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Fatigue Crack Growth of Aircraft Aluminum Alloys

  • Sp. G. Pantelakis
  • Al Th. Kermanidis
Part of the Solid Mechanics and its Applications book series (SMIA, volume 152)

The microstructural characteristics and the influence of existing corrosion on fatigue crack growth in 2024 T351 aircraft aluminium alloy are investigated. Examined is the elongated grain morphology due to the rolling process that exhibited higher crack growth resistance than the microstructure of the sheet material with smaller equiaxed grains. Moreover, plate microstructure with high purity composition offered better damage tolerance characteristics in contrast to the conventional sheet microstructure. Shown is the need to account for the influence of pre-existing corrosion on the aluminum alloys in order to obtain more reliable results from fatigue and damage tolerance analyses of components with corroded areas.

Keywords

Fatigue Crack Crack Growth Rate Fatigue Crack Growth Crack Closure Fatigue Crack Propagation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer Science+Business Media B.V 2008

Authors and Affiliations

  • Sp. G. Pantelakis
    • 1
  • Al Th. Kermanidis
    • 2
  1. 1.Laboratory of Technology and Strength of Materials (LTSM)Department of Mechanical Engineering & Aeronautics University of PatrasPatrasGreece
  2. 2.Department of Mechanical and Industrial EngineeringUniversity of ThessalyVolosGreece

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