Effect of Natural Aging and Fatigue Crack Propagation Rate on Welded and Non-Welded Aluminum Alloy (AA2219˗T87)
 
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1
Department of Mechanical Engineering, International Islamic University, Islamabad, Pakistan
2
Institut für Metallformung, TU Bergakademie Freiberg, Bernhard-von-Cotta-Strasse 4, 09599 Freiberg (Sachsen), Germany
3
Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Rome 00186, Italy
4
Department of Mechanical Engineering, University College of Engineering and Technology, Sargodha, Pakistan
CORRESPONDING AUTHOR
Hassan Elahi   

Sapienza University of Rome, Rome 00186, Italy
Publication date: 2019-09-01
 
Adv. Sci. Technol. Res. J. 2019; 13(3):129–143
 
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ABSTRACT
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.