EFFECT OF SPECIMEN THICKNESS ON FATIGUE CRACK GROWTH BEHAVIOUR UNDER CONSTANT AND VARIABLE AMPLITUDE LOADING | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Article 23, Volume 8, ASAT Conference, 4-6 May 1999, May 1999, Pages 1-13 PDF (2.17 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/asat.1999.24899 | ||
| Authors | ||
| M. M.I. HAMMOUDA1; S. S.E. AHMAD2; M. H. SELEEM2 | ||
| 1Professor, Dpt. Of Mechanical Eng., Al- Azhar University, Cairo, Egypt. | ||
| 2Assistant Prof., Dpt. Of Materials Eng., Zagazig University, Zagazig, Egypt. | ||
| Abstract | ||
| Mode I fatigue crack growth behaviour was experimentally investigated under constant and following the application of a single spike overload. Different specimen thicknesses were investigated at different overload ratios. A previously developed crack tip deformation model to correlate fatigue crack growth behaviour following k a single overload cycle was used to correlate that behaviour for different specimen thicknesses. It was found that the effect of specimen thickness on the fatigue crack growth behaviour under constant amplitude of loading is marginal especially at growth rates greater than le mm/cycle. The retardation due to the application of a tensile single overload decreases with the increase in specimen thickness. Good agreement between relevant experimental results and those predicted using three dimensional crack tip deformation parameter was found. | ||
| Keywords | ||
| Fatigue Crack Growth; Constant Amplitude Loading; Single Overload; Plate Thickness; Crack Tip Deformation | ||
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