Combustor for gas turbine and gas turbine having the same

1. A combustor for a gas turbine, comprising:

a flange portion to be mounted to a casing;

an extension portion having an annular shape and extending from the flange portion along an axial direction of the combustor;

a pipe portion having a first end connected to the flange portion and a second end connected to an outer peripheral surface of the extension portion, the pipe portion extending from the first end to the second end at an outer side of the extension portion in a radial direction; and

at least one fuel nozzle configured to receive supply of a fuel via the pipe portion and a passage disposed inside the extension portion,

wherein the pipe portion includes:

an axial-direction pipe portion including the first end and extending along the axial direction of the combustor;

a radial-direction pipe portion including the second end and extending along a radial direction of the combustor; and

a connection pipe portion connecting the axial-direction pipe portion and the radial-direction pipe portion, and

wherein the pipe portion has a length L including the connection pipe portion, the length L being larger than a sum of LA and LB, where LA is an axial-direction distance between the first end and the second end and LB is a radial-direction distance between the first end and the second end.

2. The combustor for a gas turbine according to claim 1 ,

wherein the passage includes an annular passage communicating with an inner flow passage of the pipe portion, and

wherein the combustor is configured such that the fuel is supplied to a plurality of the fuel nozzles via the annular passage.

3. The combustor for a gas turbine according to claim 1 ,

wherein the at least one fuel nozzle is disposed at an inner peripheral side of the extension portion.

4. The combustor for a gas turbine according to claim 1 ,

wherein the fuel nozzle is formed inside the casing, and configured to inject a fuel into an air passage through which air to be used in combustion of the fuel passes.

5. The combustor for a gas turbine according to claim 4 ,

wherein the extension portion includes an air-passage forming portion which forms the air passage at an opposite side of the flange portion across the pipe portion in the axial direction.

6. The combustor for a gas turbine according to claim 1 ,

wherein the at least one fuel nozzle is formed inside the casing and configured to inject the fuel into an air passage through which air to be used in combustion passes and generate a fuel-gas mixture of the air and the fuel, and

wherein the combustor further includes a downstream nozzle disposed at a downstream side in a flow direction of the fuel gas mixture and configured to inject the fuel to the fuel gas mixture.

7. A gas turbine, comprising:

the combustor according to claim 1 ; and

a stator vane and a rotor blade disposed at a downstream side of the combustor.

8. The combustor for a gas turbine according to claim 1 ,

wherein the pipe portion has an inner flow passage formed inside the pipe portion so as to extend between the first end and the second end, and

wherein the inner flow passage of the pipe portion is in communication with a passage inside the extension portion for allowing the fuel to pass through toward the at least one fuel nozzle.

9. A combustor for a gas turbine, comprising:

a flange portion to be mounted to a casing;

an extension portion having an annular shape and extending from the flange portion along an axial direction of the combustor;

a pipe portion having a first end connected to the flange portion and a second end connected to an outer peripheral surface of the extension portion, the pipe portion extending from the first end to the second end at an outer side of the extension portion in a radial direction; and

at least one fuel nozzle configured to receive supply of a fuel via the pipe portion and a passage disposed inside the extension portion,

wherein the first end and the second end of the pipe portion are positioned offset from one another in a circumferential direction of the combustor.

10. The combustor for a gas turbine according to claim 1 ,

wherein the pipe portion is disposed inside a space surrounded by the casing at an outer peripheral side of the extension portion.

11. A gas turbine comprising:

the combustor according to claim 9 ; and

a stator vane and a rotor blade disposed at a downstream side of the combustor.

12. A combustor for a gas turbine, comprising:

a flange portion to be mounted to a casing;

an extension portion having an annular shape and extending from the flange portion along an axial direction of the combustor;

a pipe portion having a first end connected to the flange portion and a second end connected to an outer peripheral surface of the extension portion, the pipe portion extending from the first end to the second end at an outer side of the extension portion in a radial direction;

at least one fuel nozzle configured to receive supply of a fuel via the pipe portion and a passage disposed inside the extension portion; and

a fuel supply pipe connected to an end surface opposite to the pipe portion, the end surface being one of two opposite end surfaces of the flange portion,

wherein the combustor is configured such that the fuel is supplied to the passage inside the extension portion via the fuel supply pipe, a flange internal passage disposed inside the flange portion, and the pipe portion.

13. The combustor for a gas turbine according to claim 12 ,

wherein the fuel supply pipe, the flange internal passage, and the first end of the pipe portion are disposed along a line substantially parallel to the axial direction of the combustor.

14. A gas turbine comprising:

the combustor according to claim 12 ; and

a stator vane and a rotor blade disposed at a downstream side of the combustor.

15. A combustor for a gas turbine, comprising:

a flange portion to be mounted to a casing;

an extension portion having an annular shape and extending from the flange portion along an axial direction of the combustor;

at least one fuel nozzle configured to receive supply of a fuel via a passage disposed inside the extension portion;

and a fuel supply pipe for supplying the fuel to the passage, the fuel supply pipe being connected to the flange portion,

wherein the flange portion has, in a first angular range around a center axis of the combustor, a first region whose protruding amount outward in a radial direction is greater than that in a second angular-range other than the first angular range, and

wherein the fuel supply pipe is connected to an end surface of the flange portion opposite to the extension portion, the end surface being one of two opposite end surfaces of the flange portion, at a portion of the flange portion including the first region.

16. A gas turbine, comprising:

the combustor according to the claim 15 ; and

a stator vane and a rotor blade disposed at a downstream side of the combustor,

wherein the first region of the flange portion is disposed at a position farther away from a center axis of the gas turbine than the center axis of the combustor.