Method and apparatus for turbine system combustor...

F - Mech Eng,Light,Heat,Weapons – 02 – C

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60/137

F02C 9/16 (2006.01) F02C 9/00 (2006.01)

Patent

CA 1042671

ABSTRACT OF THE DISCLOSURE A method and apparatus for operating a gas turbine system are disclosed utilizing an adiabatic com- bustion 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. Such combustion may be conducted in the presence of an oxidation catalyst and the combustion zone, including any catalyst, is maintained at an approximately constant temperature. In a mode of operation which is preferred when conditions permit, such temperature is substantially above the instantaneous auto-ignition temperature of the fuel-air admixture but below a temperature that would result in any substantial formation of oxides of nitrogen. The resulting effluent is characterized by high thermal energy useful for generat- ing power and may be low in atmospheric pollutants, includ- ing oxides of nitrogen.

238500

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