用于眩光应用的2024飞机铝合金超薄板材的加速腐蚀暴露( Accelerated corrosion exposure in ultra thin sheets of 2024 aircraft aluminium alloy for GLARE applications )

ND Alexopoulos CJ Dalakouras P Skarvelis SK Kourkoulis Experimental/ aerospace materials aluminium alloys brittle fracture corrosion protection crystal microstructure ductile-brittle transition fracture hydrogen embrittlement mechanical testing rolling sheet materials tensile strength/ accelerated corrosion exposure ultra thin sheets 2024 aircraft aluminium alloy GLARE applications microstructural analysis mechanical properties hydrogen diffusion hydrogen embrittlement mechanical testing sheet rolling crevice corrosion quantitative tensile properties corrosion degradation ductile-to-brittle transition tensile fracture quasi-cleavage fracture corrosion protection/ A8160B Surface treatment and degradation of metals and alloys A8170 Materials testing A6220M Fatigue, brittleness, fracture, and cracks A6480G Microstructure A8140E Cold working, work hardening post-deformation annealing, recovery and recrystallisation textures A8140G Other heat and thermomechanical treatments A8140L Deformation, plasticity and creep A8140N Fatigue, embrittle

研究了腐蚀暴露对超薄(T<0.4mm)2024-T3铝板厚度的影响。显微组织分析表明，在较低的加速腐蚀时间下，不存在表面劣化，因此，相应的力学性能劣化被认为是由氢扩散和随后的脆化引起的。中等暴露次数会导致断面减小，形成次表面腐蚀产物，而较高暴露次数则会出现明显的缝隙腐蚀。对拉伸试样进行单面或双面预腐蚀，然后进行机械试验。在L和T两个轧制方向上，即使在几分钟的曝光后，力学性能也有所下降，横向轧制方向在相同的曝光时间下具有更高的退化值。研究发现，单面腐蚀试样需要大约两倍的暴露时间才能达到与双面腐蚀试样相同的延性下降。对定量的拉伸性能退化结果进行了讨论；结果与观察到的腐蚀降解机理相关联。通过对拉伸断口“未腐蚀”区域的分析，指出随着腐蚀暴露时间的增加，拉伸断口机制逐渐由韧脆转变。单面试样在腐蚀保护面以下区域呈现准解理断口。

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