Abstract
A modified Trantina–Johnson model was developed to characterize corrosion fatigue crack growth behavior. Crack growth accumulative methodology based on the Willenborg–Chang rule was used to evaluate the residual lifetimes of corrosion fatigue crack growth. Fatigue crack growth tests were performed on 2524-T3 and 7050-T7451 aluminum alloys subjected to constant amplitude and random spectra loading under the environments of dry air and 3.5% NaCl sodium chloride solution, and the load–environment interaction and load interaction mechanisms were deduced from fractographic analysis. The developed models showed good correlation with experimental results.
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