Claims
- 1. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, vanadium in an amount of 0.1 to 0.3% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 6000° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 2. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, tungsten in an amount of 0.1 to 3.0% by weight, vanadium in an amount of 0.1 to 0.3% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 3. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, vanadium in an amount of 0.1 to 0.3% by weight, cobalt in an amount of 0.1 to 3.0% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 4. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, tungsten in an amount of 0.1 to 3.0% by weight, vanadium in an amount of 0.1 to 0.3% by weight, cobalt in an amount of 0.1 to 3.0% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 5. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, vanadium in an amount of 0.1 to 0.3% by weight, at least one selected from the group consisting of tantalum in an amount of 0.01 to 0.15% by weight, nitrogen in an amount of 0.001 to 0.05% by weight, and boron in an amount of 0.001 to 0.015% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 6. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% % by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, tungsten in an amount of 0.1 to 3.0% by weight, vanadium in an amount of 0.1 to 0.3% by weight, at least one selected from the group consisting tantalum in an amount of 0.01 to 0.15% by weight, nitrogen in an amount of 0.001 to 0.05% by weight, and boron in an amount of 0.001 to 0.015% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.01% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 7. A high pressure and low pressure integrated turbine rotor comprising an alloy having an alloy composition comprising:carbon in an amount of 0.20 to 0.35% by weight, silicon in an amount of 0.15% by weight or less, manganese in an amount of 0.05 to 1.0% by weight, nickel in an amount of 0.3 to 1.5% by weight, chromium in an amount of 1.0 to 3.0% by weight, molybdenum in an amount of 0.5 to 1.5% by weight, tungsten in an amount of 0.1 to 3.0% by weight, vanadium in an amount of 0.1 to 0.3% by weight, cobalt in an amount of 0.1 to 3.0% by weight, at least one selected from the group consisting of tantalum in an amount of 0.01 to 0.15% by weight, nitrogen in an amount of 0.001 to 0.05% by weight, and boron in an amount of 0.001 to 0.015% by weight, phosphorus in an amount not larger than 0.012% by weight or substantially no phosphorus, sulfur in an amount not larger than 0.005% by weight or substantially no sulfur, copper in an amount not larger than 0.15% by weight or substantially no copper, aluminum in an amount not larger than 0.0% by weight or substantially no aluminum, arsenic in an amount not larger than 0.01% by weight or substantially no arsenic, tin in an amount not larger than 0.01% by weight or substantially no tin, and antimony in an amount not larger than 0.003% by weight or substantially no antimony, the balance being iron and unavoidable impurities, except that the alloy composition contains no niobium, wherein a high-pressure part of the high pressure and low pressure integrated turbine rotor has a creep rupture time of 3000 hours or longer in a creep rupture test on an unnotched test piece under conditions of temperature of 600° C. and of stress of 147 MPa, and a creep rupture time of 10000 hours or longer in a creep rupture test on a notched test piece under said conditions.
- 8. The high pressure and low pressure integrated turbine rotor as claimed in claim 1, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
- 9. The high pressure and low pressure integrated turbine rotor as claimed in claim 2, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
- 10. The high pressure and low pressure integrated turbine rotor as claimed in claim 3, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
- 11. The high pressure and low pressure integrate turbine rotor as claimed in claim 4, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
- 12. The high pressure and low pressure integrated turbine rotor as claimed in claim 5, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
- 13. The high pressure and low pressure integrated turbine rotor as claimed in claim 6, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unotched test piece under the specific conditions is 1.6 or more.
- 14. The high pressure and low pressure integrated turbine rotor as claimed in claim 7, wherein a creep embrittlement index defined by a ratio of a creep rupture time in a creep rupture test on a notched test piece to a creep rupture time in a creep rupture test on an unnotched test piece under the specific conditions is 1.6 or more.
Priority Claims (1)
Number |
Date |
Country |
Kind |
2000-031002 |
Feb 2000 |
JP |
|
Parent Case Info
This application is a divisional of case Ser. No. 09/711,530 filed Nov. 14, 2000, now U.S. Pat. No. 6,569,269B1 issued May 27, 2003.
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5611873 |
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