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Mathematical Problems in Engineering
Volume 2017, Article ID 2147830, 13 pages
https://doi.org/10.1155/2017/2147830
Research Article

Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis

1State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace Engineering, Xi’an Jiaotong University, Xi’an 710049, China
2Dongfang Steam Turbine Co., Ltd., Deyang 618000, China

Correspondence should be addressed to Xueling Fan; nc.ude.utjx.liam@gnileuxnaf

Received 8 May 2017; Accepted 5 June 2017; Published 6 July 2017

Academic Editor: Fabrizio Greco

Copyright © 2017 Biao Li et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

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.