Yttria stabilized zirconia (YSZ) is used extensively as a ceramic top coat of thermal barrier coating (TBC) system in land-based gas turbines and aero engines. TBC enables modern engines to operate at significantly higher gas temperatures. TBCs are subjected to solid particle erosion at elevated temperature, especially during the operation of aero engines in sandy terrain. Thus, the objective of the present investigation is to evaluate the impact erosion response of these coatings as a function of various eroding conditions. Toward that purpose, YSZ TBC was deposited on Ni base alloy using air plasma spraying technique. The microstructural features of the coating are evaluated, and coated samples are subjected to erosion test employing a high temperature air jet erosion testing machine at various temperatures, different impact velocities, and at different impact angles. The results show a brittle erosion response of TBC at all temperatures. The erosion rate of TBC is generally independent of temperature under the normal impact, and it increases with temperature under oblique impact at high impact velocity. Intersplat adhesion governs the erosion mechanism.

氧化钇稳定的氧化锆（YSZ）广泛用作陆基燃气轮机和航空发动机的热障涂层（TBC）系统的陶瓷面漆。TBC使现代发动机能够在明显更高的气体温度下运行。TBC在高温下会受到固体颗粒的侵蚀，尤其是在沙地中的航空发动机运行期间。因此，本研究的目的是评估这些涂层的冲击腐蚀响应随各种腐蚀条件的变化。为此，使用空气等离子喷涂技术将YSZ TBC沉积在镍基合金上。评估了涂层的微观结构特征，并使用高温空气喷射侵蚀试验机在各种温度，不同的冲击速度，并具有不同的冲击角度。结果表明，在所有温度下，TBC的脆性腐蚀响应。在正常冲击下，TBC的腐蚀速率通常与温度无关，在高冲击速度下，倾斜冲击下，TBC的腐蚀速率随温度增加。跨板间的附着力决定着腐蚀机理。