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 process.
| Original language | English |
|---|---|
| Pages (from-to) | 1180-1189 |
| Number of pages | 10 |
| Journal | International Journal of Fatigue |
| Volume | 32 |
| Issue number | 7 |
| DOIs | |
| State | Published - Jul 2010 |
Keywords
- Crack branching
- Fatigue crack growth
- Fatigue load spectra
- Life prediction
- Retardation
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