Cooling circuits for a multi-wall blade

Patent metadata

Field	Value
Publication number	US-10352176-B2
Application number	US-201615334474-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A trailing edge cooling system for a multi-wall blade, including: a cooling circuit, including: an outward leg extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a return leg extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a turn for coupling the outward leg and the return leg; wherein the outward leg is radially offset from the return leg along a radial axis of the multi-wall blade.

First claim

What is claimed is:

1. A trailing edge cooling system for a multi-wall blade, comprising:
a coolant feed passage;
a coolant collection passage; and
a plurality of cooling circuits, each of the plurality of cooling circuits including:
an outward leg channel extending toward a trailing edge of the multi-wall blade and fluidly coupled to the coolant feed passage, the outward leg channel configured to receive a flow of coolant from the coolant feed passage;
a return leg channel extending away from the trailing edge of the multi-wall blade and fluidly coupled to the coolant collection passage; and
a turn channel for fluidly coupling the outward leg channel and the return leg channel;
wherein the return leg channel is configured to direct all of the flow of coolant into the coolant collection passage,
wherein the outward leg channel is radially offset from the return leg channel along a radial axis of the multi-wall blade,
wherein, for at least one of the plurality of cooling circuits, the return leg channel is circumferentially offset relative to the outward leg channel, and
wherein, for at least one of the plurality of cooling circuits, the outward leg channel extends solely along a suction side of the multi-wall blade and the return leg channel extends solely along a pressure side of the multi-wall blade, or wherein the outward leg channel extends solely along the pressure side of the multi-wall blade and the return leg channel extends solely along the suction side of the multi-wall blade.

2. The trailing edge cooling system according to claim 1 , wherein the coolant collection passage is fluidly coupled to at least one other cooling circuit of the multi-wall blade.

3. The trailing edge cooling system according to claim 2 , wherein the at least one other cooling circuit provides at least one of film cooling, convection cooling, or impingement cooling.

4. The trailing edge cooling system according to claim 1 , wherein, for at least one of the plurality of cooling circuits, the radial offset of the outward leg channel from the return leg channel is selected from the group consisting of: radially outward from the return leg channel and radially inward from the return leg channel.

5. The trailing edge cooling system according to claim 1 , wherein, for at least one of the plurality of cooling circuits, the return leg channel is a different size than the outward leg channel.

6. The trailing edge cooling system according to claim 1 , wherein the plurality of the cooling circuits extend at least partially along a radial length of the trailing edge of the multi-wall blade.

7. The trailing edge cooling system according to claim 1 , wherein, for at least one of the plurality of cooling circuits, a size of the outward leg channel and a size of the return leg channel vary according to a radial position of the cooling circuit in the trailing edge of the multi-wall blade.

8. A multi-wall turbine blade, comprising:
a trailing edge cooling system disposed within the multi-wall turbine blade, the trailing edge cooling system comprising:
a coolant feed passage;
a coolant collection passage; and
a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the multi-wall blade, each of the plurality of cooling circuits including:
an outward leg channel extending toward the trailing edge of the multi-wall blade and fluidly coupled to the coolant feed passage, the outward leg channel configured to receive a flow of coolant from the coolant feed passage;
a return leg channel extending away from the trailing edge of the multi-wall blade and fluidly coupled to the coolant collection passage; and
a turn channel for fluidly coupling the outward leg channel and the return leg channel;
wherein the return leg channel is configured to direct all of the flow of coolant into the coolant collection passage,
wherein the outward leg channel is radially offset from the return leg channel along a radial axis of the multi-wall blade,
wherein, for at least one of the plurality of cooling circuits, the return leg channel is circumferentially offset relative to the outward leg channel, and
wherein, for at least one of the plurality of cooling circuits, the outward leg channel extends solely along a suction side of the multi-wall blade and the return leg channel extends solely along a pressure side of the multi-wall blade, or wherein the outward leg channel extends solely along the pressure side of the multi-wall blade and the return leg channel extends solely along the suction side of the multi-wall blade.

9. The multi-wall turbine blade according to claim 8 , wherein the coolant collection passage is fluidly coupled to at least one other cooling circuit in the multi-wall blade.

10. The multi-wall turbine blade according to claim 9 , wherein the at least one other cooling circuit provides at least one of film cooling, convection cooling, or impingement cooling.

11. The multi-wall turbine blade according to claim 8 , wherein, for at least one of the plurality of cooling circuits, the radial offset of the outward leg channel from the return leg channel is selected from the group consisting of: radially outward from the return leg channel and radially inward from the return leg channel.

12. The multi-wall turbine blade according to claim 8 , wherein, for at least one of the plurality of cooling circuits, the return leg channel is a different size than the outward leg channel.

13. The multi-wall turbine blade according to claim 8 , wherein, for at least one of the plurality of cooling channels, a size of the outward leg channel and a size of the return leg vary according to a radial position of the cooling circuit in the trailing edge of the multi-wall blade.

14. 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 turbine blades, at least one of the turbine blades including a multi-wall blade; and
a trailing edge cooling system disposed within the multi-wall blade, the trailing edge cooling system including:
a coolant feed passage;
a coolant collection passage; and
a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the multi-wall blade, each of the plurality of cooling circuits including:
an outward leg channel extending toward the trailing edge of the multi-wall blade and fluidly coupled to the coolant feed passage, the outward leg channel configured to receive a flow of coolant from the coolant feed passage;
a return leg channel extending away from the trailing edge of the multi-wall blade and fluidly coupled to the coolant collection passage; and
a turn channel for fluidly coupling the outward leg channel and the return leg channel;
wherein the return leg channel is configured to direct all of the flow of coolant into the coolant collection passage,
wherein the outward leg channel is radially offset from the return leg channel along a radial axis of the multi-wall blade, and the outward leg channel is circumferentially offset relative to the return leg channel, and
wherein, for at least one of the plurality of cooling circuits, the outward leg channel extends solely along a suction side of the multi-wall blade and the return leg channel extends solely along a pressure side of the multi-wall blade, or wherein the outward leg channel extends solely along the pressure side of the multi-wall blade and the return leg channel extends solely along the suction side of the multi-wall blade.

15. The turbomachine o

Assignees

• Gen Electric

Inventors

• Weber David Wayne
• Foster Gregory Thomas

Classifications

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2220/32

  in gas turbines · CPC title