某航空发动机热端件寿命消耗计算模型及寿命监视

在航空发动机热端件寿命消耗模型中考虑了离心负荷、热负荷及蠕变的影响。在计算中通过对一般军用发动机飞行剖面的数据处理提取出影响寿命的３个主要循环进行其寿命消耗的计算。应用线性累积损伤理论将各种形式的寿命消耗百分数叠加以得到每次飞行发动机的寿命消耗和剩余寿命。以航空发动机高压涡轮盘作为算例，针对榫槽第二喉部、轮缘与腹板连接处和盘中心孔三危险处进行了寿命消耗计算。按本文模型编制的计算程序可对发动机热端件进行实时寿命监视

A COMPUTATIONAL MODEL FOR LIFE CONSUMPTION AND LIFE MONITORING OF AEROENGINE

A mathematical model is set up for life consumption of the high temperture parts in aero-engine.Low Cycle Fatigue, Thermal Fatigue,Creep,and any combination of them are considered in the model.Engine life usage must be determined for each flight mode by its mission analysis.A military engine flight mode can be divided into three types of cycle:zero-maximum RPM-zero,cruise-intermediate-cruise,idle-maximum-idle.The relative life consumption and remaining life of the high temperature parts of an engine for every flight can be obtained by the Miner's Rule summation.As an example,the life consumption of the high pressure turbine disk of a given engine is calculated by the model.Based on the mathematical model and its computational program in C language,the real-time life monitoring of high temperature parts in an aeroengine can be conducted.