Gas turbine engine wall assembly with offset rail

Patent metadata

Field	Value
Publication number	US-2016265784-A1
Application number	US-201415032354-A
Country	US
Kind code	A1
Filing date	Aug 29, 2014
Priority date	Nov 4, 2013
Publication date	Sep 15, 2016
Grant date	—

Abstract

A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.

First claim

What is claimed is:

1 . A liner panel within a gas turbine engine, comprising:
a perimeter rail that defines a first height from a cold side; and an intermediate rail that defines a second height from the cold side, wherein the second height is less than the first height.

2 . The liner panel as recited in claim 1 , further comprising a multiple of studs that extend from the cold side.

3 . The liner panel as recited in claim 2 , wherein the multiple of studs extend from the intermediate rail.

4 . The liner panel as recited in claim 2 , wherein the multiple of studs include a first row of studs that extend from the cold side generally forward of the intermediate rail and a second row of studs that extend from the cold side generally aft of the intermediate rail.

5 . The liner panel as recited in claim 1 , wherein the perimeter rail includes a forward circumferential rail, an aft circumferential rail axial spaced from the forward circumferential rail and first and second axial end rails between the forward circumferential rail and the aft circumferential rail.

6 . The liner panel as recited in claim 5 , wherein the intermediate rail is generally parallel to the forward circumferential rail and the aft circumferential rail.

7 . The liner panel as recited in claim 1 , wherein the second height is less than the first height by about 0.005-0.020 inches (0.1-0.5 mm).

8 . A wall assembly within a gas turbine engine, comprising:
a support shell; and a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panel includes a perimeter rail that defines a first height from a cold side and an intermediate rail that defines a second height from the cold side, wherein the second height less than the first height.

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

10 . The wall assembly as recited in claim 8 , further comprising a multiple of studs that extend from the liner panel through the support shell.

11 . The wall assembly as recited in claim 10 , wherein the multiple of studs extend from the intermediate rail.

12 . The wall assembly as recited in claim 11 , wherein the multiple of studs include a first row of studs that extend from the cold side generally forward of the intermediate rail and a second row of studs that extend from the cold side generally aft of the intermediate rail.

13 . The wall assembly as recited in claim 8 , wherein the perimeter rail includes a forward circumferential rail, an aft circumferential rail axially spaced from the forward circumferential rail and a first and second axial end rail between the forward circumferential rail and the aft circumferential rail.

14 . The wall assembly as recited in claim 13 , wherein the intermediate rail is generally parallel to the forward circumferential rail and the aft circumferential rail.

15 . The wall assembly as recited in claim 8 , wherein the second height is less than the first height by about 0.005-0.020 inches (0.1-0.5 mm).

16 . A method of assembling a wall assembly within a gas turbine engine, comprising:
locating a stud that extends from a cold side of a liner panel through a support shell; and threading a fastener onto the stud to at least partially close a preassembly gap between an intermediate rail and the support shell.

17 . The method as recited in claim 16 , further comprising deflecting the support shell toward the liner panel.

18 . The method as recited in claim 16 , further comprising deflecting the support shell toward the liner panel adjacent to the intermediate rail.

19 . The method as recited in claim 18 , further comprising deflecting the support shell relative to a perimeter rail that extends from the cold side.

20 . The method as recited in claim 19 , further comprising deflecting the support shell within the perimeter rail.

Assignees

• United Technologies Corp

Inventors

• Bangerter James P
• Low Kevin J

Classifications

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• 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

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title