高雷诺数下多柱绕流特性研究

采用改进的延迟分离涡方法数值模拟了高雷诺数下的柱体绕流,包括单圆柱绕流、单方柱绕流、串列双圆柱绕流和串列双方柱绕流,研究了不同雷诺数下圆柱绕流与方柱绕流的水动力特性.计算结果与实验数据及其他文献的数值计算结果吻合良好,研究表明,单方柱绕流在2.0×10~3Re1.0×10~7范围内未出现类似于单圆柱绕流的阻力危机现象,其平均阻力系数C_d、升力系数均方根C'_1及斯特劳哈尔数S t维持在一定范围内波动.串列双圆柱绕流与串列双方柱绕流中,均选取L/D=2.0,2.5,3.0,3.5和4.0这五中间距比进行计算.串列双圆柱绕流中,当Re=2.2×10~4时,在3.0L/D3.5内存在一临界间距比(L_c/D)使得L_c/D前后上下游圆柱的升阻力系数发生跳跃性变化,且当L/DL_c/D时,下游圆柱的阻力系数为负数.而当Re=3.0×10~6时,则不存在临界间距比,且下游圆柱的阻力系数始终为正数.串列双方柱绕流在Re=1.6×10~4和Re=1.0×10~6两种工况下的临界间距比分别处于3.0L/D3.5和3.5L/D4.0区间内,且当L/DL_c/D时,两个雷诺数下的下游方柱阻力系数均为负数.     

构造活动地区工程构造稳定性研究

在０．６１×１０￣５Ｒｅ６．０１×１０￣５，０．９３Ｈ／Ｄ２．５０（Ｈ为波高，Ｄ为圆柱直径）的范围内实验研究了弹性圆柱在浪流联合作用下的流体载荷。通过测量柱表面压力，得到了脉动升力和阻力系数，并给出了Ｍｏｒｉｓｏｎ公式中的Ｃ＿Ｄ，Ｃ＿Ｍ值随Ｋｃ数的变化关系，实验结果表明：在浪流联合作用下的圆柱体，其流体载荷与雷诺数的变化密切相关，并且圆柱的振动对流体载荷也有影响。     

分块法研究圆柱绕流升阻力

使用新的分块耦合方法，分别对单圆柱和串列双圆柱绕流进行了数值模拟．对于单圆柱绕流，低Re下计算所得到的定常涡尺寸与实验非常接近．对于串列双圆柱绕流，研究分析了改变双圆柱中心间距对上下游圆柱的升阻力系数和脉动频率所产生的影响，计算结果与实验非常吻合，为进一步研究涡致振动提供了依据．     

规则波作用下垂直圆柱局部波浪力

在ＫＣ为４０～３５，雷诺数Ｒｅ为６×１０３～２×１０４参数范围内就规则波作用下垂直圆柱局部波浪力进行了实验研究．给出横向力随ＫＣ数类型变化的划分．基于Ｓｔｏｋｅｓ二阶波理论和Ｍｏｒｉｓｏｎ公式得到圆柱阻力系数ＣＤ，惯性力系数ＣＭ和最大升力系数ＣＬｍａｘ沿桩柱的分布及其随ＫＣ数的变化规律．结果表明，在波表面间歇区的桩柱的局部水动力系数变化显著，越向波峰位水动力系数ＣＤ和ＣＬｍａｘ越减小，而ＣＭ值却越增高．     

相同雷诺数下串列双圆柱绕流的仿真分析

为研究均匀水流场中串列排布的柱群之间的干涉影响,本文以三维串列双圆柱为例,通过计算流体力学(CFD)软件FLUENT15.0中双方程k-ε模型,分析模拟了双圆柱所受平均阻力、平均升力、后柱周向压力、斯特劳哈尔数等水动力特性。结果表明:在雷诺数为Re=2×10~4的串列双圆柱绕流中,两圆柱中心间距L与圆柱直径D的比值为L/D=4时,后柱受前柱绕流尾流影响大,明显高于单圆柱绕流的平均阻力系数,后柱的周向压力值也随前柱尾流的摆动呈现显著的不对称性;当L/D=8时,前柱绕流尾流对后柱影响逐渐减弱;当L/D=12时,两圆柱之间的相互干扰几乎可以忽略,可以看作是相互独立的单圆柱绕流。最后,计算的斯特劳哈尔数与单圆柱绕流对应的斯特劳哈尔数相近且仿真数值在计算数值范围之内,验证了整个仿真分析的准确性,也进一步说明了双圆柱绕流的柱群的干涉影响。双圆柱间距越大,前、后柱之间的干涉影响越弱。     

分块法研究圆柱绕流升阻力

 使用新的分块耦合方法，分别对单圆柱和串列双圆柱绕流进行了数值 模拟. 对于单圆柱绕流，低$Re$下计算所得到的定常涡尺寸与实验非常接近. 对于 串列双圆柱绕流，研究分析了改变双圆柱中心间距对上下游圆柱的升阻力系数和脉动频率所 产生的影响，计算结果与实验非常吻合，为进一步研究涡致振动提供了依据.     

串列双圆柱绕流问题的数值模拟

本文运用有限体积方法,对绕串列放置的双圆柱的二维不可压缩流动进行了数值计算。为研究两圆柱不同间距对圆柱相互作用和尾流特征的影响,选取间距比Ｌ／Ｄ（Ｌ为两圆柱中心间的距离,Ｄ为圆柱直径）在１．５～５．０之间每隔０．５共八个有代表性的间距进行了计算模拟。计算均在Ｒｅ＝２００条件下进行。计算结果表明：对该绕流问题,流动特征在很大程度上取决于间距的大小。且间距存在一临界值,间距比从小于临界值变化到大于临界     

圆柱绕流三维不稳定性的低维Galerkin法分析

利用低维Ｇａｌｅｒｋｉｎ方法及Ｆｌｏｑｕｅｔ稳定性分析理论,计算分析了圆柱绕流的三维线性不稳定性．分析中构造了能较好描述尾迹区流动的周向基函数,建立了完备的合理的基函数组,改进了计算机算法．结果证实圆柱二维周期流对展向小扰动为不稳定的,正确地预计了出现三维长波不稳定性的临界雷诺数Ｒｅｃ＝１９０;扰动展向波长为λｃ一３．６ｄ．对雷诺数Ｒｅ为１８０,１９０两种工况下的圆柱三维绕流流场的计算进一步证实了这种流动的整体不稳定性．本文所预计的临界值比Ｎｏａｃｋ等人的结果更为精确,与Ｂａｒｋｌｅｙ等人的ＤＮＳ解一致,与Ｗｉｌｌｉａｍｓｏｎ的实验相符．     

侧柱与串列双柱绕流之间的干优

本文给出了关于串列双柱与侧柱间流动干扰的实验研究结果。当三个圆柱排成等边三角形关靠得很近时，由于三圆柱间强烈的缝隙流动，大大地改变了绕流其中的串列双圆柱的流态，特别，当三圆柱中心距等于二倍圆柱直径时，在串列双柱的前，后柱之间形成了强烈的偏斜的缝隙流，出现了独特的压力分布以及要比单柱高出三倍以上的旋涡脱落频率。     

侧柱与串列双柱绕流之间的干扰

本文给出了关于串列双柱与创柱间流动干扰的实验研究结果。当三个圆柱排成等边三角形并靠得很近时，由于三圆柱间强烈的缝隙流动，大大地改变了绕流其中的串列双圆柱的流态。特别，当三圆柱中心距等于二倍圆柱直径时，在串列双柱的前、后柱之间形成了强烈的偏斜的缝隙流，出现了独特的压力分布以及要比单柱高出三倍以上的旋涡脱落频率。     

Passage of a supersonic flow over intersecting surfaces

Using the linear formulation, the problem of passage of a supersonic flow over slightly curved intersecting surfaces whose tangent planes form small dihedral angles with the incident flow velocity at every point is considered. Conditions on the surfaces are referred to planes parallel to the incident flow forming angles 0≤γ≤2π at their intersection [1]. The problem reduces to finding the solution of the wave equation for the velocity potential with boundary conditions set on the surfaces flowed over and the leading characteristic surface. The Volterra method is used to find the solution [2]. This method has been applied to the problem of flow over a nonplanar wing [3] and flow around intersecting nonplanar wings forming an angle γ=π/n (n=1, 2, 3, ...) with consideration of the end effect on the wings forming the angle [4]. In [5] the end effect was considered for nonplanar wings with dihedral angle γ=m/nπ. In the general case of an arbitrary angle 0≤γ≤2π the problem of finding the velocity potential reduces to solution of Volterra type integrodifferential equations whose integrands contain singularities [1]. It was shown in [6] that the integrodifferential equations may be solved by the method of successive approximation, and approximate solutions were found differing slightly from the exact solution over the entire range of interaction with the surface and coinciding with the exact solution on the characteristic lines (the boundary of the interaction region, the edge of the dihedral angle). The solution of the problem of flow over intersecting plane wings (the conic case) for an arbitrary angle γ was obtained in terms of elementary functions in [7], which also considered the effect of boundary conditions set on a portion of the leading wave diffraction. In [8, 9] the nonstationary problem of wave diffraction at a plane angle π≤γ≤2π was considered. On the basis of the wave equation solution found in [8], this present study will derive a solution which permits solving the problem of supersonic flow over nonplanar wings forming an arbitrary angle π≤γ≤2π in quadratures. The solutions for flow over nonplanar intersecting surfaces for the cases 0≤γ≤π [6] and π≤γ≤2π, found in the present study, permit calculation of gasdynamic parameters near a wing with a prismatic appendage (fuselage or air intake). The study presents a method for construction of solutions in various zones of wing-air intake interaction.     

小Kc数振荡流中圆柱绕流流场结构的数值分析

本文综合Chorin的涡方法、网格涡方法和泊松方程快速解法的优点,采用固定离散涡的数目和位置,随时间变化调整离散涡强度的计算方法,对Kc数在1到5之间,β数在10到1665之间圆柱在振荡流动中的流场结构进行了数值模拟。并与U型振荡水槽中的流场涡结构显示照片比较,计算结果表明,数值解在稳定性和收敛性方面都是比较好的。与显示照片相比,其符合程度也是令人满意的。     

基于波传播系数构建填实爆炸下花岗岩中运动及变形场

为利用球面波实验测得的有限个粒子速度信息来分析地下爆炸下介质的运动及变形特性，基于黏弹性球面波理论和局部黏弹性等效假设，提出了一种构建地下爆炸运动及变形场的新方法。首先，利用0.125 g TNT填实爆炸下花岗岩中相邻测点的粒子速度频谱给出相应的频谱比；其次，结合黏弹性球面波理论给出的理论频谱比求解出相邻测点之间区域内等效的球面波传播系数；再次，利用局部黏弹性等效假设给出相邻测点之间任意一点的粒子速度频谱，再通过傅里叶逆变换给出粒子速度的时域波形；最后，利用运动场和变形场的物理关系，完成整个分析区域内运动场和变形场的构建。结果表明:由相邻测点反演得到的波传播系数，可高精度地构建相应测点之间区域内介质的运动及变形场；在半径15～50 mm区域内，径向压缩应变峰值约从1.7×10?2降为2.1×10?3，切向拉伸应变峰值约从4.7×10?3降为0.4×10?3，径向压缩应变率峰值约从5.1×104 s?1降为2.5×103 s?1，切向拉伸应变率峰值约从5.0×103 s?1降为1.4×102 s?1，涵盖了高应变（率）到中低应变（率）加、卸载的全过程。     

Ti6Al4V合金激光熔覆Ti3SiC2增强Ni60复合涂层组织与摩擦学性能

为了提高Ti6Al4V合金的耐磨减摩性能,在其表面利用激光熔覆技术制备出两种不同配比的Ti₃SiC₂/Ni60复合涂层,分别是5%Ti₃SiC₂+Ni60(N1)和10%Ti₃SiC₂+Ni60(N2)(均为质量分数),研究了这两种涂层在室温、300和600 ℃下的微观组织、显微硬度、摩擦学性能表现及相关磨损机理. 结果表明:涂层主要由硬质相TiC/TiB/Ti_xNi_y,γ-Ni固溶体连续相和润滑相Ti₃SiC₂组成. N1、N2涂层的显微硬度均为基体(350HV_0.5)的3倍左右,分别为1 101.90HV_0.5 和1 037.23HV_0.5 ,在室温、300和600 ℃下的摩擦系数分别为0.39、0.35、0.30和0.41、0.45、0.44,均小于基体的摩擦系数(0.51、0.49、0.47). N1、N2涂层在室温、300和600 ℃下的磨损率分别为3.07×10?5、1.47×10?5、0.77×10?5 mm3/(N·m)和1.45×10?5、0.96×10?5、0.62×10?5 mm3/(N·m),均远小于基体[35.96×10?5、25.99×10?5、15.18×10?5mm3/(N·m)]. 在本文中Ti₃SiC₂提高了Ti6Al4V合金的耐磨减摩性能,使得N1涂层表现出更好的减摩性能,N2涂层表现出更好的耐磨性能. 室温下,磨粒磨损、塑性变形以及轻微的黏着磨损为两种涂层的主要磨损机理;300 ℃时,塑性变形、氧化磨损和黏着磨损是N1涂层的对应机理,600 ℃时出现了三体磨粒磨损;在300和600 ℃时,黏着磨损、氧化磨损及磨粒磨损为N2涂层的主要磨损机理.      

Shock and wave dynamics in cavitating compressible liquid flows in injection nozzles

Due to the exceptional high inlet pressures up to 2,000 bar flow dynamics and efficiency of modern injection systems are controlled by high frequency wave dynamics of the compressible liquid flow. Corresponding to alternating shock and expansion waves the liquid fluid evaporates and recondenses instantaneously. Here we present CFD simulations of the time accurate evolution of cavitating flows in 2-D plane and in six-hole injection nozzles with focus on the wave dynamics just after initialisation of the flow and within the time scale Δt ≤ 10^?4 s of pilot and multi-point injection. Due to shock reflections at the bottom of the sack hole the instantaneous maximum pressure increases more than three times higher as compared with the prescribed pressure at the nozzle inlet. For instance, in case of an inlet pressure of 600 bar the maximum pressure in the sack and therefore ahead of the nozzle bore holes reaches about 2,100 bar. It is quite reasonable that this amplification of the pressure affects the evolution of the convective flow and therefore the mass flow through the nozzle bore holes.     

Measurements of gravity and gravity-capillary waves in horizontal gas-liquid pipe flow using PIV in both phases

An experimental study was performed in stratified wavy flow of air and water through a horizontal pipe. The velocity fields in both phases were measured simultaneously using PIV and the interfacial shape was resolved using a profile capturing technique. The objective of the study was to investigate the interfacial characteristics and the velocities of the liquid and gas phases in two wave patterns: ‘3D small amplitude’ and ‘2D large amplitude’ waves. The wave patterns were shown to consist of gravity and gravity-capillary waves, respectively, with substantial differences in the wave characteristics and liquid velocities. Contrary to this, the effect of the waves on the gas velocities was rather similar in both wave regimes, with both wave regimes causing an increase in the velocity fluctuations close to the interface. The current measurements also produced a valuable dataset that can be used to further improve the numerical modeling of the stratified flow pattern.     

Interaction of a point sink with a transmitted shock wave in water

The structure of a wave of rarefaction (relief wave) created by the interaction of a shock wave with a point sink is considered. A singular region occurs in the relief wave in the angular range π/2≤θ≤3/2π; in this region the pressure exceeds that in the transmitted wave. Qualitative comparison is made with experimental results.     

Wave influence on turbulence length scales in free surface channel flows

In order to predict sediment movements in coastal environments, the interaction between these particles and turbulence should be better understood. Although previous studies have particularly shown the importance of the turbulence length scales on sediment transport for current flows, few measurements have been made on wave/current flows. The purpose of our experiments is to get a better knowledge on wave action on these characteristic length scales. For this study, in the context of a grid-generated turbulence, we aimed to describe evolution of turbulence macro and micro scales in two kinds of free surface flow. Indeed, current and wave/current flows are studied. Two data analysis techniques are used to estimate these characteristic length scales depending on flow conditions. Whereas a well-known energetic method is used for current flow, a specific analysis based on correlation measurements is lead to describe temporal evolution of turbulence length scale over the wave period. As a main result, we show that the free surface causes a vortex stretching for current flow and that turbulence length scales follow a periodic evolution with a frequency which is twice as the swell period. The turbulence length scales also depend on wave period and amplitude.     

A Combined Theoretical/Experimental Approach for Reducing Ringing Artifacts in Low Dynamic Testing with Servo-hydraulic Load Frames

One of the most challenging tasks facing computer-aided engineering (CAE) analysis is the acquisition of accurate tensile test data that spans quasi-static to low dynamic (10^?5/s?≤ $ \overset{.}{\varepsilon } $ ≤5?×?10²/s) strain rates ( $ \overset{.}{\varepsilon } $ ). Critical to the accuracy of data acquired over the low dynamic range is the reduction of ringing artifacts in flow data. Ringing artifacts, which are a consequence of the inertial response of the load frame, are spurious oscillations that can obscure the desired material response (i.e. load vs. time or load vs. displacement) from which flow data are derived. These oscillations tend to grow with increasing strain rate and peak at the high end of the low dynamic range on servo-hydraulic tensile test frames. Common practices for addressing ringing are data filtering, which is often problematic since filtering introduces distortion in smoothed material data, or trial-and-error design of test specimen geometries. This renders techniques for reducing ringing based upon the mechanics of the load frame and optimization of tensile specimen geometry quite attractive. In the present paper, relationships between load, stress wave propagation, and specimen geometries are addressed, to both quantify ringing and to develop specimen designs that will reduce ringing. A combined theoretical/experimental approach for tensile specimen design was developed for reducing ringing in flow data over the low dynamic range of strain rates (10^?5/s≤ $ \overset{.}{\varepsilon } $ ≤5?×?10²/s). The single camera digital image correlation (DIC) method was used to measure the displacement fields and strain rates with specimens resulting from the combined theoretical/experimental approach. While the approach was developed on a specific commercial load frame with a TRIP steel subject to a two-step quenching and partitioning heat treatment (Q&P980), it is readily adaptable to other servo-hydraulic load frames and metallic alloys. The developed approach results in a 90 % reduction in ringing artifact (with no filtering) in a tensile flow curve for Q&P980 at $ \overset{.}{\varepsilon}\kern-4pt $ = 5?×?10²/s. Results from split Hopkinson bar tests of Q&P980 were performed at $ \overset{.}{\varepsilon } $ = 500/s and compare favorably with the test data generated by the developed testing approach. Since the Q&P980 steel represents a new generation of advanced high strength steels, we also evaluated its strain rate sensitivity over the low dynamic range.     

Quantification of the effect of surface heating on shock wave modification by a plasma actuator in a low-density supersonic flow over a flat plate

This paper describes experimental and numerical investigations focused on the shock wave modification induced by a dc glow discharge. The model is a flat plate in a Mach 2 air flow, equipped with a plasma actuator composed of two electrodes. A weakly ionized plasma was created above the plate by generating a glow discharge with a negative dc potential applied to the upstream electrode. The natural flow exhibited a shock wave with a hyperbolic shape. Pitot measurements and ICCD images of the modified flow revealed that when the discharge was ignited, the shock wave angle increased with the discharge current. The spatial distribution of the surface temperature was measured with an IR camera. The surface temperature increased with the current and decreased along the model. The temperature distribution was reproduced experimentally by placing a heating element instead of the active electrode, and numerically by modifying the boundary condition at the model surface. For the same surface temperature, experimental investigations showed that the shock wave angle was lower with the heating element than for the case with the discharge switched on. The results show that surface heating is responsible for roughly 50 % of the shock wave angle increase, meaning that purely plasma effects must also be considered to fully explain the flow modifications observed.