Turbine airfoil with trailing edge cooling circuit

Patent metadata

Field	Value
Publication number	US-9938836-B2
Application number	US-201514978224-A
Country	US
Kind code	B2
Filing date	Dec 22, 2015
Priority date	Dec 22, 2015
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.

First claim

What is claimed is:

1. A turbine airfoil comprising:
a trailing edge having:
a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel;
a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and
a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.

2. The turbine airfoil of claim 1 , further comprising a first set of crossover holes fluidly connecting the second section to the second cooling channel.

3. The turbine airfoil of claim 2 , wherein the first set of crossover holes are angled toward a pressure sidewall of the turbine airfoil.

4. The turbine airfoil of claim 2 , further comprising:
a first set of raised features, each raised feature in the first set of raised features corresponding to a crossover hole in the first set of crossover holes and each raised feature in the first set of raised features extending toward a suction sidewall of the turbine airfoil.

5. The turbine airfoil of claim 1 , further comprising a third section radially inward of the second section, the third section including a third pin bank cooling arrangement and being fluidly connected to the second cooling channel.

6. The turbine airfoil of claim 5 , further comprising:
a second set of crossover holes fluidly connecting the third section to the second cooling channel.

7. The turbine airfoil of claim 6 , wherein the second set of crossover holes are angled relative to a pressure sidewall of the turbine airfoil.

8. The turbine airfoil of claim 7 , wherein the second set of crossover holes are angled at an acute angle.

9. The turbine airfoil of claim 6 , further comprising:
a second set of raised features, each raised feature in the second set of raised features corresponding to a crossover hole in the second set of crossover holes and each raised feature in the second set of raised features extending toward a suction sidewall of the turbine airfoil.

10. The turbine airfoil of claim 1 , wherein the first and second pin bank cooling arrangements extend to a position that is less than 0.5 inches from an axial downstream end of the trailing edge.

11. A gas turbine comprising:
a turbine section;
an airfoil within the turbine section, the airfoil including a trailing edge having:
a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel;
a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and
a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.

12. The gas turbine of claim 11 , further comprising a first set of crossover holes fluidly connecting the second section to the second cooling channel.

13. The gas turbine of claim 12 , wherein the first set of crossover holes are angled toward a pressure sidewall of the turbine airfoil.

14. The gas turbine of claim 13 , wherein the first set of crossover holes are angled at an acute angle.

15. The gas turbine of claim 12 , further comprising:
a first set of raised features, each raised feature in the first set of raised features corresponding to a crossover hole in the first set of crossover holes and each raised feature in the first set of raised features extending toward a suction sidewall of the turbine airfoil.

16. The gas turbine of claim 11 , further comprising a third section radially inward of the second section, the third section including a third pin bank cooling arrangement and being fluidly connected to the second cooling channel.

17. The gas turbine of claim 16 , further comprising:
a second set of crossover holes fluidly connecting the third section to the second cooling channel.

18. The gas turbine of claim 16 , wherein the second set of crossover holes are angled relative to a pressure sidewall of the turbine airfoil.

19. The gas turbine of claim 16 , further comprising:
a second set of raised features, each raised feature in the second set of raised features corresponding to a crossover hole in the second set of crossover holes and each raised feature in the second set of raised features extending toward a suction sidewall of the turbine airfoil.

20. The gas turbine of claim 11 , wherein the first and second pin bank cooling arrangements extend to a position that is less than 0.5 inches from an axial downstream end of the trailing edge.

Assignees

• Gen Electric

Inventors

• Weber David Wayne
• Foster Gregory Thomas
• Iduate Michelle Jessica
• Leary Brendon James
• Smith Aaron Ezekiel

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/304

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