Turbine airfoil with trailing edge cooling circuit

Patent metadata

Field	Value
Publication number	US-10619491-B2
Application number	US-201815883498-A
Country	US
Kind code	B2
Filing date	Jan 30, 2018
Priority date	Dec 22, 2015
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

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; 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; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.

First claim

What is claimed is:

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

2. The trailing edge of 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 trailing edge of 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 trailing edge of 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 trailing edge of 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 trailing edge of 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 trailing edge of 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 trailing edge of 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.

9. The trailing edge of the turbine airfoil of claim 1 , further comprising:
a pressure side panel having a pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel; and
a support at an axially outer end of the pressure side panel.

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

11. The gas turbine of claim 10 , further comprising a first set of crossover holes fluidly connecting the second section to the second cooling channel.

12. The gas turbine of claim 11 , wherein the first set of crossover holes are angled toward a pressure sidewall of the turbine airfoil.

13. The gas turbine of claim 11 , 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.

14. The gas turbine of claim 10 , 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.

15. The gas turbine of claim 14 , further comprising:
a second set of crossover holes fluidly connecting the third section to the second cooling channel.

16. The gas turbine of claim 14 , wherein the second set of crossover holes are angled relative to a pressure sidewall of the turbine airfoil.

17. The gas turbine of claim 14 , 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.

18. The gas turbine of claim 10 , further comprising:
a pressure side panel having a pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel; and
a support at an axially outer end of the pressure side panel;
wherein the pressure side panel is fluidly connected to the first cooling channel via a third set of crossover holes.

19. A turbine airfoil comprising:
a trailing edge having:
a first section having a first pin bank cooling arrangement, the first section fluidly connected to a first cooling channel; and
a pressure side panel having a second pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.

20. The turbine airfoil of claim 19 , wherein the pressure side panel is fluidly connected to the first cooling channel via a third set of crossover holes.

Assignees

• Gen Electric

Inventors

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

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/203

  by transpiration cooling · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title