elongation, %(h)
21 15 12 16 15
Hardness RD(e) lIRE
56 73 49 46 50
67 83 57 51 59
Shear strength MFa ksi
145 160 130
21 23 19
130
19
Compressive yield strength(a) MFa ksl
Ultimate bearing strength(d) MFa ksi
Bearingyield strength(d) ksi MFa
110 180 97 83
485 495 385
290 325 230
16 26 14 12
70 72 56
42 47 33
(a) At0.2% offset. (b) In 50 rom(2 in.).(e)500 kg load, 10romball.(d) 4.75 rom(0.19in.)pin diameter
AZ31B-O: Microstructure. Alloy AZ318-0 sheet. Longitudinal edge view of structure recrystallized by annealing. Particles of manganese-aluminum compound (dark gray) and fragmented Mg17A1 12 (outlined). 200x
AZ31 B: Microstructure. Alloy AZ318 tooling plate. Longitudinal edge view. Essentially recrystallized structure resulting from anneal flattening; outlined particles of fragmented M917AI12 • 200x
AZ61A Chemical Composition. Composition Limits. 5.8 to 7.2 AI, 0.15 Mn min, 0.40 to 1.5 Zn, 0.10 Si max, 0.05 Cu max, 0.005 Ni max, 0.005 Fe max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. Excessive Cu, Ni, or Fe degrades corrosion resistance Specifications (U.S. and/or Foreign). (AMS) Extrusions: 4350. Forgings: 4358; (ASTM) Extrusions: B 107. Forgings: B 91; SAE J466. Former SAE alloy numbers: 520 (extrusions) and 531 (forgings); UNS M1l61O; (Government) Extruded bar, rod, and shapes: QQ-M-3IB. Extruded tubing: WW-T-825A. Forgings: QQ-M-40B; (Foreign) Elektron AZ61 (extruded bar, sections, and tubing). (British) Extruded bar, sections, and tubing, BS 3373 MAGl21; forgings, BS 3372 MAGl21. (German) DIN 97153.5612; castings, DIN 17293.5612. (French) AFNOR G-A6Z1
Characteristics Applicationsrrypical Uses. Used in sheet form for battery applications F temper (as-fabricated)
Mechanical Properties See Tables for typical room temperature mechanical properties, and for typical tensile properties of extrusions at various elevated temperatures
Fabrication Properties General-purpose extrusions have good properties Forgings have good mechanical properties In gas-shielded arc welding, AZ61A or AZ92A rod is used (the former is preferred). Stress relief is required after welding. Resistance welding properties are excellent
Wrought Magnesium Alloys /425
Recommended Heat Treating Practice
AZ61A-F: Typicalproperties of extrusionsat various temperatures
Annealing. Material in F condition is treated at 345°C (650 OF) for 1 h or more
-c
Thstlng temperature
Stress Relieving Treatments. Annealed sheet is treated at 345°C (650 OF) for 2 h. Hard rolled sheet is treated at 205°C (400 OF) for 1 h
-185 -130 -73 -18 21 93 150 200 315
Recrystallization Temperature. 1 h at 285°C (550 oF), following 20% cold work Hot Working Temperature. 230 to 400°C (450 to 750 "F) Hot Shortness Temperature. 415°C (775 OF)
OF
-300 -200 -100 0 70 200 300 400 600
'Ienslle strength MPa ksi
YIeld strength MPa ksi
379 355 331 317 310 286 217 145 52
317 296 265 238 228 179 134 97 34
55.0 51.5 48.0 46.0 45.0 41.5 31.5 21.0 7.5
46.0 43.0 38.5 34.5 33.0 26.0 19.5 14.0 5.0
Elongation in 50 nun (2 in.), %
4 6.5 9.5 13 16 23 32 48.5 70
AZ61A-F: Typical room-temperature mechanical properties
Fonn andcondition
Thnsile strength MPa ksi
Thnslle yield strength(a) MPa ksi
Forgings Extrudedbar,rod,andshapes Extrudedtubingandhollowshapes Sheet
295 305 285 305
180 205 165 220
43 44 41 44
26 30 24 32
Elongation, %(b)
12 16 14 8
Hardness IID(c) HRE 55 60 50
66
72 60
Shearstrength MPa ksl 145 140
21 20
Compressive yield strength(a) ksi MPa 125 130 110 150
18 19 16 22
UltJmate hearing
Bearingyield
strength(d) MPa ksi
MPa
ksi
470
285
41
68
strength(d)
(a) At 0.2%offset. (b) In 50 mm(2 in.).(c)500 kg load, IOmmball. (d) 4.75 mm(0.19 in.) pin diameter
AZ61A-F: Microstructure. AZ61A-F extrusion. Longitudinal View of hot-worked structure. Small, equiaxed recrystallized grains; stringers of fragmented Mg17AI 12 • 250x
AZ61A-F: Microstructure. AZ61A-F extrusion. Longitudinal view of hot-worked structure. Small, equiaxed recrystallized grains. Specimen is not etched, making stringers of fragmented Mg17A112 more visible. 250x
AZ80A Chemical Composition. Composition limits. 7.8 to 9.2 AI, 0.20 to 0.80 Zn, 0.12 Mn min, 0.10 Si max, 0.05 Cu max, 0.005 Ni max, 0.005 Fe max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. Excessive Si, Cu, Ni, or Fe degrades corrosion resistance
Specifications (U.S.and/or Foreign). (AMS) Forgings: 4360; (ASTM) Extruded rod, bar, and shapes: B 107. Forgings: B 91; SAE J466. Fonner SAE alloy numbers: 523; UNS MII800; (Government) Extruded bar, rod, and shapes: QQ-M-3IB. Extruded tubing: WW-T-825. Forgings: QQ-M40B
Next Page
426/ Heat Treater's Guide: Nonferrous Alloys
Characteristics
Recommended Heat Treating Practice
ApplicationsITypical Uses. Extruded products and press forgings. This alloy can be heat treated
T5 temper (artificially aged only) is commonly applied
Mechanical Properties See Tables for typical room temperature mechanical properties, and for typical mechanical properties at various temperatures
Fabrication Properties Fabrication processes include extrusion, forging, and welding. ill gasshielded arc welding, AZ6lA or AZ92A rod is used (the former is preferred). After welding with this process, stress relief is required. Resistance welding properties are rated excellent
AZ80A-F: Microstructure. AZ80A-F extrusion. Longitudinal view of hot-worked structure. Small, equiaxed recrystallized grains; small amount of M917A112 discontinuous precipitate at the grain boundaries. 250x
AZ80A-T5: Microstructure. AZ80A-T5 forging. Longitudinal view of hot-worked structure, showing large, recrystallized grains and spheroidized M917A1 12 discontinuous precipitate mainly in the grains near the boundaries. 200x
Annealing. Material in the F, T5, and T6 conditions is annealed at 385°C (725 OF) for I h or more Stress Relieving Treatment. For extrusions and forgings, 260°C (500 OF) for 0.25 h Recrystallization Temperature. I h at 345°C (650 "F), following 10% cold work Hot Shortness Temperature. 415°C (775 oF)
AZ80A-T5: Microstructure. AZ80A-T5 extrusion. Longitudinal view showing much mottled M917A1 12 discontinuous precipitate near the grain boundaries, resulting from the artificial aging treatment. 250x
AZ80A·F: Typical mechanical properties at various temperatures Testingtemperature OF °C
Tensilestrength ksi MPa
Yieldstrength ksi MPa
-73 -18 21 93 150 205 260
386 355 338 307 241 197 110
269 252 248 221 176 121 76
-100 0 70 200 300 400 500
56.0 51.5 49.0 44.5 35.0 28.5 16.0
39.0 36.5 36.0 32.0 25.5 17.5 11.0
Elongation in 50 rom (2 in.), %
8.5 10.5 11.0 18.0 25.5 35.0 57.0
Previous Page Wrought Magnesium Alloys I 427
AZ80A: Typical room-temperature mechanical properties Teusile Form and condition
Forgings As-forged Aged (f5 temper) Bar, rod, and shapes As-extruded Aged (f5 temper)
Compressive yield strength MPa ksl
strength MPa ksl
Thusileyield strength(a) MPa ksi
330 345
48 50
230 250
33 36
11 6
69 72
80 82
150 160
22 23
170 195
25 28
340 380
49 55
250 275
36 40
11 7
67 80
77 88
150 165
22 24
240
35
Elongation, %(h)
Hardness BB(c) lIRE
Shear strength MPa ksi
Ultimate hearing strength MPa ksi
Bearing yield strength MPa ksi
550
350
80
51
(a) AtO.2% offset. (b) In 50 mm (2 in.). (c) 500 kg load, 10 mm ball
HK31A Chemical Composition. Composition Limits. 2.5 to 4.0 Th, 0.4 to 1.0 Zr, 0.3 Zn max, 0.1 Cu max, om Ni max, 0.3 max other (total), bal Mg Specifications (U.S. and/or Foreign). (AMS) Annealed sheet and plate: 4384E; (ASTM) Sheet and plate: B 90; SAE J465. Former SAE alloy number: 507; UNS M1331O; (Government) Sheet and plate: MIL-M26075
Recommended Heat Treating Practice Basic temper designation T6 (solution treated and artificially aged is the common heat treatment for this alloy) Annealing. Material in strain hardened condition (H24) is treated at 400 °C (750 OF) for 1 h or more Stress Relieving Treatments. For annealed sheet, 345°C (650 "F) for
Characteristics
1h
Product Forms. Sheet and plate. Also, a casting alloy is available
For hard rolled sheet, 290°C (555 OF) for 0.5 h
Mechanical Properties See Table for typical tensile properties at elevated temperatures See Figure for typical stress-strain curves for sheet
Fabrication Properties Sheet and plate have excellent formability and weldability. High strength is maintained up to 315°C (600 OF). In gas-shielded metal arc welding, HK31A or EZ3A rod is used (latter is preferred). Resistance welding properties are also excellent. Sheet and plate can be stress relieved, but it is not required
HK31A-H24: Typical tensile properties of sheet at elevated
temperatures Testing temperature
-c
21 150 205 260 315 345
OF
70 300 400 500 600 650
Thusilestrength MPa ksl
MPa
ksi
Elongation in SOmm(21n.), %
260 180 165 140 89 55
205 165 145 115 48 28
30 24 21 17 7 4
8 20 21 19 70 >100
38 26 24 20 13 8
Yieldstrength
HK31A: Microstructure. HK31A-H24 sheet. Longitudinal edge view, showing structure with less Mg4Th precipitated in grains and more at the elongated grain boundaries. 500x
428/ Heat Treater's Guide: Nonferrous Alloys
HK31A: Typical stress-strain curves for 1.63 mm (0.064 in.) thick HK31A-H24 sheet
LIVE GRAPH
300 ,-----,r----,---,----,
Click here to view
300
Longitudinal tension
LIVE GRAPH Transverse tension
40
250 t---II---I---t---::-:-:::-i
24 ·C
Click here to view
40
250
30
200 I----+--§--l---_l_
30
200 'iii
""
'"
20 ~
en
io a.
149 ·C 204 ·C
'"
260·C
~
e
] 20
en
100 t--j'4-jf---t-----t----j
~ en
100 316·C
10
10 50 H.L---::Jl_=--I---t---j
50 371 ·C
0 0.4
0.8
1.2
0
0
1.6
0
0.4
Strain, %
LIVE GRAPH
1.2
1.6
Strain, %
300 ,-------r---,-----.-----,
Click here to view
0.8
40
Longitudinal compression
Click here to view
40
Transverse compression
250 I - - - - - - j - - - - + - - - + - - - ;
200 t - - - I - - - t - - - + - - - I
LIVE GRAPH
300
250
30
200 f - - - + - - - f - - - f - - - j
]
'"
20 l!?
en
100 t----1I1-1I-----t---t---I
30
]
a.
~
Ii 150 I-----A'-n.-F----t---+---I
20
l!?
~
en
en 100 10
10 50 f-Ic.:.......,~I---+----+--.-;
50 371 ·C
-L-Il---+---r-OL-_---J'--_----'_ _- - L_ _- ' 0
o
0.4
0.8 Strain, %
1.2
lB
~_--l
_ _--J._ _--l._ _- '
0.4
0.8
1.2
0
1.6
Strain, %
HK31A: Microstructure. HK31A-O sheet. Longitudinal edge view of structure recrystallized by annealing. Most of the M94Th precipitate shown in microstructure for HK31A-H24 sheet has redissolved. See also microstructure for unetched HK31A-O sheet. 250x
Wrought Magnesium Alloys I 429 .
HK31A: Microstructure. HK31A-O sheet. Longitudinal edge view of structure recrystallized by annealing, but not etched, which has added to the visibility of fragmented massive M94Th compound. 500x
HM21A Chemical Composition. Composition Limits. 1.5 to 2.5 Th, 0.45 to 1.1 Mn, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (AMS) Sheet and plate: 4390. Forgings: 4363; (ASTM) Sheet and plate: B 90. Forgings: B 91; UNS M1321O; (Government) Sheet and plate: MIL-M-8917; Forgings QQ-M40
Characteristics Product Forms. Sheet, plate, and forgings are available. Alloy is usable for service at 345°C (650 OF) and above
Mechanical Properties See Tables for typical tensile and compressive properties at elevated temperatures, and for typical creep properties of sheet
The alloy is forged, cold worked, and welded. Gas-shielded metal arc welding with EZ33A rod is rated excellent. Resistance welding has "very
HM21A: Typical tensile and compressive properties at elevated temperatures
-c
'F
Tensilestrength MPa ksi
Tensile yleldstrength MPa ksi
Compressive yieldstrength MPa ksi
Elongation, %(a)
HM21A-T8 sheet(b) 21 205 260 315 370
70 400 500 600 700
235 125 110 97 76
34 18 16 14 11
170 115 105 83 55
25 17 IS 12 8
130 105 105 83 55
19 15 15 12 8
8 30 25 IS 50
230 110 90 76
33 16 13
140 90 76 55
20 13 11 8
115
17
15 49(d) 37(d) 43(d)
HM21A-T5 forgings(c) 21 205 315 370
70 400 600 700
11
Recommended Heat Treating Practice Commonly applied heat treatments are for T5 (artificially aged only), for T6 (solution treated and artificially aged), and for T81 tempers. T81 is a mill modification of T8 to improve mechanical properties
Annealing. Material in T5, T8, and T81 conditions is treated at 455°C (850 OF) for 1 h or more Stress Relieving Treatment. Extrusions and forgings are treated at 370°C (700 OF) for 0.5 h Hot Working Temperature is in range of 455 to 595°C (850 to 1100 "F)
Fabrication Properties
Testingtemperature
good" rating. Stress relieving after welding, to prevent stress corrosion cracking is necessary only for alloys containing over 1.5% Al
(a) In 50 mm (2 in.). (b) Under 100-hexposure. (e) Rapid heating, except for forging tested at 21 'C (70 'F). (d) In 25 mm (I in.)
HM21A: Microstructure. HM21A-T8 sheet. Longitudinal edge view of worked structure, showing M94Th, both as outlined particles of fragmented massive compound and as precipitate within grains and at boundaries of the elongated grains. 500x
430 I Heat Treater's Guide: Nonferrous Alloys
HM21A-T8 Sheet: Typical creep properties Thstingtemperature OF -c
0.1% (creep) MPa ksi
150 205 260 315 370
103 92 55 34 16
300 400 500 600 700
Stress to produce. in 100h. extensionof 0.2% (total) 0.5% (total) ksi MPa ksi MPa
80 72 48 34 18
14.9 13.3 8.0 5.0 2.3
11.5 10.5 7.0 5.0 2.6
15.6 13.5 9.0 6.0 3.5
108 93 62 41 24
HM31A Chemical Composition. Composition Limits. 2.5 to 3.5 Th. 1.2 Mn min. 0.30 max other (total), bal Mg
Gas-shielded arc welding with EZ3A rod is rated excellent. Resistance welding is rated "very good." Stress relief after welding is not necessary
Specifications (U.S. and/or Foreign). (AMS) As-extruded: 4388. Extruded and aged: 4389; SAE J466; UNS M13312; Government MIL-M8916
Mechanical Properties See Tables for typical tensile and compressive properties ofextrusions, and for typical creep properties of extrusions
Characteristics
Recommended Heat Treating Practice
Product Forms. Primarily bar, rod, shapes, and tubing
The alloy is commonly heat treated to T5 (artificially aged only) temper
Fabrication Properties/Applications. Weldable alloy was developed primarily for elevated-temperature structural service in the form of extruded bar, rod, shapes, and tubing. Exposure to temperatures up to 315°C (600 OF) for 1000 h causes virtually no change in short-time room- and elevated-temperature properties. Superior elastic modulus, particularly at elevated temperatures. Although certain extruded sections developed optimum properties in the as-extruded (F) temper, other sections require aging to the T5 temper.
HM31A: Typical tensile and compressive properties of extrusions up to 2600 mm 2 (4 in. 2 ) in area Testing temperature OF °C
21 150 205 260 315 370 425 480
70 300 400 500 600 700 800
900
'Thnsile strength MPa ksi
283 195 165 145 115 90 55 14
'Thnsile yieldstrength MPa ksi
Compressive yieldstrength MPa ksi
230 180 160 140 110 83 48 7
165 170 160 140 110
41 28 24 21 17 13 8 2
33 26 23 20 16 12 7 1
Elongationin 50mm (2 ln.), %
24 25 23 20 16
10 30 32 25 22 35 60 100
HM31A: Typical creep properties of extrusions Testingtemperature OF °C
205 260 315
400 500 600
0.1% (creep) MPa ksi
110 76 41
16 11 6
Stress to produce, in 100h, extensionof 0.2% (total) 0.5% (total) MPa ksi MPa ksi
83 69 41
12 10 6
115 83 48
17 12 7
Annealing. Material in H24 condition is treated at 400°C (750 "F) for 1 hormore Stress Relieving Treatment. Extrusions and forgings in T5 condition are treated at 430°C (800 oF) for 1 h Recrystallization Temperature. 1 h at 400°C (750 "F), following 50% cold work Hot Working Temperature. Range is 370 to 540 °C (700 to 1000 OF)
HM31A: Microstructure. HM31A-T5 extrusion. Longitudinal view of banded hot-worked structure. Small, recrystallized grains; dark M94Th grain-boundary precipitate; light islands are solid solution rich in thorium and so more resistant to hot working; gray particle is manganese. 500x
Wrought Magnesium Alloys I 431
ZC71 Chemical Composition. Composition Limits. 6.0 to 7.0 Zn, 1.0 to 1.5 Cu, 0.5 to 1.0 Mn, 0.20 Si max, O.OlO Nimax, 0.30 other max (total), balMg Specifications (U.S. and/or Foreign). (ASTM)Extrusions:B 107;UNS M167lO
Characteristics Product Forms. Extrusions
Mechanical Properties Alloy has good mechanical properties and high elongation
Recommended Heat Treating Practice ZC71A is commonly heat treated to the F, T5, and T6 temper Stress Relieving Treatment. ZC71A extrusions in T5 condition are stress relieved at 330°C (625 OF) for I h Aging. In T5 condition, ZC71A is aged at 180°C (355 OF) for 16 h. Quenching from solution treating temperature is either in water at 65°C (150 OF) or in other suitable medium Solution Heat Treating. In T6 condition, the alloy is solution treated at 430 ± 6 °C (800 ± lO oF) Aging after Solution Treating. Alloy is aged at 180 ± 6 °C (355 ± lO OF) for 16 h
Fabrication Properties A weldable, extrusion alloy. Welding is with gas-shielded arc process, using ZC71 rod
ZK60A Chemical Composition. Composition Limits. 4.8 to 6.2 Zn, 0.45 Zr min, 0.30 max other (total), bal Mg
Recommended Heat Treating Practice The alloy is commonly heat treated to T5 condition (artificially aged only)
Specifications (U.S. and/or Foreign). (AMS) Extrusions: 4352. Forgings: 4362; (ASTM) Extrusions: B 107. Forgings: B 91; SAE J466. Former SAE alloy number: 524; UNS M1660; (Government) Extruded rod, bar, and shapes: QQ-M-31. Extruded tubing: WW-T-825.Forgings: QQ-M-40; (Foreign) Elektron ZW6. (British) BS 3373 MAG161. (German) DIN 9715 3.5161. (French) AFNOR G-Z5Zr
Stress Relieving Treatment. ZK60 sheet in the F condition is annealed at 230°C (450 "F) for 3 h
Characteristics
Extrusions are treated at 260°C (500 OF) for 0.25 h
Product Forms. Extruded rod, bar, shapes, and forgings
ZK60A-T5 extrusions are treated at 150°C (300 "F) for 1 h
Fabrication Properties
Aging. ZK60A is aged at 150°C (300 OF) for 24 h in the air, followed by air cooling
Annealing. ZK60A in the F, T5, or T6 conditions is annealed at 290°C (555 OF) for 1 h or more
Extruded products and press forgings are weldable, have high strength, and good ductility. Gas-shielded metal arc welding is possible, but not recommended-because the alloy is prone to hot shortness cracking. However, welds free of cracks exhibit high welding efficiency. Resistance welding has excellent rating
Hot Shortness Temperatures. For wrought product, 510°C (950 OF). For cast product, 315°C (600 OF)
ZK60A: Microstructure. ZK60A-F extrusion. Longitudinal view of banded hot-worked structure. Small, recrystallized grains; light islands are solid solution deficient in zinc and zirconium (due to alloy segregation) and so more resistant to hot working. 250x
ZK60A: Microstructure. ZK60A-F extrusion artificially aged to T5 temper. Structure appears to be the same as that of ZK60Aextrusion in F condition. Precipitate formed during aging is not resolvable by microscopy. 500x
Hot Working Temperature. Ranges from 315 to 400 °C (600 to 750 OF)
Previous Page
Cast Magnesium Alloys /441 See Tables for typical tensile properties of EZ33A-T5 sand castings at elevated temperature, and for typical creep properties of EZ33A-T5 sand castings
Recommended Heat Treating Practice EZ330 is generally heat treated to the T5 temper (artificially aged only)
Aging. Alloy is in F (as-fabricated) condition. Aging takes place at 175 ± 6 "C (345 ± 10 OF) over 16 h period
EZ33A·T5: Typical tensile properties of sand castings at elevated temperatures Properties determined using separately cast test bars. Testing temperature °C
24 150 205 260 315
OF
75 300 400 500 600
'Iensile strength MPa ksl 160 150 145 125 83
23 22 21 18 12
Yield strength MPa ksi 110 97 76 69 55
16 14 11 10 8
Elongation in 50 rom(2 In), % 3 10 20 31 50
EZ33A-T5: Typical creep properties of sand castings Properties determined using separately cast test bars.
EZ33A·T5 sand casting: Microstructure. Interdendritic network of massive MggR compound.The precipitate in the dendritic grains of magnesiumsolid solution is not visible. 100x
'Iensile stress resulting intotalextenslon(a) of TImeuuder load, h
0.1%
MPa
0.2%
0.5%
1.0%
ksi
MPa
ksi
MPa
ksl
MPa
1 10 100 1000
41 41 34 28 At 260 °C (500 oF)
6 6 5 4
69 62 55 41
10 9 8 6
89 83 69 48
13 12 10 7
105 89 76 55
1 10 100 1000
34 28 14 14 At 315°C (600 oF)
5 4 2 2
55 34 21 14
8 5 3 2
69 48 28 14
10 7 4 2
83 55 34 21
12 8 5 3
1 10 100 1000
2 2 2 1
21 14 7 7
3 2 1 1
28 21 14 7
4 3 2 1
34 21 14 7
5 3 2 1
ksi
At 205°C (400 oF)
14 14 14 7
15
13 11 8
(a)Totalextensionequalsinitialextensionpluscreepextension
HK31A A magnesium zirconium alloy (See also wrought alloy HK31 A) Chemical Composition. Composition Limits. 2.5 to 4.0 Th, 0.40 to 1.0 Zr, 0.30 Zn max, 0.10 Cu max, om Ni max, 0.30 max other (total), bal Mg
See Tables for typical tensile properties of HK31A-T6 sand castings at elevated temperatures, and for creep properties ofHK31A-T6 sand castings. See Figure for typical stress strain curves for sand cast test bars
Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4445; (ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; SAE J465. Former SAE alloy number: 507; UNS M1331O; (Government) Sand castings: QQ-M-56 and MIL-M-46062. Permanent mold castings: QQ-M-55 and MIL-M-46062
Fabrication Properties
Characteristics Product Forms. Sand castings, permanentmold castings, investment castings Applicationsrrypical Uses. Sand castings for use at temperatures up to 345 -c (650 oF)
Mechanical Properties Tensile Properties. T6 temper, tensile strength is 220 MPa (32 ksi); yield strength is 105 MPa (15 ksi); elongation is 8% in 50 mm (2 in.) Hardness. T6 temper, 66HRE
A weldable casting alloy. Welding is with gas-shielded arc process, using EZ33A or HK31A rod (former is preferred). Rating is "very good." Sand castings that have been welded require stress relief
Recommended Heat Treating Practice HK3lA is typically heat treated to the T6 condition (solution heat treated and artificially aged) Note: HK31A castings must be loaded in furnace which is at temperature, then brought back to temperature as quickly as possible
Solution Heat Treating. The alloy is treated at 565 ± 6 "C (1050 ± 10 OF) for 2 h. Maximum heat treatment temperature is 570 "C 0060 "F) Note: After solution treating and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur dioxide, or 0.5 to 1.5 sulfur hexafluoride in carbon dioxide as protective atmosphere when furnace temperature is above 400 -c (750 OF)
442/ Heat Treater's Guide: Nonferrous Alloys Aging. After solution treatment castings are treated 205 ± 6 °C (400 ± 10 OF) for 16 h
HK31A-T6: Typical tensile properties of sand castings at elevated temperatures
See Table for postweld heat treatment of HK31A-T6. See micro of HK31A-T6 sand casting
Properties determined using separately cast test bars.
LIVE GRAPH
'Thsting temperature
Click here to view
HK31 A: Typical stress-strain curves for separately sand cast test bars 150
0C
OF
24 205 260 315 370
75 400 500 600 700
Yield strength MPa ksI
'Thnsile strength MPa ksi
llO
31 24 23 20
215 165 160 140 89
16 14 13 12 8
97 89 83 55
13
Elongation in 50 mID (2 in.), %
6 17 19 22 26
20 125 16
'"
0..
:2 100 12
~
t> 75 <: Q)
~
t> .!!!
.!!!
'iii
] ui lI)
ui lI)
HK31A-T6: Microstructure. Sand casting. Intergranular particles of massive M9 4Th compound (gray, outlined). The precipitate in the grains of magnesium solid solution is not visible. 500x
'iii c
~
50
I-
25
0.2
0.4
0.6 0.8 Strain. %
1.0
0 1.2
HK31A-T6: Postweld heat treatments for magnesium alloy castings
Alloy
Welding rod
AZ63A AZ63Aor AZ92A(a)
AZ8IA AZ92Aor AZIOI AZ91C AZ92Aor AZIOI
'Iemper
Desired
before welding
temperafter
F
T4
12hat385±6 °C(725± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385 ±6 °C (725± 10 0F)(b),plus5 h at 220 °C (430 oF) 30 min at 385 ± 6 °C (725± 10oF) 30 min at 385 ± 6°C (725± 10 "F), plus5 h at 220°C (430 OF) 30 min at 415±6 °C (775± 1O°F)(c)
T4
T4
30minat415±6 °C (775± 1O°F)(c)
welding
T40rT6
T6
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T4orT6
T6
EZ33A
EZ33A
ForT5
T5
HIOIA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T4orT6
T6 T5 T6
QH21A
T6
T4orT6
WE43A WE43A
T40rT6
T6
WE54A WE54A
T40rT6
T6
ZC63A
T40rT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
ZC63A
ZE4IA ZE4IA(g) ZH62A ZH62A(g) ZK5IA ZK5IA(g)
HK31A-T6: Creep properties of sand castings Properties determined using separately cast test bars. 'Thnsile stressresulting intotalextension(a) of TImeunder
30minat415 ±6 °C (775± 1O°F)(c), plus4h at215 °C (420 oF)or 16hat 170°C (340°F) 30minat41O±6 °C (765± 1O°F)(c) 30minat41O±6 °C(765 ± 10°F)(c),plus4h at 260 °C (500 OF) or 5 h at 220°C (430oF) I h at 505 ±6°C (940± 10oF),quench,16h at 205°C (400 OF) 2 h at 345°C (650 °F)(d),and/or5 h at 215 °C(420°F), or24h at 220 °C (430°F) 16h at 205°C (400°F)(e) 16hat 315°C (600 oF) I hat 510 ± 6 °C (950± 10OF), quench, 16h at 205°C (400 "F) I h at 510 ± 6 °C (950± 10 "F), quench, 16h at 205°C (400 "F) I hat 510 ± 6 °C (950± 10 "F), quench, 16h at 205°C (400OF) I hat 510 ± 6 °C (950± 10OF), quench, 16h at 205°C (400oF) I h at 425 ± 6°C (795± 10 "F), quench, 16hat205 °C (400°F) 2 hat330 °C(625 0F)(f) 12hat 250°C (480°F)(f) 2 hat330 °C(625 oF),plus 16hat 175°C(345 oF)
(a) AZ63A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 OF) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63A in the T4 orT6 condition unless AZ63Arod is required by specifications.(b)Preheatto 260 °C (500 "F): heat to specifiedtemperatureat no more than 83 0C/h(150 °FIh).(c)Use carbondioxide or sulfur dioxide atmosphere, (d) Heating for 2 h at 345°C (650 "P) results in slight loss of creep strength.(e) Alternativetreatment: I hat315°C(6oo°F), plus 16hat205 °C(4OO°F). (f)Alternative treatment:2 h at 330°C (625 oF),plus 16h at 175°C (345 OF). (g) Or EZ33A
0.1%
0.2%
0.5%
1.0%
ksi
MPa
ksi
MPa
ksI
MPa
ksi
41 I 10 40 100 39 37 1000 At 260 °C (500 oF)
6.0 5.8 5.6 5.4
71 68 66 63
10.3 9.8 9.5 9.1
103 103 103 97
15.0 15.0 15.0 14.0
llO llO llO 109
16.0 16.0 16.0 15.8
I 36 10 30 100 24 21 1000 At 290 °C (550 oF)
5.25 4.4 3.5 3.1
69 59 43 29
10.0 8.6 6.3 4.2
97 88 67 47
14.0 12.7 9.7 6.8
107 100 84 52
15.5 14.4 12.2 7.6
54 31 17
7.8 6.4 4.5 2.5
85 66 43 22
12.3 9.5 6.3 3.2
43 33 20 8
6.2 4.75 2.9 1.1
72 50 24 10
10.4 7.2 3.5 1.4
85 60 28 II
12.3 8.7 4.1 1.55
30 16 7 4
4.4 2.3 1.0 0.63
41 22 9 5
6.0 3.2
load,h
AZ92A
QH21A
Postweld heattreatment
MPa
At 205 °C (400 oF)
I 10 100 1000 At 315 °C (600 oF) I 29 10 22 15 100 1000 6 At 350 °C (600 oF) I 10 100 1000
44
4.15 3.25 2.15 0.94
(a)Total extensionequals initialextension plus creep extension
1.3
0.72
Cast Magnesium Alloys I 443
HZ32A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 1.7 to 2.5 Zn, 2.5 to 4.0 Th, 0.10 rare earths max, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Consequence of Exceeding Impurity Limits. More than 0.1% rare earths causes a loss in creep resistance Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4447; (ASTM) Sand castings: B 80; UNS M13320; (Government) Sand castings: QQ-M-56, Mll..-M-46062; (Foreign) Elektron ZTl. (British) BS 2970 MAG8. (German) DIN 17293.5105
Mechanical Properties Tensile Properties. T5 temper, tensile strength is 185 MPa (27 ksi); yield strength is 90 MPa (13 ksi); elongation is 4% in 50 mm (2 in.) Hardness. 55 HB See Table for typical tensile properties of HZ32A-T5 sand castings at elevated temperatures. See Figure for typical stress-strain curves for sand cast test bars
Fabrication Properties A weldable casting alloy, using gas-shielded metal arc process and H232A or EZ33A rod. Rating of process: "Fair." Stress relief is required after welding castings with heavy sections
Characteristics Product Forms. Sand castings Applicationsrrypical Uses. Sand castings used in the artificially aged condition (T5 temper), with moderate strength and an optimum combination of properties for medium- and long-time exposure at temperatures above 260°C (500 OF). Castings are pressure tight, and under long-time exposure can withstand higher stresses and higher temperatures than any other commercially available magnesium alloy
HZ32A-T5. Typical stress-strain curves for separately sand cast test bars
Recommended Heat Treating Practice HZ32A is typically heat treated to T5 temper (artificially aged only). When treated, castings are in F condition (as-fabricated)
Aging. Castings are treated at 315
± 6°C (600 ± 10 "F) for 16 h
For postweld heat treatment, see Table in datasheet for HK3l A
HZ32A·T5: Typical tensile properties of sand castings at elevated temperatures Testing temperature
-c
·F
24 93 150 205 260 315 370
75 200 300 400 500 600 700
Tensile strength MPa ksi
Yield strength ksi MPa
200 180 150 115 97 83 69
105 97 83 69 63 55 48
Elongation in SOmm(2in.),%
140 20
24·C
120
15
100
29 26 22 17 14 12 10
15 14 12 10 9 8 7
6 15 23 33 33 28 29
149 ·C
I
'"
c,
-"
260 ·C I 316 ·C
10 tl
'--371 ·C
~
e'"
I
en
tl
~
'0;
c
60
~
I
427 ·C
40
20 H + - - t - - - t - - - t - - - - j
0.4
'0;
204 ·C
:2 80
0.8 Strain, %
1.2
e'" en
~
'0;
c
.HZ32A-T5: Microstructure. Sand castings. Intergranular MgTh compounds: Bunches of acicular compound (dark gray) and small areas of massive M94Th. The precipitate within matrix grains is not Visible. 2% nital, 250x
444/ Heat Treater's Guide: Nonferrous Alloys
QE22A A magnesium-zirconium alloy Chemical COlT'lposition. Composition Limits. 2.0 to 3.0 Ag, 1.75 to 2.5 Nd-rich rare earths, 0.4 to 1.0 Zr, 0.1 Cu max, 0.01 Ni max, 0.3 max other (total), bal Mg .
Consequence of Exceeding Impurity Limits. Zr content below 0.5%
ApplicationsfTypical Uses. Sand and permanent mold castings used in the solution-treated and artificially aged condition (T6 temper), with high yield strengths at temperatures up to 200 °C (390 OF). Castings have excellent short-time elevated-temperature mechanical properties and are pressure tight and weldable
may result in somewhat coarser as-cast grains and lower mechanical properties
Mechanical Properties
Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4418C;
Tensile Properties. T6 temper, tensile strength is 260 MPa (38 ksi); yield strength is 195 MPa (28 ksi); elongation is 3% in 50 mm (2 in.)
(ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; UNS M18220; (Government) Sand castings: QQ-M-56B. Sand and permanent mold castings: MIL-M-46062B. Permanent mold castings: QQ-M-55; (Foreign) Elektron MSR-B. (British) DTD 5055. (French) MSR-B AECMA MG-C-51. (German) DIN 17293.5164
Characteristics
Hardness. 65 to 85 HB See Tables for typical tensile properties of QE22A sand castings at various temperatures, and for long time creep properties of QE22A sand castings. See Figures for effect of temperature on strength of QE22A sand castings, for effect of temperature on elastic modulus of QE22A sand castings, and for short-time, creep-rupture properties of QE22A sand castings
Product Forms. Sand castings, permanent mold castings, investment
Fabrication Properties
castings
A weldable casting alloy. Welding is with gas-shielded arc process using QE22A rod. Process rating is "Good"
QE22A: Postweld heat treatments for magnesium alloy castings
QE22Ais typically heat treated to T6 temper (solution treating and artificial aging)
Recommended Heat Treating Practice
Alloy
Weldingrod
A7f>3A
A7f>3Aor AZ92A(a)
AZ8IA AZ91C
AZ92A
AZ92Aor AZIOI AZ92Aor AZIOI
AZ92A
Temper
Desired
beCore welding
temper after
F
T4
12 h a1385±6 °C(725± 10 0F)(b)
F
T6
T4 T4orT6
T4 T6
T4
T4
12 h at 385 ± 6 °C (725 ± 10 0F)(b),plus 5 h al220 °C(430°F) 30 min at 385 ± 6 °C (725 ± 10 oF) 30 min al385 ± 6 °C (725 ± 10°F), plus 5 h al220 °C(430°F) 30minaI415±6°C(775± 1O°F)(c)
T4
T4
30 min al415 ±6 °C (775 ± 10°F)(c)
T40rT6
T6
T4 T4 or T6
T4 T6
30minal415 ±6 °C (775 ± 10°F)(c), plus4h at 215 °C(420°F) or 16halI70°C(34O°F) 30 min a141O±6 °C (765 ± 10°F)(c) 30 min a1410±6 °C (765 ± 10 °F)(c), plus4h al 260 °C (500 oF) or 5 h al220 °C (430 oF) I h at 505 ± 6 °C (940 ± 10 "F), quench, 16 h at 205°C (400 oF) 2h at 345 °C (650 °F)(d), andlor 5 h at 215°C (420 oF), or 24 haI220°C(430°F) 16haI205°C(4OO°F)(e) 16 h al315 °C (600 oF) I hat 510±6°C(950± 1O°F),quench,16hal 205°C(400 oF) I haI510±6°C(950± 10°F),quench,16hat 205°C (400 oF) I haI51O±6°C(950± 10°F),quench, 16hat 205°C(400 oF) I haI51O±6°C(950± 1O°F),quench,16hal 205°C(400 oF) I hat425±6 °C(795 ± 10 oF),quench, 16 h at 205°C (400 oF) 2 h al330 °C (625 0F)(t) 12 h al250 °C (480 0F)(t) 2 h at 330°C (625 oF), plus 16 h at 175°C (345 oF)
welding
EQ2IA
EQ21A
T4 or T6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HZ32A QE22A
HIOIA(g) HZ32A(g) QE22A
T40rT6 ForT5 T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ZE41A ZH62A ZK5IA
ZE4IA(g) ZH62A(g) ZK5IA(g)
ForT5 ForT5 ForT5
T5 T5 T5
Solution Heat Treating. QE22A is treated to T6 condition at 525 ± 6 °C Postweldheat treatment
(a) A7f>3A rod must be used for welding AZ63A in the F temper because 12 h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod nonna1ly is used for welding A7f>3A in the T4 orT6 condition unless AZ63A rod is required by specifications. (b) Preheat to 260 °C (500 "F); heal 10specified temperature at no more than 83 0C/h (150 °PIh).(c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h al345 °C (650 "F) results in slight loss of creep strength. (e)Altemalivetreatment: 1 haI315°C(6OO°F), plus 16hat205°C(4OO°F). (t)A1temative treatment: 2 h at 330 °C (625 OF),plus 16hat 175 °C(345 oF). (g) OrEZ33A
(970 ± 10°F) for 4 to 8 h. Maximum treatment temperature is 540°C (1000 oF) Castings are quenched from solution treating temperature in water heated to 65°C (150 OF), or in some other suitable medium.
Aging after Solution Treatment. Castings are treated at 205 ± 6 °C (400 ± 10 oF) for 8 h Note: After solution treatment and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated, use carbon dioxide, sulfur dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as protective atmospheres when furnace temperatures exceed 400°C (750 oF) See Table for postweld treatments of castings
QE22A: Long-time creep properties of sand castings TIme under load,h
Thosile stressresulting in creepexlensioD(a) oC 0.05%
MPa
ksi
0.1%
MPa
0.2%
IIsI
MPa
IIsI
0.5% ksi
MPa
1.0% ksi
MPa
At 150°C (300 oF) 10 100 1000
150 21.6 120 17.4 90 13.0
140 20.5 105 15.5
165 23.8 125 18.0
150 21.7
At 205°C (390 oF) 10 100 1000
83 55
12.0 8.0
105 15.0 73 10.6
87 55
12.6 8.0
105
32 16
4.7 2.3
40
15.0
72 10.5
110 16.0 78 11.3
At 250 °C (480 oF) 10 100 1000
32 17
4.7 2.5
41 26
10
(a) Does not include initial extension
6.0 3.7 1.4
22
5.8 3.2
26
3.8
Cast Magnesium Alloys /445
QE22A: Typical tensile properties of sand castings at various temperatures -c
Testinglemperature ·F
20 100 205 300
Tensile strength ksl
Yieldstrength ksl
MPa
68 212 392 572
263 235 193 83
MPa
38.1 34.1 28.0 12.0
208 193 166 69
30.2 28,0 24.0 10
QE22-T6: Effect of temperature on the elastic modulus of sand castings
QE22A-T6: Effect of temperature on the strength of sand castings LIVE GRAPH
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Temperature, ·F 200 400
600 300 r---n----,r-----n---,.,..---,
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-100
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100
200
300
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~
400
Temperature, ·C
190 t-------"o".r-----==f"'-""""=--j-------I---..::;::::",~
28 21
~
:2, 180 }------+-----t=""""-=-t----1---.:.:::::l 26
~
1;;
~ 110 t------i-----t-----j-------I---=~
25
---l
104
.
~
23
--=::l
22 105
Time,s
QE22A-T6: Microstructure. Sand casting. Massive MggR compound is present at the boundaries of grains of magnesium solid solution, resulting from partial solution and coalescence of the magnesium-didymium eutectic. 100x
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160
24 22
:2
140
~'
.!!
~ 120
~
26 5%
0..
~' .~
24
150·C (300·F)
160 t - - - - - - i - - - - - t - - - - - j - - - - - - - I - - - - - l
LIVE GRAPH 180
29
103
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.~
QE22A-T6: Short-time creep-rupture properties of sand castings
-L
600
r---
E
5
10
150' - - - - - - ' - -_ _-'--1 10 102
400
I
gf 40
~
c
200
/1.
2!
100
100 200 Temperature, ·C
~
o
CJ
200 ~="'i"--k:::~.,J----!---9 30
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Temperature, ·F
20
..
18
~
16 100
~
~.
.~
~
14 12
80 1
10
103
102
104
105
Time,s
QE22A-T6: Microstructure. Sand casting, Alloy segregation (coring), characterized by intragranular precipitation of didymium and zirconium hydrides (formed during solution treatment by reaction with water vapor) and by less MggR at grain boundaries than normal. 500x
446/ Heat Treater's Guide: Nonferrous Alloys
QH21A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 2.0 to 3.0 Ag, 0.6 to
Fabrication Properties
1.6 Th, 0.6 to 1.5 rare earths (composed of at least 70% Nd), 0.40 to 1.0 Zr, 0.20 Zn max, 0.10 Cu max. 0.01 Ni max, 0.30 max other (total), bal Mg. Optimum total for Th plus rare earths, 1.6 to 2.2
A weldable, fme grain casting alloy. Fully weldable with gas-shielded arc process, using QH21A rod
Specifications (U.S. and/or Foreign). (Foreign) Elektron QH21A
Recommended Heat Treating Practice
Characteristics
QH21A is typically heat treated to T6 temper (solution treated and artificially aged)
Product Forms. Sand castings ApplicationslTypical Uses. Castings used in solution-heat-treated and artificially aged condition (T6 temper). Ideally suited for aircraft and aerospace components, especially where pressure tightness is required. This alloy is of particular interest to designers and stress engineers for highly stressed components operating at temperatures up to 250°C (480 "F),
Solution Heat Treating. Alloy is treated at 525 ± 6 °C (970 ± 10 oF) for 4 to 8 h. Maximum treatment temperature is 540 ± 6 °C (1000 ± 10 "F) Alloy is quenched from solution treating temperature with water heated 65 °C (150 OF), or in some other suitable medium
Aging. QH21A is aged at 205 ± 6°C (400 ± 10 oF) for 8 h See Table for postweld heat treatments of castings
Mechanical Properties See Table for properties before and after exposure to elevated temperatures See Figures for effect of temperature on strength of sand castings, for effect of temperature on strength of QH21A, for fatigue characteristics of sand castings, and for creep properties of sand castings
QH21A: Postweld heat treatments for magnesium alloy castings
Alloy
Temper before Welding rod welding
AZ63A AZ63Aor AZ92A(a)
AZSIA AZ92Aor AZIOI AZ91C AZ92Aor AZIOI
AZ92A
AZ92A
Desired
temper after welding
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385 ±6 °C (725± 100F)(b), plus5 h at 220°C(430 oF) 30minat385±6°C (725± 10°F) 30 minat 385± 6 °C (725± 10 "F), plus5 h at 220°C (430oF) 30min at415±6 °C (775± 10°F)(c)
T4
T4
30minat415±6 °C (775± 10°F)(c)
T40rT6
T6
T4 T40rT6
T4 T6
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
QH21A
T40rT6
T6
WE43A WE43A
T40rT6
T6
WE54A WE54A
T40rT6
T6
ZC63A
T40rT6
T6
ZE4IA ZE4IA(g) ForT5 ZH62A ZH62A(g) ForT5 ZKSIA ZKSIA(g) ForT5
T5 T5 T5
EIongatlon In
lIsi
MPa
ksi
so mm(2 in.), ...
Unexposed(a) Exposed500h at 200°C (390oF) Exposed1000h at 200°C (390oF)
276 284 282
40.0 41.2 40.9
207 205 200
30.0 29.7 29.0
4 8 8
QH21A-T6: Creep propertiesof sand castings 110
15 100 14
If
.~
:;
EQ21A
ZC63A
Thllllile yield strength
MPa
(a) Room-temperature valuesdeterminedusingseparatelycast lestbars 12hat 385±6 °C (725± 10 0F)(b)
EQ21A
QH21A
Thllllile strength Exposure condition
Postweld heattreatment
T4
F
QH21 A-T6: Typical tensile properties of castings before and after exposure to elevated temperature
30 min at415±6 °C (775± 10°F)(c),plus4h at215 °C (420oF)or 16hat 170°C (340oF) 30min at41O±6 °C (765± 1O°F)(c) 30minat41O±6 °C (765± 1O°F)(c), plus4 h at260°C (500oF)or5 h at 220°C (430oF) I h at 505± 6 °C (940± 10 "P), quench,16h at 2050C(4OO oF) 2hat345 °C (650°F)(d),and/or5 h at215 °C (420°F), or24 hat220 °C (430°F) 16hat205°C(4OO°F)(e) 16hat315°C(6OO°F) I hat51O±6°C(950± 10°F),quench,I6h at205°C (400oF) I hat510±6°C(950± 1O°F),quench, 16h at205°C (400oF) I hat51O±6°C(950± 1O°F),quench, 16h at205°C (400oF) I hat510±6°C(950± 10°F),quench, 16h at205 °C (400oF) I hat425±6°C(795± 10°F),quench,16h at 2050c(400oF) 2 h at 330°C (6250F)(I) 12h at 250°C (4800F)(I) 2 h at 330°C (625oF),plus 16h at 175°C (345oF)
(a) AZ63Arod must be used for weldingAZ63Ain the F temperbecause 12h at 385°C (725 "F) causes germinationin welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63Ainthe T4 orT6 conditionunlessAZ63Arod isrequiredby specifications. (b)Preheatto 260 °C (500"F); heattospecifiedtemperature at nomorethan830C/h(150 °FIh). (c)Usecarbondioxide or sulfur dioxideatmosphere.(d) Heatingfor 2 h at 345°C (650 "F) results in slight loss of creep strength.(e)Altemativetreatment:I hat315 °C (600oF),plus16h at205 °C (400°F).(I)Altemative treatment:2 h at 330 °C (625 oF),plus 16h at 175°C (345 oF).(g) Or EZ33A
~. '
...
~
.
90 I----~ ,,".:\-----I---------d 13
~
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c:
~
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---l
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3 104
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Cast Magnesium Alloys I 447
QH21A-T6: Effect of temperature on the strength of sand castings
Temperature, of
300
400
500
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30
200
.><
~
t;;
20
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."c: ~
~
.""c: ~
100 10
0
100
0
300
200
0
Ternperature.f'C
QH21A·T6: Fatigue characteristics of sand castings. Rotating beam (Wohler) tests; machine speed, 2960 Hz 175 150
~
125
:2
+1
~
100
E ::I E
75
t: ·x
~
50
\
25
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175
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-,
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-
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--
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20 ~
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-. r--
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E ::I E
·x ~
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Cycles of stress
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WE43 A magnesium-zirconium alloy Chemical Composition. Composition Limits. 3.7 to 4.3 Y, 2.4 to 4.4 rare earths, 0.4 to 1.0 Zr, 0.15 Mn max, 0.2 Zn max, 0.03 Cu max, 0,01 Si max, 0.005 Ni max, 0.2 Li max, ba1 Mg. Rare earths consist of 2.0 to 2.5% Nd with the remainder comprising heavy rare earths (HRE), principally Tb, Er, Dy, and Gd, The HRE fraction is directly related to the Y content ofthe alloy (that is, Y is present in a nominal80Y-20HRE mixture) Consequence of Exceeding Impurity Limits. Zr content below 0.5% may result in somewhat coarser as-cast grains and lower mechanical properties Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80. Permanent mold castings: B 93. Investment castings: B 199; UNS M18430
Characteristics Product Forms. Sand castings, permanent mold castings, investment castings ApplicationslTypical Uses. Sand castings used in the solution-heattreated and artificially aged condition (T6). Castings retain properties at elevated temperatures (~250 °C, or 480 OF) for extended periods of time (>5000 h), and they are pressure tight and weldable
Mechanical Properties Tensile Properties. T6 temper, tensile strength is 250 MPa (36.3 ksi); yield strength is 162 MPa (23.5 ksi), elongation is 2% See Figure for effect of test temperature on tensile properties. See Table for elevated temperature properties of sand cast specimens
448/ Heat Treater's Guide: Nonferrous AUoys Hardness. 75 to 95 HB Corrosion Resistance. ASlM B 117 salt fog test. 0.1 to 0.2 mg/cm2/day
WE43: Elevated-temperatureraroperties taken from specimens of sand cast 25 mm (1 in.) thick pate 'ThII temperature OF
Fabrication Properties
OC
A weldable casting alloy. Welding is with gas-shielded metal arc process, using WE43 rod
200
Recommended Heat Treating Practice
250 300
WE43A is typically heat treated to T6 temper (solution treated and artificially aged)
Solution Heat Treating. WE43A is treated at 525 ± 6 °C (970 ± 10 oF) for 4 to 8 h. Maximum treatment temperature is 535°C (995 OF) Castings are quenched from the solution treating temperature in water heated 65°C (150 "F), or in some other suitable medium
150
YOW!lI'smodulus
GPa
10'pst
47 39 36 36
6.8 5.7 5.2 5.2
300 390 480 570
Alloy
1\'Zf)3A
10mper belo", WeldiDgrod weldiDg
AZSIA AZ91C
1\'Zf)3Aor
AZ92Aor AZIOI AZ92Aor AZIOI
WE43: Effect of test temperature on the tensile properties
120
300 (43.5)
--
.i,
250 (36.25)
(29)
~
150 (21.75)
=
~
1"-0...
-I---..
IV
100 (14.5)
-,
\.
<,
\
." 60*C
50 (7.25)
Elongation ____
o
570
ltreng!h
0.2% yield strength
200 ~ ::!!.
Temperature, OF 210 300 390 480
o
50
40 .2
/
100 150 200 250 Temperature,oC
10
300
20 g' o o iii
25-26 23-26 22-25 16-19
240-250 240-260 210-230 ISO-170
35-36 35-38 30-33 22-25
EIoogatloo,
...
4-8 8-14 15-20 30-50
Desiml tempera/ler welding
POIlWeld heal treatment
F
T4
12hat385 ±6°C (725± 10°F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat 385±6°C(725± 1O°F)(b),plus5h at220°C (430°F) 30 minat385± 6 °C(725± 10oF) 30 minat385±6 °C(725± 10°F),plus5 h at220°C(430°F) 30minat415 ±6 °C(775± 1O°F)(c)
T4
T4
30mlnat415 ±6°C(775± 1O°F)(c)
T40rT6
T6
30minat415±6 °C(775± 10°F)(c), plus4 h at215°C(420°F)or 16hal170°C(34O°F) 30 minat41O±6 °C(765± 10°F)(c) 30 minat410±6 °C(765± 1O°F)(c), plus4 h al260 °C (500oF)or 5h al220 °C(425oF) I hat 505±6°C(940± 1O°F),quench, 16h at205°C(400oF) 2 h at345°C(650°F)(d), and/or5h at215°C (420oF), or24h at 220°C(430oF) 16hal 205°C(400°F)(e) 16h al315 °C(600oF) I hat510±6°C(950±10°F),quench,16h at205°C(400oF) I hat510±6°C(9SO±IO°F),quench,16h 81205 °C(400oF) I hat51O±6°C(9SO± 10°F),quench,16h at205°C(400oF) I hat 510±6°C(950± 1O°F),quench, 16h 81205 °C (400oF) I hat430±6°C(795± 1O°F),quench,16h 81205 °C(400oF) 2 h at330°C (6250F)(f) 12hal250 °C(4800F)(f) 2 h at330°C(625oF),plus 16h at 175°C(345oF)
AZ92A(a)
See Table for postweld heat treatments of castings
Click here to view
170-180 160-180 150-170 110-130
ThnoiIe ot""'ph lui MPa
WE43: Postweld heat treatments for magnesium alloy castings
Aging after Solution Treating. Castings are treated at 250 ± 6 °C (480 ± 10 OF) for 16 h
LIVE GRAPH
G.2 'hield strength MPa lui
AZ92A
AZ92A
T4 T4orT6
T4 T6
EQ2IA
EQ21A
T40rT6
T6
FZ33A
FZ33A
ForT5
T5
HK3IA HK3IA(g) T4orT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
QH2IA
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ZE41A ZE4IA(g) ForT5 ZH62A ZH62A(g) ForT5 ZKSIA ZKSIA(g) ForT5
T5 T5 T5
(a) 1\'Zf)3A rod must be usedfor welding1\'Zf)3A in lheF temperbecause12h 81385°C (725 "P) causes germination in weldsmade wilh AZ92Arod: AZ92A rod nonnally is used for welding 1\'Zf)3A in the T4 or T6 conditionunlessAZ63Arod isrequiredby speciflcatlons,(b) Preheatto 260°C (500 "F):heal to specifiedlemperatureal no morethan 83 °CJh(150 °FIh).(c) Usecarbon dioxideor sulfur dioxideatmosphere, (d) Heatingfor 2 h at 345°C (650 "F) results In slight lossof creepstrength,(e)Alternative treatment: I hal315 0C(6OO 0F),plus 16h al205 °C(400°F). (f)Altematlve treatment: 2 h al330 °C (625oF),plus 16h 81175°C(345oF).(g) Or FZ33A
WE54 A magnesium-yttrium-rare earth alloy Chemical Composition. Composition Limits. 4.75 to 5.5 Y, 2.0 to 4.0 rare earths, 0.4 to 1.0 Zr, 0.15 Mn max, 0.2 Zn max, 0.03 Co max, 0.01 Si max, 0.005 Ni max, 0.2 Li max, bal Mg. Rare earths consist of 1.5 to 2.0% Nd with the remainder comprising heavy rare earths (HRE), princi-
pally Tb, Er, Dy, and Gd. The HRE fraction is directly related to the Y content of the alloy (that is, Y is present in a nominal80Y-20HRE mixture)
Consequence of Exceeding Impurity Limits. Zr content below 0.5% may result in somewhat coarser as-cast grains and lower mechanical properties
Cast Magnesium Alloys I 449 Specifications (U.S.and/or Foreign). AMS 4426; (ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; UNS MI8410
See Figure for effect of test temperature on tensile properties. See Table for creep rupture properties 2/day
Corrosion Properties. ASTM B 117 salt fog test, 0.1 to 0.2 Mglcm
Characteristics
Fabrication Properties
Product Forms. Sand castings, permanent mod castings, investment cast-
A weldable casting alloy. Welding is with gas-shielded metal arc process, using WE54 rod
ings
Applicationsrrypical Uses. Sand castings used in the solution-heat-
Recommended Heat Treating Practice
treated and artificially aged (T6) condition. Castings retain properties at high temperatures (300°C, or 570 OF) for short-term applications (up to 1000 h) and are pressure tight and weldable
WE54A is typically heat treated to T6 temper (solution treated and artificially aged)
Mechanical Properties Tensile Properties. T6 temper, tensile strength is 250 MPa (36.5 ksi);
Solution Heat Treating. Alloy is treated at 527 ± 6 °C (980 ± 10 oF) for 4 to 8 h. Maximum treating temperature is 535°C (995 oF) Quenching is from solution treating temperature in water heated to 65°C (150 oF), or in some other suitable medium
yield strength is 172 MPa (24.9 ksi); elongation is 2%
Aging after Solution Treatment. WE54Ais treatedat250±6 °C (480
Hardness. 75 to 95 HB
± 10 oF) for 16 h See Table for postweld heat treatments of castings
WE54: Effect of test temperature on the tensile properties
LIVE GRAPH Click here to view 120
---
300 (43.5)
250 (36.25) 200 ~
8!. ~
li
Temperature, OF 210 300 390 480 1
ensr'1 e stren -...; r-.....
r-,
r-......
570
th
WE54: Postweld heat treatments for magnesium alloy castings
-,
Alloy
\ 0.2% yield strengt~ <,
(191
150 (21.75)
AZ63A AZ63Aor AZ92A(a)
y
~
en
100 (14.5)
50 (7.25)
Elongation
o o
100 150 200 250 Temperature,oC
50
AZSIA AZ92Aor AZlOl AZ91C AZ92Aor AZlOl
60 "1fl. C 40 .~ 20 g> 300
o
~
WE54: Creep properties Stressto produceindicatedcreepor total strain in
Typeand amount oCstrain
lOb
MPa
lOOb
ksi
Creep strain at 200 °C (390 °Fl, % 0.05 0.1 0.2 Total slrain al200 °C (390°Fl, % 0.5 Creep strain at 250°C (480 °Fl, % 0.1 90 13.1 0.2 110 16 0.5 135 19.6 Thtal slrain at 250°C (480°Fl, % 0.2 56 8.1 0.5 108 15.7 1 140 20.3
'nmper
Desired
berore
temperafter welding
Welding rod weldlng F
T4
12hat385±6°C(725± 100F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385±6°C(725± 10°F)(b),plus5h at 220°C (430oF) 30 minat 385±6 °C (725± 10oF) 30 minat 385±6°C(725± 10°F), plus5h at 220°C (430°F) 30min at415 ±6 °C(775 ± 10°F)(c)
T4
T4
30minat415±6°C(775± 10°F)(c)
T40rT6
T6
30 min at415 ±6 °C(775± 10°F)(c),plus4h at215 °C (420°F)or 16hat170°C(340°F) 30 minat41O±6 °C(765 ± 10°F)(c) 30 minat41O±6 °C(765 ± 10°F)(c),plus4h at 260°C (500°F) or 5 h at 220°C (430°F) 1 hat505±6°C(940±10°F),quench, 16h at205°C(400°F) 2 h at345°C (650°F)(d),and/or5 h at215 °C (420°F),or 24 h at 220°C (430°F) 16hat205°C(4OO°F)(e) 16hat315°C(600°F) 1 hat510±6°C(950±10°F),quench,16h at 205°C (400oF) 1hat510±6°C(950± 1O°F),quench,16h at 205°C (400°F) 1 hat510±6°C(950± 10oF),quench,16h at 205°C (400oF) 1 hat510±6°C(950± lO°F),quench, 16h at 205°C (400oF) 1hat425±6°C(795± 10°F),quench,16h at 205°C (400oF) 2 h at 330°C (6250F)(f) 12 hat 250°C (4800F)(f) 2 h at 330°C (625oF),plus 16h at 175°C (345oF)
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
FZ33A
ForT5
T5
HK31A HlGIA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
QH21A
T40rT6
T6
WE43A WE43A
T40rT6
T6
WE54A WE54A
T40rT6
T6
ZC63A
T40rT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
lOOOb
MPa
ksi
MPa
ksi
131 160 170
19.0 23.2 24.7
80 102 132
11.6 14.8 19.2
126
18.3
47 61 81
6.8 8.8 11.7
16 32 48
2.3 4.6 7.0
41 75 90
5.9 10.9 13.1
26 45 60
3.8 6.5 8.7
QH21A
ZC63A
ZE41A ZE41A(g) ZH62A ZH62A(g) ZKSIA ZKSIA(g)
Postweld heal trealment
(a) AZ63Arod must he used for weldingAZ63A in the F temperbecause 12 h at 385°C (725 "P) causes gennination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63Ain theT4 or T6 conditionunlessAZ63Arod is requiredby specifications. (b) Preheatto 260 °C(500 "F); heat tospecifiedtemperature at nomorethan83 0C/h(150°FIb).(e)Use earbondioxide or sulfurdioxide atmosphere,(d) Heatingfor 2 h at 345°C (650 "F) resultsin slight loss of creep strength.(e)Alternativetreatment; 1hat315 °C (600°F),plus 16h at205°C(400°F). (f)Alternative treatment: 2 h al330 °C (625oF),plus 16hat 175°C (350oF).(g) Or EZ33A
450 I Heat Treater's Guide: Nonferrous Alloys
ZC63 A magnesium-zinc-copper alloy Chemical Composition. Composition Limits. 5.5 to 6.5 Zn, 204 to
ZC63: Postweld heat treatments for magnesium alloy castings
3.0 Cu, 0.25 to 0.75 Mn, 0.20 Si max, 0.010 Ni max, 0.30 max other (total), balMg
Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80. Permanent mold castings: B 199. Investment castings: B 403; UNS Ml6631
welding
welding
AZfJ3A
AZfJ3Aor AZ92A(a)
F
T4
12hat385 ±6 °C (725 ± 10 01')(b)
F
T6
T4 T4orT6
T4 T6
T4
T4
12hat 385 ±6 °C (725 ± 10 01')(b).plus 5 h at2WOC(430°1') 30 min at 385 ±6 °C (725 ± 10°1') 30 min at 385 ±6 °C (725 ± 10°1'), plos5 h at2WOC(430°1') 30minat415 ±6°C(775± 10°F)(c)
T4
T4
30 min at415 ±6 °C (775± 10°F)(c)
T40rT6
T6
30 minat415 ±6 °C (775 ± 10°F)(c), plus4h - at215°C(4W°F)or l6hat 170 °C (340°1') 30 minat410±6 °C (765 ± 1O°F)(c) 30 min at410±6 °C(765 ± 10°F)(c), plus4h at 260 °C (500 oF) or 5 h at 2WoC (430 oF) I hat505±6°C(940± 10°F),quench,16h at 205°C (400 oF) 2 h at 345°C (650 oF)(d), and/or 5 hat 215°C (420 oF), or 24 h at 220°C (430 01') 16hat205°C(4OO°F)(e) 16hat315°C(600°1') I hat51O±6°C(950± 10 oF),quench, 16h at205°C(4OO°F) I hat51O±6°C(950±10°I'),quench, 16h at 205°C (400 oF) I hat 510 ± 6 °C (950 ± 10 "F), quench, 16 h at 205°C (400 oF) I hat51O±6°C(950± 1O°F),quench, 16h at 205 °C (400 01') I hat425±6°C(795± 10°F),quench. 16h at 205 °C (400°F) 2 h at 330°C (625 0F)(t) 12 hat250 °C (480 0F)(t) 2 hat330 °C (625 OF), plus 16hat 175°C (345 oF)
castings
Mechanical Properties In T6 temper, the alloy has a tensile strength of 210 MPa (30.5 ksi), yield strength of 125 MPa (18.1 ksi), and 3 to 5% elongation
Hardness. 55 to 65 HB
Fabrication Properties A weldable casting alloy. Welding is with gas-shielded arc method, using ZC63 rod
AZSIA AZ91C
AZ92Aor AZIOI AZ92Aor AZIOI
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ2lA
EQ2lA
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HZ32A QE22A
HK3IA(g) T40rT6 HZ32A(g) ForT5 QE22A T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
See Table for postweld heat treatments
WE43A
WE43A
T40rT6
T6
Recommended Heat Treating Practice
WE54A
WE54A
T40rT6
T6
The alloy is commonly solution treated and artificially aged to the T6 condition
ZC63A
ZC63A
T40rT6
T6
ZE4IA ZH62A ZK5IA
ZE4IA(g) ZH62A(g) ZK5IA(g)
ForT5 ForT5 ForT5
T5 T5 T5
Solution Heat Treating. ZC63A is treated to the T6 condition at a temperature of 440°C (820 "F) for 4 to 8 h. Maximum treating temperature is 445°C (830 "F)
Aging after Solution Treating. The alloy is treated at 200°C (390 oF) for 16 h Note: Quenching from the solution treating temperature is in water at a temperature of 65°C (150 OF), or in some other suitable medium
Pootweldheat treatmeoI
Weldingrod
Product Forms. Sand castings, permanent mold castings, investment
treated and artificially aged (T6) condition. Superior properties to AZ91Capplications with better castability. Useful in pressure-tight applications. Can be welded
Desired lemper after
Alloy
Characteristics
ApplicationsfTypical Uses. Sand castings used in the solution-heat-
before
Thmper
(a) AZfJ3A rod must be used for welding AZfJ3A in the F temper because 12 h at 385°C (725 oF) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63A in the T4 or T6 condition unless AZfJ3Arod is required by specifications. (b) Preheat to 260 °C (500 "F); heatto specified temperature at no more than 83 0C/h (150 °PIh).(c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 01')results in slight loss of creep strength. (e)Altemative treatment: I hat315 °C(600 "P), plus 16 hatW5 °C (400°F). (t)A1temative treatment: 2 h at 330°C (625 oF), plus l6 h at l75 °C (345 oF). (g) Or EZ33A
ZE41A Chemical Composition. Composition Limits. 3.5 to 5.0 Zn, 0.75 to 1.75 rare earths (as mischmetal), 0040 to 1.0 Zr, 0.15 Mn max, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg
Consequence of Exceeding Impurity Limits. Content of less than 0.6% soluble Zr may increase grain size and thus reduce mechanical properties; weldability also may decrease
strength up to 93°C (200 OF). Useful in pressure-tight applications. Can be welded. Stress relieved at 345°C (650 "F)
Mechanical Properties Tensile Properties. T5 temper: Tensile strength, 205 MPa (30 ksi); yield strength, 140 MPa (20 ksi); elongation, 3.5%
.
Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80;
Hardness. 55 to 65 HB or 72 HRE
UNS MI64lO; (Foreign) Elektron RZ5. (British) BS 2970 MAG5. (German) DIN 1729 3.5101. (French) AIR 3380 RZ5
See Figure for stress-strain curves for ZE41A cast test bars. See Tables for typical tensile properties ofZE41A at elevated temperatures, and for creep properties of ZE41A sand castings
Characteristics Product Forms. Sand castings ApplicationsfTypical Uses. Sand castings used in the artificially aged condition (T5 temper). Has better castability than ZK51A and good
Cast Magnesium Alloys I 451
Fabrication Properties
See Table for postweld heat treatments for castings
A weldable casting alloy. Welding is with gas-shielded arc process, using ZE41A rod. Process is rated "good." All welding must be completed before hydrogen treatment; welded castings must be stress relieved
ZE41A: Postweld heat treatments for magnesium alloy castings
Recommended Heat Treating Practice
Alloy
Welamgrod
ZE41A in F (as-fabricated) condition is typically heat treated to T5 temper (artificially aged only)
AZ63A
AZ63Aor AZ92A(a)
Aging. Alloy is treated at 330 ± 6 °C (625 ± 10 "F) for 2 h. This treatment is adequate for development of satisfactory properties. Treatment may be followed by 16 h at 177 ± 6 °C (350 ± 10 OF). Result is slight improvement in mechanical properties
AZSIA AZ91C
ZE41A-T5: Creep properties of sand castings
MPH
0.1%
0.5%
MPH
ksi
MPH
ksl
6.8 6.6 6.1 5.4
85 83 76 68
12.3 12.0 11.0 9.8
135 130 125 115
20.0 19.0 18.1 16.5
1 10 100 1000
43 43 41 34 At 20S °C (400 oF)
6.3 6.2 6.0 5.0
74 71 68 63
10.7 10.3 9.9 9.1
112 105 99 86
16.3 15.2 14.3 12.5
I 10 100 1000
38 33 23 14 At2600C (500°F)
5.5 4.8 3.4 2.1
67 56 41 23
9.7 8.1 6.0 3.3
104 91 74 37
15.1 13.2 10.7 5.4
1 10 100 1000
4.1 2.3 1.0 0.84
39 23 12 7
5.6 3.4 1.8 1.0
55 35 21 10
8.0 5.1 3.0 1.4
MPH
ksi
At 93°C (200 oF) 47 46 42 37
At 156 °C (300 oF)
28 16 7 6
12h 31385 ±6 °C (725 ± 100F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12 h at 385 ± 6 °C (725 ± 10 0F)(b),plus 5 h at 220 °C (430 oF) 30rDinat385±6 °C (725 ± 10°F) 30 min at385±6 °C (725 ± 10°F), plus 5 h at 220 °C (430°F) 30 min at415±6 °C (775 ± 1O°F)(c)
T4
T4
30 min at415±6 °C (775 ± 1O°F)(c)
T4orT6
T6
30 min at415±6 °C(775 ± 10 °F)(c), plus4h at 215°C (420 oF) or 16 h at 170°C (340 oF) 30rDin at41O±6 °C (765± 10 °F)(c) 30 min at410±6 °C (765 ± 10 °F)(c), plus4h at 260 °C(500 oF) or 5 h at 220°C (430 oF) 1 hat 505±6 °C(94O± 10 oF),quench, 16 h at 205 °C (400 oF) 2 h at 345°C (650 °F)(d), and/or 5 h at 215°C (420 oF).or 24 h at 220 °C (430 oF) 16 hat205 °C (4OO°F)(e) 16 h at 315°C (600 oF) 1 hat51O±6°C(950± 1O°F),quench,16h at 205 °C (400 oF) 1hat51O±6°C(950± 10°F),quench,16h at205°C(4OO°F) I hat51O±6 °C(950± 10°F),quench, 16h at 205°C (400 oF) 1 hat51O±6 °C(950± 1O°F),quench, 16h at 205°C (400 oF) 1 hat425±6°C(795± 1O°F),quench, 16h at 205 °C (400 oF) 2 h at 330°C (625 0F)(t) 12 h at 250°C (480 0F)(t) 2h at 330 °C (625 °F),plus 16hat 175 °C(345 oF)
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK3IA HZ32A QE22A
HK31A(g) HZ32A(g) QE22A
T40rT6 ForT5 T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ZE4IA ZH62A ZKSIA
ZE4IA(g) ZH62A(g) ZKSIA(g)
ForT5 ForT5 ForT5
T5 T5 T5
1.0%
ksi
I 10 100 1000
T4
AZ92A TewilJe stress resultingin total extewilon(H) or 0.1%
66 43 25 12
9.5 6.2 3.6 1.7
(a) Total extension equals initial extension plus creep extension
Postweldheat t....tment
F
AZ92Aor AZ101 AZ92Aor AZ101
Properties determined using separately cast test bars.
Timeunder Ioad,h
Temper Desired before temperafter welding welding
(a) AZ63A rod must be used for welding AZ63A in Ihe F temper because 12 h at 385°C (725 "P) causes germination in welds rnade wilh AZ92A rod: AZ92A rod normally is used for welding AZ63Ain Ihe T4 orT6 condition unless AZ63Arod is required by specifications. (b) Preheat to 260 °C (500 "F); heat to specified temperature at no more than83 0C/h (150 °F/h). (c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 oF) results in slight loss of creep strength.(e) Alternative treatment: I hat 315°C (600 oF), plus 16 h at 205°C (400 oF). (t) Alternative treatment: 2 h at 330°C (625 of), plus 16 h at 175°C (345 oF). (g) Or EZ33A
ZE41A: Typical stress-strain curves for separately cast test bars
LIVE GRAPH
200
r----r----,-----,-------,------,-----,---...,
Click here to view 25°C
25
150°C
20
150 lU
~
0..
::2
e
1ii
Vi II>
205°C
Vi II>
15
100 260°C
~
~
~
'iii c:
'iii c:
10 ~
315°C
~
50
1L-_ _----JL...-_ _---'
0.2
0.4
---'
--1.
0.6
0.8 Strain. %
---l...
1.0
--'0
- L -_ _
1.2
1.4
452/ Heat Treater's Guide: Nonferrous Alloys ZE41 A-T5: Typical tensile properties of sand castingsat elevated temperatures Properties determined on separately cast test bars,
'Il>sling lemperature "C OF 93
ISO 205 260 315
200 300 400 500 600
'Thmlle s1reogth Ml'II ksJ
'ThosiJe yields1rength MPa ksJ 138 130
106
28,0 25,0 20,5 15.4
82
11,9
69
193 172 141
114
88
20,0 18,8 16.5 12,7 10,0
EIougolion in SOmm(2ln.),'"
8 12 31 40 45
ZE63A A magnesium-zirconium casting alloy Chemical Composition. Composition Limits. 5.5 to 6.0 Zn, 2,1 to 3.0 rare earths, 0.40 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other
See Table for postweld heat treatments of castings
(total), bal Mg
Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4425; UNS M16630; (Government) Sand castings: MIL-M-46062B; (Foreign) Elektron ZE63A. (British) DTD 5045
ZE63A: Postweld heat treatments for magnesium alloycastings
Characteristics
Alloy
Product Forms. Sand and investment castings
AZfJ3A AZ63Aor AZ92A(a)
Applicationsf1\tpical Uses. Sand and investment castings used in solution-heat-treated and artificially aged condition (T6 temper). Especially useful in thin-section castings for applications requiring high mechanical strength and freedom from porosity. Special heat treatment in hydrogen is required to develop properties
Mechanical Properties
AZSIA AZ91C
Tensile Properties. T6 temper, tensile strength is 300 MPa (44 ksi);
Weldingrod
AZ92Aor AZI0l AZ92Aor AZLOI
yield strength is 190 MPa (28 ksi); elongation is 10% in 5,65 fA
Hardness. 60 to 85 HB See Tables for typical tensile properties at various temperatures, and for creep properties of ZE63A sand castings
Fabrication Properties A weldable casting alloy. Welding is with gas-shielded arc process, using ZE63A rod, Process rating: "Very good." Welding must precede heat treatment
Recommended Heat Treating Practice Alloy is typically heat treated to T6 temper (solution treating and artificial aging) The alloy must be solution treated in a special hydrogen atmosphere because its mechanical properties are developed through hydriding some of its alloying elements, Hydriding time depends on section thickness; as a guide, 6.4 mm (0.25 in.) sections require about 10 h; 19 mm (0.75 in.) sections require about 72 h. Following heat treatment, the alloy should be quenched in oil, water, spray, or air blast
Solution Heat Treating. ZE63A is treated at 480 ± 6 °C (900 ± 10 oF) for 10 to 72 h. Maximum treatment temperature is 490°C (910 "F) Aging after Solution Treating. Castings are treated at 140 ± 6 °C (285
± 10 "F) for 48 h
'Thmper Desired before lemperafter welding welding F
T4
12 h a1385± 6 °C (725 ± LO 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12 hat 385 ±6 °C (725± LO°F)(b),plus 5 h at 220°C (430 oF) 30 minat 385 ±6 °C (725 ± 10°F) 30 min at 385 ± 6°C (725 ± 10 "F), plus 5 h at 220 °C (430 oF) 30 minat 415 ±6 °C(775 ± LO°F)(c)
T4
T4
30 minat415 ±6 °C (775 ± LO°F)(c)
T40rT6
T6
30 min at 415 ±6 °C (775 ± LO°F)(c),plus 4h at215 °C (420 oF) or 16hat 170°C (340°F) 30 min at4LO±6 °C (765 ± LO°F)(c) 30 min at4LO±6 °C (765± LO°F)(c),plus 4 h at 260°C (500 oF) or 5 h at220°C (430°F) Ihat505±6°C(940±10°F),quench,16h at 205°C (400 oF) 2hat345 °C (650 °F)(d), and/or 5 h at215 °C (420 oF), or24 h at 220°C (430 oF) 16haI205°C(400°F)(e) 16hat315 °C (600 oF) 1 hat510±6°C(950±10°F),quench,16h at 205°C (400 oF) 1 hat510±6°C(950± 10°F), quench, 16h at 205°C (400 oF) 1 hat510±6°C(950± LO°F),quench, 16h al205 °C (400 oF) 1 hat5LO±6°C(950± LO°F),quench, 16h at 205°C (400 oF) 1 hat425±6°C(795±LO°F),quench,16h at 205 °C (400°F) 2 h al330 °C (625 0F)(f) 12 h at 250 °C (480°F)(f) 2 h at 330°C (625 oF),plus 16h at 175°C (345 oF)
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
FZ33A
ForT5
T5
HK3IA HK31A(g) HZ32A HZ32A(g) QE22A QE22A
T4orT6 ForT5 T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
ZE41A ZE41A(g) ZH62A ZH62A(g) ZKSIA ZKSIA(g)
PosIweldheallreotmenl
(a) AZfJ3Arod must be used for welding AZfJ3A in the F temper because 12 h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZfJ3Ain the T4 or T6 condition unless AZfJ3Arod is required by specifications. (b) Preheat to 260 °C (500 "F); heat to specified temperature atno more than 83 0C/h (150 °FIh). (c) Use carbon dioxide or sulfur dioxide atmosphere. (d) Heating for 2 h at 345°C (650 oF) results in slight loss of creep strength. (e) Alternative treatment: I h at 315°C (600 oF), plus 16 h at 205 °C (400°F), (f) Alternative treatment: 2h at 330°C (625 oF), plus 16h at 175°C (345 oF), (g) Or FZ33A
Cast Magnesium Alloys I 453
ZE63A: Typical tensile properties of sand castings at various temperatures
ZE63A: Creep properties of sand castings Stress
MPa
ksI
0.15%
0.2%
0.25%
Thoe, h,toreach totaIextension(a) of 0.3% 0.5% 0.75% 1.0% 2.0%
3.0%
4.0%
At 100 °C (212oF) 46 25 6.7 62 9.0 77 11.1 92 13.3 At 150°C (300oF) 39 5.7 70 46 6.7 20 54 7.8 62 9.0 70 10.1 77 11.1
650 120
1440 480 30
530 156 8 5
960 135 IS
20 100 l50
1250 280 1400
912 50 35 12 5
720 335 135 35
840 1200 350 550 90 145
200
920 290
350
'Iensile strength ksi MPa
Thsting temperature
-c
OF
41.9 34.1 27.1 19.0
289 235 187 131
68 212 300 390
'Iensile yield strength MPa
ksI
173 131 111
25.1 19.0 16.1 14.1
97
390
(a)Totalextensionequalsinitialextension pluscreepextension
ZH62A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 5.2 to 6.2 Zn, 1.4 to 2.2 Th, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), balMg Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4448; (ASTM) Sand castings: B 80; SAE J465. Former SAE alloy number: 508; UNS M16620; (Government) Sand castings: QQ-M-56, MIL-M-46062; (Foreign) Elektron 1£6. (British) BS 2970 MAG9. (German) DIN 1729 3.5102. (French) AIR 3380 1£6
Characteristics
ZH62A: Postweld heat treatments for magnesium alloy castings
Alloy
Weldingrod
AZ63A AZ63Aor AZ92A(a)
AZ8IA
Product Forms. Sand and permanent mold castings ApplicationslTypical Uses. Sand and permanent mold castings used in artificially aged condition (T5 temper) for room-temperature service. Highest in yield strength of all magnesium
AZ92Aor AZlOl AZ91C AZ92Aor AZlOl
'Iemper before welding
temperafter
F
T4
12hat385 ±6 DC (725± 10°F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385 ±6 DC (725± 100F)(b), plus5 h at220DC (430oF) 30minat385± 6 DC (725± 10oF) 30minat385 ± 6 DC (725± 10oF), plus5 h at220DC (430oF) 30 minat415±6 DC (775± IO°F)(c)
T4
T4
30 minat415±6 DC (775± IO°F)(c)
T40rT6
T6
30minat415±6 DC (775± lO°F)(c),plus4h at215 °C(420°F)orI6hat 170DC (340OF) 30minat410±6 DC (765± lO°F)(c) 30minat410±6 DC (765± lO°F)(c), plus4h at260DC (500oF)or 5 h at220DC (430oF) I h at505± 6 DC (940± 10OF), quench, 16h at205DC (400OF) 2h at345DC (650°F)(d), and/or5h at215DC (420oF), or 24h at220DC (430oF) 16h at205DC (400°F)(e) 16hat315°C(600°F) 1hat510±6°C(950± LO oF),quench, i6h at205DC (400OF) 1hat 510±6°C(950± 10°F),quench,16h at205DC (400OF) 1h at510±6°C(950± 10oF),quench, 16h at205DC (400OF) 1hat510±6°C(950± 10°F),quench,16h at205DC (400OF) 1h at425± 6 DC (795± 10oF),quench, 16h at205DC (400OF) 2hat330°C(625 0F}(f) 12h at250DC (4800F)(f) 2h at330°C (625°F),plus 16hat 175DC (345oF)
Desired
welding
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForTS
T5
HK3IA HK31A(g) HZ32A HZ32A(g) QE22A QE22A
T40rT6 ForTS T40rT6
T6 T5 T6
Fabrication Properties
QH21A
QH21A
T40rT6
T6
A weldable. casting alloy. Welding properties are "poor." Process is gasshielded arc method, using EZ33A or ZH62A rod. Castings should be heat treated after welding
WE43A
WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ForTS ForTS ForTS
T5 T5 T5
Mechanical Properties Tensile Properties. T5 temper, tensile strength is 240 MPa (35 ksi); yield strength is 150 MPa (22 ksi); elongation is 4% in 50 mm (2 in.) Hardness. 70 HB See Figures for distribution of tensile properties of ZH62A-T5 cast test bars, and for microstructure ofZH62A-T5
Recommended Heat Treating Practice ZH62A is typically heat treated in F condition (as-fabricated) to T5 temper Aging. Alloy is treated at 330 °C (350 ± 10 "F) for 16 h
± 6 °C (625 ± 10 "F) for 2 h, plus 177 ± 6
See Table for postweld heat treatment of ZH62A castings
ZE4IA ZE41A(g) ZH62A ZH62A(g) ZK51A ZK51A(g)
Postweld beattreatment
(a) AZ63Arod must be used for weldingAZ63Ain the F temperbecause12h at 385 DC (725oF) causes genninatlonin welds made with AZ92A rod: AZ92A rod nonna11y is used for welding AZ63AintheT4 orT6 conditionunlessAZ63Arodisrequiredbyspecifications. (b)Preheat to 260 DC (500oF);heattospecifiedtempemtureat nomorethan830C/h(150°FIh).(c)Usecarbondioxide or sulfurdioxideatmosphere. (d) Heatingfor 2 h at 345 DC (650 oF)resultsin slightloss of creep strength. (e)Alternativefreatment: 1hat315 DC (600OF), plus16hat 205DC (400OF). (f)Alternative lreabnent: 2 h at 330DC (625oF),plus 16h at 175DC (350oF).(g)OrEZ33A
454/ Heat Treater's Guide: Nonferrous Alloys
ZH62A-T5: Distribution of tensile properties for separately cast test bars of ZH62A-T5
15
~ ~
.-----------------~
49 tests 101-------------.",.----------1
48 tests
50 tests
(;
Q;
-g
51-------
:>
z
o' - - - - ' - - - - = 250 (36)
260 (38)
275
290
(40)
(42)
305 (44)
Tensile strergth, MPa (ksi)
165 (24)
180 (26)
195 (28)
Yield strength, MPa (ksi)
4
6
8
10
Elongation in 50 mm (2 in.), %
ZH62A-T5: Microstructure. ZH62A-T5 sand casting. Characteristic lamellar, or filigree, form of eutectic magnesium-thoriumzinc compound at the boundaries of grains of magnesium solid solution. 2% nltal, 250x
ZK51A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 3.6 to 5.5 Zn, 0.50 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (AMS) Sand castings: 4443; (ASTM) Sand castings: B 80; SAE J 465. Former SAE alloy number: 509; UNS M1651O; (Government) Sand castings: QQ-M-56A, MIL-M-46062; (Foreign) Elektron Z5Z. (British) BS 2970 MAG4. (French) AIR 3380 Z5Z
Characteristics Product Forms. Sand castings
Hardness. 62 HB or 72 HRE See Tables for tensile properties of ZK51A-T5 at elevated temperatures, and for creep properties of ZK51A-T5 sand castings See Figure showing microstructure ofZK51A-T5
Fabrication Properties A weldable, casting alloy. Welding properties are poor. Process used: Gasshielded arc method, with E33A or ZH62A rod. Castings should be heat treated after welding
ApplicationslTypical Uses. Sand castings used in artificially aged condition (T5 temper), with high yield strength and good ductility. This alloy is suggested for highly stressed parts that are small or relatively simple in design. Solution treatment is not required
Alloy in F (as-fabricated) condition. is typically heat treated to T5 (artificially aged) temper
Mechanical Properties
Aging. ZK51A-F is treated at 177 ± 6 °C (350 ± 10 "F) for 2 h
Tensile Properties. T5 temper, tensile strength is 205 MPa (30 ksi); yield strength is 140 MPa (20 ksi); elongation is 3.5% in 50 rum (2 in.)
See Table for postweld heat treating of castings
Recommended Heat Treating Practice
An alternative treatment: 8 h at 220 ± 6°C (425 ± 10 OF)
Cast Magnesium Alloys I 455
ZK51A-T5: Creep properties of sand castings
ZK51 A-T5: Typical tensile properties of sand castings at elevated temperatures
Properties determined using separately cast test bars.
Properties determined using separately cast test bars. TIme under
laad,h A195 °C (200 oF) 1 10 100 1000 At 150°C (300 oF) 1 10 100 1000 At 205 °C (400 oF)
0.1% MPa ks!
Tensile stress resulting in totalexteusiontej of 0.2% 0.5% MPa ksl MPa ksi
1.0% MPa ksl
Testing temperature OF °C
Tensile strength MPa ksi
Yield strength MPa ksi
275 205 160 115 83 55
180 145 115 90 62 41
Elongation in 50mm(2In.), %
47 46 42 37
6.8 6.6 6.1 5.4
85 83 76 68
12.3 12.0 11.0 9.8
138 20.0 131 19.0 125 18.1 114 16.5
25 95 150 205 260 315
43 43 41 34
6.3 6.2 6.0 5.0
74 71 68 63
10.7 10.3 9.9 9.1
112 105 99 86
ZK51A: Postweld heat treatments for magnesium alloy castings
1 10 100 1000 At 260 °C (500 oF)
38 33 23 14
1 10 100 1000
28 16 7 6
5.5 4.8 3.4 2.1 4.1 2.3 1.0 0.84
67 56 41 23 39 23 12 7
9.7 8.1 6.0 3.3 5.6 3.4 1.8 1.0
104 91 74 37 55 35 21 10
16.3 15.2 14.3 12.5
Alloy
15.1 13.2 10.7 5.4 8.0 5.1 3.0 1.4
75 200 300 400 500 600
Welding rod
AZ63A AZ63Aor AZ92A(a) 66 43 25 12
9.5 6.2 3.6 1.7
(a) ToW extensionequals initialextensionpluscreepextension
ZK51 A: Microstructure. ZK51 A-T5 sand castings. Fine, degenerate eutectic magnesium-zinc compound at the grain boundaries. The grains of magnesium solid solution are essentially homogeneous.250x
AZ81A AZ92Aor AZ101 AZ91C AZ92Aor AZ101
40 30 23 17 12 8
8 12 14 17 16 16
Temper before welding
lemperafter welding
F
T4
12hat385±6°C (725± 10 0F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12h at385 ± 6 °C (725± 100F)(b), plus5 h at 220 °C (430oF) 30 min at385 ± 6 °C (725± 10 "F) 30 min ill385± 6 °C(725± 10 "F), plus5 h at220°C (430oF) 30 min at415±6 °C (775± 1O°F)(c)
T4
T4
30 min at415±6 °C(775± 1O°F)(c)
T40rT6
T6
30 min at415 ±6 °C(775± 1O°F)(c), plus4h at215 °C (420oF)or 16hat170°C (340°F) 30 minat41O±6 °C(765± 10 °F)(c) 30 min at41O±6 °C(765 ± 1O°F)(c),plus4h at 260°C (500oF)or 5 hat 220°C (430oF) I h at 505 ± 6 °C (940± 10"F), quench. 16h at 205 °C (400oF) 2 h at 345 °C (650°F)(d),andlor5 h at 215°C (420 oF),or24h at 220°C (430oF) 16h at 205°C (400°F)(e) 16hat315°C(600°F) I hat51O±6°C(950±1O°F),quench,16h at 205 °C (400oF) 1 hat51O±6 °C(950± IOOF),quench, 16h at 205 °C (400OF) 1 hat51O±6 °C(950± 1O°F),quench,16h at 205 °C (400oF) 1 hat51O±6 °C(950± 10°F),quench, 16h at 205°C (400oF) I 11 at425 ±6°C(795 ± 10°F),quench.16h at 205 °C (400oF) 2 h at 330 °C (6250F)(f) 12h at 250 °C (480°F)(O 2hat330 °C(625 oF),plus 16hat175 °C(345 oF)
Desired
AZ92A
AZ92A
T4 T40rT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
HK31A HK31A(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
QH21A
QH21A
T40rT6
T6
WE43A WE43A
T40rT6
T6
WE54A
WE54A
T40rT6
T6
ZC63A
ZC63A
T40rT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
ZE4IA ZE41A(g) ZH62A ZH62A(g) ZK51A ZK51A(g)
26 21 17 13 9 6
Postweld heat treatment
(a) AZ63Arod must beused for weldingAZ63A in the F temperbecause 12 h at 385°C (725 "P) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63A in theT4 orT6 conditionunlessAZ63Arod is requiredby specifications. (b)Preheatto 260 °C (500 "F); heat tospecifiedtemperatureat no more than83 0C/h(150 °FIh). (c)Usecarbondioxide or sulfur dioxide atmosphere.(d) Heating for 2 h at 345 °C (650 oF)results in slight loss of creep strength.(e)Alternativetreatment:I hat315°C(600°F), plus 16hat205°C(4OO°F). (l)A1temative treatment:2 h at 330 °C (625 oF),plus 16h at 175°C (345oF).(g) Or EZ33A
456/ Heat Treater's Guide: Nonferrous Alloys
ZK61A A magnesium-zirconium alloy Chemical Composition. Composition Limits. 5.5 to 6.5 Zn, 0.6 to 1.0 Zr, 0.10 Cu max, 0.01 Ni max, 0.30 max other (total), bal Mg Specifications (U.S. and/or Foreign). (ASTM) Sand castings: B 80; SAE J465. Former SAE alloy number: 513; UNS M1661O; (Government) Sand castings: QQ-M-56B
Characteristics
ZK61A: Postweld heat treatments for magnesium alloy castings Temper Alloy
Welding rod
AZ63A AZ63Aor AZ92A(a)
Product Forms. Sand castings Applicationsfrypical Uses. Simple, highly stressed castings of uniform cross section. High in cost. Intricate castings subject to microporosity and cracking due to shrinkage. Not readily welded. Sometimes used in the artificially aged condition (f5 temper) but usually in the solution-heattreated and artificially aged condition (f6 temper) to develop properties fully
Desired
temper after welding welding before
AZ8IA AZ92Aor AZIOI AZ91C AZ92Aor AZIOI
F
T4
l2hat385±6°C (725± 100F)(b)
F
T6
T4 T40rT6
T4 T6
T4
T4
12hat385 ±6°C (725± 100F)(b), plus5 h at 220°C (430°F) 30 minat385±6°C(725± 10°F) 30 minat 385± 6 °C(725± 10"F), plus5 h at 220°C(430°F) 30minat415±6 °C(775± 1O°F)(c)
T4
T4
30 minat415±6 °C(775± 1O°F)(c)
T40rT6
T6
30 minat415±6 °C(775 ± 1O°F)(c),plus4h at215 °C (420oF)or 16hat 170°C(340°F) 30 minat41O±6 °C(765± 1O°F)(c) 30minat41O±6 °C(765± 1O°F)(c),plus4h at 260°C (500oF)or 5 hat 220°C (430°F) I h at505± 6 °C (940± 10"F), quench,16h at 205°C (400oF) 2h at345 °C(650°F)(d),and/or5 hat215 °C (420°F),or24 h at 220°C (430oF) 16h at205°C (400°F)(e) l6hat315°C(600°F) I h at51O±6°C(950± 1O°F),quench,16h at 205°C (400oF) I h at51O±6°C(950± 1O°F),quench, 16h at205°C(4OO°F) I h at51O±6°C(950± 1O°F),quench, 16h at 205°C (400oF) I hat51O±6°C(950± 1O°F),quench, 16h at 205°C (400oF) I hat425 ±6°C (795± 1O°F),quench, 16h at 205°C (400oF) 2 h at330°C (6250F)(t) 12hat250°C(480°F)(t) 2hat330°C(625 OF), plus 16hat 175°C (345oF)
AZ92A
AZ92A
T4 T4orT6
T4 T6
EQ21A
EQ21A
T40rT6
T6
EZ33A
EZ33A
ForT5
T5
Castable alloy with limited weldability, Thorium or rare earth additions decrease porosity and improve weldability
HK3IA HK3IA(g) T40rT6 HZ32A HZ32A(g) ForT5 QE22A QE22A T40rT6
T6 T5 T6
Recommended Heat Treating Practice
QH21A
QH21A
T40rT6
T6
Alloy (in F, as-fabricated condition) is typically heat treated to T4 (solution treated) and T6 (solution treated and artificially aged) tempers
WE43A WE43A
T40rT6
T6
WE54A WE54A
T40rT6
T6
ZC63A
T4orT6
T6
ForT5 ForT5 ForT5
T5 T5 T5
Mechanical Properties Tensile Properties. T6 temper, tensile strength is 310 MPa (45 ksi); yield strength is 195 MPa (28 ksi); elongation is in 50 mm (2 in.), 10%
Fabrication Properties
Aging. Castings are treated to T5 temper at 150 ± 6 °C (300 ± 10 "F) for 48h Solution Heat Treating. Castings are treated at 500 ± 6 °C (930 ± 10 "F) for 2 h. Maximum treatment temperature is 502°C (935 "F) Alternative treatment: 10 h at 480 ± 6 °C (900 ± 10 "F)
Note: After solution treating and before aging, castings are cooled to room temperature by fast fan cooling, except where otherwise indicated. Use carbon dioxide, sulfur, dioxide, or 0.5 to 1.5% sulfur hexafluoride in carbon dioxide as practice atmospheres if furnace temperatures exceed 400 °C (750 OF)
ZC63A
ZE4IA ZE4IA(g) ZH62A ZH62A(g) ZK5IA ZK5IA(g)
Postweld heattreatmenl
(a) AZ63Arod must be used for weldingAZ63Ain the F temperbecause 12h at 385°C (725 "F) causes germination in welds made with AZ92A rod: AZ92A rod normally is used for welding AZ63AintheT4 orT6 conditionunlessAZ63Arodisrequiredbyspecifications. (b)Preheatto260 °C(500 "F); heattospecified temperature atnomorethan83°CIb(150°FIb). (c)Usecarbondioxide or sulfur dioxideatmosphere. (d) Heatingfor 2 h at 345°C (650 "F) results in slight lossof creep strength.(e)Altemativetreatment: I h at 315°C (600 "F), plus 16hat 205 °C (400 "F), (fj Altemativetreatment: 2 h at330°C (625 "F), plus 16h at 175°C (345 "F), (g) OrEZ33A
Artificial Aging. Castings are treated at 130 ± 6 °C (265 ± 10 "F) for 48 h See Tabie for postweld heat treatments
ZK61A: Microstructure. Segregation of zinc-zirconium-iron compound in a ZK61A-F sand casting. This compound and Zr 2Zn a form under similar conditions; the two can be distinguished by etching with 10% HF,which attacks Zr ~na but not zinc-zirconiumiron. 250x
Titanium Alloys
Heat Treating Titanium Alloys Titanium and titanium alloys are heat treated in order to: • Reduce residual stresses developed during fabrication (stress relieving) • Produce an optimum combination of ductility, machinability, and dimensional and structural stability (annealing)
• Increase strength (solution treating and aging) • Optimize special properties such as fracture toughness, fatigue strength, and high-temperature creep strength
Alloy Types and Response to Heat Treatment The response of titanium and titanium alloys to heat treatment depends on the composition of the metal and the effects of alloying elements on the a-p crystal transformation of titanium. In addition, not all heat treating cycles are applicable to all titanium alloys, because the various alloys are designed for different purposes. Alloys Ti-5AI-2Sn-2Zr-4Mo-4Cr (commonly called Ti-17) and Ti-6AI-2Sn-4Zr-6Mo are designed for strength in heavy sections; Ti-6AI-2Sn-4Zr-2Mo and Ti-6AI-5Zr-0.5Mo-O.2Si, for creep resistance; Ti-6AI-2Nb-lTa-lMo and Ti-6AI-4V-ELI. for resistance to stress corrosion in aqueous salt solutions and for high fracture toughness; Ti-5AI-2.5Sn and Ti-2.5Cu, for weldability; and Ti-6AI-6V-2Sn, Ti-6Al-4V, and Ti-lOV-2Fe-3Al, for high strength at low-to-moderate temperatures. Alloy Types. Based on the types and amounts of alloying elements they contain, titanium alloys are classified as a, near-a, a-p, or p alloys. The response of these alloy types to heat treatment is briefly described below. Alpha and near-alpha titanium alloys can be stress relieved and annealed, but high strength cannot be developed in these alloys by any type of heat treatment (such as aging after a solution beta treatment and quenching). Near-a alloys are alloys with predominantly a stabilizer, plus limited p stabilizers (normally, 2% or less). The commercial p alloys are, in reality, metastable p alloys. When these alloys are exposed to selected elevated temperatures, the retained p
Table 1 Summary of heat treatments for a-p Ti alloys Heallrealmenl designation Duplexanneal
Heallrealment cycle
Solutiontreatat 50-75°C (90-135oF) belowTp(a),air cool and age for 2-8h at 540-675°C (1000-1250 oF) Solutiontrealandage Solutiontreatat-4O °C (70 oF) below Tp,waterquench(b)and age for 2-8h a1535-675 °C (995-1250oF) Betaanneal Solutiontreat ai-15°C (30 "F) above Tp,aircoolandstabilizeat 650-760°C(1200-1400 oF) for 2 h Betaquench Solutiontreatat-15°C (30 oF) above Tp,waterquenchand temperat 650-760°C(1200-1400oF) for2 h Recrysta1lization anneal 925°C (1700"F) for4 h, cool at 50 °CJh(90°FIb)to 760°C (1400"F), air cool Millanneal lX-~ hot workplus annealat705 °C (1300 oF) for30 min to several hoursand air cool
Microstructure Primarya, plus
Widmanstlinen lX-~ regions
Primary a, plustempered lX' or a P-lX mixture Widmanstatten lX-~ colony microstructure Temperedri Equiaxed n wilh ~ at grainboundary triplepoints Incompletely recrystallized lX wilha smallvolumefraction ofsmall~ particles
(a)Tpis Ihe ~ transustemperature fortheparticularalloyinquestion.(b)In moreheavily~-stabilized alloyssuchasTi-6AI-2Sn-4Zr-6MoorTi-6AI-6V-2Sn, solutiontreatment isfollowed by air cooling. Subsequentagingcausesprecipitation of lX phaseto forman lX-~ mixture
phase decomposes and strengthening occurs. For p alloys. stress-relieving and aging treatments can be combined, and annealing and solution treating may be identical operations. Alpha-beta alloys are two-phase alloys and, as the name suggests, comprise both a and p phases at room temperature. These are the most common and the most versatile of the three types of titanium alloys. Phase compositions, sizes, and distributions can be manipulated by heat treatment within certain limits to .enhance a specific property or to attain a range of strength levels. A summary of typical heat treatments for a-/3 titanium alloys is given in Table 1. Beta transus temperatures for various commercial titanium alloys are listed in Table 2. When the heat treatment involves heating near the p transus, the transus temperature of each heat in a lot must be accurately determined.
Table 2 Beta transformation temperatures of titanium alloys Betatramus
Alloy Commercially pureTi,0.25 02 max Commercially pure'Il,0.40 Oz max a or near-a aUoys Ti-5Al-2.5Sn Ti-8Al-IMo-tV Ti-2.5Cu(lMl230) TJ-6Al-2Sn-4Zr-2Mo Ti-6Al-5Zr-0.5Mo-O.2Si (lMl685) Ti-5.5Al-3.5Sn-3Zr-lNb-0.3Mo-0.3Si (lMl829) TJ-5.8A1-4Sn-3.5Zr-0.7Nb-0.5Mo-0.3Si (IMI 834) Ti-6Al-2Cb-lTa-0.8Mo Ti-0.3Mo-O.8Ni rncode12) a-Jlalloys Ti-6Al-4V Ti-6Al-7Nb (IMI 367) Ti-6Al-6V-2Sn (Co + Fe) Ti-3Al-2.5V Ti-6A1-2Sn-4Zr-6Mo TJ-4Al-4Mo-2Sn-0.5Si (lMl550) TJ-4A1-4M0-4Sn-0.5Si (lMl551) Ti-5Al-2Sn-2Zr-4M0-4Cr(1i-17) Ti-7A1-4Mo TJ-6A1-2Sn-2Zr-2Mo-2Cr-0.25Si Ti-8Mn JI or near-jl alloys TJ-13V-llCr-3A1 Ti-lI.5Mo-6Zr-4.5Sn (BetaIll) Ti-3A1-8V-6Cr-4Zr-4Mo (BetaC) Ti-l0V-2Fe-3A1 Ti-I5V-3A1-3Cr-3Sn (a)±20. (b)±30. {c)±35.(d)±50
"C,±15
°F,:lZ5
910 945
1675 1735
1050 1040 895 995 1020 1015 1045 1015 880
1925 1900 1645 1820 1870 1860 1915 1860 1615
l000(a) 1010 945 935 940 975 1050 900 1000 970 800(c)
183O(b) 1850 1735 1715 1720 1785 1920 1650 1840 1780 1475(d)
720 760 795 805 760
1330 1400 1460 1480 1400
+
+
460 I Heat Treater's Guide: Nonferrous Alloys
Stress Relieving
Table 3 Recommended stress-relief treatments for titanium and titanium alloys Parts can be cooled from stress relief by either air cooling or slow cooling.
Titanium and titanium alloys can be stress relieved without adversely affecting strength or ductility. Table 3 presents combinations of time and temperature that are used for stress relieving titanium and titanium alloys. The rate of coolingfrom the stress-relievingtemperatureis not critical. Uniformity of cooling is critical, however, particularly in the temperature range from 480 to 315°C (900 to 600 "F), Oil or water quenching should not be used to acceleratecooling because this can induce residual stresses by unequal cooling. Furnace or air cooling is acceptable. Weldments. The temperatures used for stressrelievingcomplex weldments of a or a-~ alloys should be near the high ends of the ranges given in Table3.
Annealing The annealing of titanium and titanium alloys serves primarily to increase fracture toughness, ductility at room temperature, dimensional and thermalstability, and creepresistance.Many titaniumalloys are placed in service in the annealed state. Because improvement in one or more properties is generallyobtained at the expense of some other property, the annealing cycle should be selected according to the objective of the treatment. Common annealing treatments are: • • • •
Mill annealing Duplex annealing Recrystallizationannealing Beta annealing
Recommended annealing treatments for several alloys are given in Table 4. Either air or furnace cooling may be used, but the two methods may result in different levelsof tensile properties. If distortion is a problem, the cooling rate should be uniform down to 315°C (600 "F), It may be difficult to prevent distortion of close-tolerance thinsections duringannealing.
'ThmperalW'e
Alloy
Commercially pure11 (all grades) a or near-a titanium alloys 11-5AI-2.5Sn 11-8AI-IMo-IV 11-2.5Cu (IMl230) 11-6A1-2Sn-4ZJ"-2Mo 11-6AI-5ZJ"-0.5Mo-O.2Si (IMl685) 11-5.5Al:3.5Sn-3ZJ"-1Nb-0.3Mo-O.3Si (IMl829) Ti-5.8AI-4Sn-3.5ZJ"-0.7Nb-0.5Mo-O.3Si (IMl834) Ti-6Al-2Cb-lTh-0.8Mo Ti-O.3Mo-O.8Ni (11Code 12) a-p titanium alloys Ti-6AI-4V 11-6AI-7Nb (IMl367) 11-6Al-6V-2Sn (Cu+ Fe) Ti-3AI-2.5V 11-6AI-2Sn-4ZJ"-6Mo 11-4AI-4Mo-2Sn-O.5Si (IMl550) 11-4AI-4M0-4Sn-0.5Si (IMl551) 11-5Al-2Sn-4Mo-2ZJ"-4Cr (11-17) 11-7AI-4Mo 11-6A1-2Sn-2Zr-2Mo-2Cr-0.25Si Ti-8Mn Por near-jl titanium alloys 11-13V-11Cr-3Al 11-l1.5Mo-6ZJ"-4.5Sn (BetaTIl) 11-3AI-8V-6Cr-4ZJ"-4Mo (BetaC) 11-IOV-2Fe-3Al 11-15V-3Al-3Cr-3Sn
Time,
-c
OF
h
480-595
900-1100
0.25-4
540-650 595-705 400-600 595-705 530-570 610-640 625-750 595-650 480-595
1000-1200 1100-1300 750-1110 1100-1300 980-1050 1130-1190 1160-1380 1100-1200 900-1100
0.25-4 0.25-4 0.5-24 0.25-4 24-48 1-3 1-3 0.25-2 0.25-4
480-650 500-600 480-650 540-650 595-705 600-700 600-700 480-650 480-705 480-650 480-595
900-1200 930-1110 900-1200 1000-1200 llOO-1300 1ll0-129O 1ll0-129O 900-1200 900-1300 900-1200 900-1100
1-4 1-4 1-4 0.5-2 0.25-4 2-4 2-4 1-4 1-8 1-4 0.25-2
705-730 720-730 705-760 675-705 790-815
1300-1350 0.0833-0.25 1325-1350 0.0833-0.25 1300-1400 0.167-0.5 1250-1300 0.5-2 1450-1500 0.0833-0.25
Table 4 Recommended annealing treatments for titanium and titanium alloys Temperature Alloy
Commercially pure11(all grades) a or near-a titanium alloys Ti-5AI-2.5Sn 11-8AI-IMo-IV 11-2.5Cu (IMl230) Ti-6AI-2Sn-4ZJ"-2Mo 11-6AI-5ZJ"-0.5Mo-O.2Si (IMl685) Ti-5.5AI-3.5Sn-3ZJ"-1Nb-0.3Mo-O.3Si (IMl829) 11-5.8AI-4Sn-3.5ZJ"-O.7Nb-O.5Mo-O.3Si (IMl834) 11-6A1-2Cb-lTa-0.8Mo a-p titanium alloys 11-6AI-4V 11-6A1-7Nb (IMl367) 11-6A1-6V-2Sn (Cu+ Fe) 11-3AI-2.SV 11-6AI-2Sn-4ZJ"-6Mo 11-4AI-4Mo-2Sn-O.SSi (IMlSSO) 11-4AI-4M0-4Sn-O.5Si (IMlSSl) 11-SAI-2Sn-4Mo-2Zr-4Cr (11-17) 11-7Al-4Mo 11-6AI-2Sn-2ZJ"-2Mo-2Cr-0.25Si 11-8Mn Por near-jl titanium alloys 11-13V-11Cr-3AI 11-11.5Mo-6ZJ"-4.SSn (BetaTIl) 11-3AI-8V-6Cr-4ZJ"-4Mo (BetaC) 11-10V-2Fe-3Al 11-1SV-3Al-3Cr-3Sn
°C
OF
Time, h
Cooling method
650-760
1200-1400
0.10-2
Air
720-845 790(a) 780-800 9OO(b) (c) (c)
1325-1550 1450(a) 1450-1470 165O(b) (c) (c)
0.167-4 1-8 0.5-1 0.5-1
Air Air or fumace Air Air
(c)
(c)
790-900
1450-1650
1-4
Air
705-790 700 70S-81S 6S0-76O (c) (c) (c) (c) 70S-79O 70S-81S 6S0-76O
1300-1450 1300 1300-1S00 1200-1400 (c) (c) (c) (c) 1300-14S0 1300-1S00 1200-1400
1-4 1-2 0.7S-4 0.S-2
Air or furnace Air Air or furnace Air
1-8 1-2 O.S-1
Air Air (d)
70S-79O 690-760 790-81S (c) 790-81S
1300-14S0 0.167-1 Air or water 127S-14OO 0.167-1 Air or water 14S0-1S00 0.25-1 Air or water (c) 14S0-1S00 0.0833-0.25 Air
(a) Forsheetand plate,followby 0.25 h at 790 °C (l4S0°F), then air cool.(b) Forsheet,followby 0.25 h at790 °C (14S0"F), thenaircool (plus2 h atS9S°C, or 1100OF, then air cool,in certainapplications). Forplate.followby 8 h atS9S °C (1100"F), then air cool.(c)Not normallysuppliedor usedin annealedcondition(seeThble3). (d)Furnaceor slowcoolto S40°C(1000oF),then air cool
Titanium and Titanium Alloys /461
Solution Treating and Aging A wide range of strength levels can be obtained in a-~ or ~ alloys by solution treating and aging. With the exception of the unique Ti-2.5Cu alloy (which relies on strengthening from the classic age-hardening reaction of Ti2CU precipitation similar to the formation of Guinier-Preston zones in aluminum alloys), the origin of heat-treatingresponsesoftitanium alloys lies in the instability of the high-temperature ~ phase at lower temperatures. Heating an a-~ alloy to the solution-treating temperature producesa higher ratio of ~ phase.This partitioningof phases ismaintained by quenching; on subsequentaging, decompositionof the unstable ~ phase occurs, providing high strength. Commercial ~ alloys, generally supplied in the solution-treatedcondition, need only be aged. Time/temperaturecombinationsfor solution treating are given in Table 5. A load may be charged directly into a furnace operating at the solutiontreating temperature. Although preheating is not essential, it may be used to minimize the distortion of complex parts. Solution treating of titanium alloys generally involves heating to temperatureseither slightly above or slightly below the ~ transus temperature. The solution-treating temperature selected depends on the alloy type and practical considerations briefly described below. Beta alloys are normally obtained from producers in the solutiontreatedcondition. If reheating is required, soak timesshouldbe only as long as necessary to obtain complete solutioning. Solution-treating temperatures for ~ alloys are above the ~ transus; because no second phase is present, grain growth can proceed rapidly. Alpha-Beta Alloys. Selection of a solution-treatment temperature for a-~ alloys is based on the combination of mechanical properties desired after aging. A change in the solution-treating temperature of a-~ alloys
alters the amounts of ~ phase and consequently changes the response to aging (see Table 6). Near-Alpha Alloys. Like the a-~ alloys, solution treatment above the ~ transus provides optimum creep resistance at the expense of reduced ductility and fatigue strength. To obtain the best combination of creep strength and fatigue strength, the solution temperaturemust be very close to but below the transus, so that only 10 to 15%of primary (untransformed) a remains. Quenching. The rate of cooling from the solution-treatingtemperature has an important effect on strength. If the rate is too low, appreciable diffusion may occur during cooling, and decomposition of the altered ~ phase during aging may not provide effective strengthening. For alloys relatively high in ~-stabilizer content and for products of small section size, air or fan cooling may be adequate; such slow cooling, where allowed by specified mechanical properties, is preferred because it minimizes distortion. Beta alloys are generally air quenched from the solution-treatingtemperature. Water, a 5% brine, or caustic soda solution is preferred for quenching a-~ alloys because these quenchants provide the cooling rates necessary to prevent the decomposition of the ~ phase obtained by solution treating, in order to provide maximumresponse to aging.The need forrapid quenching is further emphasized by short quench-delay requirements. Depending on the mass of the sections being heat treated, some a-~ alloys can tolerate a maximumdelay of? s, whereasmore highly ~-stabilized alloys can tolerate quench delay timesof up to 20 s. The effectof quenchdelays on Ti-6AI-4V bar is shown in Fig. 1.
Table 5 Recommended solution-treating and aging (stabilizing) treatments for titanium alloys Alloy
a ornear-a alloys TI-8Al-IMo-IV TI-2.5Cu (lMJ230) TI-6Al-2Sn-4Zr-2Mo TI-6Al-5Zr-O.5Mo-O.2Si (lMJ685) TI-5.5Al-3.5Sn-3Zr-INb-O.3Mo-0.3Si (lMJ 829) TI-5.8Al-4Sn-3.5Zr-O.7Nb-O.5Mo-O.3Si (lMJ 834) a-ll alloys TI-6AI-4V TI-6Al-6V-2Sn (Cu + Fe) TI-6Al-2Sn-4Zr-6Mo TI-4AI-4Mo-2Sn-O.5Si (lMJ 550) TI-4Al-4Mo-4Sn-O.5Si (lMJ 551) TI-5Al-2Sn-2Zr-4Mo-4Cr TI-6Al-2Sn-2Zr-2Mo-2Cr-025Si Pornear-p alloys TI-13V-IICr-3Al TI·II.5Mo-6Zr-4.5Sn (Beta III) TI-3Al-8V-6Cr-4M0-4Zr(Beta C) TI-IOV-2Fe-3Al TI-15V-3Al-3Cr-3Sn
Solution temperature OF -c
Solution tlme,h
CooUngrate
°C
OF
tlme,h
565-595 390-410 465-485 595 540-560 615-635 625
1050-1100 735-770 870-905 1100 1005-1040 1140-1175 1155
8-24 (step I) 8(step 2) 8 24 2 2
900-1100 1300-1400 900-1100 1075-1125 915-950 915-950 1075-1125 900-1100
4-8 2-4 4-8 4-8 24 24 4-8 4-8
800-900 900-1100 850-1000 925-975 950-1100
4-100 8-32 8-24 8 8-24
Aging temperature
980-1010{a) 795-815
1800-1850(a) 1465-1495
I 0.5-1
Oil or water Air orwater
955-980 1040-1060 1040·1060 1020(b)
1750-1800 1905-1940 1905-1940 1870(b)
I 0.5-1 0.5-1 2
Air
955-970(c)(d) 955-970 885-910 845-890 890-910 890-910 845-870 870-925
1750-1775(c)(d) 1750-1775 1625-1675 1550-1650 1635-1670 1635-1670 1550-1600 1600-1700
I I I I 0.5-1 0.5-1 I I
Water Water Water Air Air Air Water
480-595 705·760 480-595 580-605 490-510 490-510 580-605 480-595
775-800 690·790 815-925 760-780 790-815
1425-1475 1275·1450 1500-1700 1400-1435 1450-1500
0.25-1 0.125-1 I I 0.25
Air orwater Air orwater Water Water Air
425-480 480·595 455-540 495-525 510-595
Oil Air oroil
Oil
Air
Aging
(a) For certainproducts. use solution temperature of890°C (1650 "F) for Ih.then air cool orfaster. (b) Temperature should be selected from transus approachcurve togive desired a content. (c) For thin plate orsheet. solution temperature can be used down to890 °C (1650 "F) for 6to 30min; then water quench. (d) This treatment isused to develop maximum tensile properties in this alloy
462/ Heat Treater's Guide: Nonferrous Alloys
Table 6 Variation oftensile properties ofTi-6AI-4V bar stock with solution-treating temperature Solution-treating lempemture
"C
845 870 900
925 940
OF
1550 1600 1650 1700 1725
Room-lempemlnre tensile propel1ies(a) Thnsile strength YIeld strength(b) MPa ksi ksi MPa
1025 1060 1095 1Il0 1140
149 154 159 161 165
980 985 995 1000 1055
142 143 144 145 153
Elongation
in4D, %
18 17 16 16 16
Fig. 1 Effects of quench delay on tensile properties of li-6AI-4V bar. Bar, 13 mm (0.5 in.) in diameter, was solution treated 1 h at 955°C (1750 OF), water quenched, aged 6 h at 480°C (900 OF), and air cooled
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High Purity Titanium This grade has half the oxygen content of commercial pure (ASTM grade 1) titanium. Oxygen content usually is in the neighborhood of 500 ppm or less. See adjoining table for specifications and compositions. Common names for this grade are iodide Ti or electrolytic Ti. A UNS number has not been assigned.
Characteristics Typical uses include experimentation and research and commercial applications requiring minimum interstitial alloying elements (oxygen, nitrogen, carbon, and hydrogen). Pure Ti is supplied as single crystals, crystal bars, and polycrystalline wrought forms. Product conditions are cold worked, stress relieved, annealed.
Beta Transus. At atmospheric pressure, titanium has the alpha (cph) structure at low temperature and transforms at 880 ± 2 °C (1615 ± 3.5 "F) to the beta (bcc) structure. The assumed transformation temperature of880 ± 2 °C is based on phase diagram data for binary Ti systems, as well as on direct measurement (see adjoining figures for phase diagrams). Superconductivity. A state of superconductivity is stable only if temperature, magnetic field strength, and current density are all below the critical levels, or thresholds. The three critical parameters of temperature (Tc), magnetic field
Critical Temperature of Superconductivity. Atypical value for pure titanium is 0.40 ± 0.04 K (B.W. Roberts, Properties of Selected Superconducting Materials, 1978 Supplement, NBS Technical Note 983). Critical temperatures as high as 0.56 K have been reported (T.S. Smith and 1.G. Daunt, Phy. Rev., Series 2, Vol 88, 1952, P 1I72).
Corrosion resistance. Depends on the formation of a protective oxide layer. General corrosion becomes a concern in reducing acid environments, particularly as acid concentration and temperature increase. In strong and/or hot reducing acids (in the absence of inhibitors) the oxide film can deteriorate and dissolve, and the unprotected metal is oxidized to the soluble trivalent ion (Ti3+ + 3e).
Oxidation. This property does not differ significantly from that of ASTM commercially pure titanium grades I and 2 (UNS R50250 and R50400),
Pure Titanium: Effect of grain size on room-temperature yield strength of three purities of titanium Material
Impurilies (bywelgbt), ppm
A70(ASTM 2830 O. 25 C. 250N. 67 H. 3700 Fe grade4) Battelle 3300, 25C.14ON.62H, 90 Fe Iodide 300. 18C. 110N.18H
HB1I-Pelcb Caclol'5(a) Friction stress (m)(b) GrainSizeconsl~ MPa kgf/mm' kgf/mm'!z MP 40
390
0.86
266
18 14
175 137
0.32 0.47
99 145
(a)Factors in the HaIl-Petchrelation:yieldstress = OJ + KVd, where d is the averagegrain size. (b) Frictionstressfor a strainrate 00 x 10-4/s
and thin oxide films form in air temperatures between 315 and 650°C (600 and 1200 "F). The oxide film is barely perceptible after exposure at 315 °C (600 "F), but it becomes darker and thicker with increasing temperature and time at temperature. The changes in surface color can be used as a rough guide of exposure temperature in air (see Table), while time at temperature becomes a more significant factor for temperatures above 500 °C (see Figure). Care must be used in estimating temperature due to the time factor mentioned, and the oxide color at a given temperature is strongly influenced by the cleanliness of the surface. A surface exposed to elevated temperature with, for example, oil on the surface, will have a different color than a clean surface.
Hydrogen Damage. Titanium and its alloys suffer hydrogen damage primarily by hydride phase formation. Commercially pure titanium is more sensitive to hydrogen damage. The amount of hydrogen necessary to induce ductile-brittle transition behavior in CP titanium is one-half the amount needed in pure titanium. Tensile Properties. Typical room-temperature tensile properties ofpure titanium are: • 235 MPa (34 ksi) ultimate tensile strength • 140 MPa (20 ksi) tensile yield strength (0.2% offset) • 50% elongation in 50 mm (2 in.)
Effect of Impurities. Interstitial impurities have a strong influence on tensile properties, which can be correlated to the hardening effect of the impurities (see adjoining Figures). Grain Size Effect. Effect of grain size on tensile yield strength obeys the Hall-Petch relation, but the effect is less pronounced for the more pure grades of titanium (see adjoining Figure). Hardness Properties. Ingot melted from electrolytic titanium has a typical hardness of70 to 74 HB. Ingot produced from iodide titanium has a hardness of 65 to 72 HB. See adjoining Figures for effect of impurities on hardness and correlation of tensile properties with hardness.
Heat Treating Properties In keeping with commonly observed behavior, increasing amount of cold work prior to annealing decreases the subsequent recrystallization temperature and grain size (see Figure). Increasing the amount of cold work before annealing also decreases the spread in grain volume distribution (Met. Trans., Voll6A, May 1985, p 703-708). The reason for the decrease in grain size distribution is not completely clear. See adjoining Figure for effect of annealing temperature and degree of deformation on grain size.
IMlll0 titanium sheet: Guaranteed mechanical properties MinimnmO.2% yieldstrength Ultimatetensilestrength Minimumelongationon 50 mm (2 in.) Maximumbendradius: Sheetup to 1.83mm (0.072in.) Sheetup to 1.83-3.25mm (0.128in.)
130MPa (18.8ksi) 270-350MPa (39-50ksi) 30% IT 2T
High-purity Titanium compositions SpeciJ1calion designalion
Form(s)
C
1}tpical %.electrolytic Ti Typical%.IodideTi IMI 110,maxwt%
Crystalbar Sheet
0.008 0.001 0.02
H
N
0.004
0.004 0.002 0.005
0
Cu
0.037 0.007 0.03-0.06 <0.001 0.05 0.02
Fe
Mn
Sn
Si
Zr
CI
Mg
0.009 0.002 0.G25
<0.001 0.003 0.05
<0.020 0.001 0.G2
0.002 0.005 0.02
<0.001 0.050
0.073 0.002
<0.001 0.003
1ibal
99.837 99.87
464/ Heat Treater's Guide: Nonferrous Alloys
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30
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Iodide Titanium: Grain size vs, annealing and deformation. Influence of annealing temperature (1 h duration) and degree of deformation on the grain size of cold-deformed sheet-strips of iodide titanium 600 E
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466/ Heat Treater's Guide: Nonferrous Alloys
Pure Titanium: Correlation of tensile properties with hardness. Impurity contents of binary alloys range from 0.04 at.% to 2.0 at.%. Annealed, high-purity titanium
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Previous Page 498/ Heat Treater's Guide: Nonferrous Alloys
Ti-8AI-1 Mo-1 V Common Name. Ti-811 UNS Number. R54810 Chemical Composition. The Ti-8Al-IMo-1 V alloy contains a relatively large amount of the alpha stabilizer, aluminum, and fairly small amounts of the beta stabilizers, molybdenum and vanadium (plus iron as an impurity). Although this is a metallurgically alpha-beta alloy, the small amount of beta stabilizer in this grade (1Mo + IV) permits only small amounts of the beta phase to become stabilized. See Tables for specifications and compositions, and commercial compositions
Characteristics ProductCondition/Microstructure. Past work on the phase relationships of Ti-8AI-IMo-IV (D.E. Austin, Boeing Document T6-314, 1965) indicates that the ~ phase transforms to martensite at temperatures in the a-~ field from the transus down to about 900°C (1650 OF). Below this temperature, the ~ phase is sufficiently enriched in molybdenum and vanadium to be retained. The ~ phase decomposes during tempering below about 450°C (840 OF). Like other a alloys, structure is predominantly a, with small amounts of ~. The a phase may also undergo a metallurgical reaction, resulting in an ordered structure (D019-type superlattice) of the type found in binary titanium-aluminum alloys. It has been suggested that the presence of the ordered structure is responsible for the differences in mechanical properties between duplex and mill annealed material and is also responsible for the poor stress-corrosion resistance of this alloy
Beta Transus. Approximately 1040 °C (1905 OF) with normalinterstitial contents
ProductForms. Ti-811 was developed for engine use, principally as forgings. Available forms include billet, bar, plate, sheet, and extrusions Applications. Ti-811 has the highest tensile modulus of all the commercial titanium alloys and exhibits good creep resistance at temperatures up to 455°C (850 OF). Ti-811 has a room-temperature tensile strength similar to that ofTi-6AI-4V, but its elevated-temperature tensile strength and creep resistance are superior to those of other commonly available alpha and alpha+beta titanium alloys. Ti-811 is used for airframe and turbine engine applications demanding short-term strength, long-term creep resistance, thermal stability, and stiffness. Ti-811 is predominantly an engine alloy and is available in three grades, including a "premium grade" (triple melted) and a "rotating grade," for use in rotating engine components
Use Limitations. Like the alpha-beta alloys, Ti-811 is susceptible to hydrogen embrittlement in hydrogenating solutions at room temperature, in air or reducing atmospheres at elevated temperatures, and even in pressurized hydrogen at cryogenic temperatures. Oxygen and nitrogen contamination can occur in air at elevated temperatures and such contamination becomes more severe as exposure time and temperature increase. Ti-811 is susceptible to stress-corrosion cracking in hot salts (especially chlorides) and to accelerated crack propagation in aqueous solutions at ambient temperatures General Corrosion Properties. The alloy has high susceptibility to stress-corrosion cracking, but few published data are available on the general or localized corrosion of Ti-8AI-IMo-lY. One study, however, indicates repassivation behavior that is similar to that of CPTi and Ti-6Al4V in neutral salt solution (see Figure). Successful application of Ti-811 can be expected in mildly reducing to highly oxidizing environments in which protective oxide films spontaneously form and remain stable. On the other hand, hot, concentrated, low-pH chloride salts corrode titanium. Warm or concentrated solutions of hydrochloric, phosphoric, and oxalic acids also are damaging. In general, all acidic solutions that are reducing
in nature corrode titanium, unless they contain inhibitors. Strong oxidizers, including anhydrous red fuming nitric acid and 90% hydrogen peroxide, also cause attack. Ionizable fluoride compounds, such as sodium fluoride and hydrogen fluoride, activate the surface and can cause rapid corrosion. Dry chlorine gas is especially harmful
Stress Corrosion Cracking. Ti-8AI-IMo-IV is one of the most susceptible titanium alloys to stress-corrosion cracking (SCC), which stems from the increased tendency to form the highly ordered ThAI (a2) phase when aluminum content exceeds 5 wt%
Fabrication Properties Forging. Ti-811 is an a alloy that is commercially produced in all forging product types, although closed die forgings and rings predominate. The alloy is produced on all types of commercially available forging equipment; however, because the major commercial application for the alloy is high-volume turbine engine compressor blades and vanes, rapid-strain-rate hammers, mechanical presses, and/or screw presses are the primary equipment used to forge this alloy. The alloy is forged to precise airfoil shapes requiring minimal final machining. Ti-811 is generally subtransus forged Ti-8ll: Forging process temperatures Melaltempera1urn
OF
Process
Conventional forging
900-1020
1650-1875
Forming. Forming practices for Ti-811 are similar to those of other a-rich alloys. The ~ transus of this alloy is higher than Ti-6AI-4V, and this permits higher hot work temperatures. Finish working temperatures above the ~ transus (approximately 1035 °C, or 1895 "F) produce coarser grain size than is characteristic of finishing below the ~ transus. Sheet forming is more difficult than in Ti-6AI-4V, and for severe operations, forming temperatures between 715 and 745°C (1320 and 1375 OF) are required. Duplex annealed Ti-811 can be hot formed in a broad temperature range without reduction in properties provided the material after forming is heat treated to 785°C (1445 "F) for 15 min followed by quick cooling Welding. The alloy, like other alpha or near alpha alloys, has good weldability. Weldments are similar in strength to the base metal, but lower in ductility. The filler metal must be the same as the base metal
Machining. Like other titanium alloys, machining of Ti-811 is comparable to that of a good grade of stainless steel. In general, very sharp tools with a slightly larger rake angle and very keen edge work quite well. Slower speed and heavier cuts are preferred, because they keep tool temperatures down and produce coarse chips. Drilling of thin-walled titanium is not much of a problem as long as the drill is sharp. Thicker walled tube requires a heavy flood of coolant to remove heat and chips
Recommended Heat Treating Practice Like Ti-6AI-2Sn-4Zr-2Mo, a variety of heat treatment conditions are possible with Ti-811. A particular condition is usually selected on the basis of part section size, fabrication history, service environment, and the mechanical properties desired. For example, a thick section product for engine use may be most desirable in the duplex annealed condition having maximum creep strength, whereas a sheet may be heat treated to produce a formable condition
Stress Relief Annealing. Treatment should consist of thermal exposures that do not disturb the metallurgical stability of the alloy. Annealing data for temperatures between 595 and 785°C (1100 to 1445 "F) have been developed. Complete relaxation occurs in about 2 h at 595°C (1100 "F) to about 15 to 20 min at 785°C (1445 OF). Differences in cooling from the stress-relief annealing temperatures, particularly if temperatures on the
Alpha and Near-Alpha Alloys I 499
high side of the range are used, may significantly affect mechanical properties. When stress relief annealing is at 760 to 785°C (1400 to 1445 "F), it is possible to control the annealed properties by thermal exposure time and terminal cooling rate in the same way that is used by the mill in supplying the two conditions-mill and duplex annealed Reannealing. In the shop, forming, machining, or joining operations may require reannealing to regain the properties inherent in the as-received metal. This may be a step beyond stress relief annealing, although it may be accomplished in much the same way. In the above cases, longer exposure time followed by slow cooling at about 55 °C/h (100 °F/h) from 785 to 480°C (1445 to 900 OF) results in the mill-annealed condition. A 20-min exposure followed by faster cooling (785 to 480°C, or 1445 to 900 OF in less than 1 h, i.e., air cooling is quite satisfactory) results in the duplex-annealed condition. Intermediate cooling rates result in mechanical properties that are intermediate to those of mill and duplex-annealed material Strengthening Heat Treating. Ti-811 may be strengthened by solution heat treatment followed by aging. Solution treatment is performed high in the a-~ field at 900 to 1010 °C (1650 to 1850 OF), followed by water quenching. Usually aging is accomplished at intermediate temperatures in the 480 to 650°C (900 to 1200 OF) aging temperature range. Strengthening is limited to smaller sections and is not w,idely used.
See Table for typical heat treatments and Figures for volume fraction of alpha and beta, stress relief, and effect of cooling on properties
Ti-811: Forming temperatures Tempemture Method Hotsizing Brakeforming Drophammer Stretching
785 730 730
Drawing Spinning
785
Pressforming Hydropress Matcheddie Rollfonning
730 785 540
Creepforming Joggling Dimpling
785
Comments
·F
OC
1445 15-minexposure,ceramicdies 1345 Severeforming 1345 Severe Temperatures above540·C (1000oF) arerequired before significantimprovement in stretchability is obtained 1445 Betterfonnabilitystartsat 540·C (1000"F) and increases rapidlyat 650°C (1200 oF) 1345 Severe 1445 Severe 1000 I Tbend radiusafter20 roll passeswithrollsheatedto95 to 260°C (20510500 oF). Alphacaseremovedperpass 1445 750 0.56-16.0rom(0.022100.63 in.) sheet;lower temperatures are permissible, butspringbackis greaterandmoreerratic
400
Ti-8AI-l Mo-l V: Commercial compositions Composition, WI% Specification France Ugine Germany DeutscheT Japan Kobe USA Chase Ext. OREMET
RMI Timet
Designation
Description
AI
C
Fe
H
Mo
N
0
V
Other
UTA8DV
BarFrgDA
7.3-8.5
0.08
0.3
0.006-0.015
0.75-1.25
0.05
0.12
0.75-1.25
balTI
ContimetAIMoV8-1-1
PltBarFrgAnn
7.5-8.5
0.08
0.3
0,0]5
0.75-1.25
0.05
0.12
0.75-1.25
balTI
KS8-1-1
BarFrgSTA
7.35-8.35
0.3
0.015
0.75-1.25
0.05
0.12
0.75-1.25 balTI
8Al-IMo-IV TI-8-1-1 RMI8AI-IMo-IV TIMEfAL8-1-1
MuitFormsDA Ann
7.5-8.5 7.35-8.35
0.3 max
0,0]5 0.015max
0.75-1.25 0.75-1.25
0.05 0.05 max
0.12 0.12 max
0.08 0.08 max
0.75-1.25 0.75-1.25
balTI balTI
Ti-8AI-l Mo-l V: Specifications and compositions Composition. WI% Specilication UNS China
Designation
Descriplion
R54810
AMS4915F AMS4916E AMS4933A AMS4955B AMS4972C
L-7102
7.5-8.5 ShStepPlt BarExtAnn 7.35-8.35 Sh StepPItAnn
ShStrpPItAnn ShStepPltDupAnn ExtRugSHT/Stab WeldFillWir BarWrrRngBil SHT/Stab AMS4973C Frg BilSHTlStab AWSAS.I6-70 ERTI-8Al-IMo-IV WeldFillMet MlLF-83142A Comp5 FegAnn MILT-81556A CodeA-4 MlLT-9046J CodeA-4 ShStepPltAnn MlLT-9047G Ti-8AI-IMo-IV BarBiiDupAnn SAEJ467 Ti-8-1-1 OT.others total
C
Fe
H
Mo
N
0
V
8
Ti-8AI-IMo-IV Spain UNE38-717 USA AMS4915C
AI
balTi
0.1 max
0.3 max
0.015 max
0.75-1.25
0.04 max
0.15 max
0.08
0.3
0,0]5
0.75-1.25
0.05
0.12
0.015 max
0.75-1.25
0.05 max
0.12 max
0,0]5 0,0]5 0.015 om 0,0]5
0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25
0.05 0.05 0.05 0.05 0.05
0.12 0.12 0.12 0.12 0.12
0,0]5 0.008 Om5 0,0]5 0,0]5 0,0]5
0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 1
0.05 0,03 0.05 0.05 0.05 0.05 0.02 max
0.12 0.12 0.15 0.15 0.15 0.15
7.35-8.35 0.08 max 0.3 max 7.35-8.35 7.35-8.35 7.35-8.35 7.35-8.35 7.35-8.35
0.08 0.08 0.08 0.08 0.08
Other
0.3 0.3 0.3 0.3 0.3
7.35-8.35 0.3 0.08 7.35-8.35 0.05 0.25 7.35-8.35 0.3 0.08 7.35-8.35 0.08 0.3 7.35-8.35 0.08 0.3 7.35-8.35 0.3 0.08 8 0.04 max 0.15max
0.75-1.25 SiO.l5 max;balTi 0.75-1.25 OT 0.4;balTi 0.75-1.25 OTO.4max;YO.005max;OE 0.1max;balTi 0.75-1.25 OTO.4;YO.005;balTi 0.75-1.25 OTO.4;YO.005; balTi 0.75-1.25 OTO.4;YO.005; balTi 0.75-1.25 OTO.4;YO.005; balTi 0.75-1.25 OTO.4;YO.005; balTi 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 0.75-1.25 I
OTO.4;Y 0.005;balTi balTi OT 0.4;balTi OTO.4;balTi OTO.4;balTi OTO.4;YO.005; balTi Si 0.07max;Ni 0.008max;balTI
500 I Heat Treater's Guide: Nonferrous Alloys
Ti-8AI-1Mo-1V: Tensile modulus of duplex annealed sheet. 0.6 mm (0.025 in.) sheet duplex annealed at 1010 °C (1850 OF), 15 min, AC + 750°C (1380 OF), 15 min, AC
Ti-8AI·1Mo-1V: Tensile modulus comparison Temperature, of 400 600 800
200
1000
150 20
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Ti-8ll : Typical heat treatments Heat ......tment Stressrelief Millannealing Solutiontreating Aging Duplexannealfor thicksections(a) 1ststage stabilization Duplexannealforsheet lst stage (mill anneal) 2nd stage
Thmperature
Cooling method
Time. h
OC
of
600-700 760-790 980-1010 565-595
1ll0-1290 1400-1455 1795-1850 1050-1100
900-1010 600-745
1650-1850 1110-1375
760-790 600-790
1400-1455 1ll0-1455
0.25-4 Air orslowcool 1-8 Air orfurnacecool 1 Oilor waterquench Air coot
Ti-8AI-l Mo-l V: Environments known to produce
Organic compounds Methylalcohol(anhydrous)
Air orfurnace cool Aircool
Methylchloroform Ethylalcohol(anhydrous) Ethyleneglycol Trichloroelbylene Trichlorofluoroethane Salts Hotsalt:chlorideandother halidesalts/residues SeawaterlNaOsolution
(a)Treatmentfor goodcreep strength
Ti-8AI-l Mo-l V: Effect of hydrogen content on hardness Pro<essingfcondlllon Asreceived, millannealed As received, millannealed Annealedat 870°C (1600oF) in vacuum,8 h, furnacecooled Annealed at 870°C (1600"P) in vacuum, 8 h, furnacecooled
Thlckn... Hydrogen, Hardness, mm In. ppm HRC 17 17 17 17
0.673 0.673 0.673 0.673
(twice) Annealedat 870°C (1600"F), hydrogenated, 8 h, furnacecooled 17 0.673 Annealed at 1065°C (1950"F) in vacuum, 4 h, furnacecooled 15 0.597
Thmperature, °c
Medium
Air cool Air cool
1-8
7
36 36 33 33
39 21
33 -30
14-21 14-21 5
see
Environment
TI-6Al-4V, grade2TI, Grade4TI, TI-4Al-3Mo-1V,Ti-3Al-8V-6Cr-4Zr-4Mo (BetaC), TI-13V-11Cr-3Al, TI-5Al-2.5Sn 370 TI-6Al-4V,TI-5Al-2.5Sn, TI-13V-11Cr-3Al TI-5Al-2.5Sn RT NoalloysotherthanTI-8Al-1Mo-1V RT 370,620, 815 TI-5Al-2.5Sn TI-5Al-2.5Sn, TI-6Al-4V,TI-13V-llCr-3Al 788 lIT
230-430
370 340
Mostcommercialalloysexcept grades1,2,7,11,12, and9 Unalloyed Ti (with oxygencontent>0.3%) Ti-2.5AI-lMo-llSn-5Zr-n.2Si(IMl-679), Ti-3Al-11Cr-13V,TI-5AI-2.5Sn, TI-8Mn, n6Al-4V,TI-6Al-6V-2Sn, Ti-6Al-2Nb-ITa, TI-4Al-3Mo-1V,TI-6AI-2Sn-4Zr-6Mo TI-13V-l1Cr-3Al TI-6Al-4V
RT 288 35,340 300-500
Ti-5Al-2.5Sn, Ti-11.5Mo-6Zr-4.5Sn (Betaill) No alloysotherthanTI-8Al-1Mo-1V Ti-5Al-2.5Sn No alloysotherthanTi-8Al-1Mo-1V
RT
Mercury(liquid) Ag-5Al-2.5Mn (bracealloys) Miscellaneous Distilledwater Chlorinegas 10%HCI Moltenchloridelbromide salts
Alloywas received in the hot rolled and mill annealedcondition.Chemicalcompositionwas 7.92 wt%Al,0.03wt%C,0.15wt%Fe,H asindicated,0.98 wt%Mo,0.01wt%N, 0.11wt% 0, and 1.01 wt%V
Othertitanium alloys withknown suoceptibillty
Ti-8ll : Turning parameters for annealed material Thol IIllIlerial
Rough turning Brazedcarbide(C2) Throwawaycarbide(C2) High-speedsteel (M, T5,T15) Finish turning Brazedcarbide(C3,C2) Throwawaycarbide(C3,C2) High-speed steel (M3, T5,TI5)
Thol
Depthorcnt
Feed
Speed
geometry(a)
mm
In.
mmfrev
In./rev
mfmin
.rm
A,E,F A,E,F B,D,E,F
2.5-6.35 2.5-6.35 2.5-6.35
0.10-0.25 0.10-0.25 0.10-0.25
0.25-0.38 0.25-0.38 0.25-0.38
0.010-0.015 0.010-0.015 0.010-0.015
21-42 46-60 73-22O(b)
70-140 150-200 240-72O(b)
A,C A,C C,E,F
0.635-2.5 0.635-2.5 0.635-2.5
0.025-n.10 0.025-0.10 0.025-n.1O
0.13-0.25 0.13-0.25 0.13-0.25
0.005-0.010 0.005-0.010 0.005-0.010
27-47 50-56 73-183(b)
90-155 165-185 240-6OO(b)
(a) See accompanyingtablefor toolgeometrycodes. (b) Thesehigh speedswould be loweredif slowerfeedsand deepercuts aremade withhigh-speedsteelcutters
Alpha and Near-Alpha Alloys I 501
Ti-8AI-1Mo-1V: Effect of solution temperature on hardness. Alloy was supplied in the form of 64 mm (2.5 in.) square bar stock. Chemical composition was 7.6 wt% AI, 0.022 wt% C, 0.06 wt% Fe, 0.005 wt% H, 1.1 wt% Mo, 0.008 wt% N, 0.09 wt% 0, and 1.1 wt% V. Hardness measurements were made on 13 mm (0.5 ln.) cubes in the plane normal to the rolling direction. Cube surfaces had been ground at least 1.3 mm (0.050 ln.) and mechanically polished. Hardness was also determined for Jominy bar that had been sectioned along the center line and surface ground. Specimens were solution treated in air for 1 h, followed by brine quench
Solution temperature, OF 1600 1800 2000 1400
1200
150
45 ST 6 STA (24 h, 80°C) .. Percent bet o
40 0
125 100
0::
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75
c
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0
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600
1000 800 Solution temperature, "C
1200
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Ti-811: Forging pressure. Forging pressures at 10% upset reduction with 4340 steel presented for comparison
----
700 600
100
til
'(ij
60
0.300
~
~
c
'0,
40
Ti-8AI-1Mo-1va~
(; 200
u,
:>
a.
Ti-13V -11er-3AI al 980°C
Ol
e Ol
c
'e>
10 Strain rate, mm/mm
a
P 1000
~ ./
e 900
I~
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a.
2
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Ol
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1600
b
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1000
i 0.2
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2000
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20
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650°C
0::
40
0 102
Ti-811: Volume fraction of IX and p
E
0
~ ~ a; 60
u,
AISI 4340 a11260'e
1
:>
c- 80
AISI 4340 at 1095 -c
0
~
c>'!.
0
20 100
----~
-7~5 ~e
-'"
~
100
80
Ti-13V-l1er-3A~
oi' :; 400
120 785°C
Ti-BAI-l Mo-l V at 760°C
~ 500
Ti-811: Stress relief. 1.4 mm (0.056 in.) sheet mill annealed at 785°C (1445 OF) for 8 h, then cold worked
1.0
1.0 Heating time, h
10.0
Ti-811: Microstructure. Forged with a starting temperature of 900°C (1650 OF), which is below the normal temperature range for forging this alloy. Structure: equiaxed 0: grains (light) in a matrix of transformed ~ (dark). Kroll's reagent (ASTM 192). 250x
5021 Heat Treater's Guide: Nonferrous Alloys
Ti-811: Effect of cooling on properties. Sheet cooled from 785°C (1445 OF) after heating 8 h
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1100
o
0
18
..Furnace cool heat treatment followed by air cooling
Furnace cool heat treatment followed by air cooling 16
1050
0
.•
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150._
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-'"
c0
(/)
.c
UTS
0,
c
C
~
e
en
140 950
en
~ 14 0> C 0
ill
Elongation 12
TYS
AC Q
900
LIVE GRAPH
10
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2
3
4
5
10 10 10 10 10 Cooling rate between 785 'C and 425 'C/h
WQ
10 6
Ti·811: Microstructure. Forged with starting temperature of 1005 °C (1840 OF), which is within the normal range, and air cooled. Equiaxed grains of "primary" a (light) in a matrix of transformed ~ (dark) containing fine acicular a. Kroll's reagent (ASTM 192). 250x
10
2
3
4
5
10 10 10 10 Cooling rate between 785 'C and 425 'C/h
6
10
Ti·811: Microstructure. The starting temperature for forging was 1095 °C (2000 OF), which is above the ~-transus temperature, and the finished forging was rapidly air cooled. The structure consists of transformed ~ containing coarse and fine acicular a (light). Kroll's reagent (ASTM 192). 250x
TIMETAL®1100 Ti-6AI-2.75Sn-4Zr-0.4Mo-0.45Si; Ti-1100 UNS Number. Unassigned Chemical Composition. The composition of this alloy, which is a modification of Ti-6242-Si, is the result of a development program to determine the effects of tin, iron, oxygen, silicon, zirconium, molybdenum, and aluminum on creep, strength, and stability properties. Chemistry differences between the two alloys appear to be subtle, but they are quite dramatic in their effect on creep response, as indicated by the following findings: • Silicon: Creep resistance is significantly enhanced up to 0.5% silicon, but beyond that point post-creep ductility (stability) is compromised with no further creep enhancement. • Tin: A similar relationship exists for tin, with stability sacrificed above the 3% level.
• Iron: Iron demonstrates a strong effect on time to 0.2% creep strain at the 510 °C (950 OF), 410 MPa (59 ksi) test condition, necessitating iron levels well below those typically encountered in the Ti-6242-Si alloy. • Aluminum: The aluminum level in the new alloy was kept at 6% due to stability problems at higher levels and strength problems at lower levels. • Zirconium: Zirconium was kept high to promote a uniform distribution of silicides in light of the high silicon level. Thus, the chemistry of this alloy was optimized not only for creep strength, but also for stability, strength, and uniformity See Table for typical composition range
Characteristics Phases and Structures. Typical microstructures for Ti-llOO include equiaxed a-~ for billet and sheet stock. It also transforms to a Widmanstat-
Alpha and Near-Alpha Alloys I 503 ten or colony a+~ structure depending on cooling rate. The effects of cooling rate on the transformed ~ structure are as follows: alpha-beta processing with a normal cooling rate results in equiaxed primary a plus transformed ~ with a colony structure plus silicides; beta processing with rapid cooling results in a Widmanstiitten structure, whereas slower cooling after ~ processing results in a colony structure. In addition to a and ~ phases, various silicides exist for both a + ~ or ~ processed conditions. The silicide solvus has been measured at between 1030 and 1065 "C (1885 and 1950 OF). The a-2 solvus is approximately 740°C (1365 oF). The ~ transus is nominally 1015 -c (1860 OF)
Product Forms. Ti-1100 has been processed to billet, bar, sheet, and weld wire. Forgings have been produced using isothermal and warm die methods, and foil has been produced for use in metal matrix composites. Investment castings have been produced. No data are available on PIM products
Applications. Ti-1100 is designed for applications requiring excellent creep strength or fracture properties at temperatures up to approximately 600°C (1110 OF). High-pressure compressor disks, low-pressure turbine blades, and automotive valves are typical examples
Fabrication Properties Forging. Ti-1100 may be hammer forged or press forged using isothermal, warm die, or conventional die methods. The resulting properties will vary depending on the effective cooling rate and strain rate of the defonnation process. Finer structures will result in higher tensile strength at the expense ofcreep strength at high temperatures. Forging below the ~ transus followed by a beta anneal to obtain the appropriate microstructure generally is not recommended. However, early forging operations (e.g., preform block) may be conducted in the subtransus field with the finish forging conducted in the ~ field. As with other difficult to fabricate near-a alloys, precoats or other surface coating techniques are essential on billet stock and intermediate forging shapes during fumacing for forging operations. Ti-1100 may be sensitive to the excessive formation of a case during reheating processes, which may lead to undue surface cracking in forging deformation. As with other a alloys, care must be exercised if the use of dry abrasive grinding techniques used for crack repair
Recommended Forging Temperatures. The recommended beta forging range is 1090 to 1120 "C (1995 to 2050 "F), To achieve desired elevated-temperature and creep performance characteristics, Ti-ll00 is designed to be beta processed, creating a transformed, Widmanstatten a-type microstructure, with minimum grain boundary a. To date, thennomechanical processing work with the alloy suggests that ~ forging, followed by an appropriate post-forging cooling process based on section size, and final stabilization thermal treatment provide optimum properties. Subtransus forging and beta heat treatment are not currently recommended because Ti-l ltx), as a near-alpha alloy, is characterized by high unit pressures. However, hot working above the ~ transus is not cumulative; thus, if multiple forging steps are required (e.g., preform, block, and finish), early forging operations may be conducted subtransus, with the finish forging being conducted above the transus with a sufficiently high level of work. Supratransus, beta forging of Ti-l100 significantly reduces unit pressure requirements and crack sensitivity and is conducted from a temperature
Ti-ll 00: Typical composition range
Minimum Maximum Nominal
AI
Sn
Zr
Composition, WI% Fe Mo Sl
5.7 6.3 6.0
2.4 3.0 2.7
3.5 4.5 4.0
0.35 0.50 0.40
0.02
0.35 0.50 0.45
O.
0.09 0.07
N.
0.03
c
above the silicide solvus-1040 "C (1905 °F)-to avoid excessive silicide formation, Typically, beta forging reductions of 50 to 75% are recommended for Ti- ] 100. Low levels of deformation above the ~ transus should be avoided
Post-Forging Treatment. The post-forging cooling rate is not highly critical, and generally an air cool is sufficient. However, for thicker section forgings, fan cooling or oil quenching may be required to achieve final part mechanical properties. Final stabilization age thermal treatments may be adjusted to modify final strength properties. Stabilization treatments are generally in the range of 500 to 650°C (930 to ]200 "F) Casting. In a study, the strength of cast Ti-1100 was found to be equivalent to cast Ti-6AI-2Sn-4Zr-2Mo at 540°C (1000 "F), but was stronger at 595°C (1100 "F), Ti-lloo is somewhat weaker in thick cross sections than thin ones and exhibits a significant creep advantage relative to Ti-6AI-2Sn4Zr-2Mo. It also has higher low-cycle fatigue strength at 550°C (1020 "F) than Ti-6AI-2Sn-4Zr-2Mo Forming. Ti-1100 has limited cold formability and behaves similarly to Ti-6AI-2Sn-4Zr-2Mo in cold and hotforming. Although the a + ~ window is relatively small, the alloy has demonstrated superplasticity in a simulated manufacturing environment Machining. Ti-11oo machines essentially the same as Ti-6AI-2Sn-4Zr2Mo
Joining. Welding and brazing properties ofTi-1100 are similar to those of Ti-6AI-2Sn-4Zr-2Mo Rolling characteristics and texture formation are similar to Ti-6Al-2Sn4Zr-2Mo
Recommended Heat Treating Practice In surface treating, the alloy is expected to behave essentially as Ti-6AI2Sn-2Mo
Ti-1100 is designed for elevated-temperature use up to 600 "C (1110 "F), It was developed to be used primarily in the beta-processed (beta-worked or beta-annealed) condition. Ti-ll00 offers the highest combination of strength, creep resistance, fracture toughness, and stability of any commercially available titanium alloy. The two standard conditions recommended for the alloy are (1) beta processed (T> 1065 -c, 1950 oF) and annealed (T= 595°C, 1100 OF) and (2) alpha-beta processed; beta annealed (T> 1065 "C, 1950 "F) plus anneal (T= 595°C, 1100 OF). The alloy has only a slight response to cooling rate or section size from the solution treatment (or processing) temperature. Very rapid quenches increase strength and decrease elevated-temperature creep resistance. Ti1100 generally is used in the beta-processed or beta heat-treated condition, but it is provided in an equiaxed alpha-beta condition for the product forms to enhance processibility Ti-ll 00: Fracture toughness of beta forged and annealed material
Heat treatment
1095 °C (2000 oF),FAC + 595°C (1100 oF),8 h 1095 °C (2000 oF), OQ + 595°C (1100 oF),8 h 1l50°C (2100 oF),FAC+ 705 °C (1300 oF),8 h 1095 °C (2000 oF),FAC + 995°C (1825 oF), 1 h + 595°C (1100 oF),8 h 1095 °C (2000 oF), FAC+ 1095°C (2000 oF), 0.5h+595 °C (1100 oF),8h 995°C (1825 oF),FAC + 995°C (1825 oF), Ih+595 °C (1100 oF),8 h 995°C (1825 oF),FAC + 1095 °C (2000 oF), O.5h +595 °C(Il00°F), 8h
Fracture tougbness lKJ,,) Exposed at 650 oc (l200l Cor 300 h As~essed
MPa~
ksI'liii:'
62.9 63.7 53.5 64.1
57.2 57.9 48.7 58.3
43.5 40.2 45.7 53.2
39.6 36.6 41.6 48.4
71.0
64.6
48.3
43.9
39.4
35.8
30.3
27.5
75.9
69.0
44.4
40.4
MPa
0.04 Note: As expected, the alpha-beta heat treated material has the lowest fracture toughness
ksi'IiiL
.5041 Heat Treater's Guide: Nonferrous Alloys
IMI230 Ti-2.5Cu; AECMA Ti-P11 Chemical Composition. IMI 230 is a binary alloy containing 2.5 wt% copper. See Table for specification properties.
Characteristics Beta Transus. 895 ± 10 °C (1645 ± 20 oF) Product Forms. Available forms include billet, bar, rod, wire, extruded sections, and sheet. Sheet, extrusions, and bar for machining are supplied annealed, and solution treated (suitable for aging)
Applications. IMI 230 combines the formability and weldability of unalloyed titanium with improved mechanical properties, particularly at elevated temperatures. This alloy can be used at temperatures up to 350°C (660 oF) and is used in the annealed condition as sheet, forgings, and extrusions for fabricating components such as bypass ducts of gas turbine engines
Fabrication Properties Forging. IMI Titanium 230 is very easy to forge. A certain amount of forging in the alpha+beta field is required to develop optimum properties. The ideal forging preheating temperature is 800 to 820°C (1470 to 1510 "F), though a preheating temperature of 850 °C (1560 "F) is commonly used. It may, on occasion, be permissible to go as high as 875°C (1610 "F) for initial roughing operations, provided that a reduction of at least 2-fo-l or 4-to-l is subsequently carried out at the lower temperature. IMI 230 is an easier alloy to work than the well-known Ti-6AI-4V alloy at their recommended forging temperatures. Preheating time should be kept as short as possible consistent with uniform heating; as a rough guide, a preheating time of 0.5 h per 25 mm (1 in.) of section thickness should be allowed Welding. IMI 230 can be joined by fusion, resistance, flash-butt, and pressure welding. Fusion welds can be made by both argon-arc and elec-
tron-beam welding. With adequate control of welding techniques, welds of 100% strength can be obtained, with only a slight loss in tensile or bend ductility. If the alloy is to be used in the annealed condition, then welding should be followed by stress relieving for 0.5 h at 600°C (1110 "F)
Brazing. It is possible to make brazed joints, but difficulty arises owing to the formation ofbrittle intermetallic phases between the titanium and the filler metal Forming. Although forming operations are often performed prior to aging, IMI 230 may in fact be cold worked at any stage after solution treatment. The cold working of sheet after partial aging (24 h at 400°C, or 750 "F) or after duplex aging gives material which, when fully aged, has higher yield and tensile strength and only slightly lower ductility than if it had been cold worked in the solution-treated condition and then fully aged (see Table). Warm forming temperatures of 350°C (660 "F) or below are preferable, since they do not interfere with subsequent aging at 400 to 475 °C (750 to 890 oF). See Table for effect of cold working on aged properties
Recommended Heat Treating Practice IMI 230 has a structure consisting mainly of a supersaturated solid solution • of copper in alpha (close-packed hexagon) titanium in the solution-treated state. This structure is amenable to an age-hardening reaction similar to that in the conventional AI-Cu-Mg type of alloy. The aging treatment causes precipitation of a finely divided compound, ThCo, giving the usual strainhardening effect. Aging treatmentraises room-temperature tensile properties by about 25%, and almost doubles the elevated-temperature properties (e.g., creep at 200 "C), See Tables for recommended heat treatments and for typical room temperature properties of a variety of products in different heat treated conditions
IMI230: Specification properties Uhlmate tensile strength MPa ksi
Condition
andform
Annealed sheet STAsheet Annealed barandforging stock STAbarandforging stock
Spocllkalion
Bendmdlus
BSTA21 BSTA52 BSTA22 and23 BSTA53 and54
2T(max)(a) 2T(max)(a)
540-700 690-920 540-770 650-880
Thnsileyield strength (min) MPa ksi
78-101 100-133 78-lll 94-127
460 550 400
525
66.7 80 58 76
MInImum elongation,
Minimum
%
%
18(b) 10(b) 16(e) 10(e)
35 25
RA,
(a)BendradiusfromO.5to3 mm(0.0210 0.12in.)only.(b)Elongation on50 mm(2 in.)withthickness above0.9 mm(0.035in.).(c)Elongation on 5D
IMI230: Typical room-temperature properties IMI230 is relatively free from directionality apart from yield strength which is about 30 to 80 MPa (4 to 12 ksi)higher in the transverse direction.
Condition andform
Thkkness mm in.
Annealed sheet Solution treated sheet(transverse) STAsheet(e) STAsheet(transverse) Annealed bar Solution treated bar STAbar(e) STAbar Annealed exnuslon STAexbUsion
1.3
Bend mdlw
0.05 1.5T
1.3
0.05
13
0.5
13
0.5
2T
Uhlmate tensile strength ksi
MPa
620 620 770 770 655 630 793 740 630 790
90 90 112 112 95 91 115 107 91 115
0.1 %~.2 % tensile yield strength(a) \lsi MPa
480 510-530 585 650-660 480 500(d) 620 580 500 670
70 74-77(b) 85 94-96(b) 70 72
90 84(d) 72.5 97
Elongation, %
24 24 22 24 27 27 22 22 30 28
45 41 40 30
(a)0.1% yieldstressunlessnoted.(b)0.1 and0.2%yieldstress,respectively. (c)STAlreatment: 850°C (1560oF), plus24 h at 400 °C (750oF), 8 h 8t475 °C (890 oF), air cooled.(d)0.2%yieldstress
Alpha and Near-Alpha Alloys 1505 IMI230: Recommended heat treatments
IMI 230: Effectof cold working on aged properties
Thmpemture
0.1% proof stress MPa lid
Sheet
I. Solutiontreated(m 2. ST + 24 h/400·C 3. ST +duplexage 4.As 2 + 20%coldwork+ 8 h/475·C 5. As 2 + 30%coldwork+ 8 h/475·C 6.As 2 +40% coldwork+ 8h/475·C 7. As 3 +30%coldwork 8.As 3 + 30%coldwork+ 6h/475·C
550 580 685 810 800 780 895 700
Thnsilestrength MPa lid
80 84 99 117.5 116 113 130 101.5
630 690 820 900 900 880 955 865
Eiongalion on25mm(lo.) %
91 100 119 130 130 127.5 138.5 125
Trealmenl
Stressrelief Annealing Solutionheattreat Aging(frrststage)(b) Aging(secondstage)(b)
21 21 16 10 10 9 8 8
-c
·F
Dumlion
t:oollog method
600 675-785 850 400 475
1110 1250-1450(a) 1560 750 885
Ih 0.5102h(a) 0.5h 8h 8h
Air cool Aircool Forced air Air cool Air cool
(a) Annealingfrom 675 to 700·C (1245to 1290·F) is frequentlyusedfor fullannealing.Duration dependson product lhickness.(b) Two-stage aging is recommended
IMI417 Chemical Composition. IMI 417 is the general engineering version of
ofexcellent creep resistance, fatigue strength, and tensile strength/ductility. A target primary alpha content of 12 to 15% is recommended for solution treatment of IMI 417. This is equivalent to a heat treatment temperature of 1020 to 1025 °C (1875 to 1880 OF) for a typical transus approach curve. Current experience indicates that for sections exceeding 15 mm, highest tensile strength and creep resistance are obtained by heat treatment for 2 h at temperature followed by oil-quenching and aging at 700°C for 2 h, air cool. For optimum ductility after heat treatment, aging at 625°C for 2 h, air cool, is recommended. For thinner sections, air cooling or equivalent inert gas quenching after vacuum heat treatment is adequate.
the IMI 834 near-alpha alloy. The two alloys have identical composition specifications and are ideal for high-temperature (600°C, max) fatiguesensitive applications. See Table for typical composition range and density. See datasheet article on IMI834
Applications. Major uses include cast or wrought parts for turbine
ann
internal combustion engines. Product manufacture may differ for IMI 417 applications versus the aerospace IMI 834 alloy
See Table for effect ofprimary alpha content and aging on tensile properties
Recommended Heat Treating Practice Like IMI 834, the carbon addition in IMI 417. widens the a + Pphase field and thus allows solution treatment high in the a + Pfield for a combination
IM1417: Typical composition range (wt%) and density
Minimum Maximum Nominal
AI
Sn
Zr
Nb
Mo
5.5 6.1 5.8
3.0 5.0 4.0
3.0 5.0 3.5
0.5 1.0 0.7
0.25 0.75 0.5
SI
C
Fe
0,
N,
IL
0.20 0.6 0.35
0.04 0.08 0.06
0.05
0.075 0.150 0.10
0.G3
0.006
Compositionanddensityare identical10IMI 834
IM1417: Effect of primary alpha content and aging on tensile properties MelalJurgkaI condition Alpha phase, T
7.5
15
Room-temperature tensile properties E1ongallon Thoslle (5D) %
AgIng lempemlure, ·C
0.2% yield stress MPa
streogthMPa
625 700 625 700 750
943 957 949 945 942
1092 1086 1086 1079 1058
15 12 14 12 12
Reduction 10...... %
l00-h total plastic strain, %. al: 700·C and 50 MPa 6OO·C and 125 MPa 600 OCand 150 MPa
32 22 31 23 17
0.130 0.072 0.136 0.082
0.110 0.054 0.054
0.193 0.151 0.146
5061 Heat Treater's Guide: Nonferrous Alloys
IMI679 Ti-11 Sn-5Zr-2.25AI-1 Mo-O.25Si Chemical Composition. See Table for typical composition ranges and density
Fabrication Properties
Characteristics
Forging and machining properties are comparable to those ofTi-8Al-IMo1V. Welding is not recommended
Phases and Structures. The combination of low-aluminum, mediumzirconium, and high-tin strengthens and stabilizes the alpha phase. Considerable strengthening at all temperatures is derived from the active eutectoid compound TixSiy . The alloy may be classified as both a weakly stabilized, martensitic alloy and an active eutectoid. It displays the isothermal transformation characteristics of two-phase titanium alloys.
Forging. To develop optimum mechanical properties, hot working should be restricted to the alpha+beta+compound field and a maximum temperature of925 °C (1695 OF) is recommended. The normal preheating temperature for forging is 900 to 920°C (1650 to 1690 "F),
See Ti-Si diagram and time-temperature transformation diagram
Recommended Heat Treating Practice
Prime Transus/Beta Transus. The alloy has a prime transus of 870 to 890°C (1600 to 1635 OF), and a beta transus of 950 ± 10 °C (1740 ± 20 "F) Applications. IMI 679 is a high-temperature alloy for jet engine components, but has been superseded by other alloys such as Ti-6242S. IMI679 has a maximum use temperature of about 450°C (840 OF) and appears to be metallurgically stable up to 455 °C (850 OF). For comparable products in the annealed condition, the strength of IMI 679 from room temperature to 540°C (1000 OF) exceeds that of Ti-6AI-4V and Ti-8AI-IMo-IV and is about equal to Ti-6AI-2Sn-4Zr-2Mo. Its creep strength is superior to Ti-8Al- lMo-lV and Ti-6AI-4V at all temperatures, but inferior to Ti-6Al2Sn-4Zr-2Mo at temperatures above 480°C (900 "F), At elevated temperatures, this alloy is less fatigue resistant than Ti-8Al-lMo-IV and Ti-6Al2Sn-4Zr-2Mo.
See Figure for resistance to deformation
Solution treatment at 900 °C (1650 OF), followed by air cooling and aging 24 h at 500°C (930 OF), has been found to produce the best combination of creep strength and ductility. Faster cooling from solution-treatment temperature by oil quenching significantly increases the tensile strength while slightly decreasing ductility. Thin sections, such as gas-turbine compressor blades, are usually air cooled and aged; thicker sections, such as discs and spacer rings, are more usually oil quenched and aged. Above 450°C (840 OF), creep strength of oil-quenched material is slightly lower than that of air-cooled material. See Tables for recommended heat treatments and for minimum tensile properties at room temperature obtained with aging and different quenching practices.
See Figure for tensile properties as a function of thermal exposure IMI 679: Typical composition range (wt%) and density AI
Minimum Maximum Nominal
2.0 2.5 2.25
Sn
Zr
Mo
Si
Fe
10.5 11.5 11.0
4.0 6.0 5.0
0.8 1.2 1.0
0.10 0.50 0.25
0.20
Ti
N,
C
0.20
0.125 bal
3
DensityofIMI 679 is 4.84 glcm (0.175Ib/in.J)
IMI 679: Minimum tensile properties at room temperature
CondJlion
Rulingsection IDOl in.
Oil quenchedandaged:
50(a) 2(a)
900°CIWQ, 500 °CJ24h1AC Aircooledandaged:900 75(b) 3(b) °ClAC,500°CJ24
Minimum
Minimum
ultimate tensile strength
tensUeyleld strength
IMI-679: n-si diagram
elongation
Click here to view
MPa
ksi
MPa
ksi
%
RA %
1110
161
970
140
8
25
1030(c)149(c)
LIVE GRAPH
Minimum
150 0 1300
2500
880(c) 127(c)
8
30
»: ./
o
/'
°ai 1100 :;
hlAC
~ Q)
(a)Bar,forgingstock,andforgingsperBSTA18,19,and20,respectively. (b)Bar,forgingstock,and forgingsper BSTA25, 26, and 27, respectively. (c) Slightlylowervalues arequoted in AMS 4974 andMIL-T-9047D
g-
~
a+p 900
........
I ----/
V
'Iemperature
Stressrelief Solutiontreatment Aging
c.
E Q) 1500 t-
o °C
OF
Duration
Cooling method
480-510 900
900-950 1650
5toIOh lto2h
500
930
24h
Aircool Air cool or oil quench Aircool
:::I
~Q)
al 700 a+ TIsSi3
f
Treatment
p + Ti sSi3
1000
50 0
IMI 679: Recommended heat treatments
u..
°
2000 ~
1
2
Weight percent silicon
3
Alpha and Near-Alpha Alloys I 507
LIVE GRAPH
IM1679: Time-temperature transformation diagram
Click here to view 100o All beta
I
-1 800
I 1730 OF
I
900
u+ f3 + Compound
~ .
u'transus _
I .: ---\ -, -. ...Y'~
:
o
°i :J
800 ~ Q)
c.
E Q)
.
700
I
I
f3-7U
I-
-1 700 ,
,
-1 600 Start
LL I
-1 500 Finish
I I I
!5
I
~Q)
i
-1 400 ~
c. E
i
! u + f3 + Compound
\
°c»
-1 300
I
1
i
I
600
o
<,
'\.
10
I
!
I
I
20
40
30
Ms
-,
-1 200
50
Time, min
LIVE GRAPH
IM1679: Resistance to deformation
Click here to view -270 300
-180
Degrees from optimum temperature, 8°F -90
o
IMI834
IMI829 IMI685
40
---------
-100
-50 Degrees from optimum temperature, 8°C
90
o
5081 Heat Treater's Guide: Nonferrous Alloys
IM1679: Tensileproperties as a functionofthermal exposure. Solutiontreated,air cooled,and aged bar: 900°C (1650 OF) for 2 h, AC, plus 500°C (930 OF) for 24 h, AC. Each point an averageof ten tests on 6.35 mm (0.25 in.) specimen
600
700
800
Exposure and test temperature, of 900 1000
1100
1200
I
1100
Exposure lime Unexposed 0.25 hr 10hr 100 hr 1000 hr
• 0 0
900
{;
..
UTS
-1 40
- 120
OJ
0.. ~
:=:::::::::::::'--
lZ
-- -- -
I!! 700
1ii Q)
l...-
~
c:
{!!.
Yield slrenglh
- 1001ii Q)
-;:::.~
~
c:
""Cl t-.
eo
500
~
0
~~ I.
{!!. 'Q
0
{;
~=
i
-8 o
<, "0-
-.....
""' Q....
-, -6o
<,
Q.... 300 400
300
700
600
500 Exposure and lesllemperalure, °c
LIVE GRAPH
(8)
Click here to view
600
500 100
. 0
8 Ol-
D {;
.. '#.
700
Exposure lime Unexposed 0.25 hr 10 hr 100 hr 1000 hr
60
1100
1200
1300
/ 0/
/
RA
.. ..
~ U :::J Cl
Exposure and lesllemperalure, of 800 900 1000
{;
~ ..
.---
/~
/
40 I
/ ,..0
.--- 0.---
Elongalion
20
-4>
•
0
o 250
(b)
350
450 550 Exposure and lesllemperalure, °c
LIVE GRAPH Click here to view
~
650
750
Alpha and Near-Alpha Alloys I 509
IMI68S Ti-6AI-5Zr-O.5Mo-O.25Si density
per heat are likely, alpha-beta forging from 980 to 1000 °C (1795 to 1830 oF) is recommended.
Characteristics
Preheat times in the beta field should be the minimum necessary for uniform soaking of the material prior to forging
Chemical Composition. See Table for typical composition range and
Applications. IMI 685 is an alloy developed to meet aerospace-engine requirements. It was the first of the near-alpha alloys, and represented a significant step forward in combining good creep strength, weldability, and ease of working
Welding. The alloy can be joined by the processes normally used in the fabrication of titanium, including argon-arc, electron-beam, and friction welding. Material should be fully heat treated prior to welding, and also given a suitable postweld treatment (for example, 4 to 8 h at 550°C). The weld zone of material treated in this way will have similar structure, and hence similar properties, to those of the parent metal
Fabrication Properties
Recommended Heat Treating Practice
Forging. The aim is to provide a material which on subsequent treatment in the beta field recrystallizes to a fine uniform beta grain structure of average grain sizes less than 1.5 mm.
See Tables for typical room temperature tensile properties, per product form and heat treatment, for the effect of cooling rate on room temperature properties after aging, for recommended solution treating and aging (STA) treatment for optimum creep resistance, and for the effect of cooling rate on creep resistance and post-creep tensile properties after aging.
Preheating in the beta field at temperatures up to 20 to 30°C (35 to 55 "F) above the beta transus is permissible provided sufficient work is introduced per heat to avoid undesirable grain coarsening effects. If small reductions
IM1685: Typical composition range (wt%) and density AI
Zr
Mo
81
Fe
C
0,
N,
IL
5.7 6.3 6
4.5 6.0 5
0.25 0.75 0.50
0.15 0.35 0.25
0.05
0.08
0.20
0.03
0.01
Minimum Maximum Nominal
'11
bal
Density ofIMI 685 is 4.45 glcm 3 (0.161Ib/in?)
IM1685: Effect of cooling rate on room-temperature tensile properties after aging 'Il!nsiIe strength
Heat treatment
MPa
kst
MPa
kst
1050 °C. OQwithin 15 s 1050 °C, delay 30 S, OQ 1050 °C. delay 60 S, OQ 1050°C,AC
924 881 873 858
134 128 126.5 124
1060 1030
153 149 145 142.5
0.2% yieldstre..
1000 983
Elongation on5D%
Reduction in area %
Notched\ensilemtioKt = 3
10
22 26 25 20
1.64 1.62 1.62 1.65
10 10
10
IMI685 rod: Typical tensile properties vs. temperature. Beta heat treated rod 1000 Tensile strength
os
Q.
:::;
110~ Ql
e
1001;;
1ij
0-2% proof stres 90
600
80
LIVE GRAPH 0
~
'iii
c
'#.
~20 1) ::>
0
Ql
t-
400
30
"iii -"
c
~
C Ql
130 120
800
~ c 'iii
40
140
l-
10
LIVE GRAPH
70
Click here to view 200
400
Temperature. °C
60 600
I Elongation on 501
0 0
Click here to view 200
400 Temperature, °C
600
510 IHeat Treater's Guide: Nonferrous Alloys IM1685: Effectof cooling rate on creep resistance and post-creep tensile properties after aging Heal treatment
'Ibtal plastic straln % in 100 h, 310 MPa a1520 ·C
1050·COQ within15s 1050·C, delay 30s.0Q 1050·C. delay 6Os.OQ
0.2 yield stress MPa ksi
'Iensile strength MPa ksi
0.041
920
133
1010
0.053
920
133
0.055
890
129
Elongation Reduction onSD In area
%
%
146.5
13
20
1000
145
11
19
990
143.5
11
19
IM1685: Recommended STA heat treatment for optimum creep resistance 'Iempemture Treatment
Solutiontreatment Aging
0C
OF
Duration
Coating method
1050 550
1920 1020
30 min per 25 mm (I in.) of thickness 24 hours
Oil quench(a) Air cool
(a)The transfertime betweenfurnace and oil bath should not be prolonged. Amaximum of 15to 30 s, dependingon part mass. is recommended
IMI829 Ti-5AI-3.5Sn-3.0Zr-1 Nb-O.3Si Common Name. Ti-5331S Chemical Composition. For high creep resistance, IMI 829 is lean in beta stabilizers. Hardenability is limited. Property levels are good in sections up to about 75 mm (3 in.) thick.
High Temperature Strength. IMI 829 is regarded as having good creep performance up to around 550°C (1020 "F) and somewhat higher for short-time applications. At 540 °C (1000 "F) a total plastic strain of less than 0.1 % in 100 h is achieved under a stress of about 300 MPa (43.5 ksi)
Fabrication Properties
See Table for typical composition range and density
Casting. IMI 829 is an excellent casting alloy because it is designed to be
Characteristics Phases and Microstructure. IIi the beta solution treated aged condition, the alloy has a microstructure of acicular transformed beta with a grain size typically -0.5 mm (0.02 in.), The alphalbeta to beta transus temperature for 1M! 829 is 10 15°C ± 10 °C (1860 OF ± 20 oF) Product Forms. The alloy is available in the form of bar, billet, plate, sheet, wire, and castings Applications. IMI 829 is a near-alpha alloy of medium strength and high-temperature capability up to -540°C (1000 OF). IMI 829 develops its properties from a combination of solid-solution strengthening and "beta" heat treatment which produces an acicular transformed structure.
used in the microstructural condition analogous to casting (i.e., beta heat treated). Cast properties approach, or are better than, those of wrought products
Forging. IMI 829 is readily forgeable by conventional hammer, press, or isothermal forging. Its flow stress is a little higher than most other titanium alloys and forging temperature must not be allowed to drop excessively. Typical forging temperature is 1000 °C (1830 oF) Forming. IMI 829 can be superplastically formed although it requires a relatively high temperature to achieve the required two-phase microstructure (at about 975°C, or 1785 OF) Welding. IMI 829 is weldable using all of the normal techniques for titanium. Properties of welds are comparable with those of the parent metal
Discs and blades in aerospace compressors represent the major use
Recommended Heat Treating Practice
Mechanical Properties Hardness. Heat treated IMI 829 is typically 320 HV (20 kg) or 32 HRC Notch Tensile Ratio. Typically 1.6 (K t =3) Fracture Toughness. Typically -75 MPa-frll (68 ksiVin.)
Parts are typically beta solution treated. The treatment consists of 30 min at 1050 °C (1920 "F), followed by oil quenching. Aging is at 625°C (1155 OF) for 2 h, followed by air cooling. Air cooling is recommended when parts are under 30 mm (1.2 in.) in diameter. See Table for recommended heat treatments.
IMI 829: Room-temperature tensile properties Property
IMI 829: Recommended heat treatments
Typical
MinImum
860(125) 950(142)
820(119) 930(135) 9 15
'Iempemture
0.2% PSMPa (ksi) D.T.S.MPa (ksi) El(5D)% Reductionin area %
11
19
Treatment
Solutiontreatment Aging
-c
·F
Duralion
Coating method
1050 625
1920 1155
0.5h 2h
Oil quench(a) Air cool
(a) For sections less than 30 mm (1.25 in.), aircooling is recommended
Discs. -75 mm (3 in.)ruling section, heat treated
IM1829: Typicalcomposition range (wt%) and density
Minimum Maximum Nominal
AI
So
Zr
Nb
Mo
51
Oz
Nl
lL
5.2 5.7 5.6
3.0 4.0 3.5
2.5 3.5 3.0
0.7 1.3 1.0
0.20 0.35 0.25
0.20 0.50 0.30
0.09 0.15 0.115
0.03
0.0060
Density of1Ml829 is 4.54 glcm3 (0.1641b/in.J)
Alpha and Near-Alpha Alloys I 511
IM1829: Typical tensile properties vs, temperature. Heat-treated disc forging -75 mm (3 in.) ruling section
LIVE GRAPH
LIVE GRAPH Click here to view 100
200
l'"
900
r1.
::<
I\. 800
m700
-,
1il
1000
1200 140
,
<,
!
<, <,
600
120
i
J"-.....
'iii
c
(!!. 500
Te nslle strength
......
I
400
i
v;
1 00 ~ 1il
~I
r--- ---J I
.~ 80
0.2%P~ s ress
~
'iii
cQ)
i
40
i
100
200
300 400 500 Temperature, °C
600
0
60
700
:/
I
I
./
I
~
~
V
o o
,
in area
I !
:
100
~ctlon
~
i
10
200
1300
1046
:,
, 0
t-
I
300
o
284
30 50
Click here to view
Temperature, of 538 792
I I
e
~
Temperature. OF 400 600 800
300 400 500 Temperature, °C
t:longallon
600
700
IMI834 Ti-5.8AI-4Sn-3.5Zr-D. 7Nb-D.5Mo-D.35Si Chemical Composition. IMI 834 has a low beta stabilizer content and therefore has limited hardenability. It retains a good level of properties in sections up to around 75 mm (3 in.) diameter, with small reductions in strength in larger sections.
temperatures. Typically, the alloy has less than 0.1 % total plastic strain in 100 h at 600°C (1110 "F) under a stress of150 MPa (21.8 ksi). See Figure for tensile properties at different temperatures
See Table for composition range and density
Fabrication Properties
Characteristics
Casting. IMI 834 can be cast using the normal techniques developed for titanium alloys. Typical tensile properties at room temperature and at 600 °C (1110 OF) are given in Tables. Cast IMI 834 has lower tensile ductility than the alpha-beta wrought product but has better creep performance
Product Forms. The alloy is available as bar, billet, plate, sheet, wire, and castings Applications. The alloy has medium strength (typically 1050 MPa, or 152 ksi) and temperature capability up to about 600°C (1110 OF) combined with good fatigue resistance. Compressor discs and blades for the aerospace industry are the main applications
Mechanical Properties Hardness. Heat treated IMI 834 typically has a hardness of 350 HV (20 kg load) or about 35 HRC Notch Tensile Ratio. Typically 1.5 (Kt = 3) Impact Strength. Typical Charpy (Usnotch) impact strength is 15 J (11 ft . Ibf) at room temperature Fracture Toughness. Typically 45 MPa'-'ll1(40 ksi-.Jin.) in heat treated discs.
Forging. IMI 834 is readily forgeable using conventional hammer, press, or isothermal techniques. Typical forging temperature is around 1010 °C (1850 OF). IMI 834 is stiffer than most other titanium alloys, but it has good forgeability at its recommended forging temperature. See Table for flow stress at different temperatures; welding. All established titanium welding techniques may be used
Forming. IMI 834 has very limited cold formability, but good hot formability. It can be fabricated in sheet and plate form. Typical sheet properties are shown in an adjoining Table. Superplastic forming is also possible at about 990°C (1815 OF)
Recommended Heat Treating Practice
See Figure for Young's modulus (dynamic)
The alloy derives its properties from solid-solution strengthening, and heat treatment high in the alpha+beta phase field. The addition of carbon facilitates treatment by widening the heat treatment window.
High Temperature Strength. IMI 834 has useful strength up to 600 °C (1110 OF) and provides long term creep performance up to around 600°C (1110 "F) and good short term performance up to significantly higher
IMI 834 is normally alpha+beta solution treated. See Tables for recommended solution treating and aging treatments, and for typical tensile properties after recommended solution treating and aging treatments.
512/ Heat Treater's Guide: Nonferrous Alloys
IM1834: Typical composition range (wt%) and density
Minimum Maximum Nominal
AI
Sn
Zr
Nb
Mo
Si
C
Fe
Oz
N,
lh
5.5 6.1 5.8
3.0 5.0 4.0
3.0 5.0 3.5
0.5 1.0 0.7
0.25 0.75 0.5
0.20 0.60 0.35
0.04 0.08 0.06
0.05
0.Q75 0.150 0.10
0.03
0.006
Density ofIMI 834 is 4.55 glcm3 (O.I64lb/in.~
Cast IMI 834: Tensile properties at 600°C
Cast IMI 834: Room-temperature tensile properties Yield strength Bar condition
(0.2%) MPa ksi
Cast+«(l+~)Hll'+ 1070°C
944
137.0
Ulllmate teosile strength MPa ksi 1071
Reduction Elongation in area
155.4
%
%
5
7
Yield strength condition Cast+(a+~)Hll'+
Ullimate tensile strength ksi MPa
(0.2%)
Bar
1070°C
Eiongatlon,
Reduction tn area,
%
%
MPa
ksl
526
76.3
663
96.2
6
16
515 467 472 518
74.7 67.8 68.5 75.2
669 566 575 682
97.1 82.1 83.5 99.0
10 6 7 23
29 16 16 52
AC+2h7oo°C
AC+2h7oo°C 966 898 901 950
Cast + ~Hll' + 2 h 700 °C Wrought(15%alpha)OQ + 2 h 700 °C 50 mm bar(2 in.)
140.2 130.3 130.8 137.9
1072 1040 1025 1070
155.6 147.2 148.8 155.2
5 6 4 13
9 10 9 23
Cast+ ~Hll'+2h7oo°C Wrought(15%alpha)OQ + 2 h 700 °C 50 mm (2 in.) bar
IMI 834: Typical tensile properties after recommended heat treatment (STA)
IMI 834: Recommended heat treatments Thmpemlure
Roomtemperature
600°C
1110OF
Treatment
950(138) 1050(152) 12
520 650 20 50
(75.4) (94.3)
Solutiontreatment(15%alpha) Aging
0.2% MPa (ksi) U.T.S.MPa (ksi) Elongation(in 50), % Reductionin area, %
20
1015±5 700
1860±9 1290
Dumtion
Cooling method
2h 2h
Oil quench(a)
Air cool
(a) For sectionsless than about IS mm (0.6 in.), air cooling is recommended
IMI 834: Properties of 2 mm sheet Yield strength Material condition(a) Room-temperature properties RoUed+ *Annealed(800 "C) *1025 °C(aI~)AC+2h7oo°C *1060°C(~)AC+2h7oo°C
(0.2%)
Ultimate tensile strength MPa ksi
Creep
Elongation (SOmm),
sIrain(h),
%
%
OrienlatloDS
MPa
ksl
L T L T L T
996 1014 998 1009 947 963
144.6 147.2 144.8 146.4 137.4 139.8
1114 U20 U45 Ull 1098 1103
161.7 162.5 166.2 161.2 159.4 160.1
U.5 12 U.5 11 6 6
L T L T L T
473 510 518 546 554 532
68.7 74.0 75.2 79.2 80.4 77.2
671 720 702 728 716 729
97.4 104.5 11.6 105.7 103.9 105.8
18 14 16 18 12 12
High-temperature (600 0c) properties RoUed+ *Annealed(800 "C) *1025°C (aI~)AC+2h 700°C *1060°C(~)AC+2h7oo°C
(a) An asterisk * indicatesa heating durationonOminutes. (b) Totalplastic strainafter exposureof 150MPa (21.8 ksi) at 600 °C (1110 "F) for 100 hours
0.213 0.247 0.055 0.064
Alpha and Near-Alpha Alloys I 513
IMI834: Beta approach curve. Betatransusapproach curvesof IMI 834, IMI829, andTi-6AI-4V LIVE GRAPH Click here to view
IM1834:Young's modulus (dynamic). The dynamicmodulusof IMI 834 is typical of other near-alphatitaniumalloys. Heat treated bar Temperature, of
200
1800 100
400
600
800 1000 1200 1400
130
18.85 'iii
os
'i- 95
c.
D.
e
ai
E
vi 110
'0 > 90
:; 'C o
~
15.95
IMI834
:>
:>
vi
:>
's '0 0
E
E
o
s: c.
~ m
0
.~ 90
13.05 'E
os c: >. 0
c:
85
tJ
80'-
---' 1000
980
1020
LIVE GRAPH Click here to view
70'-
o
1060
1040
~
200
400
--' 10.15 800
600
Ternperature.f'O
Temperature, °C
IM1834: Typical tensile properties. Heat treateddiscs
LIVE GRAPH
LIVE GRAPH Click here to view
Click here to view
Temperature, of
200
400
600
800
1000
1200
50 Reduction in area
40
Elongation
10
------------
O'-_...L-_--'-_---'_ _.L..-_...J...._--'-_----I
o
100
200
300
400
500
600
700
Temperature, °C
(b)
IMI 834: Flow stress. As-rolledbar tested with a plastometerup to 1100°C (2010 OF) at a strain rate of 15/s
Temperature, of
1700
1600 300
1800
1900
2000 i
JMI829
-1 40
j I
~
r::
~30 ~ i
§
i
~
, I
OJ U
~20 ~
Ti·6AI·4V
1~
-110 .-
I,
:fl
II:
LIVE GRAPH Click here to view
0'----
850
--'0
900
950
1000
Temperature, °C
1050
1100
Commercially Pure and Modified Titanium Unalloyed Titanium, ASTM Grade 1, UNS R50250 Chemical Composition. This grade has impurity limits of 0.180,0.20 Fe, 0.03 N, and 0.10 C wt.% max. The other three grades of unalloyed titanium, by comparison, are classified in terms of their mechanical properties because small variations in interstitial properties may raise yield strengths above maximum permitted values or lower ductility below minimum specifications. Hydrogen content as low as 30 to 40 ppm can induce severe hydrogen embrittlement in all grades of CP titanium.
Characteristics Among the four grades, Grade 1 has the highest purity, lowest strength, and best room temperature ductility and formability. It should be used where maximum formability is required and where low iron and interstitial contents might enhance resistance to corrosion. This grade has excellent resistance to corrosion in highly oxidizing to mildly reducing environments, including chlorides. Grade 1 can be used in continuous service up to 425°C (795 OF) and in intermittent service up to 540 °C (1000 OF). In addition, it has good impact properties at low temperatures. Grade 1 is available in all wrought forms; and like other grades of titanium, it can be welded, machined, cold worked, hot worked, and cast. Typically,
this grade has an annealed alpha structure in wrought, cast, and PIM forms. Yield strength is comparable to that of fully annealed 304 stainless steel.
Applications Typical uses are in chemical, marine, and similar applications. The list includes heat exchangers, components for chemical processing and desalination equipment, condenser tubing, pickling baskets, and anodes ofvarious types. In the chemical and engineering industries, grade 1 is an ideal material for a wide variety ofchemical reactor vessels because ofresistance to attack by seawater, moist chlorine, moist metallic chlorides, chlorite, and hypochlorite solutions, nitric, and chromic acids. However, Grade 1 lacks resistance to biofouling.
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595°C (900 to 1100 OF); times range from 15 min to 4 h; air cooling or step cooling processes are used Annealing. Temperatures range from 650 to 760°C (1200 to 1400 OF); times range from 6 min to 2 h; parts are air cooled
Commercially pure (99%) titanium sheet: As-rolled to 1 mm (0.040 in.) at 760°C (1400 OF). Alpha grains have been equiaxed by cold working. Kroll's reagent (ASTM 192). 250x
Unalloyed titanium grade 1 compositions: Producer specifications Specillcalion
Designation
Description
Contimet30
C
Fe
H
N
0
Si
OE
OT
Other
Germany DeutscheT Fuchs Japan Daido Kobe Kobe Kobe Kobe Kobe
Sh StrpPltBarWrr Frg Pip Frg
0.06
015
0.13
0.05
0.12
baITi
T2
DTI KS40 KS40LF KS40S KS50 KS50LF
RodBar ShStrpFrgAnn Sh StrpThPitWrrBarPipAnn LowFe grade Ann Ann Low Fe grade
0.1
0.2 0.1 0.05 0.1 0.15 0.05
0.0125 0.01 0.01 0,01 0.01 0,01
0.03 0.03 0.03 0.03 0.03 0.03
0.18 0.1 0.1 0.08 0.15 0.15
baITi baITi baITI baITi baITi baITi
Sumitomo
ST-40
(continued)
468/ Heat Treater's Guide: Nonferrous Alloys Unalloyed titanium grade 1 compositions: Producer specifications (continued) SpeclIkation
Desigoallon
Description
UK Imp.Metal Imp.Metal
IMIllO IMI1l5
OE
or
C
Fe
H
N
0
Rod Allfonns
0.1
0.2
0.013
0.03
0.15
Ti99.8 balTi
Chemical/marine/airframe apps
0.08
0.2
0.015
0.03
0.18
balTi
0.1 max
0.02 max
0.15 max
0.03 max
0.18 max
balTi
0.03 max 0.05 0.05 0.1
0.1 max 0.2 0.2 0.2
0.005 max 0.012 max 0.008 0.02 0.008 0.02 0.015 0.03
0.1 max 0.1 0.1-0.15 0.18
balTi balTi balTi balTi
0.05
0.15
0.015
0.03
0.15 0.2 0.2 0.2
Sl
Otber
USA
ChaseExI. OREMEI RMI Tel.Rodney 1MCA UNS UNS UNS UNS
CDXGR-l TI-l RMI25 A35 TIMEfAL35A TI-l R50100 R50120 R50125 R50250
China GB3620
TA-l
TIMEr
Ann
balTi
0.1
Europe AECMAprEN2525 AECMAprIN3441 AECMAprEN3487
0.6 0.6 0.6
balTi balTi balTi
POI POI POI
ShSlIp ShSlIpAnnHR ShSlIpAnnCR
0.08 0.08 0.08
0.2 0.2 0.2
0.0125 0.0125 0.0125
0.05 0.05 0.05
T-35
Sh Strp
0.08
0.12
om
0.05
3.7025 3.7025 3.7025 3.7025 3.7025
PII Sh Strp Rod Wir Frg Ann Sh Strp Pit Rod Wrr FrgAnn ShSlIp Rod WIre Frg
0.08 0.08 0.08 0.08 0.08 0.08
0.2 0.2 0.2 0.2 0.2 0.2
0.013 0.013 0.013 0.013 0.013 0.013
0.05 0.05 0.05 0.05 0.05 0.05
0.1 0.1 0.1 0.1 0.1 0.1
balTi balTi balTi balTi balTi balTi
TIClass 1 TP28H1CClass 1 TR28H1CCIass 1 TTP28DIE Class 1 TTP28WIWDClass 1 TTH28D Class 1 TTH28WIWDClass I TB28aH Class 1 TW28Class 1
HRCRSh HRCrSlIp SmIspipe As-weldlweld & drawn pipe SmIs tube for heat excn Weld tube for heat exch HWCDBar WIre
0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2
0.015 0.013 0.013 0.015 0.015 0.015 0.015 0.015 0.015
0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05
0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.15 0.15
balTi balTi balTi balTi balTi balTi balTi balTi balTi
0.006 0.008 0.3 0.001 0.3 0.3 0.2
0.04 0.04 0.015 0.004
0.12 0.15 0.04 0.15 0.04 0.04 0.04
0.1
balTi balTi balTi balTi balTi balTi
0.1 0.1 0.1
Fmnce AIR 9182
balTi
0.04
Germany DIN 17850 DIN 17850 DIN 17860 DIN 17862 DIN 17863 DIN 17864 Japan nsClass I nsH4600 nsH4600 nsH4630 nsH4630 nsH4631 nsH4631 nsH4650 nsH4670
Til
Russia WeIdel WeIdel All forms
0.12 0.03 0.1 0.03 0.05 0.05 0.05
om om
OST 1.90013-71
VTl..()()
Sh PIIStrp Foil Rod Frg Ann
UK BS2TA.l
2TA.l
ShSlIpHT
0.2
0.01
BarBiI
0.2
0.013 0.005 0.015 0.015 0.015 0.015 0.015 0.01-0.0125 0.015 0.0125 0.0125 0.0125 0.0125 0.01250.015 0.005 0.008 0.008 0.015 0.015 0.015
DTD5013
0.008
0.15 0.15 0.15 0.15
0.15 0.15 0.15
0.1
0.08
0.1 Ti99.78 min' balTi
USA AMS4951E ASMESB-265 ASMESB-381 ASTM B265-79 ASTMB337-87 ASTM B338-87 ASTM B348-87 ASTMB381-87 ASTM F467-84a ASTMF467M-84b ASTMF468-84a ASTMF468M-84b ASTMF67-88
AMS4951 TIGradeI F-l TIGradel TIGradel TIGradel TIGrade 1 F-l TIGradel TIGradeI TIGradel TIGradeI TIGradeI
Fill met gas-mel W arc weld Sh Strp PltAnn FrgAnn Sh Strp Plr Ann Weld smIs pipeAnn SmIs weld tube Exch Conds Ann Bar Bil Ann FrgAnn NUl Metric Nut Boll Screw Stud Metric Boll Screw Stud SurgimpHWCWFrgAnn
0.08 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1
0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2
AWSA5.16-70 AWSA5.16-70 AWSA5.16-70 MIL T-81556A MIL T-81915A MILT-0946J
EIm-l EIm-2 EIm-3
Weld ftIl met Weld ftIl met Weldftllmet EXIBar Shap Ann
0.03 0.05 0.05 0.08 0.08 0.08
0.1 0.2 0.2 0.2 0.2 0.2
CF4
Invesr Cast CF4
Sh StrpPit Ann
0.05 0.03 0.03 0.03 0.03 0.03 0.03 0.03 0.05 0.05 0.05 0.05 0.03
0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18 0.18
0.012 0.02 0.Q2 0.05 0.05 0.05
0.1 0.1 0.1-0.15 0.15 0.2 0.15
0.1 0.1
0.6 0.4 0.4 0.4 0.4 0.4 0.4 0.4
0.3 0.6 0.3
balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi
Commercially Pure and Modified Titanium I 469
Unalloyed Titanium, ASTM Grade 2, UNS R50400 Chemical Composition. This grade has same nitrogen content as Grade
Grade 2 can be welded, machined, cast, and cold worked. It is available in all wrought product forms; has an annealed alpha structure in wrought, cast, and PIM forms; is not heat treatable.
1 (0.030% max), the same iron content limits as Grade 3 (0.30% max), and a maximum oxygen concentration of 0.25%, which is about midway between the 0.18 to 0.40% range for the other three ASTM grades.
Applications
Effectof Impurities. Increased iron and oxygen concentrations,compared
The list of typical uses includes airframe skin and nonstructural components, heat exchangers, cryogenic vessels, components for chemical processing and desalination equipment, condenser tubing, pickling baskets, anodes, shafting, pumps, vessels, and piping systems. Major applications are in aircraft, reaction vessels and heat exchangers, and electrochemical processing equipment. Reaction vessels and heat exchangers are major applications because of the material's resistance to attack by seawater, moist chloride, moist metallic chlorides, chlorite and hypochlorite solutions, nitric and chromic acids, organic acids, sulfides, and many industrial gaseous atmospheres. The insulating property of the anodic film on titanium makes Grade 2 an ideal and cost efficient material for anodizing jig and plating baskets. Related applications include high efficiency, heat exchanger systems for electrolytes.
with those of Grade I, impart additional tensile strength (345 vs. 240 MPa, or 50 vs. 35 ksi) and yield strength (275 vs. 170 MPa, or 40 vs. 25 ksi) to Grade 2, but the gain is at the expense of ductility (20% elongation for Grade 2 vs. 24% for Grade 1). Higher iron and interstitial contents also may degrade corrosion resistance in comparison with that of Grade 1. Further, hydrogen content as low as 30 to 40 ppm can induce hydrogen embrittlement.
Characteristics Grade 2 is the workhorse in industrial applications, having a combination of a guaranteed minimum yield strength of 275 MPa (40 ksi), good ductility, and good formability. Yield strength is comparable to that of annealed austenitic stainless steel. It is the choice where excellent formability is required and where low interstitials might enhance resistance to corrosion.
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595°C (900 to ] 100 OF); time ranges from 15 min to 4 h; air cooling or step cooling processes are used
Impact properties at low temperatures are good; resistance to erosion and corrosion by seawater and marine atmospheres is excellent. The material can be used in continuous service at temperatures up to 425°C (795 OF) and in intermittent service up to 540 °C (1000 "F),
Annealing. Temperatures range from 650 to 760°C (1200 to 1400 oF); time ranges from 6 min to 2 h; cooling is in air
Unalloyed titanium grade 2 compositions: Producer specifications Spedllcatlon France Ugine Ugine Germany OtloFuchs Thyssen Thyssen Japan Daido Kobe Kobe Nippon Sumitomo Sumitomo Thho Toho Toho Toho
Designation
Description
lIT35 UT40
C
Fe
H
N
0
Sh PItBarFrgAnn Sh PitBarFrgAnn
0.08 0.08
0.25
0.0125 0.0125
0.05 0.06
0.2 0.25
balTi balTi
T3 Contimel35 Contirnel35D
Frg ShSIJpPItBarWrrPipAnn MultformsAnn
0.06 0.06
0.2 0.25
0.013 0.013
0.05 0.05
0.18 0.25
TI99.5 balTi balTi
DT2 KS60 KS60LF
RodBarShSIJpFrgAnn ShSIJpThbPitWrrBarPiAnn Low FeAnn
0.1
0.3 0.3 0.05 0.5
0.0125 0,0) 0.01
0.03 0.03 0.03 0.1
0.2 0.2 0.2 0.2
balTi balTi balTI balTi
0.1 0.05 0.15 0.05
0.005 0.005 0.005 0.005
0,0)5 0,0) 0.D2 0.01
0.15 0.15 0.25 0.25
TI99.7 min TI99.7 min TI99.6 min TI 99.6 min
T1X
Si
OR
OT
Olher
ST-50 ST6 TIB TIBLF TIC TICLF
Low Fe
0.03 0.D2 0.03 0.02
lMl125 lMl130
Multforms ShBar
0.1 0.1
0.2 0.2
0.013 0.013
0.03 0.Q3
0.2 0.25
balTI balTi
RMl40 A40
MultformsAnn
0.08
0.25
0,0)5
0.03
0.2
balTi
TIMErALSOA
Ann
0.08max
0.2 max
LowFe
UK Imp.MetaI Imp.MetaI
USA Chase Ext.
OREMET RMl
TeI.Rodney TIMEr TMCA
CDXGR-2 TI-2
TI2
0.0125max 0.05max
balTi
470 I Heat Treater's Guide: Nonferrous Alloys
Unalloyed titanium grade 2 and equivalents: Specifications and compositions Specilleation
Designation
UNS UNS
R50130 R50400
Description
C
Fe
H
N
0
0.05 0.1
OJ OJ
0.008 0.D15
0.D2 0.03
0.15-0.25 0.25
0.1 max
0.3 max
0.015 max
0.05 max
0.2 max
0.08 0.08 max 0.08 max 0.08 max 0.08 max 0.08 max 0.08 max 0.08 max
0.2 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max
0.D1 0.0125 max 0.0125 max 0.0125 max 0.0125 max 0.0125 max 0.0125 max 0.0125 max
0.06 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max
0.25 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max 0.25 max
0.08 0.08
0.12 0.12
0.D15 0.D15
0.05 0.05
0.08 0.1 0.08 0.1 0.08 max 0.08 max 0.08 max 0.08 max 0.08 0.08
0.25 0.3 0.25 0.3 0.25 max 0.25 max 0.25 max 0.25 max 0.2 0.25
0.013 0.013 0.013 0.013 0.013 max 0.013 max 0.013 max 0.013 max 0.0125 0.0125
0.06 0.06 0.06 0.06 0.06 max 0.06 max 0.06 max 0.06 max 0.05 0.06
0.2 0.25 0.2 0.25 0.2 max 0.2 max 0.2 max 0.2 max 0.2 0.25
0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25
0.D15 0.015 0.013 0.013 0.D15 0.D15 0.D15 0.D15 0.D15
0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05
0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2
Si
OE
OT
Other
balTI baITI
China GB3620
TA-2
baITI
0.15 max
Europe AECMAprEN2518 AECMAprEN2526 AECMAprEN3378 AECMAprEN3442 AECMAprEN3451 AECMAprEN3452 AECMAprEN3460 AECMAprEN3498
TI-P02 TI-P02 TI-P02 TI-P02 TI-P02 TI-P02 TI-P02 TI-P02
ShSIrpBar Sh Strp Wif ShSIrpAnnHR FrgNHf FrgAnn Bar Ann Sh Strp Ann CR
T-35 T-40
ShCR Sh
TIll TIrn WL3.7035 WL3.7055 3.7035 3.7035 3.7035 3.7035
Sh Strp Pit Rod Wir Frg Ann Sh Strp Pit Rod Wif Frg Ann Pit Sh Strp Rod wuFrg Ann Sh Plt Strp Rod Wif Frg Ann ShSIrp Rod Wif Frg Sh Wir Ann Sh Bar Frg Wif Ann
0.1 max 0.1 max 0.1 max 0.1 max 0.1 max 0.1 max 0.1 max
0.6 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max
baITI balTI balTI balTI balTI baITI balTI balTI
France AlR9182 AlR9182
TI99.69min TI99..69 min
0.04 0.04
Germany DIN 17850 DIN 17850 DIN 17850 DIN 17850 DIN 17860 DIN 17862 DIN 17863 DIN 17864 WL3.7024 WL3.7034
0.6 0.6
baITI baITI baITi balTI balTi balTi baITi baITI balTI balTI
Japan TISH436 I nSH4600 TISH4600 nSH4630 TISH4630 TISH4631 TISH4650 TISH4670
Class 2 TfH 35D Class 2 TP35 HlC Class 2 TR 35 HlC Class 2 TTP 35 DIE Class 2 TTP35 WfWD Class 2 TfH 35 WfWD Class 2 TB 35 CJHClass 2 TW35Class2
SmlsThb ShHRCR SIrpHRCR SmlsPip Weld Pip WeldThb Bar Rod HW CD Wif
VTI-O VTlL
Mult Forms Ann Cast
0.07 0.15
0.3 0.3
0.D1 0.D15
0.04 0.05
0.2 0.2
L-7001 L-7002
ShPlt Strp Bar Wir Ext Ann Sh Pit Snp Bar Wir Ext Ann
0.08 0.08
0.2 0.25
0.0125 0.0125
0.05 0.05
0.2 0.25
2TA,3 2TA,4 2TA,5
ShSIrpHf BarHT FrgHT FrgHT Thb
0.D1max 0.D1max
0.2 0.2 0.2 0.2 max 0.2 max
0.D1 0.D1 0.01 0.015 max O.oI5 max
0.08 0.1 0.1 0.1 max 0.1 max 0.1 0.1
0.3 0.2 0.3 0.3 max 0.3 max 0.3 0.3
0.D15 0.D15 0.D15 O.oI5max 0.D15max 0.D15 0.D15
0.05 0.05 0.03 0.03 max 0.03 max 0.03 0.03
0.2 0.25 0.25 0.25 max 0.25 max 0.25 0.25
0.1 0.1 max 0.1 0.1 max 0.1 max 0.1 max 0.1 max 0.1 0.05 0.08 0.08 0.08
0.3 0.2 max 0.3 0.3 max 0.3 max 0.3 max 0.3 max 0.3 0.3 0.3 0.2 0.3
0.0125-0.01 0.015 max O.oI5 0.0125 max 0.0125 max 0.0125 max 0.0125 max 0.015-0.0125 0.008 0.D15 0.D15 0.D15
0.03 0.05 max 0.03 0.05 max 0.05 max 0.05 max 0.05 max 0.03 0.02 0.05 0.05 0.05
0.25 0.4 max 0.25 0.25 max 0.25 max 0.25 max 0.25 max 0.25 0.15-0.25 0.2 0.2 0.2
baITi balTI baITI balTi balTi balTI balTi balTI balTI
Russia OST 1.90000-76 OST 1.90060-72
0.1 0.15
0.3 0.3
baITI WO.2;baITI
Spain UNE 38-7 II UNE38-712
balTI baITI
UK BS2TA.2 BS2TA,3 BS2TA.4 BS2TA.5 DTD5073
Ti 99.78 min Ti 99.78 min Ti 99.79 min TI99.78 min balTl
USA AMS4902E AMS4941C ASM4942C ASMESB-265 ASMESB-381 AS1MB265 AS1MB337 AS1MB338 AS1MB348 AS1MB367-87 AS1MB381 AS1MF467-84 AS1MF467M-84a AS1MF468-84 AS1MF468M-84b ASTMF67 AWSAS.16-70 MIL T-81556A MlLT-81915 MlLT-9046J
ShStrpPltAnn
TlGrade2 F-2 TIGrade2 TI Grade 2 TI Grade 2 TI Grade 2 11 Grade 2 11 GradeF-2 TIGrade2 TI Grade 2 11 Grade 2 TI Grade 2 11Grade 2 EIITi-4 CodeCP-3 'JYpeICompA CodeCP-3
WeidThbAnn SmlsThbeAnn ShSIrpPltAnn FrgAnn Sh Strp Pit Ann PipAnn Tubefor heat exchlcond BarBilAnn Cast FrgAnn NUl Nut Met Bit Scr Sid BltScrStdMet SurgimpHWCWFrgAnn Weld Fill Met ExtBar ShpAnn Air/chern/marine apps CastAnn Sh StrpPltAnn
0.1 max 0.1 max
0.1 max
0.3 0.15 0.3 0.4 max 0.4 max 0.4 0.4 0.4 0.4 max
0.3 0.6 0.3
balTI baITI baITI baITI balTi balTI balTI balTI baITI balTI balTI balTI baITI baITI baITI baITI baITI balTI baITi balTi
Commercially Pure and Modified Titanium /471
Unalloyed Titanium, ASTM Grade 3, UNS R50550 Chemical Composition. Iron limits are lower than those for Grade 4 (0.3 wt% vs. 0.5 wt% max); and of the four unalloyed grades, has the highest oxygen content (0.35 wt%). Only Grade 4 has higher strength levels. Excessive impurities may raise yield strength above maximum permitted values and reduce elongation or reduction in area below minimum values. Higher iron and interstitial contents can affect corrosion resistance. Hydrogen content as low as 30 to 40 ppm can induce hydrogen embrittlement.
Characteristics Grade 3 is the general purpose grade of unalloyed titanium, combining excellent resistance to corrosion in highly oxidizing to mildly reducing environments, including chlorides, and an excellent strength to weight ratio. Like other titanium metals and alloys, it bridges the gap between steel and aluminum and provides many of the desirable properties of each. Another plus: good impact toughness at low temperatures.
Applications Nonstructural aircraft parts and a variety of other parts requiring resistance to corrosion are typical applications. The list includes chemical and marine applications, airframe skin and nonstructural components, heat exchangers, cryogenic vessels, components for chemical processing and desalination equipment, condenser tubing, and pickling baskets. Grade 3 is available in all wrought product forms, and can be welded, machined, and cast. Most forming operations are at room temperature. Warm forming reduces springback and power requirements.
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595°C (900 to 1100 OF); times range from 15 min to 4 h; air cooling or step cooling processes are used Annealing. Temperatures range from 650 to 760°C (1200 to 1400 oF); times range from 6 min to 2 h; cooling is in air
Unalloyed titanium grade 3 and equivalents: Specifications and compositions Specilkation
Designation
UNS
R50550
Description
C
Fe
B
0.1
0.3
0.08 0.1 0.1 0.1 max 0.1 max 0.1 max 0.1 max
Si
.OE
OT
Other
0.4
baITi
N
0
0,015
0.05
0.35
0.25
0.015
0.07
0.35 0.35 0.3 max 0.3 max 0.3 max 0.3 max
0.013 0.013 0.013 max 0.013 max 0.013 max 0.013 max
0.07 0.07 0.06 max 0.06 max 0.06 max 0.06 max
0.3 0.3 0.25 max 0.25 max 0.25 max 0.25 max
baITi baITi baITi baITi baITi baITi
0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3
0,015 0.013 0.013 0,015 0,015 0.015 0.015 0,015 0.015
0.07 0.07 0.07 0.07 0.07 0.07 0.07 0,07 0.07
0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3
baITi baITi baITi baITi baITi baITi baITi baITi baITi
0.2 0.2 0.2 0.2 0.2 max 0.2 max 0.2 max
0.01 0.01 0.01 0.015 0.0125 max 0.0125 max 0.0125 max
France AIR9182
T-50
ShAnn
'TIN WL3.7065 3.7055 3.7055 3.7055 3.7055
Sh Strp PItRod Wir FIg Ann Pit Sh Strp Rod WII'Frg Ann ShStrp Rod WII' Frg
Gas, 3 TP49 HlC Class 3 TR49 HlCClass 3 TTP49 DIE Gass 3 TTP49 WIWD Class 3 TIH 49 D Class 3 TIH 49 WIWD Class 3 1'849 CIH Class 3 TW49 Class 3
ShHRCR StrpHRCR SmIs Pip Hot Ext CD Weld Pip SmlsThbCD WeldThb BarHWCD WII'
0.04
Ti99.54min
Germany DIN 17850 DIN 17850 DIN17860 DIN 17862 DIN 17863 DIN 17864 Japan
ns llSH4600 llSH4600 nSH4630 llSH4630 llSH4631 llSH4631 nSH4650 nSH4670
UK BS2TA.6 BS2TA.7 BS2TA.8 BS2TA.9 DTD5023 DTD5273 DTD5283
ShStrpHT BarHT Frg FrgHT ShStrp Bar Frg
Ti99.78 min Ti 99.78 min Ti99.79min Ti 99.78 min baITi baITi baITi
USA AMS4900J AMS 495 IE ASMESB-265 ASMESB-381 ASTMB265 ASTMB337 ASTMB338 ASTMB348 ASTMB381 ASTMB367-87 ASTMF67 MIL T-81556A MILT-9046J
Grade 3 F-3 Grade 3 Grade 3 Grade 3 Grade 3 GradeF-3 C-3 Grade 3 CodeCP-2 CodeCP-2
ShStrpPltAnn WeldWII' Sh StrpPlt Ann FrgAnn Sh StrpPltAnn Weld SmIs Pip Ann Smls WeldTub Ann BarBilAnn FrgAnn Cast Surglmp ExtBarShpAnn Sh Strp PltAnn
0.08 0.08 max 0.1 max 0.1 max 0.1 0.1 0.1 0.1 0.1 0.1 max 0.1 0.08 0.08
0.3 0.015 0.2 max 0.005 max 0.3 max 0.015 max 0.3 max 0.015 max 0.3 0.015 0.3 0.015 0.3 0.015 0.3 0.0125 0,015 0.3 0.25 max 0.Dl5max 0.3 0.015-0.0125 0.3 0.015 0.3 0.015
0.05 0.05 max 0.05 max 0.05 max 0.05 0.05 0.05 0.05 0.05 0.05 max 0.05 0.05 0.05
0.3 0.18 max 0.35 max 0.35 max 0.35 0.35 0.35 0.35 0.35 0.4 max 0.35 0.3 0.3
0.1 max 0.1 max 0.1 max
0.1 max
0.3 0.6 max 0.4 max 0.4 max 0.4 0.4 0.4 0.4 0.4 0.4 max 0.3 0.3
baITi baITi baITi baITi baITi baITi baITi baITi baITi baITi baITi baITi baITi
472/ Heat Treater's Guide: Nonferrous Alloys Unalloyed titanium grade 3 compositions: Producer specifications Specification
Deslgnatlon
Deouiption
UTSO
OE
OT
Other
C
Fe
H
N
0
ShBarFrgAnn
0.08
0.25
0.0125
0.G7
0.35
haiTI
SI
France Ugine Germany Thyssen TItan Japan Daido Kobe Kobe Sumitomo Toho
Conlimet55 lIT 20
MultFonnsAnn
0.06 0.1
0.3 0.35
0.013 0.013
0.05 0.07
0.35 0.3
haiTI haiTI
DT3 KS70 KS70LF ST-70 TID
MultFonns Ann Ann I.AJw FeMultFonns Ann
0.1
0.3 0.3 0.05
0.0125 0.Gl 0.Gl
0.05 0.05 0.05
0.35 0.3 0.3
haiTI haiTI haiTI
0.05
0.2
0.01
0.04
0.3
TI99.4min
UK Imp. Metal
lMI130
0.08
0.25
0.Gl5
0.05
0.3
haiTI
O.Imax
0.2 max
0.015max
0.05max
0.35 max
haiTI
USA O1aseExt
CDXGR-32 TI-3 RMI RMI55 Tel.Rodney A55 TIMETAL65A TIMET TI3 TMCA OREMEr
MultFonns Ann Ann
Unalloyed Titanium, Grade 4, UNS R50700 Chemical Composition. Of the four unalloyed grades, this one is the highest in oxygen content (0.40 wt%) and iron content (0.50 wt%). Higher iron content and interstitials can reduce corrosion resistance. Also, hydrogen content as low as 30 to 40 ppm can induce hydrogen embrittlement.
Characteristics
Grade 4 typically has an annealed alpha structure in wrought, cast, and PIM forms. Because of its excellent resistance to corrosion and erosion, this grade has a wide range of chemical and marine applications where it is often used interchangeably with Grade 3. It can be in continuous service at temperatures up to 425°C (795 "F), and intermittent service up to 540°C (1000
This grade, strongest of the four unalloyed grades, also provides good ductility and fair formability. Strengthllightness benefits are retained at moderate temperatures. The strength-to-weight ratio is higher than that of AISI type 301 stainless steel at temperatures up to 315°C (600 "F), Resistance to corrosion fatigue in salt water is outstanding. Stress required to cause failure (several millions of cycles) is 50% higher vs. that for K-Monel or AISI type 431 stainless steel.
oF).
Grade 4 is available in all product forms, and can be machined, cast, welded, and cold worked. Forming generally is at room temperature. Warm forming at 150 to 425°C (300 to 795 "F) reduces springback and power requirements. Warm forming is required for complex shapes.
times range from 6 min to 2 h; cooling is in air
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595 °C (900 to 1100 "F); times range from 15 min to 4 h; air cooling or step cooling processes are used
Annealing. Temperatures range from 650 to 760°C (1200 to 1400 "F);
Commercially Pure and Modified Titanium /473 Unalloyed titanium grade 4 commercialequivalents:Compositions SpeeUkaIIoo
Franc:e Ugine Germany 0110 Fuchs Japan Daido Kobe Sumitomo UK Imp. Metal Imp. Metal USA ChaseExI.
Crucible OREMEl' RMI Tel. Rodney TIMEr TIMEr TMCA
C
Fe
H
N
0
0.1
0.35
0.0125
0.Q7
0.4
Si
OK
OT
Otber
Deslgnation
Descriplion
Uf60
Bw:FrgSI1 PItAnn
T6
Frg
DT4 KS85 ST-80
BarRodSl1pFrg Ann SI1 StrpPitWrrBarAnn
0.1
0.5 0.4
0.0125 0.Ql
0.05 0.05
0.5 0.4
balTi balTi
IMI 155 IMII60
SI1 RodBarBilWrr
0.1 0.1
0.2 0.2
0.013 0.017
0.03 0.05
0.38 0.4
balTi balTi
CDXGR-4 A-70 Ti-4 RMI70 A40 Ti-75A TIMErAL lOOA Ti4
Ann
Ti99
0.Q7 max
0.05-0.15
balTi
0.08
0.5
0.Ql5
0.05
0.4
balTi
0.1 max 0.Ql max
0.3 max 0.3 max
O.ol5 max O.ol max
0.05 max
0.4 max 0.4 max
balTi balTi
MultFormsAnn Ann Ann
balTi
Unalloyed titanium grade 4 and equivalents:Specifications and compositions Speellkation
Deslgnation
UNS China GB36W Europe AECMAprEN2519 AECMAprEN2520 AECMAprEN2527 AECMAprEN3443 AECMAprEN3453 AECMAprEN3461 AECMAprEN3496 AECMAprEN3499 France AIR 9182 Germany DIN DIN 17860 DIN 17862 DIN 17863 DIN 17864 Spain UNE38-714 UK BS2TA6 BS2TA7 BS2TA8 BS2TA9 USA AMS490IL AMS492IF ASTMB265 ASTMB348 ASTMB367 ASTMB367 ASTMB381 ASTMF467-84 ASTMF468-84 ASTMF67 MlLF-83 142 MILT-81556A MlLT-9046J MILT-9047-G MlLT-9047G
RS0700
Description
TA-3 Ti-P04 Ti-P04 Ti-P04 Ti-P04 Ti-P04 Ti-P04 Ti-P04 Ti-P04
BarFrg SI1 Strp Frg ShStrp StrpShAnnCR FrgNHT BarAnn FrgAnn ShStrpAnnCR
T-60
ShAnn
3.7064 3.7065 3.7065 3.7065 3.7065
ShRodBarFrg Ann SI1Strp Rod Wrr Frg
L-7004
MultFormsAnn ShStrp Bar Frg
C
Fe
B
N
0
0.1
0.5
O.ol5
0.05
0.4
0.1 max
0.4 max
0.015max
0.05 max
0.3 max
0.08 0.08 max 0.08 max 0.08 max 0.08max 0.08 max 0.08 max 0.08 max
0.35 0.2 max 0.2 max 0.2 max 0.2 max 0.2 max 0.2 max 0.2 max
0.01-0.0125 0.0125 max 0.0125 max 0.0125max 0.0125max 0.0125max 0.0125 max 0.0125max
0.07 0,07max 0.07 max 0.07 max 0.07max 0.07max 0.07 max 0.07 max
0.4 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max
0.08
0.3
O.ol5
0.08
0.08 0.1 max 0.1 max 0.1 max 0.1 max
0.35 0.35 max 0.35 max 0.35 max 0.35 max
0.0125 0.013 max 0.013 max 0.013 max 0.013 max
0.Q7 0.07max 0.07 max 0.07 max 0,07 max
0.4 0.3 max 0.3 max 0.3 max 0.3 max
balTi balT! balTi balTi balTi
0.1
0.4
0.0125
0.Q7
0.4
balTi
0.08 max 0.08 max 0.08 max
0.2 max 0.2 max 0.2 max 0.2 max
0.0125max 0.0125max 0.Ql max 0.015 max
0.08 0.08 0.1 0.1 0.1 0.1 0.1 0.1 max 0.1 max 0.1 0.08 0.08 0.08 0.08 max 0.08
0.5 0.5 0.5 0.5 0.2 0.25 0.5 0.5 max 0.5 max 0.5 0.5 0.5 0.5 0.5 max 0.5
O.ol5 0.0125 O.ol5 0.0125-0.ol O.ol5 O.ol5 O.ol5 0.0125max 0.0125max 0.015-0.0125 0.0125 O.ol5 O.ol5 0.Ql5max 0.0125
Frg
Grade4 Grade4 GradeC-2 GradeC-3 GradeF-4 Grade4 Grade4 Grade4 Compl CodeCP-I CodeCP-I SP-70 Ti-CP-70
ShStrpPltAnn BarWrrFrgBilRngAnn ShPlt StrpAnn BarBilAnn Cast Cast FrgAnn Nut BltScrwStd SI1StrpBarHRCRAnnFrg FrgAnn ExtBarSlIpAnn ShStrpPltAnn Bar BarBilAnn
Si
OK
OT
Other
0.4
balT! balTi
0.15 max
0.1 max 0.1 max 0.1 max 0.1 max 0.1 max 0.1 max 0.1 max
0.6 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max 0.6 max
0.04
balTi balTi balTi balTi balTi balTi balTi balTi Ti 99.56min
balTi balTi balTi balTi 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.07 max 0.07max 0.05 0.05 0.05 0.05 0.05 max 0.05
0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 max 0.4 max 0.4 0.4 0.4 0.4 0.4 max 0.4 max
0.3 0.3 0.4 0.4 0.4 0.4 0.4
0.3 0.3 0.3 0.3 max 0.3
balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi balTi YO.OO5;baITi
474/ Heat Treater's Guide: Nonferrous Alloys
Modified Ti (Ti-O.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Chemical Composition. A relatively small addition of palladium(0.15 to 0.20 wt%) permits the use of unalloyed titanium in stronger reducing media, such as mild sulfuric and hydrochloric acids.
Higher oxygen content (0.25 wt%) and higher iron content (0.30 wt%) in the Grade 7 alloy reduces ductility and cold formability, but provides higher strength than Grade 11, which has a maximum oxygen content of 0.18 wt% and a maximum iron content of 0.20 wt%. Hydrogen as low as 30 to 40 ppm hydrogen can induce embrittlement of both grades.
Characteristics These two grades have better resistance to crevice corrosion at low pH and elevated temperatures than ASTM Grades 1,2, and 12, and are recommended for chemical industry applications when environments are moderately reducing or fluctuate between oxidizing and reducing. Palladium content extends the range of titanium applications in hydrochloric, phosphoric, and sulfuric acid solutions. Fabrication and welding properties of the two grades, along with their strength properties, are similar to those of corresponding grades of unalloyed titanium. Grade 7 is comparable to Grade 2 in strength, while Grade 11 is comparable to Grade 1 in strength.
Both grades are available as flat rolled products, extrusions, wire, tubing, and pipe. They can be cast, welded, machined, and hot worked. Most forming operations are at room temperature. Warm forming is done at 150 to 425°C (300 to 795 OF). Both grades have annealed alpha structures.
Applications Typically, applications are for chemical industry equipment and where requirements for corrosion resistance are special. Good cold formability is another plus. Cold pressed plate/frame heat exchangers and chlor-alkali anodes are examples. Both grades can be used in continuous service up to 425°C (795 "F) and in intermittent service up to 540 °C (1000 OF).
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595°C (900 to 1105 OF); times range from 15 min to 4 h; air cooling or step cooling processes are used Annealing. Temperatures range from 650 to 760°C (1200 to 1400 "F); times range from 6 min to 2 h; cooling is in air
Ti-O.2Pdgrades 7 and 11 compositions: Producer specifications Spe
OT
C
Fe
R
N
0
Pd
Sh Pit Bar FrgAnn
0.08
0.2
0.015
0.05
0.2
0.2
baITi
Contimet Pd 02130 Contimet Pd 02135 Contimet Pd 02135 D RT 12(Pd) RTI5(Pd) RT 18(Pd)
Mult Forms Ann MultFormsAnn MultFormsAnn Sh Strp Bar Frg
0.06 0.06 0.06 0.08 0.08 0.1
0.15 0.2 0.25 0.2 0.25 0.3
0.013 0.013 0.013 0.013 0.013 0.013
0.05 0.05 0.05 0.05 0.06 0.06
0.12 0.18 0.25 0.1 0.2 0.25
0.15-0.25 0.15·0.25 0.15-0.25 0.15-0.25 0.15-0.25 0.15-0.25
baITi baITi baITi baITi baITi baITi
KS40PdA KS40PdB KS50PdA KS50PdB KS70PdA KS70PdB ST-40P ST-50P ST-60P
MultFormsAnn MultFormsAnn MultFormsAnn Mult Forms Ann MultForms Ann MultFormsAnn
0.05 0.05 0.05 0.05 0.05 0.05
0.01 0.01 0.01 0,01 0.01 0.01
0.03 0.03 0.03 0.03 0.05 0.05
0.1 0.1 0.15 0.15 0.3 0.3
0.12-0.2 0.17-0.25 0.12-0.2 0.17-0.25 0.12-0.2 0.17-0.25
baITi baITi baITi baI11 baITi baITi
0.05 0.08 0.05 0.08
0.005 0.005 0.005 0.005
0.01 0.015 0.01 0.015
0.1 0.15 0.1 0.15
0.15 min 0.15 min 0.2 min 0.2 min
baITi baITi baITi baITi
0.15 0.15
baITi baITi
0.2
baITi
Designation
Description
Uf35-02
Si
Other
France Ugine Germany
Deursche T DeutscheT DeutscheT
DeutscheT DeutscheT DeUlscheT
Frg
Japan Kobe Kobe Kobe Kobe Kobe Kobe Sumitomo Sumitomo Sumitomo Toho Toho Toho Toho
15PfJ
0.02 0.03 0.02 0.03
15PBT 20PfJ 20PBT
UK Imp. MetaI Imp. MetaI
1MI260 1MI262
Sh Mult Forms
USA Crucible OREMET OREMET RM1 TIMEr TIMEr TIMEr TMCA TMCA
A-40Pd 11·11 11-17 RMIO.2%Pd Ti-0.2Pd TIMErAL35APd TIMErAL50APd Ti-7 Ti-11
MultFormsAnn
0.08
0.3
0.015
0.03
0.2
Commercially Pure and Modified Titanium I 475
Ti-O.2Pd grades7 and 11 andequivalents: Specifications and compositions Spedflc8lion
De
Description
C
Fe
H
N
0
Pd
UNS UNS UNS Germany DIN 17851 DIN 17851 DIN 17851 Japan TIS H 4635 type 11 TIS H 4635 type 11 TIS H 4635 type 11 TISH4635 type 11 TIS H 4635 type 12 TIS H 4635 type 12 TISH4635 type 12 TIS H 4635 type 12 TIS H 4635 type 13 TIS H 4635 type 13 TIS H 4635 type 13 TIS H 4635 type 13 TIS H 4636 type 11 TIS H 4636 type 11 TIS H 4636 type 11 TIS H4636 type 12 TIS H 4636 type 12 TIS H 4636 type 12 TIS H 4636 type 13 TIS H 4636 type 13 ns H 4636 type 13 TIS H 4655 type 11 TIS H 4655 type 11 TISH4655 type 12 TISH4655 type 12 TIS H 4655 type 13 TIS H 4655 type 13 TIS H 4675 type 11 TIS H 4675 type 12 TISH4675 type 13 Russia
R52250 R52400 R52401
Grade 11 Grade7 Filler
0.1 0.1 0.05
0.2 0.3 0.25
0.015 Om5 0.008
0.D3 0.D3 0.02
0.18 0.25 0.15
0.12-0.25 0.12-0.25 0.15-0.25
0.06 max 0.06 max 0.06 max
0.15 max 0.2 max 0.25 max
0.0013 max 0.0013 max 0.0013max
0.05 max 0.05 max 0.05 max
0.12 max 0.18 max 0.25 max
0.12-0.25 0.12-0.25 0.12-0.25
0.2 max 0.2 max 0.2 max 0.2 max 0.25 max 0.25 max 0.25 max 0.25 max 0.3 max 0.3 max 0.3 max 0.3 max 0.2 max 0.2 max 0.2 max 0.25 max 0.25 max 0.25 max 0.3 max 0.3 max 0.3 max 0.2 max 0.2 max 0.25 max 0.25 max 0.3 max 0.3 max 0.2 max 0.25 max 0.3 max
0.015 max Om5 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max 0.015 max
0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.D7 max 0.D7 max 0.07 max 0.07 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.05 max 0.07 max 0.07 max 0.07 max 0.05 max 0.05 max 0.05 max 0.05 max 0.07 max 0.07 max 0.05 max 0.05 max 0.07 max
0.15 max 0.15 max 0.15 max 0.15 max 0.2 max 0.2 max 0.2 max 0.2 max 0.3 max 0.3 max 0.3 max 0.3 max 0.15 max 0.15 max 0.15 max 0.2 max 0.2 max 0.2 max 0.3 max 0.3 max 0.3 max 0.15 max 0.15 max 0.2 max 0.2 max 0.3 max 0.3 max 0.15 max 0.2 max 0.25 max
0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25
0.Q7
0.18
0.01
0.04
0.12
0.15-0.3
3.7225 3.7235 3.7255 TIP28PdD TIP28PdE TIP28PdW TIP28PdWD TIP35PdD TIP35PdE TIP35PdW TIP35PdWD TIP49PdD TIP49PdE TIP49PdW TIP49PdWD TIH28PdD TIH28PdW TIH28PdWD TIH35PdD TIH35PdW TIH35PdWD TIH49PdD TIH49PdW TIH49PdWD TB28PdC TB28PdH TB35PdC TB35PdH TB49PdC TB49PdH TW28Pd TW35Pd TW49Pd
SmlsPipCD SmlsPipHE WeldPip WeldPip CD SmlsPip CD SmlsPip HE WeldPip WeldPip CD SmlsPip CD SmlsPipHE WeldPip WeldPip CD SmlsPip CD WeldPip WeldPip CD SmlsPipCD WeldPip WeldPipCD SmlsPip CD WeldPip WeldPipCD Rod BarCD RodBarHW BarRod CD BarRodHW BarRod CD BarRodHW WIT WIT WIT
4200 Spain UNE38-715
1.-7021
Sh Pit Sup Bar Wrr ExtAnn
0.08
0.25
0.0125
0.05
0.25
0.12-0.25
USA ASTMB265 ASTMB265 ASTMB337 ASTMB337 ASTMB338 ASTMB338 ASTMB348 ASTMB348 ASTMB367 ASTMB381 ASTMB381 ASTMF467-84 ASTM F467M-84a ASTMF468-84 ASTMF468M-84b AWSA5.16-70
Grade 11 Grade7 Grade 11 Grade7 Grade 11 Grade7 grade 11 Grade7 GradeTI-Pd7B GradeF-11 GradeF-7 Grade7 Grade7 Grade7 Grade7 ERTi-O.2Pd
ShPltSIIp Ann Sh StrpPltAnn SmlsWeldPip WidSmlsPip Ann SmlsWeldThbAnn SmlsWeldThbAnn BarBilAnn BarBilAnn Cast FrgAnn FrgAnn Nut MetNut BitScrwStd Met Bit Scrw Std WeldFillMet
0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.1 max 0.1 max 0.1 max 0.1 max 0.05
0.2 0.3 0.2 0.3 0.2 0.3 0.2 0.3 0.2 0.2 0.3 0.3 max 0.3 max 0.3 max 0.3 max 0.25
0.015 0.015 0.015 0.015 0.015 0.015 0.0125-0.01 0.0125 0.015 0.015 0.015 0.0125 max 0.0125 max 0.0125 max 0.0125 max 0.008
0.D3 0.D3 0.D3 0.D3 0.D3 0.D3 0.03 0.03 0.05 0.D3 0.D3 0.05 max 0.05 max 0.05 max 0.05 max 0.02
0.18 0.25 0.18 0.25 0.18 0.25 0.18 0.25 0.4 0.18 0.25 0.25 max 0.25 max 0.25 max 0.25 max 0.15
0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.12-0.25 0.15·0.25
Si
OT
Other
balTi balTI balTI 0.4 max 0.4 max 0.4 max
balTI balTI balTi balTi balTI balTI balTI balTi balTi balTI balTI balTi balTi balTI balTi balTi balTi balTi balTi balTi balTi balTi balTI balTi balTi balTI balTi balTI balTI. balTI balTI balTI balTi
0.1
0.3
balTi balTI
0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
balTi balTi balTI balTI balTI balTi balTI balTI balTI balTI balTi balTI balTi balTi balTI balTI
476/ Heat Treater's Guide: Nonferrous Alloys
Modified Titanium Sheet (Ti-o.2Pd): Hot rolled with starting temperature of 760°C (1400 OF), annealed for 2 h at 705°C (1300 OF), and slowly cooled. Equiaxed grains of alpha; iron-stabilized beta (black dots). 2 mL HF, 10 mL HNOa, 88 mL Hp. 250x
Ti..O..3Mo",O..8Ni, ASTM Grade 12, R53400 Chemical Composition. See adjoining Table for specifications, designations, product forms, and compositions, and adjoining Table for international specifications, designations, product forms, and compositions. Except for a lower carbon content (0.08 wt% vs. 0.0 wt% max), Grade 12 has allowable nitrogen, carbon, hydrogen, iron, and oxygen levels comparable to those of Grade 2 and Grade 7. Grade 12's titanium content is lowered through the addition of two beta stabilizers, molybdenum and nickel. Also, hydrogen content as low as 30 to 40 ppm can induce hydrogen embrittlernent
Characteristics Designed for corrosion resistant applications, Grade 12 is superior to unalloyed titanium in several respects, including: better resistance at lower cost to corrosion in hot brines (protection is similar to that provided by Ti-Pd); better resistance to corrosion in acids than the unalloyed grades (but less resistance, in this instance, than Ti-Pd); and significantly greater strength than unalloyed grades in high temperature, high pressure applications. The last named advantage often permits use of thinner wall sections in pressure vessels and piping. Grade 12 has less resistance than Ti-Pd to crevice corrosion resistance at low pH «3 pH). In near neutral brines, crevice corrosion properties are similar to those of Ti-Pd. Grade 12 products typically have an annealed alpha structure. Tensile and yield strengths are higher than those Of Grade 2 and Grade 7. Tensile and yield strengths are double those of Grade 11.
Applications Grade 12 is typically used where moderate strength and enhanced resistance to corrosion are needed, such as in equipment for the chemical and marine industries. Suitable environments include seawater, brines, moist chlorine at temperature above 120°C (250 OF), hot process streams containing chlorides where crevices may be present, oxidizing acids, dilute reducing acids, and combinations of the preceding conditions with hot, brackish, or saline cooling waters. Applications include heat exchangers, pressure vessels, chlorine cells, salt evaporators, piping, and pollution control equipment.
Fabrication Properties This grade is readily forged and can be cold worked on equipment used for stainless steels. It is available in all wrought forms, and can be cast, welded, and machined.
Recommended Heat Treating Practice Stress Relieving. Temperatures range from 480 to 595 °C (900 to 1100 OF); times range from 15 min to 4 h; air cooling or step cooling processes are used Annealing. Temperatures range from 650 to 760°C (1200 to 1400 "F); times range from 6 min to 2 h; cooling is in air
Ti-O.3Mo-O.8Ni grade 12 and equivalents: Specifications and compositions Specification
Designation
UNS
R53400
Description
C
Fe
H
Mo
N
Nl
0
0.08
0.3
0.D15
0.2-0.4
0.03
0.6-0.9
0.25
0.08 0.08 0.08 0.08 0.08
0.3 0.3 0.3 0.3 0.3
0.D15 0.D15 0.D15 0.0125 0.D15
0.2-0.4 0.2 0.2-0.4 0.2-0.4 0.2-0.4
0.03 0.03 0.03 0.03 0.03
0.6-0.9 0.6-0.9 0.6-0.9 0.6-0.9 0.6-0.9
0.25 0.25 0.25 0.25 0.25
OT
Other
balTi
USA ASTMB265 ASTMB337 ASTMB338 ASTMB348 ASTMB381
Grade 12 Grade 12 Grade 12 Grade 12 GradeF-12
Sh Strp PItAnn Smls WeldPip Ann Smls WeldThb Ann Bar Bill Ann FrgAnn
0.4 0.3
0.3
balTi balTi balTI balTi balTi
Commercially Pure and Modified Titanium /477
Ti-O.3Mo-O.8Ni grade 12 commercialequivalents: Compositions Specillcalion
Germany DeutscheT Japan Kobe Kobe
Designation
Descripllon
ContimetTJNiMo83
Ann
KSG12 KSG12S
MultFormsAnn SoftMu1tFormsAnn
11-12 TIMETAL Code12 1112
HeatExch
OT
Other
C
Fe
H
Mo
N
Ni
0
0.06
0.25
0.013
0.2·0.4
0.03
0.6-0.9
0.25
baITi
0.3 0.3
0.01 0.01
0.2·0.4 0.2-0.4
0.03 0.03
0.6-0.9 0.6-0.9
0.25 0.2
baITi baITi
0.3 max
0.015max
0.2-0.4
0.03 max
0.6-0.9
0.25max
baITi
USA OREMEf TIMET 1MCA
0.08 max
Alpha and Near-Alpha Alloys Ti·3AI·2.5V Common Name. Tubing alloy, ASTM Grade 9 UNS Number. R56320 Chemical Composition. With 3 wt% aluminum as an alpha stabilizer and 2.5 wt% vanadium as a beta stabilizer, Ti-3AI-2.5V is sometimes referred to as "half 6-4." High impurity levels may raise yield strength above maximum permitted values or decrease elongation or reduction in area below minimum values.
See accompanying Tables for specifications and compositions and commercial compositions
Characteristics Product ConditionlMicrostructure. This near-alpha alpha-beta alloy is generally used in the cold-worked and stress-relieved condition. Can be heat treated to high strength, but it has very limited hardenability.
With a phase structure consisting mostly of a grains, with small amounts of ~ titanium in the matrix and grain boundaries, the major microstructural features of Ti-3AI-2.5V are the morphology of the a phase and the alignment (texture) of the a crystals. The structure is typically cold worked and partially recrystallized. However, transformation products can be obtained by heat treatment Beta Transus. 935 ± 15°C (1715 ± 25 OF) Alpha Morphology. Can vary from 5 to 80% equiaxed alpha, depending on the amount of working and recrystallization. As a tubing material,large amounts of cold working produce and elongated structure of a grains, with the ~ phase strung out at the grain boundaries. Annealing recrystallizes the cold-worked structure to more rounded grains. Grain refinement during forging develops more slowly for Ti-3AI-2.5V than for commercial-purity titanium.
See accompanying Figures showing isothermal transformation and continuous cooling transformations Product Forms. The alloy is available as foil, seamless tubing, pipe, forgings, and rolled products. Seamless tubing is readily cold formed on the same type of conventional tube-bending equipment used for forming stainless steel. In production shops, cold worked and stress relieved tubing generally is not bent to radii less than 3 times the outer diameter, although radially textured tubing can be bent to 1.5. Relatively thin-wall tubing should be bent using tubing fillers or other inside-diameter constraints. Tubing is readily welded by standard gas tungsten-arc welding with inertgas shielding and by use of automatic welding tools with built-in inert-gas purge chambers Applications. Ti-3AI-2.5V seamless tubing was originally developed for aircraft hydraulic and fuel systems and has a proven performance record in high-technology military aircraft, spacecraft, and commercial aircraft. This alloy also can be readily rolled in strip and foil.
Ti-3AI-2.5V is also employed, mostly in tubular form, in various nonaerospace applications such as sports equipment (golf-club shafts, tennis racquets, and bicycle frames), medical and dental implants, and expensive ballpoint-pen casings Use Limitations. The rotary flexure fatigue life of pressurized Ti-3Al2.5V tubing is influenced by its crystallographic texture by residual stresses produced in straightening operations, surface roughness, and ovality. Flattening during bending operations reduces the impulse fatigue life of tubing
as a result of the superposition of three additive stresses: residual stresses due to flattening, membrane stresses following pressurization, and bending stresses in the flattened tube wall. Over-pressurization of tubing (auto-frettage) can decrease flattening, increasing impulse fatigue life. The reliability of tubing is adversely affected by cracking in service resulting from internal and surface irregularities. Production defects may be inclusions, separations in the tubing wall, or fissures at the inner and outer surfaces. Surface damage usually takes the form ofchafing or denting General Corrosion Properties. The general corrosion behavior ofTi3AI-2.5V is similar to that of unalloyed titanium. The nature of the oxide film on titanium alloys basically remains unaltered in the presence ofminor alloying constituents; thus, small additions «2 to 3%) of most commercially used alloying elements or trace alloy impurities generally have little effect on the basic corrosion resistance of titanium in normally passive environments. However, under active conditions in which titanium exhibits significant general corrosion, certain alloying elements may accelerate corrosion.
Although CP titanium has a higher pitting potential than Ti-3AI-2.5V in seawater, CP titanium may be susceptible to crevice corrosion in an environment that contains more than 1000 ppm chloride at temperatures of about 75°C (165 "F), Therefore, titanium alloys with improved crevice corrosion resistance are desirable for marine applications. In some cases, Ti-3AI-2.5V has better crevice corrosion resistance than CP titanium. For example, when anodic polarization tests were performed in seawater at 96°C (205 OF), the passive region of Ti-3AI-2.5V was more stable than that at a CP TiIPTFE gasket contact. Crevice corrosion specimens ofTi-3AI-2.5V have been tested in boiling seawater for 130 days with no detectable pitting or crevice corrosion. Ti-3AI-2.5V is essentially immune to stress-corrosion cracking in boiling seawater and simulated sour-gas well brines at room temperature (Te-Lin Yau, Corrosion of Ti-3AI-2.5V in Seawater, in Corrosion 89, 1989). Like CP titanium, Ti-3AI-2.5V is also immune to hot-salt cracking. See accompanying Figures comparing corrosion rates of CP Grade 2 and several Ti alloys, plus comparative Crevice Corrosion properties of CPTi and Ti-3AI-2.5V Hardness. Typical hardness of about 24 HRC has been reported with a range of 15 to 27 HRC. Hardness is highly dependent on annealing temperature Microhardness. When texture is developed in highly worked Ti-3Al2.5V, the shape of the Knoop indenter results in anisotropic hardness readings. Vickers hardness typically ranges from 220 to 300 HV,depending on heat treatment.
See accompanying Figures and Table on: effect of annealing temperature on hardness; Knoop hardness vs. annealing temperature; effect of heat treatment on hardness; and hardness vs. homogenizing heat treatment/cooling Cryogenic Properties. Accompanying Figures show cryogenic tensile properties of annealed sheet and tubing and cryogenic tensile properties of tubing
Fabrication Properties Ti-3Al-2.5V is intermediate in strength between unalloyed titanium and Ti-6AI-4V. Like Ti-6AI-4V, Ti-3AI-2.5V has a high strength-to-weight
Alpha and Near-Alpha Alloys I 479
long as the drill is sharp. Thicker walled tube requires a heavy flood of coolant to remove heat and chips
ratio and is lighter than stainless steel. Ti-3AI-2.5V has 20 to 50% higher strength than unalloyed titanium at both room and elevated temperatures. It has comparable weldability, and is much more amenable to cold working than Ti-6AI-4V (which does not have good cold forming properties).
Welding. Ti-3AI-2.5V has good weldability and, like all titanium alloys, is weldable by all methods except shielded arc welding and submerged arc welding (because no flux is permitted)
Ti-3AI-2.5V is used primarily as seamless tubing, which can exhibit variations in crystallographic orientation ranging from a radial texture to a circumferential texture. Texture variations of Ti-3AI-2.5V tubing provide a useful means of tailoring properties, and a radial texture has the characteristic of increasing both tensile yield strength and elongation (see Figures). Extruded tube intermediates can be cold worked to a moderately high-strength ductile product. For higher strengths and potential weight savings on aircraft hydraulic tubing, a seamless Ti-6AI-4V tubing product has been developed.
Filler Metal. Recommended mler metals are AWS Ti-9 and ER Ti-9ELI. Accompanying Table gives examples of primary working temperature; Figure compares hot ductility of CP-50 and several alloys
BendingProperties. Both annealed and cold worked plus stress relieved conditioned tube can be readily formed at room temperature using the same dies and plug mandrels used in forming stainless steel tubing. Bend radii of 2.5 and 3.0 times the OD are typical for annealed and cold worked plus stress relieved tubing, respectively. Spring back is about 15 to 25°. Thbing should be left in its protective sleeve or separator tray and handled carefully in bending to prevent surface damage that will reduce the fatigue life of the tube assembly.
Accompanying Figure shows effect of tube reductions on texture and properties
Primary Working. Extrusion of billet to shapes such as tube hollows may be accomplished at temperatures of less than 870°C (1600 "F). Extruded tube intermediates may be cold worked to final tube sizes with appropriate intermediate annealing treatments as required. Cleaning and pickling operations are included at appropriate intervals.
Drawability of Ti-3AI-2.5Vincreases as the fraction of a phase increases, whereas low drawability occurs even after tempering of ~ quenched material. The best combination of strength and drawability is obtained by quenching from just below the ~ transus
Mill products other than tubing can be produced following similar schedules. Typically, ingot breakdown may occur at temperatures above the ~ transus, major working of bloom and billet to intermediate section thickness at a-~ temperatures (see Table), and fmal primary fabrication steps at ambient temperatures with appropriate intermediate annealing
Recommended Heat Treating Practice Ti-3AI-2.5 v is used in the annealed or in the cold worked plus stress relieved conditions. However, due to the small amount of ~ stabilizer present, a small age hardening response is possible from the solution heat treated condition. Only a small increase in strength is possible in thin sections by solution treating and aging. For example, 1.7 mm (0.070 in.) sheet solution treated 15 min at 910°C (1670 "F) water quenched, and aged 8 h at 510 °C (950 oF) produces strengths only 138 to 172 MPa (20 to 25 ksi) greater than the annealed values and not much different from those achieved by cold working and stress relieving.
Cold Working. Ti-3AI-2.5V offers excellent cold formability in combination with 30 to 50% higher tensile strengths than unalloyed titanium. Ti-3AI-2.5V can be cold worked 75 to 85% to result in moderately high strength and good ductility Machining. Not a common practice on titanium alloy tubing. Hack sawing, abrasive wheel cut-off, and ordinary tube cutters are used in cutting tubing. With the use ofconventional machining techniques, titanium alloys are comparable to machining a good grade of stainless steel. In general, very sharp tools with a slightly larger rake angle and a very keen edge are suitable. Slower speed and heavier cuts are preferred because they maintain lower tool temperatures. Drilling of thin-walled titanium is not difficult as
See accompanying Table for typical heat treatment conditions; and Figures showing effect of aging on strength and tensile strength vs. annealing temperatures
Ti-3AI-2.5V: Isothermal transformation. Composition: 3.1 wt% AI, 2.4 wt% V, 0.006 wt% C, 0.064 wt% Fe, 0.0035 wt% H, 0.0070 wt% N, 0.0795 wt% 0, bal Ti LIVE GRAPH Click here to view 980
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1200
650
1100
10
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480 I Heat Treater's Guide: Nonferrous Alloys
Ti-3AI-2.5V: Continuous cooling transformations. Composition: 3.1 wt% AI, 2.4 wt% V, 0.006 wt% C, 0.064 wt% Fe, 0.0035 wt% H, 0.0070 wt% N, 0.0795 wt% 0, bal Ti LIVE GRAPH Click here to view 980
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Ti-3AI-2.5V: Corrosion rate vs. Ti alloys. General corrosion in
Ti-3AI-2.5V: Anodic polarization in seawaterat 96 DC. Ti-3AI-
naturally aerated HCI solutions
2.5V had a more stable passive region than CP titanium, and crevice corrosion occurred inconsistently at the CP Ti/PTFE-gasket contact. Test conditions: Pickled sample; scan rate, 6 V/h
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0.1
1
10 /1 Alcm
, Annealing temperature, OF
800
900 1000 1100 1200 1300 1400 1500 1600
30
25
oa: J:
• • • • • • • • • •
gf 20 Q) c
"E
J:
15
400
500
600
1000
Ti-3AI-2.5V: Effect ofannealing temperature onhardness. Alloy supplied as tubing 15.8 mm (0.625 in.) 00 by 0.9 mm (0.038 in.) wall, 50% cold worked (CW), annealed 2 h in vacuum, vacuum cooled to 425 DC (795 OF), air cooled
• • • •
•
• •
10
100
2
• •-• • •
700
Annealing temperature, °C
800
LIVE GRAPH Click here to view
900
Alpha and Near-Alpha Alloys I 481
Ti-3AI-2.5V: Specifications and compositions Spedllcation
DeslgD8tlon
Description
UNS UNS Cbina
R56320 R56321
WeldFillWtr
TI-3Al-2.5V Europe AECMATI-P69 Russia GOST GOST USA AMS4943D AMS4944D
prEN3120
ThbCWSR
ASTMB337 ASTMB338 ASTMB348 ASTMB381 ASTMB265-79 AWSAS.l6-70 AWSAS.I6-70 MILT-9046J MlLT-9047G
Fe
H
2.5-3.5 2.5-3.5
0.05 0.04
0.25 0.25
0.013 0.005
0.02 0.012
0.12 0.1
2-3 2-3
baITI baITI
2.5-3.5
0.08max
0.3 max
0.015max
0.05 max
0.12 max
2-3
SiO.15max; balTI
2.5-3.5
0.05max
0.3 max
O.oI5max
0.02 max
0.12 max
2.5-3.5
0.3
O.oI
0.03
0.25-0.35 0.16
2.5 2
3 3
Powd
AMS4944D AMS4945
Other
C
AK2
IMP-7
Composition, WI% N 0
AI
OT
V
0.04 max
balTI Si 0.6; bal Ti
ThbAnn SmlsThbCWSR
2.5-3.5 2.5-3.5
0.05 0.05max
0.3 0.3 max
O.oI5 O.oI5max
0.02 0.02 max
0.12 0.12 max
2-3 2-3
0.4 0.4 max
ThbCWSR SmlsThb
2.5-3.5 2.5-3.5
0.05 0.05max
0.3 0.3 max
O.oI5 0.015max
0.02 0.02 max
0.12 0.12 max
2-3 2-3
0.4 0.4 max
2.5-3.5 2.5-3.5
0.05 0.1
0.25 0.25
0.013 0.013
0.02 0.02
0.12 0.12
2-3 2-3
0.4 0.4
2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5
0.05 0.05 0.1 max 0.04 0.05 0.05 0.05
0.25 0.25 0.25 max 0.25 0.25 0.3 0.3
0.0125 O.oI5 0.015max 0.005 0.008 O.oI5 0.015
0.02 0.02 0.02 max 0.012 0.02 0.02 0.02
0.12 0.12 0.15 max 0.1 0.12 0.12 0.12
2-3 2-3 2-3 2-3 2-3 2-3 2-3
0.4 0.4
Grade9 Grade9
SmlsWeldPip Ann SmlsWeldThbCW SR Grade9 BarBiiAnn GradeF-9 FrgAnn Sh StrpPit EIm-3AI-2.5V-I WeldFillMet EIm-3AI-2.5V WeldFillMet CodeAB-5 ShStrpPltAnn TI-3Al-2.5V BarBilAnn
YO.005max;OEO.I max;balTI
YO.005;bal Ti YO.005max;OEO.1 max; balTi Y 0.005;bal Ti YO.005max;OEO.I max.bal Ti balTI balTI balTI balTI balTI balTI balTI balTI Y 0.005;bal Ti
0.4 0.4
Ti-3AI-2.5V: Commercialcompositions Composition,WI % Spedllcatlon
Germany DeutscheT Japan Kobe Sumitomo Toho USA Cabot Crucible OREMEf RMl RMl RMl
T1MEf TMCA
DesIgD8tlon
Description
Contirnet AlV32 KS3-2.5
AI
C
Fe
H
N
0
V
Pit BarFrgPipAnn
2.5-3.5
0.05
0.3
O.oI5
0.04
0.12
2-3
balTI
Pit ShWtrBarAnn
2.5-3.5
0.3
0.0125
0.02
0.12
2-3
balTI
OT
Other
S~-325 325~
TI-3Al-2.5V 3Al-2.5V U3-25 RMI3AI-2.5V RMI3AI-2.5V RMI3Al-2.5V T1MEfAL3-2.5 Ti325
BarThbStrpAnn Bar'Iub StrpAnn BarThb StrpCWSR
2.5-3.5
0.1
0.25
0.013
0.12
0.12
2-3
balTI
2.5-3.5 2.5-3.5 2.5-3.5
0.05 0.05 0.05
0.3 0.3 0.3
0.0125 0.0125 0.0125
0.02 0.02 0.02
0.12 0.12 0.12
2-3 2-3 2-3
balTI balTI balTI
Ti-3AI-2.5V: Typical heat treatment conditions Heat treatment
Minimumstressrelief 'Iypical stressrelief(a) Annealing(b) Solutiontreating Aging
Temperature
Ti-3AI-2.5V: Examples of primaryworkingtemperatures
"C
OF
Thn.. h
CooUng method
315 370-650 650-760 870-930 480-510
600 700-1200 1200-1400 1600-1700 900-950
0.5 min 0.5 t020r3 0.5t02 0.25-0.33 2t08
AC AC AC WQ AC
(a)Heatingabove 540°C (1000 "F) substantially reducedstrengthand hardness.(b)Heating to705 "C (1300 "F) for 2 h appearsto developa fullyannealedcondition.There is no advantagein annealing above 800 °C (1470 oF), and annealingin the ~ phasefieldreducesimpactstrength
Product Corm/condition
660mm(26in.)diarningot,preheatedto(200 oF), 5 to7 h, forgedto457 mm(18in.)squarebillet 457 mm(18 in.) squarebilletforgedto355mm (14in.)squarebillet 355 mm(14in.)squarebilletforgedto250mm (lOin.) squarebillet 250mm (10in.) squarebilletforgedto203 mm (8 in.) squarebillet 203mm(8 in.) squarebilletforgedto 150mm (6 in.)diarneterbillet Note: Intermediateconditioningoperationsas required
Worldngtemperature
900to 1095-c (1650to2000 oF) 900to 1035°c (1650to 1895oF) min 900to980°C (1650to 1795OF) min 785 to 900°C (1455to 1650oF) min 900 -c(1650oF)
482/ Heat Treater's Guide: Nonferrous Alloys
Ti-3AI-2.5V: Knoop hardness vs. annealing temperature. Alloy supplied as tubing 13 mm (0.5 in.) 00 by 0.8 mm (0.033 in.) wall, 55% cold worked and partially recrystallized at 600°C (1110 OF) for 1 h, annealed for 1 h, and air cooled. The different data points indicate the results of using various indenter orientations Annealing temperature for 105, of 1400 1600 1800 2000 2200
1200
Ti-3AI-2.5V: Hardness vs. homogenizing heat treatment/cooling. Effect of homogenizing heat treat temperature and cooling rate from that temperature on microhardness of small samples taken from forged billet. As-forged hardness was about 210 HV Homogenizing heat treat temperature, OF 1400 1500 1600 1700
2400
Water quenched Air cooled Furnace cooled
325
o
Oi 300__---__-----"~-1__---1___--_l a a
LIVE GRAPH
•
~
Click here to view
/
~
•
/
I 2751__---,n--~}--_p....->.-\____;;.__--1___--_l • 0
••
./ .....
"E ~ 250~---Ja-:!c\t*+-lL_---~--_1
•
~.
LIVE GRAPH Click here to view 225'---------''''--_'--_--'-_'-600
'-----_ _--'
800 1000 1200 Annealing temperature for 10 5, °C
770 840 910 Homogenizing heat treat temperature, °C
1400
Ti-3AI-2.5V: Effect of tube reductions on texture and properties. The contractile strain ratio (CSR) is the ratio of diametral to radial strain from a given stress. AMS 4945 specified a 1.3 minimum CSR for most tube sizes. Low and high CSR both reduce fatigue strength, whereas a midrange CSR increases fatigue strength
980
Ti-3AI-2.5V: Hot ductility. The on-cooling hot ductility behavior of titanium alloys with varying aluminum content. li-3AI-2.5V and unalloyed titanium do not exhibit a "hot ductility dip" as in other alloys containing more aluminum
LIVE GRAPH
Click here to view 800
1000
Break temperature, OF 1200 1400 1600 1800
2000
100
AasalPole
Hexagonal unit cell
I::tJ:J
./
;ft.
.. ~
CP-50
80
TI·3AI·2.5V
.....
60
'0 c 0
U :J
Ti-BAI
40
/'
"0
Q)
ll:
20
Random texture
l
Random texture
l
Large wall reduction (high a)
Large diameter reduction
l
l
~0
~
Radial texture (high eSR) High eSR increases: • Tensile strength • Tensile elongation • Burst strength
0 400
600
(Iowa)
00 ri?W
Circumferential texture (low CSR) Low CSR increases: • Wall thinning • Flattening • Flaring • Swaging
800 1000 Break temperature, °C
1200
Ti-3AI-2.5V: Effect of heat treatment on hardness Heattreatment condition As-quenched 750 °C (1380 oF) 20 min, WQ 800°C (1470 oF) 20 min, WQ 850°C (1560 oF) 20 min, WQ 900 °C (1650 oF) 20 min,WQ 950 °C (l74O oF) 20 min, WQ 'Thmpered 750°C (1380 oF) 20 min, WQ, 500°C (930 oF) 5 h, AC 800°C (1470 oF) 20 min, WQ, 500°C (930 oF) 5 h,AC 850°C (1560 oF) 20 min, WQ, 500°C (930 oF) 5 h,AC 900 °C (1650 oF) 20 min, WQ, 500°C (930 oF) 5 h.AC 950°C (1740 oF) 20 min, WQ, 500°C (930 oF) 5 h, AC
261 258 257 299
304 263 254 278 301
292
Note:Commerci~ produced,annealedsheet0.7 mm (0.03in.)thick.Heat treatmentswere carried OUI in vacuum(10
10
10-slorr)
Alpha and Near-Alpha Alloys I 483
Ti-3AI-2.5V: Tensile strength vs. anneal temperature. Effect of 2 h annealing (or stress relieving) temperature on room-temperature tensile properties of full hard (50% cold worked) tubing. With a room-temperature full hard strength of 999 MPa (145 ksi) UTS and 896 MPa (130 ksi) tensile yield strength. 15.8 mm (0.625 in.) OD x 0.96 mm (0.038 in.) wall 50% CW + anneal, 2 h in vacuum, vacuum cool to approximate 425°C (800 OF), AC 600 1200
Anneallemperalure, 'F 800 1000 1200 1400
UTS
~,,"-,c~"-
'"
a.
600
400
TYS
:::;
-;
----:l
140
s;
120
I!!
100 80
60
Full hard (50% CWj
0 400
500 600 700 800 Anneal temperature, 'C
-II
- .
120 'iii
a,
160
800
"'" 110
en c
~ iff el c
~
40 200
300
140 130
Click here to view
~, '\ 800
'"
Click here to view 1000
-
1000
g'""
LIVE GRAPH
1600
LIVE GRAPH
:;; £
Ti-3AI-2.5V: Effect of aging on strength. Effect of 540°C (1000 OF) age on room-temperature tensile properties of 3.5 mm (0.140 in.) strip after solution treatment at 910°C (1670 OF) for 15 min and water quench
20
iil
~ c
I!!
700
100 iil
TYS"", .B
600
T
L 0
• UTS ·TYS
0
500 0
2
4
6
90 80 8
Age time, h
0 900
Ti·5AI·2.5Sn Common Name. Ti-5-2.5 and Ti-5-2.5 ELI UNS Numbers. R54520/R5452l Chemical Composition. As interstitial element content increases, both yield and tensile strengths increase and fracture toughness decreases. The extra low interstitial (ELI) grade of Ti-5AI-2.5Sn (UNS R54521) is especially well suited for service at cryogenic temperatures and exhibits an excellent combination of strength and toughness at -250°C (-420 "F). See adjoining Tables for specifications and compositions
Characteristics One of the first alloys to be developed commercially, Ti-5AI-2.5Sn was designed as an intermediate strength, weldable alloy. Primary usage was in products requiring moderate strength combined with excellent weldability. This alloy is being replaced by Ti-6AI-4V, but it is available from all producers Product Condition/Microstructure. Ti-5AI-2.5Sn is an all-alpha titanium alloy. It has very high fracture toughness at both room temperature and elevated temperatures and is used only in the annealed condition. The microstructure of Ti-5AI-2.5Sn is either acicular or equiaxed o, depending on prior processing. Acicular lX is observed after thermal excursions above the 13 transus. Equiaxed alpha results from working the metal below the 13 transus, followed by annealing in the lX field. There commonly is a very small amount of 13 in microstructures ofTi-5AI-2.5Sn that contains high iron. Equiaxed lX is most frequently encountered in mill products of either standard Ti-5AI-2.5Sn or Ti-5AI-2.5Sn (ELI) Beta Transus. The 13 phase transforms to lX on cooling at 1040 to 1090 °C (1905 to 1995 oF) Alpha Transus. On heating
lX
to 13 at 955 to 985°C (1750 to 1805 "F)
Beta Transus of ELI Grade. This occurs at 1010 ± 15°C (1850 ± 25 oF)
Product Forms. Ti-5AI-2.5Sn is available as bar, plate, sheet, strip, wire, forgings, and extrusions. The ELI grade is quite difficult to hot work into some product forms, particularly when converting from ingot to billet because of shear cracking, often referred to as strain-induced porosity Applications. Ti-5AI-2.5Sn is used for gas turbine engine castings and rings, rocket motor casings, aircraft forgings and extrusions, aerospace structural members in hot spots (near engines and leading edges of wings), ordnance equipment, chemical-processing equipment requiring elevatedtemperature strength superior to that of unalloyed titanium and excellent weldability, and other applications demanding good weld fabricability, oxidation resistance, and intermediate strength at service temperatures up to 480°C (900 oF). Ti-5AI-2.5Sn ELI is employed for liquid hydrogen tankage and high-pressure vessels at temperatures below -195°C (-320 OF), structural members for aircraft, and gas turbine parts. It is used in applications requiring ductility and toughness greater than those of the standard grade, although at some sacrifice in strength, particularly in hardware for service at cryogenic temperatures Precautions in Use. The elevated temperature, stress-corrosion resistance of this alloy in the presence of solid salt is lower than that of other commonly used titanium alloys. Use of Ti-5AI-2.5Sn (like all titanium alloys) in contact with liquid oxygen, or in contact with gaseous oxygen at pressures above approximately 345 kPa (50 psi), constitutes severe fire and explosion hazards General Corrosion Properties. Few published data on the general corrosion rates of Ti-5AI-2.5Sn are available. It can be used in mildly reducing to highly oxidizing environments in which protective oxide ftlms spontaneously form and remain stable. The nature of the oxide film basically remains unaltered in the presence of minor alloying constituents. Consequently, small additions (<2 to 3%) of most commercially used alloying elements or trace alloy impurities generally have little effect on basic corrosion resistance in normally passive environments. In boiling
484/ Heat Treater's Guide: Nonferrous Alloys HCI concentrations below 0.5%, for example, Ti-5AI-2.5Sn is comparable to grade 2 titanium. Corrosion of the Ti-5AI-2.5Sn alloy is expected in hot, concentrated, low-pH chloride salts. Warm or concentrated solutions of hydrochloric, phosphoric, and oxalic acids also are damaging. In general, all acidic solutions that are reducing in nature corrode titanium, unless they contain inhibitors. Strong oxidizers, including anhydrous, red fuming nitric acid and 90% hydrogen peroxide, also cause attack. Ionizable fluoride compounds, such as sodium fluoride and hydrogen fluoride, activate the surface and can cause rapid corrosion. Dry chlorine gas is especially harmful. Because tin and aluminum promote the formation of ordered ThAI (a.2) structures, Ti-5AI-2.5Sn is one of the titanium alloys most susceptible to stress-corrosion cracking. Like step-cooled Ti-8AI-IMo-lV, the Ti-5Al2.5Sn alloy is susceptible to corrosion cracking in distilled water
forming can be done at 150 to 315°C (300 to 600 OF), and simple forming may be done at room temperature. Most forming and welding operations are followed by an annealing treatment to relieve residual stresses imposed by the prior operation Machining. Machinability is comparable to that of a good grade of stainless steels. In general, very sharp tools with a slightly larger rake angle and very keen edge are suitable. Slower speed and heavier cuts are preferred because they maintain lower tool temperatures and produce coarse chips, which are more difficult to ignite. Drilling of thin-walled titanium is not a problem as long as the drill is sharp. Thicker walled tube requires a heavy flood of coolant to remove heat and chips Welding. Weldability ofTi-5AI-2.5Sn is good. Like all titanium alloys, it is weldable by all methods except shielded arc welding and submerged arc welding (because no flux is permitted)
Fabrication Properties
Filler Metals. Recommended ftller metals are AWS Ti-6 and ER Ti-6 ELI
Forging. Ti-5AI-2.5Sn is used commercially in the full range of forging products, e.g., open die forgings, closed die forgings, rings, etc., and is fabricated on all commercially available types of forging equipment.
Recommended Heat Treating Practice
Ti-5AI-2.5Sn and its extra-low interstitial (ELI) grade are among the most difficult to forge of all titanium alloys. They are characterized by high unit pressures (flow stresses) and crack sensitivity in all types of forging processes, which may restrict the amount of reduction possible in a given forging step. Alpha phase predominates the final microstructure of Ti-52.5. Consequently, it is not thermomechanically processed in forging manufacture. Final thermal treatments consist of an anneal at 705 to 815 °C (1300 to 1500 "F), with, in some cases, a subtransus solution treatment at 1010 or 995°C (1850 or 1825 "F) for the two alloy variants, followed by air cooling or faster quenches prior to annealing, to refine a. grain size Forming. Ti-5AI-2.5Sn is not as readily formed into complex shapes as other alloys with similar room-temperature properties. Except for some forging operations, fabrication of Ti-5AI-2.5Sn is conducted at temperatures where the structure remains all a.. Severe forming operations may be accomplished at temperatures up to 650°C (1200 "F), Moderately severe Ti-SAI-2.SSn: Effect of annealing on tensile properties Annealed
Colddrawn 15%
982.5 (142.5) 879.1(127.5) 844.6(122.5) 17.0 39.0 108.2(15.7) flat0.5 cup
1206.6(175.0) 1041(151.0) 517(75.0) 10.0 28.0 99.3 (14.4) flat 0.5 cup
Property
urs (0.2%offset),MPa (ksi) Tensileyieldstrength,MPa (ksi) Proportionallimit, MPa (ksi) Elongationin 50 mm(2 in.), % RA,% Elasticmodulus,GPa (106 psi) 1YPe of fracture
Because Ti-5AI-2.5Sn is a single-phase a. alloy, heat treatment is confined to stress relief or full annealing Temperatures above 870°C (1600 OF) are seldom used for annealing, because excessive grain growth and oxidation can occur. Annealing in the preferred a. temperature range imparts or restores optimum ductility and toughness Thermal Stability. Measurements made by comparing room-temperature properties before and after thermal exposure (stressed or unstressed) have indicated that this alloy is metallurgically stable under any conditions of stress, temperature, and time up to the annealing temperature. The only changes in properties due to thermal exposure that have been observed are believed to be traceable to the relief of residual stresses. For example, tensile and fatigue specimens prepared from butt-fusion-welded sheet were found to change in strength and ductility after a 500-h, 370°C (700 OF) exposure Ti-SAI-2.SSn: Recommended heat treatmentconditions Thmperalure
Heat treatment
Stressrelief Annealing
540-650 705-870
1000-1200 1300-1600
Time, h
Cooling method
0.25 to 1 0.16t04
AC AC
Ti-SAI-2.SSn: Environments known to promotestress-corrosion cracking Medium
Thmperature, °C (OF)
Othertilanium alloyswithknown susteptihility
OxidIzers
Ti-SAI-2.SSn: Forming temperatures Thmperalu.... MeChod
"C
Hot sizing
650
Brakeforming Drophammer
205-315 540-705
Stretching
Drawing Spinningor shear forming Pressforming Matched die Hydropress Roll forming Creepforming Dimpling
540-705 650-760
OF
Comments
15 min forO.8mm(O.032in.)sheet,20 min for 1.6rom (0.063 in.) 400-600 . Mild forming 1000-1300 Severeformingabove540 °C (1000 oF); maximumstretchof 12.6%at480 °C (900oF) in annealedcondition Thmperatures above540 °C (1000 oF) are requiredfor significantimprovementin stretch formability 1000-1300 1200-1400 Thmperatures up to 870°C (1600 oF) maybe neededfor spinning 1200
480-540 205-315
900-1000 400-600
540-705 870-980
1000-1300 1600-1800
Severeforming Mild forming
Nitricacid (red fuming) Organic compounds Methylalcohol (anhydrous) Methylchloroform Ethylalcohol(anhydrous) 1iicWorofluoroethane Chlorinateddiphenyl Salts Hotchlorideandother halidesalts/residues SeawaterlNaOsolution
MIscellaneous Distilledwater Agmetal+AgO IO%HCl
lIT
Ti,Ti-8Mn,Ti-6AI-4V
TI-6A1-4V, Gr.2TI,Gr.4 TI, Ti-4A1-3Mo-lV.Ti-3AI-8V-6Cr-4Zr-4Mo, TI-8AI-IMo-IV,TI-13V-llCr-3A1 Ti-8AI-IMo-IV,TI-6A1-4V, TI-13V-llCr-3A1 370(700) Ti-8A1-IMo-lV lIT Ti-8A1-lMo-IV,TI-6A1-4V, Ti-13V-llCr-3A1 788(1450) 315-370(600-700) No alloyotherthanTi-5A1-2.5Sn
lIT
230-430(450-800) Mostcommercialalloysexcept grades 1,2, 7,II,12,andTi-3A1-2.5V UnalloyedTI (withoxygencontent>0.3%): lIT Ti-2.5A1-lMo-IISn-5Zr-02Si (IMl-679), Ti-3AI-llCr-I3V, Ti-8Mn,Ti-6A1-4V, Ti-6A1-6V-2Sn, TI-7A1-2Nb-lTa, Ti-4A1-3MoIV, Ti-8A1-IMo-IV,Ti-6A1-2Sn-4Zr-6Mo Ti-8A1-IMo-IV, Ti-ll.5Mo-6Zr-4.5Sn(BetaIIl) lIT 230-480(450-900) 7A1-4Mo Ti-8A1-lMo-IV 35-340(95-645)
Alpha and Near-Alpha Alloys I 485
Ti-5AI-2.5Sn: Specifications and compositions ComposilloD, WI%(a) Speci.Ikalion
DesignaJlon
Description
UNS UNS UNS UNS China GB3620 Germany
R54520 R54521 R54522 R54523
EU WeldFiUMet EUWeid FiU Met
DIN 17851 DIN 17851 Russia GOST
TA-7 WL3.7114 TI-5Al-2.5Sn WL3.7115
Sh StrpPItRod wu PitSh StrpAnn
VT5-IKT
Other
OT
AI
C
Fe
H
N
0
So
4-6 5 4.7-5.6 4.7-5.6
0.1
0.5
0.02
0.05
0.2
0.05 0.04
0.4 0.25
0.008 0.005
0.03 0.012
0.12 0.1
2-3 2.5 2-3 2-3
baiTI baiTI baiTI baiTI
4-6
0.1 max
0.3 max
0.015 max
0.05 max
0.2 max
2-3
SiO.l5 max:balTI
4.5-5.5 4-6
406
0.08 0.08 0.08
0.5 0.5 0.5
0.015-0.02 0.02 0.02
0.05 0.05 0.05
0.2 0.2 0.2
2-3 2-3 2-3
4-5.5
0.05
0.2
0.08
0.04
0.12
2-3
0.4
baiTI baiTI baiTI :a 0.2; MnO.I; Si 0.1: baiTI :a0.3: Si 0.15; balTi
VT5-1
Sh PItStrpRod FrgAnn
4-6
0.1
0.3
0.D15
0.05
0.15
2-3
L-7101
Sh Strp PItBar FrgExt
4.5-5.5
0.15
0.5
0.02
0.D7
0.2
2-3
baiTI
4-6 4-6 4-6 4-6
0.08 max 0.08 max 0.08 max
0.5 max 0.5 max 0.5 max 0.5 max
0.0125 max 0.0125 max 0.0125 max 0.015 max
2-3 2-3 2-3 2-3
baiTI baiTI baiTI baiTI
EUSh StrpPltAnn
4.5-5.75
0.05
0.25
0.0125
0.035
0.12
2-3
0.3
AMS4910J AMS4924D
ShStrpPltAnn EU BarFrgRngAnn
4.5-5.75 4.7-5.6
0.08 0.05
0.5 0.25
0.02 0.0125
0.05 0.035
0.2 0.12
2-3 2-3
0.4 0.4
AMS4926H AMS4953D AMS4966J ASTMB265 ASTMB348 ASTMB367 ASTMB381 AWSAS.I6-70 AWSAS.I6-70 MIL F-83142A MILF-83142A MILF-83142A MILT-81556A MILT-81556A MILT-81915 MILT-9046J MILT-9046J MILT-9047G MILT-9047G
BarWtrBilRngAnn WeldFillWlf FrgAnn ShStrpPit Ann BarBilAnn Cast FrgAnn EUWeldFiUMet WeldFiUMet FrgAnn FrgHT EUFIgAnn ExtBarShpAnn EU ExtBarShp Ann CastAnn ShStrp PItAnn EUShStrpPltAnn BarBilAnn ELIBar BilAnn
4-6 4.5-5.75 4-6 4-6 4-6 4-6 4-6 4.7-5.6 4.7-5.6 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75 4.5-5.75
0.08 0.08 0.08 0.1 0.1 0.1 0.1 0.04 0.05 0.08 0.08 0.05 0.08 0.05 0.08 0.08 0.05 0.08 0.05
0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.25 0.4 0.5 0.5 0.25 0.5 0.25 0.5 0.5 0.25 0.5 0.25
0.02 0.D15 0.02 0.02 0.0125 0.D15 0.02 0.005 0.008 0.02 0.02 0.0125 0.02 0.0125 0.D2 0.02 0.0125 0.02 0.0125
0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.012 0.03 0.05 0.05 0.035 0.05 0.035 0.05 0.05 0.035 0.05 0.035
0.2 0.175 0.2 0.2 0.2 0.2 0.3 0.1 0.12 0.2 0.2 0.12 0.2 0.12 0.2 0.2 0.12 0.2 0.12
2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-3
0.4 0.4 0.4 0.4 0.4 0.4 0.4
GOSTI9807-74 Spain UNE38-716 UK BSTAI4 BSTAI5 BSTAI6 BSTAI7 USA AMS4909D
Sh Bar Frg Frg
Grade6 Grade6 GradeC-6 GradeF-6 ERTI-5Al-2.5Sn-1 ERn-5Al-2.5Sn Comp2 Comp2 Comp3 CodeA-I CodeA-2 lYpe II CompA CodeA-I CodeA-2 TI-5AI-2.5Sn TI-5AI-2.5Sn ELI
0.3
0.4 0.4 0.3 0.4 0.3 0.4 0.4 0.3 0.4 0.3
Y0.005; 0 + Fe = 0.32: baiTI YO.005:balTi YO.005:0 + Fe =0.32: baiTI Y 0.005: balTI YO.005;balTi Y0.005: balTi baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI baiTI Y0.005: balTi YO.005:balTi
(a) Maximumunless a range is specified
Ti-5AI-2.5Sn: Tensile properties of annealed and cold drawn specimens Property
trrs, MPa (ksi) TYS (0.2%offset),MPa (ksi) Proportionallimit,MPa (ksi) ILin 50 mm(2 in), % RA,% Elasticmodulus,GPa (106 psi) Typeof fracture
Annealed
Cold drown 15%
982(142.5) 879(127.5) 844(122.5) 17.0 39.0 108(15.7) Flat0.5 cup
1206 (175.0) 1041(151.0) 517 (75.0) 10.0 28.0 99(14.4) Flat 0.5 cup
Ti-5AI-2.5Sn: Typical tensile properties UItimotelemlle strength Grade
MPa
ksi
Standard EU
861 779
125 113
Thmileyieldstrength (0.2%) MPa ksi
827 717
EJongationID
so mm(2 la), %
120 104
15 17
Ti-5AI-2.5Sn: Forging process temperatures Metaltemperature Process
Conventional (subtransus) forgingofTI-5AI-2.5Sn ConventionalforgingofTI-5AI-2.5SnELI Supratransus forging(*)
·C
·F
900-1010 885-995 PT+30t055 ·C
1650-1850 1625-1825 PT+50to 100°F
(*) Due to thehighflowstresses,Pforgingmay be used inearlyforgingoperations,includingupset-
tingand open dieforging.Typical transusis 1050·C (1920 oF) forTi-5Al-2.5Snand 1035°C (1895 oF) forTi-5Al-2.5SnELI
486/ Heat Treater's Guide: Nonferrous Alloys
Ti-5AI-2.5Sn:Compositions Composition, WI%(aj Specification Designation France Ugine Ugine Germany Deutsche'T Deutsche T Fuchs Japan Kobe Kobe MMA
Sumitomo Toho USA OREMET
RMI RMI TIMET TIMEr
Description
AI
C
Fe
H
N
0
Sn
OT
Other
UTA5E UTASEL
ShBarAnn EU BarAnn
4.5-5.5 4.5-5.75
0.15 0.05
0.5 0.25
0.02 0.0125
0.07 0.035
0.2 0.12
2-3 2-3
baITi baITi
ContimetAlSn52 ContimetAISn52 ELI TL52
ShStrpPitBarFrgPipAnn EUPlt BarFIg PipAnn Frg
4.5-5.5 4.7-5.6 5
0.08 0.06
0.5 0.15
0.Q2 0.013
0.05 0.05
0.2 {).12
2-3 2-3 2.5
baITi baITi baITi
KS5-2.5 KS5-2.5EU 5137 SAT-525 525AT
Ann EUAnn
4-6 4.7-5.6
0.5 0.25
0.Q2 0.0125
0.05 0.035
0.2 0.12
2-3 2-3
baIti baITi
0.5
0.02
0.05
0.3
2-3
baITi
0.2 0.13 0.2 max 0.12 max
2-3 2-3 2-3 2-3
baITi baITi baITi
115-2.5 RMI5Al-2.5Sn RMI5Al-2.5Sn ELI TIMETAL5-2.5 TIMErAL5-2.5ELI
MultFonnsAnn ELIMultFonnsAnn Ann Ann
4-6
0.03
4-6 4.7-5.75 4-6 4.5-5.75
0.08 0.08 0.1 max 0.05max
0.5 0.0175-0.02 0.05 0.25 0.0125-0.015 0.03 0.5 max 0.02max 0.05max 0.25max 0.0125max 0.035max
(a) Maximumunlessa range isspecified
Ti-5AI-2.5Sn:Turningparameters for annealed material Thot material Rough turning Brazedcarbide(C2) Throwaway carbide(C2) High-speed steel(M3,T5,Tl5) Finish turning Brazedcarbide(C3, C2) Throwaway carbide(C3, C2) Highspeedsteel(MS, T5,Tl5)
Feed
Thol geometry(a)
mm
Depth ofcut in.
mmfrev
in./rev
mfmiu
.rm
A,E,F,G A,E,F.G B,D,E
2.5-6.35 2.5-6.35 2.5-6.35
0.10-0.25 0.10-0.25 0.10-0.25
0.25-0.38 0.25-0.38 0.25-0.38
0.010-0.015 0.010-0.05 0.010-0.015
42-55 43-67 110-290(a)
140-180 140-220 36O-96O(a)
A,B,C A,B,C C,E
0.635-2.5 0.635-2.5 0.635-2.5
0.025-0.10 0.025-0.10 0.025-0.10
0.13-0.25 0.13-0.25 0.13-0.25
0.005-0.010 0.005-0.010 0.005-0.010
50-65 67-76 146-290(0)
165-215 220-250 480-960(0)
Speed
(a) Thesehighspeedswouldbeloweredifhigherfeedsand deepercuts are madewithhigh-speedsteelcutters
Ti-5AI-2.5Sn:Toolgeometrycode Thol angles andnose radius forIndicated 1001 geometry code Backrake, degrees Siderake,degrees Endrelief, degrees Siderelief, degrees Endcuttingedges,degrees Sidecuttingedge (lead), degrees Noseradius,mm(in.)
A
B
C
-5 -5 5
+5to-5 +61000to-6 5-10 5-10 6-15 5-20 0.7-1.0(0.003-0.04)
5 15-45 15-45 0.8-1.2(0.03-0.05)
D
E
F
G
o
o
50r6 5 5 15ar5 15 1.2(0.05)
15 5 5 10-15 15to 45 1.2(0.05)
Oto+5 +5to+15 5-7 5-7 5-7 15-20 0.5-0.7(0.Q2-0.Q3)
Oto+1O Oto+l0 6-8 6-8 5-10 0-30
+6 to +10 Oto+15 6-10 6-10 5-15 0-45 0.7-1.0(0.03-0.04)
Ti"5AI-2.5Sn: Effectof coolingfrom ~ anneal on tensileproperties Heating into the ~ field without subsequent working in the a. field causes loss of ductility. Quenching reduces the loss.
Annealing treatment
UIIimale lensile strength ksi MPa
Tensile yield strength MPa ksl
1150°C (2100oF), waterquench 1150°C (2100oF), aircool 1150°C (2100oF), furnace cool 1010°C(1850oF), waterquench 1010°C(1850oF), aircool 1010°C(1850oF), furnacecool 870°C (1600 oF), aircool 650°C (1200oF), aircool
1055 1027 1046 1008 989 994 954 1006
1052 957 973 906 958 973 908 987
Note: Annealedalloyextrudedat 925°C (1695"F) (a.-~ extruded)
153.1 149.0 151.8 146.3 143.5 144.2 138.4 146.0
152.6 138.8 141.2 131.4 139.0 141.2 131.8 143.2
Elongation
Redudioo
in4D,
orarea,
%
%
12.5 8.3 7.5 16.7 16.7 15.5 16.7 16.7
25.0 15.2 13.9 50.0 45.7 43.7 50.3 43.4
Alpha and Near-Alpha Alloys I 487
Ti-5AI-2.5Sn Ell: Minimum tensile properties of bars, forgings, and rings Nominal diameter In.
MP.
ksi
MPa
ksi
L
Elongation 1n4D, % LT
~2.000
689 689
100 100
620 620
90 90
10 10
10 10
or distance between
Ultlmate
parallel sides
tensile strength
mm
550 >50-100
>2.00-4.00
Yield Strength (0.2%offset)
ST
6
L
Reduction of area,% LT
ST
20 15
15 15
10
Ti-5AI-2.5Sn: Room-temperature properties after various treatments Tensile yield strength (0.2%)
Ultimatetensile
strength Heattreatedcondition
MP.
ksi
MP.
760 °C (1400oF),2h,AC 900 °C (1650oF),10h,AC 9OO°C(1650°F),looh,AC(inargon) 760 °C(1400°F), 2h, AC+595 °C (1100°F),8 h, FC to 500 °C (930oF),120h 900 °C (1650oF),I h,WQ 1095°C(2000 OF), 30 min,WQ
953 911 898 964 933 965
138.2 132.1 130.3 139.8 135.4 140.0
890 862 818 899 856 873
Ti-5AI-2.5Sn: Stress-corrosion cracking in distilled water 180
LIVE GRAPH
140
N
K;,~
28 35 29 23 29 40
0..
i
~
ea. en
.~ 1001--~.,.L-=------b~=-o
3%8all
u,
4 Time, min
6
2o 8
'-----------------'0 0.1 1
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80 0
3~0 °c
0
0..
w
O~~
100
80
gj
60
1il
w
480°C
lI)
lI)
Q)
1;;
400
(ij :J "0
'00 Q)
IT:
200
o o
~1-0--r---... "'-:
~ t:-20
~
(ij :J "0
40
595°C
2o
650°C 705°C
10
40
:J
Ti·5AI·2.5Sn: Residual stress relief
:2
26 32 27 21 27 37
:2 2001---------1--------='.LC----j
Strain rate, min-
ro 60
kSi'Jlii:"
lZ
No faiiure 2
72 90 92 46 103 119
79 99 101 50 113 130
K,=
ro
20
o
MP.\Iiii"
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1
~
ksi'Ai"
LIVE GRAPH
iiled water
\ 0""- ----
K"
300
1
0
129.2 125.11 118.7 130.5 124.2 126.6
MP.\Iiii"
Ti-5AI-2.5Sn: Forging pressures at 870°C. Forging pressures for a 10% upset reduction at 870°C (1600 OF)
Click here to view
Air
ksi
30 Time, min
40
50
0 60
.~ IT:
1
Ti·5AI·2.5Sn: Microstructure. Hot worked below the 0: transus, annealed 30 min at 1175 °C (2145 OF), which is above the p transus, furnace cooled to 790°C (1455 OF) in 6 h, and furnace cooled to room temperature in 2 h. Coarse, platelike 0:. Kroll's reagent (ASTM 192). 100x
488/ Heat Treater's Guide: Nonferrous Alloys
Ti-5AI-2.5Sn: Microstructure. Hot worked below the a. transus, annealed 30 min at 1175 °C (2145 OF), which is above the ~ transus, and air cooled from the annealing temperature instead of furnace cooled. The faster cooling rate produced acicular a. that is finer than the platelike a. in preceding Figure. Prlor-B grains are outlined by the a.that was first to transform. Kroll's reagent (ASTM 192).100x
Ti-5AI-2.5Sn: Microstructure. Hot worked below the a. transus, annealed 30 min at 1175 °C (2145 OF), which is above the ~ transus, but water quenched from the annealing temperature instead of furnace cooled and shown at a higher magnification. The rapid cooling produced fine acicular o; A prtor-B grain boundary can be seen near the center of the micrograph. Kroll's reagent (ASTM 192). 250x
Ti",6AI..2Nb",1 Ta",O..8Mo Common Name. Ti-621/0.8 UNS Number. R56210 Chemical Composition. Ti-621/0.8 is a modification of Ti-7AI-2NbITa (Ti-72l) composition, which is itself a modification of the original Ti-8AI-2Nb-ITa (Ti-821) alloy. The Ti-721 alloy was developed specifically to avoid weld cracking problems encountered in Ti-821 thick plate. Ti-621/0.8 was developed as a modification of Ti-72I to achieve resistance to stress-corrosion in salt water Effect of Impurities. For optimumtoughnessin deep submersibles, oxygen content should be kept below 0.10%, and other interstitials should be limited to minimum levels. Oxygen content influences the strength and toughness of this alloy. A modest but consistent increase in smooth tensile strength accompanies an increase in oxygen level from 0.058 to 0.122 wt.%. The alloy has a typical hardness of 30 HRC. See Tables for specifications and compositions and for commercial compositions
Characteristics Product ConditionlMicrostructure. Ti-621/0.8 is a near-alpha titanium alloy for applications requiring high toughness and moderate strength. On the basis of fracture appearance, it is considered resistant to seawater stress corrosion. However, sustained-load tests on precracked specimens indicate that the load-carrying ability of this alloy is reduced in seawater, although no evidence of stress-cracking was observed on the fracture surfaces of failed specimens. Microstructure can be varied greatly by modifications in primary processing procedures and heat treatment, similar to Ti-6AI-4V. By suitable selection of working and annealing temperatures with respect to the ~ transus temperature, microstructures can be developed having equiaxed, platelet, or grain-boundary a. in a transformed ~ matrix; both phases can be fine,
medium, or coarse, and continuous or noncontinuous. The platelike a. precipitates that nucleate and grow below the ~ transus produce a Widmanstatten structure. The plates often precipitate in colonies of the same crystallographic orientation, presumably because of autocatalytic nucleation. Martensite may form in quenched alloys with a platelike or lath morphology. The individual plates tend to have different crystallographic orientations, in contrast to the colony microstructure formed by nucleation and growth, and they often have an internal structure. In addition, TbAI may precipitate in the a. phase during aging at 500 °C (930 OF) Product Forms. Ti-621/0.8 is available as bar, plate, sheet, wire, extrusions and billet. The alloy has excellent weldability; the weld metal develops the same strength, ductility, and toughness as those of the base metal Applications. Ti-621/0.8 is used for hulls of marine, hydrospace, and deep-submersible vehicles; for pressure vessels; and for other high-toughness applications Precautions in Use. Like most titanium alloys with alpha-beta microstructure,Ti-621/0.8 is susceptible to hydrogen embrittlement in hydrogenating solutions at room temperature, in air or reducing atmospheres at elevated temperatures, and even in pressurized hydrogen at cryogenic temperatures. Oxygen and nitrogen contamination can occur in air at elevated temperatures, and such contamination becomes more severe as exposure time and temperature increase. Ti-621/0.8 is susceptible to stresscorrosion cracking in hot salts (especially chlorides) and to accelerated crack propagation in aqueous solutions at ambient temperatures. The environments in which this alloy is to be used should be carefully controlled to prevent degradation of properties General Corrosion Properties. Stress-corrosion cracking threshold in seawater has been estimated at 77 to 90 MPa-{ffi (70 to 82 ksifu) (Aerospace Structural Metals Handbook, Code 3720, Battelle Columbus Laboratories, June 1969)
Alpha and Near-Alpha Alloys I 489
Fabrication Properties This alloy is used commercially in the full range of forging product types and is produced on all types of forging equipment. As with other a titanium alloys, it is difficult to fabricate into forgings. exhibiting high flow stresses and crack sensitivity. However, the alloy has been commercially produced in forgings for several applications including pressure vessels, reactor components, and armor where its excellent weldability is beneficial.
alpha-beta field is difficult due to the alloy's relatively high cracking tendency
Recommended Heat Treating Practice Ti-6211 generally is used in the as-fabricated or fabricated plus annealed conditions. A small increase in strength can be obtained by solution treating and aging, but at a sacrifice in ductility and toughness. For further information on heat treating this alloy, see adjoining Figures
Ti-6211 is characterized by high unit pressures (flow stresses) and crack sensitivity in forging processes. The final microstructure of Ti-6211 is manipulated by thermomechanical processing in forging manufacture using combinations of sub- and/or supra-beta transus forging followed by thermal treatments. Final thermal treatments consist of an anneal, at 705 to 815°C (1300 to 1500 "F) and for some applications, duplex annealing, a sub-transus solution treatment at 995°C (1825 OF) followed by air cooling prior to anneal is used to refme the final structure and enhance strength or fracture-related properties Machining. Ti-6211 is similar to Ti-5AI-2.5Sn in this respect Welding. Ti-6211 has excellent weldability. Like other titanium alloys, it is weldable by all methods except shielded arc welding and submerged arc welding (because no flux is permitted). Recommended filler metal is the same as the base metal Hot Working. Normally preformed in the beta-phase region. However, Ti-62110.8 may be processed in the alpha-beta field, which results in improved strength at some sacrifice in toughness. Hot working in the
Ti·6211: Recommended heat treatment conditions Heat \realmeDl
'IOmperature
Stressrelief Annealing Solutiontreating Aging
"C
OF
h
CooUng method
595-650 790-900 1010 620
1100-1200 1455-1650 1850 1150
0.25t02 1104 1 2
AC AC WQ AC
TIme,
Ti-6AI-2Nb-1Ta-O.8Mo: Specifications and compositions Composition, WIII> Spedlkallon
Deslgnatbn
UNS
Desaiplion
Fe
AI
R56210
H
6
Mo
N
0
Nb
0.8-8
Other
1h
balTt
2
USA AWSAS.16-70 MILT-9046J
ERI'i-6Al-2Cb-lTa-IMo COdeA-3
WeldFillMet ShStrpPItAnn
5.5-6.5 5.5-6.5
0.15 0.25
0.005 0.0125
0.5-1.5 0.5-1
0.012 0.03
0.1 0.1
1.5-2.5 1.5-2.5
0.15-1.5 0.5-1.5
CO.04;balTt CO.05; Of 0.4; balTi
Ti-6AI-2Nb-1Ta-O.8Mo: Commercial compositions Composition, WI% Speclllcalion
Deslgnalion
Deseription
AI
Fe
H
Mo
N
Nb
0
5.5-6.5
0.25
0.0125
0.5-1
0,03
1.5-2.5
0.1
Other
USA RMI Timet
RMI6AI-2Cb-lTa-lMo TIMEfAL6-2-1
0.5-1.5
C 0.05; bal Tt
Ti-6211: Summary of heat treatment and microstructure of the Widmanstatten-type structure
Ti-6211: Corrosion rates in specific media Concenlration,
'IOmperalure,
Corrosion rate,
Heattreatment
Medlum
%
"C
nnnJyr
Widmanst§tten (1+ ~ Widmanst§llen ex+~ Widmansl§llen ex + ~ Coarse,blockyprimaryex in fine Widmanst§nen ex + ~ matrix Fine Widmansllltten ex+~ WidmanstlUten ex+ ~
Ferricchloride Hydrochloric acid
10 0.5 10.0 5
Boiling Boiling Boiling Boiling
nil 0.020 1.07 0.051
Fine Widmansllltten ex+ ~ (same as No.5 exceptfor prior ~ grainsize) Widmansl§nen ex+ P(same asNo.6 exceptforprior ~ grain size) Temperedmartensite
Ti-6211: Forging process temperatures
I. 2. 3. 4.
As-received Anneal:950°C,6h,AC+700°C,2h,AC Anneal:900°C,6h,AC+700°C,2h,AC Anneal:IOW°C, Ih;FCin 10°Csteps, holding 4hateachstept0980°C, AC+ 700°C, 2h,AC 5. Anneal: 1050°C,2h,AC+700°C,2h,AC 6. Anneal:1050°C, 2h, AC + 950°C, 6h, AC+700°C,2h,AC 7. Anneal: 1050°C,4Omin,AC+700°C,2h,AC 8. Anneal: 1050°C,4Omin,AC+950°C,6h, AC+700°C,2h,AC 9. Anneal:10S00C,40 min,WQ + 800°C, I h, WQ + 500 °C,2h,AC 10. Anneal;1050°C,4Omin,WQ+700°C,2h, AC 11. Anneal:800°C, 40 min, WQ+500°C,2h,AC 12. Anneal:9S00C,40 min,WQ+500°C,2h,AC
Mkrostruclure
Temperedmartensite Widmanst§tten ex+ P Widmanst§nen ex+ ~ + martensite
Hydrochloricacid +0.1 % FeCI)
MelIIltemperalure Process
Conventional forging Betaforging
°C
OF
940-995 1040-1120
1725-1825 1895-2050
490 I Heat Treater's Guide: Nonferrous Alloys
Ti-6211: Effect of heat treatment on impact strength of 25 mm (1 in.) rolled plate Thst
Condition
dlm:lion
As-rolled
L T L T L T L T L T L T L T L T
uannealed: 870°C (1600 oF), 1h,AC u-p annealed,aircooled:990°C (1815"F), 1h,AC u-p solutiontreated,quenched:990°C (1815 oF), 1 h, WQ u-p solutiontreated,aged:990 °C (1815 oF), 1 h, WQ + 595°C (1100oF), 2 h,AC
Pannealed, aircooJed:1035°C (1900oF), 1 h,AC Psolutiontreated,quenched:1035°C (1900 oF), 1 h, WQ Psolutiontreated,aged: 1035°C (1900oF), I h, WQ + 595°C (1100oF), 2 h, AC
lOmBeyield
Chorpy V-nolch impacl
strength at RT MPa ksI
toughness at -62 °C(-80 OF) J /l·1hf
701.9 723.9 683.9 740.5 673.6 717.0 697.7 747.4 744.6 819.8 699.1 712.9 759.8 744.6 807.4 801.1
101.8 105.0 99.2 107.4 97.7 104.0 101.2 108.4 108.0 118.9 101.4 103.4 110.2 108.0 117.1 116.2
Drop weighl tear energy al 0 (32 oF)
-c
23.5 23.0 29.2 32.2 32.5 28.2 27.8 32.2 25.5 29.0 33.0 28.2 30.5 26.8 24.0 23.2
31.8 31.2 39.6 43.6 44.0 38.2 37.7 43.6 34.5 39.3 44.7 38.2 41.3 36.3 32.5 31.4
J
/l·1hf
3072 2909 3312 3858 3471 3072 3471 3312 2828 2583 3549 2665 3072 3072 2336 2909
2266(a) 2146(a) 2442 2846 2560 2266 2560 2443 2086 1905 2618 1966 2266 2266 1723 2146
Note: All valuesaverageof two testsexceptdrop weight tear values,which areindividualresults.(a)In a separatestudy on thissameheal, thefollowingresults wereobtained:3232 J (2384 ft ·Ibf) and 2418J (1784 ft ·Ibf) T direction
Ti-6211: Effect of oxygen content on ~ transus temperature. The ~ transus temperature increases in a linear manner with oxygen content at an approximate rate of 13 "O (23 OF) per 0.1 wt% oxygen. Sample ~-annealed: heated to 1065 °e (1950°F) for 2 h in a vacuum, followed by a moderate cooling rate in a helium atmosphere.
LIVE GRAPH
Click here to view
Ti-6211: Effect of oxygen content on grain size. Grain size is reduced by a factor of three when the oxygen content is increased from 0.075 to 0.290%. The grain size is more sensitive to oxygen content in low levels up to about 0.2% oxygen, beyond which further addition of oxygen does not significantly alter the ~ grain size. Sample ~-annealed: heated to 1065 "O (1950 OF) for 2 h in a vacuum, followed bv a moderate coolino rata in ~ hAliJ 1m ",t.....",,-I- , re.
1000
3. 5
1820
2. 8
E E
l!f
2. 1
'iii
c
'ii! Cl
~
o
1.4
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\
\ ~
\
~I
<;
m
I
0.7
I
f
I
940.L-_ _--l.
o
-L i
0.1
.L-_ _--I
0.2
o o
0.4
0.3
Oxygen content, wt%
0.1
0.2
r
1
T --l,
0.3
Oxygen content, wt%
Solution temperature, OF
1750 1200 Il
1800
.. •0
1100
1850
1900
1950
170
L T
160 I
150
~ 1000
i
:;;
i
~ 90 0 c: ~
0-
ii5 80 0
!
-
g>
-...a..;.;
120
Ullimate tensile strength
.I
Il
~"'i I
60o As rolled 950
140 ~ £ 130
.
~
.!-
70 Oa-
975
Ti-6211: Tensile strengths vs. solution treatment. Quenched plate, 25 mm (1 ln.) plate solution treated, 1 h, water quenched as 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks. Each data point is an average of two tests.
2000
TenSilj yield strength
i 1000
1025
I !
!
i
1050
1075
Solution temperature,
°e
~
ii5
110 100
LIVE GRAPH
90
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1100
Alpha and Near-Alpha Alloys I 491
Ti-6211: Effect of oxygen content on hardness. FiveTi-6211 alloyswith varying oxygencontents, ranging between0.075 to 0.290 wt% (0.22 to 0.87 at.%), were preparedin 125-lb heats and fabricated by upset forging and hot rollingat 1065 °C (1950 OF) followed by an annealingtreatmentat 925°C (1695OF) for 1 h and air cooling. Sampleswere then heat treatedat 1065°C (1950OF) for 2 h and air cooled. 410
34. 5
!
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-:
I
400
I
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I
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,
~39 0
/ /-
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I
/'
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o ~
VI
~ 380
'E lU
I
370
31. 5
uI VI
Q)
I
uI
c: ~ 30.0
.:
/
./
28.5
I
o
V
I
I
360
-:
LIVE GRAPH
33. 0
/'
27. 0
0.1 0.2 Oxygen content, wt%
o
0.3
0.1 0.2 Oxygen content, wt%
0.3
Ti-6211:Tensile strengths vs. solution treatment. Air-cooled plate. Solutiontreated tensile properties of plate specimens air cooled or furnacecooled fromvarioussolutiontemperatures. Specimens were25 mm (1 in.) plate solutiontreated 1 h, as 25 by 150 by 150 mm (1 by 6 by 6 in.) specimenblanks.Each data point is the averageof two tests.
LIVE GRAPH
1600
1700
1800
1100
1000 lU
n,
950
:2 sO 0, 900 c
I
j
I
i
I
i I
i
i
i
--
0 .
--
-
---
0
.. 'l
I I
I
-•
I
~
(jj 85 0
--
800
.....lZ...
~
:
900
•
o
1000
950
r
o
•
Tensile yield strength 0
I-
:
850
•
0
-+
!
700 As rolled
..
Ultimate tensile strength
~
..... f:
0
750
i I
-.e
0-
L.
~
2200
2100
i
I I
1050
Click here to view
Solution temperature, of 1900 2000
'I
I
1050 1100 Solution temperature.
2300
L AC from solution temperature AC from solution temperature FC from solution temperature to 1650 °c (900 of). AC FC from solution temperature to 1650 °c (900 of), AC T AC from solution temperature AC from solution temperature FC from solution temperature to 1650 °c (900 of), AC FC from solution temperature to 1650 °c (900 of). AC I
-1 50 _ - 140 -
-----= 1 -1 20 -
I
I
I
I
1150
1200
1250
-1 10
1300
°c
Ti-6211: Effect of quench delay on tensile properties. 25 mm (1 in.) plate; 1095 °C (2000 OF), 1 h, delay (in air), water quenchedas 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks.Eachdata point is an averageof two tests. 1100
0
"-
•
..
1000 lU
c, :2 900 sO
rnc ~
(jj
:
. "
40
L L T T
150
Ultimate tensile strength ~
:
800
==: 700
Tensile yield strength
S
LIVE GRAPH
30
140
~
130
]1 sO
rn
120 ~ (jj 110
c Q)
~ 20 Q) n,
0
.. • ..
L L T T
--
10 100
600 60 80 70 Quench delay, s
•
~
~
..•-
LIVE GRAPH Click here to view
90 50
°
Elongation in 25 mm (1 In.)
Click here to view 40
Reduction of area
90
100
0 40
50
60
70 80 Quench delay. s
90
100
492/ Heat Treater's Guide: Nonferrous Alloys
Ti-6211: Effect of aging temperature on tensile strengths. 25 mm (1 in.) plate; 1095 °C (2000 OF), 1 h, 70 s delay (in air), water quench + age, 2 h, air cooled 25 by 150 by 150 mm (1 by 6 by 6 in.) specimen blanks. Each point is an average of two tests.
Ti-6211: Effect of annealing temperature on yield strength. Effect of annealing temperature on yield strength and ductility of WidmansUitten a + p material, annealed 40 min, water quenched + 500°C (930 OF), 2 h, AC.
LIVE GRAPH
Temperature, of
800
1000
1000
1200
1400
1600 0
LIVE GRAPH
900
a~
0, c
. ~: °
0
:2
800
iii 700
•
o
0
120
"
~
.><
~
0, c
m Q)
110
400
Unaged
500
100 90
600
700
800
Aging temperature,
900
a-
50
:2 600
a+~
ui' (J) ~
t> '0
Q;
I~
1000
°c
Ti-6211: Microstructure. Plate, hot rolled with starting temperature below the ptransus of about 1000 °C (1830 OF), annealed for 30 min at 900°C (1650 OF) and air cooled. Structure: slightly elongated a grains (light) and intergranular p (dark). 10 mL HF, 5 mL HN0 3 , 85 mL Hp. 100x
40
~
ai ~
til
~
.2
400
30
g
'0
;;::
Tensile yield strength
600
60
til
'iii
~
1100 80 70
"
800
130
Click here to view
°c 1000
900
800 1000
140
Ultimate tensile strength
..
~
1800 L L
"
Click here to view
til
Temperature,
Q)
200 0 800
"
20 a:
As quenched TYS TYS RA
900
10 0 1000
1100
Temperature,oC
Ti·6211: Microstructure. Plate, hot rolled with a starting temperature of 1150 °C (2100 OF), which is above the ptransus. Structure: acicular a (light), intergranular p (dark), with boundaries of elongated pgrains. 10 mL HF, 5 mL HN03 , 85 mL Hp. 100x
Ti",6AI",2Sn",4Zr",2Mo",Om08Si Common Name. Ti-6242S Ti-6242Si UNS Number. R54620 Chemical Composition. The 6 percent aluminum addition in the Ti6AI-2Sn-4Zr-2Mo composition is a potent alpha-phase stabilizer, while the 2 percent molybdenum addition represents only a moderate quantity of this potent beta-phase stabilizer. The tin and zirconium additions are solid-solution strengthening elements that are neutral with respect to phase stabilization. The net effect of this combination of alloying elements is the
generation of a weakly beta-stabilized, alpha-beta alloy. Since it is weakly beta stabilized, the alloy is also properly described as a near-alpha, alphabeta alloy. The original composition of this alloy contained no silicon, but RMI introduced a nominal 0.08% silicon content which allowed the alloy to meet the creep requirements forits intended jet-engine applications. Before any major commercial applications were developed, all producers had added silicon to the original Ti-6242 composition.
Alpha and Near-Alpha Alloys /493 See adjoining Tables for specifications and compositions and commercial compositions
Characteristics Product ConditionlMicrostructure. TI-6242Sis sometimesdescribed as a near-alpha or super-alpha alloy, but in its normal heat treated condition this alloy has a structure better described as alpha-beta. Proper treatment is needed to develop good creep resistance. Limited hardening of TI.6242S can be done by solution treating and aging. The structures of Ti-6AI-2Sn-4Zr-2Mo alloy are typically equiaxed a in a transformed ~ matrix, or a fully transformed structure that maximizes creep resistance. The equiaxed a grains found in sheet products tend to be smaller than those found in forgings, as with other alloys, and are present in greater proportion than in forgings. Primary a is typically about 80 to 90% of the structure in sheet products and can be somewhat lower than this in forged products, because the final forging temperature is normally higher than the final rolling temperature used for sheet. As in other near-a alloys, small amounts of residual Bphase can be observed metallographically within the transformed Ill/l portion of the structure, typically between the acicular a grains of the transformed phase. Breakup of lamellar a into equiaxed a occurs during working (see Figure) Beta Transus. 995 ± 15°C (1825 ± 25 oF) Product Forms. Available mill forms include billet, bar, plate, sheet, strip, and extrusions. Cast Ti-6242S products constitute about 7% of cast titanium products Applications. Ti-6AI-2Sn-4Zr-2Mo-0.08Si (Ti-6242S or Ti-6242Si), is an elevated-temperature alloy with an outstanding combination of tensile strength, creep strength, toughness, and high-temperature stability for long-term applications at temperatures up to 425°C (795 OF). Ti-6242S is one of the most creep-resistant titanium alloys and is recommended for use up to 565°C (1050 "F). Proper heat treatment is important in allowing the alloy to develop its maximum creep resistance. Ti-6242S is used primarily for gas turbine components such as compressor blades, disks, and impellers, and also in sheet-metal form for engine afterburner structures and for various "hot" airframe skin applications, where high strength and toughness, excellent creep resistance, and stress stability at temperatures up to 565°C (1050 OF) are required General Corrosion Properties. The corrosion resistance ofTi-6242 in various media is not well documented, although it is probably comparable to other Ti-6AI-base alloys such as Ti-6AI-4V. The molybdenum content of Ti-6242 is not high enough to impart additional corrosion resistance in reducing environments. The crevice corrosion resistance of Ti-6242 is probably less than grade 2 titanium, because crevice corrosion generally is associated with acidification from oxidant depletion Oxidation. A blue oxide film typically forms in about 6 to 10 h in exposures not exceeding 540°C (1000 "F), Degradation of mechanical properties from oxidation at longer times and usual service temperatures has not been observed. In a strong oxidizing environment, resistance is probably comparable to grade 2 titanium or Ti-6AI-4V
Fabrication Properties Forging. Ti-6242 (and its modification Ti-6242S) is a near-alpha alloy produced commercially in all forging product types, although closed die forgings and rings predominate. The alloy is fabricated using all commercially available types of forging equipment. The silicon-modified version, Ti-6242S, but to its superior creep performance, predominates in commercial forging applications and is a preeminent titanium alloy for elevatedtemperature service criteria, particularly rotating and static parts in turbine engines and heated airframe structures. For turbine engine disc forgings, hot die and isothermal forging technologies are important forging fabrication methods, producing near-net closed die forged product with significantly less machining ForminglWelding. Some forming operations can be carried out at room temperature, and warm forming (425 to 705°C, or 795 to 1300 "F) is employed when necessary. Ti-6242S has fair weldability. The molten weld metal and adjacent heated zones must be shielded from active gases (nitrogen, oxygen, and hydrogen)
Recommended Heat Treating Practice A variety ofheat treatments for Ti-6242 are possible. A particular condition is usually selected on the basis of product type, part section size, and properties desired Annealing. Several different annealing treatments are available. Choice depends on the product form and the section size of the product as well as on the properties desired (see Tables). A general annealing treatment consists of a I to 8 h exposure at 705 to 845°C (1300 to 1555 "F) followed by slow cooling to 565 "C (1050 "F) and subsequent air cooling. For bar and forged sections, solution annealing for I hat 900 to 955°C (1650 and 1750 OF) plus stabilization annealing for 8 h at 595°C (1100 OF), and air cooling are recommended. In this condition, the guaranteed room-temperature properties of 25 mm (I in.) diameter bar are as follows: Strengthening Heat Treating. Ti-6242 may be heat treated to obtain higher uniaxial tensile strengths by conventional solution heat treatment and aging exposures. Because the ~ content of this a-~ alloy is small, the response to such a strengthening heat treatment is not great. Furthermore, material in the solution treated and aged condition has lower creep strength than that is the annealed-plus-stabilized condition. See adjoining Tables and Figures for information on general types of heat treatment, annealing treatments for sheet, annealing treatment for bar and forgings, and duplex and triplex annealing strengths
Ti-6242S: Forging process temperatures MetaIlemperalure
OF
°C 900-975 1010-1065
Process
Conventional forging Betaforging
1650-1785 1850-1950
Ti-6242: Annealing treatments for bar and forgings 'Iemperature
Stress Corrosion Cracking. Under stress, Ti-6AI-2Sn-4Zr-2Mo has been shown to be subject to stress-corrosion cracking (SCC)-at room temperature in the presence of aqueous chloride solution and a preexisting crack (the so-called accelerated crack-growth type of salt-stress corrosion) and at elevated temperatures in the presence of a halogen salt (e.g., NaCI). The SCC susceptibility ofTi-6242 in hot salt appears to be less than that of Ti-8AI-IMo-IV and Ti-6AI-4V (see Figure). In ambient salt solution, the SCC threshold of Ti-6242 in the STA condition in comparable to mill annealed (MA) Ti-8AI-IMo-lY. Triplex annealing appears to improve resistance to cracking slightly versus a duplex anneal
'treatment
0C
Sections <63.5 mm (2.5 ln.) dlam Anneal 955 Stabilization 595 Sections >63.5 mm (2.5 In.) diam Anneal 900 or 955(a) Stabilization 595
Cooling method
OF
1750 liOO
1 8
AC AC
1650or 1750(a) liOO
1 8
AC AC
(a) The 900 °C (1650 "P) treatment,alongwith the 595°C (1i00 "F) stabilizationanneal,provides somewhathighertensilestrengthsat roomand elevatedtemperatures,whereasthe955°C (1750 oF) treatmentcombinedwith595 °C (IiOO"F) stabilizationas aboveresultsinsuperiorcreepresistance at thehigher temperaturesand improvedstability
494/ Heat Treater's Guide: Nonferrous Alloys
Ti-6AI-2Sn-4Zr-2Mo-O.08Si: Specifications and compositions Composllion, wt % Other
AI
Fe
H
Mo
N
0
So
Zr
6 5.5-6.5
0.05
0.015
2 1.8-2.2
0.15
0.3
2 1.8-2.2
4 3.6-4.4
baITI CO.04;CrO.25;balTi
5.5-6.5
0.25
0.Q15
1.8-2.2
0.05
0.15
1.8-2.2
3.6-4.4
CO.05;balTI
Sh StrpPltAnn
5.5-6.5
0.25
0.015
1.8-2.2
0.05
0.12
1.8-2.2
3.6-4.4
C 0.05; OTO.4;bal TI
ShSIrpPlt
5.5-6.5
0.25 max
1.8-2.2
0.05 max
0.12 max
1.8-2.2
3.6-4.4
AMS4919G AMS4975E AMS4975F
Sh Strp PItDA 5.5-6.5 Bar WrrRug Bil STA 5.5-6.5 BarRng HT 5.5-6.5
0.25 0.25 0.1 max
1.8-2.2 1.8-2.2 1.8-2.2
0.05 0.05 0.05 max
0.12 0.15 0.15 max
1.8-2.2 1.8-2.2 1.8-2.2
3.6-4.4 3.6-4.4 3.6-4.4
AMS4976C AMS4976D
FrgSTA FrgHT
5.5-6.5 5.5-6.5
0.25 0.1 max
1.8-2.2 1.8-2.2
0.05 0.05 max
0.15 0.15 max
1.8-2.2 1.8-2.2
3.6-4.4 3.6-4.4
ExtBar ShpAno Ext Bar Shp STA CastAno ShSIrpPltDA ShSIrpPItTA Bar BilDA BarBilSTA
5.5-6.5 5.5-6.5 5.5·6.5 5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5
0.25 0.25 0.35 0.25 0.25 0.25 0.25
0.Q15 max 0.Q15 0.0125 0.0125 max 0.0125 0.0125 max 0.015 0.015 0.015 0.Q15 0.Q15 0.Q15 0.Q15
1.8-2.2 1.8-2.2 1.5-2.5 1.8-2.2 1.8-2.2 1.8-2.2 1.8-2.2
0.04 0.04 0.05 0.04 0.04 0.04 0.04
0.15 0.15 0.12 0.15 0.15 0.15 0.15
1.8-2.2 1.8-2.2 1.5-2.5 1.8-2.2 1.8-2.2 1.8-2.2 1.8-2.2
3.6-4.4 3.6-4.4 3.6-4.4 3.6-4.4 3.6-4.4 3.6-4.4 3.6-4.4
CO.05max; Si 0.06-0.1; YO.005max; OEO.l max;OTO.3 max; bal TI CO.05;SiO.l; YO.005;OTO.3; balTI CO.05;YO.005;OTO.3; sio.i: bal TI C 0.05 max; Si 0.06-0.1; Y 0.005 max; OEO.1 max; OTO.3 max; bal TI C 0.05; Y 0.005; OTO.3;Si 0.1; bal TI C 0.05 max; Si 0.06-0.1; YO.005max; OEO.l max;OTO.3 max;bal TI CO.05;YO.005;Si 0.06-0.1; OTO.3; bal TI CO.05;SiO.06-0.1;YO.005;OTO.3; bal TI CO.08;OTO.4;bal TI CO.05;OTO.3;bal TI CO.05;OTO.3;bal TI C 0.05; OTO.3;YO.005; bal TI C 0.05; Y 0.005; OT 0.3; bal TI
Specllication
Designation
UNS UNS Germany
R54620 R54621
Description
WeldFill Met
WL3.7144 Spain UNE38-718 USA AMS4919C
L-7103
MILT-81556A MILT-81556A MILT-81915 MILT-9046J MILT-9046J MILT-9047G MILT-9047G
CodeAB-4 CodeAB-4 JYpeillCompB CodeAB-4 CodeAB-4 Ti-6AI-2Sn-4Zr-2Mo TI-6AI-2Sn-4Zr-2Mo
Ti-6AI-2Sn-4Zr-2Mo-O.08Si: Compositions Specllication France Ugine Germany DeutscheT DeutscheT DeutscheT Fuchs Japan Kobe USA OREMET RM1
TIMEr
Designation
Des
Fe
AI
Mo
H
Compo,ition, wI% 0 N
UT6242
BarFrgAno
5.5-6.5
ContimetAlSnZrMo6-2-4-2 ContimetAlSnZrMo6-2-4-2 LT24 TL62
PItBar FrgAnn PltBarFrgSTA Aged Frg
5.5·6.5 5.5-6.5 5.5-6.5 6
0.25 0.25 0.25
0.Q15 0.Q15 0.015
1.8-2.2 1.8-2.2 1.8-2.2 2
0.05 0.05 0.05
KS6-2-4-2
BarFrgSTA
5.5-6.5
0.25
0.015
1.8-2.2
TI-6242 RMI6AI-2Sn-4Zr-2Mo-O.lOSi TIMETAL6-2-4-2
Bar Bil PItSh STA BarBilPltShSTA
5.5-6.5 5.5-6.5
0.25 0.25
0.01-0.0125 0.01-0.0125
1.75-2.25 1.75-2.25
Other
Sn
1.8-2.2
3.6-4.4
0.15 0.15 0.12
1.8-2.2 1.8-2.2 1.8-2.2 2
3.6-4.4 3.6-4.4 3.6-4.4 4
0.05
0.15
1.8-2.2
3.6-4.4 balTI
0.05 0.05
0.12 0.12
1.75-2.25 1.75-2.25
1.8-2.2
CO.05;SiO.06-o.12;balTI CO.05;SiO.06-o.12;balTI CO.05;balTI balTI
3.5-4.5 CO.08;SiO.1;bal TI 3.5-4.5 CO.OS; Si 0.1;bal TI
Ti-6242: Effect of heat treatment on saltwater SCC of sheet
(precracked) Applied Heat treatment(.) 730°C (1345 oF),8 h, FC
900 °C (1650 oF), 30 min,AC + 785°C (1455 OF), 15 min,AC 900 °C (1650 oF), 30min,AC+785°C (1455 oF),15min, AC+595°C (1100oF),8 h,AC (a) No failure,lest discontinued
Time10 rupture
net stress
MP. 617 466 308 551 586 689 758 551 586 620 689
Ti-6242: Effect of thermomechanical processing on tensile properties
in3.5%
ksi
89.5 67.7 44.7 80 85 100 110 80 85 90 100
N.CI Broke on loading I min 7 min >73h(a) >42h(a) >43h(a) >68h(a) >48 h(a) >42h(a) >24h(a) >2h(a)
Condition Ti-6242 a+ p forged +STA(a) Ti-6242 + 0.25 wt% Si a + Pforged + 965°C (1770 "F), 1 h, AC+595 °C (1100oF),8h,AC a+ pforged+%5°C(I770°F), 1 h, WQ + 595°C (1100oF),8 h, AC p forged+ 965 °C(1770°F),lh, AC + 595°C (1100oF),8 h, AC pforged+%5°C(I770°F),lh, AC + 595°C (1100oF),8 h,AC
ThnsiIe yield strength MP. ksi
UItimote temlle strength ksi MP.
RedudioD
Elongation,
or.......
%
%
1028
149
938
136
16
35
1007
146
1063
154
13
34
1090
158
1187
172
12
20
952
138
1035
150
11
25
1042
151
1145
166
7
15
(a) STA= 985°C (1805 oF) (Tp-15 °C (27 0F), air cool +595 °C (1100 oF),8 h, air cool
Alpha and Near-Alpha Alloys I 495 Ti-6242: Design tensile properties of duplex annealed bar, forgings, and triplex annealed sheet Product
Ultimatetensilestrength MPa IIsI
Basis
Bar and forgings s:TS mm (3 ln.) thick STA(duplexannealed)bar(b)perAMS4975
S
896(e) 951(d) 993(d) 896
130(b) 138(d) 144(d) 130
S
999(g)
145(g)
S A B
STA(duplexannealed) forgings(e) per AMS4976 Triplex annealed (TA)sheet(t) Sheet~.75 mm (0.187in.)perMIL-T-9046
TeIl5iJe yieldstrength MPa IIsl
EIongatioo(a), 'I
RA(a), 'I
827(e) 862(d) 903(d) 827
120(e) 125(d) 131(d) 120
lO(e)
25(e)
lO(e)
25(c)
930(g)
135(g)
(g)
2
Note: Propertiesapplicablein L, LT,andST directions,exceptas noted.(a) S-basis.(b) Cross-sectional arealess than 103em (16 in.\ (e)Applicablein LTand ST directioniftransversedirectionis greater than63.5 mm (2.5 in.),(d)Longitudinaldirectiononly.(e)Cross-sectionalarealess than58 em2 (9 in.\ (t) S-basisvaluesare representative oftest specimensexcisedfromduplexannealedmaterialand then treatedto achievea triplexannealedeonditionin the labomtory. (f) Specifiedonly inL andLTdirections. (g)8% for 0.64 to 1.57mm (0.025to 0.062in.) and 10%for thieknessabove 1.57mm (0.062in.)
Ti-6242S: Mechanical properties of alloy forgings Forgel healtreat conditious
Creepta),
htoO,2'1 strain
KI<
time(h), h
MPa'liii lIsi'liii:'
TIS MPa lIsi
81 -71(e) -49(e) -38(e) -55 (e) -77(e) -82(e) 83 79
903 924 951 1068 896 930 937 896 841
325
199 169 56 19 164 185 160 116 134
(u+IWP (u+P)/P (u+ P)/(u+b) (u+P)/P (u+P)/(u+P) p/(u+P) p/(u+P) p/(u+P) PIP
RT
Creep rupture
275
74 -65(e) -45(e) -35(e) -50(e) -70(e) -75(e) 76 72
131 134 138 155 130 135 136 130 122
4800C TIS MPa ksI
Elongation, 'I
13 10 14 3 14 11 10 11 7
(900°F)
Post-«eep
Elongation, 'I
TIS
MPa
ksI
Elongation, 'I
537 565 593 855 565 579
78 82 86 124 82 84
13 11 15 5 17 17
889
129
10
565 551
82 80
15 12
924 882
134 128
12 12
(a) Creepcondition:565°C (1050 "F), 172MPa (25 ksi). (b) Creeprupture:565°C (1050 "F), 344MPa (50ksi).(e) Estimatedvalue
Ti-6242: General types of heat treatment Heat
Ti-6242: Annealing treatments for sheet
Temperature
Stressrelief(a) Annealing Solutiontreating Aging
480-700
900-1295 0.25-4 Variesbyproduct form 1750-1795 1 1000-1100 8
955-980 540-595
Cooling
Time, h
OF
°C
treatment
method
AC or slowcool WQ
AC
(a) Stressreliefvariesdependingon theportionof residualstress to be relieved
Ti-6242S: Alpha content vs. solution temperature. Solution treated, 1 h, AC + 595°C (1100 OF), 8 h, AC
OF
Duration, h
CooUog
°C 900 785
1650 1455
0.5(a) 0.25
AC AC
900 785 595
1650 1455 1100
2.5(a) 0.25 2
AC AC AC
Temperature 'Ireatmeot
Duplexanneal 1ststage 2ndstage Triplexarmeal(b) 1ststage 2ndstage 3rdstage
method
(a) For sheetless than 3.1 mm (0.125in.) in thickness,a shorterannealtime at 900 °C (1650 "F) is recommended. Ten minutes has been suggested. (b) The advantage of triplex anneal is higher uniaxialstrength
Solution temperature below transus, AOF
-90
-120
-60
o
-30
o
Ti·6242: Time-temperature-transformation diagram
LIVE GRAPH
10 1
1050
Click here to view
20 :
993°C 1800
1
-a. 30r iii
1900
P o
I
o
'I /r: ___~/-_o.?
;t 501 0
60l
Y
P
-40
E
OJ
1500 {!!.
t-
Beta transus ----'"
-10 Solution temperature below transus, A°C -50
-30
-20
0
e-
1600 ~ a.
OJ
a.
/
!!,3
~
C
E
o -----''-----60
1700
e-
:::l
/'
70'_' -70
,
/
~40: E I
1400
750
(1.'
700 1
10 Time, s
LIVE GRAPH Click here to view
1300 100
496/ Heat Treater's Guide: Nonferrous Alloys
Ti-6242: Effect of silicon on beta transus temperature
Ti-6242: Comparison of CCl diagram and isothermal diagram LIVE GRAPH Click here to view
1010,-----------------.1850 1000
.~
P 1000
1700
u..
1830 ° •
/
vi
til
~
illc:
til
c:
jg
m~
«l 1820 ::.
/ 990
•
I
i
• •
1810
Click here to view
o
0.04
900
p
e! ~
e
0.2
750
Gl
--Heat A HeatB HeatC HeatD
Gl
I-
705
650
0.1
Ti-6242: RT hardness vs. high-temperature exposure. Duplex annealed sheet, 1.0 mm (0.040 in.) thick, heat treated for 30 min at 900°C (1650 OF) and air cooled. then for 15 min at 790 °C (1455 OF), and air cooled Click here to view
I
400
Temperature, of 600 800 1000
~
36
~~' li 34~
.
~ 32
L 100 h .. 1000 h
l'!
c
.-
:E 400 480°C (900 OF)
600
750
200
Temperature, OF 400 600 800
Click here to view 1000
1100
~O_
.~
300 450 Temperature,oC
LIVE GRAPH
100
~-
li
'lii 500 E ~ E
~
150
Ti-6242: Duplex and triplex anneal strength. Elongation ductility is similar for both treatments
90
:E
•
30'---
Click here to view RT «l600
.
As received • 10 h
o
LIVE GRAPH
.'
C
J:
I
..,.
.. Exposure time
~
J1300
1200
38
100
10 Time,s
n,
100
LIVE GRAPH
Ti-6242: RT and 480°C fatigue properties of duplex annealed bar. Specimens were 28.5 mm (1.125 in.) diameter bar duplex annealed at 970°C (1775 OF), 1 h, AC + 595°C (1100 OF), 8 h, AC. Ultimate tensile strength, .1006 MPa (146 ksi); tensile yield strength, 958 MPa (139 ksi); smooth, rotating beam tests 700
1300
10
'-----~_~~~...L-_~~~~"--"-'h200
1
transformation
650
0.24
j'000. j,~O
a+p
a. E
~ontinuous cooling a+p
200
P
e 760
!'
P
-
--Duplex anneal Triplex anneal UTS
1000
~ 80
vi
!II
l'!
'lii 70 E ~ E .~
60 :E 50
300
«l 900 n, :E vi 800 700
140 130 'iii
120 "". !II !II
til
~
150
110 ~ Ul
TYS(0.2%)
100 90
600
80 500
4
10
5
10
6
10 Cycles to failure
~a.
E Gl 1400 I-
Gl
1600
~
~
1500
700
Click here to view
~
l'!
Time,s
870
P
u..
1600 ° .
a. 800 E
I-
1800
Ti-6242: Continuous cooling transformation diagram. Effect of heat-to-heat variations, within specification, on continuous cooling transformation LIVE GRAPH
815
ptransus a+p
Gl
__'__ _____'
0.08 0.12 0.16 Silicon, wt%
Isothermal transformation
850
LIVE GRAPH
980'--_---'---_~ _ __'___~_
1800
P
950
1840
7
10
6
10
0
100
200 300 400 Temperature.vc
500
600
Next Page Alpha and Near-Alpha Alloys I 497
Ti-6242: Microstructure. Alpha-beta forged billet macroslice illustrating "tree rings," which represent minor composition fluctuations. The slices are from two ingot locations. 0.63x
Ti-6242: Fatigue strength of duplex annealed forgings at 315 and 480 °e. Specimens were compressor disk forgings duplex annealed at 955 °C (1750 OF), 1 h, AC + 595°C (1100 OF), 8 h, AC. Specimens were stress relieved at 540°C (1000 OF), 2 h in vacuum before testing. Reverse bending (cantilever); R = -1; frequencv. 120 cvcles/s 300 315°C (600 OF)
ro 250
c.. :2
~40
..
~
1ii 200 E ~
480°C (900 OF)
.~
:2 150
-.,20 Notched specimens, K, = 3
LIVE GRAPH Click here to view
Ti·6242: Microstructure. Test bar taken from finished forging was reheated to 995°C (1825 OF), the beta-transus temperature. The microstructure consists entirely of alpha prime. Test bar was etched with Kroll's reagent (ASTM 192). 100x
Alpha-Beta Alloys Ti-5AI-2Sn-2Zr-4Mo-4Cr Common Name. Ti-17 UNS Number. R58650 Chemical Composition. Ti-17 may be classified as a "beta-rich" alphabeta alloy, because it has a beta-stabilizer (Mo + Cr) content of 8% See Tables for specifications and compositions, and for commercial compositions
Characteristics Phases and Structures. Various types of phase transformations can be achieved by the decomposition of ~ during continuous quenching and isothermal treatment of Ti-17. At high isothermal temperatures or low cooling rates, the transformation structure has a characteristic Widmanstiitten or basketweave appearance, with a thick a layer initially nucleated along grain boundaries. The prior ~ phase transforms to a Widmanstiitten a + ~ mixture by nucleation and growth according to the classical Burger orientation. At temperatures above 500°C (930 "F), the a forms first on the grain boundaries and then grows into the ~ matrix. Below 500°C (930 "F), a precipitates and grows throughout the ~ matrix as well as in the ~ grain boundaries. At moderate cooling rates, the fineness of the a structure increases and is fairly uniform over the matrix, with some preference for a formation at prior ~ grain boundaries as cooling rates increase Beta Transus. 890°C (1635 OF) See Figures for continuous cooling transformation diagram, and for isothermal transformation diagram
quently produced using hot die or isothermal forging techniques, resulting in near-net closed die forgings with reduced final machining. Ti-17 is a highly forgeable alloy with lower unit pressures (flow stresses), improved forgeability, and less crack sensitivity than the a-~ alloy Ti-6Al4Y. The final microstructure of Ti-17 forgings is developed by thermomechanical processing in forging manufacture tailored to achieve specific microstructural and mechanical-property objectives. Thermomechanical processes use combinations of subtransus and/or supratransus forging followed by subtransus thermal treatments to fulfill critical mechanical-property criteria. Final thermal treatments for Ti-17 forgings include two- or three-step practices of single or two-step solution treatments followed by quenching and aging. Solution treatment is subtransus, at 800 °C (1470 "F), followed by water quench or fan air cool for thin sections. For forgings fabricated conventionally, a solution anneal at 855°C (1570 "F), followed by an air cool, may be used to improve toughness and creep properties. Aging treatment is conducted at 620°C (1150 "F), Subtransus thermomechanical processes (forging and thermal treatment) for Ti-17 forgings achieve equiaxed (20 to 30%) a in transformed ~ matrix microstructures that enhance strength, ductility, and particularly low-cycle fatigue properties. Supratransus thermomechanical processes (beta forging followed by subtransus thermal treatments) achieve transformed, Widmanstiitten a microstructures that enhance creep and/or fracture-related properties
Ti-17: Forging process temperatures
Product Forms. Ingot, billet, forgings Applications. Ti-17 is a high-strength, deep harden able, forging alloy that was developed primarily for gas turbine engine components, such as disks for fan and compressor stages. Ti-17 has strength properties superior to those of Ti-6AI-4V, and also exhibits higher creep resistance at intermediate temperatures. This alloy is used for heavy-section forgings up to 150 mm (6 in. thick) for gas turbine engine components and other elevated-temperature applications demanding high tensile strength and good fracture toughness. It is used only by General Electric
Melallemperulme
Process
Conventional forging Belaforging
°C
OF
800-845 915-940
1470-1555 1680-1725
Recommended Heat Treating Practice
Fabrication Properties
The recommended heat treatment depends on process history. For a-~ processed material, the heat treatment consists of a double solution treatment followed by aging. The first solution treatment should be done at 815 to 860°C (1500 to 1580 "F) for 4 h, followed by rapid air cooling. The higher temperature (855°C, or 1570 OF) produces higher toughness as a result of an increased amount of acicular or, which precipitates both during cooling and subsequent heat treatment: The second solution treatment is done at 800°C (1470 "F) and nucleates additional acicular a and produces a ~ matrix, that is responsive to subsequent aging. Fan air cooling may be used from the second solution treatment for sections up to 75 mm (3 in.) thick, although more consistent and slightly higher strengths are achieved with a water quench. Heat treatment of ~-processedmaterial includes only a single 800 °C (1470 OF) 4 h solution treatment, because acicular a is already nucleated or precipitated during cooling from the forging temperature. An aging treatment of 620 to 650°C (1150 to 1200 "F) for 8 h is recommended for both the a-~ and ~ processed material.
Forging. Ti-17 is a high-strength, highly beta-stabilized, a-~ (near-beta) alloy whose primary commercial application is turbine engine rotating components. It can be fabricated into all forging product types, although closed die forgings and rings predominate. Ti-17 is commercially fabricated on all types of forging equipment. Turbine engine disks are fre-
Ti-17 can be heat treated to yield strengths of 1030 to 1170 MPa (150 to 170 ksi). It is more ductile than Ti-6AI-6V-2Sn, and it is superior to Ti-6AI-4V in creep behavior. With hardenability characteristics comparable to those of some beta type alloys, Ti-17 is lower in density and higher in modulus. and creep strength than the beta alloys.
General Corrosion Properties. No data are available on the corrosion of Ti-17, but it should be susceptible to stress-corrosion cracking because its aluminum content is above 3 wt%. Corrosion may be similar to that of Ti-6AI-2Sn-4Zr-2Mo given the comparable compositions Mechanical Properties. Typical hardness is 39 to 40 HRC. Ti-17 retains a high fraction of its strength at elevated temperatures. Its notched tensile to tensile ratio is also stable at elevated temperatures. See Tables for typical tensile properties of parts at various temperatures after solution treating and aging, and for typical notch tensile properties of parts under same conditions, and for typical creep properties of parts under same conditions
Alpha-Beta Alloys /515 In addition, see Figures showing the effect of aging temperature or tensile yield strength, effect of solution temperatures on tensile strength, and effect of solution treatment on aged strength
See Table for three treatments: double solution treat and age; solution treat and age; and stress relief
Ti-5AI-2Sn-2Zr-4Mo-4Cr: Specifications and compositions
UNS
R58650
Composition, wt'1> N Sn
AI
Cr
Fe
H
Mo
4.5-5.5
3.5-4.5
0.3 max
0.0125 max
3.5-4.5
0.04 max
1.5-2.5
1.5-2.5 Mn 0.1 max; OJ 0.1max;00.08-0.13; CO.05max;OT 0.3 max;OEO.1 max;Y0.005max;balTI 1.5-2.5 MnO.1max; OJ 0.1max;00.08-0.13; CO.05;OTO.3; YO.005;balTI 1.5-2.5 Mn 0.1 max; OJ 0.1 max;00.08-0.12; CO.05;OTO.3; YO.005;balTI
Specillcation Designation Description
USA AMS4995
BUSTA
4.5-5.5
3.5-4.5
0.3
0.0125
3.5-4.5
0.04
1.5-2.5
AMS4997
Powd
4.5-5.5
3.5-4.5
0.3
0.0125
3.5-4.5
0.04
1.5-2.5
Other
Ti-5AI-2Sn-2Zr-4Mo-4Cr: Comrnerclal'Composltlons Specill
Designation
Desaiption
KS5-2-2-4-4
BarFrgSTA
AI
Cr
Fe
H
4.5-5.5
3.5-4.5
0.3
0.0125
Composition, WI '1> Mo N
3.5-4.5
0.04
Other
Sn
Zr
1.5-2.5
1.5-2.5
00.08-0.13; bal Ti
TI-17 TIMETAL17
TIMEf
Ti-17: Typical STA tensile properties 'IenslJe yield
24 93 205 315 370
Ultimate tensile strength MPa ksl
strength
'Iemperature "C OF 75 200 400 600
700
MPa
ksi
1035-1075 930-1000 795-860 760-825 700-760
150-170 135-145 115-125 110-120 100-110
1105-1240 1035-1105 930-1000 930-1000 860-930
Ti-17: Typical STA notch tensile properties 'Iemperature OF °C 24 93 205 315 370
75 200 400 600 700
Notched tensile strength(a) MPa ksi 1380-1515 1450-1515 1380-1450 1275-1345 1275-1345
200-220 210-220 200-210 185-195 185-195
Reduction Elongation, '1>
160-180 150-160 135-145 135-145 125-135
Stress
OF
MPa
ksi
205
400
315
600
425
805
480 510
900
999 982 979 965 948 896 793 482 482
145 142.5 142 140 137.5 130 115 70 70
950
20-45
30-45 30-45 30-45 30-45
Ti-17: Typical STA creep properties 'Iemperature OF °C NTSjUTS 1.3 1.4 1.4 1.4 1.4
Ti-17:Creep-rupture of a-p processed forging Temperature
'1>
8-15 8-15 8-15 8-15 8-15
205
400
315
600
425
805
Stress
(a)K,=4.0
°C
orarea,
MPa
ksi
nmeto O.2'1>,h
793 814 690 724 745 241 310 345 414
115 118 100 105 108 35 45 50 60
2200 400
1000 500 125 150 75 75 30
Ti-17: Recommended heat treatments nme, h 0,01 >671.9 793.6 0.1 >670.5 >721.5 8 >140 -16
Note: Spoolforgingswereheattreatedat 845·C (1555 "P) for 4 h, aircooled,then800 °C (1470"F) for 4 h, furnaceair cooled,and aged at 620 °C (l150 "F) for 8 h, air cooled
Treatment Double solution treat and age STI ST2
Age Solution treat and age ST Age Stress relief Beforemachining Other
Tempemture OF °C
Duration,
Cooling
h
method
860 800 620
1580 1470 1150
2 4
WQ
AC
8
AC
800 635
1470 1175
4 8
AC AC
550 480-650
1020 900-1200
4 1-4
AC AC or slowcool
516/ Heat Treater's Guide: Nonferrous Alloys
Ti·17: Effectof agingtemperature on tensileyieldstrength. Alpha-beta processed disks heat treated at 855°C (1570 OF), 4 h, AC, 800 °C (1470 OF), 4 h, water quench (WO) or oil quench (00) or fan air cool (FAC)
LIVE GRAPH
Click here to view
Aging temperature, of 1200
1100
1300 180
1250
170 1150 160
lU
00;
a-
.>l
::i:. 1050 s:
wa/oa
0> c ~
1ii u
iii
150
950
>= 850
~ c
----"""-25 mm -50mm ----+--125-175 mm FAC -025mm -050mm -tJ.125-175mm
~
140
~ iii
>= 130 120
750
110
550
650 Aging temperature,
600
n-17: Effectof solution temperatures on tensile strengths. Alpha-beta processed disk forgings heat treated at 855°C (1570 OF), 4 h, AC + solution treated, 4 h, WO, 620°C (1150 °F), 8 h, AC
700
750
"c
Ti·17: Effectof solution treatmenton aged strength. Solution treated at indicated temperature for 4 h, WO, and aged at 635°C (1175 OF) for8 h
LIVE GRAPH Click here to view
LIVE GRAPH Click here to view 1300 1400
1600 200
lU
a-
180
::i:
~ 1200
::i: 1300
~ N
~
.c
170
~
~
I
1600 200 190 ~
I
:
'i
180
0>
170 ~
e
1ii
1ii
u
iJ 1100
160
1100
~ s:
0> c
Ii)
Ii)
Beta-processed Alpha·bela processed
II
0 ;; 1200
0>
c
I
°
lU
a-
190
1300
Solution temperature, OF 1500 1400
1300 1400
160 iii
>=
>= 150
150
1000
1000
700
750 800 850 Solution temperature, °c
900
700
Temperature, of 1480 1500 1520 1540 1560 1580 1600 1620 1640 80
in.) thick compact tension specimen from 457 mm (18 in.) diam x 50 mm (2 in.) thick disk forging. Indicated solution temperature plus 785°C (1445 OF), 4 h, WO + 620°C (1150 OF), 8 h
70
-;,60/-----f----+-----cf--+------1 ";(9~ 50 -;; l3m '" m c c .£:
.£:
~ ~~ B 401-------+-----,.+----+----::1 B ~
~
~
1124 MPa (163 ksi) YS
~a
~
I
~
MPa (165 ksl)'--'YS 20L..-_1137 _~ 800
825
900
Ti·17: Effectof solution temperature ontoughness. 25 mm (1
E ~ a::i:
~
800 850 750 Solution temperature, °c
~
---'-
--'20
875
900
LIVE GRAPH Click here to view
Alpha-Seta Alloys /517
Ti-17:Continuous coolingtransformation cliagram. Solution treated at 930°C (1700 OF) for 30 min
LIVE GRAPH Click here to view
100 0
I
I
j
- - -
JI
-
800
o °
PI
II
I !
600
~
-
-
_ ,_ p_tr~nsu~
-
~.
~Fine
G:ain boundary
'. i a layer
'\..
'-:-
Ol
c.
E 400
-
-
{ IX
L "Start
1
I
- z
.:
-
-
- : "- 1 500
Widmanstiilten IX plates LL
phase -
:
:
Finish
-
°PI ":'1 000 ::> ~
Ol
c.
E
I
~
II
,,
i I I
200 ~.
,
I
Undercooled p phase
o
I
1
10
~
a+ pmixture
i
I I
, I
~
i
- 500
I !
I
Time, s
Ti-17: Isothermal transformation diagram. Solution treated at 930°C (1700 OF)
LIVE GRAPH Click here to view
1000
I I
Start Finish
i
LL
°ai -1000 :;
~
I
Ol
c.
I Undercooled p phase
E
400-,
~
I ! 01.-..
1
I'--
'--
--'-
I
--'-
--'
10 Time, S
Ti-6AI-2Sn-4Zr-6Mo Common Name. Ti-6246 UNS Number. R56260 Chemical Composition. Ti-6246 is a solid-solution-strengthened alloy that responds to heat treatment as a result of the beta-stabilizing effect of
its 6% molybdenum content. Silicon additions (0.08 wt%) improve creep resistance. As for all alpha-beta alloys, excessive amounts of aluminum, oxygen, and nitrogen can decrease ductility and fracture toughness. See Tables for specifications/compositions and for commercial compositions
518/ Heat Treater's Guide: Nonferrous Alloys
Characteristics Phases and Structures. Special ingot melting practices must be employed, particularly during final melting, to minimize microsegregation of the beta-stabilizing element, molybdenum, which could result in "beta flecks." Forging and heat treating practices require special controls to minimize beta flecks, which could result in microregions of high strength and low fracture toughness. Beta flecks are less of a problem for Ti-6246 than for Ti-17. The microstructure of Ti-6246 is typically equiaxed primary a in a transformed ~ matrix; this can vary, depending on processing and heat treatment history. A microstructure with an optimum combination of strength, ductility, and toughness contains about 10% equiaxed a (primary a) plus a transformed ~ matrix with relatively coarse secondary a and aged ~
Beta Transus. 935°C (1715 oF). The 1020 °C transus in figures on p 520 is
final microstructure of forgings is developed by thermomechanical processing in forging manufacture tailored to achieve specific microstructural and mechanical-property objectives. Thermomechanical processes use combinations of subtransus and/or supratransus forging followed by subtransus thermal treatments to fulfill critical mechanical-property criteria. Final thermal treatments for forgings include two-step practices of solution treatments followed by quenching and aging. Solution treatment is subtransus at 870 to 900°C (1600 to 1650 OF), followed by water or oil quenching and/or fan air cooling for thin sections. Aging is conducted at 535 to 620 °C (995 to 1150 OF). Subtransus thermomechanical processes (forging and thermal treatment) for forgings achieve equiaxed a (20 to 40%) in transformed ~ matrix microstructures that enhance strength, ductility, and particularly low-cycle fatigue properties. Supratransus thermomechanical processes (~ forging followed by subtransus thermal treatments) achieve transformed, Widmanstatten a microstructures that enhance creep and fracture-related properties such as fatigue-crack growth resistance
suspect
Product Forms. Primarily billet and bars for forging stock Applications. Ti-6246 is designed to combine the long-term, elevatedtemperature strength properties of TI-6Al-2Sn4Zr-2Mo-0.08Si (fi-6242S) . with much-improved short-term strength properties of a fully hardened alpha-beta alloy. lt is used for forgings in intermediate-temperature sections of gas turbine engines, particularly in compressor disks and fan blades. This alloy is used at lower temperatures than Ti-6242S, but should be considered for long-term load-carrying applications at temperatures up to 400°C (750 OF) and short-term load-carrying applications at temperatures up to 540 °C (1000 oF)
General Corrosion Properties. Molybdenum addition greater than 4 wt% improve the corrosion resistance of titanium alloys in reducing media, and this effect is evidenced by the general corrosion of Ti-6246 in HCI solutions. The increase in reducing environment resistance is achieved, however, at the expense of oxidizing environment resistance. Because Ti-6246 is less resistant to oxidizing media than CP Ti, it is expected that pitting resistance would likewise suffer. This is indeed the situation observed for repassivation potentials, which represent conservative measures of anodic pitting below which pitting cannot be sustained
Crevice Corrosion. In contrast to the anodic breakdown associated with pitting, crevice corrosion is usually the result of acidification in the crevice region by oxidant depletion. Therefore, Ti-6246 should be very resistant to crevice corrosion due to its reducing environment resistance from molybdenum
Ti-6246: Forging process temperatures Process
Conventional forging Belaforging
-c
Metal temperature
845-915 955-1010
1555-1680 1750-1850
Forming. Ti-6246 may be formed similar to Ti-6AI-4V alloy, although the reported bend properties are somewhat inferior. The room-temperature minimum bend radius, for Ti-6246 ranges between 3.5 and 6.0 for solution treated or duplex annealed sheet. Hot forming and sizing of sheet may be accomplished in the 595 to 705°C (1100 to 1300 "F) range using the usual titanium forming techniques. If hot forming is performed in the 595 to 705 °C (1100 to 1300 OF) range, stress relief annealing would not ordinarily be required; limited cold forming is possible. Depending on property requirements, stress relief in the 595 to 705°C (1100 to 1300 "F) range is satisfactory Superplasticity. Flow stresses and strain rate sensitivity of a + ~ preforms indicate superplastic behavior (High-Temperature Deformation of Ti-6246, Titanium, Science and Technology, Vol2, DGM, 1985, P 745-752) Machinability. Machining practice for Ti-6246 in the as-forged condition is similar to that of annealed Ti-6AI4V and Ti-6AI-6V-2Sn. In the solution treated and aged condition, practice is similar to that of Ti-6Al-6V-2Sn in same type heat treated condition
Stress Corrosion Cracking. Resistance to stress-corrosion cracking in salt water is reported to be better after ~ forging than a-~ forging (WymanGordon Co., Project EM-06-1, Dec 1968). Duplex annealing also improves cracking resistance in salt water
Welding. Ti-6246 is very difficult to weld. Recommended filler metal is
Mechanical Properties. Typical room temperature hardness in the solution treated and aged condition (STA) ranges from 36 to 42 HRC. As-forged hardness is reported to be about 33 to 38 HRC. Adjoining Figures show the effects of treatments such as solution treating, aging, duplex annealing (DA) and triplex annealing (fA) on properties such as hardness and tensile strength
Recommended Heat Treating Practice
Fabrication Properties Forging. Ti-6246 can be fabricated into all forging product types, although closed die forgings and rings predominate. Ti-6246 is commercially fabricated on all types of forging equipment. Thrbine engine disks are frequently produced using hot die or isothermal forging techniques, resulting in near-net closed die forgings with reduced final machining. Ti-6246 is a reasonably forgeable alloy with unit pressures (flow stresses), forgeability, and crack sensitivity similar to the a-~ alloy Ti-6AI-4V. The
the same as the base alloy
Ti-6246 may be used in a number of heat treated conditions, which can be categorized as anneals, or solution treatment and aging (see Tables). As previously described, optimum combinations of strength, ductility, and toughness in forgings are obtained by superimposing the heat treatments on processing schedules, which result in a microstructure having about 10 vol% equiaxed primary a and a relatively coarse transformed ~ matrix. If relatively high fabrication temperatures are used, solution heat treatment on the low side of the range can be used. If moderate a-~ fabrication temperatures are used, double solution treatments-the first at a high temperature, the second at about 845°C (1555 °F)-should result in the desirable structure. Adjoining Tables and Figures provide information on such topics as typical heat treatment conditions, annealing temperatures, solution treatment conditions, hardenability, and effect of aging on transverse temperature properties of sheet.
Alpha-Beta Alloys /519
Ti 6246: Specifications and compositions Composition, wi % Specilkation
Deslgnation
UNS USA AMS4981B MlLF-83142A MlLF-83142A MlLT-9047G
R56260
Description
Fe
AI
H
Mo
6
Compll Comp11 Ti-6AI-2Sn-4Zr-6Mo
BarWrrFrgBil FrgAnn
FrglIT BarBUDA
N
Zr
2
4
1.75-2.25 1.75-2.25 1.75-2.25 1.75-2.25
3.5-4.5 3.6-4.4 3.6-4.4 3.6-4.4
6
5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5
5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5
0.15 0.15 0.15 0.15
Other
Sn
0
balTi C 0.04;OTO.4;YO.005; balTi CO.04;balTi CO.04;balTi CO.04;OTO.4;YO.005;balTi
0.15 0.15 0.15 0.15
0.0125 0.0125 0.0125 0.0125
AI
Fe
H
Mo
N
0
Sn
Zr
0.04 0.04 0.04 0.04
Ti 6246: Commercial compositions Designation
Description
KS6-2-4-6
BarFrgSTA
5.5-6.5
0.15
0.0125
5.5-6.5
0.04
0.15
1.75-2.25
3.5-4.5
balTi
Ti-6Al-2Sn-4Zr-6Mo
Bar
5.5-6.5
0.15 max
0.0125
5.5-6.5
0.04
0.15
1.8-2.2
3.6-4.4
CO.l max; balTi
RMI
Ti-6246 6Al-2Sn-4Zr-6Mo
BarBilS'D\
5.5-6.5
0.15
0.0125
5.5-6.5
0.04
0.15
1.75-2.25
3.5-4.5
CO.04;baITi
ThI.AlIVac Timet
TlMEfAL6-2-4-6
DA
5.5-6.5
0.15 max
0.0125 max
5.5-6.5
0.04 max
0.15 max
1.75-2.25
3.5-4.5
CO.04max;balTi
Specilkation Japan Kobe USA Astra Howmet MartinMar Oremet
Ti-6246: Rockwell hardness of different forging and treatment conditions
Ti-6246: Typical heat treatment conditions
Forging conditions
Heattreatmenl
treatment
IX-~ forge(Pt- 100of), AC + finish (~tl- 25 °f),AC IX-~ forge(Pt- 100of), AC + finish
885°C (1625of), I h, AC + 595°C (1100oF),8 h,AC 885°C (1625oF),I h, AC+ 705°C (1300oF),1 h, AC 885°C (1625of), I h, AC+ 595°C (l1OO°f),AC
(~I -
100°f),AC ~ forge (~, + 75 of), AC
39.3 38.4
MP.
ksi
MP.
ksi
%
10 to 20% primaryIX + STA(a) 10 to 20% primaryIX + STOA(b)
1118 1021 1152 1070 1049
162 148 167 155 152
1214
176 158 180 166 174
13 16 14 14 6.5
40 to 50%primaryIX + STA(a) 40 to 50%primaryIX + STOA(b) ~ forged+ STA(c)
1090
1242 1145 1201
Reduellon orarea, %
37 42 42 41 13
Ti-6246: Solution treatment conditions Thmperature Common Sheet Forgings
·C 870 870 845-900
·F 1600 1600 1555-1650
Duralion, b Up to I 0.25 Uptol
595-705 815-930 580-605 >650
1100-1300 1500-1700 1080-1120 >1200
'lime, b
Cooling
0.25-4 1 4-8
Air or slow cool Wateror oil quench AC
method
Ti-6246: Fracture toughness of forgings
(a) STA= 885°C (1625 of), I h, aircool + 595°C (1100 "F), 8 h, air cool. (b) STOA= 885°C (1625 "F), I h, air cool + 705°C (1300 "F), I h, air cool. (c) STA=985 °C(l805 "F), (Pt-15 "C), air cool +595 °C(l1OO°F},8h, air cool
Product
OF
(a)Seeseparatetablefor specifictemperaturesby productform.(b) The mostcommonlyusedaging temperatureis 595°C (1100oF)
Ultim.tetensile Elongation, strengtb
Condiuon
Stressrelief Solutiontrealing(a) Aging(b) Overaging
OC
39.9
Ti-6246: Typical variations in tensile properties with heat treatment/condition Thnsileyield strengtb
ThmperalUre
Heat
Hardness,HRC
Other
Cooling metbod WQ or OQ Quench(a) WQorOQ
(a) Solution treatmentof sheet may be followedby a stabilizationexposure of 0.25 h at 720 to 730 °C (1325 to 1345 oF)withan air cool priortoaging. Sheetmay beage hardenedto optimumproperties in as little as 2hat595 °C (1100 of) (air cooled)
ThnsUe yield strengtb Condition
MP.
ksI
IX+~forged
1116
IX+~forged+S'D\(a)
+STA(a) (10%primarya)
(50%primaryIX) IX + ~ forged+ anneaIed(b) (50%primaryIX) ~ forged+ STA(a)
UItbnate lensile streogtb
Elongation,
Kr
MPa'liii'ksI'1iii"
MP.
ksi
%
162
1213
176
13
34
31
1150
166
1240
180
14
26
23
1061
154
1130
164
13
26
23
1047
152
1199
174
7
57
52
(a) 885 °C(l625 OF), 1 h,AC+595 °C (1100oF),AC. (b) 705 °C(13OO°F),I h,AC
Ti-6246: Fracture toughness of STA forgings: two forging conditions and three specimen locations Fracture toughne.. (KI,) for material:
Specimen location Centertangential Outsidetangential Centerdiametral
IX+ 6 fO~ at 8BO ·C (1620 oF) MP. m ksi'liii" 28.28 24.47 26.49
25.74 22.27 24.11
IIfO~II0I0 OC (1850 .F) MPa ksI~ 21.81
19.85
21.45
19.52
Nole: Klcvalues determined with precracked three-pointnotched bend specimens.Heat treatment was at 870°C (1600 of) for 1 h, waterquench, then at 595 ·C (1100oF)for 8 h, air cool
520 I Heat Treater's Guide: Nonferrous Alloys Ti-6246: Annealing treatments Temperature
-c
'fiealment Solutionannea1 (SA) Duplexanneal Firsl stage (SA) Second stage (age) Triplexannea1 SA stage First age(a) Second age(a)
Ti-6246: Effect of aging on transverse tensile properties of sheet Cooling of
method
815-930
1500-1700
AC
815-930 540-730
1500-1700 1000-1345
AC AC
815-925 540-730(a) 540-730(a)
1500-1695 l000-1345(a) l000-I345(a)
AC AC AC
Tempemture
AgInglrealmenl(a) TIme,h
1 16 1 2 16 1 16 1 16
540
1000
595
1100
650
1200
705
1300
TYS
UTS
OF
°C
MPa 1648 1579 1489 1517 1461 1406 1296 1255 1158
Elongation,
ksi
MPa
ksI
....
239 229 216 220 212 204 188 182 168
1455 1420 1379 1386 1365 1337 1261 1220 1110
211 206 200 201 198 194 183 177 161
3 4 6 3 6 7 9 6 12
(a) Firstaginghigherthanthesecond
.
(a)Solutiontreatmentfor0.25 h, 870°C (1600 "F), air cooled
Ti-6246: Continuous cooling transformation and aging dlagram
Ti·6246: Continuous cooling transformation diagram
LIVE GRAPH
LIVE GRAPH
Click here to view 1200
Solution annealed at 900°C for 20 min
1000
~
E Q)
I--
1000
c:=
800
M.
-,1500 ~
~
ll!
-11000 ~ E Q)
600
Q)
c.
E Q)
I--
a
-'1500 ~
a
i!!
.a
I--
~1000 ~
E Q)
400
a
200
0
i!!
:>
~
M,
~500
200
-,2000
13, = 1020 °C- ~
~ 800
i!!
I
400
Solution annealed at 1050 °C at 20 min
-i2000
13, = 1020 °C
i!! :>
600 ~ Q) c.
Click here to view 1200
I--
.
-;500
0
1
10
2
10
10'
s 10
4
10
1
2
10
10
Time,s
Ti-6246: Effect of aging on Vickers hardness. Isothermal aging curves for alloy aged at 773 and 873 K after water quenching from the ~ field. Chemical composition: 5.48 wt% AI, 0.072 wt% Fe. 6.35 wt% Mo, 0.004 wt% N, 0.083 wt% 0, 1.94 wt% Sn, and 4.00 wt% Zr. Beta transus temperature was 1211 K. Alloy used was in the form of flat bar stock previously warm worked in the cx+~ field. Hardness determinations were obtained on electropolished specimens using a Zwick diamond pyramid hardness tester at a load of 10 kg
10' Time,s
4
10
s 10
Ti·6246: Tensile strength of duplex annealed sheet. Duplex annealed 870°C (1600 OF) 15 min. AC, 700°C (1290 OF), 15 min, AC
LIVE GRAPH
200
Temperature, OF 400 600 BOO
Click here to view 1000
1500 200 /
Ultimate tensile strength
1BO
500
'iii
""
160.r:-
ic:
e;,
c: 140 ~
~
en
C/)
900 Tensile yield
0
Click here to view Aged at 773 K
o Aged at 873 K
350L..-~_"'-~~"""'~~""""~~""""L....-.~"""'" 0.01
0.1
10 Time, h
120 100
600
LIVE GRAPH •
strength~
100
1000
200 400 Temperature.vc
600
Next Page Alpha-Beta Alloys I 521
Ti-6246: Tensile strength of triplex annealed sheet. Triplex annealed sheet, 855°C (15.70 OF), 15 min, FAC; 730°C (1345 OF) 15 min, AC; 595°C (1100 OF), 2 h, AC
Ti-6246: Hardenability. Variation of room-temperature tensile properties across a 150 mm (6 in.) section; solution treated 1 hat 870°C (1600 OF), WQ + aged 8 h, 595°C (1100 OF), AC
Temperature, of
200
400
600
800
8?
190
1000 1200 1400
1500
200
~ 170
1000
:2
~
Tensile yield strength
.;
s 160 m
c;, c
~
(jj
180
500 50
150 Out
0'---_ _-'--_ _-'-_ _--'_ _---'0
o
200
400
600
800
Temperature, °C
Center
Out
140L-........L_--'-_--'-_....l...-_-'--_.l-_'----' 4 -4 -3 -2 -1 0 1 2 3 Section location and dimensions, In,
Ti-6246: Microstructure. Forged at 870°C (1600 OF), solution treated 2 h at 870°C (1600 OF), air cooled, aged 8 h at 595°C (1100 OF), and air cooled. Elongated "primary" ex grains (light) in aged transformed p matrix containing acicular ex. Kroll's reagent (ASTM 192). 500x
Ti-6246: Microstructure. Bar forged at 870°C (1600 OF), solution treated 1 hat 870°C (1600 OF), water quenched, and aged 8 h at 595°C (1100 OF). The structure is similar to that in preceding microstructure, except that, as the result of water quenching, no acicular ex is visible. 2 mL HF, 10 mL HN03 , 88 mL H20 . 250x
Ti-6246: Microstructure. Forged at 870°C (1600 OF) solution treated at 915 °C (1680 OF), which reduced the amount of "primary" ex grains in the ex + p matrix. Kroll's reagent (ASTM 192). 500x
Ti-6246: Microstructure. Forged at 870°C (1600 OF) solution treated at 930 °C (1700 OF), which reduced the amount of ex grains and coarsened the acicular ex in the matrix. Kroll's reagent (ASTM 192).500x
Previous Page 522/ Heat Treater's Guide: Nonferrous Alloys
Ti-6246: Microstructure. Forged at 870°C (1600 OF) but solution treated at 955 °C (1750 OF), which is above the ~ transus. The resulting structure is coarse, acicular <X (light) and aged transformed ~ (dark). Kroll's reagent (ASTM 192). 500x
Ti·6246: Microstructure. Forging, solution treated 2 h at 955°C (1750 OF), above the ~ transus, and quenched in water. The structure consists entirely of <X/ (martensite). Kroll's reagent (ASTM 192). 50 Ox
Ti..6AI..4V Common Name. Ti64, 6AI-4V, 6-4 UNS Number. R56400 (normalinterstitial grade); R56401 (extra-lowinterstitial grade); R56402 (fillermetal) Chemical Composition. Effects of Impurities and Alloying. Ti64 is produced in a number of formulations, Depending on the application, the oxygen content may vary from 0.08 to more than 0.2% (by weight), the nitrogen content may be adjusted up to 0.05%, the aluminum content may reach 6.75%, and the vanadium content may reach 4.5%. The higher the content of these elements, particularly oxygen and nitrogen, the higher the strength. Conversely, lower additions of oxygen, nitrogen, and aluminum will improve the ductility, fracture toughness, stress-corrosion resistance, and resistance against crack growth ELI Grade. Ti-6AI-4V is available in ELI (extra-low interstitial) grades with high damage-tolerance properties, especially at cryogenic temperatures. The principal compositional characteristics are low oxygen and iron contents Ti·6AI-4V-Pd. A grade that has palladium additions (about 0.2 wt% Pd) for enhanced corrosion resistance. Sumitomo Titanium has produced this grade. See Tables for Ti64 and equivalents: specifications and compositions and commercial equivalents: compositions
Characteristics Product Forms. Ti-6AI-4V is available in wrought, cast, and powder metallurgy (PIM) forms, Properties vary depending on interstitial contents and thermal-mechanical processing Wrought Product Forms. Ti-6AI-4V is available in a wide range of wrought product forms Castings. Ti-6AI-4V of the same chemistry as for wrought materials has excellent casting characteristics. However, the high reactivity of titanium in the molten state requires suitable casting technology and has limited the
number of titanium foundries. In general terms, the mechanical and fatigue properties of castings will be slightly lower than for the wrought product, but fracture toughness, stress-corrosion resistance, and crack growth resistance will be comparable to that of annealed wrought Ti-6AI-4V PIM Products. The major reason for using the PIM products is to produce near-net shapes Applications. Designed primarily for high strength at low to moderate temperatures, Ti-6AI-4V has a high specific strength (strength/density), stability at temperatures up to 400°C (750 "F), and good corrosion resistance Aerospace Applications. Wrought Ti-6AI-4V is used extensively for turbine engine and airframe applications. Engine components include blades, discs, and wheels. Wrought forms are used for airframe components. Aerospace casting applications include the range from major structural components weighing more than 135 kg (300 Ib) each to small switch guards weighing less than 30 g (l oz). Wrought Ti64 is a useful material for surgical implants because of its low modulus, good tensile and fatigue strength, and biological compatibility. In the automotive industry, wrought Ti-6AI-4V is used in special applications in high-performance and racing cars where weight is critical, usually in reciprocating and rotating parts, such as valves, valve springs, connecting rods, and rocker arms.
Wrought Ti-6AI-4V applications include armaments, sonar equipment, deep-submergence craft, hydrofoils, and capsules for telephone-cable repeater stations. Casting applications include water-jet inducers for hydrofoil propulsion and seawater ball valves for nuclear submarines
Product Condition/Microstructure Annealed Condition. Although Ti-6AI-4V is commonly used in the mill-annealed condition, other annealing treatments are utilized. For example, annealing just above the beta transus, or annealing high in the <X + ~
Alpha-Seta Alloys I 523 phase field, creates a Widmanstiitten or lamellar a + ~ microstructure with good fracture toughness, stress-corrosion resistance, and crack growth resistance, and creep resistance. Recrystallization annealing of wrought alloy improves tensile ductility and fatigue performance Solution Treated, Quenched, and Aged Ti-6AI-4V Alloy. Solution-treated and quenched alloys may either have an acicular a'-martensite structure (quenched from above ~-transus) or mixed a' + a microstructure (quenched from 900-1000 0c) or mixed a" + a microstructure (quenched from 800-900 °C), of which the latter is exceptionally soft and ductile. They serve as starting conditions for subsequent aging treatments. Quenched components contain high residual stresses which may not be fully relieved upon aging at low temperatures. Such components may distort during machining. Ti-6AI-4V has excellent hardenability in sections up to about 25 mm (l in.) thick; strengths as high as 1140 MPa (165 ksi) may be achieved at aging temperatures between 300 and 600°C Lamellar Structures. Can be readily controlled by heat treatment. Slow cooling into the two-phase region from above the ~ transus leads to nucleation and growth of the a-phase in plate form starting from ~-grain boundaries. The resulting lamellar structure is fairly coarse and is often referred to as plate-like alpha. Air cooling results in a fine needle-like alpha phase referred to as acicular alpha. Certain intermediate cooling rates develop Widmanstiitten structures. Water-quenching from the ~-phase field followed by annealing in the (a + ~)-phase region leads to a much finer lamellar structure. Quenching from temperatures greater than 900°C (1650 OF) results in a needlelike hcp martensite (a'), while quenching from the 750 to 900°C (1380 to 1650 "F) temperature range produces an orthorhombic martensite (a'') Equiaxed Microstructures. Are obtained by extensive mechanical working (>75% reduction) the material in the (a + ~)-phase field, where the breakup of lamellar alpha into equiaxed alpha depends on the exact deformation procedure (e.g., see Figure). Subsequent annealing at about 700°C (1290 OF) produces the so-called "mill-annealed" microstructure, which gives a microstructure that is very dependent upon previous working. A more reproducible equiaxed structure is obtained by a recrystallization anneal of 4 h at 925°C (1695 OF) followed by slow cooling. The resulting structure is fairly coarse with an o-grain size of about 15-20 11m
that is welded in the ~ annealed/solution treated and aged condition followed by stress relieving. See Tables and Figures showing minimum and typical tensile properties, the effect of oxygen, the effect of texture, and the effect of processing
Fabrication Properties Forging. Ti-6AI-4V is supplied in several forging types, including open die (or hand) forgings. rings, closed die forgings, and precision forgings. It is more difficult to forge, as measured by flow stress and crack sensitivity, than most ferrous alloys (and all aluminum alloys), but is less difficult to forge than most nickel- and cobalt-base superalloys.
Ti-6AI-4V may be forged using either conventional (sub-B transus) or ~ (supra-B transus) forging techniques. Both techniques are used in combination with annealing and solution treating and annealing or aging thermal treatments. Other thermal treatments such as recrystallized annealing and/or ~ annealing or ~ solution treatment and annealing may be combined with conventional forging to achieve tailored properties. Conventional forging of Ti-6AI-4V predominates commercially because it achieves an equiaxed a in a transformed ~ matrix microstructure that is preferred for many applications. Beta forging of Ti-6AI-4V creates an acicular a microstructure that is preferred for service conditions where fracture-related and/or creep properties are highly critical Thermomechanical Processing. Thermomechanical processing is a key to obtaining selected microstructures in forging Ti-6AI-4Y. Several final treatments are available, such as annealing (A), solution treating, quenching (water, oil or air) and annealing or aging (STA or STAN). recrystallization annealing (RA), and beta annealing (BSTAN or BA).
See Tables and Figures for recommended forging temperatures; forging equipment and die temperatures; for forging properties (minimum room temperature) per composition, forging process, and heat treatment; for the effect of different thermomechanical processes; and for typical microstructures after working and annealing
Corrosion and Chemical Properties
Forming. Ti-6Al-4V typically is hot formed above 540°C (1000 OF). Normal production hot forming is usually at 650°C (1200 "F), but hot forming temperatures can be between 540 and 760 °C (1000 and 1400 "F), or even higher for superplastic forming. At 760°C (1400 "F), stresses are self-relieved
Although not as corrosion-resistant as commercially pure titanium alloys, Ti-6AI-4V has excellent corrosion resistance compared to other alloy systems. The exceptional corrosion resistance is due primarily to oxidefilm formation
Surface Treatment. Forming and bending must be done with sheet free of a case. If the sheet has a case on the surface, it will crack when bent. Residual a case must be removed with chemical cleaning before bending procedures can be used
Oxidation. The oxidation behavior of Ti-6AI-4V alloy is similar to that of unalloyed titanium. The reaction rate laws range from logarithmic (at 300-500 "C) to parabolic (500-750 "C) to linear (above 750°C) with increasing temperatures of oxidation
Bending. Bending properties of Ti-6AI-4V sheet vary with processing temperature. For production operations on mill annealed Ti-6AI-4V sheet, the room-temperature bend radius is essentially 6t. This bend radius will usually cover both longitudinal and long-transverse grain (sheet rolling) directions
Hydrogen Damage. Hydrogen damage of titanium and titanium alloys is manifested as a loss of ductility (embrittlement) and/or a reduction in the stress-intensity threshold for crack propagation. The damage is caused by hydrides, which form as hydrogen diffuses into the material during exposure with either gaseous or cathodic hydrogen. Because the phenomenon depends on both hydrogen diffusion and hydride formation, there may be a peak in hydrogen embrittlement as a function of temperature.
Alloy Ti-6AI-4V has moderate sensitivity to hydrogen damage
Typical Room Temperature Properties Room-temperature tensile properties are affected by heat treatment (microstructure), composition (oxygen content), and texture (primarily in sheet). Tensile strength can be changed by more than 200 MPa (30 ksi) by heat treatment and about 70 to 100 MPa (10 to 15 ksi) by oxygen content. Textured sheet can also exhibit variations on the order of200 MPa (30 ksi) as a function of direction Weldments. Failure is normally in the base metal. Generally, weld strength is higher and ductility is lower. The exception to this is material
Superplastic Forming. Superplastic forming performance is affected by several factors. Most procedures are based on Ti-6AI-4V sheet.
See Tables for forming temperatures Machining Properties. Based on a rating system in which AISI B1112 steel has a machinability rating of 100, the machinability of Ti-6AI-4V in the annealed condition is 22.
See Table for comparative machinability ratings of different metals Welding Processes. Ti-6AI-4V may be welded by a wide variety of conventional fusion and solid-state processes, although its chemical reactivity typically requires special procedures and precautions. In the United States, fusion welding is performed principally in inert-gas-shielded arc and high-energy beam welding processes.
See Tables for more information on: • Gas tungsten arc welding • Gas metal arc welding
524/ Heat Treater's Guide: Nonferrous Alloys • • • •
Plasma arc welding Electron beam welding Laser beam welding Resistance spot welding
Recommended Heat Treating Practice Annealing. Ti-6AI-4V is most commonly used in the fully annealed condition, often referred to as mill annealed. It has limited hardenability, but is sometimes used in the solution treated and aged (STA) condition. Using STA, strengths as high as 1110 MPa (160 ksi) can be achieved in section thicknesses up to 12.7 to 19 mm (0.5 to 0.75 in.) Damage tolerance properties are optimized (fracture toughness is maximized and the crack growth rate is minimized) by ~ annealing (BA), which provides a totally transformed ~ structure. This, however, results in reduced ductility (although the material would still have at least 5% elongation) and reduced fatigue strength. Beta annealing should not be used on sheet gages due to the possible incidence of a single prior ~ grain across the entire thickness. Improvements in fatigue performance can be achieved by water quenching from above the ~ transus temperature of 995 °C (1825 "F), This refines the transformed structure. Recrystallization annealing (RA) also increases damage tolerant properties. Fracture toughness and crack growth resistance are typically not quite as good as BA, but fatigue performance and ductility are improved. To maximize damage tolerance properties, the extra-low-interstitial (ELl) grade, which contains lower oxygen, should be used with both the recrystallization anneal and the ~ anneal. Another option for achieving improved damage tolerance over mill annealing is a duplex anneal, although this is not a common heat treatment. The first anneal of a duplex anneal is high in the a-~ phase field. On cooling, the ~ at temperature transforms to a lamellar a-~ structure, which improves damage tolerance properties. The higher the first anneal temperature, the higher the fracture toughness and crack growth resistance; fatigue strength diminishes until the anneal temperature exceeds the ~ transus. The high-temperature anneal is followed by a full anneal or mill anneal. This heat treatment is very similar to RA, except the cooling rate from the first anneal temperature is faster, resulting in the transformed structure. The RA treatment uses a slower cooling rate, resulting in a predominantly equiaxed structure
Thermomechanical Processing. A recent patent (Patent No. 5,118,363, ALCOA, Pittsburgh, PA) has been issued for improving mechanical properties of forgings. The processing steps include heating slightly above the ~ transus temperature to form the ~ phase, followed by rapid cooling; reheating the billet (which now has a fine ~ transformed structure) to 855 to 925 °C (1570 to 1695 "F); forging to obtain a reduction ratio of about 3:1; cooling and solution treating to form primary a particles; and aging and cooling
Furnaces and Atmospheres. Heat treatment should be in atmospheres free of reducing gases and other contaminants that might produce excessive hydrogen pick up. Gas-fired furnaces should have oxidizing flames, and there should be no flame impingement on the part. Furnaces used above 650°C (1200 OF) that have contained endothermic or dissociated ammonia atmospheres should be equipped to prevent leakage, purged, and tested for hydrogen pickup prior to heat treating the first load of titanium parts. The use of inert gas or vacuum atmospheres minimizes contamination when properly controlled. Molten salt and fluidized beds should not be used. See MIL-H-81200 for further guidelines
Stress Relieving. The effect of time and temperature on stress relieving at elevated temperatures is shown in the nomograph for Ti-6AI-4V. At 595 °C (1100 OF), it takes 50 h to achieve a full stress relief; a 50% stress relief would take about 1 hat 595°C (1100 OF) or 5 h at 540°C (1000 "F). Such a diagram is extremely valuable in selection of thermal treatments to reduce residual stress levels. Stress relaxation data can often be fitted to a timetemperature parameter such as the Larson-Miller parameter.
SELECTED REFERENCES • C.R. Brooks, Heat Treatment, Structure and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 361-376 • lA. Burger and D.K. Hanink, Heat Treating Titanium and Its Alloys, Met. Prog., Vol 91 (No.6), June 1957, p 70-75 • ASM Trans, 1956, p 657-676 • W. Herman et al., HeatTreating of Titanium and Titanium Alloys, Metals Handbook, Vol 4, 9th ed., Heat Treating, American Society for Metals, 1981, p 763-774 • R.A. Wood and R.I. Favor, Titanium Alloy Handbook, MCIC-HB-02, Battelle Memorial Institute, 1972 For further information see: • Table listing heat treatments and procedures • Table listing mechanical properties obtained with different heat treatments • Figure indicating stress relief obtained at different times • Nomograph for stress relief showing relationship of time, temperature, and percent of stress relief • Figure showing effect of temperature on tensile properties • Table showing variation in tensile properties of bar stock with solution treating temperature Beta Heat Treated Microstructures • Figure for heat treatment cycles of transformed beta Alpha + Beta Annealed Microstructures • Figures for typical microstructures, and for processing cycles used to obtain fme microstructures in alpha + beta alloys • See Figure for microstructure of equiaxed a and a"
Ti·6AI·4V: Wrought products Product
SizeIlIId weighl ranges
Pricecomparison(&)
Ingot Billet
3200to 13,600kg (7000to 30,000Ib) Nonnally100mrn(4 in.)diamto about355mrn (14in.)diam orsquare.Billetsupto 5000Ib havebeensold,butthisis nOI necessarily the upperlimit Cross-secrions up to0.4 x 0.4 m (16 x 16in.) Bar Dieforging From<0.5kg to >1300kg «lib to >3000Ib) Ti,$301lb; AI,$IOIlb; stainless steel,$8Ilb 'Iyplcaldimensions: Thickness: 5 to75 mrn Plale (0.1875to 3 in.); Width:915and 1220mrn (36and48 ln.); Length:1.8,2.4.and3 m (72, 96,and 120 in.) Typicaldimensions: Thickness: 0.4 to4.75mrn Ti,$16Ilb;stainless steel,$3I1b; AI, Sheet (0.016to 0.187 in.); Width:915 and 1220mrn $24I1b;Inco718,$IOllb (36and48 in.); Length:1.8,2.4,and3 m (72. 96,and 120in.) Tube Specialty item Ti, $8I1b; stainlesssteelandAI, Forgedblock Available in a widerangeof sizes,with $2.5Q.3I1b maximumsizerelatedto ingotsizeandthe amountof work thatcan be impartedtothe forgedblock Extrusion Fromcirclesizesofaboul25 to760 mrn(Ito 30 Ti,$13·15Ib; 300seriesstainless ln.) Warn. MInimumthicknessof about3 mrn steel,$3·4I1b; 15·5PH,$4-5I1b; (0.125in.)forsmallcirclesizes,andabout13 13·8PH,$9·1211b;AI, $2411b mrn(0.5 in.)forlargecirclesizes 'Iypicallymanufactured in sizesrangingfrom 0.25 in. wire: n, $261lb; A283, Wire $6IIb; stainlesssteel,$7.501lb; 0.281012.2mrn(O.01lto0.480in.)diam 8740,$llIb; AI7075,$2.301lb (a)Duetoitslowerdensity,Llbof'titanlurnisapproximately 1.7101.8moremeterialby volumethan lIb of steelor nickel-basealloy
Alpha-Beta Alloys I 525
Ti-6AI-4V andequivalents: Specifications andcompositions Spe
Designation
Description
AI
C
Fe
H
N
0
V
UNS UNS UNS Europe AECMAprEN2517 AECMAprEN2530 AECMAprEN253l AECMAprEN33LO AECMAprEN3311 AECMAprEN33l2 AECMAprEN3313 AECMAprEN3314 AECMAprEN3315 AECMAprEN3352 AECMAprEN3353 AECMAprEN3354 AECMAprEN3355 AECMAprEN3456 AECMAprEN3457 AECMAprEN3458 AECMAprEN3464 AECMAprEN3467 Fmnce AIR9l83 AIR9184 Germany DIN DIN DIN 17850 DIN 17851 DIN 17860 DIN 17862 DIN 17864 Russia GOST19807-74 OST 1.90000-70 OSTl.90060-72
R56400 R56401 R56402
WeldWrr
0.1
0.4
0.015
0.05
0.2
FillMet
5.5-6.75 6 5.5-6.75
0.04
0.15
0.005
0.012
0.1
3.5-4.5 4 3.5-4.5
TI-P63
ShStrpPitBarAnn BarAnn FrgAnn FrgNHf BarAnn FrgAnn FrgNHf BarS'D\ FrgSTA lov CastAnnIllP BarWrrSTA ShAnn ExtAnn ShStrpAnn FrgNHf BarWrrAnn PItAnn RemeltNHf
5.5-6.75 0.08 5.5-6.75 0.08max 5.5-6.75 0.08 max 5.5-6.75 0.08 max 5.5·6.75 0.08 max 5.5-6.75 0.08 max 5.5-6.75 0.08 max 5.5-6.75 0.08max 5.5-6.75 0.08 max 5.5-6.75 0.1 max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08max 5.5-6.75 0.08 max
0.3 0.3 max 0.3 max 0.3 max 0.3 max 0.3max 0.3 max 0.3max 0.3max 0.3max 0.3 max 0.3 max 0.3 max 0.3 max 0.3max 0.3max 0.3 max 0.3 max
om 0.0125max 0.Ol25max 0.0125max 0.0125max 0.0125max 0.0125max 0.Ol25max 0.0125max 0.015max 0.0125max 0.0125max 0.0125max 0.0125max 0.0125max 0.0125max 0.0125max 0.0125max
T-A6V T-A6V
BarRodFrg BIt
3.7164 3.7264 3.7165 3.7165 3.7615 3.7615 3.7615
ShStrpPItBarFrgAnn CastAnn PltShStrpRodWrrAnn ShPltStrp RodWrrAnn ShStrp Rod Frg
5.5·6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75
0.08 0.1 0.08 0.08 0.2 max 0.08 max 0.08 max
VT6S VT6 VT6L
ShPItStrpFoilRodAnn ShPItStrpFoilRodFrgAnn Cast
5.3-6.8 5.5-7 5-6.5
L-7301 1.-7301
ShPitStrpBarExAnn ShPitStrpBarExlIT
5.5-6.75 5.5-6.75
BS2TA.lO
ShStrplIT
BS2TA.ll
Other
OT ~alTI
balTI balTI
0.05 0.2 0.05max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05 max 0.2 max 0.05 max 0.2 max 0.05 max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05 max 0.22 max 0.05max 0.2 max 0.05 max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05max 0.2 max 0.05 max 0.2 max
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
0.012 0.12 max
0,07 0.07max
0.2 0.2 max
3.5-4.5 3.5-4.5
0.3 0.3 0.3 0.3 0.3 max 0.3 max 0.3 max
0.0125-0.015 0.Q15 0.Q15 0.Q15 Om5max 0.015max 0.015 max
0.05 0.05 0.05 0.05 0.05max 0.05 max 0.05 max
0.2 0.2 0.2 0.2
0.4 0.4
0.2 max 0.2 max
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
balTI balTI balTI balTI balTI balTI balTI
0.08 0.1 0.1
0.25 0.3 0.3
0.007 0.Q15 0.Q15
0.05 0.05 0.05
Om5 0.2 0.15
3.5-4.5 4.2-6 3.5-4.5
0.3 0.3 0.3
ZrO.3; SiO.15;balTI SiO.l5;balTI ZrO.3;SiO.15;W 0.2;balTI
0.1 0.1
0.3 0.3
0.125 0.125
0.05 0.05
0.2 0.2
3.5-4.5 3.5-4.5
0.4 0.4
balTI balTI
5.5-6.75
0.3
0.01
Bar
5.5-6.75
0.3
0.Q1
0.05
0.2
BS2TA.l2 BS2TA,13 BS2TA.28 BS3531 Pan2 BSTA.56
Frg FrglIT WrrFrglIT Quen SrgImp Pitto 100romlIT
5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75
0.3 0.3 0.3 0.3 max 0.3
0.Q1 0.Q1 0.Q1 Om5 max
0.05
0.2 0.2 0.2 0.2 max
BSTA.59 DTD5303 DTD5313 DTD5323 DTD5363 USA AMS4905A
ShStrp BarAnn FrgAnn FrgAnn Cast
5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75
0.08max 0.2 max
0.3 max 0.3 max 0.3 max 0.3 max 0.3 max
0.0125max 0.0125max 0.01 max 0.Q15 max 0.15 max
0.05max 0.05max 0.2 max 0.05max 0.2 max 0.05max 0.25 max
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
EUPlt
5.6-6.3
0.05 max 0.25max
0.0125max
0.03max 0.12max
3.6-4.4
AMS4905A AMS4906 AMS4907D AMS4911F AMS4920 AMS4928K AMS4930C AMS4931 AMS4934A AMS4935E AMS4954D AMS4956B AMS4965E
PitBetaAnn 5.6-6.3 0.05 ShStrp 5.5-6.75 0.08 max BUSh StrpPItAnn 5.5-6.5 0.08 ShStrpPltAnn 5.5·6.75 0.08 FrgAnn 5.5-6.75 0.1 BarWrrFrgBilRugAnn 5.5-6.75 0.1 BU Bar Wlr FrgBilRugAnn 5.5-6.5 0.08 EU BarFrgBilRng 5.5-6.5 0.08 ExRngSTA 5.5-6.75 0.1 ExRngAnn 5.5-6.75 0.1 FillmetgasrnetlW-arc weld 5.5·6.75 0.05 0.Q3 EUFillMetWrr 5.5-6.75 BarFrgRugSTAlMach Pressyes 5.5-6.75 0.08
0.0125 0.0125max 0.0125 0.Q15 0.0125 0.0125 0.0125 0.0125 0.0125 0.0125 0.015 0.005 0.0125
0.Q3 0.05max 0.05 0.05 0.05 0.05 0.05 0.Q3 0.05 0.05 0.03 0.012 0.05
3.6-4.4 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
Spain UNE38-723 UNE38-723
5.5-7 5.5-7
0.08 0.25 0.08 max 0.25max
0.4 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4max 0.4 max 0.4max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4 max 0.4max
balTI OEO.lmax;balTI OEO.lmax;balTI OEO.lmax;balTI OEO.l max;balTI OEO.l max;balTI OEO.l max;balTI OEO.l max;balTI OEO.l.max;balTI OEO.l max;balTI OEO.lmax;balTI OEO.l max;balTI OE0.1max;balTI OEO.l max;balTi OEO.l max.balTi OEO.l max;balTI OEO.l max;balTI OEO.l max;balTI balTI balTI
UK
0.08max
0.25 0.3 max 0.25 0.3 0.3 0.3 0.25 0.25 0.3 0.3 0.3 0.15 0.3
(continued)
0.05
0.12 0.2 max 0.13 0.2 0.2 0.2 0.13 0.13 0.2 0.2 0.18 0.08 0.2
3.5-4.5 3.5-4.5 3-5 3.5-4.5 3.5-4.5
V.3.5-4.5;TI88.18 max;O+N= 0.25 y'3.5-4.5;TI88.18 max; TI88.19max; TI88.18max; TI88.19max; balTI TI88.2max;O+N= 0.25 N+O=0.25;balTI balTI balTI balTI N+O=O.27;balTI 0.4max YO.005max;OEO.l max;balFe 0.4 YO.005;balTI 0.4max YO.005 max; balTI YO.005;balTI 0.3 balTI 0.4 YO.005;balTI 0.4 0.4 balTI YO.005;balTI 0.4 YO.005;balTI 0.4 0.4 YO.005;balTI YO.005;balTI 0.4 0.4 YO.005; balTI 0.1 YO.005; balTI 0.4 YO.005;balTI
526/ Heat Treater's Guide: Nonferrous Alloys Ti-6AI-4Vand equivalents: Specifications and compositions (continued) Specilicatlon
AMS4967F AMS4985A AMS4991A AMS4993A
Designation
Description
AI
C
H
Fe
OT
N
0
V
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
CastAnn PowdSintNuts
5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75
0.08 0.1 0.1 0.1
0.3 0.3 0.3 0.3
0.0125 0.015 O.ol5 0.01
0.05 0.05 0.05 0.05
0.2 0.2 0.2 0.3
AMS4996
BillPowdAnn
5.5-6.75
0.1
0.3
0.0125
0.04
0.13-0.19
3.5-4.5
AMS4996
EUBU
5.5-6.75
0.1 max
0.3 max
0.0125max
0.04 max
0.13-0.19
3.5-4.5
AMS4998
EUPowd
5.5-6.75
0.1 max
0.3 max
0.0125 max
0.04max
0.13-0.19
AMS4998
Powd
5.5-6.75
0.1
0.3
0.012
0.04
0.13-0.18
3.5-4.5
ShStrpPlt Ann BarBilAnn cast FrgAnn EU WroughtAnnforSurgImp B1tScrStd BltScrStd WeldFillMet WeldFillMet WITRod
5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.5 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75
0.1 0.1 0.1 0.1 0.08 0.1 max 0.1 max 0.05 0.04
0.4 0.4 0.4 0.4 0.25 0.4 max 0.4 max 0.25 0.15
O.ol5 0.0125 O.ol5 0.0125 0.012 0.0125 max 0.0125max 0.008 0.005
0.05 0.05 0.05 0.05 0.05 0.05 max 0.05 max 0.02 0.012
0.2 0.2 0.25 0.2 0.13 0.2 max 0.2 max 0.15 0.1
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
WeldArmorPitAnn FrgAnn FrgHT EUFrgAnn EUFrgHT Ex BarShpAnn Ex BarShp STA ELIExtBarAnn
5.5-6.5 5.5-6.75 5.5-6.75 5.5-6.5 5.5-6.5 5.5-6.75 5.5-6.75 5.5-6.5 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.5 5.5-6.75 5.5-6.5 5.5-6.75 6.18
0.04 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.08 0.023
0.25 0.3 0.3 0.2-0.25 0.25 0.3 0.3 0.25 0.3 0.3 0.3 0.25 0.3 0.25 0.3 0.22
0.0125 0.015 0.015 0.0125 0.0125 O.ol5 0.0125 0.0125 O.ol5 0.0125 0.0125 0.0125 O.ol5 0.0125 O.ol5 0.008
0.02 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.026
0.14 0.2 0.2 0.13 0.13 0.2 0.2 0.13 0.2 0.2 0.2 0.13 0.2 0.13 0.2 0.097
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
ASTMB265 ASTMB348 ASTMB367 ASTMB381 ASTMF136 ASTMF467-84 ASTMF468-84 AWSAS.I6-70 AWSAS.16-70 MlLA-46077D MlLF-83142A MlLF-83142A MlLF-83142A MlLF-83142A MILT-81556A MILT-81556A MILT-81556A MlLT-81915 MlLT-9046J MlLT-9046J MlLT-9046J MlLT-9047G MlLT-9047G MlLT-9047G SAE J467
BarFrg RngMachlSTA Pressves Cast Ann
Grade5 Grade5 GradeC-5 GradeF-5 Grade5 ElITi-6AI-4V ElITi-6AI-4V-I Comp6 Cornp6 Comp7 Comp7 CodeAB-I CodeAB-I CodeAB-2 TypeIIICamp A CodeAB-I CodeAB-I CodeAB-2
MIL-T-9047G
Cast Ann
Sh StrpPitAnn Sh StrpPitSTA EU Sh StrpPitAnn BarBilSTA EUBar BilAnn BarBilAnn EU
Ti-6AI-4V: Forming temperatures
direction
Thll.'llleyield strength ksl MPa
Longitudinal(a) Transverse(b)
883 1063
lest
Method
Hotsizing
650
1200
540-650 540-785 870-925 540-785 540-785 205-315 480-540 480-785 540-650
1000-1200 1000-1450 1600-1700 1000-1455 1000-1455 400-600 900-1000 900-1455 1000-1200
Brakefanning Drophammer Superplastic Drawing Spinning Hydropress Pressforming Matched die Creepforming
0.4 0.4 0.4 0.3 0.3 0.4 0.4 0.3 0.4 0.4 0.4 0.4 0.3 0.4
baITI baITI baITI baITI baITI baITI baITI baITI baITI baITI baITI baITI YO.005; baITI YO.005; baITI Y 0.005;baITI baITI
Ti-6AI-4V: Effect of basal texture on tensile properties
Normal production hot forming usually is done at 650°C (1200 OF). Thmperalure(a) OF °C
0Iher
Y 0.005;baITI 0.4 YO.005;baITI 0.4 YO.005;baITI 0.4 SiO.05;NaO.15;Cl 0.4 0.15;bal TI 0.2 MoO.1max;SnO.1 max;:aO.lmax; MnO.lmax;Cu 0.1 max;YO.OOI; baITI 0.2 max vuoor max;OEO.1 max;baITI 0.2 max YO.oolmax;OEO.1 max;baITI MoO.1max;SnO.1 0.2 max;:a0.1 max; Mn 0.1 max;Cu 0.1 max; voooi, baITI baITI 0.4 0.4 baITI 0.4 baITI baITI 0.4 baITI baITI baITI baITI balTI
Comments
3 to 15min for 0.8 mm (0.032in.)sheet;3 to20 min for 1.6mm (0.063in.)sheet
128 154
Ultimate tOll.'llle strength MPa ksI
918 ll32
133 164
Elongation, 'Ao
Iledudion inaroa, 'Ao
GPo
lO'ps
13 16
32 33
llO 146
16.0 21.2
E
(a) Normalto highdensityofbasaI poles. (b) Parallelto highdensityofbasaI poles
Temperatures up to 870°C (1600 "F) maybeneeded Temperatures up to 870°C (1600 "P) maybe needed Temperatures up to 870 °C (l600 "F) maybeneeded Mild fanning Hydrofonn andfinishdie Temperatures up to 870°C (1600 "F) may beneeded
(a)Temperatures shouldbe held to a minimumto reducescaling.TImeat temperatureis important. becausethe titaniumsurfaceis embrittledby oxygenabove 540 °C (1000 "F) as a functionof time and temperature. Generally,2h is maximumfor 705°C (1300"F); 20 min is maximumfor 870 °C (1600 "F), These are accumulatedtimes to includeheatingtimes for singleor multistagefanning, intermediatestressrelief.andfinalstressrelief
Ti-6AI-4V: Tensile strength compared to other materials Thll.'llle strength
Maleria!
TI-6Al-4V TItaniumaIloys Alloysteel Aluminum Copper Stainlesssteel
MPa
ksl
895-1250 240-1500 100-2300 70-700 170-1500 400-1500
130-180 35-215 15-335 10-100 25-220 60-220
Alpha-Beta Alloys I 527
Ti·6AI·4V commercial equivalents: Compositions Spedllcalion France Ugine Ugine Germany DeutscheT. Fuchs Fuchs Thyssen Thyssen Thyssen Japan Daido Daido Daido Kobe Kobe Toho Toho UK IMI USA Orernet RMI RMI RMI Tel.Allvac TIMEr TIMET TIMEr
Designation
Description
lTfA6V UTA6V
AI
C
Fe
H
N
0
V
ShStrp PItBar Frg Ann Sh StrpPItBar Frg STA
5.5-6.75 5.5-6.75
0.08 0.08
0.3 0.3
0.015 O.ot5
0.Q7 0.Q7
0.2 0.2
3.54.5 3.54.5
baITI baiTi
LT31 TL64 TL64ELI ContimetAIV64 ContimetAlV64 ContimetAlV64ELI
Ann Frg ELIFrg PitBar FrgAnn PItBarFrgSTA ELIPItBarFrgPip Ann
5.5-6.5 6 6 5.5-6.75 5.5-6.75 5.5-6.75
0.08
0.25
0.013
0.07
0.2
0.1 0.1 0.06
0.3 0.3 0.15
0.015 0.015 0.013
0.05 0.05 0.05
0.2 0.2 0.13
3.54.5 4 4 3.54.5 3.54.5 3.54.5
baITI baITI baITI baITI balTi balTi
DAT5 DAT5 DT5 KS6-4 KS6-4ELI 64AT 64AT
RodBarRng Frg Ann RodBar RngFrgSTA RodBar FrgRng STA PltShWITBarAnn ELIPltShAnn
5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.75 5.5-6.5 5.5-6.75 5.5-6.75
0.1 0.1 0.1
0.3 0.3 0.3 0.3 0.25 0.4 0.4
0.015 0.015 O.ot5 0.0125 0.0125 0.0125 0.0125
0.05 0.05 0.05 0.05 0.05 0.05
0.05 0.2 0.2 0.2 0.13 0.2 0.2
3.54.5 3.54.5 3.54.5 3.54.5 3.54.5 3-5 3-5
balTi balTi balTi balTi balTi balTi balTi
IMI318
ShRodBarBil WirPItEx
4
balTi
3.54.5 3.54.5 3.54.5 4 3.54.5 3.54.5 3.54.5
baITI balTi balTi balTi balTi balTi balTi
STA
Ti-6A14V 6Al4V-ELI 6AI4V 6A1-4V Allvac64 TIMErAL64 TIMErAL64 ELI TIMErAL64 STA
0.03 0.03
6
ELI BarBil Ex PltShStrp Ann BarBilExPltShStrpWlrAnn BarBil Ex PItSh Strp WIT
5.5-6.5 5.6-6.75 5.6-6.75 6 5.5-6.75 5.5-6.5 5:5-6.75
Ann ELIAnn log Bil Bar PItSh Sir STA
0.08 0.08 0.08 0.18 0.1 max 0.08 max 0.1
Ti·6AI·4V: Effect of oxygen content on tensile properties Oxygen Condition BA STOA RA
BQ
centent
Low(a) Standardtb) Low Standard Low Standard(c) Low Standard
Thnsileyleld strength MPa ksi 773 883 904 945 711 1055 863 980
112 128 131 137 103 153 125 142
Ultimate tensile strength MPa ksI 856 994 973 1042 876 1076 932 1076
a + Ilforged+ recrystallization annealed(a) a + Ilforged+ mill annealed (minimumvalues) a+ Ilforged+STA(aged4h at 590 DC, or 1095oF) a + Ilforged+ STOA(aged 24 hat 590 DC, or 1095oF) Ilforged+ AC (BA)+ 705°C. or 1300°FI2hiAC Ilforged+ WQ (BQ)+ 705°C, or 1300°FI2hlAC a+ IlforgedDA(870°C, or 1600°FI2hlAC + 705°C, or 1300°FI2h1AC)
711
103
876
127
828
120
897
876
127
904
0.13 0.2 0.2
0.4 max 0.25 max 0.4
0.015 max 0.0125 max O.ot5
0.05 max 0.05 max 0.05
0.2 max 0.13 max 0.2
Reduction of area,
%
%
Alloy
11 11 16 14 12 13 6 10
23 20 47 33 36
6Al4V
6 20
Conditlon
Ultimate tensile strength(a) MPa ksl
Annealed 900-993 130-144 Solutiontreated 1172 170 + aged 830-896 120-130 6Al-4V(lowoxygen) Annealed
Thnsile yield strength 0.2% oII"set(a} Elongation, ksI
MPa
%
830-924 120-134 1103 160
14 10
760-827 110-120
15
(a)Lower values areminimumsand uppervalues areaverages
Ti·6AI·4V: Recommended forging temperatures
Ti·6AI·4V: Effect of thermomechanical processing on tensile properties Ultimate tensile strength MPa ksI
0.05 0.05
Elongation,
124 144 141 151 127 156 135 156
Thnsileyield strength ksI MPa
om-oms om.oms om-o.ors
Other
Ti·6AI·4V: Minimum and typical tensile properties
(a) 0.12 W1% oxygen. (b) 0.19 wt% oxygen.(c) 0.20 wt% oxygen(plate)
Condition
0.25 0.25 0.25
OT
Alloy
Belatransus OF °C
Ti-6A14V
995
1825
Ti-6Al-4VELI
975
1785
Forging process Conventional Bela forging Conventional Bela forging
Metal temperature OF OC
870-980 900-1065 870-950 990-1045
Elongation,
Reduction orarea,
%
%
12.4
36
Ti·6AI·4V: Forging equipment and die temperatures
130
10.0
25
Forging type/ equipment
938
136
15.2
34
131
973
141
15.5
47
773
112
856
124
11.2
23
863
125
932
135
5.9
6
856
124
911
132
15.3
47
(a) 925°C (1695 °F)/4 hlcool at 50 °C (90 0F)lh to 760 °C (1400 °F)/air cool
Opendie forging Ringrolling Closeddieforging Hammers Upsetters Mechanicallscrew presses Orbital forging Spin forging Roll forging Hydraulic presses Hot die forging Isothermal forging
1600-1795 1650-1950 1600-1740 1815-1915
Die temperature
150-260 95-260
300-500 200-500
95-260 150-260 150-315 150-315 95-315 95-260 315480 705-870 930-980
200-500 300-500 300-600 300-600 200-600 200-500 600-900 1300-1600 1700-1800
528/ Heat Treater's Guide: Nonferrous Alloys
Ti·6AI·4V: Effect of commercially available thermomechanical processing routes Forging Composition(a) Std CMG Std Ell Std Std Ell
Std
ELI Std Ell
Std Ell
Std CMG
process(b)
Heat trealment(c)
alP alP alP alP pI P2 P2 pHDF POOP alP alP P2 P2 alP alP
MA MA RA RA MA MA MA MA MA pA C'JA DuplexSTAN DuplexSTAN DuplexSTA DuplexSTA
Strength
K"
Smooth HCF
Notched HCF
FCGR
LCF
(+)
(-)
(+)
(=) (=)
(=) (=)
~)
(+)
(++)
(=) (-) (-) (-) (-)
~) ~)
(+) (+) (+)
(+)
H
(++) (++) (++)
(-)
(+)
(~
(++) (-) (-)
(-)
(+) (+) (+) (+) (+) (+) (+) (+)
(+) (+)
(=) (=)
Product cost
Product unironnily
100 105 105 115 95 90 95 110 115 105 115 102 110 110 115
100 100 120 130 90 85 95 110 110 130 150 110 115 120 120
Baseline (=) (-) (-) (-) (-) (=) (-)
H (-) (=) (-)
(+) (++)
(++) (=)
(+)
H (-)
(=) (=) (-) (-) (-) (-) (-) (-) (-) (-) (-)
(++)
(+) (++) (++) (+++)
(+) (++) (=) (=)
(+) (++)
LEGEND: (a) Std, standardcomposition; ELI, controlledcomposition; CMG, high interstitial composition. (b) alP, 11+P working; PI, beta preformingonly; p2,beta preformblock;pOOF,betahotdie forged. (c)MA, mill anneal;RA, recrystallized anneal;BA, betaanneal;STNSTAN, solutiontreatedandaged/annealed
Ti·6AI·4V: Forging properties (minimum room temperature values) Forging
Heat
Composition
process
treatment
Standard(a) Standard(a) Special(b) Standard(a) Special(b) Standard(a) Standard(a) Special(b)
l1+P l1+P l1+p l1+P l1+P p preform,11 + p blockandfmish p preform,p block,11 + Pfmish P preform,p block,11 + P fmish
MA RA RA
PA
pA MA MA DuplexSTAN
Thmlleyleld strength MPa
Ultimate tensile strength MPa ksI
ksi
12Q.125 115-120 110-115 115-125
827-862 793-827 758-793 793-862 758-827 813-848 813-848 758-793
13Q.135 125-130 12Q.125 135-145 12Q.125 13Q.135 125-130 12Q.125
896-931 862-896 827-862 931-1000 827-862 896-931 862-896 827-862
uo-izo
118-123 118-123 110-115
Reduction FJongolion, %
of'area,
10 10 10 6-8 6-8 10 8-10 6-8
2Q.25 2Q.25 2Q.25 1Q.15 1Q.15 2Q.25 15-20 IQ.15
Fracture toughness MPa'lii: ksI'1iii:'
%
44-45 60-71 77-88 82-93 88-99 66-77 71-88 82-93
40-50 55-65 7Q.80 75-85 80-90 60-70 65-80 75-85
(a)Standardspecimen: 5.5-6.75AI, 0.10 C, 0.30Fe,0.015H, 0.05 N, 0.20 0, 3.5-4.5V,0.40other.(b)Specialcomposition: 5.5-6.2AI,0.08 C, 0.25Fe, 0.0125H, 0.05 N, 0.13 0, 3.5-4.5V, 0.30other
Ti·6AI·4V: Typical parameters andconditions for plasma-arc welding Travel speed,
Current
Arc
(DC EN),
In./min
A
voltage, V
Shleldlng gDJ
20 13 10 10 7
185 175 225 270 250
21 25 38 36 39
Argon Argon 75He-25Ar 50He-50Ar 50He-50Ar
Gasllow,n'/h Orilke Shleldlog gas gDJ
. Ti-6AI·4V: Typical alpha case afterhotforming Amount orremoval
Thmperature "C
OF
540-595
1000-1100
595-650
1100-1200
Squareburt V-groove
650-705
1200-1300
Note: Backinggas and trailingshieldrequired;keyholetechniqueused with orifice-to-work distanceof 0.187 in.
705-760
1300-1400
Thickness, In.
0.125 0.187 0.390 0.500 0.600
8 18 32 27 30
60 60 60 60 60
Squarebult Squarebult Square butt
In.
4 12 2 6 1 2 12 I
2
0.013 0.025 0.013 0.025 0.013 0.025 0.051 0.025 0.051
0.0005 0.001 0.0005 0.001 0.0005 0.001 0.002 0.001 0.002
Ti·6AI·4V: Formability comparison MInImum bend, Rh Longltudloal(a) Tnwsvene(h)
70 400 600 795 1000 1200 1400 1500
necessary perside nun
Jolnllype
Ti-6AI-4V: Minimum bendradius
21 205 315 425 540 650 760 815
Time, h
4.5-6 3.5-4 3.5 3-3.5 2.5-3 2-2.5 1.5 I
5-7 3.5-6.5 3-5.5 2.5.5 2.5-4 2-3 1.5-2 1
Process
Brakepress(min radius at KI) Drophammer (max stretch)at 455-510°C (850-950"F) Hydropress (trapped rubber)at315-370°C (60().700 "F): Stretch,max Shrink,max Joggle-depth ratio at: RT
315-370°C (60().700 oF) Maximumstretchwrapat RT Maximumskinstretchat 455-510°C (85Q.950 oF)
(a)Bendaxisperpendicular to rollingdirection.(b)Bendaxis parallelto rollingdirection (a)Solutiontreatedcondition
11-SAl-2.SSn
~Al4V
11-13V-11Cr-3Al
3.5T
4.5T
13%
13%
1.5T 16%
5% 3%
5% 4%
10% 6%
4 4.5 8% 12.5%
4.5 3.0 3.5% 17%
1.25 1.00 5.5%(a) 13.5%(a)
Alpha-Beta Alloys I 529
Ti-6AI-4V: Typical parameters and conditions for gas tungsten-arc welding
Ti-6AI-4V: Heat treatments Comment!
Heat treatment
Stressrelief annealing
2t04h595 °C (1100OF), aircool
Fullannealing 2 h, 735± 15°C (millannealing) (1355±25 oF), aircool
Relievesresidualstressesfromwelding, forming, etc.This cycleonlyprovidesa partia1 stress relief.Afull annealmustbeusedforfullstress relief.Lowstrength,goodductility Mostcommonheattreatment, hasgoodoverall properties combinations. Lowstrength, good ductility Approximately thesamestrengthandductilityas above,butwithimprovedfracture toughness
5 min 870°C (1600oF), rapidfurnacecooled, plus5 min 595°C (1100oF), aircool Recrystallization 4 or moreh, 925°C (1695 UsuallyusedforEUmateriai. Strength oF), furnacecoolto760 annealing comparabletoaboveconditions, but improved °C (1400 oF) at 55°C damagetolerance(fracture toughness, stress(100 0F)lh (orslower), corrosionresistance, reducedcrackgrowth coolto 480°C (900 oF) rates).StrengthislowerforELImaterial at 370°C (700 0F)lh (or faster), aircool Duplexannealing 10 min, 940°C (1725oF), Improveddamagetolerance aircool,plus4 h 675°C (1245"P), aircool 30 min, 1035°C (1895oF), Usedto maximizedamagetoleranceproperties. Betaannealing aircool,plus 2h,130°C Theseproperties are attained witha slightlossof (1345oF), aircool ductility anda significant fatigueloss.A preliminary treatmentfollowed suchas annealing 30 min, 1035°C (1895oF), BetaSfA waterquenchplus4h, 510 to680°C (950to 1250oF) 30 min, 1035°C (1895oF), Similarto betaannealwithimprovement in fatigue BetaSTOA waterquenchplus2to 4 performance. May be preferable to betaanneal h,675 t0730 °C becauseof improved fatigueproperties, butat a (1245to 1345oF) costin damagetolerantproperties 10 min, 940°C (1725oF), Usedasan intermediate stepfor formingmaterial Solutionheat waterquench ultimately to beusedin the STAcondition. Not treatment to beusedas a finalcondition dueto instability 10 min, 940 0c( 1725oF), Higheststrengthcondition, butlessductility, stressSolutionheat treatmentand corrosionresistance, andfracture toughness than waterquench,pIus4 h, aging 510 to 540 °C (950to annealed 1000"P), aircool Solutionheat 10 min, 940°C (1725"P), Strengthintermediate between annealedandSfA, treatmentand waterquench,plus4 h, but improvedductility anddamagetolerance overaging 675°C (1245 oF), aircool properties comparedtoSTA Annealingfor continuously rolledsheet
Ti-6AI-4V: Typical parameters and conditions for electron beam welding Material
Ae<eIerating vobge,
thIcIwess,
in.
kV
0.125 0.20 0.66 1.0 2.0 3.5
20 28 45 36.5 45 90.0
Beam current, mA
Travel rate, In./mIn
95 170 275 375 450 500
30 98 45 44 26 20
'l\mg!ten Materiot electrode tbielme&ol(o), diameter, in. in.
Filler
rod dlometer, In.
Nozzle
Shielding
Welding
Number
size ID,in.
gasOow,
currentlb),
of
ft'fh
A
puleS
3/8 5/8 5/8 5/8 5/8
18 18 25 25 25
20-35 85-140 170-215 190-235 220-280
I I I 2
6 6 8 8 8
5/8 3/4 3/4
30 35 40
275-320 300-350 325-425
2 2 3
8 6 6
Square-groove and fillet welds 1/16 0.024 1/16 0.063 1/16 3/32 0.093 1/16 3/32 0.125 1/8 3/32 0.188 V-grooveand fillet welds 1/8 1/8 0.25 1/8 1/8 0.375 5/32 1/8 0.50
Travel speed(c), in.[lnln
I
Note: Tungstenusedfor the electrode;first choice2% thoriatedEWTh2,secondchoice 1% thoriated BW1h I. Use ftIlermetalone or twogradeslowerInstrengththanthe basemetal.Adequategas shieldingis essentialnotonly for the arc,but for heatedmaterialalso.Backinggas is recommended at all times.A trailinggasshieldis also recommended. Argonis preferred.Forhigherheatinput,on thickermaterialuse argon-helium mixture, Withoutbackingor chill bar, decreasecurrent20%. (a) Or filletsize. (b) Directcurrentelectrodenegative.(c)Per pass
Ti-6AI·4V: Machinability comparison/ratings ABoy 2017aluminum Leadedbrass B1112, resulfurized steel 1020carbonsteel 4340alloysteel CPTI Type302stainlesssteel TI-5A1-2.5Sn A4340alloysteel TI-8Mn TI-6A1-4V TI-8A1-IMo-IV TI-6A1-6V-2Sn TI-6A1-4V TI-6A1-6V-2Sn TI-13V-llCr-3A1 TI-13V-llCr-3A1 A4340alloysteel HS25(cobaltbase) Rene41 (nickelbase)
Condltlon(o)
Rotlng(b)
T4
300 200 100 70 45 40 35 30 25 25 22 22 20 18 16 16 12 10 10
HR
CD A
A A
A Q&T (40 HRC) A A A A HT HT
A HT
Q&T (52 HRC) A HT
6
(a)T4, solutionheat treatedand artificially aged; HR, hot rolled;A, annealed;HT, solutiontreated and aged;CD,cold drawn;Q&T,quenchedand tempered.(b) Basedon AlSIBI1l2 steelsas 100
Ti-6AI-4V: Typical parameters and conditions for laser beam welding Materiolthiclmess, in.
Loserbeompower(o), kW
Travel rate,ln.[lnln
5.5 5.5 13.0
60-70 50-60 NA
0.140 0.230 0.50 (a) CO2laser,continuouspower
Ti-6AI-4V: Parameters and conditions for gas metal-arc welding Material thlckness(o), in. 0.125 0.250 0.500 0.625 l.00(e) 2.00(e)
Wire
Shielding-
Ceed speed(b),
gos IIow(c),
Welding current,
voltage(d),
in.[lnln
ft'/b
A
V
Travel rate, in.[lnln
200-225 300-320 375-400 400-425 380 550
36 36 36 50 36 50
250-260 300-320 340-360 350-370 320-350
20 30 40 45 36 33
15 15 15 15 20-23 25
Arc
(a)Groove weldsproducedin flat position.(b) 0.062 in. diamfillerwire.(c) 75% Ar+ 25% He. (d) DCEP.(e)Multipassweld
Ti-6AI-4V: Typical parameters and conditions for resistance spot welding Materiol tbielmm.
Welding current,
Electrode Coree(o),
In.
kA
Ib
0,035 0.062 0.093
10.6
5.5 12.5
600 1500 2400
(a)RWMAclass2 copperalloyelectrodes, 75 mm (3 in.) faceradius
Weld time, cycles(60 Hz)
7
10
16
530 I Heat Treater's Guide: Nonferrous Alloys
Ti-6AI-4V: Mechanical properties vs, heat treatment Ultimate tensile strength MPa ksi
Tensile yield strength MPa ksi
1020 930 930
148 135 135
951 869 860
138 126 125
1000 1000
145 145
895 938
930 1000
135 145
860 990
Heat treatment
Mill anneal
STOA ELl STD Recrystallize anneal ELl STD Betaanneal ELl STD Duplexanneal ELl, forged STD, plate ELl, sheet STD, bar ELl, bar Beta,STOA ELl STD BetaSTA,STD Soluticntreatand age
Elongation, %
Reduction of area, %
K"
MPa\liii'
ksi'Jiii:'
43(a)
39(a)
15 10
20
55
50
130 136
12
30
60 47
55 43
860 931
125 135
10
25
83 56
75 51
125 144
795 910
115 132
8 11
20 20
99 95
90 86
892 931 945 1014 9343
129 135 137 147 136
814 903 895 903 832
118 131 130 131 121
12 16 15 17 13
36
124(b)
112(b)
176(e)
16O(e)
90
82
938 972 1172 1270 1186 1117
136 141 170 184 172 162
860 900 1069 1181 1069 951
125 130 155 171 155 138
II 9 8 16 16 17
18 13 15 41.5 56 60
134(b) 99
I22(b) 90
Solutiontreat
47
(a) Estimated.(b) KIc invalid.(e)K c
Ti-6AI-4V: Time-temperature-transformation diagram. Solution annealed at 1020 °C (1875 OF), and quenched directly to reaction temperatures LIVE GRAPH Click here to view 900
p
1600
800~~
700
~:J
~---;~+a
A p
Ms -
.
-
--
-
-
1400
~+a
-
-
-
!;'-
1200 e:> ::>
~Q)
~ 600 Q) a. E ~ 500
a.
1000 E Q)
f-
800
Ti-6AI-4V: Variation of tensile properties of bar stock with solution treating temperature Room-temperature tensile propertlesta)
Sotution-treating
-c
temperature OF
845 870 900 925 940
1555 1600 1650 1695 1725
Tensile strength MPa ksi
Yield streugth(b) MPa ksi
1025 1060 1095 1110 1140
980 985 995 1000 1055
149 154 159 161 165
142 143 144 145 153
Elongation in4D, %
18 17 16 16 16
(a)Propertiesdetennioed on 13mm(0.5in.)baraftersolutiontreating,quenchingand aging.Aging treatment: 8h at 480 °C(900 OF),aircool.(bj At 0.2% offset
Ti-6AI·4V: Microstructure (TEM). Equiaxed a (dark) and a" (light)
Alpha-Beta Alloys /531
Ti-6AI-4V: Thermal treatments with three different cooling rates
T 1050'C 850'C
®
800'C
c<.
.
0
.
650'C
V
Ti-6AI
-100x
-lOOx
- 500x
- 500x
Ti-6AI-4V: Hydrogen embrittlement susceptibility vs. temperature. Ti-6AI with a continuous 0: phase and Ti-6AI-4V exhibit a maximum in crack growth susceptibility near 0 °C (32 OF), whereas Ti·6AI·6V-2Sn with continuous p phase exhibits a maximum near 50°C (120 OF). No maximum was observed for Ti-5AI-2.5Sn at the temperatures tested. All crack-growth rates correspond to an applied stress intensity near 50 MPa.ym (45 ksifu)
LIVE GRAPH
Click here to view -300
-400 10-1 l>
.!!!
E 10-2 E
A
0
Metall. Metall. Metall. Metall. Metall.
Trans., Trans., Trans., Trans., Trans.,
Temperature, OF -100
-200
Vol 3, 1972, p 2107-2113 Vol 11A, 1980, p 973-981 Vol 9A, 1978, P 23-29 Vol 11A, 1980, p 1391-1400 Vol 11A, 1980, p 1391-1400
o
200
100
---------7-=--;-----------j
.;..-1
~ 10-3 ~
~ 10-4J-..-----~---------___,_-----------+_--·Ti-6AI-6V-2Sn--- 38 ppm H
s:
~ 10-5
Ti-6A1 100 ppm H
0,
-'"
~ 10.£
Ti-6AI-4V 233-255 ppm H
0 10-7
Ti-6AI-4V 50-70 ppm H
10-8
-250
-200
-150
-100 -50 Temperature,OC
o
50
100
532/ Heat Treater's Guide: Nonferrous Alloys
Ti-6AI-4V: Typical microstructure after working and annealing
lamellar structure following "beta-processing"
Rolled 30% 955"C
Annealed 925°C
2 hr
-
Rolling Direction
Forged 70% 955"C
Annealed 925°C
2 hr
Forging Direction
t Extruded 140% 955°C
Extrusion Direction
Annealed 925°C
2 hr
Alpha-Beta Alloys I 533
Ti-6AI-4V: Tensile properties of annealed castings vs. oxygen. Test specimens 6.4 mm (0.252 in.) in diameter were cast to size and polished with grit paper. Specimens were annealed in argon at 705°C (1300 OF) for 2 h, air cooled. Each data point represents an average of at least four tests
Ti-6AI-4V: Stress relief vs. time
Click here to view 260°C (500 of)'
LIVE GRAPH
Ultimate tensile strength
.
950
/
tc:
900
~50'nIt\--+---f----+-----'----~
I 1140
ur
ur
II)
II)
~
I·
50
OJ
~
g>
'0
'iii
OJ
OJ
([
([
25
~
~
.
~
::>
::>
~250·1-+--f-----c--+-~-+---+-----l
£
130
~
480°C (gOO of),
'lii
.
• ~ • •
n,
:::;;
100
.
Click here to view 1000
LIVE GRAPH
iii
595 °c (1100 of)
850 30
15 120
8ooL-
---'-
0.12
60,--h--j0 , 25
Time
-'-----
0.14
45
min
50
----.J
0.18
0.16
Oxygen content, wt%
Ti-6AI-4V: Heat treatment cycles of transformed p. Cooling rate through the transus determines the fineness of transformed structures (
Processing cycles for fine microstructures in a + palloys. Although not indicated here, recrystallization anneal has the slower cooling rate
13- Transus
i3-Transus
t
t
T
T
we.
AC
\ fin'e coarse a' lamellar lamellar
time --
time __
Ti-6AI-4V: Effect of temperature on tensile strength (0.5 h exposure)
LIVE GRAPH Click here to view
400
Temperature, of 600 800
I
i
Ti-6AI·4V (STA)
:
iTi-6AI-6V-2Sn (ANN)
o 120 0
200
I I
..
I
~ 110 0 £ C,
I I
,
c: ~
I
Ti-6AI-4V (ST)
------
V
~
Ti-6AI-4V (DA)
.:
--.....
I
'lii ~
"iii
~ 100 0
f-
I
T,I.8AI.l Mo-l VI(DA)
, , I I I
90 0 -100
o
TI-6AI-4V (MA)
I
I
I 100
200
I
-1 70
I
~
-1 60 ~ £
'\
C, c:
~\
-~
~
- 150
300 400 Temperature, °c
500
600
700
~
"iii c:
{!?
<,
I I
I I
1400
,~
/
/
1200
1000
-1 40
800
534/ Heat Treater's Guide: Nonferrous Alloys
Ti-6AI-4V: Stressreliefnomograph. Relationship of time, temperature, and percentof stress reliefofli-6AI-4V. Twoexamples(50% and 100% relief)shown 900 .......- - - - - - - - - - - - - . . . . . - - - - - - - - - - - - - - - - - - . . . . . , 106 10,000
5000 500 ·C 100
10 5 1000
500
1000 85
Stress relief, %
60 1100
5
25
1200
-L.
...L.._ _-L
--J
Alpha-Beta Alloys I 535
Ti-6AI-4V: Typical microstructures. (a) Transverse view of mill annealed textured plate. (b) Conventionally processed plate (recrystallization annealed). Mill annealed treatment: 690°C (1275 OF) for 2 h, AC. Recrystallization anneal: 980°C (1795 OF) for 30 min, FC. 500x
(b)
(a)
Ti-6AI-4V: Quenching and aging process schematic. Lower solution temperatures allow higher amounts of solute, which generally favors the formation of orthorhombic (0:') martensite upon quenching 1200 1000
- - -
Ptransus p quench
U
0
u+P
BOO
Boooe Soft quench
i:J
~Q) 600 a. E Q)
I-
550 0 e Aging range
400
Aged, fine u+P
Primary u and aged fine u+P
u and aged
350 0 e
200
Primary u+a' As-quenched structures
u+u" (soft martensite)
a+P
536/ Heat Treater's Guide: Nonferrous Alloys
Ti-6AI-4V: Primary a and transformed
p:
Microstructure. A
broad primary a lamellae recrystallized into a string of a grains and is surrounded by transformed p. No effort is made to distinguish between a' and secondary a in the transformed region. TEM micrograph. 4300x
Ti-6AI-4V: Needlelike «' and prior primary a: Microstructure. The primary a lamellae segments are divided into recrystallized grains. Channeling contrast SEM
Ti..6AI..6V..2Sn Common Name. Ti-662
Characteristics
UNS Number. R56620
Phases and Structures. Alloy Ti-662 is normally processed in the a + p two-phase field, resulting in primary equiaxed a and some p. For example, annealing treatments (-760°C or 1400 "F) moderately low in the two-phase a + p field after normal a + p processing result in microstructures with a high volume percentage of primary a with stabilized p at the equiaxed a grain boundaries. If the processing involves less exposure time or less working in the a + p region and is subsequently annealed at approximately 760°C (1400 OF), the primary a grains appear more elongated, and the volume percentage is high. Both structures develop acceptable mechanical properties.
Chemical Composition. Ti-662 contains a total of about 1% (Cu + Fe) in approximately equal proportions, which give it much-improved heat treatability. Its nominal 6% aluminum content stabilizes the alpha phase and increases the hot workability range by raising the beta transus temperature to approximately 945°C (1735 OF). Cooling from above this temperature with little concurrent or subsequent deformation generally results in inferior ductility. As a neutral stabilizer, the 2% tin strengthens both the alpha and beta phases, and in combination with the aluminum, provides better room- and elevated-temperature strength properties than those of Ti-6AI-4V and other lower-alloy phase-beta compositions. Beta stabilization is accomplished by nominal additions of 6% vanadium, 0.5% copper, and 0.5% iron. Acting together, these elements permit heat treatment of the alloy to high strength levels by solution treatment and aging Alloy Segregation. Ingot composition must be controlled within specified limits, and special melting practices, particularly for the final melt, are required to minimize segregation during solidification. Excessive macrosegregation results in ''beta flecks," which are harder, less-ductile areas after heat treatment. Detrimental effects of beta flecks have not been demonstrated for this alloy Exceeding Composition Limits. As for all alpha-beta alloys, excessive amounts of aluminum, oxygen, and nitrogen can decrease ductility and fracture toughness. Excessive amounts of beta stabilizers (molybdenum and vanadium) affect the stability of the alloy and increase its heat treatability, therefore making control of properties more difficult. Excessive impurity levels may raise yield strength above maximum permitted values or decrease elongation or reduction in area below minimum values. See Tables for equivalent specifications, and for commercial compositions
Totally transformed p structures are often considered unacceptable, although acicular products do have advantages. Annealing temperatures and cooling rates determine the presence and the coarseness of secondary a (transformed P). For solution treatments up to 825°C (1520 "F), P is sufficiently enriched with vanadium to prevent decomposition into martensitic a. At temperatures above 900 °C (1650 OF), Pdecomposes completely to martensitic a. Between these two temperatures, partial transformation of poccurs (see the isothermal TIT diagram after quenching from 850°C or 1560 OF). From above the p transus, the M, temperature is about 420°C (790 OF)
Beta Transue, 945 ± 10 °C (1735 ± 20 oF) to 955 ± 5 °C (1750 ± 10 oF) See Figures for time-temperature transformations from 850°C (1560 "F), for isothermal transformation diagrams, and for phase transformation diagram
Product Forms. Ti-662 is produced by all U.S. titanium melters as bar and billet for forging stock. Plate, sheet, wire, and extrusions are also available Applications. This alloy was developed as a higher strength version of Ti64, with an ultimate tensile strength of 1200 MPa (175 ksi) in the heat treated condition in diameters up to 25 mm (1 in.).
Alpha-Seta Alloys I 537 Ti-662 is used as sheet, light gage plate, extrusions. and small forgings when service requirements call for high strength at temperatures up to 315 °C (600 "F), usage generally is limited to secondary airframe structures because the attractiveness of higher strength efficiency is minimized by lower fracture toughness and fatigue properties. Ti-662 is used for aircraft structural members. centrifuge parts, and rocket-engine parts
Limitations in Use. As is characteristic of other titanium alloys, exposure to stress at elevated temperature produces changes in the retained mechanical properties. The stress and temperature limits below which these changes will not occur have not been established for this alloy
Chemical/Corrosion Properties. Ti-6AI-6V-2Sn has less corrosion resistance in reducing media than several other titanium alloys. It also is one of the least resistant to crevice corrosion in salt solution. See Figures for corrosion resistance in HCl solutions, and for crevice corrosion in saturated brine
Mechanical Properties. See Table for typical hardness at room temperature. See Figures for variations in Rockwell C hardness, and for Knoop hardness after oxidation
Fabrication Properties Forging. This alloy can be fabricated into all forging product types, although closed-die forgings predominate. Ti·6AI-6V-2Sn is a reasonably forgeable alloy with lower unit pressures (flow stresses), improved forgeability, and less crack sensitivity than the a-13 alloy Ti-6AI-4V. The final microstructure of Ti-6AI-6V-2Sn forgings is developed by conventional thermomechanical processing-a combination of subtransus forging followed by subtransus thermal treatments
Ti-6AI-6V-2Sn: Temperatures for hot forming -c
Alloy
CPTI(allgrades) Alphaand near-alpha alloys TI-8Al-IV-IMo 11-5Al-2.5Sn Alpha-betaaUoys 11-6Al-6V-2Sn Beta alloy 11-13V-11Cr-3Al
Forming temperature
OF
480-705
900-1300
790± 15 620-815
1455±25 1150-1500
790± 15
1455±25
605-790
1120-1455
Note: Annealedor solutiontreatedmaterial
Welding. Ti-6AI-6V-2Sn is difficult to weld. Like all titanium alloys, it is weldable by all methods except shielded arc welding and submerged arc welding (because no flux is permitted). The ductility of Ti-6AI-6V-2Sn weldments is poor unless a postweld annealing treatment is used. Solution heat treatment followed by water quenching does not improve weld ductility, and subsequent aging of such conditioned material results in weld metal embrittlement. Solution of the weld metal ductility problem is possible in some applications by using an annealing treatment. The treatment of 4-h exposure at 725°C (1335 "F), followed by air cooling has been recommended
Machining. Machinability is comparable to that of a good grade of stainless steel
Recommended Heat Treating Practice Ti-662:Forgingprocess temperatures
Annealing. Ti-6AI-6V-2Sn is one of the strongest titanium grades availMetaltempelllture
Process
Conventional forging Supratransus forging
-c
OF
845-915
1555-1680
(a)
(a)
(a)Supratransus may be usedinearlyforging operations. but it mustbe followed by sufficient subtransusreduction
Final Thermal Treatments. Treatments for forgings include. annealing (A), solution treatment and annealing (STAN), and solution treatment and aging (STA), with final thermal treatment selected based on strength requirements. Ti-6AI-6V-2Sn forgings may be supplied in an annealed condition to facilitate machining and subsequently solution treated and aged to optimum strength levels. Annealing is conducted at 705 to 760°C (1300 to 1400 OF). Solution treatment is subtransus, at 845 to 900°C (1555 to 1650 "F), followed by water quenching. Forgings may then be annealed or aged. Aging is conducted at 510 to 620 °C (950 to 1150 OF) depending on strength mechanical-property objectives for the STA condition. Subtransus thermomechanical processes (forging and thermal treatment) for Ti-6AI-6V-2Sn forgings achieve equiaxed a in transformed 13 matrix microstructures that enhance strength, ductility, and high-cycle fatigue properties. Annealed microstructures consist of 40 to 80% a. Solution treated and aged microstructures are 10 to 20% equiaxed a. See Tables for forging process temperatures, and for effect of thermomechanical processing on properties
Forming. Ti-6AI-6V-2Sn is readily formable in the annealed condition. Sheet or plate is generally used in the annealed condition. When Ti-6Al6V-2Sn sheet and plate are hot formed at any temperature over 540°C (1000 OF) and air cooled, the material should be stabilized by reheating to 540 °C (1000 OF) followed by air cooling
able in the annealed condition, which consists of about 2 to 8 h of exposure at 705 to 760°C (1300 to 1400 "F), followed by air cooling or furnace cooling. This alloy is so highly beta stabilized that annealing should ideally be terminated by slow cooling from the annealing temperature to an intermediate temperature. Slow cooling, such as furnace cooling, produces maximum annealed strength. Air cooling may be used from annealing temperatures below 760°C (1400 OF). but strength will generally be lowered. Annealing at temperatures higher than 760 °C (1400 OF) is also possible
Solution Heat Treating. 885°C (1625 "F) is a workable solution temperature for a wide range ofproducts and applications. About 30% primary a, balance 13 phase, is found in the microstructure after this treatment. Water quenching is the standard method of terminating solution heat treatment, although fast air cooling achieved by forced air stream may be satisfactory for thin-section material because the 13 phase in this alloy is fairly stable. Solution treatment above the transus results in a severe loss of ductility. See Tables for stress relief and annealing treatments, and for solution treatment and aging. See Figures for effect of 565°C (1050 "F) aging on tensile properties (a) and (b); and for effect of solution treatment on tensile properties (a) and (b)
Ti-662:Stress relief and annealing treatments Heat
'Iemperature
treatment
Typlcal stressreliefrange 50 to90%relaxation ofresidual stress Typical anneal Extended annealrange
480-650 595 705-760 705-815
900-1200 1100 1300-1400 1300-1500
Time, h
Cooting method
Air or slowcool Air cool 2-8 Air or slowcool 0.75-4 Air or slowcool{a) 1-4 2
(a)Annealing at thehighertemperature, followed by a furnace coolto595°C (11OO°F) thenair cooling toroomtemperature isrecommended
538/ Heat Treater's Guide: Nonferrous Alloys
Ti-662: Equivalent specifications Specillcalioo UNS
Desigoalioo RS6620
China GB3620
TC-I0
AI
Other
Cu
Fe
H
N
0
So 2
V
5.5
5.5
hal1i(a)
5.5-6.5
0.5
0.5
O.oI5 max
0.04 max
0.2 max
1.5-2.5
5.5-6.5
Des
C 0.1 max;SiO.15max; balTI
Europe AECMATI-P64 prEN3316
Sh Strp Ann
5-6
0.35-1
0.35-1
0.0125 max 0.04 max
0.2 max
1.5-2.5
5-6
AECMATI-P64 prEN3317
PltAnn
5-6
0.35-1
0.35-1
0.0125 max 0.04 max
0.2 max
1.5-2.5
5-6
AECMA TI-P64 prEN3318
FrgNlIT
5-6
0.35-1
0.35-1
0.0125 max 0.04 max
0.2 max
1.5-2.5
5-6
AECMATI-P64 prEN3319
BarAnn
5-6
0.35-1
0.35-1
0.0125 max 0.04 max
0.2 max
1.5-2.5
5-6
AECMATI-P64 prEN3320
FrgAnn
5-6
0.35-1
0.35-1
0.0125 max 0.04 max
0.2 max
1.5-2.5
5-6
Germany WL3.7174
Sh Strp PItBarFrgAnn
5-6
0.35-1
0.35-1
WL3.7174
Sh Strp Pit BarFrg STA
5-6
0.35-1
0.35-1
Sh Strp PItBarExt Ann Sh Strp Pit Bar Ext lIT
5-6 5-6
0.35-1 0.35-1
AMS4936C
Sh StrpPlt Ann ExtRngAnn Ext RngSTA BetaExt AnnRng Rsll WId
5-6 5-6 506 5-6
AMS4971C AMS4978B AMS4978C
BarFrg WIT Rng BilAnn Bar WITFrg Bil RngAnn BarFrgRngAnn
5-6 506 5-6
Spain UNE38-725 UNE38-725
L-7303 L-7303
CO.05max; orua max; OEO.l max;balTI CO.05max;arO.4max; OEO.1 max;balTI CO.05max; OTO.4max;OEO.1 max;balTI CO.05max;arO.4max;OEO.l max;balTI CO.05max;OTO.4max; OEO.1 max;balTI
0.01250.015 0.0125O.oI5
0.04
0.2
1.5-2.5
5-6
C 0.05; OTO.4;balTI
0.04
0.2
1.5-2.5
5-6
CO.05;OTO.4;balTI
0.35-1 0.35-1
0.0125 0.0125
0.04 0.04
0.2 0.2
1.5-2.5 1.5-2.5
5-6 5-6
CO.05;OTO.4;balTI CO.05;OTO.4;balTI
0.35-1 0.35-1 0.35-1 0.35-1
0.35-1 0.35-1 0.35-1 0.35-1
0.015 O.oI5 O.oI5 O.oI5 max
0.04 0.04 0.04 0.04 max
0.2 0.2 0.2 0.2 max
1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5
0.35-1 0.35-1 0.35-1
0.35-1 0.35-1 0.35-1
O.oI5 O.oI5 0.015 max
0.04 0.04 0.04 max
0.2 0.2 0.2 max
1.5-2.5 1.5-2.5 1.5-2.5
0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.35-1 0.7 (nom)
0.015 O.oI5 0.015 0.0.15 O.oI5 0.015 O.oI5 O.oI5 O.oI5 O.oI5
0.04 0.04 0.04 0.04 0.04 0.04 0.04 0.04 0.04 0.04 0.02 max
0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2
1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5 2 (nom)
USA AMS4918F
AMS4936B AMS4936B
AMS4979B MILF-83142A Comp8 FrgAnn MILF-83142A Comp8 FrglIT MIL T-81556A CodeAB-3 Ext BarSlipAnn MIL T-81556A CodeAB-3 Ext Bar SlipSTA MILT-9046J CodeAB-3 Sh Sup PItAnn MILT-9046J CodeAB-3 Sh Strp PItST MILT-9046J CodeAB-3 Sli Strp P]tSTA MILT-9407G Ti-6Al-6V-2Sn BarBilAnn MILT-9047G Ti-6Al-6V-2Sn BarBilS'D\ SAEJ467 Ti662
5-6 0.35-1 5-6 0.35-1 5-6 0.35-1 5-6 0.35-1 5-6 0.35-1 5-6 5-6 5-6 5-6 0.35-1 5-6 0.35-1 5.5 (nom) 0.7 (nom)
CO.05;OTO.4;YOJlO5; balTI CO.05;OTO.4;YO.oo5;balTI CO.05;OTO.4;Y0.005; balTI CO.05max; oro.a max; YO.005 max;OEO.l max; bal TI 5-6 CO.05;OTO.4;YO.005;bal Ti 5-6 CO.05;OTO.4;YO.005;balTI 5-6 C 0.05 max;OTO.4max;YO.005. max; OE 0.1 max;balTI 5-6 C 0.05;OTO.4;YO.005;balTI 5-6 CO.05;OTO.3;balTI C 0.05; OTO.3;balTi 5-6 5-6 C 0.05; OTO.3;bal Ti 5-6 CO.05;OTO.3;balTI 5-6 C 0.05; OTO.3;hal TI 5-6 C 0.05; OTO.3;balTI 5-6 C 0.05; OTO.3;balTI 5-6 enos. OTO.3;YO.005;balTi 5-6 CO.05;OT0.3;YO.005; balTI 5.5 (nom) C 0.Q2max;Ni 0.006 max; Si 0.1 max;balTI 5-6 5-6 5-6 5-6
(a) OT, others total; OE, others each, single valuesare maximums
LIVE GRAPH Click here to view
Ti-662: Phase transformation diagram. Solution treatment tem-
Ti-662: Isothermal transformation diagram. Quenched from
perature
field to temperature indicated 1600 '$.
1400
.;
ffl
os s: Q.
'0
c: o
u
£
830·C . ;
(p,-110 ·C)
u'
Q)
E
Primary n
:::J
'0
Ms"""""
>
p+u'
Low ~
-) High
Solulion lrealmenllemperalure
10
10
Time, min
600
2
~
Alpha-Beta Alloys I 539
Ti-662: Commercial compositions Specification France Ugine Ugine Germany DeutscheT Deutsche T
Designation
Description
AI
Cu
Fe
H
N
0
So
V
Other
Uf662 Uf662
ShPltFrgAnn ShPltFrgQA
5-6 5-6
0.35-1 0.35-1
0.35-1 0.35-1
0.Ql5 0.015
0.04 0.04
0.2 0.2
1.5-2.5 1.5-2.5
5-6 5-6
balTI balTI
ContimetA1VSn6-6-2 Contimet AIVSn6-6-2 LT33 LT33
PItBarFrgPipAnn PitBarFrgPipSTA FrgAged FrgAnn
5-6 5-6 5-6 5-6
0.35-1 0.35-1 0.35-1 0.35-1
0.35-1 0.35-1 0.35-1 0.35-1
0.015 0.Ql5 0.Ql5 0.Ql5
0.04 0.04 0.04 0.04
0.2 0.2 0.2 0.2
1.5-2.5 1.5-2.5 1.5-2.5 1.5-2.5
5-6 5-6 5-6 5-6
CO.05;balTI CO.05;balTI CO.05; balTI CO.05;balTI
KS6-6-2 KS6-6-2 Ti-6A1-6V-2Sn 662AT
PltShAnn PItShSTA
5-6 5-6
0.35-1 0.35-1
0.35-1 0.35-1
0.0125 0.0125
0.04 0.04
0.2 0.2
5-6 5-6
balTI balTi
STA
5-6
0.35-1
0.015
0.04
0.12-0.2
1.5-2.5
5-6
CO.05;balTi
CO.08;balTi C0.08;balTi CO.05max; balTi CO.05; balTi
DeutscheT DeutscheT Japan Kobe Kobe Sumitomo Toho USA OREMEf RMI RMI Timet
Ti6-6-2 RMI6AI-6V-2Sn RMI6A1-6V-2Sn T1METAL6-6-2
MultFonnsAnn MultFonnsSTA Ann
5-6 5-6 5-6
0.35-1 0.35-1
0.35-1 0.35-1 0.35-1
0.0125-0.015 0.0125-0.015 0.Ql5
0.04 0.04 0.05max
0.2 0.2 0.2 max
1.5-2.5 1.5-2.5 1.5-2.5
5-6 5-6 5-6
Timet
T1METAL6-6-2STA
BilBarPitShStrSTA
5-6
0.35-1
0.35-1
0.Ql5
0.04
0.2
1.5-2.5
5-6
Singlevaluesare maximums
Ti-662: Effect of thermomechanical processing on properties Microstructural observation of thermomechanical processing options for T1-662 suggest that a morphology is the key microstructural feature affected by this processing route. However, a grain size modification is least significant. Cost and product uniformity implications are similar to those for T1-6AI-4V.
Alloy
'lMPoplion
Ti-6AI-6V-2Sn Std
a+ ~ forgeJMA a + ~ forgeJRA
Ti-6AI-6V-2Sn Eli
a + ~ forgeJRA
Ti-6AI-6V-2Sn Std
~ prefonnIMA ~ prefonnlblockIMA
'Thnsileyield
UltimatetensJle
strength
strength
120
ksi
MPa
ksi
%
%
MPa'lm'
ksi'liii:"
L T L T L T .L T L T
1094 1049 1041 1028 1022 993 1032 1021 1024 973
158 152 151 149 148.2 144 150 148.0 148.5 141
1164 1128 1110 1095 1089 1068 1094 1090 1110 1076
169 163 161 159 158 155 158.6 158.1 161 156
18 15
31 24 33 29 37 29 22 23 19 22
39
35
50
45
74 68 58 59
67 62 52 53 64 63
Temperalure, OF 140 160 180 200
0
0
Click here to view 220
240
6
•
• o
J: a.
5 4
•
3
•
Crevice corrosion
BP
2'---_---I----L~_ ___'_
__'__..l-_
_1
25
100
125
50
75 Temperalure, °C
71
69
'Thmpemlure 'fteatment SoluIion treatments Typicalfor mostproducts Sheet<3.22mm (0.125in.)thick Sheet>3.2mm (0.125in.)thick Bar,forging, extrusions Aging 'tYPical Low agingtemperature Overage Flatrolledproducts Bar,forgings. extrusions
No crevice corrosion 7
17
16 19 15 11 12 9 10
Ti-662: Solution treatment and aging
9 8
Kk
MPa
LIVE GRAPH 100
of area,
Dire<:tion
Ti-662: Crevice corrosion in saturated brine
80
Reduction Elongation,
CoolIng
°C
OF
Dumtion
method
885± 15 830-870 845-885 845-900
1625±25 1525-1600 1555-1625 1555-1650
60 min 5 to 15min 30 min 60 min
WQ WQ WQ WQ
540-620 480-540 595-650 565-620 510-595
1000-1150 900-1000 1100-1200 1050-1150 950-1100
408h
AC AC AC AC AC
4h 4012h
Next Page
540 I Heat Treater's Guide: Nonferrous Alloys
Ti·662: Corrosion comparison in HCI solutions. General corrosion of annealed titanium alloys in naturally aerated HCI solutions
3 100 ~
~
~
~2
80
ai
c:
ai 60 ~ c
"iii
"iii
g1
g
1!! 0
"E 0
40
0
0
0
0
20
LIVE GRAPH
0 0
0.5
o
20
1 1.5 Concentration of HCI, %
1
:l!500 c:
"E
'0.40 " 0 o
s:
o
~
16 h, 730°C (1350 oF) (A)
- - 1 0 h, 730°C (1350 OF) (B)
~ ~8 h, 705°C (1300 oF) (C) C \ ~,
yA
B' <,
{ :""? ::: ---=
.
D
300
Ti·662: Knoop hardness after oxidation 120
~ Depth of visible a case
60 0 ~
Click here to view
2.5
Distance from surface, llIT1 40 60 80 100
70 0
J: ui
2
E,F
6 h, 705°C (1300 °F)(D)
:- ~--=- --=- --==-- --=-12 h, 650°C (1200 oF) (E) 8 h, 650°C (1200 of ) (F)
20 0
o
234 Distance from surface, mils
LIVE GRAPH Click here to view
5
Ti-662: Variations in Rockwell C hardness. Chemical composition (wt%): 5.08 AI, 0.66 Cu, 0.55 Fe, 0.002 H, 0.02 N, 0.172 0, 1.78 Sn, and 5.41 V. Jominy bars with diameter of 28.55 mm (1.125 in.) and length of 125 mm (5 in.) were trepanned longitudinally from a position approximately halfway from the center of a 150 mm (6 in.) diameter forging. Bars were solution treated at 870 °C (1600 OF) for 2 h, followed by a conventional Jominy end quench. Aged specimens were held at indicated temperatures for 3 h and air cooled. Hardness measurements were performed along the length of the bar on which a surface flat had been ground at the center line of the bar LIVE GRAPH
Ti-662: Time-temperature transformations from 850°C (1560 OF). Dilatometric tests indicated M. temperature of 640°C (1185 OF), and X-ray measurements indicated that a.' martensite formed when isothermal holds were stopped by quenching before line A. Beyond line B, ~ is sufficiently enriched with vanadium to prevent martensitic transformation. Measurements indicated the disappearance ofli 3AI(y) beyond line C. 25 mm (1 in.) diam specimens solution treated at 850°C (1560 OF) for 1 h. Composition (wt%): 5.5 V, 5.65 AI, 2.35 Sn, 0.5 Cu, 0.62 Fe 850
Click here to view 51 o
• I:>
......
800
,"""
700
if- 650 i!!
" 1!.,
o ~45
."
(l+~+Y
.>:
750
As quenched Aged 480°C (900 oF), 3 h Aged 620°C (1150 OF), 3 h
600
a' ----.. Q+P
Q.
..... U+P+l a+~
a+~
.,
E 550
ui
f-
III
Ql
500
c:
~42 J:
•
450 400
2
5 Seconds
Minutes Time ---.-.
o
6 12 18 24 30 Distance from quenched end of Jomlny bar,
\6 in.
36
3 Hours
4
5
,j
Previous Page Alpha-Beta Alloys /541
treatm~nt temperature (1 h exposure terminated by water quenching) on the aged tensile properties of die forgings aged 3 h, 585°C (1090 OF), air cooled
Ti-662: Effectof solutiontreatment on tensile properties. Effect of solution heat
LIVE GRAPH
LIVE GRAPH 1300 40
1300 1400 1500 1600 1700 1800 1900 2000 1500
1400
1500
1600
1700
(}
1400
'" :;
-
30
200
190~
~ 1300
~
0
til
0
<:
e
<:
180 til 0
1200
1100
900
800
---
Elongation
170
• As forged »:
700
•-
1000
Solution temperature,
0
160 1100
700
°c
1900
2000
J
1- Beta transus
<,
'iii -"
0-
1800
I
210
e
Click here to view
Solution temperature, OF
Solution temperature, OF
Click here to view
1 / ~sforged
800
I RA
I
\: l\~
900
1000
Solution temperature,
1100
°c
(b)
(a)
Ti-662:Effectof565°C (1050of) agingontensileproperties. 1.5 mm (0.060 in.) sheet solution treated 15 min at 885°C (1625 OF), water quenched
LIVE GRAPH
LIVE GRAPH
Click here to view
Click here to view 1500
7
210 '" 1400 0:; £
.......
6 -c-,
.---
<,
6'-.
0, <:
e
TYS
til 1300
"0
~ <: <,
i!!
190 til
'$. C
o
~5 Ol
<:
o
iii
EI
4
180 1200 0.1
3
1
0.1
10
-:
Aging time, h (a)
1 Aging time, h
/
/ 10
(b)
Ti·7AI·4Mo UNS Number. R56740
Characteristics
Chemical Composition. The molybdenum addition, in stabilizing the
Product ConditionlMicrostructure. Ti-7AI-4Mo is an alpha-beta alloy with more beta in the annealed condition than Ti-6AI-4V because ofthe much lower solubility of molybdenum in alpha. The strength of Ti-7Al4Mo is about 100 MPa (15 ksi) higher than Ti-6AI-4V in the annealed condition and about 170 MPa (25 ksi) in the solution treated and aged condition. The depth of hardening is similar to that of Ti-6AI-4V. Guaranteed minimum tensile properties for reforge and upset tests are 10% higher than those ofTi-6AI-4V
beta phase, improves heat treatment and strengthens beta by solid solution. Compared with Ti-6AI-4V. both the alpha and beta phases are more highly alloyed and consequently stronger. The replacement of vanadium with molybdenum and the addition of 1% aluminum are the reasons why the elevated-temperature properties of this alloy are better than those of Ti6Al-4Y. This improvement reflects itself in increased resistance to deformation at forging temperatures in comparison with Ti-6AI-4V, although this difference may be small. See Tables for equivalent specifications, and for commercial compositions
Product Forms. Billet, bar, plate, wire, extrusions are available. Ti-7Al4Mo is used primarily in the form of light and intermediate forgings and extrusions
542/ Heat Treater's Guide: Nonferrous Alloys Applications. Ti-7AI-4Mo is a heat-treatable alloy with roughly 10% higher strength than Ti-6AI-4Y. In the annealed condition. It offers a considerable improvement in creep resistance at temperatures up to 480°C (900 OF) over Ti-6AI-4V. Short-term high-temperature tensile properties are improved as well. Ti-7AI-4Mo is used up to 455°C (850 "F), although it offers good stability under stress at temperatures at least as high as 480 "C (900 "F) for prolonged loading times. Usage is primarily for horns on ultrasonic welding equipment. Bar, forgings, and forging stock are in limited use for jet engine disks, compressor blades and spacers
This alloy is reasonably forgeable, with higher unit pressures (flow stresses), less forgeability, and higher crack sensitivity than Ti-6AI-4V. The final microstructure of Ti-7AI-4Mo forgings is developed by conventional thermomechanical processing-a combination of subtransus forging followed by subtransus thermal treatments
Final thermal treatments for forgings include annealing and solution treatment and aging, with final thermal treatment selected based on strength requirements. Forgings may be supplied in an annealed condition to facilitate machining and subsequently solution treated and aged to optimum strength levels.
General Corrosion Properties. General corrosion data on Ti-7AI-4Mo
Mechanical Properties
Annealing is conducted at 815°C (1500 "F), followed by fumacecooling to 565°C (1050 "F) and then air cooling. Solution treatment is subtransus at 925 to 955°C (1695 to 1750 OF), followed by water quenching. Forgings may then be annealed or aged. Aging is typically at 535 to 620°C (995 to 1150 OF), depending on strength objectives for the STAcondition. Subtransus thermomechanical processes (forging and thermal treatment) for forgings produce equiaxed a. in transformed ~ matrix microstructures that enhance strength, ductility, and high-cycle fatigue properties. Annealed and solution treated and annealed microstructures consist of 40 to 80% o; whereas solution treated and aged microstructures are 10 to 20% equiaxed o,
Hardness. Reported typical hardness value range is 32 to 38 HRe for solution treated and aged material
See Table for forging process temperatures
are limited. Molybdenum additions may increase corrosion resistance in reducing (nonoxidizing) environments at the expense of less resistance in oxidizing environments. Molybdenum also is usually beneficial for stresscorrosion cracking (SeC) resistance, but sec thresholds in salt solutions are comparable to Ti-6AI-4V with similar yield strengths (see Table). Hot-salt sec of a Ti-7AlAMo power plant component has been observed in conjunction with silver coatings (Metals Handbook, Corrosion, Vol 13, 9th ed., 1987, P 1039-1040)
Typical Tensile Properties. Typical room-temperature tensile proper-
Machining. Machinability is comparable to that of a good grade of
ties are higher than the guaranteed minimums (see Table), which vary with section size. Lower strengths occur in the annealed condition, or when STA material has been worked in the ~ phase field prior to heat treatment.
stainless steel
See Tables for Vickers hardness, and for minimum room temperature tensile properties in solution treated and aged condition
Fabrication Properties Ti-7AI-4Mo can be fabricated into all forging product types, although closed die forgings predominate. It is commercially fabricated on all types of forging equipment.
Welding. Weldability of Ti-7AI-4Mo is fair. Like all titanium alloys, Ti-7AI-4Mo is weldable by all methods except shielded arc welding and submerged arc welding (because no flux is permitted). Recommended filler metal is the same as the base metal.
Recommended Heat Treating Practice Ti-7AlAMo is used in the annealed or solution treated and aged condition. See Table for typical heat treating procedures.
Ti-7AI-4Mo: Commercial compositions Spedlication Designation
Descriplion
France Ugine USA
FrgQuenAged
RMl
Timet
UTA7D
Ti-7AI-4Mo Bil TIMETAL7-4 Ann
OT
AI
C
Fe
H
Mo
N
0
Other
6.5-7.3
0.08
0.25
0.0125
3.5-4.5
0.5
0.2
bam
6.5-7.3
6.5-7.5 0.1 max
0.08max 0.3 max
0.25 max 0.13 max
0.01 3.5-4.5
3.5-4.5 0.05 max
0.05 max 0.2 max
bam bam
Ti-7AI-4Mo: Minimum RT tensile properties in STA condition Thickness as
rol1ed orforged mm
in.
Thicknessas heatjreated IDOl in.
";13 >13-25 >25-50 >50-100 >100(a) >100(b)
$.5 >0.5 >1-2 >2-4 >4(a) >4(b)
$13 >13-25 >25-50 >50-100 25 22
>100-150
>4-6
$25
$.5 >0.5-1 >1-2 >2-4 1 0.875 square ";1
U1Iin:uile tensile
strength
'Ienslle properties (guaranteed mloimum) Thnsile Yield Eloogalion in strength 4D,% (0.2% 011"0
MPa
ksi
MPa
ksi
L
1240 1170 1105 1035 1170 1170
180 170 160 150 170 170
1135 1105 1035 965 1105 1105
165 160 150 140 160 160
8 8 8 8
1105
160
1035
150
6
Nole: Specimenswereheattreared.(a) Upsetforged10 25 mm (l in.) maximumusing3 to 1ratio. (b) Reforgedto22 mm (0.875in.)square
T
6 6 8
Reduclionof
area, % L
20 20 20 20
T
12 10 15
20
8 4
15
12
Alpha-Beta Alloys I 543 Ti-7AI-4Mo: Equivalentspecifications Specification
Designation
UNS R56740 USA AMS4970E MILF-83142A Comp9 MILT-9047G TI-7A14Mo
Descriplion
AI
Fe
C
H
Mo
7 Frg Bar Wrr BilSTA
FrgHf BarBiiSTAAnn
845°C (1555 oF) I h. WQ. 480°C (900 oF) 16h.AC
870°C (1600 oF) I h, WQ. 480°C (900 oF) 16h.AC
0
OT
Other barn
0.05 0.05 0.05
0.2 0.2 0.2
0.4 0.4 0.4
Y 0.005; balTI Y 0.005; balTI Y 0.005; balTI
4
6.5-7.3 6.5-7.3 6.5-7.3
0.1 0.1 0.1
0.3 0.3 0.3
Ti-7AI-4Mo: Vickershardness Heat treatment
N
0.013 0.013 0.013
3.5-4.5 3.5-4.5 3.5-4.5
Ti-7AI-4Mo: Forgingprocess temperatures Ultimate tensile strength MPa ksI
1148 1147 1138 1135 1128 1139 1146 1168 1196 1165 1168 1148 1145 1150 1153 1174 1198 1248
166.5 166.4 165.1 164.7 163.3 165.2 166.3 169.5 173.5 169.0 169.5 166.6 166.1 166.8 167.2 170.3 173.8 181.0
Metallemperature
°C
Process Hardness, HV
400 360 388 376 373 365 349 366 386 348 347 355 348 348 356 360 367 364
Note: Measurements were made from consecutive 9.5 rnm (0.375 in.) locations on a standard Jominybar
Conventionalforging Supratransusforging
900-985
1650-1805
(a)
(a)
(a) Bela forgingcan be performed in earlyforging operationsifit is followedby substantialsubtransus working
Ti-7AI-4Mo: Heat treatment conditions Heat trealment
-c
Thmperalure OF
TIme,
Cooting
h
method
480-705 705-790 790
900-1300 1300-1455 1455
1-8 1-8 I
Air or slow cool Air cool Furnacecool to 565°C (1050 oF), then air cool
Solutiontreatmentrange 870-980 Recommendedsolutiontreatment 930-955 Aging range (min to max) 510-620 Typicalage 565
1600-1795 1700-1750 950-1150 1050
0.5 to 1.5 I Upl024 4-8
WQ WQ
Stressrelief Annealingrange Recommendedanneal
AC AC
TIMETAL® 625 Ti-6AI-1.7Fe-O.1 Si Common Name. 62S
Characteristics
UNS Number. Unassigned
Phases and Structures. The microstructural response of 62S to heat treatment is quite similar to that of Ti-6AI-4V. The transformed p microstructure is typically a colony structure after air cooling, but can be Widmanstiitten for more rapid cooling. Alpha-beta processing results in a structure consisting of primary ex with transformed 11 The transformed p structure varies with the cooling rate
Chemical Composition. In a study of the effect of iron and oxygen contents on the properties of this alloy, the following conclusions were made: • On average, an increase of about 0.07 wt% oxygen is equivalent to (or provides) about a 60 MPa increase in strength (i.e., about 8.5 MPa per 0.01 wt% oxygen) • On average, a 1 wt% change in iron content resulted in only about a 40 MPa increase in strength • For all heat treated conditions, the combination of high iron (2.4%) and high oxygen (0.25%) resulted in unacceptable post-creep ductility • Although annealing treatment had only a minor effect on creep properties (700°C anneal was worse than 790°C), the solution treated and aged condition provided substantially better properties than both an. nealed conditions • Post-creep ductility was maximized by the 790°C (1455 "F) anneal, low oxygen, and in general low iron. See Table for typical composition range
Product Forms. Ingot is available in 710,815, or 865 rom (28 to 34 in.) diameters in masses ranging from 3180 through 6365 kg (7000 through 14000 lb). Bloom is a semifmished form forged from above the p transus. Forging billet and bar are available as rounds, squares, or rectangles. Sheet and plate are also available. Plate is available in thickness from 4.8 to 102 rom (0.2 to 4 in.) in widths up to 3.05 m (10 ft) and lengths up to 10.67 m (35 ft). The distinction between plate and sheet is made at 4.8 rom (0.19 in.). The standard sheet thickness minimum is 0.41 rom (0.016 in.). Sheet widths are available up to 1220 mm (48 in.). Cut lengths beyond 4880 mm (192 in.) are not standard. Finish grinding on both sides is standard procedure. 62S is typically processed to plate or billet either in the p or ex-p temperature fields. Beta processing is used to improve yield and reduce the cost of processing in cases where the p structure is acceptable such as industrial
544/ Heat Treater's Guide: Nonferrous Alloys applications (in which the corrosion resistance and low density are the primary reasons for use) and automotive applications (in which improved creep strength may be used). Alpha-beta processing is used for applications such as armor for improved ballistic response Applications. Because iron is used as a stabilizer in lieu of more expensive elements, alloy 62S has a lower formulation cost than most titanium alloys, yet properties and processing characteristics are equivalent to or better than those of Ti-6AI-4V. The combination of reasonable cost and excellent mechanical properties makes 62S a practical substitute for other engineering materials in numerous industrial applications that require low weight and high corrosion resistance. The microstructural response of 62S to heat treatment is quite similar to that of Ti-6AI-4Y. The alloy has a relatively high modulus-to-density ratio.
625: General corrosion rates for
The alloy has industrial, automotive, and defense applications General Corrosion Properties. See Table listing general corrosion rates for alpha-beta processed sheet Mechanical Properties. In both the beta- and alpha-beta processed conditions, tensile properties are comparable to those of Ti-6AI-4V. Creep properties and Larson-Miller plots are also expected to be essentially the same as similarly processed Ti-6Al-4Y. See Table for minimum tensile properties of 62S vs. Ti-6AI-4V Fabrication Properties. Bulk working, forming, machining, and welding properties are similar to those of Ti-6AI-4V
Recommended Heat Treating Practice See Table for typical treatments: stress relief, mill anneal, recrystallization anneal, and aging
a-p processed sheet Conuslon rate, mm/year
Solutionfcondltlon
0.25%HCI,boiling 0.5%HCI,boiling 1.0%HCI,boiling 1.0%HCI,65°C (145oF) 3.0%HCI,65°C (145oF) 5.0%HCI,65°C (145oF) Seawater. pH 1.5,boiling Seawater. pH3.0,boiling Seawater. pH3.5.boiling 50 vol%acetic acid,50vol%formic acid.boiling 10vol%aceticacid,10vol%formic acid.boiling
1.19 2.3475 8.35 1.15 4.675 11.45 5.45 0.00375 0.000 1.775 3.625
625: Typical composition range
Minimum Maximum Nominal
AI
Fe
5.5 6.5 6.0
1.3 2.0 1.65
Composltlon, WI% Oz SI
0,07 0.13 0.10
0.15 O.W
0.18
625: Typical heat treatments 'Iemperature
625: Minimum tensile properties 'Thnsile yield
Alloy
Ultimate tensile st",ngth MPa ksi
MPa
ksI
Elongation, %
62S TI-6AI-4V
930 895
895 825
130 120
10 10
135 130
OF
Duratlon,h
CooHng method
Stressmlief(a) 480-650 700-790 Millanneal Recrystallization anneal 970
900-1200 1290-1455 1775
Ito 4 2 1
Solution treatment Age
Pr-llO°F 1000
1 8
Aircool Aircool furnace coolto 760°C (1400 oF), hold2 h, fanaircool Waterquench Aircool
'Ireatment strength
Note: Aonealed plateand forgings to 75 rom(3 in.) thick.62S and11-6AI-4V a-p processed plus annealedat700 to790 °C (1290to 1455oF) for2 h, air cooled
·C
Pr-60°C 540
(a)StressreliefsameasTI-6Al-4V
Ti-4.5AI-3V-2Mo-2Fe Common Name. SP-700 UNS Number. Unassigned Chemical Composition. See Table for composition requirements
Characteristics Beta Transus. 900 ± 5°C (1650 ± 9 OF) Product Forms. SP-700 is available in all mill product forms (plate, sheet, round bar, etc.), as well as in cast and powder metallurgy (P/M) forms Applications. SP-700 is a ~-rich a-~ titanium alloy designed to offer superplastic formability properties superior to those of Ti-6AI-4V. The low flow stress of the alloy, together with its fine microstructure, results in excellent superplastic formability at a temperature level of 700°C (1290 OF), which provides the origin of the name SP-700.
The fine microstructure results in an excellent combination of mechanical properties. The alloy exhibits excellent heat treatability, cold formability, and hot forgeability. SP-700 is specified in either the annealed or the solution-treated and aged condition. The alloy consists of a very fine microstructure in all heat treatment conditions-for example, the primary a grains are typically smaller than 3 11m in the recrystallization armealed condition. It can be hardened to 450 HV or higher by solution treatment in the a + ~ region followed by short-time aging. SP-700 is superplastically formed into such components as aerospace parts, metal wood golf club heads, and metal balloons. Other uses include working tools, automobile parts, wrist watch casings, and mountain-climbing equipment
Alpha-Beta Alloys I 545 Annealing. Mill annealing requires 0.5 to 2 h at 650 to 750°C (1200 to
Corrosion Properties General Corrosion. The corrosion resistance of SP-700 depends on the formation of a protective oxide layer, such as commercially pure titanium. SP-700 resists corrosion under a salt environment and has slightly higher corrosion resistance in hot or concentrated solutions of reducing acids such as hydrochloric and sulfuric acid than pure titanium and Ti-6AI-4V. Corrosion resistance in acid solutions depends on concentration and temperature
1380 "F) followed by furnace or air cooling. Recrystallization annealing (see Table) provides maximum cold working capability. The highest volume fraction of ~ phase, 40%, was retained for the annealing at 800°C (1470 OF)
Mechanical Properties
Solution Heat Treating. Requires 0.5 to 2 h at temperature range of 800 to 850°C (1470 to 1560 "F), followed either by water quenching to obtain very high strength or by air cooling to obtain high strength with good ductility
Hardness. Mill-annealed SP-700 has a hardness of 300 to 330 HV
Aging. Requires 1 to 6 h at 450 to 600 °C (840 to 1110 "F), followed by
Recrystallization-annealed SP-700 has a hardness of 280 to 320 HV. Solution treated and aged SP-700 offers a wide range of hardness, from 350 to 510 HV, depending on solution treating and aging conditions.
air cooling (see Figures). A relatively short aging period is enough to achieve an excellent combination of strength and ductility (see Figure)
See Table for typical tensile properties of sheet
Fabrication Properties Forgeability. SP-7OO exhibits much higher resistance to hot deformation cracking than Ti-6AI-4V. See Figure for effect of temperature on flow stress; and Figure comparing forgeability with that of Ti-6AI-4V
Cold Formability. SP-700 has much better cold formability in comparison with Ti-6AI-4V
Superplastic Formability. SP-700 shows excellent formability at 775 °C (1425 oF), more than 100°C (180 "F) lower than the Ti-6AI-4V forming temperature See Table comparing cold formability vs. that ofTi-6AI-4V; and Figure (a) and (b) comparing superplastic fonnability with that of Ti-6AI-4V
Weldability. The alloy can be fusion and spot welded
Recommended Heat Treating Practice SP-700 is specified either in the annealed condition or in the fully heattreated condition
Hardenability. SP-700 has better hardenability than Ti-6AI-4v' SP-700 is also less sensitive to section size on quenching. The greater stability of the ~ phase of SP-700 compared to Ti-6AI-4V provides greater flexibility during heat treatment. SP-700 is relatively insensitive to quench delays of up to 30 s. It is also less sensitive than Ti-6AI-4V with regard to cooling rate down to about 1 °C/s (2 °F/s) and relatively insensitive to cooling rate in the range of about 7 to 150 °C/s (13 to 270 °F/s). See Tables for: • • • •
Minimums of annealed sheet Comparison of annealed tensile properties Properties of heat treated plate Recommended heat treatments
See Figures for: • • • • • •
Effect of aging temperature on hardness and tensile properties (a), (b), (c) Effect of aging time on tensile properties (a), (b) Aging response Effect of delay time of quenching on strength Effect of cooling rate on strength Effect of quenched section size on strength
SP-700: Cold formability versus Ti-6AI-4V Alloy
SP-700: Comparison of annealed tensile properties among product forms 0.2 ~ Yield strength
'Thn5IIe streogth
Elongollon,
Product ronn
MPa
IIsI
MPa
ksI
~
Plate Sheet Bar
990 949 936
144 138 136
1028 1025 1007
149 148 146
16.8 22.8 18.4
Mill-annealed material.Tensiletestingwasperformed on 6.25 nun(0.25in.) diamroundspecimens with a 25 nun (1 in.) gagelengthfor a 15 nun (0.6in.) thickplateand a 22 nun (0.9in.)bar,and on rectangularspecimenswitha 6 nun (0.24in.) widthand a 25 nun (l in.) gagelengthfor a 3.8 nun (0.15in.)thicksheet
SP-7oo Ti-6Al-4V
Element Aluminum Vanadium Molybdenum Iron
Oxygen Carbon
Nitrogen Hydrogen yttrium
4.0-5.0 2.5-3.5 1.8-2.2 1.7-2.3 0.15max 0.08max 0.05max 0,0\ max 0.005max
Other Each Total
Titanium
0.10max 0.40max bal
Coldrolling reduction limit, ~
L T L,T
2.1 2.1 4
69 58 20
SP-700: Properties of heat-treated 15 mm (0.6 in.) plate 0.2~ YIeld
SP-7OO Wt~
Bend factor(RIl)
(a) L, longitudinal; T, transverse. SP-7oowas recrystallization annealed; Ti-6AI-4V was mill annealed.Bendfactorsweredetermined bybendingtestson specimens 20 nun (0.8in.)wide, 140nun (5.5 in.) long,and 4 nun (0.16in.) thick.Maximumreductionlimitswereobtainedby cold rolling tests
Alloy
SP-700: Composition requirements
Dire
Heat treatment Mill annealing
(720gC/1 WAC) Recrystallization annealing (800 -oi WAC) Sf (WQ) andaged (850°C/I hlWQ + 560°C/6WAC) Sf (AC)andaged (850°C/I WAC + 510°C/6WAC) Ti-6AI-4V Mill annealing (720gC/1 WAC) SfA(955-cn hlWQ + 538gc/6 WAC)
streogth lis! MPa
'!ensUe streogth IIsI MPa
Reduction Elongation,
of area,
~
~
972
141
1023
148
19.0
61.9
917
133
966
140
20.8
61.6
1240
180
1371
200
11.6
28.0
1114
162
1213
176
14.4
39.6
945
137
1003
145
19.6
38.0
1129
164
1205
175
10.5
31.4
Tensiletestingwas performed on 6.25 nun (0.25 in.) diamround specimens with a 25 nun (1 in.) gagelength
546/ Heat Treater's Guide: Nonferrous Alloys
SP-700: Superplastic formability, compared with Ti-6AI-4V. Data for Ti-6AI-4V are not necessarily representative, as elongations up to 2000% have been reported for this material. 13.5 mm (0.53 in.) diam mill-annealed bar. Tension testing was performed on 5 mm (0.2 in.) diam round specimens with a 6 mm (0.24 in.) gage length
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SP-700: Effect of temperature on flow stress. 3 mm (0.12 in.) thick mill-annealed sheet. High-temperature tensile testing was performed on 5 mm (0.2 in.) wide rectangular specimens with a 5 mm (0.2 in.) gage length
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SP-700: Forgeability, compared with Ti-6AI-4V. Hot compression testing was performed on specimens 6 mm (0.24 in.) in diameter and 10 mm (0.4 ln.) long with a circumferential notch. Open circles denote samples that did not exhibit cracking at 70% height reduction. Closed circles denote samples that showed cracking
102
700 800 Temperature, °c
600 Temperature,
700
800 Temperature,
850
°c
800
°c SP-700: Typical tensile properties of sheet Thickness
Minimums of annealed SP-700 sheet: Ultimatetensilestrength Tensileyieldstrength Elongationin 0.50-2.00nun (0.02-0.078in.) Elongationin 2.01-5.00nun (0.079·0.2in.)
960MPa(l40ksi) 900 MPa (130 ksi) 8% 10%
SP-700: Recommended heat treatments Thmpemture 'ftealmenl Mill anneal Recrystallizationanneal Solutiontreatment Aging
Dumtion,
Cooling
"C
OF
b
method
650-750 750-850 800-850 450-600
1200-1380 1380-1560 1470-1560 840-1110
0.5·2 0.5-2 0.5-2 1-6
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mm
in.
Dlrectlon(a)
0.8
0.03
2.0
0.08
3.0
0.12
3.8
0.15
L T L T L T L T
0.2% Yield strength MPa ksl 1023 1023 953 924 910 1009 949 929
148 148 138 134 132 146 137 135
'IensUestrengtb MPa ksi 1073 1073 1014 996 1020 1042 1025 1015
156 156 147 144 148 151 149 147
Elongation, %
lOA 10.2 13.2 15.0 18.5 19.7 22.8 21.0
(a)L, longitudinal;T,lransverse. Mill-annealedsheet. Tensiletestingwas performedon rectangular specimenswith a 6 nun (0.24 in.) width and a 25 nun (1 in.) gage length
Alpha-Beta Alloys J 547
SP-700: Effect of aging time on tensile properties. A 15 mm (0.6 in.) thick plate was solution treated at 850°C (1560 OF) for 1 h, followed by either water quenching or air cooling. Aging was done at 510°C (950 OF) for 1 to 6 h, followed by air cooling .
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548/ Heat Treater's Guide: Nonferrous Alloys
SP-700:Effectof delaytime of quenching on strength. Solution treatmentwas done on 12.5mm (0.5 in.) thick plates,followed by a quench delay rangingfrom 2 to 30 s before water quenching. SP-700: Solution treated at 850°C (1560 OF) for 1 h, followed by water quenching; aged at 510°C (950 OF) for 6 h, followed by air cooling.li-6AI-4V: Solutiontreated at 950°C (1740 OF) for 1 h. followed by water quenching; aged at 540 °C (1000 OF) for 6 h, followed by air cooling LIVE GRAPH
SP-700: Effect of quenched section size on strength. Solution treatment was done on plates with thicknesses ranging from 12.5to 80 mm (0.5t03 in.) forSP-700 and from 12.5t032 mm (0.5 to 1.3 in.) for Ti-6AI-4V. SP-700: Solutiontreated at 850°C (1560 OF) for 1 h, followed by water quenching; aged at 510°C (950 OF) for 6 h, followed by air cooling. Ti-6AI-4V: Solution treated at 950 °C (1740OF) for 1 h, followed by water quenching;aged at 540°C (1000 OF) for 6 h, followed by air cooling
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Alpha-Bela Alloys /549
IMI367 Ti-6AI-7Nb Chemical Composition. See Table for typical composition range
Recommended Heat Treating Practice
Characteristics
Heat treatment is a 1 h anneal at 700°C (1290 "F), followed by air cooling
Beta Transus. 1010 ± 15°C (1850 ± 30 OF) Product Forms. The alloy is available as 8 to 100 mm (0.30 to 4 in.) rod
IM1367: Typical composition range (wt%) and density
and as rectangular (25 by 75 mm, or 1 by 3 in.) bar
Applications. IMI 367 is a high strength alloy developed for femoral components in hip prostheses Fabrication Properties. Hot forging procedures and mechanical working practices are the same as those for standard interstitial Ti-6AI-4V
Minimum Maximum Nominal
AI
Nb
1ll
Fe
C
0,
N,
H,
5.50 6.50 6.0
6.50 7.50 7.0
0.50
0.25
0.08
0.20
0.05
0.009
n
bal
3
DensityoflMI 367is 4.52g/cm (0.1631b/in.3)
IMISSG Ti-4AI-4Mo-2Sn-O.5Si Trade Names. IMI 550 (Previously Hylite 50) Chemical Composition. See Table for typical composition ranges
Characteristics Product ConditionlMicrostructure. Normal usage is in the solution treated and aged (STA) condition, which has a microstructure of primary alpha, transformed beta, and silicide
Product Forms. The alloy is available as bar, billet, plate, sheet, and castings
Applications. Major usage is in the aerospace industry, as airframe and aeroengine components. Typical components are flap-tracks and engine compressor discs Mechanical Properties. Heat treated hardness typically is 360 HV (50 kg). This medium strength alloy has a typical ultimate tensile strength of lIOO MPa (159 ksi), and temperature capability up to about 400°C (750 OF).
Extrusion. IMI 550 can be alpha beta or beta extruded. Property levels in the alpha beta extruded condition are similar to those of the forged or rolled forms. Beta extruded materials exhibit lower ductility, but better fracture toughness than the equivalent alpha beta extruded product Forging. IMI 550 is readily forgeable by conventional hammer, press, or isothermal forging and is one of the easier titanium alloys to forge. Typical forging temperature is 900°C (1650 "F) Flow stress of IMI 550 at its typical forging temperature is slightly stiffer than that of Ti-6AI-4V. The flow stress of IMI 550 increases slightly more rapidly than that of Ti-6AI-4V as temperature falls See Table for typical mechanical properties of extrusions
Forming. IMI 550 can, in general, only be formed hot, and it can be treated in the same way as other high-strength alpha-beta alloys such as Ti-6AI-4Y. Plate and sheet can be produced by conventional rolling techniques. IMI 550 is also very amenable to superplastic forming; its fine grain size giving good flow characteristics and high m values (about 0.8). See Table for tensile properties of superplastically formed sheet
See Figure showing creep properties at 100 and 300 °C. Useful creep performance ranges up to about 400°C (750 OF). Plastic strain is less than 0.1 % total in 100 h at 465 MPa (67 ksi)
welding techniques. Electron beam welded compressor discs are in service in military aeroengines
Fabrication Properties
Recommended Heat Treating Practice
Casting. IMI 550 can be cast using the normal techniques developed for titanium alloys. It has similar flow and "castability" performance to that of Ti-6AI-4V (IMI318).
The alloy derives its properties from solid solution strengthening and age hardening. Because of the significant level of beta stabilizer content, IMI 550 exhibits a useful aging response in sections up to 150 mm (6 in.) thick.
Mechanical property levels of cast IMI 550 are generally equivalent, or superior, to the wrought product and to cast Ti-6Al-4V. Tensile ductility and low-cycle fatigue performance are inferior in both instances
See Tables showing recommended heat treatments (alpha-beta solution treating, aging, and stress relief), and tensile properties after various heat treatments
Welding. IMI 550 is weldable using controJled electron beam or laser
550 I Heat Treater's Guide: Nonferrous Alloys
IMI 550: Typical mechanical properties of extrusions Testpiece(a) direction
Section shape and extrusion type(a) Extrudedin a+ Pfield
L T L T
Extrudedin Pfield
0.1%Proof stress MPa ksl
Thnslle MPa
957 1016 998 1009
1107 1127 1183 1236
Reductlon
Fracture
in area,
ksi
Elongation, %
%
~
MPa'liil
kSi'Iii:
161 163 172 179
14 14.5 12.5 10.5
40 40
53.6T-L 46.3L-T 62.9T-L 64.7L-T
48.7 42.0 57.1 58.8
strength
139 147 145 146
24.5 16
(a) Testpieces taken from heat treated web sections
IMI 550: Tensile properties of superplastically formed sheet
Condition SPF SPF SPF SPF+ STA
Approximate SPFstrain % O(a} 100 100 100
0.1%Yield stress MPa ksi 908 937 965 1126
Thosile strength MPa ksi
132 136 140 163
1097 1109 1123 1338
IMI-550: Typical composition range (wt%) and density Elongation % 12 7 5 7
159 161 163 194
Minimum Maximum Nominal
Solution treated900 °ClO.5 hlAC Fully aged, 900 °C/O.5 hlAC + 500 °C/24 hlAC Stress-relieved650 0C/2hlAC
930 135 1070 155 1020 148
Fe
Mo
Si
Oz+2N,
Ih
3.0 5.0 4
1.5 2.5 2
0.2
3.0 5.0 4
0.3 0.7 0.5
0.27
0.0125
IM1550: Creep properties at 100 and 300°C. Heattreated bar 9 0 0 , - - - - - - - - - - - - - - - -....130
IMI 550: Tensile properties after various heat treatments
'Ireatment
So
Density ofIMI 550 is 4.60 g/cm3 (O.166lb/in.3)
(a) 'Iestpiecestaken from the flange were not deformed in the superplastic formed (SPF) condition but were exposed to the SPF heat cycle. STA,solution treated and aged. Material/Iest conditions: 2 mm (0.08 in.) sheet, annealed prior to fanning, strain rate 2 x lO-4/s
0.2%Proof stress MPa ksi
AI
(in SO mm),
LIVE GRAPH Click here to view
Thnsile Elongation Reduction strength (lnSD) lnarea, MPa ksi % % 1080 157 1200 174 1130 164
12 14 12
40
42 42
120 CU
800
a. ~
0.05% -----..:::::-
iii
~
en
700
IMI 550: Recommended heat treatments
~
100°C
======:=---8:a~~ - ---
110 iii Ul
e en
_0.2%
100 300°C
Temperature
'Ireatmenl Alpha-betasolution treatment Aging Stressrelief
Duration
CooUng method
90
600L-~~~~"_____'"~...............u-___'.........~~...
900 500 650
1650 930 1200
1h 24h 2h
Air cool Air cool Air cool
10
IMI551 Ti-4AI-4Mo-4Sn-O.5Si Chemical Composition. See Tables for typical composition range, and for British standard specifications
Characteristics Applications. IMI Titanium 551 belongs to the same alloy group as IMI 550; however, the higher alloying content of IMI 551 increases strength at room temperature, while preserving good forging characteristics. IMI551 is one of the strongest of the commercially available titanium alloys, with room-temperature strengths ranging from 1250 to 1400 MPa (181 to 203 ksi), and useful creep properties up to 400 °C (750 OF). The alloy is primarily intended for airframe structural forgings and machined parts such as undercarriage components, mounting brackets, and
pump casings where strength is required at low weight; and for gas-turbine engine components. This alloy is also suitable for general engineering and chemical applications such as steam-turbine blades, axial and radial compressor parts, connecting rods, and other high-speed rotating and reciprocating components Mechanical Properties. See Table for typical tensile properties for various section sizes
Fabrication Properties Forging. IMI 551 has a higher beta transus temperature than most other titanium alloys. Beta transus is 1050 ± 15°C (1920 ± 30 "F), This permits a fairly high forging temperature to be used so that, despite the high
Alpha-Seta Alloys I 551 room-temperature strength of the alloy, it is only marginally more difficult to forge than Ti-6AI-4Y. To obtain good properties in a finished component, the alloy should be given at least a 4: 1 forging reduction in the alpha + beta phase field. So as to ensure that no part of the forging exceeds the beta transus temperature as a result of internal work, it is recommended that the initial forging preheat temperature should not exceed 950°C (1740 OF). The preheat temperature should be reduced to 930 °C (1700 "F) for subsequent forging operations to obtain the optimum combination of strength and ductility
can be developed on aging, but only at the expense of ductility and creep strength. It is better to slow down the cooling rate of thin sections (for example, in a box filled with refractory material) to avoid the undesirable effects of an excessive cooling rate (see Table). Various solution-treatment temperatures have been suggested for IMI 551, but 900 °C (1650 "F) followed by air cooling has been found to give the best strength, while avoiding the low ductility brought about by oil or water quenching. See Table for typical tensile properties of small rod after different heat treatments
Welding. Generally, alloy is not weldable
Recommended Heat Treating Practice
IMI Titanium 551: British Standard Specifications
Recommended practice consists of solution treatment at 900 °C (1650 "F) for 1 h per 25 mm of section thickness (1 h/in.), followed by air cooling and aging for 24 h at 500°C (930 OF) and again air cooling.
limiting nillng ••dlon
When small-diameter sections of 16 mm (0.7 in.) or less are air cooled, or when thicker sections are water or oil quenched, higher tensile strengths
Up to 25 nun (I in.) Over25 and up to 75 mmtt toa in.)
Barfor IIllIChining
Forging IIIock
Forgings
TA38 TA40
TA39 TA41
TA42
IMI-551: Typical tensile properties for various section sizes TeoslIe streogth
0.2% yield stress
Product
Sample
MPa
ksi
MPa
ksi
175nun (7 in.)diam billet 100to 125nun(4t05 in.)squarebillet 75 nun (3 in.), squarebarheat treated
Transverse, 3:1 upset, heat treated Transverse, 3:1upset.heattreated Longitudinal. surface Longitudinal, center Longitudinal, center Center
1140 1200 1210 1150 1140 1340
165 174 175 167 165 194
1300 1310 1320 1260 1300 1480
188.5 190 191 183 189 215
25 to 50 nun (1 to 2 in.)rod 16nun (0.625in.)rod
Typical tensile properties after various heat treatments of small rod, 16 mm diameter (0.625 in.)
'Ireatment
Tensile
stress
strength MPa ksi
MPa
1h9OO°C.WQ,24h5OO°C,AC 1390 1h9OO°C,AC, 24 h 500°C.AC 1310 1h 900 DC. coolin vermiculite. 24 h 1240 500 °C.AC
ksl
200 190 180
1650 1450 1410
240 210 205
Elongation Reduction on5D In area
ReductIon in_ %
9 10 13 16 12 10
25 30 40 37 40 28
IM1551: Typical composition range (wt%) and density AI
0.2% yield
on5D %
Elongation
Fe
c
0.3 0.7 0.5
0.20
0.05 0.20
%
%
Minimum Maximum Nominal
3 10 13
9 28 47
(a)0.15 wt% maximumofH2 in forgings.Typical densityis 4.62 rlcm J (O.1671bf/in.3)
3.0 5.0 4.0
3.0 5.0 4.0
SI
3.0 5.0 4.0
0.25
0.05 0.125(a)
Ti·6·22·22S Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si UNS Number. Unassigned
Characteristics
Chemical Composition. The only specifications for Ti-6-22-22S to date are those written by LockheedIBoeing/General Dynamics for the ATF fighter. Composition limits are established (except Si content may be reduced). See Table for minimum and maximum compositions
Phases and Structures. Triplex heat treatment results in a coarse lamellar a structure in a transformed 13 matrix. Cooling rates from the solution treatments must be controlled within a given window to provide desired strengths. The retained 13 contains a fine acicular a precipitate due to aging. Very fine, submicron-size silicides have been observed in this alloy.
Effects of Impurities and Alloying. Exceeding impurity limits may decrease ductility and fracture toughness below required minimums due to the associated increase in strength. As with other a-13 titanium alloys, excessive aluminum, oxygen, and nitrogen can reduce ductility and fracture toughness. High amounts of the 13 stabilizers, chromium and molybdenum, may result in higher strength than desired
Sheet can be used in the annealed or solution treated and aged condition. An air cool from the solution treatment temperature provides adequate heat treatment response. The annealed condition consists basically of equiaxed a with intergranular 13. Material in the solution treated and aged condition is very similar to that of Ti-6AI-4V, with equiaxed <X in a 13 matrix. With solution treatments below about 850°C (1560 "F), 13 phase at temperature
552/ Heat Treater's Guide: Nonferrous Alloys will be retained upon cooling (for sheet gages with an air cool), which provides a strength minimum in the solution treated condition. Solution treating at temperatures above this results in increased amounts of martensite formation as the temperature is increased and higher strengths. See Figure for mill annealed microstructure Product Forms. Ti-6-22-22S has been produced in standard wrought product forms such as sheet, plate, bar, and forgings Applications. Ti-6-22-22S was conceived to provide high strength in heavy sections with good fracture toughness and to retain that strength up to moderate temperatures through the addition of silicon. A strong effort is underway to develop thermomechanical processing procedures to optimize strength, toughness, and crack growth rate properties in sheet, plate, and forged forms. Ti-6-22-22S can be used in the annealed and heat treated conditions; solution treatment and aging can provide significant strengthening. The main emphasis at present, except for sheet, is on a triplex heat treatment involving a ~ solution treatment with a controlled cooling rate followed by an a-~ solution treatment followed by aging to maximize damage-tolerant properties. Sheet should be used in the a-~ processed condition. There are no production applications at this time, but it is bill-of-material for the aft fuselage of the F-22 ATF fighter. Primary interest lies in improved damage tolerance properties with respect to strength in relation to Ti-6A1-4V
Corrosion Properties Stress Corrosion Cracking. Boeing has reported the stress-corrosion threshold for this alloy to be about 55 MPa-JiD (50 ksi'J'ifi.) in an aqueous 3.5% NaCI solution Tensile Properties. Because Ti-6-22-22S is an age-hardenable alloy, a range of tensile properties is attainable. The alloy can be heat treated in sections up to 75 to 100 mm (3 to 4 in.) thick. Strength is not very sensitive to aging temperature over a fairly wide temperature range.
Final thermal treatments. Forgings treatments include two- or threestep practices of single or two-step (duplex) solution treatments followed by controlled cooling and aging (stabilizing).. Subtransus thermal treatments, used in combination with conventional and/or ~ forging processes, are done at 30°C (50 OF) below the ~ transus temperature, followed by air or fan cooling. Aging (stabilization) is at 480 to 540°C (900 to 1000 "F), See Table for forging TMP conditions and mechanical properties
Other Fabrication Methods Rolling. The rolling schedule is very much like that for Ti-6AI-4V. Sheet is rolled below the ~ transus and has a very small grain size Forming. Formability is similar to that of Ti-6AI-4V with slightly higher pressure required for hot forming due to higher strength of Ti-6-22-22S. Superplastic forming properties are similar to those of Ti-6-AI-4V Machining. Characteristics are similar to those of Ti-6AI-4V; and preliminary investigations indicate that Ti-6-22-22S may machine slightly easier than Ti-6AI-4Y. See Table. Effect of post superplastic forming-aging on sheet
Recommended Heat Treating Practice See Table for typical heat treatments (mill annealing, sheet solution treatment (first and second stages), beta processed plate solution treating, and aging. See Figures for: • Strength and ductility vs. solution treating temperature • Effect of solution temperature on tensile properties • Yield strength vs. aging temperature • Effect of aging temperature on tensile properties See additional Tables for: • Effect of temperature on tensile, compressive, and shear properties • Mechanical properties after aging
See Table for typical mechanical properties of alpha-beta processes STA products
See micros (a), (b), (c), (d) for effect of solution treating and cooling
Fabrication Properties
Ti-6-22-22S: Typical mechanical properties of p-processed STA products
Forging. The alloy can be fabricated into all forging product types, although closed die and precision forgings predominate. It is commercially fabricated on all types of forging equipment at the process temperatures indicated (see Table). Ti-6-22-22S: Recommended forging process temperatures Process
Thmpemture
parameter
865-930 980-1015
'IOnsUe yield
strength
Product
MPa
!<si
strength MPa ksi
50mm (2in.)plate 100mm(4in.)plate 150 mm(6 in.)plate
1138 1103 1076
165 160 156
1020 979 958
Elongation, %
Reduction orarea, %
10 10 10
17 15 15
148 142 139
Il-r- 28°C (50·F) for I h. Ac/54O·C (IOOO·F) age,8 h.AC
°C
Metaltemperature Conventionalforging Beta forging(a) Die temperatures
Ultimatetensile
1590-1700 1795-1860
Ti-6-22-22S: Typical heat treatments Thmpemture
(a) Betatransus,960°C (1760oF)
'fieatment
Ti-6-22-22S is a reasonably forgeable alloy with comparable unit pressures (flow stresses). forgeability, and crack sensitivity to Ti-6AI-4V. Final microstructure is developed by thermomechanical processing---combinations of conventional (subtransus) and/or ~ (supratransus) forging followed by subtransus and/orsupratransus thermal treatments
Mill anneal Sheetsolutiontreatment PlateJbillet solutiontreatment First stage (supratransus) Second stage (subtransus) Betaprocessed platesolutiontreat Age(allproductforms)
°C
OF
Thne/Cooling
730 1l-r-28
1345 1l-r-50
30minlAC
1l-r+28 1l-r-28 1l-r-28 540
1l-r+50 1l-r-50 1l-r-50 1000
2h1AC
IhlAC IhlAC IhlAC 8h1AC
Ti-6-22-22S: Composition limits Composition. wi %
Minimum Maximum
AI
So
Zr
Mo
Cr
Sl
Fe
0
C
N
B
5.25 6.25
1.75 2.25
1.75 2.25
1.75 2.25
1.75 2.25
0.20 0.27
0.15
0.13
0.04
0.03
125ppm
Alpha·Beta Alloys I 553
Ti·6·22·22S: Effect of solution treating temperature on tensile properties. 1.6 mm (0.062 in.) thick sheet
Ti-6·22·22S: Yield strength vs. aging temperature. 1.2 mm
(0.050in.) sheet heat treatedas indicated Aging temperature, OF 900 1000 1100
BOO 1500
•
1400
'"
:::!E
1200
•
210
~
e!
"
1BO
0
0
.~\ ...
:::!E
i
c:::
0
BOO C> c::: e!
"0
til
>-
Solullon treated at 900°C Solution treated at 925°C . Solution treated at B70 °C
• l!.
160
400
500 600 Aging temperature, °C
20
15 .: 0
~
0
10
600
0
•
400
Ultimate tensile strength Tensile yield strength Elongation
" 0
150
1000
25
l!.
~
170:91
Qj
1100··
'" 1000
D..
tc:::
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~
1200 200 190 -
:; 1200 ..
LIVE GRAPH
Solution temperature, of 1400 1500 1600 1700
1300 1400
~ 1300
>=
...
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•
•
D..
LIVE GRAPH
5
200
700
'" S
iii
0
700
750
BOO B50 900 Solution temperature, °C
950
1000
Ti-6·22·22S: Effect of solution temperature on tensile properties. 1.6 mm (0.063in.) thick sheet heat treatedas indicated
LIVE GRAPH
LIVE GRAPH Click here to view
Solution treating temperature, OF 1500 1550 1600 1650 1700
Click here to view
sonmon (reatlng temperature, OF 1550 1600 1650 1700
1500 15
,
1BO
UTS 11BO
160
9BO\.'""=~=..
/,
~
BBO .. As annealed
As annealed
EI
.: o
~ c:::
1
til
iii 5
....... ····140 e!
/
c::: o
120 7BO 6BOL-
'--
BOO
0'--
~100
B50 900 Solution treating temperature, °C
950
(8)
--' B50 900 Solullon treating temperature, °C
BOO
950
(b)
Ti-6·22·22S: Strength and ductility vs. solution treating temperature. 1.2 mm (0.050 in.) sheet solution treated 30 min, AC,
Ti·6·22·22S: Effect of aging temperature on tensile properties. 1.6 mm (0.062 in.) thick STAsheet, solution treated at 870
no aging
°C (1600 OF) 1500 1500 1400
Solution treallng temperature, OF 1550 1600 1650
900
•
14
0
1700
12 1300
'" 1300
10 .:
:::!E
0
~ 1200 c:::
e!
til
B 1100 1000 900 BOO
'''':::; 1100 D..
~
~
0
~
c::: '"
iii
C> c:::
6
LIVE GRAPH Click here to view B20 B40 B60 BBO 900 920 Solution treallng temperature, °C
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:=:~
900 700 500
().
0
~ • l!.
0
4 940
Ultimate tensile strength Tensile yield strength Elongation
300 450
1200 20
LIVE GRAPH
1500
...-.
D..
Aging temperature, OF 1100 1000
600 500 550 Aging temperature, °C
15
.: 0
10 ~ c
'" 0
iii 5
0 650
554/ Heat Treater's Guide: Nonferrous Alloys
Ti·6·22·22S: Cooling rate/microstructure correlation. 150 mm (6 ln.) p forged billet machined to 100 mm (4 in.) thick with a treatment. Times to half temperature for the various cooling rates were: (a) 100s, (b) 1000 s, (c) 2000 S, and (d) 2880 s
(a) 011 quench, 169 ksl UTS
(c) Slow oven cool, 154 ksl UTS
(b) Fanalrcool.160ksiUTS
(d) ST In vacuum, 140 ksl UTS
+ psolution
Alpha-Beta Alloys I 555
Ti-6-22-22S: Mill annealed microstructure. 1.2 mm (0.050 in.) sheet annealed at 730°C (1345 OF), 15 min, AC
Ti-6-22-22S: Effect of aging temperature on tensile properties. 1.6 mm (0.062 in.) thick STA sheet, solution treated at 925 °C (1695 OF)
LIVE GRAPH
Click here to view
Aging temperature, OF
900
1000
1100
1200 20
250
~
200
·~~~:i~ey::~s~~~~;~9th1
1- :
500
550
~
co
10 ~
Ol
c
~~~
100
15
o
ill 5
600
Aging temperature, °C
Ti·6·22·22S: Effect of superplastlc forming temperature on tensile properties of sheet. As-formed properties at 75% strain
LIVE GRAPH
LIVE GRAPH Click here to view 1400 1200
~
1150
0
~' As annealed
f1100.'
tJi
Temperature, OF
1500
1600
I~
~
160
~
c
tc
o ~ 10
tJi
ill
~
840
880
920
1700
15
J
800
1600
As annealed
170
Ol
c
o
5
150
lO00L-_ _'--_ _'--_ _'--_ _-'--_--' 760
1500
1400 20
1700
~
1050
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Temperature, OF
O'--_ _..L-_ _- ' -_ _- ' -_ _--I.._ _- - - '
960
760
800
840
880
920
960
Ternperature.X;
Temperature.Xl
(a)
(b)
Ti-6-22-22S: Mechanical properties after aging Aging temperature
°C
OF
Direction
Tensileyield strength, MPa (ksi)
Ultimate tensile strength,MPa (ksi)
Elongation, %
425
795
480
900
510
950
540
1000
565
1050
595
1100
620
1150
L ST L ST L ST L ST L ST L ST L ST
1048 (152.0) 980(142.2) 1096 (159.0) 1028 (149.1) 1096 (159.0) 1011 (146.7) 1106 (16004) 1024 (148.6) 1061 (154.0) 1042 (151.1) 1117 (162.0) 1049(152.1) 1113 (161.5) 1030(149.5)
1206 (175.0) 1121 (162.7) 1223 (177.4) 1197 (173.6) 1224(177.6) 1138 (165.1) 1218 (176.7) 1139 (165.3) 1162 (168.6) 1155 (167.5) 1205 (174.8) 1157 (167.8) 1183 (171.6) 1102 (l~9.9)
7.0 6.2 10.0 10.1 8.5 10.1 9.0 8.6 10.0 13.3 8.0 10.9 6.5 6.2
Note: 50 mm (2 in.) thick a.-p rolled plate heat treated as follows:
Reduction of area, %
7.8 10.6 12.3 16.6 9.7 16.5 9.7 13.8 12.7 36.3 9.3 21.5
704
Fracture toughness (K,,) MPaf.ll (ksi~)
88 (80.3)(a) 87 (79.8)(a) 85 (77 A)(a) 83 (76.2)(a) 74 (67.8Xa) 62 (56.3)(a) 49 (45.3)(a)
11.1
P, plus 28°C (50 "F), fan cool, reheat to 40 °C (70 "F) below Ph air cool, + age as indicated for 8 h, air cool. (a) T-Ldirection
556/ Heat Treater's Guide: Nonferrous Alloys Ti·6·22·22S: Forging thermomechanical processing conditions and mechanical properties Preform forging
Finish forging
Heal treatments
a.~
~ finish 28°C (50 oF)above ~ IraIlSUS ~ finish 50°C (90 oF)above ~ transus
~,-22 °C(4O°F),
a.~
~prefonn ~prefonn
ll'~ fmish (25%) a·~fmish(50%) ll'~ finish (50%) a·~fmish(50%)
n-Bpreform a·~prefonn
1 h. FAC+ 540 °C(I000 oF).8h,AC
ThnslJe yield strength
UltlmalelenslJe strength
Elongation,
Redudion ofarea,
MPa(\<sl)
MPa(\<5i)
%
%
1110(161) 1117 (162) 1124(163) 1117 (162) 1110(161) 1096 (159)
11 12 12 12 10 10
21 21 25
993 (144) 1000(145) ~,-22 °C(4O°F),lh.FAC+54O°C(1000°F), 8h.AC 1034(150) ~,-22 °C(4O°F), 1 h. FAC+540°C(lOOO oF),8h,AC 1027 (149) ~,+ 28 °c.(50 oF).0.5 h, FAC + 540 °C (1000 oF).8 h. AC 958 (140) P, + 28 °C (50 "P), 0.5 h., FAC + ~,- 50°C (90 "P), 1 h. AC + 540 972(141) °c.(I000 oF),8 h, AC ~,-22 °C (40 oF), 1 h. FAC + 540 °C(1000 oF),8h.AC
Fracture toug\lne8s
MPa~·ruL)
25
15 17
90.4(82) 87.6(79) 68.0(62) 58.4(53) 75.1 (68) 85.1 (77)
Note: Heal treatment sequence temperature, time. cooling method
Ti·5AI·2.5Fe Trade Name. Tikrutan LT 35
Mechanical Properties
Common Name. DIN 3.7110
Hardness. After undergoing deformation at 850°C (1560 oF), Ti-5Al-
Chemical Composition. See Table for minimum and maximum composition of annealed sheet or bar
2.5Fe has a typical Vickers hardness of 320 to 340 HV.
Characteristics
See Figure for effects of aging on hardness
Fabrication Properties
Phases and Structures. Deformation in the ex + ~ phase field and annealing at 850°C (1560 "F) produces a fine-grained ex + ~ microstructure. Age
Forgeability. Comparable to that of Ti-6AI-4V in the alpha + beta and
hardening is possible.
beta phase
The ex + ~ transus is 950°C (1740 "F) for an alloy composition of 5.15 wt.%AI,2.45 wt.%Fe, 0.14 wt.% O,0.09wt.%N,0.01 wt.%Si, and 0.025 wt.%H.
Formability. Poor at room temperature. Good formability (even superplastic deformation) is achieved in the ex + ~ phase field at 850 to 950°C (1560 to 1740 OF), as well as good formability in the ~ phase field at temperatures above 950°C (1740 oF)
See TTT diagram
Product Forms. Hot rolled strip, sheet, or plate can be manufactured upon request. Hot rolled, extruded, or drawn round bar is available, as well as square and flat bar with a maximum cross-sectional width-to-thickness ratio of 5:1 Applications. This alloy is designed for permanent implants in the human body. Cast implant devices, such as sockets of hip prosthesis, are readily produced
Weldability. Like other titanium alloys, Ti-5AI-2.5Fe can be welded, but preferably by the more sophisticated methods such as gas tungsten-arc and electron beam welding. Precautionary procedures such as preheating, postheating, control of interpass temperature, and control of environmental conditions should be used Machinability. Ti-5AI-2.5Fe is readily machinable, but only under wellcontrolled conditions. Like other titanium alloys, reduced rates of speed, feed, and depth of cut should be used Extrusion. Properties are better than those of Ti-6AI-4V in the alpha + beta and beta phase fields due to lower flow stresses
Ti·5AI·2.5Fe: TTl diagram
Castability. Similar to that of other alloys. Investment casting is possible
LIVE GRAPH
with special molding materials that exhibit a limited reaction with molten material, i.e., graphite artificial resin, thermodynamic stable oxides or oxide binders (fh02, Y203, CaO), and high-melting metals/oxide binders (tungsten and molybdenum). Centrifugal casting is possible with permanent molds of copper, which do not react due to high heat conductivity
Click here to view 1000
1800
900 1600
P
l;'-
~
1400
:::J
:::J
e!.,
e!.,
Q.
.,E
I-
~
r
-
-
-
-
1200
~
{3!.
'TiFe start
600
1000
Powder Metallurgy. A special application: porous implant devices. Pore size (>50 11m) makes it possible to secure implants via tissue growth into the pores. Examples for such devices are heart pacemaker electrodes and dental implants
Recommended Heat Treating Practice Annealing. Temperature is 850°C (1560 oF) Solution Heat Treating. Temperature range is 800 to 920 °C (1470 to
10.
1
10 10 Time, min
2
10
3
10
4
1690 "F), in the ~ phase field, the temperature is 1000 °C (1830 oF), aging is 400 to 700°C (750 to 1290 oF)
Aging. Temperature range is 400 to 700 °C (750 to 1290 oF)
Alpha-Beta Alloys /557
LIVE GRAPH Click here to view
Ti-5AI-2.5Fe: Chemical composition of annealed sheet or bar
Minimum Maximum
AI
Fe
Composition, wi % o H
3.0
2.0 3.0
0.2
5.0
0,015
N
c
0.05
0.08
Ti-5AI-2.5Fe: Effects of aging on hardness. Isothermallyaged after annealing 10 min at 1000 °C (1830 OF), and water quenching
500·C 600 ·C 700 ·C --.._~:::---------
800·C 900 ·C
10 10 2 Time, min
Ti-5AI-5Sn-2Zr-2Mo-O.25Si Common Name. Ti-5522-S UNS Number. R54560 Chemical Composition. For minimum, maximum, and aim compositions, see Table Specifications. Ti-5A1-5Sn-2Zr-2Mo-0.25Si is listed in government specifications MIL-T-9046, MIL-T-9047, and MIL-T-81556 Effects of Impurities and Alloying. Exceeding impurity limits may result in raising yield strength above maximum permitted or in lower elongation or reduction in area below minimum. As for all a-p alloys, excessive aluminum, oxygen, and nitrogen can reduce ductility and fracture toughness. Excessive beta stabilizers (for example, molybdenum or vanadium) affect the stability of the alloy and increase its heat treatability, making it more difficult to control properties
Characteristics Phases and Structures. Annealed Ti-5522-S has a hexagonal closedpacked crystal structure with a small amount of beta phase at room temperature. Microstructures resulting from cooling through the p-transus temperature typically consist of packets of a-platelets, similarly aligned and crystallographic ally oriented, that are separated by films of p-phase. Beta annealing results in a long a-platelet structure while p-working results in a shorter a-platelet structure Beta Transus. The alloy has a beta transus of980 ± 15°C (1800 ± 25 "F) Product Forms. Alloy Ti-5522-S is available in standard wrought product form as a forged billet or bar. In addition, it is produced as a special wrought product in the form of plate and sheet Applications. A semicommercial alloy developed for use in aircraftcomponents subjected to prolonged exposure near 500°C (930 "F), It is a beta-lean a-p alloy with relatively low content of P-stabilizing elements. Ti-5522-S exhibits good tensile, stress rupture, and creep properties at elevated temperature into the 425 to 540°C (795 to 1000 OF) range. It can be welded, formed at room temperature, or at warm forming temperatures of 540 to 700 "C (1000 to 1290 OF) Corrosion/Chemical Properties. The corrosion-resisting characteristics of Ti-5522-S are comparable to unalloyed titanium and to other near-
alpha and a-p titanium alloys. This alloy is unaffected after 1000 h in the standard ASTM salt-spray test
Mechanical Properties. Hardness. Ti-5522-S has a room temperature hardness of 32 to 38 lIRe Mechanical Properties. Minimum room temperature properties (no heat treatment specified) include: tensile strength, 900 MPa (130 ksi); yield strength, 830 MPa (120 ksi); elongation, 10%; reduction in area, 25%. Properties at 535°C (995 "F), minimum values: tensile strength, 689 MPa (100 ksi); yield strength, 517 MPa (75 ksi); elongation, 15%; reduction in area, 35%. See Table for typical tensile properties
Fabrication Properties Forging. Ti-5522-S should be forged at the lowest possible temperature to minimize surface contamination by oxygen. Heat to and start forging at 925 to 955°C (1695 to 1750 OF), finish at 790 to 815 -c (1455 to 1500 oF) Forming. Most forming operations can be done at room temperature, but warm (425 to 700 "C, or 795 to 1290 OF) forming is sometimes employed. Bend radius recommendations: • For t < 1.8 mm «0.070 in.); 4.5 t • For t ~ 1.8 mm (~0.070 in.); 5.0 t
Grinding. In grinding operations, the alloy requires many of the same precautions against surface damage as other titanium alloys Welding. Ti-5522-S can be welded readily by inert-gas shielded arc welding, using it as the filler metal. Oxyacetylene welding and other forms of welding using active gases, electrode coatings, or fluxes are not recommended because the gases tend to embrittle the titanium and make it impossible to produce ductile welds Machining. Like many titanium alloys, Ti-5522-S has a seizing tendency and requires sharp tools, correct tool angles, heavy feeds, slow speeds; rigid tool supports, and adequate coolant
558/ Heat Treater's Guide: Nonferrous Alloys
Recommended Heat Treating Practice The alloy is usually given a full anneal with a reheat. A beta anneal enhances creep resistance and toughness.
The alloy cannot be hardened or strengthened by any thermal treatment. After cold or warm forming, it may need stress relief or a full anneal. See Table for typical heat treatments: stress relief anneal, full anneal, beta anneal
Ti·5522·S: Typical heat treatments Heat Heat treatment
Reheat
Time
Cooting method
2 1 1
Air Air Air
Temperature
Stress-relief anneal Fullannea\ Betaannea\
°C
OF
595-650 955 1015
1100-1200 1750 1860
Condltlon Mill annealed
lIT
315.5 426.6 537.7 975°C (1785 oF) 0.5 h. AC + 595 °C (1100 oF) 2h.AC
lIT
315.5 426.6 537.7
lIT 600
800 1000 lIT 600
800 1000
mlimaletenslle strength MPa
ks!
965 813 745 730 1048 793 780 690
140 118 108
106 152 115 113 100
Time
Cooting method
595 595
1100 1100
2 2
Air Air
Ti·5522·S: Typical composition
Ti·5522·S: Typical tensile properties Tempernlure OF °C
OC
OF
Temperature
Yield
strength MPa ks! 868 586 558 552 965 565 530 503
126 85 81 80 140 82 77 73
Elongation, %
12 18 20 20 13 15 17 19
Reduction in ares, %
35 41 50 50
Min Max Aim
AI
Sn
Zr
Mo
Si
Fe
C
N
0
4.5 5.5 5
4.5 5.5 5
1.75 2.25 2
1.75 2.25 2
0.20 0.30 0.25
0.15
0.04
0.03
0.13
n
bal
Beta and Near-Beta Alloys Ti·11.5Mo·6Zr·4.5Sn Common Name. Beta III UNS Number. R58030 Chemical Composition. See Tables for specifications and compositions, and for commercial compositions. The chemistry balance (1l.5 Mo, 6 Zr, 4.5 Sn wt%) is a solute-rich composition developed by a semi-empirical balancing of desired properties. Molybdenum is a strong beta stabilizing element completely soluble in beta titanium at elevated temperatures, and the nominal composition of Beta III contains enough of this element by itself to stabilize the beta phase to room temperature. Zirconium and tin, often called neutral stabilizing additions to titanium, augment the beta phase stabilization in the quantities used in the Beta III alloy. Both zirconium and tin strengthen the alpha and beta phases of titanium and are soluble in both phases
Characteristics Phases and Structures. Beta III solution annealed above the transus is completely 13, which becomes enriched with molybdenum in some regions during aging through alloy partitioning as alpha-phase precipitation occurs. As with other 13 alloys this enrichment affects the lattice parameter and makes the 13 phase more stable at lower temperatures. Consequently, 13 decomposition can be sluggish in Beta III, as in other 13 alloys Beta Transus. About 760°C (1400 "F) at nominal molybdenum concentrations. Beta III forms athermal coduring quenching and isothermal co during aging at low temperatures. It is generally recognized that co phase formation leads to ductility losses, although proper control of cophase volume fraction can lead to high strength and reasonable ductility Product Forms. Availability of all mill products is limited Applications. Aircraft fasteners, especially rivets, and sheet metal parts where cold formability and strength potential can be used to greatest advantage. Commercial applications have included springs and orthodontic appliances. Possible use: in plate and forging applications where high strength, deep hardenability, and resistance to stress corrosion are required and somewhat lower ductility is acceptable Chemical/Corrosion Properties. The high molybdenum content of Beta III alloy imparts excellent corrosion resistance under reducing conditions and should provide excellent crevice corrosion resistance (because crevice corrosion is generally associated with acidification from oxidant depletion in the crevice region). At room temperature, the general corrosion of Beta III alloy in HCI of concentrations up to about 20% is acceptable; for unalloyed titanium, the HCI concentration limit is about 5%. A similar advantage was observed in boiling H2S04. Enhanced corrosion resistance in reducing environments (from molybdenum) is obtained at the expense of corrosion resistance in oxidizing conditions. Pitting and repassivation potential are expected to be lower than that of most other titanium alloys, although no data are available Stress Corrosion Cracking. The high molybdenum content of Beta III is also probably responsible for its relatively good resistance to stress-corrosion cracking in aqueous-chloride and hot-salt environments. Beta alloys solution treated to contain 100% beta stabilized by molybdenum, vanadium, niobium, or tantalum are immune to aqueous stress-corrosion cracking. In the solution treated and aged condition, however, Beta III has
exhibited stress-corrosion cracking susceptibility in distilled water (B.E Brown, "Stress Corrosion Cracking in High Strength Steels and in Titanium and Aluminum Alloys," Naval Research Labs, 1972). Addition of halide ions such as Cl", Br", and I" increase susceptibility in Beta III and can induce susceptibility in other alloys that are immune to stress-corrosion cracking in distilled water
Mechanical Properties See Table for typical mechanical properties of rivet wire, bar, plate, sheet, and lab foil following solution treatment. See Figure for effect of aging on Rockwell hardness
Fabrication Properties Forging. The alloy can be fabricated into all forging product types, although closed die forgings predominate. Beta III is commercially fabricated on all types of forging equipment. Beta III is a highly forgeable alloy (when forged above the 13 transus) In comparison with a-f3 Ti-6AI-4V, unit pressures (flow stresses) are comparable, forgeability is better, and crack sensitivity is reduced. Final thermal treatments for Beta III forgings include solution treating and aging. Forgings may be supplied in the solution treated condition and/or fully aged. In the solution treated condition, Beta III has lower strengths, but much higher ductility and toughness than in the solution treated and aged condition. Solution treatment is conducted at 690 to 730°C (1275 to 1345 OF), followed by water quenching. Aging is conducted at 565 to 595 -c (1050 to 1100 OF). Beta III, as with all 13 alloys, has a higher affinity for hydrogen than other alloy classes. Beta III forms less a case from heating operations than other alloy classes, meaning less metal removal in chemical pickling (milling processes). But control of chemical removal processes is essential to preclude excessive hydrogen pickup
Beta Ill: Forging process temperatures Melallemperalure
Process
Betaforging
·C
700-955
1300-1750
Forming. All of the 13 titanium alloys are highly cold formable, but Beta III has the lowest yield strength combined with excellent ductility of any of the beta compositions. Cold workability is particularly advantageous for rivets and other fasteners. Beta III parts can be warm formed to eliminate the springback that occurs during some cold forming operations. Solution treated material may be formed at temperatures as low as 315°C (600 OF) where yield strength may be as low as 550 to 620 MPa (80 to 90 ksi) and elongation as high as 25%. On the other hand, temperatures of 510 to 540°C (950 to 1000 "F) were found to minimize springback in hot sizing (see Figure). Hot draw forming at 200°C (390 "F) was found to result in considerable springback. Forming at 510 "C (950 OF) appears to be required for obtaining a precise shape. Either cold or warm forming followed by a hot-sizing operation, which can be a part of the aging heat treatment, appears as an acceptable method of processing parts
560 I Heat Treater's Guide: Nonferrous Alloys Rolling Sheet. The overall cold rollability of Beta III is at least as good as that of commercially pure unalloyed titanium. The cold rolling limit, as determined by the onset of edge cracking, is reported to be somewhat greater than 90% reduction. The resistance to rolling is about the same for Beta III and unalloyed titanium. Because ofthis capability and ease for cold work, thin strip and foils and other sophisticated mill products can be produced in Beta III relatively inexpensively. Foil has been made down to 0.025 mm (0.001 in.) thick at a width of 635 mm (25 in.) Welding. Weldability of sheet and plate is considered to be very good. Welds have good ductility with strength comparable to solution treated and aged material. Like all titanium alloys, Beta III is weldable by all methods, except shielded arc and submerged arc welding (because no flux is permitted). Ductility is better if aging is done after welding
Recommended Heat Treating Practice Beta III may be supplied in either the solution treated (highly formable) or the solution heat treated plus aged condition (high strength or moderately high strength, depending on treatment selected). Heat treatment may consist of simply aging the material from the solution treated condition supplied, or re-solution treatment prior to aging may be preferred to achieve maximum ductility and toughness in heavily worked areas of the aged part.
Beta III: Effect of aging on Rockwell hardness 85
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Solution treatments Aging vs. tensile properties of sheet Effect of pre-age and cold work on age time Aging vs. tensile properties of sheet
Heal
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'Ireatment
5 min 370°C (700 OF)
100
1 10 840 OF aging time, min
1000
LIVE GRAPH
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500 550 Aging temperature, °C
....160 600
730-785 690-730 815-870
1350-1450 1275-1350 1500-1600
Cooling
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ACor WQ ACorWQ ACorWQ
5
5 5(b)
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1500
; 1400 0> c
OF
Beta III: Effect of pre-aging and cold work. Effect of pre-aging heat treatments with and without prior cold work on tensile strength of aged (450 °C, 840 OF) specimens. Solution heat treated 5 min at 730 °C (1345 OF) and water quenched priorto cold working or pre-aging LIVE GRAPH 1600
~
0C
Note:The bestcombination of properties is obtained by solutiontreatmentnearthe beta transus. (a) Eitheraircool(AC)or waterquench(WQ) mightalloythesameagingresponsedepending onsectionthickness. (b)Exposureis usuallyshort,but may be longerfor thickersections
1100 210._
TIme, min
'Iemperature
TypicalST LowSTforrod, wire,etc. HighSTforthickersection
<,
Beta III: Tensile strength vs. age temperature. Effect of 8-h aging temperature on tensile strength of specimens solution treated at 730 to 745 °C (1345 to 1375 OF)
850
See Tables for:
LIVE GRAPH
75 0.01
The recommended aging heat treatment for producing the' high strength condition in Beta III alloy is 8 h at 480 °C (900 "F) followed by air cooling. An overaged condition may be achieved by exposure for 8 h at 595 °C (1100 OF) and air cooling. Precipitation of the IX phase in 8-h exposure in the 480 to 595 °C (900 to 1100 "F) temperature range results in tensile strengths in the range 1380 to 930 MPa (200 to 135 ksi), respectively.
Beta III: Solution treatments
/:
2 min 315°C (600 OF) + 2 min 370°C (70
III
Annealing. Practice is the same as that for solution treating. The recommended annealing temperature range for Beta III alloys is 705 to 760 °C (1300 to 1400 oF), generally for short times and usually followed by either water quenching or air cooling.
• Effect of pre-aging and cold work • Tensile strength vs. aging temperature • Effect of aging temperature and cold work on tensile properties (a) and (b)
-- --
10 mln 370·0 (700
oJ,
Stress Relief Annealing. Treatment may consist of re-solution heat treatment or an aging heat treatment. Re-solution treatment may be accomplished in as short a time as 1 to 2 min at 715 to 730 °C (1320 to 1345 "P), followed by either water quenching or air cooling. A stress relief annealing treatment is not required
See Figures for:
10 min ~1 ~ o_C ~6QO ~Fl 2 min 315°C (600 OF) +
The best combination ofproperties is obtained after solution treatment near the ~ transus
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1000
os cw
200
5
. 2
10 10 Aging time, min
Beta and Near-Beta Alloys I 561
Beta III: Typical mechanical properties Aging temperature
-c
Rivet wire(c) As solutiontreated 480 510 540 565 590 Bar, 13.6 mm (0.522in.) diam(c) As solutiontreated 480 540 590 Plate 13 and 25 mm (0.5and 1.0 ln.) thlck(c)(d) Assolutiontreated 480 510 540 590 Sheet 1.6 mm (0.063fn.) thick Solutiontreated, 720°C(1325oF) Aircooled Waterquenched 480 540 Solutiontreated, 770°C (1425oF) Aircooled Waterquenched 480 540 Lab foil specimen(e) Assolutiontreated, 760°C(1400oF) 0.010in.thick 0.005 in.thick 0.002in.thick 480 0.010in.thick 0.005in.thick 0.002in.thick 540 0.010in.thick 0.005in.thick 0.002in.thick
ThnsUe yield strength(a) MPa ksl
Ultimate IeIl5ile strength ksi MPa
OF
EIongallon(h),
Redudlon oCarea,
%
%
900 950 1000 1050 1100
993 1365 1303 1186 1089 986
144 198 189 172 158 143
792 1269 1213 1124 1034 945
115 184 176 163 150 137
24 15 18 21 25 27
65 36 38 44 56 65
900 1000 1100
855 1386 1165 1041
124 201 169 151
752 1317 1096 1007
109 191 159 146
21 11 17 17
72 33 63 67
900 950 1000 1100
896 1351 1289 1255 1041
130 196 187 182 151
827 1262 1200 1179 979
120 183 174 171 142
22 3 5 4.8 11
62 6.4 10.7 12.3 24
900 1000
972 841 1413 1158
141 122 205 168
882 738 1317 1089
128 107 191 158
17 20 7 8
45 52 29 45
900 1000
896 827 1310 1138
130 120 190 165
834 745 1234 1062
121 108 179 154
18 21 6 8
45 48 35 42
1000 979 1014
145 142 147
958 924 958
139 134 139
8.0 8.5 6.5
1282 1510 1586
186 219 230
1248 1413 1538
181 205 223
6.7 4.5 2.0
1158 1262 1344
168 183 195
1082 1186 1276
157 172 185
6.5 8.2 4.0
900
1000
(a)0.2% offset.(b) In 2 in. or 4dwhere d is diameterof reducedsectionof tensiletestspecimen. (c) Solutiontreated730 to 790 °C (1350to 1450"F), waterquenched, aged 8 h. (d) Longitudinalproperties. (e)Solutiontreated,descaledandpickled,aged8 h
Beta III: Aging vs,tensile properties of sheet Room-temperature tensile properties of 13 mm (0.5 in.) thick plate as rolled, solution treated, and aged Solution Quench 8-haging Ulthnate Irealmenllemperature delay, lemperalure lensUe strengfh OF OF -c -c s MPa ksi As hotrolled(a) 785(b) 1450(b)
73O(b)
73O(b)
1350(b)
1350(b)
15 480 540 595
900 1000 1100
480 510 540 565 595
900 950 1000 1050 1100
480 540 595
900 1000 1100
15
30
992 922 1359 1297 1086 834 1343 1288 1219 1143 1090 949 1397 1255 1036
143.9 133.7 197.2 188.1 157.6 121.0 194.9 186.9 176.9 165.8 158.2 137.7 202.6 182.0 150.3
ThnsiJe yield strength (0.2 %) ksi MPa 921 862 1281 1207 1026 728 1248 1200 1137 1057 1023 906 1277 1158 979
133.6 125.1 185.9 175.1 148.8 105.6 181.1 174.1 165.0 153.3 148.4 131.4 185.3 168.0 142.1
Elongation 1n4D, %
20.0 20.0 4.0 4.0 10.0 34.0 2.0 5.0 6.0 8.0 8.0 20.0 4.0 6.0 13.0
Reduction ofarea,
CluupyV-DOlch impaclloug~(a)
%
J
I\·lhf
67.2 69.5 8.2 13.7 22.6 68.3 8.2 10.7 11.5 13.4 29.7 56.6 8.1 14.8 26.7
10.8 20.3 10.8
8 15 8
14.9 35.2
11 26
10.8 10.8
8 8
13.5 23.0 6.7 12.2
10 17 5 9
(a)At -40 °C (-40 "P), (b)Plate27.9 mm (1.1in.) thick washot rolledto 13mm (0.5in.) thickness usingfurnacetemperature925°C (1700"F), reheattemperatureof925 °C (1700 oF), final passexittemperature895°C (1640"F), Platestraightened warmwithoutreheating. Note:Panelswerelaboratory solutiontreatedfor 15minat theindicatedtemperature and waterquenchedwith theindicateddelaytime
562/ Heat Treater's Guide: Nonferrous Alloys
Beta III: Commercial compositions Specillcalion
Designation
Descripllon
Ugine Ugine USA
IDI2ZrE IDI2ZrE
BarSh Quen BarSh Quen Aged
Crucible Crucible Orernet
Betam Betam TI Beta 3
Ann ill
C
Fe
Composillon, WI % (nomlnalcontentonly) Mo N 0
H
Sn
Zr
Other
11.5 11.5
4.5 4.5
6 6
balTI baITI
11.5 11.5
4.5 4.5
6 6
balTI balTI
Fmnce
Beta III: Aging vs, tensile properties of sheet Room-temperature tensile properties of 1.7 mm (0.067 in.) thick hand sheet as solution treated and after various aging treatments 8-haging UllhnatelensUe TensUe yietd temperature Spechnen strength(a) strength(0.2%) OF "C direcllon MPa ksi MPa ksi
In SOrom(2 in.), %
Elongation
Reduction ofarea, %
Solution treated 3 min, 730 °C (1350 oF) and air cooled None 480
900
510
950
540
1000
595
1100
L T L T L T L T L
955 925 1397 1418 1311 1383 1201 1184 966
138.5 134.2 202.7 205.7 190.2 200.6 174.3 171.8 140.1
900 901 1350 1397 1208 1297 1117 1100 903
130.6 130.7 195.8 202.6 175.3 188.1 162.1 159.6 131.0
10.8 10.0 3.7 2.7 7.3 5.5 6.0 7.0 11.0
56.2 52.4 18.2 9.3 33.2 23.9 37.2 37.2 62.4
837 809 1370 1419 1348 1354 1237 1288
121.4 117.4 198.7 205.8 195.6 196.4 179.4 186.9
753 718 1337 1407 1247 1279 1173 1233
109.2 104.2 194.0 204.1 180.9 185.6 170.1 177.4
19.2 29.7 4.0 2.8 5.5 5.5 5.0 5.0
61.2 66.2 26.4 11.3 26.5 30.1 40.5 29.8
Solution treated 3 min, 730 °C (1350 oF) and water quenched None 480
900
510
950
540
1000
L T L T L T L T
(a) Tensile properties are average of duplicate tests
Beta III: Specifications and compositions SpeciJlcatloo
Designation
UNS
R58030
Description
Composilion, WI % 0
C
Fe
H
Mo
N
So
Zr
0.1
0.35
0.02
10-13
0.05
Sh Str Bar Frg lObe ill
0.1
0.35
0.02
10-13
BarWrrSill Bar WrrSTA ShPltStrST PipST lObe Heat Ex/Con Sill Bar Bil FrgAnn FrgHT ST BarBiiSill
0.1 0.1 0.1 0.1 0.1 0.1 max 0.1 max 0.1 0.1 0.1 0.1
10-13 10-13 10-13 10-13 10-13 10-13 10-13 10-13 10-13 10-13 10-13
Other
0.18
3.75-5.25
4.5-7.5
0.05
0.18
3.75-5.25
4.5-7.5
OTO.4; bal TI
0.05 0.05 0.05 0.05 0.05 0.05 max 0.05 max 0.05 0.05 0.05 0.05
0.18 0.18 0.18 0.18 0.18 0.18 max 0.18 max 0.18 0.18 0.18 0.18
3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25 3.75-5.25
4.5-7.5 4.5-7.5 4.5-7.5 4.5-7.5 4.5-7 4.5-7.5 4.5-7.5 4.5-7.5 4.5-7.5 4.5-7.5 4.5-7.5
OTO.4; YO.005; bal TI OTO.4; YO.005; bal TI OTO.4; bal TI OTO.4;balTI OTO.4; bal TI OTO.4 max; OEO.l max; balTI OTO.4max;OEO.l max;balTI OTO.4; bal TI OTO.4;balTI OTO.4; balTI OTO.4; Y 0.005; bal TI
Spain UNE38-730
L-7702
USA AMS4980B AMS4980B ASIMB265 ASIMB337 ASIMB338 ASIM B348(10}-87 ASIM B348(10}-87 MIL F-83142A MILF-83142A MILT-9046J MILT-9047G
Grade 10 Grade 10 Grade 10
Comp13 Comp13 CodeB-2 TI-4.5Sn-6Zr-11.5Mo
0,015 0.35 0,015 0.35 0,02 0.35 0,02 0.35 0.35 0.02 0.35 max 0.02 max 0.35 max 0.015 max 0,02 0.35 0,02 0.35 0.35 0.02 0.35 0.02
Beta III: Effect of pre-age and cold work on age time Pre-age, min, an 315"C (600 oF)
0 2 2 2 2 10 0
370"C (700 oF)
0 10 2 2 2 0 5
Coldwork, % 0 0 0 10 20 0 0
TImeto fuU strength, min 1440 2 10-20 7 3 20 100
Note: Effects pre-aging and cold work on aging time al450 °C (840 oF) to reach full strength
Beta and Near-Beta Alloys I 563
Beta III: Effect of aging temperature and cold work on tensile properties. Effectof prior cold work on the tensile properties of aged specimens. Solutionheattreated5 min at 730°C (1345 OF) and waterquenchedpriorto cold working or aging. Agingtimesnot given (they are peak agingtimes)
LIVE GRAPH
LIVE GRAPH Click here to view
Aging temperature, OF 700 800 900 1000
1100
Click here to view
Aging temperature. ·F 700 800 900
600
1000
5 /20% cold rolled
240
~ 1500
::!
, .
s:
s: C,
200 C, c:
~
lii
c:
lii
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10% cold rolled __ . . 220 No cold rolling ~
No cold rolling 10% cold rolled ._._ 20% cold rolled
o
~
1250-
180
TYS, no cold roiling 1000L-300
----'
400 500 Aging temperature, ·C
350
600
(s)
400 450 Aging temperature, ·C
500
550
(b)
Ti·3AI·8V·6Cr·4Mo·4Zr (Beta C) Common Name. Beta C™, 38-6-44 UNS Number. R58640 Chemical Composition. See Tables for specifications and for commercial compositions.
Beta C is formulated by depressing the beta transus with the beta isomorphous elements, molybdenum and vanadium, and the sluggish beta eutectoid element, chromium. It is slightly more beta-stabilized than Ti-ll.5Mo6Zr-4.5Sn (Beta III) and less beta-stabilized than Ti-13V-I1Cr-3Al
Characteristics Phases and Structures. As a solute-rich p alloy, precipitation of ex within the solute-lean p regions (~') of Beta C is slow. Prior cold work accelerates the formation of intragranular ex and also reduces the extent of grain boundary ex. Peak aging occurs at around 480°C (900 "F), and smaller quantities of ex (in the form of coarse precipitates) are found at higher temperatures. Type 2 ex occurs during certain aging treatments. Recrystallization occurs after short times above the ~ transus, although p grain growth is not a problem. The possibility of a second phase responsible for inhibiting grain growth above the p transus has been suggested (R.A. Wood and RJ. Favor, Titanium Alloys Handbook, MCIC-HB-02, Battelle Columbus Laboratories, 1972, Section 1-12, p 72-1) Beta Transus. 730°C (1345 "P), Previously published Figure, 795°C (1465 "F), is too high ChemicaVCorrosion Properties. Molybdenum additions improve the corrosion resistance of titanium alloys in reducing media, and this effect is evidenced by the general corrosion rates of Beta C in reducing media such as hydrochloric and sulfuric acid. This increase in reducing environment resistance is achieved, however, at the expense of corrosion resistance in oxidizing environments such as nitric acid. Oxidizing agents such as ferric chloride (FeC13) have a similar adverse effect on corrosion in sulfuric acid Crevice Corrosion. In contrast to the anodic breakdown associated with pitting, crevice corrosion is usually the result of acidification in the crevice region by oxidant depletion. Therefore, Beta C is expected to outperform CP Ti in terms of crevice corrosion resistance
Stress Corrosion Cracking. In ~ titanium alloys, the ~ phase may be susceptible to either transgranular or intergranular stress-corrosion cracking (SCC), depending on alloy composition and microstructure. Intergranular cracking has only been observed in a few aged p alloys, particularly with fine ex precipitates formed at lower aging temperatures. Beta phase stabilized by either molybdenum, vanadium, niobium, or tantalum is immune to SCC, except for a pphase stabilized by the eutectoid elements manganese and chromium. Although p + 0} phase structures appear to be highly resistant, the precipitation of compounds, such as TiCr2 in Beta C can be expected to degrade cracking resistance
Mechanical Properties Hardness. For effect of aging temperature on hardness, see Figure Tensile Properties. For typical room temperature tensile properties of strip, sheet, plate, pipe, fastener stock, spring wire, and billet, see Figure
Fabrication Properties Forging. Beta C is a very high strength, deep hardening, metastable p alloy. It can be fabricated into all forging product types, although closed die forgings predominate.
Beta C is a highly forgeable alloy (when forged above the p transus), with lower unit pressures (flow stresses), improved forgeability, and less crack sensitivity in forging than the a-p alloy Ti-6AI-4Y.Flow stresses and unit pressures exceed that of the near-B alloy Ti-lOV-2Fe-3Al. Beta C is thermomechanically processed in forging manufacture to achieve the desired final microstructure of fine transformed p, limited grain boundary films, with a fine recrystallized prior ~ grain size, in preparation for final thermal treatments. The highly refined microstructures of Beta C forgings are responsible for its excellent corrosion, strength, and fatigue properties. Beta C is forged above the transus through one or more forging operations. Reheating for subsequent forging operations recrystallize the alloy from prior hot work refining prior p grain size. Beta C is not subtransus (a + P) forged, because no microstructural advantages are gained and there is a significant increase in unit pressure requirements
564/ Heat Treater's Guide: Nonferrous Alloys Final Thermal Treatments. Treatments for Beta e forgings include annealing or solution annealing and aging. Forgings may be supplied in the annealed or solution annealed (ST) condition and/or fully aged (STA). In the ST condition, Beta e has lower strength, but much higher ductility and toughness than in the STA condition (not recommended for high-temperature use). Solution treatment is conducted at 815 to 925 "C (1500 to 1695 OF), followed by air cooling. Aging is conducted at 455 to 540 "C (850 to 1000 OF). For thick section Beta e forgings, it has been reported that a three-step heat treatment process improves the overall combination of strength, ductility, toughness, and fatigue.
overaged condition, stress relief annealing may be accomplished simultaneously with the aging or overaging heat treatment. Annealing for Beta e is the same as solution treating
Solution Heat Treating. Some care should be exercised in matching the solution annealing treatment with the mill product form being used, its processing history, and the mechanical properties expected. A typical recommended solution annealing treatment for Beta e is 30 min at 815 "C (1500 OF) (terminated by either water quenching or air cooling). However, good properties (high ductility in the solution annealed condition and combinations of good strength and ductility in the aged condition) also may be obtained by solution annealing at temperatures up to 925 "C (1695 OF). The higher temperatures (e.g., 925°C) are generally favored for thicker section products such as plate and bar, whereas the lower temperatures (e.g., 815 to 840 "C, 1500 to 1545 OF) may be used for products such as wire and sheet. Solution annealing temperature has a significant effect on the ductility of plate, but little effect on the properties of small-diameter rod
For effect of thermomechanical processing on properties, see Table
Forming. Total cold reductions of 60 to 70% are common for Beta C, and the capacity for cold work enhances the manufacture of seamless tubing, rod, wire, strip, and foil products. The material is markedly strengthened by cold work to about 60% but further cold work has little additional effect. As in other ~ titanium alloys, prior cold work accelerates the aging reaction, and a fine, uniformly dispersed IX precipitate may be obtained. Limited information is available on warm working of Beta C, but good results would be expected in the 230 to 345 "C (450 to 650 "F) range. Data suggest that aged material would not be very workable below about 540 "C (1000 oF)
Aging. Temperatures range from 455 to 540 "C (850 to 1000"F). Typical aging times range from 6 to 12 h at the aging temperature, although 12 to 24 h exposure may be used to age material to maximum strength at aging temperatures of 455 to 465 "C (850 to 870 OF). Aging is terminated by air cooling.
Recommended Heat Treating Practice Beta e is capable of achieving many strength/ductility combinations, depending on processing history and heat treatment. A wide range of aging heat treatments may be used for Beta e to achieve a preferred strength level and associated mechanical properties.
Figure (a) and (b) in both instances, show effect of aging time on room temperature tensile properties and effect of aging and cold work.
Full annealing may be used to alleviate undesirable residual stresses in Beta e, and in certain cases where the material is to be used in the aged or
Beta C: Effect of aging temperature on hardness. Blocks 5 x 20 x 60 mm (0.2 x 0.8 x 2.3 in.) were cut from hot rolled plate and solution treated at 750°C (1380 OF) 30 min, WO, plus 20 h age at indicated temperatures. Specimens were mounted in resin. Testing surfaces were planed 1 mm (0.04 in.) to remove oxide scale and the contaminated layer and were polished and buffed to smooth surfaces. Vickers hardness measurements were carried out at 10 kgf
Beta C: Microstructure. Rod, cold drawn, solution treated 30 min at 815°C (1500 OF), and aged 6 hat 675°C (1245 OF). Precipitated IX (dark) in grains of ~. Kroll's reagent (ASTM 192). 250x
Aging temperature, 'F
700
800
900
1000
1100
500
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380
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530
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Beta C: Commercial compositions Specification Designation
Description
AI
Cr
3-4
5.5-6.5
3-4 3-4 3-4
5.5-6.5 5.5-6.5 5.5-6.5
Fe
Mo
Composition, % N 0
V
'h
other
USA Astro
Oremet RMI Teledyne Timet
Ti-3AI-8V-6Cr-4Zr4Mo BarSprgPip TI-38-644 3Al-8V-6Cr-4Zr4Mo ShPItBarBilWirEx Tel-TI-3Al-8V-6Cr4M04Zr TIMETAL 3-8-644 IngBiiSTA
0.3 0.3 0.3
3.5-4.5
0.03max
0.14max
7.5-8.5
3.54.5
C0.05max;balTI
3.5-4.5 3.5-4.5 3.5-4.5
0.Q3 0.03 0.03
0.14 0.14 0.14
7.5-8.5 7.5-8.5 7.5-8.5
3.54.5 3.54.5 3.54.5
CO.05;balTI HO.02;CO.05;balTI
Beta and Near-Beta Alloys /565
Beta C:Typical RT tensile properties Elongation,
Reduction ofarea,
MPa
ksl
MPa
ksl
II
II
SA STA SA
L L L
STA
L
896 1338 896 931 1372 1441 924 924 1276 1296 1151 876 11I7 1469 1193 1207 1220
130 194 130 135 199 209 134 134 185 188 167 127 162 213 173 175 177
855 1241 883 917 1276 1344 896 910 1179 1207 1014 862 1048
124 180 128 133 185 195 130 132 171 175 147 125 152
1145 1151 1158
166 167 168
16 7 10 6 8 5 14 6 II 9 II 27 18 12 9 9 9
'Thst
Condition
Strip,0.5nun (0.Q20 in.) Sheet.1.2nun (0.050in.)
T T Plate.12nun (0.500in.)
L
SA
T STA
L
STA SA STA CW+age STA
L L L L
T Pipe.75 nun 00 x 50 in. ID (2.95in. 00. 2.00in. ID) Fastenerstock,4.7mm(0.187in.) diam Springwire. 5.8mm(0.229in.) diam Billet.150nun (6 in.)diam
'Thmlle yield strength
VIIlmate temlle strength
direction
Product
L-edge L-midradius Lcenter
37 21 13 16 25
50 44 28 18 17 16
Note: STA.solutiontreatedandaged:SA,solutionannealed
Beta C: Aged tensile properties vs. cold work. Effect of increasing amounts of cold work on the room-temperature tensile properties of aged alloy cold drawn as indicated plus aged for 6 h at 480°C (900 OF) and air cooled 2000
60
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40 60 Cold reduction, %
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(b)
(8)
Beta C: Effect of aging and cold work (6 h age). Effect of aging temperature variation and of cold work plus aging temperature on the tensile properties of tubing. 19 mm (0.75 in.) OD x 1.0 mm (0.042 in.) wall. Aged for 6 h
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1000
Aging temperature, OF 1100 1200 I
1600
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220 20 200
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550 600 Aging temperature,
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1000
700
(b)
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550
600 Aging temperature,
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650
700
566/ Heat Treater's Guide: Nonferrous Alloys BetaC: Specifications SpeeillcaJion
Designation
UNS
R58640
Description
AI
Cr
3
6
3-4 3-4 3-4 3-4 3-4 3-4
5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5 5.5-6.5
Fe
Mo
N
Composition, wi % V 0
Zr
Other
8
4
balTi
7.5-8.5 7.5-8.5 7.5-8.5 7.5-8.5 7.5-8.5 7.5-8.5
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
4
USA AMS4957 AMS4958 MILT-9046J MILT-9046J MILT-9047G MILT-9047G
Code B-3 Code B-3 Ti-3Al-8V-6Cr-4M04Zr Ti-3Al-8V-6Cr-4M04Zr
BarWlfCD BarRodSTA Sh Strp Pit SHT ShStrp Pit STA BarBilSTA BarBilSHT
0.3 0.3 0.3 0.3 0.3 0.3
3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5 3.5-4.5
0.03 0.03 0.03 0.03 0.03 0.03
0.12 0.12 0.12 0.12 0.12 0.12
HO.03;CO.05;OTO.4;YO.005;balTI HO.03;CO.05;OTO.4;YO.005;balTI H 0.02; C 0.05; OTO.4;bal Ti HO.02; CO.05; OTO.4;balTI HO.02;CO.05;OTO.4;YO.005;balTi HO.02; CO.05; OTO.4; YO.005; bal Ti
BetaC: Effect of TMPon properties Due to the fine microstructural features of aged ~ alloys, their resistance to crack growth is generally inferior to a + ~ alloys.
Forging route ~,+85"C ~,+85"C ~,+195"C ~,+85"C
Heat treatmeDl 535 "C, 8h 91O"C,AC+535"C,8h 910 "C, AC+535 "C,8h 815 "C, AC+565 ·C, 8h
Thnsileyield
Ultimate tensile
strength MPa ksi
strength MPa lIsi
1123 1199 1190 1151
1179 1262 1258 1192
163 174 172 167
171 183 182 173
Reduction
Elongation,
ofarea,
%
%
6 8 3 11
14 7 22
9
Fracture toughness ~KI')
MPa m
ksi'fut
53 48 50 57
48 43 45 52
Critical crack length(a) mm in. 2.5 1.8 1.9 3.0
0.10 0.071 0.075 0.12
Smoothfatigue llK",(h) MPa'liii' ksl'liii:"
<4.4 <4.4 4.4
<4 <4 4
stress(c)
MPa
lIsi
790 800 700 780
114 116 114 113
7
(a) Critical crack length, = 1.1 eKlrlYsl (b) Mih is the threshold stress-intensity in fatigue crack growth rate tests. ec)Smooth fatigue stress at 10 cycles, lests conducted al R = 0.1 to 0.3, F=30 10 125 Hz
Ti·10V·2Fe·3AI Common Name. Ti-1O-2-3 UNS Number. Unassigned Chemical Composition. Ti-1O-2-3 has a near-beta composition and is slightly more beta stabilized than Ti-ll.5Mo-6Zr-4.5Sn (Beta III). Inclusions rich in titanium, phosphorus, sulfur, and silicon can occur. Chemical microsegregation (or beta flecks), which is found in other p alloys and even some ex + p alloys, is due to iron segregation Specifications. Ti-lOV-2Fe-3AI is capable of being heat treated to provide a wide range of properties. There are four AMS specifications (AMS 4984,4986, 4987, and 4983A) covering strengths ranging from 965 to 1240 MPa (140 to 180 ksi), with the lower strengths being utilized when higher fracture toughness is required. See Tables for AMS specifications and compositions, and for commercial compositions
Characteristics Phases and Structures. As a solute-lean p alloy, the microstructure of Ti-lOV-2Fe-3AI typically has a bimodal (equiaxed and lamellar) ex phase in a p matrix. The precise microstructural characteristics depend on the deformation and heat treatment history of the alloy. Coarse, globular ex, which has little effect on strength but has desirable effects on ductility, is produced during solution treatment in the ex + p lamellar ex as a result of <X111 work. The remnant acicular alpha, which detracts from ductility, is necessary to meet fracture toughness requirements. Ti-lOV-2Fe-3AI generally is not solution treated above the p transus because ductility and toughness are lower than that of <X1p solution treated material. However, extreme overaging of p quenched material can restore ductility and toughness to acceptable levels Grain Structure. Recrystallization and grain structure of Ti-lOV-2Fe3AI are influenced greatly by minor modifications in thennomechanical
processing. High amounts of deformation and high temperatures enhance dynamic recrystallization and the formation of equiaxed p, whereas high volume fractions of ex retard recrystallization. High deformation also reduces the aspect ratio of ex platelets. Forgings are normally beta forged followed by ex-p forging, with about 10 or 15 to 25% reductions (for high-strength condition) to break up grain-boundary ex and recrystallize some of the primary ex to a globular shape for improved ductility. See Figure for effect of solution temperature on primary alpha content. See TTT diagram for beta solution treated alloy Beta Transus. 800°C (1470 "F) is often reported as the typical transus, with a range of 790 to 805°C (1455 to 1480 OF) Physical Properties. See Table for corrosion rates in specific media Product Forms. Ti-1O-2-3 has the best hot-die forgeability of any commercial titanium alloy and is often used fornear-net-shape forging applications. Mill products are billet, bar, and plate Applications. Ti-1O-2-3 is a near-beta alloy, capable of attaining a wide variety of strength levels depending on selection of heat treatment. Major advantages are its excellent forgeability; its high toughness in air and saltwater environments; and its high hardenability. It is used by the aerospace industry. A major advantage of Ti-1O-2-3 over commercially available alpha-beta compositions of similar strength levels is its toughness in air and salt water environments. This near-beta alloy was developed primarily for highstrength and toughness applications at temperatures up to 315°C (600 "F) and tensile strengths of 1240 MPa (180 ksi) in order to provide weight savings over steels in airframe forging applications. Of special interest for high-strength forgings, it is being used for components by much of the aerospace industry. Ti-1O-2-3 is used where medium-to-high strength and high toughness are required in bar, plate, or forged sections up.to 125 mm (5 in.) thick. It can
Beta and Near-Beta Alloys I 567
be heat treated over a wide strength-toughness range, allowing the tailoring of properties. It is selected for applications requiring uniformity of tensile properties at surface and center locations. Uses include aerospace airframes, hot-die and conventional forgings, and other forged parts. The major user, Boeing, uses the alloy at service temperatures up to 260°C (500 "F)
treated. With such conventional processes, the alloy achieves high strength and fatigue properties and superior ductility, but has poor toughness and fracture-related properties
Ti-l OV-2Fe-3AI: Forging processtemperatures
Mechanical Properties Hardness. The very high hardnesses obtained by aging at temperatures of 370°C (700 "F) or below are due to the precipitation of omega at these low temperatures. Hydrogen is a ~ stabilizer, so high H2 concentrations stabilize the ~, making the aging reaction more sluggish TYpical Vickers Hardness. 300 to 470 HV Typical Rockwell C Hardness. 32 to 41 HRC See Table for effect of forging conditions on Rockwell hardness. See Figure for effect of aging on Vickers hardness
RT Tensile Properties. Almost all product forms are capable of being heat treated over the strength range cited in the adjoining Table. Two exceptions: castings (Ti-IO-2-3 is not considered a casting alloy) and the conventional, high Cl blended elemental powder compacts. The alloy is capable of being heat treated to 1190 MPa (173 ksi) in section thicknesses up to 75 mm (3 in.) thick with uniform properties. Uniform properties can be obtained for heavier section thicknesses at lower strength. See Table for typical tensile properties of various product forms
Effect of Microstructure. The strength-ductility-toughness relationship is dependent on the microstructure (and the processing which provides the microstructural variations). In general terms, globular primary a provides higher ductility at a given strength. The ductility of a microstructure with no primary a will be minimum; ductility will then improve with increasing amounts of primary a, and then decrease again as the amount of primary a is increased. The formation of ro will provide high strengths, but poor ductility, often nil Effect of Hydrogen. The addition of hydrogen can strongly influence tensile properties in Ti-IO-2-3. The type and magnitude of hydrogen effects, for a given microstructure, is a function of both hydrogen concentration and thermal processing prior to and/or subsequent to hydrogen introduction. Hydrogen can display two separate types of effects in Ti-I 02-3; the first is as an intrinsic embrittling agent, akin to the hydrogen embrittlement observed in other metals. The intrinsic embrittling effect is generally observed as decreased ductility and a reduction in tensile strength. The second hydrogen effect results from hydrogen being a powerful beta stabilizing element. Changes in tensile properties may be a direct result of hydrogen-induced changes in microstructure. Generally, hydrogen introduced into the material after final thermo mechanical processing results in an intrinsic effect. See Tables for effect of microstructure on tensile properties, and for tensile properties of selected microstructures. See Figure for effect of Hz concentration on yield strength
Fabrication Properties Forging. Ti-IOV-2Fe-3Al is among the most forgeable of all titanium alloys, with lower unit pressures (flow stresses), improved forgeability, and significantly less crack sensitivity in forging vs. the a-~ alloy Ti-6AI-4Y. Forgings are supplied at three major strength/fracture toughness combination levels: 1190 MPa (173 ksi) ultimate tensile strength and 44 MPa-frll (40 ksi --fuL) fracture to.!!Shness (K~ 1100 MPa (160 ksi) ultimate tensile strength and 60 MPa"m (55 ksi--fuL) fracture toughnesUKIc); and 965 MPa (140 ksi) ultimate tensile strength and 88 MPa-frll (80 ksi--fuL) fracture toughness (KIc). The preferred forging process to meet the preceding mechanical-property criteria is controlled ~ forging followed by controlled aJ~ forging. This, in combination with final thermal treatment, provides the optimum combination ofstrength, ductility, toughness, fatigue, and fracture-related properties. Ti-IOV-2Fe-3Al may be conventionally a + ~ forged and thermally
Metal temperature
Conventional forge Betaforge
700-785 815-870
1300-1450 1500-1600
Final Thermal Treatments. Treatments for forgings include twoand/or three-step subtransus solution treating, quenching, and aging. Forgings may be supplied in the annealed or solution and aged (STA) condition and/or overaged (STOA) conditions. In the STA condition, Ti-IOV-2Fe3Al has lower strengths, higher ductility, and toughness than in the STA condition. Solution treatment is conducted at 745 to 765°C (1375 to 1410 "F) followed by air cooling or faster for very thin section precision forgings, with water and/or other quenchants (including polymers) for thicker section forgings. Aging is conducted at 480 to 525°C (900 to 970 "F) for the highest strength; 510 to 540 °C (950 to 1000 "F) for the intermediate strength; and 565 to 620°C (1050 to 1100 "F) for the lower strength. Thermomechanical Processing. Unlike other ~ alloys, thermomechanical processing (TMP) of Ti-lOV-2Fe-3Al achieves desired final microstructure through manipulation of a phase morphology. Microstructural objectives range from fully transformed, aged ~ structures to controlled amounts of elongated primary a in an aged ~ matrix, characterized by extremely fme secondary (aged) a. The latter microstructure is preferred for most aerospace applications and forms the basis for most commercial use of the alloy in forgings. The highly refined microstructures achieved in Ti-IOV-2Fe-3Al forgings are responsible for its superior strength and high-cycle fatigue properties and excellent fracture toughness and low cycle fatigue properties. See Tables for mechanical properties offorgings solution treated and aged and solution treated and overaged, and for thermomechanical treatments for forgings
Recommended Heat Treating Practice Ti-IOV-2Fe-3Al is used in the solution treated and aged condition. In general, aged strength can be increased by increasing the solution temperature or decreasing the aging temperature. There are applications in which it may be desirable to create a stable microstructure that will not change greatly with service exposure at intermediate temperatures. One way to achieve this is to solution treat, followed by furnace cooling to an overaging temperature, overaging, and air cooling. A final long-time (48 h) age at 480°C (900 "F) would further stabilize the alloy. The aging temperature should be at least 475 °C (890 OF) to avoid the formation of ro phase. See Tables for typical heat treatments and for heat treating schedules for forgings. See Figures for effect of solution treatment on tensile properties and for effect of aging on ultimate tensile strength
Ti-l OV-2Fe-3AI: Corrosion ratesin specific media Concentration, Medium
Ferricchloride Hydrochloric acid Hydrochloric acid+0.1% FeCh
%
10
0.5 5
'Thmperatnre, OC
Cormskm rate, mmfyr
Boiling Boiling Boiling
nil 1.10 0.008
Thesedatashould beusedonlyas a guidelinefor alloyperformance, Ratesmay varydepending on changesin mediumchemistry, temperature, lengthof exposure,and otherfactors. Totalalloysuitabilitycannotbeassumedfrom thesevaluesalone,becauseotherformsofcorrosion. suchas localizedattack,maybe limiting. Incomplex,variable, andlordynamicenvironments, insitutestingmay providemorereliabledata
568/ Heat Treater's Guide: Nonferrous Alloys
Ti-l OV-2Fe-3AI: Typical tensile properties of various productforms Thnslle peWstrength MPa k.d
Ultimate tensile strength MPa k.d
Product fonn High-strength condition Isothermal forgings Conventional forgings Pancakeforgings Extrusions PfM high strength Prealloyed, HIP Prealloyed, HIP+ isothermal forge PIS(0.19wt%Cl max) PIS+ HIP Reduced strength condition Isothermal forgings Pancakeforgings Extrusions PIMprealloyedHIP+ isothermal forge PIMP/S+HIP Castings
Elongation,
Reduction ofarea,...
...
1300-1380 1230-1350 1275-1310 1240
188-200 178-196 185-190 l80
1200-1255 1145-1280 1150-1160 1170
174-182 166-185 167-168 169
3-6 4-10 5-8 4
5-13 5-28 5-29
29 44-60 47
26 40-54 43
1310 1345-1400 1195 1228-1275
190 195-203 173 177-185
1205 1240-1305 1110 1185-1245
175 180-189 161 172-180
9 6-8 3.5 7-9
13 15-28
28
25
28-29
25-26
1060-1100 965 1110-1170 1125-1145 1120-1160 1105-1130
l54-159 140 161-169 163-166 162-168 160-164
985-1060 930 1000-1105 1050-1090 1070-1105 1010-1030
143-154 135 145-160 152-158 155-160 146-149
8-12 16 6-7 13-15 9-10 6-10
22-32 50 10-18 37-45
70 100 45-48 55 32
64 92 41-44 50 29
6-15
Ti-l OV-2Fe-3AI: Mechanical properties of forgings Thoslle yield Heat lreatmenl(a)
MPa
ksi
U1limate tensile strength MPa ksi
STA STA STOA
1100 1000 895
160 145 130
1195 1100 965
strength
Reduction ofarea,
Elongation,
...
...
l73 160 140
4 6 8
~Kr,)
mm
in.
44
40 54 80
1.8 4.1 10.7
0.07 0.16 0.42
Smooth Fatigue I!reSS(dl ksI MPa
AKth(c) MPa'liii ksI'AiL
lengthlbl
ksi'AiL
60 88
15 20
Critkalcrack
Fracture toughness
MPa~
4.0 4.1 4.3
3.6 3.7 3.9
895 860 830
130 125 120
(a)STAiSTOA: singleor duplexsolutiontreatedand aged or overaged,Forgingprocessis ~ hot die forgeor ~ block/a + ~ finish perAMS4983.4986. and4987. (b) Criticalcracklength, ~ 1.1 (Kr,fYS)2. (c) 7 dKlhis the thresholdstress-intensity in fatiguecrack growth ratetests.(d)Smoothfatiguestressat 10 cycles.testsconductedat R O.l to 0.3. F 30 to 125Hz
=
=
Ti-l0V-2Fe-3AI: Specifications and compositions SpedfJC8tion
Composition, Designation
USA AMS4986 AMS4983A AMS4984 AMS4987
Description
AI
C
Fe
H
N
FrgSTOA FrgSTA FrgSTA FrgSTOA
2.6-3.4 2.6-3.4 2.6-3.4 2.6-3.4
0.05 0.05 0.05 0.05
1.6-2.2 1.6-2.2 1.6-2.2 1.6-2.2
0.Q15 0.Q15 0.015 0.Q15
0.05 0.05 0.05 0.05
wt'"
0
V
Y
Other
0.13 0.13 0.l3 0.13
9-11 9-1I 9-11 9-11
0.005 0.005 0.005 0.005
OTO.3;balTI OTO.3;balTI OTO.3;balTI OTO.3;balTI
Ti-l OV-2Fe-3AI: Commercial compositions Specillcalion Japan Kobe USA Timet
Composition, Designation
Description
KSIO-2-3
BarFrgSTA
TIMETAL10-2-3
Frg
Fe
H
N
2.6-3.4
1.6-2.2
0.Q15
2.6-3.4
1.6-2.2
0.Q15
C
AI
wt'"
0
V
0.05
0.13
9-11
balTI
0.05
0.13
9-11
balTI
Other
Y
Ti-l OV-2Fe-3AI: Effect of microstructure on tensile properties
Microstructure 20%primarya + ~ + athermalOJ ~ + athermalro a + ~ + isothermalOJ ~ + isothennalOJ 20%primarya+~+a(unifonn) ~ + a (uniform)
20%primarya + ~ + a (sympathetic) ~ +a (sympathetic)
Heat treatment 730°C (1345oF)(48 h)+ WQ 850°C (1560oF)(2 h) + WQ 700°C (1290oF)(300 min) + WQ+ 250°C (480°:"> (6000min) 850 -c (1560oF)(2 h)+ WQ + 250°C (480°F) (10 min) 720°C (1330oF)(100min)+ WQ + 370°C (700°F) (1000min) 850°C (1560 "P) (100min)+ WQ + 370°C (700oF)(1000min) 730°C (1345oF)+ WQ + 500°C (930oF)(60 min) 850°C (1560oF)(100 min) + WQ+ 500 °C (930oF)(240min)
Thnsile yield strength MPa ksi
UltJmate tenslle strength MPa k.d
741 107 262 38 1218 176 Brittle,no yield 1240 180 Brittle.no yield 1063 154 1225 177
862 878 1266
125 127 183
1430
207
1106 1243
160 180
Unlfonn elongation,
Elongation
...
toratlure,
Reduction ofarea,
9.7 l5.7 0.26 0 2.7 0 4.6 2.3
18.6 21.8 0.58 0 8.9 0 17.5 8.7
35 32 2.25 0 16 0 58 14
...
...
Note: Tensiletestingwas performedon an Instron machineusing a clip-onextensometer. The strainrate was 0.00055Is. and the tensilespecimengage sectionswere0.640em (0.25 in.) in diarnand3.2 cm (1.3In.)in length.Specimenswerepulledwith the rollingdirectionparallelto the tensileaxis
Beta and Near-Beta Alloys I 569
Ti-l0V-2Fe-3AI: Heat treatingschedules for forgings Solutiontreat andage
Ti-10V-2Fe-3AI: Effect of solution temperature on primary a content LIVE GRAPH
75010765°C(l385 to 1410°F),lh, WQ 48010495 -c(90010950oF),8 h,AC 730°C (1350oF),1h,AC 580 to595°C (1075to 1l00°F), 8h,AC 765°C (1400oF),1h, Fe to565°C (1050oF) 565°C (1050oF),8 h,AC 480°C (900 oF),48 h, AC(optional) 815°C(1500°F), 1h,AC 620°C (1150oF),8 h,AC
Solutiontreatand overage Stabilize
Beta anneal and overage
Click here to view Solution treatmenttemperature, OF
E
51 30
'S
S-
II
E
Ti-l0V-2Fe-3AI: Heat treatmentper AMS specifications
20
<,
<.
~
Q)
MlnUTS MPa l<5i
Speeillcotion
AOC
AOF
OC
OF
AMS4984 AMS4986 AMS4987 AMS4983A
15-4O(e) 15-4O(e) 15-4O(e)
60-100 60-100 60-100
480-510 510-540 565-620 480-510
900-950 950-1000 1050-1150 900-950
1190 1100 965 1240
1450
1500
<,
Q.
Aging tempemture(b)
1400
<,
:::>
'1:
o;
Solutiontreatment(o) 'Iempemture below transus
1350
1300 40
~ 10
"<, <,
:::>
;g
173 160 140 180
o 700
725
750
775
K 825
800
Solution treatmenttemperature, DC
(a) Holdfor a minimumof30 min. (b) Hold within±5 °C (10 "F) for not less than8 h. (e)Conver-
sionsfor l!.°C perspecification
Ti-l OV-2Fe-3AI: Tensile properties of selected microstructure Heat
ThwiIeyield strength (0.2 % oifoet) ksi MPa
M1crollrncture
treatment
Ultimate tensile lI ...ngth Elongation,
Stroln
MPa
1<51
%
10 fracture
Primary« 725°C (1330oF)20h, WQ + 500°C(930 oF)1h (salt) 725 °C(1330°F) 100min, WQ+370°C (700°F) 103 min 780°C (1435°F)3h, WQ + 500°C (930°F) 1h(salt) 780°C (1435°F)3h, WQ+500°C (930°F) 1 hfair) 850°C (1560oF)2h, WQ+ 500°C (930oF)4h (salt)
30%primarya +largesecondary a 30%primary a + smallsecondary a 10%primarya + largesecondary a 10%primarya +smallsecondary a 0% primarya + grainboundary a + largesecondary a
1063 1246 1202 1445 1250
154 181 174 209 181
1106 1419 1247 1544 1308
160 206 181 224 190
17.7 7.6 10.3 2.4 3.9
0.99 0.19 0.63 0.09 0.16
Elongated primary « 700°C (1290oF)8 h, WQ+ 200°C (390oF)6800min 850°C (1560oF)2h, WQ+ 500°C (930oF)4 h (salt) 760 °C(l4OOoF)75 min, WQ+ 500°C(930oF)1h (salt) 700°C (1290oF)75min,WQ+ 350°C (660 oF)103 min
35%primarya + OJ 0% primarya + largesecondary« + grainboundary a -10% primarya + largesecondary a -30% primarya + smallsecondaryn
1218 1182 1298 1239
176 171 188 180
1266 1265 1381 1395
184 183 200 202
0.5 3.8 4.6 3.9
0.02 0.17 0.23 0.11
Ti-10V-2Fe-3AI: ITT diagram. Solutiontreatedat 860°C (1580 OF) for 240 s OTA, differential thermalanalysis 900
1600
LIVE GRAPH Click here to view 800
_
f3transus 5% a
790°C (420 OF)
•
700 oU
1400
•
o
u.
o
1200
i:J
ei 600 l'l.
(!!.
500
i
.a
,e!
o
Ms 555 °c
E
0
Q)
Q.
-Ii-
E
-0---6-
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400 f3 +
OJ +
o
martensite
-
.
800
300L.-_--L_........................................I-_ _.............--L--r......................_ _........--'_......................"""-'-_ _........_ .............................olo..I.J600 100 1000 10000 10 100000 Time, s
570 I Heat Treater's Guide: Nonferrous Alloys Ti-1 OV-2Fe-3AI: Thermomechanical processing route for forgings Forging processCH) Block
Finish
'Thnslle yield strength
AgIng
Solution beal trealmenl(h)
Reduction ofarea,
Ultimate tensile
Fradure
\O!,Jme.. (K~ MPH~ ksilD.
Quenching
lempemlUre(c), ·C
MPH
ksi
strength MPH ksi
WQ WQ WQ WQ AC!WQ WQ WQ
510 510 510 510 495 540 580
1296 1158 1179 1268 1213 1048 990
188 168 171 184 176 152 143
1365 1269 1317 1413 1268 1144 1049
198 184 191 205 184 166 152
10 6 3 2 7 11 14
28 18 6 5 10 24 33
25 32 46 43 51 73 99
22 29 42 39 46 66 90
WQ WQ
485 485 485 485 485 485 485 485 485 485 485 485 540 540 590 590
1158 1220 1172 1193 1144 1144 1199 1158 1207 1227 1193 1240 1034 1069 938 958
168 177 170 173 166 166 174 168 175 178 173 180 150 155 136 139
1269 1316 1269 1289 1254 1260 1330 1248 1351 1365 1303 1372 1131 1138 1027 1006
184 191 184 187 182 183 193 181 196 198 189 199 164 165 149 146
7 8 8 8 9 9 10 13 11 9 13 13 9 7 16 16
15 19 23 16 21
51 46 55 46 55 64 48 55 57 48 52 56 66 68 90 89
46 42 50 42 50 58 43 50 52 43 47 51 60 62 82 81
Conventional closed die forgings Single alP alP Single alP P Single alP II Single P P Duplex alP P Single alP II Single alP II Hot die/isothermal forging Single P
(f)
WQ AC (f)
WQ AC (f)
WQ AC (f)
WQ (f)
WQ (f)
Elongation, %
%
20
26 28 22 21 30 34 31 27 53 52
(a) Block is the initialprocess;finish is the finalprocess in closeddie forging.(b)Single:Solutiontreatmentat IItransus30°C plus quench.Duplex:Solutionannealat p transus25°C, ACprior to solution treatment. (c) 8-haging treatment.(d) Metaltemperature. (e)Die temperature. (f) Controlledcoolingrate plusdirectaging
Ti-1 OV-2Fe-3AI: Effect of forging conditions on Rockwell hardness Forging temperature OF -c 954 871 788 760 732 954 704 871 677 788 643 760 732 704 677 643
1750 1600 1450 1400 1350 1750 1300 1600 1250 1450 1190 1400 1350 1300 1250 1190
Forging speed
Calculated now stress
Hardness,
mmfmin
in.fmin
HRC
MPH
ksi
0.75 0.75 0.75 0.75 0.75 75 0.75 75 0.75 75 0.75 75 75 75 75 75
0.03 0.03 0.03 0.Q3 0.03 3.00 0.03 3.00 0.03 3.00 0.03 3.00 3.00 3.00 3.00 3.00
32.2 3\.6 32.1 33.0 34.3 32.1 33.7 3\.8 34.1 34.5 33.8 35.6 35.9 35.9 37.0 40.7
18 30 35 50 67 74 88 110 109 133 139 165 199 233 269 312
2.6 4.3 5.1 7.2 9.8 10.7 12.7 16.0 15.9 19.3 20.2 23.9 28.8 33.8 39.0 45.2
Note: Hardnessmeasurements for alloyforgedisothermallyto 0.50 nunlrnm (inlin.) (nominal)at variousconditions;mean grain diameter,255 11m. Composition,2.95%AI, 0.008%C, \.90% Fe, 0.051% H, 0.020%N, 0.116% 0, 10.10%V, 0.08% other total.Materialwas obtainedfromTitaniumMetalsCorporationof Americafroma singleheatof?5 cm (3 in.)diambar.Hardnesswas determinedfor eachringspecimenforgedtoO.50in.!in.(nominal)at each temperature andspeedindicated.Measurements weremade at randomlocationswith at least ten measurements per specimen. Surfaceswerepreparedby grindingandetching;finalpolishingwas donewith4OO-grit siliconcarbide paper
Stressrelief Beta Solutiontreatingrange Agingrange Overage
'ThmpemlUre
LIVE GRAPH
Click here to view 500 450
> J:
°C
OF
min
Cooling method(h)
657-700(a) 1500 730-775 480-62O(b) 580-620
1250-1300(a) 815 1325-1425 900-1100(b) 1075-1150
0.5-2
Air or slowcool
1 8 8
WQ AC AC
Time,
(a)Agingat 480°C (900 "F) andabovealsoeffectivelystressrelieves.(b)Aging temperature should beatleast475 °C (885 oF) toavoidformationofro phase.Forhigh to intermediate strength,themost usefulaging temperatures are480 to 540°C (900 to 1000 "F), respectively
400
vi
IIIc: ~ 350
J:
Ti-1 OV-2Fe-3AI: Typical heat treatments Heat Treatment
Ti-10V-2Fe-3AI: Effect of aging on Vickers hardness. Hardness as a function of aging time at various temperatures for solution treated alloy processed at 780 °C (1435 OF), 2 h, water quenched. Alloy was supplied in the form of round bars, 18 mm (0.7 in.) in diameter. a. + ~ forged. Chemical composition: 3.20 wt% AI, 0.041 wt% C, 1.98 wt% Fe, 0.0125 wt% N, 0.1480 wt% 0, and 10.24 wt% V. Microstructure in the as-received condition was fully recrystallized, with globular a. in a ~ matrix. The transformation temperature, microscopically determined, was 830 + 10°C (1525 + 18 OF). Specimens were solution treated below the ~ transus temperature, at 780°C (1435 OF) for 2 h and water quenched. Isothermal aging treatments were performed in salt baths or in an air furnace on cylindrical blanks 14 mm (0.55 in.) in diameter. Age hardening response of the alloy was observed by means of Vickers hardness measurements
• • 525°C (975 OF)
10-1 1 Aging time, days
10
Beta and Near-Beta Alloys I 571
LIVE GRAPH Click here to view
Ti-10V-2Fe-3AI: TTT diagramfor /3-solution treatedalloy. Qualitative diagram illustrating the competition between nucleation regimes 900
1600 I3transus
Grain bounda
800 700
.u
/
/
i:::l 600
IX
Sympathetic IX start
start
~
1400 Sympathetic IX tinish
1200.IL
i
.a
/
~ Q)
1000 ~ Q. E
~500
Q)
i
l-
800
Transition
400 ~
'--300
Uniform
---
Unifonn _00
200 0.1
100
10
IX
IX
~
finish
600
start
start (approximate)
1000
400 100000
10000
Time,min
Ti-10V-2Fe-3AI: Effectof H2 concentration on yield strength.
800
The base hydrogen level was 0.2 at.% (40 ppm). Additional hydrogen was introduced into the test material with the use of a Sievert's apparatus at temperatures ranging from 765 to 800 DC (1410 to 1470 OF). No appreciable difference in /3 grain size was detected due to varying the hydrogen charging temperature within this range. Hydrogen levels greater than 29 at.% were obtained by this method (although not for each microstructure). Sievert's charging was done prior to heat treating to establish the desired microstructure
100 OJ
600
a.
80
g>4oo I!!
60
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1ii
1ii
0
"0
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0
200
"0
~ 0
Qj
40
>=
0
20
LIVE GRAPH 0 10
0
Click here to view
0 30
20
Hydrogen concentration, at.%
Ti-10V-2Fe-3AI: Effect of solution treatment on tensile properties. Typical properties after solution treating for 8 h at various temperatures and aging at 500 DC (930 OF) for 60 min
Ti-10V-2Fe-3AI: Effect of aging on UTS. All specimens were solution treated at 750 DC (1380 OF) followed by water quenching. Aging time was 8 h LIVE GRAPH Click here to view Aging temperature, OF
Solution treatmenltemperature, OF
850 1400
13OO1~1~1~1~1~01~1~14M
1600 1500
70
LIVE GRAPH
60
Click here to view
0
o:
..
40 30
EL .---.-.
1000
10
900L 700
20
-:....._ _.:::::.===~0 720
740
760
780
Solution treatment temperature,
°c
800
950
1000
1050
1100 200
OJ
190
~ 1300
50 UTS TVS RA
900
~ 0-
.~
~
Cl
t
~ 1200
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1100
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150
o
1000
140
o
900L..450
-'500
550
Aging temperature,
°c
----' 600
~
:s
572/ Heat Treater's Guide: Nonferrous Alloys
Ti-10V-2Fe-3AI: Microstructure. Deformed at 1150 °C (2100 OF). (a) demonstrates the as-deformed structure that has been heavily etched. Specimen was recrystallized at 925°C (1695 OF) for 1 h in a vacuum of 10-lltorr. Recrystallization caused thermal etching of the recrystallized grains. (b) shows recrystallized structure. Prior unrecrystallized structure can still be observed as ghost boundaries remnant from the initial overetching. (a): 60 mLHp,40 mLHNOa, 10 mLHFfor30min. (b): 60 mLHp,40mLHNOa, 10 mLHFfor30 min + thermally etched at 925°C (1700 OF) for 1 h in vacuum (10-lltorr). Magnification not known
(a)
(b)
Ti..13V..11Cr..3AI Common Name. Ti-13-11-3 UNS Number. R58010 Chemical Composition. As a solute-rich beta alloy, Ti-13-11-3 contains a relatively large amount of beta-stabilizer elements and relatively small amounts of alpha-stabilizer elements. At the nominal composition, Ti-13V-3Al base plus 11 percent chromium and low oxygen content, the alloy is hypoeutectoidal. The high vanadium content contributes to the stabilization of the beta phase, but it does not contribute to the titaniumchromium eutectoid relationship. See Tables for specifications and for commercial compositions
Characteristics Phases and Structures. Strengthening of Ti-13V-llCr-3Al occurs from the precipitation of TiCr2 and ex in solute-lean 13 regions (W). As might be expected, long periods at solution treatment temperatures result in undesirable grain growth and the associated breakdown of favorable nucleation sites for strengthening precipitates Beta Transus. At nominal alloying concentrations and commercialgrade oxygen contents of 0.15 wt% 02, Ti-13V-llCr-3Al has a 13 transus of about 700°C (1300 OF). For lower oxygen concentrations (0.05 wt%), the 13 transus is lowered to about 650°C (1220 OF) Transformation Products. Normal air cooling from above the 13 transus retains a room-temperature 13 structure that is metastable. However, because the decomposition of metastable 13 is so sluggish in this solute-rich f3 alloy, decomposition of 13 below about 315°C (600 "F) is essentially nonexistent for practical purposes. Deformation can accelerate the decomposition of 13, however. See Figure for phase diagram with variable chromium content, for phase diagram with variable aluminum content, and for TTT diagram
Product Forms. Current usage is confined to some sheet metal airframe parts and for springs. Wrought forms include billet, bar, plate, sheet, and wire. For several years, Ti-13-11-3 was the only beta alloy of commercial significance. Its decline came with the advent of such alloys at Ti-I-2-3, Ti-15-3, and Beta C Applications. Ti-13-11-3, also known as BI20VCA, is suitable for operation in the range from -54 to +315 °C (-65 to +600 "F) and higher in certain uses. It has good ductility for ease of fabrication. When aged, it can be hardened to extremely high strength levels. Its high strength and low density make one of the most efficient structural materials available. It was used for airborne structures that must live in temperatures up to 650°C (1200 OF) for short periods and for lightweight pressure vessels that operate at temperatures of -54 to +315 °C (-65 to +600 "F), As a high-strength fastener material it has cold headability and shear strengths over 825 MPa (120 ksi). The alloy is cold rollable; and can be solution treated without distortion because it can be air cooled. It is highly ductile in the solution-treated condition and can be severely cold worked without intermittent annealing. It has little directionality in sheet and strip, low scratch sensitivity, and a relatively high tolerance for hydrogen Chemical/Corrosion Properties. The chemical reactivity of Ti-13V11Cr-3Al is fairly typical of titanium alloys. In either the solution treated or aged condition, it resists corrosion in seawater, salt, other natural environments, oxidizing media, inhibited reducing acids, alkalies, and metallic chlorides at room temperature. In salt-spray tests, aged Ti-13V-11Cr-3Al exhibits no pitting and experiences no general corrosion or degradation in mechanical properties. Its corrosion resistance in reducing environments appears to be less than other titanium alloys. In hot air, however, the alloy does not appear to discolor and scale
Beta and Near-Beta Alloys I 573 as badly as other titanium alloys at temperatures 260 to 315°C (500 to 600
case from heating operations than other alloy classes, control of chemical removal processes is essential to preclude excessive hydrogen pick up.
Stress Corrosion Cracking. Like most titanium alloys, Ti-13V-llCr3Al can be fairly resistant to aqueous halide stress-corrosion cracking (SCC) when used in its standard metallurgical condition. However, stepcooled Ti-13V-llCr-3Al is highly susceptible to SCC in neutral salt solutions, in that loading of smooth samples can show cracking susceptibility.
See Figure for forging pressures
oF)
In /3 titanium alloys, the /3 phase may be susceptible to either transgranular or intergranular see in aqueous media, depending on alloy composition and microstructure. Intergranular cracking has only been observed in a few aged /3 alloys, particularly with fme a precipitates formed at lower aging temperatures. See Table for environments known to promote cracking
Mechanical Properties
Typical Tensile Properties. See Tables for room temperature tensile properties of forged and heat treated bars, and for effect of cold work on tensile properties of solution treated and aged sheet
Fabrication Properties Forging. Ti-13-11-3 is a very high strength, metastable /3 alloy. The alloy can be fabricated into all forging product types, although closed die forgings predominate. All types of forging equipment are used.
Ti-13-11-3: Forging process temperatures
Belaforge
Ti-13-11-3 in the solution treated condition is more amenable to cold forming than any other of the high-strength titanium alloys. It also has good cold heading properties. In severe cold forming, such as spinning or deep drawing, intermediate anneals may be advisable. Forming by all conventional methods is possible.
Hardness. See Tables for Knoop and Rockwell hardness of unwelded sheet and single bead welded sheet, and for Vickers hardness ofweldments subjected to different treatments. See Figure for Rockwell hardness vs. aging time and for Rockwell hardness vs. reduction in area at room temperature
Process
Forming. The alloy normally is fabricated to flat rolled products in the /3-phase temperature field. However, the fmal fabrication of sheet by rolling to finish gages is often done cold to obtain improved flatness and gage uniformity. Similarly, in the production of rod and wire products aimed at spring manufacture, initial fabrication at elevated temperatures may be followed by cold working to improve the finished surface and the mechanical properties of the finished product.
-c 650-955
Metal temperature
OF
1200-1750
Ti-13-11-3 is a moderately forgeable alloy (above the /3 transus), with higher unit pressures (flow stresses), improved forgeability, and less crack sensitivity in forging than the a-/3 alloy Ti-6Al-4V. Due to the high alloying content ofTi-13-11-3, its flow stresses are among the highest of commonly forged titanium alloys, more than double that of the near-B alloy Ti-lOV2Fe-3Al. The desired final microstructure is transformed /3 with a fine recrystallized prior /3 grain size in preparation for final thermal treatments. Ti-13-11-3 is typically forged above its transus through one or more forging operations. Reheating for subsequent forging operations recrystallizes the alloy, thus refining prior beta grain size. Ti-13-11-3 may be subtransus (a + /3) forged in final stages, with a significant increase in unit pressure requirements Final Thermal Treatments. Treatments include solution treatment annealing and aging. Forgings may be supplied in the solution treatment annealed (ST) condition and/or fully aged (STA). In the solution treatment annealed condition, Ti-13-11-3 has lower strengths but much higher ductility and toughness than in the STA condition. Solution treatment is at 775 °C (1425 "F), followed by air cooling. Aging is at 425 to 480°C (795 to 900 OF) Beta Forging Working. Ti-13-11-3 requires hot work sufficient to reach final macrostructure and microstructure objectives. Generally, reductions in any given forging process are 30 to 50% to achieve desired dynamic and static recrystallization. Very low levels of /3 reduction are not recommended. Although Ti-13-11-3 is cold worked in other product forms (sheet), forgings are not cold worked Surface Treatment. Ti-13-11-3, as with all /3 alloys, has a higher affinity for hydrogen than other alloy classes. Although Ti-13-11-3 forms less a
See Table for hot forming temperatures in treating annealed or solution treated material Welding. Much of the available data on stress relief annealing pertains to weldments. Fusion weldments in 6.4 mm (0.250 in.) plate are reported to be stress relieved to zero residual stress levels by any of the following treatments: • • • •
4 h at 480°C (900 OF), AC 1 h at 540°C (1000 OF), AC <30 min at 595°C (1100 oF), AC . <30 min at 650°C (1200 oF), AC
A 285°C (550 OF) preheat may also reduce residual tensile stresses in weldments. It has been reported that 15 min at 760°C (1400 "F) or 5 min at 980 °C (1795 OF) results in weld embrittlement (R.A. Wood, Beta Titanium Alloys, Battelle Columbus Laboratories, 1972, p 26)
Recommended Heat Treating Practice High strength can be achieved by solution treating and aging. Strength and ductility combinations from aging and the rate of aging depend on the processing history of the metal being heat treated. Optimum aged properties are obtained when the prior history of the metal is such that it creates a favorable nucleation distribution. Therefore, some residual strain energy should promote aging response. Cold working or warm working can be used to achieve the residual strain required. Residual strain energy accelerates the aging reaction and imparts somewhat better ductility for some strength levels Solution Heat Treating. Within the broad solution treatment range of 705 to 1035 °C (1300 to 1895 OF), there is little change in aging response. However, long periods at solution temperatures degrade ductility, presumably from grain growth and the breakdown of nucleation site distribution. Water quenching from the solution heat treatment temperature does not offer a significant advantage over air cooling, except where it might aid in removing heat from thick sections. See Tables for solution treating and aging practice, and for stress relief and annealing treatments. See Figures for: • • • •
Aging response variations (a) and (b) Grain size at solution temperatures Effect of solution treatment on hardness Effect of working on aging (a) and (b)
Ti-13V-ll Cr-3AI: Knoop and Rockwell hardness Condition
Unwe1ded sheet,965 MPa (140 ksi) urs Single-bead weld,950MPa (138ksi) urs
Knoop hardness
RockwellC hardness
300
30.6 30.1
320
574/ Heat Treater's Guide: Nonferrous Alloys
Ti-13V-llCr-3AI: Specifications Composition, wt% Specification
Designation
UNS Russia
R5S010
3
11
13
balTI
IMP-lO
3
11
13
balTI
Spain UNE3S-729 UNE3S-729 USA AMS4917D AMS4917D AMS4959B AWSA5.16-70 MlLF-S3142A MlLF-S3142A MlLT-9046J MlLT-9046J MlLT-9407G MlLT-9047G
Des
L-710I £.-7701
ERIi-13V-11Cr-3Al Compl2 Comp12 CodeB-1 ClxleB-l TI-13V-llCr-3AI TI-13V-llCr-3Al
C
AI
Cr
Fe
H
N
Other
V
0
sliStrPit WrrBar Ann Sh Strp Pit WrrBarHf
2.5-3.5 2.5-3.5
0.05 0.05
10-12 10-12
0.35 0.35
0.02 0.02
0.05 0.05
O.IS O.IS
12.5-14.5 12.5-14.5
OTO.4;bal TI OTO.4; balTI
ShSlrPltSHf Sh Str Pit STA
2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5 2.5-3.5
0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05
10-12 10-12 10-12 10-12 10-12 10-12 10-12 10-12 10-12 10-12
0.35 0.35 0.35 0.25 0.35 0.35 0.15-0.35 0.15-0.35 0.35 0.35
0.D25 0.025 0.03 O.OOS 0.025 0.025 0.025 0.D25 0.025 0.025
0.05 0.05 0.05 0.03 0.05 0.05 0.05 0.05 0.05 0.05
0.17 0.17 0.17 0.12 0.17 0.17 0.17 0.17 0.17 0.17
12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5 12.5-14.5
OTOA; balTI OTOA; bal TI
WlfRod FrgAnn FrgHf Sh Str Pit SHf ShStrPltSTA BarBilSHf Bar Bil S'D\
OTO.4;Y0.005; balTI balTI OTO.4;balTI OTOA; balTI OTOA; balTI OTO.4;balTI OTOA; YO.005;balTI OTO.4; YO.005;balTI
Ti-13V-ll Cr-3AI:Commercial compositions Composition, % Specification
Designation
Description
KS13-11-3 KS13-11-3
BarFrgSHT BarFrgSTA
2.5-3.5 2.5-3.5
TI-13V-llCr-3Al 13V-11Cr-3Al Tel-TI-13V-llCr-3Al TIMETAL13-11-3
BarBilSprg
2.5-3.5"
log PItSh Sir STA
2.5-3.5
Other
Cr
Fe
H
N
0
V
10-12 10-12
0.35 0.35
0.025 0.025
0.05 0.05
0.17 0.17
12.5-14.5 12.5-14.5
balTI balTI
0.05 max
10-12
0.35 max
0.025
0.05 max
0.17
12.5-14.5
balTI
0.05
10-12
0.35
0.025
0.05
0.17
12.5-14.5
balTI
C
AI
Japan Kobe Kobe USA Astro RMI Teledyne Timet
Ti-13-11-3: Hot forming temperatures for annealed or solution treated material Fonnlngtemperature Alloy CPTI (allgrades)
°C
OF
4S0-705
900-1300
790± 15 620-S15
1450±25 1150-1500
790± 15
1450±25
605-790
1125-1450
aand near-aalloys TI-SAI-IV-IMo TI-5AI-2.5Sn a-~alloys
Ti-6AI·6V-2Sn /Jalloy TI-13V-11Cr-3Al
Ti·13-11-3: Stress relief and annealing treatments Thmperature 1reatment Interstage annea1 ofsheet after severe defonnation Stressreliefof ST stock Typicalstressrelief Typicalanneal
Duration,
°C
OF
730-760
1350-1400
54O(a) 700-7S5(b)
looo(a) 1300-145O(b) Sarneas solution treatment
min
Ti-13V-llCr-3AI: Environments known to promote cracking Environment
Medium
Temperature OC OF
Organic compounds Methyl alcohol(anhydrous)
RT
RT
370 790
700 1455
Methylchloroform Trichlorofluoroethane Salts Chlorideand otherhalide salts/residues SeawaterlNaCI solution
230430 RT
Othertitaniumalloys with known suoceptihility
TI-6Al4V, Gr.2Ti, Gr.4Ti, TI-4Al-3Mo-IV, Ti-SV-3Al-6Cr4Zr4Mo (Beta C), Ti-SAlIMo-I V,Ti-5Al-2.5Sn Ti-SAl-IMo-IV, TI-6Al4V, TI-5Al-2.5Sn Ti-SAl-IMo-IV, TI-5Al-2.5Sn, Ti-6Al4V
445-S05 Mostcommercialalloysexcept grade I, 2, 7. 11,12.and9 UnalloyedTI(withoxygencontent>O.3%) RT Ti-2.5Al-IMo-11Sn-5Zr-O.2Si (lM1-679), TI-5Al-2.5Sn, TI-SMn,Ti-6Al4V, Ti-6AI6V-2Sn.TI-6Al-2Nb-1Ta,Ti4Al-3MoIV, Ti-SAI-IMo-IV, Ti-6AI-2Sn4Zr-6Mo
Metal embrittlement Cooling method
Cadmium(solid +liquid) Mercury(liquid)
25·600 370
75-1110 TI-SMn.grade2, TI-6Al4V 700 GrATI,TI-6Al4V. TI-8Al-IMo-IV
AC 15 5-15
AC AC ACorWQ
(a) Stressrelief if aging is not planned; stress reliefcartbe accomplishedduring4S0 °C (900 "P) aging. (b) Stress relieffor materialother than weldments
Ti-13-11-3: Solution treatment and aging Thmperalure OC
OF
Time, h
Cooling method
>760 775-S00
>1400 1425-1475
0.25-1 0.25-1
ACorWQ ACorWC
700-1040 425-540 425-510
1300-1900
0.25-1
SOO-950
20-100
ACorWQ AC AC
Heat
'Ireatmenr
Typicalsolutiontreatment Narrowsolutiontreating range BroadST range Agingrange Typicalage
aoo-iooo
Beta and Near-Beta Alloys I 575
Ti-13V-ll Cr-3AI: RTtensile properties of forged and heat treated bars
Harsize nun In.
150
480 0C (900 OF) aging treatDirection menf.h
6
L
48
T 100
4
48
L
T 75
3
L
48
T 30
L
T 50
2
30
L
30
1.2
20
L
T
Ultimate lensUe strength MPa ksl
'Iensileyield strength (0,2 % offset) MPa ksl
1264 1297 1474 13% 1478 1462 1438 1407 1368 1340 1424
1153 1169 1388 1307 1369 1364 1341 1288 1241 1232 1290
183.3 188.1 213.9 202.5 214.4 212.1 208.6 204.1 198.5 194.4 206.6
Ti-13V-ll Cr-3AI: Vickers hardness of weldments Post-weld b..tt ....tment
BasemetaJ
Hardnessla), HV HAZ
Weldzone
280 257 287 265
278 287 291 281
253 315 368 383
Reduction Elongation, ofarea,
167.2 169.6 201.3 189.6 198.6 197.9 194.6 186.9 180.0 178.7 187.2
%
%
8.0 8.0 4.0 4.0 6.0 3.0 6.5 5.0 7.0 5.0 10.0
13.7 8.5 11.6 12.4 9.3 6.2 8.5 12.0 10.0 12.0 15.8
As welded Weld + 2h 315°C (600°F) Weld+4h 315°C (600°F) Weld + 8 h 315°C (600 oF)
(a) Spot weldingcharacteristics were investigated by hardnesstestinga cross sectionof the weld nugget.The hardnesssurveyindicatedthatdecomposition takesplaceaftershort-termthermal exposureat 315°C (600 "F), Increasein hardnessis confinedto theweldmetal.(a 15Q.g load)
Ti-13V-11Cr-3AI: Phase diagram with variable aluminum content LIVE GRAPH
Centerofbar samples.Barsageddirectlyfromforgingoperation
Click here to view 800 Nominal aluminumcontent
fBeta transus with high oxygeniontent I _
750
Ti-13V-11Cr-3AI: Phase diagram with variable chromium content LIVE GRAPH Click here to view 800
I
P 700
t IBeta transus with highe
1300
o
i! Q)
c. E Q)
a+(3+TiCr2
0.05wt%02 500L-_-'-_ _L-_-'-_ _' - - _ - ' - _ - l 8
5
6
9
10 11 12 Chromium content, wt%
13
1000
Ti-13V-11Cr-3AI: Rockwell hardness vs. aging time. The rapid increase in hardness that follows the initial stages of aging occurs at times corresponding to the appearance of the ex phase. Strips from sheet were vacuum annealed at 850°C (1560 OF) for about 4 h and cold rolled to a thickness of0.4 mm (0.015 in.). Coupons were prepared from rolled material and solution treated at 800°C (1470 OF) for 90 min in purified helium, then quenched in water, oil or air. Several coupons were solution treated at 900 °C (1650 OF) and water quenched. Aging was done in salt baths held at 250 to 500°C (480 to 930 OF) to 1000 h
14
Ti-13V-11Cr-3AI: TTl diagram
LIVE GRAPH Click here to view 800
60 1400 Beta transus te'!!R-erature ~ -
I
~
1300 U
so
II:
1100 @ :J
~ 500 \ As solution trea
~"
55
1200 ~
(3/ ---
I
400
2 3 4 Aluminum content, w1%
1100 f-
550
Q)
1000
500L.-_-'-_---I._ _...L-_---''--_-'-_---'
2F
Q)
e
1100 f-
0.05w10/0°2
!I:::>
1200
c. E ~ 600
~600
1200 f! Q) c. E Q)
a+ (3 + TICr2
oxygen content
:::>
U
i
a
~ 650
1400
i! 650
700
1300 !l-
~ 600
---- - -l _//
2F
--+~
P 700 i:::>
aE
Nominal chromium content
750
1400
-,
1000 d 900
--... ...;::: As solulion treated "<, ,+ 25% cold worked 10
Time, h
~
I
iii
LIVE GRAPH Click here to view
~400°C(7S0°F)
---+--450 °C (840 OF) --o--SOO °C (930 OF)
45
III
Q)
o
-640
l-
I
~
--300°C (570 OF) --+--350 °C (660 OF)
iii
35
30 2
10
10
100 Aging time, h
1000
Next Page 576/ Heat Treater's Guide: Nonferrous Alloys
Ti-13-11-3: Grain size at solution temperatures
Ti-13V-llCr-3AI: Rockwell hardness vs. reduction of area at room temperature 50
Shear formed
•
'"
E E .:
~40
650·C 760·C 870·C 980·C
D 0
~
0
Iii
.J:)
0.03 E
:::l
c
01 N
'iii
01
J: ui
LIVE GRAPH
01
Click here to view
III C
E ;:;
'c"
'"
'"
'e!
Cl
c
c
'E"
01
::l;
01
Cl
ST Reduced + age 480 ·C (900 ·F), 24 h, AC Reduced + ST 770·C (1425 ·F), AC + age 480 ·C (900 ·F), 24 h, AC
0
0.02
0.1
'e!
"E
J: 30
c
'"
0.01 I-
::l;
!fl
LIVE GRAPH Click here to view
20
0.01 25
0
75
50
0
256
Reduction, %
Tlme,min
Ti-13-11-3: Aging response variations. Effect of aging time on the longitudinal tensile properties of sheet 30
1600 '" 15001-----+---'
425 DC
n, ::l;
£ 14001-----+----;-"~M---I\___:::!<,..__'i9rl_\~.-->....Linoo C,
~
540 ~C aging
1300
III
~
s01
!
~
180
.~ 1200
160
0 \
5 1000j--,l"Y-"c---+~--+-425 ~ a Ino----I 25
50 Aging time, h
~
75
140
Cold
U1limaletensile
Thll'lileyield
sIre'Wh
%
MPa
ksi
s1rength (0.2 %l MPa lis!
0 10 20 30 40 50
924 1013 1117 1206 1289 1372 1434 1489 1537
134 147 162 175 187 199 208 216 223
903 951 1013 1103 1193 1268 1337 1399 1482
60 70 80
131 138 147 160 173 184 194 203 215
o'-o
100
-'--25
_
Elongation in50mm(2ln.l,
Reduction ofarea,
%
%
25 17 12 8 6 6 5 4 2
50 42 36 32 28 25 22 22 16
_
........
0
........
50 Aging time, h
LIVE GRAPH
Ti-13V-ll Cr-3AI: Effectof cold work on tensile properties of STA sheet reduction,
o _
i
Click here to view
(a)
540 DC
~ ~
595°C aging 1100
ic
100
75
LIVE GRAPH Click here to view
(b)
Ti~13-11-3:
Effect of solution temperature on hardness. Effect of solution temperature on the annealed and annealed plus 480 °C (900 OF) aged Vickers hardness. Hardnesses shown are averages of five impressions, using a 5-kg load
LIVE GRAPH
1000
Solution temperature, OF 1400 1600 1800 2000
1200
II
I"
II •
>
J: 400 ui III
01
C
~ 350
J:
, .-- I II
Beta transus 720°C
,
./
0
250 500
rl
~
Solution,treated plus aged 100 h at 480°C
I 300
2200
I
500
450
Click here to view
I
-/
t
/
.
Solution treated only, 30 min 700 900 1100 Solution temperature, °c
1300
Previous Page Beta and Near-Beta Alloys I 577
Ti-13-11-3: Effect of working on aging. Effect of warm and cold rolling on longitudinal aged tensile properties
~J
1600 Aging at 480 DC
os 1500 ll.
--- ---
;'
::E £ 1400 0, c ~ 1300
/
•
s
Ql
~ 1100
/
.1.
.I
30 Aging at
220 I
-.-'
"'"
..-- ..---.
V
y
<,
c
~
180
, t--..
8
16
24
32
40
48
Aging lime, h
140
(a)
56
64
o o
72
LIVE GRAPH Click here to view
rolled 20% at 760 DC
-
/~
900
o
~ '-...., war~ .- . / V--f-- - ---plus aged
~
5
jnneatd PI,S agjd
DC,
Annealed plus aged
£ 2000,
/ v Wa~ rOIl,~d 20% at 760 DC $~ 60 ~ r-, plus red I 1
V
jO
~
Cold rolled plus aged
"'-
.91 .~ 1200
5"" 1000
I,
-1 1
-r 8
rOlljd
16
-
r--<
-
-
i--
PIUj age1 24
32
40
Aging lime, h
(b)
48
56
64
72
LIVE GRAPH Click here to view
Ti·15V·3Cr·3AI·3Sn Common Name. Ti-15-3 UNS Number. Unassigned Chemical Composition. See Tables for specifications and compositions, and for commercial compositions. Ti-15-3 is formulated by depressing the beta transus with vanadium and chromium additions. It is less beta-stabilized than Ti-13V-ll Cr-3AI
Characteristics Phases and Structures. Ti-15-3 can retain an all-beta structure with sufficiently rapid cooling (e.g., air cooling of a 6.5-mrn thick section from the p field). Subsequent aging produces a fine a phase, which is very difficult to resolve optically as it is extremely fine Beta Transus. 750 to 770 DC (1380 to 1420 oF) See Figure for annealing time vs. recrystallized grain size Transformation Products. As a solute-rich p alloy, Ti-15-3 undergoes a phase separation into a solute-rich phase (P) and a solute-lean phase (P,) prior to the formation of uniform, needle-like a within the W. This uniformly dispersed a provides strengthening, but its formation requires longer aging times because of slower nucleation kinetics (compared to solute-lean p alloys). The refinement of the size and spacing of a precipitates can be achieved by minimizing the amount of recovery and recrystallization after deformation. Stored energy (deformation) alters the aging kinetics of uniform a and generally produces a finer precipitate. An accelerated rate of intragranular a formation also reduces the extent of grain boundary a formation. Like other solute-rich palloys, Ti-15-3 is also susceptible to the formation of grain boundary a. The tendency to form grain boundary a is more pronounced because the nucleation kinetics of grain boundary a is not as solute sensitive as the kinetics of homogeneous 0: precipitation Product Forms. They include ingot, billet, plate, sheet, strip, seamless tubing, castings, and welded tubing
Applications. Ti-15-3 is used primarily as sheet metal applications because it is strip-producible, age-hardenable, and highly cold-formable. It is used in a variety of airframe applications, in many cases replacing hotformed Ti-6AI-4V. Ti-15-3 can also be produced as foil, is an excellent casting alloy, and has also been evaluated for aerospace tankage applications, high-strength hydraulic tubing, and fasteners, High strength castings are in use Use Limitations. Ti-15-3, like other beta titanium alloys, is highly susceptible to hydrogen pickup and rapid hydrogen diffusion during heating, pickling, and chemical milling. However, because of the much higher solubility of hydrogen in the beta phase than in the alpha phase of titanium, this alloy has a higher tolerance to hydrogen embrittlement than the alpha or alpha-beta alloys Corrosion Properties. Ti-15-3 tolerates mildly reducing to highly oxidizing environments in which protective oxide films spontaneously form and remain stable. On the other hand, hot, concentrated, low-pH chloride salts corrode titanium; warm or concentrated solutions of hydrochloric, phosphoric and oxalic acids also are damaging. In general, all acidic solutions that are reducing in nature corrode titanium, unless they contain inhibitors. Strong oxidizers, including anhydrous red fuming nitric acid and 90% hydrogen peroxide, also cause attack. Ionizable fluoride compounds, such as sodium fluoride and hydrogen fluoride, activate the surface and can cause rapid corrosion. Dry chlorine gas is especially harmful Stress Corrosion Cracking. Ti-15-3 is expected to be less susceptible to stress-corrosion cracking (SCC) than Ti-6AI-4V due to its high vanadium content and lower aluminum content. A p phase stabilized by vanadium (or molybdenum, niobium, or tantalum) is immune to SCC in aqueous media. (R. Schutz, Stress-Corrosion Cracking of Titanium Alloys, in Stress-Corrosion Cracking: Materials Performance and Evaluation, ASM International, 1992)
Mechanical Properties Hardness. See Tables for effect of warm work-extrusion on Rockwell hardness, for effect of heat treatment on Knoop hardness, and for the effect of aging time on hardness
578/ Heat Treater's Guide: Nonferrous Alloys Tensile Properties. Ti-15-3 sheet can be aged to a tensile strength of at least 1310 MPa (190 ksi) while guaranteeing ductility in excess of 5%. Between aging temperatures of 510 and 540°C (950 and 1000 OF), fully aged strength is a linear function of aging temperature. Aging at 455 to 480 °C (850 to 900 "F) would be recommended only in those situations requiring the highest possible strength and where ductility is of lesser importance.
tructural features of Ti-15-3 achieved in forgings are responsible for its excellent strength, corrosion, and fatigue properties. Thus, Ti-15-3 is typically forged above the ~ transus through one or more forgings operations. Reheating for subsequent forging operations recrystallizes the alloy, thus refining prior ~ grain size. Ti-15-3 is generally not subtransus (ex + ~) forged, because there is no microstructural advantage and there is a significant increase in unit pressure requirements.
For the aged condition, cold deformation of up to at least 40% does not significantly affect the relationship between aged strength and ductility.
Ti-15-3: Forging process temperatures
See Table for tensile properties vs. aging temperature. See Figures for typical aging curves for sheet, and for effect of prior cold work on aging
Process
Annealed Tensile Properties. Typical variations of tensile properties in the annealed condition are from test direction and lot-to-lot differences, the latter being larger. Sample location within a coil is oflittle consequence. Test direction differences typically are small, but can amount to 30 MPa (4 ksi); the lot-to-lot difference can be up to about twice as much. These values are small, however, when compared with unalloyed titanium strip or ex-~ alloy sheet. Cold deformation over the range of 20 to 60% has an approximately linear effect on strength. See Table for typical annealed tensile properties
Cast Tensile Properties. A study of the tensile properties of various castings and suppliers does not show any significant trends regarding strength as a function of supplier. In general, thicker material exhibits a slightly lower average tensile strength. Ductility, however, does exhibit significant variation from supplier to supplier and as a function of thickness. It should be noted that a material with a higher oxygen content was not associated with higher strength or lower ductility. For more information on study, see (a) and (b) in Figure titled variation in tensile strength
Fabrication Properties Forging. The alloy can be fabricated into all forging product types, although closed die forgings predominate. Ti-15-3 is a moderately forgeable alloy above the ~ transus. Due to the high alloying content, flow stresses are almost double those of the near-B alloy Ti-lOV-2Fe-3AI. The desired final microstructure from thermomechanical processing of Ti-15-3 during forging manufacture is fine transformed ~, with limited grain boundary films and with a fine recrystallized prior ~ grain size in preparation for final thermal treatments. The very fine micros-
Metal temperature
Betaforge Temperaturerelative to transus(a)
-c
OF
790-925 30 to 65 above transus
1450-1700 55 to 120 above transus
(a) Subtransus forging ofTi-15-3 has not been found advantageous due to high unit pressures
Final thermal treatments for forgings include solution annealing and aging. Forgings may be supplied in the solution armealed (ST) condition and/or fully aged (STA). In the ST condition, Ti-15-3 has lower strengths, but much higher ductility and toughness than in the STA condition. Solution treatment is conducted at 785°C (1445 "F), followed by air cooling or equivalent cooling rates. Aging is at 480 to 620°C (900 to 1150 "F)
Beta Forging Working. Ti-15-3 requires hot work sufficient to reach final macrostructure and microstructure objectives. Generally, reductions in any given forging process are 30 to 50% to achieve desired dynamic and static recrystallization. Very low levels of ~ reduction are not recommended. Cold working is not used for forgings. Ti-15-3 may be isothermally or hot die forged. Ti-15-3, as with all ~ alloys, has a higher affinity for hydrogen than other alloy classes. Although Ti-15-3 forms less ex case from heating operations than other alloy classes, control of chemical removal processes is essential to preclude excessive hydrogen pickup. See Table for effect of post-forge heat treatment on properties
Form ing. Ti-15-3 approaches the formability of the higher strength commercial-purity grades of titanium. See Figure for forming limit diagram. See Tables for room temperature formability comparison of annealed alloys, and for typical formability of annealed alloy
Welding. Ti-15-3 can be welded in the solution-treated condition; however, welding is not recommended after solution treating and aging. Care is necessary in pickling to minimize hydrogen absorption. Few published data on the corrosion resistance of weldments are available for most ~ alloys. Under marginal or active conditions (for corrosion rates ~.1O mm/year or 4 mils/year) weldments may experience accelerated corrosion attack relative to the base metal
Ti-15-3: Effect of heat treatment on Knoop hardness Hardness drops below peak values when samples are annealed at higher temperatures.
Recommended Heat Treating Practice
Heat treatment
See Tables for stress relief and solution annealing treatments, and for aging treatments. See Figures for:
Hardness, UK (500 g)
Quenched from 900 °C (1650 oF) Quenched + 300 °C (570 oF), 2.5 h Quenched +345°C (650 oF), 4 h Quenched + 565°C (1045 "F), 3 h
268 474 481 303
• Effect of cold work on strength and ductility • Effect of aging on tensile properties (a) and (b) • Effect of aging on property scatter
Ti-15-3: Specifications and compositions Spe
Desaiptioo
AI
Cr
Fe
H
ShStrpSHT ShStrpSTA
2.5-3.5 2.5-3.5
2.5-3.5 2.5-3.5
0.25 0.25
0,015 0,015
Composition,WI% N 0
So
v
Olber
2.5-3.5 2.5-3.5
14-16 14-16
C 0.05; OTO.4; bal n C 0.05; OTO.4; bal n
USA AMS4914 AMS4914
0.05 0.05
0.13 0.13
Beta and Near-Beta Alloys I 579
Ti-15-3: Commercial compositions Composition, WI% SpeciJication
DesIgoatlon
Description
AI
Cr
Fe
H
N
0
So
V
Other
KSI5-3-3-3 KSI5-3-3-3
PItSh SHT PItSh STA
2.5-3.5 2.5-3.5
2.5-3.5 2.5-3.5
0.25 0.25
O.oI5 O.oI5
0.05 0.05
0.13 0.13
2.5-3.5 2.5-3.5
14-16 14-16
balTi balTi
TIMEfAL 15-3 TIMEfAL 15-3
StrpPitSh FrgSHT StrpPItSh Frg STA
2.5-3.5 2.5-3.5
2.5-3.5 2.5-3.5
0.25 0.25
O.oI5 O.oI5
0.05 0.05
0.13 0.13
2.5-3.5 2.5-3.5
14-16 14-16
balTi balTi
Japan Kobe Kobe USA Timet Timet
Ti-15-3: Tensile properties vs, aging temperature 14-baging temperature 510°C(950 oF) Ultimate tensile strength,MPa (ksi)
Mean(a) 0.99% point Mean(a) 0.99% point Mean(a) 0.66% point
'Iensile yieldstrength,MPa (ksi)
Elongation
S25OC (975oF)
T
T
L
1335(193.6) 1311(190.1) 1245(180.5) 1190(172.6)
1313(190.5) 1276(185.0) 1222(177.2) 1161(168.4)
540OC (1000oF)
L
T
1225 (177.6) 1205(174.7) 1202 (174.3) 1169(169.6) 1126(163.3) 1105(160.2) 1075 (155.9) 1047(151.9) 10.2 8.2
7.8 5.7
L
1114(161.6) 1090(158.1) 1009(146.3) 954 (138.4)
1096(159.0) 1059 (153.6) 987 (143.2) 927 (134.4) 12.6 10.6
(a)Means and percentagepoints calculatedby regression technique.Regresseddata from four lots. Gages: 0.89 to 1.78 mm (0.035 to 0.070 in.)
Ti-15-3: Effect of post-forge heat treatment on properties Port-forge treatment
Thwileyield rtrength ksi MPa
mUmate tensile rtreogtb MPa ksi
STA785°C,AC+51O°C,8h STA785°C, AC + 535°C, 8 h DA51O°C,8h DA535°C,8h
1192 1055 1165 1096
1275 1151 1234 1158
173 153 169 159
FJoogalion,
Reduction ofarea,
%
%
9 II 10 12
22 30 24 32
185 167 179 168
Fracturetoughness ~KI') MPa ksl'Jiii:" 57 61 59 67
52 55 53 61
Crltlcalcmck Iengtb(a) rom
in.
2.5 3.6 2.8 4.1
0.09 0.14 0.11 0.16
Smootb . fatigue(c) MPa ksi
M,,(b) MPa'frii' ksl'liii:"
4.4 4.4
840 810 830 810
4.0 4.0
122 117 120 117
Note: Likemost commercial palloys,Ti-15-3does not respond 10 thermomechanicalprocessingto improve fractureproperties because a morphology is not Significantly modified. (a) Criticalcrack length
~ l.l [KtJYSf (b) Mob is the thresholdstress-intensityin fatigue crack growth rate tests.(c) Smooth fatigue stress at 10 cycles, testsconductedat R = 0.1 to 0.3, F= 30 to 125 Hz
Ti-15-3: Typical formability of annealed alloy
Ti-15-3: Effect of warm work-extrusion on Rockwell hardness Product
bend radius Cup height Draw Flange Stretch Shrink Joggle Ud
2
d/I
hardness, BRA
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Note: Holed extrusionbillets (machinedfrom as-quenchedforging)were coated with lubricant, inductionheated to 595 to 980°C (1100-1800"F), transferredautomaticallyto the press and extruded over a mandrel.The extrusion process was essentially isothermaland was characterized by a slow extrusionspeed (<30 inlrnin) with relativelylow extrusionratios (<20).Extruded tube was cold reduced as indicated
(a) Limit of dies, not of material,(b) Specialprocedurescan improve this significantly
Ti-15-3: Room-temperature formability comparison of annealed alloys
Alloy
Thnsileyield strength MPa ksi
Ti-15-3
758
110
CPTi
275
40
Ti-6AI-4V
827
120
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Minimum Strelcb bend rormlimit, radius % 2.4/ 2.4/ 3.0/ 3.0/ 4.7/ 5.5/
28 20 20 7 7
Hydrofonn limit, % Stretcb Shrink 12 20 12 12 8 8
Ti-15-3: Stress relief and solution annealing treatments Heal treatment
1.0 1.5 1.0
Typicalstressrelief Solutiontreatingrange Typicalsolutiontreatment
°C
OF
TIme, miD
Cooling metbod
650 790-815 790
1200 1450-1500 1450
12 5-30 15
AC AC AC
'Iemperature
580 I Heat Treater's Guide: Nonferrous Alloys
Ti-15-3: Annealing time vs. recrystallized grain size. 80% cold rolled. Unrecrystallized regions were present for annealing times of 1 s and for several samples with grain sizes less than 20
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Beta and Near-Beta Alloys I 581
Ti·15·3: Variation in tensile strength. Castingsweresuppliedby TiTech, Howmet, liline, and Precision Castpartsfromthe UnitedStates. and from lital in Germany. The compositions were within the requirements of AMS 4914 for Ti-15-3 sheet except for oxygen. The oxygen content rangedas high as 0.1645wt% (the specification maximum is 0.13%). Sources are identified randomlyas SourcesA through E The startingmaterialwas selectedwith a rangeof sectionsizes and consistedof roundcast test bars from 12.7to 25.4 mm (0.5 to 1 in.) in diam, rectangular cast test barsfrom 25.4 x 25.4 mmto 25.4 x 152.4mm (1 x 1 to 1 x 6 ln.) in size, cast test plate from 3.8 to 25.4 mm (0.15 to 1 in.) in thickness, and complexcastingswith gages ranging from about 2 mm (0.08in.) to 50 mm (2 in.) in thickness. The castingswere all hot isostatically pressed at either 895°C, 103.4MPa,2 h (1645 of, 15 ksl, 2 h) or 955°C, 103.4MPa,2 h (1750 of, 15 ksi, 2 h). followed by directaging at 525°C (970OF) for 12 h. The castingsobtained by the Universityof Daytonweresolutiontreatedat 955 °C (1750OF), 1 h. after HIP and prior to aging. Numbersin parentheses are the numberof tests for each source
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582/ Heat Treater's Guide: Nonferrous Alloys
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TIMETAL® 21 5 Ti-15Mo-3AI-2.7Nb-O.25Si Common Name. Beta-2lS UNS Number. R58210 Chemical Composition. See Table for typical composition range (min, max, and aim). Composition is based on the objective of obtaining a cold rollable, stripproducible alloy for economical processing into foil. The metastable J3 alloy can be processed to very high strengths. Oxidation and corrosion resistance are rated as excellent
Characteristics Phases and Structures. The microstructure of Beta-2lS consists of recrystallized J3 grains with occasional unrecrystallized J3 grains. ill addition, titanium silicides are present. The principal aging product is a (close-
packed hexagonal a). Omega (ro) also has been observed, though it would not be a problem with proper heat treatment
Beta Transus. 795 to 810 °C (1460 to 1490 OF) Product Forms. Beta-21S is available as cut sheet, strip, plate, bar, billet, and bloom. It is typically provided in the beta solution treated condition, which precipitates a to provide strengthening on aging. The morphology and distribution of the a depend on the heat-treatment temperature and the oxygen content. Lower heat-treatment temperatures and higher oxygen contents result in homogeneous spheroidal a; higher aging temperatures and lower oxygen result in lath-type a. Strip is the main product form. Beta-2lS is also well suited for metal matrix composites because it can be economically rolled to foil and is compatible
Beta and Near-Beta Alloys I 583 with most fibers. Strip is available in gages from 0.3 to 2.5 mm (0.012 to 0.100 in.) Applications. Beta-21S is most useful for applications above 290°C (555 "F), with thermal stability up to 625 °C (1155 OF) and creep resistance comparable to Ti-6A1-4V. Developing commercial applications include forged prosthetic devices and cold rolled foil for metal matrix composites. Special properties include a modulus that is comparable to bone, improved oxidation resistance up to 650°C (1200 OF), and resistance to aerospace hydraulic fluids (e.g., Skydrol). The latter properties have led to a number of aircraft engine applications. Excellent corrosion and hydrogen embritdement resistance have led to chemical and offshore oil use Corrosion Resistance. Molybdenum improves corrosion resistance in reducing media, and this well-known effect is apparent when the corrosion rate of Beta 21S and grade 2 Ti are compared in HCI solution (see Figure). However, the increased resistance from molybdenum in reducing media generally comes at the expense of resistance in oxidizing media. Crevice corrosion resistance improves with molybdenum additions. A chloride crevice corrosion test (5% NaCI at 90°C, pH adjusted to 0.5 and 1.0) indicated a chloride crevice corrosion threshold between pH 0.5 and 1.0 Hydrogen Damage. Beta-21S retains ductility up to hydrogen levels of 2000 ppm. High hydrogen levels (2000 ppm) will slow down aging kinetics.
Thermomechanical Processing. The fme microstructural features of Beta-2lS achieved in forgings are responsible for its excellent mechanical properties and fatigue resistance. Reheating for subsequent forging operations recrystallizes the alloy from prior hot work, refining the grain size. Beta-21S is generally not subtransus forged because there is no microstructural advantage, and there is a significant increase in unit pressures. Final thermal treatments for Beta-21S include a simple anneal (or solution anneal) for low-modulus applications, or solution anneal and aging for higher strength levels. Forgings may be supplied annealed, solution annealed, and/or fully aged (STA). Annealing or solution annealing generally is conducted at 815 to 870°C (1500 to 1600 "F), Aging is conducted at 540 to 595 °C (1000 to 1100 oF). Generally, reductions in any given forging process are 30 to 50% to achieve desired dynamic and static recrystallization. Very low levels of beta reduction are not recommended Hydrogen. Beta-2IS, as with all beta alloys, has a high affinity for hydrogen. Although Beta-21S forms less a case from heating operations than other alloy classes, control of chemical removal processes is essential to preclude excessive hydrogen pickup Recommended Forging Metal Temperatures. Range is 790 to 850 °C (1455 to 1560 oF) Formability. Limited forming data indicate a similarity to Ti-15V-3Cr3AI-3Sn (Ti-15-3). Machining, welding, and brazing of Beta-2lS is typical ofbeta alloys and is considered similar to that ofTi-15-3
See Table for general corrosion behavior Tensile Properties. Although oxygen levels below 0.33 wt% do not appear to significantly affect the strength/ductility relationship, results of tests on sheet from two heats containing 0.14 and 0.25 wt% oxygen showed a deleterious effect on ductility for the higher oxygen content in the series aged at 595°C (1100 OF). In the annealed condition, there is another effect of oxygen, which could be important in certain types of forming operations. In the annealed condition, the difference between yield, and ultimate tensile strengths decreased as the oxygen level increased from 42 MPa (6.1 ksi) at 0.09% oxygen to 12 MPa (1.7 ksi) at 0.33% oxygen. This behavior implies a decrease in work-hardening capability with increasing oxygen and, concomitantly, an increase in the tendency to neck locally and fail during stretching or drawing operations.
Recommended Heed Treating Practice See Table for selected heat treatments: Solution treatment (beta anneal), aging, and duplex age-first stage and second stage. See Figures for tensile strength vs. aging time, and for ultimate tensile strength vs. aging time. In cases where high-temperature exposure is anticipated, a duplex overage is used to retain ductility. The high temperature age "weakens" the grains relative to the grain boundaries and the second age stabilizes the grains against embrittlement
See Table for RT tensile properties of sheet and bar vs. oxygen content 8eta-21 S: Typical composition range
Fabrication Properties Forging. Beta-2lS can be fabricated into all forging product types, although closed die forging predominates. Beta-21S is a reasonably forgeable alloy above its beta transus. Compared with Ti-AI6-4V, this alloy has higher unit pressures (flow stresses), improved forgeability, and less crack sensitivity in forging. Due to the high alloying content of Beta-2IS, flow stresses are higher than those of the near-beta alloy Ti-IOV-2Fe-3AI. The desired final microstructure from thermomechanical processing of Beta21S during forging manufacture is a fine transformed 13, with limited grain boundary films and a fine, recrystallized prior 13 grain size in preparation for final thermal treatments .
Minimum Maximum Aim
AI
Nb
Mo
Si
2.5 3.5 3.0
2.4 3.0 2.S
14.0 16.0 15.0
0.15 0.25 0.20
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8eta-21 S: General corrosion behavior Beta annealed material. Corrosionrnte,
8eta 21 S: Selected heat treatments 'Ireatment Solutiontreatment {betaanneal) Aging(a)
'Iempemture OF
°C
Duration
Cooling metbod
AC AC AC AC AC
SOO-SI5 480 540 595
1470-1500 1000 1100
4 min, minimum 24h Sh Sh
690 650
1275 1200
Sh Sh
900
Duplexage First stage Second stage
(a) Three selectedaging treatmentsthatcoverstrengthlevels likely to be used in commercialapplications
n
Medium
mmJyear
3% boilingH2S04 10%FeCb, boiling 0.5%HO, boiling 1%HCI,boiling 1.5%HCI,boiling 2%HCI,boiling 2.5%HO, boiling 3%HC1, boiling 4% HCI,boiling 10%HC~ boiling 15%HCl, boiling 2S%HCI,boiling,deaerated 10%formicacid, 10%aceticacid,boiling,deaerated
0.16 0.01 0.00254 0.0050S 0.01016 O.OI77S 0.02794 0.04064 0.127 4.0 15.0 55.0 0.0
584/ Heat Treater's Guide: Nonferrous Alloys
Beta-21 S: RTtensile properties of sheet and bar vs, oxygen content Simulilled strip(b} 'ThnslJe yield
UItimale lellSile Heal t....lmenl(.)
Oxygen,
....
MPo
ksi
845°C (1555oF), 10min,AC
0.090 0.120 0.130 0.183(c) 0.229(d) 0.334(e) 0.090 0.120 0.130 0.183(c) 0.229(d) 0.334(e) 0.090 0.120 0.130 0.183(c) 0.229(d) 0.334(e) 0.090 0.120 0.130 0.183(c) 0.229(d) 0.334(d)
813.6 859.8 874.3 900.5 930.8 970.8 1336.9 1443.1 13?1.4 1447.3 1541.7 1579.6 1157.0 1314.2 132Q.4 1421.7 1434.8 1461.1 937.0 1068.0 1060.5 1152.8 1223.2 1289.4
118.0 124.7 126.8 130.6 135.0 140.8 193.9 209.3 201.8 209.9 223.6 229.1 167.8 190.6 191.5 206.2 208.1 211.9 135.9 154.9 153.8 167.2 117.4 187.0
845°C(1555°F),10min, AC + 480°C (900 oF),14 h,AC
845°C(l555 °F),10min, AC + 540°C (1000oF),8 h, AC
845°C (1555 oF),10min, AC + 595 (1100 OF), 8 h, AC
strength
strength ksi MPo
771.6 819.8 847.4 888.8 912.9 958.4 1258.3 1341.8 1306.6 1375.6 1470.7 1462.4 1024.6 1232.8 1243.2 1319.7 1377.6 1359.7 822.6 986.0 987.4 1081.8 1148.0 1194.2
111.9 118.9 122.9 128.9 132.4 139.0 182.5 194.6 189.5 199.5 213.3 212.1 148.6 178.8 180.3 191.4 199.8 197.2 119.3 143.0 143.2 156.9 166.5 173.2
Ultimatetensile
Hoirolled bar 'ThnslJe yield
Ileduction
strength
strength
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ksi
ksi
MPo
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837.1 847.4 874.3 882.6 899.1 917.0
121.4 122.9 126.8 128.1 13Q.4 132.9
795.7 815.7 843.9 853.6 890.1 913.6
115.4 118.3 122.4 123.8 129.1 132.5
66.8 66.2 61.8 63.6 66.1 61.4
22.5 24.0 23.0 23.3 27.0 26.5
1431.4 1434.2 1494.8 1583.1 1540.3 1202.5 1325.2 1326.6 1395.5 1467.3 1425.2 1045.3 1103.2 1099.8 1166.6 1232.1 1259.0
207.6 208.0 216.8 229.6 223.4 174.4 192.2 192.4 202.4 212.8 206.7 151.6 160.0 159.5 169.2 178.7 171.2
1352.1 1346.6 1415.5 1501.7 1443.1 1037.0 1253.5 1254.9 1329.5 1388.0 1332.8 947.4 1010.1 1011.5 1084.6 1146.6 1180.4
196.1 195.3 205.3 217.8 209.3 15Q.4 181.8 182.0 192.8 201.3 193.3 137.4 146.5 146.7 169.2 166.3 171.2
15.8 15.9 12.5 10.4 5.0 47.6 24.3 24.4 19.0 19.2 8.0 44.2 35.5 35.2 26.9 22.5 16.0
7.0 6.5 4.5 4.5 2.0 10.9 8.3 8.5 7.0 7.8 4.0 11.5 14.0 13.5 12.0 10.3 8.3
(a) Annealing limefor sheet was 10min,for bar 1h. (b) Coldrolled50%prior10annealing. (c)Annealed 857°C. (d)Annealed 870DC. (e)Annealed885°C
Beta-21S: Tensile yield strength vs. aging time. Beta annealed 1.5 mm (0.06 ln.) sheet aged for indicated times and temperatures LIVE GRAPH Click here to view
Beta·21S: Ultimate tensile strength vs. aging time. Beta annealed 1.5 mm (0.06 in.) sheet aged for indicated times and temperatures LIVE GRAPH Click here to view
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Ti-5AI-2Sn-4Zr-4Mo-2Cr-1 Fe Common Name. Beta-CEZ®
Characteristics
Chemical Composition. See Table for chemical composition.
Crystal Structure. In the solution treated and aged condition, the microstructure consists of (X + ~ phases. The lattice parameters of the closepacked hexagonal (X phase are a =2.9287 Aand c =4.6606 A, whereas the lattice parameter of the body-centered cubic ~ phase is a = 3.2040 A
Beta-CEZ® is a multifunctional near-B titanium alloy exhibiting high strength, high toughness, and intermediate-temperature creep resistance. Processing flexibility makes it suitable for a wide range of applications
Beta and Near-Beta Alloys I 585 Grain Structure. The microstructure is typical of pmetastable alloys and may be p or a + p, either equiaxed or lamellar. Highest strength and ductility are achieved with an equiaxed primary a phase and a finely precipitated secondary a phase microstructure. Optimum toughness is obtained with lamellar primary a microstructures
Transformation Products. The continuous cooling (CCT) diagram for
Beta-CEZ® is similar to that ofTi-17. Alpha precipitation occurs first at p grain boundaries and secondly inside the grains. For instance, the time difference between grain boundary and intragranular precipitation is about 1 h when cooled at 1°C/min (1.8 of/min) from the pfield. A temperature of>750°C (1380 "F) is recommended for solution treatments below the transus, whereas aging treatments are performed below 700°C (1290 oF)
Beta Transus. 890°C (1635 OF) Chemical Corrosion Resistance. Corrosion resistance in acid or seawater, as well as hydrogen uptake and embrittlement are currently being studied. Data are not available
Product Forms. Typical product forms consist of forged billets in diameters ranging from 150 to 300 mm (6 to 12 in.) and forged or rolled bar in diameters ranging from 10 up to 110 mm (0.4 to 4.3 in.). Rolled plate and sheet are also available in thicknesses ranging from 25 to 3 mm (1 to 0.1 in.) and 500 mm (20 in.) wide. Products are supplied in the forged or solution treated conditions. The microstructure is fine and equiaxed
Fabrication Properties Forming. Because the strain-rate sensitivity exponent of Beta-CEZ® is rather high compared to conventional alloys (0.3 for Beta-CEZ® versus 0.2 for Ti-6Al-4V), plastic flow is more stable and enhances formability. The metastable nature of the alloy lowers its sensitivity to temperature. Hot working in the a + p range is recommended at 800 to 860°C (1470 to 1580 oF) to maintain a fine equiaxed microstructure. In the p range, a temperature around 920°C (1690 "F) is suggested to obtain a lamellar structure by pprocessing
"Through the Transus" Processing. A patented technique that results in a "necklaced" microstructure. It is applied to a 100% p metastable structure below 890°C (1635 "F), Lamellae in the core of the grains and fine equiaxed grains at the boundaries are thus obtained, which leads to an excellent combination of strength, ductility, and toughness Superplastic Forming. The alloy displays superplastic properties between 725 and 775°C (1335 and 1425 "F); 1000% ductility can be reached at strain rates as high as 8 x 10-4 S-1. Diffusion bonding is being studied. Superplastic properties of Beta CEZ® alloy are obtained at temperatures as low as 725°C (Scripta Met, Vol 29, No.4, 1993, p 503-508)
Recommended Heat Treating Practice
Applications. Typical applications include heavy section forgings for medium-temperature compressor disks in which an optimum combination of strength, ductility, toughness, and creep resistance is required. BetaCEZ® is a structural alloy with very high strength and a good combination of strength, ductility, and toughness. Near-net shape forgings are possible due to the excellent formability of the alloy. Component applications are as forged parts, springs, and fasteners
Solution treatment is at 750 to 860°C (1380 to 1580 "P) for from 1 to 4 h.
Mechanical Properties
Beta-CEZ®: Chemical composition
Tensile properties depend strongly on microstructure. Forged or rolled bars exhibit an equiaxed microstructure, whereas p processed and "through the p transus" processed pancakes exhibit lamellar and necklaced microstructures, respectively. Beta-CEZ® can maintain a high strength level at high temperatures for both the equiaxed or lamellar microstructures.
Element
See Table for typical tensile properties
Aging is at 525 to 650°C (970 to 1200 "F) for from 30 min to 8 h. As a function of aging time, hardness evolves rapidly. Maximum hardness is about 560 HV. See Table for hardness kinetics for equiaxed microstructures
Compooltion, wi %
4.5-5.5 1.5-2.5 3.5-4.5 3.5-4.5 1.5-2.5 0.5-1.5 800-1300ppm <150ppm
Aluminum Tin Zirconium
Molybdenum Chromium Iron
Oxygen Hydrogen
Beta-CEZ®: Typical tensile properties Product fonn
150 mm (6 in.) diamforged bar
12.7 mm(~in.) diamrolledbar
25 mm (1 in.) thickrolledplate
300 mm(12 in.) diamJ}-processed pancake 300 mm (12 in.)diam"through the transus" processed
Heal treatment
As forged 830°C (1525oF).1 h,WQ +550 °C (1020oF),8 b,AC 830°C (1525oF),1 h, WQ+600°C(lllO°F), 8b,AC 860°C(l580°F), Ib, WQ+550°C(I020°F),8h,AC 860°C (1580oF),1 h, WQ+600 °C(lllO°F),8h,AC As rolled 830°C (1525oF),1 h, WQ+550°C(I020°F), 8 b,AC 830°C (1525oF),1 b,WQ + 600°C (1110oF),8h,AC 860°C (1580oF),1 h.WQ+550°C(l020°F), 8h,AC 860°C (1580oF),1h, WQ + 600 °C (1110oF),8h,AC As rolled.L Asrolled,T 830°C (1525oF),1 h, WQ + 600°C (1110oF),8h,AC, L 830°C (1525OF), 1 h, WQ + 600°C (1ll0 oF),8h,AC, T 860°C (1580oF),1h, wQ +600 °C (1l1OoF).8h,AC, L 860°C (1580oF);1 h, WQ +600 °C (1110oF),8 h,AC, T 600 °C (1110oF),8 h,AC 830°C (1525oF),1h, WQ +570°C (1060 ~F), 8 h,AC 830°C (1525oF),1 h, WQ+600°C(1ll0°F),8h,AC 600°C (1110oF),8b,AC 830°C (1525oF),1h, WQ + 570°C (1060oF),8 h,AC 830°C (1525oF),1h. WQ + 600 °C (1l1OoF),8h.AC
0.2% yield streogth
Ultimate strength MPa
lui
MPa
lui
EIoogaIIoo, %
1040 1601 1283 1557 1370 1490 1506 1373 1723 1540 1222 1260 1334 1351 1405 1418 1608 1357 1326 1227 1314 1263
150 232 186 226 198 216 218 199 250 223 177 182 193 196 203 205 233 197 192 178 190 183
960 1518 1208 1478 1304 1345 1460 1349 1683 1485 1124 1163 1287 1300 1338 1340 1472 1171 1188 1138 1200 1170
139 220 175 214 189 195 211 195 244 215 163 168 186 188 194 194 213 170 172 165 174 169
18 2 II 2 5 II 13 15 7 9 15 II 13 12 10 6 2 5 6 10 10 II
586/ Heat Treater's Guide: Nonferrous Alloys 8eta-CEZ®: Hardness kinetics for equiaxed microstructures Aging lime,
Product form
IJ),
Heal treatment
150mm(6 in.) diamforgedbar
min
As forged 860 °C (1580 oF),2 h, WQ + 550°C (1020 oF), t,AC
o I 3
to 30 100 300
1000 3000
Hardness (30kg), HV
345 380
440 470 485 480
465 460 460
Ti-8Mo-8V-2Fe-3AI Common Name. Ti-8823
Fabrication Properties
Chemical Composition. See Table for typical composition range
Forging. Ti-8823 should be hot forged and hot rolled above its beta transus temperature of775 °C (1425 OF). The recommended hot working temperature is 760 to 980°C (1400 to 1795 OF) with breakdown at the higher temperatures and finishing at the lower temperatures. Cold working is used to finish such products as sheet, strip, plate, rod, and wire. Intermediate annealing may be necessary during these cold working operations
Characteristics Product Forms. Primarily a high strength, formable sheet alloy Applications. The alloy has hardenability in sections up to 100 mm (4 in.) and possibly up to 150 mm (6 in.). It has been considered as a possible fastener alloy, spring alloy, and structural forging alloy. Additionally, Ti-8823 has good fracture toughness, notch fatigue strength, modulus of elasticity, stress-corrosion resistance, and thermal stability at least to 315°C (600 OF). The good formability of Ti-8823 in the annealed condition, its deep hardenability, and capability for heat treatment to very high strength levels are consistent with the general advantages of beta titanium alloys. Limitations are consistent with some of the disadvantages in general of beta titanium alloys, such as higher density (than for example alpha-beta alloys), relatively poor creep strength at moderately high temperatures, and marginal weld properties in the heat-treated condition. Also, smooth specimens of the Ti-8823 alloy do not appear to have the fatigue strength that might be expected from such a"hightensile strength material. Ti-8823 also suffers from melting problems due to its high molybdenum content Tensile Properties. Ti-8823 is cold workable, and this characteristic allows an excellent combination of strength and ductility to be achieved for certain applications. High strength levels can be obtained in this alloy, which translate to high stnictural efficiency. As with most beta titanium alloys, usage is limited to about 315°C (600 "F), See Figures for: • Tensile properties of sheet • Vickers hardness • Tensile properties vs. aging temperature See Tablesfor mechanicalpropertiesof fastener stock,for RTshear and tensile properties vs. cold work or heat treatment,and for tensileproperties of welded sheet at 315°C (600 oF)
Forming. The formability of the Ti-8823 alloy in the annealed or solution heat treated condition is excellent. It has relatively low yield strength, tolerably low work-hardening characteristics, and high ductility in tension and compression Machining. Ti-8823 is machinable by most conventional techniques. It is more easily machined in the solution treated condition than in the aged condition. It requires rigid set up, heavy feed, slow speed, and adequate coolant Welding. Ti-8823 has fairly good weldability and weld stability. Through the use of conventional titanium welding practices, this alloy can be joined and useful mechanical properties maintained. The as-welded material exhibits properties similar to those of solution treated annealed material, except for lowered tensile ductility. Generally, properties of welded material using a postweld aging treatment are somewhat less desirable than those of unwelded solution treated plus aged material
Recommended Heat Treating Practice See Table for recommended heat treatments: solution treatment (anneal), aging, overage (stabilization). See Tables for tensile properties of heavy sections vs. section size and location, per heat treatment; for tensile properties of foil vs. cold rolling and heat treatment, such as annealing and stabilization; and for tensile properties of rod and wire vs. processing and heat treatment, such as HR + CR + 8 h at 480°C (900 "F), and air cooling
Ti-8823: Mechanical properties of fastener stock Thnsile yield Heat treatment
Ti-8823: Typical composition range
Minimwn Maximum
Nominal
AI
V
Fe
Mo
2.6 3.4 3.0
7.5 8.5 8.0
1.6 2.4 2.0
7.5 8.5 8.0
C
Oz
0.05
0.1 0.16
N,
0.05
IL
0.Ql5
15 min, 785 °C(I445 oF), AC+8h,650°C(l200°F),AC 20 min, 775 °C(1425 oF), AC+8h,650°C(12OO°F),AC Unspecified, except650 °C (1200 oF) aging
strength MPa ksl
Ultimate lemile strength MPa ksI
%
Shear strength MPa ksi
Elongation,
960
139
1027
149
22
703
102
875
127
930
135
24
662
96
682-703
99-102
Beta and Near-Beta Alloys I 587
Ti-8823:Room-temperature shearand tensile properties vs, cold workor heat treatment Diameter In.
CondltloD/ beattreatmenl
mm
20 min, 775°C(1425°F),AC 20 min,775 °C(1425°F),AC+8h, 495 °C (920°F),AC 15min, 785°C(1445°F),AC 15min,800°C (1470oF),AC Hotrolled HR+14%CR HR+36%CR HR+53%CR HR + 53%CR + 8 h, 495°C (920°F),AC HR+61%CR HR+61%CR+8h,495°C(920°F),AC 15min,785 °C(1445°F),AC+8h, 650 °C (1200°F),AC 20 min,775 °C (1425°F),AC+8h, 650 °C (1200°F),AC
7.9 7.9 4.8 7.9 7.9 7.2 6.2 5.3 5.3 4.8 4.8 4.8 7.9
0.312 0.312 0.190 0.312 0.312 0.284 0.244 0.208 0.208 0.191 0.191 0.190 0.312
Thnsile yield strength IIsI MPa
UltImatetensile strength MPa lIsi
862 1268 889 862 937 993 1151 1220 1599 1282 1613 958 875
889 1344 930 868 972 1034 1179 1255 1661 1303 1668 1027 930
125 184 129 125 136 144 167 177 232 186 234 139 127
Elongation,
Reductlon Or&Ie8,
%
%
29 8 17 28 24 21 12 12 6 10 9 22 24
58 21 58 64 68 64 57 57 18 52 35
129 195 135 126 141 150 171 182 241 189 242 149 135
Double shear strength ksI MPa 655 834 662 620
95 121 96 90
655 696 703 924 724 951 703 662
95 101 102 134 105 138 102 96
Ti-8823:Tensile properties of welded sheet at 315°C (600 OF) strength MPa ksI
Thnsile yield strength MPa ksI
593 605 605 1275 1296 1255 613 593 613 848 813 820 1103 1096 161 1151 1110 1110
579 600 593 1193 (a) (a) 600 579 586 731 675 799 1013 1041 151 1082 1061 1041
UltImatetensile
Heattreatment 800 °C (1470oF),30 min,AC + 480°C (900 oF), 8 h, AC + weld 800°C (1470oF),30 min,AC + weld + 480°C (900 "F), 8 h, AC 800°C (1470oF),30min,AC + 595 °C(1100 oF), 16 h, AC + weld 800°C (1470oF),30 min,AC + 595°C (1100 oF), 16 h, AC + weld 800°C(1470 °F),30min,AC + 595°C (1100 oF),8 h, AC + weld + 480°C (900 "P), 3h,AC
86 88 88 185 188 182 89 86 89 123 118 119 160 159 1041 167 161 161
Eloogalion in: 50mm (2 lu), % Local
84 87 86 173 (a) (a) 87 84 85 106 98 116 147 151 5 157 154 151
35 30 45 15 5 5 25 40 35 20 5 20 5 10 0 10 10 10
Uolform 0 0 0 0 0 0 0 0 0 0 2.5 2.5 0 2.5 2 2.5 2.5 2.5
Young's modulus lO'ps; GPo
lJmm ThtaI
(0.5In.),%
1.5 3.5 5 2 2 1 5 5.5 4 3.5 4.5 4.5 2 3 2.5 3 3 3
14 12 18 6 2 2 10 16 14 8 2.5 8.5 2.5 4 104 4 4 4
101 106 102 105 117 110 69 104 82 96 90 102 101 94 15.1 109 100 95
14.7 15.4 14.9 15.2 17.0 16.0 10.0 15.1 11.9 13.9 13.1 14.8 14.7 13.7 15.9 14.6 13.8
(a) Brokebeforereachingyieldstress
Ti-8823:Recommended heat treatments Cooling
'trealmeot
Durnlion
Solutiontreatment(anneal) Aging Overage(stabilization)
785-800 48G-51O 650
1455-1470 900-950 1200
(a)
8h
method ACor OQ(h) AC AC
(a) Durationdependson thickness.(h) Sufficientrate to prevent uformation
Ti-8823:Tensile propertiesof foil vs, cold rolling and heat treatment Condilion 93% coldroUed Annealed2 min, 785°C (1445°F)(a) Stabilized4 h, 675°C (1245°F)(h) Annealed+ stabilized(c) Annealed+ 6 h, 510°C (950°F)(d)
ThIl'lileyield strength MPa ksi
Ullimate lensile strength MPa IIsI
1268 937
184 136
1365 944
198 137
1 7
82 96
12 14
1110
161
1179
171
8
124
18
930 1441
135 209
986 1530
143 222
13 5
110 131
16 19
Elongation, %
Ti-8823: Tensile properties of heavysections vs. section size and location
Modulus or elastkllv GPa lolpsi
(a) Fastcool in vacuum.(h) Slow cool in vacuum.(c) (a) treatmentplus (h) treatment,(d) (a) treatment plus the 510 °C (950 "P) treatment,vacuumcooled
SecUon stul heatlreatmeol
Uilimale tensile strength lIsi Location MPa
lOOmm (4in.)square,800°C L-O (1470 oF), 1 h, WQ + 540°C L-MR (1000 oF),8 h, AC L-C L-O 150mm (6 in.) square,800°C (1470 oF), I h, WQ + 540°C L-MR (1000 oF),8 h, AC L-C 200 mm (8 in.) square,800°C L-O (1470 "P), 1 h, WQ + 540°C L-MR (1000 oF),8 h, AC L-C
1210 1197 1182 1186 1232 1213 1183 1213 1226
175.6 173.7 171.5 172.1 178.7 176.0 171.6 176.0 177.8
ThIl'lileyield Elongation Reduction strength(0.2 %) (40), ohrea, MPa ksi % % 1133 1150 1160 1120 1165 1146 1103 1148 1155
164.4 166.9 168.3 162.5 169.0 166.3 160.0 166.5 167.6
10.0 8.0 9.0 8.0 6.0 7.0 6.0 5.5 4.0
24.1 14.6 16.6 14.8 12.1 14.0
im
6.6 5.5
588/ Heat Treater's Guide: Nonferrous Alloys Ti·8823: Tensile properties of rod and wire vs. processing and heat treatment ProcessIngf beat treatment
Cold work,
Diameter
ThD5ile yield
Ulllmale lensiJe
s1reng1b
strengtb
Eiongation(o),
Reduclion ofmeo
mm
In.
%
MPH
ksi
MPo
ksi
%
%
7.9 7.2 7.2 6.2 6.2 6.2 5.3 5.3 5.3 4.8 4.8 4.8 2.3 1.6 0.9
0.312 0.284 0.284 0.244 0.244 0.244 0.208 0.208 0.208 0.191 0.191 0.191 0.090 0.063 0.036
None
937 993 1489 1151 1751 1572 1227 1599 1468 1282 1613 1489
136 144 216 167 254 228 178 232 213 186 234 216
972 1034 1586 1186 1827 1675 1255 1661 1523 1303 1668 1544 1324 1330 1365
141 150 230 172 265 243 182 241 221 189 242 224 192 193 198
24 21
64
As hot rolled HR+CR HR + CR + 8 h, 480°C (900 oF),AC HR+CR HR + CR + 24 h.430°C (800 oF),AC HR +CR +4 h, 480°C (900 oF),AC HR+CR HR+CR+8h,48O°C(9OO°F),AC HR +CR + 8 h, 510°C (950 °F),AC HR+CR HR + CR + 8 h, 480 °C (900 oF),AC HR+CR + 8h, 510°C (950°F),AC HR+CR
14 14 36 36 36 53 53 53 61 61 61 91 96 99
68
10
33 57 11 30 57 18 38 52 35
13 3 10 12 6 10 9
10
46
12 O.l9(b) 0.15(b) 0.14(b)
58 65 59
(a) In 4D exceptas indicated.(b) In 250 rom(10 in.)
Ti-8823: Tensile properties. Effect of aging heat treatment variables on the tensile properties of 1.27-mm (0.050-in.) sheet solution heat treated 15 min at 815°C (1500 OF), water quenched LIVE GRAPH Click here to view 1600 --Ultimate tensile strength -Tensile yield strength
220
I
480 °c (900 OF) 200
'"
Q.
::!
~ 1200,t---+-f-r>rt----+--F---,--+---__j
180
/
c
~
/ /
160
~
'if.
'6> c::
'iii 10
til
iii
s: ~
425°C (800 OF) 140
C 0
Ol
c::
0
5
LIVE GRAPH Click here to view 120 8
16 Aging time, h
32
24
0 0
4
8
12 16 Aging lime, h
20
24
28
Ti-8823: Vickers hardness. Effect of aging heat treatment hard-
Ti-8823: Tensile properties vs. aging temperature. Effect of 8-
ness of 1.5 mm (0.060 in.) sheet solution heat treated 30 min at 800°C (1470 OF) and air cooled
h aging temperature on tensile properties of 6.5 mm (0.256 in.) diameter rod solution heat treated 15 min at 785°C (1445 OF), air cooled LIVE GRAPH
LIVE GRAPH
Click here to view
Click here to view 450
~ .Q
450 200
4251----+---480 DC(900 OF)
190
400t----+--------,-""'---+----j--_f_--__j
180
~---I---t-----jI---1
~
~ 375t----+-r---
Aging temperature, DC 550 650 ___ Ultimate tensile strength
40
~ 170
>
s:
CD
til 150
'"
140
~ 3501/1----"."=::i==::::~~?i~1
~ 325t---+_f_-7'<----~ol-.......,~~-_f_--__j J:
'6>160 c ~
10
30°t-ir-TT----::::;:~z::::;SF~~F=+===lj " " 650 DC(1200 OF) 4
8
750 50
12 16 Aging time, h
20
24
550 650 Aging temperature, DC
Beta and Near-Beta Alloys I 589
Ti-15Mo-5Zr Chemical Composition. See Table for chemical composition of bar, wire, and sheet
Characteristics
at around 400°C (750 "F), but elongation is very low because of 0) phase precipitation. The practical high-strength aging temperature ranges from 450 to 500 °C (840 to 930 OF). See Table for mechanical properties of hot rolled bar at room temperature
Crystal Structure. Body-centered cubic single-phase ~ is obtained in the solution treated condition. Close-packed hexagonal 0) phase and cph phase a are precipitated during aging below 400°C (750 oF)- and above 450 °C (840 "F), respectively. Omega phase is usually avoided because it causes embrittlement Grain Structure. The grain structure and distribution of phases depend on thermomechanical history. The P grain size after annealing ranges from approximately 20 to 100 IJ.m Product Forms. Forging billet and bar, hot rolled plate and bar, cold rolled sheet, and cold drawn wire are available. Cold rolled sheet is available in thicknesses up to 0.1 mm (0.004 in.). The standard cold drawn wire diameter minimum is 1.0 mm (0.04 in.)
Fabrication Properties Forming. Properties are similar to those of Ti-15V-3Cr-3Sn-3AI or Ti15Mo-5Zr-3Al Machining. Characteristics are similar to other
p titanium alloys
Welding. Filler rod ofTi-15Mo-5Zr is recommended. Hardness increases minimally in the heat-affected and fusion zones. Ti-15Mo-5Zr can be welded with commercially pure titanium as well. Corrosion and wear resistance of parts made of commercially pure titanium can be enhanced by overlay welding and hardening
Recommended Heat Treating Practice
Applications. Ti-I5Mo-5Zr is a metastable P type alloy that exhibits good cold formability and age hardenability. It isP stabilized by molybdenum to enhance corrosion resistance to reducing atmospheres. Zirconium is added to (1) enhance corrosion resistance above the level achieved by molybdenum, (2) suppress 0) transformation to prevent embrittlement, and (3) to improve thermal stability of the p phase. Zirconium additions of 5% minimum are used to enhance thermal stability. TI-I5Mo-5Zris used in the chemical industry because ofits high strength, good cold formability, and high corrosion resistance. In addition, it is used as an erosion-resistant overlay for steam turbine blades in which 0) phase is intentionally used to obtain an extremely high hardness in spite of being brittle
Ti-15Mo-5Zr typically is processed to plate, billet, or bar in the p temperature fields. Solution treatments in the p region are used to obtain low flow stress and high ductility for cold processing. Products usually are supplied in the annealed condition. Annealing is carried out just above the p transus temperature for a fine-grained recrystallized microstructure. Beta transus: 730°C (1345 oF).
Corrosion Resistance. Ti-I5Mo-5Zr has high corrosion resistance to reducing atmospheres. It has better corrosion resistance in boiling hydrochloric acid or sulfuric acid solutions than commercially pure titanium. Additionally, Ti-I5Mo-5Zr has higher erosion resistance compared to Ti-6AI-4V or other p titanium alloys. See Figure for corrosion resistance at 90 °C (195 "P)
After aging at low temperatures of around 400 °C (840 OF), the alloy is highly strengthened but is extremely brittle because of 0) phase precipitation. However, during aging over 450°C (840 "F), a phase precipitates without embrittlement. The maximum amount of a phase is obtained at around 500°C (930 "F), The optimum combination of strength and ductility can be obtained by solution treating and aging at 730 °C (1345 "F), I h, water quenching + 475°C (890 OF) for 100 to 1000 min, AC.
Mechanical Properties The ductility of Ti-15Mo-5Zr is approximately twice that ofTi-6AI-4V at the same strength level. A maximum tensile strength is obtained by aging
Solution treating at 730 °C (1345 "F), I h, followed by water quenching is recommended. With sheet thicknesses less than 3 mm (0.1 in.) or wire of diameters less than 3 mm (0.1 in.), air cooling is acceptable. Recommended aging temperatures are 450 to 500°C (840 to 930 OF).
See Figures for aging transformation diagram, for amount of alpha and alpha phases during aging (a and b), and for isochronal curve of tensile properties vs. aging temperature
Ti-15Mo-5Zr: Amount of 0) and a phases during aging. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF), 98% reduction; X-ray diffraction analysis. In = I {1010}JI{200}p I., = I {1122}jl{200}p
LIVE GRAPH
LIVE GRAPH Click here to view 600
Temperature, OF BOO 900
700
1000
1100
700
0.6
I _8
oj
gj 0.4
i 5000 min
'./
-"
I'"~
.
Click here to view 1100
1200
-, /'
_.
l'i 4
OJ
s:
s:
0.
0.
S
tl
'0
'0
~ ~ 0.2
J
\ "100 min
~
~2
~
Ql
E 0 300
(a)
BOO
6
5000 min
Temperature, OF 900 1000
0 400 500 Temperature, DC
600
350
(b)
--:: IIf
20 min 0
450 Temperature,
550
°c
650
590 I Heat Treater's Guide: Nonferrous Alloys
Ti·15Mo-5Zr: Corrosion resistance at 90 DC. Typical corrosion in 12 wt% H2S04 , 20 wt% Na2S04 , 2 wt% ZnS04 , and 66 wt% H20
1.6
1.2~H---+---+--'-"--T-==L--\---------j
oj Cl
c:
"ficu :<:Cl
~
0.811-+---+--+---+-----+----------j
0.411+----¥---~,.....,,~=~~+_1,--__l
LIVE GRAPH Click here to view 400
200
800
600
Time, h
Ti,15Mo-5Zr: Isochronal curve oftensile properties vs. aging temperature. Specimens were 9.5 mm (0.35 in.) diameter hot rolled bar at 880 DC (1615 OF); 98% reduction. Solution treated at 730 DC (1345 OF), WQ. Aged as indicated
Temperature, of
600
800
700
900
2100
1100
1000
300
---0--20 min - e - '100mln -"-1000 min - i > - 5000mln
-- .i->:
,./
280 260
160 900l..-
......L.
---l
300
350
..L-
...L.
400
450
500
600
550
°c
Temperature,
LIVE GRAPH
....:..l 140
L-
Click here to view
(a)
Temperature, of
600
700
800
900
,
---0--20 min - e - '100 min 2 0f-------.. -l000 min - i > - 5000min
~ 15
c:o :;
Cl
c:
/~
A
5
300
/.
" ",~
o\ -
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,
V
'
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~ ~~ -
~~k'iV-
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~
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/-
£-. p. /
r-,
" ""~~
~~y
2;-
350
LIVE GRAPH (b)
y /' /
iB 10 ['\
1100
1000
I
25
Click here to view
400
450 Temperature,
500
°c
550
600
Beta and Near-Beta Alloys I 591 Ti-15Mo-5Zr: Mechanical properties of hot rolled bar at room temperature Alloy
Uhimate tensile strength ksi MPa
TI-I5Mo-5:lI(a) Ti-15Mo-O.2Pd(a) CPTi(b) TI-6AI-4V(b) Ti-5AI-2Cr-1Fe(b)
961 1118 412 961 1000
Reduction
CJuupy impact
Elongation,
oCarea,
Iougbnea,
%
%
J/em'
Hardn .... HV
25 20 41 13 19
65 55 70 35 40
59 39 176 39 49
283 278 140 330 320
Thmiley\eld
strength (0.2%) MPa ksi
139 162 59 139 145
922 1069 323 892 951
133 155 47 129 138
(a)Solutiontreated.(b)Annealed.Source:Kobe Steel
Ti-15Mo-5Zr: Aging transformation diagram. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF), 98% reduction. Xray diffraction analysis 1100
600
• !;' 500
i:::l
~
Ol
a.
E
~ 400
• •
J3+a
Ti-15Mo-5Zr: Chemical composition of bar, wire, and sheet Chemical composition, % Fe(a) Zr
H(a)
O(a)
N(a)
0.020
0.20
0.05
0.35
4.5-5.5
Mo
1'1
14.0-16.0
rem
(a)Maximum
1000 u.
... .... ..
J3+ro+a
tJ.
900
tJ. tJ.
800
°
i
~
Ol
a.
E
Ol
I-
J3+ro
..
600
300 10
700
100
1000
10000
LIVE GRAPH Click here to view
Time, min
Ti-15Mo-5Zr-3AI Chemical Composition. See Table for chemical composition. Molybdenum enhances corrosion resistance to reducing atmospheres. Zirconium is added to: (I) further enhance corrosion resistance above that achieved by a single molybdenum addition, (2) suppress 0) transformation to prevent 0) embrittlement, and (3) to improve thermal stability of ~ phase. Zirconium additions of 5% minimum are required to enhance thermal stability. An aluminum addition of 3% is needed to suppress 0) transformation effectively at lower temperatures and longer times. Moreover, aluminum enhances post-aging strength and resistance to oxidation as well
Characteristics Crystal Structure. Body-centered cubic ~ phase is obtained after solution treating in the ~ temperature region and quenching. Close-packed hexagonal ~ phase and 0) phase precipitate during aging above and below 425°C (795 "F), respectively. Compared with Ti-15Mo-5Zr, embrittlement caused by 0) phase does not occur as predominantly because the amount of 0) phase is reduced by the 3% aluminum additions Grain Structure. The grain structure and distribution of phases depend on the thermomechanical history of the material. The grain size obtained by solution treating above the ~ transus generally ranges from approximately 20 to 100 11m Beta Transus. 785°C (1445 OF) Product Forms. Forging billet and bar, hot rolled plate and bar, cold rolled sheet, and cold drawn wire are available: Cold roIled sheet is
available in thicknesses up to O. I mm. The standard cold drawn wire diameter minimum is 1.0 mm
Applications. Ti-15Mo-5Zr-3AI is characterized by high strength, good cold formability, and in particular, high corrosion resistance to reducing atmospheres. Its corrosion resistance is superior to that of Ti-0.2Pd. Ti-15Mo-5Zr-3AI can be used in various applications where many other titanium aIIoys cannot be used. For example, it is a candidate material for sour gas weII plants because of its high strength-to-density ratio and resistance to atmospheric stress-corrosion cracking. It is currently used as an erosion shield material for 1015 mm (40 in.) titanium turbine blades in power plants
Corrosion Properties. Ti-15Mo-5Zr-3AI has high corrosion resistance to reducing atmospheres. Its erosion resistance is somewhat inferior to that of Ti-15Mo-5Zr. However, the strength, ductility, and toughness of Ti15Mo-5Zr-3AI are superior to Ti-15Mo-5Zr, and it is used as an erosion shield as well as Ti-15Mo-5Zr. Stress-corrosion cracking properties in a H2S-saturated solution with 5% NaCI and 0.5% CH3COOH for solution treated and aged samples are shown
Mechanical Properties Tensile Properties. With optimum heat treatment this aIloy can reach a tensile strength of 1470 MPa (213 ksi) with an elongation of 15%. A higher tensile strength of over 1570 MPa (227 ksi) can be obtained by duplex aging.
592/ Heat Treater's Guide: Nonferrous Alloys See Tables for mechanical properties of aged specimens, and for mechanical properties of duplex aged specimens
Fabrication Properties Forming. Ti-15Mo-5Zr-3AI is hot worked or cold worked. Prior to cold working, the material is solution treated to obtain low flow stress and high ductility. Products usually are supplied in the solution treated condition. Solution treatment is carried out alternatively either in the I} temperature field (at 800 to 850°C, or 1470 to 1560 "F) for cold formability, or in the a-I} field at 735 °C (1355 "F) for a good combination of strength and ductility after aging. In the former case, the microstructure consists of a small amount of a phase and recovered I} phase. See Table for effect of solution treatment temperatures on n-value
tion of strength and ductility after aging, the material should be solution treated at735 °C (1355 "F) for 0.5 to 1 h. Water quenching is preferable for cooling after solution treating
Aging. Treatment should be carried out at temperatures of 425
to 500 °C (795 to 930 "F), Maximum strength can be obtained after aging at temperatures of 425 to 450°C (795 to 840 OF), but long times are required. However, age hardening occurs relatively rapidly at temperatures of475 to 500 °C (890 to 930 oF).
To obtain a higher strength, duplex aging is sometimes used. The first aging is carried out at 425°C (795 "F) for a phase to precipitate finely; and the second aging at 475 to 500 °C (890 to 930 "F) is used to accelerate the growth of the a precipitates. See Figures for:
Recommended Heat Treating Practice Solution treatment conditions depend on subsequent product application. When cold formability is required, the material should be solution treated just above the I} transus (785°C, or 1455 OF). To obtain a better combina-
• • • •
Effect of solution treating temperature on tensile properties Effect of solution temperature on STA tensile properties Aging transformation diagrams Amount of alpha phase during aging
Ti-15Mo-5Zr-3AI: Effectof solutiontemperature on tensileproperties. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF); 98% reduction. Specimens were solution treated for one hour and aged at 500 °C (930 OF) for indicated times
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785 835 885 Solullon temperature, °C
Ti-15Mo-5Zr-3AI: Effectof solutiontemperature on tensileproperties. I} transus is 785°C. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF); 98% reduction. Condition: Solution treated
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Solution temperature, OF 1500 1600
1400
1400
1700 80
1100
~ 1000
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Solullon temperature, OF 1500 1600
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785 835 885 Solution temperature, °C
935
735
180 785 835 885 Solution temperature, °C
935
Beta and Near-Beta Alloys I 593
Ti-15Mo-5Zr-3AI: Effect of solution treatment temperatures on n-value. 1 mm (0.04 in.) thick cold rolled sheet heat treated at 1100 QC (2010 QF), 90%, hot rolled + ST, 30 min, WQ + 86%, cold rolled + ST, 30 min, WQ
Ti-15Mo-5Zr-3AI: Aging transformation diagrams. 9.5 mm (0.35 in.) diameter bar hot rolled at 880°C (1615 OF); 98% reduction, X-ray diffraction
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0
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900
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10
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1475(214) 14 59 412 1.06{a) 3.06 685(100)
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700
.. 0.--
8
5000 mn
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..
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1100
1000
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Ti-15Mo-5Zr-3AI: Mechanical properties of duplex aged specimens
425°C(795°F),1ooomin+475°C (890 oF),1000min 42SOC(795oF),1000min+ 500 °C (930 oF),1000min
Reduetkm oforea, %
Hardness
ElongatIDn, %
(lOkgl, HV
1585
230
10
52
413
1558
225
10
58
417
Note: 9.5 mm (0.35 in.) diameter bar hot rolled at 880 °C (1615 oF),98% reduction.(a) Solution treatment:735°C (1355 oF),60 min, WQ
Ti-15Mo-5Zr-3AI: Chemical composition H(a)
O(a)
N(a)
Chemicalcomposition,% Fe(a) AI Zr
0.020
0.20
0.05
0.35
2.5-3.5
(a)Maximum. All product forms bar, wire, sheet,plate
4.5-5.5
Mo
'Ii
14.0-16.0
rem
o 350
400
'.
1/
, ,
. ,I;
<,
I·
t
'A
-,
10 , min./'
'!ensile strength MPa ksi
Ql
I-
Ti-15Mo-5Zr-3AI: Amount of a. phase during aging. '0 = /{101O}) 1{200}~. 9.5 mm (0.35 in.) diameter bar hot rolled at 880 DC (1615 OF), 98% reduction. X-ray diffraction
Note: Specimensaged at 735 °C{1355 "P), WQ + 500 °C{930 oF),1000min. 9.5 mm (0.35in.) diameter bar hot rolled at 880°C (1615 "F), 98% reduction. (a) Notched tensile strength/tensile strengthratio wilh notch factor (K,) indicated
Aging treatmeot(a)
l!!' :::l
Time, min
Ti-15Mo-5Zr-3AI: Mechanical properties of aged specimens Tensilestrength,MPa (ksi) Elongation,% Reductionof area, % Hardness,HV (1Okg) NTSIIS ratio(withK, = 5.3) Charpy impactstrength, kg . m1cm2 Fatigue strength, MPa (ksi)
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300
•
700
1000
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350
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550
-r-o
600
594/ Heat Treater's Guide: Nonferrous Alloys
Ti-11.5V-2AI-2Sn-11 Zr Commercial Names. Common name. Transage 129; Trade names. Transage 129. T 129
UNS Number. Unassigned Chemical Composition. See Tables for composition limits of wrought alloy. Transage 129 is a martensitic, high-hardenability, age-hardenable, highstrength titanium-base alloy. It is a noncommercial, experimental alloy
Characteristics Product Forms. Transage 129 can be produced in all mill product forms Applications. The alloy is intended to improve structural efficiency in chemical and air frame applications. Transage 129 is less sensitive to the usual impurities than other (non-Trans age) titanium alloys and has excellent fatigue resistance
under a triaxial stress state, e.g.,.at the tip of a crack loaded in tension, undergoes strain-initiated, stress-induced transformation. This is an energy-absorbing phenomenon that increases resistance to crackpropagation. See Tables for: • Recommended heat treatments • Oxidation and contamination • Effect of alpha case on tensile properties See Figures for: • Mechanical properties vs. solution annealing • Ductility vs. solution annealing • Mechanical properties vs. solution annealing
Fabrication Properties
Transage 129: Oxidation and contamination
The alloy is formable. weldable, and forgeable. It has good formability and can be drawn at room temperature into deep cups with reasonable die radii. Transage 129 is especially recommended for cold formable sheet applications and it can be welded by all methods.
Oxide and excase depth vs. Larson-Miller parameter for heating in air for l-h exposure
Weld efficiency of 100% has been demonstrated to strength levels to 1446 MPa (210 ksi) for two-pass electron beam transverse weldments on 1.4 mm (0.056 in.) sheet. The alloy has excellent net-shape capability by isothermal forging, which can be done at temperatures as low as 650°C (1200 "F), although beta forging at 760 to 815 °C (1400 to 1500 OF) is considered optimum
Recommended Heat Treating Practice Transage 129 is typically aged to strength levels of 1240 MPa (180 ksi) or higher. In common with other Transage alloys, it has exceptionally high hardenability. Uniform age hardening is obtainable in heavy sections that are air cooled from beta solution heat treatment to achieve strengths of 1240 MPa (180 ksi) or higher. In the age-hardened condition, Transage 129
Treatment
Solution(~) annealof sheet 760 1400 Solution(~) annealof heavy sections 815 1500 Aging (after solutionanneal) 455-565 850-1050 425-540 795-1000 Isothermal transfonnation(b) Triplextreabnent(c) See above 1st stage (~ anneal) 2nd stage (ex-~ anneal) 650 1200 3rd stage (age) 425-480 8OD-9oo
°C
OF
677 732 760 788 815 871
1250 1350 14OO(a) 1450 1500 1600
Oxide fllm Ihkkness
JlID
0.1 0.3 0.36 0.4 0.6 0.6
Contwnlnation
'lbtaI o>dele and
depth
oontwnlnation
mils
JlID
mils
JlID
mils
2 8 9 10 14 15
1.0 2.1 2.2 2.3 2.4 3.3
25 53 56 58 62 83
1.1 2.4 2.6 2.7 3.0 3.8
27 61
Transage 129: Composition limits of wrought alloy Compooltloo, wt iii
Element
yttrium
1.7-2.7 0.08 max 0.20 max 0.05 max 0.I5max 1.5-2.5 10.5-12.5 10.0-12.0 0.03 max 0.015 max 0.005 max
Residualelements Each Total TItanium
0.10 max 0.40 max bal
Iron
Duration,
Cooling
h
method
0.3 1 24 24
Fan air cool Waterquench(a) Air cool Air cool
1 24
Fan air cool Air cool Air cool
(a) Waterquenching for heavy sectionfor maximumformability, If aging follows solutionanneal, any convenient cooling rate may be used. (b) Solution treatment and isothermal transformation (STlT)produceshighertoughnessthanSTA.(c) For superiorfatigue resistance
66
68 76 98
Note: From730 to 815°C (1345 to 1500 "F) intergranulardiffusionof oxygen is faster than intragranular.At 870°C (1600 "F), the two rates areabout equal,and oxide dissolutionat the interfaceis fasterthanoxide formation.(a)Interpolatedvalues
Aluminum Carbon
Transage 129: Recommended heat treatments Thmpernlure
'Iemperature
Nitrogen Oxygen TIn Vanadium(a) Zirconium Boron Hydrogen
(a)The vanadium-aluminummasteralloy (nominally 15to 17 W!%aluminum)additionis to be calculated toobtain the nominalvanadiumcontent of 11.5 W!%
Transage 129: Effect of ex case on tensile properties Queocbing
Fan air cool Fan air cool Water Water
Milled!o)
No Yes No Yes
Ultimate tenslle strength MPo ksi
781±6 834±0 788±4 824±2
113.3±0.9 121.0±0.0 14.3±0.6 1l9.5±0.3
ThIL'Jile yield strength MPo ksI
593±16 520±8 365±27 295±14
86.0±2.3 75.4± 1.2 52.9±3.8 42.8±2.0
Elongation,
Reduction
iii
or area, iii
9.0 ± 0.0 18.7± 1.2 13.3±0.6 19.0±0.0
11.6±0.9 33.7±2.7 27.1 ±3.0 39.7
Note: 6.6 mm (0.26in.) plate producedfrom 820 kg (1800 Ib) ingot.Beta solutionannealedat815 °C (l5oo "F), I h. Sand blasted 10 remove oxide scale. Tensiletest valuesgiven are average and standard deviationfor three tests.(a)Milled 0.25 mm (0.010 in.) from surfaces
Beta and Near-Beta Alloys I 595
195
45
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gf 35 Q)
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a 30
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~ 25
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175
170,1-._ _--'-_ _---L-_ _----'--_ _- - - '_ _----' 1300
1400
1500
1600
Temperature,
:J
20,L._ _-'-_ _--'-_ _-'-_ _-'-_ _--'
1800
1700
1300
OF
1400
1500
1600
Temperature,
1700
1800
OF
(b)
(8)
20
\
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\
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Transage 129: Mechanical properties vs. solution annealing. Effect of solution heat treatment temperature on tensile properties and fracture toughness of 25 mm (1.0 in.) Transage 129 plate. The solution heat treatments were followed by a water quench. Aged at 510°C for 24 h, AC
1400
1500
-'-----_ _~
1600
Temperature,
1700
1800
OF
(c)
Ti·12V·2.5AI·2Sn·6Zr Commercial Names. Common name. Transage 134; Trade names. Transage 134,Tl34 UNS Number. Unassigned Chemical Composition. Transage 134 is a noncommercial, experimental alloy. See Table for wrought and cast compositions
Characteristics Product Forms. Transage 134 can be produced in all mill product forms Applications. Transage 134 is a high-strength titanium-base alloy recommended for applications where high strength and high fracture toughness are desired in heavy sections. Like Transage 129 and 175, Transage 134 is an age-hardenable ~ alloy that partially transforms to martensite during quenching. For typical applications, Transage 134 can be aged to strength levels of 1140 MPa (165 ksi) or higher. At high strength levels it has the highest fracture toughness of the Transage alloys. In common with other Transage alloys, Transage 134 has exceptionally high hardenability. Uniform age hardening is obtainable in heavy sections air cooled from ~ solution heat treatment to achieve strengths of 1140 MPa (165 ksi) or higher
Fabrication Properties The alloy is weldable, castable, and forgeable. Weldability and castability are good, and the alloy has net-shape capability by isothermal forging, which can be performed at temperatures as low as 650°C (1200 oF), although 815 °C (1500 OF) is considered optimum
Recommended Heat Treating Practice Transage 134 has exceptional hardenability. For example, a 45 kg (100 lb), 200 mm (8 in.) diam billet was air cooled from ~ solution heat treatment and age hardened uniformly to a yield strength of 1014 MPa (147 ksi). For maximum fracture toughness and fatigue resistance at strength levels higher than 1240 MPa (180 ksi) , continuous grain-boundary must be controlled. Continuous a in prior-B grain boundaries results when a cooling rate from ~ solution annealing slower than a water quench is followed by an a-~ solution anneal. This grain-boundary a is detrimental to fracture toughness. Continuous grain-boundary a does not result when an a-~ solution anneal follows a water quench from ~ solution anneal because of the differences in the mechanisms ofage hardening between orthorhombic (stress-induced) martensite (o") and hexagonal close-packed (hcp) (a'). See Tables for recommended heat treatments, and for effects of heat treating variables on double-aged mechanical properties.
596/ Heat Treater's Guide: Nonferrous Alloys Transage 134: Recommended heat treatments
Transage 134, wrought, cast: Composition (wt%) Element
Thmperature
wt%
-c
'freatment Aluminum Carbon
yttrium
2.0-3.0 0.08 max 0.20 max 0.05 max 0.15 max 1.5-2.5 11.0-13.0 5.5-6.5 0.03 max O.oI5 max 0.005 max
Other Each Tola! Titanium
0.10 max 0.40 max bal
Iron
Nitrogen Oxygen
Tm Vanadium(a) Zirconium Boron Hydrogen
OF
815 Betasolutionanneal 440-525 Agefor maximum strength (1l70-1585MFa, or 170-230ksi) Doubleagefor maximum toughness: 550-595 First age 455-480 Second age Treatment for maximumtoughnessandfatigueresistance: 815 Solution anneal 650-705 aJ~ anneal 455 or 480 Age
CooUng method
Duration
1500 820-970
0.25-1h ACorOQ(a) 24 h below480°C AC (900 oF), or 4 h for higher temperatures
1020-1100 850-900
2h 24h
WQ AC
1500 1200-1300 850-900
0.25-lh Ih 24h
WQ ACor OQ(a) AC
(a)Oilquench(OQ)forheaviersections,but do not waterquench(WQ)
(a)The vanadium-aluminum masteralloy(nominally15to 17 Wl% AI)additionis to be calculated to obtainthenominalvanadiumcontentof 12.0Wl%
Transage 134: Typical tensile properties Material andsolullon healtreatment
Aglng treatment Fin!
1.4mm (0.056in.)sheet,coldrolled28%reduction 760°C (14000F)lO.5 hlFAC 25 mm(1 in.) platerolledfrom870°C (1600"P), 45 kg (100lb)ingot,815°C (l500°F)lI hlAC 13mm (0.5 in.) platerolledfrom815°C (1500oF), 273 kg (600Ib) ingot,815°C (1500°F)lI hiAC,fITSt agingfollowedbyWQ 19x 102x 1220mm(0.75x4x48in.)hanunerforged bar273kg (600lb) ingot,815°C(1500 °F)ll hlFAC, !irstagingfollowedby FAC 51 x51 x76mm(2x2x3 in.)blockisothermal1y forged initially at 815°C (1500oF) andfmishedat732°C (1350 oF), 273kg (600Ib)ingot,815°C (1500°F)lI hlFAC 127mm(5 in.jbarextruded from815°C (1500oF) from273 kg (600lb)as-eastingot,815°C (1500°F)/24hlAC; 815°C (1500 °F)lI hlAC (averagecoolingratefrom650t0315 °C (1200to 600 oF) 8 °Clmin (14 OF/min) Cast-to-size andIDPbars. 6.4mm (0.25in.)reducedsection, 815°C (15000F)l 1 hlAC, averagecoolingrate35 °Clmin(64OF/min) 203 mm(8 in.) diam45 kg (100Ib)forgedbillet, 815°C (1500°F)ll hlACin ordertoestimatethe age-hardening responseof a 1364kg (3000lb) S!reSS joint
°C(°F)
h
440(820) 455(850) 595 (1100)
24 24 1
No. or
Second °C(°F) h
specimen
Ultimate tensile strength MPa ksi
ThmUeyield strength MPa ksI
1593 1531 1138
231 222 165
1551 1489 1060
Redudion
Elongation, of'area, %
%
225 216 154
1.3 1.8 14
45
8.5
25
480(900)
4
3 2 2
595 (1100)
480(900)
4
2
1193
173
1135
165
595 (1100)
480(900)
4
3
1205
175
1135
165
10
29
2
1197
174
1142
166
5
9
524(975)
4
705 (1300)
480(900)
4
2
1289
187
1172
170
4
6.5
650(1200)
538 (1000)
4
2
1151
167
1082
157
6.5
9.0
2
1227
178
1165 1014
169 147
5.0
6.0
540(1000) 552(1025)
24 2
Transage 134: Effectsof heat treatment variables on double-aged mechanical properties Ulthnate temile strength Variable
Direclion(a)
MPa
870°C vs. 815 ·C/I hfAC; 565 °C/l hf AC; 480 ·C/4 h/AC 870°C(I600 oF) L 1200 815°C (1500 oF) L 1269 Netchange -69 870°C/l hfAC; 565°C/l hfWQ vs, AC; 480 ·C/4 hfAC WQ 1248 L AC 1200 L Net change +48 815·C/I h/FAC; 565 OC vs. 595 ·C/2 hfWQ; 455 ·C/24 hfAC 565°C (1050 oF) T 1207 595°C (1100oF) 1131 T Netchange +76
Yield strength
Reduction
Fracture tougl1na>
Elongation,
of area,
ksi
MPa
ksl
%
%
MPa'liii"
ksl'JiiL
174 184 -10
1138 1213 -76
165 176 -11
7.0 4.0 +3.0
17 7 +10
53.1 55.4 -2.3
48.3 50.4 -2.1
181 174 +7
1200 1138 +62
174 165 +9
7.5 7.0 +0.5
12 17 -5
55.3 52.7 +2.6
50.4 48.0 +2.4
175 164 +11
1131 1069 +62
164 155 +9
9.0 10.0 -1.0
33 33 0
51.1 50.3 +0.8
46.5 45.8 +0.7
Note: Conclusionsfrom thislimitedstudyare thatfor higherstrengthand slightlyhigherfracturetougbness: (1)solutionannealat 815°C (1500 "F) rather thanat 870 °C (1600 "F), (2) firsttemperature age at 565°C (1050 oF) ratherthanat 595°C (1100 "P), and (3)followwithwaterquenchingratherthan air cooling.(a)L,longitudinal;T, transverse
Beta and Near-Beta Alloys I 597
Ti-13V-2.7AI-7Sn-2Zr Commercial Names. Common name. Transage 175; Trade names. Transage 175 and T175 UNS Number. Unassigned Chemical Composition. Transage 175 is an experimental alloy. See Table for chemical compositions of wrought and cast Transage 175
Characteristics Product Forms. The alloy can be produced to all mill product forms Applications. Transage 175 can improve the structural efficiency of and reduce cost-of all applications for titanium alloys. Compared to the most commonly used titanium alloys, it can extend service temperature ranges. Transage 175 exhibits particularly good fatigue resistance in wrought and cast forms. It has demonstrated good endurance limits under various types of fatigue loading and at various temperatures Mechanical Properties. See Tables for typical mechanical properties and for typical tensile properties
Fabrication Properties This age-hardenable, high strength alloy is castable, weldable, forgeable, and extrudable. Castability is rated good.
air cooling for thin sections to be cold formed, or followed by any convenient cooling rate in preparation for age hardening; and (2) solution anneal followed by aging at 425 to 565°C (795 to 1050 "F) depending on strength level desired. For a given aging temperature, the slower the cooling rate from the solution anneal, the lower the yield strength obtained. This type of heat treatment produces yield strength up to 1450 MPa (210 ksi). The annealing temperature required to obtain the lowest strength state is 815°C (1500 OF) for 15 min to 1 h followed by rapid air cool or water quench depending on section size. However, from the standpoint of stress relief, age hardening, per se, eliminates residual stress due to the unique age-hardening mechanism of Transage titanium alloys. Consequently, partial or total age hardening facilitates machining because the workpiece is more stable geometrically as metal is removed. Yield strength can vary from 895 to 1450 MPa (130 to 210 ksi) in inverse relation to age hardening temperature. For a given component, it may be necessary to determine the aging temperature by trial to get a desired combination of strength and ductility and/or toughness. Transage 175 has exceptional hardenability. The alloy readily age hardens to strength levels of 1170 MPa (170 ksi) or higher, following the slow cooling rates imposed by hot isostatic processing facilities and by superplastic forming operations. In steel terms, the ideal round size exceeds 200 mm (8.0 in.). See Tables for typical heat treatments, and for effect of solution temperature. See also Table for tensile properties vs. treatment temperature of cast impeller .
Weld repair capability, by titanium alloy standards, is excellent. Net shape parts can be isothermally forged. Extrusion properties are excellent. In forming sheet, all cold and hot forming methods generally used for titanium alloys are applied. See Table for recommendations for the production of near-net shape and net-shape forgings. See Figure for effect of forging temperatures on mechanical properties. See Table for tensile properties of electron beam welded specimens
Recommended Heat Treating Practice 1\vo types of heat treatments may be applied to Transage 175: (1) solution anneal, preferably at 815°C (1500 OF) for 15 min to 1 h followed by fan
Transage 175: Typical heat treatments STAwrought bar 815°C (1500oF) for I h,coolingrateoptional fromair cool10 waterquenchdepending onsection size,ageal455 °C (850"P) or highertemperature, depending onstrength desired andapplication temperature, for21024 h Castings STA:900°C(1650"P) for2 h, air cool,fanair cool,or forced gascool,age at 540°C(1000oF) for2 h.air cool HIP:900°C (1650oF), 103MPa(15 ksi) for2 h,forcedgascool,ageat540°C (1000"F) for2 h, air cool
Transage 175: Effect offorging temperature on mechanical properties. Tension test properties versus isothermal forging temperature ofa+ ~ preforms upsetto 62% reduction. Specimens were 818 kg (1800 Ib) ingots processed to 160 mm (6.3 in.) round, then cogged to 100 mm (4.0 in.) round at 730°C (1345 OF) for 58% reduction to make a-~ preform stock. Preforms were upset isothermally at various temperatures and 0.42 mm/s (1.0 in.lmin) platen speed. Heat treated at 720°C (1325 OF), 2 h, WO, 480°C (900 OF), 24 h, AC
LIVE GRAPH
LIVE GRAPH
Temperature, OF
Click here to view
1300 1500
140OI-
'" :2
1350
. 0
l:.
o.
1400
1450
1500
I I UTS, radial UTS, tangential TYS, radial TYS, tangential
1300 60 210
~
c
~
....... o. 1:.-"'"
til 1200
.........
190 ~
r---
--
c
UTS
0
..
---<>
TYS
1100 700
725
750
775
Temperature, DC
e
0
•
800
1350
180 til
'if.
40
0_
RA(
~30
U :::l
o
./ 20
--
10
160 825
o
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725
1500
RA, radial RA, tangential Elongation, radial Elongation, tangential
-............
~ -1:.-
~ E\Ongation
o.
700
•
1450
~I'-o-.....
1:.--
170
1400 0
50
200
II.
~ 1300
Click here to view
Temperature, OF
750
-775
Temperature, DC
-
-
•
............ 0
800
825
598/ Heat Treater's Guide: Nonferrous Alloys Transage 175: Effectof solution temperature
Transage 175: Recommendations for the production of near-net-shape and net-shape forgings
RTtensile properties of cast impeller after aging at 540°C (1000 OF), 2 h, AC Ultimatetensile
Thnsileyield
Slnmgth
strength (0.2%) MPa ksi
MPa
ksi
No homogenization(a) 1193 173 1261 183 1193 173 1165 169 1268 184 845°C (1555 oF), 2 h(b) 1152 167.1 1133 164.3 1215 176.3 870 ~C (1600 oF), 2 h(b) 1110 161.0 1211 175.7 1262 183.1 900 °C (1650 oF), 2 h(b) 1202 174.4 1196 173.5 1204 174.7 930°C (1700 oF), 2 h(b) 164.7 1135 1147 166.4 1226 177.9
Reduclion Elongation,
erarea,
%
%
1186 1261 1172 1165 1255
172 183 170 169 182
0.3 0.2 3.9 0.4 0.9
0.8 0.8 9.4 0.0 0.0
1137 1096 1194
164.9 159.0 173.2
3.9 3.5 3.0
5.2 4.8 3.2
Equipment Thmperature of diesand workpiece Platenspeed Solutionheattreatment Temperature Time Coolingrate Heavy sections Light sections Agingtreatment Temperature Time Coolingrate
1195 1235
173.4 179.1
3.1 2.9 3.3
2.4 2.4 3.2
1161 1163 1155
168.5 168.7 167.5
4.1 4.6 4.3
3.2 7.8 5.6
1089 1107 1192
158.0 160.6 172.9
3.1 3.6 3.7
4.0 3.2 3.2
Isolhermalpress 815°C ± 15(1500± 25 oF) 0.21mm1s (0.5 inJmin) 815 °C±15°C (l500±25 oF) 0.5tolh
Fan aircool,or waterquench Aircool 455t054O±5 °C (850to lOoo± 10 oF), dependingon strenglhdesired. Strenglhrange from 1520to 1170MPa (220to 170ksi) 4 h forshort-timestrenglh;24 h for long-timestrenglhat elevated temperatures and agingtemperatures below480°C (900 "F) Aircool
Note: At 815°C (1500"F), Transage175 has a flowstressof 43 MPa (6200psi).The alloywillflow at constantload as long as the load per unit plan areaexceeds the flow stress.If shape is to be net, chemicalmill to removesurfacecontaminationand to meet drawingdimensions
Transage 175: Chemical composition Composillon,
Speclllcatlonrequirements
wt%
(a)Baseline;no homogenization; 815°C (1500"P), 2h, gasfan cool. (b) Plusfurnacecooledto 540 °C (1000 "F), thenremovedfromfurnaceandair cooled.Solutionheat treatedat 815°C (1500"F), 2h, gasfancooledandaged540 °C (1000 "F), 2h,AC
Aluminum Carbon Iron Nitrogen Oxygen Tm
Transage 175: Tensile properties vs. solution treatment temperature of cast impeller. Tensile properties with standard deviation bars for specimens taken from the base of 267 mm (10.5 in.) diameter cast impeller vs. temperature of 2-h solution heat treatments; 900°C (1650 OF) appears to be optimum for solution heat treatment or HIP temperature. Processing: HIP 815 °C (1500 OF), 2 h, 103 MPa (15 ksi), heat treated at 900 °C (1650 OF), 2 h, furnace cooled to 540 °C (1000 OF), then AC, 540°C (1000 OF), 2 h,AC LIVE GRAPH
Vanadium(a) Zirconium Boron Hydrogen yttrium
Residualelements, each Residualelements, total TItanium
'Irsnsage175,wrought
'ftansage175C,caotiugo
2.2-3.2 0.08 max 0.20 max 0.05 max 0.15 max 6.5-7.5 12.0-14.0 1.5-2.5 0.03 max 0.D15max 0.005 max 0.10 max 0.4 bal
2.0-3.0 0.08 max 0.20 max 0.05 max 0.15 max 6.5-7.5 11.0-13.0 1.5-2.5 0.03 max 0.015 max 0.005 max 0.10 max 0.40 max bal
(a)The vanadium-aluminum (nominally15to 17 wt% aluminum)masteralloyadditionis to becalculatedtoobtainthenominalvanadiumcontentof 13.0 wt% for wroughtproductsand 12.0wt% for electrodestockforcastings
Click here to view 1500
Solution treat temperature, OF 1550 1600 1650 1700
Transage 175: Tensile properties of electron-beam welded specimens
1300
~
/ ~
1200
'~ V.
~
£ C, c
~
en
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180
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1100
0 1000 800
'"
--
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1
Thnsile yield strength (0.2 %) IW MPa
strength MPa ksi
None
1256 1284 1270 1293 1340 1317 1317 1310 1313
1330 1352 1341 1340 1374 1357 1350 1384 1367
150 950
°c
Uhhnate lensBe
No.of EBpasses
Avg. One
UTS TYS 850 900 Solution treat temperature,
<,
Tensile properties of specimens containing transverse EB weldments, post-weld aged at 525 °C (970 OF), 22 h, AC
Avg. '!\yo Avg.
182.1 186.3 184.2 187.5 194.4 191.0 191.0 190.0 190.5
192.9 196.1 194.5 194.4 199.3 196.8 195.8 200.7 198.2
EIoogation, %
5 5 5 4 4 4 5 5 5
Fracture IIlte
BM BM BM BM
Note:The rnaterial ,a 356mm (14in.) diameterspin-forgedcylindermachinedto 1.8mm (0.070in.) thickness,was preaged510°C (950 "F), 2 h, ACfor stabilityin machining,welded,and post-weld aged 525°C (970 oF), 22 h, AC.Testspecimenswereaxial,and the gage dimensionswere6.4x 25 mm (0.25x 1 in.)
Beta and Near-Beta Alloys
I 599
Ti·8V·5Fe·1 AI UNS Number. Unassigned
Welding. Not recommended
Chemical Composition. See Table for typical composition
Recommended Heat Treating Practice
Characteristics Product Forms. The alloy is supplied only on special order, generally as bar and billet Applications. Ti-8V-5Fe-IAI is a metastable ~-titanium alloy that is capable of achieving an ultimate tensile strength of more than 1380 MPa (200 ksi) and a shear strength of more than 795 MPa (115 ksi). Special precautions must be taken when melting the alloy because of the segregation tendency of iron.
Ti-8V-5Fe-IAI has been used for aerospace fasteners and has potential in applications where high ultimate and shear strengths are critical
The alloy can be hardened by solution treating and aging. It has a beta transus of 830 ± 14°C (1525 ± 25 "F). See Tables for: • • • • •
Typical heat treatments Guaranteed STA room temperature properties Annealed room temperature tensile properties Effect of cooling on STA properties Effect of aging on RT tensile properties
Fabrication Properties
See Figures for:
Forging. TI-8V-5Fe-IAl is readily forgeable. However, the material should receive final reductions of at least 50% below 815°C (1500 OF) to optimize ductility
• Effect of solution treatment temperature on tensile properties (a) and (b) • Effect of solution treatment and aging on tensile properties (a), (b), (c), and (d)
LIVE GRAPH
Ti-8V-5Fe-1AI: Effect of aging on RT tensile properties. 16 mm (0.625 in.) diam bar 1800 - - - - - - - - - - : . .
LIVE GRAPH
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• Ultimate strength
Yield strength
260
80
250
70
240
60
230 ';;;
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220
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AC AC AC AC
Reduction of area
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760°C, 760°C, 760°C, 760°C,
50
s
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24
0
4
8
12 16 Aging time, h
20
24
Ti-8V-5Fe-1 AI: Effect of solution treatment temperature on tensile properties. 16 mm (0.625 in.) diam bar, solution treated 1 h, water quenched + 540°C (1000 OF), 8 h, air cooled
LIVE GRAPH Click here to view
LIVE GRAPH Solution temperature, OF 1380 1400 1420 1440 1460 1480 1500
1700
17
J
Ultimate Jength lU
1600
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\ Elongation (25 mm)
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o
190 760 780 800 Solution temperature, °c
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240
Yield strength
c/
Solution temperature, OF 1400 1420 1440 1460 1480
820
740
(b)
i
I_
!~ 0
760 780 800 Solution temperature, °c
820
600 I Heat Treater's Guide: Nonferrous Alloys
Ti-8V-5Fe-1 AI: Effect of solution treatment and aging on tensile properties. 14 mm (0.625 in.) diam bar. solution treated 0.5 h, water quenched, aged 2 h, air cooled; room-temperature tests
LIVE GRAPH
LIVE GRAPH Click here to view 930
Aging temperature, of 940 950 960 970 980
990 1000
930
1650
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Aging temperature, of 940 950 960 970 980
990 1000
1700 240
230 III
15501t-----=.......± : - - - - - t - - - - - - - - t
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00
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----I
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510 525 Aging temperature, °c
510 525 Aging temperature, °c
540
(8)
(b) 930
Aging temperature, of 950 960 970 980
940
990
1000
930
20
60 --7750C 760°C - . 745 °c
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510 525 Aging temperature, °c
495
(c)
510 525 Aging temperature, °c
(d)
Ti-8V-5Fe-1AI: Elastic modulus
Ti-8V-5Fe-1AI: Annealed room-temperature tensile properties Elasticmodulus
'Thmperature of "C
lIT
315
600
540
Annealed 10'ps; GPa
114 101
16.5 14.7
Solutiontreated + aged GPa 10' psi
114 100
Ti-8V-5Fe-l AI: Guaranteed STAroom-temperature properties Property
Ultimate tensilestrength,MPa(ksi) Tensile yieldstrength,MPa(ksi) Elongation (in4D), % Reduction inarea,% Ultimate shearstrength,MPa(ksi) (a)Minimums forsizesup to 27 mrn(1.0625 in.)in diameter
16.5 14.5
YJe1d lilreogth
Ultimate Anneallng
strength
Reduction Elongation or........
treatment
MPa
IIsI
MPa
lis!
...
...
675°C (1245 oF), 30 min,AC 720°C (1325 oF), 30 min,AC 760°C (1400oF), 30 min,AC 675°C(1245oF), 30 min,Fe to 480°C (900°F),AC
1263 1210 1179 1236
183.0 \75.3 170.9 179.1
1233 1170 1151 1214
178.7 169.5 166.8 175.9
15.0 16.0 13.5 20.5
47.5 47.7 43.0 52.9
Thnsile properties of6.4 mrn(0.25in.)specimens from9.5mrn(0.38in.)bar annealedas indicated
MinImumvalue(a)
1448(210) 1380(200) 6.0 12.0 793(115)
Ti-8V-5Fe-1AI: Typical heat treatments 'Thmpemture 'fteatmeot
Suess relief Anneal Alternate production anneal Solution treat Alternate solution annealing range Aging
"C
OF
DllI8tion
Cooling
540-590 675 675-730 760 730-79O(a) 480-540
1000-1100 1245 1245-1345 1400 1345-1455(a) 900-1000
Ih Ih 1-2h Ih
Aircool Pumacecool Air cool Waterquench
2h
Air cool
(a)Depending on productformanddesiredproperties
Beta and Near-Beta Alloys 1601
Ti·16V·2.5AI UNS Number. Unassigned
Recommended Heat Treating Practice
Characteristics
The alloy is strengthened by solution treating and aging.
Phases and Structures. In the solution-treated condition, Ti-16V-2.5A1 consists of all Il phase. The alloy is relatively lean in Il-stabilizers and can form stress-induced martensites when deformed in the solution annealed condition. After aging, the microstructure consists of fine a in a Il matrix
A range of tensile properties is attainable, with yield strength values greater than 1240 MPa (180 ksi) possible. The formation of stress-induced martensite in solution-annealed material can result in a relatively low ratio ofyield to tensile strengths.
Beta Transus. Not available
See Table for room temperature moduli of STA sheet
Product Form. Alloy is available only (as sheet) on special order Applications. Alloy was developed for high strength sheet applications
Ti-16V-2.5AI: Room-temperature moduli of STA sheet
in aircraft
Sheet thkkness DUD
10.
Direction
0.5
0.Q2
Final forging temperatures should be maintained in the a-Il phase field
1.6
0.063
Machining. Ti-16V-2.5AI is expected to have machinability similar to other metastable Il titanium alloys, such as Ti-15V-3Sn-3Zr-3Cr and Ti3AI-8V-6Cr-4Mo-4Zr
3.2
0.125
L T L T L T
Fabrication Properties Forging. Like most Il titanium alloys, Ti-16V-2.5AI has good forgeability.
Thnsilemodulus IO'psi GPa
99.3 96.5 95.8 97.9 95.2 96.5
14.4 14.0 13.9 14.2 13.8 14.0
Compressivemodulus 10' psi GPa
'J7.2 'J7.2 102 103
14.1 14.1 14.8 15.0
Solutiontreatedat750 to 765°C (1380101410 "F) for 30 min.aircooledand aged at 52510530°C (970 to 985 oF) for 4 to 6 h
Heat Treating Cast and P/M Titanium As the adjoining Table indicates, advances are being made in the thermal and thermochemical methods of heat treating cast and PIM titanium. Conventional heat treatment of titanium castings is for stress relief anneal after any weld repair. The Ti-6AI-4V alloy is typically heat treated at 730 to 845°C (1350 to 1550 "F), This is done in a vacuum to ensure the removal of any hydrogen pickup from chemical milling and to protect the
titanium chemically milled surface from oxidation. As with HlP and weld repair, castings must be chemically cleaned prior to heat treatment if diffusion of surface contaminants is to be avoided. Alternate heat treatments for property improvement, such as the solution treating and aging of castings are outlined in the Table titled ''Treatments for modifying the microstrucure of cast and PIM titanium products."
Modifying Microstructure Most Ti-6AI-4V titanium castings produced commercially today are supplied in the annealed condition. However, much microstructural modification development work has been done recently, and it can be expected that solution-treated and aged or other postcast thermal processing will eventually become specified on cast and PIM parts requiring certain property enhancement such as fatigue or tensile strength. Modification of microstructure is one of the most versatile tools available in metallurgy for improving the mechanical properties of alloys. This is commonly achieved through a combination of cold or hot working followed by the heat treatment known as thermomechanical processing. Net shapes such as castings or PIM products cannot be worked, which limits the options for controlling microstructures. Most of the new treatments can be applied to both cast parts and PIM compacts.
In the case of titanium alloy castings, the main goal has been to eliminate the grain-boundary ex phase, the large ex plate colonies, and the individual ex plates. This is accomplished either by solution treatments or by a temporary alloying with hydrogen. In some cases, the hydrogen and solution treatments are combined. The typical resulting microstructures of the ex-~ solution treatment (ABST), ~ solution treatment (BST), broken-up structure (BUS), and high-temperature hydrogenation (HTH) methods are shown in an adjoining Figure. As can be seen from the photomicrographs, these treatments eliminate the large ex plate colonies and the grain-boundary ex phase. A substantial improvement of both tensile and fatigue properties results.
Hot Isostatic Pressing Hot isostatic pressing may be used to ensure the complete elimination of internal gas and shrinkage porosity. The cast part is chemically cleaned and placed inside an autoclave, where it is typically subjected to an argon pressure of 103 MPa (15 ksi) at 900 to 955°C (1650 to 1750 "F) for a 2 h hold time (Ti-6AI-4V alloy) for void closure and diffusion bonding. Recently, a HIP pressure of 206 MPa (30 ksi) has been employed in the hot isostatic pressing of high-temperature titanium alloys to ensure pore clo-
sure in these harder-to-deform materials. This practice has been shown to reduce the scatterband of fatigue property test results and improve fatigue life significantly. HIP temperature may coarsen the ex platelet structure, causing a slight loss in tensile strength, but the benefits of HlP normally exceed the decrease, and the practice is widely used for' aerospace cast parts.
Weld Repair The weld repair of titanium castings is an integral step in the manufacturing process and is used to eliminate surface-related defects, such as HlP-induced surface depressions or surface-connected pores that did not close during the HIP cycle. Thngsten inert-gas (TIG) welding practice in argon-filled glove boxes is used with weld filler wire of the same composition as the parent metal. Generally, all weld-repaired castings are stress relief annealed. Excellent-quality weld deposits are routinely obtained in
proper practice. Weld deposits may have higher strength but lower ductility than the parent metal because of microstructural differences due to the fast cooling rate of the welding process and some oxygen pickup. Those differences may be eliminated by a postweld solution heat treatment, but standard practice is for stress relief or anneal only. Also, welding rods containing lower oxygen-content alloys are commonly used.
Cast and P/M Titanium 1603
Photomicrographs of Microstructures. Photomicrographs of microstructures resulting from a variety of hydrogen and solution heat treatments used to eliminate large a plate colonies and grain boundary a phase in a+ ptitanium alloys. (a) ASST. (b) SST. (c) SUS. (d) HTH
(0)
(b)
(0)
(d)
Treatments for modifying the microstructure of cast and P/M titanium products Method(a)
Typical
Hydrogenation
solution treatmcnt(h)
temperature OF °C
BUS GTEC
1040°C(1905 OF) for0.5h 1050°C (1920 oF) for0.5h
BST ABST HVC (Hydrovac process) TCT CST
1040°C (1905oF) for0.5 h andGFC 955°C (1750"F) for I h andGFC
HTH
1040°C (1905oF) for0.5 h
Intermediate treatment(c) °C
OF
Dehydrogenation temperature OF °C
Typical
annealing or aging treatment 845°C (1555 oF) for24 h 845°C (1555 "F) for0.5h and 705°C (1300 oF) for 2 h 540 °C (1000 oF) for8 h 540°C (1000 oF) for8 h
650 595 870
1200
900
1650
llOO 1600
870(e) 1600(e) CooltoRT No intermediatestep (continuousprocess) CooltoRT
Applied to product forms(d)
Ref
Cast,PIM, JJM Cast
34-37 38 39 39 40,41 41-43
45
760 760 815
1400 1400 1500
Cast,JJM Cast,JJM PIM,JJM Cast, PIM, JJM Cast
705
1300
Cast, PIM,JJM
44
(a)Most data apply to Ti-6AI-4V, ~ transustemperature approximately 995°C (1825 "F), (b) GFC, gas fan cooled.(c)RT,room temperature. (d) PIM,powdermetallurgy; JJM, ingot metallurgy. (e) Glass encapsulatedprior to heat treatment
6041 Heat Treater's Guide: Nonferrous Alloys Typical room-temperature tensile properties of titanium alloy castings (bars machined from castmgs)
Standard industry specifications applicable to titanium castings
Specification minimums are lessthan these typical properties.
MIL-T-81915 AMS4985A AMS4991 ASTMB367 MIL-STD-2175 MIL-STD-271 MIL-STD453 MIL-Q-9858 MIL-I-6866B MIL-H-81200 ASTMEI55 ASTMEI92 ASTMEI86 ASTME446 ASTMEI20 ASTME8 AMS-2249B AMS4954 AMS4956
AIJoy(a)(b)
Yieldstrength MPa ksl
Commercially pure(grade2) TI-6Al4V,annealed TI-6Al4VEU TI-Il00, Beta-STA(e) TI-6Al-2Sn4Zr-2Mo, annealed IMI-834, Beta-STA(e) TI-6Al-2Sn4Zr-6Mo, Beta-STAle) Ti-3Al-8V-6Cr4Zr4Mo, Beta-STA(e) Ti-15V-3Al-3Cr-3Sn, Beta-STA(e)
448 855 758 848 910 952 1269 1241 1200
65 124
no
123 132 138 184 180 174
Ultimate strength ksI MPa
552 930 827 938 1006 1069 ,1345 1330 1275
80 135 120 136 146 155 195 193 185
Elongation, ReduclloooC
...
18 12 13 11
10 5 1 7 6
area,'" 32 20 22 20 21 8 1 12 12
(a) Solution-treated and aged(STA) heat treatments may be variedto producealternate properties. (b) ELI,extralowinterstitial. (c)Beta-STA, solutiontreatment withP-phase fieldfollowedbyaging
TItanium andtitanium alloycastings, investment Titanium alloycastings, investment orrammed graphite Titanium alloycastings, investment TItanium andtitanium alloycastings Castings, classification andinspection of Nondestructive testingrequirements for metals Inspection, radiographic Qualityprogram requirement Inspection, penetrantmelhod of Heattreatment oftitanium andtitanium alloys Reference mdlographs forinspection ofaluminum andmagnesium castings Reference mdlographs, investment steelcastings Reference radiographs, steelcastings 50-102mm(24 in.) Reference radiographs, steelcastings upto50mm(2 in.) Standard melhods forchemical analysts oftitaniumandtitanium alloys Melhods oftension testingof metallic materials Chemlcal-check analysis limitsfortitanium andtitanium alloys Titanium alloyweldingwireTi-6Al4V TItanium aIloyweldlng wireTI-6AI4V,extralowinterstitial
Comparison of Fatigue Properties. Comparison of wroughtannealedTi-6AI-4V scatterband with (a)li-6AI-4V investment castingssubjectedto variousthermaland hydrogentreatmentsand (b) heat-treated ptitaniumalloycastings.Fordata in (a),smoothaxialfatiguemeasuredat roomtemperature with R = +0.1 ; frequency = 5 Hz usingtriangularwave form 1200
LIVE GRAPH
160
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1000
140 ]I
::;
ui
ui
~
'lii E :::> E
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120 'lii
800
E :::> E
100
'iii
::;
'iii
::;
600 80 60
400 10 3
10 4
10 5
106
10 7
108
Cycles to failure, N, (a) 1200
LIVE GRAPH
3 - - - Ti-3AI-8V-6Cr-4Zr-4Mo(Bela-C) 10 - - Ti-10V-2Fe-3AI
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1000
-----------
'\
::;
ui
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800
160
- - - - - 3,3
140 ]I
gj
-----3,2 -----3.1
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E :::> E
100
'iii
::;
'iii
::;
600 80 400 10 3
60 10 4
10 5
106
Cycles to failure, M (b)
E :::> E
107
108
Cast and PIM Titanium 1605
Compositions andcomparisons of cast titanium alloys Alloy
TI-6Al-4V TI-6Al-4V EU(b)(cO Commercially puretitanium (grade2) TI-6Al-2Sn-4Zr-2Mo TI-6Al-2Sn-4Zr-6Mo TI-5Al-2.5Sn TI-3Al-8V-6Cr-4Zr-4Mo (Beta-C) TI-15V-3Al-3Cr-3Sn (11-15-3) TI-11oo IMl-834 Thtal
Eotimated relatlwwe orcastings
85% 1% 6% 7% <1% <1% <1% <1% <1% <1% 100%
0
N
C
H
AI
0.18 0.11 0.25 0.10 0.10 0.16 0.10 0.12 0.07 0.10
0.015 0.010 0.015 0.010 0.010 0.015 0.015 0.015 0.015 0.015
0.04 0.G3 0.G3 0.03 0.03 0.03 0.03 0.G3 0.04 0.06
0.006 0.006 0.006 0.006 0.006 0.006 0.006 0.006 0.006 0.006
6 6
Superior,relativetoTI-6AI-4V. (b)lIT,roomtemperature.
6 6 5 3.5 3 6.0 5.8
Nominalcomposition,w i '1> Fe V Cr
0.13 0.10 0.15 0.15 0.15 0.2 0.2 0.2 0.02 0.02
Sn
Mo
Nb
Zr
4 4 2 2 2.5 8.5 IS
6 3
3 2.75 4.0
2 6
4 4
4
4
0.4 0.5
0.7
4.0 3.5
Si
Special pl1lpertles(o)(b)
Generalpwpose Cryogenic toughness Corrosionresistance Elevated-temperature creep Elevated-temperature strength Cryogenic toughness lITstrength lITstrength 0.45 Elevated-temperature properties 0.35 Elevated-temperature properties
Zinc Alloys
Heat Treating Zinc Alloys Zinc alloys are used extensively in both gravity castings (permanent mold and sand castings) and in pressure die castings. On occasion, heat treatment is required for some of the various alloys. Alloys requiring treatment are generally the Zamak die casting alloys (No.2, No.3, No.5, and No.7) and the ZA alloys (ZA-8, ZA-12, and ZA-27), which are used in both permanent mold castings and in pressure die castings.
Slush casting alloys, such as An-4 and 75Al-O.25Cu, do not require heat treatment. Forming die alloys, such as Zn-0.08PB, typically are applied as-cast. Wrought alloys, such as the rolled zinc alloy, Zn-1.OCu, normally do not require heat treatment.
Heat Treatment of Zamak and ZA Alloys 1\vo treatments are available for pressure die castings of both types of alloys: stress relief and stabilization. A different stabilization treatment is available for ZA-27 die castings because they are more susceptible to aging than ZA-8 and ZA-12. A homogenization treatment is also available for ZA-27.
Heat treating practices for these alloys are spelled out in the datasheet articles that follow.
Reasons for Heat Treating The rapid chilling rate inherent in zinc die castings results in minor property and dimensional changes with time, particularly if castings are quenched from the die rather than air cooled. As-cast properties (tensile strength and hardness) of pressure die cast Zamak and ZA alloys are adversely affected by wall thickness and by significant aging that takes place with time at room temperature. In the
aging process, the thinner the wall the greater the reduction in tensile properties. In addition, tensile and yield strength drop markedly with increases in temperature. At 100°C (212 OF) tensile strength and hardness are 65 to 75% of those at room temperature. Creep strength is similarly reduced. Also, ZA permanent mold and sand castings sometimes contain residual stresses due to high thermal gradients during solidification.
Supporting Documentation The effects of temperature on mechanical properties of both Zamak and ZA alloys are given in Table 1. Table 2 gives nominal compositions of rolled zinc alloys. Table 3 lists applications of wrought zinc and zinc alloys. The effects of aging time on the tensile strengths of ZA-27, ZA-8 and alloys No.2, No.3, and No.5 are shown in Fig. 1. Aging results in a general reduction in tensile strength and hardness. The thinner the wall, the greater the degree of reduction. In comparing the performance ofZA-8 with that of the No.3 and No.5 alloys, it appears that ZA-8 is less susceptible to aging, indicating that it would be the most suitable of the three alloys in applications requiring retention of properties. Tensile strengths ofZA-8, No.3, and No.5 die cast strip as a function of time at room temperature are shown in Fig. 2.
Tensile strengths ofZA-8, No.3, and No.5 die cast strip as a function of aging time at 100°C (212 "F) are shown in Fig. 3. Vickers hardnesses of ZA-8, No.3, and No. 5 die cast strip as a function of aging time at 100 °C (212 OF) are shown in Fig. 4. Percentage of elongation in 2.54 cm (1.00 in.) gage lengths of ZA-8, No.3, and No.5 are shown in Fig. 5. Tensile strengths ofas-cast ZA-8, No.3, and No.5 as a function of wall thickness after aging 4 h at 100°C (212 oF) are shown in Fig. 6. Individual datasheet articles, including heat treating practices for the Zamak and ZA alloys, follow. Heat treatment of permanent mold and sand castings is not covered in the datasheets, with the exception of ZA alloy castings.
6101 Heat Treater's Guide: Nonferrous Alloys
Table 1 Effect of temperature on the mechanical properties of zinc-alloyand zinc-aluminum alloy castings Fracture lougJme!oo (averageKkl Alloy
Thmperature OF °C
designation
Conventional die casting alloys No.2 NO.3
21
70
-40
-40
-20 0 21 24 40 95 -20 0 21 40 95
-4 32 70 75 104 203 -40 -4 32 70 104 203
-40
-40
-20 -10 0 20 50 95 150
-4 14 32 68 122 203 302
-40
-40
-20 -10 0 20 24 40 50 60 80 100
-4 14 32 68 75 104 122 144 176 212
-40
-40
-20 0 20 24 40 50 60 80 100 150
-4 32 68 75 104 122 140 176 212 302
-40
-40
-20 -10 0 24 20 40 50 60 80 100 150
-4 14 32 75 68 104 122 140 176 212 302
-40
No.5
No.7
Zinc-aluminum casting alloys ZA-8
ZA-12
ZA-27
Thosilestrength(al ksl MPa
Impactenergy(b) J ft·lbr
359 308.9 301.3 284.8 282.7
52.1 44.8 43.8 41.3 41.0
47.5 2.7 5.4 31.2 58.3
35 2 4 23 43
244.8 195.1 337.2 340.6 333.0 328.2 295.8 242.0 308.9 299.2
35.5 28.3 48.9 49.4 48.3 47.6 42.9 35.1 44.8 43.4
282.7
41.0
232.4 193.1 120.0
33.7 28.0 17.4
57.0 54 2.7 5.4 55.6 65.1 62.4 58.3 1.4 1.9 2.4 3.8 54.2 58.3 54.2 43.4
42 40 2 4 41 48 46 43 1.0 1.4 1.8 2.8 40 43 40 32
409.6 402.7
59.4 58.4
382.7 373.7
55.5 54.2
1 1 2 2 42
1 1 1.5 1.5 31
54
40
56 65 63 1.5 1.5 3 29
41 48 46 1 1 1.7 21
35
26
40 46 46
29 33 34
328.2
Pressure dieeast MPa~m ksNin.
Sand east MPa~m kII'lin.
10.1
9.2
12.3
11.2
10.2
9.3
12.6
11.5
27.7 11.2
25.2 10.2
9.8
8.9
14.4
13.1
14.5
13.2
29.0
26.4
29.1
26.5
11.9
10.8
16.4
14.9
20.2
18.4
23.7
21.6
35.2
32.0
42.1
38.3
47.6
224.1 450.2
32.5 65.3
434.4 403.4
63.0 58.5
349.6
50.7
228.9 119.3 520.6 500.6
33.2 17.3 75.5 72.6
497.1
72.1
425.4
61.7
397.8
57.7
259.3 129.0
37.6 18.7
2 3 7
1.5 2.5 5
13 15
9.5 11
16 16 16
12 12 12
(a) As-cast. (b) As-cast. unnotched 6.35 mm (0.25 in.) square specimen. Source: Engineering PropeniesofZinc Alloys. International Lead-Zinc Research Organization. 1989 and the Noranda Technology Center
Table 2 Nominal compositions of rolled zinc alloys per ASTM B69 Alloy
UNSnumber
Cu
Ph
Cd
Composition, % Femax
AImax
Other max
Zn
Zn-0.08Pb Zn-O.06Pb-O.06Cd Zn-0.8Pb-0.3Cd Zn-ICu Zn-lCu-O.OlOMg
Z21210 Z21220 Z21540 Z44330 Z45330
0.001 max 0.005 max 0.005 max 0.85-1.25 0.85-1.25
0.10 max 0.05-0.10 0.25-0.50 0.10 max 0.15 max
0.005 max 0.05-0.08 0.25-0.45 0.005 max 0.04 max
0.012 0.012 0.002 0.012 0.015
0.001 0.001 0.001 0.001 0.001
bal bal bal bal bal
Zn-0.8Cu-0.15Ti Zn-0.8Cu
Z41320 Z40330
0.50-1.50 0.70-0.90
0.10 max 0.02 max
0.05 max 0.02 max
0.012 0.01
0.001 0.005
0.001 Sn 0.001 Sn O.OOISn 0.001 Sn 0.006-0.016 Mg O.OOISn 0.12-0.50110.001 Sn 0.02Ti
Commondesignalion
bal bal
Zinc Alloys /611
Fig.1 Effect of Aging Time on Tensile Strength of Zinc Alloys. Aging temperature, 100°C (212 OF). (a) 0.76 mm (0.030 in.) casting wall thickness. (b) 1.52 mm (0.060 in.) casting wall thickness. (c) 2.54 mm (0.100 in.) casting wall thickness. Source: Noranda Technology Center
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Applkalioll'l
Deep-drawn hardware. expanded metal Buildingconstruction materials, deep-drawn hardware, coinage Roofing. gutters, anddownspouts; building construction materials; deep-drawn hardware; address plates; solarcollectors Zn-Pb-Cd-Fe Buildingconstruction materials. dry-cellballe!)' cans,deep-drawn hardware, address plates,electrical components Zn-Al(superplastic zinc) Shapedcomponents suchastypewriter casings, computer panels, and COVelli
Purezinc
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Fig. 2 Tensile strengthof (a) 0.76 mm (0.030in.), (b) 1.52mm (0.060in.), and (c) 2.54 mm (0.100in.) thick strips of ZA-8, No.5 and No.3 as a function of time at roomtemperature, 20°C (68 OF). Source: NorandaTechnology Center
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Fig.4 Vickers hardnessof ZA-8, No.5, and No.3 as functionof aging time at 100°C (212 OF): (a) 0.76 mm (0.030 in.), (b) 1.52 mm (0.060 in.), and (c) 2.54 mm (0.100 in.). Source: NorandaTechnical Center
LIVE GRAPH
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1.52 mm (0.060 In.)
160
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160
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Fig.5 Percentageelongationover 2.54 em (1.00in.) gage lengthof ZA-8, No.5, and No.3 as a function of time at 100 °C (212 OF): (a) 0.76 mm (0.030 in.), (b) 1.52 mm (0.060 in.), and (c) 2.54 mm (0.100 in.). Source:NorandaTechnical Center
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24
20
20
20
16
16
16
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614/ Heat Treater's Guide: Nonferrous Alloys
Fig.6 (a) Tensile strengthof as-cast No.3, No.5, andZA-8 as functionof wallthickness. (b) Tensile strengthof the alloysafter aging for 4 hat 100°C (212 OF) as function of wall thickness. Source: NorandaTechnical Center
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Thickness, In.
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Conventional Zinc Die Casting Alloys AC43A Zn-4AI-2.5Cu-O.04Mg Commercial Names. Trade name. No. 2 die casting alloys; Previous trade name. Zamak 2; Foreign. Mazak 2
some loss of impact strength and ductility. Alloy No.2 has good bearing properties
Chemical Composition. Composition Limits. ASTM B 86: 2.5 to 4.3 AI, 2.5 to 3.0 Cu, 0.020 to 0.05 Mg, 0.100 Fe max, 0.005 Pb max, 0.004 Cd max, 0.003 Sn max, bal Zn
Typical Uses. Die castings such as automotive parts, household appliances and fixtures, office and computer equipment, building hardware
Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking Specifications (U.S. and/or Foreign). ASTM B 86: Alloy AC43A (die castings). B 240: Alloy AC43A(ingot); SAEAlloy 921; UNS Z35540 (ingot), Z35541 (castings); (Foreign) AFNOR-ZA4U3G; BS 1004; DIN1743
Characteristics Alloy No.2 has the highest tensile strength, creep strength, and hardness of all alloys in the hypoeutectic Zamak series ofdie casting alloys. The high copper content (3.0% Cu) causes some dimensional instability and leads to a net expansion of approximately 0.0014% after 20 years. It also causes
Recommended Heat Treating Practice For Stress Relief of Alloy No.2. Temper at temperatures up to 100°C (212 OF) for 2 to 10 h. Above this temperature die castings blister due to the presence of gas porosity For Stabilizing Treatment of Alloy No.2. Treat at temperatures up to 100°C (212 "F) for up to ten days, depending on degree of stability required
• Full treatment is used for exceptional dimensional stability • In other applications, treatment time of 2 to 5 h suffices Treatment is also used prior to secondary operations, such as post die forming (upsetting) or for staking to enhance ductility
AG40A Zn-4AI-O.04 Mg Commercial Names. Trade name. No. 3 die casting alloy; Previous trade name. Zamak 3; Foreign. Mazak 3 Chemical Composition. Composition Limits. ASTM B 86: 3.5 to 4.3 AI, 0.020 to 0.05 Mg, 0.25 Cu max, 0.100 Fe max, 0.005 Pb max, 0.004 Cd max, 0.003 Sn max, bal Zn Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking Specifications (U.S. and/or Foreign). ASTM B 86: Alloy AG40A (die castings). B 240: Alloy AG40A (ingot); SAE J468, alloy 903; UNS Z33521 (ingot), Z33520 (castings); U.S. Government QQ-Z-363; (Foreign) AFNOR-ZA4G; BS I004A; CSA HZ-3 (ingot), HZ-ll (castings); DIN-1743; JIS H 2201 class 1 (ingot), H 5301 ZDC 2 (castings); SAAAS1881
Characteristics Alloy No. 3 is the most widely used zinc die casting alloy in the United States. It provides the best overall combination of strength, castability, dimensional stability, ease of finishing, and cost
Typical Uses. Die castings such as automotive parts, household appliances and fixtures, office and computer equipment, building hardware
Recommended Heat Treating Practice For Stress Relief of Alloy No.3. Temper at temperatures up to 100°C (212 OF) for 2 to 10 h. Above this temperature die castings blister due to the presence of gas porosity For Stabilizing Treatment of Alloy No.3. Treat at temperatures up to 100 °C (212 "F) for up to ten days, depending on degree of stability required
• Full treatment is used for exceptional dimensional stability • In other applications, treatment time of 2 to 5 h suffices Treatment is also used prior to secondary operations, such as post die forming (upsetting) or for staking to enhance ductility
616/ Heat Treater's Guide: Nonferrous Alloys
AC41A Zn-4AI-1 CU-O.05Mg Commercial Names. Trade name. No. 5 die casting alloy; Previous trade name. Zamak 5; Foreign. Mazak 5
Chemical Composition. Composition Limits. ASTM B 86: 3.5 to 4.3 AI, 0.75 to 1.25 Cu, 0.030 to 0.08 Mg, 0.100 Fe max, 0.005 Pb max, 0.004 Cd max, 0.003 Sn max, bal Zn Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking
Specifications (U.S. and/or Foreign). ASTM B 86: alloy AC41A (die castings); B 240: alloy AC41A (ingot); SAB J468, alloy 925; UNS Z35530 (ingot), Z35531 (castings); Government QQ-Z-363; (Foreign) AFNOR-ZA4UIG; BS 1004A; CSAHZ-3 (ingot), HZ-ll (castings); DIN1743; JIS H 2201 class 2 (ingot), H 5301 ZDC I (castings); SAA-AS1881
Characteristics Alloy No.5 produces castings that are both harder and stronger than those made from alloy No.3. However, these improvements come at the expense of ductility: and postforming operations such as riveting, swaging, or crimping must be done with additional care. The creep resistance of alloy
No. 5 is second only to that of alloy No. 2 among the hypoeutectic zinc-aluminum alloys
Typical Uses. Die castings such as automotive parts, household appliances and fixtures, office and computer equipment, building hardware
Recommended Heat Treating Practice For Stress Relief of Alloy No.5. Temper at temperatures up to 100 °C (212 "F) for 2 to 10 h. Above this temperature die castings blister due to the presence of gas porosity For Stabilizing Treatment of Alloy No.5. Treat at temperatures up to 100 °C (212 "F) for up to ten days, depending on degree of stability required • Full treatment is used for exceptional dimensional stability • In other applications, treatment time of 2 to 5 h suffices Treatment is also used prior to secondary operations, such as post die forming (upsetting) or for staking to enhance ductility
AG40B Zn-4AI-O.015Mg Commercial Names. Trade name. No. 7 die casting alloy; Previous
Typical Uses. Die castings such as automotive parts, household appli-
trade name. Zamak 7; Foreign. Mazak 7
ances and fixtures, office and computer equipment, building hardware
Chemical Composition. Composition Limits. ASTM B 86: 3.5 to 4.3 AI, 0.25 Cu max, 0.005-0.020 Mg, 0.Q75Fe max, 0.003 Pb max, 0.002 Cd max, 0.001 Sn max, 0.005-0.020 Ni, bal Zn
Recommended Heat Treating Practice
Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking
For Stress Relief of Alloy No.7. Temper at temperatures up to 100°C (212 OF) for 2 to 10 h. Above this temperature die castings blister due to the presence of gas porosity
Specifications (U.S. and/or Foreign). ASTM B86: Alloy AG40B
For Stabilizing Treatment of Alloy No.7. Treatattemperatures up to
(die castings). B 240: Alloy AG40B (ingot); UNS Z33522 (ingot), Z33523 (castings)
100 °C (212 "F) for up to ten days, depending on degree of stability required
Characteristics
• Full treatment is used for exceptional dimensional stability • In other applications, treatment time of 2 to 5 h suffices
Alloy No.7 is essentially a high-purity version of alloy No.3. Because of its lower magnesium content, alloy No. 7 has even better castability than alloy No.3, enabling excellent reproduction of surface detail in castings. Alloy No.7 has the highest ductility among the hypoeutectic alloys
Treatment is also used prior to secondary operations, such as post die forming (upsetting) or for staking to enhance ductility
nc-Aluminum Casting Alloys ZA·8 Zn-8AI-1 CU-O.02Mg Commercial Names. Trade name. ZA-8, zinc foundry alloy Chemical Composition. Composition Limits. ASTM B 669 (ingot): 8.2 to 8.8 AI, 0.8 to 1.3 Cu, 0.020 to 0.030 Mg, 0.065 Fe max, 0.005 Pb max, 0.005 Cd max, 0.002 Sn max, bal Zn. ASTM B 791 (castings): 8.0 to 8.8 AI, 0.8 to 1.3 Cu, 0.Ql5 to 0.030 Mg, 0.075 Fe max, 0.006 Pb max, 0.006 Cd max, 0.003 Sn max, bal Zn
ZA·S: Microstructure. As-cast in a permanent mold. Coarse zinc-rich dendrites in a matrix of IX + 11 eutectic phase. Microstructure finer than that obtained in sand casting. Etchant: 200 g cro; 15 g Na2S0 4 , 1000 mL Hp. 500x
Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking Specifications (U.S. and/or Foreign). ASTM B 791 (castings), B 669 (ingot); UNS Z35635 (ingot), Z35636 (castings); (Foreign) BS DD 139 (castings)
Characteristics Alloy ZA-8 is the only member of the hypereutectic alloys that can be hot chamber die cast along with the hypoeutectic alloys. It is equivalent to alloy No.2 in many respects, but ZA-8 has higher tensile, fatigue, and creep strengths, is more dimensionally stable, and has lower density. Alloy ZA-8 castings can be readily finished, combining their high structural strength with excellent appearance
Typical Uses. For pressure die castings and gravity castings wherever high strength is required: automobiles, general hardware, agricultural equipment, electronic and electrical fittings, domestic and garden appliances, computer hardware, business machines, recording machines, radios, and hand tools
Recommended Heat Treating Practice For Stress Relief of ZA·S, ZA·12, and ZA·27 Die Castings. Temper at temperatures up to 100°C (212 OF) for 2 to 10 h
ZA..12 Zn-11 AI-1 CU-O.025Mg Commercial Names. Trade name. ZA-12, zinc foundry alloy; Previous trade name. ILZRO 12 Chemical Composition. Composition Limits. ASTM B 669 (ingot): 10.8 to 11.5 AI, 0.5 to 1.2 Cu, 0.020 to 0.030 Mg, 0.065 Fe max, 0.005 Pb max, 0.005 Cd max, 0.002 Sn max, bal Zn. ASTM B 791 (castings): 10.5 to 11.5 AI, 0.5 to 1.2 Cu, 0.015 to 0.030 Mg, 0.075 Fe max, 0.006 Pb max, 0.006 Cd max, 0.003 Sn max, bal Zn Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking. High iron causes excessive tool wear
Specifications (U.S. and/or Foreign). ASTM B 791 (castings), B 669 (ingot); UNS Z35630 (ingot), Z35631 (castings); (Foreign) BS DD 139 (castings); SAA-ASI881
Characteristics Alloy ZA-12 has very good castability in cold chamber die casting machines. It is lower in density than all other zinc alloys except ZA-27, and it is frequently specified for castings that must combine casting quality with optimum performance. The plating quality of ZA-12 is lower than that of ZA-8, but it has excellent bearing and wear properties
618/ Heat Treater's Guide: Nonferrous Alloys Typical Uses. For pressure die castings and gravity castings wherever high strength is required: automobiles, general hardware, agricultural equipment, electronic and electrical fittings, domestic and garden appliances, computer hardware, business machines, recording machines, radios, and hand tools. This alloy is used in bearings
ZA-12: Microstructure. As pressure die cast. Coarse zinc-rich dendrites in a matrix of eutectic a + 11 phase. Pressure die casting results in a much finer microstructure. Etchant: 5 mL HN03 and 100 mL H20. 500X
Recommended Heat Treating Practice For Stress Relief of ZA-a, ZA-12, and ZA-27 Die Castings. Temper at temperatures up to 100 °C (212 OF) for 2 to 10 h
ZA.. 27 Zn-27AI-2Cu-O.015Mg Commercial Names. Trade name. ZA-27, zinc foundry alloy Chemical Composition. Composition Limits. ASTM B 669 (ingot): 25.5 to 28.0 AI, 2.0 to 2.5 Cu, 0.012 to 0.020 Mg, 0.072 Fe max, 0.005 Pb max, 0.005 Cd max, 0,002 Sn max, bal Zn. ASTM B 791 (castings): 25.0 to 28.0 AI, 2.0 to 2.5 Cu, 0.01 to 0.02 Mg, 0.075 Fe max, 0,006 Pb max, 0.006 Cd max, 0.003 Sn max, bal Zn Consequence of Exceeding Impurity Limits. Alloy becomes subject to intergranular corrosive attack and fails prematurely by warping and cracking. High iron causes excessive tool wear Specifications (U.S. and/or Foreign). ASTM B 791 (castings), B 669 (ingot); UNS Z35840 (ingot), Z35841 (castings); (Foreign) BS DD 139 (castings); SAA-AS1881
Characteristics Alloy ZA-27 is the lightest, hardest, and strongest of all the zinc alloys, but it has relatively low ductility and impact strength when pressure die cast. Because of the wide freezing range of ZA-27, casting quality can suffer unless care is taken. The secondary creep strength ofZA-27 is better than that of all other zinc alloys except for the now rarely used ILZRO (International Lead-Zinc Research Organization) 16; however, ZA-8 has better primary creep strength. Alloy ZA-27 demonstrates the highest sound and vibration damping properties of all the zinc casting alloys; as a group, zinc
alloys have a damping resistance equal to that of cast irons at elevated temperatures, Alloy ILZRO 16 was developed specifically for optimum creep resistance, particularly at elevated temperatures. It does have the highest creep resistance of all zinc alloys, but it is difficult to manufacture and suffers from melt instability; for these reasons, ZA-8 often is used in its place Typical Uses. For pressure die castings and gravity castings wherever very high strength is required: in automobile engine mounts and drive trains, general hardware, agricultural equipment, domestic and garden appliances, and heavy-duty hand and work tools. This alloy is extensively used in bearings and bushings for high-load low-speed applications
Recommended Heat Treating Practice Temper at temperatures up to 100 °C (212 "F) for 2 to 10 h Dimensional changes in permanent mold and sand castings due to aging of ZA-27 are greater than those for ZA-8 and ZA-12. Two special treatments are available for this alloy: For Stabilization of ZA-27. Treat at a temperature of 250 °C (482 OF) for 12 h, followed by furnace cooling For Homogenizing of ZA-27. Treat at a temperature of 320 °C (608 OF) for 3 h, followed by furnace cooling. Ductility and impact strength are increased
Lead Alloys
Heat Treating Lead and Lead Alloys Lead is normally considered to be unresponsive to heat treatment. Yet, some means of strengthening lead and lead alloys may be required for certain applications. Lead alloys for battery components, for example, can benefit from improved creep resistance in order to retain dimensional tolerances for the full service life. Battery grids also require improved hardness to withstand industrial handling. The absolute melting point of lead is 327.4 °C (621.3 "F). Therefore, in applications in which lead is used, recovery and recrystallization processes and creep properties have great significance. Attempts to strengthen
the metal by reducing the grain size or by cold working (strain hardening) have proved unsuccessful. Lead-tin alloys, for example, may recrystallize immediately and completely at room temperature. Lead-silver alloys respond in the same manner within two weeks. Transformations that are induced in steel by heat treatment do not occur in lead alloys, and strengthening by ordering phenomena, such as in the formation of lattice superstructures, has no practical significance. Despite these obstacles, however, attempts to strengthen lead have met with some success.
Solid-Solution Hardening In solid-solution hardening of lead alloys, the rate of increase in hardness generally improves as the difference between the atomic radius of the solute and the atomic radius of lead increases. A useful level of strengthening normally requires solute additions in excess of the room-temperature solubility limit. In most lead alloys, homogenization and rapid cooling result in a breakdown of the supersaturated solution during storage. Although this breakdown produces coarse structures in certain alloys (lead-tin alloys, for example), it produces fine structures in others (such as lead-antimony alloys). In alloys ofthe lead-tin system, the initial hardening produced by alloying is quickly followed by softening as the coarse structure is formed,
At suitable solute concentrations in lead-antimony alloys, the structure may remain single phase with hardening by Guinier-Preston (GP) zones formed during aging. At higher concentrations, and in certain other systems, aging may produce precipitation hardening as discrete second-phase particles are formed, Alloys that exhibit precipitation hardening typically are less susceptible to overaging and therefore are more stable with time than alloys hardened by GP zones. Lead-calcium and lead-strontium alloys have been observed to age harden through discontinuous precipitation of a second phase-c-PbjCa in lead-calcium alloys and Pb3Sr in lead-strontium alloysas grain boundaries move through the structure.
Solution Treating and Aging Useful strengthening of lead can be attained by adding sufficient quantities of antimony to produce hypoeutectic lead-antimony alloys. Small amounts of arsenic have particularly strong effects on the age-hardening response of such alloys, and these effects are enhanced by solution treating and rapid quenching prior to aging. Hardness Stability. For any given alloy, both heat treatments result in somewhat comparable hardnesses after I min and after 2 years, as indicated
in adjoining Figures. For most of the two-year period, the solution-treated specimens were harder than the quench-cast specimens. Other investigations have also shown that alloys cooled slowly after casting are always softer than quenched alloys. As shown in adjoining Figure, the alloys with 2 and 4% Sb harden comparatively slowly, and the alloy containing 6% Sb appears to undergo optimum hardening.
Dispersion Hardening Another mechanism for strengthening oflead alloys involves elements that have low solubilities in solid lead, such as copper and nickel. Alloys that contain these elements can be processed so that no homogenization results; most of the strengthening that occurs is developed through dispersion hardening, with some solid-solution hardening taking place as a
secondary effect. The resulting structure is more stable than those developed by other hardening processes. Dispersion strengthening also has been achieved through powder metallurgy methods in which lead oxide, alumina, or similar materials are dispersed in pure lead.
622/ Heat Treater's Guide: Nonferrous Alloys
Fabrication Although alloy selection is important, care must be taken in fabrication as well. Castings should be cooled rapidly to a temperature below that at which the structure breaks down, or a coarse structure will be extruded at a temperature above the breakdown temperature, and extrusions should not
be allowed to cool slowly. Rolled alloys often are processed at insufficient temperatures; when this occurs, homogenization after rolling is required if age hardening is to produce a beneficial response.
Cold Storage Cold storage has been shown to improve the response of lead-antimony alloys to age hardening. Cooling a homogenized Pb-2Sb alloy to -10 °C (15 OF)and holding for one or two days prior to room-temperature aging results in increases in both the rate of age hardening and the maximum hardness attained. This behavior has been explained as the result of a
reduction in the mobility of quenched-in free vacancies and a consequent reduction in their annihilation. The process allows the vacancies to form complexes with solute atoms, and these complexes improve the efficiency of nucleation during aging.
Service Temperatures Service temperatures for lead alloys must be kept low to prevent overaging. Some cable-sheathing alloys, for example, have retained most of their creep resistance for up to 20 years, but exposure to elevated temperatures could have reduced this performance substantially. Even the
normally stable age-hardened lead-antimony and lead-calcium alloys can be altered detrimentally by high service temperatures or excessive working.
Age hardening of lead-antimony alloys, solidified and water quenched
Age hardening of lead-antimony alloys, solution treated 4 h at 250°C (480 oF) and water quenched
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Heat Treating lead and lead Alloys I 623
Age hardening of lead-antimony-arsenic alloys, solution treated 4 h at 250 °C (480 ° F) and water quenched
Age hardening of lead-antimony-arsenic alloys, solidified and water quenched
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624/ Heat Treater's Guide: Nonferrous Alloys
Can solder (Pb-2Sn), slowly solidified. Light gray lead-rich grains with dark gray tin precipitate in grain boundaries and within grains. 1 part acetic acid, 1 part HN03 , 8 parts glycerol. 400x
Section through automotive body, showing body solder (Pb2.6Sn·5.25Sb·O.5As) beneath four coats of paint (top). Dark lead-rich grains and intergranular ternary eutectic of antimony-tin phase and antimony (both light) and lead (dark). 2 mL acetic acid, 98 mL methanol. 325x
Refractory Metals and Alloys
Heat Treating Refractory Metals and Alloys Most commercially available refractory metals (molybdenum, tungsten, niobium, and tantalum) derive their strength from either cold work or solution hardening. Precipitation is not used as a primary strengthening
mechanism for any of the commercial refractory metal alloys. Consequently, stress relief and recrystallization annealing are the common heat treatments.
General Annealing Treatments Molybdenum and tungsten alloys are normally cold worked plus stress relieved to develop their best mechanicalproperties such as low ductilebrittle transition temperatures. Recrystallization destroys the strengthening developed by cold working and raises the ductile-brittle transition temperature to relatively high levels. Adjoining Figure shows the effect of recrystallization on the ductile-brittle transition in bending for unalloyed molybdenum sheet. Stress-relief annealing reduces the level of residual stress in components and restores some of the ductility exhausted by the heavy cold reductions used in making mill products, permitting further fabrication with less danger of cracking and delamination. Stress-relief annealing is mandatory after welding these materials and may also be employed after extensive machining operations. Normally, a stress-relief temperature is chosen to produce a small amount (<10%) of recrystallization in the microstructure. This treatment produces optimum ductility without significant loss of strength. It also allows annealing to be confirmed by either simple hardness testing or metallographic observation. Stress-relief annealing of material to be further worked is usually performed at lower temperatures to avoid a partially recrystallized microstructure. Working of mixed microstructures can lead to variable properties and ductility problems in the finished product. Prior processing parameters, such as the amount of reduction prior to annealing and the temperature at which deformation takes place, markedly affect the recrystallization of molybdenum and tungsten and therefore also have a strong effect on the choice of stress-relief conditions. The effect of degree of working is shown in adjoining Figure for molybdenum rolled at 1200 °C (2200 OF).
Proprietary stress-relief annealing practices used by the manufacturers of molybdenum and tungsten mill products are designed to optimize fabrication properties such as the capability for hot spinning, drawing, and stamping. Typically they involve annealing to obtain a controlled amount of recrystallization in the microstructure. It is strongly recommended that users consult with a primary producer of molybdenum and tungsten to specify the appropriate product for a particular application or to optimize a specific property. Producers are also a valuable resource for advice on the heat treatment of fabricated molybdenum and tungsten products. The adjoining Table lists common commercial alloys of molybdenum and tungsten, along with typical temperature ranges for stress-relief and recrystallization annealing. Tantalum and niobium differ greatly from molybdenum and tungsten in that these metals are ductile in the recrystallized condition. For this reason, they and their alloys are most frequently recrystallized prior to fabrication or use. In the as-rolled condition, alloys are susceptible to cracking during forming. Stress-relief treatments are typically used after welding to reduce residual thermal stresses and after forming operations to eliminate residual forming stresses. If components are coated after welding or forming to provide oxidation resistance, the thermal treatment involved in the coating process itself usually provides sufficient stress relief. The common commercial alloys of tantalum and niobium are listed in the adjoining Table, along with typical stress-relief and recrystallization annealing temperature. The specific temperature required depends on the degree of cold work and the processing history of the alloy.
Molybdenum and Tungsten Annealing Practice Furnace atmosphere considerations are important when choosing heat-treating equipment for molybdenum and tungsten because both metals form carbides and volatile oxides. Adjoining Figure shows the recession of molybdenum in a variety of oxygen-containing atmospheres. The tendency to form brittle surface carbides and the phenomenon of volatile oxide evaporation indicate that carbon- and oxygen-containing atmospheres are to be avoided, especially for thin products such as sheet and foil. Thick-section products such as rod, bar, and plate can frequently tolerate surface recession due to oxidation and are sometimes annealed in air-atmosphere furnaces. Both hydrogen and nitrogen may be considered inert to pure molybdenum and tungsten, but internal nitriding can occur in alloys containing titanium, zirconium, and hafnium. High-purity dry hydrogen is the preferred atmosphere for annealing molybdenum and tungsten because of its compatibility with the metals and because it improves surface cleanliness by reducing surface oxides during annealing. High-quality vacuum systems may also be used to anneal these materials.
Cleaning of molybdenum and tungsten is desirable to remove compounds that could cause carbon contamination during heat treatment. A variety of cleaning agents may be used to remove oils and hydrocarbons. Vapor degreasing and hand or automatic washing with detergent solutions both work well. For chemical cleaning, molten caustic (1.5 to 3% sodium nitrite in sodium hydroxide at 425°C, or 800 "F) followed by hot water rinsing effectively removes heavy surface oxides. Recrystallization behavior of molybdenum is shown in adjoiningFigure. Data for the Figure were obtained on 1.6 mm (0.625 in.) vacuum arc-cast sheet, but are also useful for estimating the behavior of other gages. Thinner sections, having greater degrees of cold work, will have curves shifted to lower temperatures. Thicker sections will recrystallize at higher temperatures. Stress-relief annealing of tungsten and molybdenum may be accomplished by annealing slightly below the temperature required to initiate recrystallization.
628/ Heat Treater's Guide:
Nonferrous Alloys
Tantalum and Niobium Annealing Practice The Table below lists general recommendations for annealing temperatures of tantalum and niobium materials. The trend toward bonding tantalum and niobium to other metals presents special problems that must be carefully reviewed from a metallurgical standpoint. Recommendations in the Table probably do not apply to most clad materials. It is suggested that users contact the supplier of the primary fabricated metal to review plans and procedures prior to any thermal treatment of tantalum, niobium, or their alloys. Furnace atmosphere control during the heat treatment of tantalum and niobium is even more important than it is for tungsten and molybdenum. These metals absorb oxygen, nitrogen, and hydrogen from the atmosphere as temperatures increase above 650°C (1200 "F). The surface oxidation of both metals occurs in air above 300 °C (570 OF), and the oxidation rate increases with increasing temperature. Carbon can also be absorbed if the carbon potential of the furnace atmosphere is sufficient. Hydrogen embrittlement may occur in hydrogen-containing atmospheres. Hydrogen absorption in tantalum and niobium takes place at low temperatures but desorption occurs as temperatures increase from 200 to 1000 °C (400 to 1830 OF). Although this provides a method of hydrogen removal, cooling in the presence of hydrogen should be avoided. Furnace Selection. Because these alloys are easily contaminated during annealing, special care must be exercised in furnace selection, cleanliness of work, and annealing practice. Cold-wall radiant-heated furnaces with refractory metal heating elements, primary heat shields, permanent hearth materials, and support fixtures are normally used when heat treati~ niobium and tantalum. These furnaces operate at vacuums of 0.01 Pa (10 torr) or greater and have low leak rates. Hot-wall argon atmosphere furnaces have also been used to anneal tantalum and niobium, but adsorbed gases and metals on hot furnace walls are likely to cause contamination. Argon must be free of hydrogen and have a dew point below -50°C (-60 OF). Leak rate control is the key to the successful heat treating of tantalum and niobium alloys, especially with products having high surface-to-volume ratios, such as low-gage wire, tube, and strip. Leak rate must be measured in a stabilized system, that is, one that has pumped for a period of time and is no longer outgassing. It is defined as the pressure rise (typically in torr) per second, per liter of chamber volume. Furnace Cleanliness. Furnaces must be clean and usually must not be used for other operations or other metals unless a given practice has been found to be satisfactory. Furnaces previously used to perform brazing operations should not be used. Good practice dictates that furnaces be heated to a temperature 100°C (180 "F) above the annealing temperature in the empty condition to remove adsorbed gases. As further insurance,
tantalum foil is frequently used as an outer wrapping on parts to react with impurities in the furnace. Cleaning of tantalum and niobium is a critical step in preparation for heat treatment. All surface contamination must be removed by machining or grinding and pickling before annealing because of the embrittlement mentioned previously. Cleaning and degreasing present no special problems. Conventional methods and materials may be used, although hot caustics must be avoided. Recrystallization annealing is the most common thermal treatment applied to tantalum and niobium alloys. The recrystallization temperature is so highly dependent on purity, amount of cold work, and prior history that current practice is to anneal pilot samples to ensure that the correct temperatures are used. Time at temperature is typically 1 h.
Recrystallization behavior of 1.6 mm (0.625 in.) vacuum arccast molybdenum sheet, as reflected by room-temperature hardness after 1 h anneals at the indicated temperature Reheating temperature, OF 1800 1900 2000 2100 2200 2300
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Nominalalloy addltlous, AHoy designation
Annealin~ temperatures for molybdenum and tungsten and their
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Nominalalloy
deslgnatiou
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Molybdenum alloys Mo(a) None Mo-1ZM(a) 0.5TI,0.1 Zr,O.03C Mo-MHC(a) 1Hf,0.05C Mo-30W(a) 30W DopedMo 0.07si, 0.05K Thngsten alloys W None
Annealing temperatures Stress-relief Re
850-950 1100-1300 1100-1350 1150-1200 1250-1350 1100-1200
1560-1740 2010-2370 2010-2460 2100-2190 2280-2460 2010-2190
1000-1200 1350-1475 1400-1600 1300-1450 1400-1600 1250-1350
(a) Arc-castorpowdermetallurgy: allothercompositions powdermetallurgy
1830-2190 2460-2690 2550-2910 2370-2640 2550-2910 2280-2460
1300
lhntalum alloys Th Th FS63 FS61(KBI-6) Th-IOW (FS6O, KBI·I0) T111 T222 Niobium alloys Nb Nb-1Zr(FS80, WC lZr, KBI-l) SNb291,WC291 Nb752 C129Y FS85 C103
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OF
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850 1000 1000
1560 1830 1830
1100
2010
1000-1250 1200-1350 1200-1300 1400-1550 1300-1600
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1100 1100
2010 2010
1400-1650 2550-3000 1400-1650 2550-3000
None lZr IOTa,lOW IOW,2.5Zr IOW,IOHf,O.1Y 28Th,11W,0.8 Zr IOHf, 1TI,O.7Zr
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1830
900
1650 2100
1150
(a)Powdermetallurgy; all othercompositions arc-cast
900-1200 1150-1250
1650-2190 2100-2280
1150-1200 1300-1400 1150-1250 1300-1400 1250-1375
2100-2190 2370-2550 2100-2280 2370-2550 2280-2510
Refractory Metals and Alloys /629
Oxidation of molybdenum in pure oxygenand air.T, temperature
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630 I Heat Treater's Guide: Nonferrous Alloys
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Niobium Alloy: Microstructure. FS-85 niobium alloy (Nb-28Ta11 W-0.8Zr), 2.8-mm (0.110-in.) thick sheet. Arc melted, hot extruded, warm rolled at 705°C (1300 OF), 50 to 75% reductions between anneals. Final anneal in vacuum at 1315 °C (2400 OF) for 1 h. Longitudinal section of fully recrystallized structure showing typical banding. ASTM grain size 7. Etchant: ASTM 163. 250x
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Tungsten Alloy: Microstructure. Ta-10W alloy 1.0-mm (0.040in.) thick sheet. Electron-beam melted, warm forged, cold rolled, and annealed. Final annealed in vacuum at 1480 °C (2700 OF). Longitudinal section showing fully recrystallized structure and banding. ASTM grain size 6. Etchant: ASTM 163. 250x
Tungsten Wire: Microstructure. Tungsten wire (not doped), 0.2-mm (0.007-in.) diam, annealed at 2700 °C (4890 OF) for 5 min. Fully recrystallized, equiaxed grains. Murakami's reagent (mod). 200x
Molybdenum Alloy: Microstructure. Mo-0.5li alloy, cold rolled and annealed by heating to 1315 °C (2400 OF). The structure consists of elongated grains. Murakami's reagent. 200x
Tin-Rich Alloys
Heat Treating Tin-Rich Alloys In heat treating these alloys. it is difficult to secure an effective and permanent degree of hardening. Tin melts at 232°C (505 K). and room temperature (about 295 K) is well over one-half the absolute melting point. High-temperature behavior such as recrystallization and recovery can
occur in fairly short times. even at room temperature. Tin is also an unusual metal because it can work soften under certain conditions. and so heat treating can be used in these cases to restore some of the original hardness and strength.
Binary Alloys Tin-antimony. tin-bismuth. tin-lead. and tin-silver alloys can all be temper hardened by solution treatment and aging. However. only the tin-antimony alloys can be permanently strengthened by heat treatment; all other tin-rich binary alloys will gradually soften at room temperature. The greatest improvement obtainable in binary tin-antimony alloys occurs in
the alloy that contains 9% Sb; a hardness of 21 HB and a tensile strength of 51 MPa (7.4 ksi) can be increased to 26 HB and 65 MPa (9.4 ksi). This alloy is tempered for 48 h at 100 °C (212 "F) after being quenched from 225°C (435 "F), During this tempering treatment, ductility decreases from 20 to 10% elongation (in 50 rnm, or 2 in.).
Ternary Alloys Permanent effects produced by heat treatment also carry over into ternary alloys of tin, antimony, and cadmium. For example, the strengthening effect of cadmium in the terminal solution tin phase (alpha) is much greater than that of antimony. Alloys containing cadmium generally have compositions that restrict the formation of the primary (CdSb) epsilon phase. The maximum combination of strength, ductility, and hardness is obtained in alloys that have finely dispersed precipitates of the sigma and " epsilon phases in an alpha matrix, or finely dispersed epsilon in a matrix of alpha with a eutectoid of alpha plus gamma (cadmium-rich solid solution). These structures are typically achieved by quenching or rapid cooling from elevated temperatures to avoid precipitation of primary sigma and epsilon. Other compositions also provide improvements in permanent properties.
In studies of cold workable alloys containing 3 to 8% Cd and 1 to 9% Sb, it was found that a maximum tensile strength of 101 MPa (14.6 ksi) can be obtained with an Sn-3Cd-7Sb alloy quenched from 190°C (375 "F), then aged for either 24 h at 100°C (212 "F), or 18 months at room temperature. In work on alloys containing 7 to 10% Sb and 0 to 3% Cd (for bearings serving at mildly elevated temperatures), optimum properties (tensile strength: 92 MPa, or 13.4 ksi) were obtained in a Sn-9Sb-1.5Cd alloy quenched from 220°C (430 oF) and then aged for 10000 h at 140°C (285 "F), This alloy consists of finely divided sigma and epsilon phases in a matrix of alpha.
Pewter The hardness values of spun pewterware, or of other articles that have been manufactured by mechanically working the metal, can be restored by heat treatment at temperatures from 110 to 150°C (230 to 300 OF). The time required varies from 3 h at the lower temperature to a few minutes at the
higher temperature. A tin alloy containing 6% Sb and 2% Cu hardens to 90% of the hardness of the as-cast material after annealing for 1 h at 200 °C (390 OF). Longer annealing times at lower temperatures have smaller but similar effects on the recovery from work softening.
634/ Heat Treater's Guide: Nonferrous Alloys
Sn·12Sb·10Pb·3Cu alloy. Structure consists of CuaSn s needles and SbSn crystals (both light) in dendrites of tin-rich solid solution, along with some interdendritic eutectic. 150x
Sn-40Pb alloy, section of a wave-soldered printed circuit board joint that was thermally cycled. Structure shows a thermal fatigue crack propagating through the tin-lead fillet. The tinlead structure has coarsened in the highly stressed region near the crack. 80x
Sn-31Pb-18Cd alloy. Structure is a lamellar ternary eutectic of solid solutions of cadmium in tin (light), tin in lead (gray), and cadmium in lead (dark). 375x
Glossary
los!.aryof A age hardening. Hardening by aging, usually after rapid cooling or cold working. See also aging. age softening. Spontaneous decrease of strength and hardness that takes place at room temperature in certain strain hardened alloys, especially those of aluminum. aging. A change in the properties of certain metals and alloys that occurs at ambient or moderately elevated temperatures after hot working or a heat treatment (quench aging in ferrous alloys, natural or artificial aging in ferrous and nonferrous alloys) or after a cold working operation (strain aging). The change in properties is often, but not always, due to a phase change (precipitation), but never involves a change in chemical composition of the metal or alloy. See also age hardening, .artificial aging, interrupted aging, natural aging, overaging, precipitation hardening, precipitation heat treatment, progressive aging, quench aging, step aging, and strain aging. annealing. A generic term denoting a treatment, consisting of heating to and holding at a suitable temperature followed by cooling at a suitable rate, used primarily to soften metallic materials, but also to simultaneously produce desired changes in other properties or in microstructure. The purpose of such changes may be, but is not confined to: improvement of machinability, facilitation of cold work, improvement of mechanical or electrical properties, and/or increase in stability of dimensions. When the term is used without qualification, full annealing is implied. When applied only for the relief of stress, the process is properly called stress relieving or stress-relief annealing. In nonferrous alloys, annealing cycles are designed to: (a) remove part or all of the effects of cold working (recrystallization mayor may not be involved); (b) cause substantially complete coalescence of precipitates from solid solution in relatively coarse form; or (c) both,
depending on composition and material condition. Specific process names in commercial use are cycle annealing, final annealing, flame annealing, full annealing, intermediate annealing, partial annealing, recrystallization annealing, stress-reliefannealing, and anneal to temper. annealing twin. A twin formed in a crystal during recrystallization. anneal to temper. A final partial anneal that softens a cold worked nonferrous alloy to a specified level of hardness or tensile strength. artificial aging. Aging above room temperature. See also aging. Compare with natural aging.
beta annealing. Producing a beta phase by heating certain titanium alloys in the temperature range at which this phase forms followed by cooling at an appropriate rate to prevent its decomposition. black oxide. A black finish on a metal produced by immersing it in hot oxidizing salts or salt solutions. breaks. Creases or ridges usually in "untempered" or in aged material where the yield point has been exceeded. bright annealing. Annealing in a protective medium to prevent discoloration of the bright surface. brine quenching. A quench in which brine (salt water-chlorides, carbonates, and cyanides) is the quenching medium. The salt addition improves the efficiency of water at the vapor phase or hot stage of the quenching process. Brinell hardness test. A test for determining the hardness of a material by forcing a hard steel or carbide ball of specified diameter into it under a specified load. The result is expressed as the Brinell hardness number, which is the value obtained by dividing the applied load in kilograms by the surface area of the resulting impression in square millimeters.
Fig. 1 Macroscopic appearance of ductile (a and b) and brittle (c and d) tensile fractures
(a)
(b)
(e)
(d)
638/ Heat Treater's Guide: Nonferrous Alloys
Fig. 2 Columnar structure as seen through the transverse section of a commercially pure aluminum ingot. 1.5x
brittle fracture. Separation of a solid accompanied by little or no macroscopic plastic deformation. Typically, brittle fracture occurs by rapid crack propagation with less expenditure of energy than for ductile fracture. Brittle tensile fractures have a bright, granular appearance and exhibit little or no necking (Fig. 1). burning. (1) Permanently damaging a metal or alloy by heating to cause either incipient melting or intergranular oxidation. See overheating, grain-boundary liquation. (2) In grinding, getting the work hot enough to cause discoloration or to change the microstructure by tempering or hardening.
c carburizing flame. A gas flame that will introduce carbon into some heated metals, as during a gas welding operation. A carburizing flame is a reducing flame, but a reducing flame is not necessarily a carburizing flame. car furnace. A batch-type furnace using a car on rails to enter and leave the furnace area. Car furnaces are used for lower stress relieving ranges. caustic quenching. Quenching with aqueous solutions of 5 to 10% sodium hydroxide (NaOH). CCT diagram. See continuous cooling transformation diagram. cementation. The introduction of one or more elements into the outer portion of a metal object by means of diffusion at high temperature. checks. Numerous, very fine cracks in a coating or at the surface of a metal part. Checks may appear during processing or during service and are most often associated with thermal treatment or thermal cycling. Also called check marks, checking, heat checks. close annealing. Same as box annealing. coalescence. (1) The union of particles of a dispersed phase into larger units, usually effected at temperatures below the fusion point. (2) Growth of grains at the expense of the remainder by absorption or the growth of a phase or particle at the expense of the remainder by absorption or reprecipitation. coarsening. An increase in the grain size, usually, but not necessarily, by grain growth. coherent precipitate. A crystalline precipitate that forms from solid solution with an orientation that maintains continuity between the crystal lattice of the precipitate and the lattice of the matrix, usually accompanied by some strain in both lattices. Because the lattices fit at the interface between precipitate and matrix, there is no discernible phase boundary.
Fig. 3 Dendritic structure in the columnar region of a Cu-30Ni ingot showing coring (variation in solute concentration). 20x
cold die quenching. A quench utilizing cold, flat, or shaped dies to extract heat from a part. Cold die quenching is slow, expensive, and is limited to smaller parts with large surface areas. cold-worked structure. A microstructure resulting from plastic deformation of a metal or alloy below its recrystallization temperature. cold working. Deforming metal plastically under conditions of temperature and strain rate that induce strain hardening. Usually, but not necessarily, conducted at room temperature. Contrast with hot working. columnar structure. Acoarse structure of parallel elongated grains formed by unidirectional growth, most often observed in castings (Fig. 2), but sometimes in structures resulting from diffusional growth accompanied by a solid-state transformation. conditioning heat treatment. A preliminary heat treatment used to prepare a material for desired reaction to a subsequent heat treatment. For the term to be meaningful, the exact heat treatment must be specified. constitution diagram. See phase diagram. continuous cooling transformation (CCT) diagram. Set of curves drawn using logarithmic time and linear temperature as coordinates, which define for each cooling curve the beginning and end of the transformation of the initial phase. continuous precipitation. Precipitation from a supersaturated solid solution in which the precipitate particles grow by long-range diffusion without recrystallization of the matrix. Continuous precipitates grow from nuclei distributed more or less uniformly throughout the matrix. They usually are randomly oriented, but may form a Widmanstiitten structure. Also called general precipitation. Compare with discontinuous precipitation and localized precipitation. controlled cooling. Cooling from an elevated temperature in a predetermined manner, to avoid hardening, cracking, or internal damage, or to produce desired microstructure or mechanical properties. cooling curve. A curve showing the relation between time and temperature during the cooling of a material. It is used to find the temperature at which phase changes occur. cooling stresses. Residual stresses resulting from nonuniform distribution of temperature during cooling. coring. A condition of variable composition between the center and surface of a unit of microstructure (such as a dendrite, grain, carbide particle); results from nonequilibrium solidification, which occurs over a range of temperature (Fig. 3). critical point. (1) The temperature or pressure at which a change in crystal structure, phase or physical properties occurs. Same as transformation temperature. (2) In an equilibrium diagram, that specific value of composition, temperature and pressure, or combinations thereof, at which the phases of a heterogeneous system are in equilibrium. critical strain. The strain just sufficient to cause recrystallization; because the strain is small, usually only a few percent, recrystallization takes
Glossary of Terms Related to Heat Treating /639
Fig. 4 Scanning electron micrograph of dendrites in a Cu-10Co casting. 150x
place from only a few nuclei, which produces a recrystallized structure consisting of very large grains. critical temperature. (I) Synonymous with critical point if the pressure is constant. (2) The temperature above which the vapor phase cannot be condensed to liquid by an increase in pressure. critical temperature ranges. Synonymous with transformation ranges, which is the preferred term. cycle annealing. An annealing process employing a predetermined and closely controlled time-temperature cycle to produce specific properties or microstructures.
D dead soft. A temper of nonferrous alloys corresponding to the condition of minimum hardness and tensile strength produced by full annealing. deformation. A change in the form of a body due to stress, thermal change, change in moisture, or other causes. Measured in units of length. dendrite. A crystal that has a treelike branching pattern, being most evident in cast metals slowly cooled through the solidification range (Fig. 4). dendritic segregation. Inhomogeneous distribution of alloying elements through the arms of dendrites. dew point. The temperature and pressure at which a gas begins to condense to a liquid. dew point analyzer. An atmosphere monitoring device that measures the partial pressure of water vapor in an atmosphere. differential heating. Heating that intentionally produces a temperature gradient within an object such that, after cooling, a desired stress distribution or variation in properties is present within the object. diffusion. (1) Spreading of a constituent in a gas, liquid, or solid, tending to make the composition of all parts uniform. (2) The spontaneous movement of atoms or molecules to new sites within a material. diffusion coefficient. A factor of proportionality representing the amount of substance diffusing across a unit area through a unit concentration gradient in unit time. dilatometer. An instrument for measuring the linear expansion or contraction in a metal resulting from changes in such factors as temperature and allotropy. discontinuous precipitation. Precipitation from a supersaturated solid solution in which the precipitate particles grow by short-range diffusion, accompanied by recrystallization of the matrix in the region of precipitation. Discontinuous precipitates grow into the matrix from nuclei near grain boundaries, forming cells of alternate lamellae of precipitate and depleted (and recrystallized) matrix. Often referred to as cellular or nodular precipitation. Compare with continuous precipitation and localized precipitation.
dislocation. A linear imperfection in a crystalline array of atoms. Two basic types are recognized: (I) an edge dislocation corresponds to the row of mismatched atoms along the edge formed by an extra, partial plane of atoms within the body of the crystal; (2) screw dislocation corresponds to the axis of a spiral structure in a crystal, characterized by a distortion that joins normally parallel planes together to form a continuous helical ramp (with a pitch of one interplanar distance) winding about the dislocation. Most prevalent is the so-called mixed dislocation, which is any combination of an edge dislocation and a screw dislocation. disordered structure. The crystal structure of a solid solution in which the atoms of different elements are randomly distributed relative to the available crystal lattice sites. Contrast with ordered structure. dissociation. As applied to heterogeneous equilibria, the transformation of one phase into two or more new phases of different composition. Compare with order-disorder transformation. double aging. Employment of two different aging treatments to control the type of precipitate formed from a supersaturated matrix in order to obtain the desired properties. The first aging treatment, sometimes referred to as intermediate or stabilizing, is usually carried out at higher temperature than the second. drawing. Misnomer for tempering. ductile fracture. Fracture characterized by tearing of metal accompanied by appreciable gross plastic deformation and expenditure of considerable energy. Contrast with brittle fracture (see also Fig. I accompanying brittle fracture). ductility. The ability of a material to deform plastically without fracturing, measured by elongation or reduction of area in a tensile test, by height of cupping in an Erichsen test, or by other means.
E edge dislocation. See dislocation. elastic limit. The maximum stress that a material is capable of sustaining without any permanent strain (deformation) remaining upon complete release of the stress. embrittlement. The severe loss of ductility or toughness or both, of a material, usually a metal or alloy. Many forms of embrittlement can lead to brittle fracture. Many forms can occur during thermal treatment or elevated-temperature service (thermally induced embrittlement). Other metals and alloys can be embrittled by environmental conditions (environmentally assisted embrittlement). Various types of both thermally induced embrittlement and environmentally assisted embrittlement are defined in the ASM Handbook series and in the ASM Materials Engineering Dictionary. equilibrium diagram. A graphical representation of the temperature, pressure, and composition limits of phase fields in an alloy system as they exist under conditions of complete equilibrium. In metal systems, pressure is usually considered constant. eutectic. (1) An isothermal reversible reaction in which a liquid solution is converted into two or more intimately mixed solids on cooling, the number of solids formed being the same as the number of components in the system. (2) An alloy having the composition indicated by the eutectic point on an equilibrium diagram. (3) An alloy structure of intermixed solid constituents formed by a eutectic reaction. eutectic melting. Melting oflocalized microscopic areas whose composition corresponds to that of the eutectic in the system. eutectoid. (1) An isothermal reversible reaction in which a solid solution is converted into two or more intimately mixed solids on cooling, the number of solids formed being the same as the number of components in the system. (2) An alloy having the composition indicated by the eutectoid point on an equilibrium diagram. (3) An alloy structure of intermixed solid constituents formed by a eutectoid reaction. extra hard. A temper of nonferrous alloys and some ferrous alloys characterized by tensile strength and hardness about one-third of the way from ful! hard to extra spring temper.
640 I Heat Treater's Guide: Nonferrous Alloys
Fig. 5 As-castAI-lSi ingotsshowingthe effectsof grain refinement. (a) No grain refiner. (b) Grain refinedwith AI-5Ti-1 B addition. Both 2x
(a)
extra spring. A temper of nonferrous alloys and some ferrous alloys corresponding approximately to a cold-worked state above full hard beyond which further cold work will not measurably increase the strength and hardness.
F final annealing. An imprecise term used to denote the last anneal given to a nonferrous alloy prior to shipment. finishing temperature. The temperature at which hot working is completed. fixture. A device designed to hold parts to be joined in proper relation to each other. fixturing. The placing of parts to be heat treated in a constraining or semiconstraining apparatus to avoid heat-related distortions. See also racking. fluidized-bed heating. Heating carried out in a medium of solid particles suspended in a flow of gas. fog quenching. Quenching in a fine vapor or mist. forced-air quench. A quench utilizing blasts of compressed air against relatively small parts such as a gear. freezing range. That temperature range between liquidus and solidus temperatures in which molten and solid constituents coexist. full annealing. An imprecise term that denotes an annealing cycle to produce minimum strength and hardness. For the term to be meaningful, the composition and starting condition of the material and the time-temperature cycle used must be stated. full hard. A temper of nonferrous alloys corresponding approximately to a cold-worked state beyond which the material can no longer be formed by bending. In specifications, a full hard temper is commonly defined in terms of minimum hardness or minimum tensile strength (or, alternatively, a range of hardness or strength) corresponding to a specific percentage of cold reduction following a full anneal. For aluminum, a full hard temper is equivalent to a reduction of 75% from dead soft; for austenitic stainless steels, a reduction of about 50 to 55%.
(b)
G grain. An individual crystal in a polycrystalline material; it mayor may not contain twinned regions and subgrains. grain boundary. A narrow zone in a metal corresponding to the transition from one crystallographic orientation to another, thus separating one grain from another; the atoms in each grain are arranged in an orderly pattern. grain-boundary liquation. An advanced stage of overheating in which material in the region of austenitic grain boundaries melts. Also termed burning. grain coarsening. A heat treatment that produces excessively large grains in polycrystalline metals. grain growth. (l) An increase in the average size of the grains in polycrystalline metals, usually as a result of heating at elevated temperature. (2) In polycrystalline metals, a phenomenon occurring fairly close below the melting point in which the larger grains grow still larger while the smallest ones gradually diminish and disappear. See also recrystallization. grain refiner. A material added to a molten metal to induce a finer-thannormal grain size in the final structure (Fig. 5). grain refinement. The manipulation of the solidification process to cause more (and therefore smaller) grains to be formed and/or to cause the grains to form in specific shapes. The term refinement is usually used to denote a chemical addition to the metal (Fig. 5) but can refer to control of the cooling rate. grain size. For metals, a measure of the areas or volumes of grains in a polycrystalline material, usually expressed as an average when the individual sizes are fairly uniform. In metals containing two or more phases, the grain size refers to that of the matrix unless otherwise specified. Grain sizes are reported in terms of number of grains per unit area or volume, average diameter, or as a grain-size number derived from area measurements. grain size distribution. Measures of the characteristic grain or crystallite dimensions (usually, diameters) in a polycrystalline solid; or of their populations by size increments from minimum to maximum. Usually determined by microscopy. Guinier-Preston (G-P) zone. A small precipitation domain in a supersaturated metallic solid solution. A G-P zone has no well-defined crystalline
Glossary of Terms Related to Heat Treating /641
structure of its own and contains an abnormally high concentration of solute atoms. The formation of G-P zones constitutes the first stage of precipitation and is usually accompanied by a change in properties of the solid solution in which they occur.
H half hard. A temper of nonferrous alloys characterized by tensile strength about midway between that of dead soft and full hard tempers. hardening. Increasing hardness by suitable treatment, usually involving heating and cooling. When applicable, the following more specific terms should be used for nonferrous alloys: age hardening and precipitation hardening. hardness. Resistance of metal to plastic deformation, usually by indentation. However, the term may also refer to stiffuess or temper, or to resistance to scratching, abrasion, or cutting. Indentation hardness may be measured by various hardness tests, such as Brinell, Rockwell, Knoop, and Vickers. hardness profile, Hardness as a function of distance from a fixed reference point (usually from the surface). hard temper. Same es full hard temper. heat checks. See checks. heat tinting. Coloration of a metal surface through oxidation by heating to reveal details of the microstructure. heat-treatable alloy. An alloy that can be hardened by heat treatment. heat-treating film. A thin coating or film, usually an oxide, formed on the surface of metals during heat treatment. heat treatment. Heating and cooling a solid metal or alloy in such a way as to obtain desired conditions or properties. Heating for the sole purpose of hot working is excluded from the meaning of this definition. holding. The portion of the thermal cycle during which the temperature of the object is maintained constant. holding temperature. The constant temperature at which the object is maintained. holding time. Time for which the temperature of the object is maintained constant. homogenizing. Holding at high temperature to eliminate or decrease chemical segregation by diffusion. See also coring. hot isostatic pressing. (1) A process for simultaneously heating and forming a compact in which the powder is contained in a sealed flexible sheet metal or glass enclosure and the so-contained powder is subjected to equal pressure from all directions at a temperature high enough to permit plastic deformation and sintering to take place. (2) A process that subjects a component (casting, powder forging, etc.) to both elevated temperature and isostatic gas pressure in an autoclave. The most widely used pressurizing gas is argon. When castings are hot isostatically pressed, the simultaneous application of heat and pressure virtually eliminates internal voids and microporosity through a combination of plastic deformation, creep, and diffusion. hot quenching. An imprecise term used to cover a variety of quenching procedures in which a quenching medium is maintained at a prescribed temperature above 70°C (160 OF). hot-wire test. Method used to test heat extraction rates of various quenchants. Faster heat-extracting quenchants will permit more electric current to pass through a standard wire because it is cooled more quickly. Compare with hot-wire analyzer. hot working. (1) The plastic deformation of metal at such a temperature and strain rate that recrystallization takes place simultaneously with the deformation, thus avoiding any strain hardening. Also referred to as hot forging and hot forming, (2) Controlled mechanical operations for shaping a product at temperatures above the recrystallization temperature. Contrast with cold working. hypereutectic alloy. In an alloy system exhibiting a eutectic, any alloy whose composition has an excess of alloying element compared with the eutectic composition, and whose equilibrium microstructure contains some eutectic structure.
hypereutectoid alloy. In an alloy system exhibiting a eutectoid, any alloy whose composition has an excess of alloying element compared with the eutectoid composition, and whose equilibrium microstructure contains some eutectoid structure. . hypoeutectic alloy. In an alloy system exhibiting a eutectic, any alloy whose composition has an excess of base metal compared with the eutectic composition. and whose equilibrium microstructure contains some eutectic structure. hypoeutectoid alloy. In an alloy system exhibiting a eutectoid, any alloy whose composition has an excess of base metal compared with the eutectoid composition, and whose equilibrium microstructure contains some eutectoid structure.
I induction heating. Heating by combined electrical resistance and hysteresis losses induced by subjecting a metal to the varying magnetic field surrounding a coil carrying alternating current. intense quenching. Quenching in which the quenching medium is cooling the part at a rate at least two and a half times faster than still water. See also Grossmann chart. intercritical annealing. Any annealing treatment that involves heating to, and holding at, a temperature between the upper and lower critical temperatures to obtain partial austenitization, followed by either slow cooling or holding at a temperature below the lower critical temperature. intergranular. Between crystals or grains. Also called intercrystalline. Contrast with transgranular. intergranular cracking. Cracking or fracturing that occurs between the grains or crystals in a polycrystalline aggregate. Also called intercrystalline cracking. Contrast with transgranular cracking. intergranular fracture. Brittle fracture of a polycrystalline material in which the fracture is between the grains, or crystals, that form the material. Also called intercrystalline fracture. Contrast with transgranular fracture. intermediate annealing. Annealing wrought metals at one or more stages during manufacture and before final treatment. interrupted aging. Aging at two or more temperatures, by steps, and cooling to room temperature after each step. See also aging, and compare with progressive aging and step aging. interrupted quenching. A quenching procedure in which the workpiece is removed from the first quench at a temperature substantially higher than that of the quenchant and is then subjected to a second quenching system having a different cooling rate than the first, interval test. Method used to test heat extraction rates of various quenchants. This test measures the increase in temperature of a quenchant when a standard bar of metal is quenched for five seconds. Faster quenchants will exhibit greater temperature increases. isothermal transformation. A change in phase that takes place at a constant temperature. The time required for transformation to be completed, and in some instances the time delay before transformation begins, depends on the amount of supercooling below (or superheating above) the equilibrium temperature for the same transformation. isothermal transformation (IT) diagram. Set of curves drawn using logarithmic time and linear temperature as coordinates, which define for each level of temperature the beginning and end of the transformation of the initial phase under isothermal conditions.
K Knoop hardness test. An indentation hardness test using calibrated machines to force a rhombic-based pyramidal diamond indenter having specified edge angles, under specified conditions, into the surface of the material under test and to measure the long diagonal after removal of the load.
642/ Heat Treater's Guide: Nonferrous Alloys
L
Fig. 6 Plate-shpaed appearance of martensite in a Cu-12AI alloy. 500x
latent heat. Thermal energy absorbed or released when a substance undergoes a phase change. liquation temperature. The lowest temperature at which partial melting can occur in an alloy that exhibits the greatest possible degree of segregation. liquid spray quench. Same as spray quenching. localized precipitation. Precipitation from a supersaturated solid solution similar to continuous precipitation, except that the precipitate particles form at preferred locations, such as along slip planes, grain boundaries, or incoherent twin boundaries.
M magnetic quenchometer test. Method used to test heat extraction rates of various quenchants. The test works by utilizing the change in magnetic properties of metals at their Curie point - the temperature above which metals lose their magnetism. martensite. A generic term for microstructures formed by diffusionless phase transformation in which the parent and product phases have a specific crystallographic relationship. Martensite is characterized by an acicular pattem in the microstructure in nonferrous alloys (Fig. 6). martensitic transformation. A reaction that takes place in some metals on cooling, with the formation of an acicular structure called martensite. Mr temperature. For any alloy system, the temperature at which martensite formation on cooling is essentially finished. microhardness. The hardness of a material as determined by forcing an indenter such as a Vickers or Knoop indenter into the surface of a material under very light load; usually, the indentations are so small that they must be measured with a microscope. Capable of determining hardnesses of different microconstituents within a structure, or of measuring steep hardness gradients such as those encountered in case hardening. See also Knoop hardness test and Vickers hardness test. microsegregation, Segregation within a grain, crystal, or small particle. mill annealing. A general-purpose treatment given to all mill products. It is not a full anneal and may leave traces of cold or warm working in the microstructure of heavily worked products, particularly sheet. See also full annealing. mill scale. The heavy oxide layer formed during hot fabrication or heat treatment of metals. M, temperature. For any alloy system, the temperature at which martensite starts to form on cooling.
o oil hardening. Quench-hardening treatment involving cooling in oil. optical pyrometer. An instrument for measuring the temperature of heated material by comparing the intensity of light emitted with a known intensity of an incandescent lamp filament. overaging, Aging under conditions of time and temperature greater than those required to obtain maximum change in a certain property, so that the property is altered in the direction of the initial value. See also aging. overheating. Heating a metal or alloy to such a high temperature that its properties are impaired. When the original properties cannot be restored by further heat treating, by mechanical working, or by a combination of working and heat treating, the overheating is known as burning. oxidation. (1) A reaction in which there is an increase in valence resulting from a loss of electrons. (2) A corrosion reaction in which the corroded metal forms an oxide; usually applied to reaction with a gas containing elemental oxygen, such as air. oxidizing agent. A compound that causes oxidation, thereby itself becoming reduced. oxidizing flame. A gas flame produced with excess oxygen in the inner flame. oxygen probe. An atmosphere-monitoring device that electronically measures the difference between the partial pressure of oxygen in a furnace or furnace supply atmosphere and the external air.
p
natural aging. Spontaneous aging of a supersaturated solid solution at room temperature. See also aging, and compare with artificial aging. neutral flame. A gas flame in which there is no excess of either fuel or oxygen in the inner flame. Oxygen from ambient air is used to complete the combustion of C02 and H2 produced in the inner flame. neutralization number. An ASTM number given to quenching oils that reflects the oil's tendency towards oxidation and sludging. See also saponification number: nucleation. The initiation of a phase transformation at discrete sites, the new phase growing on nuclei. See nucleus. nucleus. The first structurally stable particle capable of initiating recrystallization of a phase or the growth of a new phase, and possessing an interface with the parent matrix. The term is also applied to a foreign particle that initiates such action.
partial annealing. An imprecise term used to denote a treatment given cold-worked material to reduce the strength to a controlled level or to effect stress relief. To be meaningful, the type of material, the degree of cold work, and the time-temperature schedule must be stated. phase diagram. A graphical representation of the temperature and composition limits of phase fields in an alloy system as they actually exist under the specific conditions of heating or cooling (Fig. 7). A phase diagram may be an equilibrium diagram, an approximation to an equilibrium diagram, or a representation of metastable conditions or phases. Synonymous with constitution diagram. Compare with equilibrium diagram. plastic deformation. The permanent (inelastic) distortion of metals under applied stresses that strain the material beyond its elastic limit. polymorphism. The property of a chemical substance crystallizing into two or more forms having different structures, such as diamond and graphite.
Glossary of Terms Related to Heat Treating /643
Fig. 7 Aluminum-silicon phase diagram and cast microstructures of pure components and of alloys of varying compositions. Alloys with less than 12% Si are referred to as hypoeutectic, those with close to 12% Si as eutectic, and those with over 12% Si as hypereutectic. 3000 r-----.-,..,----r--,--,----y----.---r--,-----,
99.95% AI
~-:r~
\ I=-~ .~~~~~~~ 12% Si
postheatlng, Heating weldments immediately after welding, for tempering, for stress relieving, or for providing a controlled rate of cooling to prevent formation of a hard or brittle structure. postweld heat treatment. Any heat treatment that follows the welding operation. pot annealing. Same as box annealing. precipitation. In metals, the separation of a new phase from solid or liquid solution, usually with changing conditions of temperature, pressure, or both. precipitation hardening. Hardening caused by the precipitation of a constituent from a supersaturated solid solution. See also age hardening and aging. precipitation heat treatment. Artificial aging in which a constituent precipitates from a supersaturated solid solution. preheating. Heating before some further thermal or mechanical treatment. For some nonferrous alloys, heating to a high temperature for a long time, to homogenize the structure before working. In welding and related processes, heating to an intermediate temperature for a short time immediately before welding, brazing, soldering, cutting, or thermal spraying. press quenching. A quench in which hot dies are pressed and aligned with a part before the quenching process begins. Then the part is placed in contact with a quenching medium in a controlled manner. This process avoids part distortion. process annealing. An imprecise term denoting various treatments used to improve workability. For the term to be meaningful, the condition ofthe material and the time-temperature cycle used must be stated. progressive aging. Aging by increasing the temperature in steps or continuously during the aging cycle. See also aging and compare with interrupted aging and step aging.
20% Si
50%Si
protective atmosphere. The atmosphere in a heat treating or sintering furnace designed to protect the parts or compacts from oxidation, nitridation, or other contamination from the environment. Examples are inert gases (e.g., argon), combusted fuel gases, hydrogen, and vacuum. pyrometer. A device for measuring temperatures above the range of liquid thermometers.
Q quarter hard. A temper of nonferrous alloys characterized by tensile strength about midway between that of dead soft and halfhard tempers. quench aging. Aging induced by rapid cooling after solution heat treatment. quench cracking. Fracture of a metal during quenching from elevated temperature. Most frequently observed in hardened steels. quenching. Rapid cooling. When applicable, the following more specific terms should be used: brine quenching, caustic quenching, cold die quenching, forced-air quenching, intense quenching, press quenching, spray quenching, fog quenching, hot quenching, interrupted quenching, selective quenching, time quenching, water quenching, and water/polymer quenching.
R racking. A term used to describe the placing of parts to be heat treated on a rack or tray. This is done to keep parts in a proper position to avoid heat-related distortions and to keep the parts separated. See fixturing.
644/ Heat Treater's Guide: Nonferrous Alloys recovery. Reduction or removal of work-hardening effects, without motion oflarge-angle grain boundaries. recrystallization. (1) The formation of a new, strain-free structure from that existing in cold-worked metal, usually accomplished by heating. (2) The change from one crystal structure to another, as occurs on heating or cooling through a critical temperature. recrystallization annealing. Annealing cold-worked metal to produce a new grain structure without phase change. recrystallization temperature. (1) The lowest temperature at which the distorted grain structure of a cold-worked metal is replaced by a new, strain-free grain structure during prolonged heating. Time, purity of the metal, and prior deformation are important factors. (2) The approximate minimum temperature at which complete recrystallization of a coldworked metal occurs within a specified time. recrystallized grain size. (1) The grain size developed by heating coldworked metal. The time and temperature are selected so that, although recrystallization is complete, essentially no grain growth occurs. (2) In aluminum and magnesium alloys, the grain size after recrystallization, without regard to grain growth or the recrystallized conditions. See also recrystallization. reducing flame. A gas flame produced with excess fuel in the inner flame. refractory. (1) A material of very high melting point with properties that make it suitable for such uses as furnace linings and kiln construction. (2) The quality of resisting heat. residual stress. An internal stress not depending on external forces resulting from such factors as cold working, phase changes, or temperature gradients. Rockwell hardness test. An indentation hardness test based on the depth of penetration, under constant load, as a measure of hardness. Either a 1200 diamond cone with a slightly rounded point or a 1.6 or 3.2 mm (0.0625 in or 0.125 in.) diam steel ball is used as the indenter.
s salt bath heat treatment. Heat treatment carried out in a bath of molten salt. saponification number. A number given to quenching oils that reflects the oils' amount of compounding with fatty materials, which thereby helps evaluate the condition of these oils in service. See also neutralization number. secondary recrystallization. The process by which a few large grains are nucleated and grow at the expense of a fine-grained, but essentially strain-free matrix. Also known as abnormal or discontinuous grain growth. See also primary recrystallization. selective heating. Intentionally heating only certain portions of a workpiece. selective quenching. Quenching only certain portions of an object. severity ofquench. Ability of quenching medium to extract heat from a hot metal workpiece; expressed in terms of the Grossmann number (H) number. sintering. The bonding of adjacent surfaces in a mass of particles by molecular or atomic attraction on heating at high temperatures below the melting temperature of any constituent in the material. Sintering strengthens a powder mass and normally produces densification and, in powdered metals, recrystallization. soaking. Prolonged holding at a selected temperature to effect homogenization of structure or composition. soft temper. Same as dead soft temper. solid solution. A single, solid, homogeneous crystalline phase containing two or more chemical species. solute. The component of either a liquid or solid solution that is present to a lesser or minor extent; the component that is dissolved in the solvent. solution heat treatment. Heating an alloy to a suitable temperature, holding at that temperature long enough to cause one or more constituents to enter into solid solution, and then cooling rapidly enough to hold these constituents in solution.
spalling. A chipping or flaking of a surface due to any kind of improper heat treatment. spinodal hardening. See aging. spinodal structure. A fine homogeneous mixture of two phases that form by the growth of composition waves in a solid solution during suitable heat treatment. The phases of a spinodal structure differ in composition from each other and from the parent phase but have the same crystal structure as the parent phase. spray quenching. A quenching process using spray nozzles to spray water or other liquids on a part. The quench rate is controlled by the velocity and volume of liquid per unit area per unit of time of impingement. spring temper. A temper of nonferrous alloys characterized by tensile strength and hardness about two-thirds of the way fromfull hard to extra spring temper. stabilizing treatment. Before finishing to final dimensions, repeatedly heating a ferrous part to or slightly above its normal operating temperature and then cooling to room temperature to ensure dimensional stability in service. step aging. Aging at two or more temperatures, by steps, without cooling to room temperature after each step. See aging, and compare with interrupted aging and progressive aging. strain aging. Aging following plastic deformation. strain hardening. An increase in hardness and strength of metals caused by plastic deformation at temperatures below the recrystallization range. Also known as work hardening. stress equalizing. A low-temperature heat treatment used to balance stresses in cold-worked material without an appreciable decrease in the mechanical strength produced by cold working. stress relieving. Heating to a suitable temperature, holding long enough to reduce residual stresses, and then cooling slowly enough to minimize the development of new residual stresses. supercooling. Cooling below the temperature at which an equilibrium phase transformation can take place, without actually obtaining the transformation. superheating. Heating above the temperature at which an equilibrium phase transformation should occur without actually obtaining the transformation. superplasticity. The ability of certain metals (most notably aluminum- and titanium-base alloys) to develop extremely high tensile elongations at elevated temperatures and under controlled rates of deformation.
T temper. In nonferrous alloys the hardness and strength produced by mechanical or thermal treatment, or both, and characterized by a certain structure, mechanical properties, or reduction in area during cold working. thermal analysis. Amethod for determining transformations in a metal by noting the temperatures at which thermal arrests occur. These arrests are manifested by changes in slope of the plotted or mechanically traced heating and cooling curves. When such data are secured under nearly equilibrium conditions of heating and cooling, the method is commonly used for determining certain critical temperatures required for the construction of equilibrium diagrams. thermal electromotive force. The electromotive force generated in a circuit containing two dissimilar metals when one junction is at a temperature different from that of the other. See also thermocouple. thermal fatigue. Fracture resulting from the presence of temperature gradients that vary with time in such a manner as to produce cyclic stresses in a structure. thermal shock. The development of a steep temperature gradient and accompanying high stresses within a structure. thermal stresses. Stresses in metal resulting from nonuniform temperature distribution.
Glossary of Terms Related to Heat Treating /645
Fig. 8 Widmanstatten precipitation in a Cu-3Ti alloy aged 10 h at 730°C (1345 OF). 420x
thermochemical treatment. Heat treatment carried out in a medium suitably chosen to produce a change in the chemical composition of the object by exchange with the medium. thermocouple. A device for measuring temperatures, consisting of lengths of two dissimilar metals or alloys that are electrically joined at one end and connected to a voltage-measuring instrument at the other end. When one junction is hotter than the other, a thermal electromotive force is produced that is roughly proportional to the difference in temperature between the hot and cold junctions. thermomechanical working. A general term covering a variety of processes combining controlled thermal and deformation treatments to obtain specific properties. Same as thermal-mechanical treatment. three-quarters hard. A temper of nonferrous alloys characterized by tensile strength and hardness about midway between those of halfhard and full hard tempers. time quenching. A term used to describe a quench in which the cooling rate of the part being quenched must be changed abruptly at some time during the cooling cycle. time-temperature-transformation (TTT) diagram. See isothermaltransformation(IT) diagram. toughness. The ability of a metal to absorb energy and deform plastically before fracturing. transformation ranges. Those ranges of temperature within which a phase forms during heating and transforms during cooling. The two ranges are distinct, sometimes overlapping but never coinciding. The limiting temperatures of the ranges depend on the composition of the alloy and on the rate of change of temperature, particularly during cooling. See also transformation temperature. transformation temperature. The temperature at which a change in phase occurs. The term is sometimes used to denote the limiting temperature of a transformation range.
transgranular. Through or across crystals or grains. Also called intracrystalline or transcrystalline. transgranular cracking. Cracking or fracturing that occurs through or across a crystal or grain. Also called transcrystalline cracking. Contrast with intergranularcracking. transgranular fracture. Fracture through or across the crystals or grains of a metal. Also called transcrystalline fracture or intracrystalline fracture. Contrast with intergranularfracture. transition temperature. (1) An arbitrarily defined temperature that lies within the temperature range in which metal fracture characteristics (as usually determined by tests of notched specimens) change rapidly, such as the ductile-to-brittle transition temperature (DB'IT). The DBTT can be assessed-in several ways, the most common being the temperature for 50% ductile and 50% brittle fracture (50% fracture appearance transition temperature, or FATT),or the lowest temperature at which the fracture is 100% ductile (100% fibrous criterion). The DBTT is commonly associated with temper embrittlement. (2) Sometimes used to denote an arbitrarily defined temperature within a range in which the ductility changes rapidly with temperature. twin. 1\vo portions of a crystal with a defmite orientation relationship; one may be regarded as the parent, the other as the twin. The orientation of the twin is a mirror image of the orientation of the parent across a twinning plane or an orientation that be derived by rotating the twin portion about a twinning axis. See also annealing twin.
u undercooling. Same as supercooling.
v vacuum annealing. Annealing carried out at subatmospheric pressure. Vickers hardness test. A microindentation hardness test employing a 136° diamond pyramid indenter and variable loads, enabling the use of one hardness scale for all ranges of hardness - from soft lead to cemented tungsten carbide. Also known as the diamond pyramid hardness test.
w water quenching. A quench in which water is the quenching medium. The major disadvantage of water quenching is its poor efficiency at the beginning or hot stage of the quenching process. Widmanstiitten structure. A structure characterized by a geometrical pattern resulting from the formation of a new phase along certain crystallographic planes of the parent solid solution. The orientation of the lattice in the new phase is related crystallographic ally to the orientation of the lattice in the parent phase. The structure was originally observed in meteorites, but is readily produced in many alloys ferrous and nonferrous - by appropriate heat treatment (Fig. 8).
Conversion Tables
Conversion Tables /649
Common Units for Converting From the English to the Metric (SI) System The International System of Units (SI for short) is a modernized version of the metric system. It is built upon seven base units' and two supplementary units. Derived units are related to base and supplementary units by formulas in the right-hand column. Symbols for units with
specific names are given in parentheses. The information supplied in this Data Sheet, adapted from the revised Metric Practice Guide, Standard E380 ASTM, includes a selected list of factors for converting U. S. customary units to SI units.
Metric Units and Conversion Factors
'Ib convert from
Quantity
Unit
Base units length. . . . . . . . . . . . . . . . . .. mass time . . . . . . . . . . . . . . . . . . . . electric current . . . . . . . . .. thermodynamic temperature amount of substance . . . .. luminous intensity
kelvin (K) mole (mol) candela (cd)
Supplementary units plane angle solid angle
radian (rad) steradian (sr)
Metric Conversion Factors Formula
metre (rn) kilogram (kg) second (s) ampere (A)
Derived units acceleration . . . . . . . . . . . .. metre per second squared mis' activity (of a radioactive source) disintegration per second (disintegrationl/s angular acceleration . . . .. radian per second squared rad/s' angular velocity radian per second rad(s area square metre m density kilogram per cubic metre kg/rn" electric capacitance '" farad (F) A· s/V electric conductance siemens (8) A/V electric field strength . . . . volt per metre Vim electric inductance henry (H) V's/A electric potential difference . . . . . . volt (V) W/A electric resistance. . . . . . . . ohm Co') VIA electromotive force volt (V) W/A energy joule (J) N'm entropy joule per kelvin J/K force . . . . . . . . . . . . . . . . . . .. newton (N) kg vm/s" frequency . . . . . . . . . . . . . .. hertz (Hz) (eyclel/s illuminance lux (lx) lm/rn" luminance candela per square metre cd/rn" luminous flux lumen (lm) cd v sr magnetic field strength ampere per metre A/m magnetic flux weber (Wb) V 's tesla (T) magnetic flux density Wb/m' ampere (A) magnetomotive force power watt (W) st« pressure pascal (Pa) N/m' quantity of electricity coulomb (e) A· s quantity of heat joule (J) N'm radiant intensity watt per steradian W/sr specific heat joule per kilogram-kelvin J/kg' K stress . . . . . . . . . . . . . . . . . .. pascal (Pa) N/m' thermal conductivity ..... watt per metre-kelvin W/m·K metre per second velocity m/s Pa s pascal-second viscosity, dynamic square metre viscosity, kinematic per second m'/s voltage volt (V) W//'>. volume cubic metre m3 wavenumber reciprocal metre (wave)/m work joule (J) N'm r
Multiply by
'Ib
1.013 25 x 105 1.055 056 x 10 3 2.930 711 x 10- 1 J 4.186800(a) 1.000 OOO(a) x 10- 3 Pa . s 1.000 OOO(a) x 10- 6 m:/s 5.067 075 x 10- 10 m tC = (tF - 32)/1.8 °C 3.048 OOO(a) x 10- 1 m 9.290 304(a) x 10-' m" 2.831 685 x 10- 2 m" J . 1.355818 2.259 697 x 10-' W 3.048 OOO(a) x 10- 1 m(s2 3.785412 x 10-3 m 7.460000(a) x 102 W 2.540 OOO(a) x 10-' m 6.451 600(a) x 10-< m' 1.638 706 x 10-5 m" Pa 3.376 85 x 103 2.4884 x 10' Pa 9.806 650(a) x 10< Pa N 4.448 222 x 103 6.894 757 x 106 Pa 2.957 353 x 10- 5 m" 2.780 139 x 10- 1 N 2.834 952 x 10-' kg kg/m' 3.051 52 x 10- 1 2 3.390 575 x 10-' kg/m 4.731 765 x 10-< m" N 4.448222 4.535 924 x 10- 1 kg Pa 6.894 757 x 103 kg/rn" 2.767 990 x 10< kg/m3 1.601 846 x 10 9.463 529 x 10-< m" kg 9.071 847 x 10' Pa 1.333 22 x 10' 3.600 OOO(a) x 103 J 9.144 OOO(a) x 10- 1 8.361 274 x 10- 1 7.645 549 x 10- 1 yard3 •••••••••••••••••••••••••••• rn"
atmosphere (760 mm Hg) Btu (International Table) Btu (International Tablet/hour calorie (International Table) centipoise centistoke, Circular mil. degree Fahrenheit foot foot" foot" foot-pound-force foot-pound-force/minute foot/second' gallon (U. 8. liquid) horsepower (electric) inch inch' inch" inch of mercury (60 F) inch of water (60 F) kilogram-force/centimetre' kip (1000 IbO kip/inch' (ksi) ounce (U. 8. fluid) ounce-force (avoirdupois) ounce-mass (avoirdupois) ounce-mass/It" ounce-mass/yard' pint (U. 8. liquid) pound-force (lbf avoirdupois) pound-mass (Ibm avoirdupois) pound-force/inch' (psi) pound-mass/inch" pound-mass/foot" quart (U. S. liquid) ton (short, 2000 Ibm) torr (mm-Hg) watt-hour
Pa J W
~:~~2::: :: ::::: ::: :: ::: ::: :::: :::~, (a) Exact
Multiplication Factors Multiplication factors
1 000 000 000 000 = 1 000 000 000 = 1 000 000 = 1000 = 100 = 10 = 0.1 = 0.01 = 0.001 = 0.000 001 = 0.000 000 001 = 0.000 000 000 001 = 0.000 000 000 000 001 = 0.000 000 000 000 000 001 = (a) 'Ib be avoided where possible
10 12 10' 10 6 10 3 10' 10 1 10- 1 10-' 10- 3 10- 6 10-' 10-1 ' 10- 15 10- 18
Prefix
SI symbol
tera giga mega kilo hecto(a) dekala) deci(a) centila) milli micro nano pico femto atto
T G M k h da d c m !L
n
~ a
Cross Reference
Cross Reference to Nonferrous Alloys The following index was developed to help the Heat Treater cross-index chemically similar specifications. The specifications are listed alpha-numerically by country of origin. It is recommended that this index serve only as a guide. Any determination of the true equivalence of any two alloys should only be made after careful comparison of their chemical compositions. For further information on the chemical compositions and mechanical properties of the alloys listed in this index the reader may find it useful to consult such publications as the Worldwide Guide to Equivalent Nonferrous Metals and Alloys, 3rd edition, ASM, 1995 and Waldman s Engineering Alloys. 8th Edition, ASM, 1994.
Designation
Alloy Name
A3004 B4043
3004.Alclad 3004 4043
Page
Australia 182 185
Austria Onorm AlCuMgl AlCuMg2 AIMg5 AlZnMg-Cul.5 E-AIMgSi
2017 2024.A1c1ad 2024 5056,Alclad 5056 7075, A1c1ad 7075 6101
S12P SC51 SC84 SGIIP SGl21 SN122 ZG62 ZG62A1c1ad
1100 1050 295.0 (4.5Cu-l.ISi) 2014,Alclad 2014 2011 2024. Alclad 2024 2017 242.0 (4Cu-2Ni-2.5Mg) 514.0 (4Mg) 520.0 (lOMg) 5454 5083 5356 5056,A1c1ad 5056 5052 5154 5254 6061.Alclad 6061 AG4OA; Zn-4Al-0.04Mg AC41A;Zn-4A1-lCu-0.05Mg AG4OA; Zn-4A1-0.04Mg AC41A;Zn-4A1-lCu-0.05Mg 3003.Alclad 3003 4043 443.0.A443.0, B443.0, C443.0 (5.2Si) 413.0,M13.0 (118i) 355.0.C355.0 (5Si-1.3Cu-0.5Mg) 380.0,A380.0 (8.5Si-3.5Cu) 6151 4032 336.0 (l2Si-2:5Ni-lMg-lCu) 7075,Alclad 7075 7075, Alclad7075
159 159 188 221' 209
151 149 250 155 155 159 159 249 264 265 194 189 194 188 187 191 193 201 615 616 615 616 180 185 264 263 255 261 209 184 252 221 221
GB3620TA-2 GB 3620TA-3 GB3620TA-7 GB 3620TC-1O Ti-3A1-2.5V Ti-8A1-lMo-lV
UnalloyedTitanium. ASTM Grade 1. UNS R50250 UnalloyedTitanium, ASTM Grade2, UNS R50400 UnalloyedTitanium.Grade 4, UNSR50700 Ti-5AI-2.5Sn Ti-6A1-6V-2Sn Ti-3A1-2.5V Ti-8A1-lMo-IV
Ti-6AI-4V UnalloyedTitanium, ASTM Grade2. UNS R50400
prEN2526Ti-P02 prEN2527Ti-P04 prEN2530 prEN2531 prEN3120Ti-P69 prEN3310 prEN3311 prEN3312 prEN3313 prEN3314 prEN3315 prEN3316Ti-P64 prEN3317Ti-P64 prEN3318Ti-P64 prEN3319Ti-P64 prEN3320Ti-P64 prEN3352 prEN3353 prEN3354 prEN3355 prEN3378Ti-P02 prEN3441 PO1 prEN3442 Ti-P02 prEN3443Ti-P04 prEN3451 Ti-P02 prEN3452Ti-P02 prEN3453Ti-P04 prEN3456 prEN3457 prEN3458 prEN3460Ti-P02 prEN3461 Ti-P04
467 prEN3496Ti-P04 469 prEN3498Ti-P02 472 483 536 478 498
Europe AECMA prEN2517Ti-P63 prEN2518Ti-P02
prEN2520Ti-P04
prEN3464 prEN3467 prEN3487POI
China GB3620TA-l
AECMA prEN2519Ti-P04
prEN2525POI
Canada CSA 990C 9950 C4 C541N CB60 CE42 CM41 CN42 G4 GlO GM31N GM41 GM50P GM50R GR20 GR40 GR40 GSllN HZ-3 HZ-3 HZ-ll HZ-II MCIO S5 S5
Designation
522 469
prEN3499Ti-P04
Alloy Name
UnalloyedTitanium,Grade4. UNSR50700 UnalloyedTitanium,Grade4. UNSR50700 UnalloyedTitanium.ASTM Grade I, UNS R50250 UnalloyedTitanium,ASTM Grade2. UNSR50400 UnalloyedTitanium,Grade4. UNSR50700 Ti-6AI-4V Ti-6AI-4V Ti-3AI-2.5V Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V Ti-6A1-4V Ti-6A1-4V Ti-6A1-4V Ti-6AI-6V-18n Ti-6A1-6V-2Sn Ti-6AI-6V-2Sn Ti-6AI-6V-2Sn Ti-6A1-6V-2Sn Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V UnalloyedTitanium.ASTM Grade2, UNS R50400 UnalloyedTitanium,ASTM Grade 1. UNS R50250 UnalloyedTitanium,ASTM Grade2, UNS R50400 UnalloyedTitanium.Grade 4. UNSR50700 UnalloyedTitanium.ASTM Grade2. UNS R50400 UnalloyedTitanium,ASTM Grade2. UNS R50400 UnalloyedTitanium,Grade4. UNSR50700 Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V UnalloyedTitanium.ASTM Grade2, UNSR50400 UnalloyedTitanium,Grade 4. UNSR50700 Ti-6AI-4V Ti-6AI-4V UnalloyedTitanium,ASTM Grade 1. UNS R50250 UnalloyedTitanium,Grade 4. UNSR50700 UnalloyedTitanium,ASTM Grade2. UNS R50400 UnalloyedTitanium,Grade 4. UNSR50700
Page
472 472 467 469 472 522 522 478 522 522 522 522 522 522 536 536 536 536 536 522 522 522 522 469 467 469 472 469 469 472 522 522 522 469 472 522 522 467 472 469 472
Foreign Elektron A8 AZ31 AZ61 AZ91
AZ81A AZ3IB.AZ31C AZ61A AZ91A.AZ91B.AZ91C, AZ9lD. AZ91E
435 423 424 436
Designation
Alloy Name
Elektron AZG MSR-B QH21A RZ5 1'26 Z5Z ZE63A ZREI ZTl ZW6
AZ63A QE22A QH21A ZE41A ZH62A ZK51A ZE63A EZ33A HZ32A ZK60A
Page
433
444 446
450 453 454 452 440 443 431
France AFNOR G-A371 G-A6Z1 G-Z5Zr ZA4G ZA4U3G ZA4U1G AIR 3380G-A9 3380G-AZ91 3380RZ5 33801'26 3380Z5Z 3380ZREI 9182T-35 9182T-35 9182T-40 9182T-50 9182T-60 9183T-A6V 9184T-A6V MSR-BAECMA MG-C-51 NF A-GO.6 A-Gl A-G2.5C A-G2.5MC A-G4MC A-G5 A-GSIL A-GSUC A-GlO A-GC3 A-MI A-MIG A-S5 A-SI2N2G A-SI2UN A-SI3 A-U2GN A-U4G1 A-U4N A-U4NT A-U4Pb A-U4SG A-U6MT
AZ31B.AZ31C AZ61A ZK60A AG4OA; Zn-4A1-0.04Mg AC43A; Zn-4A1-2.5Cu-0.04Mg AC41A;Zn-4A1-ICu-O.05Mg
423 424 431 615 615 616
AZ81A AZ91A.AZ91B,AZ9IC. AZ9lD.AZ91E ZE41A ZH62A ZK51A EZ33A UnalloyedTitanium,ASTM Grade 1. UNS R50250 UnalloyedTitanium.ASTM Grade2. UNS R504ll0 UnalloyedTitanium,ASTM Grade 2. UNS R504ll0 UnalloyedTitanium,ASTM Grade 3. UNS R50550 UnalloyedTitanium.Grade4. UNSR50700 Ti-6AI-4V Ti-6A1-4V
435 436 450 453 454 440 467 469 469 471 472 522 522
QE22A
444
5005 5050 5052 5454 5086.A1c1ad 5086 5356 6101 6061, A1c1ad 6061 520.0 (10Mg) 5154 3003. Alclad3003 3004. Alc1ad 3004 4043 336.0 (12Si-2.5Ni-lMg-lCu) 4032 413.0. M13.0(118i) 2618 2024, A1c1ad 2024 2218 242.0 (4Cu-2NI-2.5Mg) 2011 2014. A1c1ad 2014 2219, A1clad 2219
185 186 187 194 191 194 209
201 265 191 180 182 185 252 184 263 179 159 173 249 155 155 174
654/ Cross Reference to Nonferrous Alloys Designation
Alloy Name
Page
NF A-U46 A5 A5/L A45 Uglne TD12ZrE UT35 UT35-02
UT40 UT50 UT60 UT662 UT6242 UTA5E UTA5EL UTA6V UTA7D UTA8DV
Alloy Name
Page
DIN 2017 1050 1350 1100 Ti-l1.5Mo-6Zr-4.5Sn Unalloyed Titanium, ASTM Grade 2, UNS R50400 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 . Unalloyed Titanium, Grade 4, UNSR50700 Ti-6A1-6V-2Sn Ti-6A1-2Sn-4Zr-2Mo-O.08Si Ti-5Al-2.5Sn Ti-5Al-2.5Sn Ti-6AI-4V Ti-7AI-4Mo Ti-8AI-IMo-IV
159 149 154 151 559 469
474 469 471 472 536 492 483 483 522 541 498
Germany DIN 17293.5101 17293.5102 17293.5103 17293.5105 17293.5164 17293.5612 17293.5812 17293.5912
Designation
ZE4IA ZH62A EZ33A HZ32A QE22A AZ6IA AZSIA AZ91A,AZ91B,AZ91C, AZ9lD,AZ9lE 1743 AC41A; Zn-4AI-1Cu-0.05Mg 1743 AC43A; Zn-4AI-2.5Cu-0.04Mg 1743 AG40A; Zn-4AI-0.04Mg 97153.5161 ZK60A AZ3IB,AZ31C 97153.5312 97153.5612 AZ61A 17850 3.7025 Unalloyed Titanium, ASTM Grade I, UNS R50250 Ti-6Al-4V 178503.7165 17850TiI Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM 17850Ti II Grade 2, UNS R50400 Unalloyed Titanium, ASTM 17850Tiill Grade 2, UNS R50400 17850 TiN Unalloyed Titanium, ASTM , Grade 3, UNS R50550 17850 WL 3.7035 Unalloyed Titanium, ASTM, Grade 2, UNS R50400 17850 WL 3.7055 Unalloyed Titanium, ASTM , Grade 2, UNS R50400 17850 WL 3.7065 Unalloyed Titanium, ASTM, Grade 3, UNS R50550 178513.7165 Ti-6A1-4V 178513.7225 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 17851 3.7235 Modified Ti (Ti-0.2Pd), Grade 7, , UNS R52400; Grade n, UNSR52250 178513.7255 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 17851 Ti-5Al-2.5Sn Ti-5Al-2.5Sn 17851 WL 3.7115 Ti-5AI-2.5Sn 17860 3.7025 Unalloyed Titanium, ASTM Grade I, UNS R50250 178603.7035 Unalloyed Titanium, ASTM Grade 2, UNS R50400 17860 3.7055 Unalloyed Titanium, ASTM Grade 3, UNS R50550 17860 3.7065 Unalloyed Titanium, Grade 4, UNSR50700
450 453 440 443
444 424 435 436 616 615 615 431 423 424 467 522
17860 3.7615 17862 3.7025 178623.7035 178623.7055 178623.7065 178623.7615 178633.7025 17863 3.7035 178633.7055 178633.7065 17864 3.7025 17864 3.7035 17864 3.7055 17864 3.7065 17864 3.7615 AICuBiPb AICuMgl AlCuMg2 AlCuSiMn AlMgl AIMg2.5 AlMg2.7Mn AlMg4 AlMg4.5Mn AlMg5 AlMn AlMnlMgl AISi5 AIZn-MgCu1.5 A199.5 E-AI99.5 E-AlMgSiO.5 Otto Fuchs TI
467 TI 469 T6 469 471 469 469 471 522
TL52 TL62 TL64 TL64ELI Thyssen Contimet 30 35 35D
474 55 474
474 483 483 467
AlMoV8-1-1 AISn52 AlSn52ELI AISnZrMo 6-2-4-2 AIV32 AIV64 AIV 64 ELI AIVSn6-6-2 Pd 02130
469 471 472
Pd 02135
Ti-6A1-4V Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6Al-4V Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Unalloyed Titanium, Grade 4, UNSR50700 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6A1-4V 2011 2017 2024, AIclad 2024 2014, Alclad 2014 5005 5052 5454 5086, Alclad 5086 5083 5056, Alclad 5056 3003, Alclad 3003 3004, Alclad 3004 4043 7075, Alclad 7075 1050 1350 6101
522 467 469 471 472 522 467 469
Designation
ThyssenLT 24 31 33 ThyssenRT 12(Pd)
15(Pd)
471 472
18(Pd)
467 469
Titan RT 20
471 472 522 155 159 159 155 185 187 194 191 189 188 180 182 185 221 149 154 209
Alloy Name
Thyssen Contimet Pd02l35 D Modified Ti (Ti-Q.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 TiNiMo83 Ti-0.3Mo-O.8Ni, ASTM Grade 12, R53400
Werkstoff-Nr 3.1325 3.2245 3.3207 3.3457 3.4365 3.7064 3.7164 3.7264 WL 3.7024 3.7034 3.7114 3.7144 3.7174
Ti-6Al-2Sn-4Zr-2Mo-O.08Si Ti-6AI-4V Ti-6Al-6V-2Sn Modified Ti (Ti-Q.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-Q.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-Q.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASTM Grade 3, UNS R50550 2017 4043 6101 5083 7075, Alclad 7075 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6AI-4V Ti-6Al-4V Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Ti-5AI-2.5Sn Ti-6AI-2Sn-4Zr-2Mo-O.08Si Ti-6AI-6V-2Sn
Page
474 476 492 522 536
474
474
474
471 159 185 209
189 . 221 472 522 522
469 469 483 492 536
Italy Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, Grade 4, UNSR50700 Ti-5Al-2.5Sn Ti-6AI-2Sn-4Zr-2Mo-O.08Si Ti-6A1-4V Ti-6A1-4V Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Ti·8Al-IMo-IV Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-6Al-2Sn-4Zr-2Mo-O.08Si Ti-3AI-2.5V Ti-6AI-4V Ti-6Al-4V Ti-6AI-6V-2Sn Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250
467 469 472 483 492 522 522
UNI P-AlCu4.5MgMn P-AlMgO.9 P-AlMg1.5 P-AlMg2.5 P-AISi 12MgCuNi P-AISiO
DTI
469
DTI
469
DT4
471 498 483 483 492 478 522 522 536
DT5
474
159 198 186 187 184 209
Japan Daido DTl
467
474
2024, Alclad 2024 5657 5050 5052 4032 6101
JIS Class 1 Ti Class 1 Class 2 Class 3 H 2201 Class I H 2201 Class 2 H 4361 TTH 35D Class 2 H 4600 TP 28 HlC Class 1
Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6Al-4V Unalloyed Titanium, ASTM Grade 1, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 AG4OA; Zn-4Al-O.04Mg AC41A; Zn-4AI-1Cu-0.05Mg Unalloyed Titanium,ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade I, UNS R50250
467 469 471 472 522
467 469 471 615 616 469 467
Cross Reference to Nonferrous Alloys I 655 Designation JlS H 4600 TP 35 HlC Class 2 H 4600 TP 49 HlC Class 3 H 4600 TR 28 HlC Class 1 H 4600 TR 35 HlC Class 2 H 4600 TR49 HlC Class 3 H 4630 TTP28 DIE Class 1 H 4630 TTP28 WfWDClass 1 H 4630 TTP 35 DIE Class 2 H4630TTP35 WfWD Class 2 H4630TTP49 DIE Class 3 H 4630 TTP49 WfWDClass3 H4631 TTH28 D Class 1 H4631 TTH28 WfWDClass 1 H4631 TTH35 WfWD Class 2 H463I TTH49 DClass 3 H463I TTH49 WfWDClass3 H 4635 type 11 TTP28PdD H 4635 type 11 TTP28PdE H 4635 type 11 TTP28PdW H 4635 type 11 TTP28PdWD H 4635 type 12 TTP35PdD H 4635 type 12 TTP35PdE H 4635 type 12 TTP35PdW H 4635 type 12 TTP35PdWD H 4635 type 13 TTP49PdD H 4635 type 13 TTP49PdE H 4635 type 13 TTP49PdW H 4635 type 13 TTP49PdWD H 4636 type 11 TTH28PdD H 4636 type 11 TTH28PdW H 4636 type 11 TTH28PdWD H 4636 type 12 TTH35PdD
Alloy Name
Unalloyed TItanium, ASlM Grade 2, UNS R50400 Unalloyed TItanium, ASlM Grade 3, UNS R50550 Unalloyed TItanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 3, UNS R50550 Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed TItanium, ASlM Grade 3, UNS R50550 Unalloyed TItanium, ASlM Grade 3, UNS R50550 Unalloyed TItanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 3, UNS R50550 Unalloyed TItanium, ASlM Grade 3, UNS R50550 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti·0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250
Page
469 471
Designation JlS H4636 type 12 TTH35PdW H 4636 type 12 TTH35PdWD
467 469 471
H 4636 type 13 TTH49PdD H 4636 type 13 TTH49PdW
467 467 469 469 471 471 467 467 469 471 471
474
474
474
474
474
474
H 4636 type 13 TTH49PdWD H4650TB28 CIHClass I H4650TB 35 CIHClass2 H4650TB49 ClHClass 3 H 4655 type 11 TB28PdC H 4655 type 11 TB28PdH H 4655 type 12 TB35PdC H 4655 type 12 TB35PdH H 4655 type 13 TB49PdC H 4655 type 13 TB49PdH H4670TW28 Class I H4670TW35 Class 2 H 4670 TW49 Class 3 H 4675 type II TW28Pd H 4675 type 12 TW35Pd H 4675 type 13 TW49Pd
474
474
474
474
474
474
474
H 5301 ZDC 1 H530I ZDC2 Kobe KS3-2.5 KS5-2-2-4-4 KS5-2.5 KS5-2.5ELI KS6-2-4-2 KS6-2-4-6 KS6-4 KS6-4ELI KS6-6-2 KS8-1-1 KSIO·2-3 KS13·1I·3 KSI5-3-3-3 KS40 KS40LF
474 KS40PdA 474 KS40PdB 474
Alloy Name
Modified Ti (Ti-0.2Pd), Grade 7. UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Unalloyed Titanium, ASlM Grade 1, UNS R50250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium. ASlM Grade 3, UNS R50550 Modified Ti (Ti-O.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 3, UNS R50550 Modified Ti (TI-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 AC4IA; Zn-4AI-lCu-0.05Mg AG40A; Zn-4AI-0.04Mg
Page
Designation Kobe KS40S
474
KS50 KS50LF
474 KS50PdA 474 KS50PdB 474 KS60 474
KS60LF
467
KS70
469
KS70LF
471
KS70PdA
474
KS70PdB
474
KS85 KSGl2
474 KSGl2S 474
474
MMA 5137
TlX Sumilomo SAT-325
467 467 467
474
474 469 469 471 471
474
474 472 476 476
Ti-5AI-2.5Sn
483
Unalloyed Titanium, ASlM Grade 2, UNS R50400
469
Ti-3AI-2.5V
478
Ti-5AI-2.5Sn Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade I, UNS R50250 Modified Ti (Ti-Q.2Pd),Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASlM Grade 3, UNS R50550 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6AI-6V-2Sn
483
469 471
SAT-525 ST-6 ST-40
474 ST-40P 474 ST-50 474 616 615
ST-50P
ST-60P Ti-3AI-2.5V Ti-5AI-2Sn-2Zr-4Mo-4Cr Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-6A1-2Sn-4Zr-2Mo-0.08Si Ti-6AI-2Sn-4Zr-6Mo Ti-6Al-4V Ti-6AI-4V Ti-6AI-6V-2Sn Ti-8AI-IMo-IV Ti-IOV-2Fe-3Al Ti-13V-11Cr-3AI Ti·15V-3Cr-3AI-3Sn Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250
Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Unalloyed Titanium, ASlM Grade I, UNS R50250 Modified ri (Ti-O.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-Q.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 2, UNS R50400 Unalloyed Titanium, ASlM Grade 3, UNS R50550 Unalloyed Titanium, ASlM Grade 3. UNS R50550 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNSR52250 Unalloyed Titanium, Grade 4, UNSR50700 Ti-0.3Mo-0.8Ni, ASlM Grade 12, R53400 Ti-0.3Mo-O.8Ni, ASlM Grade 12, R53400
Page
Nippon
474 467
Alloy Name
478 514 483 483 492 517 522 522 536 498 566 572 577 467
ST-70 ST-80 Ti-6AI-6V-2Sn
467
474 469
474
474 471 472 536
Toho 15PAT
15PBT
20PAT
467 20PBT 474
474
469
MAT 325AT 525AT
Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNS R52250 Modified Ti (Ti-O.2Pd),Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-Q.2Pd),Grade 7, UNS R52400; Grade II, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Ti-6AI-4V Ti-3Al-2.5V Ti-5Al-2.5Sn
474
474
474
474 522 478 483
656/ Cross Reference to Nonferrous Alloys
Deslgnallon
Alloy Name
Page
Alloy Name
Page
BS
Thho 662AT TIB
Ti-6AI-6V-18n UnalloyedTitanium.ASTM Grade2. UNS RS0400 UnalloyedTitanium.ASTM Grade2. UNS RS0400 UnalloyedTitanium.ASTM Grade2. UNS RS0400 UnalloyedTitanium. ASTM Grade2, UNS RS0400 UnalloyedTitanium. ASTM Grade3. UNS RS0550
TIBLF TIC TICLF TID
536 469 469 469 469 471
Russia 4200
ModifiedTi (Ti-0.2Pd), Grade7. UNS RS2400;Grade 11. UNSRS2250
GOST 1.90000-70 VT6 Ti-6AI-4V 1.90000-76 VTI-O UnalloyedTitanium.ASTM Grade2, UNS RS0400 1.90013-71 VTI-OO UnalloyedTitanium, ASTM Grade I. UNS RS0250 1.90060-72 VT6L Ti-6Al-4V 1.90060-72 VTIL UnalloyedTitanium.ASTM Grade2. UNS RS0400 19807-74VT5-1 Ti-5AI-2.5Sn 19807-74VT6S Ti-6Al-4V AK2 Ti-3AI-2.5V IMP-7 Ti-3Al-2.5V IMP-IO Ti-13V-llCr-3AI VT5-IKT Ti-5AI-2.5Sn
474
AG40A;Zn-4AI-0.04Mg AC4IA; Zn-4AI-lCu-0.05Mg ZA-12; Zn-llAI-lCu-0.025Mg ZA-27; Zn-27Al-2Cu-0.015Mg
469 467 522 469 483 522 478 478 572 483
615 616 617 618
UNE UnalloyedTitanium.ASTM Grade 2. UNS RS0400 UnalloyedTitanium.ASTM Grade2, UNS RS0400 UnalloyedTitanium,Grade4. UNSRS0700 ModifiedTi (Ti-0.2Pd), Grade7, UNS RS2400;Grade II, UNSRS2250 Ti-5AI-2.5Sn Ti-8AI-1Mo-IV Ti-6AI-2Sn-4Zr-2Mo-O.08Si Ti-6Al-4V Ti-6Al-6V-18n Ti-13V-11Cr-3AI Ti-11.5Mo-6Zr-4.5Sn 1350 2024, Alclad2024 2218
38-712L-7002 38-714L-7004 38-715L-7021 38-716L-7101 38-717 L-7102 38-718L-7103 38-723L-7301 38-725L-7303 38-729L-7701 38-730L-7702 Al 99.5E L-314 L-315
469 469 472
7075. Alclad7075 2218 6101 7075. Alclad7075 5050
FCI H8 Hll HI2 HI5 H2O Ll8 L95 L96 N3 N5 N62L58 N21 N41 N51 TAI4 TAI5 TAI6 TAI7 TA56 TA59 2TAI 2TA2 2TA3 2TA4 2TA5
474 483 498 492 522 536 572 559 154 159 173
Switzerland Alclad AI-Zn-Mg-Cu-Al VSMAI-Cu-Ni VSMAI-Mg-Si VSMAl-Zn-Mg-Cu VSMAI1.5Mg
2970MAG4 2970MAG5 2970MAG6 2970MAG8 2970MAG9 2970MAGl3 3370MAGill 3372MAGl21 3373 MAG11I 3373MAGI21 3373MAGl61 3531 Part 2 DD 139 DD 139 DD 139
IE
Spain 38-711L-7001
2970MAG3
E6
522
South Africa SAA-ASI881 SAA-ASI881 SAA-ASI881 SAA-ASI881
2TA6 2TA6 2TA7 2TA7 2TA8 2TA8 2TA9
221 173 209 221 186
United Kingdom BS 1B 3L44 91E 150A 1004 1004A lOO4A 2970 MAGI
Designallon
2TA9 2TAIO 2TAll 2TA12 2TA13 2TA28
149 186 209 159 615 616 615 435
165 5004 5013 5023 5045 5055
Alloy Name
Page
DID AZ9IA. AZ9IB, AZ9IC. AZ91D.AZ91E ZKSIA ZE4IA EZ33A HZ32A ZH62A EQ21 AZ3IB.AZ3IC AZ6IA AZ3IB.AZ31C AZ6IA ZK60A Ti-6AI-4V ZA-8;Zn-8AI-ICu-0.02Mg ZA-12; Zn-llAI-lCu-0.025Mg ZA-27;Zn-27AI-2Cu-0.015Mg 6463 2011 5083 6066 2618 2014,Alclad2014 6061,Alclad6061 1350 2017 7075. Alclad7075 7075, Alclad7075 3003. Alclad3003 5154 5056, Alclad5056 4043 5005 5454 Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-5Al-2.5Sn Ti-5AI-2.5Sn Ti-6AI-4V Ti-6AI-4V UnalloyedTitanium,ASTM Grade I. UNS RS0250 Unalloyed Titanium.ASTM Grade2, UNS R50400 UnalloyedTitanium, ASTM Grade2. UNS RS0400 UnalloyedTitanium, ASTM Grade2, UNS R50400 UnalloyedTitanium, ASTM Grade2. UNS RS0400 UnalloyedTitanium.ASTM Grade3, UNS R50550 UnalloyedTitanium,Grade4. UNSRS0700 UnalloyedTitanium.ASTM Grade3, UNS RS0550 UnalloyedTitanium,Grade4, UNSRS0700 UnalloyedTitanium, ASTM Grade3. UNS R50550 UnalloyedTitanium,Grade4. UNSR50700 UnalloyedTitanium,ASTM Grade3. UNS R50550 UnalloyedTitanium,Grade4. UNSRS0700 Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V Ti-6Al-4V
5073 436 454 450
5273
440
5283
443 453 439 423 424 423 424 431 522 617 617 618 214 155 189 208 179 155 201 154 159 221 221 180 191 188 185 185 194 483 483 483 483 522 522 467 469 469 469 469 471 472 471 472 471 472 471 472 522 522 522 522 522
DID 1050 5050 6101 2017 AC43A; Zn-4AI-2.5Cu-0.04Mg AC41A;Zn-4A1-ICu-0.05Mg AG40A;Zn-4AI-0.04Mg AZSIA
Deslgnallon
514.0 (4Mg) 2219.Alclad2219 UnalloyedTitanium, ASTM Grade I. UNS RS0250 UnalloyedTitanium,ASTM Grade3, UNS RS0550 ZE63A QE22A
264 174 467 471 452 444
5303 5313 5323 5363 IMI 110
115 125 130 130 155 160 260 262 318
UnalloyedTitanium.ASTM Grade2, UNS R50400 UnalloyedTitanium.ASTM Grade3. UNS R50550 UnalloyedTitanium.ASTM Grade3. UNS RS0550 TI-6Al-4V Ti-6AI-4V Ti-6Al-4V TI-6AI-4V UnalloyedTitanium,ASTM Grade I, UNS R50250 UnalloyedTitanium,ASTM Grade I. UNSRS0250 UnalloyedTitanium,ASTM Grade2, UNS R50400 UnalloyedTitanium,ASTM Grade2. UNS R50400 UnalloyedTitanium.ASTM Grade3. UNS R50550 UnalloyedTitanium.Grade4. UNSRS0700 UnalloyedTitanium.Grade4, UNSRS0700 ModifiedTi (Ti-0.2Pd), Grade7. UNS RS2400;Grade 11. UNSR52250 ModifiedTi (Ti-O.2Pd), Grade7. UNS RS2400; Grade 11. UNSRS2250 Ti-6Al-4V
469 471 471 522 522 522 522
467 467 469 469 471 472 472 474 474 522
United States
201.0 204.0 206.0 208.0 238.0 242.0 295.0 296.0 308.0 319.0 332.0 336.0 339.0 354.0 355.0 356.0 357.0 359.0 360.0 380.0 383.0 384.0 390.0 413.0 443.0 514.0 518.0 520.0 535.0 712.0 713.0 771.0 850.0
16-25-6 17-14CuMo 19-9DL 201.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-0.25Ti) 204.0 (4.6Cu-0.25Mg-0.17Fe0.17Ti) 206.0,A206.0(4.5Cu-0.30Mn0.25Mg-O.22Ti) 208.0 (4Cu-3Si) 238.0 (10.0%Cu-4.0%Si-0.3%Mg) 242.0 (4Cu-2Ni-2.5Mg) 295.0 (4.5Cu-l.lSi) 296.0 (4.5Cu-2.5Si) 308.0 (5.5Si-4.5Cu) 319.0 (6Si-3.5Cu) 332.0 (9.5%Si-3.0%Cu-1.0%Mg) 336.0 (12Si-2.5Ni-IMg-1Cu) 339.0 (12.0%Si-1.0%Ni1.0%Mg-2.25%Cu) 354.0 (9Si-1.8Cu-0.5Mg) 355.0.C355.0(5Si-I.3Cu-0.5Mg) 356.0, A356.0(7Si-0.3Mg) 357.0,A357.0(7Si-0.5Mg) 359.0 (9Si-0.6Mg) 360.0,A360.0(9.5Si-0.5Mg) 380.0,A380.0(8.5Si-3.5Cu) 383.0 (1O.5Si-2.5Cu) 384.0.A384.0(11.2Si-3.8Cu) 390.0. A390.0(17.0Si-4.5Cu0.6Mg) 413.0,A413.0(118i) 443.0,A443.0.B443.0.C443.0 (5.2Si) 514.0 (4Mg) 518.0 (8Mg) 520.0 (10Mg) 535.0.A535.0.B535.0(7Mg) 712.0 (5.8Zn-0.6Mg-0.5Cr-0.2Ti) 713.0 (7.5Zn-0.7Cu-0.35Mg) 771.0 (7Zn-0.9Mg-O.13Cr) 850.0 (6.2Sn-lCu-INi) 1050 1060 1100 1145
118 119 119 244 245 246 248 248 249 250 251 251 252 252 252 253 253 255 257 259 259 260 261 261 262 262 263 264 264 265 265 266 266 267 267 268 149 150 151 153
Cross Reference to Nonferrous Alloys /657 Designation
Alloy Name 1199 1350 2011 2014, AlcIad2014 2017 2024, AlcIad2024 2048 2090 2091 2124 2218 2219, Alclad 2219 2319 2618 3003, AlcIad3003 3004, AlcIad3004 3105 4032 4043 5005 5050 5052 5056,AlcIad5056 5083 5086,AlcIad5086 5154 5182 5252 5254 5356 5454 5456 5457 5652 5657 6005 6009 6010 6061, Alclad 6061 6063 6066 6070 6101 6151 6201 6205 6262 6351 6463 7005 7039 7049 7050 7072 7075, AlcIad7075 7175 7178, AlcIad7178 7475 8090 A-286 AC41A;Zn-4AI-lCu-0.05Mg AC43A;Zn-4AI-2.5Cu-0.04Mg AG40A; Zn-4AI-0.04Mg AG4OB; Zn-4Al-0.015Mg Air-Resist213 AMlOOA Astroloy AZ3IB,AZ31C AZ61A AZ63A AZ80A AZ81A AZ91A,AZ91B,AZ91C, AZ9ID, AZ91E AZ92A Berylliumcopper 21C (97Cu-2Be-lCo) Berylliumcopper nickel72C (68.8Cu-30Ni-I.2Be) CP276 CustomAge 625 PLUS D-979
Page 153 154 155 155 159 159 169 271 274 171 173 174 178 179 180 182 184 184 185 185 186 187 188 189 191 191 192 193 193 194 194 195 197 198 198 200 200 201 201 206 208 208 209 209 211 211 212 213 214 214 215 217 218 221 221 238 239 241 276 108 616 615 615 616 106 432 17 423 424 433 425 435 436 438 402 403 279 40 19
Designation
Alloy Name
Page
Discaloy Elgiloy EQ21 EZ33A HastelloyB HastelloyB-2 Hastelloy C HastelloyC-4 HastelloyC-276 HastelloyN HastelloyS HastelloyW HastelloyX Haynes 25; L-605 Haynes 188 Haynes214 Haynes230 Haynes242 Haynes 556 High Purity Titanium HK3IA HK31A HM2IA HM31A HZ32A IMI 230; Ti-2.5Cu;AECMATi-Pll IMI 367;Ti-6Al-7Nb IMI417 IMI 550; Ti-4Al-4Mo-2Sn-0.5Si IMI 551; Ti-4A1-4Mo-4Sn-0.5Si IMI 679; Ti-llSn-5Zr-2.25AIIMo-O.25Si IMI 685; Ti-6AI-5Zr-0.5Mo-0.25Si IMI 829; Ti-5AI-3.5Sn-3.0ZrINb-O.3Si IMI 834;Ti-5.8AI-4Sn-3.5Zr0.7Nb-0.5Mo-0.35Si IN 100 IN 102 Incoloy800 Incoloy801 Incoloy802 Incoloy807 Incoloy825 Incoloy901 Incoloy903 Incoloy907 Incoloy909 Incoloy925 Inconel6oo Inconel601 Inconel604 Inconel617 Inconel625 Inconel702 Inconel706 Inconel718 Inconel721 Inconel722 Inconel751 InconelX 750 ModifiedTi (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSRS2250 Monel 400 MoneIK-500 MonelR-405 MP35N MPI59 N-155 NA-224 Nickel 200 Nickel 201 Nimonic75 Nimonic80A Nimonic86 Nimonic90 NimonicPEI6 Nimonic PK33 Pyromet31 Pyromet860 Pyromet CfX-l
Designation
120 106 439 440 33 33 35 36 37 37 37 38 38 99 102 39 40 40 121 463 427 441 429 430 443 504 549 505 549 550 506 509 510 511 19 25 112 114 115 115 115 26 117 117 117 118 81 88 88 88 88 41 29 41 59 59 33 30 474 127 127 127 105 106 119 97 126 126 97 60 40 62 81 81 59 62 122
AMS 470
Alloy Name
Page
PyrometCfX-3 QE22A QH21A RA-330 RA-333 Refractory26 Rene 41 Rene 95 Rene 100 S-816 Stellite6B TI-0.3Mo-O.8Ni, ASlM Grade 12,RS3400 TI-3Al-2.5V 11-3Al-8V-6Cr-4Mo-4Zr (Beta C) TI-4.5Al-3V-2Mo-2Fe Ti-5Al-2.5Fe 11-5A1-2.5Sn 11-5AI-2Sn-2Zr-4M0-4Cr 11-5Al-2Sn-4Zr-4Mo-2Cr-lFe 11-5AI-5Sn-2Zr-2Mo-O.25Si 11-6-22-22S; Ti-6Al-2Sn-2Zr2Mo-2Cr-O.25Si 11-6Al-2Nb-lTa-0.8Mo TI-6A1-2Sn-4Zr-2Mo-O.08Si 11-6Al-2Sn-4Zr-6Mo 11-6Al-4V 11-6A1-6V-18n 11-7AI-4Mo 11-8AI-IMo-lV 11-8Mo-8V-2Fe-3Al Ti-8V-5Fe-IAI TI-I0V-2Fe-3AI TI-l1.5Mo-6Zr-4.5Sn TI-l1.5V-2AI-18n-llZr 11-12V-2.5AI-2Sn-6Zr TI-13V-llCr-3Al TI-13V-2.7AI-7Sn-2Zr 11-15Mo-5Zr 11-15Mo-5Zr-3A1 11-15V-3Cr-3Al-3Sn 11-16V-2.5AI TIMETAL21S; Ti-15Mo-3AI2.7Nb-0.25Si T1METAL 618; Ti-6AI-1.7Fe-0.ISI TIMETAL1100;Ti-6Al-2.75Sn4Zr-0.4Mo-0.45Si; n.noo Udimet500 Udimet520 Udimet700 Udimet710 UMCo-50 UnalloyedTitanium,ASTM Grade I, UNS RS0250 UnalloyedTitanium,ASTM Grade 2, UNS R50400 UnalloyedTitanium,ASTM Grade 3, UNS R50550 UnalloyedTitanium,Grade 4, UNSRS0700 UnitempAF2-IDA V-36 V-57 W-545 Waspaloy WE43 WE54 Weldalite049 ZA-8; Zn-8Al-lCu-0.02Mg ZA-12; Zn-l1AI-lCu-0.025Mg ZA-27; Zn-27Al-2Cu-0.015Mg ZC63 ZC71 ZE41A ZE63A ZH62A ZK51A ZK60A ZK61A
122 444
CI1000 (99.95Cu-0.04O)
300
446 120 97 63 63 68 69 98 98
476 478 563 544 556 483 514 584 557 551 488 492 517 522 536 541 498 586 599 566 559 594 595 572 597 589 591 577 601 582 543 502 69 70 70 74 107 467 469 471 472 74 107 112 112 76 447 448 269 617 617 618 450 431 450 452 453 454 431 456
658/ Cross Reference to Nonferrous Alloys Designation
Alloy Name
Page
AMS 4000 4001 4003 4004 4005 4006 4007 4008 4010 4011 4014 4015 4016 4017 4018 4019 4020 4021 4022 4023 4025 4026 4027 4028 4029 4031 4033 4034 4035 4037 4038 4039 4040 4041 4042 4043 4044 4045 4046 4047 4048 4049 4050 4051 4052 4053 4056 4057 4058 4059 4060 4061 4062 4065 4067 4069 4070 4071 4072 4073 4074 4075 4078 4079 4080 4081 4082 4083 4084 4085 4086 4087 4088 4089 4090 4094 4095 4096 4097 4098
Designation
Alloy Name
Page
150 151 151 187 188 180 159 180 180 153 155 187 187 187 191 191 201 201 201 201 201 201 201 155 155 174 159 159 159 159 221 221 159 159 159 201 221 221 221 221 221 221 218 239 239 201 189 189 189 189 159 159 151 180 180 187 187 187 159 159 159 159 221 201 201 201 201 201 241 241 159 159 159 241 241 174 174 174 159 159
4099 4101 4102 4103 4104 4105 4106 4107 4108 4109 4111 4112 4113 4114 4115 4116 4117 4119 4120 4121 4122 4123 4124 4125 4127 4128 4129 4132 4133 4134 4135 4139 4142 4143 4144 4145 4146 4148 4149 4150 4152 4153 4154 4156 4157 4158 4159 4160 4161 4162 4163 4164 4165 4167 4168 4169 4170 4172 4173 4179 4180 4182 4190 4192 4193 4194 4195 4210 4212 4214 4217 4218 4220 4222 4228 4229 4230 4231
Alloy Name
Page
AMS
AMS 1060 llOO llOO 5052 5056. Alclad 5056 3003. A1cIad 3003 2024. Alclad 2024 3003. Alclad 3003 3003. AlcIad 3003 1145 2014. Alc1ad 2014 5052 5052 5052 5154 5154 6061. A1clad 6061 6061. A1clad 6061 6061. A1cIad 6061 6061. Alclad 6061 6061. Alclad 6061 6061, AlcIad 6061 6061. A1clad 6061 2014. A1cIad2014 2014. Alclad 2014 2219. AlcIad 2219 2024. AlcIad 2024 2024. Alclad 2024 2024. Alclad 2024 2024. A1c1ad2024 7075, A1clad 7075 7075. A1clad 7075 2024. Alclad 2024 2024. A1cIad 2024 2024. AlcIad 2024 6061. A1cIad 6061 7075. Alclad 7075 7075. Alclad 7075 7075. AlcIad 7075 7075. Alclad 7075 7075. Alclad 7075 7075. A1clad 7075 7050 7178. Alclad 7178 7178. A1clad 7178 6061. Alclad 6061 5083 5083 5083 5083 2024. Alclad 2024 2024. AlcIad 2024 llOO 3003. AlcIad 3003 3003. Alclad 3003 5052 5052 5052 2024. Alclad 2024 2024. Alclad 2024 2024, Alclad 2024 2024. AlcIad 2024 7075. Alclad 7075 6061. A1cIad 6061 6061. AlcIad 6061 6061. Alclad 6061 6061. AlcIad 6061 6061. Alclad 6061 7475 7475 2024. Alc1ad 2024 2024. Alclad 2024 2024. Alclad 2024 7475 7475 2219. Alclad 2219 2219. Alclad 2219 2219. Alclad 2219 2024. Alclad 2024 2024, Alc1ad 2024
Designation
2024, A1cIad2024 2124 llOO 2024. A1cIad 2024 2024. A1clad 2024 2024. Alclad 2024 2024, A1clad 2024 7050 7050 7175 7049 2024. Alclad 2024 6061. Alclad 6061 5052 6061. Alc1ad 6061 6061. A1clad 6061 6061, Alclad 6061 2024, A1c1ad2024 2024, Alclad 2024 2014. A1cIad2014 7075. A1clad 7075 7075. A1clad 7075 7075. Alclad 7075 6151 6061. Alclad 6061 6061. Alclad 6061 6061. A1clad 6061 2618 2014. Alclad 2014 2014. Alclad 2014 2014. A1clad 2014 7075. Alclad 7075 2218 2219. A1clad 2219 2219. Alclad 2219 4032 6061. Alclad 6061 7175 7175 6061. Alclad 6061 2024. Alclad 2024 2014. Alclad 2014 7075. Alclad 7075 6063 7049 7178. A1clad 7178 7049 6061. Alclad 6061 6061. Alclad 6061 2219, Alclad 2219 2219, Alclad 2219 2024. Alclad 2024 2024. A1clad 2024 7075. AlcIad 7075 7075, Alclad 7075 7075. Alclad 7075 7075. Alclad 7075 6061. Alclad 6061 6061. Alclad 6061 7175 llOO 5056. Alclad 5056 4043 2024. AlcIad 2024 2024. Alclad 2024 2024. Alclad 2024 2024. Alclad 2024 355.0. C355.0 (5Si-1.3Cu-0.5Mg) 355.0. C355.0 (5Si-1.3Cu-0.5Mg) 355.0. C355.0 (5Si-1.3Cu-0.5Mg) 356.0. A356.0 (7Si-0.3Mg) 356.0. A356.0 (7Si-0.3Mg) 242.0 (4Cu-2Ni-2.5Mg) 242.0 (4Cu-2Ni-2.5Mg) 201.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-0.25Ti) 201.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-0.25Ti) 295.0 (4.5Cu-1.lSi) 295.0 (4.5CU-l.lSi)
159 171 151 159 159 159 159 218 218 238 217 159 201 187 201 201 201 159 159 155 221 221 221 209 201 201 201 179 155 155 155 221 173 174 174 184 201 238 238 201 159 155 221 206 217 239 217 201 201 174 174 159 159 221 221 221 221 201 201 238 151 188 185 159 159 159 159 255 255 255 257 257 249 249 244 244 250 250
4235 4236 4237 4240 4260 4261 4275 4280 4281 4282 4283 4284 4285 4286 4290F 4291 4350 4352 4357 4358 4360 4362 4363 4376 4384E 4388 4389 4390 4417 4418C 4420 4422 4424 4425 4426 4434 4437 4442 4443 4445 4446 4447 4448 4453 4455 4482 4484 4490 4500 4505 4507 4510 4520 4530 4532 4555 4555 4558 4610 4611 4612 4614 4615 4625 4650 4655 4701 4710 4712 4720 4725 4842
206.0. A206.0 (4.5Cu-0.30Mn0.25Mg-O.22Ti) 206.0, A206.0 (4.5Cu-0.30Mn0.25Mg-O.22Ti) 206.0, A206.0 (4.5Cu-0.30Mn0.25Mg-O.22Ti) 520.0 (lOMg) 356.0. A356.0 (7Si-0.3Mg) 356.0. A356.0 (7Si-0.3Mg) 850.0 (6.2Sn-1Cu-1Ni) 355.0. C355.0 (5Si-1.3Cu-0.5Mg) 355.0. C355.0 (5Si-1.3Cu-0.5Mg) 296.0 (4.5Cu-2.5Si) 296.0 (4.5Cu-2.5Si) 356.0, A356.0 (7SI-0.3Mg) 356.0, A356.0 (7Si-0.3Mg) 356.0. A356.0 (7Si-0.3Mg) 360.0. A360.0 (9.5Si-0.5Mg) 380.0. A380.0 (8.5Si-3.5Cu) AZ61A ZK60A AZ3IB.AZ31C AZ61A AZ80A ZK60A HM21A AZ3IB.AZ3IC HK31A HM31A HM31A HM21A EQ21 QE22A AZ63A AZ63A AZ63A ZE63A WE54 AZ92A AZ91A. AZ9IB. AZ91C. AZ9ID.AZ91E EZ33A ZK51A HK31A AZ91A. AZ91 B. AZ91C. AZ9ID.AZ91E HZ32A ZH62A AZ92A AM100A AM100A AZ92A AZ91A. AZ9IB. AZ91C, AZ9ID,AZ91E CllOOO (99.95Cu-0.04O) C26000 (70Cu-30Zn) C26000 (70Cu-30Zn) C51000 (94.8Cu-5Sn-0.2P) C54400 (88Cu-4Pb-4Sn-4Zn) CI7200. C 17300 CI7200. C 17300 C26000 (70Cu-30Zn) C33000 (66Cu-33.5Zn-0.5Pb) C33200 (66Cu-32.4Zn-1.6Pb) C36000 (61.5Cu-35.5Zn-3Pb) C46400, C46500. C466OO. C46700 (6OCu-39.2Zn-0.8Sn) C46400. C46500. C466OO, C46700 (6OCu-39.2Zn-0.8Sn) C37700 (6OCu-38Zn-2Pb) C65500 (97Cu-3Si) C51000 (94.8Cu-5Sn-O.2P) CI7200. C 17300 C65500 (97Cu-3Si) C1l3OO. Cll400. C1l5OO, C1l600 (99.96Cu+Ag-OAO) C26800. C27000 (65Cu-35Zn) C26800.C27000(65Cu-35Zn) C51000 (94.8Cu-5Sn-O.2P) CI72oo. C 17300 C93700 (80Cu-IOSn-IOPb)
246 246 246 265 257 257 268 255 255 251 251 257 257 257 260 261 4Z4 431 423 424 425 431 429 423 427 430 430 429 439 444 433 433 433 452 448 438 436 440 454 441 436 443 453 438 432 432 438 436 300 334 334 360 363 316 316 334 343 344 347 356 356 349 370 360 316 370 306 339 339 360 316 396
Cross Reference to Nonferrous Alloys I 659 Designation AMS 4860A 4862 4880 4890 4900J 490lL 4902E 4905A 4906 49070 49090 4910J 4911F 4914 4915C 4915F 4916E 49170 4918F 4919C 4919G 4920 4921F 49240 4926H 4928K 4930C 4931 4933A 4934A 4935E 4936B 4936C 4941C 4942C 49430 49440 4945 495 IE 495IEAMS4951 49530 49540 4955B 4956B 4957 4958 4959B 4965E 4966J 4967F 4970E 4971C 4972C 4973C 4975E 4975F 4976C 49760 4978B 4978C 4979B 4980B 4981B 4983A 4984 4985A 4986 4987 4991A 4993A 4995 4996
Alloy Name
Page
C86500 (58Cu-39Zn-1.3FeIAl-0.5Mn) C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C95500 (8ICu-4Fe-4Ni-I1AI) C82500 (97.2Cu-2Be-0.5Co-0.25Si) Unalloyed Titanium, ASTM Grade 3, UNS RS0550 Unalloyed Titanium. Grade 4. UNSRS0700 Unalloyed Titanium, ASTM G rade 2. UNS RS0400 Ti-6Al-4V Ti-6AI-4V Ti-6AI-4V Ti-5Al-2.5Sn Ti-5Al-2.5Sn Ti-6AI-4V Ti-15V-3Cr-3AI-3Sn Ti-8AI-IMo-1V Ti-8Al-IMo-IV Ti-8AI-IMo-1V Ti-13V-I1Cr-3AI Ti-6AI-6V-2Sn Ti-6AI-2Sn-4Zr-2Mo-0.08Si Ti-6Al-2Sn-4Zr-2Mo-0.08Si Ti-6AI-4V Unalloyed Titanium, Grade 4. UNSRS0700 Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-6AI-4V Ti-6AI-4V Ti-6AI-4V Ti-8AI-IMo-IV Ti-6AI-4V Ti-6AI-4V Ti-6AI-6V-2Sn Ti-6AI-6V-2Sn Unalloyed Titanium, ASTM Grade 2, UNS RS0400 Unalloyed Titanium, ASTM Grade 2. UNS RS0400 Ti-3AI-2.5V Ti-3AI-2.5V Ti-3AI-2.5V Unalloyed Titanium, ASTM Grade 3, UNS RS0550 Unalloyed Titanium, ASTM Grade I. UNS RS0250 TI-5AI-2.5Sn Ti-6AI-4V Ti-8AI-IMo-IV Ti-6Al-4V Ti-3AI-8V-6Cr-4Mo-4Zr (Beta C) TI-3AI-8V-6Cr-4Mo-4Zr (Beta C) TI-13V-I1Cr-3AI Ti-6AI-4V TI-5AI-2.5Sn Ti-6AI-4V TI-7Al-4Mo TI-6AI-6V-2Sn TI-8AI-IMo-IV Ti-BAI-IMo-IV TI-6Al-2Sn-4Zr-2Mo-0.08Si TI-6A1-2Sn-4Zr-2Mo-0.08Si Ti-6AI-2Sn-4Zr-2Mo-0.08Si TI-6AI-2Sn-4Zr-2Mo-0.08Si TI-6AI-6V-2Sn TI-6AI-6V-2Sn Ti-6AI-6V-2Sn Ti-l1.5Mo-6Zr-4.5Sn Ti-6AI-2Sn-4Zr-6Mo Ti-lOV-2Fe-3Al Ti-lOV-2Fe-3Al Ti-6Al-4V Ti-lOV-2Fe-3Al Ti-IOV-2Fe-3Al Ti-6AI-4V TI-6AI-4V TI-5AI-2Sn-2Zr-4Mo-4Cr TI-6AI-4V
390 390 399 386 471
Designation
Alloy Name
AMS 4997 4998 5662 5664 5667 Alclad 7178
Ti-5AI-2Sn-2Zr-4Mo-4Cr Ti-6AI-4V lnconel718 Inconel718 lnconel X 750 7178, Alclad 7178
514 522 41 41 30 239
H38.4 H38.12
469 522 522 522 483 483 522 577 498 498 498 572 536 492 492 522
ASME B209 B 210 B211 B 221 B234 B 241 B 345 B404 B 483 SBI1 SB12 SB43 SB96 SB98 SB98 SBlll SBI11 SBlll SBlll SBI11 SBII1 SBlll SBI48 SBI48
469
SBI50 SBI50 SBI52
469 478 478 478
SBI69 SBI69 SB17l
471
SB171
467 483 522 498 522 563 563 572 522 483 522 541 536 498 498 492 492 492 492 536 536 536 559 517 566 566 522 566 566 522 522 514 522
SB171 SB171 SB17l SB171 SB209 SB209 SB210 SB211 SB211 SB221 SB221 SB221 SB221 SB234 SB241 SB241 SB241 SB247 SB247 SB265 Grade 3 SB265 Ti Grade I SB265 Ti Grade 2 SB271 SB283 SB315 SB315 SB359 SB359
Designation ASME SB359 SB359 SB359 SB359 SB381 F-I SB381 F-2
ANSI
472
472 483 483 522 522 522 498 522 522 536 536
Page
2017 2017 1060 1060 1060 1060 1060 1060 1060 1060 1060 Cl1000 (99.95Cu-0.04O) Cl1000 (99.95Cu-0.04O) C23000 (85Cu-15Zn) C65500 (97Cu-3Si) C65100 (98.5Cu-1.5Si) C65500 (97Cu-3Si) C23000 (85Cu-15Zn) C28000 (60Cu-40Zn) C443OO, C444OO. C44500 (71Cu-28Zn-lSn) C60800 (95Cu-5AI) C70600 (9OCu-IONi) cnooo (80Cu-20Ni) C71500 (70Cu-30Ni) C95200 (88Cu-3Fe-9Al) C95400 (85Cu-4Fe-IIAI) and C95410 C61400 (9ICu-7AI-2Fe) C62300 (87Cu-IOAl-3Fe) C1l3OO. C114OO. C1l5OO. CI1600 (99.96Cu+Ag-0.40) C61000 (92Cu-8Al) C61400 (9ICu-7AI-2Fe) C365OO.C366OO.C367OO.C368OO (60Cu-39.4Zn-0.6Pb) C443oo, C444OO. C44500 (71Cu-28Zn-ISn) C464OO, C465OO, C466OO, C46700 (60Cu-39.2Zn-0.8Sn) C61400 (9ICu-7AI-2Fe) C70600 (90Cu-IONi) C71500 (70Cu-30Ni) 1100 3003, Alclad 3003 3003, Alclad 3003 2014, Alclad 2014 2024. Alclad 2024 1100 2024. Alclad 2024 3003. Alclad 3003 6063 3003. Alc1ad 3003 1100 3003. Alclad 3003 6063 2014, Alclad 2014 3003. Alclad 3003 Unalloyed TItanium. ASTM Grade 3, UNS RS0550 Unalloyed Titanium. ASTM Grade I, UNS RS0250 Unalloyed TItanium. ASTM Grade 2, UNS R50400 C95200 (88Cu-3Fe-9AI) C37700 (60Cu-38Zn-2Pb) C65100 (98.5Cu-1.5Si) C65500 (97Cu-3Si) C23000 (85Cu-15Zn) C443OO, C444OO. C44500 (71Cu-28Zn-ISn)
159 159 150 150 150 150 150 150 150 150 150 300 300 332 370 370 370 332 341
SB381 F-3 SB395 SB395 SB395 SB395 SB395 SB402 SB402 SB466 SB466 SB466 SB467 SB467 SB467 SB543 SB543 SB543 SB543 SB584
354 363 373 375 376 398
ASTM Bl BI Bl BI BI
399 365 367
B2 B2 B2 B2 B2
306 364 365 349
B3 B3 B3 B3
354 B4 356 365 373 376 151 180 180 155 159 151 159 180 206 180 151 180 206 155 180 471 467 469 398 349 370 370 332 354
B5 B8 B8 B8 B9 BI1 B B B B B
12 12 12 12 12
B 16 B 19 B21 B21 B 21 (CA482) B22 B22 B 26 B 30 B 30 B30 B30 B 30
Alloy Name
Page
C60800 (95Cu-5AI) C70600 (9OCu-IONi) cnooo (80Cu-20Ni) C71500 (70Cu-30Ni) Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 C23000 (85Cu-15Zn) C60800 (95Cu-5AI) C70600 (9OCu-IONi) cnooo (80Cu-20Ni) C71500 (70Cu-30Ni) C70600 (9OCu-IONi) C71500 (7OCu-30Ni) C70600 (9OCu-IONi) cnooo (80Cu-20Ni) C71500 (70Cu-30Ni) C70600 (9OCu-IONi) (8OCu-20Ni) C71500 (70Cu-30Ni) C19400 (Cu-2.35Fe-0.03P-0.12Zn) C443OO, C444OO, C44500 (71Cu-28Zn-ISn) C70600 (9OCu-IONi) C71500 (70Cu-30Ni) C97600 (64Cu-4Sn-4Pb-8Zn-20Ni)
363 373 375 376
cioioo and CI0200
295 298 300 306
cnooo
CI04OO, C105OO. CI0700 Cl1000 (99.95Cu-0.04O) cmoo (99.95Cu-0.04O-0.0ICd) Cll3OO, CI1400, C115OO. CI1600 (99.96Cu+Ag-o.40) cioioo and CI0200 CI04OO.CI0500,CI0700 Cl1000 (99.95Cu-0.040) cmoo (99.95Cu-0.04O-0.0ICd) Cll3OO, CI1400, cusoo, CI1600 (99.96Cu+Ag-0.40) ciotoo and CI0200 CI04OO,CI0500.CI0700 Cl1000 (99.95Cu-0.04O) CI13OO,CI1400. CI15OO,CI1600 (99.96Cu+Ag-o.40) C125OO, C127OO. CI28oo, C129OO. C13000 CI1000 (99.95Cu-0.04O) CI1000 (99.95Cu-0.04O) cnioo (99.95Cu-0.04O-0.0ICd) Cll3OO, Cl1400. C1l5OO, C1l6OO (99.96Cu+Ag-0.40) CI6200 (99Cu-ICd) C125OO, C127OO. C128OO. C129OO. C13000 crotoo and CI0200 CI0300 CI04OO,CI0500.CI0700 CI0800 C125OO, CI27oo. C128OO. CI2900. C13000 C36000 (61.5Cu-35.5Zn-3Pb) C26000(70Cu-30Zn) C46400. C465OO. C466OO. C46700 (60Cu-39.2Zn-0.8Sn) C48200 (60.5Cu-38Zn-0.8Sn-0.7Pb) C48500 (6OCu-37.5Zn-1.8Pb-0.7Sn) C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C93700 (80Cu-IOSn-IOPb) C268oo. C27000 (65Cu-35Zn) C861OO. C86200 (64Cu-24Zn-3Fe-5AI-4Mn) C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C86400 (59Cu-0.75Sn-0.75Pb37Zn-I.25Fe-0.75Al-0.5Mn) C86500 (58Cu-39Zn-1.3FelAI-0.5Mn) C86700
467 469 471 332 363 373 375 376 373 376 373 375 376 373 375 376 326 354 373 376 401
306 295 298 300 306 306 295 298 300 306 308 300 300 306 306 314 308 295 298 298 300 308 347 334 356 358 359 390 396 339 389 390 390 390 391
660 I Cross Reference to Nonferrous Alloys Designation
Alloy Name
Page
ASTM 830 830 830 830 830 830 830 830 830 830 830 830 830 830 830 830 830 830 B30 B30 B30 830 B30 B30 B30 B 33 833 836 B36 B 36 836 836 B42 B42 842 B42 B 43 B 47 B47 B47 B47 B48 B48 B48 B 48 B49 B49 B49 B49 B49 861 B66 B 68 868 B68 B75 875 B75 B80 B80 B80 B 80 B 80 880 880 880 880 B 80 B 80 880 B80 B80 880 880
C87300 (formerly csno» C87600 C87610 C875OO, C87800 (82Cu-4Si-14Zn) C87900 C92200 (88Cu-6Sn-l.5Pb-4.5Zn) C92300 (87Cu-8Sn-IPb-4Zn) C92500 (87Cu-IISn-1 Pb-lNi) C92700 (88Cu-l0Sn-2Pb) C92900 (84Cu-lOSn-2.5Pb-3.5Ni) C93200 (83Cu-7Sn-7Pb-3Zn) C93400 C93500 (85Cu-5Sn-9Pb-IZn) C93700 (80Cu-l0Sn-IOPb) C93800 (78Cu-7Sn-15Pb) C95200 (88Cu-3Fe-9AI) C95300 (89Cu-lFe-l0Al) C95400 (85Cu-4Fe-IIAI) and C95410 C95500 (81Cu-4Fe-4Ni-llAI) C95600 (91Cu-2Si-7AI) C95700 (75Cu-3Fe-8AI-2Ni-12Mn) C95800 (82Cu-4Fe-9A1-4Ni-lMn) C97300 (56Cu-2Sn-IOPb-20Zn12Ni) C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) C97800 (66.5Cu-5Sn-1.5Pb-2Zn25Ni) cioioo and CI0200 cnooo (99.95Cu-0.04O) C21000 (95Cu-5Zn) C22000 (9OCu-IOZn) C23000 (85Cu-15Zn) C24000 (80Cu-20Zn) C26000 (70Cu-30Zn) cioioo and CI0200 CI0300 CI0400.CI0500.CI0700 CI0800 C23000 (85Cu-15Zn) cunoo and CI0200 cnoeo (99.95Cu-0.04O) cmeo(99.95Cu-0.04O-0.0ICd) CII3oo, C1l4OO. C1l5OO. C1l6OO (99.96Cu+Ag-0.40) CI0100 and CI0200 CI0400,CI0500.CI0700 cneoo (99.95Cu-0.04O) CII3oo, C1I4OO.C1I5OO,CII600 (99.96Cu+Ag-0.40) cioroo and CI0200 CI0400.CI0500,CI0700 cueoo (99.95Cu-0.04O) ciuoo (99.95Cu-0.04O-0.01Cd) C1l3OO, C1I4OO.C1I5OO,C11600 (99.96Cu+Ag-0.40) C92200 (88Cu-6Sn-l.5Pb-4.5Zn) C93800 (78Cu-7Sn-15Pb) ClOloo and CI0200 CI0300 CI0800 croioo and CI0200 CI0300 CI0800 AMlOOA AZ63A AZ81A AZ91A.AZ91B,AZ9IC, AZ9ID. AZ91E AZ92A EQ21 EZ33A HK31A HZ32A QE22A WE43 WE54 ZC63 ZFAIA ZH62A ZK51A
392 392 392 393 393 393 394 394 395 395 395 396 396 396 397 398 398 399 399 399 400 400 401 401 401 295 300 328 330 332 334 334 295 298 298 300 332 295 300 306 306 295 298 300 306 295 298 300 306 306 393 397 295 298 300 295 298 300 432 433 435 436 438 439 440 441 443
444 447 448 450 450 453 454
Designation ASTM 880 886 886 886 886 888 888 888 890 B90 B90 B 91 B 91 891 B91 891 893 893 B93 B 93 B 93 B 93 B94 B96 B97 B97 B98 B98 899 B99 B 100 B 100 B 100 BIOI B 103 B 103 B 103 B 103 B 103 B 105 B 105 B 105 B 107 B 107 B 107 B 107 B 107 B11I 8 III Bill B11I Bill 8111 BIll B11I B11I 8111 Bill Bill B 113 B 116 B 116 8116 8116 B 121 B 121 B 121 B 121 B 121 B 122 8122 B 122 B 122 8122 B 122
Alloy Name
ZK61A AC41A; Zn-4AI-1Cu-0.05Mg AC43A; Zn-4AI-2.5Cu-0.04Mg AG4OA; Zn-4AI-0.04Mg AG4OB;Zn-4AI-0.015Mg croioo and CI0200 CI0300 CI0800 AZ3IB.AZ31C HK31A HM21A AZ3IB.AZ31C AZ61A AZSOA HM21A ZK60A AMlOOA AZ63A AZ81A AZ91A, AZ91B. AZ91C, AZ9ID.AZ91E AZ92A WFA3 AZ91A. AZ9IB. AZ91C, AZ9ID. AZ91E C65500 (97Cu-3Si) C65100 (98.5Cu-1.5Si) C65500 (97Cu-3Si) C65100 (98.5Cu-1.5Si) C65500 (97Cu-3Si) C65100 (98.5Cu-l.5Si) C65500 (97Cu-3Si) C51000 (94.8Cu-5Sn-0.2P) C51100 (95.6Cu-4.2Sn-0.2P) C65500 (97CU-3Si) cnooe (99.95Cu-0.04O) C51000 (94.8Cu-5Sn-0.2P) C51100 (95.6Cu-4.2Sn-0.2P) C52100 (92Cu-8Sn) C52400 (9OCu-IOSn) C54400 (88Cu-4Pb-4Sn-4Zn) C16200 (99Cu-lCd) C41100 (91Cu-8.5Zn-0.5Sn) C50500 (98.7Cu-1.3Sn) AZ3IB,AZ3IC AZ6IA AZSOA ZC71 ZK60A ctoioo and CI0200 CI0300 CI0800 C19200 (98.97Cu-1.0Fe-0.03P) C23000 (85Cu-15Zn) C28000 (6OCu-4OZn) C443OO. C44400. C44500 (71Cu-28Zn-lSn) C60800 (95Cu-5AI) C70400 (92.4Cu-5.5Ni-1.5Fe0.6Mn) C70600 (9OCu-10Ni) C71000 (8OCu-20Ni) C71500 (70Cu-30Ni) CI0800 cioioo and CI0200 cueoo (99.95Cu-0.040) C11I00 (99.95Cu-0.040-0.01Cd) Cl13OO. C1l4OO, C1l5OO, CII600 (99.96Cu+Ag-0.40) C33500 (65Ca-34.5Zn-0.5Pb) C34000 (65Cu-34Zn-IPb) C34200 (62Cu-36.2Zn-2Pb), C35300 (62Cu-36.2Zn-1.8Pb) C35000 (65.5Cu-36.4Zn-l.IPb) C35600 (62Cu-35.5Zn-2.5Pb) C70600 (90Cu-l0Ni) C71000 (80Cu-20Ni) C71500 (70Cu-30Ni) C74500 (65Cu-25Zn-lONi) C75200 (65Cu-18Ni-17Zn) C77000 (55Cu-27Zn-18Ni)
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456 616 615 615 616 295 298 300 423 427 429 423 424 425 429 431 432 433 435 436 438 447 436 370 370 370 370 370 370 370 360 361 370 300 360 361 361 362 363 314 351 359 423 424 425 431 431 295 298 300 325 332 341 354 363 373 373 375 376 300 295 300 306 306 344 345 345 347 347 373 375 376 378 379 381
Designation
Alloy Name
ASTM 8124 8124 B 124
cioioo and CI0200 cuooo (99.95Cu-0.04O)
8124 8124 B 124 8124 8124 8124 B 129 8130 Bl3l B 133 B 133 B 133 B 133 B 133 B 133 B 133 B 134 B 134 B 134 B 134 B 134 B 134 B 135 B 135 B 135 B 135 B 135 B 135 B 135 B 135 B 139 B 139 B 139 B 139 B 140 B 140 B 148 B 148 B 148 B 148 B 148 B 148 B 148 B 150 B 150 B 151 B 151 B 151 B 151 B 151 B 151 B 152 B 152 B 152 B 152 B 152 B 152 B 152 B 157 B 159 B 159 B 159 B 159 B 169 B 169 B 169 BI71 BI71 B 171
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C125OO. C127OO, C128OO, C12900, C13000 C14500 (99.5Cu-0.Te) C37700 (6OCu-38Zn-2Pb) C46400. C465oo, C466OO, C46700 (6OCu-39.2Zn-0.8Sn) C48200 (6O.5Cu-38Zn-0.8Sn-0.7Pb) C48500 (6OCu-37.5Zn-1.8Pb-0.7Sn) C65500 (97Cu-3Si) C26000 (70Cu-30Zn) C22000 (9OCu-10Zn) C22000 (9OCu-IOZn) CI0100 and CI0200 CI0300 CI0400,CI0500.CI0700 CI0800 cuooo (99.95Cu-0.04O) Cll100 (99.95Cu-0.04O-O.0ICd) CI25oo.CI27oo.CI28oo. C12900, C13000 C21000 (95Cu-5Zn) C22000 (9OCu-10Zn) C23000 (85Cu-15Zn) C24000 (80Cu-20Zn) C26000 (70Cu-30Zn) C268oo.C27ooo(65Cu-35Zn) C22000 (9OCu-IOZn) C23000 (85Cu-15Zn) C26000 (70Cu-30Zn) C268oo.C27ooo(65Cu-35Zn) C28000 (6OCu-40Zn) C33000 (66Cu-33.5Zn-0.5Pb) C33200 (66Cu-32.4Zn-1.6Pb) C37000 (6OCu-39Zn-IPb) C51000 (94.8Cu-5Sn-0.2P) C52100 (92Cu-8Sn) C52400 (9OCu-IOSn) C54400 (88Cu-4Pb-4Sn-4Zn) C31400 (89Cu-9.IZn-1.9Pb) C31600 (89Cu-8.1Zn-l.9Pb-INi) C95200 (88Cu-3Fe-9Al) C95300 (89Cu-lFe-l0A I) C95400 (85Cu-4Fe-llAI) and C95410 C95500 (81Cu-4Fe-4Ni-IIAI) C95600 (9ICu-2Si-7AI) C95700 (75Cu-3Fe-8AI-2Ni-12Mn) C95800 (82Cu-4Fe-9AI-4Ni-IMn) C61400 (91Cu-7AI-2Fe) C62300 (87Cu-IOAI-3Fe) C70600 (9OCu-IONi) C71500 (70Cu-30Ni) C74500 (65Cu-25Zn-IONi) C75200 (65Cu-18Ni-17Zn) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) CI0100 and CI0200 CI0300 CI04oo. CI05oo, CI0700 CI0800 cneoo (99.95Cu-O.04O) Cl13OO. C114OO. C1l5OO. CII600 (99.96Cu+Ag-O.40) C125OO. C127OO. C128OO. CI2900. CI3000 CI0300 cmoo(99.95Cu-0.04O-0.0ICd) C51000 (94.8Cu-5Sn-O.2P) C52100 (92Cu-8Sn) C52400 (9OCu-10Sn) C60600 (95Cu-5AI) C61000 (92Cu-8AI) C61400 (91Cu-7A1-2Fe) C365oo.C36600,C367oo.C368oo (60Cu-39.4Zn-0.6Pb) C443OO. C44400, C44500 (71Cu-28Zn-lSn) C46400. C465OO. C466OO, C46700 (60Cu-39.2Zn-0.8Sn)
295 300 308 309 349 356 358 359 370 334 330 330 295 298 298 300 300 306 308 328 330 332 334 334 339 330 332 334 339 341 343 344 349 360 361 362 363 343 343 398 398 399 399 399 400 400 365 367 373 376 378 379 381 381 295 298 298 300 300 306 308 298 306 360 361 362 363 364 365 349 354 356
Cross Reference to Nonferrous Alloys /661 Designation
ASTM B 171 B 171 B 171 B 172 B 172 B 172 B 173 B 173 B 173 B 174 B 174 B 176 B 176 B 176 B 176 B 187 B 187 B 187 B 187 B 187 B 187 B 188 B 188 B 188 B 188 B 188 B 188 B 189 B 189 B 189 B 194 B 194 B 196 B 196 B 197 B 199 B 199 B 199 B 199 B 199 B 199 B 199 B 199 B 199 B 199 B 199 B206 B206 B206 B206 B206 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209 B209
Alloy Name
C61400 (91Cu-7AI-2Fe) C70600 (90Cu-l0Ni) C71500 (70Cu-30Ni) C11000 (99.95Cu-0.040) C11100 (99.95Cu-0.Q4(}.0.01Cd) CI1300, C114OO. C11500. C11600 (99.96Cu+Ag-0.4O) Cll000 (99.95Cu-0.04O) Cl1100 (99.95Cu'0.04O-0.0ICd) CI1300. C114OO. C11500. Cl1600 (99.96Cu+Ag-0.40) CIIOOO (99.95Cu-0.040) C11100 (99.95Cu-0.04O-0.0ICd) C86800 C87500, C87800 (82Cu-4Si-14Zn) C87900 C99750 C10100 and C10200 C10300 CI0400,CI0500,CI0700 C10800 Cll000 (99.95Cu-0.04O) C11300, C1I4OO,C11500. CI1600 (99.96Cu+Ag-0.4O) C10100 and C10200 CI0300 CI0400. C10500, C10700 C10800 C11000 (99.95Cu-0.040) C11300. C114OO. C11500, C11600 (99.96Cu+Ag-0.40) C10100 and CI0200 C11000 (99.95Cu-0.04O) C11300, C114OO. C11500, C11600 (99.96Cu+Ag-0.4O) C17000 (98Cu-1.7Be-0.3Co) CI7200. C 17300 C17000 (98Cu-1.7Be-0.3Co) CI7200. C17300 CI7200, C17300 AMl00A AZ81A AZ91A,AZ91B.AZ91C, AZ9ID, AZ91E AZ92A EQ21 EZ33A "lOlA QE22A WE43 WE54 ZC63 C71000 (80Cu-20Ni) C74500 (65Cu-25Zn-lONi) C75200 (65Cu-18Ni-17Zn) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) 1100 2014, Alclad 2014 2024, Alclad 2024 2124 2219. Alclad 2219 3003, Alclad 3003 3004. A1c1ad 3004 3105 5005 5050 5052 5083 5086. Alclad 5086 5154 5252 5254 5454 5456 5457 5652 5657 6061, Alclad 6061 7072 7075, Alclad 7075
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365 373 376 300 306 306 300 306 306 300 306 391 393 393 402 295 298 298 300 300 306 295 298 298 300 300 306 295 300 306 314 316 314 316 316 432 435 436 438 439
440 441
444 447 448 450 375 378 379 381 381 151 155 159 171 174 180 182 184 185 186 187 189 191 191 193 193 194 195 197 198 198 201 221 221
Designation
ASTM B209 B 210 B210 B210 B 210 B210 B210 B 210 B 210 B 210 B 210 B210 B210 B210 B210 B211 B211 B211 B211 B211 B211 B211 B211 B211 B 211 B211 B 211 B211 B216 B 221 B221 B221 B221 B221 B221 B 221 B 221 B221 B 221 B221 B221 B 221 B 221 B221 B221 B 221 B221 B221 B 221 B221 B 221 B224 B226 B226 B226 B228 B228 B229 B229 B229 B230 B 231 B232 B234 B234 B234 B234 B236 B240 B240 B240 B240 B241 B241 B241 B 241 B241
Alloy Name
7178. Alclad 7178 1100 2011 2014. Alclad 2014 2024. Alclad 2024 3003. Alclad 3003 5050 5052 5083 5154 5456 6061, Alclad 6061 6063 6262 7075. Alclad 7075 1100 2011 2014,Alclad2014 2017 2024. Alclad 2024 2219. Alclad 2219 3003. Alclad 3003 5052 5056. Alclad 5056 5154 6061, Alclad 6061 6262 7075. Alclad 7075 CI2500. CI2700. C12800, CI2900. C13000 1100 2014. Alclad 2014 2024, Alclad 2024 2219. Alclad 2219 3003, Alclad 3003 3004, Alclad 3004 5052 5083 5086. Alclad 5086 5154 5454 5456 6005 6061, Alclad 6061 6063 6066 6262 6351 6463 7005 7075, Alclad 7075 7178, A1c1ad 7178 C11000 (99.95Cu-0.04O) C11000 (99.95Cu-0.04O) C11100 (99.95Cu-0.04O-0.01Cd) CI1300. C11400, CI1500. C11600 (99.96Cu+Ag-0.4O) C11100 (99.95Cu-0.04O-0.01Cd) CI1300. C11400, C11500. C11600 (99.96Cu+Ag-0.4O) CI1000 (99.95Cu-0.04O) C11100 (99.95Cu-0.04O-0.01Cd) CI1300. C11400, C11500, C11600 (99.96Cu+Ag-0.4O) 1350 1350 1350 3003.Alclad3003 5052 5454 6061. Alclad 6061 1350 AC41A; Zn-4AI-lCu-0.05Mg AC43A; Zn-4AI-2.5Cu-0.04Mg AG4OA; Zn-4AI-0.04Mg AG40B; Zn-4AI-0.015Mg 1100 2014. Alclad 2014 2024. Alclad 2024 2219. Alclad 2219 3003. Alclad 3003
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239 151 155 155 159 180 186 187 189 191 195 201 206 212 221 151 155 155 159 159 174 180 187 188 191 201 212 221 308 151 155 159 174 180 182 187 189 191 191 194 195 200 201 206 208 212 213 214 214 221 239 300 300 306 306 306 306 300 306 306 154 154 154 180 187 194 201 154 616 615 615 616 151 155 159 174 180
Designation
ASTM B 241 B 241 B 241 B241 B 241 B 241 B241 B241 B 241 B241 B 241 B 245 B246 B246 B246 B246
Alloy Name
Page
5052 5083 5086. Alclad 5086 5254 5454 5456 5652 6061. Alclad 6061 6063 7075. Alclad 7075 7178. Alclad 7178 5083 C10100 and CI0200 C11000 (99.95Cu-0.04O) C11100 (99.95Cu-0.04O-Q.OICd) C11300. C114OO. C11500. C11600 (99.96Cu+Ag-0.40) B247 1100 B 247 2014. Alclad 2014 B247 2219. Alclad 2219 B 247 2618 B 247 3003. Alclad 3003 B247 4032 B 247 5083 B247 6061. Alclad 6061 B 247 7075, Alclad 7075 C11000 (99.95Cu-0.04O) B248 C11000 (99.95Cu-0.04O) B249 B250 CI1000 (99.95Cu-0.04O) B 251 C10300 B 251 C10800 B 265 Grade 3 Unalloyed Titanium, Grade 3. UNSRS0550 B 265 Grade 4 Unalloyed Titanium. Grade 4. UNSRS0700 B 265 Grade 5 TI-6A1-4V B 265 Grade 6 TI-5A1-2.5Sn B 265 Grade 7 Modified Ti (Ti-Q.2Pd), Grade 7. UNS R524OO; Grade 11. UNSR52250 B 265 Grade 10 TI-11.5Mo-6Zr-4.5Sn B 265 Grade 11 Modified Ti (Ti-Q.2Pd). Grade 7. UNS R524OO; Grade 11. UNSRS2250 B 265 Grade 12 TI-0.3Mo-O.8Ni. Grade 12. R53400 B 265 Ti Grade 2 Unalloyed Titanium. Grade 2, UNSR50400 B 265-79 TI-3AI-2.5V B 265-79 Ti Grade 1 Unalloyed Titanium, ASTM Grade 1. UNS R50250 B271 C86100. C86200 (64Cu-24Zn-3Fe-5A1-4Mn) B271 C86300 (64Cu-26Zn-3Fe-3AI-4Mn) B271 C86400 (59Cu-0.75Sn-0.75Pb37Zn-l.25Fe-0.75Al-0.5Mn) B271 C86500 (58Cu-39Zn-1.3Fe-1 A1-0.5Mn) B 271 C86700 B271 C87300 (formerly C87200) B271 C87500. C87800 (82Cu-4Si-14Zn) B271 C92200 (88Cu-6Sn-1.5Pb-4.5Zn) B271 C92300 (87Cu-8Sn-lPb-4Zn) B271 C93200 (83Cu-7Sn-7Pb-3Zn) B271 C93500 (85Cu-5Sn-9Pb-lZn) B271 C93700 (80Cu-l0Sn-l0Pb) B271 C93800 (78Cu-7Sn-15Pb) B271 C95200 (88Cu-3Fe-9AI) B 271 C95300 (89Cu-lFe-IOAI) B 271 C95400 (85Cu-4Fe-IIAl) and C95410 B 271 C95500 (81Cu-4Fe-4Ni-11AI) B 271 C95800 (82Cu-4Fe-9AI-4Ni-IMn) B 271 C97300 (56Cu-2Sn-l0Pb-20Zn12Ni) B 271 C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) B271 C97800 (66.5Cu-5Sn-l.5Pb-2Zn25Ni) B 272 CI0l00 lind CI0200 B272 CI0300 B272 CI0400. CI0500. CI0700 B 272 C11000 (99.95Cu-0.04O)
187 189 191 193 194 195 198 201 206 221 239 189 295 300 306 306 151 155 174 179 180 184 189 201 221 300 300 300 298 300 471 472 522 483
474 559
474 476 469 478 467 389 390 390 390 391 392 393 393 394 395 396 396 397 398 398 399 399 400 401 401 401 295 298 298 300
662/ Cross Reference to Nonferrous Alloys Designation ASTM B272 B 272 B280 B280 B280 B283 B283 B283 B 283 B 283 B283 B 283 (CA485) B286 B 286 B286 B286 B298 B298 B298 B298 B301 B 301 B 301 B 302 B 302 B306 B 306 B 313 B 313 B313 B 313 B 313 B 313 B 313 B 313 B 315 B 315 B 316 B 316 B 316 B 316 B 316 B 316 B 316 B 316 B 316 B316 B 317 B 324 B 334 B 334 B 337 Grade 3 B 337 Grade 7
B 337 Grade 9 B 337 Grade 10 B 337 Grade 11
B 337 Grade 12 B 337 Ti Grade 2 B 337-87Ti Grade 1 B 338 Grade 3 B 338 Grade 7
B 338 Grade 9 B 338 Grade 10
Alloy Name
Page
C11300, CII400, C11500, C11600 (99.96Cu+Ag-0.40) C12500, C12700, C12800, C12900, C13000 C10100 and C10200 CI0300 CI0800 cueoo (99.95Cu-0.04O) C14500 (99.5Cu-0.Te) C37700 (60Cu-38Zn-2Pb) C46400,C46500,C46600,C46700 (60Cu-39.2Zn-0.8Sn) C62300 (87Cu-IOAI-3Fe) C65500 (97Cu-3Si) C48500 (6OCu-37.5Zn-1.8Pb-0.7Sn) CIOIOOand CI0200 cueoo (99.95Cu-0.040) Clll00 (99.95Cu-0.04O-0.0ICd) CII300, Cl1400, C11500, C11600 (99.96Cu+Ag-0.40) CIOIOOand CI0200 cnoeo (99.95Cu-0.040) ClllOO (99.95Cu-0.040-0.01 Cd) C11300, Cl1400, C11500, C11600 (99.96Cu+Ag-0.40) C14500 (99.5Cu-O.Te) C14700 (99.6Cu-0.45) C18700 (99Cu-lPb) C10300 C10800 C10300 C10800 !lOO 3003, Alclad 3003 3004, AIc1ad3004 5050 5052 5086, Alc1ad 5086 5154 6061, Alclad 6061 C65100 (98.5Cu-1.5Si) C65500 (97Cu-3Si) 1100 2017 2024, Alclad 2024 3003, Alclad 3003 5005 5052 5056, Alclad 5056 6061, Alc1ad 6061 7075, Alclad 7075 7178, Alclad 7178 6101 1350 cmoo (99.95Cu-0.040-0.01Cd) Cll300, Cll400, C115OO, CII600 (99.96Cu+Ag-0.40) Unalloyed Titanium, ASTM G rade 3, UNS RS0550 Modified Ti (Ti-0.2Pd), Grade 7, UNS R524oo; Grade ll, UNSR52250 Ti-3AI-2.5V Ti-II.5Mo-6Zr-4.5Sn Modified Ti (Ti-0.2Pd), Grade 7, UNS R524oo; Grade ll, UNSR52250 Ti-0.3Mo-0.8Ni, ASTM Grade 12, R53400 Unalloyed Titanium, ASTM Grade 2, UNS RS0400 Unalloyed Titanium, ASTM Grade I, UNS RS0250 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Modified Ti (Ti-0.2Pd), Grade 7, UNS RS24oo; Grade 11, UNSR52250 Ti-3AI-2.5V Ti-11.5Mo-6Zr-4.5Sn
Designation
Alloy Name
Page
ASTM B 381 Grade F-7
ASTM B 338 Grade 11 306 308 295 298 300 300 309 349 356 367 370 359 295 300 306 306 295 300 306 306 309 309 325 298 300 298 300 151 180 182 186 187 191 191 201 370 370 151 159 159 180 185 187 188 201 221 239 209 154 306 306 471
474 478 559
474 476 469 467 471
474 478 559
Modified Ti (TI-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Ti-0.3Mo-0.8Ni, ASTM B 338 Grade 12 Grade 12, RS3400 Unalloyed Titanium, ASTM B 338 Ti Grade 2 Grade 2, UNS R50400 Unalloyed Titanium, ASTM B 338-87Ti Grade I, UNS R50250 Grade 1 3003, AIc1ad3003 B 345 5086, AIc1ad5086 B 345 6061, AIc1ad6061 B 345 6063 B 345 6070 B345 6351 B345 Unalloyed Titanium, ASTM B 348 Grade 3 Grade 3, UNS RS0550 Unalloyed Titanium, Grade 4, B 348 Grade 4 UNSRS0700 Ti-6AI-4V B 348 Grade 5 Ti-5AI-2.5Sn B 348 Grade 6 Modified Ti (Ti-0.2Pd), Grade 7, B 348 Grade 7 UNS RS2400; Grade II, UNSR52250 Ti-3AI-2.5V B 348 Grade 9 Modified Ti (TI-0.2Pd), Grade 7, B 348 Grade 11 UNS R52400; Grade 11, UNS RS2250 Ti-0.3Mo-0.8Ni, ASTM B 348 Grade 12 Grade 12, RS3400 Unalloyed Titanium, ASTM B 348 Ti Grade 2 Grade 2, UNS R50400 Ti-I1.5Mo-6Zr-4.5Sn B 348(10)-87 B 348-87 Ti Grade I Unalloyed Titanium, ASTM Grade I, UNS RS0250 CI0100 and C10200 B 355 cuooo (99.95Cu-0.04O) B 355 C11100 (99.95Cu-0.04O-0.01Cd) B355 C11300, Cl1400, CII500, C11600 B355 (99.96Cu+Ag-O.40) CI0800 B357 C10100 and CI0200 B 359 CI0300 B359 C19200 (98.97Cu-1.0Fe-0.03P) B 359 C23000 (85Cu-15Zn) B 359 C44300, C44400, C44500 B 359 (71Cu-28Zn-ISn) C60800 (95Cu-5AI) B 359 C70400 (92.4Cu-5.5Ni-1.5FeB 359 0.6Mn) C70600 (9OCu-IONi) B 359 cnooo (80Cu-20Ni) B359 C71500 (70Cu-30Ni) B359 C10800 B 360 B 367 Grade C-2 Unalloyed Titanium, Grade 4, UNSRS0700 Unalloyed Titanium, Grade 4, B 367 Grade C-3 UNSR50700 Ti-6AI-4V B 367 Grade C-5 Ti-5AI-2.5Sn B 367 Grade C-6 Modified Ti (Ti-0.2Pd), B 367 Grade 7, UNS RS2400; Grade Ti-Pd 7B Grade 11, UNS RS2250 Unalloyed Titanium, ASTM B 367-87 C-3 Grade 3, UNS R50550 Unalloyed Titanium, ASTM B 367-87Ti Grade 2, UNS R50400 Grade 2 cioioo and CI0200 B 370 cnooo (99.95Cu-0.04O) B 370 B 371 (CA694) C69400 (81.5Cu-14.5Zn-4Si) cioioo and C10200 B 372 C10300 B 372 B 372 CI0800 C22000 (90Cu-l0Zn) B 372 1145 B 373 Unalloyed Titanium, ASTM B 381 Grade F-3 Grade 3, UNS R50550 B 381 Grade F-4 Unalloyed Titanium, Grade 4, UNSR50700 Ti-6AI-4V B 381 Grade F-5 Ti-5AI-2.5Sn B 381 Grade F-6
Designation
474 476 469 467 180 191 201 206 208 213 471 472 522 483
474 478
474 476 469 559 467 295 300 306 306 300 295 298 325 332 354 363 373 373 375 376 300 472 472 522 483
474 471 469 295 300 372 295 298 300 330 153 471 472 522 483
Alloy Name
Page
Modified Ti (11-0.2Pd), Grade 7, UNS RS2400; Grade II, UNSRS2250 474 B 381 Grade F-9 TI-3AI-2.5V 478 B 381 Grade F-II Modified Ti (Ti-O.2Pd),Grade 7, UNS RS2400; Grade 11, UNSRS2250 474 B 381 Grade F-12 TI-0.3Mo-O.8Ni, ASTM Grade 12, RS3400 476 B 381 Ti Grade F-2 Unalloyed Titanium, AStM Grade 2, UNSR50400 469 Unalloyed Titanium, ASTM Grade I, B 381-87 F-l UNSRS0250 467 CI0l00 and CI0200 295 B 395 298 B 395 CI0300 C10800 300 B 395 C19200 (98.97Cu-I.OFe-o.o3P) 325 B 395 C23000 (85Cu-15Zn) 332 B 395 C44300, C44400, C44500 B 395 (?lCu-28Zn-ISn) 354 C60800 (95Cu-5Al) 363 B 395 C70400 (92.4Cu-5.5Ni-1.5Fe-0.6Mn)373 B395 C70600 (9OCu-10Ni) 373 B 395 C71000 (80Cu-20Ni) 375 B 395 C71500 (70Cu-30Ni) 376 B 395 185 5005 B 396 185 B 397 5005 211 6201 B 398 211 6201 B399 154 B400 1350 154 1350 B401 C70600 (9OCu-10Ni) 373 B 402 C71500 (70Cu-30Ni) 376 B402 432 AMlOOA B403 435 AZSIA B403 AZ91A,AZ91B,AZ91C, B403 AZ9ID, AZ91E 436 438 AZ92A B403 439 EQ21 B403 440 EZ33A B403 441 HK31A B403 QE22A 444 B403 448 WE54 B403 450 ZC63 B403 3003, Alclad 3003 180 B404 187 5052 B404 194 5454 B404 6061, Alclad 6061 201 B404 C92900 (84Cu-l0Sn-2.5Pb-3.5Ni) 395 B427 6061, Alclad 6061 WI B429 206 6063 B429 CI0100 and C10200 295 B432 298 CI0300 B 432 C10800 300 B 432 C365oo, C366OO, C367OO, B432 C36800 (60Cu-39.4Zn-O.6Pb) 349 C70600 (9OCu-10Ni) 373 B432 C17500 (97Cu-0.50Be-2.5Co) 321 B441 croroo and CI0200 295 B447 298 CI0300 B447 300 B447 CI0800 cneoo (99.95Cu-0.04O) 300 B447 cnooo (99.95Cu-0.04O) 300 B 451 C33500 (65Ca-34.5Zn-0.5Pb) 344 B453 C34000 (65Cu-34Zn-IPb) 345 B 453 C34200 (62Cu-36.2Zn-2Pb), B453 C35300 (62Cu-36.2Zn-1.8Pb) 345 C35000 (65.5Cu-36.4Zn-l.lPb) 347 B453 C35600 (62Cu-35.5Zn-2.5Pb) 347 B453 C38500 (57Cu-40Zn-3Pb) 350 B455 C19400 (Cu-2.35Fe-0.03P-0.12Zn) 326 B465 C70400 (92.4Cu-5.5NiB466 l.5Fe-0.6Mn) 373 C70600 (9OCu-10Ni) 373 B466 C71000 (8OCu-20Ni) 375 B466 C71500 (70Cu-30Ni) 376 B466 C70600 (9OCu-IONi) 373 B467 cnooo (80Cu-20Ni) 375 B467 C71500 (70Cu-30Ni) 376 B467 C19200 (98.97Cu-1.0Fe-0.03P) 325 B469 cnooo (99.95Cu-0.04O) 300 B470
Cross Reference to Nonferrous Alloys I 663 Designation ASTM B483 B483 B483 B483 B483 B483 B483 B483 B491 B491 B491 B491 B496 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B505 B506 B508 B 531 B534 B543 B543 B543 B543 B543 B544 B547 B547 B547 B547 B547 B547 B547 B547 B547 B549 B552 B552 B569 B570 B570 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584 B584
Alloy Name
Page
1100 3003, Alclad 3003 5005 5050 5052 6061, Alclad 6061 6063 6262 1050 1100 3003, Alclad 3003 6063 C11000 (99.95Cu-0.04O) C86100, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C92200 (88Cu-6Sn-1.5Pb-4.5Zn) C92300 (87Cu-8Sn-IPb4Zn) C92500 (87Cu-lISn-IPb-INi) C92700 (88Cu-IOSn-2Pb) C92900 (84Cu-lOSn-2.5Pb-3.5Ni) C93200 (83Cu-7Sn-7Pb-3Zn) C93400 C93500 (85Cu-5Sn-9Pb-IZn) C93700 (80Cu-IOSn-IOPb) C93800 (78Cu-7Sn-15Pb) C95200 (88Cu-3Fe-9AI) C95300 (89Cu-IFe-lOAl) C95400 (85Cu-4Fe-IIA1) and C95410 C95500 (8ICu-4Fe-4Ni-11AI) C95800 (82Cu-4Fe-9AI-4Ni-IMn) C11300, Cl1400, C1I500, C11600 (99.96Cu+Ag-0.4O) C41100 (9ICu-8.5Zn-0.5Sn) 5005 C17500 (97Cu.0.50Be-2.5Co) CI0800 C19400 (Cu-2.35Fe-Q.03P-0.12Zn) C44300, C44400, C44500 (71Cu-28Zn-ISn) C70400 (92ACu-5.5Ni1.5Fe-0.6Mn) C70600 (9OCu-lONi) 1350 1100 3003, Alclad 3003 3004, Alclad 3004 5050 5052 5083 5086, Alclad 5086 5154 5454 6061, Alclad 6061 C70600 (9OCu-IONi) C71500 (70Cu-30Ni) C26000 (70Cu-3OZn) C17000 (98Cu-1.7Be-0.3Co) CI7200, C 17300 C86100, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) C86300 (64Cu-26Zn-3Fe-3Al-4Mn) C86400 (59Cu-0.75Sn-Q.75Pb37Zn-I.25Fe-Q.75AI-0.5Mn) C86500 (58Cu-39Zn-I.3FeIAI·0.5Mn) C86700 C87500, C87800 (82Cu-4Si-14Zn) C87600 C92200 (88Cu-6Sn-I.5Pb-4.5Zn) C92300 (87Cu-8Sn-IPb4Zn) C93200 (83Cu-7Sn-7Pb-3Zn) C93500 (85Cu-5Sn-9Pb·IZn) C93700 (80Cu-IOSn-lOPb) C93800 (78Cu-7Sn-15Pb) C97300 (56Cu-2Sn-IOPb· 20Zn-12Ni) C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) C97800 (66.5Cu-5Sn-I.5Pb2Zn-25Ni)
151 180 185 186 187 201 206 212 149 151 180 206 300 389 390 393 394 394 395 395 395 396 396 396 397 398 398 399 399 400 306 351 185 321 300 326 354 373 373 154 151 180 182 186 187 189 191 191 194 201 373 376 334 314 316 389 390 390 390 391 393 392 393 394 395 396 396 397
Designation ASTM B585 B 586 B587 B587 B591 B591 B 591 B 591 B 591 B 591 B591 B592 B609 B632 B669 B669 B669 B763 B763 B763 B763 B 791 B 791 B791 B 808 B 951 B 1743 F9 F 136 F 467-84 Grade 4 F 467-84 Grade 5 F 467-84 Grade 7
F467-84 Ti Grade 2 F467-84a Ti Grade I F467M-84a Grade 7 F467M-84a TiGrade2 F467M-84b Ti Grade I F468-84 F 468-84 Grade 4 F 468-84 Grade 7
F468-84 TiGrade2 F468-84a TiGrade I F468M-84b Grade 7 F468M-84b Ti Grade I F468M-84b TiGrade2 F67 Grade 3
F67 Grade 4 F 67 Ti Grade 2 F 67-88 Ti Grade I
401 401 401
F68 SB209 SB210
Alloy Name
Page
C87300 (formerly C872(0) 392 C19400 (Cu-2.35Fe-0.03P-0.I2Zn) 326 C26000(70Cu-30Zn) 334 C26800, C27000 (65Cu-35Zn) 339 C40500 (95Cu-4Zn-ISn) 351 C40800 (95Cu-2Sn-3Zn) 351 351 C41100 (9ICu-8.5Zn-O.5Sn) C41500 (9ICu-7.2Zn-1.8Sn) 352 C42200 (87.5Cu-11AZn-I.1Sn) 353 C42500 (88.5Cu-9.5Zn-2Sn) 353 C43400 (85Cu-14.3Zn-0.7Sn) 354 C68800 (73.5Cu-22.7Zn-3AAI371 OACo) 154 1350 6061, Alclad 6061 201 617 ZA-8; Zn-8AI-ICu-0.02Mg ZA-12; Zn-11Al-ICu-0.025Mg 617 618 ZA-27; Zn-27AI-2Cu-0.015Mg 391 C86700 C87300 (formerly C872(0) 392 392 C87600 C95600 (9ICu-2Si-7AI) 399 617 ZA-8; Zn-8Al-ICu-0.02Mg 617 ZA-12; Zn-IIAI-I Cu-0.025Mg ZA-27; Zn-27AI-2Cu-0.015Mg 618 201 6061, Alclad 6061 354 C43000 (87Cu-1O.8Zn-2.2Sn) C11300, C11400, C1I500, C11600 306 (99.96Cu+Ag-0.4O) C18200, C18400, C18500 324 (99Cu-ICr) 522 Ti-6AI-4V Unalloyed Titanium, Grade 4, 472 UNSR50700 522 Ti-6AI-4V Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, 474 UNSR52250 Unalloyed Titanium, ASTM 469 Grade 2, UNS RS0400 Unalloyed Titanium, ASTM 467 Grade I, UNS R50250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, 474 UNSR52250 Unalloyed Titanium, ASTM 469 Grade 2, UNS RS0400 Unalloyed Titanium, ASTM 467 Grade I, UNS RS0250 522 Ti-6AI-4V Unalloyed Titanium, Grade 4, 472 UNSR50700 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, 474 UNSR52250 Unalloyed Titanium, ASTM Grade 2, 469 UNSR50400 Unalloyed Titanium, ASTM 467 Grade I, UNS RS0250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, 474 UNSR52250 Unalloyed Titanium, ASTM Grade I, 467 UNSRS0250 Unalloyed Titanium, ASTM Grade 2, UNSR50400 469 Unalloyed Titanium, ASTM Grade 3, UNSRS0550 471 Unalloyed Titanium, Grade 4, 472 UNSR50700 Unalloyed Titanium, ASTM Grade 2, UNS R50400 469 Unalloyed Titanium, ASTM Grade I, UNS R50250 467 ClOlOO and CI0200 295 1060 150 1060 150
Designation
Alloy Name
ASTM SB221 SB234 SB241
1060 1060 1060
150 150 150
Ti-3AI-8V-6Cr-4Mo-4Zr (Beta C)
563
Ti-6AI-2Sn-4Zr-6Mo Ti-13V-IICr-3Al
517 572
Astro Ti-3AI-8V6Cr-4Zr-4Mo Ti-6AI-2Sn4Zr-6Mo Ti-13V-11Cr-3AI AWS A5.l6-70 ERTi0.2PdGrade 7 A5.l6-70 ERTi-1 A5.16-70 ERTi-2 A5.l6-70 ERTi-3
Modified Ti (Ti-0.2Pd), UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade I, UNS R50250
A5.16-70 ERTi-3Al-2.5V Ti-3AI-2.5V A5.16-70 ERTi-3Al-2.5V-I Ti-3AI-2.5V A5.16-70 ERTi-4 Unalloyed Titanium, ASTM Grade 2, UNS R50400 A5.16-70 ERTi-5AI-2.5Sn Ti-5AI-2.5Sn A5.16-70 ERTi5AI-2.5Sn-1 Ti-5AI-2.5Sn A5.16-70 ERTi-6AI2Cb-ITa-IMo Ti-6AI-2Nb-1Ta-0.8Mo A5.16-70 ERTi6AI-4V Ti-6A14V A5.16-70 ERTi6AI-4V-I Ti-6AI4V A5.16-70 ERTi8AI-IMo-IV Ti-8Al-IMo-IV A5.l6-70 ERTi13V-11Cr-3Al Ti-13V-lI Cr-3Al Cabot Ti-3AI-2.5V
Page
474 467 467 467 478 478 469 483 483 488 522 522 498 572
Ti-3Al-2.5V
478
Ti-8AI-IMo-IV Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, Grade 4, UNSRS0700 Unalloyed Titanium, ASTM Grade 3, UNS R50550
498
478
Beta III
Ti-3AI-2.5V Modified Ti (Ti-Q.2Pd),Grade 7, UNS R52400; Grade 11, UNSR52250 Unalloyed Titanium, Grade 4, UNSRS0700 Ti-11.5Mo-6Zr4.5Sn
472 559
FormerAMS 4238A 4239
535.0, A535.0, B535.0 (7Mg) 535.0, A535.0, B535.0 (7Mg)
266 266
713.0 (7.5Zn-O.7Cu-0.35Mg) 413.0, A413.0 (12Si) 713.0 (7.5Zn-O.7Cu-0.35Mg) 295.0 (4.5Cu-l.ISi) 242.0 (4Cu-2Ni-2.5Mg) 201.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-Q.25Ti) 208.0 (4Cu-3Si) 514.0 (4Mg) 518.0 (8Mg) 520.0 (IOMg) 535.0, A535.0, B535.0 (7Mg)
267 263 267 250 249
Chase Ext. CDX 8Al-IMo-IV GR-I GR-2 GR-4 R-32 Crucible 3AI-2.5V A-4OPd
A-70
FormerASTM B26ZC81A B85 SI2A B108 ZC81B C4A CN42A CQ51A CS43A G4A G8A GlOA GM70B
467 469 472 471
474
244 248 264 265 265 266
664/ Cross Reference to Nonferrous Alloys Designation
Alloy Name
Page
FormerASTM S5A S5B S5C Sl2B SC51A SC5lB SC64A SC64D SC84A SC84B SC92A SC102A SC103A SC114A SG70A SG70B SG91A
sorcox
soiooa
SNI22A ZG61A ZG7lB
264 264 264 263 255 255 251 252 261 261 253 261 252 262 257 257 259 260 260 252 266 267
238.0 (l0.0%Cu-4.0%Si-0.3%Mg)
248
242.0 (4Cu-2Ni-2.5Mg) AZ63A 713.0 (7.5Zn-0.7Cu-0.35Mg) 332.0 (9.5%Si-3.0%Cu-1.0%Mg) 208.0 (4Cu-3Si) AZ92A AZ91A, AZ9lB, AZ91C, AZ9lD,AZ9lE AZ91A,AZ91B,AZ91C, AZ9lD,AZ9lE AMlooA AZ91A, AZ9lB, AZ91 C, AZ9lD,AZ9lE AZS1A EZ33A HK31A HK31A ZH62A ZK51A ZK61A AZ61A AZSOA ZK60A AZ61A
249 433 267 252 248 438
436 435 440 427 441 453 454 456 424 425 431 424
C92200 (88Cu-6Sn-l.5Pb-4.5Zn) lloo 2014, Alclad 2014 6061, Alclad 6061 6070 7075, Alclad 7075 354.0 (9Si-l.8Cu-0.5Mg) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 357.0, A357.0 (7Si-0.5Mg) 359.0 (9Si-0.6Mg) 2014, Alclad 2014 2219, Alclad 2219 2618 6061, Alclad 6061 6151 7075, Alclad 7075 5083 5456 5083 5456 5083 5456 6070 2219, Alclad 2219 2024, Alclad 2024 3003, Alclad 3003
393 151 155 201 208 221 253 255 259 259 155 174 179 201 209 221 189 195 189 195 189 195 208 174 159 180
FormerSAE 39 50 315 332 380 500 501 50lA 502 504 505 506 507 507 508 509 513 520 523 524 531
436 436 432
Government CA922 MIL-A-12545 MIL-A-12545 MIL-A-12545 MIL-A-12545 MIL-A-12545 MIL-A-21180 MIL-A-21180 MIL-A-21180 MIL-A-21180 MIL-A-22771 MIL-A-22771 MIL-A-22771 MIL-A-22771 MIL-A-22771 MIL-A-2277I MIL-A-45225 MIL-A-45225 MIL-A-46027 MIL-A-46027 MIL-A-46083 MIL-A-46083 MlL-A-461 04 MIL-A-46118 MIL-A-81596 MIL-A-81596
Alloy Name
Page
Government 443.0, A443.0, B443.0, C443.0 (5.2Si) 443.0, A443.0, B443.0, C443.0 (5.2Si) 443.0, A443.0, B443.0, C443.0 (5.2Si) 413.0, A413.0 (12Si) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 308.0 (5.5Si-4.5Cu) 319.0 (6Si-3.5Cu) 380.0, A380.0 (8.5Si-3.5Cu) 380.0, A380.0 (8.5SI-3.5Cu) 354.0 (9SI-I.8Cu-o.5Mg) 383.0 (1O.5Si-2.5Cu) 332.0 (9.5%SI-3.0%Cu-1.0%Mg) 384.0, A384.0 (l1.2Si-3.8Cu) 356.0, A356.0 (7Si-0.3Mg) 356.0, A356.0 (7Si-0.3Mg) 359.0 (9Si-0.6Mg) 360.0, A360.0 (9.5Si-0.5Mg) 360.0, A360.0 (9.5Si-0.5Mg) 336.0 (12Si-2.5Ni-1Mg-1Cu) 712.0 (5.8Zn-0.6Mg-0.5Cr-0.2Ti) 771.0 (7Zn-0.9Mg-O.l3Cr)
FormerCS 104A,138
Designation
MIL-A-815% MIL-A-815% MIL-B-11553B (Alloy 14) MIL-B-13501 MIL-B-13506 (AlloyA2) MIL-B-15345 MIL-B-15894 MIL-B-15894 (Class 3) MIL-B-16166 MIL-B-16261 (Alloy IV) MIL-B-16261 (Alloy VI) MIL-B-16541 MIL-B-18907 MIL-B-1923I MlL-B-19231 MIL-B-20292 MIL-B-24480 MIL-B-24480 MIL-C-50 MIL-C-3383 MIL-C-10375 MIL-C-1l553 (Alloy 12) MIL-C-1l866 (Composition 17) MIL-C-1l866 (Composition 19) MIL-C-1l866 (Composition 20) MIL-C-1l866 (Composition 21) MIL-C-11866 (Composition 22) MIL-C-12166 MIL-C-13351 MIL-C-15345 (Alloy 4) MIL-C-15345 (Alloy 5) MIL-C-15345 (Alloy 6) MIL-C-15345 (Alloy 10) MIL-C-15345 (Alloy 13) MIL-C-15345 (Alloy 14) MIL-C-15345 (Alloy 17) MIL-C-15345 (Alloy 28) MIL-C-15726 MIL-C-15726 E(2) MIL-C-I6420 MIL-C-171l2 MIL-C-17324 MIL-C-19311 MIL-C-19464 (Class 2) MIL-C-19464 (Class IV) MlL-C-21180 (Class 12) MIL-C-21657 MIL-C-21768 MIL-C-21768 MIL-C-22087 MIL-C-22087 MIL-C-22087 (Composition 4) MIL-C-22087 (Composition 5) MlL-C-22087 (Composition 7)
5052 5056, Alclad 5056
187 188
C93500 (85Cu-5Sn-9Pb-IZn) C51000 (94.8Cu-5Sn-0.2P)
396 360
C93700 (80Cu-IOSn-IOPb) C92200 (88Cu-6Sn-l.5Pb-4.5Zn) C87900
396 393 393
C875OO, C87800 (82Cu-4Si-14Zn) C62300 (87Cu-IOAI-3Fe)
393 367
C93800 (78Cu-7Sn-15Pb)
397
C93200 (83Cu-7Sn-7Pb-3Zn) C92200 (88Cu-6Sn-l.5Pb-4.5Zn) C22000 (9OCu-IOZn) Cl04OO,Cl05oo,Cl07oo C113OO, C1l4OO, Cll5OO, Cll600 (99.96Cu+Ag-0.40) C22000 (9OCu-IOZn) C95700 (75Cu-3Fe-8AI-2Ni-12Mn) C95800 (82Cu-4Fe-9AI-4Ni-IMn) C26000 (7OCu-30Zn) C22000 (90Cu-l0Zn) C26000 (70Cu-30Zn)
395 393 330 298 306 330 400 400 334 330 334
C93200 (83Cu-7Sn-7Pb-3Zn)
395
C82500 (97.2Cu-2Be-0.5Co-O.25Si) 386 C87300 (fonnerly C872OO) C861OO, C86200 (64Cu-24Zn-3Fe-5AI-4Mn)
392 389
C86300 (64Cu-26Zn-3Fe-3AI-4Mn) 390 C95300 (89Cu-1Fe-l0AI) C11000 (99.95Cu-0.040) C37700 (60Cu-38Zn-2Pb) C86500 (58Cu-39Zn-1.3FelAl-0.5Mn) C861OO, C86200 (64Cu-24Zn-3Fe-5AI-4Mn)
398 300 349 390 389
C86300 (64Cu-26Zn-3Fe-3AI-4Mn) 390 C92300 (87Cu-8Sn-1Pb-4Zn) C95400 (85Cu-4Fe-llAl) and C95410
399
C95500 (81Cu-4Fe-4Ni-llAI)
399
C93200 (83Cu-7Sn-7Pb-3Zn)
395
C95800 (82Cu-4Fe-9AI-4Ni-1Mn) C71500 (70Cu-30Ni) C70600 (90Cu-l0Ni) C70600 (90Cu-IONi) C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) C82500 (97.2Cu-2Be-0.5Co-0.25Si) C182OO, C184OO, C18500 (99Cu-1Cr)
400 376 373 373 401 386
394
324
C82500 (97.2Cu-2Be-0.5Co-0.25Si) 386 C82800 (96.6Cu-2.6Be-0.5Co-0.3Si) 388 356.0, A356.0 (7Si-0.3Mg) CI72oo, C 17300 C21000 (95Cu-5Zn) C22000 (9OCu-IOZn) C82500 (97.2Cu-2Be-0.5Co-O.25Si) C93400
257 316 328 330 386 396
C875OO, C87800 (82Cu-4Si-14Zn) C86500 (58Cu-39Zn-1.3FelAI-0.5Mn) C861OO. C86200 (64Cu-24Zn3Fe-5AI-4Mn)
393 390 389
Designation Government MIL-C-22087 (Composition 8) MIL-C-22087 (Composition 8) MIL-C-22087 (Composition 9) MIL-C-22087 (Composition 9) MIL-C-22229 MIL-C-22229 MIL-C-22229 MIL-C-22229 (Composition 6) MIL-C-22229 (Composition 6) MIL-C-22229 (Composition 7) MIL-C-22229 (Composition 8) MIL-C-22229 (Composition 9) MIL-C-22229 (Composition 10) MIL-C-46087 MIL-C-81021 MIL-C-81519 MIL-E-16053 MIL-E-16053 MIL-E-16053 MIL-E-16053 MIL-E-23765 MIL-E-23765 MIL-F-17132 MIL-H-6088 MIL-M-8916 MIL-M-8917 MIL-M-26075 MIL-M-46062 MIL-M-46062 MIL-M-46062 MIL-M-46062 MIL-M-46062 MIL-M-46062 MIL-M-46062 MIL-M-46062B MIL-M-46062B MIL-P-25995 MIL-P-25995 MIL-R-430 MIL-R-6944 MIL-R-24243 MIL-S-22499 MIL-T-1638 C(2) MIL-T-6945 MIL-T-6949 MIL-T-7081 MIL-T-8231 MIL-T-15OO5F MIL-T-16243 MIL-T-16420 MIL-T-19OO5 MIL-T-20168 MlL-T-20219 MIL-T-22214 MIL-T-23520A(4) MIL-T-46072 MIL-T-46072 MIL-T-46072 MIL-T-50777 MIL-T-52069 MIL-V-11-87 MlL-W-85 MIL-W-85 MIL-W-3318 MIL-W-3318 MIL-W-3318 MIL-W-3318
Alloy Name
Page
C95400 (85Cu-4Fe-11AI) and C95410
399
C95500 (81Cu-4Fe-4Ni-11Al) C861OO, C86200 (64Cu-24Zn3Fe-5AI-4Mn)
399
C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C87300 (fonnerly C872OO) C93400 C95200 (88Cu-3Fe-9AI) C95400 (85Cu-4Fe-11Al) and C95410
390 392 396 398
C95500 (81Cu-4Fe-4Ni-llAI) C86500 (58Cu-39Zn-1.3FeIAI-0.5Mn)
399
389
399
390
C86300 (64Cu-26Zn-3Fe-3AI-4Mn) 390 C861OO, C86200 389 (64Cu-24Zn-3Fe-5AI-4Mn) C861OO, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) 389 321 C17500 (97Cu-0.50Be-2.5Co) 321 C17500 (97Cu-0.50Be-2.5Co) C96600 (69.5Cu-30Ni-0.5Be) 400 151 1100 178 2319 185 4043 194 5356 C52100 (92Cu-8Sn) 361 C61000 (92Cu-8Al) 364 6061, Alclad 6061 201 7049 217 HM31A 430 HM21A 429 HK31A 427 AZ91A,AZ91B,AZ91C, AZ9lD, AZ9lE 436 AZ92A 438 EQ21 439 HK31A 441 HZ32A 443 ZH62A 453 ZK51A 454 QE22A 444 ZE63A 452 3003, Alclad 3003 180 6061, Alclad 6061 201 2017 159 EZ33A 440 5052 187 C26000 (70Cu-30Zn) 334 C70600 (9OCu-l0Ni) 373 C46400, C465OO,C466OO, C46700 (60Cu-39.2Zn-0.8Sn) 356 C26000 (70Cu-30Zn) 334 6061, Alclad 6061 201 C65500 (97Cu-3Si) 370 C70600 (9OCu-IONi) 373 C82800 (96.6Cu-2.6Be-0.5Co-0.3Si) 388 C71500 (70Cu-30Ni) 376 C71500 (70Cu-30Ni) 376 C23OOO(85Cu-15Zn) 332 C26000 (70Cu-30Zn) 334 C71500 (70Cu-30Ni) 376 C70600 (9OCu-IONi) 373 03000 (66Cu-33.5Zn-0.5Pb) 343 C33200 (66Cu-32.4Zn-1.6Pb) 344 07000 (6OCu-39Zn-1Pb) 349 2024, Alclad 2024 159 C22000 (9OCu-IOZn) 330 C95600 (91Cu-2Si-7Al) 399 6061, Alclad 6061 201 C22000 (9OCu-IOZn) 330 C10100 and CI0200 295 C104OO, cinsoo, Cl0700 298 C11000 (99.95Cu-0.04O) 300 C125OO, C127OO,C128OO, Cl2900, C13000 308
Cross Reference to Nonferrous Alloys I 665 Designation Government MIL-W-3381 MIL-W-6712 MIL-W-6712 MIL-W-6712 MIL-W-6712 MIL-W-6712 MIL-W-6712 MIL-W-23068 MIL-W-23351 QQ-250/10 QQ-A-2oo/1 QQ-A-2ooll QQ-A-2ool2 QQ-A-2ool3 QQ-A-2oo/4 QQ-A-2oo/5 QQ-A-2oo/6 QQ-A-2oon QQ-A-2oo/8 QQ-A-2oo/1O QQ-A-2oo/13 QQ-A-2ooIl4 QQ-A-22215 QQ-A-2251l QQ-A-22512 QQ-A-22513 QQ-A-225/4 QQ-A-225/6 QQ-A-225n QQ-A-225/8 QQ-A-225/9 QQ-A-2501l QQ-A-25012 QQ-A-25012 QQ-A-250/3 QQ-A-250/4 QQ-A-250/5 QQ-A-250/6 QQ-A-250n QQ-A-250/8 QQ-A-250/9 QQ-A-2501l1 QQ-A-2501l3 QQ-A-250/14 QQ-A-2501l5 QQ-A-2501l8 QQ-A-250/19 QQ-A-250120 QQ-A-25012l QQ-A-250122 QQ-A-250128 QQ-A-250129 QQ-A-250130 QQ-A-255/1O QQ-A-365 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-367 QQ-A-37I QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-430 QQ-A-566 QQ-A-591 QQ-A-591
Alloy Name
C113OO, C114OO, Cll5OO, C11600 (99.96Cu+Ag-0.4O) 1100 4043 C11000 (99.95Cu-0.04O) C22000 (9OCu-lOZn) C268oo, C27000 (65Cu-35Zn) C51000 (94.8Cu-5Sn-0.2P) 6061. Alclad 6061 6061, Alclad 6061 5454 3003, Alclad 3003 7075, Alclad 7075 2014, Alclad 2014 2024, Alclad 2024 5083 5086, Alclad 5086 5454 5456 6061, Alclad 6061 6066 7178, A1c1ad 7178 7178, Alclad 7178 2017 1100 3003, Alclad 3003 2011 2014, Alclad 2014 2024, Alclad 2024 5052 6061, Alclad 6061 7075, Alclad 7075 1100 3003, Alclad 3003 7075, Alclad 7075 2014, Alclad 2014 2024, Alclad 2024 2024, Alclad 2024 5083 5086, A1c1ad 5086 5052 5456 6061, Alclad 6061 7075, Alclad 7075 7178, Alclad 7178 7178, Alclad 7178 7075, Alclad 7075 5086, Alclad 5086 5456 7178, Alclad 7178 7178, A1c1ad 7178 7178, AIc1ad7178 2124 2219, AIclad 2219 6262 2014, Alclad 2014 2014, A1c1ad 2014 2218 2219, AIclad 2219 2618 4032 5083 6061, Alclad 6061 6066 6151 7049 7075, Alclad 7075 535.0, A535.0, B535.0 (7Mg) 1100 2017 2024, A1c1ad 2024 2219, Alclad 2219 3003, Alclad 3003 5005 5052 5056, A1c1ad 5056 6061, Alclad 6061 7075, Alclad 7075 2319 360.0, A360.0 (9.5Si-0.5Mg) 380.0, A380.0 (8.5Si-3.5Cu)
Page
306 151 185 300 330 339 360 201 201 194 180 221 155 159 189 191 194 195 201 208 239 239 159 151 180 155 155 159 187 201 221 151 180 221 155 159 159 189 191 187 195 201 221 239 239 221 191 195 239 239 239 171 174 212 155 155 173 174 179 184 189 201 208 209 217 221 266 151 159 159 174 180 185 187 188 201 221 178 260 261
Designation
Alloy Name
Page
Government QQ-A-591 384.0, A384.0 (l1.2Si-3.8Cu) 262 QQ-A-591 443.0, A443.0, B443.0, C443.0 (5.2Sij64 QQ-A-591 518.0 (8Mg) 265 QQ-A-591 (Class 2) 413.0, A413.0 (l2Si) 263 QQ-A-596 356.0, A356.0 (7Si-O.3Mg) 257 QQ-A-596 (Class 3) 242.0 (4Cu-2Ni-2.5Mg) 249 QQ-A-596 (Class 4) 296.0 (4.5Cu-2.5Si) 251 QQ-A-596 (Class 6) 308.0 (5.5Si-4.5Cu) 251 QQ-A-596 (Class 6) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 255 QQ-A-596 (Class 9) 336.0 (l2Si-2.5Ni-lMg-lCu) 252 QQ-A-596 (Class 12) 713.0 (7.5Zn-0.7Cu-0.35Mg) 267 QQ-A-596 (Class 15) 850.0 (6.2Sn-lCu-lNi) 268 QQ-A-601 356.0, A356.0 (7Si-0.3Mg) 257 QQ-A-601 535.0, A535.0, B535.0 (7Mg) 266 QQ-A-601 443.0, A443.0, B443.0. (Class 2) C443.0 (5.2Si) 264 QQ-A-601 (Class 4) 295.0 (4.5Cu-l.ISi) 250 QQ-A-601 (Class 5) 514.0 (4Mg) 264 QQ-A-601 (Class 6) 242.0 (4Cu-2Ni-2.5Mg) 249 QQ-A-601 (Class 8) 208.0 (4Cu-3Si) 248 QQ-A-601 (Class 10) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 255 QQ-A-601 (Class 16) 520.0 (lOMg) 265 QQ-A-601 (Class 17) 712.0 (5.8Zn-0.6Mg-0.5Cr-0.2Ti) 266 QQ-A-601 (Class 22) 713.0 (7.5Zn-0.7Cu-0.35Mg) 267 QQ-A-60lE 771.0 (7Zn-0.9Mg-O.l3Cr) 267 QQ-A-673 C1IOOO (99.95Cu-0.040) 300 QQ-A-1876 1100 151 QQ-A-1876 1145 153 QQ-B-6B C34000 (65Cu-34Zn-lPb) 345 QQ-B-225 (Alloy number 1) C92200 (88Cu-6Sn-1.5Pb-4.5Zn) 393 QQ-B-502 cnroo(99.95Cu-0.040-0.01Cd) 306 QQ-B-613 C23000 (85Cu-15Zn) 332 QQ-B-613 C24000 (80Cu-20Zn) 334 QQ-B-613 C26000 (70Cu-30Zn) 334 QQ-B-613 C268oo, C27000 (65Cu-35Zn) 339 QQ-B-613 C28000 (60Cu-4OZn) 341 QQ-B-613 C33500 (65Ca-34.5Zn-0.5Pb) 344 QQ-B-613 C34200 (62Cu-36.2Zn-2Pb), C35300 (62Cu-36.2Zn-1.8Pb) 345 QQ-B-613 C35000 (65.5Cu-36.4Zn-1.1Pb) 347 QQ-B-613 C35600 (62Cu-35.5Zn-2.5Pb) 347 QQ-B-613 C36000 (61.5Cu-35.5Zn-3Pb) 347 QQ-B-613 C37000 (60Cu-39Zn-lPb) 349 QQ-B-626 C23000 (85Cu-15Zn) 332 QQ-B-626 C24000 (80Cu-20Zn) 334 QQ-B-626 C26000 (70Cu-30Zn) 334 QQ-B-626 C268oo, C27000 (65Cu-35Zn) 339 QQ-B-626 C28000 (60Cu-4OZn) 341 QQ-B-626 C33500 (65Ca-34.5Zn-0.5Pb) 344 QQ-B-626 C34000 (65Cu-34Zn-lPb) 345 QQ-B-626 C34200 (62Cu-36.2Zn-2Pb), C35300 (62Cu-36.2Zn-1.8Pb) 345 QQ-B-626 C35000 (65.5Cu-36.4Zn-l.IPb) 347 QQ-B-626 C35600 (62Cu-35.5Zn-2.5Pb) 347 QQ-B-626 C36000 (61.5Cu-35.5Zn-3Pb) 347 QQ-B-626 C37000 (60Cu-39Zn-IPb) 349 QQ-B-626 C37700 (60Cu-38Zn-2Pb) 349 QQ·B-626 C464OO, C465OO, C466OO, C46700 (60Cu-39.2Zn-0.8Sn) 356 QQ-B-626 C48200 (60.5Cu-38Zn-0.8Sn-0.7Pb) 358 QQ-B-626 C48500 (60Cu-37.5Zn-1.8Pb-0.7Sn) 359 QQ-B-637 C464OO, C465oo, C466OO, C46700 (60Cu-39.2Zn-0.8Sn) 356 QQ-B-637 C48200 (60.5Cu-38Zn-0.8Sn-0.7Pb) 358
Designation Government QQ-B-637 QQ-B-639
Alloy Name
Page
C48500 (6OCu-37.5Zn-1.8Pb-0.7Sn) 359 . C46400,C465oo,C46600,C467oo (60Cu-39.2Zn-0.8Sn) 356 QQ-B-639 C48200 (60.5Cu-38Zn-0.8Sn-0.7Pb) 358 QQ-B-639 C48500 (6OCu-37.5Zn-1.8Pb-0.7Sn) 359 QQ-B-650 C24000 (80Cu-20Zn) 334 QQ-B-650 C26000 (70Cu-30Zn) 334 QQ-B-675 C95600 (91Cu-2Si-7Al) 399 QQ-B-750 C51000 (94.8Cu-5Sn-{).2P) 360 QQ-B-750 C52400 (9OCu-10Sn) 362 QQ-B-750 C54400 (88Cu-4Pb-4Sn4Zn) 363 QQ-B-825 CI0400, CI05oo, C10700 298 QQ-B-825 C11000 (99.95Cu·0.04O) 300 Cl1100 (99.95Cu-0.04O-{).0ICd) QQ-B-825 306 QQ-B-825 Cll3OO, C1I4OO. C1I5OO, C1I600 (99.96Cu+Ag-{).4O) 306 QQ-B-865 ciuoo (99.95Cu·0.04O-{).01Cd) 306 QQ-C-390 C82500 (97.2Cu-2Be-0.5Co-O.25Si) 386 QQ·C-390 C82600 (97Cu-2.4Be-0.5Co) 387 QQ-C-390 C82800 (96.6Cu-2.6Be-0.5Co-O.3Si) 388 QQ-C-390 C861OO, C86200 (64Cu-24Zn-3Pe-5A1-4Mn) 389 QQ-C-390 C86300 (64Cu-26Zn-3Pe-3AI4Mn) 390 QQ-C-390 C86400 (59Cu-0.75Sn-0.75Pb-37Zn1.25Pe-0.75AI-0.5Mn) 390 QQ-C-390 C86500 (58Cu-39Zn-1.3Pe-lAI-0.5MJllO QQ-C-390 C86800 391 QQ-C-390 C87300 (formerly C87200) 392 QQ-C-390 C875OO, C87800 (82Cu-4Si-14Zn) 393 QQ-C-390 C92300 (87Cu-8Sn-lPb4Zn) 394 QQ-C-390 C93200 (83Cu-7Sn-7Pb-3Zn) 395 QQ-C-390 C93400 396 QQ-C-390 C93500 (85Cu-5Sn-9Pb-lZn) 396 QQ-C-390 C93700 (80Cu-lOSn-lOPb) 396 QQ-C-390 C93800 (78Cu-7Sn-15Pb) 397 QQ-C-390 C95200 (88Cu-3Pe-9AI) 398 QQ-C-390 C95300 (89Cu-lPe-lOAl) 398 QQ-C-390 C95400 (85Cu-4Pe-11Al) and C9541099 QQ-C-390 C95500 (8ICu-4Pe-4Ni-11AI) 399 QQ-C-390 C95800 (82Cu-4Pe-9AI-4Ni-lMn) 400 QQ-C-390 (CA820) C82000 (97Cu-2.5Co-O.5Be) 384 QQ-C-390 (CA824) C82400 (98Cu-1.7Be-0.3Co) 386 QQ-C-450 C60600 (95Cu-5A1) 363 QQ-C-450 C61000 (92Cu-8A1) 364 QQ-C-450 C6I3OO (9OCu-7AI-0.3Sn) 364 QQ-C-450 C61400 (91Cu-7AI-2Pe) 365 QQ-C-465 C60600 (95Cu-5AI) 363 QQ-C-465 C61400 (91Cu-7AI-2Fe) 365 QQ-C-502 cioroo and C10200 295 QQ-C-502 CI0400,CI0500,CI0700 298 QQ-C-502 cuooo (99.95Cu-0.04O) 300 QQ-C-502 ciuoo (99.95Cu-0.04O-Q.OICd) 306 QQ-C-502 Cll3OO, C1I4OO, C115OO, C1I600 (99.96Cu+Ag-{).40) 306 QQ-C-523 C861OO, C86200 (64Cu-24Zn-3Fe-5A1-4Mn) 389 QQ-C-523 C86300 (64Cu-26Zn-3Pe-3AI4Mn) 390 QQ-C-523 C86400 (59Cu-0.75Sn-0.75Pb-37Zn1.25Fe-0.75AI-0.5Mn) 390 QQ-C-525 C93200 (83Cu-7Sn-7Pb-3Zn) 395 QQ-C-525 (Alloy 7) C93800 (78Cu-7Sn-15Pb) 397 QQ-C-530 CI72oo, C 17300 316 QQ-C-533 C 17000 (98Cu-1. 7Be-0.3Co) 314 QQ-C-533 CI72oo, C 17300 316 QQ-C-576 C10100 and C10200 295 QQ-C-576 CI0400,CI0500,CI0700 298 QQ-C-576 cuooo (99.95Cu-0.04O) 300 QQ-C-576 cmoo (99.95Cu-0.04O-0.01Cd) 306 QQ-C-576 Cll3OO, C1I4OO, C115OO, C1l6OO (99.96Cu+Ag-{).40) 306 QQ-C-585 C74500 (65Cu-25Zn-l0Ni) 378 QQ-C-585 C75200 (65Cu-18Ni-17Zn) 379 QQ-C-585 C77000 (55Cu-27Zn-18Ni) 381 QQ-C-586 C74500 (65Cu-25Zn-l0Ni) 378 QQ-C-586 C75200 (65Cu-18Ni-17Zn) 379 QQ-C-586 C77000 (55Cu-27Zn-18Ni) 381 QQ-C-591 C65100 (98.5Cu-1.5Si) 370 QQ-C-591 C65500 (97Cu-3Si) 370 QQ-C-645 C60600 (95Cu-5AI) 363 QQ-L-225 (Alloy 12) C93200 (83Cu-7Sn-7Pb-3Zn) 395
666/ Cross Reference to Nonferrous Alloys Designation
Government QQ-L-225 (Alloy 14) QQ-L-225 (Alloys 19 and 7) QQ-M-31 QQ-M-31B QQ-M-31B QQ-M-31B QQ-M-38 QQ-M-40 QQ-M-40 QQ-M-40 QQ-M-40B QQ-M-40B QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-55 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56 QQ-M-56A QQ-M-56B QQ-M-56B QQ-R-566 QQ-R-566 QQ-R-566 QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-32I QQ-W-343 QQ-W-343 QQ-W-343 QQ-W-343 QQ-W-343 QQ-Z-363 QQ-Z-363 WW-B-35I WW-P-377 WW-P-402 WW-T-575 WW-T-700/1 WW-T-700n WW-T-700/3 WW-T-700/4 WW-T-700/5 WW-T-700/6 WW-T-79I WW-T-79I WW-T-79I WW-T-825 WW-T-825 WW-T-825A WW-T-825B WW-V-1967 WW-V-1967 Bowmet Howmet
Alloy Name
C93500 (85Cu-5Sn-9Pb-1Zn) C93800 (78Cu-7Sn-15Pb) ZK60A AZ3IB.AZ3IC AZ61A AZSOA AZ91A, AZ9IB. AZ91C, AZ9ID, AZ91E AZ31B,AZ3IC HM21A ZK60A AZ6IA AZSOA AMlOOA AZ63A AZSIA AZ91A,AZ9IB,AZ91C, AZ9ID,AZ91E AZ92A EZ33A HK3IA QE22A AZ63A AZSIA AZ91A,AZ91B,AZ91C, AZ9ID,AZ91E AZ92A EZ33A HK3IA HZ32A ZH62A ZKSIA QE22A ZK61A 1100 4043 5356 caiooo (95Cu-5Zn) C22000 (90Cu-IOZn) C23000 (85Cu-15Zn) C24000 (80Cu-20Zn) C26000 (70Cu-30Zn) C26800, C27000 (65Cu-35Zn) C51000 (94.8Cu-5Sn-0.2P) C74500 (65Cu-25Zn-IONi) C75200 (65Cu-18Ni-17Zn) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) CIOIOOand C10200 CI0400,CI0500,CI0700 cuooo (99.95Cu-0.04O) ClllOO (99.95Cu-0.04O-0.0ICd) C11300, C11400, C11500, C11600 (99.96Cu+Ag-0.40) AC4IA; Zn-4AI-lCu-0.05Mg AG40A; Zn-4AI-0.04Mg C23000 (85Cu-15Zn) cuoco (99.95Cu-0.04O) 3004, Alclad 3004 CIOIOOand C10200 1100 3003, Aldad 3003 2024, Alclad 2024 5052 5086, Alclad 5086 6061, Alclad 6061 C23000 (85Cu-15Zn) C28000 (60Cu-40Zn) C33000 (66Cu-33.5Zn-0.5Pb) AZSOA ZK60A AZ6IA AZ3IB, AZ31C C86800 C87300 (formerly C87200) Ti-6AI-2Sn-4Zr-6Mo
Page
396 397 431 423 424 425 436 423 429 431 424 425 432 433 435 436 438 440 441 444 433 435 436 438 440 441 443 453 454 444 456 151 185 194 328 330 332 334 334 339 360 378 379 381 381 295 298 300 306
Page
Designation
Alloy Name
ICI ICI-Cu-2-10780 ICI-Cu-2-10785
C82500 (97.2Cu-2Be-0.5Co-0.25Si) 386 C82800 (96.6Cu-2.6Be-0.5Co-0.3Si) 388
424 500A 500D 500E 500G 500T
389 C83300 C92700 (88Cu-IOSn-2Pb) 395 C92600 (87Cu-IOSn-IPb-2Zn) 395 C92300 (87Cu-8Sn-IPb-4Zn) 394 C92200 (88Cu-6Sn-1.5Pb-4.5Zn) 393 C92500 (87Cu-IISn-1Pb-1Ni) 394 C93700 (80Cu-IOSn-IOPb) 396 C93400 396 C93200 (83Cu-7Sn-7Pb-3Zn) 395 C93800 (78Cu-7Sn-15Pb) 397 C93500 (85Cu-5Sn-9Pb-IZn) 396 C97600 (64Cu-4Sn-4Pb-8Zn-20Ni) 401 C95200 (88Cu-3Fe-9Al) 398 C95300 (89Cu-IFe-IOAI) 398 C95400 (85Cu-4Fe-11AI) and C954IG99 C95500 (8ICu-4Fe-4Ni-11AI) 399 C95800 (82Cu-4Fe-9AI-4Ni-IMn) 400 C95600 (9ICu-2Si-7Al) 399 C86400 (59Cu-0.75Sn-0.75Pb-37Zn1.25Fe-0.75AI-0.5Mn) 390 C86500 (58Cu-39Zn-1.3Fe-IAI-0.5MlJ¥) C86tOO, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) 389 C86300 (64Cu-26Zn-3Fe-3AI-4Mn) 390 C87300 (formerly C87200) 392 C87600 392 C87610 392 C87900 393 C87500, C87800 (82Cu-4Si-14Zn) 393
ISO A199.0Cu AlCu4Ni2Mg2 AICu4Si AICu4SiMg AlMgl AlMg1.5 AlMg2.5 AlMg3 AlMg3.5 AlMg3Mn AlMg4 AlMg4.5Mn AlMg5 AlMglO AlMgSiCu AlMnlCu AISi6Cu4 AlSi7Mg AISi12 AIZn6MgCu
1100 242.0 (4Cu-2Ni-2.5Mg) 295.0 (4.5Cu-l.lSi) 2014, Alclad 2014 5005 5050 5052 514.0 (4Mg) 5154 5454 5086, Alclad 5086 5083 5056, Alclad 5056 520.0 (IOMg) 6061, Alclad 6061 3003, Alclad 3003 319.0 (6Si-3.5Cu) 356.0, A356.0 (7Si-0.3Mg) 413.0, A413.0 (12Si) 7075, Alclad 7075
151 249 250 155 185 186 187 264 191 194 191 189 188 265 201 180 252 257 263 221
Ti-6AI-2Sn-4Zr-6Mo
517
7039 7039 7039 Ti-6A1-4V C82000 (97Cu-2.5Co-0.5Be) Unalloyed Titanium, Grade 4, UNS R50700 Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-8AI-IMo-IV Ti-6AI-4V Ti-6AI-4V Ti-6AI-6V-2Sn Ti-7AI-4Mo Ti-6AI-2Sn-4Zr-6Mo Ti-13V-11Cr-3Al Ti-11.5Mo-6Zr-4.5Sn Unalloyed Titanium, ASTM Grade I, UNS RS0250 Ti-5AI-2.5Sn Ti-5AI-2.5Sn Ti-8Al-IMo-IV
215 215 215 522 384
421 423
Martin Mar 306 616 615 332 300 182 295 151 180 159 187 191 201 332 341 343 425 431 424 423 391 392 517
Martin Mar
MIL A-2277 I A-45225 A-46063 A-46077D C-19464 (Class I) F-83142 Comp I F-83142A Comp 2 F-83142AComp 3 F-83142A Comp 5 F-83142A Comp 6 F-83142A Comp 7 F-83142A Comp 8 F-83142A Comp 9 F-83 142A Comp 11 F-83142AComp 12 F-83142AComp 13 T-0946J Code CP-4 T-81556ACodeA-1 T-81556A Code A-2 T-81556A Code A-4
Alloy Name
Page
MIL
Ingot code number 131 206 215 230 245 250 305 310 315 319 326 412 415 415 415 415 415 415E 420
Designation
472 483 483 498 522 522 536 541 517 572 559
T-81556A CodeAB-l T-81556A CodeAB-2 T-81556A CodeAB-3 T-81556A CodeAB-4 T-81556A CodeCP-1 T-81556A CodeCP-2 T-81556A CodeCP-3 T-81556A CodeCP-4 T-81915 Type I CompA T-81915 Type II CompA T-81915 Type ill CompA T-81915 Type ill CompB T-81915A T-9046J Code A-I T-9046J Code A-2 T-9046J CodeA-3 T-9046J Code A-4 T-9046JCodeAB-t T-9046J Code AB-2 T-9046J Code AB-3 T-9046J Code AB-4 T-9046J Code AB-5 T-9046J Code B-1 T-9046J Code B-2 T-9046J Code B-3 T-9046J Code CP-I T-9046J Code CP-2 T-9046J Code CP-3 T-9047G T-9047G SP-70
522
TI-6AI-4V
522
TI-6A1-6V-2Sn
536
TI-6AI-2Sn-4Zr-2Mo-O.08Si Unalloyed Titanium, Grade 4. UNS R50700 Unalloyed Titanium. ASTM Grade 3, UNS RS0550 Unalloyed TItanium. ASTM Grade 2, UNS RS0400 Unalloyed TItanium, ASTM Grade I, UNS RS0250 Unalloyed Titanium, ASTM Grade 2, UNS RS0400
492
OREMET Ti Beta 3 Ti-l
Ti-3 Ti-3-25
472 471 469 467 469
TI-5AI-2.5Sn
483
Ti-6AI-4V
522
Ti-6At-2Sn-4Zr-2Mo-O.08Si Unalloyed TItanium, ASTM Grade I, UNS R50250 Ti-5Al-2.5Sn TI-5Al-2.5Sn TI-6AI-2Nb-1Ta-0.8Mo Ti-8AI-IMo-IV Ti-6AI-4V TI-6AI-4V TI-6AI-6V-2Sn TI-6AI-2Sn-4Zr-2Mo-O.08Si TI-3Al-2.5V TI-13V-11Cr-3AI TI-I1.5Mo-6Zr-4.5Sn Ti-3AI-8V-6Cr-4Mo-4Zr (Beta C) Unalloyed Titanium, Grade 4, UNSRS0700 Unalloyed Titanium, ASTM Grade 3, UNS R50550 Unalloyed TItanium, ASTM Grade 2, UNS R50400 Ti-6AI-4V Unalloyed Titanium, Grade 4, UNSRS0700
492
T-9047GTiTi-3AI-2.5V 3AI-2.5V T-9047G Ti-3AI-8V6Cr-4Mo-4Zr TI-3AI-8V-6Cr-4Mo-4Zr (Beta C) T-9047G Ti-4.5Sn6Zr-11.5Mo Ti-11.5Mo-6Zr-4.5Sn T-9047GTi5AI-2.5Sn Ti-5AI-2.5Sn T-9047GTITi-5AI-2.5Sn 5AI-2.5Sn ELI T-9047G Ti-6Al2Sn-4Zr-2Mo Ti-6AI-2Sn-4Zr-2Mo-0.08Si T-9047G Ti-6AI2Sn-4Zr-6Mo TI-6AI-2Sn-4Zr-6Mo T-9047GTi6Al-6V-2Sn Ti-6AI-6V-2Sn T-9047GTITi-7AI-4Mo 7AI-4Mo T-9047GTiTi-8AI-IMo-IV 8AI-IMo-IV T-9047GTiTI-13V-11Cr-3AI 13V-IICr-3AI T-9047G Ti-CP-70 Unalloyed Titanium. Grade 4. UNSRS0700
Ti-2 467 483 483 498
TI-6AI-4V
Ti-11.5Mo-6Zr-4.5Sn Unalloyed TItanium, ASTM Grade I, UNS R50250 Unalloyed Titanium. ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS R50550 TI-3AI-2.5V
467 483 483 488 498 522 522 536 492 478 572 559 563 472 471 469 522 472 478 563 559 483 483 492 517 536 541 498 572 472 559 467 469 471 478
Cross Reference to Nonferrous Alloys I 667
Designation OREMET Ti-4 Ti-5-2.5 Ti-6-6-2 Ti-6Al-4V TI-8-1-1 TI-11
Ti-12 Ti-17
Ti-17 Ti-38-6-44 Ti-6242 Ti-6246
AiloyName
Unalloyed Titanium, Grade 4, UNSRS0700 TI-5Al-2.5Sn Ti-6AI-6V-2Sn TI-6Al-4V TI-8Al-1Mo-1 V Modified TI (Ti-0.2Pd), Grade 7, UNS R52400; Grade 11, UNSRS2250 Ti-o.3Mo-O.8Ni, ASTM Grade 12, R53400 Modified Ti (Ti-0.2Pd), Grade 7, UNS RS2400; Grade 11, UNSRS2250 TI-5AI-2Sn-2Zr-4Mo-4Cr Ti-3Al-8V-6Cr-4Mo-4Zr (Beta C) Ti-6Al-2Sn-4Zr-2Mo-0.08Si TI-6Al-2Sn-4Zr-6Mo
Page
472 483 536 522 498
474 476
474 514 563 492 517
Resistance WeldIng Manufactnrers' Association Classll Classill Classill Class ill Classill Class IV Class IV
C81400 C17500 (97Cu-0.50Be-2.5Co) C17600 C81800 (97Cu-l.5Co-1Ag-OABe) C82200 (98Cu-1.5Ni-0.5Be) C17000 (98Cu-l.7Be-0.3Co) C 17300
cnzco,
383 321 323 384 385 314 316
Modified TI (Ti-0.2Pd), Grade 7, UNS RS2400; Grade 11, UNSRS2250 TI-3Al-2.5V
474 478
TI-3AI-8V-6Cr-4Mo-4Zr (Beta C) TI-5Al-2.5Sn Ti-5Al-2.5Sn Ti-6Al-2Nb-lTa-0.8Mo
563 483 483 488
TI-6AI-2Sn-4Zr-2Mo-0.08Si Ti-6Al-2Sn-4Zr-6Mo TI-6Al-4V Ti-6AI-4V TI-6Al-6V-2Sn Ti-8AI-1Mo-1V TI-13V-11Cr-3Al Unalloyed Titanium, ASTM Grade I, UNS RS0250 Unalloyed Titanium, ASTM Grade 2. UNS RS0400 Unalloyed Titanium, ASTM Grade 3, UNS RS0550 Unalloyed Titanium. Grade 4, UNSRS0700 TI-7AI-4Mo
492 517 522 522 536 498 572
RMI 0.2%Pd
3AI-2.5V 3AI-8V-6Cr4Zr-4Mo 5AI-2.5Sn 5AI-2.5Sn ED 6AI-2Cb-1Ta-1Mo 6AI-2Sn-4Zr2Mo-O.10Si 6AI-2Sn-4Zr-6Mo 6AI-4V 6AI-4V-ELI 6AI-6V-2Sn 8AI-1Mo-1V 13V-11Cr-3AI 25 40 55 70 Ti-7AI-4Mo
467 469 471 472 541
SAE 38 303 304 305 306 308 309 310 320 321 322 323 324 326 330 380 382 383 510 921 J451 J452 J452
295.0 (4.5Cu-l.1Si) 384.0, A384.0 (1l.2Si-3.8Cu) 443.0, A443.0, B443.0, C443.0 (5.2Si) 413.0, A413.0 (l2Si) 380.0, A380.0 (8.5Si-3.5Cu) 380.0, A380.0 (8.5Si-3.5Cu) 360.0, A360.0 (9.5Si-0.5Mg) 712.0 (5.8Zn-0.6Mg-0.5Cr-0.2Ti) 514.0 (4Mg) 336.0 (l2Si-2.5Ni-1Mg-1Cu) 355.0, C355.0 (5Si-l.3Cu-0.5Mg) 356.0, A356.0 (7Si-0.3Mg) 520.0 (lOMg) 319.0 (6Si-3.5Cu) 308.0 (5.5Si-4.5Cu) 296.0 (4.5Cu-2.5Si) 20l.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-0.25TI) 383.0 (1O.5Si-2.5Cu) AZ3IB,AZ31C AC43A; Zn-4AI-2.5Cu-0.04Mg 6005 356.0, A356.0 (7Si-0.3Mg) 360.0, A360.0 (9.5Si-0.5Mg)
250 262 264 263 261 261 260 266 264 252 255 257 265 252 251 251 244 261 423 615 200 257 260
Designation SAE J453 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J454 J460 (791) J461 J461 J461 J461 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J462 J463 J463 J463 J463 J463 J463 J463 J463 (CA176) J463 J463 J463 J463 (CA220) J463 (CA230) J463 (CA240) J463 J463
AiloyName
Page
Designation
AiloyName
Page
SAE 413.0, A413.0 (12Si) 1060 1100 2011 2017 2024, Alclad 2024 2218 2618 3003, Alclad 3003 3004, Alclad 3004 3105 4032 4043 5005 5050 5052 5056, Alclad 5056 5083 5086, Alclad 5086 5154 5252 5254 5454 5456 5652 6063 6066 6070 6101 6151 6201 6262 6463 7072 7075, Alclad 7075 7178, Alc1ad 7178 C54400 (88Cu-4Pb-4Sn-4Zn) C11100 (99.95Cu-0.040-0.01Cd) C464oo, C465OO, C466OO,C46700 (60Cu-39.2Zn-0.8Sn) C87300 (formerly C872OO) C87900 C861OO,C86200 (64Cu-24Zn3Fe-5AI-4Mn) C86300 (64Cu-26Zn-3Fe-3AI-4Mn) C86500 (58Cu-39Zn-l.3Fe1Al-0.5Mn) C87300 (formerly C872OO) C875OO, C87800 (82Cu-4Si-14Zn) C87900 C92200 (88Cu-6Sn-l.5Pb-4.5Zn) C92300 (87Cu-8Sn-IPb-4Zn) C92500 (87Cu-11Sn-IPb-1Ni) C92700 (88Cu-10Sn-2Pb) C92900 (84Cu-10Sn-2.5Pb-3.5Ni) C93200 (83Cu-7Sn-7Pb-3Zn) C93500 (85Cu-5Sn-9Pb-1Zn) C93700 (80Cu-IOSn-IOPb) C93800 (78Cu-7Sn-15Pb) C95200 (88Cu-3Fe-9AI) C95300 (89Cu-1Fe-IOA1) C95500 (8ICu-4Fe-4Ni-11AI) C95800 (82Cu-4Fe-9AI-4Ni-1Mn) C11000 (99.95Cu-0.04O) C11100 (99.95Cu-0.040-0.01Cd) C113OO, C114OO, C115OO, C11600 (99.96Cu+Ag-OAO) C16200 (99Cu-1Cd) C17000 (98Cu-l.7Be-0.3Co) C 17300 C17500 (97Cu-0.50Be-2.5Co) C17600 C182OO, C18400, C18500 (99Cu-1Cr) C18700 (99Cu-1Pb) C21000 (95Cu-5Zn) C22000 (9OCu-IOZri)' C23000 (85Cu-15Zn) C24000 (80Cu-20Zn) C26000 (70Cu-30Zn) C268oo, C27000 (65Cu-35Zn)
cnzco.
263 150 151 155 159 159 173 179 180 182 184 184 185 185 186 187 188 189 191 191 193 193 194 195 198 206 208 208 209 209 211 212 214 221 221 239 363 306 356 392 393 389 390 390 392 393 393 393 394 394 395 395 395 396 396 397 398 398 399 400 300 306 306 314 314 316 321 323 324 325 328 330 332 334 334 339
J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J463 J465 J465 J465 J465 J465 J465 J465 J465 J465 J465 J465 J466 J466 J466 J466 J466 J467 J467 J467 J468 J468 J474
Ti-8-1-1 Ti662 (Alloy 903) (Alloy 925)
Teledyne Tel-Ti-3AI-8V6Cr-4Mo-4Zr Tel-TI-BV11Cr-3AI
C33000 (66Cu-33.5Zn-0.5Pb) C34200 (62Cu-36.2Zn-2Pb), C35300 (62Cu-36.2Zn-l.8Pb) C35000 (65.5Cu-36AZn-l.lPb) C36000 (6l.5Cu-35.5Zn-3Pb) C464OO,C465OO,C466OO,C46700 (60Cu-39.2Zn-0.8Sn) C51000 (94.8Cu-5Sn-o.2P) C52100 (92Cu-8Sn) C54400 (88Cu-4Pb-4Sn-4Zn) C61400 (9ICu-7AI-2Fe) C62300 (87Cu-10AI-3Fe) C62400 (86Cu-llAl-3Fe) C65500 (97Cu-3Si) C70600 (9OCu-10Ni) C71000 (80Cu-20Ni) C71500 (70Cu-30Ni) C75200 (65Cu-18Ni-l7Zn) C77000 (55Cu-27Zn-18Ni) AMIOOA AZ63A AZ81A AZ91A, AZ9IB, AZ91C, AZ9ID,AZ91E AZ92A EZ33A HK31A HK31A ZH62A ZK51A ZK61A AZ3IB, AZ31C AZ61A AZ80A HM31A ZK60A Ti-6Al-4V Ti-8Al-1Mo-1V Ti-6AI-6V-2Sn AG40A; Zn-4AI-0.04Mg AC4IA; Zn-4AI-1Cu-0.05Mg 2219, Alclad 2219
343
Ti-3AI-8V-6Cr-4Mo-4Zr (Beta C)
563
Ti-13V-11Cr-3Al
572
TI-6AI-2Sn-4Zr-6Mo Ti-6Al-4V
517 522
345 347 347 356 360 361 363 365 367 368 370 373 375 376 379 381 432 433 435 436 438 440 427 441 453 454 456 423 424 425 430 431 522 498 536 615 616 174
Thledyne AilVac Te1.AlIVac Allvac6-4 Thledyne Rodney A35 A40 A40 A55
Unalloyed Titanium, ASTM Grade 1, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, Grade 4. UNS RS0700 Unalloyed Titanium, ASTM Grade 3, UNS R50550
467 469 472 471
TIMET Ti-0.2Pd
Modified Ti (Ti-0.2Pd), Grade 7, UNS RS2400; Grade 11, UNSRS2250 Ti-75A Unalloyed Titanium, Grade 4, UNSR50700 TIMETAL 3-2.5 TI-3Al-2.5V TIMETAL 3-8-6-4-4 TI-3Al-8V-6Cr-4Mo-4Zr (Beta C) TIMETAL 5-2.5 Ti-5AI-2.5Sn TIMETAL 5-2.5 ELI TI-5Al-2.5Sn TIMETAL 6-2-1 Ti-6AI-2Nb-lTa-0.8Mo TIMETAL 6-2-4-2 Ti-6Al-2Sn-4Zr-2Mo-O.08Si TIMETAL 6-2-4-6 Ti-6AI-2Sn-4Zr-6Mo TIMETAL6-4 TI-6Al-4V TIMETAL 6-4 ELI Ti-6AI-4V TIMETAL 6-4 STA TI-6AI-4V TIMETAL 6-6-2 Ti-6AI-6V-2Sn TIMETAL 6-6-2STA TI-6AI-6V-2Sn
474 472 478 563 483 483 488 492 517 522 522 522 536 536
668/ Cross Reference to Nonferrous Alloys
Designation
Alloy Name
TIMET TIMETAL 7-4 TIMETAL 8-1-1 TIMETAL 10-2-3 TlMETAL 13-11-3 TIMETAL 15-3 TIMETALI7 TIMETAL35A
Ti-2 Ti-3 Ti-4 Ti-7
Ti-ll
Ti-12 Ti-325
Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS RS0550 Unalloyed Titanium, Grade 4, UNSR50700 Modified Ti (Ti-0.2Pd), Grade 7, UNS R524oo; Grade 11, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7, UNS R52400; Grade II, UNSR52250 Ti-0.3Mo-0.8Ni, ASTM Grade 12, RS3400 Ti-3AI-2.5V
541 498 566 572 577 514 467
474 469
474 471 472 476
467 469 471 472
474
474 476 478
UNS A02010 A02080 A02420 A02950 A03080 A03190 A03320 A03550 A03560 A03570 A03590 A03600 A03800 A03830 A03840 A03900 A04130 A04430 A05140 A05180 A05200 A05350 A07130 A07710 A08500 A 13320 A 13560 A 13570 A 13600 A 13800 A13840 A 13900 A14130
Designation
Alloy Name
Page
UNS
Ti-7Al-4Mo Ti-8AI-IM(}-1V Ti-IOV-2Fe-3AI Ti-13V-lICr-3AI Ti-15V-3Cr-3AI-3Sn Ti-5AI-2Sn-2Zr-4M(}-4Cr Unalloyed Titanium, ASTM Grade I, UNS R50250 TIMETAL 35A Pd Modified Ti (Ti-0.2Pd), Grade 7, UNS R524oo; Grade 11, UNSR52250 TIMETAL50A Unalloyed Titanium, ASTM Grade 2, UNS RS0400 TIMETAL 50A Pd Modified Ti (Ti-0.2Pd), Grade 7, UNS R524oo; Grade 11, UNSR52250 TIMETAL65A Unalloyed Titanium, ASTM Grade 3, UNS RS0550 TIMETAL looA Unalloyed Titanium, Grade 4, UNSR50700 TIMETALCode 12 Ti-0.3Mo-0.8Ni, ASTM Grade 12, RS3400 TMCA Ti-I
Page
201.0 (4.6Cu-0.7Ag-0.35Mn0.35Mg-0.25Ti) 208.0 (4Cu-3Si) 242.0 (4Cu-2Ni-2.5Mg) 295.0 (4.5CU-I.1Si) 308.0 (5.5Si-4.5Cu) 319.0 (6Si-3.5Cu) 332.0 (9.5%Si-3.0%Cu-1.0%Mg) 355.0, C355.0 (5Si-1.3Cu-0.5Mg) 356.0, A356.0 (7Si-0.3Mg) 357.0, A357.0 (7Si-0.5Mg) 359.0 (9Si-0.6Mg) 360.0, A360.0 (9.5Si-0.5Mg) 380.0, A380.0 (8.5Si-3.5Cu) 383.0 (1O.5Si-2.5Cu) 384.0, A384.0 (11.2Si-3.8Cu) 390.0, A39O.0 (17 .0Si4.5Cu-0.6Mg) 413.0, M13.0 (l2Si) 443.0, A443.0, B443.0, C443.0 (5.2Si) 514.0 (4Mg) 518.0 (8Mg) 520.0 (IOMg) 535.0, A535.0, B535.0 (7Mg) 713.0 (7.5Zn-0.7Cu-0.35Mg) 771.0 (7Zn-0.9Mg-0.13Cr) 850.0 (6.2Sn-ICu-INi) 336.0 (l2Si-2.5Ni-iMg-lCu) 356.0, A356.0 (7Si-0.3Mg) 357.0, A357.0 (7Si-0.5Mg) 360.0, A360.0 (9.5Si-0.5Mg) 380.0, A380.0 (8.5Si-3.5Cu) 384.0, A384.0 (11.2Si-3.8Cu) 390.0, A390.0 (l7.0Si-4.5Cu-0.6Mg) 413.0, M13.0 (l2Si)
244 248 249 250 251 252 252 255 257 259 259 260 261 261 262 262 263 264 264 265 265 266 267 267 268 252 257 259 260 261 262 262 263
A 14430 AI5350 A22950 A24430 A25350 A34430 M7120 A91050 A91060 A91100 A92011 A92014 An017
An024 A92048 A92124 A92218 A92219 A92319 A93OO3 A93OO4 A95OO5 A95050 A95052 A95056 A95086 A95154 A95252 A95254 A95356 A95454 A95456 A95457 A95652 A95657 A96oo5 A96oo9 A96010 A96061 A96063 A96066 A96101 A96151 A96201 A96205 A9635 I A96463 A97oo5 A97039 A97049 A97050 A97072 A97075 A97175 A97178 A97475 AC3540
cioioo, CI0200 CI0300 C104OO, C105OO, CI0700 CI0800 C11000
443.0, A443.0, B443.0, C443.0 (5.2Si) 535.0, A535.0, B535.0 (7Mg) 296.0 (4.5Cu-2.5Si) 443.0, A443.0, B443.0, C443.0 (5.2Si) 535.0, A535.0, B535.0 (7Mg) 443.0, M43.0, B443.0, C443.0 (5.2Si) 712.0 (5.8Zn-0.6Mg-0.5Cr-0.2Ti) 1050 1060 1100 2011 2014, Alc1ad 2014 2017 2024, Alclad 2024 2048 2124 2218 2219, Alclad 2219 2319 3003, Alc1ad 3003 3004, AIc1ad3004 5005 5050 5052 5056, Alc1ad5056 5086. Alc1ad 5086 5154 5252 5254 5356 5454 5456 5457 5652 5657 6005 6009 6010 6061, AIc1ad6061 6063 6066 6101 6151 6201 6205 6351 6463 7005 7039 7049 7050 7072 7075, Alc1ad 7075 7175 7178, AIc1ad7178 7475 354.0 (9Si-I.8Cu-0.5Mg) C 10100 and CI0200 CI0300
CI0400,CI0500,CI0700 CI0800 cuooo (99.95Cu-0.040) cmoo C11100 (99.95Cu-0.040-0.0ICd) C113OO, C1I4OO, C1l3OO, C114OO, C1I5OO, C1I6OO C115OO, C11600 (99.96Cu+Ag-0.40) CI25oo, CI27oo, CI25oo, CI27oo, CI28oo, C128OO, C129OO, C129OO, C13000 C13000 CI43oo, CI4310 CI43oo, CI43 10 (99.90Cu-0.ICd; 99.8Cu-0.2Cd) CI4500 CI4500 (99.5Cu-0.Te) CI4700 CI4700 (99.6Cu-o.45) CI5000 CI5000 (99.85Cu-0.15Zr) CI5100 CI5100 (99.9Cu-0.IZr) CI5500 CI5500 (99.75Cu-0.11Mg-0.06P) CI5710 CI5710 (99.8Cu-0.2AI203) C15720 C15720 (99.6Cu-0.4AI203)
264 266 251 264 266 264 266 149 150 151 155 155 159 159 169 171 173 174 178 180 182 185 186 187 188 191 191 193 193 194 194 195 197 198 198 200 200 201 201 206 208 209 209 211 211 213 214 214 215 217 218 221 221 238 239 241 253 295 298 298 300 300 306 306 308
309 309 309 310 312 312 313 313
Designation
Alloy Name
UNS CI5735 CI6200 C17000 CI72oo, C17300 C17410 CI7500 CI7600 CI8100
Page
CI5735 (99.3Cu-0.7AI203) CI6200 (99Cu-ICd) C17000 (98Cu-1.7Be-0.3Co) CI72oo, C17300 C17410 (99.2Cu-0.3Be-0.5Co) CI7500 (97Cu-0.50Be-2.5Co) C17600 CI8100 (99Cu-0.8Cr-0.I 6ZrO.04Mg) CI82oo, C18400, C182OO, C18400, CI8500 (99Cu-ICr) CI8500 CI8700 CI87oo(99Cu-IPb) CI9200 (98.97Cu-1.0Fe-0.03P) CI9200 CI9210 CI9210 (99.87Cu-0.IFe-0.03P) CI9400 C19400 (Cu-2.35Fe-0.03P-0.12Zn) CI9500 (97Cu-1.5Fe-0.IPCI9500 0.8Co-0.6Sn) CI9700 (99.l5Cu-0.6FeCI9700 0.2P-0.05Mg) (95Cu-5Zn) czrooc C22000 C22000 (9OCu-IOZn) C22600 C22600 (87.5Cu-12.5Zn) C23000 (85Cu-15Zn) C23000 C24000 (80Cu-20Zn) C24000 C26000 (70Cu-30Zn) C26000 C268oo, C27000 C268oo, C27000 (65Cu-35Zn) C28000 (6OCu-40Zn) C28000 C31400 C31400 (89Cu-9.IZn-1.9Pb) C31600 C31600 (89Cu-8.IZn-1.9Pb-INi) C33000 (66Cu-33.5Zn-0.5Pb) C33000 C33200 (66Cu-32.4Zn-1.6Pb) C33200 C33500 (65Ca-34.5Zn-0.5Pb) C33500 C34000 C34000 (65Cu-34Zn-IPb) C342OO,C35300 C34200 (62Cu-36.2Zn-2Pb), C35300 (62Cu-36.2Zn-1.8Pb) C34900 (62Cu-37.5Zn-0.3Pb) C34900 C35000 (65.5Cu-36.4Zn-I.IPb) C35000 C34200 (62Cu-36.2Zn-2Pb), C35300 C35300 (62Cu-36.2Zn-1.8Pb) C35600 C35600 (62Cu-35.5Zn-2.5Pb) C36000 C36000 (61.5Cu-35.5Zn-3Pb) C365OO,C366OO, C365OO, C366OO, C367OO, C367OO, C36800 C36800 (60Cu-39.4Zn-0.6Pb) C37000 C37000 (6OCu-39Zn-IPb) C37700 C37700 (6OCu-38Zn-2Pb) C38500 C38500 (57Cu-40Zn-3Pb) C40500 C40500 (95Cu-4Zn-l Sn) C40800 C40800 (95Cu-2Sn-3Zn) C41100 C41100 (9ICu-8.5Zn-0.5Sn) C41500 C41500 (9ICu-7.2Zn-1.8Sn) C4 I900 C41900 (9O.5Cu-4.35Zn-5.15Sn) C42200 C42200 (87.5Cu-11.4Zn-I.1Sn) C42500 C42500 (88.5Cu-9.5Zn-2Sn) C43000 C43000 (87Cu-IO.8Zn-2.2Sn) C43400 C43400 (85Cu-14.3Zn-0.7Sn) C443OO,C444OO, C443OO, C44400, C44500 C44500 (7ICu-28Zn-ISn) C464OO,C465OO, C464OO, C465OO, C466OO, C466OO, C46700 C46700 (6OCu-39.2Zn-0.8Sn) C48200 C48200 (60.5Cu-38Zn-0.8Sn0.7Pb) C48500 C48500 (60Cu-37.5Zn-1.8Pb0.7Sn) C50500 C50500 (98.7Cu-1.3Sn) C51000 C51000 (94.8Cu-5Sn-0.2P) C51100 C51100 (95.6Cu-4.2Sn-0.2P) C52100 C52100 (92Cu-8Sn) C52400 C52400 (9OCu-IOSn) C54400 (88Cu-4Pb-4Sn-4Zn) C54400 C60600 (95Cu-5AI) C60600 C60800 C60800 (95Cu-5AI) C61000 (92Cu-8AI) C61000 C61300 (9OCu-7Al-0.3Sn) C61300 C61400 (9ICu-7AI-2Fe) C61400 C61500 (9OCu-8AI-2Ni) C61500 C62300 (87Cu-IOAI-3Fe) C62300 C62400 C62400 (86Cu-ll AI-3Fe) C62500 (82.7Cu-4.3Fe-13AI) C62500 C63800 C63800 (95Cu-2.8AI-1.8Si-0.4OCo) C65100 C65100 (98.5CU-1.5Si) C65400 C65400 (95.4Cu-3.0Si-1.5Sn-0.ICr)
cneoo
314 314 314 316 320 321 323 323 324 325 325 326 326 328 328 328 330 331 332 334 334 339 341 343 343 343 344 344 345 345 346 347 345 347 347 349 349 349 350 351 351 351 352 353 353 353 354 354 354 356 358 359 359 360 361 361 362 363 363 363 364 364 365 366 367 368 368 369 370 370
Cross Reference to Nonferrous Alloys I 669 Designation
Alloy Name
Page
UNS C65500 C68800 C69000 C69400 C70400 C70600 C71000 C71500 C71900 C72200 C72500 C74500 C75200 C75400 C75700 C77000 C78200 C8l300 C81400 C81500 C81800 C82000 C82200 CB2400 C82500 C82600 C82800 C83300 C86100, C86200 C86300 C86400 CB6500 C86700 C86800 C87300 C87500, C87800 C87600 C87610 C87900 C92200 C92300 C92500 C92600 C92700 C92900 C93200 C93400 C93500 C93700 C93800 C95200 C95300 C95400, C95410 C95500 C95600 C95700 C95800 C96600 C97300 C97600
C65500 (97Cu-3Si) C68800 (73.5Cu-22.7Zn-3.4AlO.4Co) C69000 (73.3Cu-22.7Zn-3.4Al0.6Ni) C69400 (81.5Cu-14.5Zn-4Si) C70400 (92.4Cu-5.5Ni-l.5Fe0.6Mn) C70600 (9OCu-10Ni) C71000 (80Cu-20Ni) C71500 (70Cu-30Ni) C71900 (67.2Cu-30Ni-2.8Cr) C72200 (83Cu-16.5Ni-0.5Cr) C72500 (88.2Cu-9.5Ni-2.3Sn) C74500 (65Cu-25Zn-lONi) C75200 (65Cu-18Ni.17Zn) C75400 (65Cu-2OZn-15Ni) C75700 (65Cu-23Zn-12Ni) C77000 (55Cu-27Zn-18Ni) C78200 (65Cu-25Zn-8Ni-2Pb) CBl300 CB1400 CB1500 CB1800 (97Cu-1.5Co-IAg-0.4Be) CB2000 (97Cu-2.5Co-O.5Be) C82200 (98Cu-1.5Ni-0.5Be) C82400 (98Cu-I.7Be-0.3Co) CB2500 (97.2Cu-2Be-0.5Co0.25Si) CB2600 (97Cu-2.4Be-0.5Co) CB2800 (96.6Cu-2.6Be-0.5Co0.3Si) CB3300 CB6100, C86200 (64Cu-24Zn-3Fe-5AI-4Mn) CB6300 (64Cu-26Zn-3Fe3Al-4Mn) CB6400 (59Cu-0.75Sn-0.75Pb37Zn-l.25Fe-o.75Al-0.5Mn) CB6500 (58Cu-39Zn-I.3FelAl-0.5Mn) C86700 CB6800 CB7300 (formerly C87200) CB7500, C87800 (82Cu-4Si-14Zn) CB7600 CB7610 CB7900 C92200 (88Cu-6Sn-1.5Pb4.5Zn) C92300 (87Cu-8Sn-lPb-4Zn) C92500 (87Cu-l1Sn-1Pb-lNi) C92600 (87Cu-l0Sn-lPb-2Zn) C92700 (88Cu-lOSn-2Pb) C92900 (84Cu-lOSn-2.5Pb-3.5Ni) C93200 (83Cu-7Sn-7Pb-3Zn) C93400 C93500 (85Cu-5Sn-9Pb-lZn) C93700 (80Cu-IOSn-lOPb) C93800 (78Cu-7Sn-15Pb) C95200 (88Cu-3Fe-9Al) C95300 (89Cu-lFe-lOA 1) C95400 (85Cu-4Fe-llAl) and C95410 C95500 (81Cu-4Fe-4Ni-llAI) C95600 (9ICu-2Si-7AI) C95700 (75Cu-3Fe-8Al2Ni-I2Mn) C95800 (82Cu-4Fe-9AI-4Ni-lMn) C96600 (69.5Cu-30Ni-0.5Be) C97300 (56Cu-2Sn-l0Pb-20Zn12Ni) C97600 (64Cu-4Sn-4Pb-8Zn20Ni)
370
Designation UNS C97800
371
C99400
372 372
C99500 C99750 J95182 K63198 K66220 K66286 K66545 K66545 M1660 MI0l00 M11311 M1l312 M1l61O M1l630 M11800 M11810 M11910
373 373 375 376 377 378 378 378 379 380 381 381 382 383 383 383 384 384 385 386 386 387 388 389 389 390 390 390 391 391 392 393 392 392 393 393 394 394 395 395 395 395 396 396 396 397 398 398 399 399 399 400 400 400 401 401
M11912 M11914 M11916 Ml1920 M11921 M12330 Ml3210 M13310 M13310 Ml3312 Ml3320 M16330 MI64lO M16510 Ml6610 M16620 M16630 M16631 M16710 M18220 M18410 M18430 N0660 NOOOOI N06002 N06102 N06230 N06455 N06601 N06625 N07001 N07031 N07041 N07080 N07090 N07263 N07500 N07702 N07716 N07718 N07721 N07722 N07750 N08330 N08800 N08801 N09706 N09901 N09925
Alloy Name
C97800 {66.5Cu-5Sn-1.5Pb2Zn-25Ni) C99400 {9O.4Cu-2.2Ni-2.0Fe1.2Al-1.2Si-3.OZn) C99500 C99750 5182 19-9DL Discaloy A-286 W-545 V-57 ZK60A AMl00A AZ3lB,AZ31C AZ3lB,AZ31C AZ61A AZ63A AZSOA AZSIA AZ91A,AZ91B,AZ91C, AZ9ID,AZ9lE AZ91A, AZ9lB, AZ91C, AZ9ID,AZ9lE AZ91A, AZ9lB, AZ91C, AZ9ID,AZ9lE AZ91A,AZ91B,AZ91C, AZ9ID,AZ9lE AZ92A AZ91A, AZ9lB, AZ91C, AZ9ID, AZ91E EZ33A HM21A HK31A HK31A HM3IA HZ32A EQ21 ZE41A ZK51A ZK61A
~2A
3A ZC63 Ze71 QE22A WE54 WE43 Inconel600 HastelloyB HasteUoyX IN 102 Haynes 230 Hastelloy C-4 Inconel601 Inconel625 Waspaloy Pyromet31 Rene 41 Nimonic80A Nimonic90 C-263 Udimet500 Inconel702 Custom Age 625 PLUS Incone1718 Inconel721 Inconel722 Inconel X 750 RA-330 Incoloy 800 Incoloy 801 Inconel706 Incoloy 901 Incoloy 925
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401 401 402 402 192 119 120 108 112 112 431 432 423 423 424 433 425 435
Designation UNS N09979 Nl0002 Nl0003 Nl0004 N10276 NI0665 Nl3100 N19903 N19907 N19909 R30035 R30155 R30188 R30605 R30816 RSOl00 RS0120 RS0125
436
RSOl30
436
RS0250
436
RS0400
436 438
RS0550 RS0700
436 440 429 427 441 430 443 439 450 454 456 453 452 450 431 444 448 447 81 33 38 25 40 36 88 88 76 59 63 60 62 59 69 41 40 41 59 59 30 120 112 114 29 26 118
R52250
R52400
R52401
R53400 RS4520 R54521 R54522 RS4523 R54620 RS4621 RS4810 R56210 R56260 RS6320 RS6321 R56400 R56401 R56402 RS6740 RS8010 R58030 R58640 R58650 Z33520 Z33521 Z33522 Z33523 Z35530 Z35531 Z35540 Z35541 Z35630 Z3563 I Z35635 Z35636 Z35840 Z3584 I
Alloy Name
D-979 HastelloyC HastelloyN HastelloyW Hastelloy C-276 Hastelloy B-2 In 100 Incoloy 903 Incoloy907 Incoloy 909 MP35N N-155 Haynes 188 Haynes 25; L-605 S-816 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 1, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade I, UNS R50250 Unalloyed Titanium, ASTM Grade 2, UNS R50400 Unalloyed Titanium, ASTM Grade 3, UNS RS0550 Unalloyed Titanium, Grade 4, UNSRS0700 Modified Ti (Ti-o.2Pd), Grade 7, UNS RS2400; Grade 11, UNSRS2250 Modified Ti (Ti-o.2Pd), Grade 7, UNS R52400; Grade 11, UNSR52250 Modified Ti (Ti-0.2Pd), Grade 7. UNS R52400; Grade 11, UNSRS2250 TI-0.3Mo-O.8Ni, ASTM Grade 12, RS3400 Ti-5Al-2.5Sn TI-5Al-2.5Sn Ti-5AI-2.5Sn TI-5AI-2.5Sn Ti-6Al-2Sn-4Zr-2Mo-O.08Si TI-6Al-2Sn-4Zr-2Mo-O.08Si TI-8Al-IMo-IV TI-6AI-2Nb-ITa-0.8Mo TI-6Al-2Sn-4Zr:6Mo TI-3AI-2.5V TI-3AI-2.5V TI-6Al-4V TI-6AI-4V TI-6Al-4V Ti-7Al-4Mo TI-13V-llCr-3Al TI-l1.5Mo-6Zr-4.5Sn TI-3AI-8V-6Cr-4M0-4Zr (Beta C) TI-5AI-2Sn-2Zr-4Mo-4Cr AG4OA; Zn-4Al-O.04Mg AG4OA; Zn-4AI-O.04Mg AG4OB; Zn-4Al-0.015Mg AG40B; Zn-4AI-0.015Mg AC41A; Zn-4Al-lCu-o.05Mg AC41A; Zn-4Al-lCu-o.05Mg AC43A; Zn-4Al-2.5Cu-0.04Mg AC43A; Zn-4AI-2.5Cu-0.04Mg ZA-12; Zn-llAI-lCu-0.025Mg ZA-12; Zn-llAl-lCu-0.025Mg ZA-8; Zn-8AI-lCu-(l.02Mg ZA-8; Zn-8AI-ICu-0.02Mg ZA-27; Zn-27Al-2Cu-0.015Mg ZA-27; Zn-27Al-2Cu-0.015Mg
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474
474
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