Thermal Barrier Coatings (TBCs) are widely used in aeroand land-based gas turbines because of their ability to sustain high thermal gradients in the presence of adequate backside cooling. [1±3] A TBC system is hence used to protect the metallic components of the turbine hot parts from degradation at high temperatures, erosion, oxidation and corrosion phenomena. Four primary constituents, as listed below, comprise the TBC system and enable the above functions: ± the top-coat; i.e., the ceramic TBC, which is commonly manufactured using air plasma spray process and behaves as the thermal insulator;± the substrate materials, most commonly a superalloy, which sustains the structural loads;± n aluminum containing bond-coat (BC), usually MCrAlY where M represents Ni, Co or a combination of these two elements, located between the metallic substrate and the ceramic. The BC is usually manufactured using plasma spraying or flame spraying and provides oxidation protection to the substrate and behaves as a compliance layer due to the linear coefficient mismatch between the ceramic TBC layer and the substrate;± a thermally grown oxide (TGO), predominantly a-alumina, [4] that grows between the ceramic TBC and the BC during the initial thermal cycles of the system and plays a relevant role in the BC/TBC adhesion. [5±6] Besides corrosion occurring at high temperatures due to sulfur impurities in fuel, the two main damage mechanisms of TBC are: (i) the metal/ceramic thermal linear expansion mismatch during thermal cycling; (ii) the growth of the TGO which induces stresses into the ceramic top coat. This damage induces failure of the TBC system by spallation of the ceramic top coat.For advanced gas turbines, improvements of TBC properties would seek a higher life time, a lower thermal conductivity, a higher thermal stability and a lower surface roughness. These improvements are sought to decrease maintenance frequency and/or to increase efficiency by increasing gas temperatures at the combustion chamber outlet.One way to improve TBC properties consists in modifying the layer architecture by an alternative manufacturing process. To reach this goal, plasma spray processing has been combined with laser remelting in this study to alter the porecrack architecture of the TBC; and hence to modify the TBC
COMMUNICATIONSTable 1. Coating structural attributes (see literature [5] for details). structural attributes and physical characteristics as-sprayed in situ remelted (at 1.87 J.mm ±2 ) porosity level [%] 11 ± 0.3 17.2 ± 4.3 non-connected pores [%] 7 16 connected pores [%] 4 1 globular pores [%] 5 ± 0.2 13.3 ± 4.3 cracks [%] 6 ± 0.2 3.7 ± 0.2 vertical cracks [%] 30 ± 2 2 9 ± 1 horizontal cracks [%] 70 ± 2 7 1 ± 1 apparent thermal conductivity [W.m ±1 .K ±1 ] 1.4 ± 0.1 0.9 ± 0.1 phase tetragonal metastable (T¢)