The definition of the critical levels of microstructural damage that can lead to the propagation of fatigue cracks under high-cycle fatigue loading conditions is a major concern with respect to the structural integrity of turbine-engine components in military aircraft. The extremely high cyclic frequencies characteristic of in-flight loading spectra, coupled with the presence of small cracks resulting from fretting or foreign object damage (FOD), necessitate that a defect-tolerant design approach be based on a crack-propagation threshold. The present study is focused on characterizing such near-threshold fatigue-crack propagation behaviour in a Ti-6Al-4V blade alloy (with approximately 60% primary alpha in a matrix of lamellar alpha+beta), at high frequencies (20-1500 Hz) and load ratios (0.1-0.95) in both ambient temperature air and vacuum environments. Results indicate that 'worst-case' thresholds, measured on large cracks, may be used as a practical lower bound to describe the onset of naturally initiated small-crack growth and the initiation and early growth of small cracks emanating from sites of simulated FOD.


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    Titel :

    High-cycle fatigue of Ti-6Al-4V


    Weitere Titelangaben:

    Hochlastwechsel-Ermüdung von Ti-6Al-4V


    Beteiligte:
    Ritchie, R.O. (Autor:in) / Davidson, D.L. (Autor:in) / Boyce, B.L. (Autor:in) / Campbell, J.P. (Autor:in) / Roder, O. (Autor:in)


    Erscheinungsdatum :

    1999


    Format / Umfang :

    11 Seiten, 31 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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