Integral ceramic matrix composite fastener with polymer rigidization

Patent metadata

Field	Value
Publication number	US-10371011-B2
Application number	US-201514686842-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	May 8, 2014
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

First claim

The invention claimed is:

1. A method of forming an integral fastener for a ceramic matrix composite component comprising the steps of:
(a) forming a fiber preform;
(b) applying a polymer material to the fiber perform to form a rigid perform structure;
(c) machining an opening in the rigid preform structure;
(d) forming a fiber fastener;
(e) inserting the fiber fastener into the opening;
(f) removing the polymer material;
(g) infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener; and
wherein step (f) includes oxidizing the polymer material from the rigid preform structure prior to step (g).

2. The method according to claim 1 wherein step (g) includes using a chemical vapour infiltration process.

3. The method according to claim 1 wherein step (a) includes forming the preform to be a gas turbine engine component, and wherein step (g) includes integrally forming the fastener and ceramic matrix composite component to provide a single-piece gas turbine engine component and fastener without any gaps between a head of the fastener and the ceramic matrix composite component.

4. The method according to claim 1 Wherein step (a) is accomplished using at least one of the following methods: two dimensional fabric lay-up, three dimensional weaving, knotting, or braiding.

5. The method according to claim 1 wherein step (c) includes machining the opening to be wider at one surface of the ceramic matrix composite component than at an opposite surface to accommodate a head of the fastener formed in step (d).

6. The method according to claim 1 wherein step (d) includes weaving the fastener from fibers.

7. The method according to claim 1 wherein
step (a) includes forming the preform to be a gas turbine engine component,
step (d) includes forming the fastener to include a head portion and a foot portion,
step (c) includes forming the opening to be wider at one surface such that the head portion does not fall through the opening during step (e), and
(h) machining the foot portion of the fastener to receive a connecting structure subsequent to step (g) such that the fastener can be used to attach the gas turbine engine component to an engine support structure when the connecting structure is installed on the foot portion.

8. The method according to claim 1 wherein step (d) includes forming the fastener from a ceramic matrix composite fiber material comprising a two-dimensional fabric lay-up.

9. The method according to claim 1 including forming the ceramic matrix composite component and integral fastener as a monolithic structure.

10. The method according to claim 1 wherein step (f) includes having fibers from the rigid preform structure spreading into a weave of the fiber fastener prior to step (g).

11. The method according to claim 10 including infiltrating the matrix material into the fibers of the rigid preform structure and the weave of the fiber fastener to form the ceramic matrix composite component with the integral fastener.

12. The method according to claim 11 including forming the ceramic matrix composite component as a nozzle liner to be connected to an underlying engine support structure with the integral fastener.

13. A method of forming an integral fastener for a ceramic matrix composite component comprising the steps of:
(a) forming a fiber preform;
(b) rigidizing the preform with a polymer based material to provide a rigid preform structure;
(c) machining an opening in the rigid preform structure;
(d) weaving a fiber fastener;
(e) inserting the fiber fastener into the opening;
(f) oxidizing the rigid perform structure to remove the polymer based material; and
(g) infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener.

14. The method according to claim 13 wherein step (g) includes using a chemical vapour infiltration process, polymer impregnation pyrolysis process, a slurry impregnation process, and / or a glass transfer molding process.

15. The method according to claim 13 wherein
step (d) includes forming the fiber fastener to have a head portion and a foot portion that has a smaller width than the head portion,
step (c) includes machining the opening to be wider at one surface of the ceramic matrix composite component than at an opposite surface to accommodate the head portion formed in step (d), and
(h) machining the foot portion of the fiber fastener to receive a connecting structure subsequent to step (g).

16. The method according to claim 13 including forming the fiber preform as a gas turbine engine component.

17. The method according to claim 13 including forming the ceramic matrix composite component and integral fastener as a monolithic structure.

18. The method according to claim 13 wherein step (f) includes having fibers from the rigid preform structure spreading into a weave of the fiber fastener prior to step (g).

19. The method according to claim 18 including infiltrating the matrix material into the fibers of the rigid preform structure and the weave of the fiber fastener to form the ceramic matrix composite component with the integral fastener.

20. The method according to claim 19 including forming the ceramic matrix composite component as a nozzle liner to be connected to an underlying engine support structure with the integral fastener.

21. The method according to claim 19 wherein
step (d) includes forming the fiber fastener to have a head portion and a foot portion that has a smaller width than the head portion,
step (c) includes machining the opening to provide an enlarged recess starting at one surface of rigid preform structure that transitions into a narrowing portion at an opposite surface of rigid preform structure,
step (e) includes positioning the head portion within the enlarged recess and the foot portion within the narrowing portion, and
including infiltrating the matrix material into the rigid preform structure and into the fiber fastener such that the ceramic matrix composite component and fastener comprise a monolithic structure without any gaps between the fiber fastener and the ceramic matrix composite component.

Assignees

• United Technologies Corp

Inventors

• Jarmon David C

Classifications

• C04B35/638

  Removal thereof · CPC title

• D03D25/005

  Three-dimensional woven fabrics · CPC title

• F23M2900/05004

  Special materials for walls or lining · CPC title

• C04B2237/385

  Carbon or carbon composite · CPC title

• C04B2235/5248

  Carbon, e.g. graphite · CPC title