高空滑行期间氧化剂泵壳体冷却方案研究  

Investigation on cooling of oxidizer pump case during coast period

作　　者：张忠利[1] 

机构地区：[1]陕西动力机械设计研究所,陕西西安710100

出　　处：《火箭推进》2005年第1期24-28,共5页Journal of Rocket Propulsion

摘　　要：详细分析了高空多次启动泵压式液体火箭发动机氧化剂泵壳体在滑行期间的热环境,应用数值分析方法对氧化剂泵壳体与涡轮壳体温度进行耦合计算,提出了采用吹气冷却和排放冷却的氧化剂泵冷却方案。经过地面模拟试验及分析后认为,采用排放冷却可满足发动机二次启动可靠工作且在结构上较易实现。Thermal environment of the oxidizer pump case of a high attitude restartable pump fed liquid rocket engine during coast period is studied in detail. Numerical analysis is used for temperature coupling calculation of turbine case. Blow and dump cooling of the oxidizer pump are proposed in this paper. Simulation tests and analysis indicate that dump cooling can meet restart working condition of the engine and easily realized in structure.

关 键 词：液体火箭发动机 涡轮泵 仿真计算 模拟试验 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]