Engine component wall with a cooling circuit

Patent metadata

Field	Value
Publication number	US-10458259-B2
Application number	US-201615152887-A
Country	US
Kind code	B2
Filing date	May 12, 2016
Priority date	May 12, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include an opening. A framework can be disposed in the opening adapted to reduce the required flow through the opening to increase the efficiency of the engine and improve cooling.

First claim

What is claimed is:

1. An airfoil for a turbine engine, the airfoil comprising:
an outer wall having an outer surface and an inner surface bounding an interior, 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 opening formed in the outer wall;
a framework provided within the at least one opening defining interstitial spaces within the framework; and
a porous structure provided in at least some of the interstitial spaces.

2. The airfoil of claim 1 wherein the porous structure is provided in all the interstitial spaces.

3. The airfoil of claim 1 wherein the framework are integrally formed with the outer wall.

4. The airfoil of claim 1 wherein the framework defines at least one of a mesh, interlaced structure, or lattice with the interstitial spaces.

5. The airfoil of claim 1 wherein the framework is made of solid elements that are coupled to each other.

6. The airfoil of claim 5 wherein at least some of the solid elements are not coupled to each other.

7. The airfoil of claim 1 further comprising discrete orifices formed through the framework.

8. The airfoil of claim 1 wherein the at least one opening defines a centerline and at least a portion of the framework is arranged parallel to the centerline.

9. The airfoil of claim 8 wherein at least some of the framework is not parallel to the centerline.

10. The airfoil of claim 9 wherein at least some of the parallel and non-parallel framework intersects each other.

11. The airfoil of claim 10 wherein at least some of the framework includes discrete orifices.

12. The airfoil of claim 11 wherein at least an end portion of some of the framework is angled with respect to the centerline to define angled portions.

13. The airfoil of claim 12 wherein the angled portions are located within one of an inlet or outlet of the at least one opening.

14. The airfoil of claim 1 wherein at least some of the framework extends beyond the opening.

15. An engine component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas flow from the cooling fluid flow and having a first surface along with the hot gas flow in a hot flow path and a second surface facing the cooling fluid flow;
at least one opening formed in the wall;
a framework provided within the at least one opening, with interstitial spaces defined within the framework, wherein at least some of the framework extends beyond the at least one opening; and
a porous structure provided in at least some of the interstitial spaces.

16. The engine component of claim 15 wherein the porous structure is provided in all the interstitial spaces.

17. The engine component of claim 15 wherein the framework is integrally formed with the wall.

18. The engine component of claim 15 wherein the framework defines at least one of a mesh, interlaced structure, or lattice with the interstitial spaces.

19. The engine component of claim 15 wherein the framework includes solid elements that are coupled to each other.

20. The engine component of claim 19 wherein at least some of the solid elements are not coupled to each other.

21. The engine component of claim 15 wherein at least some of the framework has discrete orifices.

22. The engine component of claim 15 wherein the at least one opening defines a centerline and at least some of the framework is arranged parallel to the centerline.

23. The engine component of claim 22 wherein at least some of the framework is not parallel to the centerline.

24. The engine component of claim 23 wherein at least some of the parallel and non-parallel portions of the framework intersect each other.

25. The engine component of claim 24 wherein at least some of the framework has discrete orifices.

26. The engine component of claim 25 wherein at least an end portion of some of the framework is angled relative to the centerline to define angled portions.

27. The engine component of claim 26 wherein the angled portions are located within one of an inlet or outlet of the at least one opening.

28. An engine component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas flow from the cooling fluid flow and having a first surface along with the hot gas flow in a hot flow path and a second surface facing the cooling fluid flow;
at least one opening formed in the wall including an inlet and an outlet, and defining a centerline;
a framework provided within the at least one opening and including an end portion, with interstitial spaces defined within the framework, with at least some of the framework including discrete orifices and with at least some of the framework arranged parallel to the centerline and at least some of the framework not arranged parallel to the centerline, wherein at least some of the parallel portions of the frame work and some of the non-parallel portions of the framework intersect each other, and wherein the end portion is angled relative to the centerline to define an angled portion of the framework with the angled portions located within one of the inlet or the outlet of the at least one opening; and
a porous structure provided in at least some of the interstitial spaces.

29. The engine component of claim 28 wherein the porous structure is provided in all the interstitial spaces.

30. The engine component of claim 28 wherein the framework defines at least one of a mesh, interlaced structure, or lattice with the interstitial spaces.

31. The engine component of claim 28 wherein the framework includes solid elements that are coupled to each other.

32. The engine component of claim 31 wherein at least some of the solid elements are not coupled to each other.

Assignees

• Gen Electric

Inventors

• Allen Jason Randolph
• Bunker Ronald Scott

Classifications

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2230/31

  Layer deposition · CPC title

• F05D2260/203

  by transpiration cooling · CPC title

• F01D5/186

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