Experimental Study of the Influence of a Deposition Technology on the Structure and Properties of a Thermal Barrier Coating on Gas Turbine Engine Blades

The influence of a deposition technology on the structure and properties of a ceramic coating on a turbine blade is studied. The proposed technical solution of satellite rotation of a blade relative to a vapor flow is found to increase the uniformity of the coating thickness and to form a thermal barrier layer on the turbine blade platform. The microstructure of the thermal barrier coating layer around the perimeter of the blade airfoil is investigated.