三组元火箭发动机推力室试验研究  

Experimental research on the thrust chamber of tripropellant rocket engine

作　　者：沈赤兵[1] 李清廉[1] 罗世彬[1] 周进[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《火箭推进》2006年第5期1-6,共6页Journal of Rocket Propulsion

基　　金：国家"863"基金;项目编号:203AA722011。

摘　　要：通过冷试研究了多种喷嘴的特性,总结了工作参数和结构参数对喷嘴性能的影响规律;进行了大量三组元推力室双工况热试,研究了不同工作参数和结构参数对三组元推力室燃烧性能的影响;利用旁通阀方案和液氧可调汽蚀文氏管方案分别成功进行了三组元工况与两组元工况的模态转换试验,实现了大范围工况调节;对三组元推力室内部燃烧和传热过程进行了数值仿真,考察了推力室冷却方案的可行性。The research group has devoted itself to tackle key technologies of the thrust chamber of Tripropellant Rocket Engine （TRE） with LO2/Kerosene/GH2 for many years. The optimization design scheme of sub-orbiter was obtained by use of optimizing the main design parameters of TRE and optimization algorithm. The effects of work and structure parameters on the injectors＇ performance were summarized on the basis of the cold-flow test study on many kinds of injectors. The effects of work and structure parameters on the combustion performance of Tripropellant Chamber （TC） were studied by many times of hot-fire tests of TC operating in dual mode. The mode-transition process between tripropellant mode and bipropellant mode was successfully accomplished by means of two kinds of supply system schemes, such as scheme of bypass valves and scheme of controllable cavitating Venturi with LO2. Moreover, regulating operating condition under the wide range was realized. The feasibility of scheme of cooling TC was investigated by numerical simulation of combustion process and heat-transfer process of TC.

关 键 词：三组元火箭发动机 仿真 喷注器 冷试 热试 燃烧稳定性 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]