<p>Under high-temperature adverse environments, the premature failure of air plasma spray thermal barrier coatings (APS-TBCs) is a preliminary phenomenon that can significantly limit the application of TBCs in gas turbine engines. The delamination failure of TBCs typically occurs at the interfaces between the topcoat and bond coat due to thermal mismatch stress and thermal gradient, resulting in crack propagation and final spallation failure of the coating. This paper undertakes a study of the delamination of TBCs using multi-physics methodologies. Heat transfer was cyclically implemented into the TBC model, resulting in a thermal gradient, to simulate the in-service operation of the TBC system. A variational-based sintering model for a topcoat of TBCs is incorporated into the simulation. The high-temperature creep model of the topcoat, thermal growth oxide (TGO) and bond coat is included. The stress field across the TBCs was calculated during the thermal cycles, with the location of high-stress concentration selected as the potential crack initiation site. Phase field damage modelling was conducted to study crack propagation, initially located at the high-tensile stress off-peak interface. Results indicate that at the off-peak interface, the crack propagates rapidly in the top right direction during the first few cycles, then stops propagating as the TGO thickens, because the location of the maximum principal stress is moved away from the interface. Since the accumulated stress at the crack tip at the end of cycles, cracks have the potential to propagate with a prolonged thermal cycle service.</p>