2014
DOI: 10.1016/j.msea.2014.03.024
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Strengthening mechanisms of T1 precipitates and their influence on the plasticity of an Al–Cu–Li alloy

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Cited by 153 publications
(44 citation statements)
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References 33 publications
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“…Confocal laser scanning microscopy (CLSM): (272). (217, 227, 229 -231, 233, 238, 239, 241, 243, 245, 247, 250, 252 -254, 256, 265, 269, 273, 283, 287, 290 -292, 300, 301, 303, 305, 311 -321, 324, 326, 327, 329, 331 -336, 339, 340, 342, 344, 345, 354, 363 -365, 371, 380, 385, 391, 393, 394, 396, 399 -401).…”
Section: Positron Annihilation Lifetime Spectroscopy (Pals) / Coincidmentioning
confidence: 99%
“…Confocal laser scanning microscopy (CLSM): (272). (217, 227, 229 -231, 233, 238, 239, 241, 243, 245, 247, 250, 252 -254, 256, 265, 269, 273, 283, 287, 290 -292, 300, 301, 303, 305, 311 -321, 324, 326, 327, 329, 331 -336, 339, 340, 342, 344, 345, 354, 363 -365, 371, 380, 385, 391, 393, 394, 396, 399 -401).…”
Section: Positron Annihilation Lifetime Spectroscopy (Pals) / Coincidmentioning
confidence: 99%
“…T 1 phase is an equilibrium phase, which shows hexagonal Àake or needle shape, about 100 nm in length, 1 nm in thickness, belonging to hexagonal (a=0.497 nm, c=0.934 nm). The T 1 is a hexagonal crystal structure with (0001) T 1 //{111} Al and (0101) T 1 //<110>Al [20].…”
Section: Methodsmentioning
confidence: 99%
“…It is reported that geometrically necessary dislocations which are stored to accommodate the strain gradient between the deforming matrix and the non-deforming particle, drive the plastic relaxation [26]. On the other hand, the initial work hardening rates such as those found in the NA temper, have been attributed to increased strength of the dislocation junctions owing to high solute contents [10].…”
Section: Methodsmentioning
confidence: 99%
“…Recent studies of Al-Cu-Li-Mg-based alloy systems have focussed on AA2198 [9][10][11][12] which has shown an outstanding combination of static strength and damage tolerance along with good weldability and is therefore envisaged as a replacement for the AA2024/AA7475 alloys presently used in fuselage skin applications in commercial aircrafts [13,14]. Although the peak aged (PA) temper of this alloy is of application interest, detailed investigation of the structure-property relationships of other temper states is required since it provides the basis for understanding the influence of process-induced microstructural changes on the post-processing properties of the alloy.…”
Section: Introductionmentioning
confidence: 99%