Combustor wall having cooling element(s) within a cooling cavity

Patent metadata

Field	Value
Publication number	US-2016238249-A1
Application number	US-201415025455-A
Country	US
Kind code	A1
Filing date	May 23, 2014
Priority date	Oct 18, 2013
Publication date	Aug 18, 2016
Grant date	—

Abstract

A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.

First claim

What is claimed is:

1 . A combustor wall for a turbine engine, the combustor wall comprising:
a shell defining a first set of apertures; a heat shield defining a second set of apertures; and a cooling element extending between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield, wherein the tapered cavity is fluidly coupled with the first and the second sets of apertures and the cooling element is thermally coupled to one of the shell and the heat shield.

2 . The combustor wall of claim 1 , wherein the cooling element comprises a positive dimple.

3 . The combustor wall of claim 1 , wherein the cooling element comprises a rib.

4 . The combustor wall of claim 1 , wherein the cooling element includes a concave outer surface extending within the cooling cavity.

5 . The combustor wall of claim 1 , wherein the cooling element includes a convex outer surface extending within the cooling cavity.

6 . The combustor wall of claim 1 , wherein the cooling element includes a wall defining an indentation.

7 . The combustor wall of claim 1 , wherein the cooling element extends from the heat shield.

8 . The combustor wall of claim 7 , wherein the first set of apertures includes an impingement aperture adapted to direct air into the cooling cavity to impinge against the cooling element.

9 . The combustor wall of claim 7 , further comprising a second cooling element that extends into the cooling cavity from the shell.

10 . The combustor wall of claim 7 , further comprising:
a second cooling element and a third cooling element which each extend into the cooling cavity from the shell; wherein the cooling element is positioned opposite and between the second and the third cooling elements.

11 . The combustor wall of claim 7 , further comprising:
a second cooling element that extends into the cooling cavity from the heat shield; wherein the second set of apertures include an aperture positioned opposite and between the cooling element and the second cooling element.

12 . The combustor wall of claim 1 , wherein the cooling element extends into the cooling cavity from the shell.

13 . The combustor wall of claim 1 , wherein the tapered cooling cavity includes a tapered portion defined by respective portions of the shell and the heat shield converging toward one another.

14 . The combustor wall of claim 1 , wherein
the cooling cavity extends radially between the shell and the heat shield; and the cooling element extends radially into the cooling cavity.

15 . The combustor wall of claim 1 , wherein the shell and the heat shield are configured to couple to a combustor bulkhead at an upstream end thereof.

16 . A combustor for a turbine engine, the combustor comprising:
a combustor shell defining a first set of apertures; a combustor heat shield defining a second set of apertures, the heat shield attached to the shell; and a cooling element, wherein the shell and the heat shield at least partially define a cooling cavity therebetween with the cooling element extending into the cooling cavity and the cooling cavity fluidly coupling the first and the second sets of apertures.

17 . The combustor of claim 16 , wherein
the cooling element extends into the cooling cavity from the heat shield, and the first set of apertures includes an impingement aperture configured to direct air into the cooling cavity to impinge against the cooling element.

18 . The combustor of claim 16 , wherein the cooling cavity includes a tapered portion defined by respective portions of the shell and the heat shield that converge toward one another.

19 . The combustor of claim 16 , further comprising:
a plurality of additional cooling elements; wherein the cooling element and each of the additional cooling elements extends a respective height into the cooling cavity, and the respective heights of the cooling elements vary along the shell and the heat shield.

20 . The combustor of claim 16 , further comprising:
a first combustor wall; wherein the shell, the heat shield and the cooling element are included within a combustor second wall, and the first and the second combustor walls are configured to be coupled a combustor bulkhead.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Jr Stanislav

Classifications

• F23R3/002 Primary

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

• F23R2900/03041

  Effusion 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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title