MECHANICAL BEHAVIORS OF TBC IN AEROENGINE HOT SECTION

A systematical study on the mechanical behaviors of Thermal Barrier Coating(TBC),the thermal compatibility of TBC with basic material of turbine blade,and the interface residual stress caused by various TBC materials.The change of the blade working temperature leads to crack,separation and scars between TBC and substrate,that results in TBC failure,so the blade cannot work normally.It is discovered from the experiments that addition of trace elements Zr-Y-Nb-AL in the thermal barrier coating as the interface coherent layer enhances the combination strength between TBC and substrate significantly,increases the thermal burst resistance,improves the surface smoothness.The operating temperature of the blades with TBC is enhanced up to 200℃-300℃ higher than that of the blades without TBC.The thermal barrier coating not only can be applied to turbine blade,but also has a significant effect on the surface protection of the combustor and jet exhaust nozzle of aeroengine.