Verification of the Heat protection and Cooling Effects for Thermal Barrier Coating on Turbine Blade

Abstract

Aiming at the difficulty of directly testing the heat protection effect of thermal barrier coating (TBC) on turbine blades in real working conditions of Aero-engines, in order to obtain the heat protection performance and TBC cooling effect on turbine blades, this study first conducted a simulation test of heat protection effect at 1100K test temperature on a tester, and then combined with the test results of TBC heat protection effect, completed the verification in real working conditions of Aero-engine. The test results verify that the actual heat protection effect of the TBC is roughly equivalent on the suction surface and pressure surface of the blade, but it is the worst in the trailing edge region with the blade basin, with an average relative cooling efficiency of about 0.642 in the middle section, and a maximum absolute heat protection effect of about 41 K. At the same time, the blade has no ablation phenomenon, and the TBC is in good state on the blade surface, and it is free of defects such as cracks, wrinkling, and peeling, as verified by the coupon test with a maximum gas temperature of 1800K for a cumulative period of 21 hours.