Method to produce a protective surface layer having a predetermined topography on a ceramic matrix composite

Patent metadata

Field	Value
Publication number	US-11186525-B2
Application number	US-201916524397-A
Country	US
Kind code	B2
Filing date	Jul 29, 2019
Priority date	Jul 29, 2019
Publication date	Nov 30, 2021
Grant date	Nov 30, 2021

Abstract

A method to produce a protective surface layer having a predetermined topography on a ceramic matrix composite is described. The method includes applying a slurry layer to a surface of a fiber preform, and drying the slurry layer to form a particulate layer. A surface of the particulate layer is machined to improve surface smoothness and to form a machined surface. A ceramic tape is attached to the machined surface, and a tool comprising one or more features to be imprinted is placed on the ceramic tape, thereby forming a compression assembly. Heat and pressure are applied to the compression assembly to consolidate and bond the ceramic tape to the machined surface, while the one or more features of the tool are imprinted. Thus, a protective surface layer having a predetermined topography is formed.

First claim

What is claimed is:

1. A method to produce a protective surface layer having a predetermined topography on a ceramic matrix composite, the method comprising:
applying a slurry layer to a surface of a fiber preform;
drying the slurry layer to form a particulate layer;
machining a surface of the particulate layer to improve surface smoothness, thereby producing a machined surface;
attaching a ceramic tape to the machined surface;
placing a tool on the ceramic tape, the tool comprising one or more features to be imprinted, thereby forming a compression assembly; and
applying heat and pressure to the compression assembly to consolidate and bond the ceramic tape to the machined surface while the one or more features are imprinted, thereby forming a protective surface layer having a predetermined topography.

2. The method of claim 1 , wherein the fiber preform comprises a slurry-infiltrated fiber preform or a melt-infiltrated fiber preform.

3. The method of claim 2 , wherein the fiber preform comprises the slurry-infiltrated fiber preform, and further comprising, after forming the protective surface layer, infiltrating the fiber preform with a molten material and cooling, thereby forming a ceramic matrix composite having the protective surface layer.

4. The method of claim 2 , wherein the fiber preform comprises the melt-infiltrated fiber preform, and wherein the protective surface layer is formed on a ceramic matrix composite.

5. The method of claim 1 , wherein the slurry layer is applied by spraying, spin coating, dipping, or brushing.

6. The method of claim 1 , wherein the slurry layer comprises ceramic particles in a carrier liquid comprising an aqueous or organic liquid, the carrier liquid being removed upon drying.

7. The method of claim 6 , wherein the ceramic particles are selected from the group consisting of: silicon carbide particles, silicon nitride particles, and silicon nitrocarbide particles, and
wherein the slurry layer further comprises other particles selected from the group consisting of: silicon particles and carbon particles.

8. The method of claim 1 , wherein drying is carried out at room temperature for a time duration from two hours to 24 hours.

9. The method of claim 1 , wherein, after machining, the machined surface has an average surface roughness R a of about 100 micro-in or less.

10. The method of claim 1 , wherein the ceramic tape comprises ceramic particles and an organic binder, the ceramic particles being selected from the group consisting of: silicon carbide particles, silicon nitride particles, and silicon nitrocarbide particles.

11. The method of claim 10 , wherein the ceramic tape further comprises other particles selected from the group consisting of: silicon particles and carbon particles.

12. The method of claim 1 , wherein the ceramic tape has a thickness in a range from about 50 μm to about 250 μm.

13. The method of claim 10 , wherein, prior to attaching the ceramic tape to the machined surface, an adhesive comprising the organic binder is deposited onto the machined surface.

14. The method of claim 1 , wherein more than one ceramic tape is applied to the machined surface.

15. The method of claim 1 , wherein applying heat and pressure to the compression assembly comprises vacuum bagging, autoclaving, laminating, and/or mechanical pressing.

16. The method of claim 1 , wherein the compression assembly is heated at a consolidation temperature in a range from about 90° C. to about 150° C.

17. The method of claim 1 , wherein the compression assembly further comprises flexible compression multilayers on opposing sides of the fiber preform to secure the tool and the ceramic tape during the application of heat and pressure.

18. The method of claim 1 , wherein the heat and pressure are applied in a controlled environment comprising a vacuum or inert gas atmosphere.

19. The method of claim 1 , wherein the protective surface layer comprises one or more surface features selected from the group consisting of: a seal slot, an antirotation slot, and a loading pad.

20. A gas turbine engine component comprising a ceramic matrix composite having the protective surface layer formed by the method of claim 1 .

Assignees

• Rolls Royce High Temperature Composites Inc

Inventors

• Shim Sungbo
• Sellappan Pathikumar

Classifications

• C04B2237/368

  Silicon nitride · CPC title

• C04B35/645

  Pressure sintering · CPC title

• C04B2237/08

  Non-oxidic interlayers · CPC title

• C04B35/83

  Carbon fibres in a carbon matrix · CPC title

• C04B2237/083

  Carbide interlayers, e.g. silicon carbide interlayers · CPC title