TURBINE VANE OF A GAS TURBINE

摘要

The invention relates to a vane (10) of a gas turbine, especially a gas t urbine aircraft engine, comprising a base body (11) provided with an outer s urface forming a suction side (13) and a pressure side (12), said outer surf ace of the base body being at least partially coated with a heat insulating layer (16). According to the invention, the heat insulating layer (16) exten ds continuously at least mostly over the suction side (13) and mostly over t he pressure side (12) of the surface of the base body (11) of the vane, the layer thickness of the heat insulating layer (16) being variable.