无升力双体水动力干扰计算

根据势流理论给出任意运动的2个水下无升力物体间流体动力干扰的二维和三维计算模型.从壁面附近圆柱干扰力计算结果出发,指出水下物体相互接近过程中,理论上存在某种干扰最小的路径.采用3种不同的网格划分比例计算回转椭球体附加质量,单元数确定时,加密纵向网格则与纵向运动有关的计算精度提高,横向的精度降低,因此网格划分应合理分配纵横比例.对三维Rankine体进行了壁面干扰规律的模型试验和计算研究,间距较大时物体受到壁面的吸力,随间距的减小,该吸力先逐渐增加后减小,最后变为排斥力,分布源计算值与试验值的比较表明:分布源法可有效预测壁面间距较大情况下的流动干扰力,随着Reynolds数的增加,分布源法有效性的壁面间距下限增大.论文中的数值模型也适用于多个无升力物体作6自由度运动的情况.     

高速双体船的水动力特征研究

发展了基于二维半理论的预报排水型双体船在波浪上的水动力特征及运动性能的数值方法。在定解条件中，自由面条件是三维的，而控制方程和物面条件则是二维的，所以称为二维半理论。采用时域自由面Green函数将定解问题转化为物面上的积分方程，进而求解水动力系数和船舶运动方程。已经对NPL4b双体船型的运动性能作了理论预报，预报结果与试验结果相当接近。对NPL5b双体船型的计算再次表明二维半理论预报结果与试验结果在中流航速吻合很好。通过改变片体间距，考察了双体船的水动力系数及波浪力特征，表明考虑片体间水动力干扰现象对双体船运动预报是必要的。     

贴壁凸体湍流分离的数值分析

根据二维贴壁凸体湍流分离区附近湍动能及其耗散率分布特性的数值预报结果,文中给出了贴壁凸体湍流分离、产生回流的一种解释;还根据分离前后湍动能的平衡关系,提出了贴壁凸体湍流分离点、重汇点的判别条件。     

全方向推进器主要参数对其水动力性能的影响

为优化全方向推进器的模型设计,采用面元法分析全方向推进器主要参数的变化对非定常水动力性能的影响.基于螺旋桨面元法理论建立了全方向推进器的非定常水动力性能计算的数学模型,进行了数值预报,采用关于扰动速度势的基本积分微分方程,以双曲面元消除面元间的缝隙,在桨叶随边满足压力Kutta条件.应用Morino解析公式计算面元的影响系数,用Yanagizawa方法求得物体表面上的速度分布.分析了全方向推进器主要参数对水动力性能的影响.计算结果表明,周期螺距角的值对全方向推进器的非定常水动力性能起决定性作用.该文的计算结果可以作为下一步试验研究的基础.     

表面圆柱形突体流动特性的数值模拟

数值模拟技术作为研究复杂流动问题的有效工具常被用于研究高水头、大流量泄洪洞内高速 水流问题． 采用该项技术对泄水建筑物过流壁面上圆柱形突体的水平二维和垂直二维流场进行了 数值模拟,分别考虑了不同高度圆柱形突体和不同掺气浓度对空化区内流动特性的影响,给出水平 二维和垂直二维的流速分布和压力分布,对圆柱形突体引发空化的水力特性进行探讨,并与在直流 式水洞中使用PIV 设备所采集的实测结果作了比较,结果表明,数值模拟能较好模拟因圆柱形突体 引发的空化现象．     

脉冲袋式除尘器喷吹气流的数值模拟

借助计算流体动力学方法,采用二维非稳态流动数学模型,对脉冲袋式除尘器滤袋内喷吹气流的压力分布进行了数值模拟.通过与喷吹压力实验值对比,验证了数值模拟结果的可靠性,表明可将数值模拟作为脉冲喷吹的研究方法.在用不同时刻的滤袋壁面压力分布图来表示的模拟结果中显示,随着气流向袋底方向运动,滤袋壁面压力的最大值不断下移,距袋口0.5 m处,峰值压力和压力上升速率都达到最大值.     

螺旋桨空泡的数值分析

螺旋桨空泡会降低螺旋桨性能,产生空化剥蚀和噪声,从而导致船体振动.文章采用基于速度势的低阶面元法对螺旋桨水动力性能和空泡的范围及厚度进行求解,分别用Morino提出的Kutta和等压Kutta条件对压力分布进行计算,讨论了两种Kutta条件对压力分布的影响.计算了空泡产生后的压力分布,验证了在空泡表面上的压力等于水的汽化压力.对空泡起始点对空泡形状的影响进行了研究,结果表明,空泡起始点对空泡范围有很大影响,空泡起始点离导边越远,空泡范围越小.     

砂卵石地层圆形深基坑支护结构土压力

在以砂卵石地层为主的成都平原地区,近年来圆形深基坑工程逐渐出现,但一直无适宜的支护结构土压力的确定方法,对土压力分布特征尚不清楚。运用弹塑性数值模拟方法,充分考虑桩土变形协调关系,确定了成都地区砂卵石地层的圆形深基坑支护结构上土压力的分布规律,呈现出在围护桩中下部偏大的近似三角形分布模式,平均值小于Rankine主动土压力。开展了模型试验研究,针对试验模型,数值计算值与试验值分布规律整体上具有相似性,二者较为接近,说明了数值计算结果具有一定的合理性。     

基于FLUENT对惰性多孔介质中湍流预混燃烧的模拟

采用了多孔介质气固间局部热平衡假定,建立了二维的多孔介质中湍流燃烧模型.通过用户自定义函数在FLUENT6.1的多孔介质模型中引入湍流和辐射的作用,对多孔介质中甲烷-空气预混燃烧的特性进行了数值模拟.得到的多孔介质中的计算流场更加合理,流速均匀且消除了多孔区近壁面速度高而中心低的不合理速度场.计算结果显示多孔介质中温度分布均匀,壁面温度和中心温度相差很小,比FLUENT软件不考虑多孔介质辐射的结果更加合理.通过计算甲烷-空气的两步反应,得到了多孔介质中速度场、温度场和浓度场的分布理论预示结果,并与试验结果进行了比较,发现二者趋势一致.利用FLUENT软件求解多孔介质中燃烧问题是有效的,该二维惰性多孔介质燃烧模型是合理的.     

方形卧式分离器的PIV流场试验研究

应用粒子成像测速(particle image velocimetry, PIV)技术对方形卧式分离器的内部流场进行了测量，得到分离器内典型的颗粒运动分布状态.采用灰度互相关法处理试验图像数据，得到分离器内3个不同截面的二维瞬时速度分布，结果表明在分离器内气流为顺时针旋流，中间流速高而边壁流速低，在分离器的右上角存在有角涡.根据试验结果计算了方形卧式分离器中间面的平均二维速度分布，与应用雷诺应力模型(RSM)数值计算模拟得到的分离器内气流速度分布进行了对比，结果表明除了近壁面区域差别较大外，其他区域基本吻合.     

Characteristics of supersonic flow in new type externally pressurized spherical air bearings

In order to predict accurately the characteristics of supersonic flow in new type externally pressurized spherical air bearings under large bearing clearance and high air supply pressure, which could decrease their load carrying capacity and stability, a CFD-based analysis was introduced to solve the three-dimensional turbulent complete compressible air flow governing equations. The realizable κ-ɛ model was used as a turbulent closure. The supersonic flow field near air inlets was analyzed. The flow structures illustrate that the interaction exists between shock waves and boundary layer, and the flow separation is formed at the lower corner and the lower wall around the point of a maximum velocity. The numerical results show that the conversion from supersonic flow to subsonic flow in spherical air bearing occurs through a shock region (pseudo-shock), and the viscous boundary layer results in the flow separation and reverse flow near the shock. The calculation results basically agree with the corresponding experimental data.     

Improvement and application of wall function boundary condition for high-speed compressible flows

In order to develop a wall function boundary condition for high-speed flows so as to reduce the grid-dependence of the simulation for the skin friction and heat flux,a research was performed to improve the compressible wall function boundary condition proposed by Nichols.Values of parameters in the velocity law-of-the-wall were revised according to numerical experiments and the expression of temperature law-of-the-wall was modified based on theoretical analysis and numerical simulation.Besides,the formula of the heat conduction term in near-wall region was derived so that the coupling between the wall function boundary condition and CFD code was realized more accurately.Whereafter,the application study of the modified wall function was carried out.The numerical case of supersonic turbulent boundary layer on a flat plate illustrated that the modified wall function produces reasonable results of skin friction and heat flux,and profiles of velocity,temperature and turbulent eddy viscosity for coarse grids with the initial wall spacing of y+<400,and that the modifications to the original wall function can obviously improve the simulation precision.As for the application of separation flows,it was found from the numerical cases of supersonic cavity flow and hypersonic axisymmetric compression corner that the compressible velocity law-of-the-wall originally established based on the fully-developed attached turbulent boundary layer approximately holds in the near-wall region inside the separation flows,which ensures that reliable skin friction and heat flux can be given by the wall function inside the separation flows,while for the region near separation and reattachment points,the wall function gives results with a relatively large error,because the velocity law-of-the-wall used in the wall function takes on obvious deviation from the real velocity profiles near the separation and reattachment points.     

一种适于多级粘性计算的三维网格生成方法

给出了一种适于多级叶片机粘性计算的三维网格生成方法。通过对Ｎ．Ｓ方程求解对网格特殊性要求的分析,给出了几种形式的网格在多级计算中的优缺点,发展了一种代数法与微分方程求解相结合的网格生成技术。采用本方法生成的网格在壁面附近具有Ｏ型网格的特点,而网格的拓扑结构 Ｈ型的,因此该种网格不但可以方便地在级间施以加密技术,以对该区域的任意划分,保证了边界条件在壁面得以准确而简单地实施,减少了壁面附近由于网格在     

Gao’s interacting shear flows (ISF) theory and its inferences and their applications

Gao’s viscous /in-viscid interacting shear flows( ISF) theory,proposed by professor Gao Zhi in Institute of Mechanics,China Academy of Science,and its inferences and their applications in computational fluid dynamics( CFD) are reviewed and some subjects worthy to be studied are proposed in this paper. The flow-field and motion law of ISF,mathematics definition of strong viscous shear layer flow in ISF,ISF equations,wall-surface compatibility criteria( Gao’s criteria),space scale variety law of strong viscous shear layer reveals flow mechanism and local space small scale triggered by strong interaction that cause some abnormal severe local pneumatic heating phenomenon in hypersonic flow. Gao’s ISF theory was used in near wall flow,free ISF flow simulation and design of computing grids,Gao’s wall-surface criteria were used to verify calculation reliability and accuracy of near wall flows,ISF theory approximate analytical result of shock waves-boundary layer interaction and ISF equations were used to obtain the numerical exact solution of local area flow( such as stationary point flow). Some new subjects,such as,improving near-wall turbulent models according to the turbulent flow simulation satisfying the wall-criteria and illustrating relation between grid-convergence based on the wall criteria and other convergence tactics,are suggested. The necessity of applying Gao’s ISF theory and wall criteria is revealed. Difficulties and importance of hypersonic viscous / inviscid interaction phenomenon were also emphasized.     

近壁区网格Δy对TTU建筑风场湍流计算的影响

为了研究近壁区网格厚度旬对建筑物风场绕流时湍流计算结果的影响,提高k-ε EARSM湍流模型用于建筑物数值风洞模拟的准确性,结合TTU试验建筑的实测数据,以△y为参数进行了数值风洞模拟。对k-ε EARSM的雷诺方程进行了解析,并推导了旬的简化计算公式。基于准稳态时步逼近技术,计算了（y=0．001、0．005、0．01、0．05和0．1m等5种工况下的时均流态,对绕流特征、湍动能分布和中轴线脉动风压系数、平均风压系数进行了比较。研究表明,过小的△y会导致高湍动区渗透进入近壁区,计算稳定性变差;过大的细则会降低高湍动区计算结果的准确性。据此,给出兼顾模拟精度与计算稳定性要求的△y变化范围为0．01～0．05m;并给出了△y上限值的经验计算公式。     

湍流模型在翼身组合体流场数值模拟中的应用研究

通过求解三维Reynolds平均Navier-Stokes方程，采用4种湍流模型：代数B—L、J—K90A／J—K92模型和两方程k-g模型，分别数值模拟了ONERA—M6机翼、细长旋成体及NASA TN D-712翼身组合体标模的跨声速及超声速流场。计算结果表明，对于附体及小分离流动，4种湍流模型的数值计算结果与实验值吻合良好；对于强激波、大分离等具有强烈上游历程效应的粘性流动，k-g和J-K模型较B—L，模型有更好的模拟能力；对于具有多体干扰的复杂流场，k-g模型的表现则优于其余3种模型。     

Shock wave-boundary layer interactions control by plasma aerodynamic actuation

This study demonstrates the potential for shock wave-boundary layer interaction control in air by plasma aerodynamic actuation. Experimental investigations on shock wave-boundary layer interactions control by plasma aerodynamic actuation are conducted in a Mach 3 in-draft air tunnel. Schlieren imaging shows that the discharges cause the oblique shock to move forward. Schlieren imaging and static pressure probes also show that separation phenomenon shifts backward and the size of separation is enlarged when plasma aerodynamic actuation is applied. The intensity of shock wave is weakened through wall pressure probe. Furthermore, numerical investigations on shock wave-boundary layer interactions control are conducted with plasma aerodynamic actuation. The discharge is modeled as a steady volumetric heat source which is integrated into the energy equation. The input energy level is about 7 kW through discharge process. Results show that the separation phenomenon shifts backward and the intensity of shock is reduced with plasma actuation. These numerical results are consistent with the experimental results.     

螺旋管内流场数值模拟

螺旋管以其结构简单等优点在油水分离领域得到广泛应用。数值模拟作为一种可替代实验研究的 方法,广泛应用于螺旋管内流场变化规律的研究。采用VOF模型对螺旋管油水两相流进行数值模拟,得出了螺旋 管内流场变化特性:第9圈油水分离度达到95%,近进口端水相分布较大,沿重力方向水相分布变化不大并出现油 水重混合现象;靠近进口处湍动能强度、动压最大,动压在进口处突降而在外沿轴向线性递减;在进口端外侧剪切应 力最大,沿管道轴向分布变化不大。螺旋管内的油水分离数值模拟,为螺旋管油水分离技术的改进提供了一定的理 论基础。     

液黏调速离合器中摩擦副间隙内流体传热分析

为了研究流体润滑条件下液黏调速离合器摩擦副间隙内流体主要传热方式的问题,分别建立等温、绝热及对流换热3种热边界条件下流体流场的简化数学模型,并考虑流体黏温特性的影响,采用商用计算流体动力学软件Fluent对流场进行求解,分别获得等温、绝热及对流换热条件下流场温度分布的数值解;在数值计算的基础上,利用液黏调速离合器实验装置分别测量不同输入转速及输入流量条件下摩擦副间隙内流体温度.研究结果表明等温边界条件下的数值计算结果与实验测试结果比较接近,绝热边界条件下的数值计算结果与实验结果之间偏差最大;流场温度随着摩擦副间隙或输入流量的增加而降低,随着输入转速的增加而增加.     

螺旋桨诱导的船尾脉动压力的数值模拟

利用奇点分布的方法计算船尾脉动压力．在用面元法计算螺旋非定常水动力性能的基础上,在船舶尾部分面元并分布奇点,通过迭代求解船尾和螺旋桨的相互影响,在此计算过程中,采用较为简捷的关于扰动速度势的基本积分微分方程,并采用双面曲形状的面元以消除面元间的间隙,Newton-laphson迭代过程被用来在桨叶随边满足压力Kutta条件,使桨叶上下表面的压力在随边有良好的一致性,在计算面元的影响系数时,应用了Morino导出的解析计算公式,加快了数值计算的速度．从面元法的基本积分方程得到的偶极强度和源汇强度,直接求得流场中的速度分布,并以此计算船尾和螺旋桨的相互影响,得到稳定的流场以后,通过伯努里方程计算船尾压力分布,并通过傅里叶变换得到各个阶脉动压力,最后将计算结果和试验结果作了比较分析。