| Many failures between tenon and mortise in aero-engine are founded under fretting circumstance, sometimes it is a main cause of failure and it is important to research the fretting fatigue life of tenon/mortise. The research method of fretting fatigue life and the mechanism of fretting damage are represented. The problem of elastic contact is solved based on the ANSYS, and the distribution of contact stress and contact status of dovetail joint are obtained. Based on the existing fretting fatigue life predicted by the nominal stress method, the influence of friction power is concerned, and the prediction model of fretting fatigue life is improved. The fretting fatigue life of dovetail joint is predicted under the low-cycle load, and the fretting fatigue experimentations of dovetail joint are done under the three-types loading. The validity of the proposed model and the approach was verified by experiments. Based on the strain-monitor technology, the observation system of fretting fatigue crack was designed, which ensured to observe crack in time and validly, avoiding the complex crack-observation work, and improved the efficiency and precision of the experiment.
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