Turbine engine combustor heat shield with one or more cooling elements

Patent metadata

Field	Value
Publication number	US-10690348-B2
Application number	US-201415032080-A
Country	US
Kind code	B2
Filing date	Nov 4, 2014
Priority date	Nov 4, 2013
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

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 comprising a shell surface; and
a heat shield attached to the shell, the heat shield including a rail and a cooling element connected directly to the rail in a cavity, the cavity extending in a vertical direction between the shell surface and the heat shield, and the cavity fluidly coupling a plurality of apertures in the shell with a plurality of apertures in the heat shield;
wherein the rail has a vertical height and a distal rail end that contacts the shell, and the rail extends in the vertical direction to the distal rail end;
wherein the cooling element has a vertical height that is less than the vertical height of the rail;
wherein the cooling element has a distal end surface that faces and is parallel with the shell surface;
wherein the cooling element extends laterally out from the rail to a distal end;
wherein the cooling element has a length that is between two and three times greater than a width of one of the apertures in the shell; and
wherein the length and the width are measured in a direction that is perpendicular to the vertical direction.

2. The combustor wall of claim 1 , wherein the vertical height of the cooling element is less than seventy-five percent of the vertical height of the rail.

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

4. 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.

5. The combustor wall of claim 4 , wherein the cooling element projects out from a surface of the base to the distal end of the cooling element, and the distal end surface is parallel to the surface of the base.

6. 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.

7. The combustor wall of claim 6 , wherein the cooling elements include a first element and a second element that is separated from the first element by a gap.

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

9. The combustor wall of claim 6 , wherein the cooling elements include a first element and a second element that has a different configuration than the first element.

10. The combustor wall of claim 6 , wherein the cooling elements include a first element and a second element that has an identical configuration as the first element.

11. 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.

12. The combustor wall of claim 1 , wherein the distal end surface is contiguous with and perpendicular to a surface of the rail.

13. A combustor wall for a turbine engine, the combustor wall comprising:
a shell comprising a shell surface; and
a heat shield attached to the shell, the heat shield including a rail and a cooling element connected directly to the rail in a cavity, the cavity extending in a vertical direction between the shell surface and the heat shield, and the cavity fluidly coupling a plurality of apertures in the shell with a plurality of apertures in the heat shield;
wherein the rail has a vertical height and a distal rail end that contacts the shell, and the rail extends in the vertical direction to the distal rail end;
wherein the cooling element has a vertical height that is less than the vertical height of the rail;
wherein the cooling element has a distal end surface that faces and is parallel with the shell surface;
wherein the cooling element extends laterally out from the rail to a distal end;
wherein the cooling element is one of a plurality of cooling elements that are arranged along and connected to the rail; and
wherein the cooling elements include a first element and a second element that is contiguous with the first element.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

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

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R3/50

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

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03045

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