叶顶端翼提升主动襟翼叶型气动性能的数值研究

本文在振荡来流条件下,数值模拟叶顶端翼对加装主动Gurney襟翼的垂直轴风力机叶片非定常气动特性的影响。采用NACA0015翼型的直叶片,并在尾缘前6%弦长位置安装主动襟翼。在最大出力工况(折合频率为0.1)下,对比原型叶片,加装主动襟翼叶片的切向力系数提高了4.47%,安装有叶顶端翼的主动襟翼叶片的切向力系数提高21.18%。通过比较叶片端部涡结构分布,发现叶顶端翼不仅阻止了叶片压力面及吸力面的叶梢涡分支在尾缘处汇合,同时也隔断了主动襟翼产生的角涡与叶梢涡的融合,有效的降低了叶片端部损失,提升了风力机的整体性能。

Numerical Study of Blade Aerodynamic Performance With Active Gurney Flap and Blade-Tip Plate

Under oscillating flow condition,numerical simulation is carried out to investigate the influence of the tip plate on the unsteady aerodynamic performance of the vertical axis wind turbine blades with active Gurney flap.The straight blades of NACA0015 airfoil are employed,installed active flap at 6%C from the trailing edge.At the maximum output condition(reduced frequency=0.1),the effect of the blade-tip plate on the aerodynamic performance of the active Gurney flap airfoil was studied.The tangential force coefficient of the active Gurney flap blade is increased by 4.47%,and the tangential force coefficient of the active Gurney flap blade with the blade-tip plate is augmented by 21.18%.The vortex structures at the blade tip show that the blade-tip plate can pcevent the tip vortex branches of the pressure surface and suction surface from converging at the trailing edge and isolate the corner vortex caused by the active Gurney flap from the tip vortices.Thus,the tip plate can reduce the end-losses,and improve the overall performance.