一种大面积比喷管的分段式设计与数值分析  

Design and numerical analysis of segmental nozzle with high area ratio

作　　者：丁兆波[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2013年第1期19-23,共5页Journal of Rocket Propulsion

基　　金：国家863高科技基金(2007AA702)

摘　　要：为了满足大推力上面级发动机大面积比喷管的设计需求,采用了排放冷却前段和单壁辐射冷却尾段的分段式设计方案。在排放冷却前段传热计算的基础上,通过对内流场进行数值模拟,重点研究了单壁尾段在引入上游排放冷却气氢情况下的冷却特性和喷管效率。结果表明:对于大面积比喷管,采用带二次流的单壁金属喷管延伸段是现实可行的,有望达到较好的冷却保护效果并提高喷管效率。To meet the needs of the nozzle with high area ratio for large thrust upper-stage engine, a segmental design scheme for the nozzle is adopted, whose forepart is cooled by dump-cooling mode and end-piece by single-wall radiation cooling mode. Based on the heat transfer calculation of the dump-cooled forepart, the cooling characteristics and efficiency of single-wall end-piece with secondary flow was mainly studied. Numerical simulation of flow field shows that the high area ratio nozzle is feasible for single-wall metal nozzle extension （NE） with secondary flow. It is hopeful to protect the nozzle wall, and improve the nozzle efficiency. The interaction between secondary flow and main stream is analyzed.

关 键 词：大面积比 分段式 单壁喷管 二次流 冷却特性 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]