Needled ceramic matrix composite cooling passages

Patent metadata

Field	Value
Publication number	US-12570580-B2
Application number	US-202017020455-A
Country	US
Kind code	B2
Filing date	Sep 14, 2020
Priority date	Jan 5, 2018
Publication date	Mar 10, 2026
Grant date	Mar 10, 2026

Abstract

A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

First claim

What is claimed:

1. A core for a ceramic matrix composite component, comprising:
a first core portion;
a second core portion spaced from the first core portion to define a space between the first core portion and the second core portion; and
a rod extending from within the first core portion across the space and to and within the second core portion, wherein the first core portion comprises a hole for the rod coaxial within a hole for a hollow member.

2. The core as recited in claim 1 , wherein the first core portion is adjacent a trailing edge of the ceramic matrix composite component.

3. The core as recited in claim 2 , wherein the second core portion is adjacent a leading edge of the ceramic matrix composite component.

4. The core as recited in claim 3 , wherein the second core portion will form an impingement passage within the ceramic matrix composite component.

5. The core as recited in claim 1 , wherein the rod is manufactured of the same material as the first core portion and the second core portion.

6. The core as recited in claim 1 , wherein the rod is of a desired cooling hole shape.

7. The core as recited in claim 1 , wherein the rod is glued into the first core portion.

8. The core as recited in claim 1 , further comprising a first ceramic matrix composite material that wraps the first core portion, the first ceramic matrix composite material forms an internal wall within an airfoil.

9. The core as recited in claim 8 , wherein the first ceramic matrix composite material comprises a plurality of fibers through which the rod extends but does not cut.

10. The core as recited in claim 9 , further comprising a second ceramic matrix composite material that wraps the first core portion and the second core portion.

11. The core as recited in claim 1 , wherein an inner surface of the hollow member is sized to receive the rod, the hollow member extending between the first core portion and the second core portion.

12. The core as recited in claim 1 , wherein each of the first core portion and the second core portion include a multiple of grooves.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Propheter-Hinckley Tracy A

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/187

  Convection cooling · CPC title