Thermal barrier coating has good thermal insulation effect and high temperature oxidation resistance, which can significantly increase the service temperature and life of high temperature components in aeroengines. The development of advanced aeroengine has put forward higher requirements for the protective effect and service life of ceramic thermal barrier coating materials. The research progress of thermal barrier coating system for advanced aeroengine is reviewed. The ceramic layer and bond layer material system and preparation technology of thermal barrier coating at home and abroad in recent years are described in detail, while the failure of coating is analyzed. The research and application prospect of the next generation high-performance thermal barrier coatings for aeroengine are prospected.

Developing new high-entropy rare-earth zirconate (HE-RE₂Zr₂O₇) ceramics with low thermal conductivity is essential for thermal barrier coating materials. In this work, the average atomic spacings, interatomic forces, and average atomic masses of 16 rare-earth elements occupying the A site of the cubic A₂B₂O₇ crystal structure were calculated by density functional theory. These three physical qualities, as vectors, characterize the corresponding rare-earth elements. The distance between two vectors quantitatively describes the difference between two rare-earth elements. For greater differences between two rare-earth elements, the disorder degree of HE-RE₂Zr₂O₇ is greater, and therefore, the thermal conductivity is lower. According to the theoretical calculations, the thermal conductivity of the ceramics gradually increases in the order of (Sc_0.2Y_0.2La_0.2Ho_0.2Yb_0.2)₂Zr₂O₇, (Sc_0.2Ce_0.2Nd_0.2Eu_0.2Gd_0.2)₂Zr₂O₇, (Sc_0.2Y_0.2Tm_0.2Yb_0.2Lu_0.2)₂Zr₂O₇, and (Sc_0.2Er_0.2Tm_0.2Yb_0.2Lu_0.2)₂Zr₂O₇. Using the solution precursor plasma spray method and pressureless sintering method, four types of HE-RE₂Zr₂O₇ powder and bulk samples were prepared. The samples all showed a single defective fluorite structure with a uniform distribution of the elements and a stable phase structure. The thermal conductivities of the sintered HE-RE₂Zr₂O₇ bulk samples ranged from 1.30 to 1.45 W·m⁻¹·K⁻¹ at 1400 °C, and their differences were consistent with the theoretical calculation results. Among the ceramics, (Sc_0.2Y_0.2La_0.2Ho_0.2Yb_0.2)₂Zr₂O₇ had the lowest thermal conductivity (1.30 W∙m⁻¹∙K⁻¹, 1400 °C), highest thermal expansion coefficient (10.19×10⁻⁶ K⁻¹, 200–1400 °C), highest fracture toughness (1.69±0.28 MPa∙m^1/2), and smallest brittleness index (3.03 μm^−1/2). Therefore, (Sc_0.2Y_0.2La_0.2Ho_0.2Yb_0.2)₂Zr₂O₇ is considered to be an ideal candidate material for next-generation thermal barrier coating applications.