Effect of shock generator on fuel mixing in an annular single lobe transverse nozzle at the supersonic combustion chamber of a scramjet engine using computational fluid dynamics

This study investigates the influence of a wedge shock generator on hydrogen mixing in an annular single lobe transverse nozzle at the supersonic combustion chamber of a scramjet engine using computational fluid dynamics (CFD). The fuel mixing process is crucial for efficient combustion in scramjet engines, which operate at high speeds and require rapid mixing of fuel and air. The shock generator is a device that generates a shock wave in the flow field, which can enhance mixing by increasing turbulence and promoting the fuel penetration into the air stream. A comparison of three lobe injectors is done to attain the efficient nozzle type for the fuel mixing inside the combustion chamber. CFD simulations were done to analyze the consequence of the shock generator on fuel mixing in the nozzle and assess its potential for improving combustion efficiency. The results show that the usage of shock generator can significantly enhance fuel-air mixing in the nozzle, leading to improved combustion efficiency and reduced emissions. The findings of this study provide valuable insights into the design and optimization of shock generators for scramjet engines, which can contribute to the development of more efficient and sustainable air-breathing propulsion systems. •Influence of shock generator on the mixing of single fuel jet at supersonic flow is studied.•The shock wave interactions of the single lobe injector are investigated.•CFD method is used for the modeling of supersonic flow and cross jet at combustion chamber.•The interaction of incident shock waves has great impact on the fuel mixing downstream the jet.