A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl , each fan cowl comprising a hinged end and a closing end , each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.

A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl , each fan cowl comprising a hinged end and a closing end , each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.

Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.

Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.

A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.

An aircraft having a wing and an aeroengine having a longitudinal main axis M and including a ducted nacelle with at least one fan, the wing including an acoustic treatment surface on a bottom portion of its outer shell on either side of the main longitudinal axis M and over a width L perpendicular to the longitudinal axis M that is not greater than three times the diameter D of the fan, the acoustic treatment surface comprising a layer of porous material for attenuating acoustic waves coming from the fan.

An aircraft having a wing and an aeroengine having a longitudinal main axis M and including a ducted nacelle with at least one fan, the wing including an acoustic treatment surface on a bottom portion of its outer shell on either side of the main longitudinal axis M and over a width L perpendicular to the longitudinal axis M that is not greater than three times the diameter D of the fan, the acoustic treatment surface comprising a layer of porous material for attenuating acoustic waves coming from the fan.

An acoustic panel for an aircraft nacelle includes a cellular layer configured to trap noise, a backplate fixed to one surface of the cellular layer and a facesheet fixed to another, opposite, surface of the cellular layer. The facesheet includes a layer of a preimpregnated woven material containing weft yarns spaced apart from one another and warp yarns spaced apart from one another so that the facesheet exhibits openings between the yarns.