固体燃料超燃冲压发动机燃烧室的数值仿真

Numerical Simulation of a Solid Fuel Scramjet Combustors

基于一种固体燃料超燃冲压实验发动机的实验数据,使用数值模拟软件分别对超燃冲压发动机燃烧室的初始状态以及启动后的燃烧流动进行数值模拟。采用用户自定义函数方式给定PMMA燃料进口边界。数值模拟结果显示:燃烧室流场特性分布符合理论分析;燃烧室固体燃料壁面的燃料退移速率与实验数据有一定差异,但是整个燃面沿轴向的燃速分布规律与实验值近似;沿轴向的燃面附近的压力分布与实验结果较为吻合。研究结果表明:该数值计算模型较为合理,对固体燃料超燃冲压发动机的理论研究具有一定参考价值。

Based on a solid fuel scramjet experiment date, A CFD software is used in the numerical simulation respectively about scramjet combustor of the initial condition and the burning flow after the launch. Given the import boundary of PMMA fuel according to user defined function way. Numerical simulation results indicate that the flow field characteristics in combustor accord with theoretical analysis; it has certain different about the fuel regression rate on the surface of the solid fuel in combustor compare with experimental measurement, but the whole burning face＇s distribution curve of fuel regression rate along the axial is approximate with the experimental value; The pressure distribution near fuel surface along the axial is satisfying agreement with the experimental data. The results of the study show that the numerical model established is reasonable and have some reference value for the theory research of solid fuel scramjet.