Nozzle assembly, combustor and gas turbine comprising the same

A combustor that mixes compressed air supplied from a compressor of a gas turbine with fuel, burns the mixture, and supplies generated combustion gas into a turbine of the gas turbine, the combustor comprising:

• a nozzle casing;
• a liner connected to a turbine-side end portion of the nozzle casing, and comprising a combustion chamber formed therein and burning the mixture of the fuel and the compressed air;
• a transition piece connected to a turbine-side end portion of the liner, and supplying the combustion gas generated from the combustion chamber to the turbine;
• and
• a nozzle assembly provided in the nozzle casing, and comprising a nozzle module unit comprising a plurality of tubes injecting the fuel and the compressed air into the combustion chamber, and a casing accommodating the nozzle module unit therein,
• wherein the nozzle module unit further comprises:
• a central nozzle module injecting fuel and compressed air, and located at a central portion of the casing;
• and
• a plurality of outer nozzle modules located outside the central nozzle module while being spaced apart from the central nozzle module,
• wherein an anti-air-leakage sealing unit is provided to prevent air leakage into the combustion chamber through gaps formed between an inner circumferential surface of the casing, the central nozzle module, and the plurality of outer nozzle modules.

A gas turbine comprising:

• a compressor compressing air introduced from an outer space;
• a combustor mixing compressed air supplied from the compressor and fuel, and burning the mixture;
• and
• a turbine allowing combustion gas supplied from the combustor to pass through an inner portion thereof,
• wherein the combustor comprises:
• a nozzle casing;
• a liner connected to a turbine-side end portion of the nozzle casing, and comprising a combustion chamber formed therein and burning the mixture of the fuel and the compressed air;
• a transition piece connected to a turbine-side end portion of the liner, and supplying the combustion gas generated from the combustion chamber to the turbine;
• and
• a nozzle assembly provided in the nozzle casing, and comprising a nozzle module unit comprising a plurality of tubes injecting the fuel and the compressed air into the combustion chamber, and a casing accommodating the nozzle module unit therein,
• wherein the nozzle module unit further comprises:
• a central nozzle module injecting fuel and compressed air, and located at a central portion of the casing;
• and
• a plurality of outer nozzle modules located outside the central nozzle module while being spaced apart from the central nozzle module,
• wherein an anti-air-leakage sealing unit is provided to prevent air leakage into the combustion chamber through gaps formed between an inner circumferential surface of the casing, the central nozzle module, and the plurality of outer nozzle modules.