Numerical investigation on Staged transverse injection in a Scramjet combustor and its mixing Augmentation using expansion ramp

Abstract

This work involves an application of the computational fluid newlinedynamics to a problem associated with the flow inside the supersonic newlinecombustor region of a scramjet engine An existing supersonic combustor newlinemodel canonical model consisting of the staged transverse injection behind a newlinerearward facing step was simulated for various flow conditions to investigate newlinethe flow in detail A method for augmenting the mixing of air and the fuel in newlinethe canonical model was suggested by introducing the expansion ramps on newlineboth the sides of the injectors and its effectiveness was tested by numerical newlinemethods The intent was to promote streamwise vorticity by modifying newlinegeometry to improve the mixing characteristics in the combustor newlineThe combustor models were simulated using the finite volume newlinebased code FLUENT and the governing equations were solved by means of a newlinecoupled explicit method using shear stress transport SST K turbulence newlinemodel newline