초록 ▼

A protected article includes a substrate having a substrate surface and made of a substrate nickel-base superalloy that is susceptible to the formation of a secondary reaction zone, as when contacted by an aluminum-containing layer having more than about 20 percent by weight aluminum. A protective l

A protected article includes a substrate having a substrate surface and made of a substrate nickel-base superalloy that is susceptible to the formation of a secondary reaction zone, as when contacted by an aluminum-containing layer having more than about 20 percent by weight aluminum. A protective layer contacts the substrate surface. The protective layer is of a different composition than the substrate and is made of a protective-layer nickel-base superalloy having from about 7 to about 12 percent by weight aluminum. Preferably, a thermal barrier coating system including a ceramic layer overlies and contacts the protective layer.

대표청구항 ▼

1. A protected article comprising:a substrate having a substrate surface and made of a substrate nickel-base superalloy that is susceptible to the formation of a secondary reaction zone when contacted by an aluminum-containing layer having more than about 20 percent by weight aluminum; and a protect

1. A protected article comprising:a substrate having a substrate surface and made of a substrate nickel-base superalloy that is susceptible to the formation of a secondary reaction zone when contacted by an aluminum-containing layer having more than about 20 percent by weight aluminum; and a protective layer contacting the substrate surface, wherein the protective layer is of a different composition than the substrate and is made of a protective-layer nickel-base superalloy having from about 7 to about 12 percent by weight aluminum. 2. The protected article of claim 1, wherein the substrate has a shape of a component of a gas turbine engine.3. The protected article of claim 1, wherein the substrate has a shape selected from the group consisting of a turbine blade and a turbine vane.4. The protected article of claim 1, wherein the substrate has a nominal composition, in weight percent, of about 16.5 percent cobalt, 2 percent chromium, 5.55 percent aluminum, 8.25 percent tantalum, 6 percent tungsten, 5.95 percent rhenium, 3 percent ruthenium, 2 percent molybdenum, 0.03 percent carbon, 0.15 percent hafnium, 0.004 percent boron, 0.01 percent yttrium, balance nickel and minor elements.5. The protected article of claim 1, wherein the protective layer has a nominal composition in weight percent of about 3.1 percent cobalt, about 7.6 percent chromium, about 0.1 percent maximum molybdenum, about 3.85 percent tungsten, about 0.02 percent maximum titanium, about 1.65 percent rhenium, about 0.55 percent silicon, about 5.45 percent tantalum, about 7.8 percent aluminum, about 0.15 percent hafnium, about 0.02 percent carbon, balance nickel and minor elements.6. The protected article of claim 1, wherein the protective layer has a thickness of from about 0.0005 to about 0.004 inch.7. The protected article of claim 1, further includinga thermal barrier coating system overlying and contacting the protective layer, wherein the thermal barrier coating system comprises a ceramic layer. 8. The protected article of claim 7, wherein the thermal barrier coating system comprisesa bond coat layer contacting the protective layer. 9. The protected article of claim 7, wherein the thermal barrier coating system comprisesa bond coat layer contacting the protective layer, and the ceramic layer overlying and contacting the bond coat layer. 10. The protected article of claim 1, further includingan aluminum-containing coating overlying and contacting the protective layer. 11. A protected article comprising:a substrate having a shape of a component of a gas turbine engine and a substrate surface, and made of a nickel-base superalloy that is susceptible to the formation of a secondary reaction zone, and having a nominal composition, in weight percent, of about 16.5 percent cobalt, 2 percent chromium, 5.55 percent aluminum, 8.25 percent tantalum, 6 percent tungsten, 5.95 percent rhenium, 3 percent ruthenium, 2 percent molybdenum, 0.03 percent carbon, 0.15 percent hafnium, 0.004 percent boron, 0.01 percent yttrium, balance nickel and minor elements; a protective layer contacting the substrate surface wherein the protective layer is made of a nickel-base superalloy that is not susceptible to the formation of a secondary reaction zone, and having a nominal composition in weight percent of about 3.1 percent cobalt, about 7.6 percent chromium, about 0.1 percent maximum molybdenum, about 3.85 percent tungsten, about 0.02 percent maximum titanium, about 1.65 percent rhenium, about 0.55 percent silicon, about 5.45 percent tantalum, about 7.8 percent aluminum, about 0.15 percent hafnium, about 0.02 percent carbon, balance nickel and minor elements; and a thermal barrier coating system overlying and contacting the protective layer, wherein the thermal barrier coating system comprises a ceramic layer. 12. The protected article of claim 11, wherein the substrate has a shape selected from the group consisting of a turbine blade and a turbine vane.13. The protected article of claim 11, wherein the protective layer has a thickness of from about 0.0005 to about 0.004 inch.14. The protected article of claim 11, wherein the thermal barrier coating system comprisesa bond coat layer contacting the protective layer, and the ceramic layer overlying and contacting the bond coat layer. 15. The protected article of claim 11, further includingan aluminum-containing coating overlying and contacting the protective layer. 16. A protected article comprising:a substrate having a substrate surface and made of a substrate nickel-base superalloy that is susceptible to the formation of a secondary reaction zone; and a protective layer contacting the substrate surface, wherein the protective layer is of a different composition than the substrate and is made of a protective-layer nickel-base superalloy that is not susceptible to the formation of a secondary reaction zone. 17. The protected article of claim 16, wherein the substrate has a shape of a component of a gas turbine engine.18. The protected article of claim 16, further includingan aluminum-containing coating overlying and contacting the protective layer. 19. The protected article of claim 16, further includinga thermal barrier coating system overlying and contacting the protective layer, wherein the thermal barrier coating system comprises a ceramic layer. 20. The protected article of claim 19, wherein the thermal barrier coating system comprisesan aluminum-containing bond coat layer contacting the protective layer, and the ceramic layer overlying and contacting the bond coat layer.