| 涡流发生器弦向位置对翼型动态失速的影响机理 |
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| 引用本文： | 江瑞芳,赵振宙,王同光,孟令玉,陈明,冯俊鑫.涡流发生器弦向位置对翼型动态失速的影响机理[J].太阳能学报,2022,43(11):253-258. |
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| 作者姓名： | 江瑞芳 赵振宙 王同光 孟令玉 陈明 冯俊鑫 |
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| 作者单位： | 1.河海大学能源与电气学院,南京 211100; 2.南通河海大学海洋与近海工程研究院,南通 226019; 3.南京航空航天大学江苏省风力机设计高技术研究重点实验室,南京 210016 |
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| 基金项目： | 国家自然科学基金（51876054; 11502070）; 南通市民生科技重点项目（MS22019018） |
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| 摘 要： | 采用k-ω SST湍流模型,研究加三角翼涡流发生器（VGs）的DU91-W2-250翼段的动态失速过程,从升阻力系数、表面压力系数、流场、VGs脱落涡发展过程等方面,分析VGs弦向位置（x/c）对动态失速抑制作用的影响规律。结果表明x/c对翼型动态失速过程中的增升效果影响较大,VGs增大了翼型的失速攻角。升阻力及压力结果显示,x/c=0.25时增升效果最佳,翼段上表面压力系数Cp较大;x/c=0.20~0.25时尾缘附着流动较好;从涡量峰值变化看,x/c过大、过小时对分离涡的抑制作用有所减弱;从VGs脱落涡的变化看,x/c=0.20~0.25时VGs下游脱落涡强相对较大,旋涡耗散速度较慢。总而言之,VGs在x/c=0.20~0.25时对翼段气动性能提升效果最佳。
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| 关 键 词： | 流动控制 数值模拟 风力机 动态失速 涡流发生器 k-ωSST湍流模型 |
| 收稿时间： | 2021-05-07 |
INFLUENCE OF VORTEX GENERATORS CHORD POSITION ON AIRFOIL DYNAMIC STALL |
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| Jiang Ruifang,Zhao Zhenzhou,Wang Tongguang,Meng Lingyu,Chen Ming,Feng Junxin.INFLUENCE OF VORTEX GENERATORS CHORD POSITION ON AIRFOIL DYNAMIC STALL[J].Acta Energiae Solaris Sinica,2022,43(11):253-258. |
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| Authors: | Jiang Ruifang Zhao Zhenzhou Wang Tongguang Meng Lingyu Chen Ming Feng Junxin |
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| Affiliation: | 1. College of Energy and Electrical Engineering, Hohai University, Nanjing 211100, China; 2. Institute of Ocean and Offshore Engineering, Hohai University, Nantong 226019, China; 3. Jiangsu Key Laboratory of Hi-Tech Research for Wind Turbine Design, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | The dynamic stall process of DU91-W2-250 blade section with delta wing vortex generators（VGs） is studied by using the k-ω SST turbulence model. The effect and law of the chordal position of VGs（x/c） on the dynamic stall inhibition is analyzed from the aspects of the lift and drag coefficient, surface pressure coefficient, flow field and the development process of VGs shedding vortex. The results show that x/c has a great influence on the lift increase effect during the dynamic stall of airfoil, and VGs increase the stall angle of attack of airfoil. The results of lift, resistance and pressure show that when x/c=0.25, the lift increase effect is the best, and the Cp on the upper surface of the blade section is larger. When x/c=0.20-0.25, the trailing edge adhesion flow is better. From the change of vorticity peak value, when the value of x/c is too large or too small, the inhibition effect of VGs on separated vortex is weakened. According to the variation of VGs shedding vortex, when x/c=0.20-0.25, the shedding vortex intensity is relatively large downstream of VGs, and the vortex dissipation velocity is slow. In conclusion, when the VGs are installed at x/c=0.20-0.25, the aerodynamic performance of the blade section can be improved best. |
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| Keywords: | flow control numerical simulation wind turbines dynamic stall vortex generators k-ω SST turbulence model |
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