Cmc combustor shell with integral chutes

Patent metadata

Field	Value
Publication number	US-2017059159-A1
Application number	US-201514834605-A
Country	US
Kind code	A1
Filing date	Aug 25, 2015
Priority date	Aug 25, 2015
Publication date	Mar 2, 2017
Grant date	—

Abstract

A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

First claim

What is claimed is:

1 . A combustion assembly for a gas turbine engine, the combustion assembly comprising:
a ceramic matrix composite combustor shell comprising:
a chamber defined by a wall of the ceramic matrix composite combustor shell, and
a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell, wherein the ceramic matrix composite chute extends towards a midline of the chamber of the ceramic matrix composite combustor shell.

2 . The combustion assembly of claim 1 , wherein the ceramic matrix composite combustor shell is a combustor.

3 . The combustion assembly of claim 1 , wherein the ceramic matrix composite combustor shell is a ceramic matrix composite liner configured to mount to a combustor and be disposed in a chamber of the combustor when mounted to the combustor.

4 . The combustion assembly of claim 1 , wherein the ceramic matrix composite combustor shell and the ceramic matrix composite chute comprise ceramic fibers that extend from the ceramic matrix composite combustor shell into the ceramic matrix composite chute.

5 . The combustion assembly of claim 1 , wherein the ceramic matrix composite combustor shell and the ceramic matrix composite chute form one continuous unit.

6 . The combustion assembly of claim 1 , wherein the ceramic matrix composite combustor shell is coupled to the ceramic matrix composite chute without welding or brazing.

7 . The combustion assembly of claim 1 , wherein the ceramic matrix composite chute defines a chute opening into the chamber that is in a plane substantially parallel with a plane that is tangent to the ceramic matrix composite combustor shell where the ceramic matrix composite chute and the ceramic matrix composite combustor shell intersect.

8 . A method for fabricating a ceramic matrix composite chute, comprising:
forming a porous ceramic preform comprising a plurality of ceramic fibers; forming an aperture in the porous ceramic preform; enlarging the aperture into a chute shape by inserting a layup tool into the aperture; and forming the porous ceramic preform into a ceramic matrix composite body, the ceramic matrix composite body comprising a combustor shell and a chute.

9 . The method of claim 8 , wherein forming the porous ceramic preform comprises stacking a plurality of two-dimensional weaves or unidirectional tape layups.

10 . The method of claim 9 , wherein forming the aperture in the porous ceramic preform comprises forming an opening in each two-dimensional weave or unidirectional tape layup and aligning the openings in the stacked plurality of two-dimensional weaves or unidirectional tape layups.

11 . The method of claim 8 , wherein forming the aperture in the porous ceramic preform comprises cutting the aperture into the porous ceramic preform.

12 . The method of claim 8 , wherein forming the aperture in the porous ceramic preform comprises weaving the aperture into the porous ceramic preform.

13 . The method of claim 8 , wherein forming the porous ceramic preform into the ceramic matrix composite body comprises treating the porous ceramic preform with one or more of a chemical vapor infiltration, a slurry infiltration, or a melt infiltration.

14 . The method of claim 8 , wherein the chute defines a chute opening into a chamber that is scarfed.

15 . A method for fabricating a ceramic matrix composite chute, comprising:
forming a ceramic preform into a frame for a combustor shell and a chute; and forming the ceramic preform into a ceramic matrix composite body, the ceramic matrix composite body comprising the combustor shell and the chute.

16 . The method of claim 15 further comprising enlarging an aperture in the ceramic preform with a layup tool.

17 . The method of claim 16 , wherein the layup tool includes a cylinder, the aperture is enlarged when the cylinder is inserted into the aperture.

18 . The method of claim 16 further comprising moving ceramic fibers in the ceramic preform with the layup tool when enlarging the aperture such that the ceramic fibers extend from the combustor shell into the chute in the ceramic matrix composite body.

19 . The method of claim 15 , wherein forming the ceramic preform comprises forming the ceramic preform into the frame for the combustor shell and for a plurality of chutes, and, wherein the ceramic matrix composite body comprises the combustor shell and the chutes.

20 . The method of claim 15 wherein forming the ceramic matrix composite body comprises one or more of a chemical vapor infiltration, a slurry infiltration, or a melt infiltration.

Assignees

• Rolls Royce Corp

Inventors

• Varney Bruce Edward

Classifications

• F23R3/045

  using pipes · CPC title

• B28B21/98

  for reshaping, e.g. by means of reshape moulds · CPC title

• C04B41/4539

  as a emulsion, dispersion or suspension · CPC title

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title