Integral ceramic matrix composite fastener with non-polymer rigidization

Patent metadata

Field	Value
Publication number	US-10538013-B2
Application number	US-201514686885-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	May 8, 2014
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform 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 with an opening that has a wide portion at one surface of the fiber preform and a narrow portion at an opposite surface of the fiber preform;
(b) forming a fiber fastener to comprise a fastener body extending from a first end to a second end, the fastener body defined by a first dimension and having an enlarged head at a first end of a fastener body that is defined by a second dimension that is greater than the first dimension;
(c) inserting the fiber fastener into the opening to form a dry fiber preform and fiber fastener assembly, wherein the fiber body extends through the fiber preform such that the enlarged head portion formed in step (b) is received within the wide portion of the opening; and
(d) infiltrating a matrix material into the dry fiber preform and fiber fastener assembly subsequent to steps (a) through (c) to form a ceramic matrix composite component with an integral fastener.

2. The method according to claim 1 including weaving a 2-D fabric for the fiber preform, cutting woven 2-D fabric into plies, cutting through each ply to form an opening, stacking the plies on top of each other with the openings aligned to form the fiber perform, inserting the fiber fastener through the aligned openings, and compressing the plies to a desired thickness.

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

4. The method according to claim 1 wherein step (a) includes weaving the fiber preform to provide a non-rigidized body, and wherein step (b) includes weaving the fiber fastener from fibers to comprise the enlarged head portion at the first end of the fastener body, and including inserting a filler material into the second end of the fastener body that is opposite the first end to expand the second end to create a fastener foot.

5. The method according to claim 1 wherein step (d) includes using a chemical vapour infiltration process, polymer impregnation pyrolysis process, a slurry impregnation process, and/or a glass transfer molding process.

6. The method according to claim 5 wherein:
the chemical vapour infiltration process is used to fabricate silicon carbide fiber reinforced silicon carbide (SiC/SiC), carbon fiber reinforced silicon carbide (C/SiC), and carbon fiber reinforced carbon (C/C);
the polymer impregnation pyrolysis process is used to fabricate silicon carbide fiber reinforced silicon carbide (SiC/SiC), carbon fiber reinforced silicon carbide (C/SiC), and carbon fiber reinforced carbon (C/C);
the slurry impregnation process is used to fabricate oxide fiber reinforced oxide (oxide/oxide) CMCs; and
the glass transfer molding process is used to fabricate carbon, silicon carbide, and/or oxide fiber reinforced glass CMCs.

7. The method according to claim 1 wherein step (d) includes integrally forming the fastener and ceramic matrix composite component as a single-piece structure without any gaps between a head of the fastener and the ceramic matrix composite component.

8. The method according to claim 7 wherein step (a) is accomplished using at least one of the following methods: two dimensional fabric lay-up, three dimensional weaving, knotting, or braiding.

9. The method according to claim 7 wherein step (b) includes weaving the fastener from fibers prior to step (c).

10. The method according to claim 1 including having fibers from the fiber preform spreading into a weave of the fiber fastener prior to step (d).

11. The method according to claim 10 including infiltrating the matrix material into the fibers of the fiber preform 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 liner to be connected to an underlying engine support structure with the integral fastener.

13. The method according to claim 1 including rigidizing the preform prior to step (c) to provide a rigid preform structure, and machining the opening in the rigid preform structure before inserting the fiber fastener into the opening.

14. The method according to claim 13 wherein rigidizing the preform includes applying a non-polymer based material to the preform.

15. The method according to claim 14 including removing the non-polymer based material from the rigid preform structure prior to step (d).

16. The method according to claim 15 wherein rigidizing the preform includes freezing the preform with water, and including drying the preform to remove any remaining water prior to step (d).

17. 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 non-polymer based material to provide a rigid preform structure;
(c) machining an opening in the rigid preform structure;
(d) forming a fiber fastener to have a head portion and a foot portion that has a smaller width than the head portion, and 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 the head portion formed in step (d);
(e) inserting the fiber fastener into the opening;
(f) removing the non-polymer based material from the rigid perform structure to form a dry fiber preform and fiber fastener assembly; and
(g) infiltrating a matrix material into the dry fiber preform and fiber fastener assembly to form a ceramic matrix composite component with an integral fastener.

18. The method according to claim 17 wherein step (d) includes weaving the fastener from fibers prior to step (e).

19. The method according to claim 17 wherein step (b) includes freezing the preform with water, and step (f) includes drying the preform to remove excess water prior to step (g).

20. The method according to claim 17 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.

21. The method according to claim 17 including
(h) machining the foot portion of the fiber fastener to receive a connecting structure subsequent to step (g).

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

23. The method according to claim 17 wherein step (a) includes weaving the fiber preform, and wherein step (d) includes weaving the fiber fastener from fibers to comprise the head portion at a first end of a fastener body, and including inserting a filler material into a second end of the fastener body that is opposite the first end to expand the end to create the foot portion.

24. The method according to claim 17 wherein step (f) includes having fibers from the rigid preform structure spreading into a weave of the fiber fastener prior to step (g).

25. The method according to claim 24 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.

26. The method according to claim 25 including forming the ceramic ma

Assignees

• United Technologies Corp

Inventors

• Jarmon David C

Classifications

• C04B2237/60

  Forming at the joining interface or in the joining layer specific reaction phases or zones, e.g. diffusion of reactive species from the interlayer to the substrate or from a substrate to the joining interface, carbide forming at the joining interface · CPC title

• C04B2237/80

  Joining the largest surface of one substrate with a smaller surface of the other substrate, e.g. butt joining or forming a T-joint · CPC title

• C04B2235/5256

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

• F05D2240/91

  on a stationary structure · CPC title

• C04B2235/5252

  having a specific pre-form · CPC title