Abstract
Since gas turbines operate under extremely high temperatures, the hot-section parts of gas turbines should be protected from severe environmental conditions. Thermal Barrier Coating (TBC) is a protection technique that lowers the surface temperature of the hot-section parts. To design reliable gas turbines, the delamination life of TBC should be accurately evaluated. This study evaluated the delamination life of TBC by conducting a burner-rig test simulation of thermal fatigue conditions using a hot flame. Two types of TBCs were considered: one with vertical cracks and the other without vertical cracks. To evaluate the effects of pre-isothermal deterioration on thermal fatigue life under flame conditions, burner-rig tests were performed using isothermally deteriorated specimens. The burner-rig tests were conducted until the coating layer was completely delaminated. Using the tests results, predictive equations for delamination life and delaminated TBC area were derived and analyzed.
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