Claims
- 1. A nickel-base single crystal superalloy having high creep rupture strength at high temperatures, said superalloy being obtained by subjecting a single crystal alloy having a composition consisting essentially of, by weight,
- Cr 4.5-10%,
- W 7.5-20%,
- Al 4.5-6%,
- Ta 2-12%,
- Co 5-10%,
- Ni substantially being the balance,
- W+Ta=17-24%,
- W+Ta+Cr=22-30%,
- to a solutionizing treatment, an air cooling treatment and an aging treatment.
- 2. The superalloy of claim 1 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 700 hours.
- 3. The superalloy of claim 1 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 900 hours.
- 4. The superalloy of claim 1 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 1200 hours.
- 5. The superalloy of claim 1 which is obtained by subjecting a single-crystal alloy having a composition consisting essentially of, by weight,
- Cr 4.5-10%,
- W 7.5-20%,
- Al 4.5-6%,
- Ta 2-12%,
- Co 5-10%,
- Ni substantially being the balance,
- W+Ta=17-24%,
- W+Ta+Cr=22-30%,
- to a solutionizing treatment at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.), an air cooling treatment to below 800.degree. C. (1472.degree. F.), and an aging treatment at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.).
- 6. The superalloy of claim 5 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 700 hours.
- 7. The superalloy of claim 5 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 900 hours.
- 8. The superalloy of claim 5 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 1200 hours.
- 9. The superalloy of claim 1 which is obtained by subjecting a singlg crystal alloy having a composition consisting essentially of, by weight,
- Cr 4.5-10%,
- W 7.5-20%,
- Al 4.5-6%,
- Ta 2-12%,
- Co 5-10%,
- Ni substantially being the balance,
- W+Ta=17-24%,
- W+Ta+Cr=22-30%,
- to a solutionizing treatment at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) 0.5 to 50 hours, an air cooling treatment to below 800.degree. C. (1472.degree. F.) within 10 minutes, and an aging treatment at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) for 1 to 100 hours.
- 10. The superalloy of claim 9 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 700 hours.
- 11. The superalloy of claim 9 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 900 hours.
- 12. The superalloy of claim 9 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 1200 hours.
- 13. The superalloy of claim 1 which is obtained by subjecting a single crystal alloy having a composition consisting essentially of, by weight,
- Cr 4.5-10%
- W 7.5-20%,
- Al 4.5-6%,
- Ta 2-12%,
- Co 5-10%,
- Ni substantially being the balance,
- W+Ta=17-24%,
- W+Ta+Cr=22-30%,
- to a solutionizing treatment at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 1 to 6 hours, an air cooling treatment to below 760.degree. C. (1400.degree. F.) within 3 minutes, and an aging treatment at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) for 3 to 48 hours.
- 14. The superalloy of claim 13 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 700 hours.
- 15. The superalloy of claim 13 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 900 hours.
- 16. The superalloy of claim 13 which has a creep rupture life, measured at a temperature of 1040.degree. C. (1904.degree. F.) under a stress of 14 kg/mm.sup.2 (19.9 Ksi), of at least 1200 hours.
- 17. A process for producing a nickel-basse single crystal superalloy, which comprises directionally solidifying a material having a composition consisting essentially of, by weight,
- Cr 4.5-10%,
- W 7.5-20%,
- Al 4.5-6%,
- Ta 2-12%,
- Co 5-10%,
- Ni substantially being the balance,
- W+Ta=17-24%,
- W+Ta+Cr=22-30%,
- to form a single crystal alloy, heating the single crystal alloy to a temperature of 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) to dissolve the gamma prime phase in the matrix gamma phase, air cooling it to below a temperature of 800.degree. C. (1472.degree. F.), and again heating it to a temperature of 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) to precipitate the gamma prime phase.
- 18. The process of claim 17 wherein the single crytal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 0.5 to 50 hours to dissolve the gamma prime phase in the matrix gamma phase, then air cooled to below 800.degree. C. (1472.degree. F.) within 10 minutes, and again heated at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) for 1 to 100 hours to precipitate the gamma prime phase.
- 19. The process of claim 17 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 0.7 to 10 hours to dissolve the gamma prime phase in the matrix gamma phase, then air cooled to below 800.degree. C. (1472.degree. F.) within 7 minutes, and again heated at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) for 2 to 72 hours to precipitate the gamma prime phase.
- 20. The process of claim 17 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 1 to 6 hours to dissolve the gamma prime phase in the matrix gamma phase, then air cooled to below 760.degree. C. (1400.degree. F.) within 3 minutes, and again heated at 760.degree. to 1100.degree. C. (1400.degree. to 2012.degree. F.) for 3 to 48 hours to precipitate the gamma prime phase.
- 21. The process of claim 17 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) to dissolve the gamma prime phase in the matrix gamma phase, air cooled to below 800.degree. C. (1472.degree. F.), further heated at 900.degree. to 1100.degree. C. (1652.degree. to 2012.degree. F.), and thereafter heated at 760.degree. to 900.degree. C. (1400.degree. to 1652.degree. F.) to precipitate the gamma prime phase.
- 22. The process of claim 21 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 0.5 to 50 hours to dissolve the gamma prime phase in the matrix gamma phase, air cooled to below 800.degree. C. (1472.degree. F.) within 10 minutes, further heated at 900.degree. to 1100.degree. C. (1652.degree. to 2012.degree. F.) for 0.5 to 30 hours, and thereafter heated at 760.degree. to 900.degree. C. (1400.degree. to 1652.degree. F.) for 0.5 to 70 hours to precipitate the gamma prime phase.
- 23. The process of claim 21 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 0.7 to 10 hours to dissolve the gamma prime phase in the matrix gamma phase, air cooled to below 800.degree. C. (1472.degree. F.) within 7 minutes, further heated at 900.degree. to 1100.degree. C. (1652.degree. to 2012.degree. F.) for 1 to 20 hours, and thereafter heated at 760.degree. to 900.degree. C. (1400.degree. to 1652.degree. F.) for 1 to 52 hours to precipitate the gamma prime phase.
- 24. The process of claim 21 wherein the single crystal alloy is heated at 1300.degree. to 1360.degree. C. (2372.degree. to 2480.degree. F.) for 1 to 6 hours to dissolve the gamma prime phase in the matrix gamma phase, air cooled to below 760.degree. C. (1400.degree. F.) within 3 minutes, further heated at 900.degree. to 1100.degree. C. (1652.degree. to 2012.degree. F.) for 1 to 10 hours, and thereafter heated at 760.degree. to 900.degree. C. (1400.degree. to 1652.degree. F.) for 2 to 38 hours to precipitate the gamma prime phase.
Priority Claims (1)
Number |
Date |
Country |
Kind |
59-31424 |
Feb 1984 |
JPX |
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Parent Case Info
This application is a continuation of now abandoned Ser. No. 704,094 filed Feb. 22, 1985.
US Referenced Citations (1)
Number |
Name |
Date |
Kind |
4116723 |
Gell et al. |
Sep 1978 |
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Continuations (1)
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Number |
Date |
Country |
Parent |
704094 |
Feb 1985 |
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