航空发动机叶片高应力振动疲劳试验技术研究  

High Stress Vibration Fatigue Test Technology of Aeroengine Blade

作　　者：何胜帅[1] 陈立伟[1] 强笑辉[1] 邓瑛[2] 

机构地区：[1]北京强度环境研究所,北京100076 [2]北京航空制造工程研究所,北京100024

出　　处：《装备环境工程》2013年第4期41-46,共6页Equipment Environmental Engineering

摘　　要：在电动振动台上对航空发动机叶片进行了高应力振动疲劳试验,详细研究了试验机理,提出了辅助点监测叶片最大振动应力、共振峰后定频率激励等试验方法,并成功利用振动台开环控制技术有效稳定了叶片的振动应力水平,从而获得可靠的疲劳数据。另外,从试验角度出发,对振动台激励与叶片振动应力响应之间的关系进行了研究。High stress vibration fatigue test of several aeroengine blades were carried out on electric shaker and the test mechanism was studied.New test methods were put forward,which were blade maximal vibration stress monitoring using assisting points and fixed frequency excitation after resonance frequency.Open loop control technology of vibrating table was successfully applied to stabilize vibration stress and reliable fatigue data were obtained.The relation between the excitation of electric shaker and the vibration response of blade was discussed.

关 键 词：振动疲劳试验 航空发动机叶片 共振放大 电动振动台 振动应力 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]