高速旋转发动机叶片模型的断裂力学分析  

Fracture mechanics analysis for rotating blade model of aero-engine

作　　者：陈爱军[1] 陈铖[1] 章定国[1] 廖连芳[2] 

机构地区：[1]南京理工大学理学院,南京210094 [2]中国航空工业集团公司沈阳发动机设计研究所,沈阳110015

出　　处：《航空动力学报》2011年第9期2044-2048,共5页Journal of Aerospace Power

基　　金：中国一航航空推进技术验证计划(APTD-1104-02);南京理工大学自主科研专项计划(2010GJPY026)

摘　　要：建立了带裂纹平板叶片的断裂力学模型.首先由已知参考均布载荷下的应力强度因子,得到了带裂纹叶片的权函数;然后根据权函数思想,推导出了高速旋转叶片裂纹尖端处的应力强度因子公式;最后,由断裂准则给出了叶片飞断时临界转速的估算方法.算例研究表明,裂纹的深度和位置对裂纹尖端处的应力强度因子和叶片飞断时的临界转速有很大的影响.An analysis model for the cracked plate of blade was established using fracture mechanics method.Firstly,the weight function for blade containing a single edge crack was derived from one reference stress intensity factor under uniform load.Secondly,the stress intensity factor at the tip of crack of rotating blade was calculated using weight function method.Finally,critical rotate speed of blade was inferred on the basis of fracture criterion.The analysis of examples shows that the depth and position of crack in blade have much influence on the stress intensity factor and critical rotating speed.

关 键 词：叶片 裂纹 应力强度因子 权函数法 临界转速 

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] O346.1[理学—固体力学]