# US 9,518,310 B2 · Superalloys and components formed thereof

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- Number: US 9,518,310 B2
- Document ID: US9518310B2
- Status: Granted
- Kind: B2
- Application number: 13/948,463
- Filed: 2013-07-23
- Published: 2014-07-24
- Granted: 2016-12-13
- Earliest claimed: 2009-05-29
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: David Paul Mourer; Richard DiDomizio; Timothy Hanlon; Daniel Yeuching Wei; Andrew Ezekiel Wessman; Kenneth Rees Bain; Andrew Martin Powell
- Web page: https://patentgrep.com/patent/US9518310B2

## CPC

- C22C 19/056: {with the maximum Cr content being at least 10% but less than 20%}
- B22F 5/08: of toothed articles, e.g. gear wheels; of cam discs
- C22C 1/0433: {Nickel- or cobalt-based alloys}
- C22C 19/057: {with the maximum Cr content being less 10%}
- C22C 30/00: Alloys containing less than 50% by weight of each constituent
- C22F 1/10: of nickel or cobalt or alloys based thereon
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- B22F 3/15: Hot isostatic pressing
- B22F 3/20: by extruding
- B22F 2998/00: Supplementary information concerning processes or compositions relating to powder metallurgy
- C22C: ALLOYS (treatment of alloys C21D, C22F)
- B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- C22F: CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS (surface treatment of metallic material involving at least one process provided for in class C23 and at least one process covered by this subclass, C23F17/00)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)

## Abstract

A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities. The superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours.

## Claims

### Claim 1

A gamma-prime nickel-base superalloy comprises, by weight:
16.0 to 30.0% cobalt;
9.5 to 12.5% chromium;
4.0 to 6.0% tantalum;
2.0 to 4.0% aluminum;
2.0 to 3.4% titanium;
3.0 to 6.0% tungsten;
1.0 to 4.0% molybdenum;
1.5 to 3.5% niobium;
up to 1.0% hafnium;
0.02 to 0.20% carbon;
0.01 to 0.05% boron;
0.02 to 0.10% zirconium;
the balance essentially nickel and impurities;
wherein the superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours.

### Claim 2 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the chromium content is 10.0 to 12.5 weight percent.

### Claim 3 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the niobium content is 1.8 to 2.2 weight percent.

### Claim 4 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the tungsten content is 3.0 to 5.0 weight percent.

### Claim 5 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the chromium content is 10.0 to 12.5 weight percent, the niobium content is 1.8 to 2.2 weight percent, and the tungsten content is 3.0 to 5.0 weight percent.

### Claim 6 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the titanium content is 2.5 to 2.9 weight percent.

### Claim 7 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the molybdenum content is 2.5 to 3.0 weight percent.

### Claim 8 (depends on 1)

The gamma-prime nickel-base superalloy according to claim 1, wherein the gamma-prime nickel-base superalloy consists of, by weight:
16.0 to 30.0% cobalt;
9.5 to 12.5% chromium;
4.0 to 6.0% tantalum;
2.0 to 4.0% aluminum;
2.0 to 3.4% titanium;
3.0 to 6.0% tungsten;
1.0 to 4.0% molybdenum;
1.5 to 3.5% niobium;
up to 1.0% hafnium;
0.02 to 0.20% carbon;
0.01 to 0.05% boron;
0.02 to 0.10% zirconium;
the balance essentially nickel and impurities.

### Claim 9 (depends on 8)

The gamma-prime nickel-base superalloy according to claim 8, wherein the chromium content is 10.0 to 12.5 weight percent.

### Claim 10 (depends on 8)

The gamma-prime nickel-base superalloy according to claim 8, wherein the niobium content is 1.8 to 2.2 weight percent.

### Claim 11 (depends on 8)

The gamma-prime nickel-base superalloy according to claim 8, wherein the tungsten content is 3.0 to 5.0 weight percent.

### Claim 12 (depends on 8)

The gamma-prime nickel-base superalloy according to claim 8, wherein the chromium content is 10.0 to 12.5 weight percent, the niobium content is 1.8 to 2.2 weight percent, and the tungsten content is 3.0 to 5.0 weight percent.

### Claim 13 (depends on 8)

The gamma-prime nickel-base superalloy according to claim 8, wherein the titanium content is 2.5 to 2.9 weight percent and the molybdenum content is 2.5 to 3.0 weight percent.

### Claim 14 (depends on 8)

A component formed of the gamma-prime nickel-base superalloy of claim 8.

### Claim 15 (depends on 14)

The component according to claim 14, wherein the component is a powder metallurgy component chosen from the group consisting of turbine disks and compressor disks and blisks of gas turbine engines.

### Claim 16

A gamma-prime nickel-base superalloy consisting of, by weight:
17.0 to 20.5% cobalt;
10.0 to 12.5% chromium;
4.5 to 5.5% tantalum;
3.0 to 3.4% aluminum;
2.5 to 2.9% titanium;
3.0 to 5.0% tungsten;
2.5 to 3.0% molybdenum;
1.8 to 2.2% niobium;
up to 0.6% hafnium;
0.048 to 0.068% carbon;
0.015 to 0.04% boron;
0.04 to 0.06% zirconium;
the balance essentially nickel and impurities;
wherein the superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours.

### Claim 17 (depends on 16)

The gamma-prime nickel-base superalloy according to claim 16, wherein the chromium content is a maximum of 12.0 weight percent.

### Claim 18 (depends on 16)

The gamma-prime nickel-base superalloy according to claim 16, wherein the chromium content is 10.02 to 12.08 weight percent, the niobium content is 1.97 to 2.99 weight percent, and the tungsten content is 3.1 to 4.6 weight percent.

### Claim 19 (depends on 16)

A component formed of the gamma-prime nickel-base superalloy of claim 16.

### Claim 20 (depends on 19)

The component according to claim 19, wherein the component is a powder metallurgy component chosen from the group consisting of turbine disks and compressor disks and blisks of gas turbine engines.