Aircraft gas turbine engine having a bleed channel in a guide vane root element of a bypass channel

The gas turbine has a core engine (10) which surrounds a bypass duct (29). A supercharger (30) is provided in the inlet region of the core engine. A discharge channel is provided for supplying flow of air from the supercharger in the bypass duct. A fan (12) is located downstream to the bypass duct provided with the guide vanes (32). A blade root of the guide vane is formed as the core engine superimposing structural element downstream and the bypass duct is made to open in the drainage channel.