Fuel nozzle and combustor and gas turbine including the same

A combustor comprising:

• a combustion chamber assembly comprising a combustion chamber in which fuel is combusted;
• and
• a fuel nozzle assembly comprising a plurality of fuel nozzles to inject the fuel into the combustion chamber, each of the fuel nozzles comprising:
• a shroud;
• an injection cylinder surrounded by the shroud and configured to supply fuel to the combustion chamber;
• a swirler disposed between the injection cylinder and the shroud;
• and
• a plurality of porous disks disposed on the injection cylinder downstream of the swirler to suppress a flashback phenomenon occurring due to a reduction in pressure around the swirler, the flashback being a phenomenon in which a flame produced in the combustion chamber flows back to the fuel nozzle,
• wherein the plurality of porous disks are spaced a distance from an inner circumferential surface of the shroud according to an amount of the reduction in pressure around the swirler.

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 using the combustion gas,
• wherein the combustor comprises:
• a combustion chamber assembly comprising a combustion chamber in which fuel is combusted;
• and
• a fuel nozzle assembly comprising a plurality of fuel nozzles to inject the fuel into the combustion chamber, each of the fuel nozzles comprising:
• an injection cylinder covered by a shroud and configured to supply fuel to the combustion chamber;
• a swirler on the injection cylinder and extending towards the shroud, the swirler being disposed in a middle of the injection cylinder;
• and
• a plurality of porous disks disposed on the injection cylinder downstream of the swirler to suppress a flashback phenomenon occurring due to a reduction in pressure around the swirler, the flashback being a phenomenon in which a flame produced in the combustion chamber flows back to the fuel nozzle,
• wherein the plurality of porous disks are spaced a distance from an inner circumferential surface of the shroud according to an amount of the reduction in pressure around the swirler.