Some studies on fatigue crack growth rate of aluminum alloy 6061

Jogi, Bhagwan F.; Brahmankar, P.K.; Nanda, Vikas; Prasad, Rajesh

doi:10.1016/j.jmatprotec.2007.11.302

Cited by 66 publications

(33 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The deviation of the fatigue crack orientation of about 45 • up to 60 • with respect to the vector of the loading force is probably also related to the deformation texture and the vector of maximal shear stress in the cross section. This behavior was also observed in other work dealing with the fatigue of wrought aluminium alloys, but the reason is still not fully understood [29][30][31][32].…”

Section: Discussionsupporting

confidence: 58%

Study of Relation between Shot Peening Parameters and Fatigue Fracture Surface Character of an AW 7075 Aluminium Alloy

Trško

Fintová

Nový

et al. 2018

Metals

View full text Add to dashboard Cite

Shot peening is a well-known surface treatment method used for fatigue life improvement of cyclically loaded structural components. Since three main variables are considered in the peening process (peening intensity, coverage and peening media type), there is no direct way to choose the best combination of treatment parameters for the best performance, thus it has to be based on experience and laboratory tests. When shot peening is performed with inadequate parameters, or the peening process is not stable in time (decrease of the peening pressure, deterioration of the peening media and so on), it can result in significant degradation of the treated component fatigue properties, what is commonly called as the "overpeening" effect. When a premature fatigue fracture occurs in operation, the fracture surface analysis is usually the most important method of revealing the damage mechanism. This work is aimed at the study of the relation between the shot peening parameters and the fatigue fracture surface character on an AW 7075 aluminium alloy with an objective of identifying marks of overpeening and investigating the fatigue crack initiation mechanism. After performing the tests, it was observed that shot peening with optimized parameters creates a surface layer that is able to change the mechanism of the fatigue crack propagation and improve fatigue strength. On the other hand, using extensive peening parameters decrease the fatigue strength due to the creation of surface cracks and surface layer delamination.

show abstract

Section: Discussionsupporting

confidence: 58%

Study of Relation between Shot Peening Parameters and Fatigue Fracture Surface Character of an AW 7075 Aluminium Alloy

Trško

Fintová

Nový

et al. 2018

Metals

View full text Add to dashboard Cite

show abstract

“…Both AA6061 and AA7075 are widely used in applications because of their good mechanical properties, high strength-to-weight ratio, market acceptability, and extensive use in alloy development [21][22][23][24]. Hence, understanding their mechanical properties and fatigue life behaviour can reduce maintenance costs.…”

Section: Methodsmentioning

confidence: 99%

Influence of mechanical properties on load sequence effect and fatigue life of aluminium alloy

et al. 2017

View full text Add to dashboard Cite

Most of the structural components in real applications are subjected to variable amplitude loading. The load sequence may have a significant effect on the number of cycles to failure. However, the relationship between the mechanical behaviour of material and the load sequence effects has scarcely been reported. Therefore, this paper discusses the influence of mechanical properties on the load sequence effect and fatigue life behaviour of aluminium alloys AA6061 and AA7075. Tensile and fatigue tests were performed according to ASTM E8 and ASTM E466, respectively. The variable amplitude loading signal was obtained from the engine mount bracket of an automobile in normal driving conditions. Constant amplitude loading, and high-to-low and low-tohigh spectrum loadings were derived from the variable amplitude loading to assess the effects of load sequence on fatigue life. The results showed that AA7075 has better fatigue life properties compared to AA6061. Both alloys were significantly influenced by load sequences. The number of cycles to failure for low-to-high spectrum loading is about 56 % higher than the CAL for AA6061 compared to about 82 % higher than the CAL for AA7075. Thus, it can be concluded that the load sequence effect was more pronounced on AA7075 compared to AA6061.

show abstract

“…Tensile properties of the alloys AA2024 or the T3 and T81 temper designations (Kuo et al 2005 Table 9. Chemical composition of AA6061 (wt.%) (Jogi et al 2008 Table 10. Heat degradation of the fatigue limit for 7049 (Jones 1972 …”

Section: Figuresmentioning

confidence: 99%

“…The chemical composition of 6061 is given in Table 9. The composition, however, does allow for enough variation to alter the mechanical properties, with the ranges given in Table 9 (Jogi 2008). The overall strength of AA6061 alloy tends to increase with the weight percentage of Si with an average of 45 ksi.…”

Section: Aluminum Alloymentioning

confidence: 99%

“…To balance this, in contemporary AA 6061, the ratio of weight percentage, Mg:Si, is 1.73 (Dorward 1998). AA 6061 is widely used because of its high strength-to-weight ratio, excellent weldability, high ductility, and excellent resistance to stress corrosion cracking, deformation, market acceptance, and relative ease of use (Jogi 2008;Srivatsan et al 2002). In structural components, AA 6061 alloys fail primarily under fatigue loading, due to cracks forming along grain boundaries at the edge of the material and propagating through the material (Jogi 2008;Bhandwale and Vasudevan 1978).…”

Section: Aluminum Alloymentioning

confidence: 99%

See 1 more Smart Citation

Analysis of Lightweight Materials for the AM2 System

Allison¹,

Rushing²,

Garcia³

2014

View full text Add to dashboard Cite

An analysis was performed on potential materials that could replace the 6061-T6 aluminum alloy currently used in the AM2 airfield matting for the purpose of light-weighting the design. An in-depth analysis was performed on metal and polymer matrix composites. However, neither groups of materials produced a suitable material based on operating conditions of the AM2. Newly developed extruded magnesium alloys were identified that could potentially provide weight savings of 30 to 40% while maintaining the current performance of the AM2. In addition, traditional high-strength aluminum alloys were identified that could provide substantial weight savings. However, manufacturing issues existed due to the high strength of these aluminum alloys. Finally, analysis was performed to determine the cost of manufacturing the AM2 using these alternate materials.

show abstract

Some studies on fatigue crack growth rate of aluminum alloy 6061

Cited by 66 publications

References 5 publications

Study of Relation between Shot Peening Parameters and Fatigue Fracture Surface Character of an AW 7075 Aluminium Alloy

Study of Relation between Shot Peening Parameters and Fatigue Fracture Surface Character of an AW 7075 Aluminium Alloy

Influence of mechanical properties on load sequence effect and fatigue life of aluminium alloy

Analysis of Lightweight Materials for the AM2 System

Contact Info

Product

Resources

About