固冲发动机沉积数值模拟与试验研究

Numerical simulation and experimental study of deposition for ducted rockets

分析了液滴撞壁模型的发展概况,基于Mundo模型,分析了粘附、反弹、飞溅3种状态的固冲发动机沉积模型,并对发动机内沉积问题进行了数值模拟与试验研究。结果表明,发动机内沉积主要集中在补燃室头部、进气道下游、冲压喷管收敛段;颗粒粒径分布对沉积位置影响很大;由试验压强-时间曲线换算得到的冲压喷管喉部沉积速率与数值模拟结果基本相符。

Various droplet/wall interaction models and a deposition model accounting for deposition, rebound and splash modes for ducted rockets were analyzed and deposition for ducted rockets were numerically simulated and experimentally investigated. The result shows that deposition for ducted rockets is mostly focused in the zones such as the head-end of secondary combustion chambers, downstream inlet and convergent section of nozzle. The particle size distribution has a great effect on the depositing position, and the deposition velocity at the nozzle throat computed from pressure-time curve is agreeable to numerical simulation results.