Engine components with impingement cooling features

Patent metadata

Field	Value
Publication number	US-10690055-B2
Application number	US-201515314490-A
Country	US
Kind code	B2
Filing date	May 27, 2015
Priority date	May 29, 2014
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

First claim

The invention claimed is:

1. An aircraft engine component with particulate mitigation features, comprising:
an engine component including an upstream wall, a downstream wall, having a cooled surface and a flow path on one side of the cooled surface;
said cooled surface having a plurality of open channels defined by substantially continuous walls extending either circumferentially or axially along the cooled surface and terminating in top surfaces and in end profiles separate and spaced apart from the upstream wall and the downstream wall, the continuous walls arranged in spaced relationship to form the channels therebetween;
the end profiles defined by a taper from the top surface to the cooled surface;
an insert disposed adjacent to and spaced from the top surfaces and in flow communication with said flow path, wherein the flow path impinges at least one of the end profiles, walls, top surfaces, or channels;
the insert having a plurality of openings forming an array through said insert;
said openings extending through said insert at a non-orthogonal angle to a surface of said insert facing said cooled surface; and,
said openings aimed at one of said plurality of channels and said substantially continuous walls.

2. The aircraft engine component of claim 1 , said engine component being a shroud.

3. The aircraft engine component of claim 2 , said insert being disposed between a shroud hanger and said shroud.

4. The aircraft engine component of claim 3 , said channels disposed on an outer surface of said shroud facing said insert.

5. The aircraft engine component of claim 1 , said engine component being a nozzle.

6. The aircraft engine component of claim 5 , said nozzle including an inner band, an outer band and a vane extending between said inner band and said outer band.

7. The aircraft engine component of claim 6 , said insert being disposed adjacent to an inner surface of said vane.

8. The aircraft engine component of claim 7 , said channels disposed on an inner surface of one of said vane, said inner band and said outer band.

9. The aircraft engine component of claim 1 , said substantially continuous walls having a length which is larger than a height.

10. The aircraft engine component of claim 1 , said substantially continuous walls having a rectangular cross-section.

11. The aircraft engine component of claim 1 , said substantially continuous walls varying in width.

12. The aircraft engine component of claim 1 , said channels having a rectangular cross-section.

13. The aircraft engine component of claim 1 , said channels having a curvilinear cross-section.

14. The aircraft engine component of claim 1 , said openings being circular in cross-section.

15. The aircraft engine component of claim 1 , said channels having a depth which is multiple times the size of an opening diameter.

16. An engine component assembly with impingement cooling counterflow, comprising:
an engine component including an upstream wall, a downstream wall, a cooled surface and a flow path on one side of the cooled surface;
said cooled surface having a plurality of open channels defined by substantially continuous walls extending either circumferentially or axially along the cooled surface and terminating in top surfaces and in end profiles separate and spaced apart from the upstream wall and the downstream wall, the continuous walls arranged in spaced relationship to form the channels therebetween; said engine component having a cooling fluid flow path on one side of said cooled surface;
the end profiles defined by a taper from the top surface to the cooled surface;
an insert disposed adjacent to and spaced from said engine component between said cooling fluid flow path and said engine component, wherein the flow path impinges at least one of the end profiles, walls, or channels;
said the insert having a plurality of openings through said insert forming an array, said cooling fluid flow path passing through said plurality of openings to cool said cooled surface;
said openings defining an array extending through said insert at non-orthogonal angles relative to said an insert surface facing said cooled surface;
said array including at least one first row of said openings at a first non-orthogonal angle to said insert surface;
said array including at least one second row of said openings, adjacent to said first row, said openings of said second row being disposed at a second non-orthogonal angle to said insert surface; and,
said insert array creating a counterflow of impingement cooling wherein said cooling fluid flow path passing through said first row moves in a first direction along said cooled surface and said cooling fluid flow path passing through said second row moves in a second direction along said cooled surface substantially opposite said first direction.

17. The engine component assembly of claim 16 , said engine component being at least one of a nozzle, a turbine shroud and a combustor.

18. The engine component assembly of claim 16 , said openings being at equivalent angles relative to said insert surface.

19. The engine component assembly of claim 16 , said openings being at different angles relative to said insert surface.

20. The engine component assembly of claim 16 , said plurality of openings being of a single size.

21. The engine component assembly of claim 16 , said plurality of openings being of various sizes.

22. The engine component assembly of claim 16 , said plurality of openings being at least one shape.

23. The engine component assembly of claim 16 , said plurality of openings being of uniform spacing.

24. The engine component assembly of claim 16 , said plurality of openings being of non-uniform spacing.

25. The engine component assembly of claim 16 , said cooling surface of said engine component further comprising a plurality of discrete cooling features.

26. The engine component assembly of claim 25 , said discrete cooling features being a plurality of fins.

27. The engine component assembly of claim 26 , said discrete cooling features forming an array.

28. The engine component assembly of claim 27 , said cooling fluid flow being directed one of at or between said discrete cooling features.

29. The engine component assembly of claim 16 , said cooling surface of said engine component further comprising a plurality of cooling channels.

30. The engine component assembly of claim 29 , said plurality of cooling channels defined by a plurality of walls.

31. The engine component assembly of claim 30 , said walls defined by having a length which is substantially larger than a height.

32. The engine component assembly of claim 31 , said cooling fluid flow path being directed at one of said cooling channels or said walls.

33. The engine component assembly of claim 32 wherein said cooling fluid flow path impinges at least one of a top of said walls or a sidewall of said walls.

Assignees

• Gen Electric

Inventors

• Stover Curtis Walton
• Rausch Jonathan Michael
• Atsuchi Satoshi
• Brainch Gulcharan Singh
• Briggs Robert David
• Bunker Ronald Scott
• Kulkarni Ambarish Jayant
• Meade Michael Alan
• Pritchard Byron Andrew
• Proctor Robert

Classifications

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• Y02T50/60

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

• F23R2900/03042

  Film 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

• F23R3/002

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