推力调节阀流场分析  

Flow Field Analysis of Thrust Control Valve

作　　者：张成印[1] 徐姗姗[1] 鲍锦华[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《载人航天》2016年第2期169-174,共6页Manned Spaceflight

基　　金：载人航天预先研究项目(060302)

摘　　要：为研究推力调节阀结构对内流场分布及流量特性的影响,利用计算流体力学方法对窗口式气体调节阀的流场进行了仿真计算,该调节阀在作为软着陆下降级的液氧/甲烷发动机中起到推力调节作用。仿真得到了调节阀流场的压力分布、速度分布。速度场分布给出了流场中各处流速分布及漩涡出现位置,证明了出口锥角对流场导流作用,能显著影响出口流场中的漩涡数量;压力场结果准确表明流场中节流只发生在窗口位置,不存在二次节流,验证窗口设置及结构的合理性;计算得到了不同调节工况下调节阀的流量系数,变化趋势为随着推力工况增高而降低。The aim of the paper was to analyze the effects of thrust control valve structure on the in.ternal flow field and the flux characteristic. The fluid flow of window.type thrust control valve, whichcould adjust the Lander descent engine with LOX/ methane, was simulated by the numerical methodto investigate the pressure and velocity profile in the valve. From the distribution of velocity and lo.cations of the vortex in the velocity field, it is proved that the outlet taper angle could effectively re.duce the vortex in the flow. The pressure results indicated that the throttling effect on the flow onlyoccurred nearby the window without the secondary flow. This also demonstrated the rationality of thewindow’s design. The flow coefficient of the valve under different flow conditions was documentedand showed a decrease trend by the increasing thrust.

关 键 词：下降级 推力调节 液氧/甲烷 窗口调节阀 CFD 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]