Combustor wall with tapered cooling cavity

Patent metadata

Field	Value
Publication number	US-2016252249-A1
Application number	US-201415026761-A
Country	US
Kind code	A1
Filing date	Oct 6, 2014
Priority date	Oct 7, 2013
Publication date	Sep 1, 2016
Grant date	—

Abstract

A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.

First claim

What is claimed is:

1 . A combustor wall for a turbine engine, the combustor wall comprising:
a combustor shell; and a combustor heat shield attached to the shell with first and second cavities extending between the shell and the heat shield; wherein the first cavity fluidly couples apertures defined in the shell with the second cavity, and the second cavity fluidly couples the first cavity with apertures defined in the heat shield; and wherein the shell and the heat shield converge toward one another about the second cavity.

2 . The combustor wall of claim 1 , wherein the shell defines a concavity configured to decrease a radial distance between the shell and the heat shield axially beyond the first cavity.

3 . The combustor wall of claim 1 , wherein
a height of the second cavity decreases as the combustor wall extends away from the first cavity; and the first cavity has a substantially constant height.

4 . The combustor wall of claim 1 , wherein
the combustor wall includes a rail between the first cavity and the second cavity; the rail extends between the heat shield and the shell; and the rail defines one or more apertures that couple the first cavity with the second cavity.

5 . The combustor wall of claim 1 , wherein the combustor wall is adapted to receive air in the first cavity, and direct substantially all of the air from the first cavity into the second cavity.

6 . The combustor wall of claim 1 , wherein
the second cavity extends away from the first cavity to a distal end defined by a rail; and the apertures in the heat shield are defined at the distal end.

7 . The combustor wall of claim 6 , wherein
the second cavity extends between a proximal end defined by another rail and the distal end; and the shell defines second apertures that are coupled with the second cavity and defined at the proximal end.

8 . The combustor wall of claim 1 , wherein the shell and the heat shield are adapted to
receive air in the first cavity; and direct substantially all of the air from the first cavity into the second cavity and through the apertures defined in the heat shield.

9 . The combustor wall of claim 1 , wherein the combustor wall further includes one or more cooling features arranged within the first cavity.

10 . The combustor wall of claim 1 , wherein the combustor wall further includes one or more cooling features arranged with the second cavity.

11 . A combustor for a turbine engine, the combustor comprising:
a combustor wall including a shell and a heat shield attached to the shell with a first cavity and a second cavity therebetween; the first cavity fluidly coupled between apertures in the shell and the second cavity; and the second cavity fluidly coupled between the first cavity and apertures in the heat shield; wherein a height of the second cavity decreases as the combustor wall extends away from the first cavity.

12 . The combustor of claim 11 , wherein the shell and the heat shield converge towards one another as the second cavity extends away from the first cavity.

13 . The combustor of claim 11 , wherein the first cavity has a substantially constant height.

14 . The combustor of claim 11 , wherein
the second cavity extends away from the first cavity to a distal end defined by a rail; and the apertures in the heat shield are defined at the distal end.

15 . The combustor of claim 11 , wherein the combustor wall is adapted to
receive air in the first cavity; and direct substantially all of the air from the first cavity into the second cavity and through the apertures in the heat shield.

16 . The combustor of claim 11 , further comprising:
a second combustor wall; and a combustor bulkhead extending between the combustor wall and the second combustor wall; wherein the combustor wall, the second combustor wall and the combustor bulkhead form a combustion chamber.

17 . The combustor of claim 16 , wherein the first cavity is arranged between the second cavity and the combustor bulkhead.

18 . A combustor for a turbine engine, the combustor comprising:
a combustor wall including a shell and a heat shield with a first cavity and a second cavity between the shell and the heat shield; the first cavity fluidly coupled between apertures in the shell and the second cavity; and the second cavity fluidly coupled between the first cavity and apertures in the heat shield; wherein the shell and the heat shield converge towards one another as the second cavity extends away from the first cavity.

19 . The combustor of claim 18 , wherein a height of the second cavity decreases as the combustor wall extends away from the first cavity.

20 . The combustor of claim 18 , wherein the shell defines a concavity configured to decrease a radial distance between the shell and the heat shield axially beyond the first cavity.

Assignees

• United Technologies Corp

Inventors

• Erbas-Sen Nurhak
• Cunha Frank J

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/08

  between annular flame tube sections, e.g. flame tubes with telescopic sections · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title