Fuel nozzle, and combustor and gas turbine having the same

A combustor comprising a combustion chamber assembly comprising a combustion chamber in which fuel is burned;

• and a fuel nozzle assembly comprising a plurality of fuel nozzles to inject fuel into the combustion chamber, each of the fuel nozzles comprising:
• a main cylinder extending in one direction;
• an auxiliary cylinder surrounding the main cylinder and defining a fuel passage between the auxiliary cylinder and the main cylinder;
• a shroud spaced that is apart from the auxiliary cylinder and surrounds the auxiliary cylinder;
• a swirler vane that is disposed between the auxiliary cylinder and the shroud and defines a fuel cavity having a plurality of fuel vents and communicating with the fuel passage so that fuel flowing in the fuel passage flows into the fuel cavity through a fuel aperture formed in the swirler vane;
• and
• a fuel flow guide disposed inside the fuel cavity and configured to guide fuel that flows from the fuel passage and enters the fuel cavity and to distribute the guided fuel in the fuel cavity,
• wherein the fuel flow guide includes a plurality of guide members of which the number corresponds to the number of the fuel vents, a number of portions of the fuel aperture formed by the plurality of guide members being the same as a number of the plurality of fuel vents formed inside the fuel cavity.

A gas turbine comprising a compressor to compress air;

• a combustor to produce combustion gas by mixing the compressed air with fuel for combustion;
• and a turbine to generate power by the combustion gas, the combustor comprising:
• a combustion chamber in which fuel is burned;
• and
• a fuel nozzle assembly comprising a plurality of fuel nozzles to inject fuel into the combustion chamber, each of the fuel nozzles comprising:
• a main cylinder extending in one direction;
• an auxiliary cylinder surrounding the main cylinder and defining a fuel passage between the auxiliary cylinder and the main cylinder;
• a shroud spaced that is apart from the auxiliary cylinder and surrounds the auxiliary cylinder;
• a swirler vane that is disposed between the auxiliary cylinder and the shroud and defines a fuel cavity having a plurality of fuel vents and communicating with the fuel passage so that fuel flowing in the fuel passage flows into the fuel cavity through a fuel aperture formed in the swirler vane;
• and
• a fuel flow guide disposed inside the fuel cavity and configured to guide fuel that flows from the fuel passage and enters the fuel cavity and to distribute the guided fuel in the fuel cavity,
• wherein the fuel flow guide includes a plurality of guide members of which the number corresponds to the number of the fuel vents, a number of portions of the fuel aperture formed by the plurality of guide members being the same as a number of the plurality of fuel vents formed inside the fuel cavity.