摘要
采用数值模拟方法,对NASA Rotor37跨音速轴流压气机从阻塞到近喘振工况的内部流动特征进行了分析,并同实验结果进行了对比.针对近喘振工况压气机顶部流动的特性,对间隙涡和通道激波进行顶隙吹吸干涉,分析了顶隙吹吸对该压气机特性的影响.结果表明,通过顶隙吹吸方法,可以有效地延缓顶部间隙涡及低能流体造成的通道阻塞而引发的流动失速,并使压气机的工作流量范围扩大24%。
The flow characteristics of NASA Rotor37 transonic axial-flow compressor from choke to near surge working condition are numerically simulated and validated in this paper. With the flow analysis of near surge condition, tip injection and bleeding are utilized to interact on tip leakage vortex and passage shock and the corresponding influences are investigated. Results reveal that with tip injection and bleeding, passage choke caused by fluid of low energy and tip clearance flow can be improved, thus compressor surge point can be effectively delayed. Results also show that with the injection and bleeding method used in this paper, the working range of NASA Rotor37 compressor is increased by 24%.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2008年第4期583-586,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.50676011)
关键词
顶隙吹吸
间隙涡
通道激波
tip injection and bleeding
tip leakage vortex
passage shock
