Optimization of Fuel-Air mixing for a Swept Ramp Scramjet Combustor Geometry using CFD and a Genetic Algorithm

A swept ramp scramjet combustor section has been optimized for maximum performance during a cruise condition using integrated CFD and Genetic Algorithms (GA) on a Massively Parallel Computer Cluster Network (MPCCN). The ramp geometry was made variable by varying the ramp and sweep angles for a fixed given height of the ramp. The performance goals were quantified as total pressure ratio between the inlet and outlet of the combustor and the fuel-air mixing efficiency for a dual goal optimization. Validation of the CFD grids was performed by comparing flow parameter contours against experimental data. The results of the optimization show significantly improved results under the direction of the GA for both the total pressure ratio as well as mixing efficiency. The methodology developed offers a powerful tool for preliminary analysis of future scramjet engines.