高速列车交会时的风致振动研究

摘 要：为了阐明高速列车交会过程中气动力对列车的系统动力学行为的影响,分别建立了CRH-2动车组的简化几何模型和50个自由度的车辆系统动力学模型。采用有限体积法对三维瞬态可压缩雷诺时均Navier-Stokes方程和k-e 两方程湍流模型进行求解,并通过滑移网格技术实现列车的运动,对考虑和不考虑气动力时的列车系统力学响应进行了数值模拟,并对两种情况下列车的安全性和舒适性进行了分析讨论。研究发现：气动力在列车交会过程中变化剧烈,对列车系统动力学行为的影响非常明显,交会时列车振动剧烈,头车和尾车的安全性和舒适性明显降低。     

基于CFD的水平轴风力机叶尖小翼增功研究

基于风力机叶片增功装置设计要求,以NREL 5 MW叶片为设计原型,以扭角、上反角及后掠角3种小翼外形参数为优化因素设计正交试验表,每种因素分别选取4个水平值,采用计算流体力学(CFD)方法对加装16种不同构型小翼的叶片进行数值模拟。计算结果表明,叶片整体可增功约1.466%,同时推力增加约1.570%;影响扭矩的最主要因素为扭角,影响推力的最主要因素为上反角;通过分析叶片近尾迹流场发现,优化的叶尖小翼布局可改变叶片叶尖涡强度分布,调整叶尖翼型截面气动力特性,进而改善叶片气动性能。     

基于微分雷诺应力湍流模型的车辆气动特性的数值模拟

针对Ahmed标准汽车模型,采用含有二阶矩的微分雷诺应力模型(DRSM)对车辆外流场进行了数值模拟,对照风洞试验,获得了气动阻力系数以及3个尾流横截面中速度矢量分布等结果。参考RNGk-ε模型,对比分析了DRSM数值模拟的气动阻力系数与试验值之间的误差及误差产生原因。结果表明,DRSM模型在车辆外流场模拟中有更高的计算精度,可正确地获得包括车辆尾流中的二次流等在内的复杂气动特性。     

汽车外形对智能车辆队列行驶气动特性的影响

为了研究智能交通系统中不同外形车辆在队列行驶时的空气动力特性,以及车辆纵向间距对队列行驶车辆气动特性的影响,采用数值模拟方法对阶背式、快背式和直背式轿车5车队列分别在6种纵向间距下的气动特性了进行研究。结果表明:三种车型队列的平均减阻率大约为10%~40%,节省燃油5%~20%。阶背式轿车队列的平均减阻率最大,直背式次之,快背式最小。随着纵向间距的减小,每辆车的升力都增大,稳定性都变差。     

Comparison of aerodynamic models for horizontal axis wind turbine blades accounting for curved tip shapes

Curved tip extensions are among the rotor innovation concepts that can contribute to the higher performance and lower cost of horizontal axis wind turbines. One of the key drivers to exploit their advantages is the use of accurate and efficient computational aerodynamic models during the design stage. The present work gives an overview of the performance of different state-of-the-art models. The following tools were employed, in descending order of complexity: (i) a blade-resolved Navier Stokes solver, (ii) a lifting line model, (iii) a vortex-based method coupling a near-wake model with a far-wake model, and (iv) two implementations of the widely used blade element momentum method (BEM), with and without radial induction. The predictions of the codes were compared when simulating the baseline geometry of a reference wind turbine and different tip extension designs with relatively large sweep angle and/or dihedral angle. Four load cases were selected for this comparison, to cover several aspects of the aerodynamic modeling: steady power curve, pitch step, extreme operating gust impact, and standstill in deep stall. The present study highlighted the limitations of the BEM-based formulations to capture the trends attributed to the introduction of curvature at the tip. This was true even when using the radial induction submodel. The rest of the computational methods showed relatively good agreement in most of the studied load cases. An exception to this was the standstill configuration, as the blade-resolved Navier-Stokes solver was the only code able to capture the highly unsteady effects of deep stall.     

On the extension of k−ω−SST corrections to predict flow separation on thick airfoils with leading-edge roughness

Modern wind turbines employ thick airfoils in the outer region of the blade with strong adverse pressure gradients and high sensitivity to flow separation, which can be anticipated by leading-edge roughness. However, Reynolds average Navier-Stokes simulations currently overpredict the Reynolds shear stresses near the surface, and the flow separation is not correctly predicted. Hence, these methods are not representative enough to optimize the blade design to avoid flow separation, which becomes relevant for rough blades. While several eddy-viscosity corrections in the $k-\omega -SST$ turbulence model have been previously studied to predict flow separation over smooth airfoils, the present study aims to extend their applicability to airfoils with leading-edge roughness. Two corrections, whose effect on flow physics has not been empirically quantified, are addressed. Particle image velocimetry measurements have been performed on a 30% thick airfoil to quantify the impact of these corrections. The reduction of the eddy viscosity introduced by the corrections leads to a shift of the peak location of the Reynolds shear stresses away from the surface, which, in turn, promotes flow separation and improves the prediction of the mean velocity and the pressure-coefficient distribution. Besides, the ratio between the main turbulent shear stress and turbulent kinetic energy is demonstrated to be lower than the standard value used in the $k-\omega -SST$ turbulence model at the boundary-layer outer edge. Adjusting this ratio for an angle of attack of 0° decreases the error on the predicted lift and drag coefficients from 75% to 3% and from 58% to 39%, respectively.     

High Reynolds number unsteadiness assessment using 3D and 2D computational fluid dynamics simulations of a thick aerofoil equipped with a spoiler

An operating 2-MW wind turbine has been scanned and analysed using 2D computational fluid dynamics (CFD) and blade element momentum (BEM) analysis. The current work illustrates using full-scale 3D CFD simulations the differences between 2D and 3D simulations and its impact on the local aerofoil vortex shedding frequency. The outcome shows that despite a pressure redistribution and lift change introduced by the blade span and rotation, the vortex shedding frequency remains similar between 2D and 3D thereby validating the novel fatigue calculation method previously proposed.