Abstract: Disclosed is a triple swirl gas turbine combustor using various fuels such as coal gas, DiMethyl Ether, and waste gas generated in an ironworks in a gas turbine. The triple swirl gas turbine combustor combusts three different fuels simultaneously or individually and various fuels such as LCV gas and HCV gas so that fuel flexibility can be improved. Swirl generated in a second swirler of the triple swirler is reversely jetted to increase a mixing degree of a fuel-air mixture and an intensity of a turbulent flow so that combustion efficiency can be increased, harmful exhaust gas can be reduced and vibration can be reduced.

Abstract: A dual fuel nozzle of a gas turbine combustor with a variable jetting hole diameter is disclosed. The combustor includes a plurality of swirling wings disposed along an outer peripheral surface of a central shaft to have at least one main fuel jetting hole, an air duct positioned at the lower side of the swirling wings to supply air to the swirling wings, a pilot fuel injection hole and jetting hole formed to pass through a central portion of the central shaft to supply a pilot fuel, a switching plate disposed inside the swirling wings to vary the size of the main fuel jetting hole, a driving unit disposed to be connected to the switching plate to move a position of the switching plate, and a casing containing the swirling wings, the air duct, the switching plate and the driving unit. It is possible to enhance fuel flexibility in a multiple fuel system for applying two or more fuels to a gas turbine at the same time.

Abstract: Disclosed herein are a fuel nozzle of a gas turbine combustor for dimethyl ether (DME, CH3OCH3) and a design method thereof. The fuel nozzle includes a pilot fuel injection hole formed at the center of the nozzle and a plurality of fuel injection ports formed at equiangular positions around the pilot fuel injection hole to inject DME. Each of the fuel injection ports includes a pair of upper and lower DME injection orifices communicating with a fuel-air mixture injection swirler. The upper DME injection orifice becomes gradually wider, whereas the lower DME injection orifice becomes gradually narrower. Thus, DME can be optimally combusted in the gas turbine combustor, thereby achieving cost reduction of power plants, enhancement in reliability of the power plants, and diversification of usable fuel.

Abstract: Disclosed is a triple swirl gas turbine combustor using various fuels such as coal gas, DiMethyl Ether, and waste gas generated in an ironworks in a gas turbine. The triple swirl gas turbine combustor combusts three different fuels simultaneously or individually and various fuels such as LCV gas and HCV gas so that fuel flexibility can be improved. Swirl generated in a second swirler of the triple swirler is reversely jetted to increase a mixing degree of a fuel-air mixture and an intensity of a turbulent flow so that combustion efficiency can be increased, harmful exhaust gas can be reduced and vibration can be reduced.

Abstract: Disclosed herein are a fuel nozzle of a gas turbine combustor for dimethyl ether (DME, CH3OCH3) and a design method thereof. The fuel nozzle includes a pilot fuel injection hole formed at the center of the nozzle and a plurality of fuel injection ports formed at equiangular positions around the pilot fuel injection hole to inject DME. Each of the fuel injection ports includes a pair of upper and lower DME injection orifices communicating with a fuel-air mixture injection swirler. The upper DME injection orifice becomes gradually wider, whereas the lower DME injection orifice becomes gradually narrower. Thus, DME can be optimally combusted in the gas turbine combustor, thereby achieving cost reduction of power plants, enhancement in reliability of the power plants, and diversification of usable fuel.

Abstract: A dual fuel nozzle of a gas turbine combustor with a variable jetting hole diameter is disclosed. The combustor includes a plurality of swirling wings disposed along an outer peripheral surface of a central shaft to have at least one main fuel jetting hole, an air duct positioned at the lower side of the swirling wings to supply air to the swirling wings, a pilot fuel injection hole and jetting hole formed to pass through a central portion of the central shaft to supply a pilot fuel, a switching plate disposed inside the swirling wings to vary the size of the main fuel jetting hole, a driving unit disposed to be connected to the switching plate to move a position of the switching plate, and a casing containing the swirling wings, the air duct, the switching plate and the driving unit. It is possible to enhance fuel flexibility in a multiple fuel system for applying two or more fuels to a gas turbine at the same time.