Attachment of ceramic matrix composite panel to liner

Patent metadata

Field	Value
Publication number	US-9890953-B2
Application number	US-201514588471-A
Country	US
Kind code	B2
Filing date	Jan 2, 2015
Priority date	Jan 10, 2014
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

First claim

The invention claimed is:

1. A combined liner and panel for use in a gas turbine engine comprising:
a ceramic matrix composite panel having a plurality of extending members extending away from a face of the ceramic matrix composite panel which will face hot products of combustion;
a liner including a plurality of spring members, said spring members applying a bias force biasing said extending members, said spring members biasing said extending members on said panel in a direction away from said face of said panel which will face the hot products of combustion;
wherein each of said spring members includes a spring ring received within said extending members;
wherein said extending members are rings and; and
wherein said liner has a plurality of apertures, each provided with a finger and said finger receiving said spring members.

2. The combined liner and panel as set forth in claim 1 , wherein said spring ring of each of said spring members has a central slot such that said spring ring of each of said spring members has two sides.

3. The combined liner and panel as set forth in claim 1 , wherein said spring ring of each of said spring members having chamfers on at least one end to facilitate movement of said extending members onto said spring ring of each of said spring members.

4. The combined liner and panel as set forth in claim 1 , wherein said apertures in said liner are C-shaped and surround said finger.

5. The combined liner and panel as set forth in claim 1 , wherein said spring members are separate from said finger and are fixed to said liner.

6. The combined liner and panel as set forth in claim 5 , wherein said spring members are fixed to said liner at a location beyond said fingers.

7. The combined liner and panel as set forth in claim 6 , wherein said spring members have a first end fixed to said liner, and a second end which is in contact with said finger, with said spring ring of each of said spring members being intermediate said first and second ends.

8. The combined liner and panel as set forth in claim 7 , wherein a central web is formed on said spring members between said first and second ends and is bowed away from said finger.

9. The combined liner and panel as set forth in claim 1 , wherein said extending members on said panel biases said spring rings away from a relaxed position to create the bias force.

10. A gas turbine engine comprising:
a combustor section and an exhaust section downstream of said combustor section with a panel and liner combination mounted at a location in said combustor, or downstream of said combustor, with the panel of the combination comprising a ceramic matrix composite panel having a plurality of extending members extending away from a face of the ceramic matrix composite panel which will face hot products of combustion, and the liner of the combination including a plurality of spring members, said spring members applying a bias force biasing said extending members, said spring members biasing said extending members in a direction away from said face of said panel which will face the hot products of combustion; and
each of said spring members includes a spring ring received within said extending members, said extending members are rings and said spring rings are received within said extending members, and said liner has a plurality of apertures, each provided with a finger and said finger receiving said spring members.

11. The gas turbine engine as set forth in claim 10 , wherein said spring ring of each of said spring members having chamfers on at least one end to facilitate movement of said extending members onto said spring ring of each of said spring members.

Assignees

• Ruberte Sanchez Jose E
• Mcalice Timothy J
• Rugg Kevin L
• United Technologies Corp

Inventors

• Ruberte Sanchez Jose E
• Mcalice Timothy J
• Rugg Kevin L

Classifications

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23M5/04 Primary

  Supports for linings · CPC title