北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (7): 895-900.

• 论文 • 上一篇    下一篇

航空发动机机匣损伤容限评估及剩余寿命预测

秦丽晔1, 吴素君1, 赵海涛2, 刘颖2   

  1. 1. 北京航空航天大学 材料科学与工程学院, 北京 100191;
    2. 北京航空制造工程研究所,北京 100024
  • 收稿日期:2010-07-08 出版日期:2011-07-30 发布日期:2011-08-04
  • 作者简介:秦丽晔(1986-),女,河北沧州人,硕士生,qinliye1986@163.com.

Determination of damage tolerance and remaining lifefor aeroengine crankcase

Qing Liye1, Wu Sujun1, Zhao Haitao2, Liu Ying2   

  1. 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
  • Received:2010-07-08 Online:2011-07-30 Published:2011-08-04

摘要: 使用有限元的方法,建立了某航空发动机机匣安装座处局部模型,计算得到了不同尺寸裂纹的应力强度因子的形状因子Y.基于BS7910评定方法,利用失效评估图(FAD,Failure Assessment Diagram)确定了机匣安装座结构在工作应力下的可接受裂纹尺寸为84.8 mm,结构的剩余强度随裂纹尺寸的增加而显著降低,焊缝较母材具有更低的损伤容限和剩余强度.使用缩小宽度模拟验证件模拟工作状态载荷进行了验证试验,当裂纹尺寸与试样宽度比值较小时,与模拟验证件的评估结果基本吻合.根据Paris公式,构件在工作应力下的剩余寿命为74 238周次.

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.

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