Film-assisted fatigue crack propagation in anodized aluminium alloys

Cree, Alistair; Weidmann, G. W.; Hermann, R.

doi:10.1007/bf00633144

Cited by 11 publications

(5 citation statements)

References 8 publications

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“…Contact surfaces can be modified by coating with metallic or non‐metallic materials, 1,2 the use of soft shims 3 . Several studies on fatigue behaviour of aluminium alloys with anodic film have been reported 4–8 . It has been observed that fretting fatigue strength can be improved in Ni–Cr–Mo steel 9 and carbon steel 10,11 by TiN coating.…”

Section: Introductionmentioning

confidence: 99%

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Effects of shot‐peening intensity on fretting fatigue crack‐initiation behaviour of Ti–6Al–4V

Sabelkin

Martinez

Mall

et al. 2005

Fatigue Fract Eng Mat Struct

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A B S T R A C TThe effects of shot-peening intensity on fretting fatigue crack-initiation behaviour of titanium alloy, Ti-6Al-4V, were investigated. Three intensities, 4A, 7A and 10A with 100% surface coverage, were employed. The contact geometry involved a cylinder-on-flat configuration. Residual stress and improvement in fretting fatigue life were directly related to shot-peening intensity. The magnitude of compensatory tensile stress and its location away from the contact surface increased with increasing intensity. The relaxation of residual stress occurred during fretting fatigue which increased with increasing the number of cycles. An analysis using a critical plane-based fatigue crack-initiation model showed that stress relaxation during the fretting fatigue affects life and location of crack initiation. Greater relaxation of the residual stress caused greater reduction of fatigue life and shifted the location of crack initiation from inside towards the contact surface. Modified shear stress range (MSSR) parameter was able to predict fretting fatigue crack-initiation location, which agreed with the experimental counterparts. Also, the computed parameter showed an appropriate trend with the experimental observations of the measured fretting fatigue life based on the shot-peening intensity. a = half-width of a contact zone m = coefficient N = number of cycles N f = fatigue life s 11 = normalized longitudinal normal stress s 22 = normalized transverse normal stress s 12 = normalized shear stress S 11 = longitudinal normal stresses S 22 = transverse normal stress S 12 = shear stress S 12 max = shear stresses due to the maximum applied axial force S 12 min = shear stresses due to the minimum applied axial force S b max = maximum applied force of fatigue cycle S b min = minimum applied forces of fatigue cycle Correspondence: S. Mall.

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Section: Introductionmentioning

confidence: 99%

“…3 Several studies on fatigue behaviour of aluminium alloys with anodic film have been reported. [4][5][6][7][8] It has been observed that fretting fatigue strength can be improved in Ni-Cr-Mo steel 9 and carbon steel 10,11 by TiN coating.…”

Section: Introductionmentioning

confidence: 99%

Effects of shot‐peening intensity on fretting fatigue crack‐initiation behaviour of Ti–6Al–4V

Sabelkin

Martinez

Mall

et al. 2005

Fatigue Fract Eng Mat Struct

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“…Therefore, it is postulated that the slightly more porous EPAD and ACDC anodic oxide films exhibit a higher level of zone shielding within the oxide film when compared to CAA. Although this greater porosity is not entirely evident in the images shown in Figure 10, there is some nanoindentation evidence [15] to confirm that CAA produces an oxide film which is slightly harder and more dense and compact, i.e. less porous, than the other processes tested.…”

Section: 11mentioning

confidence: 91%

“…In this instance a 22% reduction to fatigue strength was observed. Although the influence of anodising on fatigue crack initiation is quite well understood, additional evidence presented in the literature [13,14,15] suggests that fatigue crack growth rates can also be influenced by the presence of a thin surface film or coating. This aspect of the problem was not considered further in this study.…”

Section: Anodising and Fatiguementioning

confidence: 99%

Fatigue and fracture assessment of toxic metal replacement coatings for aerospace applications

Cree

Devlin

Critchlow

et al. 2010

Transactions of the IMF

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The use of corrosion resistant, and adhesion promoting films and coatings is established industrial practice for many fatigue sensitive components and structures. However, recent environmental legislation restricting the use of a range of toxic heavy metals and their derivative processes, such as chromic acid anodising (CAA), has meant that a number of new coatings systems and pretreatments are currently being developed to replace the traditional processes still in use. Typical of these new systems are the boric acid-sulphuric acid anodising (BSAA) process which can be modified to provide excellent adhesive bonding properties; the sulphuric acid anodising process, which includes an additional electrolytic phosphoric acid deoxidizing stage (EPAD) to produce a duplex oxide layer, and the recently patented ACDC sulphuric acid anodising process which produces a two layered oxide film which can be tailored to produce different porosity volume fractions within each layer. This communication reports the preliminary findings of a study carried out to assess the fatigue response of Al2618:T6 aluminium alloys to these new processes. In contrast to CAA anodising, the initial results indicate that the EPAD and ACDC processes do not appear to have a significant affect on fatigue.

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“…Improving the mechanical properties of surface by leaving the treated region in compressive residual stress states has the major benefit [27][28][29][30][31][32].…”

Section: Cover Platementioning

confidence: 99%

A Study on Surface Modification of Al7075-T6 Alloy against Fretting Fatigue Phenomenon

Mohseni

Zalnezhad

Sarhan

et al. 2014

Advances in Materials Science and Engineering

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Aircraft engines, fuselage, automobile parts, and energy saving strategies in general have promoted the interest and research in the field of lightweight materials, typically on alloys based on aluminum. Aluminum alloy itself does not have suitable wear resistance; therefore, it is necessary to enhance surface properties for practical applications, particularly when aluminum is in contact with other parts. Fretting fatigue phenomenon occurs when two surfaces are in contact with each other and one or both parts are subjected to cyclic load. Fretting drastically decreases the fatigue life of materials. Therefore, investigating the fretting fatigue life of materials is an important subject. Applying surface modification methods is anticipated to be a supreme solution to gradually decreasing fretting damage. In this paper, the authors would like to review methods employed so far to diminish the effect of fretting on the fatigue life of Al7075-T6 alloy. The methods include deep rolling, shot peening, laser shock peening, and thin film hard coatings. The surface coatings techniques are comprising physical vapor deposition (PVD), hard anodizing, ion-beam-enhanced deposition (IBED), and nitriding.

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Film-assisted fatigue crack propagation in anodized aluminium alloys

Cited by 11 publications

References 8 publications

Effects of shot‐peening intensity on fretting fatigue crack‐initiation behaviour of Ti–6Al–4V

Effects of shot‐peening intensity on fretting fatigue crack‐initiation behaviour of Ti–6Al–4V

Fatigue and fracture assessment of toxic metal replacement coatings for aerospace applications

A Study on Surface Modification of Al7075-T6 Alloy against Fretting Fatigue Phenomenon

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