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

Journal of Thermal Science 2022年第1期31卷 141-150页

作者： CUI Weiwei WANG Xinglu YAO Fei ZHAO Qingjun LIU Yuqiang LIU Leinan WANG Cuiping YANG Laishun College of Civil Engineering and Architecture Shandong University of Science and TechnologyQingdao 266590China Institute of Engineering Thermophysics Chinese Academy of SciencesBeijing 100190China School of Aeronautics and Astronautics University of Chinese Academy of SciencesBeijing 100049China Key Laboratory of Light-duty Gas-turbine Chinese Academy of SciencesBeijing 100190China Key Laboratory of Civil Engineering Disaster Prevention and Mitigation of Shandong Province Qingdao 266590China Clean Energy Laboratory Shandong University of Science and TechnologyQingdao 266590China

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%incre

关键词： pressure-side winglet blade tip aerodynamic losses leakage channel stall margin

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Aerodynamic and Heat Transfer Simulation of Cooling Turbine blade with Different tips

Aerodynamic and Heat Transfer Simulation of Cooling Turbine ...

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The 2010 International Conference on Manufacturing Science and Materials Engineering(ICMSME 2011)

作者： Kuahai Yu Xi Yang Zhixun Wen Zhufeng Yue School of Schematizing and Architectural Engineering Henan University of Science and Technology School of Material Northwestern Polytechnical University Mechanics Engineering Department Northwestern Polytechnical University

This paper studies the aerodynamic and heat transfer influence of tip structures for cooling turbine blade. Four blades with different tip features are discussed, and coupling aerodynamic and heat transfer method is used to accomplish the simulation. The results show that squealer tip can greatly reduce the heat transfer between tip surface and high temperature gas, and also it reduces tip leakage, to some extent. That’s because it exists obviously eddy near the tip surface. tip injection holes can cool the tip surface effectively, and it will greatly reduce the temperature of tip surface. However, injection holes improve tip leakage slightly.

关键词： turbine blade blade tip squealer injection holes aerodynamic and heat transfer

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