摘要
针对航空发动机涡轮叶片未及时检修发生疲劳破坏造成发动机故障问题,本文对航空发动机涡轮叶片做结构可靠性分析,从而进行故障风险评估以及优化涡轮叶片的巡检时间。以我国航空发动机常用的涡轮叶片材料——GH4033作为研究对象,利用应力-强度干涉模型,结合GH4033材料疲劳试验数据,基于P-S-N曲线对涡轮叶片寿命进行预测。同时,在应力参数和安全系数K已知,强度参数未知时,对强度参数作了极大似然估计。结果表明,极大似然估计值接近真实值。
Aiming at the problem of engine failure caused by fatigue failure of aero-engine turbine blades,this paper analyzes the structural reliability of aero-engine turbine blades,so as to carry out fault risk assessment and optimize the inspection time of turbine blades.Taking the turbine blade material GH4033 commonly used in aero-engines in China as the research object,the stress-strength interference model is used to predict the life of turbine blades based on the P-S-N curve combined with the fatigue test data of GH4033 material.At the same time,when the stress parameters and safety factor K are known and the strength parameters are unknown,the maximum likelihood estimation of the strength parameters is made.The results show that the maximum likelihood estimation is close to the true value.
作者
马雄
李翠
杨飘
Ma Xiong;Li Cui;Yang Piao(School of Data Science and Information Engineering,Guizhou Minzu University,Guiyang,China)
出处
《科学技术创新》
2024年第2期209-212,共4页
Scientific and Technological Innovation
关键词
涡轮叶片
疲劳寿命
可靠性分析
极大似然估计
turbine blade
fatigue life
reliability analysis
maximum likelihood estimation
