前缘涡振圆柱对翼型气动性能的影响  

Effect of Vortex Induced Vibrated Cylinder on the Aerodynamic Performance of Airfoil

作　　者：孙朱俊 许斌[1] 黄典贵[1] SUN Zhujun;XU Bin;HUANG Diangui(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093)

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《机械工程学报》2022年第6期242-252,共11页Journal of Mechanical Engineering

基　　金：国家自然科学基金(52036005);国家科技重大专项(HT-J2019-II-0010-0030,Y2019-Ⅰ-0002-0003)资助项目。

摘　　要：为推迟叶片表面流动分离,提升叶片气动性能,提出在叶片前缘附近设置具有涡激振动效应的钢丝。针对叶片前缘设置钢丝的问题,从二维问题开始,将弹性支承的微小圆柱安装在NACA0012翼型前缘正上方。采用ANSYS Fluent及其用户自定义函数接口对涡激振动问题进行数值模拟。侧重分析圆柱在共振状态下,不同圆柱直径和圆心到翼型前缘距离时的翼型气动性能。结果表明,在较大攻角下,合适的微小圆柱几何及位置参数可以推迟翼型的静态失速,提升翼型在一定攻角范围内的气动性能,但在来流攻角较小时,这类微小圆柱的流动控制效果是负面的。同时对比圆柱在共振与非共振状态下翼型的气动性能,发现共振圆柱可使翼型更快地脱离失速初期阶段升力系数的骤降,提升翼型的稳定性,但在其他攻角范围内,两者的升阻力系数差异不明显。相关研究成果可为翼型前缘布置微小圆柱这一流动控制方法的研究及应用提供指导。To delay the flow separation of the blade and increase the aerodynamic performance further,a passive flow control method is proposed by installing elastic steel wire near the leading edge of the blade.The 2D form of the above problem by installing an elastically mounted rigid cylinder in the vicinity of the NACA0012 leading edge is preliminarily studied.The problem of vortex induced vibration is numerically simulated by using ANSYS Fluent and its user-defined functions.With the focus on the cylinder at the resonate state,the effect of the diameter and the spacing between two components on airfoil aerodynamic performance is investigated.The results show that at high AoAs,when appropriate geometric and location parameters of cylinder are adopted,the static stall can be effectively delayed,thus improving aerodynamic performance.However,when at a small angle of attack the control effect is basically negative.Secondly the aerodynamic performance of the controlled airfoil when the cylinder in non-resonance state is also investigated and compared with the resonance one.It is found that the resonance one goes through a smaller range of AoAs that lift coefficient can suddenly drop in the initial stage of the stall,thus improving the stability of the airfoil.Among other AoAs there is no big difference in lift and drag coefficients between resonance one and non-resonance one.Related research results can hopefully provide guidance for the research and application of the flow control method of arranging tiny cylinder on the leading edge of the airfoil.

关 键 词：涡激振动 流动控制 气动性能 微小圆柱 风力机 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]