Abstract: An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.

Abstract: An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.

Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.

Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.

Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

Abstract: A turbofan including a motor, nacelle and a secondary duct therebetween. The nacelle includes a fan casing with front and rear parts, a fixed assembly including a fixed structure and the front part, a mobile assembly with an openwork frame, a mobile cowl and the rear part and mobile between advanced and retracted positions in which a window is open between the secondary duct and the exterior of the nacelle, inner doors articulated between stowed and deployed positions, a first actuator for moving the frame and a second actuator for moving each inner door. The rear part is divided into outer flaps mobile between lowered and raised positions and is moved by an electric motor. A jet engine accordingly serves to increase retraction distance by freeing up part of the fan cowl and improve orientation of flow of air passing through the window by orienting the outer flaps.

Abstract: A locking system for locking a cowl to a fixed structure including first and second parts, the first part including a first hook moveable on the cowl and a first shaft fixed to the fixed structure in which the first hook is moveable between locked and unlocked positions, in which the second part includes a handle actuateable between closed and open positions, a second hook and a second shaft fixed to the fixed structure or to another cowl symmetric with the cowl, in which the second hook is moveable between locked and unlocked positions and in which the second hook is mounted where passage of the handle from the closed to open positions causes the second hook to pass from the locked into the unlocked position and vice versa, and in which the locking system also includes a transmission system to move the first hook from the locked into the unlocked position when the handle passes from the closed into the open position, and vice versa.

Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.

Abstract: A turbofan including a motor, nacelle and a secondary duct therebetween. The nacelle includes a fan casing with front and rear parts, a fixed assembly including a fixed structure and the front part, a mobile assembly with an openwork frame, a mobile cowl and the rear part and mobile between advanced and retracted positions in which a window is open between the secondary duct and the exterior of the nacelle, inner doors articulated between stowed and deployed positions, a first actuator for moving the frame and a second actuator for moving each inner door. The rear part is divided into outer flaps mobile between lowered and raised positions and is moved by an electric motor. A jet engine accordingly serves to increase retraction distance by freeing up part of the fan cowl and improve orientation of flow of air passing through the window by orienting the outer flaps.

Abstract: A locking system for locking a cowl to a fixed structure including first and second parts, the first part including a first hook moveable on the cowl and a first shaft fixed to the fixed structure in which the first hook is moveable between locked and unlocked positions, in which the second part includes a handle actuateable between closed and open positions, a second hook and a second shaft fixed to the fixed structure or to another cowl symmetric with the cowl, in which the second hook is moveable between locked and unlocked positions and in which the second hook is mounted where passage of the handle from the closed to open positions causes the second hook to pass from the locked into the unlocked position and vice versa, and in which the locking system also includes a transmission system to move the first hook from the locked into the unlocked position when the handle passes from the closed into the open position, and vice versa.

Abstract: A structure which absorbs low-frequency sound comprising a perforated skin, a box having two lateral walls in the shape of a strip, that delimit between them an opening, and a bottom opposite the opening connecting the two lateral walls, the lateral walls becoming closer together with increasing distance from the opening to the bottom. The box is attached to the skin at the opening. Each lateral wall extends width-wise between the opening and the bottom. Each box has two tongues, each tongue being strip shaped, extending lengthwise over an entire box length, and width-wise between the opening and the bottom of the box. Each tongue has a first end attached along an edge of the opening and a second, free end which extends towards the bottom, becoming closer to the second end of the other tongue, where each tongue has an arcuate shape along its length.

Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.

Abstract: A primary nozzle of a turbomachine primary exhaust duct, the primary nozzle comprising a microperforated first wall facing towards the inside and which widens from the front as far as an intermediate zone, a one-piece second wall comprising a microperforated internal part which extends rearward and in the continuity of the first wall from the intermediate zone and narrows from the intermediate zone rearwards, an external part which faces towards the outside around the internal part, and a fold connecting the rear parts of the internal part and of the external part, where the first wall and the internal part are fixed to one another, and a noise attenuating element fixed to the first wall and to the internal part.

Abstract: An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing.

Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.

Abstract: An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing.

Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.