Airfoil having cooling circuit

Patent metadata

Field	Value
Publication number	US-10415396-B2
Application number	US-201615150634-A
Country	US
Kind code	B2
Filing date	May 10, 2016
Priority date	May 10, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

First claim

What is claimed is:

1. An airfoil for a turbine engine, the airfoil comprising:
an outer wall having an outer surface facing an exterior and an inner surface bounding an interior space, the outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a root and a tip;
at least one coating applied to the outer surface;
at least one channel formed in the outer surface and at least one film hole passing through the at least one coating to the at least one channel to fluidly connect the exterior and the at least one channel;
at least one wall cooling passage provided within at least a portion of an interior of the outer wall and another at least one film hole passing through the at least one coating and the portion of the interior of the outer wall to the at least one wall cooling passage to fluidly connect the exterior and the at least one wall cooling passage; and
first and second supply circuits located within the interior of the outer wall, with the first supply circuit fluidly coupling a first air supply to the at least one channel to define at least one skin cooling circuit and the second supply circuit fluidly coupling a second air supply to the at least one wall cooling passage to define at least one wall cooling circuit;
wherein the at least one wall cooling passage is located internally of the at least one channel between the second supply circuit and the at least one channel and the at least one skin cooling circuit and the at least one wall cooling circuit retain fluidly separate layers of cooling extending from the supply circuits to the exterior.

2. The airfoil of claim 1 wherein the first and second air supplies supply a same conditioned air.

3. The airfoil of claim 2 wherein the same conditioned air is cooling air.

4. The airfoil of claim 3 wherein the first and second supply circuits are the same supply circuit.

5. The airfoil of claim 1 wherein the first and second air supplies supply differently conditioned air.

6. The airfoil of claim 5 wherein the differently conditioned air comprises at least one cooling air supply.

7. The airfoil of claim 1 wherein the at least one skin cooling circuit and the at least one wall cooling circuit are operated in parallel.

8. The airfoil of claim 1 wherein the at least one skin cooling circuit is multiple skin cooling circuits.

9. The airfoil of claim 1 wherein the at least one wall cooling circuit is multiple wall cooling circuits.

10. The airfoil of claim 9 wherein the at least one skin cooling circuit is multiple skin cooling circuits.

11. The airfoil of claim 1 wherein the at least one channel comprises multiple channels.

12. The airfoil of claim 11 wherein the at least one film hole is multiple film holes for each of the multiple channels.

13. The airfoil of claim 1 wherein the supply circuits define a first flow direction, the at least one channel defines a second flow direction, and the at least one wall cooling passage defines a third flow direction.

14. The airfoil of claim 13 wherein at least two of the first, second and third flow directions are the same direction.

15. The airfoil of claim 14 wherein the second and third flow directions are the same direction.

16. The airfoil of claim 13 wherein at least two of the first, second and third flow directions are opposite.

17. The airfoil of claim 16 wherein the second and third flow directions are opposite.

18. The airfoil of claim 1 wherein the at least one coating comprises multiple coatings.

19. An engine component for a turbine engine, which generates a hot air flow, and provides a cooling fluid flow, the component comprising:
a wall separating the hot air flow from the cooling fluid flow and having a first surface along with the hot air flow in a hot flow path and a second surface facing the cooling fluid flow;
at least one coating applied to the first surface;
at least one channel formed in the first surface and at least one hole passing through the at least one coating to the at least one channel;
at least one wall cooling passage provided within at least a portion of an interior of the wall; and
first and second supply circuits, with the first supply circuit fluidly coupling the cooling fluid flow to the at least one channel to define at least one skin cooling circuit and the second supply circuit fluidly coupling the cooling fluid flow to the at least one wall cooling passage to define at least one wall cooling circuit;
wherein the at least one wall cooling passage is located internally of the at least one channel between the second supply circuit and the at least one channel and the at least one skin cooling circuit and the at least one wall cooling passage retain fluidly separate layers of cooling extending between the hot air flow and the cooling fluid flow.

20. The engine component of claim 19 wherein the at least one skin cooling circuit and wall cooling circuit are operated in parallel.

21. The engine component of claim 19 wherein the at least one skin cooling circuit is multiple skin cooling circuits.

22. The engine component of claim 19 wherein the at least one wall cooling circuit is multiple wall cooling circuits.

23. The engine component of claim 22 wherein the at least one skin cooling circuit is multiple skin cooling circuits.

24. The engine component of claim 19 wherein the at least one channel further comprising multiple channels.

25. The engine component of claim 24 wherein the at least one hole is multiple holes for each of the multiple channels.

26. The engine component of claim 19 wherein the first and second supply circuits define a first flow direction, the at least one channel defines a second flow direction, and the at least one wall cooling passage defines a third flow direction.

27. The engine component of claim 26 wherein at least two of the first, second and third flow directions are the same direction.

28. The engine component of claim 27 wherein the second and third flow directions are the same direction.

29. The engine component of claim 26 wherein at least two of the first, second and third flow directions are opposite.

30. The engine component of claim 29 wherein the second and third flow directions are opposite.

31. The engine component of claim 19 wherein the at least one coating comprises multiple coatings.

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott

Classifications

• F05D2230/90

  Coating; Surface treatment · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title