A fracture mechanics based approach for the fretting fatigue of aircraft engine fan dovetail attachments

摘要

The fretting fatigue and crack propagation of an aircraft engine fan dovetail attachment made of Ti-6Al-4V alloy has been numerically modeled and compared with controlled spin test results. The study suggests the fretting-specific modified SWT parameter predicts the nucleation location of the crack more accurately compared to the plain fatigue SWT parameter. The fretting model uses a prescribed coefficient of friction value of 0.7, obtained through calibration of 3D crack growth simulations with the fractured components in regards to crack trajectory, aspect ratio, shape, and propagation life.