Cooling patch for hot gas path components

Patent metadata

Field	Value
Publication number	US-10520193-B2
Application number	US-201514924742-A
Country	US
Kind code	B2
Filing date	Oct 28, 2015
Priority date	Oct 28, 2015
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

The present application provides a cooling patch for use with a hot gas path component of a gas turbine engine. The cooling patch may include a base layer with a number of cooling channels extending therethrough, and a cover layer positioned on the base layer. The base layer and the cover layer may include a pre-sintered preform material.

First claim

I claim:

1. A cooling patch configured to provide additional cooling to a hot gas path component of a gas turbine engine, the cooling patch comprising:
a base layer attached to a cold side surface of the hot gas path component, the base layer having a first surface in contact with the cold side surface and a second surface opposite the first surface;
a plurality of cooling channels formed in and extending along the second surface of the base layer; and
a cover layer positioned on the second surface of the base layer, the cover layer comprising a filter at one end thereof;
wherein the base layer and the cover layer comprise a pre-sintered preform material heat-treated in position on the hot gas path component; and wherein the hot gas path component is a combustor component larger than the cooling patch.

2. The cooling patch of claim 1 , wherein the pre-sintered preform material comprises a structural alloy powder having a first melting point, a brazing alloy powder having a second melting point less than the first melting point, and a binding agent.

3. The cooling patch of claim 1 , wherein the base layer comprises an inlet adjacent to the plurality of cooling channels.

4. The cooling patch of claim 1 , wherein the hot gas path component comprises a plurality of hot gas path component holes therethrough; and wherein the base layer comprises a plurality of outlet holes in fluid communication with the plurality of cooling channels, the plurality of outlet holes being aligned with the plurality of hot gas path component holes.

5. The cooling patch of claim 1 , wherein each cooling channel of the plurality of cooling channels comprises a width ranging from 0.05 inches to 0.08 inches and a length ranging from one inch to three inches.

6. The cooling patch of claim 1 , wherein the cover layer comprises a substantially solid plate.

7. The cooling patch of claim 1 , wherein the cover layer comprises a top surface of the plurality of cooling channels.

8. The cooling patch of claim 1 , wherein the cooling patch is in communication with a flow of air at a compressor discharge temperature.

9. A method of providing additional cooling to a hot gas path component, the method comprising:
aligning a cooling patch with a number of cooling holes on the hot gas path component, the cooling patch comprising a base layer having a first surface and a second surface, a plurality of cooling channels formed in and extending along the second surface of the base layer, a cover layer defining a top surface of the plurality of cooling channels, and a plurality of outlet holes in fluid communication with the plurality of cooling channels, the aligning of the cooling patch including aligning the plurality of outlet holes with the number of cooling holes;
attaching the first surface of the base layer of the cooling patch to a cold side surface of the hot gas path component, wherein the hot gas path component is a combustor component larger than the cooling patch;
heat treating the cooling patch in place;
providing a flow of air through a filter attached at one end of the cover layer proximate to the plurality of cooling channels of the cooling patch, such that the flow of air flows through the plurality of cooling channels to cool the hot gas path component; and
flowing the air through the number of cooling holes on the hot gas path component.

10. The method of claim 9 , wherein the step of attaching the cooling patch to the hot gas path component comprises welding the cooling patch to the hot gas path component.

11. The method of claim 9 , wherein the step of attaching the cooling patch to the hot gas path component comprises attaching the cooling patch in an orientation in which the plurality of cooling channels is disposed in a substantially parallel direction to a flow of gases within the hot gas path component.

12. The method of claim 9 , wherein the step of heat treating the cooling patch in place comprises heat treating a pre-sintered preform material.

13. The method of claim 9 , wherein the step of providing a flow of air through the cooling patch to cool the hot gas path component comprises providing a flow of air at a compressor discharge temperature.

14. The method of claim 9 , wherein the step of flowing the air through the number of cooling holes on the hot gas path component comprises flowing the air through the number of cooling holes to provide film cooling of a hot side surface of the hot gas path component.

15. A hot gas path component for use with a gas turbine engine, the hot gas path component comprising:
a combustor liner having a cold side surface and a hot side surface;
a plurality of cooling holes extending through the combustor liner from the cold side surface to the hot side surface; and
a cooling patch having a first surface positioned on and attached to the cold side surface of the combustor liner adjacent to the plurality of cooling holes, a second surface opposite the first surface, and a filter attached at one end of the cooling patch;
wherein the second surface of the cooling patch comprises a plurality of cooling channels such that a flow of air passes through the plurality of cooling channels and through the plurality of cooling holes; and wherein the cooling patch is smaller than the combustor liner.

16. The hot gas path component of claim 15 , wherein the cooling patch comprises a pre-sintered preform material.

17. The hot gas path component of claim 16 , wherein the pre-sintered preform material comprises a structural alloy powder having a first melting point, a brazing alloy powder having a second melting point less than the first melting point, and a binding agent.

18. The hot gas path component of claim 15 , wherein the cooling patch comprises a base layer having the second surface in which the plurality of cooling channels is formed and a cover layer positioned on the second surface of the base layer.

Assignees

• Gen Electric

Inventors

• Berry Jonathan Dwight

Classifications

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2230/22

  by sintering · CPC title

• B23K2101/001

  Turbines · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title