翼型尾流干涉下的柱体结构涡振特性研究

Simulation of vortex induced vibration of cylinder structure under airfoil interference

翼型尾流干涉下柱体结构涡激振动(vortex induced vibration,VIV)特性的准确预测是翼型-柱体耦合结构振动控制研究的关键。为了研究翼型位置参数对柱体结构涡激振动特性的影响,基于计算流体力学(computational fluid dynamics,CFD)、结构动力学以及嵌套网格技术建立翼型-双自由度柱体耦合结构的流固耦合动力学仿真模型。通过与国外文献试验数据对比,验证了该研究建立的数值模型的准确性。计算结果表明,在较小的约化速度下翼型尾流干涉的柱体横向振幅和频率比微小于单柱体,约化速度较大时会大于单柱体。不同的翼型与柱体之间的距离会使柱体横向振幅和频率比发生变化,在距离为3D时取得最大横向振幅。不同攻角的翼型也对柱体的影响不同,柱体的横向振幅和频率比在攻角为100°时取得最小值。

The accurate prediction of vortex induced vibration(VIV) characteristics of cylindrical structures under airfoil wake interference is the key to the vibration control of airfoil cylinder coupled structures.In order to study the influence of airfoil position parameters on the vortex induced vibration characteristics of cylinder structure,the fluid structure coupling dynamics simulation model of airfoil two degree of freedom cylinder coupling structure was established based on computational fluid dynamics(CFD),structural dynamics and nested grid technology.The accuracy of the numerical model established in this paper was verified by comparing with the experimental data in literature.The calculation results show that the transverse amplitude and frequency ratio of airfoil wake interference is slightly smaller than that of single cylinder at small reduced velocity,and larger than that of single cylinder at large reduced velocity.The distance between different airfoils and the cylinder changes the transverse amplitude and frequency ratio of the cylinder,and the maximum transverse amplitude is obtained when the distance is 3D.Airfoils with different angles of attack also have different effects on the cylinder.The transverse amplitude and frequency ratio of the cylinder reach the minimum when the angle of attack is 100 °.