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Journal articles on the topic 'Aluminium alloy 2618'

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Published: 4 June 2021
Last updated: 14 February 2022

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1

Spigarelli, S., F. Bardi, and E. Evangelista. "Hot Workability of the 2618 Aluminium Alloy." Materials Science Forum 331-337 (May 2000): 449–54. http://dx.doi.org/10.4028/www.scientific.net/msf.331-337.449.

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2

Sauerborn, M., and H. J. McQueen. "Modelling extrusion of 2618 aluminium alloy and 2618-1 10%AI203and 2618-20%AI203composites." Materials Science and Technology 14, no. 9-10 (September 1998): 1029–38. http://dx.doi.org/10.1179/mst.1998.14.9-10.1029.

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3

Cavaliere, P. "Hot and warm forming of 2618 aluminium alloy." Journal of Light Metals 2, no. 4 (November 2002): 247–52. http://dx.doi.org/10.1016/s1471-5317(03)00008-7.

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4

Nový, František, Miloš Janeček, Robert Král, and Branislav Hadzima. "Microstructure evolution in a 2618 aluminium alloy during creep-fatigue tests." International Journal of Materials Research 103, no. 6 (June 2012): 688–93. http://dx.doi.org/10.3139/146.110679.

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5

Nový, F., M. Janeček, and R. Král. "Microstructure changes in a 2618 aluminium alloy during ageing and creep." Journal of Alloys and Compounds 487, no. 1-2 (November 2009): 146–51. http://dx.doi.org/10.1016/j.jallcom.2009.08.014.

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6

Oguocha, I. N. A., and S. Yannacopoulos. "Natural ageing behaviour of cast alumina particle-reinforced 2618 aluminium alloy." Journal of Materials Science 31, no. 12 (June 1996): 3145–51. http://dx.doi.org/10.1007/bf00354660.

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7

Belelli, Filippo, Riccardo Casati, Martina Riccio, Alessandro Rizzi, Mevlüt Y. Kayacan, and Maurizio Vedani. "Development of a Novel High-Temperature Al Alloy for Laser Powder Bed Fusion." Metals 11, no. 1 (December 26, 2020): 35. http://dx.doi.org/10.3390/met11010035.

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The number of available materials for Laser Powder Bed Fusion is still limited due to the poor processability of many standard alloys. In particular, the lack of high-strength aluminium alloys, widely used in aerospace and automotive industries, remains a big issue for the spread of beam-based additive manufacturing technologies. In this study, a novel high-strength aluminium alloy for high temperature applications having good processability was developed. The design of the alloy was done based on the chemical composition of the widely used EN AW 2618. This Al-Cu-Mg-Ni-Fe alloy was modified with Ti and B in order to promote the formation of TiB2 nuclei in the liquid phase able to stimulate heterogeneous nucleation of grains and to decrease the hot cracking susceptibility of the material. The new Al alloy was manufactured by gas atomisation and processed by Laser Powder Bed Fusion. Samples produced with optimised parameters featured relative density of 99.91%, with no solidification cracks within their microstructure. After aging, the material revealed upper yield strength and ultimate tensile strength of 495 MPa and 460 MPa, respectively. In addition, the alloy showed tensile strength higher than wrought EN AW 2618 at elevated temperatures.
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8

Subawi, Handoko, and Sutarno. "The Phenomenon of Pitting Corrosion Attack on the Milled Aluminium Alloy Al 2618 Plate during Surface Preparation through Sulphuric Acid Anodising." Advanced Materials Research 896 (February 2014): 596–99. http://dx.doi.org/10.4028/www.scientific.net/amr.896.596.

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This study purposed to investigate corrosion characteristic on aluminium alloy by considering parameters that involved metal preparation, different surface treatment, and alloy types. Through series of the salt spray test, the rolled aluminium sheet revealed higher resistance to surface corrosion rather than milled aluminium plate. However trace elements, as reinforced filler in the metal alloy, may contribute to possible pitting corrosion. By employing sulphuric acid anodising, it revealed higher probability of pitting corrosion to attack the milled aluminium plate surface compared to rolled aluminium sheet. The surface pitting corrosion on the anodised aluminium alloy Al 2618 plate was observed through enlargement of pitting diameter and additional new pitting holes during 500 hours corrosion test. The corrosion propagation grew sharply during 500 hours test and it increased slowly after 750 hours. This study did not evaluate further variables either alloy composition, metal processing, or operation condition in anodising process.
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9

Tjong, S. C., and Z. Y. Ma. "Steady state creep deformation behaviour of SiC particle reinforced 2618 aluminium alloy based composites." Materials Science and Technology 15, no. 4 (April 1999): 429–36. http://dx.doi.org/10.1179/026708399101505897.

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10

Pantělejev, Libor, Daniel Koutný, David Paloušek, and Jozef Kaiser. "Mechanical and Microstructural Properties of 2618 Al-Alloy Processed by SLM Remelting Strategy." Materials Science Forum 891 (March 2017): 343–49. http://dx.doi.org/10.4028/www.scientific.net/msf.891.343.

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Paper deals with the comparison of mechanical properties and microstructure of aluminium alloy 2618 fabricated by Selective Laser Melting (SLM) and material of the same grade manufactured by standard extrusion process. The SLM specimens were fabricated with different processing strategies (meander and remelting). Presence of cracks was found in both cases of used strategies, but in case of meander strategy, crack are of shorter character and distributed rather within individual welds. In case of remelting strategy, cracks are oriented mostly parallel to building direction and transcend fusion boundaries (FB) across several layers. It was found that defects present in microstructure of SLM material significantly affect its mechanical properties. Ultimate tensile strength (UTS) for extruded material reached 392 MPa, while for SLM material produced with meander strategy UTS was 273 MPa and for remelting strategy it was 24 MPa only.
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11

Pater, Zbigniew, Andrzej Gontarz, and Arkadiusz Tofil. "Analysis of the cross-wedge rolling process of toothed shafts made from 2618 aluminium alloy." Journal of Shanghai Jiaotong University (Science) 16, no. 2 (April 2011): 162–66. http://dx.doi.org/10.1007/s12204-011-1119-2.

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12

Sauerborn, M., and H. J. McQueen. "Modelling extrusion of 2618 aluminium alloy and 2618-1 10%AI203 and 2618-20%AI203 composites." Materials Science and Technology 14, no. 9 (September 1, 1998): 1029–38. http://dx.doi.org/10.1179/026708398790613371.

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13

Bobrow, D., A. Arbel, and D. Eliezer. "The effect of elevated-temperature reverse cyclic loading on fracture toughness of aluminium alloy type 2618." Journal of Materials Science 26, no. 8 (January 1, 1991): 2045–49. http://dx.doi.org/10.1007/bf00549165.

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14

Bardi, Franco, Marcello Cabibbo, and Stefano Spigarelli. "An analysis of thermo-mechanical treatments of a 2618 aluminium alloy: study of optimum conditions for warm forging." Materials Science and Engineering: A 334, no. 1-2 (September 2002): 87–95. http://dx.doi.org/10.1016/s0921-5093(01)01775-0.

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15

Sakthivel, A., R. Palaninathan, R. Velmurugan, and P. Rao. "The Effect of Silicon Carbide Particulates on Tensile, Fatigue, Impact and Final Fracture Behaviour of 2618 Aluminium Alloy Matrix Composites." International Journal of Aerospace Innovations 3, no. 3 (September 2011): 193–206. http://dx.doi.org/10.1260/1757-2258.3.3.193.

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16

Singh, Nirbhay, Ram Khelawan, and G. N. Mathur. "Effect of stress ratio and frequency on fatigue crack growth rate of 2618 aluminium alloy silicon carbide metal matrix composite." Bulletin of Materials Science 24, no. 2 (April 2001): 169–71. http://dx.doi.org/10.1007/bf02710096.

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17

Gao, Jun Zhen, Qiang Zhu, Da Quan Li, and Yong Lin Kang. "Microstructural Changes and Thermal Stability of A201, 319s and 2618 Aluminum Alloys during Thermal Exposure." Materials Science Forum 913 (February 2018): 55–62. http://dx.doi.org/10.4028/www.scientific.net/msf.913.55.

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Turbocharger compressor wheels are often made of 3XX cast aluminum alloys and forged 2618 alloy. These age hardening aluminum alloys have high strength-to-weight ratio at ambient temperature. However, the strength of the aluminum alloys decreases rapidly when applied at high temperatures, such as for turbochargers where application temperature can be above 200 °C. The major reason is that the fine precipitated phases coarsen rapidly tending to their equilibrium states. The thermal stability of the 319s-T61, A201-T71 and 2618-T6 alloys were compared in this paper. The three alloys were exposed at 200 °C for 100 h during heat treatment. Hardness, tensile tests and TEM were carried out to investigate the mechanical properties and microstructure variation of these three alloys. The results indicated that the A201 alloy exhibited the best thermal stability among the three alloys and 319s alloy is the weakest one. TEM observation showed that with the increase of the exposure time, the strengthening precipitates phase θ′ in A201/319s alloys and S′ in 2618 alloy coarsened and then transformed to stable θ phase and S phase, respectively, while the primary strengthening phase Ω in A201 remained stable, which may be contributed the higher thermal stability of A201 than 319s and 2618.
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18

Zhu, Z., H. Peng, Y. Liu, H. Tu, J. Wang, and X. Su. "Multistage homogenization process of aluminum alloy 2618." Materialwissenschaft und Werkstofftechnik 51, no. 7 (July 2020): 992–1001. http://dx.doi.org/10.1002/mawe.201900117.

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19

Malek, Benaïssa, Catherine Mabru, and Michel Chaussumier. "Multiaxial fatigue behavior of 2618 aluminum alloy." MATEC Web of Conferences 300 (2019): 09003. http://dx.doi.org/10.1051/matecconf/201930009003.

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The purpose of the present research project is to study multiaxial fatigue behavior of 2618 alloy. The influence of mean stress on the fatigue behavior under tension and torsion is particularly investigated. Fatigue tests under combined tensile-torsion, in or out of phase, as well as combined tensile-torsion-internal pressure tests have also been conducted. Multiaxial fatigue results are analyzed according to Fatemi-Socie criterion to predict the fatigue life.
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20

Jaukovic,, Ν., and V. Asanovic,. "The Investigation of Aluminum 2618 Alloy Containing Lanthanides." Journal for Manufacturing Science and Production 8, no. 2-4 (December 2007): 97–104. http://dx.doi.org/10.1515/ijmsp.2007.8.2-4.97.

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21

Du, Z. W., G. J. Wang, X. L. Han, Z. H. Li, B. H. Zhu, X. Fu, Y. A. Zhang, and B. Q. Xiong. "Microstructural evolution after creep in aluminum alloy 2618." Journal of Materials Science 47, no. 6 (December 16, 2011): 2541–47. http://dx.doi.org/10.1007/s10853-011-6077-4.

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22

Toschi, Stefania, Eleonora Balducci, Lorella Ceschini, Eva Mørtsell, Alessandro Morri, and Marisa Di Sabatino. "Effect of Zr Addition on Overaging and Tensile Behavior of 2618 Aluminum Alloy." Metals 9, no. 2 (January 26, 2019): 130. http://dx.doi.org/10.3390/met9020130.

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The effect of Zr addition on overaging and tensile behavior in a 2618 Al–Cu–Mg–Ni–Fe alloy has been investigated in this study. The chemical composition of the base 2618 alloy, containing ~0.1 wt % of Zr, was modified by adding Zr to reach the target content of 0.25 wt %. Cast bars were T6 heat-treated according to industrial parameters, involving soaking at 525 °C for 8 h, quenching in hot water (50 °C), and artificial aging at 200 °C for 20 h. Both the T6 2618 and 2618 + Zr alloys were overaged at 250 and 300 °C for up to 192 h, to evaluate the decrease in hardness with high temperature exposure time. The tensile behavior of the alloys was investigated in the overaged condition, both at room temperature and at 250 °C. The microstructure of the as-cast and solution-treated samples was investigated by optical and scanning electron microscopy, while the precipitate microstructure at the nanoscale was analyzed by transmission electron microscopy in overaged condition. Experimental data revealed that the presence of 0.25 wt % Zr does not induce modifications at the macroscale on the microstructure of 2618 alloy while, at the nanoscale, the presence of Zr-based precipitates was observed. The overaged Zr-enriched alloy showed increased yield and ultimate tensile strength in comparison to the base alloy, at equal heat treatment condition, both at room temperature and 250 °C.
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23

Jiang, Jing Ze, Bao Li, and Bi Cheng Yang. "Second Phase Particles and Mechanical Properties of 2618 Aluminum Alloy Ring." Materials Science Forum 1035 (June 22, 2021): 212–16. http://dx.doi.org/10.4028/www.scientific.net/msf.1035.212.

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2618 aluminum alloy has been used in aerospace structural parts, but the coarse second phase particles agglomerated in the alloy usually result in poor mechanical properties. In this paper, the morphology and distribution of the second phase particles and the mechanical properties of 2618 aluminum alloy ring were investigated, and the fracture morphology is observed by scanning electron microscope (SEM) and analyzed by energy dispersive X-ray spectroscopy (EDS). The result show that the mechanical properties in the axial direction are lower than those in the circumferential direction. It is evidentially shown that the agglomeration of Al9FeNi intermetallic particles and magnesium oxides in the fracture is the main reason for the poor mechanical properties in the axial direction.
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24

Kun, Ma, Liu Tingting, Liu Ya, Su Xuping, and Wang Jianhua. "Study on Strengthening and Toughening Mechanisms of Aluminum Alloy 2618-Ti at Elevated Temperature." High Temperature Materials and Processes 37, no. 1 (January 26, 2018): 9–15. http://dx.doi.org/10.1515/htmp-2015-0226.

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AbstractThe tensile properties of the alloy 2618 and 2618-Ti were tested using a tensile testing machine. The morphologies of the fracture of tensile samples were observed using scanning electron microscopy. The strengthening and toughening mechanisms of alloy 2618-Ti at elevated temperature were systematically investigated based on the analyses of experimental results. The results showed that the tensile strength of alloy 2618-Ti is much higher than that of alloy 2618 at the temperature range of 250 and 300 °C. But the elongation of alloy 2618-Ti is much higher than that of alloy 2618 at the temperature range of 200 and 300 °C. The equal-strength temperature of intragranular and grain boundary of alloy 2618-Ti is about 235 °C. When the temperature is lower than 235 °C, the strengthening of alloy 2618-Ti is ascribed to the strengthening effect of fine grains and dispersed Al3Ti/Al18Mg3Ti2 phase. When the temperature is higher than 235 °C, the strengthening effect of alloy 2618-Ti is mainly attributed to the load transfer of Al3Ti and Al18Mg3Ti2 particles. The toughening of alloy 2618-Ti at elevated temperature is mainly ascribed to the fine grain microstructure, excellent combination between matrix and dispersed Al3Ti/Al18Mg3Ti2 particles as well as the recrystallization of the alloy at elevated temperature.
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25

Xia, K., and G. Tausig. "Liquidus casting of a wrought aluminum alloy 2618 for thixoforming." Materials Science and Engineering: A 246, no. 1-2 (May 1998): 1–10. http://dx.doi.org/10.1016/s0921-5093(97)00758-2.

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26

Malek, Benaissa, Catherine Mabru, and Michel Chaussumier. "Study and modelling of anodized 2618 aluminum behavior subjected to multiaxial fatigue." MATEC Web of Conferences 165 (2018): 16010. http://dx.doi.org/10.1051/matecconf/201816516010.

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Anodized Aluminum alloys are widely used in aeronautic construction due to their specific mechanical properties. However, anodization process often leads to a decrease of the fatigue resistance of the alloys. In order to identify and characterize the different mechanisms involved in the detrimental effect of anodization of 2618-T851 alloy on its fatigue life and to determine the impact of loading nature, several tests have been performed on specimens with different surface states at various stress ratios. It was found that roughness of machining has no effect unlike the stress ratio or mean stress in tensile tests. The tests on the pickled, anodized, impregnated and sealed specimens showed it was the anodic oxidation step which was the more detrimental for fatigue resistance under tensile loading comparing to the other steps. It has been also observed that no such detrimental effect occurred under torsion loading. Concerning the prediction of fatigue life, two critical plane-based analysis approaches have been used (Morel and Fatemi-Socie criteria) to make fatigue life prediction for uniaxial and multiaxial fatigue test. Comparisons showed that both criteria gives overestimated fatigue life for uniaxial tensile loading under compression mean stress and underestimated fatigue life for tensile-torsion in phase loading.
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27

Liu, Tingting, Xuping Su, Ya Liu, Changjun Wu, and Jianhua Wang. "Microstructural Evolution of Aluminum Alloy 2618 During Homogenization and Its Kinetic Analysis." High Temperature Materials and Processes 33, no. 1 (February 1, 2014): 85–94. http://dx.doi.org/10.1515/htmp-2013-0029.

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AbstractThe microstructure evolution of aluminum alloy 2618 and its homogenization kinetics were investigated by optical microscope, scanning electron microscope, energy dispersive spectroscopy and differential scanning calorimeter. The results show that the main constituent phases in as-cast alloy 2618 are α–Al, Al9FeNi phase and non-equilibrium binary θ (Al2Cu) phase instead of typical S (Al2CuMg) phase. The θ phase was dissolved into α–Al gradually and the continuous dendritic-network structure was broken with the increase of homogenization temperature and time. DSC analysis shows that the overburnt and liquidus temperatures of as-cast alloy 2618 are 506.4 °C and 638.0 °C, respectively. After the alloy was homogenized at optimized temperature 500 °C for 16 h, the θ phase was completely dissolved in matrix. The size and morphology of Al9FeNi phase had little change, while the liquidus temperature shifted to 641 °C. The calculated homogenization time for alloy 2618 at 500 °C is 15 h, which is in accordance with that obtained in homogenization experiments.
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28

Pradhan,, D., D. Mantha,, and R. G. Reddy,. "Mechanical Properties and Microstructure of Aluminum 2618 Alloy containing Manganese and Chromium." High Temperature Materials and Processes 28, no. 4 (August 2009): 203–10. http://dx.doi.org/10.1515/htmp.2009.28.4.203.

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29

Jauković,, Nada, Vanja Asanović,, and Žarko Radović,. "Mechanical Properties and Microstructure of Aluminum 2618 Alloy Containing Manganese and Chromium." High Temperature Materials and Processes 28, no. 4 (August 2009): 253–62. http://dx.doi.org/10.1515/htmp.2009.28.4.253.

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30

Malek, Benaïssa, Catherine Mabru, and Michel Chaussumier. "Fatigue behavior of 2618-T851 aluminum alloy under uniaxial and multiaxial loadings." International Journal of Fatigue 131 (February 2020): 105322. http://dx.doi.org/10.1016/j.ijfatigue.2019.105322.

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31

Sakthivel, A., R. Palaninathan, R. Velmurugan, and P. Raghothama Rao. "Production and mechanical properties of SiCp particle-reinforced 2618 aluminum alloy composites." Journal of Materials Science 43, no. 22 (November 2008): 7047–56. http://dx.doi.org/10.1007/s10853-008-3033-z.

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32

Zeng, Lei, Zhaoyang Li, Renqing Che, Takahiro Shikama, Shinji Yoshihara, Tadashi Aiura, and Hiroshi Noguchi. "Mesoscopic analysis of fatigue strength property of a modified 2618 aluminum alloy." International Journal of Fatigue 59 (February 2014): 215–23. http://dx.doi.org/10.1016/j.ijfatigue.2013.08.016.

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33

Ding, J. L., and W. N. Findley. "Nonproportional Loading Steps in Multiaxial Creep of 2618 Aluminum." Journal of Applied Mechanics 52, no. 3 (September 1, 1985): 621–28. http://dx.doi.org/10.1115/1.3169111.

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Experimental data on the creep behavior of 2618-T61 aluminum alloy under nonproportional loadings are presented. Among the important findings are the anisotropy induced by creep strain, synergistic effects during creep recovery, and strongly nonlinear material behavior at high stress levels. Data were compared with two theoretical models, a viscous-viscoelastic (VV) model and a viscoplastic (VP) model. In the VV model the time-dependent strain was decomposed into recoverable (viscoelastic) and nonrecoverable components. The VP model differs from the VV model in that all the time-dependent strain is assumed nonrecoverable. In each model, three viscoplastic flow rules based on different hardening natures, namely, isotropic strain hardening, kinematic hardening, and independent strain hardening were derived to describe the time-dependent nonrecoverable strain component, and compared with experiments. The viscoelastic component in the VV model was represented by the third-order multiple integral representation combined with the modified superposition principle. Predictions for all theories used material constants obtained from creep and recovery data only. Possible causes for the discrepancies between theories and experimental data were discussed. Further experimental and theoretical work necessary for the study of the time-dependent material behavior at high temperature were also suggested.
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34

Leng, Yang. "Study of creep crack growth in 2618 and 8009 aluminum alloys." Metallurgical and Materials Transactions A 26, no. 2 (February 1995): 315–28. http://dx.doi.org/10.1007/bf02664669.

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35

Yu, Kun, Wenxian Li, Songrui Li, and Jun Zhao. "Mechanical properties and microstructure of aluminum alloy 2618 with Al3(Sc, Zr) phases." Materials Science and Engineering: A 368, no. 1-2 (March 2004): 88–93. http://dx.doi.org/10.1016/j.msea.2003.09.092.

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36

Özbek, İbrahim. "A study on the re-solution heat treatment of AA 2618 aluminum alloy." Materials Characterization 58, no. 3 (March 2007): 312–17. http://dx.doi.org/10.1016/j.matchar.2006.07.002.

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37

Wang, Jianhua, Danqing Yi, Xuping Su, and Fucheng Yin. "Influence of deformation ageing treatment on microstructure and properties of aluminum alloy 2618." Materials Characterization 59, no. 7 (July 2008): 965–68. http://dx.doi.org/10.1016/j.matchar.2007.08.007.

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38

Zamarripa, A. Salas, C. Pinna, M. W. Brown, M. P. Guerrero Mata, M. Castillo Morales, and T. P. Beber-Solano. "Identification of modes of fracture in a 2618-T6 aluminum alloy using stereophotogrammetry." Materials Characterization 62, no. 12 (December 2011): 1141–50. http://dx.doi.org/10.1016/j.matchar.2011.09.005.

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39

JAUKOVIC, Nada, and Milisav LALOVIC. "Effect of Zirconium and Lanthanides on the Recovery in 2618 Base Aluminum Alloys." ISIJ International 45, no. 3 (2005): 405–7. http://dx.doi.org/10.2355/isijinternational.45.405.

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40

Leng, Y., W. C. Porr, and R. P. Gangloff. "Tensile deformation of 2618 and AlFeSiV aluminum alloys at elevated temperatures." Scripta Metallurgica et Materialia 24, no. 11 (November 1990): 2163–68. http://dx.doi.org/10.1016/0956-716x(90)90504-a.

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41

Leng, Yang. "Study of creep crack growth in 2618 and 8009 aluminum aiioys." Metallurgical and Materials Transactions A 26, no. 6 (June 1995): 1607. http://dx.doi.org/10.1007/bf02647615.

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42

Bassani, Paola, Carlo Alberto Biffi, Riccardo Casati, Adrianni Zanatta Alarcon, Ausonio Tuissi, and Maurizio Vedani. "Properties of Aluminium Alloys Produced by Selective Laser Melting." Key Engineering Materials 710 (September 2016): 83–88. http://dx.doi.org/10.4028/www.scientific.net/kem.710.83.

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Analysis of peculiar properties offered by Al alloys produced according to additive manufacturing techniques, specifically by Selective Laser Melting (SLM), is carried out. Two alloys are considered, derived by casting (AlSi10Mg) and by wrought (ENAW 2618) applications. The SLM processed samples are investigated considering their microstructural and mechanical properties after SLM and compared to cast and wrought counterparts. A strong microstructural refinement induced by SLM processing is observed for both alloys, resulting in excellent hardness properties. Investigation on integrity of samples revealed that small-size microvoids and unmelted regions could be present in SLM parts.
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43

Koutny, Daniel, David Palousek, Libor Pantelejev, Christian Hoeller, Rudolf Pichler, Lukas Tesicky, and Jozef Kaiser. "Influence of Scanning Strategies on Processing of Aluminum Alloy EN AW 2618 Using Selective Laser Melting." Materials 11, no. 2 (February 14, 2018): 298. http://dx.doi.org/10.3390/ma11020298.

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44

SAKURAI, Keizo, Takeshi SAWAI, and Katsushige ADACHI. "Performance of TiN coated flute-less tap on 15% SiC particle reinforced 2618 aluminum alloy tapping." Journal of Japan Institute of Light Metals 56, no. 6 (2006): 301–6. http://dx.doi.org/10.2464/jilm.56.301.

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45

Troconis de Rincón, Oladis, Andrés Torres-Acosta, Alberto Sagüés, and Miguel Martinez-Madrid. "Galvanic Anodes for Reinforced Concrete Structures: A Review." Corrosion 74, no. 6 (January 7, 2018): 715–23. http://dx.doi.org/10.5006/2613.

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In recent years, the use of sacrificial anodes for cathodic protection in reinforced concrete structures has increased, reflecting ease of installation, low-maintenance requirements, as well as desirability in prestressed concrete structures where the naturally controlled protection potential decreases the risk of hydrogen embrittlement. Zinc-based alloys have been among the most evaluated galvanic materials for concrete structures, especially in the United States, in many applications: thermal spray, superficial metal/mesh with and without hydrogel adhesive, embedded in concrete (point anodes) with or without salt activator, etc. However, the protection capacity lifetime of zinc alloys as used has been questioned based both on laboratory and on field application studies. Aluminum alloys have also been evaluated, sometimes showing better results as anode materials than zinc alloys. However, both zinc and aluminum alloy anodes may experience limited applicability in concrete structures exposed only to atmospheric conditions, as opposed to those in immersed, tidal, and splash zone service. This paper presents a review of the research work in the literature to date for both laboratory and field evaluations, toward identifying technically relevant situations where the use of sacrificial anodes may or may not be a practical option for reinforcement protection in concrete structures.
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46

Rockenhäuser, Christian, Christian Rowolt, Benjamin Milkereit, Reza Darvishi Kamachali, Olaf Kessler, and Birgit Skrotzki. "On the long-term aging of S-phase in aluminum alloy 2618A." Journal of Materials Science 56, no. 14 (January 11, 2021): 8704–16. http://dx.doi.org/10.1007/s10853-020-05740-x.

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AbstractThe aluminum alloy 2618A is applied for engine components such as radial compressor wheels which operate for long time at elevated temperatures. This results in coarsening of the hardening precipitates and degradation in mechanical properties during the long-term operation, which is not taken into account in the current lifetime prediction models due to the lack of quantitative microstructural and mechanical data. To address this issue, a quantitative investigation on the evolution of precipitates during long-term aging at 190 °C for up to 25,000 h was conducted. Detailed transmission electron microscopy (TEM) was combined with Brinell hardness measurements and thorough differential scanning calorimetry (DSC) experiments. The results show that GPB zones and S-phase Al2CuMg grow up to < 1,000 h during which the GPB zones dissolve and S-phase precipitates form. For longer aging times, only S-phase precipitates coarsen, which can be well described using the Lifshitz–Slyozov–Wagner theory of ripening. A thorough understanding of the underlying microstructural processes is a prerequisite to enable the integration of aging behavior into the established lifetime models for components manufactured from alloy 2618A.
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47

Nosova, E. A., A. A. Fadeeva, and M. A. Starodubtseva. "Research of grain size homogeneity effect on sheet stamping ability characteristics of Al2Mg and Al6Mg alloys." Izvestiya Vuzov Tsvetnaya Metallurgiya (Proceedings of Higher Schools Nonferrous Metallurgy, no. 3 (June 19, 2019): 47–54. http://dx.doi.org/10.17073/0021-3438-2019-3-47-55.

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The quality of products made of sheet aluminum alloys strongly depends on the technological features of the sheet stamping process, as well as on the structure of sheet semi-finished products. The grain size and grain structure uniformity are among the key structural features that influence stampability. A method is proposed and the homogeneity of the grain structure is evaluated. Stampability of Al2Mg and Al6Mg aluminium alloys was evaluated based on measurements of the spring back index, minimum bending radius, stamping ratio, and Martens strain index. Cold work (with a strain degree of 20 %) and subsequent recrystallization annealing at temperatures of 250, 350 and 450 °C for 1 h were used to obtain a grain structure of (26,8 Ѓ} 7,4)÷(126 Ѓ} 43) μm (Al6Mg alloy) and (120 Ѓ} 11)÷(264 Ѓ} 130) μm (Al2Mg alloy) in size. As a result of processing, the effect of the initial grain size was revealed: the coarser structure of the Al2Mg alloy led to a larger grain size after strain and annealing. It was found that an increase in the grain size in both alloys leads to an increase in the Martens index and a decrease in the stamping ratio, which indicates higher stampability of the alloys in the drawing operations of sheet stamping. In the Al2Mg alloy, an increase in the grain size leads to a decrease in the spring back index by 1,5–1,7 times, and an increase in the minimum bending radius. In the Al6Mg alloy, an increase in the grain size leads to an increase in the spring back index by 1,1–1,2 times, and a decrease in the minimum bending radius. The Al6Mg minimum bending radius remains higher compared to Al2Mg regardless of the grain size. Grain size inhomogeneity in the Al6Mg alloy causes an increase in the Martens index and minimum bending radius, and a decrease in the stamping ratio. In the Al2Mg alloy, grain size inhomogeneity causes an increase in the Martens index and minimum bending radius, and a decrease in the stamping ratio. For the spring back index, the increase in grain size inhomogeneity causes a high scatter of data. In the Al6Mg alloy, the low annealing temperature led to the preservation of the non-recrystallized structure, which influenced the decrease in stampability.
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48

Cameron, D. W., R. H. Jeal, and D. W. Hoeppner. "SEM Investigations of Fatigue Crack Propagation in RR 58 Aluminum Alloy." Journal of Engineering for Gas Turbines and Power 107, no. 1 (January 1, 1985): 238–41. http://dx.doi.org/10.1115/1.3239689.

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Aluminum alloy RR 58 (AA 2618) has been viewed during exposure to cyclic loading, which is applied using a load frame inserted into a scanning electron microscope. Thus observation of surface interactions of the material microstructure with a propagating crack is feasible. Photomicrographs and (for the purposes of analysis and presentation) dynamic, real-time video-recordings used to document the processes will be displayed and the nature of the observations presented in relation to existing physical understanding of fatigue. Some additional ideas will be included based on the results presented herein.
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49

Pater, Z., and J. Tomczak. "Experimental Tests for Cross Wedge Rolling of Forgings Made from Non-Ferrous Metal Alloys / Próby Doświadczalne Walcowania Poprzeczno-Klinowego Odkuwek Ze Stopów Metali Nieżelaznych." Archives of Metallurgy and Materials 57, no. 4 (December 1, 2012): 919–28. http://dx.doi.org/10.2478/v10172-012-0101-9.

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Reported in this paper are the experimental test results for hot cross wedge rolling of elementary shaft forgings made from light metal alloys which are widely used in aviation industry, such as aluminum alloys 6101A and 2618A, titanium alloy Ti6Al4V as well as magnesium alloys AZ31 (Mg 3Al-1Zn-Mn), AZ61 (Mg 6Al-1Zn-Mn) and Mg4AlZnMn. The research works were conducted by means of a flat-wedge rolling mill LUW-2, with typical wedge tools used. The experiment tests involved the analysis of force parameters, geometrical parameters, and process stability. The conducted experimental tests prove the feasibility of forming axially symmetric parts made from light metal alloys in CWR (cross wedge rolling) processes. Limitations upon the application of CWR technologies to forming such alloys are also described.
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50

Bergsma, S. C., X. Li, and M. E. Kassner. "Effects of thermal processing and copper additions on the mechanical properties of aluminum alloy ingot AA 2618." Journal of Materials Engineering and Performance 5, no. 1 (February 1996): 100–102. http://dx.doi.org/10.1007/bf02647276.

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