Turbomachine blade with trailing edge cooling circuit

Patent metadata

Field	Value
Publication number	US-10450950-B2
Application number	US-201615334448-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A turbomachine blade according to various embodiments includes: a body having: a leading edge; a trailing edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side; a root; and a tip opposing the root; and a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including: a first section extending from the root toward the tip along the pressure side; a second section extending from the first section toward the trailing edge; and a third section extending from the trailing edge along the suction side, wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge.

First claim

What is claimed is:

1. A turbomachine blade comprising:
a body having: a leading edge; a trailing edge opposing the leading edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side, extending between the leading edge and the trailing edge; a root; and a tip opposing the root; and
a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including: a first section extending from the root toward the tip along the pressure side; a second section extending from the first section toward the trailing edge; and a third section extending from the trailing edge along the suction side,
wherein the first section, the second section, and the third section are fluidly connected, and the second section and the third section collectively wrap around an interior region within the trailing edge, and
wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge.

2. The turbomachine blade of claim 1 , further comprising a pressure side heat transfer element within the second section for directing flow of the heat transfer fluid.

3. The turbomachine blade of claim 2 , wherein the pressure side heat transfer element extends only partially radially between the root and the tip.

4. The turbomachine blade of claim 1 , further comprising a suction side heat transfer element within the third section.

5. The turbomachine blade of claim 4 , further comprising a set of film holes fluidly connected with the third section proximate the suction side.

6. The turbomachine blade of claim 1 , wherein the first section includes a fluid passage extending only partially radially between the root and the tip.

7. The turbomachine blade of claim 6 , wherein the fluid passage has a tapered volume between the root and the tip, wherein the tapered volume includes a larger volume proximate the root and a smaller volume proximate the tip.

8. The turbomachine blade of claim 1 , further comprising an outlet passage connected with the trailing edge cooling circuit, the outlet passage located at the trailing edge of the body and extending only partially radially along the body.

9. The turbomachine blade of claim 1 , further comprising a set of film holes fluidly connected with the third section proximate the pressure side.

10. A turbomachine comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, the turbine component including at least one turbomachine blade including:
a body having: a leading edge; a trailing edge opposing the leading edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side, extending between the leading edge and the trailing edge; a root; and a tip opposing the root; and
a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including: a first section extending from the root toward the tip along the pressure side; a second section extending from the first section toward the trailing edge; and a third section extending from the trailing edge along the suction side,
wherein the first section includes a fluid passage extending only partially radially between the root and the tip, and
wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge.

11. The turbomachine of claim 10 , wherein the at least one turbomachine blade further includes a pressure side heat transfer element within the second section for directing flow of the heat transfer fluid.

12. The turbomachine of claim 11 , wherein the pressure side heat transfer element extends only partially radially between the root and the tip.

13. The turbomachine of claim 10 , wherein the at least one turbomachine blade further includes a suction side heat transfer element within the third section, wherein the at least one turbomachine blade further includes a set of film holes fluidly connected with the third section proximate the suction side.

14. The turbomachine of claim 10 , wherein the at least one turbomachine blade further includes an outlet passage connected with the trailing edge cooling circuit, the outlet passage located at the trailing edge of the body and extending only partially radially along the body.

15. The turbomachine of claim 10 , wherein the fluid passage has a tapered volume between the root and the tip, wherein the tapered volume includes a larger volume proximate the root and a smaller volume proximate the tip.

16. The turbomachine of claim 10 , wherein the at least one turbomachine blade further includes a set of film holes fluidly connected with the third section proximate the pressure side.

17. A turbomachine blade comprising:
a body having: a leading edge; a trailing edge opposing the leading edge; a suction side extending between the leading edge and the trailing edge; a pressure side, opposing the suction side, extending between the leading edge and the trailing edge; a root; and a tip opposing the root; and
a trailing edge cooling circuit contained within the body, the trailing edge cooling circuit including:
a first section extending from the root toward the tip along the pressure side;
a second section extending from the first section toward the trailing edge;
a third section extending from the trailing edge along the suction side,
wherein the trailing edge cooling circuit is configured to direct flow of a heat transfer fluid from the first section to the second section, and from the second section to the third section, without releasing the heat transfer fluid from the body at the trailing edge;
a pressure side heat transfer element within the second section;
a suction side heat transfer element within the third section; and
a set of film holes fluidly connected with the third section proximate at least one of the suction side or the pressure side.

Assignees

• Gen Electric

Inventors

• Weber David Wayne

Classifications

• F02C3/04 Primary

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

• F05D2250/185

  serpentine-like · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2220/32

  in gas turbines · CPC title