EN风力机翼型动态失速优化及气动特性分析
风力机翼型动态失速优化及气动特性分析
- 太阳能学报 2025年第10期 页码：680-688
- 作者机构：
- 作者简介：
- 基金信息：国家自然科学基金（52006148;52106262;52376204）;华能集团总部科技项目（HNKJ21-H66）
DOI：doi:10.19912/j.0254-0096.tynxb.2024-1018
中图分类号： K83-
网络出版：2025-10-31，
纸质出版：2025-10-31
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张强, 常林森, 缪维跑, 等. 风力机翼型动态失速优化及气动特性分析[J]. 太阳能学报, 2025,(10):680-688.
张强, 常林森, 缪维跑, et al. 风力机翼型动态失速优化及气动特性分析[J]. 2025, (10): 680-688.
张强, 常林森, 缪维跑, 等. 风力机翼型动态失速优化及气动特性分析[J]. 太阳能学报, 2025,(10):680-688. DOI： doi:10.19912/j.0254-0096.tynxb.2024-1018.
张强, 常林森, 缪维跑, et al. 风力机翼型动态失速优化及气动特性分析[J]. 2025, (10): 680-688. DOI： doi:10.19912/j.0254-0096.tynxb.2024-1018.
摘要
风力机叶片旋转时流动分离引发的动态失速会使得气动力急剧恶化。为提高翼型动态失速特性
建立一种基于代理模型的翼型气动优化框架。首先
对翼型进行参数化表征
通过拉丁超立方抽样方法在设计空间获得模型训练样本的输入向量
并利用CFD方法求解对应响应值。其次
通过高斯过程回归构建翼型气动外形与气动力的代理模型
并通过加点准则提高模型精度。最后
以减小气动力波动为目标
结合全局优化算法对一个俯仰周期的气动力进行优化设计。以风力机常用翼型S809为研究对象进行优化
结果表明：较之基准翼型
优化翼型气动外形的改变显著减小了阻力和力矩波动
有效抑制了翼型在下俯阶段的前缘动态失速。
Abstract
Dynamic stall induced by flow separation during the rotation of wind turbine blades can make the aerodynamic forces deteriorate drastically. In order to improve the dynamic stall characteristics of the airfoil
an aerodynamic optimization framework of the airfoil based on a surrogate model is established. The S809 airfoil is taken as the research object. First
the airfoil is parametrically characterized
and the input vectors of the model training samples are obtained by Latin hypercube sampling
and the corresponding response values are solved by CFD method. Secondly
the surrogate model of aerodynamic shape and aerodynamic force of the airfoil is constructed by Gaussian process regression
and the model accuracy is improved by the infill point criterion. Finally
with the objective of reducing the aerodynamic fluctuations
the aerodynamic forces of one pitch cycle are optimized and designed by combining the global optimization algorithm. The results show that compared with the baseline airfoil
the change of aerodynamic shape of the optimized airfoil significantly reduces the drag and moment fluctuations
and effectively suppresses the dynamic stall in the airfoil leading edge during the pitch-down phase.
关键词
Keywords
references
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