某型航空发动机高温总压探针基础激励疲劳寿命研究  

THE FATIGUE LIFE OF AERO ENGINE TOTAL PRESSURE PROBE ON THE BASE EXCITATION

作　　者：左泽敏[1] 武瑞娟[1] 郭斌[1] 

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《机械强度》2015年第2期355-359,共5页Journal of Mechanical Strength

摘　　要：被试航空发动机内涵高温区测试探针的可靠性直接关系发动机试飞试验安全,对其进行疲劳寿命进行预估十分必要。根据Steinberg提出的基于高斯分布和Miner法则的三区间法,结合某型发动机低压涡轮导向叶片截面的总压探针试验时工作环境,推导出发动机基础激励下该总压探针疲劳寿命模型;通过对总压探针所安装的发动机大量试飞试验数据统计分析,得到该总压探针的实际工作温度环境,并进行温度区间划分,计算各区间时间占比、平均频率等;最后通过Ansys软件计算该总压探针在划分的各温度区间下的最大等效应力,代入疲劳寿命模型得出该总压探针的疲劳寿命,从而为被试发动机试飞试验的安全可靠性提供参考。The reliability of total pressure probe is directly related to the test aero engine safe, the probe fatigue life calculation is necessary. According to the three-interval method based on Gaussian distribution, the Miner rule and the actual work environment of pressure probe, the fatigue life calculation model of the pressure probe has been obtained on the base excitation. A large number of test data of test engine pressure probe workspace temperature has been analyzed, the time percent and average frequency of each temperature range are obtained. The equivalent stress of the pressure probe has been obtained by the Ansys finite element software. The time percent, average frequency and equivalent stress of each temperature range has been substituted into the fatigue life calculation model, and acquired the pressure probe fatigue life. The fatigue life is to provide a reference for the safety and reliability of the engine fly test.

关 键 词：航空发动机 压力探针 疲劳寿命 基础激励 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]