Abstract: The invention relates to an overpressure hatch (21) intended to be mounted on a wall (23) of a nacelle (1) for a turbojet engine (5), the overpressure hatch (21) comprising a support (22) intended to be fixed to the wall (23), and at least one discharge element (25) able to move with respect to said support (22), said hatch (21) comprising at least one part (27) of lower mechanical strength than the remainder of the overpressure hatch (21) so that air at an overpressure inside the nacelle (1) can be discharged when the internal pressure applied to said hatch (21) more or less reaches a threshold pressure level lower than the maximum pressure that the nacelle structure can withstand. The invention also relates to a turbojet engine nacelle comprising at least one hatch (21) according to the invention.

Abstract: The invention relates to a nacelle (1) for a turbojet engine (8) comprising: an air intake structure (4) able to channel a flow of air towards a fan (7) of the turbojet engine (8), comprising an air intake lip (21) upstream of the nacelle (1) and attached at its ends to an outer panel (25) and an inner panel (23); a central structure (5) intended to surround said fan (7) and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity, said central structure (5) comprising a secondary, or bypass, flow path outer ring section (11) intended to surround the engine and a central outer cowl (13), and a downstream section (6), the outer panel (25) comprising a moving part (25a) attached to the air intake lip (21) and extending downstream of the inner panel (23) and at least one fixed part (25b) fixed to the central structure (5) or to the downstream section (6) and intended to nest together with the moving part (25a) through their having complementary shapes.

Abstract: Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inn

Abstract: The invention relates to a nacelle comprising an air intake structure (1) able to channel a flow of air towards a fan of the turbojet engine, said structure (1) comprising at least one inner panel (11) and one outer panel (10), the outer panel (10) being able to be moved by guide means (30) so as to open up the air intake structure (1), characterized in that it further comprises means (40, 60) for protecting the inner panel (11) against fire, said means being able to be moved in whole or in part when the air intake structure (1) is opened.

Abstract: The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer panel (40), at least one inner panel (41) and an air intake lip (4a) having an inner wall (70) to be in contact with the air flow flowing into the turbine engine and a partition (45) separating the air intake lip (4a) from the rest of the nacelle, the air intake lip (4a) having an extension (60) that can be fastened onto the inner panel (41) and that extends substantially as a continuation of the inner wall (70) towards the downstream side of the air intake structure over a length (I) at least equal to about the maximum distance (d) between the partition (45) and the air intake lip (4a). The invention also relates to a nacelle for a turbine engine comprising such an air intake structure (4).

Abstract: The invention relates to a nacelle (1) for a turbojet engine, comprising: —an air intake structure able to channel a flow of air towards a fan of the turbojet engine and comprising at least one longitudinal outer panel (40) incorporating an air intake lip (4a), —a middle structure (5) intended to surround the said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, —at least one inner panel (41) comprising an acoustic shroud (53), fixed at its downstream end to an upstream end of the middle structure (5) forming therewith a fixed structure of the nacelle (1), and —means (15) of guiding the outer panel or panels (40) which means are able to allow a substantially rectilinear movement of the outer panel (40) in the upstream direction of the nacelle (1) so as to be able to open the air intake structure, the said nacelle (1) comprising reinforcing means (90) designed to react the mechanical loads of the guide means (15) beyond a predetermined deformation thereof

Abstract: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

Abstract: The invention relates to a nacelle that comprises a fixed structure (20), a nozzle with a variable section, and a cowling (30) mounted on said fixed structure (20) so as to be capable of sliding particularly along a travel so as to modify the section of said nozzle, characterised in that the nacelle further comprises an aerodynamic continuity assembly (40) provided between the fixed structure (20) and the mobile cowling (30), said assembly (40) including an elastic means that can be compressed between the fixed structure and said mobile cowling when the cowling is in the upstream portion of the travel thereof and that can expand when the cowling is in the downstream portion of the travel thereof so as to ensure the aerodynamic continuity of the lines between said fixed structure (20) and said mobile cowling (30).

Abstract: This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said second component (3), and the assembly being noteworthy in that said connecting device (19) comprises a structural skin (21) fixed to said first component (9) and a porous material (23) attached to this structural skin and fixed by contact to said second component (3).

Abstract: This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin (1) and, by way of acoustic absorption material, a porous material (5) attached to this skin (1).

Abstract: The invention relates to a method for making a deicing system on a panel (22) of a nacelle comprising an outer skin (24) having at least one hole and an inner skin (26), characterized in that it comprises the following steps: A. a grid of resistive elements is positioned on the outer skin (24) with respect to the hole(s) by a positioning means; B. the grid of resistive elements is applied by an application means to the location determined in step A to form the deicing system; C. a surface coating is applied to the resulting deicing system. The present invention also relates to an air inlet lip and to a nacelle comprising a deicing system produced by such method.

Abstract: The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and an inner skin (13), designed to be oriented towards the inside of the lip, characterized in that it comprises at least one electric heating element (14) situated between the inner skin and the outer skin and capable of being connected to electric supply means (15, 16), at least one electric heating element extending at least partly through an acoustic attenuation zone having perforations (11) passing through the structure and associated with an acoustic attenuation structure (30) fitted to the inner skin.

Abstract: The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).

Abstract: This aircraft engine nacelle air intake assembly comprises an air intake structure comprising an air intake lip (7) and an acoustic shroud (5) extending downstream of this air intake lip (7) and designed to be mounted on a fixed structure (2), the said air intake structure being designed to be able to move with respect to the said fixed structure (2) between an operating position in which the said lip (7) is in contact with the said shroud (5), and a maintenance position in which the said lip (7) is set apart in the upstream direction away from the said shroud (5). This assembly is notable in that it comprises runway means (19) designed to centre this lip (7) with respect to this shroud (5).

Abstract: The present invention relates to a casing (5) for a rotor of a turbomachine, more particularly for a fan (1) of a turbojet engine (2), comprising a peripheral shroud (6) designed to form a clamping collar around the casing, characterized in that the shroud has at least one fitting (12, 13) or flange for the attachment of equipment.

Abstract: This propulsion unit for an aircraft comprises: a fan (3) comprising a fan casing (23) the interior wall of which has a coating (25) the upstream edge of which is set back relative to the upstream edge (29) of the said casing (23), and an air intake assembly (A) comprising an air intake structure (1) comprising an air intake lip (7) and an acoustic shroud (11) extending between this air intake lip (7) and the upstream edge of the said coating (25). The said shroud (11) is connected to the said casing (23) simply by nesting inside this casing (23), this nesting possibly being supplemented by discrete means of connection between these two elements (11, 23).

Abstract: The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off.

Abstract: The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl (6) mounted such that it can move in translation in a direction substantially parallel to a longitudinal axis of the nacelle and able to move alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers deflection means (70) and an open position in which it opens a passage in the nacelle and uncovers the deflection means, the said moving cowl also being extended by at least one nozzle section (7) mounted at a downstream end of the said moving cowl, characterized in that the nozzle section comprises at least one panel (10) mounted such that it can rotate about at least one pivot about an axis substantially perpendicular to a longitudinal axis of the nacelle, the said panel further being connected to a fixed fairing structure (2) of the turbojet engine by at least one link rod (11) mounted such that it can rotate

Abstract: The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided with peripheral locking means including at least one locking means (10) attached to the inner panel or to the air intake lip and each capable of interacting with an additional retaining means (11) respectively attached to the air intake lip or to the inner panel.

Abstract: The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition (108) defining, with the external wall, a deicing compartment (103) in the said lip and comprising an orifice, —a hot air supply device (105) intended to supply the deicing compartment (103) with hot air, the said device (105) comprising a hot air supply tube (107) and a peripheral sealing element (109) surrounding the said supply tube (107), the hot air supply tube (107) having an elbowed free end (111), the orifice (113) in the upstream partition being configured to allow the free end (111) to pass along the main axis (115) of the supply tube, and the sealing element (109) comprising a contact plate (121) surrounding the said tube (107) so as to provide sealing at the upstream partition (108).