MACHINABLE CMC INSERT
First Claim
1. An assembly for use in a gas turbine engine, the assembly comprisinga ceramic matrix composite component comprising silicon carbide fibers in a silicon carbide matrix,a ceramic insert adjacent to the ceramic matrix composite component, anda ply at least partially covering the ceramic insert such that the ceramic insert is sandwiched between the ply and the ceramic matrix composite component, and the ply extending beyond the ceramic insert in at least one direction so that the ply is joined to the ceramic matrix composite,wherein the ply comprises at least one layer of silicon carbide fibers or carbon fibers in a silicon carbide matrix.
1 Assignment
0 Petitions
Accused Products
Abstract
An assembly comprising a ceramic matrix composite component, a ceramic insert, and a ply and a method for producing the same. The ceramic matrix composite component may comprise silicon carbide fibers in a silicon carbide matrix. The ceramic inset may be adjacent to the ceramic matrix composite component. The ply may at least partially cover the ceramic insert such that the ceramic insert may be sandwiched between the ply and the ceramic matrix composite component, and the ply may extend beyond the ceramic insert in at least one direction so that the ply is joined to the ceramic matrix composite. The ply may comprise at least one layer of silicon carbide fibers or carbon fibers in a silicon carbide matrix.
11 Citations
20 Claims
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1. An assembly for use in a gas turbine engine, the assembly comprising
a ceramic matrix composite component comprising silicon carbide fibers in a silicon carbide matrix, a ceramic insert adjacent to the ceramic matrix composite component, and a ply at least partially covering the ceramic insert such that the ceramic insert is sandwiched between the ply and the ceramic matrix composite component, and the ply extending beyond the ceramic insert in at least one direction so that the ply is joined to the ceramic matrix composite, wherein the ply comprises at least one layer of silicon carbide fibers or carbon fibers in a silicon carbide matrix.
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11. A method of joining an insert to a ceramic matrix composite component for use in a gas turbine engine, the method comprising
providing a ceramic preform comprising silicon carbide fibers, positioning a ceramic insert adjacent to the ceramic preform, covering at least a portion of the insert and at least a portion of the ceramic preform with a ply comprising silicon carbide fibers, and co-infiltrating the ceramic preform and the ply with silicon metal or silicon alloy to form a silicon carbide matrix that extends through the ceramic preform and the ply.
Specification