射流技术提升风力机翼型气动性能研究  

Research on the improvement of vortex generator jets on the aerodynamic performance of airfoil of wind turbine

作　　者：丁文祥[1] 蔡新[1,2] 张羽[1] 高强[1] 

机构地区：[1]河海大学力学与材料学院,江苏南京210098 [2]沿海开发与保护协同创新中心,江苏南京210098

出　　处：《可再生能源》2016年第2期261-267,共7页Renewable Energy Resources

基　　金：江苏高校首批2011计划"沿海开发与保护协同创新中心"计划(苏政办发[2013]56号);南通市科技计划引导专项(2013400303)

摘　　要：以应用在水平轴风力机叶片上的层流翼型S809为研究对象,采用CFD数值模拟技术,结合ShearStress Transport(SST)湍流模型,数值计算了S809翼型的升阻力特性。在翼型设计中应用一种转捩延迟控制技术——射流技术,即在翼型上翼面添加射流口,并研究了射流口位置和射流速度对翼型S809气动特性的影响。结果表明:射流技术能够显著提高翼型升力,延缓翼型失速;在低攻角下,射流速度大于来流风速才能提升翼型升力;在失速前,翼型的升力系数和失速攻角随着射流速度的增大而增大,在原始翼型失速而带射流翼型未失速阶段,带射流翼型的阻力系数明显小于原始翼型;射流速度一定时,射流口位置适当靠前可增大翼型的失速攻角,射流口位置布置在翼型上翼面中后部能使翼型在失速前获得较大的升力系数。Taking the laminar airfoil $809 which applies at the blades of horizontal axis wind turbines as an study object, the lift and drag characteristics of airfoil S809 was calculation numerically by using CFD numerical simulation technology with Combination Shear-Stress Transport （SST）turbulence model. A kind of transition delay control technology--vortex generator jets technology was applied to the design of airfoil, which means adding the jet orifices on the upper surface of airfoil, the influence of the position of jet orifice and the velocity of jet on the aerodynamic characteristics of the airfoil $809 was researched. The results show that vortex generator jets technology can improve the lift of the airfoil significantly and delay the stall of airfoil; only the velocity of jet is greater than the wind speed can the lift of airfoil be improved at low angle of attack; the lift coefficient and the stall angle of the airfoil increase with the increases of the velocity of jet before the stall, at the stage when the original airfoil is stalled and the airfoil with jet is unstalled, the drag coefficient of the airfoil with jet is less than that of original airfoil; when the velocity of jet is constant, the stall angle can be improved when the position of jet orifice is placed at the front of the airfoil appropriately, the biggish lift coefficient can be achieved when the position of jet orifice is placed at the middle and back of the airfoil.

关 键 词：射流 S809翼型 转捩延迟 气动特性 CFD数值模拟 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]