涡轮叶片累积损伤指数模型及服役可靠性评估  

Cumulative damage index model and service reliability evaluation of turbine blade

作　　者：雷世英 孙见忠[1] 刘赫 LEI Shiying;SUN Jianzhong;LIU He(College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 211106)

机构地区：[1]南京航空航天大学民航学院,南京211106

出　　处：《航空学报》2022年第3期244-260,共17页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(91860139,52072176)。

摘　　要：高压涡轮(HPT)叶片是民用航空发动机的关键结构件之一,直接关系到发动机的性能、可靠性与使用寿命。提出了一种HPT叶片服役可靠性评估方法,基于服役条件下的历史工况参数,结合发动机性能模型、叶片关键点应力、温度计算模型、蠕变损伤评估模型对叶片蠕变损伤进行计算,之后考虑服役条件下的多模态数据,针对蠕变失效建立了累积损伤指数模型,融合历史协变量信息对叶片进行服役可靠性评估。仿真结果表明:采用文中定义的蠕变累积损伤指数,可充分利用发动机服役条件下的历史使用信息、状态参数及截尾失效数据,实现特定使用条件下的涡轮叶片服役可靠性评估及剩余寿命预测。相较于传统的可靠性分析方法,累积损伤指数预测模型能够基于单机服役条件提供更加可靠的评估结果,可为航空发动机运行风险评估与视情维修决策提供更好的支持。High Pressure Turbine(HPT)blades are one of the key structural parts of civil aviation engines,directly related to the performance,reliability and service life of the engine.This paper proposes a service reliability assessment method for HPT blades.The blade creep damage is evaluated based on historical flight condition data under service conditions,combined with the engine performance model,the stress and temperature calculation model of the key point,and the creep damage assessment model.After calculation,and in consideration of the multi-modal data under service conditions,a cumulative damage index model is established for creep failure,and the service reliability of the blade is evaluated by fusing the historical covariate information.The simulation results show that the creep cumulative damage index defined in the article can make full use of the historical usage information,state parameters and truncated failure data of the engine under service conditions to realize the service reliability assessment and remaining life prediction of the turbine blades under specific service conditions.Compared with traditional reliability analysis methods,the cumulative damage index prediction model can provide more reliable evaluation results based on the service conditions of a single aircraft and better support for aero engine operation risk assessment and condition-based maintenance decision-making.

关 键 词：涡轮叶片 蠕变寿命 服役可靠性 累积损伤指数模型 模型数据融合 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]