Jet nozzle, combustor, and gas turbine including same

A combustor provided to mix compressed air supplied from a compressor of a gas turbine and fuel supplied from a fuel injector to form a compressed air-fuel mixture, to combust the mixture to produce combustion gases, and to supply the combustion gases to a turbine section of the gas turbine, the combustor comprises:

• a nozzle casing;
• a liner connected to a turbine section-side end of the nozzle casing and having a combustion chamber in which the compressed air-fuel mixture is combusted;
• a transition piece connected to a turbine section-side end of the liner to supply combustion gas generated in the combustion chamber to the turbine section;
• a nozzle assembly disposed in the nozzle casing to inject fuel and compressed air into the combustion chamber;
• and
• a jet nozzle configured to supply fluid into an interior of a liner in a direction intersecting with a progress direction of combustion gases primarily combusted in the combustion chamber, the jet nozzle comprising:
• a fluid inlet, through which fluid is introduced;
• and
• a fluid outlet including a first fluid outlet member, through which a portion of the fluid introduced through the fluid inlet is discharged so as to be rotated in one direction, and a second fluid outlet member, through which the rest of the fluid is discharged so as to be rotated in a direction different from the rotation direction of the fluid discharged from the first fluid outlet member.

A gas turbine comprising:

• a compressor provided to compress air introduced from the outside;
• a combustor provided to mix the compressed air supplied from the compressor with fuel supplied from a fuel injector and combust the air-fuel mixture;
• and
• a turbine section provided to generate power for generating electricity while the combustion gases supplied from the combustor flow therethrough, the combustor comprising:
• a nozzle casing;
• a liner connected to a turbine section-side end of the nozzle casing and having a combustion chamber in which the compressed air-fuel mixture is combusted;
• a transition piece connected to a turbine section-side end of the liner to supply the combustion gases generated in the combustion chamber to the turbine section;
• a nozzle assembly disposed in the nozzle casing to inject fuel and compressed air into the combustion chamber;
• and
• a jet nozzle configured to supply fluid into an interior of the liner in a direction intersecting with a progress direction of the combustion gases primarily combusted in the combustion chamber, the jet nozzle comprising:
• a fluid inlet, through which fluid is introduced;
• and
• a fluid outlet including a first fluid outlet member, through which a portion of the fluid introduced through the fluid inlet is discharged so as to be rotated in one direction, and a second fluid outlet member, through which the rest of the fluid is discharged so as to be rotated in a direction different from the rotation direction of the fluid discharged from the first fluid outlet member.