Numerical Simulation Of The Flow And Combustion In A Scramjet Combustor

This thesis mainly focuses on an investigation on the numerical simulation of flow and combustion in a scramjet combustor. Firstly, we have implemented a new two step Taylor-Galerkin high order finite element scheme (TTGC), incorporated it into large eddy simulation and verified its applicability in the supersonic flow. The TTGC finite element scheme is capable of capturing complex structures for supersonic flow problems. Secondly, we have conducted large eddy simulation of flow and combustion in a general scramjet combustor with a strut. In non-reaction cases the results agree well with experiments. A Dynamically Thickened Flame model (DTF) is used in the corresponding reaction cases. The results show that the DTF model can be used in supersonic combustion prediction, but the accuracy of the predicted velocity results needs to be improved. Last part of the thesis introduces anisotropic mesh adaption for supersonic combustion simulation, where mesh generation is based on the flow field predicted.