Effects of Width Variation of Pressure-Side Winglet on Tip Flow Structure in a Transonic Rotor  

作　　者：CUI Weiwei WANG Xinglu YAO Fei ZHAO Qingjun LIU Yuqiang LIU Leinan WANG Cuiping YANG Laishun 

机构地区：[1]College of Civil Engineering and Architecture,Shandong University of Science and Technology,Qingdao 266590,China [2]Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China [3]School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China [4]Key Laboratory of Light-duty Gas-turbine,Chinese Academy of Sciences,Beijing 100190,China [5]Key Laboratory of Civil Engineering Disaster Prevention and Mitigation of Shandong Province,Qingdao 266590,China [6]Clean Energy Laboratory,Shandong University of Science and Technology,Qingdao 266590,China

出　　处：《Journal of Thermal Science》2022年第1期141-150,共10页热科学学报（英文版）

基　　金：This research work was sponsored by the General Program of National Natural Science Foundation of China(Grant No.52076124);Major Program of National Natural Science Foundation of China(Grant No.51790513);the General Program of Natural Science Foundation of Shandong Province(Grant No.ZR2020ME173).

摘　　要：Tip leakage flow has become one of the major triggers for rotating stall in tip region of high loading transonic compressor rotors.Comparing with active flow control method,it’s wise to use blade tip modification to enlarge the stable operating range of rotor.Therefore,three pressure-side winglets with the maximum width of 2.0,2.5 and 3.0 times of the baseline rotor,are designed and surrounded the blade tip of NASA rotor 37,and the three new rotors are named as RPW1,RPW2,and RPW3 respectively.The numerical results show that the width of pressure-side winglet has significant influence on the stall margin and the minimum throttling massflow of rotor,while it produces less effect on the choking massflow and the peak efficiency of new rotors.As the width of the pressure-side winglet increases from new rotor RPW1 to RPW3,the strength of leakage massflow has been attenuated dramatically and a reduction of 20%in leakage massflow rate has appeared in the new rotor RPW3.By contrast,the extended blade tip caused by winglet has not introduced much more aerodynamic losses in tip region of rotor,and the new rotors with different width of pressure-side winglet have the similar peak efficiency to the baseline.The new shape of the leakage channel over blade tip which replaces of the static pressure difference near blade tip has dominated the behavior of the leakage flow in tip gap.As both the new aerodynamic boundary and throat in tip gap have reshaped by the low-velocity flow near the solid wall of extended blade tip,the discharging velocity and massflow rate of leakage flow have been suppressed obviously in new rotors.In addition,the increasing inlet axial velocity at the entrance of new rotor has increased slightly as well,which is attributed to the less blockage in the tip region of new rotor.In consideration of the increased inlet axial velocity and the weakened leakage flow,the new rotor presents an appropriately linear increase of the stall margin when the width of pressure-side winglet increases,and has a nearly 15%inc

关 键 词：pressure-side winglet blade tip aerodynamic losses leakage channel stall margin 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]