0 Abstract

Thermal barrier coated high pressure turbine blades were characterized before and after the service by microstructural analysis and Cr³⁺ photostimulated luminescence piezo-spectroscopy. Thermal barrier coatings, in this study, consisted of electron beam physical vapor deposited yttria partially stabilized zirconia (YSZ; ZrO₂–8 wt.% Y₂O₃), vapor-deposited aluminide bond coat and Ni-base superalloy. Compressive residual stress in thermally grown oxide, measured by Cr³⁺ photostimulated luminescence piezo-spectroscopy, was observed to be in the order of 2.53.0 GPa and varied slightly as a function of substrate geometry. X-Ray diffraction and scanning electron microscopy equipped with energy dispersive X-ray spectroscopy were utilized to investigate the microstructural development of thermal barrier coatings. The as-deposited non-equilibrium tetragonal (t′) phase in the YSZ coatings was observed to decompose after the service, but the monoclinic (m) phase was only found in the YSZ coatings with concave substrate curvature on the pressure side of the HPT blade. Also, a significant sintering of ZrO₂–8 wt.% Y₂O₃ coating after the service was observed in the microstructure. Localized spallation of YSZ occurred within the thermally grown oxide (mostly α-Al₂O₃) and within the ZrO₂–8 wt.% Y₂O₃ coating for pressure and suction sides of the serviced high pressure turbine blade near the tip, respectively.

Author Keywords: Scanning electron microscopy; X-Ray diffraction; Thermal barrier coatings; Photostimulated luminescence spectroscopy; Turbine blade; Failure analysis