随机湍流工况低雷诺数风力机翼型优化研究

为改善小型风力机随机湍流工况适应性,以NACA0012翼型为研究对象,采用非嵌入式概率配置点法,获得随机湍流工况下小型风力机叶片翼型运行攻角分布规律;在气动优化中耦合层流分离预测,基于Transition SST模型、拉丁超立方试验设计、Kriging模型和带精英策略非支配排序遗传算法NSGA-II进行高湍流低雷诺数风力机翼型气动优化。结果表明,优化翼型叶片平均风能捕获效率分别提高3.01%和4.76%,标准差分别降低4.76%和14.93%,优化翼型湍流适应性增强。该方法将翼型设计与湍流风况相匹配,为湍流工况低雷诺数翼型及小型风力机设计提供参考。     

A method to carry out shape optimization with a large number of design variables

A new method for shape optimization with relatively large number of design variables is proposed. It is well known that gradient‐based methods converge to a local optimum. As a result, utilization of a richer design space does not necessarily lead to a better design. This is demonstrated via the design of an airfoil for maximum lift for Re = 1000 and α = 4° flow. The airfoil is represented by fourth‐order non‐uniform rational B‐splines, and the control points are used as design variables. Starting with a NACA0012 airfoil, it is found that the optimal airfoil obtained with 13 control points has far superior aerodynamic performance than the ones obtained with 39 and 61 control points. For effective utilization of a richer design space, it is proposed that the number of design variables be increased gradually. The method is demonstrated by designing high lift airfoils for Re = 1000 and 1 × 10⁴. The objective function is the maximization of the time‐averaged lift coefficient for α = 4°. The optimization cycle with 27 control points is initiated with the optimal airfoil obtained with 13 control points. The process is continued with gradual increase in the number of design variables. Beyond a certain number of control points, the optimization leads to a spontaneous appearance of corrugations on the upper surface of the airfoil. The corrugations are responsible for the generation of small vortices that add to the suction on the upper surface of the airfoil and lead to enhanced lift. A stabilized finite element method is used to solve the unsteady flow and adjoint equations. Copyright © 2012 John Wiley & Sons, Ltd.     

A Multigrid Block LU-SGS Algorithm for Euler Equations on Unstructured Grids

We propose an efficient and robust algorithm to solve the steady Euler equa- tions on unstructured grids.The new algorithm is a Newton-iteration method in which each iteration step is a linear multigrid method using block lower-upper symmetric Gauss-Seidel(LU-SGS)iteration as its smoother To regularize the Jacobian matrix of Newton-iteration,we adopted a local residual dependent regularization as the replace- ment of the standard time-stepping relaxation technique based on the local CFL number The proposed method can be extended to high order approximations and three spatial dimensions in a nature way.The solver was tested on a sequence of benchmark prob- lems on both quasi-uniform and local adaptive meshes.The numerical results illustrated the efficiency and robustness of our algorithm.     

A new direct design method for the medium thickness wind turbine airfoil

The newly developed integral function of airfoil profiles based on Trajkovski conformal transform theory could be used to optimize the profiles for the thin thickness airfoil. However, it is hard to adjust the coefficients of the integral function for the medium thickness airfoil. B-spline curve has an advantage of local adjustment, which makes it to effectively control the airfoil profiles at the trailing edge. Therefore, a new direct design method for the medium thickness wind turbine airfoil based on airfoil integral expression and B-spline curve is presented in this paper. An optimal mathematical model of an airfoil is built. Two new airfoils with similar thickness, based on the new designed method and the original integral method, are designed. According to the comparative analysis, the CQU-A25 airfoil designed based on the new method exhibits better results than that of the CQU-I25 airfoil which is designed based on the original method. It is demonstrated that the new method is feasible to design wind turbine airfoils. Meanwhile, the comparison of the aerodynamic performance for the CQU-A25 airfoil and for the DU91-W2-250 airfoil is studied. Results show that the maximum lift coefficient and the maximum lift/drag ratio of the CQU-A25 airfoil are higher than the ones of DU91-W2-250 airfoil in the same condition. This new airfoil design method would make it possible to design other airfoils with different thicknesses.     

水平轴风力机动态来流条件下翼型气动特性的数值分析

动态来流条件下,水平轴风力机的功率输出可增加30%～50%.本文通过量纲分析,确定影响水平轴风力机翼型动态来流条件下气动特性的主要参数为特征频率fr和雷诺数Re.运用CFD方法对NREL S825翼型在不同fr数和Re数条件下,进行了气动特性的对比.结果表明在动态来流条件下,低Re数对翼型特性影响较小,而fr数是影响翼型性能的关键.     

On the Use of Embedded Meshes in the LES of External Flows

In the present study, the possibility of performing cheap and accurate LES computations using unstructured grids on complex geometries has been examined. The test case considered is a turbulent flow around a thin controlled diffusion airfoil at low speed, with angle of attack of 8° to the incoming free-stream flow. The flow velocity is set to satisfy the chord Reynolds number of 1.2 × 10⁵. Two subgrid models are tested; the classical Smagorinsky model and the WALE model. The predictions are found to be in good agreement with the experimental data both in terms of flow dynamics and pressure spectra. The results are found to be independent of the LES physical models tested herein, although this conclusion is issued with the caveat that a careful grid generation procedure using (2:3 and 3:4 type) refinements was required to reduce the jump size across the different grid resolutions.     

模型昆虫翼作非定常i运动时的气动力特性

基于Navier-Stokes方程的数值解,研究了一模型昆虫翼在小雷诺数(Re=100)下作非定常运动时的气动力特性.这些运动包括翼启动后的常速转动,快速加、减速转动,常速转动中快速上仰(模拟昆虫翼的上挥或下拍、翻转等运动).有如下结果在小雷诺数下,模型昆虫翼以大攻角(α=35°)作常速转动运动时,由于失速涡不脱落,可产生较大的升力系数.其机理是翼转动时,翼尖附近(该处线速度大)上翼面压强比翼根附近(该处线速度小)的小得多,因而存在展向压强梯度,同时存在着沿展向的离心力,此展向压强梯度和离心力导致的展向流动在失速涡的轴向方向,其可避免失速涡脱落.模型昆虫翼在快速加、减速转动和快速上仰运动中,虽然雷诺数小,但由于在短时间内产生了大涡量,也可产生十分大的气动力,例如在快速上仰运动中,升力系数可大于10.     

多缝道复杂外形粘性绕流计算

使用雷诺平均NS方程、采用Johnson-King紊流模型、嵌套网格和有限体积法研究大迎角下的多缝道的多段翼型绕流。利用嵌合体技术对组合每一部分生成高质量并适于高效求解的贴体网格;将J－K模型发展应用于计算缝道流动以及具有边界层、尾迹流交汇的复杂流动。以具有17％相对厚度的GAW－1翼型带30％襟翼翼型及一个三段翼型为例进行了计算,计算结果与实验结果吻合很好,证实该方法可以较好地预示多段翼型上的粘性绕流、多缝道流动与最大升力。     

多块网格技术及其在操纵面绕流计算中的应用

采用中心有限体积法求解Navier Stokes方程组,利用点对点搭接及面搭接多块网格技术成功地进行了多段翼型和存在外形间断(剪刀差)的带操纵面三维机翼的网格生成及粘性绕流流场数值计算,使用重叠面积加权插值及Ramshaw算法实现了面搭接的多块网格之间的信息传递并保证了通量守恒,并将流场计算结果与实验数据进行了对比.     

多段翼型粘性绕流多块网格数值模拟

采用多块结构网格和分区求解技术对多段翼型绕流进行雷诺平均NS方程数值模拟,并将计算的压力分布与实验进行了比较.