摘要
为了进一步加深对转子叶尖区域非定常流动现象的认识,针对某一跨声速单转子轴流压气机,采用三维非定常数值方法开展了详细研究。对单转子在不同进气条件以及不同工作流量下分别进行非定常模拟,来研究该转子叶尖区域复杂流动结构以及叶尖非定常流动的发展过程。结果表明:不同进气条件下,转子叶尖区域流场结构形式表现不同.当进口非轴向进气时,叶尖非定常流动呈单通道周期形式;而轴向进气时,叶尖区域出现了类似于"旋转不稳定"的沿周向传播的非定常流动现象,且随着工作流量的减小,叶尖区域流场结构也相应发生改变.
The detailed three-dimensional unsteady numerical study was conducted in a transonic compressor rotor to deepen the understanding of unsteady flow phenomenon in rotor blade tip region.Unsteady numerical simulations were studied in single rotor under different inlet conditions and different mass flows,so as to investigate the complex flow structure in rotor blade tip region and the development of blade tip unsteady flow.Results showed that the structure of blade tip flow field varied under different inlet conditions.When inlet direction was non-axial,signal passage periodical form emerged for unsteady flow at blade tip,while an unsteady flow phenomenon like “rotating instability”spreading along circumferential direction,occurred in blade tip region under axial inlet condition.And with the decrease of mass flow,the structural flow field of blade tip region changed correspondingly.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第6期1481-1490,共10页
Journal of Aerospace Power
基金
国家自然科学基金(51406080)
中央高校基本科研业务费专项资金(NJ20150008)
关键词
叶尖泄漏流
旋转不稳定
非定常流动
流场结构
跨声速压气机
blade tip leakage flow
rotating instability
unsteady flow
structure flow field
transonic compressor
