Numerical Simulation of Supersonic Nonpremixed Turbulent Combustion in a Scramjet Combustor Model

摘要

Nonpremixed turbulent combustion is studied in situations relevant to those encountered in advancednairbreathing engines operating at high flight Mach number values. Accurate simulations would require modelingnboth finite rate chemical kinetics and molecular diffusion effects (mixing) as well as the complex compressiblenflowfield structure associated with the presence of multiple shock and expansion waves that significantly influencencombustion. The chemical kinetics aremodeled by using a Lagrangian framework for turbulent combustion that hasnbeen recently extended to reactive high-speed flows. The corresponding framework incorporates both finite ratenkinetics and turbulent molecular mixing rates with minimal additional parameters. An efficient anisotropic meshnadaptation strategy is used to obtain a satisfactory description of both nonreactive and reactive compressiblenflowfields. The present study confirmed that the proposed approach provides a well-suited framework for futurendevelopments devoted to nonpremixed turbulent combustion modeling in high-speed flows. A detailed comparisonnwith data gathered froman experimental study of a laboratory scramjetmodel indicated the validity of the approach.