THERMAL BARRIER COATING MATERIAL, GAS TURBINE PARTS AND GAS TURBINE

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A thermal barrier coating material can prevent spall-off from occurring during operation at high temperatures and has a high heat insulating effect. A turbine parts and a gas turbine that are protected with the thermal barrier coating material are also provided. The thermal barrier coating material of the present invention comprises a ceramic layer 23, which is formed on a high temperature heat-resistant alloy base 21 to protect the base 21 from high temperatures, the ceramic layer 23 being applied via a bonding coat layer 22 provided as a metal bonding layer and is made of ZrO2 with Er2O3 added thereto as a stabilizing agent. The turbine parts and the gas turbine of the present invention are coated with the thermal barrier coating material on the surfaces thereof.