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 door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.
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 nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.
Abstract:
A turbofan having a nacelle comprising a slider being mobile in translation between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one being mobile in rotation on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade. The maneuvering system comprises, for each blade, a shaft being mobile in rotation on the slider and on which the blade is fixed, a toothed sector being fixed to the shaft, a toothed arc being mobile in rotation on the slider, and having a bearing face, a threaded rod mounted fixed on the fixed structure, a cam having a tapped hole screwed onto the threaded rod and mounted fixed in translation with respect to the slider, and a return arrangement that presses the bearing face against the cam outer surface.
Abstract:
An acoustic absorption structure comprising a plurality of resonators. Each resonator comprises a first chamber which has a first mouthpiece delimited by an edge pressed against an inner surface of a porous zone of a skin so that the first chamber and the skin delimit a first cavity, a second chamber, in which is positioned the first chamber, which delimits, with the first chamber, a second cavity, at least one acoustic orifice passing through the first chamber, at least one drainage orifice passing through the first chamber and at least one drainage hole passing the second chamber, each drainage orifice and each drainage hole being configured to limit an accumulation of fluid in the resonator. Also, an aircraft propulsive assembly or an aircraft comprising the acoustic absorption structure are provided.
Abstract:
A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation.