High Fuel-Air Ratio (FAR) Combustor Modeling

"A high fuel-air ratio combustor/turbine computational model (computer code) is proposed for development in this SBIR project. The proposed computational model will address fuel-air ratio and temperature non-uniformities and fluctuations at the combustorand 1st stage high pressure turbine exit planes based upon actual JP-8 fuel chemical kinetics. A reduced chemical kinetic model will be developed using a detailed JP-8 chemistry mechanism and implemented into the combustor/turbine computational model. Theproposed computational combustor/turbine model will also address secondary combustion in the high pressure turbine blades film cooling. Steady-state as well as transient operational effects upon high-fuel air ratio fluctuations, chemical speciesdissociation and recombination reactions, maximum temperature rise and fluctuations, pattern factor, and film-cooling reactivity will all be predicted in an efficient manner. The proposed combustor/turbine computational model will be capable of identifyingthe impact of various operating parameters through detailed parametric studies, which can not be accomplished by the conventional multi-dimensional CFD codes. It is therefore anticipated that the proposed combustor/turbine computational model will become,once validated, an integral part of the high-fuel air ratio combustor design cycle. It is anticipated that the proposed high fuel-air ratio combustor/turbine computational model for development