一种航空发动机转子叶片振动特性及疲劳试验方法  

A method for vibration characteristics and fatigue test of aero-engine rotor blades

作　　者：吴琼 邓瑛 邓武警 何斌策 WU Qiong;DENG Ying;DENG Wujing;HE Bince(AVIC Manufacturing Technology Institute,Beijing 100024,China;Aeronautical Key Laboratory for Plastic Forming Technologies,Beijing 100024,China;Beijing Key Laboratory for Plastics Technologies and Equipment,Beijing 100024,China)

机构地区：[1]中国航空制造技术研究院,北京100024 [2]塑性成形技术航空科技重点实验室,北京100024 [3]数字化塑性成形技术与装备北京市重点实验室,北京100024

出　　处：《理化检验（物理分册）》2024年第10期57-61,共5页Physical Testing and Chemical Analysis(Part A:Physical Testing)

摘　　要：对一种航空发动机转子叶片开展振动特性和疲劳试验方法研究,通过理论计算和试验验证获得叶片前3阶弯曲振动频率,并在1阶弯曲振动模态下获取叶片所受应力与叶片自振频率、振幅之间的关系。结果表明:该结构的理论、实测振动特性一致,试验件振动应力与振幅之间服从线性变化规律,表明提出的试验方法有效,可为该转子叶片的研制提供疲劳性能数据支撑。The vibration characteristics and fatigue test methods of an aero-engine rotor blade were studied.The first three order bending vibration frequencies of the blade were obtained by theoretical calculation and experimental verification,and the relationship between the stress of the blade and the natural frequency and amplitude of the blade was obtained under the first order bending vibration mode.The results show that the theoretical and measured vibration characteristics of the structure were consistent,and the vibration stress and amplitude of the test piece obeyed the linear variation law,which indicated that the proposed test method was effective and could provide fatigue performance data support for the development of the rotor blade.

关 键 词：转子叶片 振动特性 固有频率 高周疲劳 有限元 3阶弯曲振动频率 

分 类 号：TG115.5[金属学及工艺—物理冶金] TB31[金属学及工艺—金属学]