二维高超声速后台阶表面传热特性实验研究

高超声速后台阶流动是大气层内高速飞行器发动机设计、表面热防护以及高超声速拦截器红外成像窗口气动光学效应校正等诸多先进高超声速技术研发过程中所涉及的一类基础流动问题. 研究高超声速后台阶流动特性对有效提升飞行器综合性能, 进一步掌握高超声速流动机理具有重大基础 意义. 本文以二维高超声速后台阶流动为研究对象, 在KD-01高超声速激波风洞中测量了二维后台阶模型表面传热系数和表面静压, 并将实测台阶下游表面传热系数分布同采用高超声速边界层理论所得估计值进行了比较. 为进一步验证实验结果, 使用NPLS技术测量了其中一种实验状态下台阶周围流动结构. 研究发现, 对于二维高超声速后台阶流动, 台阶下游表面传热分布受台阶处边界层外缘流动特性的直接影响; 在台阶下游分离区和再附区内, 气体黏性占主导作用; 在台阶下游远场区域, 边界层流动特性趋同于平板边界层; 下游边界层基本结构取决于台阶处边界层相对厚度. 对高超声速后台阶流动, 若使用数值模拟方法研究气动热问题, 应当使用湍流模型.     

Experimental investigation of oscillatory air flow in a bronchial tube model with HFOV mode

Mechanical ventilations for artificial respiration have been developed to improve the medical treatment of the patients showing respiratory disorder. In various types of ventilation, High Frequency Oscillatory Ventilation (HFOV) is one of the most effective techniques of medical care for pulmonary disease patients, especially, infantsor premature infants. HFOV is a ventilation technique with high breathing rate in comparison with the normal breathing rate. Some successful studies have focused on the effect of treatment using HFOV However, the mechanism of gas exchange in bronchial tube under the medical treatment by HFOV has not been clarified. In this study, the oscillatory flow in a micro-channel model of bronchial with single bifurcation in HFOV mode has been investigated experimentally with micro Particle Image Velocimetry (micro PIV) technique. The phase averaged velocity profiles changing with the driving frequency of HFOV have been inves tigated.     

Experimental investigation of magnetohydrodynamic action on a heat flux toward the surface of a model

Experimental data for magnetohydrodynamic (MHD) action on a supersonic nitrogen flow about an axisymmetric model are presented. The experiments were carried out in the Big Shock Tube (Ioffe Physical-Technical Institute), at the end of which a test section equipped with a supersonic nozzle was mounted. A test conic model coupled with a cylinder is attached to the output cross section of the nozzle. A magnetic field is produced by a solenoid placed on the cylindrical part of the model through which a pulsed current due to an external voltage source discharging passes. Electrodes on the conic part of the model initiate a gas discharge, which rotates about the axis of the model in the solenoidal magnetic field. The influence of the magnetic field on the gasdynamic pattern of the flow near the model and on the heat flux toward its surface is investigated. Schlieren patterns of the flow about the model, photographic scans of the discharge glow, and heat flux measurements are taken. It is found that the magnetic field has an effect on the gasdynamic pattern of the flow near the model and on the heat flux toward its surface. The dependence of MHD effects on the external voltage polarity is also revealed.     

Experimental investigation of a hypersonic I-shaped configuration with a waverider compression surface

Lift-to-drag ratio (L/D) is nearly the most important index in determining the aerodynamic performance of a hypersonic flight vehicle,because the flight distance is linearly proportional to the L/D according to Breguet's equation.In general,the higher the L/D of a vehicle,the greater the flight range if the specific impulse,structural mass ratio,and flight velocity are given.Naturally,the pursuit of a high L/D for hypersonic vehicles has never ceased [1,2].     

高速飞行器磁控阻力特性

采用低磁雷诺数磁流体数学模型,对外加磁场下的高超声速半球体流场进行数值模拟.选取三种简单理想磁场(轴向、径向、周向均布磁场),分析了不同磁场类型对流场结构、气动阻力与洛伦兹阻力的影响及作用机理.研究发现,轴向磁场径向"挤压"效应使得激波外形凸出,且壁面静压存在"饱和现象";径向磁场存在轴向"外推"效应,较大的磁场强度会导致肩部形成高温区;周向磁场下感应电场的存在导致增阻效果很差.进而对比了两种相同驻点磁感应强度特殊分布磁场(偶极子磁场、螺线管磁场)下的流场,发现了不同于理想磁场的径向"扩张"效应.按增阻效果从大到小依次为径向磁场、螺线管磁场、轴向磁场、偶极子磁场、周向磁场.     

高超声速飞行器磁控热防护系统建模分析

针对高超声速飞行器防热, 搭建了螺线管磁控热防护系统的物理模型. 采用低磁雷诺数磁流体数学模型, 分析了外加磁场强度及磁场形态对磁控热防护效果的影响. 对比了三种磁场类型(磁偶极子、螺线管、均布磁场)下磁控热防护效果的差异, 分析了螺线管几何参数对磁控热防护效果的影响. 研究表明, 磁场降低表面热流作用存在“饱和现象”; 三种磁场形态的磁控热防护能力从小到大依次为磁偶极子、螺线管、均布磁场; 相同驻点磁感应强度条件下, 增大螺线管半径有利于提高磁控热防护效果, 缩短螺线管与驻点距离不利于驻点和肩部防热, 螺线管长度对磁控热防护效果影响相对较小.     

Numerical investigation of the air injection effect on the cavitating flow in Francis hydro turbine

At full and over load operating points, some Francis turbines experience strong self-excited pressure and power oscillations. These oscillations are occuring due to the hydrodynamic instability of the cavitating fluid flow. In many cases, the amplitude of such pulsations may be reduced substantially during the turbine operation by the air injection/ admission below the runner. Such an effect is investigated numerically in the present work. To this end, the hybrid one-three-dimensional model of the flow of the mixture “liquid?vapor” in the duct of a hydroelectric power station, which was proposed previously by the present authors, is augmented by the second gaseous component — the noncondensable air. The boundary conditions and the numerical method for solving the equations of the model are described. To check the accuracy of computing the interface “liquid?gas”, the numerical method was applied at first for solving the dam break problem. The algorithm was then used for modeling the flow in a hydraulic turbine with air injection below the runner. It is shown that with increasing flow rate of the injected air, the amplitude of pressure pulsations decreases. The mechanism of the flow structure alteration in the draft tube cone has been elucidated, which leads to flow stabilization at air injection.     

Experimental study of different control methods for hypersonic air inlets

An experimental study of different control methods for hypersonic air inlets aimed at ensuring reliable starting of these apparatuses and improving their operating characteristics in the range of Mach numbers 2 to 8 is reported. Conditions for boundary-layer separation and possibilities for preventing this separation by using modified diffuser configurations and/or perforation bleedage are examined. An air-inlet model was tested for operation in an intermittent wind tunnel and in a blow-down wind tunnel respectively in the Mach-number ranges 2 to 6 and 5 to 8. Distributions of static and total air pressures on the walls of the model and in several cross sections were measured, together with air flow coefficients and total-pressure recovery coefficients. Perforation bleedage is shown to offer an efficient means to facilitate air-inlet starting. Perforation bleed has enabled a more than two-fold increase in the air flow coefficient on the model with sidewalls. A perforation-bleed panel installed closer to the air-inlet throat proved to be more efficient. The possibility of sudden starting of the air-inlet apparatus was checked in the intermittent wind tunnel; it was shown that, here, sudden starting could be realized. The data obtained in the intermittent wind tunnel proved to be consistent with data obtained in the blow-down wind tunnel with up to 150-ms blowdown time. This work was supported by the International Scientific and Engineering Center (Contract No. 887) and by MBDA, France.     

Experimental investigation of a swirling flow in a cubic container

A flow induced by a rotating disk mounted at the top of a cubic container totally filled with a liquid is studied experimentally. The flow pattern is visualized for Reynolds numbers in the interval 1500–6000, and the velocity variation along the axis of the container, which coincides with the axis of revolution of the disk, is observed by means of Doppler laser anemometry (DLA). As Re grows, the velocity axial component starts fluctuating because of the vortex core precession. The breakdown of the vortex helical structure becomes pronounced at Re>4000 without the formation of the return flow region (vortex breakdown bubble) at the axis. With the Reynolds number and the container height-to-disk radius ratio being the same, the axial flow patterns in standard cylindrical [1] and cubic containers differ radically. In the latter vessel at low Re, the steady flow regime and axisymmetric bubble breakdown of the vortex structure near the axis are absent.     

Pulsating optical source appearing under continuous laser energy supply to a hypersonic air flow

The spatio-temporal gasdynamic structures of plasma formations produced in a hypersonic air flow by a focused high-power laser beam are analyzed numerically using the model of inviscid non-heat-conducting equilibrium radiating air. The reasons for the emergence of pulsating gasdynamic nonuniformity in the region between the bow shock wave and the intense laser radiation absorption zone are investigated.     

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

The experimental study focuses on the heat flux on a double cone blunt body in the presence of tangential-slot super- sonic injection into hypersonic flow. The tests are conducted in a contoured axisymmetric nozzle with Mach numbers of 7.3 and 8.1, and the total temperature is about 900 K. The injection Mach number is 3.2, and total temperature is 300 K. A constant voltage circuit is developed to supply the temperature detectors instead of the normally used constant current circuit. The schlieren photographs are presented additionally to visualize the flow and help analyze the pressure relationship between the cooling flow and the main flow. The dependence of the film-cooling effectiveness on flow parameters, i.e. the blow ratio, the convective Mach number, and the attack angle, is determined. A semi-empirical formula is tested by the present data, and is improved for a better correlation.     

Generation of a gas-discharge air plasma in a supersonic magnetohydrodynamic channel

A method for ionizing a supersonic air flow is developed to obtain a flow conductivity sufficient for a magnetohydrodynamic (MHD) interaction and generation of a magnetically induced current in a supersonic nozzle. The efficiencies of several (high-frequency, multiple-pulse high-voltage, and combined) methods for initiating a gas discharge used for ionizing air are compared. The supersonic air flow is ionized by a pulse-periodic high-voltage discharge producing an air plasma with a conductivity of up to 20 S/m. The experimentally obtained magnetically induced current of 0.1 A is smaller than the rated value owing to the Hall effect and the electrode voltage drop. The theoretical possibility of obtaining a magnetically induced current in a supersonic air flow is demonstrated; such currents can subsequently be used for controlling the flow in air inlets of aircraft.     

Experimental investigation of the effect of small-obstacle-induced vortex sheet on the separated flow in cavity

In the present paper, we report results of an experimental study of the influence which a vortex-generating element installed upstream of the main obstacle has on the separated flow and heat transfer in a cross-flow cavitytrench. The element was a small cross-flow rib whose height was an order of magnitude smaller than the depth of the cavity. In the experiments, the variable parameters were the angle of inclination of the frontal and rear walls of the cavity, the rib height, and the rib-to-cavity distance. It is shown that the introduction of additional vortical perturbations into the recirculation zone leads to a substantial modification of both the vortex production process and the distributions of pressure and heat-transfer coefficients. Optimal height of the mini-turbulizer and its optimal location are defined by the fall of the re-attachment point of mini-rib-generated flow onto the rear wall of cavity. In the latter situation, the maximal value of the heat-transfer coefficient increases as compared to the case with no vortex generator used, the increase amounting to 30 %.     

冷却物冷藏间冷风机的空气除霜实验研究

冷却物冷藏间以贮藏果蔬为主,当贮藏品种产于热带地区,贮藏温度高于0℃。由于贮藏温度距水的冰点不远,制冷系统的蒸发温度会低于冰点,在工作过程中蒸发器表面必然结霜。文中对冷间温度高于冰点,蒸发温度低于冰点的冷库制冷系统,进行了空气除霜和"依次除霜法"实验,通过冷风机回风区空气温度、冷风机蒸发管组翅片温度的测量,结合肉眼观察认为,库温为5℃的情况下,依靠制冷压缩机停机阶段,冷风机风扇常开,能够基本除掉上次制冷过程产生的结霜,当制冷系统规律工作8小时,前期制冷过程积累的结冰可以通过"依次除霜法"依次关闭除霜冷风机的供液电磁阀15分钟,在保证库房降温的前提下,能够彻底除掉蒸发器表面的结霜。     

高超声速条件下7°直圆锥边界层转捩实验研究

在Ma=6低噪声风洞中开展了半锥角7?的直圆锥边界层转捩相关实验研究.利用响应频率达到MHz量级的高频压力传感器对圆锥壁面脉动压力进行了测量,研究了高超声速圆锥边界层中扰动波的发展过程.结果表明:高超声速圆锥边界层中第二模态扰动波产生的位置以及扰动波特征频率和波长等参数受雷诺数影响较大,当单位雷诺数从2×106m~(-1)增加到8×106m~(-1)时,第二模态波的特征频率从55 k Hz增加到226 k Hz;随着单位雷诺数增加,边界层中扰动增长速度加快,第二模态波出现在圆锥表面更靠近上游的位置;相同单位雷诺数条件下,随着第二模态波的向下游传播,其特征频率逐渐减小.通过对比发现自由来流湍流度对边界层中扰动波的发展同样有较大影响,自由来流湍流度降低,边界层中的第二模态波的特征频率明显减小.利用互相关分析得出第二模态扰动波在边界层中的传播速度大约为当地主流速度的0.8—0.9倍.在1?小攻角条件下,圆锥迎风面和背风面边界层发展呈现出明显的差异,背风面边界层中扰动发展提前,第二模态波出现在更靠近上游的位置,而迎风面中扰动发展受到抑制,第二模态波特征频率更大.