Turbine engine components with chemical vapor infiltrated isolation layers

Patent metadata

Field	Value
Publication number	US-2016160660-A1
Application number	US-201514956849-A
Country	US
Kind code	A1
Filing date	Dec 2, 2015
Priority date	Dec 5, 2014
Publication date	Jun 9, 2016
Grant date	—

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.

First claim

What is claimed is:

1 . An assembly for use in a gas turbine engine, the assembly comprising
a ceramic matrix composite component, 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.

2 . The assembly of claim 1 , wherein the metallic component comprises a recess along a surface of the metallic component and the spacer is positioned within the recess of the metallic component.

3 . The assembly of claim 1 , wherein the metallic component comprises a chemical element that forms a eutectic with silicon.

4 . The assembly of claim 1 , wherein the spacer is a preform of fibers selected from a group consisting of a silicon carbide-silicon carbide ceramic matrix composite, an oxide-oxide ceramic matrix composite, a polymer-infiltration-pyrolysis ceramic matrix composite, or a combination thereof.

5 . The assembly of claim 1 , wherein the ceramic matrix composite comprises a preform of ceramic fibers and a ceramic layer coating the ceramic fibers.

6 . The assembly of claim 5 , wherein the ceramic fibers are silicon carbide and the ceramic layer is silicon carbide.

7 . The assembly of claim 1 , wherein the stiffness of the spacer is between about 5 msi and about 40 msi.

8 . The assembly of claim 1 , wherein the spacer has a thickness between about 0.02 inches and about 0.04 inches.

9 . The assembly of claim 1 , wherein the width of the spacer is between about 0.1 inches and about 0.15 inches.

10 . An assembly for use in a gas turbine engine, the assembly comprising
a ceramic matrix composite component, 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.

11 . The assembly of claim 10 , wherein the seal is a full segment and is in contact with the ceramic matrix composite component and the metallic component to prevent passage of cooling air between the metallic component and the ceramic matrix composite component.

12 . The assembly of claim 10 , wherein the seal is a partial segment in contact with at least one of the ceramic matrix component or the metallic component to allow a selected amount of cooling air to pass between the metallic component and the ceramic matrix composite component.

13 . The assembly of claim 10 wherein the metallic component comprises a recess along a surface of the metallic component for holding the seal.

14 . The assembly of claim 13 , wherein the metallic component comprises a chemical element that forms a eutectic with silicon.

15 . The assembly of claim 10 , wherein the seal is a preform of fibers selected from a group consisting of a silicon carbide-silicon carbide ceramic matrix composite, an oxide-oxide ceramic matrix composite, a polymer-infiltration-pyrolysis ceramic matrix composite, or any combination thereof.

16 . The assembly of claim 10 , wherein the stiffness of the seal is between about 5 msi and about 40 msi.

17 . The assembly of claim 10 , wherein the seal has a thickness between about 0.02 inches and about 0.04 inches.

18 . The assembly of claim 10 , wherein the width of the seal is between about 0.1 inches and about 0.15 inches.

19 . A method for forming a ceramic composite spacer for use in a gas turbine engine, the method comprising
forming a ceramic composite spacer comprising fibers, and the ceramic composite spacer having a porosity of between about 5 percent and about 40 percent by volume positioning a first surface of the ceramic composite spacer to contact a silicon containing ceramic matrix composite component, and positioning a second surface of the ceramic composite spacer within a recess of a metallic component.

20 . The method of claim 19 , wherein the forming the ceramic composite spacer comprises chemical vapor infiltrating silicon carbide onto a preform of silicon carbide fibers.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Shi Jun
• Shinavski Robert J

Classifications

• F05D2300/514

  Porosity · CPC title

• F01D5/3092

  Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence) · CPC title

• C04B2237/592

  whereby the interlayer is not continuous, e.g. not the whole surface of the smallest substrate is covered by the interlayer · CPC title

• C04B2237/40

  Metallic · CPC title

• C04B2237/38

  Fiber or whisker reinforced · CPC title