Turbine engine components with chemical vapor infiltrated isolation layers
AssigneesRolls-Royce American Technologies, Inc., ROLLS-ROYCE plc
InventorsJun Shi, Robert J. Shinavski
Life of this patent
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Abstract
An assembly for use in a gas turbine engine and method for making the same are described herein. The assembly comprising a CMC component, a metallic component spaced apart from the CMC component, and a spacer. The spacer having a first surface in contact with the CMC and a second surface opposite the first surface in contact with the metallic component, the spacer comprising a CMC substantially free of silicon metal with a porosity of between about 5 percent and about 40 percent by volume to chemically isolate the CMC component from the metallic component.
Claims19
An assembly for use in a gas turbine engine, the assembly comprising
- a ceramic matrix composite component, wherein the ceramic matrix composite component comprises a preform including (1) ceramic fibers and (2) a ceramic matrix or a ceramic layer,
- a metallic component spaced apart from the ceramic matrix composite component, and
- a spacer having a first surface in contact with the ceramic matrix composite and a second surface opposite the first surface in contact with the metallic component, the spacer comprising a ceramic matrix composite substantially free of silicon metal with a porosity of between about 5 percent and about 40 percent by volume to chemically isolate the ceramic matrix composite component from the metallic component, wherein the ceramic matrix composite of the spacer comprises a preform including (1) ceramic fibers and (2) a ceramic matrix or a ceramic layer.
An assembly for use in a gas turbine engine, the assembly comprising
- a ceramic matrix composite component, wherein the ceramic matrix composite component comprises a preform including (1) ceramic fibers and (2) a ceramic matrix or a ceramic layer,
- a metallic component spaced apart from the ceramic matrix composite component,
- a seal positioned between the ceramic matrix composite component and the metallic component, the seal including a porous ceramic matrix composite to inhibit air passage between the ceramic matrix composite component and the metallic component, wherein the porous ceramic matrix composite of the seal comprises a preform including (1) ceramic fibers and (2) a ceramic matrix or a ceramic layer.
A method for forming a ceramic matrix composite spacer for use in a gas turbine engine, the method comprising
- forming a ceramic matrix composite spacer comprising (1) fibers and (2) a ceramic matrix or a ceramic layer, wherein the ceramic matrix composite spacer comprises a porosity of between about 5 percent and about 40 percent by volume, and wherein the ceramic matrix composite spacer is substantially free of silicon metal,
- positioning a first surface of the ceramic matrix composite spacer to contact a silicon containing ceramic matrix composite component, wherein the ceramic matrix composite component comprises (1) fibers and (2) a ceramic matrix or a ceramic layer, and
- positioning a second surface of the ceramic matrix composite spacer within a recess of a metallic component.
Dependencies are inferred from the claim text.