Platform core feed for a multi-wall blade

Patent metadata

Field	Value
Publication number	US-10267162-B2
Application number	US-201615239994-A
Country	US
Kind code	B2
Filing date	Aug 18, 2016
Priority date	Aug 18, 2016
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

A cooling system for a turbomachine blade including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: a central cavity and a plurality of outer cavities, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the plurality of outer cavities; and a connection for fluidly connecting a second outer cavity of the plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.

First claim

What is claimed is:

1. A cooling system for a turbomachine blade including a multi-wall blade and a platform, comprising:
a cooling circuit for the multi-wall blade, the cooling circuit including a central cavity located between a first plurality of outer cavities disposed adjacent a first side of the multi-wall blade and a second plurality of outer cavities disposed adjacent a second, opposing side of the multi-wall blade, the first and second sides of the multi-wall blade extending from a leading edge and a trailing edge of the multi-wall blade and, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the first plurality of outer cavities; and
a connection for fluidly connecting a second outer cavity of the first plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.

2. The cooling system of claim 1 , wherein the first plurality of outer cavities comprises an odd number of outer cavities.

3. The cooling system of claim 1 , wherein the central cavity is configured to change a flow direction of the flow of cooling air.

4. The cooling system of claim 3 , wherein the flow direction comprises a radial flow direction.

5. The cooling system of claim 1 , wherein the first side of the multi-wall blade is selected from the group consisting of a pressure side and a suction side.

6. The cooling system of claim 1 , wherein the cooling circuit is selected from the group consisting of a mid-blade cooling circuit, a leading edge cooling circuit, and a trailing edge cooling circuit.

7. The cooling system of claim 1 , further comprising a plurality of apertures for exhausting the cooling air from the platform core as cooling film.

8. The cooling circuit of claim 1 , wherein the flow of cooling air flows through the first outer cavity of the first plurality of outer cavities in a first radial direction, and wherein the flow of cooling air flows through the second outer cavity of the first plurality of outer cavities in a second radial direction, opposite from the first radial direction.

9. The cooling circuit of claim 8 , wherein the first radial direction is an outward radial direction, and wherein the second radial direction is an inward radial direction.

10. A turbomachine, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, the turbine component including a plurality of turbomachine blades, and wherein at least one of the turbomachine blades includes a multi-wall blade and a platform;
a cooling circuit disposed within the multi-wall blade, the cooling circuit including a central cavity located between a first plurality of outer cavities disposed adjacent a first side of the multi-wall blade and a second plurality of outer cavities disposed adjacent a second, opposing side of the multi-wall blade, the first and second sides of the multi-wall blade extending from a leading edge and a trailing edge of the multi-wall blade and, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the first plurality of outer cavities;
and
a connection for fluidly connecting a second outer cavity of the first plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.

11. The turbomachine of claim 10 , wherein the first plurality of outer cavities comprises an odd number of outer cavities.

12. The turbomachine of claim 10 , wherein the central cavity is configured to change a flow direction of the flow of cooling air.

13. The turbomachine of claim 12 , wherein the flow direction comprises a radial flow direction.

14. The turbomachine of claim 10 , wherein the first side of the multi-wall blade is selected from the group consisting of a pressure side and a suction side.

15. The turbomachine of claim 10 , wherein the cooling circuit is selected from the group consisting of a mid-blade cooling circuit, a leading edge cooling circuit, and a trailing edge cooling circuit.

16. The turbomachine of claim 10 , further comprising a plurality of apertures for exhausting the cooling air from the platform core as cooling film.

17. The turbomachine of claim 10 , wherein the flow of cooling air flows through the first outer cavity of the first plurality of outer cavities in a first radial direction, and wherein the flow of cooling air flows through the second outer cavity of the first plurality of outer cavities in a second radial direction, opposite from the first radial direction.

18. The turbomachine of claim 17 , wherein the first radial direction is an outward radial direction, and wherein the second radial direction is an inward radial direction.

19. The turbomachine of claim 10 , wherein the cooling circuit comprises a serpentine cooling circuit.

20. A power generation system, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, the turbine component including a plurality of turbomachine blades, and wherein at least one of the turbomachine blades includes a multi-wall blade and a platform;
a shaft driven by the gas turbine system;
an electrical generator coupled to the shaft for generating electricity;
a cooling circuit disposed within the multi-wall blade, the cooling circuit including a central cavity located between a first plurality of outer cavities disposed adjacent a first side of the multi-wall blade and a second plurality of outer cavities disposed adjacent a second, opposing side of the multi-wall blade, the first and second sides of the multi-wall blade extending from a leading edge and a trailing edge of the multi-wall blade and, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the first plurality of outer cavities; and
a connection for fluidly connecting a second outer cavity of the first plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.

Assignees

• Gen Electric

Inventors

• Leary Brendon James
• Black Elisabeth Kraus
• Iduate Michelle Jessica
• Weber David Wayne

Classifications

• F05D2250/185

  serpentine-like · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F05D2260/202

  by film cooling · CPC title