工程上通常用中值寿命作为航空发动机叶片寿命估算依据,这已经不能满足现代航空发动机研制的高可靠性要求。为此,从本世纪初开始,我国航空发动机研制领域应用最低疲劳极限估算叶片的安全寿命,并把它作为评价叶片疲劳性能优劣的一个重要指标。本文介绍的三参数试验方法主要是根据小样本理论,利用P-S-N曲线方程估计叶片的最低疲劳极限。这一方法不仅试验费用低、周期短,而且与常规方法相比,相对误差小,能满足实际工程需要。%The medium life method which was used to evaluate blade life of aero-engine, cannot meet the increased requirements of reliability currently. Since the beginning of this century, the minimum fatigue limit has been used to assess the safe life of blade in
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