某系列发动机压气机转子叶片技术寿命研究  

Investigation of Rotor Blade Technology Life for a Series of Aeroengine Compressor

作　　者：高庆[1] 

机构地区：[1]贵州航空发动机研究所,贵州平坝561102

出　　处：《航空发动机》2008年第3期22-26,共5页Aeroengine

摘　　要：提出了1种基于"叶片剩余振动疲劳强度储备"概念的寿命预估法。在大量的计算分析和试验基础上,综合考虑叶片低循环疲劳寿命、稳态应力、构件的实际疲劳强度衰减规律、实测振动应力等因素,并结合外场使用情况,对压气机转子叶片进行了寿命综合评估。该方法已应用在某系列发动机压气机转子叶片技术寿命研究中,对压气机转子叶片寿命的研究而言是一次有益的探索。A life prediction method based on the concept of ＂the fatigue strength margin of blade residual vibration＂ was presented. Based on lots of computational analyses and experiments, the blade low cycle fatigue life, steady stress, law of actnal fatigue strength degradation and observed vibration stress were considered comprehensively and the compre- heasive life assessment for compressor rotor blade was performed incorporating the field operating condition. The method has been used to investigate the rotor blade life for a series of aeroengine compressor. This is a beneficial exploration to the compressor rotor blade life.

关 键 词：压气机 航空发动机 转子叶片 振动疲劳 寿命 

分 类 号：V216.21[航空宇航科学与技术—航空宇航推进理论与工程] V263.5