Experimental study on flow and heat transfer characteristics of synthetic jet driven by piezoelectric actuator

To investigate the flow and heat transfer characteristics of a synthetic jet driven by piezoelectric actuator, experimental investigation utilizing particle image veloci- metry, hot-wire anemometer and infrared camera was carried out. The results show that: (1) At the jet orifice exit, pairs of vortexes are generated, broken down and merged together periodically, forming a steady jet within a several slot width from distance near the orifice exit. And during the development, the synthetic jet spreads rapidly along the minor axis direction of the orifice. While along the major axis direction, the synthetic jet contracts firstly and then spreads slowly. (2) Exci- tation frequency forced on the actuator has a great effect on the synthetic jet flow field. There are two resonance frequencies at which the mean velocity and vorticity of the synthetic jet are maximized, especially at the higher resonance frequency. The resonance frequency values obtained by the experiment are lower than the theoretical values. (3) Similarly to the common jet impingement, the convective heat transfer coefficients at the target surface impinged by the synthetic jet also take on up-down tendency varying with the jet-to-surface spacing increment. But the jet-to-surface spacing ratio for optimum cooling achievement is greater and the cooling action region is wider than the former, indicating that the synthetic jet in- troduces a stronger entrainment and more vigorous penetration in the surrounding fluid.     

基于合成射流风力机翼型气动特性的数值模拟

在翼型上引入射流,以较小流动干扰对翼型表面绕流进行主动流动控制,从而达到延迟失速、抑制分离、增升减阻的目的.通过数值模拟方法,分析了合成射流中的参数射流偏角、动量系数和无量纲频率对翼型气动特性的影响.结果表明,合理地选择射流参数可以达到抑制翼型流动分离、实现增升减阻的目的,得出了相关参数与翼型特性之间的关系曲线,为下一步射流器的选择与控制提供了一些有意义的帮助.     

Experimental investigations on separation control and flow structure around a circular cylinder with synthetic jet

Circular cylinder separation control and flow structure influenced by the synthetic jet have been experimentally investigated in a water channel. The synthetic jet issues from a slot and ejects toward upstream from the front stagnation point of the cylinder. It has been found that, similar to the traditional synthetic jet which is positioned near the separation point or inside the separation region, the present synthetic jet arrangement constitutes an efficient way to control flow separation of the circular cylinder, but with a different control mechanism. The present synthetic jet leads to an upstream displacement of the front stagnation point and the formation of a vortex pair near both sides of the exit orifice. When Re _u based on the synthetic jet average exit orifice velocity is about lower than 43, a closed envelope forms in front of the windward side of the cylinder during the blowing cycle of synthetic jet, which acts as an apparent modification for the cylinder configuration. When Re _u is high enough, an open envelope forms upstream of the cylinder, and the flow around the cylinder becomes much energetic. Thus, regardless of Re _u, the present synthetic jet can improve separation for flow around a circular cylinder. With regard to the leeward side, as Re _u increases, the flow separation region behind the cylinder gradually disappears. The flow over cylinder may be fully attached when the open envelope forms upstream of the cylinder and Re _u is greater than 344. Then, the flow past the cylinder will converge near the back stagnation point of the cylinder, where a new vortex pair shedding periodically is generated due to the high shear layer. Recommended by Prof. DONG ZengNan, Member of Editorial Committee of Science in China, Series E: Technological Sciences Supported by the National Natural Science Foundation of China (Grant No. 10425207)     

Effect of atomization gas pressure variation on gas flow field in supersonic gas atomization

In this paper, a computational fluid flow model was adopted to investigate the effect of varying atomization gas pressure (P0) on the gas flow field in supersonic gas atomization. The influence of P0 on static pressure and velocity magnitude of the central axis of the flow field was also examined. The numerical results indicate that the maximum gas velocity within the gas field increases with increasing P0. The aspiration pressure (ΔP) is found to decrease as P0 increases at a lower atomization gas pressure...     

人工压缩法计算突扩管道流

使用人工压缩法计算了突扩管道流.对计算所得不同雷诺数下的等压线图和流线图进行了对比分析,结果表明,在扩张截面的拐点处形成了低压区,扩张后在侧壁右侧形成了涡,且Re数越小涡越小,Re数越小涡心的位置离侧壁越近.同时在计算中也发现,Re数较大时在出口处将形成回流区,收敛速度也变慢.     

水下喷气推进高速射流场数值研究

为建立航行体点火初期尾部流场结构的预测方法,并揭示水下燃气喷射非定常流场与推进航行体运动的相互关系,以简化的潜射火箭为研究模型,采用流体体积法（VOF）两相流模型结合动网格方法对系留状态和运动状态下的燃气喷射流场进行数值模拟,分析了两种状态下燃气喷射形成的复杂流场结构.结果显示,喷气推进航行体在水下发射时,喷口附近形成复杂的流动结构和演化过程,并伴有较大的压力脉动产生;航行体加速运动导致的边界变化对燃气喷射流场产生较大的影响.     

射流泵内部流动的数值模拟

全面考虑了射流泵的不规则几何形状和各结构尺寸对其性能的影响 ,采用贴体坐标变换技术 ,结合混合有限分析法和k-ε紊流模型 ,给出了一套有效的射流泵内部流动计算的数值方法 .算例表明 ,其结果与实验值吻合较好 .     

射流泵内流场的大涡模拟

阐述了二维弱可压缩流体流动控制方程和大涡模拟湍流模型.基于该模型对射流泵各种运行工况进行了一系列数值模拟计算.计算中模拟了异常边界条件下射流泵的流场特性,重点模拟喷嘴出口回流旋涡并给出了可视化描述.对不同计算网格数和大涡模拟系数对计算结果的影响也作了论述.提出的网格生成和数值模拟方法具有较高的效率,计算结果可靠.     

仿生射流表面孔径与射流速度耦合减阻特性数值模拟

针对仿生射流表面流场问题,基于非光滑表面减阻的仿生学理论,对鲨鱼鳃裂部位射流特征进行分析研究,建立具有类似于鲨鱼腮裂部位射流特征的仿生射流表面模型及可拓模型.利用SST k-ω湍流模型对仿生射流表面模型进行数值模拟,在主流场速度为20 m/s时,分析了不同射流孔径与不同射流速度耦合情况对壁面摩擦阻力、压差阻力及减阻率的影响,并对仿生射流表面减阻机理进行分析.研究表明在射流孔为5 mm时与射流速度耦合情况下的平均减阻率最大,为11.566%,同时为仿生射流表面多因素耦合情况下的减阻特性研究奠定基础.     

基于仿生学原理的射流表面减阻性能研究

针对仿生射流表面减阻问题,建立仿生射流表面模型,利用SST k-ω湍流模型对其进行数值模拟,所得射流速度曲线与实验数据吻合良好。研究射流流体对边界层厚度的影响规律,探讨仿生射流表面的减阻机理。利用4因素3水平的正交试验,对射流表面和光滑表面摩擦阻力进行对比分析,得到了射流模型参数对减阻效果和节能效果的影响规律:在不考虑外加射流能量的情况下最大减阻率达50.41%;射流速度对节能效果的影响最大,主流速度对节能效果的影响其次,节能效率与主流速度成正比,最大节能效率为276。射流改变了边界层内的流场结构,使得射流表面的边界层厚度增大,垂直于射流表面的速度梯度减小,摩擦阻力减小。     

射流主动流动控制对舰船甲板流场的影响

随着舰船的发展和大量应用,舰船甲板流场的分析与控制的重要性进一步凸显出来。为改善舰船甲板流场,提出了一种新型的基于射流装置的主动流动控制方法,并以直升机桨盘位置为例分析了不同射流装置参数对于直升机桨盘流场优化的效果。首先基于Navier-Stokes方程建立了舰载直升机甲板流场的数值模型,以研究基于射流主动流动控制对舰船甲板流场的影响。然后该方法选取k-ε湍流模型,并通过算例验证了方法的有效性。最后模拟得到添加射流装置的舰船甲板流场流线与速度分布,结合流场信息对旋翼受力的影响对比分析了加装射流装置对舰船甲板流场的流动控制作用。结果表明：上射流的添加可以使得甲板流场中回流区的影响范围减小,从而使得桨盘流场速度梯度减小;桨盘流场速度梯度的减小可以有效降低旋翼气动力变化和响应水平;不同的来流角下添加上射流装置均能通过控制甲板流场从而减小响应,提高直升机的安全性。射流速度对流场控制效果影响显著,应结合射流装置安装位置选取最优射流速度从而达到较好的控制效果。     

城市燃气管道喷射火事故后果分析

高压下的城市燃气如果泄露，气体在裂口处被点燃则形成喷射火，对管道周围人员和财产安全造成极大威胁。本文运用喷射火焰对目标的入射热辐射强度计算模型，给出了火灾伤害半径和伤害面积，进而根据城市街区平均人员密度和平均财产密度确定喷射火事故造成的人员伤亡数量和财产损失程度，为城市燃气管道风险评价提供重要的依据。     

城市燃气管道喷射火事故后果分析

高压下的城市燃气如果泄露,气体在裂口处被点燃则形成喷射火,对管道周围人员和财产安全造成极大威胁。本文运用喷射火焰对目标的入射热辐射强度计算模型,给出了火灾伤害半径和伤害面积,进而根据城市街区平均人员密度和平均财产密度确定喷射火事故造成的人员伤亡数量和财产损失程度,为城市燃气管道风险评价提供重要的依据。     

Numerical investigation of cavity flow at subsonic and transonic speeds

Based on finite volume method,subsonic and transonic flow in 3-D cavity of different lengthto-depth ratios are numerically investigated by using Navier-Stokes equations with k-ωSST two-equation turbulence model and coupled implicit algorithm.The cavity streamline patterns and the static pressure coefficient distributions on the cavity floor are shown,and the flow characteristics of the cavity and the floor pressure coefficient distributions are analyzed.Numerical results demonstrate that the flow characteristics of the cavity at subsonic and transonic speeds are different from that of supersonic ones;length-to-depth ratio is the main factor that affects the flow characteristics of the cavity at subsonic and transonic speeds and causes changes of the cavity flow type;Mach number has a neglectable effect on the cavity flow fields at subsonic and transonic speeds and the cavity floor pressure distributions.     

MPI方式压缩天然气喷流的研究

在Witze亚音速空气喷流模型的基础上，经密度及超音速膨胀的影响等修正后，提出了超音速非稳定天然气喷流的数学模型，解析了从不同喷孔半径的天然气喷油器喷出的天然气喷流的贯穿距离等；并使用能够观察到天然气－空气密度梯度的纹影方法得到了数组天然气喷流的纹影照片，经画像处理得到的实验结果和理论计算结果非常一致。     

一种合成射流压电微泵关键结构参数确定方法

为增大无阀微泵流量,改进合成射流微泵设计方法,设计一种基于合成射流压电激励器的微泵结构,并提出关键结构参数的确定方法.在合成射流激励器流场模拟结果基础上,绘制其轴线上的轴向瞬时速度变化曲线以及出口横截面上的轴向速度分布曲线,利用轴线上轴向速度稳定点以及出口横截面上轴向速度分布曲线的零点确定最佳泵腔高度和出口直径.对所选用的合成射流激励器流场进行三维数值模拟,结果表明:利用该方法得到微泵结构的最佳泵腔高度为7 mm,最佳出口直径为1.78 mm.在零背压下,当雷诺数为225、频率为100 Hz时,该合成射流微泵流量可达32.1 m L/min.数值仿真与实验对比验证了方法的可行性.利用该方法可以有效地确定该类微泵在大流量且连续稳定出流性能下的关键结构尺寸.     

生物聚合物对高含水量淤泥压缩渗透特性的影响

生物聚合物可以有效改善土体的力学性质。为评估生物聚合物改性淤泥在实际工程中的应用前景,研究黄原胶(XG)、海藻酸钠(SA)、阳离子瓜尔胶(GG)对高含水量淤泥压缩性和渗透性的影响。通过一维渗透固结试验,探究生物聚合物种类及掺量对土体结构屈服应力、压缩指数、渗透系数等指标的影响。同时,通过电镜扫描(SEM)和压汞试验(MIP),分析生物聚合物改性高含水量淤泥的微观机制。结果表明,生物聚合物改性淤泥中的黏土-聚合物网络结构使其压缩性降低。随着掺量的增加,改性淤泥结构屈服应力增大,压缩性减小。当竖向有效应力大于结构屈服应力时,改性淤泥C_c显著增大,且随着掺量的变大而提高。生物聚合物改性淤泥渗透性明显降低,所用聚合物中XG的效果最显著,在1.5%掺量时达到两个数量级。     

相变情况的液－液气射流泵基本方程研究

采用准二维二相非均匀变密度模型首次导出了相变情况的液—液气射流泵基本方程．该方程具有普遍性．应用计算数学方法运用电算求出了它的数值解，并通过试验进行了初步验证     

旋转气流下AOD熔池内流体流动和混合特性的水模拟研究

在以足够高的运动相似性对双枪呀吹非旋转气流１８ｔ ＡＯＤ炉内流体流动和混合特性水模拟研究的基础上，对采用套管式螺旋板型喷枪时ＡＯＤ熔池内流体流动和混合特性作了水模拟研究，所用喷枪的中心管（主枪）内置有一厚度为０．２ｍｍ的黄铜质螺旋型板条，相应的螺距为４６．５７ｍｍ，环缝（副枪）与原模型喷枪相同。考察耻旋转射流下吹气量和枪间夹角的影响及螺旋型喷枪对实际过程的适用性。结果表明，在相同的吹气量下，与非旋     

射流陀螺流场的有限元分析

针对射流陀螺敏感元件内的流场进行了有限元分析。采用有限元方法,利用ANSYS—FLOTRANCFD软件,通过建模、划分网格、加载和求解等途径,计算了敏感元件内的流场分布。计算结果表明：由喷嘴喷出的射流柱呈喇叭状扩散,由出气孔排出时,射流流速衰减为喷嘴处流速的28．4％;出气孔截面气流最低流速为最高流速的19％;其余未经出气孔排出的部分滞留在敏感元件内形成了涡流。