The contact stress and strain of the dovetail joint of aeroengine were analyzed. According to the critical plane approach of multiaxial fatigue theory

the multiaxial fatigue damage parameters: CCB (Chu-Conle-Bonnen)

FS (Fatemi-Socie)

MSSR (modified shear stress rang)

and SWT (Smith-Watson-Topper)

were introduced to predict the fretting fatigue life of the dovetail joint. By comparing the predicted fatigue life with the experimental life

the results show that: the maximum prediction error of fretting fatigue life was 23%

helping to predict satisfactorily low-cycle fretting fatigue life. And

the minimum prediction error was 1.23% based on SWT parameter. The predicted crack tip initiated at the end of contact area in agreement with the experiment test. In general

the critical plane approach can be used to predict the fretting fatigue effectively. The models based on FS

MSSR and SWT can predict the fretting fatigue crack position

while the models based on MSSR and SWT can predict the fretting fatigue life more correctly.