Fatigue and damage tolerance behaviour of corroded 2024 T351 aircraft aluminum alloy

被引：75

作者：

Kermanidis, AT ^{[1
]}

Petroyiannis, PV ^{[1
]}

Pantelakis, SG ^{[1
]}

机构：

[1] Univ Patras, Dept Mech & Aeronaut Engn, Lab Technol & Strength Mat, Patras 26500, Greece

来源：

THEORETICAL AND APPLIED FRACTURE MECHANICS | 2005年 / 43卷 / 01期

关键词：

fatigue life; fatigue crack growth; fracture toughness; damage tolerance; corroded; 2024; hydrogen embrittlement;

D O I：

10.1016/j.tafmec.2004.12.008

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

The fatigue and damage tolerance behaviour of pre-corroded 2024 T351 aluminum alloy specimens has been investigated and compared to the behaviour of the uncorroded material. The experimental investigation was performed on specimens pre-corroded in exfoliation corrosion environment and included the derivation of S-N and fatigue crack growth curves as well as measurements of fracture toughness. The fatigue crack growth tests were performed for different stress ratios R. To obtain reference material behaviour all mechanical tests were repeated under the same conditions for uncorroded specimens. For the corroded material an appreciable decrease in fatigue resistance and damage tolerance was obtained. The results of the experimental investigation were discussed under the viewpoint of corrosion and corrosion-induced hydrogen embrittlement of the 2024 aluminum alloy. The need to account for the influence of pre-existing corrosion on the material's properties in fatigue and damage tolerance analyses of components involving corroded areas was demonstrated. (c) 2005 Elsevier Ltd. All rights reserved.

引用

页码：121 / 132

页数：12

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