颗粒直径对风力机翼型动态失速特性的影响研究  

INFLUENCE OF PARTICLE DIAMETER ON DYNAMIC STALL CHARACTERISTICS OF WIND TURBINE AIRFOIL

作　　者：李德顺[1,2] 何婷 王清 Li Deshun;He Ting;Wang Qing(School of Energy and Power Engineering,Lanzhou University of Technology,Lanzhou 730050,China;Gansu Provincial Technology Centre for Wind Turbines,Lanzhou 730050,China)

机构地区：[1]兰州理工大学能源与动力工程学院,兰州730050 [2]甘肃省风力机工程技术研究中心,兰州730050

出　　处：《太阳能学报》2023年第12期207-213,共7页Acta Energiae Solaris Sinica

基　　金：国家自然科学基金(52166014;51766009);甘肃省基础研究创新群体项目(21JR7RA277);直升机旋翼动力学重点实验室开放基金(JZX7Y201911SY004001);兰州理工大学红柳优秀青年人才资助计划(2022)。

摘　　要：采用CFD方法对风力机翼型在不同直径颗粒下的动态失速特性进行建模与数值模拟。首先,针对二维NACA 0012翼型,采用SST k-ω湍流模型对连续相与离散相耦合进行建模数值;其次,验证SST k-ω湍流模型的准确性,并对离散相模型进行可行性分析;最后,分析颗粒直径对翼型动态失速气动性能和翼型周围流场的影响,同时给出不同直径颗粒的质量浓度分布规律。研究表明:当颗粒直径小于50μm时,颗粒直径越大,升力系数变化越大,翼型前缘附近的涡量也越大,大量颗粒聚集在翼型的吸力面;当颗粒直径为50μm时,翼型运动到振荡周期的任何攻角下,升力系数都在减小,翼型前缘处的流场发生改变,涡量减小,涡强减小,大量颗粒聚集在翼型压力面,分离点后移;当颗粒直径大于50μm时,在大攻角下影响较大,小攻角下影响较小,且升力系数都在减小,翼型前缘附近的涡量随颗粒直径的增加而减小,大量颗粒聚集在翼型整个压力面上。The dynamic stall characteristics of wind turbine airfoil under different diameter particles are modeled and simulated by CFD method.First of all,the continuous-phase and discrete-phase coupling is stimulated by the SST k-ωturbulence model for 2D NACA 0012 airfoil.After that,the accuracy of the SST k-ωturbulence model is verified,and the probability of the discrete-phase model is analyzed.The final step is to analyze the influences of particle diameter on the dynamic stall aerodynamic performance,and to obtain the distribution of concentration for the mass of particles with different diameters.The study presents that increasing the diameter of particles leads to larger lift coefficient when diameter of particles is less than 50μm,resulting in more vortex volume near the leading edge of the airfoil,and plenty of particles gathering in the suction surface of the airfoil.As for the diameters equaling to 50μm,the lift coefficient will decrease for any angle of attack of the airfoil movement to the oscillation cycle.The vortex volume and vortex intensity reduce because of the change of flow field at the leading edge of the airfoil.Consequently,a massive amount of particles accumulate at the pressure surface of the airfoil and the separation point shifts back.When it comes to the diameters larger than 50μm,the larger attack angle has larger effect and vice versa,while lift coefficient decreases under both larger and small attack angles.The vortex volume near the leading edge of the airfoil decreases with the increasing of particle diameter,and a large number of particles are gathered on the whole pressure surface of the airfoil.

关 键 词：风力机 翼型 动态失速 颗粒直径 气动性能 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]