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An experimental investigation of load interaction effects in Ti-6Al-2Sn-4Zn-2Mo is presented. Simple variable amplitude loading spectra were applied to test samples, and the crack propagation stress intensity factor, KPR, was subsequently measured. The data were condensed to two equations (“master curves”) that describe the influence of an unloading cycle after constant amplitude loading and a single overload cycle, respectively. The results suggest that load interaction effects are caused by residual compressive stresses ahead of the crack front, whereas the influence of crack closure is minor.
fatigue crack propagation, crack closure, residual stresses, titanium, load interaction, life prediction
National Research Council-Associate, Air Force Research Laboratory, Materials and Manufacturing DirectorateIABG, Wright-Patterson Air Force BaseOttobrunn, OH
Air Force Research Laboratory, Materials and Manufacturing Directorate, Wright-Patterson Air Force Base, OH