초록 ▼

In accordance with an embodiment of the invention, an article is disclosed. The article comprises a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, an

In accordance with an embodiment of the invention, an article is disclosed. The article comprises a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, and the cerium oxide reduces formation of silicate glass on the substrate upon exposure to corrodant sulfates.

대표청구항 ▼

What is claimed is: 1. An article comprising: a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, and the cerium oxide reduces formation of silicate gl

What is claimed is: 1. An article comprising: a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, and the cerium oxide reduces formation of silicate glass on the substrate upon exposure to corrodant sulfates. 2. The article of claim 1, wherein the environmental barrier coating comprises a multi-layer system comprising: a bond layer comprising a silicon material and overlying the substrate; a first layer comprising mullite and overlying the bond layer; a second layer comprising barium strontium aluminosilicate and overlying the first layer; a third layer consisting of the cerium oxide and overlying the second layer. 3. The article of claim 2, wherein the first layer comprises mullite-barium strontium aluminosilicate in an amount between about 40 to 80 weight percent mullite and about 20 to 60 weight percent barium strontium aluminosilicate. 4. The article of claim 3, wherein the bond layer has a thickness between about 12.5 and 250 micrometers, the first layer has a thickness between about 25 and 250 micrometers, the second layer has a thickness between about 25 and 500 micrometers, and the third layer has a thickness of about 5 to about 75 micrometers. 5. The article of claim 4 further comprising a thermal barrier coating overlying the third layer. 6. The article of claim 2, further comprising a rare earth silicate in the environmental barrier coating. 7. The article of claim 1, wherein the substrate is formed of a material selected from the group consisting of metal matrix composites reinforced with at least one of silicon carbide, silicon nitride and silicon; composites having a matrix of at least one of silicon carbide, silicon nitride and silicon; and composites with at least one of a silicon carbide, silicon carbide matrix reinforced with at least one of silicon carbide, silicon nitride, silicon aluminum oxynitride and silicon; and metal silicides. 8. The article of claim 7, wherein the substrate is a composite comprising a silicon based matrix and a reinforcing particle. 9. The article of claim 8, wherein the substrate is selected from the group consisting of a silicon carbide fiber-reinforced silicon carbide matrix, a carbon fiber-reinforced silicon carbide matrix and a silicon carbide fiber-reinforced silicon nitride. 10. The article of claim 1 wherein the substrate is a silicon comprising metal alloy selected from the group consisting of molybdenum-silicon alloys, niobium silicon alloys, iron-silicon alloys and iron-nickel-silicon based alloys. 11. The article of claim 1, wherein the environmental barrier coating further comprises a rare earth silicate. 12. The article of claim 11, wherein the environmental barrier coating further comprises barium strontium aluminosilicate. 13. The article of claim 1, wherein the substrate is selected from the group consisting of a silicon comprising ceramic and metal alloy comprising silicon. 14. A gas turbine engine component comprising: a substrate of the gas turbine engine component comprising a silicon material; and at least one layer on the substrate selected from the group consisting of: i) a layer comprising barium strontium aluminosilicate and cerium oxide, and ii) a dual layer of barium strontium aluminosilicate and a layer consisting of cerium oxide overlying the barium strontium aluminosilicate; wherein the cerium oxide reduces formation of silicate glass on the substrate. 15. A gas turbine engine component comprising: a substrate of the gas turbine engine component comprising a silicon material; cerium oxide deposited directly on the substrate or admixed with the silicon material of the substrate, wherein the cerium oxide reduces formation of silicate glass on the substrate upon exposure to corrodant sulfates.