초록 ▼

The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for

The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.

대표청구항 ▼

What is claimed is: 1. A component for use in a heated environment comprising: a body composed of a ceramic matrix material, the body including an attachment location, the attachment location defining at least a portion of a surface of the component, and the attachment location being configured to

What is claimed is: 1. A component for use in a heated environment comprising: a body composed of a ceramic matrix material, the body including an attachment location, the attachment location defining at least a portion of a surface of the component, and the attachment location being configured to be adjacent a second component during exposure in a heated environment; and an interface layer defining at least a portion of the surface of the attachment location and having a matrix side and an outer side, wherein the interface layer is interposed between the body and the second component during exposure in the heated environment, the matrix side of the interface layer being metallurgically bonded to the body; wherein the interface layer consists of silicon and a material selected from the group consisting of silicon carbide, boron nitride, molybdenum disilicide, and alloys thereof. 2. The component of claim 1, wherein the component is a turbine engine component. 3. The component of claim 2, wherein the component is a turbine blade. 4. The component of claim 2, wherein the component is a shroud. 5. The component of claim 2, wherein the component is a combustor liner. 6. The component of claim 1, wherein the ceramic matrix material is silicon carbide. 7. The component of claim 1, wherein the interface layer is a gradient layering of silicon carbide and silicon wherein the interface layer is composed of a greater amount of silicon toward the outer side when compared to the matrix side. 8. The component of claim 1, wherein the interface layer is a gradient layering of silicon carbide, silicon, boron nitride and molybdenum disilicide wherein the interface layer is composed of a higher concentration of silicon carbide toward the matrix side when compared to the outer side. 9. The component of claim 1, wherein the outer side of the interface layer provides a surface that has a lesser degree of hardness than a surface of the body. 10. The component of claim 1, wherein the interface layer distributes operating loads between the body and the second component over a large area. 11. The composite turbine engine component of claim 1, wherein the interface layer is formed on a composite surface by chemical bonding.