Supersonic Partial Premixed Combustion Simulation Based On Unsteady FPV Model

Hypersonic vehicle is widely applied in various fields such as missiles,reconnaissance aircraft and space planes.Scramjet is a stable and efficient power plant for Hypersonic vehicles,but it is supposed to be one of the keystones and difficulties,hence domestic and foreign scholars carried out many related researches for a long time.In this paper,the numerical simulation method is used to study the supersonic combustion problem in scramjet engines,which mainly involves high resolution shock capturing schemes,turbulence model and combustion model.Through conclude and summarize results of recent years supersonic combustion,the simulation and the experiment results are similar in supersonic combustion,but the temperature and intermediate component simulation results have certain errors.Therefore,turbulent model and combustion model is thoroughly studied,finished an overview of combustion model and a study of applicability for flamelet model in supersonic combustion.Based on OpenFOAM,a fluid software,developed a solver UFPVcompressflameletFoam which can used Unsteady Flamelet/Progress Variable Model(UFPVM).U-se d the advanced combustion modelsimulatedthe Combustor of Scramjet,resolved theprobl em of temperature errors in Numerical simulation on supersonic combustion.In this paper,the standard k-? model and SST k-? model are used to simulate the DLR supersonic combustion chamber.The results show that the SST k-? model was more accurate in near wall area,and thetemperature estimate is closer to the experimental value.For resolved the problem of temperature errors,This paper compares the UFPVM and FPVM simulation results of the DLR supersonic combustion chamber after discussed different detailed chemical reaction mechanisms and three-dimensional effects on the results.The results showed that the FPVM and UFPVM are similar in the experiment results,In comparison to FPVM,UFPVM is more accurate for temperature simulation.In order to research the influence of different conditions,the numerical simulation of the cavity supersonic combustor is carried out by UFPVcompressflameletFoam.The results is similar with literatures.The fuel totalpressurehas little influence on combustion but the injection anglehas great influence.