The Effect of Temperature and Microstructure on the Fatigue Crack Growth Behavior of AL-Cu Alloy C415 PDF Download
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Author: Christopher L. Muhlstein
Publisher:
ISBN:
Category : Fracture mechanics
Languages : en
Pages : 228
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Author: Christopher L. Muhlstein
Publisher:
ISBN:
Category : Fracture mechanics
Languages : en
Pages : 228
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Author: Rodney L. Wilkinson
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 68
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Changes in the crack growth behavior of 7075-T651 aluminum specimens which has been exposed to temperatures between 150 degrees and 355 degrees F (66 deg and 179 deg C) were evaluated. Specimens were fatigue tested at room temperature under flight-by-flight loading conditions. Results from these tests were then compared with data from the baseline (as received) material. Exposure to 250 deg F (121 deg C) or more produced a definite increase in speciment life, apparently due to a decrease in crack growth rates.
Author: Robert S. Piascik
Publisher: ASTM International
ISBN: 0803124139
Category : Aluminum alloys
Languages : en
Pages : 231
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Author: Ashok Saxena
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 115
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This investigation was undertaken to clarify the role of microstructure on steady state (constant load amplitude) and transient (single periodic overload) fatigue crack growth behavior in 7XXX aluminum alloys at low stress intensity factor ranges (delta K). These results were consolidated with data in the literature to obtain an understanding of microstructural effects on crack growth response over a broad delta K range. Constant load amplitude data show that there are significant differences in near-threshold FCG resistance among 7XXX alloys. Overaging to a T7 temper reduces low delta K FCG resistance greatly, whereas intermediate and high delta K FCG resistance is increased by overaging. In the presence of moisture at intermediate delta K levels, increasing Cu content from 1.0 to 2.3% increases crack growth resistance. However, there is no consistent effect of Cu content on near-threshold fatigue performance. Similarly, no clear influence of dispersoid type (Cr vs. Zr) on low delta K FCG resistance was detected. Increasing alloy purity (lowering Fe, Si content) enhances crack growth resistance at high delta K, but has no effect at near-threshold stress intensities. The importance of near-threshold FCG performance to alloy design and materials selection for fatigue resistance is discussed. Potential tradeoffs between design philosophies which emphasize damage tolerance characteristics vs. those which focus on improved life cycle economics are examined.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721259212
Category :
Languages : en
Pages : 34
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Methods to improve the high temperature, dwell crack growth resistance of Alloy 10, a high strength, nickel-base disk alloy, were studied. Two approaches, heat treat variations and composition modifications, were investigated. Under the heat treat approach, solution temperature, cooling rates, and stabilization, were studied. It was found that higher solution temperatures, which promote coarser grain sizes, coupled with a 1550 F stabilization treatment were found to significantly reduce dwell crack growth rates at 1300 F Changes in the niobium and tantalum content were found to have a much smaller impact on crack growth behavior. Lowering the niobium:tantalum ratio did improve crack growth resistance and this effect was most pronounced for coarse grain microstructures. Based on these findings, a coarse grain microstructure for Alloy 10 appears to be the best option for improving dwell crack growth resistance, especially in the rim of a disk where temperatures can reach or exceed 1300 T. Further, the use of advanced processing technologies, which can produce a coarse grain rim and fine grain bore, would be the preferred option for Alloy 10 to obtain the optimal balance between tensile, creep, and crack growth requirements for small gas turbine engines. Gayda, John Glenn Research Center NASA/TM-2001-210814, E-12729, NAS 1.15:210814
Author: S. J. Hudak
Publisher: ASTM International
ISBN: 9780803107175
Category : Technology & Engineering
Languages : en
Pages : 384
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Author: Robert S. Piascik
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 34
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Author: John Jeffrey Kleek
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 126
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