Stress Corrosion Cracking 2011
DOI: 10.1533/9780857093769.3.307
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Stress corrosion cracking (SCC) of aluminium alloys

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Cited by 20 publications
(8 citation statements)
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“…On the other hand, the SCC performance of 7xxx series aluminum alloy plates can be improved by microalloying techniques. For instance, Bobby Kannan [6] and our previous work [20] showed that the SCC resistance of Al-Zn-Mg-Cu-Zr or Al-Zn-Mg alloys can be improved by adding 0.25 wt.% scandium, even in the peak aged state. Wang [21] indicated that Al-Zn-Mg-Cu-Zr alloys with Cr and Pr exhibited higher resistance to SCC than those without Pr-or Zr-containing dispersoids.…”
Section: Instructionmentioning
confidence: 99%
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“…On the other hand, the SCC performance of 7xxx series aluminum alloy plates can be improved by microalloying techniques. For instance, Bobby Kannan [6] and our previous work [20] showed that the SCC resistance of Al-Zn-Mg-Cu-Zr or Al-Zn-Mg alloys can be improved by adding 0.25 wt.% scandium, even in the peak aged state. Wang [21] indicated that Al-Zn-Mg-Cu-Zr alloys with Cr and Pr exhibited higher resistance to SCC than those without Pr-or Zr-containing dispersoids.…”
Section: Instructionmentioning
confidence: 99%
“…Al-Zn-Mg alloys, due to their high-strength-weight, are applied widely in aerospace structural components and for highly stressed parts in automobiles and high-speed trains for fuel saving [1][2][3]. When airplanes or trains are in service in humid environments such as those present in marine, industry or rural atmospheres, 7xxx series aluminum alloys used as air-frame structures and car body members are exposed to mechanical loading, and thus, suffer from stress corrosion cracking (SCC) [2,[4][5][6]. Adding high contents of alloying elements, such as Zn and Mg, is the main method to strengthen heat-treatable, ageing-hardenable aluminum alloys [7,8].…”
Section: Instructionmentioning
confidence: 99%
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“…Bobby et al [37][38][39][40][41][42][43] carried out an extensive work on understanding the electrochemical and EAC behavior of 7010 Al alloy by heat treatment procedures and alloying. However, EAC in Al alloys has been a serious concern for aircraft industries for decades.…”
Section: Aluminium Alloysmentioning
confidence: 99%
“…The multi-step aging treatment is advantageous over RRA treatment in that the former can be applied to even thick plates, while the latter is restricted to thin sheets because of the short retrogression treatment at elevated temperature. Bobby et al [39] further showed that a higher ductility of peak aged and over aged alloys could be achieved through multi-step aging than that was reported by Puiggali et al through conventional aging [53], Table 1 SSRT data of 7010 Al-alloys in peak aged and over aged conditions tested in air and 3.5% NaCl solution at 10' 6 /s strain rate [37] Temper % Elongation to Detailed microstructure and fractured surface analysis of heat treated 7010 Al alloy were carried out by Bobby et al [37,39,40,42] to correlate the microstructure to the failure mechanism(s). In air, the peak aged alloy exhibited 10% C f (elongation to fracture) and 10%RA and 561 MPa UTS.…”
Section: Role Of Heat Treatmentmentioning
confidence: 99%