IMPINGEMENT COOLED COMBUSTOR

• US 20130318986A1
• Filed: 06/05/2012
• Published: 12/05/2013
• Est. Priority Date: 06/05/2012
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kraemer, Gilbert Otto
• Application Number:
  US13/488,465
• Publication Number:
  US 20130318986A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F23R 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow means for creating turbulence F23R2900/03045
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers

Abstract

The present application thus provides a combustor for use with a gas turbine engine. The combustor may include a turbine nozzle and a liner cooling system integral with the turbine nozzle. The liner cooling system may include a liner with one or more cooling features thereon and an impingement sleeve.

Claims

1. A combustor for use with a gas turbine engine, comprising:

a turbine nozzle; and

a liner cooling system integral with the turbine nozzle;

wherein the liner cooling system comprises a liner with one or more cooling features thereon and an impingement sleeve.

2. The combustor of claim 1, wherein the turbine nozzle comprises a stage one nozzle.

3. The combustor of claim 1, wherein the turbine nozzle comprises a fuel injector.

4. The combustor of claim 1, wherein the combustor comprises a jet stirred combustor.

5. The combustor of claim 1, wherein the liner cooling system comprises an air gap between the liner and the impingement sleeve.

6. The combustor of claim 1, wherein the one or more cooling features comprise a plurality of ribs.

7. The combustor of claim 1, wherein the liner comprises an alloy with a thermal barrier coating thereon.

8. The combustor of claim 1, wherein the liner comprises one or more diffusion holes.

9. The combustor of claim 1, wherein the impingement sleeve comprises a plurality of impingement holes.

10. The combustor of claim 1, wherein the plurality of impingement holes comprises a plurality of variably shaped impingement holes.

11. The combustor of claim 1, wherein the impingement sleeve comprises a top side with a plurality of top impingement holes.

12. The combustor of claim 1, wherein the impingement sleeve comprises a bottom side with a plurality of bottom impingement holes.

13. The combustor of claim 1, wherein the impingement sleeve comprises a plurality of cooling feature impingement holes.

14. The combustor of claim 1, wherein the impingement sleeve comprises a head end with a plurality of head end impingement holes.

15. A method of cooling a combustor, comprising:

defining a combustion zone with a liner cooling system that is integral with a turbine nozzle;

flowing air about a head end of the combustor so as to impingement cooler a liner of the liner cooling system through an impingement sleeve; and

further cooling the liner via one or more liner surface cooling features.

16. A jet stirred combustor for use with a gas turbine engine, comprising:

a stage one nozzle; and

a liner cooling system integral with the stage one nozzle;

wherein the liner cooling system comprises a liner with one or more cooling features thereon, an impingement sleeve, and an air gap therebetween.

17. The jet stirred combustor of claim 16, wherein the one or more cooling features comprise a plurality of ribs.

18. The jet stirred combustor of claim 16, wherein the impingement sleeve comprises a top side with a plurality of top impingement holes.

19. The jet stirred combustor of claim 16, wherein the impingement sleeve comprises a bottom side with a plurality of bottom impingement holes.

20. The jet stirred combustor of claim 16, wherein the impingement sleeve comprises a head end with a plurality of head end impingement holes.