Airfoil for a turbine engine

Patent metadata

Field	Value
Publication number	US-2016201476-A1
Application number	US-201514882551-A
Country	US
Kind code	A1
Filing date	Oct 14, 2015
Priority date	Oct 31, 2014
Publication date	Jul 14, 2016
Grant date	—

Abstract

An airfoil for a turbine engine includes a cooling cavity and a cooling fluid supply cavity which supplies cooling fluid to the cooling cavity through a passage. The cooling cavity can be provided with a swirl feature for imparting a swirling motion to the cooling fluid.

First claim

What is claimed is:

1 . An airfoil for a turbine section of a turbine engine, comprising:
a body having a leading edge wall and a trailing edge wall, with a first side wall and a second side wall extending between the leading and trailing edge walls to define a hollow interior; a separating wall located within the hollow interior to fluidly separate the hollow interior into a leading edge cavity and a cooling fluid supply cavity, with the separating wall forming a back wall of the leading edge cavity; a plurality of film holes extending through the leading edge wall to fluidly couple the leading edge cavity to an exterior of the leading edge wall; at least one cooling fluid passage extending through the separating wall to fluidly couple the supply cavity with the leading edge cavity through which a cooling jet of fluid may pass from the supply cavity into the leading edge cavity; and a swirl feature provided within the leading edge cavity at the leading edge wall and in the path of the cooling jet; wherein, when the cooling jet contacts the swirl feature, a swirling motion is imparted to the cooling jet.

2 . The airfoil of claim 1 wherein the at least one cooling fluid passage is oriented such that the cooling jet of fluid flows at least approximately tangentially to an inner surface of the leading edge wall.

3 . The airfoil of claim 2 wherein the at least one cooling fluid passage is oriented such that the centerline intersects the leading edge wall at a non-orthogonal angle.

4 . The airfoil of claim 1 wherein the separating wall spans between the first and second side walls.

5 . The airfoil of claim 1 wherein the separating wall forms a junction with at least one of the first side wall and the second side wall, and the at least one cooling fluid passage is located in the separating wall proximate to the junction.

6 . The airfoil of claim 5 wherein the at least one cooling fluid passage is located at the junction.

7 . The airfoil of claim 1 wherein the swirl feature comprises a plurality of swirl features.

8 . The airfoil of claim 7 wherein at least some of the plurality of swirl features are at least one of provided in the leading edge wall or extending from the leading edge wall.

9 . The airfoil of claim 8 wherein some of the plurality of swirl features are provided in the leading edge wall and some of the plurality of swirl features extend from the leading edge wall.

10 . The airfoil of claim 9 wherein the swirl features provided in the leading edge wall comprise concavities.

11 . The airfoil of claim 10 wherein the concavities comprise at least one of dimples or grooves.

12 . The airfoil of claim 11 wherein the grooves comprise at least one of intersecting grooves or helical grooves.

13 . The airfoil of claim 12 wherein the grooves comprise intersecting grooves and wherein the swirl features extending from the leading edge comprise spaces defined between the intersecting grooves.

14 . The airfoil of claim 7 wherein the plurality of swirl features have a predetermined arrangement.

15 . The airfoil of claim 14 wherein the predetermined arrangement comprises an array.

16 . The airfoil of claim 1 wherein the swirl feature is at least one of provided in the leading edge wall or extending from the leading edge wall.

17 . The airfoil of claim 16 wherein the swirl feature provided in the leading edge wall comprises a concavity.

18 . The airfoil of claim 17 wherein the concavity comprises at least one of a dimple or a groove.

19 . The airfoil of claim 18 wherein the swirl feature provided in the leading edge wall comprises multiple intersecting grooves or helical grooves.

20 . The airfoil of claim 19 wherein the swirl feature provided in the leading edge wall comprises multiple intersecting grooves and wherein the swirl feature extending from the leading edge comprise spaces defined between the intersecting grooves.

21 . The airfoil of claim 20 wherein the spaces form diamond-shaped features.

22 . The airfoil of claim 1 wherein the airfoil comprises at least one of a nozzle, a vane or a blade.

23 . An airfoil for a turbine section of a turbine engine, comprising:
a body having body walls defining a hollow interior; a separating wall located within the hollow interior to fluidly separate the hollow interior into a cooling cavity and a cooling fluid supply cavity; a plurality of film holes extending through one of the body walls to fluidly couple the cooling cavity to the exterior of the body; at least one cooling fluid passage extending through the separating wall to fluidly couple the supply cavity with the cooling cavity through which a cooling jet of cooling fluid may pass from the supply cavity into the cooling cavity; and a swirl feature provided within the cooling cavity at one of the body walls and in the path of the cooling jet; wherein, when the cooling jet contacts the swirl feature, a swirling motion is imparted to the cooling jet.

24 . The airfoil of claim 23 wherein the at least one cooling fluid passage is oriented such that the cooling jet of fluid flows at least approximately tangentially to an inner surface of one of the body walls.

25 . The airfoil of claim 24 wherein the at least one cooling fluid passage is oriented such that the centerline intersects one of the body walls at a non-orthogonal angle.

26 . The airfoil of claim 23 wherein the separating wall spans between two body walls.

27 . The airfoil of claim 23 wherein the separating wall forms a junction with at least one of the body walls, and the at least one cooling fluid passage is located in the separating wall proximate to the junction.

28 . The airfoil of claim 27 wherein the at least one cooling fluid passage is located at the junction.

29 . The airfoil of claim 23 wherein the swirl feature comprises a plurality of swirl features.

30 . The airfoil of claim 29 wherein at least some of the plurality of swirl features are at least one of provided in one of the body walls or extending from one of the body walls.

31 . The airfoil of claim 30 wherein some of the plurality of swirl features are provided in one of the body walls and some of the swirl features extend from one of the body walls.

32 . The airfoil of claim 31 wherein the swirl features provided in one of the body walls comprise concavities.

33 . The airfoil of claim 32 wherein the concavities comprise at least one of dimples or grooves.

34 . The airfoil of claim 33 wherein the grooves comprise at least one of intersecting grooves or helical grooves.

35 . The airfoil of claim 34 wherein the grooves comprise intersecting grooves and where the swirl features extending from the one of the body walls comprise spaces defined between the intersecting grooves.

36 . The airfoil of claim 29 wherein the plurality of swirl features have a predetermined arrangement.

37 . The airfoil of claim 36 wherein the predetermined arrangement comprises an array.

38 . The airfoil of claim 23 wherein the swirl feature is at least one of provided in one of the body walls or extending from one of the body walls.

3

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott
• Bergholz Robert Frederick
• Briggs Robert David
• Feldmann Kevin Robert

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/128

  Nozzles · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2250/22

  parallelepipedal · CPC title

• F01D5/186

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