共查询到20条相似文献,搜索用时 125 毫秒
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为实现高湿环境下脱硫塔内复杂烟气的高效除尘,设计了一种预混式双流体静电雾化喷嘴,并对其喷雾特性及荷电性能进行了试验研究。试验测量了喷雾粒径、锥角和荷质比等参数,通过量纲分析,得到了该喷嘴粒径分布与雷诺数Re的数学模型。试验结果表明:喷雾粒径随气液比(GLR)的增加呈指数减小,当气液比小于0.1时,喷雾粒径随气液比增加迅速减小,当气液比大于0.1时,喷雾粒径减小幅度趋于平缓;喷雾粒径随雷诺数的增加呈线性减小。喷雾锥角随着气液比增加呈先增大后减小的趋势,当气液比为0.1时喷雾锥角最大。气液比增加,喷雾荷质比增加,荷电效果逐渐增强。荷电电压的升高使得喷雾的单分散性提高,弥散空间逐渐增加。 相似文献
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本文基于电容耦合式非接触电导检测(Capacitively Coupled Contactless Conductivity Detection,C~4D)技术,提出了一种气液两相流相含率测量新方法。该方法基于新型六电极阵列式C~4D传感器,首先获取气液两相流电导信号,然后利用所获电导信号,结合LS-SVM回归方法分别建立三种典型流型(泡状流、环状流和层状流)的相含率测量模型。实际测量时根据流型选择相应的相含率测量模型,计算获得相含率。在内径为47.5 mm管径下进行相含率测量静态实验,研究结果表明,所提出的气液两相流相含率测量新方法是可行、有效的。在三种典型流型下的相含率测量最大绝对误差均小于9%。 相似文献
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实测强风工况下高度167 m的徐州彭城电厂冷却塔的表面风荷载,并归纳历史上其他研究人员给出的实测结果,以丰富高超临界雷诺数(Re)区间二维圆柱绕流的试验成果.在低湍流度均匀流场和高湍流度大气边界层流场中分别开展4种风速8类粗糙度条件下的冷却塔刚性模型测压风洞试验,通过对比低雷诺数(Re=2.1×10~5—4.19×10~5)条件下的风洞试验结果和高雷诺数(Re=5.4×10~7—1×10~8)条件下的现场实测结果研究各种静动态绕流特征随雷诺数的变化规律,重点考察雷诺数无关现象的产生条件.研究结果表明,对于物表相对粗糙度在0.01以上的圆柱绕流,雷诺数不相关现象存在于很宽的雷诺数范围(2×10~5Re1×10~8)内;增大来流湍流度亦能引起的雷诺数无关现象,但此时该现象可能仅存在于一个较窄的低雷诺数范围内. 相似文献
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油气水三相流中的复杂相态及压力降研究 总被引:3,自引:0,他引:3
将水平管划分为三个测量段,以空气、水和高粘度油体为工质,研究了油气水三相流中由流动引起的液-液复杂相态及其所对应的三相流压力降。试验研究发现,油气水三相流在三个测量段中可由流动引起不同的液-液相态,致使对应于相同的油、气、水三相体积通量,三相流阻力损失存在多值性。对不同的液-液相态建立了与之适应的阻力损失计算模型,模型预测结果与试验结果吻合 相似文献
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考虑转动能的一维/二维Boltzmann-Rykov模型方程数值算法 总被引:1,自引:0,他引:1
研究考虑转动能的Boltzmann-Rykov模型方程,基于转动自由度对气体分子速度分布函数矩积分,引入约化速度分布函数,应用离散速度坐标法与数值积分技术,将气体运动论模型方程化为在离散速度坐标点处关于三个约化速度分布函数的联立方程组.应用拓展计算流体力学有限差分方法,数值计算考虑转动自由度的双原子气体一维、二维Boltzmann模型方程,得到高、低Knudsen数一维激波管内流动和二维竖直平板绕流问题的流场,分析验证考虑转动能的Boltzmann-Rykov模型方程全流域统一算法求解一维/二维气体流动问题的可靠性.结果表明,气体稀薄程度与分子内自由度对流场具有较大影响,且Knudsen数较高的稀薄气体流动呈现严重的非平衡流动特点. 相似文献
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通过控制变量法对混流闭式冷却塔进行测试, 采用灰色关联分析法对影响出水温度的因素进行筛选, 将关联度较大的5个因子作为输入参数, 进而建立灰色_BP神经网络预测模型, 对混流闭式冷却塔的出水温度进行预测。操作参数包括进水温度、湿球温度、补水温度、循环水流量和风量, 输出值为出水温度。网络采用三层结构, 隐含层神经元数为4个, 迭代次数为30 000次, 使用不涉及训练阶段的实验数据来验证所建立的模型。结果表明, 灰色_BP神经网络模型比传统BP神经网络模型的预测结果更加准确, 其预测值与实际值的相关系数、平均相对误差、均方根误差, 分别为0.998 9、0.293 4%和0.152 9, 因而可认为灰色_BP神经网络是预测混流闭式冷却塔出水温度的有效工具。 相似文献
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如何准确可靠地模拟从外层空间高稀薄流到近地面连续流的航天器高超声速绕流环境与复杂流动变化机理是流体物理的前沿基础科学问题. 基于对Boltzmann方程碰撞积分的物理分析与可计算建模, 确立了可描述自由分子流到连续流区各流域不同马赫数复杂流动输运现象统一的Boltzmann模型速度分布函数方程, 发展了适于高、低不同马赫数绕流问题的离散速度坐标法和直接求解分子速度分布函数演化更新的气体动理论数值格式, 建立了模拟复杂飞行器跨流域高超声速飞行热环境绕流问题的气体动理论统一算法. 对稀薄流到连续流不同Knudsen数0.002 ≤Kn∞ ≤1.618、不同马赫数下可重复使用卫星体再入过程(110–70 km)中高超声速绕流问题进行算法验证分析, 计算结果与典型文献的Monte Carlo直接模拟值及相关理论分析符合得较好. 研究揭示了飞行器跨流域不同高度高超声速复杂流动机理、绕流现象与气动力/热变化规律, 提出了一个通过数值求解介观Boltzmann模型方程, 可靠模拟高稀薄自由分子流到连续流跨流域高超声速气动力/热绕流特性统一算法. 相似文献
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A new finite volume-based numerical algorithm for predicting incompressible and compressible multi-phase flow phenomena is presented. The technique is equally applicable in the subsonic, transonic, and supersonic regimes. The method is formulated on a non-orthogonal coordinate system in collocated primitive variables. Pressure is selected as a dependent variable in preference to density because changes in pressure are significant at all speeds as opposed to variations in density, which become very small at low Mach numbers. The pressure equation is derived from overall mass conservation. The performance of the new method is assessed by solving the following two-dimensional two-phase flow problems: (i) incompressible turbulent bubbly flow in a pipe, (ii) incompressible turbulent air–particle flow in a pipe, (iii) compressible dilute gas–solid flow over a flat plate, and (iv) compressible dusty flow in a converging diverging nozzle. Predictions are shown to be in excellent agreement with published numerical and/or experimental data. 相似文献
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O. Morita 《Phase Transitions》2013,86(1-4):213-244
Baroclinic flow in a rotating annulus of fluid shows remarkable transitions of flow patterns as do Rayleigh–Benard convection and Taylor vortices. There are four flow regimes in two nondimensional parameter space, called a symmetric regime (Hadley regime), a steady wave regime (Rossby regime), a vacillating wave regime and a geostrophic turbulence regime. Laminar flow in a symmetric regime is formed between the balance of a horizontal pressure gradient force and a Coriolis torque (geostrophic balance), and this flow becomes unstable when one of the nondimensional parameters, the thermal Rossby number, becomes less than the critical value. In this paper, the characteristic features of the four flow regimes are reviewed including recent findings about the behavior of geostrophic turbulence. 相似文献
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The Boltzmann simplified velocity distribution function equation describing the gas transfer phenomena from various flow regimes
will be explored and solved numerically in this study. The discrete velocity ordinate method of the gas kinetic theory is
studied and applied to simulate the complex multi-scale flows. Based on the uncoupling technique on molecular movement and
colliding in the DSMC method, the gas-kinetic finite difference scheme is constructed to directly solve the discrete velocity
distribution functions by extending and applying the unsteady time-splitting method from computational fluid dynamics. The
Gauss-type discrete velocity numerical quadrature technique for different Mach number flows is developed to evaluate the macroscopic
flow parameters in the physical space. As a result, the gas-kinetic numerical algorithm is established to study the three-dimensional
complex flows from rarefied transition to continuum regimes. The parallel strategy adapted to the gas-kinetic numerical algorithm
is investigated by analyzing the inner parallel degree of the algorithm, and then the HPF parallel processing program is developed.
To test the reliability of the present gas-kinetic numerical method, the three-dimensional complex flows around sphere and
spacecraft shape with various Knudsen numbers are simulated by HPF parallel computing. The computational results are found
in high resolution of the flow fields and good agreement with the theoretical and experimental data. The computing practice
has confirmed that the present gas-kinetic algorithm probably provides a promising approach to resolve the hypersonic aerothermodynamic
problems with the complete spectrum of flow regimes from the gas-kinetic point of view of solving the Boltzmann model equation.
Supported by the National Natural Science Foundation of China (Grant Nos. 90205009 and 10321002) and the National Parallel
Computing Center 相似文献