Ceramic matrix composite component and process of producing a ceramic matrix composite component

Patent metadata

Field	Value
Publication number	US-10260358-B2
Application number	US-201514926718-A
Country	US
Kind code	B2
Filing date	Oct 29, 2015
Priority date	Oct 29, 2015
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

A process of producing a ceramic matrix composite component. The process includes positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein. At least a portion of the cavity includes a terminal diameter sufficiently small to permit infiltration of a densifying material. The plurality of ceramic matrix composite plies are densified to form a densified body. The densifying results in the portion of the cavity including the terminal diameter being filled with densifying material and the cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

First claim

What is claimed is:

1. A process of producing a ceramic matrix composite component, the process comprising:
positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein, the cavity including a tapered cross-sectional geometry; and
densifying the plurality of ceramic matrix composite plies to form a densified body, the densifying resulting in a terminal portion of the cavity disposed at a tapered end of the tapered cross-sectional geometry being filled with densifying material, and an internal hollow portion of the cavity being sufficiently open to permit a flow of fluid along the cavity,
wherein the internal hollow portion of the cavity is present in the densified body, and
wherein forming the cavity includes a method selected from the group consisting of:
(a) forming a void in each of the plurality of ceramic matrix composite plies and aligning the voids in the respective ceramic matrix composite plies to at least partially define the cavity in the component, the aligning including aligning the plurality of ceramic matrix composite plies; and
(b) positioning the plurality of ceramic matrix composite plies on top of one another and then forming the cavity and the tapered cross-sectional geometry by a technique selected from the group consisting of laser drilling, electrical discharge machining, cutting and machining.

2. The process of claim 1 , wherein the cavity is entirely enclosed within the densified body.

3. The process of claim 1 , wherein the cavity is a cooling channel and the fluid is a cooling fluid.

4. The process of claim 1 , wherein the ceramic matrix composite plies are pre-impregnated ceramic matrix composite plies.

5. The process of claim 1 , wherein the forming of the cavity is by positioning the plurality of ceramic matrix composite plies on top of one another and then forming the cavity and the tapered cross-sectional geometry by the technique selected from the group consisting of laser drilling, electrical discharge machining, cutting and machining.

6. The process of claim 1 , wherein positioning the plurality of ceramic matrix composite plies on top of one another and forming the cavity therein includes forming the void in each of the plurality of ceramic matrix composite plies and aligning the voids in the respective ceramic matrix composite plies to at least partially define the cavity in the component, the aligning including aligning the plurality of ceramic matrix composite plies.

7. The process of claim 1 , wherein the densifying includes melt infiltration or chemical vapor deposition.

8. The process of claim 1 , wherein the plurality of ceramic matrix composite plies include a plurality of fibers that form a greater than 10 degree angle with respect to a center axis of the cavity.

9. The process of claim 1 , wherein the densifying material is silicon.

10. The process of claim 1 , wherein the ceramic matrix composite component is a hot gas path turbine component selected from the group consisting of a liner, a blade, a shroud, a nozzle, a combustor, a nozzle end wall, and a blade platform.

11. A ceramic matrix composite component, comprising:
a plurality of ceramic matrix composite plies forming a densified body, the plurality of ceramic matrix plies forming a cavity within the densified body, wherein:
the cavity includes a tapered cross-sectional geometry;
a terminal portion of the cavity disposed at a tapered end of the tapered cross-sectional geometry is filled with an infiltrated densifying material;
an internal hollow portion of the cavity is sufficiently open to permit a flow of fluid along the cavity, and
the cavity and the tapered cross-sectional geometry are at least partially defined by a void in each of the plurality of ceramic matrix composite plies.

12. The ceramic matrix composite component of claim 11 , wherein the cavity is entirely enclosed within the densified body.

13. The ceramic matrix composite component of claim 11 , wherein the cavity is a cooling channel and the fluid is a cooling fluid.

14. The ceramic matrix composite component of claim 11 , wherein the cavity is selected from the group consisting of a laser drilled cavity, an electrical discharge machined cavity, a cut cavity, and a machined cavity.

15. The ceramic matrix composite component of claim 11 , wherein the ceramic matrix composite component is a hot gas path turbine component selected from the group consisting of a liner, a blade, a shroud, a nozzle, a combustor, a nozzle end wall, and a blade platform.

16. The ceramic matrix composite component of claim 11 , wherein the plurality of ceramic matrix composite plies include a plurality of fibers that form a greater than 10 degree angle with respect to a center axis of the cavity.

17. The ceramic matrix composite component of claim 11 , wherein the tapered cross-sectional geometry is triangular.

18. The ceramic matrix composite component of claim 11 , wherein the tapered cross-sectional geometry is trapezoidal.

19. The process of claim 1 , wherein the tapered cross-sectional geometry is triangular.

20. The process of claim 1 , wherein the tapered cross-sectional geometry is trapezoidal.

Assignees

• Gen Electric

Inventors

• Kittleson Jacob John
• Morgan Victor John

Classifications

• B32B18/00

  Layered products essentially comprising ceramics, e.g. refractory products · CPC title

• C04B2237/365

  Silicon carbide · CPC title

• C04B35/573

  obtained by reaction sintering {or recrystallisation} · CPC title

• C04B2235/524

  Non-oxidic, e.g. borides, carbides, silicides or nitrides · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title