Flamelet modeling of two-phase n-dodecane supersonic combustion using a skeletal chemical reaction mechanism

摘要

Numerical simulations of the direct-connect,hydrocarbon-air scramjet engine at Beihang University' s Supersonic Combustion Facility were conducted using the commercial CFD(Computational Fluid Dynamics)software,FLUENT 13.0.The fuel was liquid n-dodecane,which was the main component of the aviation kerosene.The reacting turbulent flow was solved using the shear stress transport(SST)k-ω turbulence model,particles stochastic trajectory model,steady-flamelet model and a skeletal chemical reaction mechanism with 57 species and 204 reactions.The numerical results including two reacting cases with different equivalence ratios were compared well with the experimental data to validate the numerical model and provide insight into the experimental flowfield behavior.The combustion efficiency and total pressure recovery were obtained to assess the combustion performance of the model combustor.The OH and CO mass fraction contours were also used to illustrate the main combustion zone.