Effect of pre-corrosion and corrosion/fatigue alternation frequency on the fatigue life of 7B04-T6 aluminum alloy

2016 ◽  
Vol 31 (24) ◽  
pp. 3869-3879 ◽  
Author(s):  
Tengfei Cui ◽  
Daoxin Liu ◽  
Jian Cai ◽  
Xiaohua Zhang
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Life ◽  
Corrosion Fatigue ◽  
Image Position

Abstract

Corrosion mechanism and fatigue behavior of 2A70-T6 aluminum alloy under alternating corrosion and fatigue

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Lei Fu ◽  
Hui Li ◽  
Li Lin ◽  
Qingyuan Wang ◽  
Qi Fan ◽  
...  
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Life ◽  
Corrosion Fatigue ◽  
Intergranular Corrosion ◽  
Fatigue Behavior ◽  
Cumulative Damage ◽  
Corrosion Mechanism ◽  
Corrosive Environment ◽  
Content Type ◽  
Damage Rule

Purpose Most supersonic aircraft were manufactured using 2A70 aluminum alloy. The purpose of this paper is to study the corrosion mechanism and fatigue behavior of an aircraft in a semi-industrial atmospheric corrosive environment, alternating effects of corrosion and fatigue were used to simulate the aircraft’s ground parking corrosion and air flight fatigue. Design/methodology/approach For this purpose, the aluminum alloy samples were subjected to pre-corrosion and alternating corrosion-fatigue experiments. The failure mechanisms of corrosion and corrosion fatigue were analyzed using microscopic characterization methods of electrochemical testing, X-ray diffraction and scanning electron microscopy. Miner’s linear cumulative damage rule was used to predict the fatigue life of aluminum alloy and to obtain its safe fatigue life. Findings The results showed that the corrosion damage caused by the corrosive environment was gradually connected by pitting pits to form denudation pits along grain boundaries. The deep excavation of chloride ions and the presence of intergranular copper-rich phases result in severe intergranular corrosion morphology. During cyclic loading, alternating hardening and softening occurred. The stress concentration caused by surface pitting pits and denudation pits initiated fatigue cracks at intergranular corrosion products. At the same time, the initiation of multiple fatigue crack sources was caused by the corrosion environment and the morphology of the transient fracture zone was also changed, but the crack propagation rate was not basically affected. The polarization curve and impedance analysis results showed that the corrosion rate increases first, decreases and then increases. Fatigue failure behavior was directly related to micro characteristics such as corrosion pits and microcracks. Originality/value In this research, alternating effects of corrosion and fatigue were used to simulate the aircraft’s ground parking corrosion and air flight fatigue. To study the corrosion mechanism and fatigue behavior of an aircraft in a semi-industrial atmospheric corrosive environment, the Miner’s linear cumulative damage rule was used to predict the fatigue life of aluminum alloy and to obtain its safe fatigue life.

Corrosion–Fatigue Life Prediction for 2024-T62 Aluminum Alloy Using Damage Mechanics-Based Approach

2011 ◽  
Vol 21 (8) ◽  
pp. 1245-1266 ◽  
Author(s):  
W. P. Hu ◽  
Q. A. Shen ◽  
M. Zhang ◽  
Q. C. Meng ◽  
X. Zhang
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Life ◽  
Fatigue Test ◽  
Corrosion Fatigue ◽  
Life Prediction ◽  
Damage Mechanics ◽  
Salt Spray ◽  
Fatigue Crack Initiation ◽  
Continuum Damage Mechanics ◽  
Fatigue Life Prediction

An approach based on the continuum damage mechanics was applied to predict corrosion–fatigue crack initiation life of 2024-T62 aluminum alloy. A fatigue test in air, a pre-corrosion–fatigue test, and a corrosion–fatigue test on smooth standard specimens were performed. The fatigue lives are strongly reduced by the corrosive environment of 5 wt.% NaCl continuous salt spray compared with non-corroded specimens. Damage evolution models for fatigue in air and pre-corrosion–fatigue of smooth specimens were established, which forms the basis for solving the corrosion–fatigue problem. Finally, the method of corrosion–fatigue life prediction was presented. The predictions comply with the experimental data.

GS10 Pre-corrosion Fatigue Life of FSWed 2024-T3 Aluminum alloy

2012 ◽  
Vol 2012 (0) ◽  
pp. _GS10-1_-_GS10-2_
Author(s):  
Takao OKADA ◽  
Ryosuke ARIUMI ◽  
Motoo ASAKAWA ◽  
Toshiya NAKAMURA ◽  
Shigeru MACHIDA
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Life ◽  
Corrosion Fatigue

The Study of Introduced Electrochemical Parameters for Corrosion Fatigue Life of Aluminum

2012 ◽  
Vol 573-574 ◽  
pp. 1211-1215
Author(s):  
Xiang Qi Meng ◽  
Zhou Ying Lin
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Crack ◽  
Fatigue Life ◽  
Corrosion Fatigue ◽  
Surface Current ◽  
Stress Control ◽  
Corrosion Fatigue Crack ◽  
Electrochemical Parameters ◽  
Etched Surface ◽  
Aluminum Alloy 7075

This work introduced electrochemical parameter etched surface current intensity to mainly study corrosion fatigue life of aluminum alloy 7075 under stress control. The S-N curve of 7075 was obtained in specified corrosion media, and a new model was proposed to predict corrosion fatigue crack initiatio.

Corrosion Parameters Distribution Rule and Influence Factors of LY12CZ Aluminum Alloy

2010 ◽  
Vol 139-141 ◽  
pp. 321-325
Author(s):  
Zhi Tao Mu ◽  
Zuo Tao Zhu ◽  
Ding Hai Chen ◽  
Bin Ye
Keyword(s):  
Aluminum Alloy ◽  
Fatigue Life ◽  
Corrosion Fatigue ◽  
Influence Factors ◽  
Gumbel Distribution ◽  
Distribution Models ◽  
Accelerated Corrosion ◽  
Corrosion Depth ◽  
Distribution Rule ◽  
Corrosion Pits

The corrosion depth, corrosion area, corrosion pit volume and area of LY12CZ aluminum alloy with different corrosion time were obtained from accelerated corrosion experiment. Four distribution models such as normal, Gumbel, Logistic and double parameter Weibull were used to test their distributions. It can found that the corrosion depth and corrosion area obey Gumbel distribution and the area and volume of corrosion pits obey double parameter Weibull distribution; Choose ten variables as the parameters of influence corrosion fatigue life, through grey relational analyze we can found that the deepest corrosion depth is the biggest influence gene of corrosion fatigue life, and the corrosion grade is an important influence gene almost equal to the deepest depth because it considered the influence of corrosion area and corrosion depth, so we can use it as an parameter to evaluate the calendar life of corrosion conditions.

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