CMC component cooling cavities

Patent metadata

Field	Value
Publication number	US-10934854-B2
Application number	US-201816127483-A
Country	US
Kind code	B2
Filing date	Sep 11, 2018
Priority date	Sep 11, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a core including an exterior surface extending along a length between a first end and a second end, wherein the core at least partially defines a first cooling cavity and a second cooling cavity on the exterior surface, the first and second cooling cavities each extending from the first end along at least a portion of the length of the core, the core at least partially defining a cross-over hole fluidly coupling the first cooling cavity and the second cooling cavity, and wherein the first and second cooling cavities are fluidly coupled to an air supply at the first end; and
an outer enclosure including an outer surface, the outer enclosure positioned outside the core and extending from the first end of the core along at least a portion of the length of the core, wherein the outer enclosure defines a first film hole in fluid communication with the first cooling cavity and a second film hole in fluid communication with the second cooling cavity, the first film hole and the second film hole extending through the outer enclosure, wherein the outer enclosure at least partially defines the first cooling cavity and the second cooling cavity.

2. The component of claim 1 , wherein the outer enclosure extends along the full length of the core.

3. The component of claim 1 , wherein the first cooling cavity extends along the full length of the core.

4. The component of claim 1 , wherein at least one of the core or the outer enclosure is formed from a ceramic matrix composite material.

5. The component of claim 1 , wherein both the core and the outer enclosure are formed from a ceramic matrix composite material.

6. The component of claim 1 , wherein the component is a turbine rotor blade and the outer enclosure defines an airfoil extending from the first end, the turbine blade further comprising:
an inner band positioned at the first end of the turbine blade, wherein the inner band is coupled to a rotating shaft of the gas turbine engine.

7. The component of claim 1 , wherein the component is a turbine stator vane and the outer enclosure defines an airfoil extending from the first end, the turbine stator vane further comprising:
an inner band positioned at the first end of the turbine stator vane; and
an outer band positioned at the second end of the turbine stator vane, wherein the airfoil extends between the inner band and the outer band.

8. The component of claim 3 , wherein the second cooling cavity extends along the full length of the core.

9. The component of claim 6 , wherein the first cooling cavity extends around the exterior surface and is located on a pressure side, a leading edge, and a suction side of the core.

10. The component of claim 1 , wherein the first film hole is one of a plurality of film holes that extend along a span length of the component.

11. The component of claim 1 , wherein the first film hole is one of a plurality of film holes that extend along a chord length of the component.

12. A partially formed component for a gas turbine engine, comprising:
a core including an exterior surface extending along a length between a first end and a second end, wherein the core at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length of the core, and wherein the cooling cavity is configured to be fluidly coupled to an air supply at the first end;
a filler material extending along at least a portion of the cooling cavity; and
an outer enclosure including an outer surface, the outer enclosure positioned outside the core and extending from the first end of the core along at least a portion of the length of the core, wherein the outer enclosure at least partially defines the cooling cavity, and wherein the outer enclosure abuts the filler material such that the outer enclosure secures the filler material within the cooling cavity,
wherein the filler material prevents the cooling cavity from collapsing during a process to finish forming the partially formed component, and wherein the filler material at least partially dissipates during the process to finish forming the partially formed component.

13. The partially formed component of claim 12 , wherein the filler material extends along a full length of the cooling cavity.

14. The partially formed component of claim 12 , wherein the cooling cavity extends along the full length of the core and the filler material extends along a full length of the cooling cavity.

15. The partially formed component of claim 14 , wherein the outer enclosure extends along the full length of the core and abuts the filler material along the full length of the cooling cavity.

16. The partially formed component of claim 12 , wherein the core at least partially defines a second cooling cavity on the exterior surface of the core and extending from the first end along at least a portion of the length of the core, wherein the second cooling cavity is configured to be fluidly coupled to the air supply at the first end, and wherein the outer enclosure also at least partially defines the second cooling cavity, wherein the partially formed component further comprises:
a second filler material extending along at least a portion of the second cooling cavity, wherein the outer enclosure abuts the second filler material such that the outer enclosure secures the second filler material within the second cooling cavity.

17. The partially formed component of claim 16 , wherein the core at least partially defines a cross-over hole fluidly coupling the cooling cavity and the second cooling cavity.

18. The partially formed component of claim 17 , further comprising:
a third filler material extending between the cooling cavity and the second cooling cavity, wherein the outer enclosure abuts the third filler material such that the outer enclosure secures the third filler material within the cross-over hole.

19. The partially formed component of claim 12 , wherein the filler material comprises at least one of a polymer matrix, a x-linked polyvinyl butyral, or a poly paraphenylene terephthalamide.

20. The partially formed component of claim 12 , wherein the filler material further comprises boron nitride.

Assignees

• Gen Electric

Inventors

• Weaver Matthew Mark
• Montgomery Kurtis C
• Verrilli Michael James

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2300/433

  Polyamides, e.g. NYLON · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D25/12

  Cooling · CPC title