Fluctuation characteristics of arc voltage and jet flow in a non-transferred dc plasma generated at reduced pressure

A torch with a set of inter-electrode inserts between the cathode and the anode/nozzle with a wide nozzle exit was designed to generate plasma jets at chamber pressures of 500–10 000 Pa. The variation of the arc voltage was examined with the change in working parameters such as gas flow rate and chamber pressure. The fluctuation in the arc voltage was recorded with an oscilloscope, and the plasma jet fluctuation near the torch exit was observed with a high-speed video camera and detected with a double-electrostatic probe. Results show that the 300 Hz wave originated from the tri-phase rectified power supply was always detected under all generating conditions. Helmholtz oscillations over 3000 Hz was detected superposed on the 300 Hz wave at gas flow rates higher than 8.8 slm with a peak to valley amplitude lower than 5% of the average voltage value. No appreciable voltage fluctuation caused by the irregular arc root movement is detected, and mechanisms for the arc voltage and jet flow fluctuations are discussed.

Effects of anode temperature on working characteristics and performance of a low power arcjet thruster

An arc-heated thruster of 130–800 W input power is tested in a vacuum chamber at pressures lower than 20 Pa with argon or H2–N2 gas mixture as propellant. The time-dependent arc voltage-current curve, outside-surface temperature of the anode nozzle and the produced thrust of the firing arcjet thruster are measured in situ simultaneously, in order to analyze and evaluate the dependence of thruster working characteristics and output properties, such as specific impulse and thrust efficiency, on nozzle temperature.

Plume Parameters and Thruster Properties of a Low Power Arcjet

Abstract. A low power arcjet-thruster of 1 kW-class with gas mixture of H2-N2 or pure argon as the propellant is fired at a chamber pressure about 10 Pa. The nozzle temperature is detected with an infrared pyrometer; a plate set perpendicular to the plume axis and connected to a force sensor is used to measure the thrust; a probe with a tapered head is used for measuring the impact pressure in the plume flow; and a double-electrostatic probe system is applied to evaluate the electron temperature. Results indicate that the high nozzle temperature could adversely affect the conversion from enthalpy to kinetic energy. The plume flow deviates evidently from the LTE condition, and the rarefied-gas dynamic effect should be considered under the high temperature and low-pressure condition in analyzing the experimental phenomena.

Study on the interaction of intense femtosecond laser pulses with nanometre-sized hydrogen clusters

The interaction of intense femtosecond laser pulses with hydrogen clusters has been experimentally studied. The hydrogen clusters were produced from expansion of high-pressure hydrogen gas (backed up to 8x10(6)Pa) into vacuum through a conical nozzle cryogenically cooled by liquid nitrogen. The average size of hydrogen clusters was estimated by Rayleigh scattering measurement and the maximum proton energy of up to 4.2keV has been obtained from the Coulomb explosion of hydrogen clusters under 2 x 10(16)W/cm(2) laser irradiation. Dependence of the maximum proton energy on cluster size and laser intensity was investigated, indicating the correlation between the laser intensity and the cluster size. The maximum proton energy is found to be directly proportional to the laser intensity, which is consistent with the theoretical prediction.

Two-dimensional numerical simulations of shock waves in micro convergent-divergent nozzles

The steady two-dimensional Navier-Stokes equations with the slip wall boundary conditions were used to simulate the supersonic flow in micro convergent-divergent nozzles. It is observed that shock waves can take place inside or outside of the micronozzles under the earth environment. For the over-expanded flows, there is a boundary layer separation point, downstream of which a wave interface separates the viscous boundary layer with back air flow and the inviscid core flow. The oblique shock wave is followed by the bow shock and shock diamond. The viscous boundary layer thickness relative to the whole nozzle width on the exit plane is increased but attains the maximum value around of 0.5 and oscillates against this value with the continuous increasing of the nozzle upstream pressures. The viscous effect either changes the normal shock waves outside of the nozzle for the inviscid flow to the oblique shock waves inside the nozzle, or transfers the expansion jet flow without shock waves for the inviscid flow to the oblique shock waves outside of the nozzle. 

聚丙烯酸钠对3种土壤持水能力及作物产量的影响

在离心机模拟不同水吸力条件下,研究了聚丙烯酸钠(sodium polyacrylate记作SP)5种使用浓度(占干土质量0,0.01%,0.08%,0.2%与1%)对3种土壤(砂土、壤土、黏土)持水能力的影响;采用大田试验研究了地表撒施2 g/m2SP对冬小麦与下季玉米产量及WUE影响。结果表明:3种土壤在0.01 MPa至1.5 MPa水吸力下的持水能力随着SP用量的增加而增加,砂土的作用效果较壤土、黏土更显著;3种土壤适宜浓度为0.08%~0.2%,最佳用量为0.2%,此用量条件下砂土、壤土、黏土的最大毛管持水量分别较对照增加了138.61%,7.22%,62.70%;不灌水条件下,SP处理较不施用SP冬小麦增产4%,WUE增加5.7%,灌浆期灌水28.5 mm条件下SP处理较不施用SP增产1%,WUE降低1%;SP处理的玉米产量较对照降低0.5%,WUE提高3%,效果明显低于对冬小麦效果。

生物活性有机锗及HPCPC双水相分离生物大分子的研究

本论文内容主要分为4个部分：“有机锗化合物抑制Maillard反应的研究”、“Ge-132对体外培养幼鼠胰岛细胞的作用研究”、“PEG／磷酸盐双水相体系中生物大分子分配的研究”和“HPCPC（High Performance Centrifugal Partition Chromatography，高效离心分配色谱）双水相体系对生物大分子分离的研究”。前两部分主要从有机锗化合物防治糖尿病及其并发症的代谢机理和细胞学角度进行研究，本文引入HPCPC和双水相体系分离生物大分子的技术，为进一步阐明有机锗化合物在Maillard反应过程中的作用机理：对双水相体系中生物大分子的分配及HPCPC在双水相体系中分离生物大分子也做了大量的基础性研究，为开发HPCPC的应用作出了有价值的探索工作。本论文的主要创新点归纳如下：一、有机锗化合物对Maillard反应的抑制作用：针对国际上有机锗发展的前沿课题，在国内首先开展了有机锗化合物对Maillard反应抑制作用的研究，取得了有价值的研究结果。1、在模拟体内的生理条件下，研究了不同浓度Ge-132对精氨酸、组氨酸、甘氨酸和缬氨酸对Maillard反应荧光峰强度的影响：不同类型的氨基酸Maillard反应产物结构上的差异和不同浓度有机锗对组氨酸糖化反应420nm处特征吸光度的影响。2、苯丙氨酸是侧链带有苯环的芳香族氨基酸，是一种具有弱的天然荧光的生物小分子，其荧光最大发射位置在281.6nm。由于aillard反应是葡萄糖和氨基酸的-NHR基发生的反应，其反应产物的特征荧光在440nm附近。这两类荧光的发射位置相差较远，相互之间没有影响，因此利用荧光法观察Phe在反应过程中自身的荧光变化和Ge-132对Phe的Maillard反应荧光产物的抑制情况。3、血清白蛋白是哺乳动物体内的重要蛋白质，可作为多种内源性、外源性物质的存储和转运蛋白，其Maillard反应已经被广泛重视，但较复杂的实验条件限制了它的研究。通过观测蛋白质Maillard反应产物特征荧光的变化是一有效的研究方法。BSA的内源性荧光是由肽链色氨酸和酪氨酸残基贡献的，其最大发射位置340nm左右。其Maillard反应产物的特征荧光在440nm附近，这两类荧光发射位置相差较远，基本上没有影响，因此能够通过荧光光谱研究BSA的Maillard反应荧光产物的情况。本文观测了Ge-132对BSA的Maillard反应荧光产物的抑制作用，同时还通过荧光法确定了一个文献中没有的新的反应位点。4、本文研究了具有更高水溶性的一类双有机锗化合物(HO)_2Ge(CHR_1CHR_2COOH)_2．2H_20抑制Maillard反应的特性，结果证明它比Ge-132具有更高的抑制作用，我们通过化合物的构效关系解释了上述作用的机制。5、本文研究了Tb(Ge-132)_3和Eu(Ge-132)_3两种含稀土的配合物对氨基酸、蛋白质Maillard反应的影响，观察了稀土离子对Maillard反应体系的影响，对实验现象作出了合理的解释。二、Ge-132对体外培养幼鼠胰岛细胞的作用为进一步考察有机锗对糖尿病的防治作用，我们与白求恩医大合作，首次观察了Ge-132对体外培养的幼鼠胰岛细胞结构和功能的影响，研究了不同剂量的含锗化合物对幼鼠胰岛细胞分泌胰岛素的作用，认为低浓度的Ge-132对胰岛细胞分泌胰岛素具有明显的促进作用。该部分内容为首次报导。三、PEG／磷酸盐双水相体系中生物大分子分配的研究双水相萃取TPE(Aqueous Two-Phase Extraction)具有下述优点：生物相容性好、界面张力低、能量低、易于工业规模的放大、可以进行连续操作等。本论文系统地研究了各种蛋白质在PEG／磷酸盐体系中的分离情况，如在各种pH条件下，从6.8到9.2，各种分子量的PEG，包括PEGl000，2000，5000，6000，10000，和20000和磷酸盐双水相体系的物化性质，以及对lysozyme（溶菌酶），BSA（牛血清白蛋白），HSA（人血清白蛋白），Hemoglobin（血红蛋白）在各种体系中的分配系数，探讨了各种因素对生物大分子分配的影响。四、HPCPC在双水相体系对生物大分子分离的研究由于荧光光谱法证实了Ge-132对牛血清白蛋白Maillard反应的抑制作用。但对于如何能够分离出糖化产物，达到进行定量表征的目的是我们研究的一个重要内容。九十年代初，由日本研制出一种色谱中新技术HPCPC。HPCPC与传统的液相色谱(LC)和高效液相色谱(HPLC)不同，不需要固体作为支持体。流动相和固定相分别为两种不相混溶的液体，通过离心力的作用使其中一相作为固定相保持在类似多级萃取器的微小分配槽中，另一相作为流动相流经固定相。HPCPC在双水相体系的应用是一种利用多级连续萃取从双水相中分离生物物质的方法它具有运行时间快、高效高选择性，流动相与固定相之间比例可以任意改变，并在任何pH值均可进行正向和反向操作并且实验室规模可一步直接放大到生产规模。它不仅可以作为一种分离的工具，而且也是一种研究生物萃取反应动力学机理，反映热力学与动力学之间相关性的重要方法。本论文中研究了常用的两种双水相体系，利用PEG6000／Dex20000／H_20对BSA和Maillard反应产生的糖化BSA进行了初步分离，取得了一些阶段性结论。另外，通过对各种条件的筛选，选择了具有代表性的lysozyme和BSA，BSA和血红蛋白(Hb)进行HPCPC色谱仪上的分离，研究了色谱分离条件如：转数、流速、pH等对分离效率及理论塔板数的影响，取得了一系列重要的结论。为工业上大规模的生物样品分离提供了重要的参数。

PRELIMINARY-RESULTS OF GAAS SINGLE-CRYSTAL GROWTH UNDER HIGH GRAVITY CONDITIONS

GaAs single crystals have been grown under high gravity conditions, up to 9g0, by a recrystallization method with decreasing temperature. The impurity striations in GaAs grown under high gravity become weak and indistinct with smaller striation spacings. The dislocation density of surcharge-grown GaAs increases with increase of centrifugal force. The cathodoluminescence results also show worse perfection in the GaAs grown at high gravity than at normal earth gravity.

Oscillation flow induced by underwater supersonic gas jets

This paper describes an experimental study on the oscillation flow characteristics of submerged supersonic gas jets issued from Laval nozzles. The flow pattern during the jet development and the jet expansion feedback phenomenon are studied using a high-speed camera and a pressure measurement system. The experimental results indicate that along the downstream distance, the jet has three flow regimes: (1) momentum jet; (2) buoyant jet; (3) plume. In the region near the nozzle exit a so-called bulge phenomenon is found. Bulging of the jet occurs many times before the more violent jet expansion feedback occurs. During the feedback process, the jet diameter can become several times that of the original one depending on the jet Mach number. The frequencies of the jet bulging and the jet expansion feedback are measured.

Research on the mechanics of underwater supersonic gas jets

An experimental research was carried out to study the fluid mechanics of underwater supersonic gas jets. High pressure air was injected into a water tank through converging-diverging nozzles (Laval nozzles). The jets were operated at different conditions of over-, full-and under-expansions. The jet sequences were visualized using a CCD camera. It was found that the injection of supersonic air jets into water is always accompanied by strong flow oscillation, which is related to the phenomenon of shock waves feedback in the gas phase. The shock wave feedback is different from the acoustic feedback when a supersonic gas jet discharges into open air, which causes screech tone. It is a process that the shock waves enclosed in the gas pocket induce a periodic pressure with large amplitude variation in the gas jet. Consequently, the periodic pressure causes the jet oscillation including the large amplitude expansion. Detailed pressure measurements were also conducted to verify the shock wave feedback phenomenon. Three kinds of measuring methods were used, i.e., pressure probe submerged in water, pressure measurements from the side and front walls of the nozzle devices respectively. The results measured by these methods are in a good agreement. They show that every oscillation of the jets causes a sudden increase of pressure and the average frequency of the shock wave feedback is about 5-10 Hz.

Study of turbulent heat transfer of aviation kerosene flows in a curved pipe at supercritical pressure

The now and heat transfer characteristics of China No. 3 aviation kerosene in a heated curved tube under supercritical pressure are numerically investigated by a finite volume method. A two-layer turbulence model, consisting of the RNG k-epsilon two-equation model and the Wolfstein one-equation model, is used for the simulation of turbulence. A 10-species kerosene surrogate model and the NIST Supertrapp software are applied to obtain the thermophysical and transport properties of the kerosene at various temperature under a supercritical pressure of 4 MPa. The large variation of thermophysical properties of the kerosene at the supercritical pressure make the flow and heat transfer more complicated, especially under the effects of buoyancy and centrifugal force. The centrifugal force enhances the heat transfer, but also increases the friction factors. The rise of the velocity caused by the variation of the density does not enhance the effects of the centrifugal force when the curvature ratios are less than 0.05. On the contrary, the variation of the density increases the effects of the buoyancy. (C) 2010 Elsevier Ltd. All rights reserved.

冲压发动机尾喷管实验新方法

阐述冲压发动机尾喷管地面模拟实验的新方法.采用双爆轰技术产生稳定的高焓燃气模拟高马赫数飞行条件下冲压发动机的燃烧气体;利用皮托管测量尾喷管推力,并对测量误差进行了分析;为研究催化复合效应增大推力提供实验基础

Modeling study on the flow, heat transfer and energy conversion characteristics of low-power arc-heated hydrogen/nitrogen thrusters

A modeling study is conducted to investigate the effect of hydrogen content in propellants on the plasma flow, heat transfer and energy conversion characteristics of low-power (kW class) arc-heated hydrogen/nitrogen thrusters (arcjets). 1:0 (pure hydrogen), 3:1 (to simulate decomposed ammonia), 2:1 (to simulate decomposed hydrazine) and 0:1 (pure nitrogen) hydrogen/nitrogen mixtures are chosen as the propellants. Both the gas flow region inside the thruster nozzle and the anode-nozzle wall are included in the computational domain in order to better treat the conjugate heat transfer between the gas flow region and the solid wall region. The axial variations of the enthalpy flux, kinetic energy flux, directed kinetic-energy flux, and momentum flux, all normalized to the mass flow rate of the propellant, are used to investigate the energy conversion process inside the thruster nozzle. The modeling results show that the values of the arc voltage, the gas axial-velocity at the thruster exit, and the specific impulse of the arcjet thruster all increase with increasing hydrogen content in the propellant, but the gas temperature at the nitrogen thruster exit is significantly higher than that for other three propellants. The flow, heat transfer, and energy conversion processes taking place in the thruster nozzle have some common features for all the four propellants. The propellant is heated mainly in the near-cathode and constrictor region, accompanied with a rapid increase of the enthalpy flux, and after achieving its maximum value, the enthalpy flux decreases appreciably due to the conversion of gas internal energy into its kinetic energy in the divergent segment of the thruster nozzle. The kinetic energy flux, directed kinetic energy flux and momentum flux also increase at first due to the arc heating and the thermodynamic expansion, assume their maximum inside the nozzle and then decrease gradually as the propellant flows toward the thruster exit. It is found that a large energy loss (31-52%) occurs in the thruster nozzle due to the heat transfer to the nozzle wall and too long nozzle is not necessary. Modeling results for the NASA 1-kW class arcjet thruster with hydrogen or decomposed hydrazine as the propellant are found to compare favorably with available experimental data.

Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters

A modelling study is performed to compare the plasma °ow and heat transfer char- acteristics of low-power arc-heated thrusters (arcjets) for three di®erent propellants: hydrogen, nitrogen and argon. The all-speed SIMPLE algorithm is employed to solve the governing equa- tions, which take into account the e®ects of compressibility, Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. The temperature, veloc- ity and Mach number distributions calculated within the thruster nozzle obtained with di®erent propellant gases are compared for the same thruster structure, dimensions, inlet-gas stagnant pressure and arc currents. The temperature distributions in the solid region of the anode-nozzle wall are also given. It is found that the °ow and energy conversion processes in the thruster nozzle show many similar features for all three propellants. For example, the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appear- ing near the cathode tip; the °ow transition from the subsonic to supersonic regime occurs within the constrictor region; the highest axial velocity appears inside the nozzle; and most of the input propellant °ows towards the thruster exit through the cooler gas region near the anode-nozzle wall. However, since the properties of hydrogen, nitrogen and argon, especially their molecular weights, speci¯c enthalpies and thermal conductivities, are di®erent, there are appreciable di®er- ences in arcjet performance. For example, compared to the other two propellants, the hydrogen arcjet thruster shows a higher plasma temperature in the arc region, and higher axial velocity but lower temperature at the thruster exit. Correspondingly, the hydrogen arcjet thruster has the highest speci¯c impulse and arc voltage for the same inlet stagnant pressure and arc current. The predictions of the modelling are compared favourably with available experimental results.