Ceramic matrix composite

Patent metadata

Field	Value
Publication number	US-9726025-B2
Application number	US-201314097857-A
Country	US
Kind code	B2
Filing date	Dec 5, 2013
Priority date	Mar 15, 2013
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.

First claim

What is claimed is:

1. A ceramic matrix composite comprising:
at least one layer of non-crimped fibers positioned substantially parallel to one another;
an elastic fiber bent around the non-crimped fibers to stitch the non-crimped fibers together, wherein a diameter of the elastic fiber is less than a diameter of the non-crimped fibers; and
a ceramic matrix deposited around the at least one layer of non-crimped fibers.

2. The ceramic matrix composite of claim 1 , wherein the elastic fiber is made from one of a polymer material, acrylic material and a carbon material.

3. The ceramic matrix composite of claim 1 , wherein the elastic fiber is configured to be at least one of dissolvable or removable by heating from the non-crimped fibers prior to depositing the ceramic matrix.

4. The ceramic matrix composite of claim 1 , wherein the elastic fiber is configured to be at least one of dissolvable or removable by heating by at least one of exposure to a liquid, exposure to a gas or exposure to heat in a vacuum.

5. The ceramic matrix composite of claim 1 , wherein the non-crimped fibers comprise a monofilament having a cross sectional diameter between approximately 20 and 300 microns.

6. The ceramic matrix composite of claim 1 , further comprising:
a plurality of layers of non-crimped fibers configured into a preform core with a desired shape.

7. The ceramic matrix composite of claim 6 , wherein the plurality of layers are held in place with the elastic fiber.

8. The ceramic matrix composite of claim 6 , wherein at least one layer includes a non-crimped fiber orientation that is different from a non-crimped fiber orientation of an adjacent layer.

9. The ceramic matrix composite of claim 1 wherein the non-crimped fibers are formed from one of silicon, silicon carbide, or carbon material.

10. The ceramic matrix composite of claim 1 , wherein a finished component made from the ceramic matrix composite is operable in a gas turbine engine.

Assignees

• Rolls Royce Corp

Inventors

• Lazur Andrew Joseph

Classifications

• F01D9/02

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• C04B2235/5256

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• C04B2235/5244

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• Y10T29/49316

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• C04B2235/616

  Liquid infiltration of green bodies or pre-forms · CPC title