流体激波污泥改性工艺提高污泥水煤浆浓度的研究

利用碱性物质对污泥改性的基础上,采用流体激波改性工艺进行了提高污泥水煤浆浓度的研究。结果表明:与单独用碱性物质相比,采用以上组合方式对污泥进行改性大大提高了污泥改性效果。主要表现在经流体激波改性后,改性污泥黏度大幅下降,流动性明显改善;其次,经流体激波改性制备的污泥煤浆性能与单纯碱性物质改性相比,浓度至少提高了2.5%。这主要是因为污泥经流体激波改性后,在高压和超细粉碎的作用下,污泥中的聚丙烯酰胺部分降解,释放出部分自由水,改善了污泥成浆性,从而使污泥煤浆浓度进一步提高。

各向异性磁流体激波跃变关系的无量纲化求解

用无量纲化方法，推出了各向压力异性等离子体中磁流体激波跃变条件及其解析解的一种普遍而简单的形式，并讨论了它在各向同性等离子体中各种特殊情况下的结果．

磁流体斜激波的汇合

本文讨论磁流体快、慢激波的汇合作用规律，主要结论如下：（１）两个前向快激波汇合之后，形成一更强的前向快激波，尾随一前向慢稀疏波、一正接触间断（后侧密度大于前侧）、一后向慢激波和一后向快稀疏浚．（２）两个前向慢激波汇合之后，形成一更强的前向慢激波，尾随一正接触间断、一后向慢稀疏波和一后向快激波２在前向慢激波前方出现一前向快波，它或为稀疏浚（中、小激波角情况），或为激波（大激波角情况）．（３）前向快激波会追上前向慢激波而发生汇合，之后互换位置且强度减弱，尾随一正接触间断和一后向稀疏波对．

磁流体斜激波的碰撞

讨论了磁流体斜激波之间的碰撞及其与接触间断的相互作用规律，主要结论如下：（１）两个快激波碰撞后交换位置，同时出现一接触间断和一慢稀疏波对．（２）两个慢激波碰撞后交换位置且强度减弱，同时出现一接触间断和一块激波对．（３）一前向快激波与一后向慢激波碰撞后交换位置，快激波强度增加，慢激波强度减弱，同时出现一后向快激波、一负接触间断和一前向慢稀疏波．（４）一前向快激波与一正（负）接触间断相互作用后交换位置，快激波减弱，同时出现一后向快稀疏波（快激波）、一后向慢激波和一前向慢激波（慢稀疏波）．（５）一前向慢激波与一正（负）接触间断相互作用后交换位置，慢激波减弱，同时出现一后向慢稀疏波（慢激波）和一快稀疏波（快激波）对．

行星际中间激波的演化

本文采用特征线方法和激波装配法,对磁流体中间激波在行星际空间的演化过程进行数值模拟。主要结论如下:(1) 2→4型中间激波通过向下游发出后向慢压缩波使下游态磁场减幅,通过向上游发出前向快压缩波使上游态磁场增幅,以致2→4型中间激波迅速经导灭激波向慢激波转化;所发出的前向快压缩波经非线性变陡形成快激波。(2)1→3型中间激波首先通过向下游发出前向慢稀疏波而很快变成1→3=4型临界中间激波,并瞬间转变为由前向快激波和前向2→4型中间激波构成的激波系统。其中,2→4型中间激波可在其前导快激波的下游传播较远的距离,有可能为 IAU 附近的飞船观测到,但最终导灭激波转变为慢激波。

行星际高速流的演化

本文采用一维时变模型，对高速流在行星际空间的演化进行数值模拟．结果表明：１．高速流前沿演化成为由前向快、慢激波和后向快激波构成的激波系统，高速流固有的低密度特征显著减弱前向慢激波的强度，并阻止后向慢激波的出现．２．高速流尾沿产生以快模为主体的前、后向稀疏波，它们对高速流前沿形成的快激波对的演化具有重要作用．

耀斑激波的各向异性传播

对飞船观测和行星际闪烁记录的分析表明,耀斑激波的最快传播方向偏离耀斑法线:在赤道面内朝东偏转,在子午面内偏向日球电流片.即便扣除背景太阳风的对流效应,上述非对称传播特征仍然存在.可是,迄今对日球赤道面内耀斑激波的数值模拟给出的最快激波传播方向几乎与耀斑法线平行,与观测结果相左.本文将证明,适当修改下边界的激波引入方式,可以获得最快传播方向东偏之结果. 既然耀斑源区随太阳自转,采用共转坐标系比较方便.在该坐标系中,日球赤道面内的理想 MHD二维平面流动满足如下方程:

蒸汽喷射真空泵性能的CFD模拟研究

采用有限体积法离散控制方程,标准 k-ε湍流模型,近壁面处使用壁面函数修正的方法对蒸汽喷射真空泵的超音速混合过程进行数值模拟。计算并分析了第二喉管与工作蒸汽喷嘴喉管面积比、喷嘴出口截面与混合段入口截面间的距离及混合段的锥度等结构参数及工作蒸汽的压力和温度、引射流体及混合流体压力等热力参数对真空泵操作性能的影响。数值计算结果表明,几何参数的改变极大地影响着波系结构,在一定的设计工况下,总存在一个最佳的面积比及一个最优的相对位置对应于最大的喷射系数,其在物理上的表现形式为通过工作蒸汽喷嘴所产生的激波系刚好能够通过第二喉管。混合段的锥度在一定范围内对真空泵的性能无显著影响,等压混合理论较等面积混合理论具更优的操作性能。根据喷射泵内的物理现象及喷射系数的变化规律将蒸汽喷射真空泵的操作状态分为临界状态、亚临界状态和回流状态三类,同时指出临界点为最佳工作点。

Combination of Supercritical Fluid Extraction with Ultrasonic Extraction for Obtaining Sex Hormones and IGF-1 from Antler Velvet

Supercritical CO2 (SC-CO2) extraction technology and ultrasonic technology were used to extract two active sex hormones, estradiol and progesterone, and insulin-like growth factor-1 (IGF-1) from antler velvet. The effects of SC-CO2 extraction condition on the extraction yield and content of sex hormones, the ultrasonic extrac-tion condition on the content of IGF-1 and the SC-CO2 extraction condition on the activity remaining of IGF-1 were studied. The optimal conditions were obtained. The experimental results showed that, in presence of 75% ethanol as the co-solvent, the mean yield and content of estradiol and progesterone were 87.67 pg·g-1 and 1224.10 pg·g-1, 12.38 ng·g-1 and 354.06 ng·g-1, respectively, with extraction pressure of 30 MPa, temperature of 35°C, extraction time of 30 min and CO2 consumption of 15 L·g-1 at the flow rate of 2.0 L·min-1. The highest content of IGF-1 was 7425.75 ng·g-1 antler velvet residue, when the pH10 ammonia-ammonium chloride buffer solution was used as the solvent, the ratio of solvent to sample was 20/1 (volume/mass), the extraction temperature was 0-35°C, and the ex-traction time was 4×15 min. Under these conditions, 93.68% activity remaining of IGF-1 in the residue was ob-tained, while little IGF-1 activity exists in traditional residue. The experimental results indicate that the technology of SC-CO2 with co-solvent is of advantage for getting high content sexual hormones and keeping high activity of IGF-1 in the residue, which can not be achieved by traditional extraction methods.

A hypersonic lift mechanism with decoupled lift and drag surfaces

In the present study, we propose a novel lift mechanism for which the lifting surface produces only lift. This is achieved by mounting a two-dimensional shock-shock interaction generator below the lifting surface. The shock-shock interaction theory in conjunction with a three dimensional correction and checked with computational fluid dynamics (CFD) is used to analyze the lift and drag forces as function of the geometrical parameters and inflow Mach number. Through this study, though limited to only inviscid flow, we conclude that it is possible to obtain a high lift to drag ratio by suitably arranging the shock interaction generator.

Navier-Stokes Computstions of the Supersonic Ejector Diffuser System with a Second Throat

The supersonic ejector-diffuser system with a second throat was simulated using CFD. An explicit finite volumescheme was aPPlied to solve tWo-dimensional Navier-Stokes equations with standard k - E tulbulence model. Thevacuum Performance of the supersonic ejector-diffuser system was investigated by changing the ejector throat arearatio and the operating Pressure ratio. Two convergent-divergent nozzles with design Mach nUmber of 2. 11 and 3.41were selected to give the supersonic operahon of the ejector-diffoser system. The presence of a second throat stronglyaffected the shock wave sir’UctUI’e inside the "dxing tube as well as the spreading of the under-expanded jetdischarging from the Primary nozzle. There were optimum values of the operating pressure ratio and ejector throatarea ratio for the vacuum performance of the system to maximize.

Hysteretic Phenomenon of Shock Wave in a Supersonic Nozzle

In recent years, hysteretic phenomena in fluid flow systems drew attention for their great variety of industrial and engineering applications. When the high-pressure gas is exhausted to atmosphere from the nozzle exit, the expanded supersonic jet with the Mach disk is formed at a specific condition. In two-dimensional expanded supersonic jet, the hysteresis phenomenon for the reflection type of shock wave is occurred under the quasi-steady flow and the transitional pressure ratio between the regular reflection and Mach reflection is affected by this phe- nomenon. However, so far, there are very few researches for the hysteretic phenomenon of shock wave in a supersonic internal flow and the phenomenon has not been investigated satisfactorily. The present study was concemed with the experimental and numerical investigations of hysteretic phenomena of shock wave in a supersonic nozzle, and discussed the relationship between hysteresis phenomenon and rate of the change of pressure ratio with time.

Computational and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation

According to the mechanism of the arc plasma heating effect,and from a phenomenological perspective of view,the plasma actuation was simplified as heating energy injected into the supersonic flow field for the numerical research on controlling detached shock of the blunt body in non-center symmetrical positions.Besides,experimental research on the form and strength of detached shock wave control by plasma aerodynamic actuation in non-center symmetrical positions was conducted in a high-speed shock tunnel(M=2).The results showed that the detached distance of shock wave increased and the strength of normal shock wave ahead of the detached shock wave reduced when plasma actuation was applied.The control effect was greatly improved after the magnetic field was applied and the effect of upwind-direction flow was the best one.When the upwind-direction flow was applied with 1000 V voltage actuation,the distance of detached shock wave would increase from 3.4 to 7.6 mm and the time average strength of normal shock wave was weaken by 5.5%.At last,the mechanism of plasma actuation on controlling the detached shock wave was briefly analyzed.

Nonexistence of a Globally Stable Supersonic Conic Shock Wave for the Steady Supersonic Isothermal Euler Flow

In this paper, for the full Euler system of the isothermal gas, we show that a globally stable supersonic conic shock wave solution does not exist when a uniform supersonic incoming flow hits an infinitely long and curved sharp conic body.

Numerical Study of Shock Tube Flows with Homogeneous and Heterogeneous Condensations in Rarefaction Wave

Shock tubes are devices in which the state of a gas is changed suddenly from one uniform state to another by the passage of shock and expansion waves.In the theory of ideal shock tube flow,it is customarily assumed that the unsteady expansion and shock waves generated by diaphragm rupture are a perfectly centered plane wave.However, such waves are generally not centered,or may not even by plane in practice.In the present research,the time-dependent behavior of homogeneous and heterogeneous condensation of moist air in the shock tube is investigated by using a computational fluid dynamics work.Further,the numerical and experimental studies were carried out in order to investigate the effect of the diaphragm rupture process on the flow characteristics of expansion and shock waves generated near the diaphragm.

Velocity Measurement of Induced Flow by a Laser Focusing Shock Wave

The objective of this study is to apply the shock wave for control in a micro channel. The shock wave was generated by a laser focusing of pulsed laser beam in the channel. Using a pulse laser to generate a shock wave, a non-stationary flow was induced in the small space between the parallel plates. The spherical and cylindrical shock propagations were observed with schlieren method. The shock Mach number decreases with time and approaches to unity. As reported in the previous investigations, the shock speed was attenuated in a short distance and time. In the present experiment, It was not found a remarkable difference in the shock speed between the spherical and cylindrical shock experiments. Subsequently, the flow induced by the cylindrical shock wave was studied using PIV technique. A smoke tracer was used in the experiment and its velocity was measured within 100 μs. A numerical simulation was carried out to investigate the momentum relaxation between the gas and smoke particle. A suitable shock initiation model was introduced in the simulation. The experimental results show that a wide acceleration and deceleration zone exist behind the shock wave. Also, the relaxation distance in the experimental data is much longer than that in numerical simulation.