高空发动机涡轮泵启动性能仿真与试验研究  

Simulation and experimental study on start-up performance of turbopump in high altitude liquid rocket engine

作　　者：付瑜[1] 王伟光[1] 李瑜 许开富[1] FU Yu;WANG Weiguang;LI Yu;XU Kaifu(Xi＇an Aerospace Propulsion Institute,Xi＇an 710100,China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2018年第5期56-60,共5页Journal of Rocket Propulsion

摘　　要：在涡轮泵启动物理模型理论分析的基础上,编写仿真程序对启动过程进行分析。搭建了涡轮泵启动性能试验台,采用某型火箭发动机涡轮泵进行试验验证。仿真结果表明该模型满足涡轮泵启动特性研究的要求,试验结果表明该试验方案适合进行涡轮泵启动性能试验研究,可用于研究涡轮泵启动过程中涡轮、泵、机械密封、轴承等重要零组件的性能。For the turbopump in liquid rocket engine,a simulation program was compiled to analyze its start-up process based on the theoretical analysis. Moreover,an experimental rig for the start-up performance of turbopump was built and the turbopump in a certain type of engine was tested for verification. The simulation results show that the model meets the study requirements of the start-up process. The experimental results show that the experimental scheme is suitable for the performance study of turbopump start-up,and can be used in the investigation of turbine,pump,mechanical seal,bearing and other important components.

关 键 词：涡轮泵 启动 性能试验 

分 类 号：V432[航空宇航科学与技术—航空宇航推进理论与工程]