Fatigue Life Extension of AA2024 Specimens and Integral Structures by Laser Shock Peening
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Fatigue Life Extension of AA2024 Specimens and Integral Structures by Laser Shock Peening. / Kashaev, Nikolai; Chupakhin, Sergey; Ventzke, Volker et al.
MATEC Web of Conferences: 12th International Fatigue Congress (FATIGUE 2018) . Hrsg. / Henaff G. Band 165 EDP Sciences, 2018. 18001 (MATEC Web of Conferences; Band 165).Publikation: Beiträge in Sammelwerken › Aufsätze in Konferenzbänden › Forschung › begutachtet
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TY - CHAP
T1 - Fatigue Life Extension of AA2024 Specimens and Integral Structures by Laser Shock Peening
AU - Kashaev, Nikolai
AU - Chupakhin, Sergey
AU - Ventzke, Volker
AU - Horstmann, Manfred
AU - Riekehr, Stefan
AU - Barbini, Alessandro
AU - dos Santos, Jorge
AU - Keller, Sören
AU - Klusemann, Benjamin
AU - Huber, Norbert
N1 - Conference code: 12
PY - 2018/5/25
Y1 - 2018/5/25
N2 - The goal of the present study is to understand the effects of laser shock peening (LSP)-induced residual stresses on the fatigue crack propagation (FCP) behaviour of the commonly used aircraft aluminium alloy AA2024 in T3 heat treatment condition. LSP treatment was performed using a pulsed Nd:YAG laser on compact tensile C(T)50-specimens with a thickness of 2.0 mm. LSP-treated specimens reveal a significant retardation of the fatigue crack propagation. The fatigue crack retardation effect can be correlated with the compressive residual stresses introduced by LSP throughout the entire specimen thickness. A possible application of the LSP process on a component like panel with three welded stringers representing a part of a fuselage structure was performed as well. The skin-stringer AA2024-AA7050 Tjoints were realised through stationary shoulder friction stir welding (SSFSW), a variant of the conventional friction stir welding process. In this relatively new process, the shoulder does not rotate and therefore does not contribute to the heat generation. Consequently, a reduced and more homogeneous heat input leads to a less affected microstructure and better mechanical properties. The efficiency of the LSP process has been demonstrated resulting in an increase of 200 – 400% in fatigue lifetime.
AB - The goal of the present study is to understand the effects of laser shock peening (LSP)-induced residual stresses on the fatigue crack propagation (FCP) behaviour of the commonly used aircraft aluminium alloy AA2024 in T3 heat treatment condition. LSP treatment was performed using a pulsed Nd:YAG laser on compact tensile C(T)50-specimens with a thickness of 2.0 mm. LSP-treated specimens reveal a significant retardation of the fatigue crack propagation. The fatigue crack retardation effect can be correlated with the compressive residual stresses introduced by LSP throughout the entire specimen thickness. A possible application of the LSP process on a component like panel with three welded stringers representing a part of a fuselage structure was performed as well. The skin-stringer AA2024-AA7050 Tjoints were realised through stationary shoulder friction stir welding (SSFSW), a variant of the conventional friction stir welding process. In this relatively new process, the shoulder does not rotate and therefore does not contribute to the heat generation. Consequently, a reduced and more homogeneous heat input leads to a less affected microstructure and better mechanical properties. The efficiency of the LSP process has been demonstrated resulting in an increase of 200 – 400% in fatigue lifetime.
KW - Engineering
UR - http://www.scopus.com/inward/record.url?scp=85048120390&partnerID=8YFLogxK
U2 - 10.1051/matecconf/201816518001
DO - 10.1051/matecconf/201816518001
M3 - Article in conference proceedings
VL - 165
T3 - MATEC Web of Conferences
BT - MATEC Web of Conferences
A2 - G, Henaff
PB - EDP Sciences
T2 - 12th International Fatigue Congress (FATIGUE 2018)
Y2 - 27 May 2018 through 1 June 2018
ER -