A nacelle for a turbofan engine includes a fan case, an inner barrel and a nose lip generally concentrically disposed about an axis. The inner barrel projects forward from and is engaged to the fan case at a first split line. The nose lip is engaged to the inner barrel at a second split line, and extends substantially radially outward directly from the second split line, then substantially axially rearward to the fan cowl as one unitary piece.

A structural panel for an aircraft nacelle may comprise a core between a perforated skin and a septum. A plurality of dividing walls may extend between the septum and a backskin to define a plurality of cavities. Each cavity may be in fluid communication with a plurality of cells in the core through the septum. The cells and the cavities may attenuate noise.

A strip-form acoustic material, the strip having a length in a longitudinal direction, a width in a transverse direction, a thickness and axial ends. At least one of the axial ends of the strip, in an end portion of the length of the strip, the strip of material is folded in a substantially transverse plane.

A process for the production of an acoustic treatment panel that includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), as well as at least one channel that is bordered at least in part by a wall (32) that is secant with at least one wall of a cell of the alveolar structure (26), includes elevating the temperature of the wall (32) and the ends of the cells of the alveolar structure (26) and injecting a pressurized gas into the channel (30) so as to expand the wall (32) of the channel so as to flatten it against the ends of the cells of the alveolar structure (26) in such a way as to produce a weld by continuous diffusion between the ends of the walls of the cells of the alveolar structure (26) and the wall (32) of the channel (30).

A co-curable thermoset acoustic liner and method of forming the same includes a sound attenuating core having a plurality of core cells. An inner face sheet having a plurality of face sheet apertures is coupled to the core by an inner thermoset adhesive sheet, which has a plurality of adhesive sheet apertures. Each of the plurality of adhesive sheet apertures is aligned within a corresponding one of the plurality of face sheet apertures so that the plurality of core cells are placed in fluid communication with airflow over the inner face sheet to create a Single Degree of Freedom (SDOF) acoustic liner.

A structure ensuring acoustic attenuation of a flow of a first fluid and heat exchange between a first fluid and a second fluid. The structure includes a first wall which is perforated, a second wall, and a plurality of intermediate walls extending between the first wall and the second wall. For each intermediate wall, there is a pipe intended to receive the second fluid and inscribed within the intermediate wall. Such a structure makes it possible to optimally integrate the acoustic wave attenuation function and the heat exchange function.

An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.

An air intake for a nacelle of an aircraft engine includes a substantially cylindrical outer wall, a substantially cylindrical inner wall, a front lip, a front mounting flange, and a support structure. The front lip connects the substantially cylindrical inner wall and the substantially cylindrical outer wall. The front mounting flange is configured to cooperate with a rear flange of a wall of the aircraft engine forming a fan casing. The support structure comprises a lower end configured to be secured to the fan casing, by the rear flange, and an upper end in contact at least with a downstream portion of the outer wall. The support structure includes access apertures configured to be crossed by maintenance tools during operations of maintenance of the air intake.

An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.

An air intake for a nacelle for an aircraft engine includes a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, and at least one acoustic structure including acoustic cells. The acoustic structure is situated in the space delimited by the internal wall, the external wall and the front lip. The acoustic structure is an added part secured to the air intake. The acoustic cells of the acoustic structure are arranged facing a region of the internal wall or of the lip at a predetermined distance so that the acoustic cells of the acoustic structure are not in contact with the internal wall or the lip while providing an acoustic attenuation function.