动水环境中有限宽窄缝湍射流的水力特性研究

本文采用粒子图像测速(PIV)系统，在分析了水中粒子跟随性的基础上，对动水环境中多种喷口长度和流速比情况下的有限宽窄缝湍射流近区流场进行测试，并结合数值模拟结果分析讨论了动水环境中有限宽窄缝湍射流的近场三维流动特性。在实验观测的流速比范围内，射流势流核长度随着流速比的增加而增大并逐渐趋近于平面自由湍射流的势流核长度，雷诺数对射流的发展轨迹影响很小，射流发展主要由流速比控制。同时，给出了射流背流面逆流区长度与流速比、喷口形状因子之间的关系。     

平面激光诱导荧光技术测量横流中射流浓度场的研究

利用已建立的考虑了二维数字校正的ＰＬＩＦ浓度场测量系统获得了横流中单孔和五孔垂向射流四种典型工况浓度场，观测到低流速比时射流出分叉现象及尾涡，并给出了马蹄涡结构沿水深的变化过程，文中还对单孔射流的特性进行了比较，分析。     

应用PIV进行二维后向台阶流流动特性的研究(1)二维后向台阶流的旋涡结构的研究

利用PIV技术，对二维后向台阶定常流的瞬态速度场进行了测量，得到层流至湍流情况下定常流流场中旋涡的生成、发展和演化的现象和规律。本文分析了各种情况下旋涡结构特点、讨论了与时均流场和自由剪切层的区别，还给出了二维后向台阶流的拓扑结构。     

横流中三维线源型浮力射流特性的研究

本文利用混合有限分析法及交错网格，对横流中有限长线源型浮力射流进行数值计算，成功模拟了端涡现象及其发展过程，并分析了扩散器长度及浮力对湍浮力射流的影响。     

横流中扩散器长度对浮力射流的影响

本文利用混合有限分析法及交错网格的思想，对横流中有限长线源型浮力射流进行数值计算，成功模拟了端涡现象及其发展过程，并分析了扩散器长度对湍浮力射流的影响。     

横流中射流及其温度标量输运大涡模拟

将动力拟序涡黏性亚格子应力模型拓展到温度标量亚格子模型中,数值模拟了横流条件下有、无温度标量场作用的射流,得到的横流条件下浮力射流的温度和速度分布与Anwar的试验值吻合一致。在此基础上,分析了有、无温度标量场作用下射流回流区域大小和射流轨迹线特性,对比分析了回流区域内涡心和分离点处湍动能和耗散率、拟涡能以及边界层处拟序结构等湍流特性。计算结果表明:温度场的作用使射流的回流区域增大,射流速度轨迹线高度增加,回流区域内湍流的湍动能增加,边界处拟序结构的周期性不如无温度场时明显。     

横流环境中射流的数值研究

本文采用标准的k-ε模型及混合有限分析法对均匀横流环境中的铅直圆形射流进行了(射流比0.5～8)数值分析。所得射流轨迹线与实验资料吻合良好，且与理论分析得出了各种射流比(射流出流速度与横流速度之比)情况下的射流轨迹线、对称面上的内外边界线的统一数学表达式，得出了水平面上示踪质影响的最大宽度、射流横断面浓度最大值偏离射流中心值与射流比的关系式，还得出了射流是否发生附壁及产生分叉现象的界限值。文中数值结果清晰地显示射流背流面存在马蹄形的流动结构。     

浅水层流射流大尺度涡流场特征数值研究

在密度均匀的浅水流体中,由于流体的上下边界作用,会抑制动量源流动的垂向传播发展,形成类似分层流体中偶极子涡的准二维大尺度涡结构。该文通过数值模拟手段,以圆形喷管射流模拟动量源,对层流动量源在浅水条件下生成准二维大尺度涡结构的流场特性进行了研究。数值研究中,为考虑浅水流体上边界自由面的影响,设置了空气层;流体的下边界层设置为固壁条件;同时还考虑了不同的雷诺数影响。研究结果针对流场中射流主流轴向速度分布、过射流轴线的水平断面和自由表面速度场和涡量场进行了分析。结果表明,由于上下边界的存在,主流轴向速度分布关于中心轴非对称,而仅在水平断面上保持轴对称,这与无界射流的情况相差较大。同时,过射流轴线的水平断面和自由表面流场具有较高的相关性,这表明大尺度涡的流动显示出很强的二维流动特性。进一步对上述两个平面的涡量场进行分析,发现流场的平均涡量与时间幂次成正比关系,而且三个不同雷诺数下平均涡量的增长和衰减规律是基本不变的。     

前缘倒圆角方柱绕流的大涡模拟

该文基于FLUENT软件采用大涡模拟方法对前缘倒圆角方柱绕流的气动特性进行数值研究。首先分析网格质量对二维大涡模拟结果准确度的影响,得出适用于钝体绕流大涡模拟计算的网格标准;然后对比二维和三维大涡模拟计算的升阻力系数、脱落涡频率、回流区长度和瞬态流场旋涡结构,以及尾迹速度分布,并与实验结果对比。最后得到二维和三维大涡模拟方法在钝体绕流非定常特性研究中的适用性。结果表明:二维和三维大涡模拟均能捕捉流场中大尺度旋涡结构,预测的脱落涡频率与实验偏差均小于0.4%;三维大涡模拟结果相比于二维大涡模拟与实验结果更加吻合。     

应用PIV进行二维后向台阶流流动特性的研究(2)二维后向台阶流起动流的研究

利用PIV技术，对二维后向台阶起动流的瞬态速度场进行了观测。得到层流至湍流情况下起动流的一些运动规律。本文分析了流动中起动涡等旋涡的运动和发展特征。分析了起动流过程中再附着点的位置、起动涡等旋涡涡心的位置等的变化规律。     

风琴管喷嘴喉部结构对射流流场流动结构影响的数值研究

本文提出了一种采用间歇涡环模型述射流流场的大尺度流动结构特性，并依据边界元方法优化设计风琴管等自激振荡型喷管的内流结构曲面和其喉部结构的数值实验方法，计算结果表明内流过渡曲面为椭球面而出口形状为锥面的风琴管式喷嘴喷射出的圆形射流流场具有良好的大尺度涡环结构。     

跌扩型底流消能漩涡特性的初步研究

多股跌扩型底流消能是一种新型消能方式,消力池内紊流特性复杂。基于RNG κ-ε紊流模型和VOF自由表面追踪法,采用非均匀结构网格技术,建立了三维紊流数学模型,对高低坎多股跌扩型底流消能工进行高精度数值计算。讨论了不同消能方案下游消力池内漩涡分布及变化特性,指出：跌扩型底流消能,水流紊动剧烈,各种漩涡结构交织,下游消力池底板、边墙及跌坎附近随机形成了强度和尺度各异的立轴和横轴漩涡,但漩涡具有一定的游移性和间歇性;消力池底板X=0+0.0~0+40.0范围为立轴漩涡高发区;边墙处漩涡主要分布在高程Z=4.0~16.0 m范围.     

NUMERICAL SIMULATION OF TURBULENT JETS WITH LATERAL INJECTION INTO A CROSSFLOW

1. INTRODUCTION The interaction of jets with crossflow generates complex flow fields which exist in a variety of industrial applications, e.g. internal film cooling of turbine blades, dilution air jets in combustion chambers, jet from V/STOL aircraft in transition flight. Systematic experimental, theoretical and numerical investigations of the flow fields began several decades ago, where the parameters studied include the jet injection angel, the jet-to-crossflow velocity ratio, the jet …     

Dynamics and geometry of developing planar jets based on the invariants of the velocity gradient tensor

Based on the direct numerical simulation(DNS), the developing planar jets under different initial conditions, e.g., the conditions of the exit Reynolds number and the exit mean velocity profile, are investigated. We mainly focus on the characteristics of the invariants of the velocity gradient tensor, which provides insights into the evolution of the dynamics and the geometry of the planar jets along with the flow transition. The results show that the initial flow near the jet exit is strongly predominated by the dissipation over the enstrophy, the flow transition is accompanied by a severe rotation and straining of the flow elements, where the vortex structure evolves faster than the fluid element deformation, in the fully-developed state, the irrotational dissipation is dominant and the most probable geometry of the fluid elements should remain between the biaxial stretching and the axisymmetric stretching. In addition, with a small exit Re and a parabolic profile for the exit mean streamwise velocity, the decay of the mean flow field and the magnitude of the turbulent variables will be strengthened in the process of the flow transition, however, a large exit Re will promote the flow transition to the fully-developed state. The cross-impact between the exit Re and the exit mean velocity profile is also observed in the present study.     

湍浮力射流形成区内特性的预报

应用作者所提出的数学模型和计算方法,对浮力射流形成区内的特性进行了预报。得出了形成区内中线流速、温度和湍动能的沿程变化,以及射流核的长度和掺入速度。也得出了流速、温度和湍动能在断面上的分布。并分析和讨论了出口条件及环境分层对这些特性的影响。     

涡旋管内强旋湍流气固两相流的数值模拟

本文建立了基于一种合理考虑湍流-离心力相互作用的新的代数Peynolds应力模型和颗粒随机轨道模型的强旋湍流气固两相流动数学模型。应用该模型对新型涡旋管内的强度湍流气固两相流进行了数值模拟，揭示了涡旋管内气固两相湍流流动的基本特性以及改变切向出口气体流率对流动的影响。     

河漫滩湿地淹没柔性植物水流涡量场研究

含植物水流的涡量场构成了河漫滩湿地水生动物生境的物理基础，形成水、营养物质的循环以及能量的分配过程。本文通过玻璃水槽试验用二维标准PIV测量研究了含淹没柔性植物二维垂直涡量场的分布。得出流速梯度是形成含植物水流涡量的关键因素，植物冠层附近对水流的干扰大，因而流速梯度大；涡量最大值出现在淹没柔性植物冠层以下约50%处；植物冠层处，涡量绝对值大，拟熵大，能量耗散率也高。植物冠层是造成水流紊动耗散的主要原因。     

Large eddy simulation of turbulent flow structure and characteristics in an annular jet pump

The large eddy simulation(LES) of the flow characteristics in an annular jet pump(AJP) is conducted, and the flow characteristics are systematically analyzed from both time-averaged and instantaneous aspects. The jet expansion, the velocity distribution and the energy are considered to analyze the time-averaged evolution of the flow field in the AJP. The transient flow characteristics can also be acquired from the analysis of the turbulence intensity and the Reynolds stress. The simulation demonstrates that in the time-averaged characteristics, the potential cores increase linearly with the increase of the flow ratio. With the flow development, the jet half-width gradually increases and the residual energy coefficient decreases. Compared with the distribution of the time-averaged axial velocity, that of the instantaneous velocity is more complex and disorderly. The high intensity of the axial turbulence mainly occurs in the mixing layer and the near-wall regions of the diffuser. The annular distribution of the Reynolds stress is mainly in the mixing layer and the recirculation region. There is a low-stress zone between the mixing layer and the high-stress region in the wall-boundary layer. The intensity of the spanwise vortexes is larger than that of the streamwise vortexes, and therefore, the former make greater contribution to the total vorticity. This research provides a better understanding of the flow characteristics in the AJP.     

静止环境中垂直平面浮力射流稳定性与混合特性数值研究

针对不同的射流参数和环境流体参数下的有限深平面垂直射流，采用混合有限分析法对近区以稳定浮力表面层形式排放和由于近区漩涡产生二次吸附的非稳定排放两种流动形态的混合流体的流速场和温度场进行了数值模拟。结果表明近区排放稳定性主要取决于排放佛汝德数和相对淹没度，而与受纳水体的远区几何形状无关；受纳水体的远区几何形状只对排放水体的混合性质产生影响，这一点对非稳定排放尤其显著。所得结果与Jirka和Harleman的理论分析和试验结果十分吻合，说明所采用数值方法可对平面浮力射流的流动现象进行完整的预报。     

Performance of the bio-inspired leading edge protuberances on a static wing and a pitching wing

It is shown that the leading edge protuberances on the flippers of a humpback whale can significantly improve the hydrodynamic performance. The present study numerically investigates the flow control mechanisms of the leading edge protuberances on a static wing and a pitching wing. For static wings, the performance in both laminar flow and turbulent flow are studied in the context of the flow control mechanisms. It is shown that the protuberances have slight effects on the performance of static wings in laminar flow. Also, it could be deduced that non-uniform downwash does not delay the stall occurrence in either laminar flow or turbulent flow. In turbulent flow, the leading edge protuberances act in a manner similar to vortex generators, enhancing the momentum exchange within the boundary layer. Streamwise vortices do contribute to the delay of the stall occurrence. The normal vorticity component also plays an important role in delaying the stall occurrence. However, for the pitching wing, the effect of leading edge protuberances is negligible in turbulent flow. Detailed analysis of the flow field indicates that for the wing with the leading edge protuberances, the leading edge vortices become more complex, while the thrust jet and the vortices in the wake are not changed significantly by the leading edge protuberances.