Numerical simulation of tensile behavior of corroded aluminum alloy 2024 T3

2015 ◽  
Vol 6 (4) ◽  
pp. 451-467 ◽  
Author(s):  
Dorothea Setsika ◽  
Konstantinos Tserpes ◽  
Spiros Pantelakis
Keyword(s):  
Aluminum Alloy ◽  
Mechanical Behavior ◽  
Corrosion Damage ◽  
Exposure Period ◽  
Tensile Specimen ◽  
Tensile Behavior ◽  
Content Type ◽  
Structural Part ◽  
Representative Unit Cell ◽  
Aluminum Alloy 2024

Purpose – The purpose of this paper is to develop a multi-scale modeling approach for simulating the tensile behavior of corroded aluminum alloy 2024 T3. Design/methodology/approach – The approach combines two FE models: a model of a three-dimensional representative unit cell representing a pit and a model of the tensile specimen. The models lie at the micro- and macro-scales, respectively. The local homogenized mechanical behavior of the corroded material is simulated for different pit configurations. Then, the behavior of the pits is introduced into different areas (elements) of the tensile specimen and final analyses are performed to simulate the mechanical behavior of the corroded material. The approach has been applied to six different exposure periods of the exfoliation corrosion test. Findings – The numerical results show that the presence of pits and exfoliated areas reduces the yield strength of the material. The comparison of predicted elongation to fracture with the experimental of each exposure period value allows for the indirect assessment of the effect of hydrogen embrittlement. Originality/value – Since the characteristics of corrosion damage evolution with exposure time are constant for the specific material, the model could be applied for the simulation of the mechanical behavior of any corroded structural part (e.g. a mechanically fastened panel) made from the aluminum 2024 T3 alloy.

Corrosion damage evolution of the aircraft aluminum alloy 2024 T3

2016 ◽  
Vol 7 (1) ◽  
pp. 25-46 ◽  
Author(s):  
Spiros Pantelakis ◽  
Dorothea Setsika ◽  
Apostolos Chamos ◽  
Anna Zervaki
Keyword(s):  
Mechanical Properties ◽  
Aluminum Alloy ◽  
Damage Evolution ◽  
Structural Integrity ◽  
Corrosion Damage ◽  
Tensile Tests ◽  
Content Type ◽  
Experimental Database ◽  
Aluminum Alloy 2024 ◽  
The Impact

Purpose – The purpose of this paper is to quantify the corrosion damage evolution that has occurred on the aircraft aluminum alloy 2024 after the exposure to Exfoliation Corrosion Test (EXCO) solution. Moreover, the effect of the evolving corrosion damage on the materials mechanical properties has been assessed. The relevance of the corrosion damage induced by the exposure to the laboratory EXCO for linking it to the damage developed after the exposure of the material on several outdoor corrosive environments or in service is discussed. Design/methodology/approach – To induce corrosion damage the EXCO has been used. For the quantification of corrosion damage the metallographic features considered have been pit depth, diameter, pitting density and pit shape. The effect of the evolving corrosion damage on the materials mechanical properties has been assessed by means of tensile tests on pre corroded specimens. Findings – The results have shown that corrosion damage starts from pitting and evolves to exfoliation, after the development of intergranular corrosion. This evolution is expressed by the increase of the depth of attack, as well as through the significant growth of the diameter of the damaged areas. The results of the tensile tests performed on pre corroded material made an appreciable decrease of the materials tensile properties evident. The decrease of the tensile ductility may become dramatic and increases on severity with increasing corrosion exposure time. SEM fractography revealed a quasi-cleavage zone beneath the depth of corrosion attack. Originality/value – The results underline the impact of corrosion damage on the mechanical behavior of the aluminum alloy 2024 T3 and demonstrate the need for further investigation of the corrosion effect on the structural integrity of the material. This work provides an experimental database concerning the quantification of corrosion damage evolution and the loss of material properties due to corrosion.

Microstructure and Mechanical Behavior of Friction-Stir-Welded 2017A-T451 Aluminum Alloy

2019 ◽  
Vol 72 (7) ◽  
pp. 1853-1868 ◽  
Author(s):  
O. Mimouni ◽  
R. Badji ◽  
A. Kouadri-David ◽  
R. Gassaa ◽  
N. Chekroun ◽  
...  
Keyword(s):  
Aluminum Alloy ◽  
Mechanical Behavior ◽  
Friction Stir

An Experimental Investigation of the Yield Loci of 1100-0 Aluminum, 70:30 Brass, and an Overaged 2024 Aluminum Alloy After Various Prestrains

1986 ◽  
Vol 108 (4) ◽  
pp. 313-320 ◽  
Author(s):  
D. E. Helling ◽  
A. K. Miller ◽  
M. G. Stout
Keyword(s):  
Aluminum Alloy ◽  
Small Strain ◽  
Yield Locus ◽  
Material Behavior ◽  
Shear Stresses ◽  
2024 Aluminum Alloy ◽  
Yield Loci ◽  
Aluminum Alloy 2024 ◽  
Von Mises ◽  
Normal And Shear Stresses

The multiaxial yield behaviors of 1100-0 aluminum, 70:30 brass, and an overaged 2024 aluminum alloy (2024-T7) have been investigated for a variety of prestress histories involving combinations of normal and shear stresses. Von Mises effective prestrains were in the range of 1.2–32%. Prestress paths were chosen in order to investigate the roles of prestress and prestrain direction on the nature of small-strain offset (ε = 5 × 10−6) yield loci. Particular attention was paid to the directionality, i.e., translation and distortion, of the yield locus. A key result, which was observed in all three materials, was that the final direction of the prestrain path strongly influences the distortions of the yield loci. Differences in the yield locus behavior of the three materials were also observed: brass and the 2024-T7 alloy showed more severe distortions of the yield locus and a longer memory of their entire prestrain history than the 1100-0 aluminum. In addition, more “kinematic” translation of the subsequent yield loci was observed in brass and 2024-T7 than in 1100-0 aluminum. The 2024-T7 differed from the other materials, showing a yield locus which decreased in size subsequent to plastic straining. Finally, the implications of these observations for the constitutive modeling of multiaxial material behavior are discussed.

Study on Corrosion Damage Rule for Two Type of Aluminum Alloy

2014 ◽  
Vol 599-601 ◽  
pp. 111-113
Author(s):  
Dan Feng Zhang ◽  
Xiao Ming Tan ◽  
Dan Gui Zhang ◽  
Fang Zhang ◽  
Wei Zhang
Keyword(s):  
Aluminum Alloy ◽  
Statistical Analysis ◽  
Marine Environment ◽  
Corrosion Test ◽  
Corrosion Damage ◽  
Aircraft Structure ◽  
Accelerated Corrosion ◽  
Damage Repair ◽  
Accelerated Corrosion Test ◽  
Damage Rule

Corrosion exists everywhere. It’s very widespread that the aluminum alloy aircraft structure suffers the corrosion damage under the marine environment particularly. The equivalent accelerated corrosion test of the new aluminum alloy 2B06 and 7B04 was carried out.Corrosion damage was inspected and measured through microscope. The rule of the corrosion damage can be obtained by statistical analysis. And which can supply the reference basis for the corrosion damage repair and evaluating the calendar life.

An alternative approach to thermal analysis using inverse problems in aluminum alloy welding

2017 ◽  
Vol 27 (3) ◽  
pp. 561-574 ◽  
Author(s):  
Elisan dos Santos Magalhaes ◽  
Cristiano Pedro da Silva ◽  
Ana Lúcia Fernandes Lima e Silva ◽  
Sandro Metrevelle Marcondes Lima e Silva
Keyword(s):  
Thermal Analysis ◽  
Heat Flux ◽  
Aluminum Alloy ◽  
Inverse Problems ◽  
Welding Process ◽  
Experimental Methodology ◽  
Function Technique ◽  
Content Type ◽  
Radiation Coefficient ◽  
Welding Processes

Purpose The purpose of this article is the determination of the temperature fields in a weld region has always been an obstacle to the improvement of welding processes. As an alternative, the use of inverse problems to determine the heat flux during the welding process allows an analysis of these processes. Design/methodology/approach This paper studies an alternative for the thermal analysis of the tungsten inert gas welding process on a 6,060 T5 aluminum alloy. For this purpose, a C++ code was developed, based on a transient three-dimensional heat transfer model. To estimate the amount of heat delivered to the plate, the specification function technique was used. Lab experiments were carried out to validate the methodology. A different experimental methodology is proposed to estimate the emissivity (radiation coefficient). Findings The maximum difference between experimental and numerical temperatures is lower than 5 per cent. The determined emissivity value for the aluminum 6,060 T5 presented a good agreement with literature values. The thermal fields were analyzed as function of the positive polarity. The specification function method proved to be an adequate tool for heat input estimation in welding analysis. Originality/value The proposed methodology proves to be a cheaper way to estimate the heat flux on the sample. The estimated power curves for the welding process are presented. The methodology to calculate the emissivity (radiation coefficient) was validated.

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