Fatigue crack initiation and growth of turbine disks often cause catastrophic damage to the aircraft, it is essential to study the failure mechanism and feature extraction of the crack for turbine disks. This paper presents a methodology to calculate the maximum crack opening displacement (MCOD) of turbine discs subjected to low cycle fatigue. Initially, the variations of the MCOD with rotational speed during cyclic loading were studied. Subsequently, the finite element method was employed to verify the results and establish the correlation between the MCOD and rotational speed. A functional correlation between the variation of the MCOD and the rotational speed change under cyclic loading was developed.

turbine disc; fatigue crack; maximum crack opening displacement; variation rules; low cycle fatigue