Abstract: Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.

Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.

Abstract: 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.

Abstract: The present disclosure concerns a method for manufacturing a composite panel including a cellular central core interposed between two skins. The manufacturing method includes the steps of manufacture of an element with a cellular structure comprising a cellular core structure interposed between two layers of structural plies intended to form the skins, positioning of the element with a cellular structure within a mold, formation of drains on either side of the cellular core structure, infusion of the element with a cellular structure so as to impregnate it with a resin, carrying out a draining of the resin through the drains in the element with a cellular structure during the infusion step, the drains having a geometry configured to provide draining, and polymerization of the impregnated element with a cellular structure to form the composite panel.

Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

Abstract: An exterior nozzle member for a turbomachine extending along an axis oriented from upstream to downstream and comprising a primary duct configured to conduct a primary flow, an annular cavity of axis and a turbine, said exterior nozzle member comprising: an acoustic attenuation panel formed by an acoustic attenuation structure on which there are mounted an interior wall and an exterior wall facing the primary duct and the annular cavity, respectively, a nozzle flange connected to the panel and comprising an upstream end configured to be connected to a turbine casing flange and a sealing member connected to the panel and comprising an interior longitudinal branch extending radially inside the nozzle flange in order to thermally protect it from the primary flow, the nozzle flange being made of a first material and the sealing member being made of a second material, the first material having a coefficient of thermal expansion greater than that of the second material.

Abstract: A system for cooling a compartment for equipment in a nacelle having a member for drawing a cooling flow and a device for admitting the cooling flow into the compartment, having: a regulating member movably mounted with the ability to move in a first direction of movement limiting the admission when the internal pressure of the compartment is below the external pressure, and in a second direction of movement increasing the admission when the internal pressure is above the external pressure; a return member configured to keep the regulating member in a neutral open position and to damp the movement of the regulating member during modifications in the ratio of the pressures; a pressing member activated by a heat-sensitive element and configured to move the regulating number into a closed position so as to isolate the compartment in the event of fire.

Abstract: An air inlet into a nacelle of an aircraft turbojet engine having a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall and an outer wall which are connected by a leading edge, the inner wall having a plurality of air delivery lines, each air delivery line having a plurality of through-holes designed to blow elementary streams from the hot air source in order to de-ice said inner wall, the air delivery lines being parallel to one another in a cylindrical projection plane, each air delivery line having a depth P3 defined along the axis X as well as a length L3 defined along the axis Y in the cylindrical projection plane, two adjacent air delivery lines being spaced apart by a distance D3, each position along the axis Y with no more than one through-hole, the ratio of the distances L3/D3 being between 0.8 and 1.

Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

Abstract: A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.

Abstract: A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.

Abstract: The disclosure relates to a method for manufacturing an air intake lip comprising: the arrangement of a blank facing a three-dimensional forming surface of a die of a hydroforming tool, the forming of an air intake lip preform by hydroforming the blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape, the outer wall of the air intake lip comprising at least one hollow housing with an inturned edge and a bottom, the housing having a shape corresponding to the shape of the at least one opening cavity, the cutting of an opening in each hollow housing keeping at least the inturned edge so as to obtain an air intake lip comprising at least one opening having an edge integrally formed with the outer wall of the lip.

Abstract: A de-icing device for an air intake of an aircraft jet engine nacelle extending along an axis in which a flow of air flows from upstream to downstream, the intake comprising an inner wall and an outer wall connected by a leading edge, the inner wall comprising a plurality of blowing lines, each blowing line comprising a plurality of through-openings configured to blow elementary streams from the hot air source in order to de-ice said inner wall, the blowing lines being parallel to one another in a cylindrical projection plane, each blowing line having a depth defined along the axis X and a length defined along the axis Y in the cylindrical projection plane, two adjacent blowing lines being spaced apart by a distance, the ratio of the distances L3/D3 being between 1 and 2.

Abstract: An acoustic treatment device for an aircraft turbojet engine nacelle forms an annular ring including several sections, each section having a sound absorption structure, an outer skin and two lateral skins attached to the inner air inlet shroud of such a nacelle by fasteners, and the sections being connected to each other by battens.

Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.

Abstract: The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

Abstract: An aircraft propulsion assembly includes a turbine engine surrounded by a nacelle with an annular air-intake lip extending around the turbine engine by two annular walls, inner and outer, respectively, intended for being swept across by air flows at least when the aircraft is in flight. The inner and outer walls each includes or supports at least one network of pipes forming heat exchangers. The inner wall pipe network having liquid outlet connected with a liquid intake of the outer wall pipe network. The propulsion assembly further includes means for circulating the liquid, connected to at least one liquid intake of the network of pipes of the inner wall.

Abstract: A method for manufacturing a cellular core for an acoustic panel is provided. The cellular core includes at least one plurality of acoustic cells and a plurality of de-icing channels that extend longitudinally, each de-icing channel being transversely interposed between two successive cells, and the de-icing channels being adapted to channel a de-icing fluid. A manufacturing step includes producing the acoustic cells and the de-icing channels as a single piece such that the cellular core manufactured during the manufacturing step forms a monolithic part.

Abstract: An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.