Method and apparatus for turbine system combustor...

Details Method and apparatus for turbine system combustor... Method and apparatus for turbine system combustor...

F - Mech Eng,Light,Heat,Weapons

02

C

60/137

F02C 3/04 (2006.01)

Patent

CA 1064269

ABSTRACT OF THE DISCLOSURE A method and apparatus for operating a gas turbine system are disclosed utilizing an adiabatic combustion process, employing combustion of a pre-mixed carbonaceous fuel-air admixture in a combustion zone. The combustion and the combustion zone are maintained at an approximately constant temperature by selective control of the fuel-to-air ratio over a period of turbine operation during which the fuel demand or the combustion air temperature varies. The fuel-air admixture is mixed with combustion products formed in a combustion zone into which the admixture is introduced. The fuel in the admixture is thermally combusted under essentially adiabatic conditions at a temperature approaching the adiabatic flame temperature to sustain the formation of combustion products. The resulting effluent is characterized by high thermal energy useful for generating power and may be low in atmospheric pollutants, including oxides of nitrogen.

310680

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