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Long/Large Fatigue Crack Growth

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Fatigue of Beta Processed and Beta Heat-treated Titanium Alloys

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Abstract

Long/large fatigue crack growth under constant amplitude loading can be considered in terms of the three regions shown in Fig. 6.1. In region I there is a threshold value, ΔKth, below which cracks do not propagate. Above this value the crack growth rate increases relatively rapidly with increasing ΔK. In region II there is a more or less linear log–log relation between da/dN and ΔK. In region III the crack growth rate curve rises rapidly towards final failure.

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Authors and Affiliations

  1. Aerospace Vehicles Division, National Aerospace Laboratory NLR, PO Box 153, 8300 AD, Emmeloord, The Netherlands

    Russell Wanhill

  2. Air Vehicle Division, DSTO Defence Science and Technology Organisation, 506 Lorimer St, Fishermans Bend, Melbourne, VIC, 3207, Australia

    Simon Barter

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  1. Russell Wanhill
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Correspondence to Russell Wanhill .

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Wanhill, R., Barter, S. (2012). Long/Large Fatigue Crack Growth. In: Fatigue of Beta Processed and Beta Heat-treated Titanium Alloys. SpringerBriefs in Applied Sciences and Technology(). Springer, Dordrecht. https://doi.org/10.1007/978-94-007-2524-9_6

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  • DOI: https://doi.org/10.1007/978-94-007-2524-9_6

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  • Publisher Name: Springer, Dordrecht

  • Print ISBN: 978-94-007-2523-2

  • Online ISBN: 978-94-007-2524-9

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