An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the chine defined by an outer mold line of the chine.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the chine defined by an outer mold line of the chine.

An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.

A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.

A propulsion assembly for an aircraft, comprising a nacelle, a propulsion system housed in the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle delimited by a nozzle wall of the fairing, a fuel tank, a supply duct which connects the tank and the combustion chamber, and a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the nozzle and the colder fuel circulating in the supply duct by thermal radiation through the nozzle wall.

A propulsion assembly for an aircraft, comprising a nacelle, a propulsion system housed in the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle delimited by a nozzle wall of the fairing, a fuel tank, a supply duct which connects the tank and the combustion chamber, and a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the nozzle and the colder fuel circulating in the supply duct by thermal radiation through the nozzle wall.

A latch assembly includes a housing including a first housing portion and a second portion including. The latch assembly further includes a first latch member disposed within the first housing portion and configured for translation along the latch axis. The first latch member includes at least two rotatable arms configured to rotate between an arm retracted position and an arm extended position in which the at least two rotatable arms extend in a first direction away from the latch axis. The latch assembly further includes a second latch member disposed within the second housing portion and configured for translation along the latch axis. The second latch member includes a second latch member body including a base portion and at least one axially extending portion extending from the base portion in a second direction toward the interior surface of the lateral wall.

A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.