Turbine nozzle compartmentalized cooling system

• US 9,011,079 B2
• Filed: 01/09/2012
• Issued: 04/21/2015
• Est. Priority Date: 01/09/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Coign, Robert Walter, Foster, Gregory Thomas, Meenakshisundaram, Ravichandran, MacMillan, Glen Arthur, Winn, Aaron Gregory
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): WHITE, ALEXANDER A
• Application Number:
  US13/345,781
• Publication Number:
  US 20130177384A1
• Time in Patent Office: 1,198 Days
• Field of Search: 415/115, 415/116, 415/139, 415/175, 415/177, 415/202, 416/96.R, 416/96.A, 416/224, 416/232
• US Class Current: 415/115
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.

Claims

1. A compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein, comprising:

a turbine nozzle;

the turbine nozzle comprising an airfoil insert and a nozzle outer sidewall; and

a cooling baffle;

the cooling baffle comprising a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit;

wherein a post-impingement pressure cavity is defined radially between the impingement plate and the nozzle outer sidewall; and

wherein the cooling baffle further comprises a first sealing layer positioned along the impingement plate and radially outward of the post-impingement pressure cavity.

2. The compartmentalized cooling system of claim 1, wherein the cooling baffle comprises a plurality of cooling baffle segments.

3. The compartmentalized cooling system of claim 2, wherein the first sealing layer is positioned between a pair of the plurality of cooling baffle segments.

4. The compartmentalized cooling system of claim 1, wherein the airfoil insert receives a first portion of the cooling flow via the high pressure cooling passage, and wherein the post-impingement pressure cavity receives a second portion of the cooling flow via the impingement plate.

5. The compartmentalized cooling system of claim 4, wherein the impingement plate is positioned radially between the post-impingement pressure cavity and a cooling supply cavity, and wherein the cooling supply cavity comprises an area of high pressure.

6. The compartmentalized cooling system of claim 1, wherein the post-impingement pressure cavity comprises an area of intermediate pressure.

7. The compartmentalized cooling system of claim 6, wherein the post-impingement pressure cavity surrounds the high pressure cooling passage.

8. The compartmentalized cooling system of claim 6, wherein the nozzle outer sidewall is positioned radially between the post-impingement pressure cavity and a combustion gas flow path of the turbine, and wherein the combustion gas flow path comprises an area of low pressure.

9. The compartmentalized cooling system of claim 1, wherein the nozzle further comprises a second sealing layer positioned along the nozzle outer sidewall and radially inward of the post-impingement pressure cavity.

10. The compartmentalized cooling system of claim 9, wherein a first leakage path is defined across the first sealing layer and a second leakage path is defined across the second sealing layer.

11. The compartmentalized cooling system of claim 1, wherein the airfoil insert comprises a plurality of cooling apertures.

12. The compartmentalized cooling system of claim 1, wherein the cooling flow is in communication with a compressor.

13. The compartmentalized cooling system of claim 1, wherein the turbine nozzle further comprises a nozzle vane extending from a nozzle inner sidewall to the nozzle outer sidewall, and wherein the airfoil insert is positioned within the nozzle vane.

14. The compartmentalized cooling system of claim 1, wherein the high pressure cooling passage comprises a tube seal.

15. A method of cooling a nozzle of a turbine, comprising:

delivering a first circuit cooling flow under high pressure to an airfoil insert of a nozzle vane through a cooling baffle;

cooling the nozzle vane with the first circuit cooling flow;

delivering a second circuit cooling flow to a post-impingement pressure cavity defined radially between an impingement plate of the cooling baffle and a nozzle outer side wall of the nozzle;

sealing the post-impingement pressure cavity with a first sealing layer positioned along the impingement plate and radially outward of the post-impingement pressure cavity; and

cooling the outer nozzle side wall with the second circuit cooling flow.

16. A compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein, comprising:

a turbine nozzle;

the turbine nozzle comprising an airfoil insert and a nozzle outer sidewall; and

a plurality of cooling baffle segments;

each of the plurality of cooling baffle segments comprising a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit;

wherein a post-impingement pressure cavity is defined radially between the impingement plates and the nozzle outer sidewall; and

wherein each of the plurality of cooling baffle segments further comprises a first sealing layer positioned along the impingement plate and radially outward of the post-impingement pressure cavity.

17. The compartmentalized cooling system of claim 16, wherein the first sealing layer is positioned between a pair of the plurality of cooling baffle segments.

18. The compartmentalized cooling system of claim 16, wherein the airfoil insert receives a first portion of the cooling flow via the high pressure cooling passages, and wherein the post-impingement pressure cavity receives a second portion of the cooling flow via the impingement plates.

19. The compartmentalized cooling system of claim 16, wherein the nozzle further comprises a second sealing layer positioned along the nozzle outer sidewall and radially inward of the post-impingement pressure cavity.

20. The compartmentalized cooling system of claim 19, wherein a first leakage path is defined across the first sealing layer and a second leakage path is defined across the second sealing layer.