基于P-S-N曲线的三参数法估计叶片最低疲劳极限的实践研究  

Practical Research on Three-Parameter Estimation Method of Minimum Blade Fatigue Limit Based on P-S-N Curve

作　　者：李勋[1] 张东明[1] 姜睿[1] 

机构地区：[1]沈阳发动机设计研究所,辽宁沈阳110015

出　　处：《燃气涡轮试验与研究》2011年第3期20-22,共3页Gas Turbine Experiment and Research

摘　　要：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 aero-engine research field. Also it has been acted as an important index to evaluate the quality of blade fatigue performance. Based on small sample test theory, the three-parameter test method introduced in this paper uses the equation of P-S-N curve to es- timate the minimum fatigue limit of blade. It has the advantages of low test cost and short period. Com- pared with conventional methods, it has a lower relative error, which can meet the requirements of practi- cal engineering.

关 键 词：疲劳极限 疲劳试验 P-S-N曲线 试验方法 

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]