(Received 2 May 2005; accepted 5 April 2006)
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The present study was aimed towards improving the prediction capability of fretting fatigue life of Ti-6Al-4V. Incremental and interrupted fretting fatigue tests were conducted. Based on the crack propagation pattern observed on the fractured surface fretting fatigue life was predicted. The disappearance of contact stresses was evidenced by the change in crack growth direction from oblique to perpendicular path to the loading direction. Thus, fatigue crack initially propagated under the influence of the contact stress, and then it grew due to the applied stress amplitude to the substrate. The transition crack length between these two conditions varied between 20 to 30 μm and depended on the contact load. This enabled the prediction of short and long crack propagation life. There was good correlation between the predicted fretting fatigue life and the experimental life.
Assistant Professor, School of Engineering, Mercer University, Macon, GA
Senior Materials Engineer, Materials & Manufacturing Directorate, U.S. Air Force Research Laboratory, Wright-Patterson AFB, OH
Professor, U.S. Air Force Institute of Technology, Wright-Patterson AFB, OH
Stock #: JAI100346