Effects of Fuel Injection Method on Gas Turbine Combustor Emissions
A series of tests have been carried out using a single segment of a tuboannular, aircraft-type, gas turbine combustion chamber to investigate the influences of operating conditions and fuel injection method on exhaust emissions. The test range included pressures up to 200 psia and inlet air temperatures from 380 to 900°K (684 to 1620°R). Concentrations of nitric oxide, carbon monoxide, unburned hydrocarbons and smoke were determined from gas samples obtained in the combustor exit plane.
KeywordsSoot Formation Fuel Flow Fuel Spray Pressure Atomizer Primary Zone
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