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A study was conducted to evaluate fretting fatigue damage of Ti-6Al-4V under flat-on-flat contact at room temperature. Results were obtained to establish the fatigue limit of the material. Axial stresses necessary to fail specimens at 107 cycles for different contact radii, applied normal stresses, and stress ratios were evaluated to determine the baseline fretting fatigue behavior. Then, the effect of fretting fatigue on specimen life was quantified by conducting interrupted fretting tests for various load ratios and normal stresses followed by residual strength uniaxial fatigue tests. Fractography was used to characterize the nature of fretting damage. Results indicate that no degradation in fatigue limit is observed when the material is subjected to up to 10 percent of fretting fatigue life.
fretting fatigue, high cycle fatigue, Ti-6Al-4V, flat-on-flat contact, fatigue damage
Assistant Research Engineer, Structural Integrity Division, University of Dayton Research Institute, Dayton, OH
Senior Scientist, Air Force Research Laboratory (AFRL/MLLN), Wright-Patterson AFB, OH