Combustor dilution hole active heat transfer control apparatus and system

Patent metadata

Field	Value
Publication number	US-2016178199-A1
Application number	US-201514862332-A
Country	US
Kind code	A1
Filing date	Sep 23, 2015
Priority date	Dec 17, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

Systems and methods are described herein whereby an air jet is configured to manipulate local aerodynamics and/or boundary layer flows associated with a dilution hole. A gas turbine component including a combustor panel, a dilution hole located within the combustor panel and an air jet located within the combustor panel positioned in close proximity to the dilution hole is described. The dilution hole is configured to produce a flow of cooling fluid. An air flow from the air jet is configured to deflect secondary flows produced within a combustor. The air jet is located close enough to a leading edge of the dilution hole such that the air flow from the air jet manipulates a pressure gradient of the dilution hole.

First claim

What is claimed is:

1 . A gas turbine component comprising:
a combustor wall; a dilution hole located within the combustor wall, wherein the dilution hole is configured to conduct a flow of cooling fluid; and an air jet located within the combustor wall positioned in close proximity to the dilution hole, wherein an air flow from the air jet is configured to deflect secondary flows produced within a combustor.

2 . The gas turbine component of claim 1 , wherein the air jet is located in a proximity sufficient to a leading edge of the dilution hole such that the air flow from the air jet influences a pressure gradient in the vicinity of the exit of the dilution hole.

3 . The gas turbine component of claim 1 , wherein the air jet is located on the upstream side of the dilution hole.

4 . The gas turbine component of claim 1 , wherein the air flow from the air jet is configured to have less momentum than the flow of cooling fluid exiting the dilution hole.

5 . The gas turbine component of claim 1 , wherein a plurality of air flows from a plurality of air jets that may be positioned in close proximity to the dilution hole, wherein the plurality of air flows from the plurality of air jets may combine to manipulate a pressure gradient in the vicinity of the exit of the dilution hole.

6 . The gas turbine component of claim 1 , wherein the air jet is located at least one of a side between a leading edge or aft of the dilution hole.

7 . The gas turbine component of claim 1 , wherein the air flow from the air jet is configured to reduce at least one of downwash flow or a recirculating flow and associated vortical structures from bringing hot temperatures within the combustor down to a liner surface of the combustor.

8 . The gas turbine component of claim 1 , wherein a flow area of the air jet is substantially equal to or less than the flow area of the dilution hole.

9 . The gas turbine component of claim 1 , wherein a shape of an opening of the air jet mirrors a portion of the shape of an opening of the dilution hole.

10 . The gas turbine component of claim 9 , wherein the opening of the air jet mirrors a curvature of the opening of the dilution hole.

11 . The gas turbine component of claim 9 , wherein the air jet extend through the combustor wall to be fed by a different source as compared to a source of the flow of cooling fluid to the dilution hole.

12 . The gas turbine component of claim 9 , wherein the air jet extended through a feature of the dilution hole to be fed by a source of the flow of cooling fluid to the dilution hole.

13 . A cooling assembly comprising:
an air jet disposed in a panel, wherein the air jet located within a combustor panel positioned in proximity to a cooling air producing structure, wherein an air flow from the air jet is configured to reduce at least one of downwash flow or a recirculating flow and associated vortical structures from bringing hot temperatures to a liner surface surrounding the cooling air producing structure.

14 . The cooling assembly of claim 13 , wherein the air jet is located close enough to a leading edge of the cooling air producing structure such that the air flow from the air jet manipulates a pressure gradient of the cooling air producing structure.

15 . The cooling assembly of claim 13 , wherein a shape of an opening of the air jet mirrors a portion of the shape of an opening of the cooling air producing structure.

16 . The cooling assembly of claim 15 , wherein the opening of the air jet mirrors a curvature of the opening of the cooling air producing structure.

17 . The cooling assembly of claim 13 , wherein the air jet extends through the panel to be fed by a different source as compared to a source of a flow of cooling fluid to the cooling air producing structure.

18 . A method of deflecting secondary flows produced within a combustor comprising:
positioning an air jet in close proximity to a dilution hole in a panel; and expelling an air flow from the air jet to manipulate a pressure gradient in the vicinity of the exit of the dilution hole.

19 . The method of claim 18 , wherein the source of the air flow to the air jet passes through a feature of the dilution hole.

20 . The method of claim 18 , wherein the opening of the air jet mirrors a curvature of the opening of the dilution hole.

Assignees

• United Technologies Corp

Inventors

• Burd Steven W

Classifications

• F23R3/002

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

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title