组合推进剂下凝相燃烧产物对喷管壁面温度的影响

Influence of concretionary combustion components of propellant to nozzle wall temperature at high-low temperature combined propellants

为研究高低燃温组合推进剂凝相产物对喷管壁面温度的影响,设计了不同低燃温推进剂含量及燃烧产物粒径的对比工况。研究结果表明,低燃温推进剂燃气有效降低了壁面温度及减少粒子对壁面的碰撞,两者对壁面温降作用相当。同时开展了组合推进剂下喷管外壁面温度测试试验,低燃温推进剂含量为6.8%时,喷管外壁面最高温度下降40.5%。最后开展了流固耦合计算,获得了喷管外壁面温度随时间的变化,计算结果与试验数据基本一致。

For researching the influence of concretionary combustion components of propellant to nozzle wall temperature at high-low temperature combined propellants, the simulation models using different mass percent of low temperature propellant and particle diameters of concretionary combustion components was designed. The simulation results indicate that the low temperature combustion-gas can effectively decline inner-wall temperature and collision between particle with inner-wall; two functions for inner-wall temperature decline are almost equivalently. High-low temperature combined propellant experiments were conducted at the same time, when the mass percent of low propellant is 6.8%, the highest temperature of nozzle out-wall is decline 40.5% compare with using pure high-temperature propellant. A simulation of flow-structure has been taken at the last, temperature change by time of noz- zle out-wall has been figure out, the results of numerical simulation are basically matched with the experiment outcome.