Endwall cooling system

Patent metadata

Field	Value
Publication number	US-10370983-B2
Application number	US-201715663462-A
Country	US
Kind code	B2
Filing date	Jul 28, 2017
Priority date	Jul 28, 2017
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

An air distribution system for cooling a component in a heated gas environment may be provided, where the air distribution system includes a wall and a plate. The wall includes an inner surface, an outer surface configured to be exposed to the heated gas environment, and a protrusion extending from the inner surface of the wall. The plate is fixedly coupled to the protrusion and is space apart from the inner surface of the wall. The plate includes an outer edge. A passage is defined between the plate and the inner surface of the wall. The inlet of the passage is defined by the outer edge of the plate.

First claim

What is claimed is:

1. An air distribution system for cooling a component in a heated gas environment of a gas turbine engine, comprising:
a wall comprising an inner surface, an outer surface configured to be exposed to the heated gas environment, and a protrusion extending from the inner surface of the wall; and
a plate spaced apart from the inner surface of the wall, the plate comprising an outer edge, the plate fixedly coupled to the protrusion, wherein a passage is defined between the plate and the inner surface of the wall, and wherein an inlet of the passage is defined by the outer edge of the plate.

2. The air distribution system of claim 1 , wherein the wall comprises an opening extending between the inner surface and the outer surface of the wall, the opening defining an outlet of the passage.

3. The air distribution system of claim 2 , wherein the opening of the wall is arranged proximate to the protrusion.

4. The air distribution system of claim 2 , wherein the opening is positioned on the wall so as to maximize distance between the outer edge of the plate and the opening of the wall.

5. The air distribution system of claim 1 , wherein the protrusion is fixedly coupled to a center of the plate.

6. The air distribution system of claim 1 , wherein the protrusion is fixedly coupled to a portion of the outer edge of the plate.

7. The air distribution system of claim 1 , wherein one of the wall or the plate comprises a rib extending into the passage, wherein the rib is configured to direct air flow from the inlet of the passage to an outlet of the passage.

8. The air distribution system of claim 1 , wherein the plate comprises an intact surface extending from a first outer edge of the plate to an opposing second outer edge of the plate.

9. The air distribution system of claim 1 , wherein one of the wall or the plate comprises a plurality of pins extending in the passage, and wherein the plurality of pins are shaped and arranged to create turbulence in a fluid that passes through the passage.

10. The air distribution system of claim 1 , comprising a plurality of plates and a plurality of protrusions, wherein each plate is coupled one of the plurality of protrusions, wherein each of the plurality of plates is spaced apart from each another, and wherein the inlet of the passage is at least partially defined by a gap between the respective outer edges of at least two of the plurality of plates.

11. A turbine vane comprising:
a wall comprising an inner surface, an outer surface, and a protrusion extending from the inner surface of the wall;
a plate spaced apart from the inner surface of the wall, the plate comprising an outer edge, wherein the plate is fixedly coupled to the protrusion; and
an airfoil extending outwardly from the outer surface of the wall, wherein a passage is defined between the plate and the inner surface of the wall, and wherein an inlet of the passage is defined by the outer edge of the plate.

12. The turbine vane of claim 11 , wherein a perimeter of the plate defined by the outer edge of the plate is greater than a perimeter of the protrusion which is fixedly coupled to the plate.

13. The turbine vane of claim 11 , further comprising a cavity within the airfoil, the passage having an outlet which is in fluid communication with the cavity of the airfoil.

14. The turbine vane of claim 13 , wherein the airfoil comprises a boss which extends inwardly from the inner surface of the wall, wherein the outlet of the passage is defined by an opening in the boss.

15. The turbine vane of claim 14 , wherein the protrusion is the boss of the airfoil.

16. The turbine vane of claim 15 , wherein the plate encircles the boss of the airfoil.

17. The turbine vane of claim 16 , wherein the wall comprises a raised element extending transversely to and aligned with the outer edge of the plate, wherein the inlet of the passage is at least partially defined by a gap between the raised element of the wall and the outer edge of the plate.

18. A method of cooling a component of a turbine vane comprising:
supplying cooling air to a passage, wherein the passage is defined by a wall of the turbine vane and a plate spaced apart from the wall, wherein the plate is fixedly coupled to a protrusion which extends between the plate and the wall, and wherein an inlet of the passage is defined by an outer edge of the plate; and
releasing the cooling air from the passage through an outlet of the passage.

19. The method of claim 18 , wherein the cooling air is released through an opening in the wall to an outer surface of the wall.

20. The method of claim 18 , wherein the cooling air is released into a cavity of an airfoil of the turbine vane.

Assignees

• Rolls Royce Corp

Inventors

• Weaver John A
• Lambert Tony A

Classifications

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F04D29/5846

  cooling by injection · CPC title

• F04D29/2255

  flow-channels with a special cross-section contour, e.g. ejecting, throttling or diffusing effect · CPC title

• F04D29/2272

  for influencing flow or boundary layer · CPC title

• F05D2240/81

  Cooled platforms · CPC title