COMPUTATIONAL ANALYSIS OF MIXING IN SCRAMJET COMBUSTOR USING CROSS FLOW INJECTION TECHNIQUE

The prime issue in supersonic combustion is proper mixing within short duration of time since the flow is supersonic. Computational study has been performed to analyze the mixing of air and fuel using cross flow injection technique. Cross flow injection is performed by placing the fuel injectors on the walls of the scramjet engine which is perpendicular to the flow. To enhance the mixing of fuel and air, cavities were introduced. The flow recirculation inside the cavity will enhance the mixing and combustion. The fuel injectors were placed just upstream of the cavity. Analyses were done by changing the injection angle configurations. The air is allowed to enter at different Mach numbers and the changes were analyzed using ANSYS software packages. The roles of cavity cross flow injection, pressure, temperature, velocity and Mach umber variation were examined in this study and the obtained results were compared between various configurations.