切流式超声速天然气分离器结构设计与数值模拟

发布时间：2018-11-22 20:04

【摘要】：超声速天然气分离器是用于天然气脱水的一种装置。它结构简单,效率高,能耗低,支持无人值守,在天然气输送中得到了广泛的应用。现代工业中使用的超声速天然气分离器都是轴流式的,分为超声速翼后置和前置两种。超声速翼后置式分离器在翼前会产生强激波从而影响系统稳定使用;超声速翼前置式分离器对翼的设计有较高的要求,往往不能产生足够大的离心加速度。本文从涡流管的进气方式中得到启发,把超声速翼从天然气分离器中移除,而把进气方式由轴向变为切向,并使用CFD软件进行了数值模拟。首先,对超声速天然气分离器工作原理从理论上进行分析与讨论。然后,对传统轴流式天然气分离器的结构参数进行理想优化选择,并据此结构参数建立相应的物理模型,利用GAMBIT软件进行网格划分,运用CFD软件对其进行了数值模拟。主要分析了其速度场、压力场、温度场,结果显示超声速翼后置式分离器在轴向x=0.19m处产生了激波,得出的结论与前人保持一致。接着在其他结构参数保持不变的情况下除去了超声速翼,并参照涡流管的结构对切流式进气喷嘴进行了设计。然后对切流式超声速天然气分离器进行了数值模拟,结果显示:高压气流在分离器内高速稳定旋转,并没有产生激波;气流切向速度在气流入口最高可达250m/s,在气液分离段气流切向速度基本保持不变,其值可达150m/s,高于超声速翼前置式分离器的切向速度,旋流比可达0.27;在气液分离段最低温度可达140k,为水蒸汽冷凝创造了良好的环境。
[Abstract]:Supersonic gas separator is a kind of device used for natural gas dehydration. It has been widely used in natural gas transportation because of its simple structure, high efficiency, low energy consumption and unattended support. The supersonic gas separators used in modern industry are axial flow, which can be divided into two types: supersonic wing rear and front. The supersonic wing rear separator will produce strong shock wave in front of the wing which will affect the stable use of the system. The supersonic wing front separator has higher requirements for the wing design and often can not produce enough centrifugal acceleration. Inspired by the intake mode of vortex tube, the supersonic wing is removed from the natural gas separator and the intake mode is changed from axial to tangential direction. The numerical simulation is carried out by using CFD software. Firstly, the working principle of supersonic gas separator is analyzed and discussed theoretically. Then, the structural parameters of the traditional axial flow gas separator are optimized, and the corresponding physical model is established according to the structural parameters. The grid is divided by using GAMBIT software, and the numerical simulation is carried out by using CFD software. The velocity field, pressure field and temperature field are mainly analyzed. The results show that shock waves are produced at the axial x _ (0.19) m in the supersonic wing rear separator, and the results are consistent with those obtained by the predecessors. Then the supersonic wing is removed while other structural parameters remain unchanged and the tangent flow inlet nozzle is designed according to the structure of the vortex tube. Then the tangential flow supersonic gas separator is numerically simulated. The results show that the high pressure gas flow rotates steadily at high speed in the separator and no shock wave is produced. The tangential velocity can reach up to 250 m / s at the inlet of the air flow, and the tangential velocity of the gas flow in the gas-liquid separation section is almost unchanged, which can reach 150 m / s, which is higher than the tangential velocity of the supersonic wing front separator, and the swirl ratio can reach 0.27; The lowest temperature in the gas-liquid separation section is up to 140 ks. which creates a good environment for water vapor condensation.
【学位授予单位】：太原科技大学
【学位级别】：硕士
【学位授予年份】：2011
【分类号】：TH237.5

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