电子束物理气相沉积（EB-PVD）热障涂层保护航空发动机热端部件，同时通过其分离的柱状结构容纳循环应变。然而，连通的间隙和羽状亚结构也为吸入环境颗粒衍生的熔融钙镁铝硅酸盐（CMAS）沉积物提供了渗入通道。渗入将涂层溶解和相演化耦合起来，导致光散射降低、刚度增加和界面损伤，削弱隔热和循环耐久性。本综述采用输运-反应-断裂框架，综合材料与加工创新，强调EB-PVD体系对结构的具体要求。将沉积物化学、粒子热历史、润湿性和柱网络拓扑与渗入、结晶和失效的时机及位置联系起来。评估了富钇锆、稀土锆酸盐、石榴石型铝酸盐、磷酸盐、反应性氧化物覆层以及新兴多组分陶瓷，同时涵盖激光表面改性、柱细化和多层设计。综合识别出一个共同的设计要求：保护必须在脆弱区域暴露之前限制连通的液体输运。
Electron-beam physical vapor deposition (EB-PVD) thermal barrier coatings protect aero-engine hot-section components while accommodating cyclic strain through their separated columnar architecture. However, the connected gaps and feather-like substructures also provide pathways for molten calcia–magnesia–alumino–silicate (CMAS) deposits derived from ingested environmental particles. Infiltration couples coating dissolution and phase evolution to reduced optical scattering, increased stiffness, and interfacial damage, undermining thermal insulation and cyclic durability. This review synthesizes materials and processing innovations using a transport–reaction–fracture framework that emphasizes the architecture-specific requirements of EB-PVD systems. Deposit chemistry, particle thermal history, wetting, and column-network topology are linked to the timing and location of infiltration, crystallization, and failure. Yttria-rich zirconia, rare-earth zirconates, garnet-forming aluminates, phosphates, reactive oxide overlays, and emerging multicomponent ceramics are assessed alongside laser surface modification, column refinement, and multilayer designs. The synthesis identifies a common design requirement: protection must restrict connected liquid transport before vulnerable regions are reached without producing a brittle cap or weakening internal interfaces. Favorable reaction products and low penetration depths are therefore evaluated against coating consumption, retained thermal resistance, compliance, and cyclic integrity. A proposed multiscale modeling workflow connects thermodynamic and infiltration analyses to fracture and component-level exposure, while distinguishing mechanistic screening from coating-system validation. Priorities include comparable deposit and thermal histories, repeated melting and deposition, and functional measurements beyond post-exposure penetration depth. The resulting design rules favor localized reactive protection, controlled column-gap connectivity, and a compliant underlying coating, providing a basis for translating laboratory mitigation strategies into reproducible and repairable aero-engine coating systems.