Abstract: A gas turbine engine for an aircraft having a core flow channel is described. Compressed air from the core flow channel can be conducted via a line through a core region radially outward into an outer jacket region. The core region is arranged radially at the outside on the core flow channel and is separated therefrom. The core region and the jacket region are separated from one another by a wall. The line is led sealingly through the wall. That part of the line which runs through the core region is completely surrounded by a further line. The lines delimit a gap space which extends in an axial direction and in a circumferential direction of the lines. The gap space is operatively connected to the jacket region and is sealed off with respect to the core region.

Abstract: Accessories are mounted to a gas turbine engine from a frame attached to a pylon which is used to mount the engine to an airframe. The frame independently mounts the accessories so that engine vibrations are not transmitted to the accessories.