Integral ceramic matrix composite fastener with polymer rigidization

Patent metadata

Field	Value
Publication number	US-12024474-B2
Application number	US-202217850430-A
Country	US
Kind code	B2
Filing date	Jun 27, 2022
Priority date	May 8, 2014
Publication date	Jul 2, 2024
Grant date	Jul 2, 2024

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

The invention claimed is:

1. A method of forming an integral fastener for a ceramic matrix composite component comprising the steps of:
forming a gas turbine engine component body of a first material comprising a ceramic matrix composite material, and wherein the gas turbine engine component body comprises a first woven structure;
forming a fastener body of a second woven structure that is woven separate from the first woven structure;
inserting the fastener body at least partially within the gas turbine engine component body, wherein fibers from the first woven structure extend into a fastener weave of the second woven structure such that the fibers bridge a fastener/component interface; and
integrally forming the fastener body with the gas turbine engine component body as a single-piece structure, wherein the gas turbine engine component body comprises a rigidized preform structure formed from a polymer based material that is oxidized out of the rigid preform structure to allow the fibers to bridge the fastener component interface.

2. The method according to claim 1 , including forming the fastener body to extend from a first end to a second end, the fastener body defined by a first dimension and having an enlarged head at the first end of the fastener body that is defined by a second dimension that is greater than the first dimension.

3. The method according to claim 1 , including forming the gas turbine engine component body as one of a combustion liner or nozzle seal.

Assignees

• Rtx Corp

Inventors

• Jarmon David C

Classifications

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2230/314

  by chemical vapour deposition · CPC title

• F05D2230/10

  by removing material · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title