摘要
为了研究液体火箭发动机涡轮内流场,发展了一种基于相对流面理论和流线曲率法的多级跨声速叶轮机械流场计算方法.首先使用流线曲率法求解流面内的流场,再采用全三维流面迭代的方法得到三维流场.计算过程中通过临界流量的对比确定跨声速流道内的喉部位置,采用混合平面法将动、静叶间的非定常流动转化为定常流动.激波和黏性等损失通过相应的损失模型进行计算.对于多级流道内不同的超声速/亚声速流动状态则采用穷举法计算所有可能情况并用出口参数筛选最接近真实情况的结果.该方法准确地计算出了多级跨声速涡轮流场中的流动参数分布和性能参数,为进一步改进涡轮设计、提高涡轮性能提供了理论依据.
A three dimension transonic flow field solver for a multistage turbine in liquid rocket engine was developed based on relative stream surface theory and streamline curvature approach. The stream surfaces were calculated with the streamline curvature approach and the full three dimension flow field was solved by stream surface iterations. The throat was located by comparison of critical mass flux. The interaction between vanes and blades was dealt with the idea of mixing plane. Loss models were adopted to calculate the influence of shock wave and viscosity. The supersonic/subsonic flow conditions in different stages were filtered by com parison of exit parameters. The solver gave accurate flow parameter distribution and performance parameters of transonic multistage turbine, thus provides a theoretical basis for improving the design and performance of liq uid rocket engine turbine.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2013年第12期1591-1595,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
液体火箭发动机
多级涡轮
跨声速流场
全三维流面迭代
liquid rocket engine
multistage turbine
transonic flow field
full 3D stream surface itera tion
