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以某1.5 MW风机叶片S818翼型为研究对象,建立了翼型流场有限元分析模型。采用基于Reynolds平均的Navier-Stokes不可压缩粘性方程作为流动控制方程,对无冰翼型、霜冰、弦长冰及角冰翼型进行数值模拟分析,得到了-2°-20°攻角下不同厚度叶片翼型的升阻比、速度矢量和表面压力分布。研究结果表明:覆冰越厚,翼型的最大升阻比降幅越大。对于弦长冰和角冰在厚度达到一定值时,使得升阻比损失产生较大的突变。在覆冰厚度都为10 mm时,角冰的最大升阻比减幅最大,达到22.04%;其次是弦长冰为11.97%,霜冰的最小为6.41%。同时结冰后的翼型会提前进入失速区,导致桨叶气动性能恶化,降低了风机的功率系数。
Taking the S818 airfoil of a 1.5 MW wind turbine blade as the research object, the finite element model of the airfoil flow field was established. Based on the Reynolds average Navier-Stokes incompressible viscous equation, the numerical simulation of ice-free airfoil, frost ice, chord ice and ice-wing airfoil is carried out. The results show that under -2 ° -20 ° attack angle Lift-drag ratio, velocity vector and surface pressure distribution of airfoil with different thickness. The results show that the thicker the icing is, the bigger the maximum lift-drag ratio of the airfoil is. For chord length ice and angle ice, when the thickness reaches a certain value, there is a big mutation in the ratio of lift to drag. When ice thickness is 10 mm, the maximum lift-drag ratio of ice is the largest, reaching 22.04%, followed by 11.97% for chord ice and 6.41% for frost ice. At the same time, the icy airfoil will enter the stall area ahead of time, resulting in deterioration of the aerodynamic performance of the blade and reducing the power factor of the fan.