圆柱绕流涡致振动的平面湍流数值模拟

为了研究工程中存在的湍流涡致振动问题,应用平面湍流k-ε模型和重整化群k-ε模型,结合分块耦合方法及任意拉格朗日欧拉法（ALE）数值模拟了圆柱绕流涡致振动,求解基于非交错网格系统, 其中包含满足连续性方程的压力泊松方程解法.计算了湍动能、湍流耗散率、湍流黏性系数及柱面涡量的变化情况.结果表明,当雷诺数为5 000～2×105时计算所得的阻力系数与实验数据吻合良好.研究发现,在涡致振动情况下的湍流耗散率比固定圆柱涡脱落情况下小得多,湍流黏性系数与雷诺数呈对数律增长.     

低雷诺数下旋转圆柱升力系数数值计算分析

平行直线流绕圆柱有环量流动,会产生升力,其大小通常利用库塔-儒科夫斯基升力公式计算.数值计算发现,雷诺数大100时,会产生卡门涡街现象,圆柱体表面出现压力脉动;雷诺数小于1时,计算时会产生回流.文中给出了雷诺数等于10时的升力系数计算结果并与理论值进行了对比,在一定范围内与理论值有可比性.     

不同雷诺数下弹性薄板流激振动实验

为了揭示流体-薄壁结构之间相互作用的机理,在4种不同的进口流动雷诺数下,采用3D-PIV流场测试系统和DH-5935N动态信号测试分析系统同步测试,分别得到方柱绕流后弹性薄板周围流场的时空演化特性和受激振动薄板的运动规律.实验结果表明,弹性薄板振动对流动雷诺数极其敏感,当周期性扰动流场与结构形成强烈的非线性耦合作用时,近壁区流动进一步受板扰动的影响,流动的边界条件发生改变,流场结构的对称性遭到破坏,受激振动板最终表现出非周期、非对称的耦合振动行为.     

方柱绕流横向驰振及涡致振动数值模拟

对Re=250下弹性支撑方柱绕流进行数值模拟.流场计算采用基于任意拉格朗日欧拉（ALE）描述的不可压流体N S方程，对流项与扩散项分别采用三阶迎风紧致格式与四阶紧致格式进行差分离散，利用分块耦合生成正交性较好的结构化网格，模型简化为弹簧阻尼质量系统，柱体运动采用经典龙格库塔方法求解.模拟了方柱的驰振和涡致振动，捕捉到了驰振到涡致振动的转变，捕获了涡致振动的“锁定”、“拍”、“相位开关”等现象.验证了该计算方法的可行性，计算结果为工程实际提供了依据.     

流体横掠圆柱数值模拟流态转换临界雷诺数的研究

采用层流模型和RNG k-ε紊流模型,对亚临界雷诺数条件(Re=300~300 000)下,流体横掠圆柱体工况进行了数值模拟,得出了此工况下扰流流态转捩的规律。与经典试验数据进行对比验证,结果表明,阻力系数Cd和斯特劳哈数St分别可在来流雷诺数小于22 000和100 000时采用层流模型计算,误差分别小于16.4%和7.3%。     

高雷诺数下并列双圆柱绕流的大涡模拟

为澄清并列双圆柱结构发生偏向流现象的流场机理,采用大涡模拟(LES)方法,在高雷诺数下(Re=1.4×10~5)研究了并列双圆柱的气动性能及其流场特性随圆柱间距比P/D(P为圆心间距,D为圆柱直径)的变化规律,重点探讨了小间距并列双圆柱的偏向流现象及其对圆柱气动性能的作用机理.研究结果表明:大涡模拟方法得到的气动力结果与文献风洞试验值吻合良好;随着并列双圆柱间距的增大,绕流场会呈现单一钝体、偏向流和平行涡街等多种流态结构;当P/D=1.1时,绕流场会间歇性地出现单一钝体和偏向流流态,两种流态的气动性能和流场特性有很大差异,圆柱的气动力会随时间发生剧烈变化,呈现非稳态特征;当P/D=1.2～1.5时,绕流场呈现偏向流流态,两个圆柱的气动力和尾流呈现不对称现象,偏向流的偏转方向会出现间歇性地变化,尾流涡脱强度弱,气动力脉动小;当P/D=2～4时,绕流场总体呈现平行涡街流态,尾流涡脱强度强,气动力脉动大,气动干扰减弱.     

弹性圆柱杆在漩涡激励下的流-固耦合振动响应计算

在Blevins的工作基础上改进了单根圆柱杆在均匀流场中亚临界雷诺数区内涡激振动响应的半经验性计算方法,着重考虑了振动对流体力之间的耦合影响,运用此方法既可计算非锁定区的横向振动响应,当计入了锁定条件后又可计算共振区的峰值响应.     

利用高精度浸没边界-格子Boltzmann流固耦合格式模拟2维刚体自由沉降运动

自由刚体的流固耦合问题是计算流体动力学领域的热点问题,也是实际工程应用中的常见问题。为了推广最新提出的基于迭代力项的浸没边界-格子Boltzmann(immersed boundary-lattice Boltzmann, IB-LB)耦合格式使之能够计算自由刚体的流固耦合问题,首先在原控制方程中添加自由刚体的运动方程组,然后利用IB-LB耦合格式离散并数值求解该数学模型。以两小球在水箱中的自由沉降运动为例,比较了本方法与其他流固耦合算法的计算结果。最后模拟了富有挑战性的矩形平板在水箱中飘动的过程,捕捉到了与实验数据相吻合的刚体运动轨迹和流态结构,通过对比本法和现有同类算法的单步平均耗时与平板平均速度,证明了推广后算法在计算复杂流固耦合问题上有较高的计算效率和精度。     

双自由度子母管线涡激振动数值研究

为了研究双自由度子母管线周围的绕流特征,本文采用高精度浸没边界方法模拟了不同布置条件下双自由度子母管线的涡激振动特性,探讨子母管线质量比、间距比、空隙比和角度对子母管线低雷诺数振动特性及水动力的影响.结果表明:随着子母管线的质量比和间距比的增大,管线涡激振动的最大振幅逐渐减小,发生锁定的区间也变窄.不同角度对子母管线涡...     

基于低雷诺数k-ε双层模型正弦波壁流动的数值模拟

正弦波壁近区流动存在顺压和逆压梯度的交替变化,并伴有流动分离现象,难以求其精确数值解.利用TTM方法在整个计算区域生成曲线贴体坐标系,然后运用低雷诺数k-ε双层紊流模型并结合混合有限分析离散格式,对正弦波壁流动进行了成功的模拟.计算结果表明,波壁背流面存在一个椭圆形分离区,分离区长度及近壁压强分布与实验资料和前人计算结果吻合较好.     

低雷诺数中等间距串列双方柱涡激振动的数值模拟

为研究典型间距比串列双方柱的涡激振动特性及其耦合机制,对雷诺数为150、柱心间距比分别为2.0和4.0的串列双方柱涡激振动进行了数值模拟,探讨了方柱振动响应随来流折减速度的变化规律,以及周围流场的流态与其演变过程,重点分析了下游方柱的能量输入机制.两方柱在不同柱心间距比下均以横流向振动为主,柱心间距比为2.0时,均在双涡脱流态内发生“弱锁定”（即方柱在振动锁定区的振动频率锁定值远小于1.0）,其横流向最大振幅皆出现在振动锁定区内且上游方柱振幅较大;在振动锁定区内,上游方柱平均阻力系数的激增导致平均柱心间距急剧减小,扰乱了下游方柱的气动升力对振动的能量输入,导致其尾流中的旋涡极不稳定.柱心间距比为4.0时,仅下游方柱在剪切层再附流态内发生“锁定”,两方柱的横流向最大振幅均出现在振动锁定区外,但上游方柱振幅远小于下游方柱,这是由于两方柱脱落的旋涡相互融合,使得气动升力对下游方柱的能量输入增强,横流向振幅和旋涡的横流向间距随之增大,造成下游方柱的尾流模态为双涡脱流态内的平行涡街模态.此外,下游方柱的横流向振幅在剪切层再附流态内也会出现较明显的极值,其对应的尾流模态均为剪切层再附流态内的平行涡街模态.     

方柱流致横向振动的CFD数值模拟

为对弹性支撑方柱的流致横向驰振与涡激振动现象进行研究,利用Fluent软件求解Re=500下的粘性不可压流场,方柱振动模型简化为质量-弹簧-阻尼体系,将Newmark-β方法写入用户自定义函数(UDF)来求解柱体运动方程,方柱和流场之间的非线性耦合作用通过动网格实现.考虑了质量比和折合阻尼对方柱振动的影响,结果得到了低频率比下方柱的驰振现象,方柱的最大驰振位移达到2.5倍边长,观察到方柱由驰振到涡激振动的转化.详细分析不同频率比下柱体的升阻力系数、横向位移特征值和尾流涡结构,获得"拍"和"相位开关"等现象.工程中对自振频率较低的方形结构进行设计时需考虑驰振作用的影响,优先采用不易发生驰振的截面形式.     

基于RANS的圆柱风致涡激振动的CFD数值模拟

采用基于RANS方法的SST湍流模型对圆柱涡致振动进行了数值模拟.2D模型建立和网格划分通过专业前处理软件ICEM-CFD实现.保持圆柱的频率不变,通过改变风速来研究圆柱涡致振动的特性.研究结果表明,当约减风速处于4.9—5.1时可以观测到锁定现象,圆柱位移峰值出现在约减风速等于5.023.而且在非锁定区域圆柱的位移反应中可以观察到“拍”的现象.将计算与试验得到的锁定区域进行比较,得到二者结果接近;同时将计算得到的圆柱振动幅值与经验公式和实验数据进行比较,得到了比较满意的结果.     

粘性流体圆柱绕流的有限元模拟

对粘性流体圆柱绕流进行了数值模拟。根据三阶Taylor展开弱解的概念,在二阶分裂步Taylor-Galerkin有限元法基础上,采用时间推进和张量分析的方法推导了对流扩散通用微分方程的ETG有限元离散格式。对Reynolds数为32、102和250的粘性流体圆柱红流流场进行了数值仿真,数值模拟结果与实验结果吻合良好。表明隐含流线迎风耗散作用并具有三阶部分展开的Taylor-Galerkin有限元法稳定性好,精度较高,可用于计算包含对流扩散耦合传递动量的绕流问题及类似的流动问题。     

三维气固圆柱绕流颗粒扩散的直接数值模拟

为了考察颗粒在圆柱尾流中扩散的运动机理，对气固两相圆柱尾迹流动进行了高精度紧致差分方法的三维直接数值模拟.在对气相流场进行高精度模拟的基础上， 采用了Lagrangrian方法来追踪颗粒场的运动.比较了不同颗粒Stokes数为0.01、1、10和不同Reynolds数为180和200下颗粒的扩散函数，考察了三维圆柱尾迹流流场中气相场的运动对颗粒相扩散的影响.模拟结果表明：当气相流场由二维特性向三维特性转变时，由于受到气流场展向涡的影响，颗粒的展向扩散函数有相当程度的增大.颗粒在横向上扩散函数随着粒径的增大而增大，而在展向上颗粒扩散函数则随着粒径的增大而减小.     

Simulation of three-dimensional nonideal MHD flow at low magnetic Reynolds number

A numerical procedure based on a five-wave model associated with non-ideal, low magnetic Reynolds number magnetohydrodynamic (MHD) flows was developed. It is composed of an entropy conditioned scheme for solving the non-homogeneous Navier-Stokes equations, in conjunction with an SOR method for solving the elliptic equation governing the electrical potential of flow field. To validate the developed procedure, two different test cases were used which included MHD Rayleigh problem and MHD Hartmann problem. The simulations were performed under the assumption of low magnetic Reynolds number. The simulated results were found to be in good agreement with the closed form analytical solutions deduced in the present study, showing that the present algorithm could simulate engineering MHD flow at low magnetic Reynolds number effectively. In the end, a flow field between a pair of segmented electrodes in a three dimensional MHD channel was simulated using the present algorithm with and without including Hall effects. Without the introduction of Hall effects, no distortion was observed in the current and potential lines. By taking the Hall effects into account, the potential lines distorted and clustered at the upstream and downstream edges of the cathode and anode, respectively.     

内孤立波与直立圆柱体相互作用特性数值模拟

为研究直立圆柱体的内孤立波载荷特性,依据三类内孤立波理论(Kd V、e Kd V和MCC)的适用性条件,使用内孤立波诱导上下层深度平均水平速度作为入口条件,采用Navier-Stokes方程为流场控制方程,建立了两层流体中内孤立波对直立圆柱体强非线性作用的数值模拟方法。系列计算结果表明,数值模拟所得内孤立波波形及其振幅与相应理论和实验结果一致,并且直立圆柱体内孤立波水平力、垂向力及其力矩数值模拟结果与实验结果吻合。直立圆柱体内孤立波载荷由波浪压差力、粘性压差力和摩擦力构成,其中摩擦力很小,可以忽略;对水平力,其波浪压差力与粘性压差力量级相当,流体粘性的影响显著;对垂向力,粘性压差力很小,流体粘性影响可以忽略。     

Numerical simulation of gurney flaps lift-enhancement on a low reynolds number airfoil

Two-dimensional steady Reynolds-averaged Navier-Stokes(RANS) equations with transition shear stress transport(SST) model were solved to investigate the effects of Gurney flaps on the aerodynamic performance of a low Reynolds number airfoil. This airfoil was designed for flight vehicles operating at 20 km altitude with freestream velocity of 25 m/s. The chord length(C) of this airfoil is 5 m and the corresponding Reynolds number is 7.76×10~5. Gurney flaps with the heights ranging from 0.25%C to3%C were investigated. It has been shown that Gurney flaps can enhance not only the prestall lift but also lift-to-drag ratio in a certain range of angles of attack. Specially, at cruise angle of attack(3°), Gurney flap with the height of 0.5%C.can increase lift-to-drag ratio and lift coefficient by 1.6% and 12.8%, respectively. Furthermore, the mechanisms of Gurney flaps to improve the aerodynamic performance were illustrated by analyzing the surface pressure distribution, streamlines and trailing-edge flow structure for this low Reynolds number airfoil. Specially, distinguished from some other numerical researches, the flow details such as the laminar separation bubble and transition phenomena for low Reynolds number airfoil with Gurney flaps were investigated and it was found that Gurney flaps can delay the transition onset position at small angles of attack(≤2°). However, with the increase of angles of attack, Gurney flaps will promote the boundary layer transition.     

Numerical simulation of flow around square cylinder using different low-Reynolds number turbulence models

ABE-KONDOH-NAGANO, ABID, YANG-SHIH and LAUNDER-SHARMA low-Reynolds number turbulence models were applied to simulating unsteady turbulence flow around a square cylinder in different phases flow field and time-averaged unsteady flow field. Meanwhile, drag and lift coefficients of the four different low-Reynolds number turbulence models were analyzed. The simulated results of YANG-SHIH model are close to the large eddy simulation results and experimental results, and they are significantly better than those of ABE-KONDOH-NAGANO, ABID and LAUNDER-SHARMR models. The modification of the generation of turbulence kinetic energy is the key factor to a successful simulation for YANG-SHIH model, while the correction of the turbulence near the wall has minor influence on the simulation results. For ABE-KONDOH-NAGANO, ABID and LAUNDER-SHARMA models satisfactory simulation results cannot be obtained due to lack of the modification of the generation of turbulence kinetic energy. With the joint force of wall function and the turbulence models with the adoption of corrected swirl stream,flow around a square cylinder can be fully simulated with less grids by the near-wall.