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2014-T6

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Published: 01 January 1996
Fig. 19 Comparison of fatigue strength bands for 2014-T6, 2024-T4, and 7075-T6 aluminum alloys for rotating-beam tests. Source: R. Templin, F. Howell, and E. Hartmann, “Effect of Grain-Direction on Fatigue Properties of Aluminum Alloys,” Alcoa, 1950 More
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Published: 15 June 2019
Fig. 1 Comparison of fatigue strength bands for 2014-T6, 2024-T4, and 7075-T6 aluminum alloys for rotating-beam tests. Source: Ref 3 More
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Published: 01 January 2002
Fig. 37 Aluminum alloy 2014-T6 hinge bracket that failed by SCC in service. (a) Hinge bracket. Actual size. Arrow indicates crack. (b) Micrograph showing secondary cracking adjacent and parallel to the fracture surface. Etched with Keller's reagent. 250× More
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Published: 01 January 2002
Fig. 38 Forged aluminum alloy 2014-T6 actuator barrel lug that failed by SCC. (a) View of the lug. 2×. Fracture at top was the initial fracture; arrow indicates location of a tiny region of pitting corrosion (on back side of lug) at which failure originated. Final fracture is at left. (b More
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Published: 01 January 1987
Fig. 14 Forged aluminum alloy 2014-T6 aircraft component that failed by fatigue. Characteristic beach marks are evident. See also Fig. 15 . More
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Published: 01 January 1987
Fig. 974 Top surface of an extruded aluminum alloy 2014-T6 bottom cap of an aircraft wing spar, showing a fatigue fracture (center) that intersected one of the rivet holes indicated by the arrows. Hardness tests near the fracture gave an average value of 85 HRB, which is acceptable. See also More
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Published: 01 January 1987
Fig. 980 Fatigue fracture of an aluminum alloy 2014-T6 heat-treated forging. Details of the heat-treatment procedure were not available. Some machining was carried out on the forging prior to heat treatment. The aircraft structural component cracked in service. The horizontal lines More
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Published: 01 December 2004
Fig. 43 Examples of eutectic melting microstructures (a) Alloy 2014-T6 closed-die forging, showing rosettes formed by eutectic melting when the solidus temperature (510 °C, or 950 °F) was exceeded during solution heat treating. Other constituents are particles of CuAl 2 (white, outlined More
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Published: 01 January 1996
Fig. 20 Comparison of fatigue strength bands for 2014-T6 aluminum alloy products, showing effects of direction. Source: ASTM Proceedings, Vol 64, p 581–593 More
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Published: 15 June 2019
Fig. 18 Effect of temperature on tensile strength of 2014-T6 More
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Published: 15 June 2019
Fig. 22 Room-temperature tensile strength of alloy 2014-T6 after exposure at elevated temperature More
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Published: 15 June 2019
Fig. 6 Comparison of fatigue strength bands for 2014-T6 aluminum alloy products, showing effects of direction. Source: Ref 9 More
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Published: 15 January 2021
Fig. 48 (a) Photograph of an aluminum alloy 2014-T6 hinge bracket. Arrow indicates crack location. (b) Micrograph of a cross section prepared through the fracture surface. Arrows indicate stress-corrosion cracking. Original magnification: 250× More
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Published: 15 January 2021
Fig. 49 (a) Photograph of forged aluminum alloy 2014-T6 actuator barrel lug that fractured due to stress-corrosion cracking. Arrow indicates location of a region of pitting corrosion on back side of lug at which the fracture originated. Final fracture occurred at bottom left. (b) Micrograph More
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Published: 15 June 2019
Fig. 5 Variation in rotating-beam fatigue for (a) 2024-T4, (b) 7075-T6, (c) 2014-T6, and (d) 7079-T6 alloys. Notches (60°) were very sharp ( K t > 12) with a radius of approximately 0.005 mm (0.0002 in.). Results are from over a thousand rotating-beam tests performed in the 1940s. Source More
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Published: 01 January 1996
Fig. 18 Variation in rotating-beam fatigue for (a) 2024-T4, (b) 7075-T6, (c) 2014-T6, and (d) 7079-T6 alloys. Notches (60°) were very sharp ( K t > 12) with a radius of about 0.0002 in. Results are from over a thousand rotating-beam tests performed in the 1940s. Sources: R. Templin, F More
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Published: 01 January 2000
Fig. 5 Stress-strain curves in tension at elevated temperature of wrought and composite 2014 aluminum alloy. (a) Wrought 2014-T6, 19.05 mm ( 3 4 in.) bar. (b) Discontinuously reinforced 2014 composite (15 vol% Al 2 O 3 , 0.5 h after T6). Source: Ref 4 , 5 More
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006596
EISBN: 978-1-62708-210-5
... and good fatigue resistance of alloy 2014-T6 led to its selection for extruded drill pipe used in the oil and gas industry. Mill product specifications are summarized in Table 2 with recommended cold workability in Tables 3 and 4 . Available product tempers include: Product Tempers...
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Published: 15 June 2019
Fig. 1 High-temperature yield strength (after different exposure times at temperature) of alloys 2040-T6 and 2014-T6 More
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Published: 01 June 2016
Fig. 13 Effects of solution heat treating temperatures on the tensile properties of 2014-T4 and 2014-T6 sheet More