Numerical Analysis of Exhaust Emission from an Aero Gas Turbine Combustor under Fuel-Rich Condition

Emission characteristic of an aero gas turbine combustor has been studied under fuel-rich condition. The combustor has been designed to operate at rich fuel-air mixture and may experience very high mixture up to equivalence ratio of 3.0 in the primary zone in the event of atomizer deterioration and flow passage distortion or during some maneuver. The concentration of major engine emission/pollutant constituents at combustor exhaust such as CO, NOx, soot, unburned hydrocarbons and atmospheric pollutants such as CO2 and water vapor has been analyzed at fuel-rich high equivalence ratio using computational model in CFX. The pollutant concentrations are found to be increased with increase in equivalence ratio. Atomization quality in terms of fuel droplet size is found to have a significant contribution in the concentration of various species at combustor exit.