Gas turbine engine wall assembly interface

Patent metadata

Field	Value
Publication number	US-10197285-B2
Application number	US-201415038847-A
Country	US
Kind code	B2
Filing date	Aug 29, 2014
Priority date	Dec 6, 2013
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.

First claim

What is claimed is:

1. A wall assembly for a gas turbine engine, comprising:
a support shell with a contoured region defining an aperture for receiving a stud; and
a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels including an end rail, and the contoured region deformable via a fastener engaging the contoured region to contact at least a portion of the end rail.

2. The wall assembly as recited in claim 1 , wherein the portion of the end rail and the contoured region of the support shell define a gap when the contoured region is in a first position.

3. The wall assembly as recited in claim 2 , wherein the portion of the end rail and the contoured region of the support shell form a seal when the contoured region is in a second position.

4. The wall assembly as recited in claim 1 , wherein the contoured region is centered with respect to an intermediate circumferential rail of the at least one of the multiple of liner panels.

5. The wall assembly as recited in claim 4 , further comprising a perimeter rail that defines a first height from a cold side of the at least one liner panel, the intermediate rail defines a second height from the cold side, the second height less than the first height.

6. The wall assembly as recited in claim 5 , further comprising a multiple of studs that extend from each of the multiple of liner panels.

7. The wall assembly as recited in claim 6 , wherein the multiple of studs extend from the at least one of the multiple of liner panels along the intermediate circumferential rail.

8. A wall assembly for a gas turbine engine, comprising:
a support shell with at least one contoured region defining an aperture for receiving a stud;
a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels including a first end rail and a second end rail; and
a multiple of fasteners mounted to the at least one of the multiple of liner panels, each of the multiple of fasteners operable to deform via engagement of at least one of the multiple of fasteners with a respective one of the at least one contoured region to seal the support shell to the first and the second end rails.

9. The wall assembly as recited in claim 8 , further comprising a multiple of studs that extend from the at least one of the multiple of liner panels through the support shell, each of the multiple of fasteners respectively received onto one of the multiple of studs.

10. The wall assembly as recited in claim 8 , wherein the contoured region is aligned with respect to an intermediate circumferential rail of the at least one of the multiple of liner panels.

11. The wall assembly as recited in claim 8 , wherein the liner panel is mounted within a combustor of the gas turbine engine.

12. The wall assembly as recited in claim 8 , wherein the first and the second end rails form a portion of a perimeter rail.

13. The wall assembly as recited in claim 12 , wherein the perimeter rail surrounds an intermediate rail.

14. The wall assembly as recited in claim 13 , wherein the perimeter rail includes a forward circumferential rail and an aft circumferential rail connected to the first and the second end rails, the first and the second end rails each includes an engagement area in contact with the support shell when the contoured region of the support shell is in a first position and when the contoured region is in a second position sealed with the first and second end rail.

15. The wall assembly as recited in claim 14 , wherein the intermediate rail is parallel to the forward circumferential rail and the aft circumferential rail.

16. The wall assembly as recited in claim 15 , wherein the intermediate rail extends less than the forward circumferential rail and the aft circumferential rail by 0.005-0.020 inches (0.1-0.5 mm).

17. A method of assembling a wall assembly within a gas turbine engine, the method comprising:
locating a stud that extends from a cold side of a liner panel through a support shell including a contoured region defining an aperture for receiving the stud; and
attaching a fastener onto the stud and at least partially closing a gap between the panel and the shell via the fastener.

18. The method as recited in claim 17 , wherein the at least partially closing the gap comprises elastically deforming the support shell toward the liner panel.

19. The method as recited in claim 17 , wherein the panel includes a rail, and wherein the rail and the contoured region define a gap when the contoured region is in a first position and contact one another when the contoured region is in a second position.

20. The method as recited in claim 17 , further comprising defining the gap adjacent to an intermediate rail.

Assignees

• United Technologies Corp

Inventors

• Bangerter James P
• Russo Thomas R
• Hanson Russell B
• Low Kevin J

Classifications

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/002

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

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic