ANGLED IMPINGEMENT INSERT

• US 20150345397A1
• Filed: 05/20/2015
• Published: 12/03/2015
• Est. Priority Date: 05/29/2014
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: BUNKER, Ronald Scott, ALLEN, Jason Randolph, PORTER, Ryan Nicholas, PRITCHARD, Byron Andrew, GREENWELL, Christopher Joseph, STONE, Timothy Deryck, Pritchard, Andrew Stephen
• Granted Patent: US 9,957,816 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• 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: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An engine component with particulate mitigation features is provided. The engine component comprises an internal engine component surface having a cooling flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, 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 engine component assembly for impingement cooling, comprising:

an engine component having a cooled surface;

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

an insert adjacent to said engine component cooled surface, said insert having a plurality of openings forming an array through said insert, said cooling flow path passing through said plurality of openings to cool said cooled surface;

a gap between said engine component and said insert; and

,

said plurality of openings extending through said insert at a non-orthogonal angle to a surface of said insert.

2. The engine component of claim 1, said engine component being at least one of a first stage nozzle, a second stage nozzle, a shroud, a blade, a combustor liner, and a combustor deflector.

3. The engine component of claim 1 further comprising an airfoil, an inner band and an outer band.

4. The engine component of claim 3, wherein said airfoil is at least partially hollow.

5. The engine component of claim 1, said insert being at least partially hollow.

6. The engine component of claim 1, said insert extending completely about an inner perimeter of said engine component.

7. The engine component of claim 1, said openings being a single size.

8. The engine component of claim 1, said openings being various sizes.

9. The engine component of claim 1, said openings being at least one shape.

10. The engine component of claim 1, said openings being multiple shapes.

11. The engine component of claim 1, said openings being uniformly spaced apart.

12. The engine component of claim 1, said openings having various spacings therebetween.

13. The engine component of claim 1 wherein said openings and cooling film holes are aligned in the direction of an axis of said openings.

14. The engine component of claim 1 wherein said openings and cooling film holes are staggered relative to an axis of said openings.

15. The engine component of claim 1, each of said angle being the same.

16. The engine component of claim 1, one or more of said angle differing.

17. The engine component of claim 1, said angle being less than about 90 degrees and greater than about 0 degrees.

18. The engine component of claim 1, said angle being between about 25 degrees and about 65 degrees.

19. The engine component of claim 1, wherein a ratio of the impingement jet average fluid velocity tangent to the cooled surface, to the impingement jet average fluid velocity normal to the cooled surface is between 0.5 and 2.

20. An engine component assembly for impingement cooling, comprising:

an engine component having a cooled surface, said engine component being at least one of a first stage nozzle, a second stage nozzle, a shroud, a blade, a combustor liner, and a combustor deflector;

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

an insert adjacent to said engine component cooled surface, said insert having a plurality of openings forming an array through said insert, said cooling flow path passing through said plurality of openings to cool said cooled surface;

a gap between said engine component and said insert; and

,

said plurality of openings extending through said insert at a non-orthogonal angle to a surface of said insert;

wherein a ratio of the impingement jet average fluid velocity tangent to the cooled surface, to the impingement jet average fluid velocity normal to the cooled surface is between 0.5 and 2.