Engine component wall with a cooling circuit

Patent metadata

Field	Value
Publication number	US-2017328221-A1
Application number	US-201615152887-A
Country	US
Kind code	A1
Filing date	May 12, 2016
Priority date	May 12, 2016
Publication date	Nov 16, 2017
Grant date	—

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 and made from solid elements coupled to the outer wall, with interstitial spaces defined by the solid elements; 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 solid elements are integrally formed with the outer wall.

4 . The airfoil of claim 1 wherein the solid elements define at least one of a mesh, interlaced structure, or lattice.

5 . The airfoil of claim 1 wherein at least some of the solid elements 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 wherein at least some of the solid elements have discrete orifices.

8 . The airfoil of claim 1 wherein the at least one opening defines a centerline and at least some of the solid elements are parallel to the centerline.

9 . The airfoil of claim 8 wherein at least some of the solid elements are not parallel to the centerline.

10 . The airfoil of claim 9 wherein at least some of the parallel and non-parallel solid elements intersect each other.

11 . The airfoil of claim 10 wherein at least some of the solid elements have discrete orifices.

12 . The airfoil of claim 11 wherein at least an end portion of some of the solid elements are angled 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 solid elements extend 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 and made from solid elements coupled to the wall, with interstitial spaces defined by the solid elements; 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 solid elements are integrally formed with the wall.

18 . The engine component of claim 15 wherein the solid elements define at least one of a mesh, interlaced structure, or lattice.

19 . The engine component of claim 15 wherein at least some of the solid elements 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 solid elements have discrete orifices.

22 . The engine component of claim 15 wherein the at least one opening defines a centerline and at least some of the solid elements are parallel to the centerline.

23 . The engine component of claim 22 wherein at least some of the solid elements are not parallel to the centerline.

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

25 . The engine component of claim 24 wherein at least some of the solid elements have discrete orifices.

26 . The engine component of claim 25 wherein at least an end portion of some of the solid elements are angled 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 . The engine component of claim 15 wherein at least some of the solid elements extend beyond the opening.

29 . A method of making an engine component for a turbine engine comprising forming a wall with an opening having a framework within the opening that defines interstitial spaces, at least some of which include a porous structure.

30 . The method of claim 29 wherein at least two of the wall, opening, framework and porous structure are formed by additive manufacturing.

31 . The method of claim 30 wherein at least three of the wall, opening, framework and porous structure are formed by additive manufacturing.

32 . The method of claim 30 wherein all of the wall, opening, framework and porous structure are formed by additive manufacturing.

Assignees

• Gen Electric

Inventors

• Allen Jason Randolph
• Bunker Ronald Scott

Classifications

• F05D2230/31

  Layer deposition · CPC title

• F01D5/183

  Blade walls being porous · CPC title

• F01D9/041 Primary

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

• F05D2260/203

  by transpiration cooling · CPC title

• F05D2300/514

  Porosity · CPC title