摘要
为满足RBCC推进系统主火箭发动机对气氧/煤油推力室的要求,对其进行了高燃烧室压力和温度、大范围变工况工作研究。气氧/煤油推力室喷注器采用中心区气液双组元内混式喷嘴和边区直流喷嘴结合结构,身部采用夹层冷却结构。通过对推力室气氧/煤油推进剂的点火及雾化混合技术、推力室喷注器及身部冷却设计技术、推力室的点火启动、稳态工作等关键技术的研究表明,推力室在室压3MPa、5MPa工况下可稳定燃烧。额定推力650N的气氧/煤油推力室方案可靠、点火工作正常,可以满足大范围变工况稳定工作要求。
To meet the requirements of the main rocket engine of RBCC propulsion system for GO2/kerosene thrust chamber, an investigation of the thrust chamber with work condition changed at a large range and in high combustion pressure and high temperature was conducted. The centre of the thrust chamber injector was one injecting element with inside gas and liquid propellant mixing. The periphery of the thrust chamber injector was spray injecting elements. The important technolo- gies included the ignition of GO2/kerosene propellant, mixing and atomizing of propellant, design of the injector, cooling of its body, design of start, and combustion of two phase stable flow. The results of the investigation show that combustion of the thrust chamber is steady when the chamber pressure changes from 3MPa to 5MPa. The design of the thrust chamber is successful and the thrust chamber works well
出处
《火箭推进》
CAS
2009年第6期23-26,共4页
Journal of Rocket Propulsion
