Effect of Prior Corrosion on the S/N Fatigue Performance of Aluminum Sheet Alloys 2024-T3 and 2524-T3

摘要: Aviation industry demand for continuous safety improvement in the face of trends toward increasing service life aircraft and cost control necessitates stronger prevention measures to avoid likelihood ofstructural failures linked widespread damage involving corrosion fatigue. New materials with improved tolerance attributes can improve margin presence damage. An excellent example one such material is new aluminum alloy 2524 (formerly C188) which has fracture toughness fatigue crack growth resistance relative incumbent 2024. In this study, effect prior on S/N performance 1.60 3.17-mm thick 2524-T3 2024-T3 bare sheet was evaluated. The strength approximately 10% greater lifetime failure 30 45% longer than that Two main factors are believed have contributed better 2524: a less damaging configuration pits its resistance.