Research Article
Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis
Figure 12
Thermal stress fields of the blade using design scheme : (a) pressure side of top-coat, (b) suction side of top-coat, (c) pressure side of the substrate, and (d) suction side of the substrate.
(a) |
(b) |
(c) |
(d) |