Fabrication of high heat capacity ceramic matrix composite aircraft brakes using spark plasma sintering

Patent metadata

Field	Value
Publication number	US-11649191-B2
Application number	US-201916595746-A
Country	US
Kind code	B2
Filing date	Oct 8, 2019
Priority date	Oct 8, 2019
Publication date	May 16, 2023
Grant date	May 16, 2023

Abstract

A method of fabricating a brake component made from a ceramic matrix composite is disclosed. In various embodiments, the method includes infiltrating a carbon fabric with a slurry containing a ceramic powder and a sintering aid; laying up the carbon fabric in a desired geometry to form a raw component; warm pressing the raw component to form a green component; and sintering the green component via a spark plasma sintering process to form a sintered component.

First claim

What is claimed:

1. A method of fabricating a brake component made from a ceramic matrix composite, comprising:
infiltrating a carbon fabric with a slurry containing a ceramic powder and a sintering aid, the carbon fabric having an opened tow ranging from about 12,000 to about 24,000 bundles of individual carbon fiber filaments, wherein the ceramic powder comprises a boron carbide;
laying up the carbon fabric in a desired geometry to form a raw component;
pressing the raw component to form a green component; and
sintering the green component via a spark plasma sintering process to form a sintered component.

2. The method of claim 1 , wherein the sintering aid includes at least one of aluminum, boron, or a boride compound.

3. The method of claim 1 , wherein the sintering aid includes an aluminum oxide.

4. The method of claim 3 , wherein the sintering aid includes the aluminum oxide and a yttrium oxide.

5. The method of claim 4 , wherein the sintering aid includes a weight percent of a mixture of the aluminum oxide and the yttrium oxide ranging from about 14 wt percent to about 85 wt percent of the aluminum oxide and wherein the slurry comprises between about 3 wt percent and about 15 wt percent of the sintering aid.

6. The method of claim 5 , wherein the ceramic powder comprises silicon carbide.

7. The method of claim 1 , further comprising machining the green component prior to sintering the green component.

8. The method of claim 7 , further comprising machining the sintered component to form the brake component.

9. The method of claim 1 , wherein the spark plasma sintering process comprises applying a pressure to the green component that is equal to or less than 68947 kPa.

10. The method of claim 9 , wherein the spark plasma sintering process is performed at a temperature equal to or less than 1,950° C.

11. The method of claim 10 , wherein the slurry comprises boron carbide and the sintering aid comprises a weight percent of a mixture of an aluminum oxide and a yttrium oxide ranging from about 14 wt percent and about 85 wt percent of the aluminum oxide and wherein the slurry comprises between about 3 wt percent and about 15 wt percent of the sintering aid.

12. The method of claim 11 , wherein the brake component includes a volume of carbon fiber ranging from about 22 vol percent to about 45 vol percent.

13. The method of claim 12 , wherein the brake component has a density ranging from about 2.3 gm/cm 3 to about 2.5 g/cm 3 .

14. A method of fabricating a ceramic matrix composite component, comprising:
infiltrating a carbon fabric having an interface coating with a slurry containing a ceramic powder and a sintering aid, the carbon fabric having an opened tow ranging from about 12,000 to about 36,000 bundles of individual carbon fiber filaments;
laying up the carbon fabric in a desired geometry to form a raw component;
pressing the raw component to form a green component; and
sintering the green component via a spark plasma sintering process to form a sintered component,
wherein the fabricated ceramic matrix composite component comprises a density with less than 5% open porosity.

15. The method of claim 14 , wherein the sintering aid includes a weight percent of a mixture of an aluminum oxide and a yttrium oxide ranging from about 14 percent to about 85 percent of the aluminum oxide and wherein the sintering aid comprises between about 3 percent and about 15 percent by weight of the slurry.

16. The method of claim 15 , wherein the spark plasma sintering process is performed at a pressure that is equal to or less than 68947 kPa.

17. The method of claim 16 , wherein the spark plasma sintering process is performed at a temperature equal to or less than 1,950° C.

18. The method of claim 17 , wherein the interface coating comprises a pyrolytic carbon or boron nitride applied by chemical vapor deposition to the carbon fabric, has a thickness from between about 0.3 microns and about 0.8 micron, and is followed by a coating of SiC applied by chemical vapor deposition.

19. The method of claim 17 , wherein the sintering aid is configured to form a liquid phase during the spark plasma sintering process.

20. The method of claim 17 , wherein brake component includes a volume of carbon fiber ranging from about 28 percent to about 36 percent and has a density ranging from about 2.3 gm/cm 3 to about 2.5 g/cm 3 .

Assignees

• Goodrich Corp

Inventors

• Lecostaouec Jean-Francois
• Wrobel Iwona

Classifications

• C04B41/5059

  Silicon carbide · CPC title

• C04B2235/604

  Pressing at temperatures other than sintering temperatures · CPC title

• C04B2235/616

  Liquid infiltration of green bodies or pre-forms · CPC title

• C04B41/009

  characterised by the material treated · CPC title

• C04B35/645

  Pressure sintering · CPC title