reacting flow simulations of a dual throatdual fuel thruster

Numerical simulation of the supersonic turbulent reacting flow field in a dual throat- dual fuel rocket thrust chamber is presented. future single stage to orbit and high lift space transportation missions aspire a reliable, efficient, and cost-effective propulsion systems. the dual throat-dual fuel concept is a simple altitude compensating propulsion alternative with reusable possibilities. turbulent reacting supersonic flow field emanating from independent thrust chambers needs to be resolved for a better understanding of the flow structures and design modifications for the performance improvement. the operation of a dual throat nozzle brings about a unique shock train in reacting supersonic flow. two-dimensional axis-symmetric compressible reacting flow field has been solved using hllc (harten, lax, van leer, with contact wave) scheme based finite volume riemann solver with multi-step finite rate chemistry model for hydrocarbon/hydrogen-oxygen combustion. the computational procedure has been validated with experimental data for species distribution of a coaxial supersonic combustor. chemical species distribution in the supersonic free shear layer is analyzed in detail to explore the nature of active reaction zones in the flow field.