摘要
大推力补燃循环液体火箭发动机主涡轮燃气在高压下由于受到真实气体效应的影响,其气体性能偏离理想气体,常规分析方法得到的涡轮性能与实际情况存在一定偏差。采用三维流动仿真方法,结合SST湍流模型,采用定物性理想气体、ARK气体状态方程和基于NIST Refprop真实物性数据库的涡轮性能进行了仿真研究,分析了甲烷和富氧燃气的涡轮性能,并与结合一维压缩因子修正的性能结果进行了对比。研究表明,基于真实物性数据的涡轮仿真性能与理想气体存在明显偏差,使用ARK气体状态方程能够有效减小性能仿真偏差,而使用合适的压缩因子修正具有较高的精度,可作为工程算法。
The performance of the main turbine gas of the high thrust afterburning liquid rocket engine deviates from the ideal gas due to the influence of the real gas effect at high pressure,and the turbine performance obtained by the conventional analysis method is somewhat different from the actual situation.In this paper,the three-dimensional flow simulation method and SST turbulence model were used to simulate the turbine performance with the ideal gas of constant properties,ARK gas state equation and NIST refprop real gas properties database,respectively.The turbine performances of methane and oxygen-enriched gas were analyzed and compared with the results of the performance modified by one-dimensional compression factor.The research shows that the simulated turbine performance based on the real gas property data has obvious deviation from that with the ideal gas.The ARK gas state equation can effectively reduce the deviation of the simulated performance,while the correction with the appropriate compression factor has enough accuracy and can be used for engineering.
作者
张鹏飞
李星
许开富
王晓峰
金路
ZHANG Pengfei;LI Xing;XU Kaifu;WANG Xiaofeng;JIN Lu(Xi'an Aerospace Propulsion Institute, Xi'an 710100, China;Academy of Aerospace Propulsion Technology,Xi'an 710100,China)
出处
《火箭推进》
CAS
2022年第2期94-104,共11页
Journal of Rocket Propulsion
基金
国家自然科学基金(51775412)。
