Exploration of shock-induced flow dynamics and turbulence-driven combustion optimization in advanced cavity configurations of hydrogen fueled scramjet combustors

Abstract This study investigates the impact of shockwaves induced by various combustor wall geometries – wedge, wavy wall, circular bumps, and triangular bumps – on scramjet combustor performance. Using CFD simulations in ANSYS Fluent 23.1 with RANS equations and the SST turbulence model, key parameters such as velocity, static pressure, temperature, turbulence intensity, and combustion efficiency are analyzed. Circular bumps exhibit superior performance, achieving higher turbulence intensity (42 %), enhanced fuel-air mixing, and minimized static pressure losses (8 %), optimizing supersonic flow dynamics. This geometry ensures better combustion efficiency, reducing unburned fuel and maximizing heat release. While wedge and triangular geometries improve mixing and flow stability, they are less effective than circular bumps. The wavy wall structure provides a balanced performance. The findings highlight the potential of circular bumps in advancing scramjet combustor designs, offering valuable insights for hypersonic propulsion system enhancements.