ENGINE COMPONENTS WITH IMPINGEMENT COOLING FEATURES

• US 20170101932A1
• Filed: 05/27/2015
• Published: 04/13/2017
• Est. Priority Date: 05/29/2014
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: RAUSCH, Jonathan Michael, ATSUCHI, Satoshi, BUNKER, Ronald Scott, KULKARNI, Ambarish Jayant, MEADE, Michael Alan, STOVER, Curtis Walton, BRAINCH, Gulcharan Singh, BRIGGS, Robert David, PRITCHARD, Byron Andrew, PROCTOR, Robert
• Granted Patent: US 10,690,055 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2250/38 angled, e.g. sweep angle
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow means for creating turbulence F23R2900/03045
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 2900/03045 Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

1. An aircraft engine component with particulate mitigation features, comprising:

an engine component having a cooled surface;

said cooled surface having a plurality of channels defined by substantially continuous walls;

said engine component having a flow path on one side of said surface;

an insert disposed adjacent to said engine component and in flow communication with said flow path, said insert having a plurality of openings forming an array through said insert;

said openings extending through said insert at a non-orthogonal angle to said surface of said insert; 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 walls having a length which is greatly 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 having a cooled surface;

said engine component having a cooling fluid flow path on one side of said cooled surface;

an insert disposed adjacent to said engine component between said cooling fluid flow path and said engine component, said 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 to said insert 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 discreet cooling features being a plurality of fins.

27. The engine component assembly of claim 26, said 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 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.