Combustor nozzle, combustor, and gas turbine including the same

1. A nozzle for a combustor configured to burn fuel containing hydrogen, comprising:

a fuel supply duct comprising a plurality of injection tubes through which air and the fuel flow and a fuel passage through which the fuel flows;

a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and

a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube,

wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction,

wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end,

wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and

wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube.

2. The nozzle according to claim 1 , wherein the tube swirler is disposed between one end of the injection tube for introducing the air and the fuel inlet holes.

3. The nozzle according to claim 1 , wherein the fuel inlet holes are arranged between one end of the injection tube for introducing the air and the tube swirlers.

4. The nozzle according to claim 2 , wherein the fuel supply duct further comprises a plurality of diffusion nozzle tubes arranged between the plurality of injection tubes, each of the diffusion nozzle tubes having an end cap formed at an end, the end cap having a plurality of diffusion injection holes formed therein.

5. The nozzle according to claim 4 , wherein the plurality of diffusion injection holes of the each of the diffusion nozzle tubes are exclusively formed on an chamfered edge, the plurality of diffusion injection holes being formed in an inclined direction with respect to a longitudinal direction of the injection tube.

6. The nozzle according to claim 5 ,

wherein the plurality of diffusion injection holes are formed perpendicular to the chamfered edge of the end cap.

7. The nozzle according to claim 1 , wherein the plurality of swirlers are hole swirlers formed through the side surface of the injection tube to contact with an inner peripheral surface and configured to guide the air introduced through the plurality of swirlers in a circumferential direction.

8. The nozzle according to claim 7 , wherein

the plurality of fuel inlet holes are formed radially through the side surface of the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, and

the plurality of fuel inlet holes are arranged between one end of the injection tube for introducing the air and the hole swirlers.

9. The nozzle according to claim 1 ,

wherein the curved shape of the swirl guide has a larger curvature radius than the side surface of the injection tube.

10. The nozzle according to claim 1 ,

wherein both longitudinal edges of the swirl guide in a longitudinal direction of the injection tube are integrally connected to both longitudinal ends of the swirl guide hole, respectively.

11. A combustor comprising:

a nozzle assembly having a plurality of nozzles configured to inject fuel and air; and

a duct assembly coupled to one side of the nozzle assembly to burn a mixture of the fuel and the air and transmit combustion gas to a turbine,

wherein each of the plurality of nozzles comprises:

a fuel supply duct comprising a plurality of injection tubes through which the air and the fuel flow and a fuel passage through which the fuel flows;

a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and

a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube,

wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction,

wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end,

wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and

wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube.

12. The combustor according to claim 11 , wherein the tube swirler is disposed between one end of the injection tube for introducing the air and the fuel inlet holes.

13. The combustor according to claim 12 , wherein the fuel inlet holes are arranged between one end of the injection tube for introducing the air and the tube swirlers.

14. The combustor according to claim 12 , wherein the fuel supply duct further comprises a plurality of diffusion nozzle tubes arranged between the plurality of injection tubes, each of the diffusion nozzle tubes having an end cap formed at an end, the end cap having a plurality of diffusion injection holes formed therein.

15. The combustor according to claim 14 , wherein the plurality of diffusion injection holes of the each of the diffusion nozzle tubes are exclusively formed on an chamfered edge, the plurality of diffusion injection holes being formed in an inclined direction with respect to a longitudinal direction of the injection tube.

16. The combustor according to claim 11 , wherein the plurality of swirlers are hole swirlers formed through the side surface of the injection tube to contact with an inner peripheral surface and configured to guide the air introduced through the plurality of swirlers in a circumferential direction.

17. The combustor according to claim 16 , wherein

the plurality of fuel inlet holes are formed radially through the side surface of the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, and

the plurality of fuel inlet holes are arranged between one end of the injection tube for introducing the air and the hole swirlers.

18. A gas turbine comprising:

a compressor configured to compress air introduced from an outside;

a combustor configured to mix fuel with the air compressed by the compressor and combust a mixture of the fuel and the air to produce combustion gas; and

a turbine having a plurality of turbine blades rotated by the combustion gas produced by the combustor,

wherein the combustor comprises a nozzle assembly having a plurality of nozzles configured to inject fuel and air, and a duct assembly coupled to one side of the nozzle assembly to burn the mixture of the fuel and the air and transmit the combustion gas to the turbine,

wherein each of the plurality of nozzles comprises:

a fuel supply duct comprising a plurality of injection tubes through which the air and the fuel flow and a fuel passage through which the fuel flows;

a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and

a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube,

wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction,

wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end,

wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and

wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube.