Radial vortex phenomenon and instability mechanism of transonic axial-flow compressor

被引：0
作者：
Hu, Jia-Guo [1 ]
Wang, Ru-Gen [1 ]
Li, Shao-Wei [1 ]
Gan, Tian [1 ]
机构：
[1] Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2014年 / 29卷 / 09期
关键词：
Flow separation; Instability mechanism; Radial vortex; Tip clearance leakage; Transonic axial-flow compressor;
D O I：
10.13224/j.cnki.jasp.2014.09.030
中图分类号：
学科分类号：
摘要：
Numerical investigation was made on NASA Rotor 37 and the result was compared with an experiment. Working conditions from blocking point to stall point were calculated to study the rules of boundary layer separation and the instability mechanism of transonic axial-flow compressor. The research discovers a radial vortex behind passage shock wave in suction side boundary layer, which facilitates boundary layer separation and converges part of airflow near suction side to blade tip. With working conditions go to stall point, blade tip passage is jammed by two pieces of blocking zone; one located in the front of blade pressure side is caused by the interference of clearance leakage vortex and passage shock, while the other located on suction side after 50% chord is caused by the interference of radial vortex and leakage flow. The two blocking zones' expansion arouses instability of the compressor.
引用
收藏
页码：2239 / 2246
页数：7
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