Experimental study and fatigue life prediction on high cycle fatigue performance of laser-peened TC4 titanium alloy

Nie, Xiangfan; He, Weifeng; Cao, Zhenyang; Song, Jingdong; Li, Xiang; Pang, Zhicong; Yan, Xueyuan

doi:10.1016/j.msea.2021.141658

Cited by 34 publications

(11 citation statements)

References 40 publications

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“…Finally, the ultrasonic bending fatigue test and the ultrasonic axial fatigue test obtained 19 and 14 valid data, respectively, as shown in Table 2. It can be seen from the fitting curve in Figure 8 that the S-N curve under bending load shows a continuous decline [40,41], and does not show the "step" characteristics of high-strength steel [26,42]. This is consistent with the existing research results.…”

Section: S-n Curvesupporting

confidence: 90%

A Novel Ultrasonic Fatigue Test and Application in Bending Fatigue of TC4 Titanium Alloy

et al. 2022

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The very high cycle fatigue (VHCF) problems of thin-plate structures are usually caused by high-frequency vibrations. This paper proposes an accelerated fatigue test method based on ultrasonic loading technology in order to develop a feasible bending testing method and explore the bending fatigue characteristics of thin-plate structures in the VHCF regime. A new bending fatigue specimen with an intrinsic frequency of 20 kHz was designed based on cantilever bending through finite element simulation. It was verified by the axial load test with R = −1. The results showed that the method could effectively transfer the dangerous cross-section at the first-order cantilever bending restraint to the internal part of the specimen, thereby making the fracture location independent of the complex stresses. The linear relationship between the vibration amplitude and the maximum stress was also verified using strain measurements. Furthermore, the S-N curves and fracture morphology for different loading types were consistent with conventional studies to a certain extent, which indicated that the design of the bending test model was reasonable.

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Section: S-n Curvesupporting

confidence: 90%

A Novel Ultrasonic Fatigue Test and Application in Bending Fatigue of TC4 Titanium Alloy

et al. 2022

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“…LSP can effectively extend the fatigue life of aircraft engines by producing CRS and inducing beneficial microstructure evolution. [50,84,119,120] The earliest investigation of the effect of laser peening on the fatigue behavior of thin sections was performed on F101-GE-102 aircraft gas turbine engine fan blades. [121] As shown in Figure 10, LSP significantly improved the fatigue life of F101-GE-102 fan blades that suffered FOD, and the LSP-treated blades were found to retain the fatigue strength of an undamaged blade.…”

Section: Lsp Improving the Fatigue Performance Of Aircraft Enginesmentioning

confidence: 99%

“…It has been proven that LSP can be used to improve the fatigue properties of various metallic materials, including magnesium alloys, [123][124][125] titanium alloys, [23,84,119,120] aluminum alloys, [2,92,126] and superalloys [127,128] that are used in aviation structures and components. Generally, the leading edges of fan or compressor blades made of titanium alloy are more vulnerable to FOD.…”

Section: Lsp Improving the Fatigue Performance Of Aircraft Enginesmentioning

confidence: 99%

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Huang

Zou³

et al. 2023

Adv Eng Mater

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Many aviation accidents are caused by the failure of aircraft engine components, and engine blades are especially vulnerable to high‐cycle fatigue fracture in severe working environments as well as to impact damage caused by foreign objects. To address this problem, the United States took the lead and has been successful in implementing laser shock peening (LSP) as a surface treatment for aircraft engine components to enhance their fatigue performance. This review provides an overview of the development of LSP for use in treating aircraft engine components over the past three decades, with a brief introduction to the development of high‐energy pulsed lasers for LSP. A particular focus of this review is on the limitations and challenges associated with the application of LSP for treating critical aircraft engine components. It is hoped that this review serves as a reference for future research and development that can lead to better performance of these components.

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“…Based on the operating conditions of the VSV mechanism in engineering practice (Zhang et al ., 2022a), the dimensional parameters (crank 1 length L 1 , crankshaft height L 2 , crank 2 upper length L 3 and second crank 2 lower length L 4 ), physical random parameters (material density ρ , rotating friction coefficient u R , ball-hinged friction coefficient u s and pneumatic moment τ ), temperature parameters (thermal conductivity λ , expansion coefficient α and gas temperature T ) and life parameters ( γ , β , S 0 ) are regarded as random variables (Li et al ., 2022e; Nie et al ., 2021), whose distribution traits are shown in Table 5. Note that all random variables are assumed to be independent of each other.…”

Section: Fatigue Reliability Analysis Of Vsv Mechanismmentioning

confidence: 99%

Fatigue reliability framework using enhanced active Kriging-based hierarchical collaborative strategy

Zhang

Song

Bai

2023

IJSI

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PurposeThe purpose of this study is to improve the computational efficiency and accuracy of fatigue reliability analysis.Design/methodology/approachBy absorbing the advantages of Markov chain and active Kriging model into the hierarchical collaborative strategy, an enhanced active Kriging-based hierarchical collaborative model (DCEAK) is proposed.FindingsThe analysis results show that the proposed DCEAK method holds high accuracy and efficiency in dealing with fatigue reliability analysis with high nonlinearity and small failure probability.Research limitations/implicationsThe effectiveness of the presented method in more complex reliability analysis problems (i.e. noisy problems, high-dimensional issues etc.) should be further validated.Practical implicationsThe current efforts can provide a feasible way to analyze the reliability performance and identify the sensitive variables in aeroengine mechanisms.Originality/valueTo improve the computational efficiency and accuracy of fatigue reliability analysis, an enhanced active DCEAK is proposed and the corresponding fatigue reliability framework is established for the first time.

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Experimental study and fatigue life prediction on high cycle fatigue performance of laser-peened TC4 titanium alloy

Cited by 34 publications

References 40 publications

A Novel Ultrasonic Fatigue Test and Application in Bending Fatigue of TC4 Titanium Alloy

A Novel Ultrasonic Fatigue Test and Application in Bending Fatigue of TC4 Titanium Alloy

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Fatigue reliability framework using enhanced active Kriging-based hierarchical collaborative strategy

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