液滴撞击超疏水壁面反弹及破碎行为研究

液滴撞击壁面时,壁面亲水性对液滴撞击壁面后的变化历程具有重要的影响。利用相界面追踪的复合Level Set-VOF方法对液滴撞击超疏水壁面的运动进行了研究。研究结果表明,撞击速度较小时,液滴撞壁后发生反弹;撞击速度较大时,液滴撞壁后会发生破碎现象;初始粒径的增大和表面张力的减小,有利于液滴撞壁后产生铺展破碎现象;撞击角度对撞壁后的液滴行为具有较大的影响。通过数值模拟,给出了一定条件下液滴垂直及倾斜撞击超疏水壁面反弹及破碎的临界条件。     

水滴撞击黄铜基超疏水表面的破碎行为研究

采用高速摄像技术,在自制的超疏水黄铜表面上开展水滴撞击后破碎行为的实验,并对水滴破碎现象力学机理、发生破碎现象的条件和破碎过程中直径铺展规律进行了分析.测试结果表明:一定速度下不同直径的水滴均会发生破碎,直径越大的水滴破碎速度越低.从能量守恒角度,对上述现象过程进行了定性的力学解释并推导出水滴在超疏水表面上发生破碎现象的临界速度的计算公式,该公式预测值与实验值的偏差小于10%.     

微纳结构超疏水表面的湍流减阻机理研究

超疏水表面的优异性质使其在现代生活和工业生产中具有十分广泛的潜在应用价值. 本文采用了碳纳米管缠绕技术和聚氟硅氧烷疏水化处理方法制备了具有二级微纳米结构的超疏水表面. 测量了由该超疏水表面构建的槽道中的流动压降,将其与普通表面构建的槽道内的流动压降进行比较,发现在层流情况下,流动阻力减小最多达到了22.8%. 在湍流的情况下,超疏水表面的减阻比例约为53.3%,减阻效果比层流更加明显.利用PIV (particle image velocimetry) 技术测量了具有超疏水表面的槽道内的速度场,通过超疏水表面速度滑移和湍动脉动场信息,分析了湍流减阻效果比层流更加明显的物理机制.     

超疏水表面滑移理论及其减阻应用研究进展

减阻技术对提高原油采收率、降低液体流动阻力具有十分重要的意义.通过论述超疏水表面结构的基本理论、超疏水表面形成的主要影响因素和近年来仿生超疏水表面的制备方法,综合分析了超疏水表面滑移理论和基于这一理论的减阻技术的研究进展,并简单介绍了其在石油储层微孔道纳米降压减阻方面的应用,展望了超疏水表面滑移理论及其减阻技术的研究重点及应用前景.      

非等温粗糙表面液滴撞击特性试验与仿真研究

非等温固体表面液滴碰撞现象广泛存在于航空航天领域机械零部件中,液滴碰撞动力学行为的研究对提升机械零部件传热换热以及润滑性能具有重要意义.为获得液滴在非等温粗糙表面的撞击特性,研究了硅油在金属表面撞击、铺展和回缩的动力学行为,并着重分析了硅油黏度、撞击速度、油滴初始直径、金属表面粗糙度及温度对硅油撞击特性的影响.结果表明,在等温表面,液滴最大铺展直径与撞击速度、基体表面温度及液滴初始直径正相关,与基体表面粗糙度、硅油黏度负相关;当表面粗糙度介于6.3～25μm时,其对液滴最大铺展直径影响较小;在非等温表面,液滴回缩过程中少量液体残留并形成尾迹,且残留尾迹随基体温度升高而愈发明显;随后数值模拟了硅油在非等温粗糙表面的碰撞过程,并揭示了基体温度和表面粗糙度的影响机制.本文中研究成果为理解非等温粗糙金属表面液滴的撞击行为提供了丰富的理论和试验依据.     

粗糙表面上微液滴的数值模拟

本文使用VOF方法将微液滴在粗糙壁面上的接触现象转化为不可压缩两相流动问题,并对其进行三维数值模拟.选择具有柱形突起和槽道两种微结构的壁面进行模拟.计算了不同粗糙系数时液滴在突起结构表面的静止形态和接触角,计算结果和实验数据吻合得较好.和理论模型进行比较,分析了经典模型的适用范围.对于微槽道结构的壁面,计算给出不同方向测量得到的液滴接触角.实现了液滴在倾斜壁面上滑落过程的模拟.液滴沿斜面下滑时,前进角和后退角的变化存在周期性,这一周期性变化和表面粗糙结构密切相关.     

基于滑移理论的超疏水表面减阻性能分析

采用滑移理论计算和数值模拟方法研究超疏水表面的减阻性能.层流流动状态的数值模拟和理论计算结果的一致性较好,并可证明滑移速度与通道内流体速度之比与无量纲压降比的数量级相当;湍流状态的数值仿真结果表明,在目前可实现的滑移速度范围内,超疏水表面对水下航行器的流体阻力影响不显著.     

超疏水沟槽表面通气减阻实验研究

减阻是解决航行体提速和增程的主要技术途径之一,对缓解日益严峻的能源危机极为重要.在重力式管道实验系统中,测试给出了湍流状态下不同通气速率时减阻率随雷诺数及沟槽无量纲间距的变化规律和气膜铺展状态,对比分析了单纯超疏水表面与超疏水沟槽表面上通气时减阻效果的差异.实验板材质为无色亚克力,沟槽结构采用机械方法加工,并在表面喷涂超疏水涂层.结果表明,持续通气能解决超疏水沟槽表面气膜层流失问题,实现气膜层长时间稳定维持;恒定雷诺数下,随通气速率增大,超疏水沟槽表面气膜铺展更趋均匀,减阻率上升;由于通气速率影响气膜横向扩展能力,致使恒定通气速率下,减阻率随雷诺数的变化呈现两种模式;在固定雷诺数及通气速率时,减阻率随沟槽尺寸的扩大先增后减, S~+≈76时减阻率最大.分析其原因在于,沟槽结构增大沾湿面积的同时,显著提升了通气状态下超疏水表面气膜层的稳定性,因而展示出与超疏水表面和沟槽表面均不相同的减阻规律,且效果更佳.     

超疏水沟槽表面通气减阻实验研究

减阻是解决航行体提速和增程的主要技术途径之一,对缓解日益严峻的能源危机极为重要.在重力式管道实验系统中,测试给出了湍流状态下不同通气速率时减阻率随雷诺数及沟槽无量纲间距的变化规律和气膜铺展状态,对比分析了单纯超疏水表面与超疏水沟槽表面上通气时减阻效果的差异.实验板材质为无色亚克力,沟槽结构采用机械方法加工,并在表面喷涂超疏水涂层.结果表明,持续通气能解决超疏水沟槽表面气膜层流失问题,实现气膜层长时间稳定维持;恒定雷诺数下,随通气速率增大,超疏水沟槽表面气膜铺展更趋均匀,减阻率上升;由于通气速率影响气膜横向扩展能力,致使恒定通气速率下,减阻率随雷诺数的变化呈现两种模式;在固定雷诺数及通气速率时,减阻率随沟槽尺寸的扩大先增后减, S⁺≈76时减阻率最大.分析其原因在于,沟槽结构增大沾湿面积的同时,显著提升了通气状态下超疏水表面气膜层的稳定性,因而展示出与超疏水表面和沟槽表面均不相同的减阻规律,且效果更佳.     

剪切变稀流体液滴撞击疏水表面回弹现象及最大铺展的研究

非牛顿流体液滴撞击固体表面的行为广泛存在于多种工农业生产中, 然而目前相关研究主要关注牛顿流体, 非牛顿流变特性对液滴撞击动力学的影响机制还有待探索. 本文研究了纯剪切变稀流体(质量分数≤ 0.03%的黄原胶水溶液)液滴撞击疏水表面后的最大铺展及回弹行为. 通过高速摄像技术捕获液滴撞击疏水表面的运动过程及形态变化, 研究了液滴的铺展回缩过程. 实验结果表明, 在相同We下, 剪切变稀特性对液滴撞击疏水表面后的铺展阶段影响很小, 但对回缩阶段影响很大. 黄原胶浓度增加使得液滴依次表现出部分回弹、完全回弹和表面沉积三种不同的回弹行为. 利用能量守恒定律推导出了液滴能在疏水表面上回弹的临界无量纲高度ξ_c理论值. 发现牛顿流体与非牛顿流体液滴最大无量纲高度ξ_max均符合标度律ξ_max ~ αWe斜率随黄原胶浓度增大而减小. 基于有效雷诺数Re_eff, 提出了一种有效黏度μ_eff表达式, 并据此建立了剪切变稀流体的最大无量纲直径β_max预测模型. 该模型在较广We区间与实验测量值取得了良好一致.      

空气炮碰撞实验台发射过程的数值模拟

利用计算流体动力学方法对单级空气炮碰撞实验台的发射过程进行了数值仿真,所得碰撞车发射速度与实验结果吻合。在此基础上,对碰撞车发射过程的流场变化、车体前后压力以及储气罐压力变化进行分析。结果表明,泄漏气体先于碰撞车充满整个发射空间,形成初始流场,使得车前压力出现正负交替现象,但其数值较小,对车体加速过程的影响可以忽略。当碰撞车进入泄压段后,受冲击射流作用,碰撞车仍处于加速状态,且速度增量约为2 m/s。

     

Numerical study on dynamic characteristics of double droplets impacting a super-hydrophobic tube with different impact velocities

ABSTRACT

The coupled level set and volume of fluid method is applied to the numerical study on the successive impact of double droplets on a super-hydrophobic tube. The impact velocity varies from 0.25 to 2?m/s. These impact processes present spread, retract, rebound, breakup and splash. The out-of-phase impact takes place with the impact velocity from 0.25 to 1.25?m/s, while the in-phase impact takes place with the impact velocity from 1.44 to 2?m/s. With the impact velocity larger than 1.25?m/s, the liquid crown presents and deforms after the trailing droplet impact, then it would gather at the film edge, rebound or break up. When impact velocities range from 1.44 to 1.5?m/s, the finger liquid film presents before the liquid crown appearing. The finger head breaks with the impact velocity of 1.5?m/s during the leading droplet spreading. The zigzag liquid film becomes more obvious for larger velocities.     

Off-centered impact of water droplets on a thin horizontal wire

The current work focuses on the initial basic stage of filtering droplets. We study the factors that have an effect upon the amount of liquid trapped on a dry smooth horizontal wire. These factors include the impact velocity, impact eccentricity, initial drop size, wire thickness, and liquid thermodynamic properties. Based on elementary analysis of some simple experiments, we propose a non-dimensional criterion for the critical eccentricity for which the maximum amount of liquid is trapped by the wire.     

铁路空调硬卧车内气流分布的数值模拟

建立了铁路空调硬卧车内CFD仿真模型,对车厢内流场、温度场和热舒适性评价指标进行了分析。采用稳态不可压缩雷诺时均N-S方程、k-ε湍流模型,应用控制容积法和交错网格进行离散。计算了空调硬卧车内三维空气流场和温度场,并与实验结果进行了对照,两者吻合较好。在此基础上分析了车厢内人体热舒适性,结果表明车厢中部和端部铺位PMV分布不同,端部人体热舒适感较好,中部较差;而且同一计算断面不同铺位的人体热舒适感差异较大:上铺有较大区域PMV<-1.0,人体感觉较凉;中铺大部分区域-0.51.0,人体感觉偏暖。     

Lattice Boltzmann simulation of multiple droplets impingement and coalescence in an inkjet-printed line patterning process

Three-dimensional computations on the basis of the index-function lattice Boltzmann method are performed to simulate the process of multiple droplets impinging and coalescing into a line pattern on a solid substrate. The employed calculation model is validated by theoretical calculated values and experimental data from the literature. The influences of the equilibrium contact angle, droplet spacing and impinging velocity on the droplets impingement and coalescence behaviours are investigated. Numerical results demonstrate the width of the formed line depends significantly on the equilibrium contact angle and droplet spacing. The droplet spacing plays a significant role in controlling the coalescence moment of multiple droplets. The resolution of the printed pattern can be slightly increased with increase in impinging velocity.     

Numerical calculations of three-dimensional turbulent vortex breakdown

Numerical solutions to the three-dimensional, unsteady, incompressible Reynolds-averaged Navier-Stokes equations have been obtained for bubble-type vortex breakdown. Two different turbulence models were employed: (1) standard K-ε and (2) an explicit, regularized algebraic Reynolds stress model. Results are computed at a Reynolds number of 10,000. The algebraic Reynolds stress model produced a breakdown bubble with a larger length-to-diameter ratio than did the K-ε model. Breakdown also occurred at lower levels of adverse pressure gradient for the algebraic stress model than for the K-ε model. In each case single-cell breakdown structures resulted. This is contrasted with numerical calculations for laminar breakdown which reveal the existence of complex multicell bubble breakdown structures.     

Multi‐resolution analysis for high accuracy and efficiency of Euler computation

A multi‐resolution analysis (MRA) is proposed for efficient flow computation with preserving the high‐order numerical accuracy of a conventional solver. In the MRA process, the smoothness of a flow pattern is assessed by the difference between original flow property values, and the values approximated by high‐order interpolating polynomial in decomposition. Insignificant data in smooth region are discarded, and flux computation is performed only where crucial features of a solution exist. The reduction of expensive flow computation improves the overall computational efficiency. In order to maintain the high‐order accuracy, modified thresholding procedure restricts the additional error introduced by the thresholding below the order of accuracy of a conventional solver. The practical applicability of the MRA method is validated in various continuous and discontinuous flow problems. The MRA stably computes the Euler equations for continuous and discontinuous flow problems and maintains the accuracy of a conventional solver. Overall, it substantially enhances the computational efficiency of the conventional third‐order accurate solver. Copyright © 2014 John Wiley & Sons, Ltd.     

过冷水滴撞击螺旋桨桨叶表面的数值模拟

本文介绍了某型螺旋桨在不同飞行状态下.求解桨叶水滴撞击特性的数值方法.该方法对桨叶运动模型进行简化,并在对绕桨叶运动的气流场计算的基础上,采用拉格朗日方法求解气流场中水滴运动方程,得到水滴运动轨迹.进而,确定了水滴对桨叶的撞击特性参数,为桨叶防冰系统设计提供条件.主要结论如下:(1)在巡航状态下,桨叶沿展向方向上总收集系数Em和局部收集系数β不断增大;(2)在爬升状态下,随着爬升高度H不断增大,飞行速度V0不断增大,水滴撞击在桨叶表面的范围有所增加,而且β随之增大;(3)随着水滴平均有效直径(MVD)的增大,水滴撞击在桨叶表面的范围明显增加同时,β在桨叶表面同一位置的值也随之增大.     

Numerical investigation of a water flow in a rib-roughened channel by using Reynolds stress model

In this paper, water flow in a rib-roughened channel is investigated numerically by using Reynolds stress turbulence models (RSM) on a three-dimensional (3-D) domain. Computational results for mean streamwise velocity component and turbulent kinetic energy show good agreements with available experimental data. Five rib pitch-to-height ratios (p/h) of 1, 5, 10, 15 and 20 are analysed for six different Reynolds numbers (Re) of 3000, 7000, 12,000, 20,000, 40,000 and 65,000. Velocity vectors, streamlines and Reynolds stresses are showed for these ratios and Re numbers. Streamlines revealed that Reynolds numbers do not affect flowfield but play an important role in the Reynolds stresses.