摘要
应用湍流κ-ε双方程模型,分析了液体火箭发动机自引射工作过程所用的超声速自引射装置(简称引射器,包括圆柱型和二次喉道型引射器)在相同二次流入口面积时的流场分布,依据流场分析值确定了激波在引射器内的位置,结果表明喷管内的气流达到满流状态,并根据有关参数计算了引射系数.对比引射器真空舱内压力仿真值和试车测量值,两者基本一致.
The analysis model of self-ejector （ejector for short, including cylindrical e- jector and second-throat ejector） was set up in liquid rocket engine. The two equation κ-ε model was employed to simulate the turbulence. The performances and the flow field fea- tures of cylindrical and second-throat ejector were gained in same gap. According as these flow fields, the site of the shock wave, the full flow in nozzle, the coefficients of ejecting were calculated. The numerical value was compared with hot fire test value in vacuum cab- in, both are same.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第1期218-224,共7页
Journal of Aerospace Power
关键词
液体火箭发动机
引射器
流场
数值模拟
引射系数
liquid rocket engine
ejector
flow fields
numerical simulation
coefficients of ejecting
