Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure

• US 20020112483A1
• Filed: 02/15/2002
• Published: 08/22/2002
• Est. Priority Date: 02/16/2001
• Status: Active Grant

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Hada, Satoshi, Kondo, Mitsuru, Tanaka, Katsunori
• Granted Patent: US 6,769,257 B2
• Time in Patent Office: Days
• US Class Current: 60/796
• 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: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A gas turbine combustor transition piece outlet structure enabling a reduction in the temperature difference of a flange formed at the transition piece outlet. A flange is formed with a cooling medium channel along the inner circumference, cooling medium channels along the left and right side surfaces, and heating medium channels along the top and bottom surfaces. By cooling the inner circumference or the side surfaces of the flange by a cooling medium or heating the top and bottom surfaces of the flange by a heating medium, the temperature difference of the flange is reduced. Note that as the cooling medium, it is possible to use compressed air, low temperature steam, or fuel, while as the heating medium, it is possible to use high temperature steam or combustion gas.

Claims

1. A gas turbine combustor transition piece outlet structure providing a flange formed at a gas turbine transition piece outlet with a temperature difference reducing means for reducing a temperature difference between an inner circumference side and an outer circumference side of said flange.

2. A gas turbine combustor transition piece outlet structure as set forth in claim 1, wherein said temperature difference reducing means is a channel formed along an inner circumference of said flange and through which a cooling medium flows.

3. A gas turbine combustor transition piece outlet structure as set forth in claim 2, wherein the cooling medium flowing through said channel is compressed air introduced from a compressor outlet.

4. A gas turbine combustor transition piece outlet structure as set forth in claim 2, wherein the cooling medium flowing through said channel is steam supplied from a steam source.

5. A gas turbine combustor transition piece outlet structure as set forth in claim 2, wherein the cooling medium flowing through said channel is fuel supplied from a fuel tank.

6. A gas turbine combustor transition piece outlet structure as set forth in claim 1, wherein said temperature difference reducing means is a channel formed along a facing surface of said flange with an adjoining flange and through which a cooling medium flows.

7. A gas turbine combustor transition piece outlet structure as set forth in claim 6, wherein the cooling medium flowing through said channel is pressurized air.

8. A gas turbine combustor transition piece outlet structure as set forth in claim 6, wherein the cooling medium flowing through the channel is steam heated after being supplied from a steam source.

9. A gas turbine combustor transition piece outlet structure as set forth in claim 6, wherein the cooling medium flowing through the channel is fuel supplied from a fuel tank.

10. A gas turbine combustor transition piece outlet structure as set forth in claim 1, wherein said temperature difference reducing means is a channel formed along a surface of said flange not facing to an adjoining flange and through which a heating medium flows.

11. A gas turbine combustor transition piece outlet structure as set forth in claim 10, wherein the heating medium flowing through the channel is heated air.

12. A gas turbine combustor transition piece outlet structure as set forth in claim 10, wherein the heating medium flowing through the channel is combustion gas discharged from a turbine part.

13. A gas turbine combustor transition piece outlet structure as set forth in claim 10, wherein the heating medium flowing through the channel is combustion gas discharged from a turbine part and reduced in temperature by an attemporator.

14. A gas turbine combustor transition piece having an outlet structure as set forth in any one of claims 1 to 13.

15. A combustor of a gas turbine comprising:

a fuel injection nozzle; and

a transition piece having an outlet structure as set forth in claim 14.

16. A gas turbine comprising:

an air compressor;

a combustor as set forth in claim 15, for combusting fuel with air compressed by said air compressor; and

a turbine driven by combustion gas exhausted from said combustor.