A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells. Each cell includes an open radially inner end in fluid communication with an interior side of the nacelle, and an open radially outer end in fluid communication with an exterior side of the nacelle. Each open end of each cell defines a respective cross sectional area. The intake liner further comprises radially inner and outer facing sheets overlying a respective radially inner and outer open ends of the respective cell. Each facing sheet defines at least one aperture overlying at least one cell, an overlying portion of the respective aperture having a smaller cross sectional area than the respective open end of the respective cell.

A cavity system (300-600) is provided. The cavity system comprises a cavity (2) and a spoiler (304-604). The spoiler (304-604) comprises at least one plate (4) having a front surface and a rear surface, and an undulating edge. The spoiler (304-604) is positioned in the proximity of a leading edge (14) of the cavity (2), the leading edge (14) being relative to an actual or intended flow direction (3) of a fluid over the cavity (2), and the spoiler (304-604) is arranged with its longitudinal axis (1) perpendicular to or at an oblique angle to the actual or intended flow direction (3) such that the front surface faces towards the flow direction (3).

A body, a cavity located on the body, enabling to place ammunition and similar payloads therein, a rear wall which is the surface on which an airflow occurring with the movement of the body leaves the cavity, and a floor over which the airflow moves along the cavity is disclosed.

Propulsion assembly for an aircraft comprising a turbomachine having at least one rotating part rotating about an axis of rotation, an attachment strut, and a structural element carrying the turbomachine via the attachment strut, the rotating part being disposed upstream of the structural element and of the attachment strut such that an air jet emerging from the rotating part, in the wake of thereof, impacts the structural element and the attachment strut, a leading edge of the structural element and/or of said attachment strut locally comprising at least one acoustic attenuation device disposed at least partly in the wake of the rotating part, the acoustic attenuation device being a local modification of the structure and/or of the profile of the leading edge.

An air inlet device includes an inlet duct, a valve and at least one helical partition positioned within the inlet duct, the helical partition having an outer edge in contact with the inlet duct and delimiting at least one helical duct within the inlet duct. The helical partition serves to increase the distance travelled by an air flow entering the inlet duct before it reaches the valve in the closed state. An aircraft including at least one air inlet device of this kind is disclosed.

A cavity system (300-600) is provided. The cavity system comprises a cavity (2) and a spoiler (304-604). The spoiler (304-604) comprises at least one plate (4) having a front surface and a rear surface, and an undulating edge. The spoiler (304-604) is positioned in the proximity of a leading edge (14) of the cavity (2), the leading edge (14) being relative to an actual or intended flow direction (3) of a fluid over the cavity (2), and the spoiler (304-604) is arranged with its longitudinal axis (1) perpendicular to or at an oblique angle to the actual or intended flow direction (3) such that the front surface faces towards the flow direction (3).