Nozzle assembly, combustor, and gas turbine including same

A combustor comprising:

• a nozzle casing configured to receive compressed air from a compressor and to receive fuel from an outside;
• a liner connected to the nozzle casing and defining a combustion chamber in which a mixture of fuel and compressed air is combusted;
• a transition piece connected to the liner to supply combustion gas generated in the combustion chamber to a turbine;
• and
• a nozzle assembly disposed in the nozzle casing and comprising a plurality of nozzle modules to inject fuel and compressed air into the combustion chamber,
• wherein each nozzle module comprises:
• a fuel supply tube defining a fuel passage configured to facilitate fuel flow from a front end toward a rear end;
• a fuel manifold coupled to a first portion of the fuel supply tube, the fuel manifold defining a fuel supply path configured to distribute fuel circumferentially and radially;
• a plurality of fuel injectors disposed at a rear end of the fuel manifold in a radially spaced configuration, each fuel injector being in fluid communication with the fuel manifold and configured to mix fuel with air to discharge a fuel-air mixture;
• and
• a pilot injector disposed at a central portion of the plurality of fuel injectors and in fluid communication with the fuel manifold,
• wherein each fuel injector comprises:
• an injector body having a first end in fluid communication with the fuel manifold and a second end defining a discharge orifice, the injector body defining a mixing passage;
• an air inflow port defined through a side surface portion of the injector body and configured to fluidly direct external air into the mixing passage;
• and
• a fuel port defined in the injector body and configured to discharge fuel from the fuel manifold into the mixing passage.

A gas turbine comprising:

• a compressor configured to compress air introduced from an outside;
• a combustor configured to mix fuel with the air compressed by the compressor and combust a mixture of the fuel and air to produce combustion gas;
• and
• a turbine comprising a plurality of turbine blades rotated by combustion gas produced by the combustor,
• wherein the combustor comprises:
• a nozzle casing configured to receive compressed air from the compressor and to receive fuel from the outside;
• a liner connected to the nozzle casing and defining a combustion chamber in which a mixture of fuel and compressed air is combusted;
• a transition piece connected to the liner to supply combustion gas generated in the combustion chamber to the turbine;
• and
• a nozzle assembly disposed in the nozzle casing and comprising a plurality of nozzle modules to inject fuel and compressed air into the combustion chamber,
• wherein each nozzle module comprises:
• a fuel supply tube defining a fuel passage configured to facilitate fuel flow from a front end toward a rear end;
• a fuel manifold coupled to a first portion of the fuel supply tube, the fuel manifold defining a fuel supply path configured to distribute fuel circumferentially and radially;
• a plurality of fuel injectors disposed at a rear end of the fuel manifold in a radially spaced apart configuration, each fuel injector being in fluid communication with the fuel manifold and configured to mix fuel with air to discharge a fuel-air mixture;
• and
• a pilot injector disposed at a central portion of the plurality of fuel injectors and in fluid communication with the fuel manifold,
• wherein each fuel injector comprises:
• an injector body having a first end in fluid communication with the fuel manifold and a second end defining a discharge orifice, the injector body defining a mixing passage;
• an air inflow port defined through a side surface portion of the injector body and configured to fluidly direct external air into the mixing passage;
• and
• a fuel port defined in the injector body and configured to discharge fuel from the fuel manifold into the mixing passage.