喉部结构对微喷管性能的影响  

Effects of throat geometry on micro nozzle's performance

作　　者：童军杰[1,2] 徐进良[1] 李玉秀[1] 岑继文[1] 

机构地区：[1]中国科学院广州能源研究所微能源系统实验室,广州510640 [2]广东海洋大学工程学院,湛江524006

出　　处：《航空动力学报》2009年第5期1048-1054,共7页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50776089)

摘　　要：以FLUENT6.1为工具,利用数值计算求解二维稳态可压缩N-S方程,模拟了喉部有无圆弧过渡以及不同的喉部曲率半径对扩张比为5.4的收缩-扩张微喷管x方向质量流速和总压力影响,进而研究了对微喷管的流量系数和推力效率影响.数值计算结果表明:喉部有无圆弧过渡以及不同的喉部曲率半径,将会影响微喷管出口处x方向的质量流速和总压力分布,随着微喷管喉部特征雷诺数的增大,相对应微喷管最大流量和推力的微喷管喉部曲率半径也相应增加.The FLUENT6.1 software was applied to simulate the supersonic flow in micro convergent-divergent nozzle with 5.4 expansion ratios.The simulation was complemented by computing steady two-dimensional Navier-Stokes equations to study the effect of mass x velocity and total pressure from throat,which has arc or not and different throat arc radius.Also,the fluent mass and thrust force effects were studied.It is observed by the study that x orientation mass velocity of thrust exit and thrust force are effected by...

关 键 词：数值计算 微喷管 推力 质量流速 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]