Integral ceramic matrix composite fastener with polymer rigidization

Patent metadata

Field	Value
Publication number	US-11370714-B2
Application number	US-201816124303-A
Country	US
Kind code	B2
Filing date	Sep 7, 2018
Priority date	May 8, 2014
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

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 gas turbine engine component comprising:
a gas turbine engine component body formed of a first material comprising a ceramic matrix composite material, and wherein the gas turbine engine component body comprises a first woven structure;
at least one fastener comprising a fastener body extending from a head portion to a foot portion, wherein the fastener body is comprised of a second woven structure that is woven separate from the first woven structure, and wherein the head portion is defined by a first dimension and the foot portion is defined by a second dimension that is less than the first dimension;
the at least one fastener at least partially received within the gas turbine engine component body such that the head portion is flush with an outer surface of 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;
the 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 comprises a rigidized preform structure formed from a polymer based material that is oxidized out of the rigid preform structure; 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 ceramic matrix composite component and the at least one fastener are a monolithic structure.

3. The gas turbine engine component according to claim 1 wherein the foot portion extends beyond an opposite outer surface of the gas turbine engine component body such that there are no gaps or openings between the head portion of the second woven structure and the first woven structure.

4. The gas turbine engine component according to claim 1 including an environmental barrier coating applied to the gas turbine engine component body.

5. The gas turbine engine component according to claim 1 wherein the second woven structure comprises a 2-D fabric lay-up or a 3-D weaving that is configured to provide a rigidized, oxidized preform structure, and wherein the first woven structure comprises a braided body.

6. 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.

7. The gas turbine engine component according to claim 6 wherein the engine support structure comprises a metal plate.

8. The gas turbine engine component according to claim 1 wherein the fastener body is comprised of a woven fiber material to provide a woven fastener that is woven from fibers to provide the fastener weave, and wherein fibers from the rigidized preform structure extend into the fastener weave of the woven fastener such that the fibers bridge the fastener/component interface.

9. The gas turbine engine component according to claim 8 wherein the foot portion comprises a machined surface and including a connecting structure that is received on the machined surface.

10. The gas turbine engine component according to claim 9 wherein the single-piece structure comprises the gas turbine engine component body and an attachment extension portion extending outwardly from the opposite side of the gas turbine engine component body to terminate at the foot portion which receives the connecting structure.

11. The gas turbine engine component according to claim 1 wherein the rigidized preform structure receives the at least one fastener, and wherein the second woven structure is formed from a woven fiber material that is infiltrated with a matrix material to form the single-piece structure as a finished component product.

12. The gas turbine engine component according to claim 11 wherein the single-piece structure that forms the finished component product does not include the polymer based material.

13. The gas turbine engine component according to claim 11 wherein the rigid perform structure is oxidized to remove the polymer based material prior to being infiltrated with the matrix material.

14. The gas turbine engine component according to claim 11 wherein the fibers from the first woven structure spread into the fastener weave of the second woven structure prior to being infiltrated with the matrix material.

15. The gas turbine engine component according to claim 14 wherein the matrix material is infiltrated into the fibers of the first woven structure and the fastener weave of the second woven structure to form the ceramic matrix composite component with the fastener body as a monolithic structure.

16. The gas turbine engine component according to claim 15 wherein the ceramic matrix composite component comprises a nozzle liner connected to the engine support structure with the fastener.

17. A gas turbine engine component comprising:
a gas turbine engine component body formed of a ceramic matrix composite material, and wherein the gas turbine engine component body comprises a first woven structure;
at least one fastener comprising a fastener body extending from a head portion to a foot portion, wherein the fastener body is a second woven structure that is woven separate from the first woven structure, and wherein the head portion is defined by a first dimension and the foot portion is defined by a second dimension that is less than the first dimension;
the gas turbine engine component body receiving the at least one fastener such that the head portion is flush with an outer surface of 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
wherein the first woven structure is infiltrated with a matrix material such that the at least one fastener is integrally formed with the gas turbine engine component body as a single-piece structure without any gaps between the head portion of the at least one fastener and the first woven structure; and
an engine support structure, wherein the at least one fastener connects the gas turbine engine component body to the engine support structure.

18. The gas turbine engine component according to claim 17 wherein the second woven structure comprises a woven fastener that is formed from a woven fiber material, and wherein the foot portion of the woven fastener extends beyond an opposite outer surface of the gas turbine engine component body that is infiltrated with the matrix material to form the single-piece structure as a finished component product, and wherein the second woven structure comprises a braided body and the first woven structure comprises a 2-D fabric lay-up or a 3-D weaving.

19. The gas turbine engine component according to claim 17 wherein the at least one fastener comprises a woven fastener that is woven from fibers to provide the fastener weave, and wherein fibers from the first woven structure extend into the fastener weave of the woven fastener such that the fibers bridge the fastener/component interface.

20. A gas turbine engine component comprising:
a gas turbine engine component body formed of a ceramic matrix composite material;
at least one fastener comprising a fastener body extending from a head portion to a foot portion, wherein the fastener body is a first woven structure comprised of a woven fiber material, and wherein the head portion is defined by a first dimens

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Jarmon David C

Classifications

• C04B37/001

  directly with other burned ceramic articles · 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

• C04B35/634

  Polymers (C04B35/636 takes precedence) · CPC title

• C04B35/573

  obtained by reaction sintering {or recrystallisation} · CPC title

• F02C7/28

  Arrangement of seals · CPC title