某发动机涡轮泵转子高温超速/疲劳试验研究  

Fatigue experiment of turbo-pump rotor at over-speed and high temperature condition

作　　者：窦唯[1] 闫宇龙[1] 金志磊 林奇燕[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2015年第1期15-22,49,共9页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司重大工艺课题研究(ZDGY2013-35)

摘　　要：涡轮转子是输送液氢/液氧推进剂的关键组件,其运行状态的好坏将直接影响发动机的性能和可靠性。超速/疲劳试验是转子质量控制、极限强度考核的一种试验方法。针对某发动机涡轮转子开展了高温超速/疲劳试验研究,首先研究了试验用转接器的设计方法,然后基于有限元方法建立了某液体火箭发动机涡轮泵转子高温超速试验的有限元模型,研究了温度对涡轮泵转子振型及临界转速等动特性的影响,分析了转子启动升速过程中常温和高温的振动幅值与支撑应力变化规律。在理论研究基础上开展了转子高温超速/疲劳试验研究,分析了高温状态下涡轮泵转子系统启动升速过程振动幅值的变化规律,研究了温度对涡轮泵转子超速动特性的影响规律。In order to study the dynamic characteristics of turbo-pump rotor system in liquid- propellant rocket engine at high speed and high temperature condition, a finite element model for high temperature and over-speed test of turbo-pump rotor system in a liquid-propellant rocket engine was built by means of the finite element method to research the influence of temperature and critical speed on mode shape and dynamic characteristics of turbo-pump rotor system. The vibration state and bearing stress change rule in the startup process of rotor system in normal and high temperature are analyzed. The fatigue experiment of turbo-pump rotor in over-speed and high temperature was carried out. Based on simulation analysis, the influence rules of high temperature on the dynamic characteristics of turbo-pump rotor system have been mastered. The research result provided a basis for further research on dynamic performance of turbo-pump rotor system at high temperature.

关 键 词：液体火箭发动机 涡轮转子 高温疲劳试验 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]