Claims
- 1. An article comprising:
- a substrate comprising silicon;
- a bond coat on the substrate, the bond coat comprising barium strontium aluminosilicate; and
- a top coat on the bond coat.
- 2. An article as recited in claim 1, wherein the bond coat consists essentially of barium strontium aluminosilicate.
- 3. An article as recited in claim 1, wherein the bond coat consists of barium strontium aluminosilicate.
- 4. An article as recited in claim 1, wherein the top coat is a ceramic material.
- 5. An article as recited in claim 1, wherein the top coat is formed of a material selected from the group consisting of yttria stabilized zirconia and yttrium silicate.
- 6. An article as recited in claim 1, wherein the substrate is formed of silicon carbide particles dispersed in a matrix material.
- 7. An article as recited in claim 1, wherein the substrate is formed of a composite having a silicon carbide matrix.
- 8. An article as recited in claim 1, wherein the substrate is formed of a composite having silicon carbide reinforcement in a silicon carbide matrix.
- 9. An article as recited in claim 1, wherein the bond coat has a thickness of about 25 to about 500 micrometers.
- 10. An article as recited in claim 1, wherein the article is a component of a gas turbine engine.
- 11. An article comprising:
- a substrate containing silicon carbide;
- a bond coat on the substrate, the bond coat consisting of barium strontium aluminosilicate; and
- a thermal-insulating layer overlying the bond coat.
- 12. An article as recited in claim 11, wherein the thermal-insulating layer is selected from the group consisting of yttria stabilized zirconia and yttrium silicate.
- 13. An article as recited in claim 11, wherein the substrate is formed of silicon carbide particles dispersed in a matrix material.
- 14. An article as recited in claim 11, wherein the substrate is formed of a composite having a silicon carbide matrix.
- 15. An article as recited in claim 11, wherein the substrate is formed of a composite having silicon carbide reinforcement in a silicon carbide matrix.
- 16. An article as recited in claim 11, wherein the bond coat has a thickness of about 25 to about 500 micrometers.
- 17. An article as recited in claim 1, wherein the article is a component of a gas turbine engine.
- 18. A gas turbine engine component having a coating system on a surface thereof, the component comprising:
- a substrate comprising a silicon;
- a bond coat on the substrate, the bond coat consisting of barium strontium aluminosilicate; and
- a yttria stabilized zirconia layer overlying the bond coat.
- 19. A component as recited in claim 18, wherein the bond coat has a thickness of about 25 to about 500 micrometers.
- 20. A component as recited in claim 18, wherein the substrate is formed of a material selected from the group consisting of metal matrix composites reinforced with silicon carbide, composites having a silicon carbide matrix, and silicon carbide matrix composites reinforced with silicon carbide.
Government Interests
This invention was made with Government support under Agreement No. NAS3-26385 awarded by NASA. The Government has certain rights in the invention.
US Referenced Citations (4)