长尾喷管两相流流场计算  

Numerical simulation of twophase flow for a tail-pipe nozzle

作　　者：淡林鹏[1] 张振鹏[1] 何大军 邬俊峰 李家玉[3] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]内蒙古动力机械研究所,内蒙古呼和浩特010010 [3]中国三江航天集团精密机械研究所,湖北武汉430000

出　　处：《推进技术》2002年第5期425-427,共3页Journal of Propulsion Technology

摘　　要：为了给长尾喷管热防护结构的烧蚀和温度场计算提供准确的热边界条件,从二维轴对称N S方程出发,采用颗粒轨道模型和有限体积的Jameson格式计算了长尾喷管纯气相流场和两相流流场。分析和比较表明:在长尾喷管喉部附近以及扩散段的相同轴向位置,两相流情况下轴线上的燃气马赫数小于纯气相情况下的马赫数,两相流情况下轴线和壁面上的燃气温度大于纯气相情况下的燃气温度;在进行长尾喷管热防护结构设计时应以两相流流场作为热边界条件。To provide thermal boundaries for the calculation of ablation and temperature fields of the heatresistant construction,particletrajectory model and Jameson scheme of finite volume method were used to simulate the onephase and twophase flow fields for a tailpipe nozzle. The numerical results show that the gas Mach number for twophase is lower than those for onephase at the centerline,the gas temperature for twophase is higher than those for onephase at both the centerline and the wall around the throat and expansion segment, twophase flow should be considered into the design of the heatresistant construction.

关 键 词：长尾喷管 喷管气流 二相流 流动分布 数值仿真 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]