涡发生器控制平板边界层分离的大涡模拟

胡昊; 李新凯; 戴丽萍; 王晓东; 康顺

doi:10.13224/j.cnki.jasp.2016.02.030

涡发生器控制平板边界层分离的大涡模拟

doi: 10.13224/j.cnki.jasp.2016.02.030

胡昊^1,2,
李新凯¹,
戴丽萍¹,
王晓东¹,
康顺^1,3

1. 华北电力大学能源动力与机械工程学院电站设备状态监测与控制教育部重点实验室, 北京 102206;
2. 华北水利水电大学电力学院, 郑州 450045;
3. 中国兵器工业集团公司西安现代控制技术研究所, 西安 710065

基金项目:

国家自然科学基金(51176046)

中央高校基金项目(JB2015193)

详细信息

作者简介:
胡昊(1979-),男,河南南阳人,博士生,主要从事风力机流动控制及气动噪声方面研究.

中图分类号: V232;TK83
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出版历程
- 收稿日期: 2015-02-10
- 刊出日期: 2016-02-28

Vortex generators control flat boundary layer separation of large eddy simulation

1. Key Laboratory of Condition Monitoring and Control for Power Plant Equipment of Ministry of Education, School of Energy Power and Mechanical Engineering, North China Electric Power University, Beijing 102206, China;
2. School of Electric Power, North China University of Water Resources and Electric Power, Zhengzhou 450045, China;
3. Xi'an Modern Control Technology Research Institute, China North Industries Group Corporation, Xi'an 710065, China

摘要

摘要: 为了研究涡发生器(VGs)间距λ对控制边界层分离效果的影响,选取了4种涡发生器间距,λ/H(H为涡发生器高度)分别为5,7,9,11.采用大涡模拟(LES)方法对带逆压梯度的平板边界层分离流动及VGs控制分离流动进行了数值模拟.分析了有无VGs控制时,湍流场中大尺度相干结构及其演化规律,分别从旋涡间距、边界层内流体动能、压差损失等方面考察了VGs间距对控制流动分离效果的影响.研究结果表明当λ/H为5时,VGs间距过小抑制了旋涡的展向发展,λ/H为9,11时,VGs间距过大边界层内流体动能偏低,当间距λ/H为7时流动控制效果更优,此时计算域压差损失最小,相比较无VGs控制时,压差损失降低了30.95%.
- 涡发生器 /
- 边界层分离 /
- 大涡模拟 /
- 流动控制 /
- 相干结构
Abstract: In order to study the effect of spacing λ of vortex generators(VGs) on the control boundary layer separation, 4 kinds of vortex generators spacing were selected, and λ/H(H is the height of vortex generators) respectively were 5, 7, 9, 11. The boundary layer separation flow of adverse pressure gradient and VGs control flow separation were simulated by large eddy simulation(LES) method. The evolution of the large scale coherent structure in turbulent flow field were analyzed with and without VGs control, and the influence of VGs spacing on the flow separation control effect were investigated from vortex spacing, fluid kinetic energy in the boundary layer, loss of pressure difference, etc. The research results show that when λ/H is 5, the spacing of VGs is too small, so that the spanwise development of vortex are suppressed, when λ/H are 9, 11, the spacing of VGs is too large lead to the fluid kinetic energy in the boundary layer is too low, when the spacing of VGs is λ/H is 7, the effect of flow control is better, then the pressure loss of calculation domain is minimum, compared with no VGs control, pressure loss is reduced by 30.95%.
- vortex generators /
- boundary layer separation /
- large eddy simulation(LES) /
- flow control /
- coherent structure

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参考文献(25)

[1]	范忠瑶.风力机定常与非定常气动问题的数值模拟研究[D].北京:华北电力大学,2011. FAN Zhongyao.Numerical simulations of steady and unsteady aerodynamics of wind turbines[D].Beijing:North China Electric Power University,2011.(in Chinese)
[2]	范忠瑶,康顺,王建录.风力机叶片三维数值计算方法确认研究[J].太阳能学报,2010,31(3):279-284. FAN Zhongyao,KANG Shun,WANG Jianlu.The validate and research on 3D numerical simulation of the aerodynamic perormance of wind turbine blades[J].Acta Energiae Solaris Sinica,2010,31(3):279-284.(in Chiniese)
[3]	张磊.风力机钝尾缘叶片及其气动性能改进研究.[D].北京:中科院热物理研究所,2011. ZHANG Lei.Wind turbine blade with blunt traling-edge and improvements of its aerodynamic performance[D].Beijing:Institute of Engineering Thermophysics,2011.(in Chinese)
[4]	Akshoy R P,Pritan S R,Vivek K P,et al.Comparative studies on flow control in rectangular S-duct diffuser using submerged-vortex generators[J].Aerospace Science and Technology,2013,28(1):332-343.
[5]	Shun S,Ahmed N A.Wind turbine performance improvements using active flow control[J].Procedia Engineering,2012,49:83-91.
[6]	Jasvipul S C,Shashikanth S,Bhalchandra P.Efficiency improvement study for small wind turbines through flow control[J].Sustainable Energy Technologies and Assessments,2014,7:195-208.
[7]	Leandro O S,Daniel J D,Jurandir I Y.Optimization of winglet-type vortex generator positions and angles in plate-fin compact heat exchanger:response surface methodology and direct optimization[J].International Journal of Heat and Mass Transfer,2015,82:373-387.
[8]	Ralph J V,Lennart S H.Measurements in separated and transitional boundary layers under low-pressure turbine airfoil conditions[J].Journal of Turbomachinery,2001,123(2):189-197.
[9]	Lin J C.Review of research on low-profile vortex generators to control boundary-layer separation[J].Progress in Aerospace Sciences,2002,38(4/5):389-420.
[10]	Godard G,Stanislas M.Control of a decelerating boundary layer: Part 1 optimization of passive vortex generators[J].Aerospace Science and Technology,2006,10(3):181-191.
[11]	Godard G,Foucaut J M,Stanislas M.Control of a decelerating boundary layer:Part 2 optimization of slotted jets vortex generators[J].Aerospace Science and Technology,2006,10(6):394-400.
[12]	Godard G,Stanislas M.Control of a decelerating boundary layer:Part 3 optimization of round jets vortex generators[J].Aerospace Science and Technology,2006,10(6):455-464.
[13]	Johansen J,Soerensen N N,Zahle F,et al.KNOW-BLADE task-2 report:aerodynamic accessories[R].Denmark:Risoe National Laboratory,Risoe-R-1482,2004.
[14]	Johansen J,Soerensen N N,Peck M,et al.Rotor blade computations with 3D vortex generators[R].Denmark:Risoe National Laboratory,Risoe-R-1486,2005.
[15]	刘刚,刘伟,牟斌,等.涡流发生器数值计算方法研究[J].空气动力学学报,2007,25(2):241-244. LIU Gang,LIU Wei,MOU Bing,et al.CFD numerical simulation investigation of vortex generators[J].Acta Aerodynamica Sinica,2007,25(2):241-244.(in Chinese)
[16]	张海灯,吴云,李应红,等.叶栅等离子体流动控制布局优化和影响规律[J].航空动力学报,2014,29(11):2593-2605. ZHANG Haideng,WU Yun,LI Yinghong,et al.Layout optimization and influence law of cascade plasma flow control[J].Journal of Aerospace Power,2014,29(11):2593-2605.(in Chinese)
[17]	张荻,樊涛,蓝吉兵,等.涡旋射流控制逆压梯度平板边界层分离的涡结构研究[J].西安交通大学学报,2012,46(1):1-8. ZHANG Di,FAN Tao,LAN Jibing,et al.Study on the special vortical structure development during flow separation control by VGJs in boundary layer of flat plate with adverse pressure gradient[J].Journal of Xi'an Jiaotong University,2012,46(1):1-8.(in Chinese)
[18]	Rao V N,Turcker P G,Jefferson-Loveday R J,et al.Large eddy simulations in low-pressure turbines:effect of wakes at elevated free-stream turbulence[J].International Journal of Heat and Fluid Flow,2013,43(2013):85-95.
[19]	高翔,胡骏,王志强.叶尖射流对风力机叶尖流场影响的数值研究[J].航空动力学报,2014,29(8):1863-1870. GAO Xiang,HU Jun,WANG Zhiqiang.Numerical study on effects of blade tip air jet on the flow field of wind turbine blade tip[J].Journal of Aerospace Power,2014,29(8):1863-1870.(in Chinese)
[20]	Monty J P,Harun Z,Marusic I.A parametric study of adverse pressure gradient turbulent boundary layers[J].International Journal of Heat and Fluid Flow,2011,32(3):575-585.
[21]	Marusic I,Perry A E.A wall-wake model for the turbulence structure of boundary layers:Part 2 further experimental support[J].Fluid Mechanics,1995,298:389-407.
[22]	Jones M B,Marusic I,Perry A E.Evolution and structure of sink-flow turbulent boundary layers[J].Fluid Mechanics,2001,428:1-27.
[23]	童秉纲,尹协远,朱克勤.涡运动理论[M].合肥:中国科学技术大学出版社,2009.
[24]	Hung S C,Kinney R B.Unsteady viscous flow over a grooved wall:a comparison of two numerical methods[J].International Journal for Numerical Method in Fluds,1988,8(1):1403-1437.
[25]	梁俊宇.涡轮叶片气膜冷却孔绕流的实验与数值模拟研究[D].北京:华北电力大学,2012. LIANG Junyu.Experimental and numerical investigation of flow around film cooling hole of turbine blade[D].Beijing:North China Electric Power University,2012.(in Chinese)