组合可调式超音速分离器设计与测试系统研究

发布时间：2018-01-29 11:11

本文关键词： 超音速分离流场模拟测试系统　出处：《西安石油大学》2015年硕士论文　论文类型：学位论文

【摘要】：超音速分离器是一种新型的天然气分离处理设备,具有系统简单、无需添加化学药剂、无需动力装置的特点。但目前国内的研究理论尚不成熟,暂不具备商业使用价值。本文设计了一套实验用组合可调式超音速分离器,并利用数值模拟的方法对分离器结构参数对流场的影响进行分析。以分离器为核心部件,进行室内实验用测试系统研究。利用现有的文献资料,考虑到便于进行结构尺寸影响研究,分离器结构使用组合可调的方式,喷管段按照从小到大设置三种入口角度,每种入口角度喉部直径均分别设置小中大三种尺寸。分离段中分离翼设计为可滑动结构,考虑密封问题,将分离翼的安装位置设为5位可调节结构,分离翼角度可旋转调节。扩压段通过加装环形垫块调节长度。对这些组合可调结构进行调节搭配,可形成多种结构,便于实验研究。利用Fluent软件,对所设计的分离器进行数值模拟,选择可压缩模型,以理想空气为介质,选择中间参数的分离器模型模拟。模拟结果表明,该模型具备低温制冷能力,可产生旋流分离效果。在该模型基础上,分别改变入口角度、喉部尺寸及分离翼安装位置进行建模分析。结论如下:(1)其他尺寸不变,喉部越小,压力降越大,最低温度值越低,速度极值越高,但同时流场均匀性越差,低温区域长度越短。因此在设计时取值不宜过于偏颇。(2)其他尺寸不变,入口角度越大,压力损失越大,速度极值越高,极低温度越低,但是流场的均匀性变差,低温区域长度越短。入口角度的选择亦需综合分析考虑。(3)分离翼位置直接影响激波出现的位置,其他尺寸不变,分离翼位置越靠近入口,流场的均匀性越好,超音速低温区越长,相应的,获得的低温极值较差,流动速度极值较小。激波出现的位置更为接近出口区,激波对流场带来的影响越小。因此在确定分离翼安装位置时,选择更为接近入口的区域安装,能够获得较好的流场特性。对组合可调式超音速分离器测试平台的研究,确定了实验的操作参数入口含液浓度Ci和压比Pr及性能评价参数分离效率Et和温度降?T,并给出了相应的计算计量方法;对实验装置及设备安装调试进行了分析规划;对实验中需重点关注的流量、温度、压力的测量展开研究,对关键部位的仪表进行选型,并对喉部流速进行测算;给出较为完整的实验方案及关键实验步骤;最后对实验的预期效果及拟解决的问题进行假设与预测。
[Abstract]:Supersonic separator is a new type of natural gas separation and treatment equipment, with the characteristics of simple system, no addition of chemical agents, no power device, but the domestic research theory is not yet mature. For the time being, it is not of commercial value. A set of combined adjustable supersonic separators for experiment is designed in this paper. Numerical simulation method is used to analyze the influence of the structure parameters of the separator on the flow field. Taking the separator as the core part, the laboratory test system is studied, and the existing literature is used. Considering that it is convenient to study the influence of structure size, the splitter structure uses the combined adjustable mode, and the nozzle section sets three kinds of inlet angles according to small to large. The diameter of the throat of each inlet angle is divided into small, medium and large sizes. The separation wing in the separation section is designed as a sliding structure. Considering the sealing problem, the mounting position of the separation wing is set to a 5-bit adjustable structure. The angle of the separation wing can be rotated and adjusted, and the length of the diffuser section is adjusted by adding ring gasket. By adjusting and matching these combined adjustable structures, a variety of structures can be formed, which is convenient for experimental study. Fluent software is used. The designed separator is simulated numerically, the compressible model is selected, and the intermediate parameter is selected to simulate the separator with ideal air as the medium. The simulation results show that the model has the capability of low temperature refrigeration. On the basis of this model, the inlet angle, throat dimension and the installation position of the separation wing can be modeled and analyzed. The conclusion is as follows: 1) the smaller the throat is, the smaller the other dimensions are. The greater the pressure drop, the lower the minimum temperature, the higher the velocity extremum, but at the same time, the worse the uniformity of the flow field, the shorter the length of the low temperature region. The greater the inlet angle, the greater the pressure loss, the higher the velocity extremum and the lower the temperature, but the worse the uniformity of the flow field is. The shorter the length of the low temperature region, the more the inlet angle should be taken into account. The position of the separation wing directly affects the location of the shock wave, and the other dimensions remain unchanged, and the position of the separation wing is closer to the inlet. The better the uniformity of the flow field is, the longer the supersonic low temperature region is, and the corresponding low temperature extreme value is worse, the flow velocity extreme value is smaller, and the location of shock wave is closer to the exit region. The impact of shock flow field is smaller. Therefore, when determining the location of the separation wing installation, choose the area closer to the entrance. The research on the test platform of the combined supersonic separator is carried out. The experimental operating parameters, such as concentration C _ I, pressure ratio pr, separation efficiency et and temperature drop, were determined. The corresponding calculation method is given. The installation and debugging of the experimental device and equipment are analyzed and planned. The measurement of flow, temperature and pressure which should be paid more attention to in the experiment is studied, the instrument of key position is selected, and the velocity of throat is measured. The experimental scheme and key steps are given. Finally, the expected effect of the experiment and the problems to be solved are hypothesized and predicted.
【学位授予单位】：西安石油大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：TE96

【参考文献】