风力机翼型动态失速过程边界层分离规律研究  

Study on Boundary Layer Separation of Wind Turbine Airfoil During Dynamic Stall

作　　者：李爽 张磊[1,2,3,4] 宋娟娟 杨科[1,2,3,4] LI Shuang;ZHANG Lei;SONG Juan-Juan;YANG Ke(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190 China;Wind Energy Utilization Laboratory of Chinese Academy of Sciences,Beijing 100190,China;National Research and Development Center of Wind Turbine Blade,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院风能利用重点实验室,北京100190 [3]国家能源风电叶片研发(实验)中心,北京100190 [4]中国科学院大学,北京100049

出　　处：《工程热物理学报》2019年第9期2043-2050,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金项目(No.51476171)

摘　　要：风力机叶片的运行工况决定了翼型实际处于俯仰振荡运动状态,伴随动态失速现象。本文选取DU91W2250翼型为研究对象,在雷诺数为3×10^6条件下,借助二维动网格对翼型在不同振荡运动状态下的动态失速特性进行数值仿真,研究了翼型动态失速过程中气动特性及二维边界层的分离及演化规律,发现了动态失速过程中折合频率、振幅、来流湍流度等因素对气动参数、分离点变化、脱落涡状态的影响规律,为后续三维翼型的动态失速模拟提供了理论基础。Airfoils are in pitching motions because of the actual operation condition of wind turbine blades,which causes dynamic stall phenomenon.Airfoil DU91W2250 is selected in this paper to operate in pitching motions under Reynolds number 3×10^6.The dynamic stall characteristics of airfoil during different pitching motions are simulated using dynamic mesh,and the aerodynamic characteristics and evolution of two-dimensional boundary layer are studied.The effects of several parameters on aerodynamic coefficients,separation point and shedding vortex are investigated,such as the reduced frequency,amplitude of angle of attack and turbulence intensity.It provides a theoretical basis for the subsequent three-dimensional airfoil dynamic stall simulation.

关 键 词：风力机 二维翼型 动态失速 边界层分离 气动特性 

分 类 号：TK89[动力工程及工程热物理—流体机械及工程]