受限空间内空心锥形喷雾-横流掺混规律

在自建的冷态横流-旋流喷雾两相掺混系统实验台上,采用PIV测量了掺混通道内气液两相掺混过程中液滴群的运动特性,获得了掺混流场中不同位置的液滴分布图像与流场结构特性。实验段结构为方腔（横截面尺寸为95 mm×95 mm）,喷嘴采用空心锥形雾化喷嘴。对影响掺混效果的主要参数（横流速度、喷嘴雾化压力、喷嘴雾化粒径）进行了详细研究,绘出了最佳掺混效果下各参数关系曲线。掺混过程主要受不同尺度的旋涡结构影响,液滴多富集于旋涡边缘,稳定的大尺度涡不利于掺混。提高掺混效果的途径即是避免流场中出现稳定的大尺度旋涡结构,采用喷嘴前倾布置、增加喷嘴个数、确定合适的横流速度均是提高掺混效果的有效途径。分析方法与研究结果为工程实际应用中掺混室结构的设计及掺混性能的改进提供了依据和参考。     

化工搅拌釜内流动测量技术的应用进展

搅拌釜内的物料混合是一个有限空间中的复杂非定常湍流问题,且常伴有强烈的传质、传热乃至反应过程。搅拌混合过程中影响因素多,理论分析难度大,实验获取搅拌釜内整场流动信息是其机理研究和搅拌混合设备优化设计的重要手段。本文归纳了在搅拌混合研究中传统流动测量技术的应用,分析其各自优缺点,着重探讨了新一代全场光学测速技术——粒子图像速度场仪（PIV）在搅拌混合实验中的应用,指出PIV在搅拌混合研究中具有广泛应用前景。PIV具有很高的空间分辨率和时间解析度,可以得到搅拌釜中混合流体的瞬时2D或3D速度场以及浓度场和温度场等信息,进行非定常湍流特性研究,有助于建立搅拌釜内多相流动模型,验证数值模拟结果,实现搅拌釜的优化设计,从而促进化工搅拌技术的进一步发展。     

涡轮桨搅拌槽内流场特性的V3V实验

用体三维速度测量技术（volumetric three-component velocimetry measurements,V3V）实验研究了涡轮桨搅拌槽内桨叶附近流场。通过速度数据得到三维流场特性,确定尾涡三维结构;分析了叶片后方30°截面轴向、径向和环向速度沿径向分布规律;对比了V3V和2D-PIV（particle image velocimetry）径向和轴向速度,发现速度分布吻合较好,特别是尾涡所在的射流区。用2D-PIV方法对尾涡发展规律进行研究,发现受流体自由液面影响,尾涡轨迹向上倾斜,并与水平方向成10°,上、下尾涡运动轨迹不对称,下尾涡运动比上尾涡稍快,衰减亦较快,这与V3V实验结果一致;叶片后方60°尾涡依然清晰可见。用V3V和2D-PIV方法对桨叶附近湍流各向同性假设进行了分析,发现桨叶区和尾涡所在位置湍动能被各向同性假设近似法高估了25%~33%,桨叶区和尾涡所在位置趋向于各向异性。     

抗拔锚板群锚基础模型试验研究

抗拔锚板上拔过程是一个复杂的锚土相互作用过程,锚板周围土体在上拔过程中的变形破坏机制对于抗拔锚板基础的极限承载力研究具有重要意义。基于PIV(particle image velocimetry)无干扰测量技术对砂土中方形锚板上拔过程中变形场进行了测量分析,研究了抗拔锚板群锚基础的破坏机制。试验结果表明:锚板间距对群锚破坏面的形状有着重要影响;在临界间距内,以锚板上部1倍边长为拐点,剪切带先内倾然后外倾向上贯通到土体表面,群锚效应系数与S/B为线性关系,由此预测出群锚效应达到100%时的锚板间距;达到临界间距后,每个锚板的剪切场和单个锚板剪切场一致,试验结果可为群锚基础极限抗拔力的预测提供参考。     

旋转射流喷嘴内旋流特性的PIV实验分析

利用二维粒子图像测速技术(PIV)对旋转水射流喷嘴内部流场进行了测量,将喷嘴入流条件分为入流流量比(切向流量与轴向流量之比)以及入流总流量两个因素,分析了两者对喷嘴出口旋流结构、切向速度分布以及喷嘴出口旋流数的影响.实验结果表明,入流流量比对喷嘴出口的切向速度大小及其径向分布都有影响,而入流总流量只影响其大小;入流流量比和入流总流量的增加均可使喷嘴出口的旋转流动增强,但只有入流流量比的增加可使喷嘴出口旋流数增加,而旋流数是喷嘴加旋效果的检验标准.     

地面驱动螺杆泵抽油杆旋转效应的研究

为了探寻抽油杆旋转效应对偏心环空中流体流动规律的影响,利用激光粒子测速技术(PIV)测试了抽油杆不同转速状态下偏心环空中流体的流场,使用差压变送器测量了在不同排量、不同抽油杆旋转速度条件下,偏心环空的流体压降.测试结果表明,当流量恒定时,偏心环空中聚合物溶液的轴向速度和径向速度随着抽油杆转速的增加而增大.模拟地面驱动螺杆泵采油中,随着抽油杆转速的增加,聚合物溶液的压力梯度先减小后增大,当抽油杆转速为17.5r/min时,其压力梯度最小.     

基于新入料形式的圆筒形重介质旋流器流场的研究

 针对目前重介质旋流器导向筒段湍流及转向突变较大的问题,设计出一种新入料形式的重介质旋流器,其主要特点是入料口向底流端倾斜5°,并且配合这一倾斜角度,设计了螺旋角为5°的螺旋形溢流顶板。在相同入料压力下采用PIV技术进行对比测试。试验结果表明,在同一截面上,尤其是在有效分选区域内,新入料形式重介质旋流器相比传统重介质旋流器的速度流场特性有较大的改善,有利于物料的分离以及降低能耗。     

基于CFD和PIV方法的单相KYF浮选机流场分析研究

本文运用CFD模拟和PIV测量的方法研究了实验型KYF0.2m3浮选机的流场特征。CFD预测结果和PIV测量结果均揭示了纵截面的上、下循环流场结构。局部的径向速度和轴向速度对比显示,二者在变化趋势和大小上均有较好的一致性。在叶轮叶片的背浆面出现了同旋转方向相反的漩涡结构,并出现了速度峰值区,其值甚至高于叶片尖端。CFD预测的功率消耗同实测值能够较好地吻合,说明CFD仿真能较真实地反映浮选机的宏观运行状态。     

A vortex panel model for the simulation of the wake flow past a vertical axis wind turbine in dynamic stall

A 2D vortex panel model with a viscous boundary layer formulation has been developed for the numerical simulation of a vertical axis wind turbine (VAWT), including the operation in dynamic stall. The model uses the ‘double wake’ concept to reproduce the main features of the unsteady separated flow, including the formation and shedding of strong vortical structures and the wake–blade interaction. The potential flow equations are solved together with the integral boundary layer equations by using a semi‐inverse iterative algorithm. A new criterion for the reattachment of the boundary layer during the downstroke of a dynamically stalled aerofoil is implemented. The model has been validated against experimental data of steady aerofoils and pitching aerofoils in dynamic stall at high and low Reynolds numbers (Re = 1.5 × 10⁶ and Re = 5 × 10⁴). For the low Reynolds number case, time‐resolved 2D particle image velocimetry (PIV) measurements have been performed on a pitching NACA 0012 aerofoil in dynamic stall. The PIV vorticity fields past the oscillating aerofoil are used to test the model capability of capturing the formation, growth and release of the strong leading edge vortex that characterizes the dynamic stall. Furthermore, the forces extracted from the PIV velocity fields are compared with the predicted ones for a quantitative validation of the model. Finally, the model is applied to the computation of the wake flow past a VAWT in dynamic stall; the predicted vorticity fields and forces are in good agreement with phase‐locked PIV data and CFD‐DES available in the literature. Copyright © 2012 John Wiley & Sons, Ltd.     

Investigation of flow behind vortex generators by stereo particle image velocimetry on a thick airfoil near stall

Stereoscopic Particle Image Velocimetry measurements investigating the effect of vortex generators (VGs) on the flow near stall were carried out in a purpose‐built wind tunnel for airfoil investigations on a DU 91‐W2‐250 profile. Measurements were conducted at Re = 0.9?10⁶, corresponding to free stream velocity U_∞ = 15 m s^?1. The objective was to investigate the flow structures induced by the vortex generators and study their separation controlling behavior on the airfoil. The uncontrolled flow (no VGs) displayed unsteady behavior with separation as observed from large streamwise velocity variations. The corresponding controlled flow (with VGs) showed the same unsteadiness, where the appearance of the vortex structures alternated with a much less separated or even attached boundary layer as also seen in the measured airfoil data: C_L = 1.56, C_D = 0.116 with VGs and C_L = 1.16, C_D = 0.135 without. On average, the controlled flow left an attached flow as opposed to the uncontrolled one. Mixing close to the wall, transferring high momentum fluid into the near wall region, was observed, and the hypothesis of variations in the streamwise velocity component in the boundary layer was supported by a Snapshot Proper Orthogonal Decomposition analysis. This analysis also revealed some of the dynamics of the induced vortices. Copyright © 2012 John Wiley & Sons, Ltd.