CMAS环境下电子束物理气相沉积热障涂层的热循环行为及失效机制

苗文辉; 王璐; 郭洪波; 彭徽; 王凯; 宫声凯

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CMAS环境下电子束物理气相沉积热障涂层的热循环行为及失效机制

1.
北京航空航天大学材料科学与工程学院, 北京 100191;
2.
中航工业沈阳黎明航空发动机(集团)有限责任公司, 沈阳 110043

基金项目: 国家自然科学基金(50771009, 51071013); 国家重点基础研究发展计划(2010CB631200)

详细信息

通讯作者:
郭洪波,教授,研究方向为热障涂层E-mail:guo.hongbo@buaa.edu.cn

中图分类号: TB332;V254.2
计量
- 文章访问数: 1186
- PDF下载量: 794
- 被引次数: 0
出版历程
- 收稿日期: 2011-08-30
- 修回日期: 2011-09-29
- 刊出日期: 2012-10-15

Thermal cycling behavior and associated failure mechanism of EB-PVD thermal barrier coatings with CMAS deposits

1.
School of Materials Science and Engineering, Beihang University, Beijing 100191, China;
2.
AVIC Shenyang Liming Aero-engine (Group) Corporation Ltd., Shenyang 110043, China

摘要

摘要: 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8 μm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。
- 热障涂层 /
- 循环热冲击 /
- CMAS /
- 互反应区 /
- 失效
Abstract: CaO-MgO-Al₂O₃-SiO₂ (CMAS in short) deposits are often generated on the surface of in-service aircraft engine blades. In this paper, the thermal cycling behavior and associated failure mechanism of EB-PVD zirconia-based thermal barrier coatings (TBCs) with CMAS deposits were investigated. The results show that the thermal cycling life of TBCs with CMAS deposits at 1200℃ is less than 100 cycles, whereas the life of TBCs without CMAS is more than 500 cycles. CMAS deposits accelerate the spallation failure of TBCs. After 210 thermal cycles at 1200℃, about 8 μm interaction layer is formed between CMAS and zirconia ceramic layer, which is mainly due to the inward diffusion of Ca²⁺ from the CMAS deposits. A large number of transverse cracks are generated in the ceramic layer of TBCs with CMAS deposits. The failure of TBCs occurs mainly by chipping spallation of the ceramic layer.
- TBCs /
- thermal cycling /
- CMAS /
- interaction zone /
- failure