Double impingement slot cap assembly

Patent metadata

Field	Value
Publication number	US-10577942-B2
Application number	US-201615354072-A
Country	US
Kind code	B2
Filing date	Nov 17, 2016
Priority date	Nov 17, 2016
Publication date	Mar 3, 2020
Grant date	Mar 3, 2020

Abstract

An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber directs cooling air inside the airfoil. The assembly comprises an impingement hole fluidly coupled with the cooling chamber. The impingement hole directs at least some of the cooling air out of the cooling chamber. A double impingement slot cap assembly forms a cover over the impingement hole. The double impingement slot cap assembly directs the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil.

First claim

What is claimed is:

1. An assembly comprising:
a cooling chamber disposed inside an airfoil, the cooling chamber configured to direct cooling air inside the airfoil;
an impingement hole fluidly coupled with the cooling chamber, wherein a first end of the impingement hole is at the cooling chamber and a second end of the impingement hole opposite the first end is spaced apart from the cooling chamber, the impingement hole configured to direct at least some of the cooling air out of the cooling chamber in a direction from the first end towards the second end; and
a double impingement slot cap assembly forming a cover over the impingement hole, wherein the double impingement slot cap assembly is separated from the airfoil by opposite first and second slots that diverge from the second end of the impingement hole to respective openings of the first and second slots, wherein the openings of the first and second slots are disposed along different exterior surfaces of the airfoil and are both elongated along a radial length of the airfoil parallel to a leading edge of the airfoil,
wherein the openings of the first and second slots are axially located between the leading edge of the airfoil and the first end of the impingement hole at the cooling chamber.

2. The assembly of claim 1 , wherein the double impingement slot cap assembly is elongated along the leading edge of the airfoil.

3. The assembly of claim 1 , wherein the double impingement slot cap assembly is elongated along a stagnation region of the airfoil.

4. The assembly of claim 1 , wherein the opposite first and second slots separating the double impingement slot cap assembly from the airfoil direct at least some of the cooling air exiting the cooling chamber through the impingement hole along the different exterior surfaces of the airfoil.

5. The assembly of claim 1 , wherein the opening of the first slot is on a pressure side of the airfoil and the opening of the second slot is on a suction side of the airfoil.

6. The assembly of claim 1 , wherein the double impingement slot cap assembly is spaced apart from the airfoil and is coupled with the airfoil by one or more supports.

7. The assembly of claim 1 , wherein the opposite first and second slots are transversely oriented with respect to the impingement hole and are configured to direct at least some of the cooling air along the exterior surfaces of the airfoil.

8. The assembly of claim 1 , wherein the double impingement slot cap assembly defines one or more cap film holes therethrough that are configured to direct the cooling air to the leading edge of the airfoil.

9. The assembly of claim 1 , wherein the impingement hole is configured to direct cooling air out of the cooling chamber to an interior surface of the double impingement slot cap assembly.

10. An assembly comprising:
a first cooling chamber and a second cooling chamber disposed inside an airfoil, the first and second cooling chambers configured to direct cooling air inside the airfoil, the second cooling chamber axially disposed between the first cooling chamber and a leading edge of the airfoil;
a first impingement hole axially disposed between the first cooling chamber and the second cooling chamber to fluidly couple the first cooling chamber with the second cooling chamber through the first impingement hole, the first impingement hole configured to direct at least some of the cooling air from the first cooling chamber into the second cooling chamber;
a second impingement hole axially disposed between the second cooling chamber and the leading edge of the airfoil, the second impingement hole fluidly coupled to the second cooling chamber; and
a double impingement slot cap assembly forming a cover over the second impingement hole, wherein the double impingement slot cap assembly is separated from the airfoil by opposite first and second slots that diverge from the second impingement hole to respective openings of the first and second slots, wherein the openings of the first and second slots are disposed along different exterior surfaces of the airfoil and are both elongated along a radial length of the airfoil parallel to the leading edge of the airfoil.

11. The assembly of claim 10 , wherein the double impingement slot cap assembly is elongated along the leading edge of the airfoil.

12. The assembly of claim 10 , wherein the double impingement slot cap assembly is spaced apart from the airfoil and is coupled with the airfoil by one or more supports.

13. The assembly of claim 10 , wherein the opposite first and second slots separating the double impingement slot cap assembly from the airfoil direct at least some of the cooling air exiting the second cooling chamber through the second impingement hole along the different exterior surfaces of the airfoil.

14. The assembly of claim 10 , wherein the opening of the first slot is on a pressure side of the airfoil and the opening of the second slot is on a suction side of the airfoil.

15. The assembly of claim 10 , wherein the opposite first and second slots are transversely oriented with respect to the impingement hole and are configured to direct at least some of the cooling air along the exterior surfaces of the airfoil.

16. The assembly of claim 10 , wherein the double impingement slot cap assembly defines one or more cap film holes therethrough that are configured to direct the cooling air to the leading edge of the airfoil.

17. The assembly of claim 10 , wherein the second impingement hole is configured to direct cooling air out of the cooling chamber to an interior surface of the double impingement slot cap.

18. An assembly comprising:
a cooling chamber disposed inside an airfoil, the cooling chamber configured to direct cooling air inside the airfoil;
an impingement hole fluidly coupled with the cooling chamber, wherein a first end of the impingement hole is at the cooling chamber and a second end of the impingement hole opposite the first end is spaced apart from the cooling chamber, the impingement hole configured to direct at least some of the cooling air out of the cooling chamber in a direction from the first end towards the second end; and
a double impingement slot cap assembly forming a cover over the impingement hole, the double impingement slot cap assembly is separated from the airfoil by opposite first and second slots that diverge from the second end of the impingement hole to respective openings of the first and second slots, wherein the openings of the first and second slots are disposed along different exterior surfaces of the airfoil and are both elongated along a radial length of the airfoil parallel to a leading edge of the airfoil,
wherein the double impingement slot cap assembly is spaced apart from the airfoil and is coupled with the airfoil by one or more supports, wherein an inner surface of the double impingement slot cap assembly defines portions of the first and second slots and the inner surface is one of planar or convex, the convex inner surface bowing towards the impingement hole.

19. The assembly of claim 1 , wherein an inner surface of the double impingement slot cap assembly is convex such that the inner surface bows towards the impingement hole.

20. The assembly of claim 18 , wherein the openings of the first and second slots are axially located between the leading edge of the airfoil and the first end of the impingement hole at the cooling chamber.

Assignees

• Gen Electric

Inventors

• Dyson Thomas Earl
• Getsinger Daniel

Classifications

• F01D5/187

  Convection cooling · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title