尾缘改型对风力机翼型性能的影响研究  

Research on the effect of trail-edge improvement on airfoils performance for wind turbine

作　　者：李仁年[1] 袁尚科[1,2] 赵子琴[2] 

机构地区：[1]兰州理工大学能源与动力工程学院,甘肃兰州730050 [2]兰州工业学院建筑工程系,甘肃兰州730050

出　　处：《空气动力学学报》2012年第5期646-652,共7页Acta Aerodynamica Sinica

基　　金：国家重点基础研究发展计划资助项目(2007CB714602)

摘　　要：针对风力机工程常用翼型,采用有限元法的SIMPLE算法,对NACA4412翼型、加装2%弦长Gurney襟翼的NACA4412翼型及对应尾缘厚度为2%弦长的钝尾缘翼型进行了以来流风速为9.5m/s、攻角为0°～25°的气动性能数值计算。结果表明,改型后的钝尾缘翼型在流场中产生了强烈的下洗作用,明显改变了翼型表面的压力分布,使其升力系数、升阻比等较原型有显著改善,同时大大推迟了翼型的失速现象。通过翼型噪声机理的研究,对上述三种翼型分别采用在时间域上积分的方式进行了频谱特性的分析,气动声学研究表明,翼型噪声具有很强的指向性,改型后的翼型声级有明显降低,为低噪声风力机的优化设计和噪声预测提供了可靠的理论依据。A numerical simulation was used for researching the aerodynamic characteristics of wind tur- bine including NACA4412 airfoil, a modified NACA 4412 airfoil with a Gurney flap of 2% chord height and another modified NACA 4412 airfoil with a blunt of 2% chord thickness. It used the SIMPLE algorithm of fi- nite element method to compute and analysis with coming wind speed was 9.5m/s and the attack angle from 0 to 25 degrees. Aerodynamic characteristic computational results showed that a strong downwash effect was produced by the modified airfoil with the blunt trailing edge, which changed the pressure distribution on the pressure and suction surface significantly. Therefore compared with the original NACA 4412 aerofoil, the lift and lift-drag ratio of the modified NACA 4412 airfoil was enhanced remarkably and the stall attack angle was increased. It had a spectrum analysis by noise mechanism of airfoils and the frequency spectrum of the noise signal, and the aerodynamic noise calculate results indicated that there existed highly directional radiation of the airfoils and the modified airfoils were reduced remarkably. It provided a reliable theory for low noise opti- mal design and noise prediction of wind turbine.

关 键 词：翼型 GURNEY襟翼 数值计算 气动性能 气动噪声 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]