叶尖小翼对小流量跨声速压气机转子的影响研究

推进技术 ›› 2017, Vol. 38 ›› Issue (11): 2522-2531.

叶尖小翼对小流量跨声速压气机转子的影响研究

牛汗,刘波,史磊,那振喆,张鹏,茅晓晨

西北工业大学动力与能源学院，陕西西安 710129,西北工业大学动力与能源学院，陕西西安 710129,西北工业大学动力与能源学院，陕西西安 710129,西北工业大学动力与能源学院，陕西西安 710129,西北工业大学动力与能源学院，陕西西安 710129,西北工业大学动力与能源学院，陕西西安 710129

发布日期:2021-08-15
作者简介:牛汗，男，硕士生，研究领域为叶轮机械气动热力学。
基金资助:
国家自然科学基金面上项目(51676162)；先进航空发动机协同创新中心资助。

Investigation of Blade Tip Winglet Effects on Transonic Rotor of Low Flow Rate Compressor

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

Published:2021-08-15

摘要/Abstract

摘要： 为了控制压气机转子叶尖泄漏流动，减少叶尖泄漏流和叶尖泄漏涡对压气机内部流场带来的不利影响，针对小流量压气机进口跨声速转子进行了叶尖小翼的数值研究，探索了叶尖小翼对小流量跨声速压气机转子性能的影响和对叶尖泄漏流的控制机理。研究表明，4倍压力面宽度的压力面叶尖小翼可以使得压气机转子的流量裕度增加24.5%；吸力面叶尖小翼和压力面叶尖小翼影响失速的主要因素不同，吸力面叶尖小翼增大了吸力面侧流体的逆压梯度，扩大了低速流体区域，压力面叶尖小翼通过降低叶尖负荷，从而减弱泄漏强度，减小了低速流体区域。

关键词: 叶尖小翼；小流量压气机；跨声速转子；叶尖泄漏流；叶尖泄漏涡

Abstract: In order to control the tip leakage flow of compressor rotor and reduce the adverse effects of tip leakage flow and tip leakage vortex on the internal flow of the compressor，a numerical simulation of blade tip winglet aimed at transonic rotor of a low flow rate compressor has been carried out，exploring the effect of blade tip winglet to the transonic rotor of low flow rate compressor and the control mechanism of tip leakage flow. Research shows that the pressure-side winglet which has four times width of thickness of pressure side can make the flow stall margin of the compressor rotor increase 24.5%.The main factors of suction-side winglet and pressure-side winglet influencing the stall of compressor stall are different. Suction-side winglet increases the adverse pressure gradient of the fluid at the suction side，expanding the low-speed fluid region and pressure-side winglet reduce the low-speed fluid region by reducing the tip load to weaken the leakage intensity.

Key words: Blade tip winglet；Low flow rate compressor；Transonic rotor；Tip leakage flow；Tip leakage vortex

牛汗,刘波,史磊,那振喆,张鹏,茅晓晨. 叶尖小翼对小流量跨声速压气机转子的影响研究[J]. 推进技术, 2017, 38(11): 2522-2531.

NIU Han,LIU Bo,SHI Lei,NA Zhen-zhe,ZHANG Peng,MAO Xiao-chen. Investigation of Blade Tip Winglet Effects on Transonic Rotor of Low Flow Rate Compressor[J]. Journal of Propulsion Technology, 2017, 38(11): 2522-2531.

参考文献

[1] Denton J D. The 1993 IGTI Scholar Lecture: Loss Mechanisms in Turbomachines[J]. ASME Journal of Turbomachinery, 1993, 115(4): 621-656.
[2] Yamada K, Funazaki K, Furukawa M. The Behavior of Tip Clearance Flow at Near-Stall Condition in a Transonic Axial Compressor Rotor[R]. ASME GT 2007-27725.
[3] 谢芳, 楚武利, 张皓光. 跨声轴流压气机激波/泄漏涡/边界层分离相互作用的影响[J]. 航空动力学报, 2012, 27(2): 425-430.
[4] 杜娟. 跨声速压气机/风扇转子叶顶泄漏流动的非定常机制研究[D]. 北京:中国科学院研究生院(工程热物理研究所), 2010.
[5] 敬荣强, 李泯江, 桂幸民. 高负荷跨声速压气机叶尖间隙流动的数值分析与比较[J]. 航空动力学报, 2003, 18(6): 827-831.
[6] Suder K L, Hathaway M D, Thorp S A, et al. Compressor Stability Enhancement Using Discrete Tip Injection[J]. ASME Journal of Turbomachinery, 2000, 123(1).
[7] 张弛明. 利用形状记忆合金控制压气机叶尖间隙的技术研究[D]. 北京:北京航空航天大学, 1997.
[8] 曹广州. 刷式封严结构的泄漏特性研究[D]. 南京:南京航空航天大学, 2006.
[9] Koch C C . Experimental Evaluation of Outer Case Blowing or Bleeding of Single Stage Axial Flow Compressor[R]. NASA CR-54592, 1970.
[10] 袁巍, 周盛, 陆亚钧. 压气机间隙流与处理机匣作用的三维数值分析[J]. 北京航空航天大学学报, 2004, 30(9): 885-888.
[11] Gallimore S J, Bolger J J, Cumpsty N A, et al. The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading, Part I: University Research and Methods Development[J]. ASME Journal of Turbomachinery, 2002, 124(4): 33-47.
[12] Gallimore S J, Bolger J J, Cumpsty N A, et al. The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading, Part II: Low and High-Speed Designs and Test Verification[J]. ASME Journal of Turbomachinery, 2002, 124(4): 49-59.
[13] 贾希诚, 王正明, 蔡睿贤. 叶轮机械中叶顶间隙形态对气动性能影响的数值研究[J]. 工程热物理学报, 2001, 22(4): 431-434.
[14] 邵卫卫, 季路成, 黄伟光. 轴流压气机叶尖片削全工况特性分析[J]. 航空动力学报, 2008, 23(2): 367-373.
[15] Whitcomb R T. A Design Approach and Selected Wind Tunnel Results at High Subsonic Speeds for Wing-Tip Mounted Winglets[R]. NASA TN D-8260, 1976.
[16] 郑国胜, 戴韧. 轴流风扇叶片端导叶作用的研究[J]. 工程热物理学报, 2006, 27(S1): 165-168.
[17] 黄中华, 陈泽, 戴韧. 带端导叶平面叶栅流动结构与性能的数值研究[J]. 流体机械, 2008, 36(6):30-33.
[18] Akturk A, Camci C. Development of a Tip Leakage Control Device for an Axial Flow Fan[R]. ASME GT 2008-50785.
[19] 韩少冰. 压气机平面叶栅加装叶尖小翼的数值研究[D]. 大连:大连海事大学, 2009.
[20] 韩少冰, 钟兢军. 变冲角下吸力面小翼对压气机叶栅气动性能的影响[J]. 推进技术, 2012, 33(3): 384-390. (HAN Shao-bing, ZHONG Jing-jun. Effects of Suction-Side Winglet on Aerodynamic Performance of Compressor Cascade at Different Incidence [J]. Journal of Propulsion Technology, 2012, 33(3): 384-390.)
[21] 韩少冰, 钟兢军. 具有叶尖小翼的压气机叶栅间隙流动分析[J]. 工程热物理学报, 2012, 33(9): 1492-1496.
[22] 钟兢军, 阚晓旭, 陆华伟, 等. 吸力面小翼对扩压叶栅旋涡结构的影响[J]. 工程热物理学报, 2014, 35(1): 46-50.
[23] 韩少冰, 钟兢军, 陆华伟. 不同宽度吸力面小翼控制压气机叶栅间隙流动的实验研究[J]. 推进技术, 2016, 37(3): 471-478. (HAN Shao-bing, ZHONG Jing-jun, LU Hua-wei. Experimental Investigation of Compressor Cascade Tip Leakage Flow Control Using Suction-Side Winglet with Different Widths[J]. Journal of Propulsion Technology, 2016, 37(3): 471-478.)
[24] 钟兢军, 韩少冰. 融合式叶尖小翼对低速压气机转子气动性能的影响[J]. 推进技术, 2014, 35(6): 749-757. (ZHONG Jing-jun, HAN Shao-bing. Effects of Blended Tip Winglet on Aerodynamic Performance of a Low Speed Compressor Rotor[J]. Journal of Propulsion Technology, 2014, 35(6): 749-757.)
[25] 韩少冰, 钟兢军, 杨凌, 等. 带压力面小翼的压气机转子叶顶间隙效应研究[J]. 工程热物理学报, 2014, 35(9): 1739-1743.
[26] 韩少冰, 钟兢军. 叶尖小翼对跨声速压气机转子变工况性能的影响[J]. 航空动力学报, 2016, 31(3).
[27] 韩少冰, 钟兢军, 孙鹏. 压力面小翼对跨声速压气机级气动性能影响的数值研究[C]. 西安:中国工程热物理学会年会热机气动热力学学术会议, 2014.
[28] 邹学奇. 轴流-离心组合压气机方案设计中应注意的问题及其对策[C]. 北京:中国航空学会21世纪航空动力发展研讨会, 2000.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2016-07-12；修订日期:2016-09-06。基金项目:国家自然科学基金面上项目(51676162)；先进航空发动机协同创新中心资助。作者简介:牛汗,男,硕士生,研究领域为叶轮机械气动热力学。E-mail: niuhanbuaa@163.com