Device and method for preventing leakage of air between multiple turbine components

Patent metadata

Field	Value
Publication number	US-9488110-B2
Application number	US-201313790965-A
Country	US
Kind code	B2
Filing date	Mar 8, 2013
Priority date	Mar 8, 2013
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.

First claim

What is claimed is:

1. A turbine, comprising:
a first turbine component being of a first material having a first coefficient of thermal expansion;
a second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component;
a space between said first and second turbine components;
a seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components;
wherein said first turbine component is a liner of a combustor; and said second turbine component is a first stage nozzle;
wherein said seal assembly further comprises a seal member and a seal carrier enveloping at least a portion of said seal member such that said seal member is isolated from contact with at least one of said liner or said nozzle; and
wherein said seal carrier further comprises a first member between said liner and a first end of said seal member and a second member between said nozzle and a second end of said seal member.

2. The turbine of claim 1 , wherein:
a first portion of said seal assembly is engaged with said liner; and
a second portion of said seal assembly is engaged with said nozzle.

3. The turbine of claim 1 , further comprising:
a barrier adapted to provide thermal insulation for at least a portion of said seal member.

4. The turbine of claim 1 , wherein said seal member includes a convoluted portion.

5. The turbine of claim 1 , wherein:
said seal member is positioned such that a first end of said seal member couples with said seal carrier and a second end of said seal member couples with one of said nozzle or said liner.

6. The turbine of claim 1 , wherein said seal carrier has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.

7. The turbine of claim 1 , wherein:
said first member includes a first flange between said liner and said first end of said seal and a second flange extending axially from said first member; and
said second member envelops a portion of said nozzle.

8. The turbine of claim 1 , wherein:
said first member further comprises a resilient portion adapted to flex in a radial direction and provide space at least the nozzle to be positioned adjacent the liner.

9. A method of preventing leakage in a turbine, comprising:
situating a seal assembly in a space between first and second turbine components wherein the first turbine component comprises a liner of a combustor and the second turbine component comprises a first stage nozzle, engaging a first portion of the seal assembly with the liner and engaging a second portion of the seal assembly with the nozzle, thereby sealing the space, wherein the first and second turbine components are of first and second materials having first and second coefficients of thermal expansion, respectively, and wherein a portion of the seal assembly has a coefficient of thermal expansion substantially similar to at least one of the first or second turbine components, wherein the seal assembly further comprises a seal member and a seal carrier;
enveloping at least a portion of the seal member such that the seal member is isolated from contact with at least one of the liner or the nozzle;
coupling the seal member with one of the liner or the nozzle;
coupling one end of the seal carrier with the liner and the other end of the seal carrier with the nozzle; and
maintaining a seal in the space during thermal expansion or contraction of said first and second turbine components.

10. The method of claim 9 , wherein the seal carrier has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.

11. The method of claim 10 , wherein the seal carrier essentially mimics a thermal expansion of at least one of the liner or nozzle, thereby preventing a relative movement between the first and second ends of the seal member.

12. The method of claim 9 , further comprising:
providing a barrier to thermally insulate at least a portion of the seal member.

13. The method of claim 9 , wherein the seal carrier further comprises a first member and a second member and the method further comprises:
positioning a portion of the first member between the liner and a first end of the seal member; and
positioning a portion of the second member between the nozzle and a second end of the seal member.

Assignees

• Gen Electric

Inventors

• Chan George Joe-Kueng
• Correia Victor Hugo Silva
• Hannwacker David
• Proctor Robert

Classifications

• F05D2300/50211

  similar · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title