高速旋转发动机叶片模型的断裂力学分析

陈爱军; 陈铖; 章定国; 廖连芳

高速旋转发动机叶片模型的断裂力学分析

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

基金项目: 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)

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出版历程
- 收稿日期: 2010-10-07
- 修回日期: 2011-01-22
- 刊出日期: 2011-09-28

Fracture mechanics analysis for rotating blade model of aero-engine

1.
School of Sciences, Nanjing University of Science and Technology, Nanjing 210094, China
2.
Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

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.
- 叶片 /
- 裂纹 /
- 应力强度因子 /
- 权函数法 /
- 临界转速
Abstract: 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.
- blade /
- crack /
- stress intensity factor /
- weight function method /
- critical rotate speed

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参考文献(12)

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