固液火箭冲压发动机燃烧室流场数值仿真

固液火箭冲压发动机通过固液两种燃料匹配工作,相比传统的固体火箭冲压发动机和液体燃料冲压发动机具有较为明显的优势.基于离散相模型和单步反应模型,采用Fluent 对设计点飞行参数下,不同结构和不同工况条件下的燃烧室两相反应流场进行了数值仿真.结果表明,燃气发生器喷管参数和进气道进气角度主要影响空气与燃气流的撞击以及头部区...

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.