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Numerical analysis of the effect of flaps on the tip vortex of a wind turbine blade

机译：襟翼对风力涡轮机叶片尖端涡流影响的数值分析

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摘要

Two oscillating flaps located close to the tip and at mid span are used to excite the unstable modes of the tip vortex system of a wind turbine blade. The two flaps are deflected in opposite directions such that the root bending moment of the wind turbine blade remains almost unchanged. To investigate the mechanism of how and to what extent the deflection of the flaps influences the tip-vortex system, Large-Eddy Simulations in the Arbitrary Lagrangian-Eulerian formulation in a rotating frame of reference are performed at an averaged chord based Reynolds number of 300,000. Periodic boundary conditions are applied in the circumferential direction such that the flow over only one of the three blades of the wind turbine needs to be computed. A subsequent simulation of the trailing tip-vortex system is performed to analyze the evolution of the disturbed tip vortex. These simulations use a far-wake model based on the parameters obtained from the wind turbine simulation as inflow condition for the wake flow field. The comparison of the flow without and with oscillating flaps shows that the tip-vortex core is displaced by approximately 5% of the rotor radius by the flap motion. The root bending moment and torque at the root of the blade with flaps vary sinusoidally. Due to the compensation by the middle span flap, the difference of the root bending moment and torque is found to be less than 5% compared to the case without moving flaps. The simulations of trailing tip vortex show considerably earlier breakdown of the excited system, which proves the concept to excite instabilities in the vortex system by oscillating flaps successful.
机译：位于顶部附近和中间跨度的两个振荡襟翼用于激发风力涡轮机叶片的顶部涡流系统的不稳定模式。这两个翼片沿相反方向偏转，以使风力涡轮机叶片的根部弯曲力矩几乎保持不变。为了研究襟翼的偏斜如何以及在多大程度上影响尖端涡旋系统的机理，在平均参考弦雷诺数为300,000的情况下，在旋转参考系中进行了任意拉格朗日-欧拉公式的大涡模拟。在周向上施加周期性边界条件，使得仅需要计算风力涡轮机的三个叶片之一上的流量。进行尾随涡旋系统的后续仿真，以分析扰动的尾旋涡的演变。这些模拟基于从风力涡轮机模拟获得的参数使用远尾流模型作为尾流流场的流入条件。对不带有和带有摆动襟翼的流动的比较表明，由于襟翼的运动，尖端涡旋芯的位移约为转子半径的5％。带襟翼的叶片根部的根部弯曲力矩和扭矩呈正弦变化。由于中间跨度襟翼的补偿，与没有活动襟翼的情况相比，发现根部弯曲力矩和扭矩之差小于5％。尾部涡流的模拟显示了受激系统的相当早的故障，这证明了通过使襟翼振荡而激发涡流系统中的不稳定性的概念。

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  • 来源
    《International Journal of Heat and Fluid Flow》 |2019年第6期|336-351|共16页
  • 作者

    Huang X.; Moghadam S. M. Alavi; Meysonnat P. S.; Meinke M.; Schroeder W.;

  • 作者单位

    Rhein Westfal TH Aachen, Inst Aerodynam, Willlnerstr 5a, D-52062 Aachen, Germany;

    Rhein Westfal TH Aachen, Inst Aerodynam, Willlnerstr 5a, D-52062 Aachen, Germany;

    Rhein Westfal TH Aachen, Inst Aerodynam, Willlnerstr 5a, D-52062 Aachen, Germany;

    Rhein Westfal TH Aachen, Inst Aerodynam, Willlnerstr 5a, D-52062 Aachen, Germany|Forschungszentrum Julich, JARA High Performance Comp, D-52425 Julich, Germany;

    Rhein Westfal TH Aachen, Inst Aerodynam, Willlnerstr 5a, D-52062 Aachen, Germany|Forschungszentrum Julich, JARA High Performance Comp, D-52425 Julich, Germany;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Large-Eddy simulation; Tip-vortex system; Wind turbine blade; Moving flaps;

    机译：大涡模拟;涡旋系统;风轮机叶片;移动风门;

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