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Fatigue crack growth behaviour and life prediction for 2324-T39 and 7050-T7451 aluminium alloys under truncated load spectra

By Rui Bao and Xiang Zhang

Abstract

This paper presents a study of crack growth behaviour in aluminium alloys 2324- T39 and 7050-T7451 subjected to flight-by-flight load spectra at different low- stress truncation levels. Crack branching was observed in the higher truncation levels for the 2324 and in all truncation levels for the 7050. Mode I crack growth life can be predicted for the 2324 alloy by the NASGRO equation and the Generalised Willenborg retardation model. However, quantitative prediction of the fatigue life of a significantly branched crack is still a problem. Material properties, test sample’s orientation and applied stress intensity factor range all play dominant roles in the fracture proce

Topics: Fatigue crack growth, Fatigue load spectra, Crack branching, Retardation, Life prediction
Publisher: Elsevier Science B.V., Amsterdam.
Year: 2010
DOI identifier: 10.1016/j.ijfatigue.2009.12.010
OAI identifier: oai:dspace.lib.cranfield.ac.uk:1826/4320
Provided by: Cranfield CERES
Journal:

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Citations

  1. A critical analysis of crack propagation laws. doi
  2. (1974). A Generalized Development of Yield-Zone Models,
  3. (2006). AFGROW users guide and technical manual, AFRL-VA-WP-TR-2006-xxxx, AFGROW, version 4.0011.14,
  4. Crack-closure behavior of 2324-T39 aluminum alloy nearthreshold conditions for high load ratio and constant Kmax tests, doi
  5. Evaluation of fatigue life and crack growth rates in 7050-T7451 aluminum plate for T-L and L-S oriented failure under truncated spectra loading, doi
  6. (1992). FASTRAN-II – A Fatigue Crack Growth Structural Analysis Program,
  7. Fatigue crack growth predictions for variable-amplitude and spectrum loading, doi
  8. Fatigue crack propagation in 7050-T7451 plate alloy, doi
  9. Fatigue crack propagation in light alloy sheet material and structures, doi
  10. (2009). Fatigue of Structures and materials (2nd Edition), doi
  11. (1998). Federal Aviation Administration, Advisory Circular - Damage Tolerance and Fatigue Evaluation of Structure, Federal Air Regu-lations 25, AC No.25.271-1C,
  12. (2004). Fracture Mechanics (2nd edition).
  13. Influence of yield strength on overload affected fatigue crack growth behaviour in 4340
  14. (1967). Numerical analysis of crack propagation in cyclic-loaded structures, doi
  15. (2009). Products: 2324 Aluminium Alloy Plate and Sheet; Website (accessed
  16. (2009). Products: 7050 Aluminium Alloy Plate and Sheet; Website (accessed Aug.
  17. (1981). Random spectrum fatigue crack life predictions with or without considering load interactions, Methods and Models for Predicting Fatigue Crack Growth under Random Loading, doi
  18. (2009). Small crack growth rates from simple sequences containing underloads in AA7050-T7451, doi
  19. (1972). Spectrum Loading and Crack Growth, Transaction of the ASME, doi
  20. Study of underload effects on the delay induced by an overload in fatigue crack propagation, doi
  21. The effect of dynamic loading on fatigue scatter factor for Al 7050, doi
  22. (1970). The Effect of Stress Ratio During Crack Propagation and Fatigue for doi
  23. The Effects of Environment and Load Frequency on the Crack Propagation Law for Macro Fatigue Crack Growth In Aluminium Alloys, doi
  24. The Influence of Low Load Truncation Level on Crack Growth for Al 2324-T39 and Al 7050-T7451, doi
  25. (1971). The Significance of Fatigue Crack Closure, Damage Tolerance in Aircraft Structures, doi

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