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Numerical analysis of geometrical parameters effect on contact zone under fretting fatigue loading

Ikhlef Chaouch Mohamed, Baltach Abdelghani, Benhamena Ali

Advances in Materials Science

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2022

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Vol. 22, nr 4(74)

5--20

EN

The fatigue process under fretting conditions is characterized by small oscillatory movements due to vibrating or cyclic loads between two surfaces in contact. Two phenomena can arise as a consequence: the surface wear of the bodies in contact, giving rise to the so-called fretting wear. The second phenomenon concerns crack nucleation in the contact region, causing a reduction in the fatigue strength of the component subjected to cyclic loading. This process is called “fretting fatigue”. In the present study, finite element models (2D-FEM) are provided to demonstrate the effect of pad radius on the contact parameters such as: contact pressure, shear traction, stresses, sliding, size of contact line and crack nucleation and its location along the contact line of aeronautical Al2024 alloy under fretting fatigue loading. Six numerical models are utilized to describe the effect of changing pad radii on contact stresses and damage of crack nucleation. The Ruiz parameter criterion should be used to predict the location of crack initiation in the contact zone. Comparison of the finite element results shows that there is a good agreement between the numerical modeling predictions with those analytical results. The stress field, relative slip, and damage parameters in fretting fatigue loading were highlighted. The pad radius substantially affects the distribution of contact parameters. Particular attention must be taken into consideration to this variable when analyzing the structure in fretting fatigue.

2

Evaluation of Material Data to the Numerical Strain‑Life Analysis of the Compressor Blade Subjected to Resonance Vibrations

Bednarz Arkadiusz

Advances in Science and Technology. Research Journal

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2020

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Vol. 14, no 1

184--190

EN

This paper presents the impact of selecting the fatigue material model on the numerically determined fatigue life of a compressor blade. In the work, the first stage compressor blade of the PZL‑10W turbine engine was used. The research object contained a geometric notch with a known location and shape. In numerical studies, 8 fatigue estimation methods were used in the ε ‑N analysis (based on the Manson‑Coffin‑Basquin model). At the same time, three methods for estimating material constants associated with the cyclic hardening were employed. On the basis of the selected models, 24 sets of fatigue parameters were obtained, which were used in numerical studies. The numerical tests were carried out under resonant conditions with amplitudes of 1.5 and 1.8 mm. The numerical tests were confirmed by the experimental fatigue tests. As a result of the above‑mentioned tests, the impact of selecting the material fatigue model and hardening model on the obtained results was determined and they were referred to the initiation of the crack with the length a = 0.2 mm (achieved during experimental studies). The obtained results will constitute the basis for further fatigue tests.

3

Observations on fatigue crack growth and fatigue life of riveted lap joints

Skorupa A., Skorupa M., Machniewicz T., Korbel A.

Mechanics and Control

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2012

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Vol. 31, no. 3

108--114

EN

Effects of variables related to design and production of riveted lap joints representative of longitudinal sheet connections for a pressurized transport aircraft fuselage were experimentally investigated. The specimens from an aircraft Al alloy D16 Alclad sheets of three different thicknesses (1.9, 1.2 and 0.8 mm) were assembled under load control using round head rivets and rivets with the compensator from a P24 Al alloy. For the joints from 1.9 mm thick sheets fatigue tests indicated a dependency of the crack initiation site and crack path on the squeeze force level and on the rivet type. At the same time, increasing the squeeze force led to improved fatigue properties of the joints, specimens assembled using the rivets with the compensator showing fatigue lives consistently longer than joints with the round head rivets. All observed trends have been explained based on hole expansion and load transfer measurements. For thin sheets connected using the round head rivets, local deformations and indentations under the driven rivet head promoted crack initiation and failure in the adjacent sheet. Fatigue test results indicated that the detrimental effect of this type imperfections could outweigh the benefits associated with a decrease in secondary bending due to thinning the sheets. The rivets with the compensator were observed to cause significant local imperfections beneath the manufactured head, which adversely affected the joint fatigue performance.

PL

Sposób zniszczenia i wytrzymałość zmęczeniowa połączeń zakładkowych stosowanych w lotnictwie zależy od wielu czynników technologicznych i konstrukcyjnych, a w szczególności od rodzaju nitu i siły jego zakuwania oraz grubości łączonych blach. W artykule omówiono te zagadnienia na przykładzie blach o różnych grubościach z lotniczego stopu aluminium D16, połączonych zakładkowo za pomocą nitów z łbem kulistym ze stopu PA24. Próbki połączeń poddawane były stałoamplitudowym obciążeniom zmęczeniowym przy różnych poziomach naprężeń nominalnych. Wykazano, że wraz ze wzrostem siły zakuwania nitów rośnie trwałość zmęczeniowa połączenia, a tor pęknięcia oddala się od przekroju netto blachy. Zaobserwowano, że pęknięcia zmęczeniowe pojawiają się w blasze, w której ekspansja otworów nitowych jest mniejsza, co z kolei zależy od rodzaju nitu. Trendy te wyjaśniono na podstawie wyników pomiarów ekspansji otworów nitowych wypełnionych nitami zakutymi przy użyciu różnych sił oraz z uwzględnieniem wyznaczonego eksperymentalnie względnego udziału poszczególnych rzędów nitów w transferze obciążenia. Stwierdzono, że nity z kompensatorem nie są odpowiednie do łączenia cienkich blach; w trakcie zakuwania powstają znaczne deformacje złącza obniżające jego własności zmęczeniowe.