Flow channel for a gaseous medium and corresponding exhaust-gas liner of a gas turbine

The invention refers to a flow channel for a gaseous medium, especially a hot exhaust gas of a gas turbine, with improved aerodynamic characteristics. In such a flow channel, a constructionally simple and effective reduction of unwanted flow separations is achieved, even in the event of changing flow parameters, by its flow-guiding contours (12, 14, 17) being equipped with an array of dimples (18). A flow channel and an exhaust-gas liner of a gas turbine are provided.