Turbine engine combustor heat shield with one or more cooling elements

Patent metadata

Field	Value
Publication number	US-2016258626-A1
Application number	US-201415032080-A
Country	US
Kind code	A1
Filing date	Nov 4, 2014
Priority date	Nov 4, 2013
Publication date	Sep 8, 2016
Grant date	—

Abstract

A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

First claim

What is claimed is:

1 . A combustor wall for a turbine engine, the combustor wall comprising:
a shell; and a heat shield attached to the shell, the heat shield including a rail and a cooling element connected to the rail in a cavity, the cavity extending in a vertical direction between the shell and the heat shield and fluidly coupling a plurality of apertures in the shell with a plurality of apertures in the heat shield.

2 . The combustor wall of claim 1 , wherein
the rail has a vertical height; and the cooling element has a vertical height that is less than the vertical height of the rail.

3 . The combustor wall of claim 1 , wherein
the rail has a vertical height; and the cooling element has a vertical height that is less than about seventy-five percent of the vertical height of the rail.

4 . The combustor wall of claim 1 , wherein
the rail has a thickness; the cooling element has a thickness that is greater than about one hundred percent of the thickness of the rail; and the thicknesses are measured in a direction that is substantially perpendicular to the vertical direction.

5 . The combustor wall of claim 1 , wherein
the cooling element has a length that is between about two and about three times greater than a width of one of the apertures in the shell; and the length and the width are measured in a direction that is substantially perpendicular to the vertical direction.

6 . The combustor wall of claim 1 , wherein
the heat shield further includes a base; and the rail and the cooling element are connected to the base.

7 . The combustor wall of claim 1 , wherein the cooling element is one of a plurality of cooling elements that are arranged along and connected to the rail.

8 . The combustor wall of claim 7 , wherein the cooling elements include a first element and a second element that is separated from the first element by a gap.

9 . The combustor wall of claim 7 , wherein one of the apertures in the heat shield is located at the spatial gap.

10 . The combustor wall of claim 7 , wherein the cooling elements include a first element and a second element that is contiguous with the first element.

11 . The combustor wall of claim 7 , wherein the cooling elements include a first element and a second element that has a different configuration than the first element.

12 . The combustor wall of claim 7 , wherein the cooling elements include a first element and a second element that has a substantially identical configuration as the first element.

13 . The combustor wall of claim 1 , wherein
the heat shield includes a panel having a downstream end; and the rail and the cooling element are attached to the panel with the rail located at the downstream end.

14 . A combustor for a turbine engine, the combustor comprising:
a combustor wall including a shell and a heat shield attached to the shell; the heat shield including a base, a protrusion extending vertically out from the base, and a cooling element connected to the protrusion within a cooling cavity of the combustor wall; wherein the protrusion has a vertical height, and the cooling element has a vertical height that is less than the vertical height of the protrusion.

15 . The combustor of claim 14 , wherein the vertical height of the cooling element is less than about seventy-five percent of the vertical height of the protrusion.

16 . The combustor of claim 14 , wherein the protrusion comprises at least a portion of an attachment that attaches the heat shield to the shell.

17 . The combustor of claim 14 , wherein the protrusion comprises a boss.

18 . A combustor wall for a turbine engine, the combustor wall comprising:
a shell; and a heat shield attached to the shell; the heat shield including a rail and a cooling element connected to the rail in a cavity; the cavity extending between the shell and the heat shield and fluidly coupling a plurality of apertures in the shell with a plurality of apertures in the heat shield; wherein at least one of the apertures in the heat shield extends through the cooling element.

19 . The combustor wall of claim 18 , wherein a vertical height of the cooling element is less than about seventy-five percent of a vertical height of the cooling element.

20 . The combustor wall of claim 18 , wherein the cooling element is one of a plurality of cooling elements that are arranged along and connected to the rail.

Assignees

• United Technologies Corp

Inventors

• Moura Dennis M
• Pacheco-Tougas Monica
• Eastwood Jonathan J
• Bouldin Lee E

Classifications

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title