DESIGN AND ANALYSIS OF THERMAL BARRIER COATING ON GASTURBINE BLADE

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 multi-objective 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 of 100μm to 500μm for the gas turbine blade. The base material of blade geometry is created using Nickel alloy and its coating material is selected as partially stabilized zirconia. Three-dimensional finite element models were built using CATIA and analyzed by ANSYS WORKBENCH, and weighted-sum approach was employed to solve the multi objective optimization problem herein. Suitable multi region top-coat thickness distribution scheme was designed with the considerations of manufacturing accuracy, productivity, and fabrication cost.

Keywords: Thermal Barrier Coatings; Oxidation; corrosion; Ceramic Top-coat thickness; Durability; Low fabrication co