Integral Ceramic Matrix Composite Fastener With Polymer Rigidization

Patent metadata

Field	Value
Publication number	US-2019010829-A1
Application number	US-201816124303-A
Country	US
Kind code	A1
Filing date	Sep 7, 2018
Priority date	May 8, 2014
Publication date	Jan 10, 2019
Grant date	—

Abstract

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

First claim

1 . A gas turbine engine component comprising:
a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure, wherein the gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material; and an engine support structure, wherein the at least one fastener connects the gas turbine engine component body to the engine support structure.

2 . The gas turbine engine component according to claim 1 wherein the rigidized preform structure has an opening to receive the fastener, and wherein the fastener initially comprises a separate woven fastener formed from a fiber based material, and wherein the woven fastener is received within the opening of the rigidized preform and subsequently infiltrated with a matrix material to form the single-piece structure as a finished component.

3 . The gas turbine engine component according to claim 2 wherein the rigidized preform structure includes the polymer based material prior to forming the opening.

4 . The gas turbine engine component according to claim 3 wherein the single-piece structure that forms the finished component does not include the polymer based material.

5 . The gas turbine engine component according to claim 2 wherein the rigid perform structure is oxidized to remove the polymer based material prior to being infiltrated with the matrix material.

6 . The gas turbine engine component according to claim 1 wherein the fastener initially comprises a separate woven fastener formed from a fiber based material, and wherein fibers from the rigidized preform structure spread into a weave of the woven fastener prior to being infiltrated with the matrix material.

7 . The gas turbine engine component according to claim 6 wherein the matrix material is infiltrated into the fibers of the rigidized preform structure and the weave of the fiber fastener to form the ceramic matrix composite component with the fastener as a monolithic structure.

8 . The gas turbine engine component according to claim 7 wherein the ceramic matrix composite component comprises a nozzle liner connected to the engine support structure with the fastener.

9 . The gas turbine engine component according to claim 1 wherein the gas turbine engine component body comprises one of a combustion liner or nozzle seal.

10 . The gas turbine engine component according to claim 9 wherein the engine support structure comprises a metal plate.

11 . The gas turbine engine component according to claim 1 wherein the ceramic matrix composite component and the at least one fastener are a monolithic structure.

Assignees

• United Technologies Corp

Inventors

• Jarmon David C

Classifications

• C04B2237/385

  Carbon or carbon composite · CPC title

• C04B2235/5256

  Two-dimensional, e.g. woven structures · CPC title

• C04B35/634

  Polymers (C04B35/636 takes precedence) · CPC title

• C04B35/76

  Fibres, filaments, whiskers, platelets, or the like · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title