7075-T6 aluminium alloy of various thicknesses frequently has been used in the manufacture of today's aging aircraft. Understanding the effect of pitting corrosion in this alloy will aid in design, life prediction, and subsequently life extension for aging aircraft where pitting is concern. Pit-to-crack transition experiments were conducted on 1.600 mm and 4.064 mm 7075-T6 aluminum alloy. Specimens were corroded using a 15:1 ratio of 3.5% NaCl solution and H2O2 prior to fatigue loading. Cracks originating from corrosion pits were visually investigated in order to understand how pit-to-crack transitions occur. All prior corroded specimens in the study fractured from cracks associated with pitting. Pit-to-crack transition was successfully acquired visually. Corroded 7075-T6-4.064 mm specimens experienced more of an overall fatigue life reduction than 7075-T6-1.600 mm specimens. Results indicated that quantities such as pit surface area and surrounding pit proximity are as important as pit depth in determining when and where a crack will form.
Pit-to-crack transition in pre-corroded 7075-T6 aluminum alloy under cyclic loading
Loch-Riss-Umwandlung in vorkorrodierter Aluminiumlegierung 7075-T6 bei zyklischer Belastung
Corrosion Science ; 47 , 9 ; 2185-2198
2005
14 Seiten, 7 Bilder, 2 Tabellen, 12 Quellen
Aufsatz (Zeitschrift)
Englisch
Lochkorrosion , Korrosionsermüdung , Ermüdungsriss , Übergangsverhalten , Übergangswahrscheinlichkeit , Aluminiumzinkmagnesiumlegierung , zyklische Belastung , Ermüdungslebensdauer , Profiltiefe , Korrosionsnarbe , Korrosionsmechanismus , Fraktographie , Voroxidation , Natriumchlorid , Wasserstoffperoxid , Rasterelektronenmikroskopie , energiedispersive Spektrometrie , Luftfahrzeug , Dickenabhängigkeit
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