| 喉部不对称对微喷管性能影响 |
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| 引用本文： | 童军杰,徐进良,岑继文.喉部不对称对微喷管性能影响[J].航空动力学报,2010,25(4):808-815. |
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| 作者姓名： | 童军杰 徐进良 岑继文 |
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| 作者单位： | 1.中国科学院 广州能源研究所微能源系统实验室 广州 510640 |
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| 基金项目： | 国家杰出青年科学基金，国家青年科学基金 |
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| 摘 要： | 以FLUENT 6.1软件为工具,利用数值计算求解二维稳态可压缩Navier-Stokes(N-S)方程,模拟了微喷管内超声速流体流动,分析了喷管喉部结构不对称对喷管内部的流场和喷管性能的影响.这种喉部结构不对称是由于喉部上下顶点在x方向偏离一定距离所造成的.数值计算结果表明,喷管喉部在流体流动方向的不对称,将导致喷管内部流体流场不平衡性,使得流量增大,喷管出口的x方向推力增加,y方向产生了多余的推力.
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| 关 键 词： | 数值计算 不对称 流量 推力 微喷管 |
| 收稿时间： | 4/8/2009 9:00:39 AM |
| 修稿时间： | 12/7/2009 9:52:05 PM |
Effects of throat asymmetry on micro nozzle's performance |
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| TONG Jun-jie,XU Jin-liang and CEN Ji-wen.Effects of throat asymmetry on micro nozzle's performance[J].Journal of Aerospace Power,2010,25(4):808-815. |
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| Authors: | TONG Jun-jie XU Jin-liang and CEN Ji-wen |
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| Institution: | 1.Micro Energy System Laboratory, Guangzhou Institute of Energy Conversion, Chinese Academy of Sciences, Guangzhou 510640, China2.Engineering College, Guangdong Ocean University of Technology, Zhanjiang 524006, China |
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| Abstract: | FLUENT 6.1 software was applied to simulate the supersonic flow in micro convergent-divergent nozzle.The simulation was complemented by computing steady two-dimensional Navier-Stokes(N-S) equations to study the effects of flow fields and performance of thruster from throat structure asymmetry.The asymmetry of throat was caused by deviation of throat upper vertex from lower vertex in x direction.The simulation results show that the asymmetry of throat causes fluids perturbation inside thruster,mass flow rate increases,and x direction thrust force decreases while additional y direction thrust force is produced at the exit of thruster. |
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| Keywords: | numerical simulation asymmetry mass flow rate thrust force micro thruster |
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