基于实验的圆柱体流固耦合升力谱模型研究

基于均匀流场的弹性圆柱体涡激振动实验,提出了一个考虑流固耦合的涡激升力谱模型。该升力模型采用了Webull 分布模型,以流速、约化速度、圆柱体直径和圆柱体固有频率为模型参数,通过引入圆柱体固有频率来考虑流固耦合的影响,避免了时域模型中直接计算圆柱体的顺流向振动响应问题。与实验结果比较表明,该模型可用于均匀流场的涡激振动预测。     

海洋输液立管涡激振动响应及其疲劳寿命研究

以FrancisBiolley改进的vanderPol尾流振子模型为基础,考虑管内流动流体和管外海洋环境荷载共同作用,建立了海洋立管涡激振动微分方程,用Hermit插值函数对立管微分方程进行离散,并用Miner理论对立管的疲劳寿命进行分析,通过编程和实例计算,分析了管内流速对涡激响应幅值和疲劳寿命的影响。结果表明,当管内流体流速变化使立管的固有频率接近漩涡脱落频率时,立管涡激振动响应将会增大,疲劳寿命将会显著减少。     

深海立管顺流与横流耦合涡激振动中的内流效应分析EI北大核心CSCD

深海立管因长径比大幅增加导致柔性增强、内流效应凸显,其在顺流和横流耦合涡激振动中的内流效应尚未得到很好理解。采用半经验时域涡激振动水动力模型,建立深海立管在均匀洋流下的横向和纵向耦合振动方程,并利用有限元法求解,探究不同内流速度、内流密度和洋流下立管在顺流和横流耦合涡激振动中的内流效应。研究发现,当洋流速度和内流密度一定时:①内流效应可使系统固有频率降低,因此随着内流速度增加,顺流和横流涡激主导频率可能脱离激励区,主导模态转移到高阶,同时主导频率发生阶跃增加;②立管横向位移均方根最大值是增加还是减少取决于横向涡激主导频率是接近还是远离涡脱频率;③当横流向涡激振动主导模态不变时,由于内流效应可以降低系统刚度,顺流向的静态位移随着内流速度的增加而逐步增加,当横流向主导模态转移至高阶时,顺流向的拖曳力系数会发生突然减少导致静态位移呈现阶跃性下降;④内流效应对顺流向振动有着不可忽略的影响。立管顺流向振动响应是内流效应、拖曳力(受横流向涡激响应影响)和顺流向涡激流体力联合作用的结果。     

尾流干涉及边界效应对两圆柱体涡激振动的影响

基于CFD数值模拟研究了不同排列方式的两圆柱体涡激振动问题,采用ANSYS/CFX计算了刚性圆柱体和弹性圆柱体的涡激升力和脉动拖曳力,计算了上下游圆柱体和横流向相邻圆柱体的涡激升力和脉动拖曳力。基于数值分析结果分析了流固耦合效应对圆柱体涡激振动的影响,分析了尾流干涉现象对尾流圆柱体和边界效应对横向相邻圆柱体涡激振动的影响。研究表明,尾流干涉及流固耦合作用将大大增加尾流圆柱体的涡激升力和脉动拖曳力;而边界效应和流固耦合对垂直来流的两圆柱体涡激升力和脉动拖曳力有增强的作用,并造成两圆柱体的涡激升力之间产生了相位差,最大相位差为180°。     

剪切来流下柔性圆柱体涡激振动响应试验研究

应用模型试验的方法,深入地研究了柔性圆柱体在剪切来流下的涡激振动响应。试验过程中通过旋转臂架从而形成相对剪切来流。通过测试得到的应变数据,基于模态叠加法得到圆柱体的涡激振动位移响应。研究结果表明:当折合速度较小时,响应频率会全程参加涡激振动;随着折合速度的上升,响应频率则会间歇性地参加涡激振动。涡激振动响应在横流方向仅存在一个锁定区域,而在顺流方向则存在两个锁定区域,其中第一个锁定区域与横流方向吻合。     

风电塔筒的涡振分析及防治措施

当气流流过塔筒的表面时,在流体黏性和逆压梯度的作用下,流体在塔筒的表面会产生边界层分离,使流体产生回流,进而在塔筒两侧的尾流区产生交替脱落的旋涡。当塔筒固有频率与涡脱频率相近时,就会引发诱发塔筒的共振。涡振严重时会造成倒塔事故。该文通过深入研究涡激振动的机理,提出了多种涡激振动响应的计算方法,并从塔筒结构形式、气动力干扰以及阻尼耗能的角度出发,分别给出了涡振减振思路。     

大跨度变截面连续钢箱梁桥涡激振动线性分析法

涡激力沿主梁跨向具有偏相关性,基于Scanlan涡激力经验线性模型,假定涡激振动风速下,整个梁段涡脱频率锁定,提出适用于变截面连续梁桥的三维涡激力经验线性模型,从而建立节段模型与变截面梁实桥之间涡激振动幅值之间的关系。通过变截面梁几个典型位置截面的节段模型风洞试验,获得描述整个变截面主梁三维涡激力经验线性模型等效参数,实现对整个变截面连续梁桥涡激振动响应的评估。并通过某典型的三跨变截面连续钢箱梁桥涡激振动风洞试验,验证了理论的有效性。     

考虑流固耦合的大柔性圆柱体涡激振动非线性时域模型

基于流固耦合的涡激升力模型和Morison方程,提出了一个非线性的圆柱体涡激振动时域分析模型。该模型不仅考虑了脉动拖曳力诱发的顺流向涡激振动,而且考虑了横向的流固耦合问题。该模型物理意义清楚,其非线性包括流体阻尼的非线性性质和涡激升力与圆柱体响应的相关性,这些非线性性质是该模型区别于现有涡激振动分析模型的主要特征。分析表明,该模型较好地反映了圆柱体涡激振动的本质,与现有的商业软件吻合较好。     

并列刚性双圆柱流激振动风洞试验研究EI北大核心CSCD

通过风洞试验研究了弹性支撑条件下并列刚性双圆柱的流激振动,试验雷诺数范围Re=3200~36200。圆柱间距比S/D=1.5~4.0,其中S为两圆柱圆心间距,D为圆柱直径。结果表明:随着间距的变化,并列双圆柱的振动幅值呈现涡激振动(vortex-induced vibration,VIV)和尾流耦合涡激振动(wake-coupled vortex-induced vibration,WCVIV)模式。WCVIV发生在间距比S/D≤3.0时,此时双圆柱之间相互干涉作用较强,双圆柱振动幅值响应呈现不一致性,振动位移之间表现为同相位或反相位耦合特征,圆柱尾流场对称点的涡脱频率也不相同,尾流呈现不对称性。而VIV发生在间距比S/D=3.5~4.0时,此时双圆柱相互独立,其振动幅值和涡脱频率几乎相同,尾流的不对称现象消失,振动位移之间相位差不再近似等于恒定值而是随时间周期性的“划动”。无论发生WCVIV还是VIV,振动频率的主频均锁定于1倍的固有频率。     

平台运动与管内流动联合作用下悬垂立管动力响应特性研究

悬垂立管因其经济性被广泛应用在深海油气开发中。悬垂立管在顶端平台运动和内流共同作用下,在顺流向(IL向)会产生动力响应,并与周围流体间形成相对振荡来流。这种相对振荡来流极有可能诱发悬垂立管产生横流向(CF向)的涡激振动(Vortex-induced Vibration,VIV)。为了研究悬垂立管在平台运动和内流联合作用下悬垂立管涡激振动响应特性,开展了悬垂立管模型试验。通过试验和数值模拟的方法,分析了IL向应变、流速、KC数、泻涡频率等分布规律。结果表明:大管径悬垂立管在振荡流场和内流共同作用下,可以产生涡激振动。该试验内流速度区间下,内流作用对于悬垂立管固有频率,KC数和泻涡频率幅值分布,以及涡激振动影响不大。顶部平台运动诱发的涡激振动具有不稳定性。     

Computational study of unsteady viscous flow around a transversely and longitudinally oscillating circular cylinder in a uniform flow at high reynolls numbers

A finite difference simulation method for the time dependent viscous incompressible flow around a transversely and longitudinally oscillating circular cylinder at Reynolds numbers of Re=4×10³ and 4×10⁴ is presented. The Navier-Stokes equations in finite difference form are solved on a moving grid system, based on a time dependent coordinate transformation. Solution of the vortex street development behind the cylinder is obtained when the cylinder remains stationary and also when it is oscillating. Time eholution of the flow configuration is studied by means of stream lines, pressure contours and vorticity contours. The computer results predict the lock-in phenomenon which occurs when the oscillation frequency is close to the vortex shedding frequency in the transverse mode or around double the vortex shedding frequency in the longitudinal mode. The time dependent lift and drag coefficients are obtained by the integration of the pressure and shear forces around the body. The drag, lift and the displacement relations are also discussed.     

Propulsive performance and vortex shedding of a foil in flapping flight

Summary. The propulsive performance and vortex shedding of an oscillating foil, which mimics biological locomotion, are investigated based on a computational fluid dynamics analysis. The objectives of this study are to investigate unsteady forces, in particular a thrust force, for the foil in pitching and plunging motion, and to deal with the relations of the propulsive performance with leading-edge vortex structure and vortex shedding in the near wake. The two-dimensional incompressible Navier–Stokes equations in the vorticity and stream-function formulation are solved by fourth-order essentially compact finite difference schemes for the space derivatives and a fourth-order Runge-Kutta scheme for the time advancement. To reveal the mechanism of the propulsive performance, the unsteady forces and the shedding of the leading- and trailing- edge vortices of the foil in the pitching and plunging motion are analyzed. Based on our calculated results, three types of the leading-edge vortex shedding, which have an effective influence on the vortex structures in the wake of the oscillating foil, are identified. The effects of some typical factors, such as the frequency and amplitude of the oscillation, the phase difference between the pitching and plunging motions, and the thickness ratio of the foil, on the vortex shedding and the unsteady forces are discussed.     

Numerical Study on the Suppression of the Oscillating Wake of a Square Cylinder by a Traveling Wave Wall

Traveling waves generated on the side surfaces of a square cylinder are employed to suppress the oscillating wake for improving the flow behavior around a square cylinder; this method is termed the traveling wave wall (TWW) method. This study aimed to evaluate the influence of the key parameters of TWW on the control of aerodynamic forces and the oscillating wake of the flow around a square cylinder. Unsteady numerical analyses at a low Reynolds number (Re) of 100 were performed using a two-dimensional CFD simulation. First, the grid independence and time step independence tests of the simulation were conducted to verify the rationality of the solving parameter settings, and the validation of flow around the fixed square cylinder at Re =100 was carried out. Subsequently, the lift and drag coefficients and the vortex shedding modes under different combinations of three TWW control parameters, including wave velocity, wave amplitude, and wavenumber, were analyzed in detail. The results show that TWW can remarkably reduce the mean value of drag coefficient and the RMS value of the lift coefficient by more than 12% compared to the method involving a standard square cylinder. Two peaks occur in the lift coefficient spectrum, with the low frequency corresponding to the vortex shedding frequency in the wake of the flow around the square cylinder and the high frequency corresponding to the traveling wave frequency. The vorticity contours show that the alternating vortices in the wake of the square cylinder are not completely suppressed under the selected control parameters.     

基于表面涡方法的单列圆柱流体诱导振动及流弹性不稳定研究

基于表面涡方法和流固耦合模型研究了Re=2.67×104时的单列圆柱流体诱导振动问题,计算了流体力、振动响应、涡脱落频率等,并给出了涡云图。计算模拟结果很好地重现了刚性单列圆柱在T/D=1.5(小间隙比)下以宽窄尾涡交替和多频为特征的非均匀流态,以及T/D=2.0的涡脱落现象。此外,该文还研究了单列弹性圆柱在T/D=1.5时的流体诱导振动以及流体弹性不稳定问题,计算了SG=1.29时圆柱列的无量纲临界速度。     

Temporal simulation of the wake behind a circular cylinder in the neighborhood of the critical Reynolds number

Summary The two-dimensional flow past a circular cylinder is simulated numerically using a time-dependent finite difference Galerkin method. The temporal evolution of disturbances in the wake of a circular cylinder is examined for the supercritical Reynolds numbers of 55 and 80. After the symmetry condition is relaxed, antisymmetric disturbances emerge in the wake at a pure frequency and at a well-defined exponential growth rate. The predicted critical Reynolds number of 42 is in reasonable agreement with the experimentally determined value of 46. An important aspect of this work examines the stabilizing influence a second smaller cylinder has on the formation of vortex shedding behind the main cylinder. The placement of this second cylinder is shown to completely suppress vortex shedding at a Reynolds number of 55.     

矩形柱二维尾流的稳定性研究

采用实验和数值模拟两种方法对长宽比为3∶1的矩形柱尾流进行了稳定性研究.实验发现当雷诺数接近临界值时,未加扰动的矩形柱尾流呈二维定常状态.当在柱体上游一定位置和下游靠近柱体的位置上沿垂直于来流方向施加一个宽度很小的短时脉冲射流扰动以后,扰动随时间放大,并出现旋涡脱落现象,并且这种扰动激发的旋涡脱落可以持续很长时间,不会衰减.而在下游较远处施加同样的扰动时,扰动将会衰减,不能激发出持续的旋涡脱落.数值模拟再现了上述实验结果,并且表明,当扰动强度(脉冲射流出口速度)较小时,不会出现持续的规则旋涡脱落,只有当扰动强度达到一定阈值时,旋涡脱落才能被激发.     

倒角切角对方柱气动性能影响的大涡模拟研究

倒角和切角措施对方柱的气动力及流场影响很大,常作为方柱流动控制的手段,采用大涡模拟方法,以雷诺数22000的方柱为研究对象,考虑了角部措施(角部变化率10%)的影响,对均匀流场下标准方柱、倒角和切角方柱周围流场及气动性能进行了模拟研究。通过将标准方柱大涡模拟结果与相关文献的试验和数值模拟结果对比,验证了该方法及参数取值的有效性;研究分析了倒角和切角措施对方柱风压分布和气动力的影响,并着重从时均流场和瞬态流场角度分析了角部处理措施对方柱气动性能的影响机理。结果表明,倒角和切角措施对方柱表面风压分布和气动力均有一定影响,其中对方柱表面流动分离区的风压系数影响更为显著。采用角部处理措施后,方柱前缘角区的流动分离受到影响,分离剪切层扩散角更小,侧面的分离涡更贴近壁面,从而在方柱侧面形成再附,尾流变窄,旋涡脱落频率成分更为复杂,使得方柱的平均阻力系数更小,气动力脉动强度更弱,旋涡脱落频率更高、强度更弱。     

圆柱绕流的流场特性及涡脱落规律研究

采用粒子图像测速技术对630、800及950三种雷诺数条件下的圆柱绕流场进行了实验,给出了圆柱下游沿流动方向4倍圆柱直径和垂直方向3倍圆柱直径区域内的速度场、涡量场以及涡脱落现象的时空演化规律.结果表明:圆柱尾流区域位于垂直方向约1.5~2.5倍圆柱直径范围内,随着雷诺数增大,这一范围呈现缩小趋势,而主流对涡的拉伸和输运能力有所增强;涡脱落频率随雷诺数增大而增大,小雷诺数时能够较为完整地捕捉到涡生成、脱落、发展和耗散过程,由于PIV采集频率的限制,大雷诺数条件下涡脱落整个过程不易被完整捕捉到.