Fatigue performance improvement of laser shock peened hole on powder metallurgy Ni-based superalloy labyrinth disc

Pan, Xinlei; Guo, Shaojun; Tian, Zeng; Liu, Ping; Dou, Lei; Wang, Xuede; An, Zhibin; Zhou, Lian

doi:10.1016/j.surfcoat.2021.126829

Cited by 24 publications

(6 citation statements)

References 46 publications

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“…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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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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“…[1][2][3] However, serious stress and strain concentrations may occur around hole edges due to geometric dimension mutations. [4][5][6] Therefore, a significant number of methods and technologies were developed to improve fatigue behaviors of holed structures, such as interference fit, [7][8][9] shot peening, 10,11 laser shocking, [12][13][14] and cold expansion. 15 Among them, cold expansion (CE), whose process is conducted by forcing an oversized mandrel going through the hole, has been extensively used in aeronautical holed structures and excellently beneficial effects were achieved.…”

Section: Introductionmentioning

confidence: 99%

Residual stress distribution and fatigue performance investigations of electromagnetic force-based dynamic cold expansion open-holed sheet

Zheng

Cao

Zuo

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part L:

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In this study, residual stress distributions and fatigue performances of electromagnetic driving dynamic cold expansion (DCE) open-holed sheets were investigated. Fatigue behaviors were tested, and residual stress fields were obtained experimentally and numerically. Furthermore, a fatigue life prediction method based on three-dimensional stress distribution was proposed. Results showed that DCE method extended higher fatigue life and produced more uniform residual stress along hole axial direction than static cold expansion (SCE) method. The stress distribution differences led to different fatigue crack initiation and propagation modes of DCE and SCE specimens. Uniform stress distributions along axial direction in DCE specimens contributed to random initiations and horizontal propagations of fatigue cracks, while the fatigue cracks in SCE specimens usually initiated at the mandrel entrance layer and propagated to the mandrel exit layer. Moreover, the predicted fatigue life results agreed well with experimental data.

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“…Furthermore, as each specimen is tested multiple times, the experimental time taken per specimen can be higher than staircase testing. Nevertheless, these effects have not been fully characterized, and the testing strategy remains in use across the academic literature 18–37 . For these reasons, step sizes are generally advised to be above 5% of the fatigue limit 4 .…”

Section: Introductionmentioning

confidence: 99%

“…Nevertheless, these effects have not been fully characterized, and the testing strategy remains in use across the academic literature. [18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36][37] For these reasons, step sizes are generally advised to be above 5% of the fatigue limit. 4 However, this requires prior knowledge of material properties and is dependent on the life being tested, as well as the continued debate over whether this is sufficient to avoid damage/coaxing.…”

mentioning

confidence: 99%

Bayesian optimized collection strategies for fatigue strength testing

Magazzeni

Rose

Gearhart

et al. 2022

Fatigue Fract Eng Mat Struct

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A statistical framework is presented enabling optimal sampling and analysis of constant life fatigue data. Protocols using Bayesian maximum entropy sampling are built based on conventional staircase and stress step methods, reducing the requirement of prior knowledge for data collection. The Bayesian Staircase method shows improved parameter estimation efficiency, and the Bayesian Stress Step method shows equal accuracy to the standard method at larger step size allowing experimentalists to lessen concerns of loading history. Statistical methods for determining model suitability are shown, highlighting the influence of protocol. Experimental validation is performed, showing the applicability of the methods in laboratory testing.

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Fatigue performance improvement of laser shock peened hole on powder metallurgy Ni-based superalloy labyrinth disc

Cited by 24 publications

References 46 publications

A Critical Review of Laser Shock Peening of Aircraft Engine Components

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Residual stress distribution and fatigue performance investigations of electromagnetic force-based dynamic cold expansion open-holed sheet

Bayesian optimized collection strategies for fatigue strength testing

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