某单室双推力复杂翼柱形燃烧室的两相流数值分析  

Numerical analysis for two-phase flow in dual-thrust chamber with finocyl grain

作　　者：谢侃[1] 刘宇[1] 熊文波[1] 杨劲松[2] 

机构地区：[1]北京航空航天大学403教研室,北京100083 [2]中国航天科技集团公司八院810所,上海200125

出　　处：《固体火箭技术》2009年第2期171-174,179,共5页Journal of Solid Rocket Technology

摘　　要：针对某单室双推力翼柱形药柱导弹在研制过程中多次出现烧穿现象,开展了数值模拟研究,考察了发动机两相流动情况。模拟结果表明,缓燃药柱前翼设计不合理,造成流场中存在壁面附着涡团,恶化了热防护条件,造成壳体烧穿。数值模拟得到的涡团位置与尺寸和实验烧穿部位吻合。经试验验证,取消前翼设计后,切向涡消失,发动机不再烧穿。A numerical simulation research for a certain dual-thrust chamber with finocyl grain was carried out, for which the burning through phenomenon, was observed many times during the development tests, and the two-phase flow in the rocket motor was reviewed. The result of simulation indicates that the front wing structure is not reasonable, which leads wall-attachment vortex in the flow field, worsens the thermal protection environment and results in burning-through the motor case. The numerical simulation results of position and size of vortex coincide with those in the experiments. The firing tests show that after the front wing structure modificatian, the vortex disappeared and the motor case is no longer burned-through.

关 键 词：两相流 固体火箭发动机 翼柱形药柱 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]