Effect of contact pressure on fretting fatigue behavior of Ti-1023

Wu, Guo Qing; Liu, X.L.; Li, H.H.; Sha, Wei; Huang, Li Jun

doi:10.1016/j.wear.2014.12.033

Cited by 19 publications

(7 citation statements)

References 40 publications

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“…Some micro-cracks on the subsurface gradually extended to the free surface, resulting in the patch delamination in the fretting contact zones of BM and Cr-Ti samples. More importantly, some micro-cracks initiated from the fretting contact zones expanded to the inner material under the tangential force and fatigue stress [12,21]. The fretting cracks initiated in a large region rather than a point, in the case of PF.…”

Section: Effects Of the Cr-alloyed And Cr-ti Solid-solutionmentioning

confidence: 99%

“…Once the residual compressive stress is released, the crack propagation resistance declines [12]. Figure 12f shows that the fretting crack region had a small depth due to the residual compressive stress decreasing rapidly in the severe worn areas [17,21]. It is thus clear that the low hardness of the Cr-Ti solid-solution layer caused the significant wear in correspondence with the fretting area and thus should be the main factor limiting the improvement in FF properties for the Cr-Ti ?…”

Section: Effects Of the Cr-alloyed And Cr-ti Solid-solutionmentioning

confidence: 99%

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A Comparison Study of Wear and Fretting Fatigue Behavior Between Cr-alloyed Layer and Cr–Ti Solid-solution Layer

Liu

Zhang

et al. 2016

Acta Metall. Sin. (Engl. Lett.)

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This work reported a comparison between the wear and fretting fatigue (FF) behaviors of a Cr-alloyed layer and a Cr-Ti solid-solution layer. The hardness and toughness of both layers were evaluated to support this comparison. The results showed that the Cr-alloyed layer had high surface hardness but poor toughness, while the Cr-Ti solid-solution layer had excellent toughness but low hardness. The FF properties of the modified Ti6Al4V alloy depended on the trade-off between two factors: wear resistance and fatigue resistance. Although the Cr-alloyed layer could effectively resist the wear in fretting areas, its poor toughness caused the fatigue resistance to drop sharply and hence led to a premature failure in FF test. Due to the relatively good fatigue resistance, the Cr-Ti solid-solution layer had slightly higher FF life than that of the Cr-alloyed layer; however, its low hardness resulted in severe wear in correspondence with the fretting area and thus a failure to improve the FF properties of Ti6Al4V alloy. When combined with shot peening post-treatment, the FF life of both layers increased by about three times compared to that of the Ti6Al4V alloy. A further study showed that the poor toughness or low hardness still exerted negative influence on combination-treated samples.

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Section: Effects Of the Cr-alloyed And Cr-ti Solid-solutionmentioning

confidence: 99%

Section: Effects Of the Cr-alloyed And Cr-ti Solid-solutionmentioning

confidence: 99%

A Comparison Study of Wear and Fretting Fatigue Behavior Between Cr-alloyed Layer and Cr–Ti Solid-solution Layer

Liu

Zhang

et al. 2016

Acta Metall. Sin. (Engl. Lett.)

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“…The saturation behaviour observed when the contact pressure exceeded 10 MPa has the same explanation as given in the last part of the last paragraph. We have studied fretting fatigue in another titanium alloy and have found that the fretting fatigue life also remains stable when the contact pressure exceeds a certain value [18].…”

Section: Metallographic Observation and Fracture Analysismentioning

confidence: 99%

Observation of fretting fatigue cracks of Ti6Al4V titanium alloy

Zhi-yan

Liu

et al. 2017

Materials Science and Engineering: A

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Using a test system developed in laboratory, the fretting fatigue mechanism of Ti6Al4V alloy has been studied, with analyses of fracture morphology and composition. The results show that fretting fatigue source area is semi-elliptical and occupies a small proportion of the total fracture surface. The area is relatively flat and smooth and shows traces of friction. With the increase of contact pressure, the depth of the source region first increases rapidly and then stabilizes, but the fatigue strength decreases rapidly and then stabilizes. Fretting causes severe oxidation of the surface. In the interface between the source and the fatigue propagation zone, the contents of O and Fe drop sharply.

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“…High-strength titanium alloys are widely used for aircraft fasteners due to their strong ability to lose weight, excellent corrosion resistance, cold formability, and good compatibility with composite materials. − For high-strength titanium alloy fasteners, fretting damage, as one of the common damage failure modes of aircraft fasteners, is the key factor restricting their reliability and service life . According to the statistics from the United States Air Force, fretting damage accounts for over one-sixth of damage in aero-engines, especially reducing the fatigue limit to only one-third of the ordinary fatigue limit. − Hence, a number of researchers have paid extensive attention to fretting damage in titanium alloys. − …”

Section: Introductionmentioning

confidence: 99%

Wear- and Surface-Fatigue-Mediated Damage during Fretting in a High-Strength Titanium Alloy

Tong

Hua

Zhang

et al. 2022

ACS Appl. Eng. Mater.

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Fretting damage is a key factor restricting the reliability and long life of high-strength titanium alloy fasteners. The fretting damage mechanisms correlated by the interplay relationship between wear damage and surface fatigue damage still need to be addressed. In the present work, fretting damage mechanisms of a high-strength titanium alloy (Ti-15Mo-2.7Nb-3Al-0.25Si, in wt %) were studied in depth. To represent the different matches of strength and toughness, three microstructures with different volume fractions of the primary α phase (A-20%, B-10%, C-1%) were applied to fretting wear tests. The evolution process of fretting wear effected by different microstructures is simulated and quantitatively combined with the sectional inclined angle of scars and the antiwear velocity of wear debris. The results demonstrate that the final worn volume of B-10% is the greatest and the best fretting wear resistance is achieved in A-20%. For wear damage, due to both the poor protective effect of the tribolayer and the fact that the tribolayer is hard to compact, B-10% has the highest wear velocity. For surface fatigue damage, the slip ratio was calculated and used as a bridge to correlate and predict wear damage and fatigue damage. The microcrack damage is most severe in C-1% but slight in A-20%. This study provides valuable experimental data for the prediction of fatigue life for fretting of titanium fasteners, and the quantitative analysis method could be generalized to other alloys.

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Effect of contact pressure on fretting fatigue behavior of Ti-1023

Cited by 19 publications

References 40 publications

A Comparison Study of Wear and Fretting Fatigue Behavior Between Cr-alloyed Layer and Cr–Ti Solid-solution Layer

A Comparison Study of Wear and Fretting Fatigue Behavior Between Cr-alloyed Layer and Cr–Ti Solid-solution Layer

Observation of fretting fatigue cracks of Ti6Al4V titanium alloy

Wear- and Surface-Fatigue-Mediated Damage during Fretting in a High-Strength Titanium Alloy

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