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    Fatigue Crack Growth of β-21S Titanium Alloy Under Constant Amplitude and miniTWIST Flight Spectra at 25°C and 175°C

    Source: Journal of Engineering Materials and Technology:;1997:;volume( 119 ):;issue: 004::page 387
    Author:
    R. R. Stephens
    ,
    R. I. Stephens
    ,
    T. P. Albertson
    ,
    A. L. Veit
    DOI: 10.1115/1.2812274
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: β-21S titanium alloy sheet fatigue crack growth behavior was investigated at 25°C and 175°C under constant amplitude (R = 0.1 and 0.5) and miniTWIST flight spectra. Based upon nominal ΔK values, constant amplitude fatigue crack growth behavior at 175°C was either similar to (R = 0.1), or slightly better than (R = 0.5) 25°C. With crack closure taken into account, the fatigue crack growth curves at 175°C, plotted as a function of Keff , were shifted to the left of the fatigue crack growth curves at 25°C at near threshold values. Under flight spectra conditions, fatigue crack growth life at 175°C was 40 to 90 percent longer than at 25°C. Flight spectra life calculations using NASA/FLAGRO based upon constant amplitude fatigue crack growth data, were primarily conservative but in good agreement with experimental data. Fatigue crack growth was transgranular with crystalline facets and striations that were evident at higher constant amplitude fatigue crack growth rates and with the miniTWIST spectra. Striations were observed to a limited extent at threshold and near threshold conditions at 25°C, but not at 175°C. Based upon desirable constant and variable amplitude fatigue crack growth and fatigue/fracture crack morphology, this β-21S sheet alloy appears to be an acceptable material for damage tolerant aerospace situations between 25°C and 175°C.
    keyword(s): Spectra (Spectroscopy) , Titanium alloys , Fatigue cracks , Flight , Fatigue , Aerospace industry , Fracture (Process) AND Alloys ,
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      Fatigue Crack Growth of β-21S Titanium Alloy Under Constant Amplitude and miniTWIST Flight Spectra at 25°C and 175°C

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    http://yetl.yabesh.ir/yetl1/handle/yetl/118761
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    • Journal of Engineering Materials and Technology

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    contributor authorR. R. Stephens
    contributor authorR. I. Stephens
    contributor authorT. P. Albertson
    contributor authorA. L. Veit
    date accessioned2017-05-08T23:53:36Z
    date available2017-05-08T23:53:36Z
    date copyrightOctober, 1997
    date issued1997
    identifier issn0094-4289
    identifier otherJEMTA8-26988#387_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/118761
    description abstractβ-21S titanium alloy sheet fatigue crack growth behavior was investigated at 25°C and 175°C under constant amplitude (R = 0.1 and 0.5) and miniTWIST flight spectra. Based upon nominal ΔK values, constant amplitude fatigue crack growth behavior at 175°C was either similar to (R = 0.1), or slightly better than (R = 0.5) 25°C. With crack closure taken into account, the fatigue crack growth curves at 175°C, plotted as a function of Keff , were shifted to the left of the fatigue crack growth curves at 25°C at near threshold values. Under flight spectra conditions, fatigue crack growth life at 175°C was 40 to 90 percent longer than at 25°C. Flight spectra life calculations using NASA/FLAGRO based upon constant amplitude fatigue crack growth data, were primarily conservative but in good agreement with experimental data. Fatigue crack growth was transgranular with crystalline facets and striations that were evident at higher constant amplitude fatigue crack growth rates and with the miniTWIST spectra. Striations were observed to a limited extent at threshold and near threshold conditions at 25°C, but not at 175°C. Based upon desirable constant and variable amplitude fatigue crack growth and fatigue/fracture crack morphology, this β-21S sheet alloy appears to be an acceptable material for damage tolerant aerospace situations between 25°C and 175°C.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleFatigue Crack Growth of β-21S Titanium Alloy Under Constant Amplitude and miniTWIST Flight Spectra at 25°C and 175°C
    typeJournal Paper
    journal volume119
    journal issue4
    journal titleJournal of Engineering Materials and Technology
    identifier doi10.1115/1.2812274
    journal fristpage387
    journal lastpage392
    identifier eissn1528-8889
    keywordsSpectra (Spectroscopy)
    keywordsTitanium alloys
    keywordsFatigue cracks
    keywordsFlight
    keywordsFatigue
    keywordsAerospace industry
    keywordsFracture (Process) AND Alloys
    treeJournal of Engineering Materials and Technology:;1997:;volume( 119 ):;issue: 004
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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