Crack and fracture fault emerged in the mortises of a given aeroengine second-stage turbine disk for a long time and seriously endangered the aircraft's regular flight.The fractography analysis indicated that the faults were caused by combined fatigue at elevated temperature.So we were engaged in this experiment to study and research a new failure criterion of the disk.A real disk was used as experimental component

we worked out a new failure experimental approach

including key technique to ensure the noninterference between the low cycle loading and high cycle loading

the high frequency induction local heating (550℃ constant temperature)

the control of high cycle vibration frequency and amplitude

and crack real-time detection.Experimental load spectrum and temperature field emulated the reality

and the experiment completely reproduced the practical flight fault. The present experimental approach can be applied to the combined fatigue analysis of any components.