Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis
Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis
复制标题
基于有限元分析的燃气轮机叶片热障涂层厚度设计
DOI：
10.1155/2017/2147830
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发表时间：
2017-01-01
影响因子：
--
通讯作者：
Jiang, Peng
中科院分区：
文献类型：
--
作者：
Li, Biao;Fan, Xueling;Jiang, Peng
Thermal barrier coatings (TBCs) are deposited on the turbine blade to reduce the temperature of underlying substrate, as well as providing protection against the oxidation and hot corrosion from high temperature gas. Optimal ceramic top-coat thickness distribution on the blade can improve the performance and efficiency of the coatings. Design of the coatings thickness is a multiobjective optimization problem due to the conflicts among objectives of high thermal insulation performance, long operation durability, and low fabrication cost. This work developed a procedure for designing the TBCs thickness distribution for the gas turbine blade. Three-dimensional finite element models were built and analyzed, and weighted-sum approach was employed to solve the multiobjective optimization problem herein. Suitable multiregion top-coat thickness distribution scheme was designed with the considerations of manufacturing accuracy, productivity, and fabrication cost.
