氩气/甲烷/空气介质阻挡放电等离子体的发射光谱诊断

为了获得可燃气体的放电及等离子体发射光谱特性,进一步揭示等离子体助燃作用下燃料在稀燃状态的点火与燃烧特性,在常压下以氩气作为载气对预混的甲烷和空气进行放电研究。实验基于平行板电极射频(13.56 MHz)介质阻挡放电的等离子体发生装置,首先在常压下对体积分数为90%氩气/10%空气的混合气体开展放电研究;再在90%氩气含量不变的情况下,调节空气含量并加入与之能形成燃烧化学当量比Φ＝1的甲烷,氩气/甲烷/空气的混合气体同样能实现稳定而均匀的放电;最后分别在90%氩气含量不变,甲烷和空气在当量比为Φ＝0.4～1.9六种情况下进行放电实验。由光谱仪记录不同放电工况下的发射光谱信息,诊断反应产物类型,利用观测到的氮分子第二正带系(0-2)380.4 nm和(1-3)375.4 nm处的发射谱线,与自编程序计算的模拟谱线拟合,得出分子转动温度(即气体温度)。研究结果表明：通过拟合模拟光谱与实验所测发射光谱的方法推测分子转动温度,进而获得气体的平动温度,氩气/空气放电的气体温度可达到1 150 K,氩气/甲烷/空气Φ＝1时放电气体温度升高到1 390 K;甲烷与空气形成不同当量比时,所测等离子体气体温度相对于90%氩气/10%空气混合气体温度的温升在70～240 K范围变化;由光谱信息观测到CH,H,OH和CH₂O等活性粒子的存在以及气体温度的升高,表明可燃成分混合气在射频电场放电作用下发生等离子体燃烧化学反应并释放出化学热。     

CH4-O2-N2预混气体爆炸二维数值模拟

 利用CFD软件,基于ISAT算法和简化的甲烷氧化基元反应模型,建立了CH₄-O₂-N₂预混气体的二维湍流爆炸模型。数值计算结果表明,该模型较好地模拟了CH₄-O₂-N₂预混气体在高温气团作用下的点火、燃烧和爆炸过程。计算中,考察了高温点火气团的初始温度和混合气体初始组分对CH₄-O₂-N₂预混气体燃烧和爆炸过程的影响。结果表明：高温气团的初始温度对CH₄-O₂-N₂预混气体的点火延迟时间和燃烧初始阶段有重要影响,但对CJ爆燃没有影响;惰性气体N₂的加入,降低了混合气体的反应活性,导致点火延迟时间增大,燃烧反应速度、爆炸超压和重要自由基浓度都随之减小。相同条件下爆炸超压峰值的计算结果与实验测量结果符合较好。     

甲烷-空气最小点火能量预测理论模型

 最小点火能是可燃气体危险性辨识的重要参数之一。为从理论上得到混合气体的最小点火能,建立了可燃气体火花点火的物理模型,给出了通过数值模拟得到的可燃气体最小点火能量的预测方法,采用该方法得到了甲烷-空气混合气火花点火的临界温度及最小点火能量。结果表明：甲烷-空气混合气的最小点火能量与浓度呈U型关系,浓度为8.5%的预混气的最小点火能量计算值为0.39 mJ,与实验值0.4 mJ吻合较好。     

液态N2、CO冲击压缩特性研究

 介绍利用液氮致冷技术实现低温靶的冷却及样品气体的液化,并通过二级轻气炮对液态气体加载进行平面冲击压缩,实验分别测得10～57 GPa一次冲击压缩下液氮和液态CO的Hugoniot关系数据。这些实验数据结果显示,33 GPa以上比其以下更容易压缩,这种现象本质是氮发生离解相变消耗内能的一种表现形势。液态在20 GPa以下表现为一种稳定的压缩过程,而在其以上则伴随有较为复杂的化学反应现象产生。此外,实验研究还发现,20 GPa以下N₂和CO两种分子液体的冲击压缩特性非常相似。     

多体作用对氦原子团簇He9压缩特性的贡献

 采用Lowdin方法计算了处于压缩状态的氦原子团簇He₉体心立方向型的排斥势及其多体分量，并由此计算出团簇微观压强及其多体分压强。结果发现，多体作用对氦原子团簇He₉压缩特性贡献较大。在相同体积下，由两体近似方法计算的体系压强比多原子体系实际压强偏高10%~30%；考虑三体分压强修正后，近似理论的计算值又会偏低1.5%~10%；只有同时考虑三体、四体修正后，近似理论计算值与实际多原子体系的压强值基本一致。团簇He₉所表现出的压缩特性与固态氦的实验结果相符合。     

平面冲击波高速撞击下Zr41Ti14Cu12.5Ni10Be22.5大块非晶合金的损伤与断裂

 利用二级轻气炮研究了在平面冲击波高速撞击下，Zr₄₁Ti₁₄Cu_12.5Ni₁₀Be_22.5大块非晶合金的损伤与断裂行为。实验结果表明：在高速冲击压缩下，大块非晶合金断裂面的角度小于通常压缩情况的角度，这是由高速撞击下材料极高的应变速率决定的；极高的应变速率变形和局域绝热剪切加热造成局部熔化；在温度和压力的共同作用下，非晶合金发生晶化现象。     

细水雾协同滑动装置对甲烷/空气预混气体爆炸特性的影响

大量甲烷爆炸事故表明,甲烷/空气预混气体爆炸容易造成大量人员伤亡和巨大财产损失。利用10 cm×10 cm×100 cm透明实验管道,探究了细水雾协同滑动装置对甲烷爆炸特性的影响,并着重分析爆炸火焰和超压。结果表明:协同作用下,细水雾对燃烧区超压的影响较小,对未燃区超压峰值有明显衰减作用,甲烷体积分数为11.5%时衰减幅度最大,为44.71%。细水雾对指形火焰有冲毁作用,可加快火焰传播速度,甲烷体积分数为11.5%时,火焰传播速度的提升幅度最大,为62.50%。滑动装置反向压缩火焰至细水雾作用区,加速火焰焠熄。甲烷体积分数为9.5%和11.5%时,火焰焠熄时间明显下降,分别为20.76%和29.65%;甲烷体积分数为7.5%时,火焰焠熄时间下降3.5 ms。     

纳米孔隙内混合气体流动特性的分子动力学模拟

纳米孔隙内气体流动的理论预测对气体微流控器件的设计和制造具有重要的理论指导作用,文章采用分子动力学方法研究了氮气、氧气和二氧化碳混合气体在平行壁纳米孔隙内的剪切流动特性和边界滑移特性.研究结果表明:随着加入二氧化碳比例的不断增加,混合气体滑移速度不断增大,并且当二氧化碳的比例低于20%时,混合气体流动速度沿孔隙宽度方向呈线性分布;而当比例达到40%后,其速度轮廓将呈现非线性趋势.当二氧化碳所占比例为20%时,随着孔隙宽度的增加,混合气体的整体边界滑移随之减小.探究了混合气体密度和气-固耦合强度对混合气体流动及边界滑移的影响机理.发现随着混合气体密度的减小,气流边界滑移增大;随着气-固界面耦合强度的增强,边界气体分子易被吸附而出现黏滑运动,气体分子在边界处的积聚现象增强,剪切应变率增大,边界滑移减小.      

用甲醇-氢混合气源在不锈钢上生长金刚石薄膜的研究

 利用甲醇-氢（CH₃OH-H₂）混合气体为气源，30 nm厚的无定形硅为过渡层，借助于微波等离子体化学气相沉积（MWCVD）成功地将金刚石薄膜生长在不锈钢上，其最低生长温度可至420 ℃，并且甲醇-氢混合气体比传统的甲烷-氢（Ch₄-H₂）更具优势，测试表明这种金刚石薄膜有希望作为耐磨层在工业上应用。     

用多次冲击压缩方法研究稠密氢氦等摩尔混合气体的物态方程

采用液氮冷却以及气体增压技术，制备了～30MPa及～90K初始状态的氢、氦等摩尔混合气体样品.以二级轻气炮作为加载工具，用不同灵敏度设置的两套多通道瞬态高温计系统获得完整、清晰的稠密氢、氦混合气体多次冲击压缩过程的光谱辐射强度信号.并建立起相应的实验数据处理和分析技术，获得了5—140GPa范围内氢、氦混合气体一至五次冲击雨贡纽物态方程，以及一次、二次和四次冲击温度实验数据.流体变分理论和离解模型用来分析和解释所获得的测量结果. 关键词： 氢、氦混合气体 多次冲击压缩 光谱辐射强度历史 物态方程     

On parametrization and mixture laws for electron ionization coefficients

In this paper we discuss the methods of calculation of electron ionization coefficient data. First we give a summary of the data for analytic parametrization of ionization coefficients. Such data may be useful for particle and radiation detectors and for studies of breakdown voltages in gas dielectrics. We have applied extended Townsend formula to fit the experimental data for a number of gases and shown that it provides excellent fits for the entire range of E/N where data are available. We also tested the application of the common E/N and the common mean energy combination of data for pure gases to obtain ionization coefficients for mixtures. The standard combination procedure gives poor results in general but the common mean energy procedure provides an extended region of reasonable usefulness. Test calculations were made for Ar–CH₄ mixtures which were found to be the most difficult combination of the selected gases for the application of the mixture law.     

Transient modes of propagation of the shock wave-reaction zone complex in methane-air mixtures

The dynamics of the combustion of stoichiometric methane-air mixtures during the passage from a larger-diameter to a smaller-diameter tube is experimentally studied. The combined effect of increases in the velocity and duration of the gas flow and in the degree of its turbulization due to a decrease in the cross sectional area of the tube and installation in it of turbulizing obstacles considerably enhance the probability of onset of combustion mode with the formation of strong shock waves. Combustion waves led by a shock wave that ignites the mixture at obstacles and propagates at a velocity of up to 1400 m/s within a distance of ～14 tube diameters are produced.     

Remote sensing of high temperature H2O-CO2-CO mixture with a correlated k-distribution fictitious gas method and the single-mixture gas assumption

Infrared spectra of high temperature H₂O-CO₂-CO mixtures are calculated using narrow band models in order to simulate hot jet signature at long distance. The correlated k-distribution with fictitious gas (CKFG) approach generally gives accurate data in such situations (especially for long atmospheric paths) but results in long computation time in cases involving mixtures of gases. This time may be reduced if the mixture is treated as a single gas (single-mixture gas assumption, SMG). Thus the lines of the single-mixture gas are assigned to the fictitious gases. In this study, the accuracy of two narrow band models is evaluated. The first narrow band model considers one single-mixture gas and no fictitious gas (CK-SMG) whereas the second model accounts for one single-mixture gas and three fictitious gases (CKFG-SMG). Both narrow band models are compared with reference spectra calculated with a line-by-line (LBL) approach. As expected, the narrow band accuracy is improved by the fictitious gas (FG) assumption particularly when long atmospheric paths are involved. Concerning the SMG assumption, it may lead to an underestimation of about 10% depending on the variation of the gas mixture composition ratio. Nevertheless, in most of realistic situations the SMG assumption results in negligible errors and may be used for remote sensing of plume signature.     

冲击波加热的氦气与氩气对电探针导通的影响

 用炸药透镜加载装置观察到置于氦气与氩气中的电探针回路有不同的导通现象。基于一维冲击波和局域热平衡假设,分别计算了两种气体的冲击状态参数。当飞片速度在3～5 km/s范围时,理论估算的氩气电离度超过1%,这说明氩气的电离已引起了探针回路的提前接通,而氦气几乎没有电离,对探针能起到很好的保护作用。     

Analysis of the effect of foreign gases in the production of hyperpolarized 129Xe gas on a simple system working under atmospheric pressure

Experimental conditions that affect the degree of polarization of 129Xe gas were tested for a higher degree of polarization to facilitate a laboratory use of 129Xe NMR, primarily on the effect of addition of foreign gases. When He, N(2), or D(2) gas was added separately to pure Xe gas with natural isotope abundance, D(2) gas gave better results than the others in enhancing the degree of polarization in 129Xe atom. When these gases were added in mixture, however, N(2) plus He was proved to be more efficient than D(2) or He in enhancing the degree of polarization. As a result, the degree of polarization was found to be increased by more than an order, when diluent gases were properly mixed; polarization as high as 35% was reached at gas composition of 5% Xe, 10% N(2), and 85% He, whereas only a few percent was attainable when Xe gas was polarized without mixing any foreign gases [J. Magn. Reson. 150 (2), 156-160 (2001)]. These results were discussed on a basis of quenching and buffer effects of foreign gases. Polarization was also measured after separating the pure Xe gas from the mixture; value of 22% was obtained for the Xe gas isolated after solidification in liquid nitrogen trap. Build-up time of the polarization was also tested, which did not change remarkably depending on the gas composition.     

Ratio of Diffusion Coefficient to Mobility for Electrons in SF6-Air and Freon-Nitrogen Mixtures

The ratio of diffusion coefficient to mobility (D/?) for electrons has been measured in SF6-air and freon-nitrogen mixtures for various concentrations of SF6 and freon in the mixtures over the range 140? E/p? 220 V.cm-1 - torr-1. In SF6-air mixtures, the values of D/? were always observed to lie intermediate between the values for the pure gases. However, in freon-nitrogen mixtures, with a small concentration (10 percent) of freon in the mixture, the values of D/? are found to lie above the boundaries determined by the pure gases. In this mixture, over the lower E/p range (140 to 190) the electrons appear to lose a large fraction of their energy by the excitation of the complex freon molecules, while at higher E/p values (200 to 240), the excitation and consequent deexcitation of nitrogen molecules and its metastables seem to cause an increased rate of ionization of freon molecules.     

Ionization and Breakdown in SF6-Air and Freon-Nitrogen Mixtures

The sparking potentials and swarm coefficients (ionization and attachment coefficients) have been measured in sulphurhexafluoride- air and freon-nitrogen mixtures over the range of 110 ? E/p ? 240 V cm-1 torr-l and gas pressures varying between 1 and 20 torr, at 20°C. Addition of strongly attaching salphur-hexafluoride and freon gases increased the sparking potentials and the rate of increase of the attachment coefficient with increasing percentage of the strongly attaching gases in the mixtures was much larger than the rate of change of the first ionization coefficient.     

Effects of pressure on flame propagation in a premixture containing fine fuel droplets

Combustion experiments on fuel droplet–vapor–air mixtures have been performed with a rapid expansion apparatus which generates monodispersed droplet clouds with narrow diameter distribution using the condensation method. The effects of fine fuel droplets on flame propagation were investigated for ethanol droplet–vapor–air mixtures at various pressures from 0.2 to 1.0 MPa. A stagnant fuel droplet–vapor–air mixture, generated in a rapid expansion chamber, was ignited at the center of the chamber using an ignition wire. Spherical flame propagation under constant-pressure conditions was observed with a high-speed video camera and flame speed was measured. Total equivalence ratio, and the ratio of liquid fuel mass to total fuel mass, was varied from 0.6 to 1.4 and from zero to 56%, respectively. The mean droplet diameter of fuel droplet–vapor–air mixtures was set at 8.5 and 11 μm. It was found that the flame speed of droplet–vapor–air mixtures less than 0.9 in the total equivalence ratio exceeds that of premixed gases of the same total equivalence ratio at all pressures. The flame speed of fuel droplet–vapor–air mixtures decreases as the pressure increases in all total equivalence ratios. At large ratios of liquid fuel mass to total fuel mass, the normalized flame speed (the flame speed of droplet–vapor–air mixtures divided by the flame speed of the premixed gas with the same total equivalence ratio), increases with the increase in pressure for fuel-lean mixtures, and it decreases for fuel-rich mixtures. The outcome is reversed at small ratios of liquid fuel mass to total fuel mass; the normalized flame speed decreases with the increase in pressure for fuel-lean mixtures, and increases for fuel-rich mixtures. The results suggest that the increase in pressure promotes droplet evaporation in the preheat zone.     

Prandtl number and thermoacoustic refrigerators

From kinetic gas theory, it is known that the Prandtl number for hard-sphere monatomic gases is 2/3. Lower values can be realized using gas mixtures of heavy and light monatomic gases. Prandtl numbers varying between 0.2 and 0.67 are obtained by using gas mixtures of helium-argon, helium-krypton, and helium-xenon. This paper presents the results of an experimental investigation into the effect of Prandtl number on the performance of a thermoacoustic refrigerator using gas mixtures. The measurements show that the performance of the refrigerator improves as the Prandtl number decreases. The lowest Prandtl number of 0.2, obtained with a mixture containing 30% xenon, leads to a coefficient of performance relative to Carnot which is 70% higher than with pure helium.