Corrosion Fatigue Crack Growth Model for Aluminum Alloys in Jet Fuel
- Zuoting Liu
, - Shilong Liu,
- Jing Cao,
- Yang Pan,
- Weixing Yao
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Zuoting Liu
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Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures
Author ProfileShilong Liu
Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures
Author ProfileJing Cao
Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures
Author ProfileYang Pan
Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures
Author ProfileWeixing Yao
![](https://d197for5662m48.cloudfront.net/assets/icons/omniauth/orcid-ca37582cd91a671ed5cec57770e0e96c01b4b79b8b5b75d8598fc1ddac18c974.svg)
Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures
Corresponding Author:[email protected]
Author ProfileAbstract
Aluminum alloys are primary structural materials in aircraft fuel
systems, where jet fuel can significantly affect the crack propagation
behavior of the materials. This paper presents a model for calculating
the crack growth rate of aluminum alloys in jet fuel environment. The
model is based on elastoplastic fracture mechanics and revises the
interaction terms in the linear superposition model by taking into
account corrosion damage and crack closure effects. The derivation
process of the model is discussed in detail. To validate the efficacy of
the model, fatigue crack propagation tests were conducted on three types
of aviation aluminum alloys, namely 2524-T3, 7050-T7451, and 7075-T62,
in the jet fuel environment. The experimental results were compared with
crack growth rates in the laboratory air environment. Findings indicate
that the proposed model effectively captures the primary trends observed
in the experimental data. In addition, the failure surfaces of the
specimens were observed using a super-depth-of-field optical microscopy
system. When subjected to jet fuel, among three materials tested, the
7075-T62 alloy was found to have the roughest failure surface. This
increased roughness contributing to crack closure was identified as one
of the reasons why its fatigue crack growth rate is significantly lower
in the jet fuel than in air.17 Feb 2024Submitted to Fatigue & Fracture of Engineering Materials & Structures 13 Mar 2024Review(s) Completed, Editorial Evaluation Pending
15 Jun 2024Review(s) Completed, Editorial Evaluation Pending
15 Aug 20242nd Revision Received
16 Aug 2024Submission Checks Completed
16 Aug 2024Assigned to Editor
17 Aug 2024Review(s) Completed, Editorial Evaluation Pending
22 Aug 2024Editorial Decision: Accept