Engine component with porous trench

Patent metadata

Field	Value
Publication number	US-10508551-B2
Application number	US-201615238150-A
Country	US
Kind code	B2
Filing date	Aug 16, 2016
Priority date	Aug 16, 2016
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

First claim

What is claimed is:

1. A component for a turbine engine, which generates a hot flow and provides a cooling fluid flow, the component comprising:
an outer wall defining an interior and separating the hot flow from the cooling fluid flow and having a hot surface facing the hot flow and a cooling surface facing the cooling fluid flow;
at least one trench disposed in the hot surface;
at least one hole including an inlet and an outlet in the outer wall fluidly coupling the interior to the trench;
a porous material at least partially filling the at least one trench and located at the outlet of the at least one hole; and
a solid non-porous element provided within the porous material.

2. The component of claim 1 wherein the at least one trench includes multiple trenches.

3. The component of claim 2 wherein the multiple trenches are spaced from each other.

4. The component of claim 3 wherein the multiple trenches are parallel to each other.

5. The component of claim 3 wherein the multiple trenches are arranged in a row.

6. The component of claim 3 wherein the multiple trenches are arranged in one of a row or parallel to one another.

7. The component of claim 6 wherein the multiple trenches include an arcuate profile defining an apex and the at least one hole is disposed on the apex.

8. The component of claim 1 wherein the at least one hole includes multiple holes.

9. The component of claim 8 wherein the multiples holes are arranged in a row.

10. The component of claim 1 wherein the solid non-porous element is shaped to direct a flow of cooling fluid passing through the porous material.

11. An airfoil for a turbine engine, the airfoil comprising:
an outer wall bounding an interior and defining a pressure side and a suction side extending chord-wise between a leading edge and a trailing edge and extending in a span-wise direction between a root and a tip;
multiple discrete trenches aligned with one another in the span-wise direction near or along the leading edge, with at least some of the multiple trenches having different lengths in the span-wise direction;
multiple holes in the outer wall fluidly coupling the interior to the multiple discrete trenches; and
a porous material provided in each of the multiple discrete trenches.

12. The airfoil of claim 11 wherein the multiple discrete trenches are arranged along the leading edge.

13. The airfoil of claim 11 wherein the multiple discrete trenches are parallel to each other.

14. The airfoil of claim 11 wherein the multiple discrete trenches are arranged in a row.

15. The airfoil of claim 11 wherein the multiple discrete trenches are arranged in one of a row or parallel to one another.

16. The airfoil of claim 11 wherein the multiple discrete trenches includes an arcuate profile defining an apex and the multiple holes are disposed at the apex.

17. The airfoil of claim 11 wherein the multiple holes are arranged in at least one row.

18. The airfoil of claim 11 further comprising a solid non-porous element extending at least partially along the multiple discrete trenches.

19. A method of providing a flow of cooling fluid along a trench disposed along a component for a turbine engine, the method comprising:
supplying the flow of cooling fluid to an interior of the component;
passing at least a portion of the flow of cooling fluid through at least one hole that includes an inlet and an outlet, and through a porous material located at the outlet of the at least one hole;
directing the flow of cooling fluid using a solid non-porous element disposed in the porous material; and exhausting the flow of cooling fluid through the trench.

20. The method of claim 19 wherein the component is an airfoil with the trench disposed along a leading edge of the airfoil.

21. The method of claim 19 further comprising providing the flow of cooling fluid from the interior with the at least one hole to the trench through a plurality of holes wherein the at least one hole is included in the plurality of holes.

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott

Classifications

• F01D5/183 Primary

  Blade walls being porous · CPC title

• F05D2250/294

  grooved · CPC title

• F05D2300/612

  Foam · CPC title

• F04D29/5846

  cooling by injection · CPC title

• F05D2260/203

  by transpiration cooling · CPC title