Method and apparatus to enhance transition duct cooling in a gas turbine engine

• US 8,549,861 B2
• Filed: 01/07/2009
• Issued: 10/08/2013
• Est. Priority Date: 01/07/2009
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Huffman, Marcus B.
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Mantyla, Michael B
• Application Number:
  US12/349,994
• Publication Number:
  US 20100170259A1
• Time in Patent Office: 1,735 Days
• Field of Search: 607/52, 607/54, 607/55, 607/56, 607/57, 607/58, 607/59, 607/60
• US Class Current: 60/760
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A method and apparatus are described that include a transition piece including a cooling sleeve. The cooling sleeve includes a first end and an opposite second end, the cooling sleeve is coupled to an inner wall of the transition piece, such that an annular passage is defined between the inner wall and the cooling sleeve. The first end defines an annular inlet and second end defines an annular outlet.

Claims

1. A method for assembling a gas turbine engine, said method comprising:

coupling a cooling sleeve including a first end and an opposite second end to an inner wall of a combustor assembly such that an annular passage is defined between the inner wall and the cooling sleeve, wherein the inner wall defines a transition piece of the combustor assembly and the cooling sleeve is defined by a solid wall extending from the first end to the second end;

orienting at least one rib on an inner surface of the cooling sleeve substantially axially between the first and second ends such that the at least one rib circumscribes the cooling sleeve and supports the cooling sleeve;

forming an annular inlet adjacent to the first end located at a downstream end of the transition piece;

coupling a rounded inlet tube adjacent to the annular inlet to support the annular inlet and to facilitate channeling a cooling fluid flow into the annular passage; and

forming an annular outlet adjacent to the second end.

2. A method in accordance with claim 1, further comprising forming the cooling sleeve, wherein forming the cooling sleeve further comprises coupling a first member and a second member about the inner wall along at least one seam, wherein the first member is coupled to the second member using at least one of a mechanical fastener, a crimping process, and a welding process.

3. A method in accordance with claim 1, further comprising coupling at least one axial rib to the inner wall such that the at least one axial rib extends at least partially into the annular passage.

4. A method in accordance with claim 1, wherein orienting the at least one rib further comprises orienting the at least one rib to facilitate increasing heat transfer between the inner wall and the cooling sleeve.

5. A method in accordance with claim 1, wherein the at least one rib is formed integrally with the cooling sleeve to the inner wall.

6. A method in accordance with claim 1, wherein forming the annular passage inlet further comprises forming at least one aperture in the cooling sleeve adjacent to the annular passage such that the aperture facilitates channeling said cooling fluid flow into the annular passage.

7. A transition piece for use with a turbine engine, said transition piece comprising:

an inner wall of a combustor assembly, said inner wall configured to channel combustion gases from a combustor chamber toward a turbine nozzle;

a cooling sleeve comprising a first end and an opposite second end, said cooling sleeve coupled to said inner wall, such that an annular passage is defined between said inner wall and said cooling sleeve, said cooling sleeve being defined by a solid wall extending from said first end to said second end, said first end being a downstream end of said cooling sleeve and defining an annular inlet, said second end defining an annular outlet, said cooling sleeve further comprising a rounded inlet tube adjacent to said annular inlet for supporting said annular inlet, and to facilitate channeling a cooling fluid flow into the annular passage; and

at least one rib oriented on an inner surface of said cooling sleeve substantially axially between the first and second ends such that said at least one rib circumscribes said cooling sleeve and supports said cooling sleeve.

8. A transition piece in accordance with claim 7, wherein said cooling sleeve comprises a first member and a second member that are each coupled substantially circumferentially about said inner wall along at least one seam, said first member is coupled to said second member using at least one of a mechanical fastener, a crimping process, and a welding process.

9. A transition piece in accordance with claim 7, wherein said annular passage further comprises at least one axial rib that extends at least partially into said annular passage from at least one wall.

10. A transition piece in accordance with claim 7 wherein said at least one rib is formed integrally with said cooling sleeve.

11. A transition piece in accordance with claim 7, wherein said at least one rib facilitates increasing heat transfer between said inner wall and said cooling sleeve.

12. A transition piece in accordance with claim 7, wherein said cooling sleeve is defined by a corrugated surface, said corrugated surface facilitates increasing a structural strength of said cooling sleeve.

13. A transition piece in accordance with claim 7, wherein said annular passage inlet comprises at least one aperture defined therein, said at least one aperture facilitates channeling said cooling fluid flow into said annular passage.

14. A gas turbine engine assembly comprising:

a compressor; and

a combustor coupled in flow communication with said compressor, said combustor comprising at least one transition piece, said transition piece comprising;

an inner wall, said inner wall configured to channel combustion gases from a combustor chamber toward a turbine nozzle;

a cooling sleeve comprising a first end and an opposite second end, said cooling sleeve coupled to said inner wall such that an annular passage is defined between said inner wall and said cooling sleeve, said cooling sleeve being defined by a solid wall extending from said first end to said second end, said first end being a downstream end of said cooling sleeve and defining an annular inlet, said second end defining an annular outlet, said cooling sleeve further comprising a rounded inlet tube adjacent to said annular inlet for supporting said annual inlet, and to facilitate channeling a cooling fluid flow into the annular passage; and

at least one rib coupled to an inner surface of said cooling sleeve between the first and second ends such that said at least one rib circumscribes said cooling sleeve to support said cooling sleeve.

15. A gas turbine engine assembly in accordance with claim 14, wherein said cooling sleeve comprises a first member and a second member that are each coupled about said inner wall along at least one seam, said first member is coupled to said second member using at least one of a mechanical fastener, a crimping process, and a welding process.

16. A gas turbine engine assembly in accordance with claim 14, wherein said transition piece further comprises at least one axial rib extending at least partially into said annular passage from at least one wall defining said annular passage.

17. A gas turbine engine assembly in accordance with claim 14, wherein said at least one rib is formed integrally with said cooling sleeve.