Multiaxial Fatigue Life Predictions Under the Influence of Mean-Stresses

Fatemi, Ali; Kurath, Peter

doi:10.1115/1.3226066

Cited by 209 publications

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“…Finally, the fatigue life is calculated by assuming a threshold value of the total damage sum. One is usually used for this threshold value as it was done in this paper, but some authors have shown that this limit can vary in a large interval [15,16].…”

Section: Comments About the Methods Using A Cycle Counting Algorithm mentioning

confidence: 99%

Fatigue life under non-Gaussian random loading from various models

Banvillet

2004

International Journal of Fatigue

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is an open access repository that collects the work of Arts et Métiers ParisTech researchers and makes it freely available over the web where possible. AbstractFatigue test results on the 10HNAP steel under constant amplitude and random loading with non-Gaussian probability distribution function, zero mean value and wide-band frequency spectrum have been used to compare the life time estimation of the models proposed by Bannantine, Fatemi-Socie, Socie, Wang-Brown, Morel and Łagoda-Macha. Except the Morel proposal which accumulates damage step by step with a proper methodology, all the other models use a cycle counting method. The rainflow algorithm is used to extract cycles from random histories of damage parameters in time domain. In the last model, where a strain energy density parameter is employed, additionally spectral method is evaluated for fatigue life calculation in the frequency domain. The best and very similar results of fatigue life assessment have been obtained using the models proposed by Socie and by Łagoda-Macha, both in time and frequency domains for the last one.

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Section: Comments About the Methods Using A Cycle Counting Algorithm mentioning

confidence: 99%

Fatigue life under non-Gaussian random loading from various models

Banvillet

2004

International Journal of Fatigue

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“…Since shear cracking is promoted in the crack nucleation of Ti-6Al-4V, shear-based critical plane parameters, particularly ones that include a normal stress parameter to account for normal mean stress effects, tend to work the best in predicting the location and orientation of the crack as well as correlating cycles to failure based on smooth specimen data [1,2,18,[36][37][38][39]. The two parameters that have exhibited the best success in correlating lives of Ti-6Al-4V include the FSK (FatemiSocie-Kurath) parameter [40,41], Key Engineering Materials Vols. 378-379 149…”

Section: Predicting Fretting Crack Formationmentioning

confidence: 99%

The Fretting Fatigue Behavior of Ti-6Al-4V

Neu

2008

KEM

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Abstract. This paper reviews the understanding of fretting fatigue with an emphasis on the behavior of Ti-6Al-4V. Advances in life prediction and assessment approaches are highlighted. The role of microstructure on fretting fatigue and its use to detect fretting fatigue damage can now be considered in assessment strategies. Various palliatives are used to enhance the fretting fatigue resistance. These include treatments to introduce compressive residual stress and surface coatings that reduce friction and/or protect the underlying structural material. IntroductionThis paper reviews the tremendous progress over the past decade to understand and predict the fretting fatigue behavior of Ti-6Al-4V, a common alloy used in applications requiring high specific strength. Fretting fatigue is of particular concern for dovetail attachments between the blades and disks in compressors of aerospace gas turbines, spline couplings of shafts, and mechanical joints in orthopedic implants. In the past decade there has been considerable focus on the fretting fatigue behavior of the duplex microstructure consisting of 60 vol. % equiaxed primary α (hcp structure) and 40 vol. % secondary lamellar α+β domains about 10 to 15 µm in size composed of alternating lathes of α and bcc-structured β. This was the baseline microstructure used for several projects carried out under the Air Force High Cycle Fatigue (HCF) program from 1995 to 2005 [1,2]. Unless noted otherwise, the majority of the data reported in this review was generated on this or similar microstructure. The microstructure has an initial random texture with yield strength 930 MPa, ultimate tensile strength 978 MPa, and cyclic yield strength of 797 MPa [1].The fretting fatigue process can be divided into two parts. The first is the formation of fretting cracks and the second is the growth of fretting fatigue cracks. The drivers for each of these processes are different. Both processes must occur to realize a catastrophic fretting fatigue failure. If fretting cracks do not form, fretting fatigue will not occur. But even if fretting cracks form, a catastrophic fretting fatigue failure will not occur if these cracks do not grow outside of the fretting fatigue process volume (FFPV) associated with the formation of the crack. Hence, the fretting fatigue limit is associated with the threshold limit for propagating the fretting cracks. In most fretting fatigue experiments and in applications, the drivers for fretting crack formation and crack growth outside of the FFPV cannot be easily separated, so there is an apparent coupling between the two. However, experiments involving the independent control of the drivers for fretting crack formation and crack growth (e.g., [3,4]) suggest that these two processes can be separated for the purposes of material response and prediction analyses. This is extremely helpful in understanding how different palliatives mitigate the fretting drivers. Some palliatives are aimed at fretting crack formation while others at reducing the fretting fatigue crack...

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“…We note that the monotonic results only consider the maximum plastic shear strain, γ max , which is used for screening the relative intensity of plastic strains near the different inhomogeneities. In reality, the maximum plastic shear strain amplitude, γ max , is an appropriate measure of the driving force for fatigue crack nucleation based on experimental observations under multiaxial loading conditions (Fatemi and Socie, 1988;Fatemi and Kurath, 1988;McDowell, 1996a, b). Consequently, the latter sections of the section will focus on the plastic shear strain amplitude under realistic cyclic loading conditions.…”

Section: Fea Simulations For Local Cyclic Plasticity: Discussionmentioning

confidence: 99%

“…Strictly speaking, the primary driving force for fatigue crack formation is the maximum local plastic shear strain range, ∆γ p* max or amplitude ∆γ p* max /2, over all possible shear strain planes (Fatemi and Socie, 1988;Fatemi and Kurath, 1988). In this section we apply various cyclic boundary conditions to the debonded idealized inclusion and the idealized void to determine local values of γ max and ∆γ p* max .…”

Section: -48mentioning

confidence: 99%

Microstructure-Property Relations in Fatigue of a Cast A356-T6 Aluminum Alloy

Horstemeyer¹

2001

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The work in this report was a five year effort to foster fundamental advances in microstructureproperty fatigue relations of a cast A356-T6 aluminum alloy. We identified and quantified microstructure-property relations and then developed a mathematical tool for fatigue analysis of a cast A356-T6 aluminum alloy that is used in automotive structural components. We focused on three main areas of research: a wide variety of cyclic experiments in which specimens were examined with scanning electron microscopic imaging, finite element micromechanical modeling, and the development of a macroscale microstructure-property model for fatigue. Collaborations with Lawrence Livermore National Laboratory (LLNL) and Oak Ridge National Laboratory (ORNL) were important to this work. LLNL provided quantitative data for casting pore size, distribution, volume fraction, and nearest neighbor distance using nondestructive methods. ORNL performed solidification modeling of the casting process and provided insight into the silicon particle size, distribution, and volume fraction; the pore size, distribution, volume fraction, and nearest neighbor distance; and the dendrite cell size. EXECUTIVE SUMMARYThe work in this report, performed by Sandia National Laboratories (SNL) in collaboration with Georgia Institute of Technology, was a five year effort to foster fundamental advances in microstructure-property fatigue relations of a cast A356-T6 aluminum alloy. The goal was to identify and quantify microstructure-property relations and then develop mathematical tools for fatigue analysis of a cast A356-T6 aluminum alloy that is used in automotive structural components. This comprehensive experimental-computational fatigue study was conducted in parallel with developing microstructure-property relations for monotonic loading conditions, covered in a companion report (Microstructure-Property Relations for a Cast A356 Aluminum Alloy). We focused on three main areas of research: a wide variety of cyclic experiments in which specimens were examined with scanning electron microscopic imaging, finite element micromechanical modeling, and the development of a macroscale microstructure-property model for fatigue. Collaborations with Lawrence Livermore National Laboratory (LLNL) and Oak Ridge National Laboratory (ORNL) were important to this work. LLNL provided quantitative data for casting pore size, distribution, volume fraction, and nearest neighbor distance using nondestructive methods. ORNL performed solidification modeling of the casting process and provided insight into the silicon particle size, distribution, and volume fraction; the pore size, distribution, volume fraction, and nearest neighbor distance; and the dendrite cell size.The mechanical, physical, and casting properties of this A356 aluminum alloy make it attractive for use in cheaper and lighter engineering components. However, to successfully use cast A356 in long life components, it is necessary to understand its resistance to fatigue. The standard method in determining fa...

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Multiaxial Fatigue Life Predictions Under the Influence of Mean-Stresses

Cited by 209 publications

References 0 publications

Fatigue life under non-Gaussian random loading from various models

Fatigue life under non-Gaussian random loading from various models

The Fretting Fatigue Behavior of Ti-6Al-4V

Microstructure-Property Relations in Fatigue of a Cast A356-T6 Aluminum Alloy

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