Improvement of hot corrosion resistance in calcium-magnesium-aluminosilicate (CMAS: CaO-MgO-Al₂O₃-SiO₂) environments is one of the main goals in the development of aero-engines especially in their thermal barrier coatings (TBCs). In this regard, this study aims to improve the quality and efficiency of the yttria-stabilized ZrO₂ (8YSZ) TBCs by substitution of new coatings such as ZGYbY: ZrO₂ 9.5Y₂O₃ 5.6Yb₂O₃ 5.2Gd₂O₃. For this purpose, 8YSZ and ZGYbY topcoats with CoNiCrAlY bond coat were applied on IN738LC substrates using atmospheric plasma spray (APS) technique. Hot corrosion behavior of the coatings was investigated in CMAS environment by a furnace method at 1150 °C in the 4-h cycles. Phase and microstructural investigations of the coatings by XRD and FESEM/EDS methods before and after the hot corrosion test indicated the better performance of ZGYbY coating (relative to 8YSZ) in preventing from the diffusion of the CMAS particles. This could be due to the formation of the impermeable apatite compounds (i.e., Ca₄Y(Yb/Gd)₆O(SiO₄)₆). Furthermore, the destruction of the TBCs in CMAS environment can be attributed to the diffusion of molten silicates through the pores and micro-cracks of the ceramic top layer to the TBC and then release of the ZrO₂ stabilizer and finally the tetragonal to monoclinic ZrO₂ phase transformation.

改善钙镁铝硅酸盐（CMAS：CaO-MgO-Al ₂ O ₃ -SiO ₂）环境中的耐热腐蚀性能是航空发动机尤其是隔热涂层（TBC）发展的主要目标之一。在这方面，本研究旨在通过替代新型涂层（例如ZGYbY：ZrO ₂ 9.5Y ₂ O ₃ 5.6Yb ₂ O ₃ 5.2Gd ₂ O ₃）来提高氧化钇稳定ZrO ₂（8YSZ）TBC的质量和效率。。为此，使用大气等离子喷涂（APS）技术将具有CoNiCrAlY粘结涂层的8YSZ和ZGYbY面漆涂覆在IN738LC基板上。通过在1150°C下于4小时的循环中的炉法在CMAS环境中研究了涂层的热腐蚀行为。在热腐蚀试验之前和之后，通过XRD和FESEM / EDS方法对涂层进行相和微观结构研究表明，ZGYbY涂层（相对于8YSZ）在防止CMAS颗粒扩散方面具有更好的性能。这可能是由于形成了不可渗透的磷灰石化合物（即Ca ₄ Y（Yb / Gd）₆ O（SiO ₄）₆）。此外，在CMAS环境中TBC的破坏可归因于熔融硅酸盐通过陶瓷顶层的孔和微裂纹扩散到TBC，然后释放ZrO ₂稳定剂，最后是四方的单斜ZrO _2。相变。