The fatigue-creep life was found to be longer than the fatigue life from the Low Cycle Fatigue experiment of turbine blade of an aeroengine.The relevant theoretical calculation and analysis were then carried out to provide a further insight into such phenomenon.The research shows that: the actual working conditions of blades were well simulated in the experimental conditions

indicating that the damage of blade was mainly attributable to fatigue damage.As compared with pure fatigue test of real turbine blade

stress relaxation occurred at the key section(serration) under fatigue-creep test conditions

showing that fatigue/creep life of blade was longer than fatigue life.The research results play a key role in ensuring the safety of engines

improving the flight reliability and developing fatigue test techniques of high-temperature components.