Nickel-based heat resistant alloy for gas turbine combustor
View Patent ↗A Ni-based heat resistant alloy for a gas turbine combustor, comprising a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, C: 0.03 to 0.15%, and a balance consisting of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.015% or less, and P: 0.015% or less, wherein the alloy has a texture in which M 6 C type carbide and MC type carbide are uniformly dispersed in γ phase matrix.
1. A Ni-based heat resistant alloy for a gas turbine combustor, having a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, and C: 0.03 to 0.15%, with a balance being Ni and unavoidable impurities,
wherein contents of S and P contained in the unavoidable impurities are controlled to be in mass %, S: 0.015% or less, and P: 0.015% or less,
wherein the alloy has a texture in which M 6 C carbide and MC carbide are uniformly dispersed in γ phase matrix,
wherein the M in the M 6 C carbide has a composition containing, in mass %, Ni: 12.0 to 45.0%, Cr: 9.0 to 22.0%, Co: 0.5 to 13.5%, W: 2.0 to 24.0%, Al: 5.0% or less, and Ti: 0.5 to 6.0%, with a balance being Mo and unavoidable impurities, and
wherein the M in the MC carbide has a composition containing, in mass %, Ni: 7.0% or less, Cr: 6.0% or less, Co: 12.0% or less, Mo: 57.0% or less, W: 15% or less, and Al: 6.0% or less, with a balance being Ti and unavoidable impurities.
2. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 1 ,
wherein the M 6 C carbide and the MC carbide each have an average grain diameter of 0.3 to 4.0 μm, and the M 6 C carbide and the MC carbide are uniformly dispersed in the matrix at a total proportion of 0.5 to 16.0 area %.
3. The member for a liner of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 1 .
4. The member for a transition piece of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 1 .
5. The liner of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 1 .
6. The transition piece of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 1 .
7. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 1 ,
wherein aging treatment is performed on the alloy by retaining the alloy at a temperature of 650 to 900° C. for 12 to 48 hours.
8. A Ni-based heat resistant alloy for a gas turbine combustor, having a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, Nb: 0.1 to 1.0%, B: 0.001 to 0.020%, and C: 0.03 to 0.15%, with a balance being Ni and unavoidable impurities,
wherein contents of S and P contained in the unavoidable impurities are controlled to be, in mass %, S: 0.015% or less, and P: 0.015% or less, and
wherein the alloy has a texture in which M 6 C carbide and MC carbide are uniformly dispersed in γ phase matrix,
wherein the M in the M 6 C carbide has a composition containing, in mass %, Ni: 12.0 to 45.0%, Cr: 9.0 to 22.0%, Co: 0.5 to 13.5%, W: 2.0 to 24.0%, Al: 5.0% or less, Ti: 0.5 to 6.0%, and Nb: 1.0% or less, with a balance being Mo and unavoidable impurities, and
wherein the M in the MC carbide has a composition containing, in mass %, Ni: 7.0% or less, Cr: 6.0% or less, Co: 12.0% or less, Mo: 57.0% or less, W: 15% or less, Nb: 65% or less, and Al: 6.0% or less, with a balance being Ti and unavoidable impurities.
9. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 8 ,
wherein the M 6 C carbide and the MC carbide each have an average grain diameter of 0.3 to 4.0 μm, and the M 6 C carbide and the MC carbide are uniformly dispersed in the matrix at a total proportion of 0.5 to 16.0 area %.
10. The member for a liner of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 8 .
11. The member for a transition piece of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 8 .
12. The liner of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 8 .
13. The transition piece of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 8 .
14. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 8 ,
wherein aging treatment is performed on the alloy by retaining the alloy at a temperature of 650 to 900° C. for 12 to 48 hours.
15. A Ni-based heat resistant alloy for a gas-turbine combustor, having a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, and C: 0.03 to 0.15%, with a balance being Ni and unavoidable impurities,
wherein contents of S and P contained in the unavoidable impurities are controlled to be, in mass %, S: 0.015% or less; P: 0.015% or less,
wherein the alloy has a texture in which M 6 C carbide and MC carbide are uniformly dispersed in matrix comprising a mixed phase of γphase and γ′ phase,
wherein the M in the M 6 C carbide has a composition containing, in mass %, Ni: 12.0 to 45.0%, Cr: 9.0 to 22.0%, Co: 0.5 to 13.5%, W: 2.0 to 24.0%, Al: 5.0% or less, and Ti: 0.5 to 6.0%, with a balance being Mo and unavoidable impurities, and
wherein the M in the MC carbide has a composition containing, in mass %, Ni: 7.0% or less, Cr: 6.0% or less, Co: 12.0% or less, Mo: 57.0% or less, W: 15% or less, and Al: 6.0% or less, with a balance being Ti and unavoidable impurities.
16. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 15 , wherein the M 6 C carbide and the MC carbide each have an average grain diameter of 0.3 to 4.0 μm, and the M 6 C carbide and the MC carbide are uniformly dispersed in the matrix at a total proportion of 0.5 to 16.0 area %.
17. The member for a liner of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 15 .
18. The member for a transition piece of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 15 .
19. The liner of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 15 .
20. The transition piece of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 15 .
21. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 15 ,
wherein aging treatment is performed on the alloy by retaining the alloy at a temperature of 650 to 900° C. for 12 to 48 hours.
22. A Ni-based heat resistant alloy for a gas-turbine combustor, having a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, Nb: 0.1 to 1.0%, B: 0.001 to 0.020%, and C: 0.03 to 0.15%, with a balance being Ni and unavoidable impurities,
wherein contents of S and P contained in the unavoidable impurities are controlled, in mass %, S: 0.015% or less; P: 0.015% or less,
wherein the alloy has a texture in which M 6 C carbide and MC carbide are uniformly dispersed in matrix comprising a mixed phase of γ phase and γ′ phase,
wherein the M in the M 6 C carbide has a composition containing, in mass %, Ni: 12.0 to 45.0%, Cr: 9.0 to 22.0%, Co: 0.5 to 13.5%, W: 2.0 to 24.0%, Al: 5.0% or less, Ti: 0.5 to 6.0%, and Nb: 1.0% or less, with a balance being Mo and unavoidable impurities, and
wherein the M in the MC carbide has a composition containing, in mass %, Ni: 7.0% or less, Cr: 6.0% or less, Co: 12.0% or less, Mo: 57.0% or less, W: 15% or less, Nb: 65% or less, and Al: 6.0% or less, with a balance being Ti and unavoidable impurities.
23. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 22 , wherein the M 6 C carbide and the MC carbide each have an average grain diameter of 0.3 to 4.0 μm, and the M 6 C carbide and the MC carbide are uniformly dispersed in the matrix at a total proportion of 0.5 to 16.0 area %.
24. The member for a liner of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 22 .
25. The member for a transition piece of a gas-turbine combustor, made of a Ni-based heat resistant alloy according to claim 22 .
26. The liner of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 22 .
27. The transition piece of a gas turbine combustor, being constituted of a Ni-based heat resistant alloy according to claim 22 .
28. The Ni-based heat resistant alloy for a gas-turbine combustor according to claim 22 ,
wherein aging treatment is performed on the alloy by retaining the alloy at a temperature of 650 to 900° C. for 12 to 48 hours.