Sacrificial 3-dimensional weaving method and ceramic matrix composites formed therefrom

Patent metadata

Field	Value
Publication number	US-11021779-B2
Application number	US-201815963212-A
Country	US
Kind code	B2
Filing date	Apr 26, 2018
Priority date	May 1, 2017
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A ceramic matrix composite (CMC) is formed using a three-dimensional (3-D) woven preform by removing the set of sacrificial fibers from the 3-D woven preform and allowing a metal or metal alloy infiltrate the 3-D woven preform. The 3-D woven preform is formed by a method that includes providing a woven layer comprising a first set of ceramic fibers oriented in a first (x) direction woven with a second set of ceramic fibers oriented in a second (y) direction; stacking a plurality of woven layers on top of each other, said woven layers providing a two-dimensional (2-D) preform; weaving a set of sacrificial fibers in a third (z) direction with the 2-D preform, said weaving providing the 3-D woven preform; and shaping the 3-D woven preform into a predetermined shape.

First claim

What is claimed is:

1. A method of forming a ceramic matrix composite (CMC), the method comprising:
providing a woven layer comprising a first set of ceramic fibers oriented in a first (x) direction woven with a second set of ceramic fibers oriented in a second (y) direction:
stacking a plurality of woven layers on top of each other, said woven layers providing a two-dimensional (2-D) preform;
weaving a set of sacrificial fibers in a third (z) direction with the 2-D preform, said weaving providing the 3-D woven preform; and
shaping the 3-D woven preform into a predetermined shape;
removing the set of sacrificial fibers from the 3-D woven preform; and
infiltrating the 3-D woven preform with a metal or metal alloy to form the ceramic matrix composite (CMC);
wherein the metal or metal alloy fills any gaps or free volume that is located between the first and second sets of ceramic fibers.

2. The method according to claim 1 , wherein the metal or metal alloy infiltrates the 3-D woven preform by a melt infiltration process, a chemical vapor infiltration process, or a combination thereof.

3. The method according to claim 1 , wherein the sacrificial fibers are removed by oxidation, chemical etching, leaching, or mechanical removal.

4. The method according to claim 1 , wherein the removal comprises exposing the 3-D woven preform up to an elevated temperature up to about 1,000° C.

5. The method according to claim 1 , wherein the method further comprises performing at least one finishing operation on the CMC.

6. A component that comprises a ceramic matrix composite (CMC) formed according to the method of claim 1 .

7. The component according to claim 6 , wherein the component is a seal segment, an airfoil, a turbine blade, or a vane.

8. The component according to claim 6 used in an aerospace or automotive application.

9. The method according to claim 1 , wherein the first set of ceramic fibers, the second set of ceramic fibers, and the sacrificial fibers are woven such that each are present in an amount that ranges between about 10 to about 20 picks per inch.

10. The method according to claim 9 , wherein the picks per inch of the sacrificial fibers in the 3-D woven preform increases in a region of the predetermined shape that represents a deltoid, sharp curve, or a change in direction.

11. The method according to claim 1 , wherein an overall amount of the sacrificial fibers present in the 3-D woven preform is less than an amount of the ceramic fibers in the x and y directions.

12. The method according to claim 1 , wherein a ratio of a number of sacrificial fibers to a number of ceramic fibers in the x or y direction is between about 0.7:1 and about 1.3:1.

13. The method according to claim 1 , wherein the method further comprises cutting or trimming any excess ceramic fibers or sacrificial fibers from the 3-D woven preform.

14. The method according to claim 1 , where the first set and second set of ceramic fibers are stable at a temperature that is at or above 1,000° C.

15. The method according to claim 1 , wherein the first set and second set of ceramic fibers are individually selected from the group of alumina, mullite, silicon carbide, silicon nitride, zirconia, carbon, or combinations thereof.

16. The method according to claim 1 , wherein the sacrificial fibers comprise individual fibers or fiber bundles made from organic polymers, co-polymers, or a mixture thereof.

17. The method according to claim 1 , wherein the sacrificial fibers have a composition selected as one from the group of consisting of: a polyvinyl alcohol (PVA), a polyamide, a polyester, and a combination thereof.

18. The method according to claim 1 , wherein a component selected from the group consisting of: a seal segment, an airfoil, a turbine blade, and a vane comprises the CMC.

Assignees

• Rolls Royce High Temperature Composites Inc
• Rolls Royce Corp

Inventors

• Barrett Chris
• Brown Steffan

Classifications

• D03D25/005

  Three-dimensional woven fabrics · CPC title

• C04B2235/5268

  Orientation of the fibers · CPC title

• C04B2235/5248

  Carbon, e.g. graphite · CPC title

• C22C47/062 Primary

  from wires or filaments only · CPC title

• D10B2101/08

  Ceramic · CPC title