Combustor nozzle, combustor, and gas turbine including the same

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.

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.