Nozzle assembly, combustor, and gas turbine including same

A combustor configured to mix compressed air supplied from a compressor of a gas turbine with fuel and to combust a mixture of the compressed air and the fuel, the combustor being configured to supply a generated combustion gas to a turbine of the gas turbine, and the combustor comprising:

• a nozzle casing;
• a liner connected to an end portion of the nozzle casing, the liner having an inner portion provided with a combustion chamber in which the mixture of the compressed air and the fuel is combusted;
• a transition piece connected to an end portion of the liner, the transition piece being configured to supply the combustion gas generated from the combustion chamber to the turbine;
• and
• a nozzle assembly mounted inside the nozzle casing and configured to discharge the fuel and the compressed air into the combustion chamber,
• wherein the nozzle assembly comprises:
• a nozzle body;
• a plurality of injection nozzles provided inside the nozzle body and disposed to be spaced apart from each other, the plurality of injection nozzles having inner portions through which the fuel and a first portion of the compressed air are mixed and flow;
• and
• a side wall which is connected to a first side of the nozzle body and through which the plurality of injection nozzles passes,
• wherein a cooling air inlet hole into which a second portion of the compressed air is introduced, as a cooling air, into a space where the plurality of injection nozzles is disposed is formed in the nozzle body, and a cooling air outlet hole through which the cooling air introduced from the cooling air inlet hole is discharged is formed in one region of the side wall.

A gas turbine comprising:

• a compressor configured to compress air introduced from outside;
• a combustor configured to mix compressed air supplied from the compressor with fuel and to combust a mixture of the compressed air and the fuel;
• and
• a turbine configured to generate power for generating electric power by passing combustion gas supplied from the combustor to an inner portion of the turbine,
• wherein the combustor comprises:
• a nozzle casing;
• a liner connected to an end portion of the nozzle casing, the liner having an inner portion provided with a combustion chamber in which the mixture of the compressed air and the fuel is combusted;
• a transition piece connected to an end portion of the liner, the transition piece being configured to supply the combustion gas generated from the combustion chamber to the turbine;
• and
• a nozzle assembly mounted inside the nozzle casing and configured to discharge the fuel and the compressed air into the combustion chamber,
• wherein the nozzle assembly comprises:
• a nozzle body;
• a plurality of injection nozzles provided inside the nozzle body and disposed to be spaced apart from each other, the plurality of injection nozzles having inner portions through which the fuel and a first portion of the compressed air are mixed and flow;
• and
• a side wall which is connected to a first side of the nozzle body and through which the plurality of injection nozzles passes,
• wherein a cooling air inlet hole into which a second portion of the compressed air is introduced, as a cooling air, into a space where the plurality of injection nozzles is disposed is formed in the nozzle body, and a cooling air outlet hole through which the cooling air introduced from the cooling air inlet hole is discharged is formed in one region of the side wall.