Effects of residual stress induced by laser shock peening on mixed-mode crack propagation behavior in 7075-T6 aluminum alloy panel
•Residual stress was calculated by an efficient LSP simulation termed continuous explicit-dynamic impact strategy.•LSP-induced residual stress can change the crack path.•The compressive residual stresses extend the effective crack length and delay the crack propagation.•The obvious crack turning poi...
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| Published in | Theoretical and applied fracture mechanics Vol. 119; p. 103358 |
|---|---|
| Main Authors | , , , , , |
| Format | Journal Article |
| Language | English |
| Published |
Amsterdam
Elsevier Ltd
01.06.2022
Elsevier BV |
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| Online Access | Get full text |
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| Abstract | •Residual stress was calculated by an efficient LSP simulation termed continuous explicit-dynamic impact strategy.•LSP-induced residual stress can change the crack path.•The compressive residual stresses extend the effective crack length and delay the crack propagation.•The obvious crack turning point near the peened area is related to the significant change of KIIload andKIIres.•The wider LSP coverage area and the shorter distance from the treated area to the crack tip improve the fatigue performance.
The effects of residual stress on mixed-mode crack propagation behavior of 7075-T6 aluminum alloy panel subject to multiple laser shock peening (LSP) impacts were investigated. Residual stress was obtained by an efficient LSP simulation termed continuous explicit-dynamic impact strategy. A numerical method, combining finite element (FE) method and residual stress intensity factor (SIF) analysis, was used to predict the mixed-mode (I/II) crack propagation in peened compact tension shear (CTS) sample. The effects of residual stress on the mixed-mode crack behaviors in different coverage areas were analyzed. It was found that the LSP-induced residual stress can change the crack path. Compressive residual stresses increase the effective crack length, and delay the crack propagation. The increased LSP coverage area and the decreased distance from the treated area to the crack tip are beneficial to the fatigue performance. The obvious crack turning point near the peened area is related to the significant change of mode II SIF components (KIIload and KIIres). The proposed numerical method provides a new idea for the damage tolerance analysis with respect to the applications of LSP technology in aircraft structures. |
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| AbstractList | •Residual stress was calculated by an efficient LSP simulation termed continuous explicit-dynamic impact strategy.•LSP-induced residual stress can change the crack path.•The compressive residual stresses extend the effective crack length and delay the crack propagation.•The obvious crack turning point near the peened area is related to the significant change of KIIload andKIIres.•The wider LSP coverage area and the shorter distance from the treated area to the crack tip improve the fatigue performance.
The effects of residual stress on mixed-mode crack propagation behavior of 7075-T6 aluminum alloy panel subject to multiple laser shock peening (LSP) impacts were investigated. Residual stress was obtained by an efficient LSP simulation termed continuous explicit-dynamic impact strategy. A numerical method, combining finite element (FE) method and residual stress intensity factor (SIF) analysis, was used to predict the mixed-mode (I/II) crack propagation in peened compact tension shear (CTS) sample. The effects of residual stress on the mixed-mode crack behaviors in different coverage areas were analyzed. It was found that the LSP-induced residual stress can change the crack path. Compressive residual stresses increase the effective crack length, and delay the crack propagation. The increased LSP coverage area and the decreased distance from the treated area to the crack tip are beneficial to the fatigue performance. The obvious crack turning point near the peened area is related to the significant change of mode II SIF components (KIIload and KIIres). The proposed numerical method provides a new idea for the damage tolerance analysis with respect to the applications of LSP technology in aircraft structures. The effects of residual stress on mixed-mode crack propagation behavior of 7075-T6 aluminum alloy panel subject to multiple laser shock peening (LSP) impacts were investigated. Residual stress was obtained by an efficient LSP simulation termed continuous explicit-dynamic impact strategy. A numerical method, combining finite element (FE) method and residual stress intensity factor (SIF) analysis, was used to predict the mixed-mode (I/II) crack propagation in peened compact tension shear (CTS) sample. The effects of residual stress on the mixed-mode crack behaviors in different coverage areas were analyzed. It was found that the LSP-induced residual stress can change the crack path. Compressive residual stresses increase the effective crack length, and delay the crack propagation. The increased LSP coverage area and the decreased distance from the treated area to the crack tip are beneficial to the fatigue performance. The obvious crack turning point near the peened area is related to the significant change of mode II SIF components (... and ...). The proposed numerical method provides a new idea for the damage tolerance analysis with respect to the applications of LSP technology in aircraft structures. (ProQuest: ... denotes formula omitted.) |
| ArticleNumber | 103358 |
| Author | Yang, Meng Peng, Yilin Ma, Yu'e Zhang, Xiushuo Wang, Zhenhai Du, Yong |
| Author_xml | – sequence: 1 givenname: Xiushuo surname: Zhang fullname: Zhang, Xiushuo organization: School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China – sequence: 2 givenname: Yu'e surname: Ma fullname: Ma, Yu'e email: ma.yu.e@nwpu.edu.cn organization: School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China – sequence: 3 givenname: Yilin surname: Peng fullname: Peng, Yilin organization: School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China – sequence: 4 givenname: Meng surname: Yang fullname: Yang, Meng organization: School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China – sequence: 5 givenname: Yong surname: Du fullname: Du, Yong organization: School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China – sequence: 6 givenname: Zhenhai surname: Wang fullname: Wang, Zhenhai email: zhwang@nwpu.edu.cn organization: School of Mathematics and Statistics, Northwestern Polytechnical University, Xi’an 710072, China |
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| Keywords | Mixed-mode fatigue crack propagation Laser shock peening 7075-T6 aluminum alloy panel Residual stress |
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| Snippet | •Residual stress was calculated by an efficient LSP simulation termed continuous explicit-dynamic impact strategy.•LSP-induced residual stress can change the... The effects of residual stress on mixed-mode crack propagation behavior of 7075-T6 aluminum alloy panel subject to multiple laser shock peening (LSP) impacts... |
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| SubjectTerms | 7075-T6 aluminum alloy panel Aircraft structures Aluminum alloys Aluminum base alloys Compact tension Compressive properties Crack propagation Crack tips Damage tolerance Fatigue failure Finite element method Laser shock peening Laser shock processing Mixed-mode fatigue crack propagation Numerical analysis Numerical methods Peening Propagation Propagation modes Residual stress Stress intensity factors Stress propagation |
| Title | Effects of residual stress induced by laser shock peening on mixed-mode crack propagation behavior in 7075-T6 aluminum alloy panel |
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