航空发动机复合材料叶片振动疲劳特性研究  

Vibration Fatigue Characteristic Study of Aeroengine Composite Blade

作　　者：杨强[1] 邵闯[1] 方可强[1] 

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《实验力学》2014年第3期361-367,共7页Journal of Experimental Mechanics

摘　　要：针对发动机复合材料叶片开展了振动疲劳特性研究。首先通过模态测试获得叶片结构的振型图,确定叶片在振动中应力最大部位疲劳薄弱部位;其次采用振动台施加窄带随机激励载荷,并监测其疲劳薄弱部位的应变水平,获得了复合材料叶片的振动响应及疲劳特性。试验结果显示,叶片在350με应变水平下的振动疲劳寿命为5.46×106;复合材料叶片的固有频率随试验时间的增加而降低。上述结果可为复合材料叶片在发动机中的应用提供部分依据。Vibration fatigue characteristic study of aeroengine composite blade was carried out. Firstly, the vibration diagrams of blade were obtained by modal tests, based on which, the position of the largest stress-fatigue weak position of vibrated blade was determined. Secondly, using vibration table, the narrowband random excitation load was applied to monitor the strain level at the fatigue weak position. Based on which, the vibration response and fatigue characteristics of composite blade were obtained. Experimental results show that the vibration fatigue life of blade is 5.46×10^6 at 350με strain level; the inherent frequency of composite blade declines with experiment time increase. Above results may offer part of important evidence for composite blade application in aeroengine.

关 键 词：复合材料叶片 模态测试 振动疲劳特性 频率 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]