An investigation of unsteady 3D effects on trailing edge flaps
An investigation of unsteady 3D effects on trailing edge flaps
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后缘襟翼不稳定 3D 效应的研究
DOI：
10.1088/1742-6596/753/2/022009
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发表时间：
2016
期刊：
影响因子：
--
通讯作者：
E. Jost
中科院分区：
文献类型：
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作者：
E. Jost
本文采用CFD方法研究了非定常和粘性三维气动效应对带后缘襟翼的风力涡轮机叶片的影响。在DTU 10 MW转子上模拟了谐波振荡，襟翼的弦长为10%，叶片半径为70%至80%。偏转频率在1p和6p之间变化。为了量化3D效应，将转子模拟与2D翼型计算进行比较。已经发现了尾涡和脱落涡结构的显著影响，它导致升力振幅的减小和升力响应中与襟翼偏转有关的滞后效应。与2D翼型模拟相比，在3D转子结果中发现了更大的振幅减小和更少的振幅。
The present study investigates the impact of unsteady and viscous three-dimensional aerodynamic effects on a wind turbine blade with trailing edge flap by means of CFD. Harmonic oscillations are simulated on the DTU 10 MW rotor with a flap of 10% chord extent ranging from 70% to 80% blade radius. The deflection frequency is varied in the range between 1p and 6p. To quantify 3D effects, rotor simulations are compared to 2D airfoil computations. A significant influence of trailing and shed vortex structures has been found which leads to a reduction of the lift amplitude and hysteresis effects in the lift response with regard to the flap deflection. In the 3D rotor results greater amplitude reductions and less hystereses have been found compared to the 2D airfoil simulations.