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为准确模拟风力机高风速偏航工况下的气动特性,以NREL Phase VI实验叶片为算例,考虑叶片旋转导致的失速延迟现象,通过Kirchhoff-Helmholz尾缘分离预估模型与Du-Selig失速延迟模型建立三维尾缘分离预估模型,并与升力面自由涡尾迹法耦合。以更精确预测分离点位置和附着涡诱导速度,讨论叶片弦向布置的涡格数量对计算准确性的影响。对比改进前后的升力面模型模拟叶片在高风速下不同偏航角工况的气动性能,结果表明:改进后升力面模型可大幅提高高风速气动性能预测的准确度,两涡格三维尾缘分离预估模型对法向力系数和弦向力系数的模拟最为精确。
In order to accurately simulate the aerodynamic characteristics of wind turbine under high wind speed and yawing conditions, taking the NREL Phase VI experimental blade as an example, the stall delay caused by the blade rotation was considered. By Kirchhoff-Helmholz trailing edge separation model and Du-Selig stall Delay model to establish a three-dimensional trailing edge separation prediction model, coupled with the free surface vortex wake trace method. In order to predict the location of the separation point and the induced vortices more accurately, the influence of the number of vortex grids on the chordwise direction of the blade on the accuracy of the calculation is discussed. The results show that the improved lift surface model can greatly improve the prediction accuracy of the aerodynamic performance of high wind speed. The three-dimensional three-dimensional trailing edge separation The prediction model is most accurate for the simulation of normal force coefficient and chord force coefficient.