Abstract: A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.

Abstract: A device for representing the direction of action (9) of a working means (3), in particular a tool or a radiation source and/or a radiation emitter, for example, of X-rays is provided. The device includes a first light source (4) which is used to produce a first beam (5). In order to represent the direction of action in a continuous manner, at least one additional light source (4?) which is used to produce an additional beam (5?) is provided. The light sources (4, 4?) and the working device (3) can be oriented in such a manner that the first beam (5) and the additional beam (5?) have a flat extension and cut in the direction of action (9) of the working means (3). The invention also relates to a corresponding method.