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A study was conducted to investigate fretting fatigue damage of Ti-6Al-4V against Ti-6Al-4V under flat-on-flat contact with blending radii at room temperature. Both the location of and the time required to nucleate fretting fatigue cracks were investigated for two static clamping stress values representative of those estimated for turbine engine blade attachments. Fatigue limit stresses for a 107 cycle fatigue life were evaluated for the selected conditions. Fretting fatigue nucleated cracks were identified in situ using shear wave ultrasonic NDI. The effect of fretting fatigue on uniaxial fatigue life was quantified by interrupting fretting fatigue tests at 10% of life, and conducting uniaxial residual fatigue life tests. Metallography, scanning electron microscopy and spectral analysis were used to characterize the fretting damage.
fretting fatigue, Ti-6Al-4V, crack nucleation
Assistant Research Engineer, University of Dayton Research Institute, Dayton, OH
Senior Research Engineer, University of Dayton Research Institute, Dayton, OH
Senior Scientist, Air Force Research Laboratory, Materials and Manufacturing Directorate, Metals, Ceramics & NDE Division (AFRL/MLLMN), Wright Patterson AFB, OH