摘要
在对某型发动机飞行参数记录仪(简称"飞参")记录的数据进行分析的基础上统计了此发动机的实际工作循环载荷谱、高压涡轮转速与排气温度时间相关矩阵;并指出了理论载荷谱与基于飞参数据的实际使用载荷谱的区别;根据温度场和应力场的有限元计算结果,确定叶身中部温度最高点、伸根处应力最大点、叶身根部应力和温度均较高的点为寿命分析考核点;依据数据统计结果确定了叶片的条件疲劳极限,基于EGD-3方法计算了各考核点的疲劳损伤和持久损伤。计算表明:飞参记录仪记录的大量高均值转速的次循环是影响叶片疲劳破坏不可忽视的因素。结合疲劳寿命和持久损伤的计算结果,采用时间-循环分数相加法估算了该叶片的疲劳/持久寿命,初步得出该叶片的实际使用寿命为950h。
This paper introduces the fatigue/endurance calculation procedure of aeroengine's turbine components.The actual cyclic load spectrum of an aeroengine is worked out based on the analysis of FPR data,and the high pressure turbine rotate-exhaust temperature correlation time matrix is obtained by statistical analysis.Futher more,this paper indicates the differences between therotical load spectrum and actual load spectrum.By analysing the distribution of the temperature field and stress field,the life assessment points of the blade are determined,they consist of the point at the middle height of aerofoil whose temperature is the highest,the point at root shank whose stress is the highest and the point at aerofoil root section whose temperature and stress are relative high.According to the statistical results,the condition fatigue limit of turbine blade is ascertained,and then the fatigue damage and the endurance damage of assessment points are calculated based on EGD-3 fatigue analysis theory.The calculation shows that the influence on the blade's fatigue life of the mass high average cycles can not be ignored.Combined fatigue damage with endurance damage,the fatigue/endurance life of the blade is estimated by using the time-cycle fraction plus method,and the life of the blade is ascertained to 950 hours preliminarily.
出处
《应用力学学报》
CAS
CSCD
北大核心
2011年第2期177-184,216,共8页
Chinese Journal of Applied Mechanics
