Large-Eddy Simulation of a Full Annular Rql Combustion Chamber: Fuel Distribution Effects on the Combustor Exit Temperature Profile

Abstract

The design of an aero engine combustion chamber is a difficult process in order to meet engine performance requirements. One of the most important problems in the design and development of an aero engine combustion chamber is to achieve uniform temperature pattern in circumferential direction and a radial temperature profile in traverse direction with a peak in the middle. The exit temperature profile affects the turbine nozzle guide vane and the overall engine life time. Moreover, Large Eddy Simulation(LES), is a substantial technique for prediction of reacting flow simulations that contain turbulent mixing and combustion process. Hence, in this study LES of non-premixed reacting flow in a full annular RQL, Rich-burn, quick-Quench, Lean-burn, combustor is performed to investigate the effects of fuel distribution on combustion chamber exit temperature for both uniform and non-uniform fuel distribution for fuel injectors. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.