无阀微泵腔内气泡对周期驱动压力的影响

气泡的存在使无阀微泵的工作性能和使用寿命大大降低, 甚至无法正常工作. 为了合理地预测无阀微泵腔内气泡对周期驱动压力的影响, 给出了用来描述收缩管/扩张管型无阀压电微泵的数学模型, 包括泵腔体积变化、连续性方程、流体有效体积弹性模量以及锥管阻力系数的计算. 同时, 分析了腔内不同气泡体积对无阀微泵周期驱动压力的影响, 并对两个气泡进入无阀微泵泵腔时压力脉动过程进行了仿真和试验研究. 通过仿真结果与试验数据的比较表明, 所提出的存在气泡时无阀微泵数学模型及仿真方法是合理的. 关键词： 无阀微泵 气泡 压力脉动     

Modeling and study of dynamic performance of a valveless micropump

This work presents an approximate nonlinear analytical model for the problem of fluid-structural interaction in a valveless micropump. The model is constructed using the lumped-mass approach and takes into account the inertial force and time variation of mass density of the working fluid within the micropump chamber, pressure viscous losses of the flow through the diffuser/nozzle elements and the structural geometric nonlinearity due to the membrane mid-plane stretching. It consists of a set of coupled partial integro-differential equations which is reduced to a third order nonlinear coupled fluid-plate vibration equation by using the assumed mode method to approximate the plate dynamic deflection. An approximate analytical solution for the nonlinear vibration model is carried out using the harmonic balance method and is used to investigate the effect of various system parameters on the performance of the micropump. The obtained model and approximate analytical results are compared with those available in the open literature. The approximate analytical results show that, depending on the micropump physical parameters and membrane driving frequency, the working fluid stiffness, which arise in the present model as a result of taking into account the variation of the fluid density with time, and the membrane geometric nonlinearity can have significant effects on the predicted micropump performance and can lead to a complex nonlinear dynamic behavior. The accuracy of these results is subject to a future numerical validation of the presented approximate theoretical model.     

涡轮叶片前缘阵列冲击冷却流动及传热特性数值研究

本文采用SST湍流模型模拟了类前缘通道内蒸汽射流阵列冲击冷却的流动与传热特性,分析了雷诺数(Re=10000~50000)、孔径比(d/H=0.5~0.9)和孔间距比(S/H=2~6)对流动及传热性能的影响规律,得到了相应的传热和摩擦关联式。结果表明:在不同雷诺数下,d/H从0.5到0.9变化时,通道压力损失系数降低了76%~79%,靶面平均努塞尔数降低了45%~49%;S/H从2增至6时,通道压力损失系数增加了1.64~1.92倍,靶面平均努塞尔数增加了54%~64%;增大d/H、减小S/H可有效提高类前缘通道蒸汽冲击冷却的综合热力系数。本文研究结果可为未来先进燃气轮机高温涡轮叶片蒸汽冷却结构的设计提供参考和借鉴。     

Characteristics of a magnetogasdynamic diffuser under different modes of electric current switching

This paper elaborates upon a previous investigation into the influence of external electric and magnetic fields on a flow through a supersonic diffuser. The aim of the present study is to correlate a change in the configuration of a shock wave emerging near the diffuser inlet at magnetohydrodynamic interaction with the amount of force and energy actions and with total pressure losses. For this purpose, the main parameters of the shock wave structure and the total pressure are measured at the diffuser outlet when the flow is subjected to magnetic and electric fields of various strengths at different routes of current passage. In the experiments, a shock tube with a supersonic nozzle is employed. The shock tube forms a flow behind the shock wave reflecting from the end of the tube, which terminates in the nozzle. The diffuser is located directly downstream of the nozzle. The investigation is carried out in xenon. The flow is subjected to external fields at the inlet of the diffuser. The shock wave structure is visualized by frame sweeping of Schlieren patterns of the flow. The total pressure is measured with a piezoelectric transducer located at the end of the channel. The results obtained make it possible to optimize the action on the flow in terms of power consumption and total pressure losses for a given design of the diffuser.     

布水器性能测试平台设计及应用

由于需要优化设计布水器,对其性能参数进行了深入研究,设计安装了布水器性能测试平台及测温系统.该平台可用于对比分析不同参数、不同类型布水器的斜温层效果,通过相关模拟计算及实验,初步得出相同出口流速的径向型布水器在大雷诺数也可以取得较好的斜温层效果,另外,在相同出口流速及一定的容忍度下,八角形布水器的斜温层效果优于径向型,而在相同雷诺数下,径向型布水器的分层效果优于八角形布水器.     

无缓冲气COIL扩压器流场数值模拟

 以无缓冲气化学氧碘激光器(COIL)实验器件的数据计算得到的混合喷管出口参数平均值作为光腔入口条件，对6种不同构型的扩压器从光腔入口至扩压器出口的流场进行了数值模拟，得出了各流场参数分布；对不同构型扩压器的流场特点、总压恢复性能进行了分析；研究了扩压器出口背压对流场参数的影响。结果表明：对于主流无缓冲气的COIL，等截面扩压器具有较好的压力恢复性能；增大扩压器出口背压可以使扩压器的压力恢复性能提高，然而，较高的背压使激波串向光腔方向移动，从而使光腔流场受到干扰，影响光腔的光束质量。     

喷管、光腔及压力恢复系统一体化设计

 对氧碘化学激光（COIL）系统的喷管和扩压器进行了3维数值模拟，对比分析了几种喷管和扩压器的设计方案，计算了从光腔入口到扩压器出口的气动力学过程。光腔内主副气流借助翼片辅助方法实现充分混合，翼片长0.77 cm，宽0.254 cm，满足气流混合要求。扩压器是1/4结构，即计算区域为入口截面高30 mm、宽60 mm的长方型，之后等截面延续500 mm，然后宽度仍然不变，高度以4°角扩张，延续700 mm，最终的出口截面高度为79 mm。采用空气入射，入口处（光腔出口）马赫数3.2，静压1 232 Pa，温度110 K；计算得到出口处总压13 300 Pa，总温300 K。结果表明：出口静压超出入口静压近10倍，该扩压器很好地起到了压力恢复的作用，而总压下降到1/4.5左右（从60 648 Pa到13 300 Pa），从而能够减轻后续的引射器的工作压力。利用高光腔压力设计可以减少一级引射器，达到整个系统小型化设计的目的。     

喷射器扩压室结构设计优化研究

扩压室对喷射器内混合流体的降速增压有着重要影响。本文基于真实流体物性,采用气体动力学方法建立改进的一维混合模型并提出扩压室结构设计优化方法。将模型计算结果与文献实验值对比验证了模型的准确性。分析了扩压室结构参数与喷射器膨胀比、喷嘴喉部直径和混合室直径之间的关系。结果表明,扩压室半锥角α随膨胀比pg/pe、扩压室出口直径与混合室出口直径之比dc/dc3以及喷嘴喉部直径与混合室直径之比dg0/dc3的增大而减小;扩压室长度Ld随膨胀比pg/pe、直径比dc/dc3及喷嘴喉部直径dg0的增大而增大,而随着混合室直径dc3的增大而减小或近似保持不变。     

脉冲流冲击冷却换热的液晶显示实验研究

采用热色液晶定量测温技术对稳态及脉冲式空气-氮气圆形浸没射流冲击冷却换热进行了实验研究.脉冲射流的实验结果表明,对于喷嘴直径D=3 mm的情形,无论脉冲频率高低,均无强化换热效果;对于D=I0 mm的情形,在较高Re数时出现个别工况的驻点换热强化.脉冲射流表现出换热系数沿径向分布趋于均匀的特点.     

带突扩段有叶扩压器的设计与分析

本文针对离心压气机采用突扩转接段后的设计问题,初步探讨了其内部流动规律,进行了型线的优化设计。首先进行的子午面计算,确定了扩压器的型线,然后对无叶扩压器作了三维数值模拟,保证了叶片进口参数的平滑均匀。最后完成了带叶扩压器的三维计算。数值计算结果表明,出口马赫数、总压恢复系数和出气角均达到了设计要求。设计的完成为复杂扩压系统的设计与数值模拟打下了良好基础。     

Characterization of a diffuser flow by time-resolved PIV

Computational fluid dynamics is extensively used in the design methodology of medical devices. However, for such applications, the predictive capabilities of CFD codes are highly dependent upon geometry, which most of the time is extremely complex, and flow conditions. The study concerns a ventricular assist device (VAD) where the exit flow, generated through a diffuser, is of particular importance for blood damage predictions. The difficulty to predict the flow lies in the fact that the Reynolds number range includes the transition Reynolds number of the separated diffuser flow as well as the critical Reynolds number of pipe flows. In order to choose the appropriate CFD methodology in terms of flow hypothesis and turbulence model, an experimental setup of the diffuser was built to run PIV velocity measurements and to analyze the flow pattern with the influence of Reynolds number. The flow is described with mean and variance values of the in-plane velocity components and timeresolved results are used to visualize the development of unsteady phenomena introduced in the diffuser separated region. An optimal filter is also used to remove noise in measured velocity vector fields.     

Realization of an advanced nozzle concept for compact chemical oxygen iodine laser

Conventional supersonic chemical oxygen–iodine lasers (SCOIL) are not only low-pressure systems, with cavity pressure of 2–3 Torr and Mach number of approximately 1.5, but also are high-throughput systems with a typical laser power per unit evacuation capacity of nearly 1 J/l, thus demanding high capacity vacuum systems which mainly determine the compactness of the system. These conventional nozzle-based systems usually require a minimum of a two-stage ejector system for realization of atmospheric pressure recovery in a SCOIL. Typically for a 500 W class SCOIL, a first stage requires a motive gas flow (air) of 120 gm/s to entrain a laser gas flow of 3 g/s and is capable of achieving the pressure recovery in the range of 60–80 Torr. On the other hand, the second stage ejector requires 4.5 kg/s of motive gas (air) to achieve atmospheric pressure recovery. An advanced nozzle, also known as ejector nozzle, suitable for a 500 W-class SCOIL employing an active medium flow of nearly 12 g/s, has been developed and used instead of a conventional slit nozzle. The nozzle has been tested in both cold as well as hot run conditions of SCOIL, achieving a typical cavity pressure of nearly 10 Torr, stagnation pressure of approximately 85 Torr and a cavity Mach number of 2.5. The present study details the gas dynamic aspects of this ejector nozzle and highlights its potential as a SCOIL pressure recovery device. This nozzle in conjunction with a diffuser is capable of achieving pressure recovery equivalent to a more cumbersome first stage of the pressure recovery system used in the case of a conventional slit nozzle-based system. Thus, use of this nozzle in place of a conventional slit nozzle can achieve atmospheric discharge using a single stage ejector system, thereby making the pressure recovery system quite compact.     

滴形颗粒在通道中沉降的格子Boltzmann-虚拟区域方法模拟

采用格子Boltzmann-虚拟区域方法对滴形颗粒在垂直通道中的沉降过程进行直接数值模拟.通过格子Boltzmann方法求解N-S方程,流体与固体之间的相互作用通过虚拟区域方法描述.研究雷诺数在10^-2到100范围内颗粒形状因子对其摩擦系数和阻力系数的影响.为便于比较,给出了圆形颗粒沉降的结果.结果发现,当雷诺数小于1的时候,颗粒的摩擦系数始终保持常数,而当雷诺数大于1时摩擦系数随雷诺数的增大而增大.此外,当雷诺数小于约30时圆形颗粒的摩擦系数和阻力系数均小于滴形颗粒,而当雷诺数大于30时情况正好相反.颗粒周围的压力分布证明了这一结论.     

光腔与扩压器的一体化优化数值模拟

采用数值模拟方法对化学氧碘化学激光器光腔通道、超声速扩压器一体化方案的优化展开研究,对扩压器的角度、构型、背压等参数对扩压性能的影响以及对光腔内流场的影响进行计算和分析。研究结果表明:传统的直接扩散型以及平直段+扩散段型的超声速扩压器,抵抗背压影响的能力较弱,且光腔出口处静压急剧升高,影响了光腔内的流场;通过在平直段+扩散段型的超声速扩压器的平直段部分,插入数片楔形体,可以将扩压器的工作背压提升33%以上,且可以有效地隔绝扩压器对光腔内流场的不利影响,从而使光腔下游的逆压梯度大大降低;同时,由于缩短了扩压器的长度,扩压器的总压损失明显降低,冷流状态下的总压恢复系数达到0.484。     

Detection of separation in S-duct diffusers using shear sensitive liquid crystals

In the present experimental investigation, shear sensitive liquid crystals have been successfully used to study the flow characteristics and detect separation in two-dimensional Sduct diffusers of different curvatures. Tapered-fin vortex generators in two different orientations were used to control flow separation that was observed on one of the curved walls of the diffuser. The results were verified by conventional oil flow visualization technique and excellent agreement was observed. In addition to visualization, detailed measurements that included wall static pressure, skin friction, diffuser exit total pressure and velocity distributions were taken in a uniform inlet flow with Reynolds number of 3.49 × 10⁵. These results are presented here in terms of skin friction distribution, distortion and total pressure loss coefficients. The extent of the separation zone (in terms of intensity of red distribution) in the diffuser with and without vortex generators (in both configurations) compared well with the Preston tube measurements. The present study demonstrates that shear sensitive liquid crystals can be efficiently used to study the flow physics in complex internal flows. In addition, the results also indicate that shear sensitive liquid crystals can be effectively used not only as flow visualization tool but also to gain quantitative information about the flow field in internal flows.     

An experimental study on convective heat transfer performance of steam and air flow in V-shaped rib roughened channels

An experimental study on heat transfer characteristics of steam and air flows in a V-shaped ribbed channels was conducted. The effects of Reynolds numbers and rib angles on heat transfer of steam and air were obtained. The area-averaged Nusselt numbers of steam flow at a Reynolds number of 12,000 were 13.9%, 20.6%, 27.1%, and 27.9% higher than those of air flow for rib angles of 90°, 75°, 60°, and 45°, respectively. The correlations for Nusselt number in terms of Reynolds number and rib angle for steam and air in V-shaped ribbed channels were developed.     

Effect of roughness elements on thermal and thermohydraulic performance of double pass solar air heater duct having discrete multi V-shaped and staggered rib roughness on both sides of the absorber plate

In this work, an experimental setup consisting of a double pass solar air heater duct provided with discrete multi V-shaped and staggered rib as artificial roughness on both sides of the absorber plate has been designed and fabricated. The parameters of interest investigated experimentally cover a wide range of Reynolds number (Re) from 2000 to 20000, relative staggered rib pitch (p’/p) from 0.2 to 0.8, relative staggered rib size (r/e) from 1 to 4, and relative roughness width (W/w) from 5 to 8. Experimental data related to heat transfer, pressure loss, and thermohydraulic performance has been determined. Substantial improvement has been obtained with some penalty of friction losses.     

Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

Abstract  

This paper describes experimental and numerical investigations into the multiple shock waves/turbulent boundary layer interaction in a supersonic inlet. The test model has a rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain the visualization images and static pressure data by using supersonic wind tunnel. Numerical simulation was performed by solving the RANS equations with the Menter’s SST turbulent model. The inflow condition was a free-stream Mach number of 2.5 and a unit Reynolds number of 7.6 × 10⁷/m. Numerical results showed good agreement with the experimental results. Based on this agreement, the flow characteristics which are often very difficult to obtain experimentally alone were analyzed with the aid of numerical simulation. The structures, pressure and velocity distributions, and total pressure loss of the pseudo-shock wave in the supersonic inlet were presented in detail from flow visualization images and static pressures.     

Experimental and computational visualization and frequency measurements of the jet oscillation inside a fluidic oscillator

PIV measurements and computational simulations (2D, unsteady Navier-Stokes) are performed to visualize the inherently unsteady jet oscillation inside a fluidic oscillator. Both the measurements and computations are obtained for a jet exit Reynolds number of 321, based on the maximum velocity and the nozzle width at the jet exit plane. The computed jet oscillation frequency is in close agreement with the measured PIV frequency. Formation of a pressure gradient across the jet is observed from the computations. The variation of the jet oscillation frequency with jet exit Reynolds number is also determined by single sensor hot-wire measurements inside the oscillation chamber.     

油基钻屑螺纹推进式换热器流动传热特性

对油基钻屑在螺纹推进式换热器内的流动换热过程进行了数值模拟,研究了螺杆转速、油基钻屑雷诺数Re和螺纹截面形状对流动换热的影响。结果表明:随着螺杆转速增加,传热系数、油基钻屑出口温度均增大;同时发现,当雷诺数Re<250时,壳侧Nusselt数随雷诺数Re增大而迅速增大,此后雷诺数对Nusselt数影响较小;Nusselt数随曲率比d_i/D增大而增大。为方便工程设计,利用数值结果给出了油基钻屑的流动换热关系式。