The fatigue behaviour of two aluminiumzincmagnesium alloys

Lynch, S.P.; Ryder, D.A.

doi:10.1016/0036-9748(72)90273-6

Cited by 5 publications

(3 citation statements)

References 8 publications

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“…overaging (proposed by Lynch and Ryder (1973)); b. aging inhomogeneities (proposed by Laird and Thomas (1967)); c. precipitate reversion or resolutionizing (proposed by McEvily et al (1963) and Abel and Ham (1966)). overaging (proposed by Lynch and Ryder (1973)); b. aging inhomogeneities (proposed by Laird and Thomas (1967)); c. precipitate reversion or resolutionizing (proposed by McEvily et al (1963) and Abel and Ham (1966)).…”

Section: Csr Behaviormentioning

confidence: 99%

Fatigue Behavior of Aluminum–Lithium Alloys

Prasad

Srivatsan

Wanhill

et al. 2014

Aluminum-Lithium Alloys

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Section: Csr Behaviormentioning

confidence: 99%

Fatigue Behavior of Aluminum–Lithium Alloys

Prasad

Srivatsan

Wanhill

et al. 2014

Aluminum-Lithium Alloys

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“…1 by the wear debris coming out of the mouth of a Stage I crack photographed during a combined tension and torsion test carried out in a SEM on a tubular specimen of Co45Ni. Lynch and Ryder [17] have shown how much Stage I growth rate in an aluminium alloy submitted to torsional fatigue is affected by a modification of the tribological conditions: in the presence of an inert fluid that tends to remove the fretting debris from the crack flanks, a four-fold increase in Stage I crack growth rate is observed, whereas Stage II crack growth rate is decreased.…”

Section: Philosophy Of the Simulationsmentioning

confidence: 99%

A First Stage in the Development of Micromechanical Simulations of the Crystallographic Propagation of Fatigue Cracks Under Multiaxial Loading

Doquet

1998

Fatigue Fract Eng Mat Struct

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Simulations of the nucleation of dislocations, glide and annihilation ahead of a fatigue crack growing along a localized slip band (a ‘long’ Stage I crack or a Stage II crack with a K value close to the threshold) are performed for the case of push–pull or reversed torsion loadings, ignoring, in a first approach, the effect of grain boundaries. The crack growth rates are deduced from the dislocation flux at the crack tip. An influence of the normal stress on the friction between the crack flanks as well as on the condition for dislocation emission is introduced. A slower Stage I growth rate is then predicted for reversed torsion, consistent with experimental data.

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“…(i) aging inhomogeneities 24 (ii) precipitate reversion or resolutioning 25,26 (iii) overaging 27 (iv) dislocation-precipitation interactions leading to precipitate shearing or disordering or, as also, dislocation annihilation 28,29 (v) microcracking of the constituent coarse particles and/or fibres, if present. 30 The degree of softening S at any particular total strain amplitude is calculated from the data as…”

Section: Cyclic Stress Responsementioning

confidence: 99%

Low cycle fatigue and creep–fatigue interaction in short fibre reinforced aluminium alloy composite

Prasad

Vogt

Bidlingmaier

et al. 2010

Materials Science and Technology

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The high temperature low cycle fatigue resistance and the creep–fatigue interaction (CFI) behaviour in terms of the effects of prior fatigue exposure on the subsequent creep behaviour are evaluated and reported for a short alumina fibre (Saffil) reinforced aluminium alloy (Al–12Si–CuMgNi) matrix composite at 623 K. The prior fatigue to study the CFI behaviour was imparted in the form of low cycle fatigue loading in a fully reversed, total strain controlled loading up to a quarter of fatigue life at a total strain amplitude of 0·006 (the plastic strain amplitude at half-life is 0·004), corresponding to a plastic strain energy per cycle value of 0·46 MJ m–3. Subsequently, isothermal tensile creep tests were conducted at 623 K to evaluate the minimum creep rate, rupture time and strain to failure as a function of applied creep stress. Also examined were the fracture features as well as the nature and extent of damage that occurs during low cycle fatigue and creep–fatigue loading. The results obtained on the composite material are compared with those of the matrix aluminium alloy to bring out the effects of reinforcement. The results showed that the reinforcement causes significant loss in high temperature low cycle fatigue resistance in terms of fatigue ductility and cyclic energy parameters. Prior fatigue loading was seen to cause a small but consistent decrease in the creep resistance, which is attributed to the combined effects of mechanical loading and microstructural damage from prior fatigue loading.

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The fatigue behaviour of two aluminiumzincmagnesium alloys

Cited by 5 publications

References 8 publications

Fatigue Behavior of Aluminum–Lithium Alloys

Fatigue Behavior of Aluminum–Lithium Alloys

A First Stage in the Development of Micromechanical Simulations of the Crystallographic Propagation of Fatigue Cracks Under Multiaxial Loading

Low cycle fatigue and creep–fatigue interaction in short fibre reinforced aluminium alloy composite

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