摘要
本文在不同攻角和不同雷诺数Re下,对离心压气机进口导叶的内部流动进行了数值分析,探讨了导叶翼型绕流尾涡的非定常发展过程。结果表明,对本文所研究的导叶,攻角在30°～60°范围内,当雷诺数Re低于80时,流动是稳定的,翼型后方不出现大尺寸的流动分离;雷诺数Re大于80时,流动是非稳态的,此时翼型后方出现流动分离,并伴随有显著的涡脱落。
The flow passing the inlet guide vanes of centrifugal compressors are calculated numerically under different incidence angles and different Re Numbers, the unsteady development of the trail vortices are discussed. The range of incidence angles are from 30 to 60 degrees in the calculations. It is found when Re Number is under 80, the flow is steady , no unsteady separation appears behind the wing, and when Re Number is beyond 80, the flow is becoming unsteady, prominent vortice shedding happens in flow field.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2003年第6期958-960,共3页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.50274047)
关键词
数值分析
进口导叶
非定常尾涡
numerical analysis
inlet guide vane
unsteady confined wakes
