两级脉冲爆震发动机激波聚焦起爆数值模拟  

Numerical simulation of shock wave imploding detonation initiation in two-stage pulse detonation engine

作　　者：王丹[1] 严宇[1] 张锋[1] 陈鹏飞[1] 

机构地区：[1]中国航天科技集团公司西安航天动力研究所液体火箭发动机技术重点实验室,西安710100

出　　处：《航空动力学报》2017年第4期942-948,共7页Journal of Aerospace Power

摘　　要：通过数值模拟手段,针对两级脉冲爆震发动机(PDE)激波聚焦点火起爆及周期性脉冲爆震进行了详细计算.结果表明:激波汇聚会在发动机内产生两个高温高压区域,且后者压力温度远高于前者,为点火关键.针对起爆失败的工况,提高温度、压力、马赫数3个条件中的任何一个都能成功起爆.通过全场周期性脉冲计算得知,保证成功点火起爆的前提下仍需要调整合适的参数才能维持稳定的周期性脉冲,发动机在入口温度600K,马赫数为2.0,压力为150kPa工况时能够产生稳定的周期性脉冲爆震,频率在300Hz附近.Ignition method and periodic pulse in two-stage pulse detonation engine （PDE） were computed by numerical simulation. Results showed that two zones with high temperature and high pressure were engendered by shock wave imploding in engine. Temper- ature and pressure of the second zone became much higher than the first one, which was the key point of ignition. Depending on temperature, pressure or Mach number improvement, detonation appeared in the unfired condition. With precondition of successful ignition, modu- lating was still necessary to get appropriate inlet condition which can keep periodic pulse. Pe- riodic pulse with frequency of 300 Hz appeared by the inlet temperature of 600 K, Mach num- ber of 2.0 and pressure of 150kPa.

关 键 词：激波聚焦 两级脉冲爆震发动机(PDE) 点火 爆震燃烧 瞬态模拟技术 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]