Study on temperature characteristics of rub-impact in rotor-stator system with composite thermal barrier coating

Rub-impact is one of the most severe failures in titanium alloy rotor-stator systems of aero-engines. This rub-impact can lead to localized high temperatures and even trigger titanium fire failure. To address this issue, thermal barrier coatings (TBCs) are widely applied to components in the rotor-stator system to mitigate the effects of rub-impact. A novel heat generation model for titanium alloy rotor-stator systems with a composite coating is proposed based on Fourier’s law of heat conduction and the Lankarani-Nikravesh contact model, incorporating the effects of the composite coating on both contact stiffness and layered heat conduction. Furthermore, a finite element model (FEM) of rotor-stator rub-impact is developed using the dynamic temperature-displacement explicit method, accounting for heat allocation and thermal gap conductance. Subsequently, the rub-impact temperature characteristics in the rotor-stator system are analyzed, emphasizing the effect of composite coating thickness variations. The proposed heat generation method and finite element model are experimentally validated, both showing a mean absolute percentage error (MAPE) of less than 2%.