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Journal articles on the topic 'Aluminium alloy 7010'

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Published: 10 December 2022

Last updated: 28 January 2023

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1

Kemp, R. M. J., R. N. Wilson, and P. J. Gregson. "A Comparison of the Corrosion Fatigue Properties of Plate Aluminium Alloys for Aerospace Applications." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 2 (July 1993): 97–104. http://dx.doi.org/10.1243/pime_proc_1993_207_253_02.

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A corrosive environment such as salt water can severely degrade the fatigue properties of aluminium alloys used in aerospace applications. The corrosion fatigue crack growth rate properties of two conventional alloys, that is Al-Zn-Mg-Cu-Zr alloy (7010-T7651) and Al-Cu-Mg alloy (2024–T351) have been compared with the more recently developed Al-Li-Cu-Mg alloy (8090-T8771). Increased growth rates were observed in salt water compared to air for 7010 and 8090 but not for 2024. Comparing the three alloys, the 8090 alloy corrosion fatigue rates were similar to those of 2024 which were considerably less than those for 7010. The increase in crack growth in 8090 due to environment was associated with a decrease in the high level of crack closure observed for tests in air. The susceptibility of an alloy to corrosion fatigue can be summarized using a ‘corrosion fatigue resistance’ index, Rcf

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2

Robinson, Jeremy S., Christopher E. Truman, M. S. Hossain, and Robert C. Wimpory. "Residual Stress and Microstructural Variations in Thick Aluminium Alloy Forgings." Materials Science Forum 571-572 (March 2008): 45–50. http://dx.doi.org/10.4028/www.scientific.net/msf.571-572.45.

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The most critical stage in the heat treatment of high strength aluminium alloys is the rapid cooling necessary to form a supersaturated solid solution. During cold water quenching of thick sections, the thermal gradients are sufficient to cause inhomogeneous plastic deformation which in turn leads to the development of large residual stresses. Two 215 mm thick rectilinear forgings made from 7075 and 7010 were heat treated, and the through thickness residual stresses measured by neutron diffraction and deep hole drilling. The distribution of residual stresses was found to be similar for both alloys varying from highly triaxial and tensile in the core to a state of biaxial compression in the surface. The 7010 forging exhibited significantly larger tensile stresses in the core. 7075 is a much more quench sensitive alloy when compared to 7010. This results in loss of supersaturation by second phase precipitation during quenching in the core of the 7075 forging.

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3

Tanner, David A., Jeremy S. Robinson, and Richard L. Cudd. "Cold Compression Residual Stress Reduction in Aluminium Alloy 7010." Materials Science Forum 347-349 (May 2000): 235–40. http://dx.doi.org/10.4028/www.scientific.net/msf.347-349.235.

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4

Madhusudhan Reddy, G., A. K. Mukhopadhyay, and A. Sambasiva Rao. "Influence of scandium on weldability of 7010 aluminium alloy." Science and Technology of Welding and Joining 10, no. 4 (July 2005): 432–41. http://dx.doi.org/10.1179/174329305x29456.

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5

Mukhopadhyay, A. K., K. Satya Prasad, and A. Dutta. "Influence of Scandium Addition on the High Temperature Compressive Strength of Aluminium Alloy 7010." Materials Science Forum 519-521 (July 2006): 871–76. http://dx.doi.org/10.4028/www.scientific.net/msf.519-521.871.

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The influence of Sc addition on the high temperature compressive strength of a commercial alloy 7010 (hereafter termed base alloy) has been examined. The base alloy, and the base alloy with 0.23 wt% Sc were cast, homogenized and subjected to compression tests at temperatures ranging from 300 to 450oC and strain rates of 10-3, 10-2, 10-1 and 1 sec-1. It is shown that Sc addition to the base alloy increases the compressive flow stress under these deformation conditions. The increase in peak flow stress is nearly 3-6 times the peak flow stress of the base alloy at temperatures 300-350oC over the strain rate range investigated. Whilst, at temperatures ³ 400oC, the flow stresses decrease significantly irrespective of the strain rate used. Transmission electron microscopy (TEM) revealed that a combination of (1) increased nucleation frequency of dispersoids, (2) evolution of smaller subgrain size, and (3) refinement of alloy phases in the Al-Zn-Mg-Cu system contribute to superior strengthening in the alloy containing Sc. Whilst, it is primarily a combination of coarsening and instability of the alloy phases in the Al-Zn-Mg-Cu system that dramatically reduces the flow stresses in both the alloys at temperatures ³ 400oC.

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6

Engler, O., E. Sachot, J. C. Ehrström, A. Reeves, and R. Shahani. "Recrystallisation and texture in hot deformed aluminium alloy 7010 thick plates." Materials Science and Technology 12, no. 9 (September 1996): 717–29. http://dx.doi.org/10.1179/mst.1996.12.9.717.

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7

Earle, T. P., J. S. Robinson, and J. J. Colvin. "Investigating the mechanisms that cause quench cracking in aluminium alloy 7010." Journal of Materials Processing Technology 153-154 (November 2004): 330–37. http://dx.doi.org/10.1016/j.jmatprotec.2004.04.067.

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8

Bhaduri, A., A. N. Tiwari, V. Gopinathan, and P. Ramaskrishnan. "Studies on Mechanically Alloyed 7010 Aluminium Alloy-SiC_p Composites." Materials Science Forum 88-90 (January 1992): 205–12. http://dx.doi.org/10.4028/www.scientific.net/msf.88-90.205.

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9

Robinson, J. S. "Influence of retrogression and reaging on fracture toughness of 7010 aluminium alloy." Materials Science and Technology 19, no. 12 (December 2003): 1697–704. http://dx.doi.org/10.1179/026708303225008383.

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10

Salazar-Guapuriche, Manuel A., Y. Y. Zhao, Adam Pitman, and Andrew Greene. "Correlation of Strength with Hardness and Electrical Conductivity for Aluminium Alloy 7010." Materials Science Forum 519-521 (July 2006): 853–58. http://dx.doi.org/10.4028/www.scientific.net/msf.519-521.853.

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The tensile strength, proof strength, hardness and electrical conductivity of Al alloy 7010 under different temper and ageing conditions were investigated with the aim to correlate strength with hardness and electrical conductivity so that the strength of the alloy can be determined nondestructively. Following the solutionising treatment, continuous age hardening was performed on a series of test coupons, taken from a large plate, to produce a wide range of precipitation hardening conditions, which gave rise to progressive variations of strength, hardness and conductivity. The relationship between strength and hardness was found to be reasonably linear, whereas the relationship between hardness and strength with electrical conductivity was non-linear. The ageing conditions and therefore the mechanical properties of the components can be predicted more accurately by the simultaneous combination of hardness and conductivity values.

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11

Robinson, Jeremy S., and Richard L. Cudd. "Electrical Conductivity Variations in X2096, 8090, 7010 and an Experimental Aluminium Lithium Alloy." Materials Science Forum 331-337 (May 2000): 971–76. http://dx.doi.org/10.4028/www.scientific.net/msf.331-337.971.

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12

Raetzer-Scheibe, H. J., and C. D. S. Tuck. "The polarisation and repassivation behaviour of the aluminium-zinc-magnesium-copper alloy 7010." Corrosion Science 36, no. 6 (June 1994): 941–56. http://dx.doi.org/10.1016/0010-938x(94)90196-1.

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13

Robinson, Jeremy S., and David A. Tanner. "The Influence of Aluminium Alloy Quench Sensitivity on the Magnitude of Heat Treatment Induced Residual Stress." Materials Science Forum 524-525 (September 2006): 305–10. http://dx.doi.org/10.4028/www.scientific.net/msf.524-525.305.

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To produce useful strengthening, precipitation hardenable aluminium alloys rely on rapid quenching from the solution heat treatment temperature to suppress the formation of coarse equilibrium second phases. An unavoidable consequence of the rapid quenching of thick sections is the severe thermal gradients that quickly develop in the material. The attendant inhomogeneous plastic flow can then result in the establishment of residual stresses. The surface and through thickness residual stress magnitudes present in heat treated high strength aluminium alloy components are frequently reported to exceed the uniaxial yield stress of small specimens of the same alloy measured immediately after quenching. In thick section plate and forgings it is proposed that these high residual stress magnitudes are a consequence of hardening precipitation that occurs during quenching which allows for a greater elastic stress to be supported. To investigate this theory, thick sections of the quench sensitive alloy 7175 and the less quench sensitive alloy 7010 were heat treated in such a way as to allow the internal hardness to be measured immediately, after quenching. The rate of cooling was also monitored during quenching and these data were used in conjunction with time temperature property data to predict the degree of precipitation and subsequent loss of hardening potential in the fully heat treated condition. The magnitudes of the residual stresses induced during quenching were determined using standard x-ray diffraction techniques.

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14

Prasad, K. Satya, A. K. Mukhopadhyay, and Vydehi A. Joshi. "On the microstructure developed in as-cast and homogenized 7010 aluminium alloy containing scandium." Zeitschrift für Metallkunde 95, no. 11 (November 2004): 1046–52. http://dx.doi.org/10.3139/146.018058.

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15

Raju, K. S. S. Eswar, A. K. Mukhopadhyay, and S. V. Kamat. "Effect of mixed mode I/III loading on fracture toughness of 7010 aluminium alloy." Materials Science and Technology 22, no. 1 (January 2006): 91–96. http://dx.doi.org/10.1179/174328406x79388.

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16

Angappan, M., V. Sampath, B. Ashok, and V. P. Deepkumar. "Retrogression and re-aging treatment on short transverse tensile properties of 7010 aluminium alloy extrusions." Materials & Design 32, no. 7 (August 2011): 4050–53. http://dx.doi.org/10.1016/j.matdes.2011.03.034.

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17

Mallireddy, Naresh, and K. Siva. "Investigation of Microstructural, Mechanical and Corrosion Properties of AA7010-TiB2 in-situ Metal Matrix Composite." Science and Engineering of Composite Materials 27, no. 1 (April 2, 2020): 97–107. http://dx.doi.org/10.1515/secm-2020-0010.

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AbstractAluminum alloys with ceramic reinforced particulates are made prospective in aerospace, transportation, and industrial applications ampler to their low mass density, stiffness, and high specific strength. In this work, Aluminium Alloy(AA) 7010 - TiB2 (Titanium Diboride) composites with different amounts of reinforcement (5, 7.5 and 10 wt.%) were produced by the exothermic reaction of halide salts K2TiF6 and KBF4 added in 120% excess to the stoichiometric ratio with molten AA7010.The effect and dispersion of TiB2 particulates in AA7010 were analyzed by microstructural, mechanical and corrosion behavior. The dispersion of reinforcement in the matrix alloy was analyzed by optical microscope and field emission scanning electron microscope (FESEM) images. X-ray diffraction patterns of the prepared composites reveal the formation of TiB2 particles in the matrix alloy. Indeed samples are tested according to ASTM G34 standard for ex- foliation corrosion rate by weight loss method. The result shows improved hardness, tensile strength and yield strength of composites to about 35%, 260%, and 240% respectively. The mechanical and corrosion resistance of 10% TiB2 shows better results compared with matrix alloy and other concentrations of reinforcements.

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18

Nandana, M. S., K. Udaya Bhat, and C. M. Manjunatha. "Effect of retrogression and re-ageing heat treatment on microstructure and microhardness of aluminium 7010 alloy." MATEC Web of Conferences 144 (2018): 02003. http://dx.doi.org/10.1051/matecconf/201714402003.

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19

Mukhopadhyay, A. K., K. S. Prasad, and D. S. K. Murali. "Rate of workhardening influencing subzero temperature tensile strength properties of heat treated aluminium alloy 7010 plates." Materials Science and Technology 27, no. 11 (November 2011): 1732–35. http://dx.doi.org/10.1179/026708310x12815992418292.

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20

Nandana, M. S., K. Udaya Bhat, and C. M. Manjunatha. "Effect of retrogression and re-ageing heat treatment on microstructure and microhardness of aluminium 7010 alloy." MATEC Web of Conferences 144 (2018): 02003. http://dx.doi.org/10.1051/matecconf/201814402003.

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Aluminium alloy 7010 is subjected to retrogression and re-ageing (RRA) heat treatment to study the influence of microstructural changes on hardness. Retrogression is performed at 190 °C for different time intervals ranging from 10 to 60 minutes. Optimum time for retrogression treatment is estimated based on the retrogression time that result with equivalent mechanical properties as that of peak aged (T6) condition. Retrogression performed for 30 minutes resulted with micro hardness of 203 HV, which is equivalent to that obtained by following T6 treatment. Microstructural characterization done with the help of transmission electron microscope (TEM) indicates RRA treatment results with the coarsened and discontinuous precipitates along the grain boundary which is similar to over aged (T7) condition, where as fine and densely populated precipitates in the matrix similar to T6 condition. Coarse and discontinuous grain boundary precipitates (GBP’s) improves resistance to stress corrosion cracking. Fine and dense precipitates in the matrix ensures hardness equivalent to that of T6.

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21

Eswar Raju, K. S. S., Ashim K. Mukhopadhyay, and Samir V. Kamat. "The effect of ageing on tensile behaviour, mode I and mixed mode I/III fracture toughness of 7010 aluminium alloy." International Journal of Materials Research 97, no. 11 (November 1, 2006): 1550–58. http://dx.doi.org/10.1515/ijmr-2006-0242.

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Abstract The effect of ageing on the tensile behaviour, mode I fracture toughness and mixed mode I/III fracture toughness of 7010 aluminium alloy plate was investigated. It was found that the 0.2% proof stress in this alloy increased from the under-aged temper to the peak-aged (T6) temper and then subsequently decreased in the over-aged (T73) temper. On the other hand, the ductility exhibited a monotonic decrease from the under-aged temper to the over-aged temper. The Ludwigson equation was found to best describe the flow behaviour in all the three ageing tempers. Under mode I as well as mixed mode I/III loading, the highest fracture toughness was seen in the under-aged temper, whereas the fracture toughness values in the peak-aged and over-aged tempers were comparable.

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22

Harvey, J., P. G. Partridge, and A. M. Lurshay. "Factors affecting the shear strength of solid state diffusion bonds between silver-coated Clad AlZnMg alloy (aluminium alloy 7010)." Materials Science and Engineering 79, no. 2 (May 1986): 191–99. http://dx.doi.org/10.1016/0025-5416(86)90404-0.

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23

Prasad, K. S., A. K. Mukhopadhyay, B. Majumdar, and D. Akhtar. "On the Nature and Stability of Phases Present in a Rapidly Solidified Aluminium Alloy 7010 Containing Scandium." Materials and Manufacturing Processes 23, no. 7 (September 4, 2008): 658–64. http://dx.doi.org/10.1080/10426910802316633.

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24

Robinson, Jeremy S., and P. Flynn. "The Effects of Thermal Treatments on the Stress Corrosoin Cracking Resistance of Forgings of the Aluminium Alloy 7010." Key Engineering Materials 99-100 (March 1995): 143–50. http://dx.doi.org/10.4028/www.scientific.net/kem.99-100.143.

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25

Flynn, Robert J., and J. S. Robinson. "The application of advances in quench factor analysis property prediction to the heat treatment of 7010 aluminium alloy." Journal of Materials Processing Technology 153-154 (November 2004): 674–80. http://dx.doi.org/10.1016/j.jmatprotec.2004.04.133.

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26

Tanner, D. A., and J. S. Robinson. "Effect of precipitation during quenching on the mechanical properties of the aluminium alloy 7010 in the W-temper." Journal of Materials Processing Technology 153-154 (November 2004): 998–1004. http://dx.doi.org/10.1016/j.jmatprotec.2004.04.226.

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27

Goudar, D. M., M. S. Hossain, Christopher E. Truman, Ed J. Kingston, and David John Smith. "Uncertainties in Triaxial Residual Stress Measurements." Materials Science Forum 681 (March 2011): 498–503. http://dx.doi.org/10.4028/www.scientific.net/msf.681.498.

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Residual stress measurement techniques using mechanical strain relaxation depend on a number of physical quantities and are therefore sensitive to errors associated with the measured data. The resulting stress uncertainties can easily become significant and compromise the usefulness of the results or lead to misinterpretation of the behaviour of the residual stress distributions. It is therefore essential to develop an error analysis procedure for the measurements undertaken. Error analysis procedures for the deep hole drilling (DHD) method are developed to consider triaxial residual stresses. A modified deep hole drilling method, called the incremental deep-hole drilling (iDHD), was applied to measure the near yield residual stress distributions in a cold water quenched aluminium 7010 alloy forged block. The experimental results are used to illustrate the errors.

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28

Eswar Raju, K. S. S., Ashim K. Mukhopadhyay, and Samir V. Kamat. "The effect of ageing on tensile behaviour, mode I and mixed mode I/III fracture toughness of 7010 aluminium alloy." International Journal of Materials Research 97, no. 11 (November 2006): 1550–58. http://dx.doi.org/10.3139/146.101420.

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29

Zuo, Yu Bo, Zhi Hao Zhao, Qing Feng Zhu, Xiang Jie Wang, and Jian Zhong Cui. "Preparing Large Sized Billet of High Strength Aluminum Alloy with the Application of Low Frequency Electromagnetic Field." Advanced Materials Research 472-475 (February 2012): 723–26. http://dx.doi.org/10.4028/www.scientific.net/amr.472-475.723.

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Grain refinement is quite important for producing 7050 alloy billet especially in large scale. Low frequency electromagnetic casting (LFEC) process was used to make 7050 aluminum alloy Φ500 mm billets and study the effect of electromagnetic field on the microstructure. The sound Φ500 mm billets of 7050 alloys without any grain refiner can be successfully prepared by the LFEC process. The results show that low frequency electromagnetic field has a significant grain refining effect on 7050 alloy and can effectively eliminate feather grain structure. The microstructures of LFEC ingot from the border to the center of the cross section are all equiaxed grains and are finer and more uniform than that of conventional direct chill (DC) cast billets. The LFEC process also shows a strong power to eliminate hot tearing during casting large sized billet of high strength aluminium alloy.

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30

Mohd Nor, Mohd Khir, Rade Vignjevic, and James Campbell. "Modelling of Shockwave Propagation in Orthotropic Materials." Applied Mechanics and Materials 315 (April 2013): 557–61. http://dx.doi.org/10.4028/www.scientific.net/amm.315.557.

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Modelling of shockwave propagation in orthotropic materials requires an appropriate description of material behaviour within elastic and plastic regimes. To deal with this issues, a finite strain constitutive model for orthotropic materials was developed within a consistent thermodynamic framework of irreversible process in this paper. The important features of this material model are the multiplicative decomposition of the deformation gradient and a Mandel stress tensor combined with the new stress tensor decomposition generalised for orthotropic materials. The elastic free energy function and the yield function are defined within an invariant theory by means of the introduction of the structural tensors. The plastic behaviour is characterised within the associative plasticity framework using the Hills yield criterion. The complexity was further extended by coupling the formulation with the equation of state (EOS) to control the response of the material to shock loading. This material model which was developed and integrated in the isoclinic configuration provides a unique treatment for elastic and plastic anisotropy. The effects of elastic anisotropy are taken into account through the stress tensor decomposition and plastic anisotropy through yield surface defined in the generalized deviatoric plane perpendicular to the generalised pressure. To test its ability to describe shockwave propagation, the new material model was implemented into the LLNL-DYNA3D code. The results generated by the proposed material model were compared against the experimental Plate Impact test data of Aluminium Alloy 7010. A good agreement between experimental and simulation was obtained for two principal directions of material orthotropy.

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31

Teng, Yunnan, Liyang Xie, and Hongyuan Zhang. "Experimental Study on Vibration Fatigue Behavior of Aircraft Aluminum Alloy 7050." Materials 15, no. 21 (October 27, 2022): 7555. http://dx.doi.org/10.3390/ma15217555.

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It has been previously noted that the development of aerospace material technology and breakthroughs are inseparable when obtaining great achievements in the aerospace industry. Materials are the basis and precursor of modern high technology and industry. As one of the most powerful aluminium alloys, 7050 is widely used in the aerospace field. In this manuscript, the vibration fatigue behaviour of aircraft aluminium alloy 7050 is studied based on experiments. A vibration fatigue experiment and the traditional fatigue testing of aluminium alloy 7050 were performed. We found that there was an extreme difference between the vibration fatigue and the traditional fatigue curves. In addition, the experimental end criteria for the vibration fatigue experiment of aluminium alloy 7050 was obtained from the acceleration reduction and the frequency reduction value. For the acceleration experimental end criterion, 2% was the acceleration reduction value for the vibration fatigue experimental end criteria of aluminium alloy 7050. For the frequency experimental end criterion, 2% was the frequency reduction value for the vibration fatigue experimental end criteria of aluminium alloy 7050.

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32

Forsyth, P. "The Expansion Rate of the Superficial Corrosion Discs that Rapidly Form on Machined Surfaces of the High Strength Aluminium Alloy AA 7010-T736 when Immersed in Saline Solutions. / Die Expansionsgeschwindigkeit von sich rasch bildenden oberflächlichen Korrosionsscheibchen auf bearbeiteten Oberflächen der hochfesten Aluminiumlegierung AA 7010-T736 bei Eintauchen in Salzlösung." Practical Metallography 39, no. 11 (November 1, 2002): 599–610. http://dx.doi.org/10.1515/pm-2002-391106.

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33

Cao, Zhong, Ju Lan Zeng, Yi Min Dai, Xun Li, and Dong Mei Luo. "Sensing Analysis of Aluminum Alloy Materials Based on Chemical Acoustic Emission Signals." Advanced Materials Research 139-141 (October 2010): 176–79. http://dx.doi.org/10.4028/www.scientific.net/amr.139-141.176.

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The frequency domain power spectra of acoustic emission (AE) signals from different metal-acid reaction processes such as 6111 Al-alloy-hydrochloric acid (HCl) and 7070 Al-alloy-HCl for evolving hydrogen gases were obtained by fast Fourier transform (FFT) program and used for chemical analysis of different metal materials. Averaged power spectra from these processes and their corresponding characteristics were extracted. The characteristic AE frequency signals could be used for chemical pattern recognition of different metal materials like 6111 and 7050 aluminum alloys from the metal-acid reaction processes, that the principal component analysis (PCA) with appropriate frequency selection procedure gave a satisfactory classification with a correct rate of 78.1%. The back-propagation (BP) algorithm of artificial neural network (ANN) could give better recognition of AE signals for 6111 and 7050 alloys with a correct rate of 100%. Moreover, the AE energetic parameters are linearly correlated with the pH value of the acidic buffer solution, which opens a new possibility for quantitatively analytical application of AE signals on metal materials.

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34

Dudzik, Krzysztof, and Mirosław Czechowski. "Influence of Joining Method for Mechanical Properties of 5083, 5059 and 7020 Aluminum Alloys Joints." Solid State Phenomena 220-221 (January 2015): 583–88. http://dx.doi.org/10.4028/www.scientific.net/ssp.220-221.583.

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The paper presents the research results on the mechanical properties of aluminum alloy 7020 and its FSW and MIG welded joints. For comparison, alloy 5083 – the most currently used in shipbuilding alloy was chosen as well as 5059 – the new high-strength alloy. Besides, the native material alloys there were investigated their joints welded by FSW and MIG – the same methods as alloy 7020. Welding parameters used for the connection of the sheets made of 7020, 5083 and 5059 alloys were presented. Metallographic analysis showed the correct construction of structural bonded joints.Friction Stir Welding (FSW) – a new technology can be successfully used for butt welding of different types of aluminum alloy sheets. FSW method can be an alternative to traditional arc welding methods, especially MIG, which is the most common method of joining aluminum alloys used in shipbuilding. The research was carried out using a static tensile test in accordance with the requirements of the Polish Standards PN-EN ISO 4136:2011 and PN-EN ISO 6892-1:2010. Flat samples cut perpendicular to the direction of rolling were used. The research was conducted at the temperature of +20 oC.Friction stir welded joints of tested alloys have higher strength properties as compared to MIG welded joints. The 7020 alloy has higher strength properties then alloys 5083 and 5059. The yield stress is higher by 14.8% as compared to alloy 5083, and by 11.7% as compared to the alloy 5059. Plastic properties of alloy 7020 are the lowest, but with reserves meet the requirements of classification societies. The joints welded by FSW of alloy 7020 have the highest strength properties of all researched joints – higher then alloys 5083 and 5059 joints welded by FSW and joints of all alloys welded by MIG.

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35

Azpilgain, Zigor, Inaki Hurtado, R. Ortubay, I. Landa, and J. Atxa. "Semisolid Forging of 7000 Series Aluminum Alloys." Solid State Phenomena 116-117 (October 2006): 758–61. http://dx.doi.org/10.4028/www.scientific.net/ssp.116-117.758.

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The achievement of lighter automotive components is an important driving force in the development and optimization of casting techniques. In this sense, semisolid forming is an emerging technology that has allowed the production of security components using aluminum alloys. The foundry alloys A356 and A357 remain, up to the present, the most used alloys for the semisolid processing of components. Nevertheless, several authors have pointed out the gain in properties that other alloy families could provide. In the present work, thixoformability of 7000 series aluminum alloys is studied. Thermodynamic calculations (CALPHAD method) and calorimetric experiments have been performed to determine the composition of alloys with an optimum process window. A modification of the 7075 alloy is proposed in order to improve its thixoformability parameters and optimize the process control. A simple component has been produced by semisolid forging and mechanical properties have been measured from tensile samples.

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36

Fan, Xi Gang, Da Ming Jiang, Chang Li Wang, Yong Liang Guo, and Xing Qiu Liu. "Influence of Microstructure on the Fracture Mechanism and Mechanical Behavior in 7010 and 7150 Alloys." Key Engineering Materials 324-325 (November 2006): 463–66. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.463.

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The effect of ageing treatment and coarse intermetallic particles on the compromise between the toughness and the yield strength of 7010 and 7150 aluminum alloys (Al-Zn-Mg-Cu alloys) are investigated. Plane-strain fracture toughness tests were performed on the compact-tension specimens of L-T orientation. The fracture toughness of 7010 alloy was higher than that of 7150 alloy at the same ageing treatment. The 7150 alloy contain a greater amount of coarse Cu-bearing particles, which deteriorate the fracture behavior and decrease the ageing hardening ability of the alloy. The toughness of the both alloys increased greatly for the overaged condition as compared to that for the T6 condition. Two dominant mechanisms of failure occur: microvoid-induced transgranular fracture and intergranular fracture modes, and the former becomes more important in the overaged ageing conditions.

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37

Rajendran, Rupesh, Crosby T. Owens, Jeffrey D. Eisenhaure, and Preet M. Singh. "Electrochemical Behavior of Additively Manufactured 7050 Aluminum Alloy in Chloride Environments." ECS Meeting Abstracts MA2022-02, no. 10 (October 9, 2022): 695. http://dx.doi.org/10.1149/ma2022-0210695mtgabs.

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The benefits of additive manufacturing (AM) process combined with the high-strength, corrosion resistant and fracture toughness properties of the 7xxx series aluminum alloys make them promising candidates for the aerospace and defense industries. However, these alloys undergo unconventional thermal cycles during additive manufacturing process like laser powder bed fusion (LPBF) as well as during post-processing treatments like hot isostatic pressing, resulting in microstructures different from equivalent wrought alloys. In our work, we investigate how the effects of microstructural differences in a modified LPBF 7050 aluminum alloy compared to an equivalent wrought alloy, results in differences in electrochemical behavior. A series of AM 7050 aluminum alloy samples with different post-processing treatments and subsequent microstructures are tested for polarization and electrochemical impedance behavior in varying chloride ion concentrations. The effects of underaging and overaging treatment on the electrochemical behavior is also studied. Localized corrosion behavior of the alloys is investigated using immersion tests and scanning vibration electrode technique (SVET), which showed differences in pitting behavior and pit stability. The results indicate that AM 7050 alloy in general, showed less corrosion susceptibility compared to an equivalent wrought alloy.

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Wang, Wei Han, Wei Fang Zhang, Wei Zhang, and Jin Song Yang. "Research on the Material Differences of 7050-T7451 Aluminum Alloy." Applied Mechanics and Materials 727-728 (January 2015): 115–18. http://dx.doi.org/10.4028/www.scientific.net/amm.727-728.115.

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Microstructure analysis and tensile fracture analysis were conducted on the domestic and imported 7050-T7451 aluminum alloy to investigate the material differences between them. Tensile test shows that the yield strength and tensile strength of domestic 7050-T7451 aluminum alloy are both higher than imported 7050-T7451 aluminum alloy, however, the material elongation and the reduction of area are both lower than imported material. Microstructure analysis shows that compared with domestic 7050-T7451 aluminum alloy, in the imported 7050-T7451 aluminum alloy, the degree of recrystallization and anisotropy is less, and the grain size is smaller. In addition, the transition from material surface to center organization of imported 7050-T7451 aluminum alloy is more smooth and uniform than domestic material. From tensile fracture analysis, it concluded that the domestic 7050-T7451 aluminum alloy has large grain size, low structural homogeneity, and little toughness characteristic of fracture, and those characteristics cause low elongation and low reduction of area of domestic 7050-T7451 aluminum alloy.

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Tiryakioğlu, M., J. S. Robinson, M. A. Salazar-Guapuriche, Y. Y. Zhao, and P. D. Eason. "Hardness–strength relationships in the aluminum alloy 7010." Materials Science and Engineering: A 631 (April 2015): 196–200. http://dx.doi.org/10.1016/j.msea.2015.02.049.

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Desmukh, Mohammed Noor, R. K. Pandey, and A. K. Mukhopadhyay. "Fatigue behavior of 7010 aluminum alloy containing scandium." Scripta Materialia 52, no. 7 (April 2005): 645–50. http://dx.doi.org/10.1016/j.scriptamat.2004.11.018.

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Patton, G., C. Rinaldi, Y. Bréchet, G. Lormand, and R. Fougères. "Study of fatigue damage in 7010 aluminum alloy." Materials Science and Engineering: A 254, no. 1-2 (October 1998): 207–18. http://dx.doi.org/10.1016/s0921-5093(98)00762-x.

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Zhang, M. L., J. M. Wang, Y. F. Jiang, Q. L. Zhang, and Q. L. Zhou. "Effect of 7050 Aluminium Alloy Microstructure on Residual Stress by Laser Shock Processing." Advanced Materials Research 463-464 (February 2012): 1363–67. http://dx.doi.org/10.4028/www.scientific.net/amr.463-464.1363.

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The solution treatment and solution and aging treatment (T6) were disposed on 7050 aluminium alloy, then local processed by laser shock processing (LSP) with high-rate neodymium glass laser. The microhardness and residual stress on the surface of 7050 aluminium alloy were tested, then how the microstructure influences the residual stress on the surface of 7050 aluminium alloy by laser shock processing was analysed. The results show that the microhardness and residual compressive stress on the surface of 7050 aluminium alloy treated by solution and aging treatment was higher, and decreased obviously treated by solution treatment; the microhardness and residual compressive stress on the surface of 7050 aluminium alloy increased obviously by solution treatment and solution and aging treatment after laser shock processing; treated by solution treatment and solution and aging treatment, the microhardness and residual compressive stress of the material with uniform original structure was higher than the material with nonuniform original structure.

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Chen, De Bin, Hui E. Hu, and Xiao Dong Kong. "Plastic Anisotropy Research of As-Rolled 7050 Aluminum Alloy Plate with T7451 Temper." Applied Mechanics and Materials 189 (July 2012): 130–33. http://dx.doi.org/10.4028/www.scientific.net/amm.189.130.

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Plastic anisotropy of the as-rolled 7050 aluminum alloy plate with T7451 temper was investigated by tensile tests, OM, SEM and TEM. The results show that the as-rolled 7050 aluminum alloy plate shows plastic anisotropy. The values of the as-rolled 7050 aluminum alloy plate deformed along ST, LT and RD are 7.178%, 10.69% and 12.877%, respectively. The as-rolled 7050 aluminum plate can be considered as a materials with two phases. Microstructure, especially grain shape and precipitate configuration, is the main source of plastic anisotropy of the as-rolled 7050 aluminum alloy plate with T7451 temper.

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Nishi, Masatomo, Naoya Miura, Katsumi Watanabe, Susumu Ikeno, Tomoo Yoshida, Satoshi Murakami, and Kenji Matsuda. "Effect of Zn/Mg on Age Hardening Behavior in 7000 System Al Alloys." Advanced Materials Research 922 (May 2014): 549–52. http://dx.doi.org/10.4028/www.scientific.net/amr.922.549.

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7000 System Al has been known as one of the aluminum alloys with the good age hardening ability and the high strength among commercial aluminum alloys. [1]In this study, hardness measurement, tensile test, SEM observation and TEM observation have been performed in order to understand the effect of Zn/Mg ratio on age hardening behaviour in Al-Zn-Mg alloys . It can be seen from hardness measurement that the alloy containing higher Zn and Mg contents became hard. Tensile test was performed for the samples of peak aged condition. It can been seen that the alloy containing higher Zn and Mg increases the tensile strength of the alloy though decrease of the elongation were observed a typical intergranular fracture. TEM observation was performed for peak aged samples. The size of precipitates became finer and the number density increased with increasing Zn and Mg contents.

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Wang, Hui, Ying Meng, Duo Duo Li, Xiu Li Fu, and Qi Hang Shi. "Study on the Influence of Anisotropy on Cutting Performance of Aviation Aluminium Alloy 7050-T7451." Materials Science Forum 990 (May 2020): 29–35. http://dx.doi.org/10.4028/www.scientific.net/msf.990.29.

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Based on the hypocycloid theory, a highspeed orthogonal cutting simulation model was established. The cutting parameters (cutting speed, feed rate) and plane forming angle of the workpiece of aeronautical aluminium alloy 7050-T7451 pre-stretched rolled sheet were simulated and validated. The mapping relationship between cutting parameters, anisotropy and cutting performance was analyzed. The results show that the degree of anisotropy and the difficulty of material cutting are proportional to the forming angle, and the anisotropy decreases with the increase of cutting speed and the decrease of feed speed. Finally, the optimal cutting process range of aluminum alloy 7050-T7451 was obtained, which provides data support for highspeed cutting of anisotropic materials.

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Almajid, Abdulhakim A. "High-Temperature Deformation of Naturally Aged 7010 Aluminum Alloy." Metals 11, no. 4 (April 2, 2021): 581. http://dx.doi.org/10.3390/met11040581.

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This study is focused on the deformation mechanism and behavior of naturally aged 7010 aluminum alloy at elevated temperatures. The specimens were naturally aged for 60 days to reach a saturated hardness state. High-temperature tensile tests for the naturally aged sample were conducted at different temperatures of 573, 623, 673, and 723 K at various strain rates ranging from 5 × 10−5 to 10−2 s−1. The dependency of stress on the strain rate showed a stress exponent, n, of ~6.5 for the low two temperatures and ~4.5 for the high two temperatures. The apparent activation energies of 290 and 165 kJ/mol are observed at the low, and high-temperature range, respectively. These values of activation energies are greater than those of solute/solvent self-diffusion. The stress exponents, n, and activation energy observed are rather high and this indicates the presence of threshold stress. This behavior occurred as a result of the dislocation interaction with the second phase particles that are existed in the alloy at the testing temperatures. The threshold stress decreases in an exponential manner as temperature increases. The true activation energy was computed by incorporating the threshold stress in the power-law relation between the stress and the strain. The magnitude of the true activation energy, Qt dropped to 234 and 102 kJ/mol at the low and high-temperature range, respectively. These values are close to that of diffusion of Zinc in Aluminum and diffusion of Magnesium in Aluminum, respectively. The Zener–Hollomon parameter for the alloy was developed as a function of effective stress. The data in each region (low and high-temperature region) coalescence in a segment line in each region.

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Petton, G., Yves Bréchet, G. Lormand, and Roger Fougères. "Modeling of Fatigue Damage Mechanisms of 7010 Aluminum Alloy." Materials Science Forum 217-222 (May 1996): 1401–6. http://dx.doi.org/10.4028/www.scientific.net/msf.217-222.1401.

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Nagaumi, Hiromi, Guan Xia Xue, Zheng Zheng Zhang, and Yu Li Ma. "Effect of Contraction Behaviors during Solidification of 7xxx Aluminum Alloys on Hot Tearing Susceptibility." Materials Science Forum 783-786 (May 2014): 300–306. http://dx.doi.org/10.4028/www.scientific.net/msf.783-786.300.

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Contraction behavior of 7xxx aluminum alloys was systematically investigated using a new device for measuring linear contraction during solidification. The effects of contraction behaviors and microstructure during solidification of three types of 7xxx series aluminum alloys on the hot tearing susceptibility were studied. It was found that the contraction behaviors of the three alloys showed extremely different shrinkage characters during solidification. The linear expansion coefficient (LEC) of 7050 and 7075 alloys shown an enormous increase from rigidity point (solid fraction is 0.69 and 0.73 respectively) to the peak value and then dropped to a constant value with the decreasing temperature. The LEC of 7022 alloy is different from the 7050 and 7075 alloys that it increases from rigidity point (solid fraction around 0.8) with a small fluctuation at the temperature little lower to the rigidity point and then they increase monotonously to the room temperature. The microstructure showed that the onset of the contraction process was the point which dendrites started coalescence. The profiles of thermal expansion coefficient of 7050 alloy were greater than the 7022’s during the solidification process, so the contraction behavior of the alloy during solidification could be used as a kind of criterion of hot tearing susceptibility.

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Spathis, Panagiotis. "Influence of anodic coatings on stress corrosion behaviour of 7017 aluminium alloy." Anti-Corrosion Methods and Materials 61, no. 1 (December 20, 2013): 27–31. http://dx.doi.org/10.1108/acmm-12-2012-1226.

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Purpose – The purpose of this work was to study the cracking susceptibility of a 7017 aluminium alloy, after anodising under various conditions. Design/methodology/approach – Slow strain tests in dry air, laboratory air and sodium chloride solution were employed. Anodic oxide films were produced with various applied current densities and thicknesses, in horizontal or vertical orientation of the coatings, at the free corrosion potential and also at various anodic or cathodic potentials. For the interpretation of the results, a metallographic study of the specimens before and after straining to failure was carried out using a scanning electron microscope. Findings – The behaviour of anodic coatings was found to depend very much on the anodising conditions. The coatings reduced the ductility of the alloy in dry air but can actually increase the ductility in laboratory air and in 3.5 per cent sodium chloride solution. In most cases, the ductility of coated specimens was greater in 3.5 per cent NaCl solution than in dry air, possibly due to crack blunting by the aggressive environment. Anodic coatings moved the free corrosion potential of the alloy in the noble direction and both the anodised and the bare alloy generally suffered a reduction in ductility at potentials anodic or cathodic to the free corrosion potential, the fall being more rapid for the anodised alloy. Research limitations/implications – The mechanism causing the increased ductility of coated specimens in 3.5 per cent NaCl solution than in dry air remains yet to be confirmed. Practical implications – The selection of suitable anodic coatings for the protection of aluminium alloys against stress corrosion cracking depends on the anodising conditions. Originality/value – The paper provides information regarding the influence of anodising conditions on the anticorrosive properties of electrolytically prepared anodic coatings on aluminium alloys.

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Yeganefar, Ali, Seyed Ali Niknam, and Victor Songmene. "Machinability study of aircraft series aluminium alloys 7075-T6 and 7050-T7451." Transactions of the Canadian Society for Mechanical Engineering 44, no. 3 (September 1, 2020): 427–39. http://dx.doi.org/10.1139/tcsme-2019-0215.

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The aluminium alloy 7050-T7451 is generally considered as the principal choice in aeronautical applications demanding adequate strength, stress corrosion cracking resistance, and toughness. Surprisingly, despite extensive research works on machining and machinability of aluminium alloys, including aluminium alloy 7075-T6, limited information was found on machining and machinability evaluation of 7050-T7451, which belongs to a similar family as 7075-T6. To remedy the lack of knowledge determined, dry ball-end milling operations were performed with coated end milling tools on both materials. Experimental characterization and cutting force measurements were performed to measure/evaluate the cutting forces, burr formation morphology, insert performance (wear/breakage), and surface quality attributes. According to experimental studies, 7050-T7451 was found more machinable than 7075-T6. Less burr formation and better surface quality were observed on 7075-T6. Machining attributes are influenced by different experimental factors. However, other machinability attributes, including residual stress, vibration modes, as well as particle emission, must be studied under various lubrication modes and machining operations in subsequent studies. This also recalls further studies on simultaneous multiple response optimization.

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