Hot gas path component having cast-in features for near wall cooling

Patent metadata

Field	Value
Publication number	US-9938899-B2
Application number	US-201514739791-A
Country	US
Kind code	B2
Filing date	Jun 15, 2015
Priority date	Jun 15, 2015
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface of the substrate defines at least one interior space. At least a portion of the outer surface of the substrate includes a recess formed therein. The recess includes a bottom surface and a groove extending at least partially along the bottom surface of the recess. A cover is disposed within the recess and covers at least a portion of the groove. The groove is configured to channel a cooling fluid therethrough to cool the cover.

First claim

What is claimed is:

1. A hot gas path component comprising:
an integrally formed, unitarily cast portion comprising a substrate, said substrate comprising an outer surface, an inner surface, and a thickness therebetween, said inner surface defining at least one interior space, said integrally formed, unitarily cast portion defining a cast-in recess having a first depth relative to said outer surface, said cast-in recess comprising a bottom surface;
a groove machined into said bottom surface of said cast-in recess, said groove having a second depth relative to said outer surface, the second depth is less than the thickness of said substrate; and
a cover disposed within said recess and covering at least a portion of said groove,
wherein said groove is configured to channel a cooling fluid therethrough to cool said cover.

2. The hot gas path component in accordance with claim 1 , further comprising an inlet passage machined into said substrate, said inlet passage extending from said groove to said at least one interior space, wherein said inlet passage is configured to channel the cooling fluid to said groove and provide convection cooling to said cover and said substrate.

3. The hot gas path component in accordance with claim 1 , wherein the first depth of said cast-in recess is a uniform depth relative to and conforming to said outer surface of said substrate.

4. The hot gas path component in accordance with claim 3 , wherein the first depth of said cast-in recess is substantially equal to a thickness of said cover.

5. The hot gas path component in accordance with claim 1 , wherein said substrate further comprises an airfoil extending between a first platform and a second platform.

6. The hot gas path component in accordance with claim 5 , wherein said substrate further comprises a cast in fillet formed at the intersection of said airfoil and respective said first and second platforms.

7. The hot gas path component in accordance with claim 1 , wherein said integrally formed, unitarily cast portion further comprises at least one cast-in reference datum defined in said outer surface of said substrate, said groove is machined in spaced relationship to said at least one cast-in reference datum.

8. A hot gas path component comprising:
an integrally formed, unitarily cast portion comprising a substrate, said substrate comprising an outer surface and an inner surface, said inner surface defining at least one interior space, said integrally formed, unitarily cast portion defining a cast-in reference datum;
a plurality of grooves machined into a recess defined in said outer surface of said substrate, each of said grooves in spaced relationship to said cast-in reference datum; and
a cover disposed over at least a portion of said groove,
wherein said grooves are configured to channel a cooling fluid therethrough to cool said cover.

9. The hot gas path component in accordance with claim 8 , further comprising an inlet passage extending from said grooves to said interior space, wherein said inlet passage is configured to channel the cooling fluid to said grooves and provide convection cooling to said cover.

10. The hot gas path component in accordance with claim 8 , wherein said integrally formed, unitarily cast portion further comprises said recess defined in said outer surface of said substrate.

11. The hot gas path component in accordance with claim 8 , wherein said recess comprises a bottom surface, said grooves extending at least partially along said bottom surface of said recess.

12. The hot gas path component in accordance with claim 8 , wherein said cover is disposed within said recess covering at least a portion of said grooves.

13. The hot gas path component in accordance with claim 8 , wherein a depth of said recess is a uniform depth relative to and conforming to said outer surface of said substrate.

14. The hot gas path component in accordance with claim 13 , wherein the depth of said recess is substantially equal to a thickness of said cover.

15. The hot gas path component in accordance with claim 8 , wherein said integrally formed, unitarily cast portion further comprises a first platform, an airfoil, and an opposing second platform integrally joined longitudinally together, and at least one cast in fillet formed at an intersection between said airfoil and at least one of said first platform and said second platform.

16. A gas turbine engine comprising:
a compressor;
a turbine coupled to said compressor; and
a hot gas path component disposed in a least one of said compressor and said turbine, said hot gas path component comprising:
an integrally formed, unitarily cast portion comprising a substrate, said substrate comprising an outer surface and an inner surface, said inner surface defining at least one interior space, said integrally formed, unitarily cast portion defining a cast-in recess, said cast-in recess comprising a bottom surface having a first width;
a plurality of grooves machined into said bottom surface of said cast-in recess, each of said grooves comprising a second width less than the first width; and
a cover disposed over at least a portion of said groove,
wherein said groove is configured to channel a cooling fluid therethrough to cool said cover.

17. The gas turbine engine in accordance with claim 16 , wherein said hot gas path component further comprises an inlet passage machined into said substrate, said inlet passage extending from said grooves to said at least one interior space, wherein said inlet passage is configured to channel the cooling fluid to said grooves and provide convection cooling to said cover.

18. The gas turbine engine in accordance with claim 16 , wherein said integrally formed, unitarily cast portion further comprises a cast-in reference datum defined in said outer surface of said substrate, said grooves are machined in spaced relationship to said cast-in reference datum.

19. The gas turbine engine in accordance with claim 16 , wherein said integrally formed, unitarily cast portion further comprises a first platform, an airfoil, and an opposing second platform integrally joined longitudinally together, and at least one cast in fillet formed at an intersection between said airfoil and at least one of said first platform and said second platform.

20. The gas turbine engine in accordance with claim 16 , wherein said cover is disposed within said recess covering at least a portion of said grooves.

Assignees

• Gen Electric

Inventors

• Miranda Carlos Miguel
• Kottilingam Srikanth Chandrudu
• Lacy Benjamin Paul

Classifications

• F05D2260/202

  by film cooling · CPC title

• F05D2230/21

  by casting · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/186

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

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title