Thermal Barrier Coatings for Aeroengine Applications
Thermal Barrier Coatings for Aeroengine Applications
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DOI：
10.2514/1.20734
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发表时间：
2006-03
影响因子：
1.9
通讯作者：
B. Gleeson
中科院分区：
文献类型：
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作者：
B. Gleeson
热障涂层（tbc）在航空涡轮发动机热段的应用已有20多年的历史。最初的应用是由于需要抑制叶片翼型中过高的热梯度引起的部件退化。TBC本质上是一种分层的多材料结构，它必须承受恶劣的温度、环境、热循环和应力条件，以适应大量的飞机起飞和降落。介绍了目前使用的TBC材料系统，并总结了目前对TBC中材料和失效问题的理解。
Thermal barrier coatings (TBCs) have been in use in aeroturbine engine hot sections for over 20 years. The initial applications were driven by the need to suppress component degradation caused by excessive thermal gradients in vane airfoils. A TBC is essentially a layered, multimaterial structure that must withstand harsh temperature, environmental, thermal cycling, and stress conditions for an extended number of aircraft takeoffs and landings. A description of the TBC materials systems presently in use is presented, together with a summary of current understanding of materials and failure issues in TBCs.