Abstract
Laser Shock Peening is a surface treatment technique used in the aerospace sector to increase fatigue life, as well as resistance to fretting fatigue and stress corrosion cracking. In this study, laser shock peening was applied to a 6-mm-thick middle-crack tension specimen made of aluminium 2524-T351. Residual stress was measured with neutron diffraction and the contour method, along the predicted crack path prior to fatigue testing. Fatigue crack growth test results showed that fatigue life improved by a factor of 4 compared to an untreated component, owing to a significant crack growth rate reduction inside the laser peened area. A linear-elastic finite-element crack growth prediction model was also developed, obtaining predicted results in excellent agreement with the experimental data.
| Original language | English |
|---|---|
| Pages (from-to) | 157-167 |
| Number of pages | 11 |
| Journal | International Journal of Fatigue |
| Volume | 123 |
| Early online date | 31 Jan 2019 |
| DOIs | |
| Publication status | Published - 1 Jun 2019 |
Bibliographical note
NOTICE: this is the author’s version of a work that was accepted for publication in International Journal of Fatigue. Changes resulting from the publishing process, such as peer review, editing, corrections, structural formatting, and other quality control mechanisms may not be reflected in this document. Changes may have been made to this work since it was submitted for publication. A definitive version was subsequently published in International Journal of Fatigue, [123], (2019)DOI: 10.1016/j.ijfatigue.2019.01.020
© 2017, Elsevier. Licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International http://creativecommons.org/licenses/by-nc-nd/4.0/
Keywords
- Crack growth
- Crack growth modelling
- Fatigue
- Laser peening
- Residual stress
ASJC Scopus subject areas
- Modelling and Simulation
- Materials Science(all)
- Mechanics of Materials
- Mechanical Engineering
- Industrial and Manufacturing Engineering