Improved Turbulent-Combustion CFD Modeling for High Fuel-Air Ratio Combustor Analysis

"Current CFD combustion codes are not capable of predicting CO and H2 emissions in high performance military combustors with high-power operating conditions approaching stoichiometric. To provide this important capability, advanced turbulent-combustionmodels with multi-step chemistry are required. Accurate combustor modeling also requires extended calculation domains (from compressor discharge through turbine inlet guide vane) and improved mixing models. In Phase I of this SBIR, the feasibility ofmodeling advanced military combustors will be demonstrated. Two innovative models will be implemented into CFD-ACE+, the starting code for this project: 1) a dynamic Schmidt number model and 2) a joint PDF turbulence combustion interaction model formulti-step chemistry. The software will be used to model the Rolls-Royce AE3007 combustor at full-power conditions. Predictions will be compared to measurements of exit temperature and averaged emissions. The calculation will be repeated at high overallfuel-air ratios to assess the code's capabilities of capturing the nonlinear behavior of CO emissions and other important combustor operating parameters. In Phase II, more advanced turbulence-combustion models will be implemented into the code, includingthe Conditional Moment Closure (CMC) model. Analysis will be performed of the Rolls-Royce JSF F136 combustor, and predictions compared to measurements. Various combustor design modification