International Journal of Fatigue最新文献

英文中文

Correction of erroneous normal stress calculation for critical plane based fatigue criteria

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-18 DOI: 10.1016/j.ijfatigue.2025.108822

Jana Christine Faes , Tien Dung Dinh , Nicolas Lammens , Wim Van Paepegem

Fatigue criteria for nonproportional loading often rely on the premise that damage initiates on the plane with the highest shear stress range. Due to the reciprocity of shear stress, at least two equivalent planes in 3D space can be found. Among these, the most critical plane is determined by its normal stress, as tensile stress on the crack surface facilitates damage formation. Many loading scenarios give rise to multiple or even an infinite number of planes with identical shear stress ranges, making it challenging to identify the most critical one. Current critical plane search methods do not address this problem, even though incorrect assessments of normal stress can lead to substantial overestimation of the fatigue life — by up to several orders of magnitude. In this work, we present a new procedure that reliably identifies the most critical plane by explicitly considering normal stress when multiple planes exhibit equivalent shear stress ranges. Our findings show that state-of-the-art methods introduce substantial errors in more than 10% of sinusoidal loading scenarios by failing to account for this additional criterion.

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引用次数: 0

Retarded fatigue crack growth in Fe–15Mn–10Cr–8Ni–4Si via reversible γ ↔ ε transformation 通过可逆γ↔ε转变延缓Fe-15Mn-10Cr-8Ni-4Si的疲劳裂纹扩展

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-18 DOI: 10.1016/j.ijfatigue.2025.108829

Fumiyoshi Yoshinaka, Takahiro Sawaguchi, Susumu Takamori, Satoshi Emura, Digvijay Singh

Crack growth and closure behavior in Fe–15Mn–10Cr–8Ni–4Si steel were investigated. The steel showed slower crack growth compared with SUS316. This was mainly due to the pronounced effect of crack closure. The gradual cyclic hardening in the Fe–15Mn–10Cr–8Ni–4Si steel have enhanced the effect of plasticity-induced crack closure compared with that in SUS316. Additionally, the rough fracture surface consisting of facets and crack branching of the Fe–15Mn–10Cr–8Ni–4Si steel have caused fracture surface roughness-induced crack closure. Transmission electron microscopy observations of the deformation microstructure beneath the fracture surface revealed that martensitic transformation occurred in both the Fe–15Mn–10Cr–8Ni–4Si steel and SUS316, with the latter exhibiting more pronounced transformation. Therefore, although transformation-induced crack closure was more enhanced in SUS316, it did not outweigh the effects of other crack closure mechanisms. The difference in crack growth rate between the Fe–15Mn–10Cr–8Ni–4Si steel and SUS316 remained even when the effect of crack closure was removed. The highly reversible nature of the dislocation motion manifesting as reversible γ ↔ ε transformation works as a crack retardation mechanism in Fe–15Mn–10Cr–8Ni–4Si steel.

研究了Fe-15Mn-10Cr-8Ni-4Si钢的裂纹扩展和闭合行为。与SUS316相比，该钢的裂纹扩展速度较慢。这主要是由于裂缝闭合效果显著。与SUS316相比，Fe-15Mn-10Cr-8Ni-4Si钢的逐渐循环硬化增强了塑性裂纹闭合的效果。此外，Fe-15Mn-10Cr-8Ni-4Si钢的粗糙断口由切面和裂纹分支组成，导致断口表面粗糙度导致裂纹闭合。断口变形组织透射电镜观察表明，Fe-15Mn-10Cr-8Ni-4Si钢和SUS316均发生马氏体相变，SUS316相变更为明显。因此，虽然在SUS316中相变诱导的裂纹闭合更强，但它并没有超过其他裂纹闭合机制的影响。即使去除裂纹闭合的影响，Fe-15Mn-10Cr-8Ni-4Si钢与SUS316之间裂纹扩展速率的差异仍然存在。在Fe-15Mn-10Cr-8Ni-4Si钢中，位错运动的高度可逆表现为可逆γ↔ε转化，这是一种裂纹延迟机制。

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引用次数: 0

A TCD-based statistical method to assess the impact of surface roughness and pores on the fatigue strength of LPBF Inconel 718 specimens

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-18 DOI: 10.1016/j.ijfatigue.2025.108821

Lorenzo Romanelli , Ciro Santus , Giuseppe Macoretta , Michele Barsanti , Bernardo Disma Monelli , Ivan Senegaglia , Adrian Hugh Alexander Lutey , Hossein Rajaei , Cinzia Menapace , Matteo Benedetti

The aim of this study is to model the impact of surface roughness and pores on the fatigue strength of plain and V-notched specimens made of Inconel 718 under as-built and machined conditions and produced by laser powder bed fusion (LPBF). Combining fractographic analyses with the Gumbel and the exponential distribution functions, the statistical analyses of the diameters of the pores and of their distances from the external surfaces were implemented. Surface roughness scans were performed with the optical profilometer. The finite element (FE) method was used to simulate a sample of pores generated by the identified probability distributions and the surface profiles obtained with the scans. The theory of critical distances (TCD) was implemented combining the blunt and sharp V-notched specimens in the machined condition, and it was combined with the Gumbel or the generalized extreme values distributions to calculate the fatigue strength concentration factors provided by the pores and the surface roughness at 99% of probability. Finally, the proposed model was used to predict the fatigue strength of the blunt V-notched specimens in the as-built conditions and of the plain specimens in the as-built and machined conditions resulting appreciably similar to the experimental data.

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引用次数: 0

High-R Notched HCF performance of macrozones in Ti-6Al-4V

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-18 DOI: 10.1016/j.ijfatigue.2025.108820

Yan Gao , Nigel Martin , Jamie Moschini , David Dye

The hypothesis is examined that the macrozones that can occur in large Ti-6Al-4V forgings, in combination with the effects of stressed volume and sustained loads, can result in a debit in high cycle fatigue (HCF) performance, which would be of concern in jet engine applications. Here, the effect of placing a notch root in hard vs. soft oriented macrozones, i.e.

{0002}

parallel or perpendicular to the loading direction, respectively, were examined. The deformation features associated with crack initiation were analysed. A significant (

10 \times

) variation in life was observed, as low as 5.6 × 10⁶ cycles in hard macrozones compared to 58.6 × 10⁶ cycles in soft macrozones, at a peak notch root stress of 912 MPa and load ratio

R

of 0.5. Local macrozones were found neighbouring the initiation facets, which were subsurface. Compared to plain fatigue, LCF or dwell fatigue, the initiating faceted grains possessed low dislocation density, which were predominantly of basal

〈 a 〉

character.

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引用次数: 0

Residual stress relaxation of railway gradient S38C steel during fatigue crack growth by neutron imaging and diffraction 铁路梯度钢S38C疲劳裂纹扩展过程中残余应力松弛的中子成像和衍射分析

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-17 DOI: 10.1016/j.ijfatigue.2025.108826

Feifei Hu , Tianyu Qin , Yuhua Su , Lunhua He , Ni Ao , Joseph Don Parker , Takenao Shinohara , Shengchuan Wu

The S38C steel axles show excellent fatigue resistance due to large-depth compressive residual stress (CRS) along the axial direction. However, residual stress (RS) relaxation may occur in case of a fatigue crack, which results in a reduced damage tolerance and a shortened service lifetime. Destructive methods cannot retain the residual stress and associated retardation effect of cracks. To tackle this concern, time-of-flight (TOF) methods of Bragg-edge transmission (BET) imaging and neutron diffraction (ND) were introduced to quasi-in situ investigate the residual stress relaxation during fatigue crack propagation by single-edge notch bending samples. The BET imaging results indicate that lattice parameters change as the crack develops, which then leads to a decrease of residual strain ε₁₁₀. It was clearly found that the maximum ε₁₁₀ was released by ∼ 31.4 % if a crack propagated to 10.0 mm. In addition, it was observed from ND results that all three RS components decrease with the crack growth. By contrast, the CRS in the axle surface was almost fully released when the crack propagated to the matrix material zone (from −566 to 41 MPa). Furthermore, RS relaxation was validated by the extended finite element method, and the effect of stress relaxation on stress field at the crack tip was also evaluated meticulously. These new insights confirm stress relaxation in railway S38C axles during crack propagation, which must be considered while carrying out the structural integrity assessment.

S38C钢车轴由于轴向深度压残余应力（CRS）而表现出优异的抗疲劳性能。然而，在疲劳裂纹的情况下，残余应力（RS）松弛可能会导致损伤容限降低和使用寿命缩短。破坏性方法不能保留裂纹的残余应力和相关的延迟效应。为了解决这一问题，引入飞行时间（TOF）的布拉格边缘透射（BET）成像和中子衍射（ND）方法，准原位研究了单边缘缺口弯曲试样在疲劳裂纹扩展过程中的残余应力松弛。BET成像结果表明，随着裂纹的扩展，晶格参数发生变化，从而导致残余应变ε110减小。当裂纹扩展到10.0 mm时，最大ε110释放量为~ 31.4%。此外，从ND结果中可以看出，随着裂纹的扩展，三个RS分量均减小。当裂纹扩展到基体材料区（- 566 ~ 41 MPa）时，轴表面的CRS几乎完全释放。采用扩展有限元法验证了应力松弛的有效性，并详细评价了应力松弛对裂纹尖端应力场的影响。这些新发现证实了铁路S38C轴在裂纹扩展过程中的应力松弛，这是进行结构完整性评估时必须考虑的。

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引用次数: 0

Accelerating phase transformation in a non-equiatomic CoCrNi alloy under low-cycle fatigue deformation 低周疲劳变形下非等原子CoCrNi合金的加速相变

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-16 DOI: 10.1016/j.ijfatigue.2025.108818

Z.Y. Li , H.Q. Liu , Z.Y. Ni , S.Y. Peng , Y.Z. Tian

Stacking fault energy (SFE) plays a key role in the deformation mechanisms and mechanical behavior of metallic materials. However, the low-cycle fatigue (LCF) behavior of low SFE materials remains unclear. This work presents the monotonic tensile and LCF behaviors of Co₃₅Cr₄₂Ni₂₃ alloy with very low SFE. In contrast to the dislocation-dominated deformation mechanism in equiatomic CoCrNi alloy, planar patterns of stacking faults (SFs) and hexagonal close-packed (HCP) phase dominated in the Co₃₅Cr₄₂Ni₂₃ alloy during fatigue deformation. At equivalent stress levels, a substantial amount of HCP phase was generated during LCF deformation, which was significantly higher than that under monotonic deformation. This accelerated phase transformation is attributed to the SFs-dominated mechanism and the strain accumulation mechanism of fatigue deformation.

层错能在金属材料的变形机制和力学行为中起着关键作用。然而，低SFE材料的低周疲劳（LCF）行为尚不清楚。本文研究了Co35Cr42Ni23合金在极低SFE条件下的单调拉伸和LCF行为。与等原子CoCrNi合金的位错主导变形机制不同，Co35Cr42Ni23合金在疲劳变形过程中以层错（SFs）和六方密堆积（HCP）相为主。在等效应力水平下，LCF变形过程中产生了大量的HCP相，显著高于单调变形。这种加速相变主要是由于sfs主导的相变机制和疲劳变形的应变积累机制。

引用次数: 0

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-16 DOI: 10.1016/j.ijfatigue.2025.108825

Lanzhou Liu , Yifei Gao , Xin Chen , Zhanbin Liu , Xuan Ren , Mingliang Zhu

Complicated interaction of twin boundary with dislocation plays a pivotal role in mechanical properties. In this study, the effect of TB on the fatigue crack initiation of Inconel 718 superalloy was investigated in vacuum environment of 650 ℃. A three-point bending fatigue test with preprocessed plate specimen was applied to trigger multi-source crack initiation. Plenty of slip band patterns and crystallographic orientations were acquired by SEM and EBSD. Twin boundary cracking was observed as the main fatigue failure mode. Crack propagation was accomplished by connecting twin boundary cracks with transgranular cracking. Perfect deformation compatibility of twin boundary was achieved only when both symmetric slip systems operated the collinear slip directions on twin boundary. It was proved that TB cracking was not prone to occur when its angle with maximum tensile stress direction is less than 10°. Twin boundary is more vulnerable with larger angle, especially at about 56° or 85°. A new orientation case that slip systems parallel to twin boundary in one or both of matrix and twin are activated has been revealed to enrich orientation-related twin boundary cracking mechanism.

孪晶界与位错的复杂相互作用对材料的力学性能起着关键作用。在650℃的真空环境下，研究了TB对Inconel 718高温合金疲劳裂纹萌生的影响。采用三点弯曲疲劳试验，对经预处理的板状试样进行了多源裂纹萌生试验。通过SEM和EBSD获得了大量的滑移带图和晶体取向。双晶界裂纹是主要的疲劳破坏模式。裂纹扩展是通过连接孪晶界裂纹和穿晶裂纹来实现的。只有当两种对称滑移系统在孪晶界上沿共线滑移方向运行时，孪晶界才能实现完美的变形协调。结果表明，当其与最大拉应力方向夹角小于10°时，不容易发生TB裂纹。孪晶界在角度较大时更易受到破坏，尤其是在56°和85°左右。揭示了一种新的取向情况，即在基体和孪晶中激活一个或两个平行于孪晶边界的滑动系统，丰富了与取向有关的孪晶边界开裂机制。

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引用次数: 0

Fatigue crack propagation in functionally graded bi-material steel obtained through wire-arc additive manufacturing

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-16 DOI: 10.1016/j.ijfatigue.2025.108819

J.L. Galán Argumedo, A. Suresh, Z. Ding, V. Bertolo, T.E. Reinton, A.C. Riemslag, M.J.M. Hermans, V.A. Popovich

This study concentrates on the fatigue crack propagation behaviour of a high-strength low-alloy (HSLA) steel and austenitic stainless (AS) steel bi-material part, as obtained by wire arc additive manufacturing (WAAM). Due to partial mixing in the weld pool, the first layer of AS steel laid onto the previously deposited HSLA steel results in a diluted interface layer of distinct chemical and microstructural characteristics. Average Paris parameters are obtained for the interface layer along transverse and longitudinal planes to the deposition direction (BD-LD plane: m = 2.79, log₁₀(C) = –7.83 log₁₀(da/dN)) (BD-TD plane: m = 3.47, log₁₀(C) = –8.39 log₁₀(da/dN)). However, it is observed that this interface layer manifests an intriguing crack propagation behaviour. FCGR consistently drop as the crack front transitions from undiluted AS steel to the interface. At ΔK = 20 MPa⋅m^0.5, the greatest Δ is −0.77 log₁₀ steps (R = 0.1). As cracks near the HSLA fusion line, rates re-accelerate up to + 0.75 log₁₀ steps (R = 0.5). The phenomenon is attributed to the interplay between deformation-induced martensitic transformation and pre-existing allotropic martensite. Our findings, derived from a series of fatigue tests in correlation with multiscale microstructural and fracture characterization, offer insights into the damage-tolerant behaviour of these bi-material structures.

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引用次数: 0

Heat build-up and thermo-mechanical fatigue life optimization of aircraft tire using deformation index concept 基于变形指数概念的飞机轮胎热累积及热机械疲劳寿命优化

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-14 DOI: 10.1016/j.ijfatigue.2025.108815

Zixu Shen , Qian Wang , Peng Li , Xiaolin Li , Fanzhu Li

Aircraft tires are a critical component for the takeoff, landing, and taxiing of an aircraft. Under high-speed and heavy-load conditions, aircraft tires are subjected to huge stresses and remarkable heat build-up. Improving tire safety and service life is crucial. The deformation index can be used to judge the control modes of different components of the tire, such as strain control, stress control, or energy control. This study details the calculation of the deformation index and emphasizes the need to vary only stiffness while holding viscoelastic parameters constant during perturbation analysis. Combined with the finite element analysis and the user-defined subroutine, the contour plot of the deformation index in each component of the aircraft radial tire under certain load, pressure, and speed conditions was obtained. On this basis, material stiffness optimized schemes for typical components in tire (such as tread, cushion, and innerliner) were proposed based on the thermo-mechanical coupling analysis method of heat build-up and fatigue life. The systematic results confirm the effectiveness of using the deformation index to improve the fatigue life of aircraft tires. When the stiffness of the tread and cushion rubber are increased by 50 % and 30 %, respectively, and the stiffness of the innerliner rubber is reduced by 50 %, the highest temperature in the shoulder region is reduced by 4.17 °C, and the fatigue life of the aircraft tire is even increased by five times.

飞机轮胎是飞机起飞、降落和滑行的关键部件。在高速和重载条件下，飞机轮胎承受着巨大的压力和显著的热量积累。提高轮胎的安全性和使用寿命至关重要。变形指标可用于判断轮胎不同部件的控制方式，如应变控制、应力控制或能量控制。本研究详细介绍了变形指数的计算，并强调在摄动分析过程中只需要改变刚度，同时保持粘弹性参数不变。结合有限元分析和自定义子程序，得到了飞机子午线轮胎在一定载荷、压力和速度条件下各部件变形指标的等高线图。在此基础上，基于积热与疲劳寿命的热-力耦合分析方法，提出了轮胎典型部件（胎面、垫层、内层）材料刚度优化方案。系统的研究结果证实了利用变形指标提高飞机轮胎疲劳寿命的有效性。当胎面和垫层橡胶刚度分别提高50%和30%，内层橡胶刚度降低50%时，胎肩区最高温度降低4.17℃，飞机轮胎的疲劳寿命甚至提高了5倍。

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引用次数: 0

Corrigendum to “High cycle fatigue performance and corresponding fracture behaviors of GH4169 studs formed by thread warm rolling process” [Int. J. Fatigue 193 (2025) 108808]

IF 5.7 2区材料科学 Q1 ENGINEERING, MECHANICAL

International Journal of Fatigue

Pub Date : 2025-01-13 DOI: 10.1016/j.ijfatigue.2025.108813

Yanli Lu, Liyuan Hu, Ting Li, Gang Ran, Xiaowei Yi, Yukun Sun, Zhenyang Kong, Kuangshi Yan, Rui Hu, Hong Wang

引用次数: 0

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