基于飞行参数的双发飞机发动机疲劳损伤差异分析  

Fatigue Damage Analysis of Aeroengine in Twin-Engine Aircraft Based on Flight Parameters

作　　者：王永旗[1] 徐可君[2] 夏毅锐[2] 

机构地区：[1]海军航空工程学院青岛校区研究生队,山东青岛266041 [2]海军航空工程学院青岛校区,山东青岛266041

出　　处：《推进技术》2014年第1期101-106,共6页Journal of Propulsion Technology

基　　金：海军航空工程学院博士研究生创新基金(2013111014)

摘　　要：为给飞机发动机单机寿命监控提供依据,对两个用户的同型飞机发动机进行疲劳寿命分析。应用雨流计数法统计分析两个用户飞行参数,获得发动机使用载荷谱。应用线性累积损伤理论计算出关键件的疲劳损伤,将其与标准循环疲劳损伤比较,得到发动机飞行换算率。将同侧发动机的飞行换算率、同一飞机左右发的飞行换算率以及两个用户之间的发动机飞行换算率进行比较。计算表明:同一用户同侧发动机飞行换算率之间和两个用户之间的飞行换算率差异较大,同一飞机左右发飞行换算率之间存在一定差异,部分飞机左右发相差较大;两个用户总体的发动机飞行换算率和各个用户内部的发动机飞行换算率均服从对数正态分布;发动机在实际使用中的高低压转子飞行换算率均服从对数正态分布。In order to provide identifiable life monitoring of single aeroengine,the flight parameters of the same type aeroengine from two users were analyzed and the rain-flow counting method to achieve the effective load spectrum was used.By using linear damage accumulation theory to calculate the fatigue damage of critical parts and comparing the value with fatigue damage caused by standard cycles,the flight conversion ratio was achieved.It was compared for the flight conversion ratio of the same side engines,left and right engine of the same plane and the engines belonging to different users.The results show that the flight conversion ratio difference of the same side engines is relative bigger,the same to the engines belonging to different users,and difference between left and right engine of the same plane is relative smaller.The statistical results show that as a whole the flight conversion ratios of the engines of the two users are submitted to lognormal distribution.The flight conversion ratios of the high and low pressure rotor of some type of engine are submitted to lognormal distribution.

关 键 词：飞行参数 飞行换算率 疲劳损伤 差异分析 

分 类 号：O346.2[理学—固体力学] V23[理学—力学]