Ceramic matrix composite liner attachment

Patent metadata

Field	Value
Publication number	US-9638133-B2
Application number	US-201213687178-A
Country	US
Kind code	B2
Filing date	Nov 28, 2012
Priority date	Nov 28, 2012
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

An attachment structure and ceramic matrix composite liner combination for a gas turbine engine has a ceramic matrix composite liner including plural flanges extending away from a face of said liner. The flanges have an opening and a bracket secured to the flanges by a securement member extending through the opening in the flange, and through an opening in the bracket. The flanges are secured to the securement member through at least one washer having a spherical face facing a spherical recess in the flanges.

First claim

The invention claimed is:

1. An attachment structure and ceramic matrix composite liner combination for a gas turbine engine comprising:
a ceramic matrix composite liner including plural flanges extending away from a face of said liner;
said flanges having an opening, and a bracket secured to said flanges by a securement member extending through said opening in said flange, and through an opening in said bracket, and said flanges being secured to said securement member through at least one washer having a spherical face facing a spherical recess formed in said flanges;
wherein there are spherical washers on both of two sides of said flange; and
wherein one of said spherical washers is positioned between an ear on said bracket and said spherical recess in said flange, and there being a second spherical recess on said flange on an opposed one of said two sides of said flange.

2. A gas turbine engine comprising:
a compressor, a combustion section, a turbine, said compressor and said turbine for rotating about a central axis and a plurality of ceramic matrix composite liners, said ceramic matrix composite liners being attached to a support structure within the gas turbine engine; and
said liners including plural flanges extending away from a face of said liner which faces away from a chamber radially inward of said liner;
said flanges having an opening, and a bracket secured to said flanges by a securement member extending through said opening in said flanges, and through an opening in said bracket, and said flanges being secured to said securement member through at least one washer having a spherical face facing a spherical recess formed in said flanges, said flanges formed of ceramic matrix composite material; and
said spherical washers being on each of two sides of each said flange, with one of said spherical washers positioned between an ear on said bracket and said spherical recess in said flange, and there being a second spherical recess on each said flange on an opposed one of said two sides of said flange.

3. The gas turbine engine as set forth in claim 2 , wherein an opening in said spherical washers through which said securement member extends has an inner bore which is more closely received with an outer periphery of said member than said outer periphery of said securement member is spaced from said opening in said flanges.

4. The gas turbine engine as set forth in claim 2 , wherein said securement member is one of a bolt or rivet.

5. The gas turbine engine as set forth in claim 2 , wherein there are a plurality of said brackets, and a plurality of said flanges secured to said plurality of said brackets.

6. The gas turbine engine as set forth in claim 2 , wherein said hanger is be attached to said support structure by a self-locking bolt and nut, and a flanged washer being captured between said self-locking bolt and nut, and within an aperture in the support structure, and an aperture in the hanger bracket, and said flanged washer allowing adjustment of the mount bracket relative to the support structure.

7. The gas turbine engine as set forth in claim 2 , wherein said gas turbine engine includes an exhaust nozzle, and said plurality of said ceramic matrix composite liners are positioned in said exhaust nozzle.

8. The gas turbine engine as set forth in claim 2 , wherein the gas turbine engine includes an augmentor, and said plurality of said ceramic matrix composite liners are positioned in said augmentor.

Assignees

• United Technologies Corp

Inventors

• Kramer George J

Classifications

• F05D2250/241

  spherical · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2240/90

  Mounting on supporting structures or systems · CPC title