Corrosion-fatigue behaviour of 7075-T651 aluminum alloy subjected to periodic overloads

Modeling of the Effect of Temperature, Frequency, and Phase Transformations on the Viscoelastic Properties of AA 7075-T6 and AA 2024-T3 Aluminum Alloys

“…[6] fits the experimental data in the prescribed temperature range, i.e., 298 K to 573 K (RT to 300°C). § § Linking the mechanical response to the kinetics of the successive microstructural transformations allows us also to test the proposed models for the process of GPZ decomposition and secondary precipitation.…”

“…of Eq. [6] accounts for the joint effect of GPZ I and GPZ II. For AA 2024, this term accounts for the joint effect of GPZ I, GPZ II, and GPBZ, and the last term accounts for the joint effect of h¢ and S¢.…”

“…[6] reflects the effect of secondary precipitates in the storage modulus. The temperatures reported in the literature for the formation of g¢ in AA 7075 and h¢/S¢ in AA 2024 (Tables III and IV) are roughly coincidental with the advent of an increase in the storage modulus leading to a local maximum, while the temperatures for g¢ and h¢/S¢ dissolution are roughly coincidental with the subsequent decrease ( Figure 1).…”

“…These alloys are key representatives of their respective families (i.e., AlZnMg and AlCuMg alloys) that, after proper age-hardening processes, feature excellent mechanical properties [3] and are highly suitable to a number of industrial applications, especially in the aerospace sector and transport industry. For instance, these alloys are widely used in aircraft skin panels, especially in military aircraft [4][5][6] but also in commercial civil aviation aircrafts. [7] Age hardening is based on the formation of intermetallic products from the decomposition of a metastable super-saturated solid solution (SSS), which is obtained by solution treatment and quenching.…”

Corrosion fatigue behaviour of aluminium alloy 6061-T651 welded using fully automatic gas metal arc welding and ER5183 filler alloy

“…The fatigue life of aluminium alloys has been shown to be significantly reduced when tested in a 3.5% NaCl solution compared to the fatigue life of the same alloy in air. This reduction in fatigue life has been attributed to premature crack initiation from surface pits by Chlistovsky et al [7], Rebiere et al [8] and Rokhlin et al [9], and higher crack growth rate resulting from synergistic interaction of fatigue and stress corrosion as observed by Maeng et al [10].…”