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Journal articles on the topic 'Aluminum alloys – Fatigue'

Author: Grafiati

Published: 4 June 2021

Last updated: 31 January 2023

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1

Dostál, Petr, Michal Černý, Jaroslav Lev, and David Varner. "Proportional monitoring of the acoustic emission in crypto-conditions." Acta Universitatis Agriculturae et Silviculturae Mendelianae Brunensis 59, no. 5 (2011): 31–38. http://dx.doi.org/10.11118/actaun201159050031.

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The work is aimed at studying corrosion and fatigue properties of aluminum alloys by means of acoustic emission (AE). During material degradation are acoustic events scanned and evaluated. The main objective of the article is a description of behavior of aluminum alloys degraded in specific conditions and critical degradation stages determination. The first part of the article describes controlled degradation of the material in the crypto–conditions. The acoustic emission method is used for process analyzing. This part contains the AE signals assessment and comparing aluminium alloy to steel. Then the specimens are loaded on high-cyclic loading apparatus for fatigue life monitoring. Also, the synergy of fatigue and corrosion processes is taken into account.The aim is the description of fatigue properties for aluminum alloys that have already been corrosion-degraded. Attention is also focused on the structure of fatigue cracks. The main part of the article is aimed at corrosion degradation of aluminium alloys researched in real time by means of AE. The most important benefit of AE detection/recording is that it provides information about the process in real time. Using this measurement system is possible to observe the current status of the machines/devices and to prevent serious accidents.

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2

Zhao, Xuehang, Haifeng Li, Tong Chen, Bao’an Cao, and Xia Li. "Mechanical Properties of Aluminum Alloys under Low-Cycle Fatigue Loading." Materials 12, no. 13 (June 27, 2019): 2064. http://dx.doi.org/10.3390/ma12132064.

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In this paper, the mechanical properties of 36 aluminum alloy specimens subjected to repeated tensile loading were tested. The failure characteristics, stress-strain hysteresis curves and its corresponding skeleton curves, stress cycle characteristics, and hysteretic energy of specimens were analyzed in detail. Furthermore, the finite element model of aluminum alloy specimens under low-cycle fatigue loading was established and compared with the experimental results. The effects of specimen parallel length, parallel diameter, and repeated loading patterns on the mechanical properties of aluminum alloys were discussed. The results show that when the specimen is monotonously stretched to fracture, the failure result from shearing break. When the specimen is repeatedly stretched to failure, the fracture of the specimen is a result of the combined action of tensile stress and plastic fatigue damage. The AA6061, AA7075, and AA6063 aluminum alloys all show cyclic softening characteristics under repeated loading. When the initial stress amplitude of repeated loading is greater than 2.5%, the repeated tensile loading has a detrimental effect on the deformability of the aluminum alloy. Finally, based on experiment research as well as the results of the numerical analysis, the calculation method for the tensile strength of aluminum alloys under low-cycle fatigue loading was proposed.

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3

KURUMADA, Akira, Makoto SOUMA, Takahito WATAKABE, and Goroh ITOH. "OS18F099 Effect of Hydrogen on the Fatigue Crack Propagation in Aluminum Alloys." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2011.10 (2011): _OS18F099——_OS18F099—. http://dx.doi.org/10.1299/jsmeatem.2011.10._os18f099-.

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4

BUAHOMBURA, Panya, Yukio MIYASHITA, Yoshiharu MUTOH, and NOBUSHIRO Seo. "409 Fatigue Crack Growth Behavior of FSWed Joint in Different Aluminum Alloys." Proceedings of the Materials and processing conference 2012.20 (2012): _409–1_—_409–4_. http://dx.doi.org/10.1299/jsmemp.2012.20._409-1_.

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5

HARLOW, D. GARY. "PARTICLE STATISTICS IN ALUMINUM ALLOYS." International Journal of Reliability, Quality and Safety Engineering 13, no. 04 (August 2006): 379–95. http://dx.doi.org/10.1142/s021853930600232x.

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Pitting corrosion and fatigue crack growth are primary degradation mechanisms that affect the durability and integrity of structures made of aluminum alloys, and they are concerns for commercial transport and military aircraft. The heterogeneous nature of aluminum alloys is the reason that these are operative damage mechanisms. Typically, there are about 2,000 constituent particles per mm2on polished surfaces. Corrosion pits commence at the constituent particles and evolve into severe pits by sustained growth through clusters of particles. The severe pits are nucleation sites for subsequent fatigue crack growth. Even when the environment is not as deleterious, fatigue cracks nucleate from clusters of particles. Thus, the role of heterogeneous clusters of constituent particles is critical to the damage evolution of aluminum alloys. To formulate stochastic models that can serve as part of structural reliability analyses for the damage evolution in aluminum alloys, it is essential that quantitative descriptions of the spatial statistics of the particles and particle clusters, including their location, size, and density are developed. The primary purpose of this effort is to estimate statistically the distribution functions of the key geometrical properties of constituent particles in aluminum alloys and their role in damage evolution.

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6

BIAN, Jian-Chun, Keiro TOKAJI, and Takeshi OGAWA. "Study on Fatigue Properties of Aluminum-Lithium Alloys,IV. Notch Sensitivity of Aluminum-Lithium Alloys in Fatigue." Journal of the Society of Materials Science, Japan 43, no. 490 (1994): 840–46. http://dx.doi.org/10.2472/jsms.43.840.

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7

Fan, Chao Hua, Yu Ting He, Heng Xi Zhang, Hong Peng Li, and Feng Li. "Predictive Model Based on Genetic Algorithm-Neural Network for Fatigue Performances of Pre-Corroded Aluminum Alloys." Key Engineering Materials 353-358 (September 2007): 1029–32. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.1029.

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In the paper, genetic algorithm is introduced in the study of network authority values of BP neural network, and a GA-NN algorithm is established. Based on this genetic algorithm-neural network method, a predictive model for fatigue performances of the pre-corroded aluminum alloys under a varied corrosion environmental spectrum was developed by means of training from the testing dada, and the fatigue performances of pre-corroded aluminum alloys can be predicted. The results indicate that genetic algorithm-neural network algorithm can be employed to predict the underlying fatigue performances of the pre-corroded aluminum alloy precisely, compared with traditional neural network.

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8

Wang, Xi-Shu, Xu-Dong Li, Hui-Hui Yang, Norio Kawagoishi, and Pan Pan. "Environment-induced fatigue cracking behavior of aluminum alloys and modification methods." Corrosion Reviews 33, no. 3-4 (July 1, 2015): 119–37. http://dx.doi.org/10.1515/corrrev-2014-0057.

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AbstractThis paper reviews the current corrosion fatigue strength issues of light metals, which include the corrosion fatigue cracking behaviors, such as the prior-corrosion pit deformation mechanism, the synergistic interaction between prior-corrosion pits and local stress/strain, the coupling damage behavior under mechanical fatigue loading, and the surrounding environmental factors such as a high humidity and a current 3.5 wt.% or 5.0 wt.% NaCl aqueous solution. The characterization of corrosion fatigue crack growth rate based on simple and measurable parameters (crack propagation length and applied stress amplitude or stress intensity factor) is also of great concern in engineering application. In addition, an empirical model to predict S-N curves of aluminum alloys at the environmental conditions was proposed in this paper. One of the main aims was to outline the corrosion fatigue cracking mechanism, which favors the corrosion fatigue residual life prediction of aluminum alloys subjected to the different environmental media that are often encountered in engineering services. Subsequently, this paper explores recently various surface modification technologies to enhance corrosion fatigue resistance and to improve fatigue strength. For example, the fatigue strength of 2024-T4 aluminum alloy has been modified using plasma electrolytic oxidation coating with the impregnation of epoxy resin modification method to compare with other oxide coating or uncoated substrate alloy.

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9

Chen, Xu, Rui Si Xing, and Xiao Peng Liu. "Multiaxial Fatigue of 6061-T6 Aluminum Alloy under Corrosive Environment." Applied Mechanics and Materials 853 (September 2016): 77–82. http://dx.doi.org/10.4028/www.scientific.net/amm.853.77.

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Aluminium alloys are widely used in the fields of automobile, machinery and naval construction. To investigate the effect of non-proportional loadings and corrosive environment on the fatigue resistance of 6061-T6 aluminum alloy, a set of uniaxial and multiaxial low cycle fatigue tests were carried out. Firstly, the results of uniaxial tests showed that the alloy exhibited cyclic hardening then cyclic softening. With the increase of stress amplitude the cyclic softening became pronounced. The increasing of plastic deformation was basically cyclically stable with small plastic strain amplitude accumulation when the stress amplitude was lower than 200MPa ,while it was increasing rapidly when the stress amplitude was higher than 220MPa. Secondly, it was observed that non-proportional cycle additional hardening of 6061-T6 aluminum alloy was little. While the fatigue life was badly affected by the loading paths. Thirdly ,the fatigue corrosion interactions were also talked about in details by performing the tests under the same loading conditions with corrosive environment. The experiment proved that the seawater corrosion has huge impact on fatigue life under pH 3. Finally, a multi-axial fatigue life prediction model was used to predict the fatigue life with or without the corrosive environment which showed a good agreement with experimental data.

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10

Yankin, Andrey, A. I. Mugatarov, and V. E. Wildemann. "Influence of different loading paths on the multiaxial fatigue behavior of 2024 aluminum alloy under the same amplitude values of the second invariant of the stress deviator tensor." Frattura ed Integrità Strutturale 15, no. 55 (December 28, 2020): 327–35. http://dx.doi.org/10.3221/igf-esis.55.25.

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2024 aluminum alloy is a common aeronautic material. During operations, construction elements made of aluminum alloys undertake complex cyclic loadings. Therefore, it is important to estimate the influence of these loadings on the durability of the material. Hereby, multiaxial fatigue tests with the same amplitude values of the second invariant of the stress deviator tensor are conducted, and test data are analyzed. The modified Sines method is utilized to predict fatigue experimental data. Results show that the model is accurate enough to fatigue behavior prediction of 2024 aluminum alloy.

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11

Gebhardt, Christian, Johannes Nellessen, Andreas Bührig-Polaczek, and Christoph Broeckmann. "Influence of Aluminum on Fatigue Strength of Solution-Strengthened Nodular Cast Iron." Metals 11, no. 2 (February 10, 2021): 311. http://dx.doi.org/10.3390/met11020311.

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The fatigue strength of high silicon-alloyed nodular cast iron is influenced by casting defects and graphite precipitates. The literature as well as the findings of this work show that these microstructural constituents can be tailored by controlling silicon microsegregation. In addition, segregations also affect the ferritic matrix microstructure locally. In the present work, silicon segregations in high silicon-alloyed ductile iron are specifically manipulated by small additions of aluminum. It was demonstrated how the aluminum content affects a wide range of microstructural constituents across a variety of length scales. Specimens from alloys with small additions of aluminum were fabricated and tested by rotating bending. Results show that the fatigue strength can be increased compared to a reference alloy with no aluminum. Microstructure analysis as well as fractography were performed concluding that microstructural changes could be attributed to the increased aluminum content, which allows the fatigue properties to be tailored deliberately. However, according to the results of this study, the negative effect of aluminum on castability and graphite morphology limits the maximum content to approximately 0.2 wt.%.

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12

Gangloff, Richard P., Robert S. Piascik, Dennis L. Dicus, and James C. Newman. "Fatigue crack propagation in aerospace aluminum alloys." Journal of Aircraft 31, no. 3 (May 1994): 720–29. http://dx.doi.org/10.2514/3.46553.

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13

JONO, Masahiro, and Atsushi SUGETA. "Fatigue crack growth resistance in aluminum alloys." Journal of Japan Institute of Light Metals 40, no. 7 (1990): 543–53. http://dx.doi.org/10.2464/jilm.40.543.

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14

USTILOVSKY, S. "Random fatigue crack growth in aluminum alloys." International Journal of Fatigue 21 (September 1999): 275–82. http://dx.doi.org/10.1016/s0142-1123(99)00098-5.

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15

Jahn, M. T., and H. C. Voris. "SEM study of humid air effect on fatigue of aluminum alloy 2024-T351." Proceedings, annual meeting, Electron Microscopy Society of America 47 (August 6, 1989): 298–99. http://dx.doi.org/10.1017/s0424820100153464.

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There is general agreement that the fatigue life of high strength aluminum alloys is reduced in humid environment. However, there are also data supporting the theory that humidity plays an insignificant role in the reduction of the fatigue life of aluminum alloy 2024-T351. In this study we examined the effects of stress level and water vapor density on the fatigue life of aluminum alloy 2024-T351 using scanning electron microscope (SEM). SEM evidence of the deleterious effect of humid air on the fatigue life of specimens cycled at intermediate stress level was presented. Discrepancies between this study and others were explained.Commercial aluminum alloy 2024-T35l (4.40Cu-1.45Mg-0.70Mn-0.23 Fe-0.15Si-0.13Zn) extruded bars were fatigue tested in reversed bending. The cycling was conducted in an environmentally controlled chamber. Ten specimens were machined for each fatigue stress level of 248, 276, 290, 317 and 359 MPa. Five specimens fran each stress level were cycled in desicated air at a relative humidity less than 45%.

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16

Krupp, Ulrich, Alexander Giertler, Stephanie Siegfanz, and Wilhelm Michels. "Mutual Interaction between Fatigue Crack Initiation/Propagation and Microstructural Features in Cast Aluminum Alloys." Advanced Materials Research 891-892 (March 2014): 488–93. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.488.

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The correlation between the microstructure, the mechanical properties and the fatigue life of the common aluminum cast alloy Al-7Si-0.3Mg (A356) was investigated. By variation the solution heat treatment temperatures and times the precipitation strengthening effect in the dendritic aluminum solid solution phase and the spheroidization of the eutectic silicon were modified. The results of fully reversed fatigues tests revealed an increase in the fatigue life of specimens that were heat treated at higher temperatures. This observation was supported by analyzing the fatigue crack propagation behavior using the direct current potential drop technique (DCPD). With (i) increasing heat treatment temperature, i.e., increasing dendritic α-Al strength and (ii) roundness of the eutectic silicon particles the resistance to technical fatigue crack initiation, expressed by the threshold value of the stress intensity range Kth, was shifted to higher values.

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17

Zhang, Yuan Bin, Hui Luo, and Tong Guang Zhai. "Pore Size Distribution and the Fatigue Properties of Several Cast Aluminum Alloys." Advanced Materials Research 139-141 (October 2010): 251–54. http://dx.doi.org/10.4028/www.scientific.net/amr.139-141.251.

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The population and size of porosities in three kinds of cast aluminum alloys, i.e. A713, A356T6-1 and A356T6-2, were statistically measured using a commercial software Spirit, and several distribution functions were tried to fit the cumulative pore size distribution data. It was found that a general extreme value (GEV) distribution function was the most appropriate function to quantify the cumulative pore size distribution in these cast aluminum alloys. The stress-number of cycles to failure (S-N) curves of these alloys were characterized by four point bend fatigue testing on MTS810 materials testing system, with the parameter f=20Hz, R=0.1, and in ambient air. The fatigue strength of A713, A356T6-1 and A356T6-2 aluminum alloy was measured to be 94.5 MPa, 150.6MPa and 117.3MPa respectively. The fatigue properties of these alloys could not be evaluated just by population and size distribution of the pores, the microstructure state, shape and position of pores, and other weakest links that may initiate a fatigue crack should be taken into account synthetically.

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18

Wang, Qing Yuan, Norio Kawagoishi, Nu Yan, and Q. Chen. "Super-Long Life Fatigue Behavior of Structural Aluminum Alloys." Key Engineering Materials 261-263 (April 2004): 1287–94. http://dx.doi.org/10.4028/www.scientific.net/kem.261-263.1287.

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The objective of this study is to determine very long life fatigue and near threshold fatigue crack growth behaviors of 7075/T6 and 6061/T6 Al-alloys using piezoelectric accelerated fatigue at 19.5KHz. The experimental results show the fatigue failure can occur beyond 107, even 109 cycles, and endurance limits could not be obtained in the Al-alloys until 109 cycles. Fatigue voids are noticed on fatigue fracture in both alloys. By using scanning electron microscopy (SEM), the crack initiation and propagation behaviors have been examined. Fatigue crack growth rates of small cracks in the Al-alloys are found to be greater than those of large cracks at the same stress intensity factor range.

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19

Oh, Kwang Keun, Yeon Wook Kim, and Jae Hoon Kim. "High Cycle Fatigue Characteristics of Aluminum Alloy by Shot Peening." Advanced Materials Research 1110 (June 2015): 142–47. http://dx.doi.org/10.4028/www.scientific.net/amr.1110.142.

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An aluminum alloy is used in airplanes and aerospace to reduce the weight of structures. Recently, researchers have studied how to intensify the strength of aluminum alloys. Shot peening is one of method to reinforce strength by hitting the surface of materials to make residual stress. In this study, high cycle fatigue characteristics of aluminum alloy Al 7075-T6 and Al 2024-T4 were analyzed. Fatigue characteristics of before and after the shot peened materials were tested by cantilever-rotary bending fatigue test machine (YRB 200, Yamamoto). Also, fractographic analysis was performed by a Scanning Electron Microscopy (SEM). The results showed that the fatigue life of both shot peened materials increased more than others.

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20

Tenkamp, Jochen, Mustafa Awd, Shafaqat Siddique, Peter Starke, and Frank Walther. "Fracture–Mechanical Assessment of the Effect of Defects on the Fatigue Lifetime and Limit in Cast and Additively Manufactured Aluminum–Silicon Alloys from HCF to VHCF Regime." Metals 10, no. 7 (July 14, 2020): 943. http://dx.doi.org/10.3390/met10070943.

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Aluminum–silicon alloys are commonly used in die-cast and additively manufactured (AM) light-weight components due to their good processability and high strength-to-weight ratio. As both processing routes lead to the formation of defects such as gas and shrinkage porosity, a defect-sensitive design of components is necessary for safe application. This study deals with the fatigue and crack propagation behavior of die-cast alloy AlSi7Mg0.3 and additively manufactured alloy AlSi12 and its relation to process-induced defects. The different porosities result in significant changes in the fatigue stress-lifetime (S–N) curves. Therefore, the local stress intensity factors of crack-initiating defects were determined in the high and very high cycle fatigue regime according to the fracture mechanics approach of Murakami. Through correlation with fatigue lifetime, the relationship of stress intensity factor (SIF) and fatigue lifetime (N) could be described by one power law (SIF–N curve) for all porosities. The relationship between fatigue limit and defect size was further investigated by Kitagawa–Takahashi (KT) diagrams. By using El Haddad’s intrinsic crack length, reliable differentiation between fracture and run out of the cast and AM aluminum alloys could be realized. SIF–N curves and KT diagrams enable a reliable fatigue design of cast and AM aluminum alloys for a finite and infinite lifetime.

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21

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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22

Li, Ning, Xiaojun Yan, Xuerong Liu, Lu Han, and Weifang Zhang. "Mechanical Properties Evolution of the 7B04-T74 Aluminum Alloy in the Marine Atmosphere." Metals 12, no. 12 (December 16, 2022): 2173. http://dx.doi.org/10.3390/met12122173.

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The 7xxx-series aluminum alloys are widely used in aircrafts due to their superior performance. The evolution of the mechanical properties of the aluminum alloys caused by marine atmospheric corrosion has become a research hotspot due to the increase in aircraft service time in the marine atmospheric environment. In this work, the evolution of the mechanical properties of the 7B04-T74 aluminum alloy was studied by an alternate immersion test. The surface microstructure was analyzed by SEM, EDS, XRD, and OM. The influence of the marine atmospheric corrosion on mechanical properties was studied by tensile and fatigue tests. The results show that the 7B04-T74 aluminum alloy has good corrosion resistance, as only pitting corrosion occurs in the marine atmospheric environment. The tensile properties of the 7B04-T74 aluminum alloy remained fundamentally the same before and after corrosion. The fatigue properties of the 7B04-T74 aluminum alloy were severely reduced, but the localized pitting corrosion only affected the initiation stage of the crack and had little effect on the crack propagation process.

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23

Ye, Xiong Lin, You Li Zhu, and Dong Hu Zhang. "Effects of Ultrasonic Deep Rolling on Fatigue Performance of Pre-Corroded 7A52 Aluminum Alloy." Advanced Materials Research 189-193 (February 2011): 897–900. http://dx.doi.org/10.4028/www.scientific.net/amr.189-193.897.

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The effects of ultrasonic deep rolling (UDR) on the fatigue behavior of pre-corroded 7A52 aluminum alloys were investigated. By means of X-Ray diffraction stress measurements and scanning electron microscopy (SEM), residual stress and fractograph of 7A52 aluminum alloys with and without UDR treatment were analyzed. The results indicated that the UDR produced compressive residual stresses with depth approaching 1mm. UDR treatment can extend the fatigue life of the pre-corroded 7A52 specimens to a large extent, depending on the level of corrosion and UDR parameter. For the slightly corrode specimens, the UDR treatment changed the fatigue crack nucleation site from surface to the transition zone between the compressive residual stresses and tensile stresses, resulted in a much longer fatigue life. For the severely corrode specimens, the crack still nucleated by intergranular cracking, however, due to the compressive residual stresses introduced and the closure of the corrosion pits and corrosion micro-crocks, UDR treatment still improved fatigue performance of the pre-corroded 7A52 aluminum alloy substantially.

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KURUMADA, Akira, Makoto SOUMA, Takahito WATAKABE, and Goroh ITOH. "OS18-1-4 Effect of Hydrogen on the Fatigue Crack Propagation in Aluminum Alloys." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2011.10 (2011): _OS18–1–4—. http://dx.doi.org/10.1299/jsmeatem.2011.10._os18-1-4-.

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25

Alexopoulos, Nikolaos D., Evangelos Migklis, and Dimitrios Myriounis. "Experimental analysis of constant-amplitude fatigue properties in 6156 (Al-Mg-Si) sheet aluminum alloy." Journal of Strain Analysis for Engineering Design 53, no. 8 (May 21, 2018): 676–86. http://dx.doi.org/10.1177/0309324718775565.

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Fatigue mechanical behavior of wrought aluminum alloy (Al-Mg-Si) 6156 at T4 temper is experimentally investigated. Constant-amplitude fatigue tests, at fixed stress ratio R = 0.1, were carried out, and the respective stress–life diagram was constructed and compared against the competitive 6xxx aluminum alloys, for example, 6082 and 6061. Fatigue endurance limit of AA6156 was found to be approximately 155 ± 5 MPa, that is, almost 30% below yield stress Rp of the material. AA6156 presents almost 50% higher fatigue life in the high-cycle fatigue area and approximately 20% higher fatigue endurance limit, when compared with other 6xxx series aluminum alloys. Significant work hardening was induced due to fatigue and was experimentally validated by the measurements of residual stiffness of fatigue loops as well as of absorbed energy per fatigue loop. Work-hardening exponent was essentially decreased by almost 25% from the first fatigue cycles and up to 10% of fatigue life. Fracture surfaces of specimens loaded at applied stresses close to fatigue endurance limit exhibited signs of coarse voids due to the formed precipitates at the matrix. The fracture mechanism was a mixture of transgranunal and intergranular fracture for the fatigue specimens tested at higher applied fatigue loadings.

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Zakharchenko, Kirill, Vladimir Kapustin, Alexey Larichkin, and Yaroslav Lukyanov. "Influence of Technology of Hot Forming of Plates from Aluminum Alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu on Resistance to Fatigue Fracture." Metal Working and Material Science 22, no. 4 (December 8, 2020): 94–109. http://dx.doi.org/10.17212/1994-6309-2020-22.4-94-109.

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Introduction. One of the primary objectives in the development of promising aircraft products is to reduce the weight of the aircraft structure. This problem can be solved by applying new low density materials such as aluminum alloys alloyed with lithium (for example, Al-Cu-Li-Zn) in the design of parts. The use of these materials in aircraft construction is limited by the processing technology, which must be such as not to damage the material and not reduce its strength properties. Such technologies include processing by pressure with heating, when creep processes are activated and the material passes into a state close to superplasticity. The purpose of the work: assessment of the effect of pressure shaping of aluminum alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu in creep mode on strength. The paper investigates the influence of the technology of pressure shaping of aluminum alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu on the resistance to fatigue failure. The work uses a method that allows to determine the ultimate stresses using diagrams of the accumulation of irreversible deformations; method of forming thick plates (40 mm) in the creep mode. The previously selected optimum temperatures for forming the plates are used. A non-contact coordinate measuring system is used to perform surface inspection after shaping. Fractography of the fracture of samples of alloy Al-Cu-Li-Zn and Al-Zn-Mg-Cu after fatigue failure is performed. Mathematical modeling of the deformation process of plates in creep mode is carried out in the MSC.Marc package. As a result, a conservative evaluation of the endurance limit for aluminum alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu is obtained. The shaping of thick plates in the creep mode is carried out. More than 80% of the board surface is formed with a deviation of less than 1 mm from the target size. Fatigue tests of samples made of molded panels of alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu are carried out, fatigue curves are plotted. The fractography of the surface of the fatigue fracture showed the presence of oxides in the samples of alloy Al-Cu-Li-Zn, in contrast to alloy Al-Zn-Mg-Cu. The results of fatigue tests are discussed, showing that the characteristics of the technological process of shaping and heat treatment do not deteriorate the fatigue properties of the investigated alloys. Comparative tests show that alloy Al-Cu-Li-Zn has higher fatigue characteristics. Mathematical modeling show that the use of the Boyle-Norton steady-state creep law is not enough to describe the process of plate forming. The necessity of setting the inverse problem of creep age forming is noted, where the coordinates of the punches of the loading device should act as boundary conditions.

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27

Mohin, M. A., H. Toofanny, A. Babutskyi, A. Lewis, and Y. G. Xu. "Effect of Electromagnetic Treatment on Fatigue Resistance of 2011 Aluminum Alloy." Journal of Multiscale Modelling 07, no. 03 (August 14, 2016): 1650004. http://dx.doi.org/10.1142/s1756973716500049.

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Beneficial effects of the electromagnetic treatment on fatigue resistance were reported on several engineering alloys. These could be linked to the dislocation activity and the rearrangement of the crystal structure of the material under the electromagnetic field (EMF), resulting in delayed crack initiation. This paper presents an experimental study on the effect of pulsed electromagnetic treatment on the fatigue resistance of 2011 aluminum alloy. Circular cantilever specimens with loads at their ends were tested on rotating fatigue machine SM1090. Fatigue lives of treated and untreated specimens were analyzed and compared systematically. It has been found that the effect of the pulsed electromagnetic treatment on the fatigue resistance is dependent on the intensity of the pulsed EMF and the number of the treatment applied. Clear beneficial effect of the pulsed electromagnetic treatment on the fatigue resistance of the aluminum alloys has been observed, demonstrating a potential new technique to industries for fatigue life extension.

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OCHI, YASUO, KIYOTAKA MASAKI, TAKASHI MATSUMURA, YOHEI KUMAGAI, TATSUHIKO HAMAGUCHI, and YUJI SANO. "FATIGUE STRENGTH IMPROVEMENT BY PEENING TREATMENT IN DEGASSING PROCESSED CAST ALUMINUM ALLOYS." International Journal of Modern Physics B 20, no. 25n27 (October 30, 2006): 3593–98. http://dx.doi.org/10.1142/s0217979206040040.

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Rotating bending fatigue tests were carried out in order to investigate effects of shot peening and laser peening treatment on fatigue properties of degassing processed cast aluminum alloys. Degassing was useful for decreasing cast defects and increasing the range of fatigue life and fatigue strength at 107 cycles compared with those of non-degassed cast alloys. The shot peening and the laser peening treatments also showed remarkable effects for increasing the resistance of crack propagation behaviors and improving the fatigue strength of the degassing processed cast aluminum alloys.

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29

Lee, Jungsub, Sang-Youn Park, and Byoung-Ho Choi. "Evaluation of Fatigue Characteristics of Aluminum Alloys and Mechanical Components Using Extreme Value Statistics and C-Specimens." Metals 11, no. 12 (November 27, 2021): 1915. http://dx.doi.org/10.3390/met11121915.

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In this study, the fatigue characteristics of aluminum alloys and mechanical components were investigated. To evaluate the effect of forging, fatigue specimens with the same chemical compositions were prepared from billets and forged mechanical components. To evaluate the cleanliness of the aluminum alloys, the cross-sectional area of specimens was observed, and the maximum inclusion sizes were obtained using extreme value statistics. Rotary bending fatigue tests were performed, and the fracture surfaces of the specimens were analyzed. The results show that the forging process not only elevated the fatigue strength but also reduced the scatter of the fatigue life of aluminum alloys. The fatigue characteristics of C-specimens were obtained to develop finite-element method (FEM) models. With the intrinsic fatigue properties and strain–life approach, the FEM analysis results agreed well with the test results.

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30

Alexopoulos, Nikolaos D., Vangelis Migklis, Stavros K. Kourkoulis, and Zaira Marioli-Riga. "Fatigue Behavior of Aerospace Al-Cu, Al-Li and Al-Mg-Si Sheet Alloys." Advanced Materials Research 1099 (April 2015): 1–8. http://dx.doi.org/10.4028/www.scientific.net/amr.1099.1.

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In the present work, an experimental study was performed to characterize and analyze the tensile and constant amplitude fatigue mechanical behavior of several aluminum alloys, namely 2024 (Al-Cu), 2198 (Al-Li) and 6156 (Al-Mg-Si). Al-Li alloy was found to be superior of 2024 in the high cycle fatigue and fatigue endurance limit regimes, especially when considering specific mechanical properties. Alloy 6156 was found to have superior constant amplitude fatigue performance that the respective 6xxx series alloys; more than 15% higher endurance limit was noticed against 6061 and almost 30% higher than 6082. Alloy 6156 presented only a marginal increase in fatigue life for the HCF regime.

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31

Zhang, Xiao Min, Jian Mao, Yun Che, and Zhong Ke Zhang. "Investigations on the Fatigue Property of the High-Strength and Toughness 211Z Casting Aluminium Alloy." Applied Mechanics and Materials 423-426 (September 2013): 197–201. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.197.

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211Z is a new type of high strength and toughness Al-Cu-Mn casting aluminum alloy. With the aid of GPS-100 high-cycle fatigue testing machine and DDL100 multifunction tensile testing machine, conventional mechanics performance tests and high-cycle fatigue tests were carried out in this paper. The conventional mechanical property results show that the tensile strength is 477.5 MPa, the theory yield strength is 397.5 MPa and the elongation is 6.625%. Fatigue experiments were performed with load control at room temperature and R =-1 in ambient air. The tensile and compression fatigue strength is 130 MPa under ten million times fatigue test, and S-N fatigue life curve of this alloy was also given in the investigations. 211Z casting aluminum alloy possessing high fatigue strength can be attributed to the fact that it owns high strength and good plasticity simultaneously. The microstructure analysis of fatigue fracture appearance shows that, the fatigue crack initiation behavior of this aluminium alloys depends mainly on the region possessing defects under the surface, there has only one crack source, which means it is belongs to low nominal stress unidirectional bending. In the crack growth stage, the width of fatigue striations decreases with the increase of stress, and a few secondary cracks were found in this stage. When cracks finally losed stability, an instantaneous fracture occured in the investigated samples. Shear lips and dimples were found in the fracture appearance and the final fracture is belongs to ductile fracture.

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32

Elboujdaini, Mimoun, and Edward Ghali. "Corrosion Fatigue of Aluminum Alloys in Chloride Media." Materials Science Forum 44-45 (January 1991): 153–68. http://dx.doi.org/10.4028/www.scientific.net/msf.44-45.153.

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33

Choi, Sung-Jong, Hak-Sun Lee, Cheol-Jae Lee, and Sang-Tae Kim. "Fretting Fatigue Behavior of High Strength Aluminum Alloys." Transactions of the Korean Society of Mechanical Engineers A 31, no. 2 (February 1, 2007): 197–204. http://dx.doi.org/10.3795/ksme-a.2007.31.2.197.

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34

Wang, Qigui, Guoqiu He, and Yucong Wang. "Fatigue Behavior of Aluminum Alloys under Multiaxial Loading." SAE International Journal of Materials and Manufacturing 7, no. 2 (April 1, 2014): 465–72. http://dx.doi.org/10.4271/2014-01-0972.

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35

Bian, J. C., K. Tokaji, and T. Ogawa. "NOTCH SENSITIVITY OF ALUMINUM-LITHIUM ALLOYS IN FATIGUE." Fatigue & Fracture of Engineering Materials and Structures 18, no. 1 (January 1995): 119–27. http://dx.doi.org/10.1111/j.1460-2695.1995.tb00146.x.

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36

Wang, Q. Y., T. Lib, and X. G. Zenga. "Gigacycle fatigue behavior of high strength aluminum alloys." Procedia Engineering 2, no. 1 (April 2010): 65–70. http://dx.doi.org/10.1016/j.proeng.2010.03.007.

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37

Lee, E. U., and R. E. Taylor. "Fatigue behavior of aluminum alloys under biaxial loading." Engineering Fracture Mechanics 78, no. 8 (May 2011): 1555–64. http://dx.doi.org/10.1016/j.engfracmech.2010.11.005.

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38

Bull, C., and R. Hermann. "Fatigue crack growth and closure in aluminum alloys." Scripta Metallurgica et Materialia 30, no. 10 (May 1994): 1337–42. http://dx.doi.org/10.1016/0956-716x(94)90269-0.

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39

Davidson, David L. "Small and large fatigue cracks in aluminum alloys." Acta Metallurgica 36, no. 8 (August 1988): 2275–82. http://dx.doi.org/10.1016/0001-6160(88)90327-6.

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40

Scala, A., A. Squillace, T. Monetta, D. B. Mitton, D. Larson, and F. Bellucci. "Corrosion fatigue on 2024T3 and 6056T4 aluminum alloys." Surface and Interface Analysis 42, no. 4 (January 25, 2010): 194–98. http://dx.doi.org/10.1002/sia.3190.

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41

DuQuesnay, D. L., and P. R. Underhill. "Fatigue life scatter in 7xxx series aluminum alloys." International Journal of Fatigue 32, no. 2 (February 2010): 398–402. http://dx.doi.org/10.1016/j.ijfatigue.2009.07.016.

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42

Barletta, M., F. Lambiase, and Vincenzo Tagliaferri. "Improvement of Fatigue Behaviour of High Strength Aluminium Alloys by Fluidized Bed Peening (FBP)." Key Engineering Materials 344 (July 2007): 87–96. http://dx.doi.org/10.4028/www.scientific.net/kem.344.87.

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This paper deals with a definition of a relatively novel technique to improve the fatigue behavior of high strength aluminum alloys, namely, Fluidized Bed Peening (FBP). Fatigue samples made from AA 6082 T6 alloy were chosen according to ASTM regulation about rotating bending fatigue test and, subsequently, treated by varying FBP operational parameters and fatigue testing conditions. First, a full factorial experimental plan was performed to assess the trend of number of cycles to rupture of fatigue samples varying among several experimental levels the factors peening time and maximum amplitude of alternating stress applied to fatigue samples during rotating bending fatigue tests. Second, design of experiment (DOE) technique was used to analyze the influence of FBP operational parameters on fatigue life of AA 6082 T6 alloy. Finally, ruptures of FB treated samples and untreated samples were discussed in order to evaluate the influence of operational parameters on the effectiveness of FBP process and to understand the leading process mechanisms. At any rate, the fatigue behavior of processed components was found to be significantly improved, thereby proving the suitability of FBP process as alternative mechanical technique to enhance fatigue life of components made from high strength aluminum alloy.

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43

Bernstein, H., and C. Loeby. "Low-Cycle Corrosion Fatigue of Three Engineering Alloys in Salt Water." Journal of Engineering Materials and Technology 110, no. 3 (July 1, 1988): 234–39. http://dx.doi.org/10.1115/1.3226042.

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Low-cycle fatigue tests were conducted under strain control in salt water on 2024 aluminum, 304 stainless steel, and 1045 steel. All three materials showed a significant reduction in life due to corrosion fatigue in the low-cycle fatigue regime. The corrosion fatigue life of the aluminum and steel was time dependent, with significantly shorter lives at lower frequencies or at longer strain hold times. The corrosion fatigue life of the stainless steel was not time dependent for the conditions studied. Elastic and plastic strain-range versus life equations were modified by a frequency term to predict the corrosion fatigue life. This model correlated the fatigue data to within a factor of 1.28. A modification of this model correlated some corrosion fatigue data in the literature to within a factor of 1.19.

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Arcieri, Emanuele Vincenzo, Sergio Baragetti, and Emanuele Borzini. "Bending Fatigue Behavior of 7075-Aluminum Alloy." Key Engineering Materials 774 (August 2018): 1–6. http://dx.doi.org/10.4028/www.scientific.net/kem.774.1.

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Light alloys are a very interesting challenge in order to have light components with high mechanical features. One of these is the 7075 aluminum alloy, which is commonly employed in aeronautic, automotive and maritime fields.On the other hand, the application of a PVD (Physical Vapor Deposition) coating can improve the hardness of the surface and the tribological properties of the component.The effectiveness of these coatings on the fatigue behavior of the sublayer material is not already clear. For this reason, bending tests on uncoated and coated specimens in air were performed in order to evaluate the S-N diagrams

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45

Malopheyev, Sergey, Igor Vysotskiy, Daria Zhemchuzhnikova, Sergey Mironov, and Rustam Kaibyshev. "On the Fatigue Performance of Friction-Stir Welded Aluminum Alloys." Materials 13, no. 19 (September 23, 2020): 4246. http://dx.doi.org/10.3390/ma13194246.

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This work was undertaken in an attempt to ascertain the generic characteristics of fatigue behavior of friction-stir welded aluminum alloys. To this end, different alloy grades belonging to both the heat-treatable and non-heat-treatable types in both the cast and wrought conditions were studied. The analysis was based on the premise that the fatigue endurance of sound welds (in which internal flaws and surface quality are not the major issues) is governed by residual stress and microstructure. Considering the relatively low magnitude of the residual stresses but drastic grain refinement attributable to friction-stir welding, the fatigue performance at relatively low cyclic stress was deduced to be dictated by the microstructural factor. Accordingly, the fatigue crack typically nucleated in relatively coarse-grained base material zone; thus, the fatigue strength of the welded joints was comparable to that of the parent metal. At relatively high fatigue stress, the summary (i.e., the cyclic-plus residual-) stress may exceed the material yield strength; thus, the fatigue cracking should result from the preceding macro-scale plastic deformation. Accordingly, the fatigue failure should occur in the softest microstructural region; thus; the fatigue strength of the welded joint may be inferior to that of the original material.

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46

Kapp, J. A., D. Duquette, and M. H. Kamdar. "Crack Growth Behavior of Aluminum Alloys Tested in Liquid Mercury." Journal of Engineering Materials and Technology 108, no. 1 (January 1, 1986): 37–43. http://dx.doi.org/10.1115/1.3225839.

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Crack growth rate measurements have been made in three mercury embrittled aluminum alloys each under three loading conditions. The alloys were 1100-0, 6061-T651, and 7075-T651. The loading conditions were fixed displacement static loading, fixed load static loading, and fatigue loading at two frequencies. The results showed that mercury cracking of aluminum was not unlike other types of embrittlement (i.e. hydrogen cracking of steels). Under fixed load static conditions no crack growth was observed below a threshold stress intensity factor (KILME). At K levels greater than KILME cracks grew on the order of cm/s, while under fixed displacement loading, the crack growth rate was strongly dependent upon the strength of the alloy tested. This was attributed to crack closure. In the fatigue tests, no enhanced crack growth occurred until a critical range of stress intensity factor (ΔKth) was achieved. The ΔKth agreed well with the KILME obtained from the static tests, but the magnitude of the fatigue growth rate was substantially less than was expected based on the static loading results. Observations of the fracture surfaces in the SEM suggested a brittle intergranular fracture mode for the 6061-T651 and the 7075-T651 alloys under all loading conditions. The fractographic features of the 1100-0 alloy under fixed load and fatigue loading conditions were also brittle intergranular. Under fixed displacement loading the cracks grew via a ductile intergranular mode.

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47

Mahdi, Huda Salih, Hussain J. Alalkawi, Muzher T. Mohamed, and Saad T. Faris. "Evaluation of creep-fatigue life and strength for AA7001-T6 under constant amplitude loading." Eastern-European Journal of Enterprise Technologies 4, no. 12 (118) (August 27, 2022): 22–28. http://dx.doi.org/10.15587/1729-4061.2022.263344.

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Aluminum alloys were widely used in the construction, automotive, marine, and aviation industries due to their low specific strength, ease of manufacture, and low weight. The fatigue behavior of aluminum alloys at different temperatures is investigated. Thanks to the rapid development of armament in recent years, 7XXX ultra-high strength aluminum alloys are now used more frequently because of their non-corrosive qualities and low weight. Aluminum alloy 7001-T6 behavior is examined at the Company State for Engineering, Rehabilitation, and Inspection (SIER) in Iraq, where chemical analysis of the AA7001 is supported. Most engineering components that operate at high temperatures will eventually fail from fatigue strain, creep damage is a time-dependent process that is primarily influenced by the history of stress and temperature applied to the component. When the two damaging factors combine their effects, This study used AA7001-T6 to conduct experiments on mechanical characteristics (UTS, YS, E, and ductility) and the interaction between creep and fatigue at four distinct temperatures: room temperature (25, 150, 280, and 330) °C, the UTS, YS, and E were lowered by 37.2, 37.2, and 24) %, respectively, as compared to the result at room temperature, but the ductility increased by 28.27 %. It has been noted that rising temperatures cause mechanical and fatigue characteristics to decline. Experimental S-N fatigue test findings showed a significant loss of fatigue strength, After 107cycles, the endurance fatigue limit was reduced from 208 MPa at (RT) to 184 MPa at 330 °C, an 11.5 % reduction. Overall, it can be said that AA7001-T6 demonstrates a significant drop in mechanical and fatigue properties at high temperatures

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48

Yamada, Ryuichi, Goroh Itoh, Akira Kurumada, and Manabu Nakai. "Further Study on the Effect of Environment on Fatigue Crack Growth Behavior of 2000 and 7000 Series Aluminum Alloys." Materials Science Forum 879 (November 2016): 2153–57. http://dx.doi.org/10.4028/www.scientific.net/msf.879.2153.

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The 7000 series alloys have the highest strength in the aluminum alloys, but lower fatigue properties than 2000 series alloys. Thus, 7000 series alloys are not applied to a large proportion of the aircraft components. However, the mechanism for this has not been elucidated yet. In humid air, hydrogen embrittlement based on intergranular cracking has been known to occur in 7000 series alloys. To date, in order to explain the difference in the fatigue crack growth behavior in the two series alloys, the effect of the test environment on the fatigue crack growth of the two series alloys has been investigated in this study. A 7075-type as well as 2024-type alloy with relatively coarse equi-axed grains was T6-tempered and subjected to fatigue crack growth test in humid and dry environments. Crack growth rate at low ΔK level seemed to be larger in the 7075-type alloy than the 2024-type alloy in the humid air, when assessed by means of gradually decreasing K method. In order to clarify this result, crack growth rate of the two alloys was assessed by means of gradually increasing K method as well as decreasing K method. Crack growth rate of the 7075-type alloy in moist air was concluded to be the largest in consistent with the previous study. Thus, the large fatigue crack growth rate of the 7075-type alloy is attributable to hydrogen embrittlement.

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49

Knysh, V. V., I. N. Klochkov, M. P. Pashulya, and S. I. Motrunich. "Increase of fatigue resistance of sheet welded joints of aluminum alloys using high-frequency peening." Paton Welding Journal 2014, no. 5 (May 28, 2014): 21–27. http://dx.doi.org/10.15407/tpwj2014.05.04.

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50

Kotyk, Maciej, and Dariusz Boroński. "Investigation of Material Properties of Layered Al-Ti Material with the Use of Microspecimens." Solid State Phenomena 224 (November 2014): 216–21. http://dx.doi.org/10.4028/www.scientific.net/ssp.224.216.

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The article presents a monotonic tensile test of two materials: aluminum alloy AA2519 and titanium alloy Ti6A14V joined by means of explosive welding. The specimens were cut out in such a way that some consisted of only titanium alloy some were made of only aluminum alloy, whereas the third series were specimens consisting of both material alloys together with the bonding layer. The main goal of the research was to compare changes in the materials fatigue properties caused by explosion welding of these two alloys.

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