热障涂层
材料科学
复合材料
立方氧化锆
陶瓷
图层(电子)
熔点
热导率
保温
涂层
胶粘剂
涡轮叶片
热的
涡轮机
机械工程
气象学
工程类
物理
出处
期刊:Elsevier eBooks
[Elsevier]
日期:2007-01-01
卷期号:: 155-232
被引量:31
标识
DOI:10.1016/b978-075068252-7/50008-1
摘要
This chapter elaborates the different aspects of thermal barrier coatings (TBCs). The function of TBC is to reduce the component temperatures, thereby increasing life. TBCs are generally a combination of multiple layers of coatings with each layer having a specific function and requirement. The topmost layer provides thermal insulation and consists of a ceramic, with low thermal conductivity, typically ZrO2, known as zirconia. The extent of the temperature reduction by TBCs has been assessed in gas turbine engines by conducting engine tests. Temperatures measured on turbine blades coated with TBC were compared with those measured on blades with metallic coatings only. This level of temperature reduction results in a several fold extension of the life of the component. In gas turbines, the TBC surface may be exposed to hot gases with temperatures in excess of 3000°F. In order to survive such environments without melting, the ceramic top coat of the TBC should also have a high melting point. It is found that coatings based on zirconia can only be deposited by processes capable of adding enough energy to the raw materials to melt, evaporate, or chemically fragment to dimensions that can be deposited with adequate cohesive and adhesive strength.
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