Numerical simulation of combustion chamber flow field for solid-liquid rocket ramjet

The solid-liquid rocket ramjet(SLRR),compared with traditional ducted solid propellant rocket or liquid fueled ramjet,has an evident advantage of matching operation of solid and liquid fuel.Based on discrete phase model(DPM) and single-step reaction model,numerical simulation of two-phase flow field in the combustion chamber with different configurations and working conditions was conducted with Fluent under design point flight parameter.The results show that the generator nozzle parameter and inlet angle of the air duct mainly influence the circumfluence in head region, and the impact of air flow and gas flow;the inlet circumferential angle decides the distribution of liquid fuel droplets;and the engine specific impulse increases firstly and then decreases with the increase of residual gas coefficient.According to the simulation results,the structure parameters and residual gas coefficient range beneficial to engine performance are presented.