摘要
为进一步揭示超声速流动条件下压气机叶排干扰机理,提高对跨/超声速压气机流动的认识,基于课题组自主研发RANS方程解算器,运用非定常数值模拟的方法对超声速压气机静/转叶栅级间干涉进行研究。研究结果表明,超声速压气机静/转叶栅通道中存在较为复杂的相互干涉,下游转子叶栅外伸激波被上游静子叶栅切割,并强烈扰动静子叶栅通道中的流动,造成静子叶片表面压力波动较大;静子叶栅尾迹区存在较强的熵增,在向下游传播的过程中被转子叶栅切割,在转子叶栅通道中,尾迹区域变形并向压力面靠拢,最终与转子叶栅尾迹相互作用,使得转子叶栅尾迹呈类卡门涡街形式脱落。
To further understand the stator-rotor interaction in supersonic compressor cascade,and enhance the understanding of transonic/supersonic cascade flow,the influence of the stator-rotor interaction in shock-in-type supersonic compressor is discussed by unsteady numerical simulation based on in-house RANS slover.The results show that the interaction of the stator-rotor cascade is very complex.The overhanging shock wave in the rotor cascade is carved up by upstream stator cascade,and the behaviour leads to complex fluid in the stator and unsteady static pressure on the stator.The wakes of the stator have high entropy production,and they are carved up by the rotor cascades.In rotor cascade channel,the wakes zone transforms and closes to the pressure side of rotor.The wakes have influences on the rotor’s wake.So the wake of the rotor cascade is similar with that in Karman vortex shedding.
作者
郝颜
江雄
邱名
王子维
HAO Yan;JIANG Xiong;QIU Ming;WANG Ziwei(Computational Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《空气动力学学报》
CSCD
北大核心
2018年第5期749-756,共8页
Acta Aerodynamica Sinica
基金
国家自然科学基金(11572339)
中国空气动力研究与发展中心风雷青年创新基金资助项目(FLYIF20160008)
关键词
内激波转子式
超声速叶栅
静转子干涉
尾迹激波干扰
非定常
数值模拟
shock-in-type rotor
supersonic cascade
stator-rotor interaction
wake-shock interaction
unsteady
numerical simulation
