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2022 , Vol. 31 >Issue 1: 141 - 150

DOI: https://doi.org/10.1007/s11630-022-1558-0

气动

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

  • CUI Weiwei ,
  • WANG Xinglu ,
  • YAO Fei ,
  • ZHAO Qingjun ,
  • LIU Yuqiang ,
  • LIU Leinan ,
  • WANG Cuiping ,
  • YANG Laishun
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  • 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

网络出版日期: 2023-11-30

基金资助

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) and the General Program of Natural Science Foundation of Shandong Province (Grant No. ZR2020ME173).

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Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
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Effects of Width Variation of Pressure-Side Winglet on Tip Flow Structure in a Transonic Rotor

  • CUI Weiwei ,
  • WANG Xinglu ,
  • YAO Fei ,
  • ZHAO Qingjun ,
  • LIU Yuqiang ,
  • LIU Leinan ,
  • WANG Cuiping ,
  • YANG Laishun
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  • 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

Online published: 2023-11-30

Supported by

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) and the General Program of Natural Science Foundation of Shandong Province (Grant No. ZR2020ME173).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
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摘要

间隙泄漏流成为触发高负荷跨声速轴流压气机转子旋转失速的主要诱因，而调整转子叶顶形状是拓展其高载荷条件下稳定工作范围的潜在手段之一。基于此，本文在NASA转子37叶顶几何形状的基础上，设计了三种最大宽度分别为2.0倍、2.5倍和3.0倍（相对于原型转子的叶顶沿程宽度）的叶尖小翼，并安装于转子叶顶的压力面侧（对应的新转子分别命名为RPW1, RPW2和RPW3）。数值结果显示，压力面小翼的宽度变化对压气机转子的工作裕度和左边界最小流量均具有显著影响，但是对转子堵塞流量和峰值效率的影响几乎很小。随着压力面叶尖小翼宽度的不断增加（由RPW1到RPW3），间隙泄漏流的强度得到明显抑制，且使得转子RPW3近失速工况的间隙泄漏流流量减少了20%左右。相比之下，压力面叶尖小翼引起的转子叶顶面积增加，并未在间隙区诱发更多的气动损失，因此加装三种不同宽度叶尖小翼的新转子与原型转子具有相似的峰值效率。新转子中由叶尖小翼重塑的新的叶顶泄漏通道形状取代转子叶顶两侧的静压差，成为决定间隙泄漏流特性的主要因素。由于压力面叶尖小翼增加了新转子叶顶的面积，而叶顶上方固壁附近的低速流体重塑并形成了间隙泄漏流新的气动边界和气动喉口结构（改变了叶顶间隙区的泄漏流速度分布特征），进而使得新转子中间隙泄漏流的泄漏流量和速度均得到明显抑制。此外，新转子在加装压力面叶尖小翼后，其叶尖进口轴向速度也有一定增加，有助于缓解转子叶尖区域的流动堵塞现象。综上分析，跨声速转子由压力面叶尖小翼宽度变化所诱发的进口轴向速度增加和间隙泄漏流强度减弱，使得新转子的工作裕度随着小翼宽度的增大呈现近似线性的增加趋势，尤其是小翼宽度最大的转子RPW3的工作裕度提升了近15%。

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

本文引用格式

CUI Weiwei , WANG Xinglu , YAO Fei , ZHAO Qingjun , LIU Yuqiang , LIU Leinan , WANG Cuiping , YANG Laishun . Effects of Width Variation of Pressure-Side Winglet on Tip Flow Structure in a Transonic Rotor[J]. 热科学学报, 2022 , 31(1) : 141 -150 . DOI: 10.1007/s11630-022-1558-0

Abstract

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% increase in new rotor RPW3.

Key words： pressure-side winglet; blade tip; aerodynamic losses; leakage channel; stall margin

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