To improve the combustion performance of solid rocket scramjet and understand the effect of combustor design parameters on combustion mode and performance,this study has analyzed the impact of the minimum geometric throat of combustor and the distance between the front edge of cavity and fuel injector port on the flow and gas-solid two-phase combustion characteristics in the combustor using numerical simulation.The results show that the minimum geometric throat of the combustor affects the position of the thermal throat by changing the degree of obstruction in the combustor.With the increasing distance between the front edge of the cavity and the fuel injector port,the resulting low-speed zone presents a stronger blocking effect on the air flow,thus increasing the retention time of the particulate phase fuel and improving the combustion efficiency.The combustion efficiency of particulate phase fuel is the key factor that dominates the overall combustion efficiency,and affects the improvement of the combustor performance and the modification of combustion mode.
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