摘要
本文提出温度及离心载荷作用下三维构件损伤容限分析方法。该方法采用新型双重边界元法分析温度及离心力载荷作用下的涡轮盘三维裂纹应力强度因子 (SIF) ,并结合 Paris公式及 Euler法获得涡轮盘销钉孔边裂纹扩展形状及裂纹扩展寿命 ,进而采用二次估计方法获得涡轮盘裂纹扩展寿命修正值。利用新型双重边界元法分析了销钉载荷、温度场、裂纹形状对轮盘孔边三维裂纹应力强度因子的影响 ,并对以往涡轮盘销钉孔边裂纹扩展寿命分析工程方法的近似性进行了讨论。文中算例表明采用本文方法分析复杂载荷三维裂纹扩展寿命具有效率高、建模方便的优点。
A new method for damage tolerance analysis of three dimensional component under temperature and centrifugal loads is proposed in this paper.First,stress intensity factors of three dimensional cracks on a pin hole of a turbine disk under temperature and centrifugal loads can be analyzed by use of the new type of dual boundary element method.Then incremental Euler forward analysis can be made to determine the shape of crack and crack growth life of the turbine disk step by step, with the help of Paris's formula of crack growth,until the maximum effective range of SIF of the 3 D crack reaches.Next,a second order estimation of crack growth life can be obtained by the trapezoid formula integration through the curve of crack length versus effective range of SIF.By virtue of the new type of dual boundary element method,influences of pin loads,temperature fields and shapes of cracks on stress intensity factors are analyzed.The crack growth life of a turbine disk is obtained using the method given in this paper afterwards.Approximation of an engineering method used before to calculate stress intensity factors of a crack near pin hole of a turbine disk is discussed too.Examples given in the paper demonstrate the high efficiency and easily modeling of three dimensional analysis of crack growth under complex loads by the present method.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第1期87-92,共6页
Journal of Aerospace Power
基金
航空科学基金资助项目 ( 99C5 30 2 6)
国家教委留学回国人员基金资助项目
西北工业大学双新人才基金资助项目
