Study on the aerodynamic effects on the excitation of the combustion flow field in solid rocket ramjet engines

This paper first analyzes the reasons for low combustion efficiency in the afterburner and proposes a solution utilizing aerodynamic effects. The accuracy of the numerical method is verified by a ground direct-connected experiment. Through analyses of combustion efficiency, particle mixing degree, and flow field characteristic, the study compares the excitation effects of single-side and double-side aerodynamic effects and investigates the optimal application position. Further comparisons are conducted between array and non-array aerodynamic effects under various flow rates. The results show that the momentum transfer between aerodynamic airflow and gas has a significant impact on the flow field. Single-side excitation outperforms double-side excitation in promoting particle-air mixing and combustion. Initiating aerodynamic intervention as early as possible after the gas passes through the air intake outlets is more effective. At the optimal position, aerodynamic excitation improves combustion efficiency by 83.5 %. The excitation effect improves with larger aerodynamic flow rates. A threshold for aerodynamic flow rate is identified. When it is below the threshold, the non-array scheme can achieve efficient energy conversion, allowing a small aerodynamic flow rate to result in a significant improvement in mixing and combustion. When it exceeds the threshold, the array scheme performs better.