Cooling holes manufactured with ebc in place

Patent metadata

Field	Value
Publication number	US-2016348511-A1
Application number	US-201514722091-A
Country	US
Kind code	A1
Filing date	May 26, 2015
Priority date	May 26, 2015
Publication date	Dec 1, 2016
Grant date	—

Abstract

A method for forming a hole in a ceramic matrix composite (CMC) component may be provided. A sacrificial fiber having an environmental barrier coating on an outer surface thereof may be inserted into a porous ceramic preform that includes ceramic fibers. The ceramic preform may be formed into a ceramic matrix composite body. The sacrificial fiber may be removed from the ceramic matrix composite body, the environmental barrier coating of the sacrificial fiber defining an opening in the ceramic matrix composite body. A ceramic matrix composite component may be provided. The ceramic matrix composite component may include an environmental barrier coating of a sacrificial fiber, where the environmental barrier coating forms a lining of a hole passing partly or entirely through a thickness of the ceramic matrix composite body.

First claim

What is claimed is:

1 . A method for forming a hole in a ceramic matrix composite (CMC) component, the method comprising:
inserting a sacrificial fiber having an environmental barrier coating on an outer surface thereof into a porous ceramic preform comprising a plurality of ceramic fibers; forming the ceramic preform into a ceramic matrix composite body; and removing the sacrificial fiber from the ceramic matrix composite body, the environmental barrier coating of the sacrificial fiber remaining and defining an opening in the ceramic matrix composite body.

2 . The method of claim 1 wherein the porous ceramic preform comprises a three-dimensional weave, and wherein inserting the sacrificial fiber comprises inserting the sacrificial fiber into the three-dimensional weave.

3 . The method of claim 1 wherein the porous ceramic preform comprises a two-dimensional weave, and wherein inserting the sacrificial fiber comprises inserting the sacrificial fiber into the two-dimensional weave.

4 . The method of claim 1 wherein the porous ceramic preform comprises a unidirectional layup, and wherein inserting the sacrificial fiber comprises inserting the sacrificial fiber into the unidirectional layup.

5 . The method of claim 1 wherein the ceramic fibers in the porous ceramic preform are braided.

6 . The method of claim 1 wherein forming the ceramic matrix composite body comprises infiltrating a molten metal or alloy into the porous ceramic preform.

7 . The method of claim 1 wherein forming the ceramic matrix composite body comprises chemical vapor infiltrating the porous ceramic preform.

8 . The method of claim 1 further comprising applying a chemical vapor infiltration coating to the ceramic fibers of the ceramic preform prior to forming the ceramic preform into the ceramic matrix composite body.

9 . The method of claim 1 wherein the sacrificial fiber is inserted into the porous ceramic preform prior to forming the ceramic preform into the ceramic matrix composite body.

10 . The method of claim 1 wherein the sacrificial fiber is removed after the ceramic matrix composite body is formed.

11 . The method of claim 1 wherein removing the sacrificial fiber comprises removing the sacrificial fiber by machining.

12 . The method of claim 1 wherein removing the sacrificial fiber comprises removing the sacrificial fiber by chemical etching.

13 . The method of claim 1 wherein removing the sacrificial fiber comprises removing the sacrificial fiber by burning.

14 . A ceramic matrix composite component comprising:
a ceramic matrix composite body comprising an environmental barrier coating from a sacrificial fiber, wherein the environmental barrier coating forms a lining of a hole passing partly or entirely through a thickness of the ceramic matrix composite body.

15 . The ceramic matrix composite component of claim 14 , wherein the ceramic matrix composite body comprises silicon carbide.

16 . The ceramic matrix composite component of claim 14 , wherein no fibers of the ceramic matrix composite body are cut at the lining of the hole.

17 . The ceramic matrix composite component of claim 14 , wherein the ceramic matrix composite body is included in an airfoil.

18 . The ceramic matrix composite component of claim 14 , wherein a diameter of the hole in the ceramic matrix composite body is in a range of about 0.005 inches to about 0.050 inches.

19 . The ceramic matrix composite component of claim 14 , wherein a thickness of the lining of a hole is in the range of about 0.001 inches to about 0.050 inches.

20 . The ceramic matrix composite component of claim 14 , wherein the hole is a passage for a thermal fluid.

Assignees

• Rolls Royce Corp

Inventors

• Varney Bruce Edward

Classifications

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title