In order to study the fatigue damage and cycle life of TC4 titanium
alloy for aero-engine blades under various load conditions, uniaxial
fatigue, multi-stage loading and multiaxial fatigue tests were carried
out. The critical plane method combined with von Mises criterion was
used to study the fatigue life distribution under various loading paths,
and the results were verified by experiments. Based on the nonlinear
residual strength model and Poisson stochastic process, the reliability
prediction of aero-engine compressor blade under maximum continuous
working condition was completed. The results show that the fatigue
damage and life distribution of TC4 titanium alloy for aeroengine blade
under various conditions can be accurately predicted by the method
proposed in this paper and the reliability of the blade can still be
maintained above 0.9 after it works for 3000 hours under the maximum
continuous working condition.