Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting s...Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented.The inviscid numerical flux is evaluated using AUSM+-up upwind scheme.An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field.The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time.The turbulence modeling has been done using RNG-based k–model.Three-stage Runge–Kutta method has been used for explicit time integration.The nonreacting twodimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream.Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor,in which species profile at various axial locations has been compared.Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.展开更多
文摘Development of an Advection Upstream Splitting Method(AUSM+-up)scheme-based Unstructured Finite Volume(UFVM)solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented.The inviscid numerical flux is evaluated using AUSM+-up upwind scheme.An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field.The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time.The turbulence modeling has been done using RNG-based k–model.Three-stage Runge–Kutta method has been used for explicit time integration.The nonreacting twodimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream.Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor,in which species profile at various axial locations has been compared.Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.
