G. ERDOGAN, Sakarya University, Sakarya, Turkey
Thermal barrier coatings (TBCs) are used in gas turbines and aerospace engines to prevent high engines metallic section at high temperatures. Additionally, TBCs increases the gas turbines engines efficiency by increasing combustion temperature while substrate temperature is stationary. Present thermal barrier coatings; generally consist a bond coat and a partially stabilized zirconia (ZrO2 + %8 Y2O3) top coat onto a nickel based super alloy. In gas turbine’s combustion chambers, TBCs are eroded result of consistently impacting combustion product and dust which comes from atmosphere.ZrO2 + %8 Y2O3 and a MCrAlY bond coat system has selected for investigation. Coating produced by using two different spraying guns. Erosion tests performed at 900°C and 25°,50°, 90° degrees. After erosion tests coatings are characterized by using SEM, Optical Microscope and AFM.
Summary: High temprature erosion behaviour is investigated for thermal barrier coatings produced different plasma gun.
