PURPOSE: To increase durability for failure in the thermal barrier coating applied to parts such as a gas turbine engine of an aircraft.

CONSTITUTION: A base material 34 being gas turbine parts is coated with a bond coat 36, a whisker 40 is grown from the bond coat 36 itself after coating and then, a thermal barrier coating 38 is applied. A Ni base alloy used for turbine parts for the base material 34, a Fe base alloy including Al for the bond coat 36, Al2O3 obtained through oxidation/growth in situ in the bond coat 36 for the whisker 40, Y2O3-stabilized ZrO2 for the thermal barrier coating 38 are respectively used for a material. Since the whisker 40 has a function to fix or peg the thermal barrier coating 38 to the base material 34, the whisker 40 provides a thermal barrier coating structure 30 excellent in durability for failure in spite of being the same thickness as a conventional one.