气动谐振管加热效应初步实验  

Preliminary experimental investigation on gas dynamic resonance tube heating effect

作　　者：梁国柱[1] 马彬[1] 程显辰[1] 张国舟[1] 张振鹏[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2002年第1期52-56,共5页Journal of Propulsion Technology

基　　金：国家"八六三"基金资助项目 (86 3 2 3 4 7)

摘　　要：为了有效地应用气动谐振管加热现象的热效应 ,以发展液体火箭发动机的气动谐振管点火新技术 ,需要获得谐振管热效应的变化规律。实验测量了三种谐振管 ,即圆柱型、阶梯型和锥柱型谐振管间的表面加热温度。实验中主要考虑喷嘴与谐振管间的分离距离以及供气压力的变化。所获得的谐振加热特性可用于实际谐振加热装置的设计。To apply effectively the thermal effects of gas dynamic resonance heating phenomenon,especially to develop new technology of gas dynamic resonance tube ignition for liquid rocket engines,it is necessary to obtain their variation laws.The experimental measurement of surface heating temperatures of three types of resonance tubes,i.e.,cylindrical,stepped and cone cylinder shaped tubes were carried out.The separation distance between the nozzle and the resonance tube and the feed pressure of the driving gas were the main considerations.The obtained resonance heating characteristics are useful to the design of real resonance tube igniters.

关 键 词：谐振管 气动加热 液体推进剂火箭发动机 点火系统 热效应 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]