摘要
以两个高负荷、高比转速离心叶轮与斜流叶轮为例,采用数值模拟的方法,在级环境下分析了两种叶轮的总体性能,以及内部流动机理.计算结果表明在高比转速情况下,斜流叶轮有利于减弱叶尖泄漏损失,改善叶轮出口均匀性,提高叶轮效率和级效率.
Two high specific speed centrifugal and mixed flow compressors were analyzed numerically using 3D viscous code. The overall performance and flow mechanism of two impellers were also analyzed. The results show that there are similar flow structures in two impellers＇ inducers. Mixed flow compressor achieves better performance and lower tip leakage loss, and flow field at outlet is more uniform in mixed flow impeller than centrifugal impeller.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第5期889-894,共6页
Journal of Aerospace Power
基金
航空支撑基金项目(04B51004)
关键词
航空、航天推进系统
斜流叶轮
离心叶轮
高比转速
叶尖泄漏
aerospace propulsion system
mixed flow impeller
centrifugal impeller
high specific speed
tip leakage
