Application Of FPV Model In Supersonic Turbulent Combustion Based On OpenFOAM

Scramjet can realize flight at hypersonic speed,and received extensive attention of scholars both at home and abroad.However,the cost of scramjet experiment is huge,with the rapid development of computational fluid dynamics(CFD)in recent years,the numerical simulation of scramjet has become an important research method.There are not only interaction among shock waves,expansion waves,boundary layers and flames,but also partial flameout and reignition phenomenon.Therefore it is greatly important to propose a combustion model which can be applied to supersonic turbulent combustion.This paper first reviews and summarizes the numerical research method and combustion model of the supersonic turbulent combustion,the most representative flame model is selected for the further study,and elaborate research status and adaptation of flame model under supersonic speed specially.In recent years,the Flamelet/Progress Variable(FPV)model developed from the flame model has been widely concerned by the scholars,because it can deal with the partial flameout and reignition problems in the combustion flow field.In the paper,based on the scramjet combustor as the research object,based on OpenFOAM open source software as platform,exploiting FPV model solver which is suitable for the supersonic turbulent combustion,using the solver simulating for the German aerospace center(DLR)supersonic combustor,and the calculated results are in good agreement with the experimental data.To validate the adaptability of the model solver further,three-dimensional complex supersonic combustion flow field of hydrogen fuel and hydrocarbon fuel are simulated respectively.From the calculation results,the typical supersonic combustion process can be well described,and can capture the phenomenon of flame lifts and the flameout.Therefore,the exploited solver can be applied to simulation supersonic combustion flow field with the cavity and the support plate of the typical stabilized flame structure combustor.In order to investigate the effect of Flamelet-Generated Manifolds(FGM)model on the numerical simulation of supersonic combustion,comparing the calculation result of two models,the results show that: the two models both use several characteristic scalars to describle the combustion state,compared with the FGM model,the FPV model's modeling thoughts are more consistent with the physical problem in the paper,the calculation results of FPV model are in good agreement with the experiment and literature results,and can better describe the supersonic combustion process,so the FPV model's calculation results are better.The results of this study can provide guidance for the selection of supersonic turbulent combustion models.