Fatigue Crack Growth of Aircraft Aluminum Alloys
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.
KeywordsFatigue Crack Crack Growth Rate Fatigue Crack Growth Crack Closure Fatigue Crack Propagation
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