초록 ▼

Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and air into a combustor downstream of the premixed reaction zone in order to achieve extremely low levels of emissions of oxides of nitrogen at the high combustor exit temperatures requ

Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and air into a combustor downstream of the premixed reaction zone in order to achieve extremely low levels of emissions of oxides of nitrogen at the high combustor exit temperatures required by advanced heavy duty industrial gas turbines. One or more premixing fuel nozzles are used to supply a lean mixture of hydrocarbon fuel and air to the main or primary reaction zone of a gas turbine combustor. This lean fuel/air mixture has an adiabatic flame temperature below the temperature that would result in substantial thermal NOx formation. After this low temperature reaction has been completed, additional fuel and air are injected into the products of combustion downstream of the main reaction zone in order to raise the temperature of the mixture to the level required to operate an advanced, high efficiency, heavy duty industrial gas turbine at high load. Formation of nitrogen oxides in the region after this secondary fuel and air injection is minimized by partial premixing of fuel and air prior to ignition and by minimizing the residence time between the secondary fuel injection and the turbine first stage inlet.

대표청구항 ▼

[ What is claimed:] [1.] A combustor for a gas turbine comprising:a primary combustion system for combusting a mixture of gaseous fuel and air, and operable in a plurality of gas turbine modes, said gas turbine modes being determined based on a load range of the gas turbine; anda secondary combustio

[ What is claimed:] [1.] A combustor for a gas turbine comprising:a primary combustion system for combusting a mixture of gaseous fuel and air, and operable in a plurality of gas turbine modes, said gas turbine modes being determined based on a load range of the gas turbine; anda secondary combustion system selectively operable in a high load range mode of the plurality of gas turbine modes, wherein said secondary combustion system comprises a lean direct injection (LDI) fuel injector assembly, said LDI fuel injector assembly comprising an air manifold, a gas fuel manifold, and a plurality of gas fuel/air injection spokes communicating with said air manifold and said gas fuel manifold.