Akademik Veri Yönetim Sistemi
Applied Surface Science, cilt.438, ss.96-113, 2018 (SCI-Expanded)
Thermal barrier coatings (TBCs) are mostly used in critical components of aircraft gas turbine engines. Hot corrosion is among the main deteriorating factors in TBCs which results from the effect of molten salt on the coating–gas interface. This type of corrosion is observed as a result of contamination accumulated during combustion processes. Fuels used in aviation industry generally contain impurities such as vanadium oxide (V 2 O 5 ) and sodium sulfate (Na 2 SO 4 ). These impurities damage turbines’ inlet at elevated temperatures because of chemical reaction. Yttria stabilized zirconia (YSZ) is a conventional top coating material for TBCs while Gd 2 Zr 2 O 7 is a new promising top coating material for TBCs. In this study, CoNiCrAlY metallic bond coat was deposited on Inconel 718 nickel based superalloy substrate material with a thickness about 100 μm using cold gas dynamic spray (CGDS) method. Production of TBCs were done with deposition of YSZ, Gd 2 Zr 2 O 7 , YSZ/Gd 2 Zr 2 O 7 ceramic top coating materials using EB-PVD method, having a total thickness of 300 μm. Hot corrosion behavior of YSZ, Gd 2 Zr 2 O 7 , YSZ/Gd 2 Zr 2 O 7 TBC systems were exposed to 45 wt.% Na 2 SO 4 and 55 wt.% V 2 O 5 molten salt mixtures at 1000 °C temperature. TBC samples were investigated and compared using scanning electron microscope (SEM), energy dispersive spectroscopy (EDS) analysis and X-ray diffractometer (XRD). The hot corrosion failure mechanisms of YSZ, Gd 2 Zr 2 O 7 and YSZ/Gd 2 Zr 2 O 7 TBCs in the molten salts were evaluated.