The invention relates to a high-temperature
thermal barrier coating material. The high-temperature
thermal barrier coating material is
rare earth niobate and a
solid solution thereof. The chemical constitution of the
rare earth niobate is Ln3NbO7, and Ln comprises the
rare earth elements of La, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y and Sc. The chemical constitution of the
solid solution is Ln3(Nb1-xTax)O7 (x is larger than or equal to 0 and smaller than 1). Ln is a combination of one or more than one of the rare earth elements. The high-temperature
thermal barrier coating material is characterized in that the heat
conductivity of the material is low, when the temperature is 1000 DEG C, the intrinsic
thermal conductivity of a compact block body is 1.1-1.4 W / m.k, compared with a commercial yttria-stabilized zirconia (YSZ) material (the
thermal conductivity is about 2.5 W / m.k) with the weight percentage being 7%-8%, the
thermal conductivity of the material is reduced by a large margin, and the material keeps
phase stability and excellent
oxygen-resistance capacity from the indoor temperature to the temperature of 1600 DEG C. The material can be applied to protection of high-temperature
metal hot end parts of
gas turbines or aero-engines.