In this study, numerical and experimental methods were used to investigate the combined effect of internal cooling channels and thermal barrier coating on temperature distribution and, ultimately, fracture of a real GEF9 turbine blade. The blade comprises TBC layers and internal cooling channels, damaged after 66,000 h of operation. Observations showed blockage of the cooling channels for the fractured blade. The blade temperature distribution was calculated before and after blockage using CFD, and simulation results were used to design the experimental tests. The results show that blockage leads to about a 100-degree increase in blade temperature, 5-µm growth in TGO, and changes in the coating porosity fraction. This causes an increase in ceramic layer stress and the TBC delamination. With the spallation of the TBC layer, the blade is exposed to higher temperatures. Finally, the blade failed due to overheating, accompanied by centrifugal forces related to the blade rotation.