共查询到16条相似文献,搜索用时 101 毫秒
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采用理论和实验的方法研究了一定汽水参数下的超音速汽液两相流升压装置的极限升压能力以及主要结构参数对其的影响规律。计算与实验的结果表明:超音速汽液两相流升压装置的极限升压能力计算值可达进汽压力的14倍左右,实验值可到进汽压力的2.6倍左右;混合腔和水喷嘴的几何尺寸是影响极限升压能力的最主要的结构参数;极限升压能力随混合腔收缩比增大而增大,随水喷嘴出口与混合腔喉部截面积比增大而减小,随蒸汽喷嘴喉部与出口截面积之比变化不大。计算和实验得到的结构参数对极限升压能力的影响规律是基本一致的。 相似文献
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对环周进汽型的变截面通道内超声速汽液两相流升压装置进行了实验及理论研究,实验中进汽压力为0.15~0.4MPa,进水压力为0.2~0.6 MPa。实验结果表明在不同的汽水参数条件下,混合腔内压力与温度分布呈现出相似的规律。在同一工况下,激波前混合腔内各点的压力基本保持不变,随着凝结激波的产生,压力突然增大。激波过程中蒸汽几乎全部凝结,激波过后温度分布趋于平缓。并在实验结果的基础上分别建立了水喷嘴、蒸汽喷嘴、混合腔内两相区和扩散段的数学模型,其预测的装置出口压与实验值之间的误差小于15%。 相似文献
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给油田的油井中注入高温高压蒸气时,从井口到井底连续地查明汽液比对节省能源和提高产出率意义重大。由于干蒸气和水的折射率不同,汽液的比例可以从汽液两相流的折射率响应特性反映出来。研制的测量装置采用蓝宝石作为折射率敏感的探测头,直接对汽液两相流的比例变化产生响应,能够应用于高温高压及狭窄工作空间的输汽环境中。装置在锅炉输汽管道中的实测响应曲线反映了输汽过程中汽液比的真实变化。该装置还在井深800m,井口蒸气温度270℃、压力10Mpa的油田注汽井中进行测量,测得的结果对注汽法采油的井况分析具有一定的作用。 相似文献
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小通道气液两相流电容测量方法研究 总被引:2,自引:1,他引:1
本文设计了一套用于小通道气液两相流的电容测量系统,并对内径为1.6 mm、2.5 mm和3.6 mm的玻璃管气液两相流进行了实验研究.文中首先对电容方法在小通道下的应用做了探索性尝试,设计了用于小通道气液两相流的电容传感器;然后利用所设计的电容传感器对小通道气液两相流弹状流电容动态数据进行采集、处理和分析;最后利用相关原理对气弹速度的测量进行了研究.研究结果表明所提出的电容方法可用于小通道气液两相流的分析研究中,是一种有效的小通道气液两相流参数检测手段,并为小通道两相流检测的研究提供了一定的借鉴. 相似文献
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M. icha L. Brdo M. Tichý L. Soukup L. Jastrabík H. Barnkov R. J. Soukup J. Tou 《等离子体物理论文集》1994,34(6):749-764
The paper presents a simple theoretical model of the breakdown of the supersonic plasma jet generated by the hollow cathode discharge inside the nozzle in the low pressure RF plasma-chemical reactor. Through the nozzle which is drilled in the RF electrode the working gas flows to the reactor chamber. If at the outlet of the nozzle the gas flow is supersonic the well defined plasma jet is created inside the reactor chamber. The results of our model are in qualitative agreement with experimental data. 相似文献
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合成气压缩机循环段由于高压和流动空间限制,难以测量内部流动参数,导致无法从工程上判断循环段流动性能。为此本文建立了高压缸出口段、混合腔和循环段叶轮流道模型,采用合成气物性,在约14.4 MPa(A)的高压进口条件下,使用CFD的方法研究了循环段内部流动混合发展规律。选取常用的七种损失模型评估了叶轮内损失,并研究了混合腔对下游叶轮性能的影响。结果表明混合腔内呈现出明显的二次流动,随着流动向下游发展,流场变得越来越均匀。混合腔损失、叶片负载损失和尾迹损失是主要的损失源。由于上游混合腔的影响,带有混合腔的叶轮的压比和效率低均低于单独均匀进口叶轮情况,且其工况范围更窄。本文的结果可为新型合成气压缩机产品的设计提供参考。 相似文献
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Electric discharge in a supersonic air jet is studied. It is ignited in a linearly polarized quasi-optical microwave electromagnetic
beam the initial field intensity of which is much lower than the breakdown level. Electric breakdown is initiated by a tubular
electromagnetic vibrator, one end of which has spikes and is covered by a quartz tube. Atmospheric air enters into a low-pressure
working chamber through the inner channel of the vibrator. As a result, an immersed supersonic air jet forms in the chamber
at the outlet from the quartz tube. A microwave discharge ignited in this jet is “attached” to aft spikes of the vibrator.
The energy deposit into the discharge plasma and the effective area of energy interaction between the discharge and excited
microwave field are estimated from the temperature and stagnation pressure distributions in the wake of the discharge. 相似文献
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The ideal gas exhaustion from an infinite volume into a gas at rest through a supersonic conical Laval nozzle is considered.
The problem was solved numerically by steadying in time in a unified formulation for the regions inside the nozzle and in
the ambient environment. In such a statement, the nozzle outlet section is no internal boundary of the region under consideration,
and there is no need of specifying the boundary conditions here. Local subsonic zones arising in the flow lie inside the region
under consideration, which eliminates the possibility of using a marching technique along one of the coordinates. The numerical
solution is constructed by a unified algorithm for the entire flow region, which gives a possibility of obtaining a higher
accuracy. The computations are carried out in the jet initial interval, where, according to monograph [1], the wave phenomena
predominate over the viscous effects.
The exhaustion process is described by the system of gas dynamics equations. Their solution is constructed with the aid of
a finite difference Harten’s TVD (Total Variation Diminishing) scheme [2], which has the second approximation order in space.
The second approximation order in time is achieved with the aid of a five-stage Runge-Kutta method. The solution algorithm
has been parallelized in space and implemented on the multi-processor computer systems of the ITAM SB RAS and the MVS-128
of the Siberian Supercomputer Center of SB RAS.
The influence of the semi-apex angle of the nozzle supersonic part and the pressure jump between the nozzle outlet section
and the ambient environment on the flow in the initial interval of a non-isobaric jet is investigated in the work. A comparison
with experimental data is presented. The computations are carried out for the semi-apex angles of the nozzle supersonic part
from 0 (parallel flow) to 20 degrees. For all considered nozzles, the Mach number in the nozzle outlet section, which was
computed from the one-dimensional theory, equaled three. Computations showed that in the case of flow acceleration in a conical
supersonic nozzle, its geometry is one of the main factors determining the formation of the jet initial interval in ambient
environment. 相似文献