Component for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10422232-B2
Application number	US-201715601007-A
Country	US
Kind code	B2
Filing date	May 22, 2017
Priority date	May 22, 2017
Publication date	Sep 24, 2019
Grant date	Sep 24, 2019

Abstract

A component for a gas turbine engine includes a wall that has an exterior surface and an interior surface spaced from the exterior surface. A cooling circuit extends from the interior surface to the exterior surface. The cooling circuit includes a feed passage that has a first end defining an inlet at the interior surface and a second end spaced from the first end. At least one second passage is in fluid communication with the feed passage. At least one slot passage is in fluid communication with the second end of the feed passage and a cooling slot in the exterior surface.

First claim

What is claimed is:

1. A component for a gas turbine engine comprising:
a wall having an exterior surface and an interior surface spaced from the exterior surface; and
a cooling circuit extending from the interior surface to the exterior surface, the cooling circuit includes:
a feed passage having a first end defining an inlet at the interior surface and a second end spaced from the first end;
at least one second passage including a first end located at the second end of the feed passage and in fluid communication with the feed passage; and
at least one slot passage including a first end located at the second end of the feed passage and in fluid communication with both the second end of the feed passage and a cooling slot in the exterior surface.

2. The component of claim 1 , wherein a second end of the at least one second passage is located at a mid-portion of the feed passage and in fluid communication with the feed passage.

3. The component of claim 2 , wherein the at least one second passage includes a plurality of second passages, the at least one slot passage includes a plurality of slot passages, and the plurality of second passages are in an alternating arrangement in a radial direction with the plurality of slot passages along the second end of the feed passage.

4. The component of claim 1 , wherein the at least one second passage is at least one exterior passage located between the feed passage and the exterior surface and the at least one exterior passage and the feed passage define a wall segment there between.

5. The component of claim 1 , wherein the at least one second passage is at least one interior passage located on an opposite side of the feed passage from the exterior surface and the at least one interior passage and the feed passage define a wall segment there between.

6. The component of claim 1 , wherein the component is an airfoil and the feed passage extends in an axial direction and feed passage includes a radial width at least equal to a radial width of both the at least one second passage and the at least one slot passage.

7. The component of claim 6 , wherein the cooling circuit is located adjacent a pressure side of the airfoil.

8. The component of claim 6 , wherein the cooling circuit is located adjacent a suction side of the airfoil.

9. A component for a gas turbine engine comprising:
a wall having an exterior surface and an interior surface spaced from the exterior surface; and
a cooling circuit extending from the interior surface to the exterior surface, the cooling circuit includes:
a feed passage having a first end defining an inlet at the interior surface and a second end spaced from the first end;
at least one second passage in fluid communication with the feed passage; and
at least one slot passage in fluid communication with both the second end of the feed passage and a cooling slot in the exterior surface, wherein the at least one second passage includes at least one interior passage and at least one exterior passage both spaced from the feed passage and the at least one interior passage, the at least one exterior passage, and the feed passage define wall segments there between.

10. The component of claim 9 , wherein a first end of each of the at least one interior passage is attached to the second end of the feed passage, a second end of each of the at least one interior passage is attached to a mid-portion of feed passage, a first end of each of the at least one exterior passage is attached to the second end of the feed passage, and a second end of each of the at least one exterior passage is attached to the mid-portion of the feed passage.

11. The component of claim 10 , wherein the at least one exterior passage, the at least one exterior passage, and the at least one slot passage are positioned in an alternating arrangement along the second end of the feed passage.

12. The component of claim 9 , wherein the at least one exterior passage is fluidly connected to the feed passage by a first plurality of connecting passages.

13. The component of claim 12 , wherein the at least one exterior passage is fluidly connected to the feed passage by a second plurality of connecting passages.

14. The component of claim 13 , wherein the first plurality of connecting passages and the second plurality of connecting passages are each spaced inward from opposing ends of the feed passage.

15. The component of claim 9 , wherein the at least one second passage is located in the wall between the feed passage and one of the interior surface or the exterior surface and the at least one second passage and the feed passage define a wall segment there between.

16. The component of claim 9 , wherein the component is an airfoil and the feed passage extends in an axial direction and feed passage includes a radial width at least equal to a radial width of both the at least one second passage and the at least one slot passage.

17. A method of forming a core assembly, the method comprising the steps of:
forming a trough in a core; and
attaching a refractory metal core to the trough, the refractory metal core comprising:
a feed portion having a first end attached to the core and a second end spaced from the core;
at least one slot portion extending from the second end of the feed portion; and
at least one second portion spaced from the feed portion configured to define a multi-walled segment in the core assembly.

18. The method of claim 17 , wherein a first end of each of the at least one second portion is attached to the second end of the feed portion and a second end of each of the at least one second portion is attached to a mid-region of the feed portion.

19. The method of claim 18 , wherein the at least one second portion includes at least one exterior portion and at least one interior portion, and the at least one slot portion, the at least one exterior portion, and the at least one interior portion are attached to the second end of the feed portion in an alternating arrangement.

20. The method of claim 17 , wherein the at least one second portion is attached to the feed portion by a plurality of stand offs.

21. The method of claim 20 , wherein the at least one second portion includes at least one interior portion and at least one exterior portion, the at least one interior portion and the at least one exterior portion are located on opposite sides of the feed portion.

Assignees

• United Technologies Corp

Inventors

• King Christopher

Classifications

• F01D25/12

  Cooling · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D5/187

  Convection cooling · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title

• F05D2220/32

  in gas turbines · CPC title