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�������պ����ѧѧ�� 2011, Vol. 37 Issue (7) :895-900    DOI:
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2. �����������칤���о���,���� 100024
Determination of damage tolerance and remaining lifefor aeroengine crankcase
Qing Liye1, Wu Sujun1, Zhao Haitao2, Liu Ying2*
1. School of Materials Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Beijing Aeronautical Manufacturing Technology Research Institute, Beijing 100024, China

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Abstract�� In order to ensure the safety of aircraft, fracture assessment for an aeroengine crankcase was carried out. Based on finite element method, a model for the local crankcase fitting seat was established and the geometry factor Y for different crack lengths was obtained. Using the procedure of BS7910, crankcase damage tolerance was calculated and verified by test, the critical allowable crack length is 84.8 mm and the remaining strength decreases with the increase of crack length. The allowable crack dimension and residual strength of weld are smaller than that of parent metal. The test results are in good agreement with the calculated results when crack is small. The remaining life of crankcase was also calculated using Paris formula.
Keywords�� damage tolerance   welds   fatigue crack propagation     
Received 2010-07-08;
About author: ������(1986-),Ů,�ӱ�������,˶ʿ��,qinliye1986@163.com.
������, ���ؾ�, �Ժ���, ��ӱ.���շ�������ϻ��������������ʣ������Ԥ��[J]  �������պ����ѧѧ��, 2011,V37(7): 895-900
Qing Liye, Wu Sujun, Zhao Haitao, Liu Ying.Determination of damage tolerance and remaining lifefor aeroengine crankcase[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(7): 895-900
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