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航空发动机涡轮叶片工作时表面经常产生CaO-MgO-Al2O3-SiO2(简称CMAS)等沉积物。本文中研究了电子束物理气相沉积(EB-PVD)制备ZrO2热障涂层(TBCs)在CMAS环境下的热循环行为及失效机制。结果表明,在1200℃热冲击条件下,表面涂覆CMAS的热障涂层的热循环寿命低于100次,而未涂覆CMAS的涂层寿命达到500次以上,CMAS的存在加速了热障涂层的剥落失效。在1200℃经过210次循环后,ZrO2陶瓷层与CMAS之间形成了约8μm厚的互反应区,其形成主要与CMAS中Ca2+内扩散有关。CMAS环境下热障涂层陶瓷层产生大量横向裂纹,涂层的失效主要以陶瓷层片状剥落为主。
Aeroengine turbine blades work surface often produce CaO-MgO-Al2O3-SiO2 (referred to as CMAS) and other sediments. In this paper, the thermal cycling behavior and failure mechanism of ZrB2 thermal barrier coatings (TBCs) prepared by electron beam physical vapor deposition (EB-PVD) under CMAS conditions were studied. The results show that the thermal cycle life of the CMAS-coated thermal barrier coating is less than 100 times at 1200 ℃, while that of the uncoated CMAS reaches more than 500 times. The presence of CMAS accelerates the thermal barrier Coating peeling failure. After 1200 cycles at 1200 ℃, a ZrO2 ceramic layer and CMAS formed a reaction zone of about 8μm thick, the formation of which is mainly related to the diffusion of Ca2 + in CMAS. Thermal barrier coating ceramic layer CMAS environment produces a large number of transverse cracks, the failure of the coating mainly flaking ceramic layer flake.