Claims
- 1. An article, comprising:a substrate; and a coating system deposited on the substrate, the coating system including a protective layer overlying the substrate, the protective layer including an uppermost layer having a composition comprising platinum and aluminum, plus, in atomic percent, on average from about 0.14 to about 2.8 percent hafnium and from about 2.7 to about 7.0 percent silicon.
- 2. The article of claim 1, wherein the substrate is formed in the shape of a gas turbine component.
- 3. The article of claim 1, wherein the substrate is formed in the shape of a gas turbine blade.
- 4. The article of claim 1, wherein the substrate is formed in the shape of a gas turbine vane.
- 5. The article of claim 1, wherein the substrate is a nickel-base superalloy.
- 6. The article of claim 1, wherein the protective layer has a composition of from about 4 to about 15 atom percent platinum, and from about 30 to about 60 atom percent aluminum.
- 7. The article of claim 1, wherein the protective layer is from about 0.0005 to about 0.004 inch thick.
- 8. The article of claim 1, further includinga ceramic thermal barrier coating layer overlying the protective layer.
- 9. The article of claim 8, wherein the thermal barrier coating layer comprises yttria-stabilized zirconia.
- 10. The article of claim 8, wherein the thermal barrier coating layer has a thickness of from about 0.004 inches to about 0.030 inches.
- 11. The article of claim 1, wherein the atomic ratio silicon:hafnium is from about 1.7:1 to about 5.6:1.
- 12. The article of claim 1, further includinga ceramic thermal barrier coating layer overlying the protective layer.
- 13. An article, comprising:a substrate formed in the shape of a gas turbine component; and a coating system deposited on the substrate, the coating system including a protective layer overlying the substrate, the protective layer including an uppermost layer having a composition comprising platinum and aluminum, plus, in atomic percent, on average from about 0.14 to about 2.8 percent hafnium and from about 2.7 to about 7.0 percent silicon, wherein the atomic ratio silicon:hafium is from about 1.7:1 to about 5.6:1.
Parent Case Info
The invention herein described was made in the performance of work under a NASA contract and is subject to the provisions of Section 305 of the National Aeronautics and Space Act of 1958, Public Law 85-568 (72 Stat. 435; 42 USC 2457).
US Referenced Citations (7)
Foreign Referenced Citations (1)
Number |
Date |
Country |
0821078 |
Jan 1998 |
EP |