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Haynes® 282® Alloy

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Haynes® 282® Alloy HIGH-TEMPERATURE ALLOYS HAYNES® 282® ALLOY A new, wrought, age-hardenable, nickel superalloy designed for improved creep strength, weldability, and fabricability. Contents Principal Features 3 Creep and Stress-Rupture Strength 4 Strain-Age Cracking Resistance 7 Tensile Properties 8 Hardness 9 Aging Kinetics 10 Oxidation Resistance 11 Thermal Stability 13 Physical Properties 15 Low Cycle Fatigue 17 Welding 18 Heat Treatment and Fabrication 22 Health and Safety 25 Service Center Information 27 H-3173 TYPICAL APPLICATIONS HAYNES® 282® alloy is designed for applications in engines for aircraft. HAYNES® 282® alloy is designed for the transition sections and other hot-gas-path components in land-based gas turbines. HAYNES® 282® alloy 2 ©2008 Haynes International, Inc. PRINCIPAL FEATURES Excellent High Temperature Strength HAYNES® 282® alloy is a new, wrought, gamma-prime strengthened superalloy developed for high temperature structural applications, especially those in aero and land-based gas turbine engines. It possesses a unique combination of creep strength, thermal stability, weldability, and fabricability not found in currently available commercial alloys. The new alloy has excellent creep strength in the temperature range of 1200 to 1700°F (649 to 927°C), surpassing that of Waspaloy alloy, and approaching that of R-41 alloy. Easily Fabricated This high level of creep strength in HAYNES 282 alloy has been attained at a relatively low volume fraction of the strengthening gamma-prime phase, resulting in outstanding resistance to strain-age cracking (normally a problem with superalloys in this creep strength range). Additionally, slow gamma-prime precipitation kinetics allow for the alloy to have excellent ductility in the as-annealed condition. Consequently, HAYNES 282 alloy exhibits superior weldability and fabricability. Product Forms HAYNES 282 alloy is designed for use in the form of plate, sheet, strip, foil, billet, bar, wire welding products, pipe, and tubing. Heat Treatment HAYNES 282 alloy is provided in the solution-annealed condition, in which it is readily formable. The typical solution- annealing temperature is in the range of 2050 to 2100°F (1121 to 1149°C). After component fabrication, a two-step age hardening treatment is required to put the alloy into the high-strength condition. The treatment includes 1850°F (1010°C) / 2 hours / AC (air cool) + 1450°F (788°C) / 8 hours / AC. Applications The features of HAYNES 282 alloy make it suitable for critical gas turbine applications, such as sheet fabrications, seamless and flash butt-welded rings, and cases found in compressor, combustor, and turbine sections. In augmented aircraft gas turbines, the new alloy will be useful for exhaust and nozzle components. In land-based gas turbines, HAYNES 282 alloy is a good candidate for transition sections and other hot-gas-path components. Nominal Chemical Composition, Weight % Ni Cr Co Mo Ti Al Fe Mn Si C B 57** 20 10 8.5 2.1 1.5 1.5* 0.3* 0.15* 0.06 0.005 * Maximum ** Nickel as balance 3 HAYNES® 282® alloy CREEP AND STRESS-RUPTURE STRENGTH HAYNES 282 alloy possesses exceptional creep strength in the temperature range 1200-1700°F (649-927°C). For example, it has superior strength to 263 alloy at all temperatures in this range in terms of both 1% creep and rupture. Despite the exceptional fabricability of 282 alloy, it compares well to less fabricable alloys designed for high creep strength. For example, its rupture strength is equivalent to the well-known, but less fabricable, Waspaloy alloy at the lower temperatures in this range and actually has a distinct advantage at the higher end of the temperature range. In terms of 1% creep strength, 282 alloy is superior to Waspaloy alloy across the entire temperature range. At temperatures of 1500-1700°F (816-927°C), 282 alloy has creep strength equivalent to even that of R-41 alloy, an alloy designed for excellent creep strength, but notorious for poor fabricability. Creep Strength of Various Superalloys in the Temperature Range 1500-1700ºF (816-927ºC) (Sheet Products) Larson-Miller Parameter (K x 10-3, C = 20) 24 25 26 27 28 30 20 100 10 9 8 7 6 5 4 Stress (ksi) 3 282® alloy Stress (MPa) R-41 alloy 2 Waspaloy alloy 263 alloy 10 1 42 44 46 48 50 52 Larson-Miller Parameter (°R x 10-3, C = 20) HAYNES® 282® alloy 4 Comparative Creep-Rupture Properties of Gamma-Prime Strengthened Alloys* (Sheet) Test Temperature Waspaloy Property 263 Alloy R-41 Alloy 282® Alloy °F °C Alloy 1200 649 75 (517) 105 (724) 81 (558) — Stress-to-Produce 1300 704 54 (372) 75 (517) 63 (434) 72 (496) 1% Creep 1400 760 37 (255) 53 (365) 41 (283) 48 (331) in 100 h 1500 816 22 (152) 32 (221) 25 (172) 32 (221) ksi (MPa) 1600 871 11 (76) 17 (117) 15 (103) 18 (124) 1700 927 6 (41) 8 (55) 6 (41) 9 (62) 1200 649 58 (400) 84 (579) 67 (462) 79 (545) Stress-to-Produce 1300 704 41 (283) 59 (407) 46 (317) 53 (365) 1% Creep 1400 760 25 (172) 34 (234) 28 (193) 35 (241) in 1000 h 1500 816 12 (83) 18 (124) 16 (110) 21 (145) ksi (MPa) 1600 871 6 (41) 9 (62) 7 (48) 10 (69) 1700 927 3 (21) 5 (34) 3 (21) 5 (34) 1200 649 77 (531) 110 (758) 92 (634) — 1300 704 60 (414) 85 (586) 75 (517) 75 (517) Stress-to-Produce 1400 760 42 (290) 63 (434) 53 (365) 56 (386) Rupture in 100 h 1500 816 25 (172) 39 (269) 32 (221) 37 (255) ksi (MPa) 1600 871 14 (97) 23 (159) 19 (131) 22 (152) 1700 927 7 (48) 13 (90) 10 (69) 12 (83) 1200 649 64 (441) 90 (621) 80 (552) 80 (552) 1300 704 45 (310) 68 (469) 58 (400) 56 (386) Stress-to-Produce 1400 760 28 (193) 43 (296) 36 (248) 38 (262) Rupture in 1000 h 1500 816 15 (103) 24 (165) 20 (138) 23 (159) ksi (MPa) 1600 871 7 (48) 13 (90) 7 (48) 12 (83) 1700 927 4 (28) 7 (48) 3 (21) 6 (41) *Age-hardened (263 alloy: 1472°F (800°C)/8h/AC, Waspaloy alloy : 1825°F (996°C)/2h/AC + 1550°F (843°C)/4h/AC + 1400°F (760°C)/16h/AC, R-41 alloy: 1650°F (899°C)/4h/AC, 282® alloy: 1850°F (1010°C)/2h/AC + 1450°F (788°C)/8h/AC) Solution Annealed* + Age Hardened** 282® Sheet Approximate Initial Stress, ksi (MPa) Test Temperature Creep To Produce Specifi ed Creep in: °F °C 100 Hours 1,000 Hours 0.5 % — 78 (538) 1200 649 1 % — 79 (545) Rupture — 80 (552) 0.5 % 70 (483) 51 (352) 1300 704 1 % 72 (496) 53 (365) Rupture 75 (517) 56 (386) 0.5 % 46 (317) 33 (228) 1400 760 1 % 48 (331) 35 (241) Rupture 56 (386) 38 (262) 0.5 % 30 (207) 18 (124) 1500 816 1 % 32 (221) 21 (145) Rupture 37 (225) 23 (159) 0.5 % 17 (117) 9.0 (62) 1600 871 1 % 18 (124) 10 (69) Rupture 22 (152) 12 (83) 0.5 % 8.3 (57) 4.2 (29) 1700 927 1 % 9.0 (62) 5.0 (34) Rupture 12 (83) 6.0 (41) 0.5 % 3.6 (25) — 1800 982 1 % 4.2 (29) 1.8 (12) Rupture 5.5 (38) 2.5 (17) *2100°F (1149°C) **1850°F (1010°C)/2h/AC + 1450°F (788°C)/8h/AC 5 HAYNES® 282® alloy Solution Annealed* + Age Hardened** 282® Plate Approximate Initial Stress, ksi (MPa) Test Temperature Creep To Produce Specifi ed Creep in: °F °C 100 Hours 1,000 Hours 10,000 Hours 0.5 % — 81 (558) — 1200 649 1 % — 82 (565) — Rupture — 85 (586) 64 (441) 0.5 % 73 (503) 53 (365) — 1300 704 1 % 75 (517) 55 (379) — Rupture 80 (552) 61 (421) 45 (310) 0.5 % 49 (338) 35 (241) — 1400 760 1 % 50 (345) 36 (248) — Rupture 57 (393) 41 (283) 27 (186) 0.5 % 32 (221) 20 (138) — 1500 816 1 % 34 (234) 22 (152) — Rupture 38 (262) 25 (172) 14 (97) 0.5 % 18 (124) 11 (76) — 1600 871 1 % 19 (131) 12 (83) — Rupture 23 (159) 14 (97) 8 (55) 0.5 % 9.4 (65) 4.8 (33) — 1700 927 1 % 10 (69) 5.2 (36) — Rupture 13 (90) 7.0 (48) 3.7 (26) 0.5 % 4.2 (29) 1.8 (12) — 1800 982 1 % 4.6 (32) 2.0 (14) — Rupture 6.2 (43) 3.6 (25) — *2075°F (1135°C) **1850°F (1010°C)/2h/AC + 1450°F (788°C)/8h/AC HAYNES® 282® alloy 6 STRAIN-AGE CRACKING RESISTANCE Resistance to strain-age cracking is a major attribute of HAYNES 282 alloy. As indicated in the chart below, 282 alloy approaches the well-known 263 alloy in this regard, and possesses much higher resistance to strain-age cracking than other nickel superalloys in its strength class (Waspaloy and R-41 alloys). Resistance to Strain-Age Cracking as Measured by the Controlled Heating-Rate Tensile (CHRT) Test Test Temperature (°C) 760 780 800 820 840 860 40 282® alloy R-41 alloy Waspaloy alloy 30 263 alloy 20 % Elongation % 10 0 1400 1450 1500 1550 1600 Test Temperature (°F) The CHRT test is an excellent measure of the resistance of gamma-prime strengthened superalloys to strain-age cracking. Samples of thickness 0.063” (1.6 mm), originally in the solution annealed condition, are heated to the test temperature at a rate of 25-30°F (14-17°C) per minute, this being representative of a typical post-weld heat treatment. Tests are performed for each alloy over a range of temperatures.
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