Effect of Natural Aging and Fatigue Crack Propagation Rate on Welded and Non-Welded Aluminum Alloy (AA2219˗T87)
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Department of Mechanical Engineering, International Islamic University, Islamabad, Pakistan
Institut für Metallformung, TU Bergakademie Freiberg, Bernhard-von-Cotta-Strasse 4, 09599 Freiberg (Sachsen), Germany
Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Rome 00186, Italy
Department of Mechanical Engineering, University College of Engineering and Technology, Sargodha, Pakistan
Publication date: 2019-09-01
Corresponding author
Hassan Elahi   

Sapienza University of Rome, Rome 00186, Italy
Adv. Sci. Technol. Res. J. 2019; 13(3):129-143
Aluminum alloys are widely used for fabrication of aircraft, civil structures, and space vehicles. Fatigue life consideration of a material is the most important design criteria in many such critical applications. In this research work, a widely used Aluminum alloy AA2219-T87 was TIG welded using AA2319 as a filler material. The effect of natural aging on Fatigue Crack Propagation Rate (FCPR) of welded and non-welded compact tension (CT) specimens (AA2219˗T87) is studied. The relationship between stress intensity factor (∆K) and crack ratio (a/W) for different value of the crack length in base metal and the welded zone is presented. Paris curves for both welded and non-welded specimens and compared to study the effect of natural aging (NA) on FCGR and compared with non-aged specimens. The results obtained provide a base for the development of Structural Health Monitoring systems for the propagation of crack growth in such components.
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