Aerodynamically shaped support and/or cladding element in the bypass of a gas turbine engine

The element has a supporting structure radially extended between inner and outer walls of a bypass duct and including a front edge part (7) and a rear edge part (8). A connecting rod (9) connects the front and rear edge parts to form a recess that extends on two sides in a longitudinal direction of the supporting structure. A lining insert (11) is detachably attached with an aerodynamically-shaped outer contour by a fastener, and aligned with the front and rear edge parts. Cavities (14) are formed in the connecting rod for enclosing installations radially extended in the duct. The fastener is selected from a group consisting of a socket-head screw or countersunk screw and a plug-type connection. The lining insert is made of material that is lighter than that of the supporting structure with reduced sound reflection and sound-absorbing effect.