Heat shield panels with overlap joints for a turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10222064-B2
Application number	US-201415025631-A
Country	US
Kind code	B2
Filing date	Sep 30, 2014
Priority date	Oct 4, 2013
Publication date	Mar 5, 2019
Grant date	Mar 5, 2019

Abstract

A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and 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 at least partially defining a combustion chamber for a turbine engine, the combustor wall comprising:
a combustor shell; and
a combustor heat shield attached to the combustor shell and positioned between the combustion chamber and the combustor shell, the combustor heat shield including a first panel and a second panel, the first panel and the second panel each having a respective inner surface positioned on a hot side of the combustor heat shield and a respective outer surface positioned on a cold side of the combustor heat shield, wherein a flange of the second panel sealingly engages with and radially contacts the outer surface of the first panel at an overlap joint to seal a gap between the first panel and the second panel, wherein the gap is defined between an end face of the first panel and an end face of the second panel, and wherein the flange of the second panel extends substantially parallel with the outer surface of the first panel at the overlap joint;
wherein a continuous cooling cavity extends between the combustor shell and the combustor heat shield, the continuous cooling cavity extends from the first panel, the second panel, and the overlap joint to the combustor shell, and the continuous cooling cavity fluidly couples a plurality of apertures in the combustor shell with a plurality of apertures in the combustor heat shield.

2. The combustor wall of claim 1 , wherein the overlap joint comprises a joggle lap joint.

3. The combustor wall of claim 1 , wherein the overlap joint comprises a double joggle lap joint.

4. The combustor wall of claim 1 , wherein the second panel is mechanically biased against the first panel at the overlap joint.

5. The combustor wall of claim 1 , wherein the second panel includes one or more cooling features located at the overlap joint within the continuous cooling cavity.

6. The combustor wall of claim 5 , wherein one or more of the plurality of apertures in the combustor shell direct cooling air into the continuous cooling cavity to impinge against one or more of the one or more cooling features.

7. The combustor wall of claim 5 , wherein a first of the one or more cooling features comprises a cooling pin.

8. The combustor wall of claim 1 , wherein the combustor heat shield extends along an axis, and an axial end of the first panel engages an axial end of the second panel at the overlap joint.

9. The combustor wall of claim 1 , wherein the combustor heat shield extends along an axis, the first and second panels are arcuate shaped, and a circumferential end of the first panel engages a circumferential end of the second panel at the overlap joint.

10. The combustor wall of claim 1 , wherein
a channel is defined by the gap between the first panel and the second panel at the overlap joint; and
one or more of the plurality of apertures in the combustor heat shield extend through the second panel between the continuous cooling cavity and the channel.

11. The combustor wall of claim 1 , wherein the combustor shell is configured to engage a combustor bulkhead at an upstream end of the combustor bulkhead.

12. A combustor for a turbine engine, the combustor comprising:
a tubular combustor shell extending along an axis;
a heat shield first panel attached to the tubular combustor shell and positioned between a combustion chamber and the tubular combustor shell, the heat shield first panel having an inner surface positioned on a hot side of the heat shield first panel and an outer surface positioned on a cold side of the heat shield first panel; and
a heat shield second panel positioned between the combustion chamber and the tubular combustor shell, a flange of the heat shield second panel being sealingly engaged with and radially in contact with the outer surface of the heat shield first panel in an overlap joint to seal a gap between the heat shield first panel and the heat shield second panel, the heat shield second panel having an inner surface positioned on a hot side of the heat shield second panel and an outer surface positioned on a cold side of the heat shield second panel;
wherein the gap is defined between an end face of the heat shield first panel and an end face of the heat shield second panel, and wherein the flange of the heat shield second panel extends substantially parallel with the outer surface of the heat shield first panel at the overlap joint;
wherein the tubular combustor shell, the heat shield first panel and the heat shield second panel form a continuous cooling cavity that fluidly couples a plurality of apertures in the tubular combustor shell with a plurality of apertures in the heat shield first panel; and
wherein the continuous cooling cavity extends from the heat shield first panel, the heat shield second panel, and the overlap joint to the tubular combustor shell.

13. The combustor of claim 12 , further comprising:
a combustor first wall;
a combustor second wall including the tubular combustor shell, the heat shield first panel and the heat shield second panel; and
a combustor bulkhead extending radially between the combustor first wall and the combustor second wall;
wherein the first wall, the second wall and the combustor bulkhead form the combustion chamber.

14. A combustor for a turbine engine, the combustor comprising:
a combustor shell extending along an axis;
a heat shield first panel attached to the combustor shell and positioned between a combustion chamber and the combustor shell, the heat shield first panel having an inner surface positioned on a hot side of the heat shield first panel and an outer surface positioned on a cold side of the heat shield first panel; and
a heat shield second panel having a flange, the flange of the heat shield second panel sealingly engaged with and radially contacting the outer surface of the heat shield first panel in an overlap joint to seal a gap between the heat shield first panel and the heat shield second panel, the heat shield second panel being positioned between the combustion chamber and the combustor shell and having an inner surface positioned on a hot side of the heat shield second panel and an outer surface positioned on a cold side of the heat shield second panel;
wherein the gap is defined between an end face of the heat shield first panel and an end face of the heat shield second panel, and wherein the flange of the heat shield second panel extends substantially parallel with the outer surface of the heat shield first panel at the overlap joint;
wherein a portion of the heat shield second panel is radially between the combustor shell and the heat shield first panel;
wherein a continuous cooling cavity fluidly couples a plurality of apertures in the combustor shell with a plurality of apertures in the heat shield first panel; and
wherein the continuous cooling cavity extends from the heat shield first panel, the heat shield second panel, and the overlap joint to the combustor shell.

15. A combustor for a turbine engine, the combustor comprising:
a combustor first wall;
a combustor second wall comprising a tubular combustor shell extending along an axis and a heat shield first panel attached to the tubular combustor shell; and
a combustor bulkhead including extending radially between the combustor first wall and the combustor second wall, and the combustor bulkhead comprising a heat shield second panel sealingly engaged with the heat shield first panel in an overlap joint;
wherein the tubular combustor shell, the heat shield first panel and the heat shield second panel at least partially form a cooling cavity that fluidly couples a plur

Assignees

• United Technologies Corp

Inventors

• Kostka Stanislav
• Cunha Frank J

Classifications

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23M5/085

  using air or other gas as the cooling medium · CPC title

• F23M5/00

  Casings; Linings; Walls · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23M5/04 Primary

  Supports for linings · CPC title