高温环境下薄壁试件的振动疲劳试验研究  

Thermal vibration fatigue test based on thin-walled specimens

作　　者：蒋波 燕群[1] 邹学锋[1] Jiang Bo;Yan Qun;Zou Xuefeng(Aircraft Strength Research Institute of China,Xi'an 710065,China)

机构地区：[1]中国飞机强度研究所五室,西安710065

出　　处：《飞行器强度研究》2022年第2期25-31,共7页Aircraft Strength Research

摘　　要：本文针对航空发动机薄壁结构,利用试验手段建立热振动综合环境,开展薄壁试验件在高温环境下的模拟声疲劳SN曲线测试,获取试验件在高温条件下的振动应变、加速度响应数据,得到航空发动机典型薄壁结构在高温条件下振动疲劳特性,为航空发动机抗高温声振疲劳设计提供依据。Based on thin-walled specimens of aviation engine,test method is used to establish the comprehensive thermal vibration environment,to carry out the component level test pieces in high temperature under the condition of simulated a coustic fatigue test turn S-N curve,to obtain vibration under the condition of high temperature strain,acceleration response data of aero engine typical structurein high vibration fatigue characteristics under warm conditions provide a basis for the design of high temperatu reresistance vibration fatigue zone of aero engine.

关 键 词：航空发动机 热振动 S-N曲线 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]