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US 6,554,920 B1Granted
High-temperature alloy and articles made therefrom
AssigneeGeneral Electric Company
InventorsMelvin Robert Jackson, Canan Uslu Hardwicke, Ji-Cheng Zhao, Charles Gitahi Mukira
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Abstract
An alloy and repair material comprising the alloy, articles comprising the alloy and repair material, and methods for repairing articles including provision of the alloy as repair material are described, with the alloy comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of the alloy is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
Claims58
An alloy comprising:
- ruthenium, nickel, aluminum, and chromium;
- wherein a microstructure of said alloy is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
An alloy consisting essentially of:
- ruthenium, in an amount ranging from about 20 atomic percent to about 40 atomic percent;
- chromium, in an amount ranging from about 10 atomic percent to about 28 atomic percent;
- aluminum, in an amount ranging from about 12 atomic percent to about 24 atomic percent;
- up to about 1.5 atomic percent of a metal selected from the group consisting of zirconium, tantalum, hafnium, niobium, yttrium, molybdenum, and mixtures thereof;
- up to about 10 atomic percent of a metal selected from the group consisting of platinum, palladium, rhodium, and mixtures thereof;
- and
- the balance nickel, wherein said nickel is present in an amount of at least about 30 atomic percent;
- wherein a microstructure of said alloy is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and from about 15 volume percent to about 40 volume percent of a B2-structured phase.
5 more elements
An alloy comprising:
- about 22 atomic percent ruthenium;
- about 25 atomic percent chromium;
- about 15 atomic percent aluminum;
- about 0.2 atomic percent zirconium;
- and
- the balance comprising nickel;
- wherein a microstructure of said alloy is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and from about 15 volume percent to about 40 volume percent of a B2-structured phase.
4 more elements
A gas turbine engine component comprising:
- an alloy comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of said alloy of said component is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
A gas turbine engine component comprising:
- an alloy comprising about 22 atomic percent ruthenium, about 25 atomic percent chromium, about 15 atomic percent aluminum, about 0.2 atomic percent zirconium, and the balance comprising nickel, wherein a microstructure of said alloy of said engine component is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and from about 15 volume percent to about 40 volume percent of a B2-structured phase.
A repair material for repairing superalloy articles, said repair material comprising:
- ruthenium, nickel, aluminum, and chromium,
- wherein a microstructure of said repair material is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
A repair material for repairing superalloy articles, said repair material consisting essentially of:
- ruthenium, in an amount ranging from about 20 atomic percent to about 40 atomic percent;
- chromium, in an amount ranging from about 10 atomic percent to about 28 atomic percent;
- aluminum, in an amount ranging from about 12 atomic percent to about 24 atomic percent;
- up to about 1.5 atomic percent of a metal selected from the group consisting of zirconium, tantalum, hafnium,,niobium, yttrium, molybdenum, and mixtures thereof;
- and
- up to about 10 atomic percent of a metal selected from the group consisting of platinum, palladium, rhodium, and mixtures thereof;
- and
- the balance nickel, wherein said nickel is present in an amount of at least about 30 atomic percent;
- wherein a microstructure of said repair material is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
6 more elements
A repair material for repairing superalloy articles, said repair material comprising:
- about 22 atomic percent ruthenium;
- about 25 atomic percent chromium;
- about 15 atomic percent aluminum;
- about 0.2 atomic percent zirconium;
- and
- the balance comprising nickel;
- wherein a microstructure of said repair is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
4 more elements
A repaired gas turbine engine component comprising:
- a repair material comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of said repair material of said engine component is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.
A repaired gas turbine engine component comprising:
- a repair material comprising about 22 atomic percent ruthenium, about 25 atomic percent chromium, about 15 atomic percent aluminum, about 0.2 atomic percent zirconium, and the balance comprising nickel, wherein a microstructure of said repair material of said engine component is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and from about 15 volume percent to about 40 volume percent of a B2-structured phase.
A method for repairing a gas turbine engine component, said method comprising:
- providing a repair material, said repair material comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of said repair material is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase;
- and
- joining said repair material to said gas turbine engine component.
A method of repairing a gas turbine engine component, said method comprising:
- providing a repair material, the repair material comprising about 22 atomic percent ruthenium, about 25 atomic percent chromium, about 15 atomic percent aluminum, about 0.2 atomic percent zirconium, and the balance comprising nickel, wherein a microstructure of said repair material is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and from about 15 volume percent to about 40 volume percent of a B2-structured phase;
- and
- joining said repair material to at least one of a leading edge section, a trailing edge section, and a tip section of an airfoil of said gas turbine engine component.
Dependencies are inferred from the claim text.