Angled impingement insert

Patent metadata

Field	Value
Publication number	US-9957816-B2
Application number	US-201514717547-A
Country	US
Kind code	B2
Filing date	May 20, 2015
Priority date	May 29, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

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.

First claim

What is claimed is:

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; and
a gap between said engine component and said insert;
wherein said plurality of openings extend through said insert at a non-orthogonal angle with at least one outer surface of said insert, said plurality of openings defining an aperture length-to-diameter ratio,
wherein said aperture length-to-diameter ratio is between about 1 and about 10,
wherein each non-orthogonal angle is less than about 90 degrees and greater than about 0 degrees, and
wherein the array through said insert defines a plane within the at least one outer surface of said insert such that each opening of the plurality of openings falls within the plane and is spaced apart in both a first direction and a second direction from at least one other opening of said plurality of openings.

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 plurality of openings being a single size.

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

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

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

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

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

13. The engine component of claim 1 wherein said plurality of openings are aligned in the direction of an axis of said openings.

14. The engine component of claim 1 wherein said plurality of openings 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 between about 25 degrees and about 65 degrees.

18. 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.

19. 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 and defining an aperture length-to-diameter ratio,
wherein said aperture length-to-diameter ratio is between about 1 and about 5,
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, and
wherein each non-orthogonal angle is less than about 90 degrees and greater than about 0 degrees, and
wherein the array through said insert defines a plane within the at least one outer surface of said insert such that each opening of the plurality of openings falls within the plane and is spaced apart in both a first direction and a second direction from at least one other opening of said plurality of openings.

20. The engine component assembly of claim 19 , said array further comprising;
a first plurality of apertures placed apart a first distance;
a second plurality of apertures placed apart a second distance; and
a third plurality of apertures placed apart a third distance,
wherein the first plurality of apertures, the second plurality of apertures, and the third plurality of apertures are placed apart in a first direction,
wherein the second distance is greater than the first distance, and
wherein the third distance is greater than the second distance.

21. The engine component assembly of claim 20 , said array further comprising;
a fourth plurality of apertures placed apart a fourth distance; and
a fifth plurality of apertures placed apart a fifth distance,
wherein the fourth plurality of apertures and the fifth plurality of apertures are placed apart in a second direction, and
wherein the fifth distance is greater than the fourth distance.

22. The engine component assembly of claim 21 , said array further comprising;
a sixth plurality of apertures placed apart a sixth distance,
wherein the sixth plurality of apertures are placed apart in a second direction, and
wherein the sixth distance is greater than the fifth distance.

23. The engine component assembly of claim 22 wherein the 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 1.5.

24. The engine component assembly of claim 23 wherein the 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 about 0.5 and about 1.0, and
wherein the plurality of openings comprises more than one shape.

25. An engine component assembly, comprising:
an engine component having a cooled surface and 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 through said insert at a non-orthogonal angle to a surface of said insert, said plurality of openings forming an array through said insert and defining an aperture length-to-diameter ratio, said cooling flow path passing through said plurality of openings toward said cooled surface; and
a gap between said engine component and said insert,
wherein said aperture length-to-diameter ratio is between about 1 and about 2.5, and
wherein each non-orthogonal angle is less than about 90 degrees and greater than about 0 degrees, and
wherein the array through said insert defines a plane within the at least one outer surface of said insert such that each opening of the plurality of openings falls within the plane and is spaced apart in both a first direction and a se

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott
• Allen Jason Randolph
• Porter Ryan Nicholas
• Pritchard Byron Andrew
• Greenwell Christopher Joseph
• Stone Timothy Deryck
• Pritchard Andrew Stephen

Classifications

• F01D25/12

  Cooling · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title