Abstract: The invention relates to a device (50) for centering a movable structure (4) on a stationary structure (5) of a nacelle, comprising: a centering pin (52) mounted on a pin holder (54) attached onto the movable structure (4) or onto the stationary structure (5), the centering pin (52) having a central axis (56) and a receiving bore (60) mounted onto a bore holder (62) attached onto the stationary structure (5) or onto the movable structure (4), said receiving bore (60) being capable of receiving at least the centering pin (52), characterized in that the centering device (50) also comprises a movable interface system, capable of overlapping the central axis (56) of the centering pin (52) and the central axis of said interface system or of the receiving bore (60) and capable of receiving said centering pin (52) in a central opening, and a locking means capable of locking said interface system. The invention also relates to a nacelle including such a device (50).

Abstract: A nacelle includes a central structure intended to surround a fan of a turbojet engine and an air intake structure attached to the central structure and able to channel a flow of air toward the fan. The nacelle includes at least one longitudinal outer panel incorporating an air intake lip. An inner panel includes an acoustic shell ring which downstream end is attached to an upstream end of the central structure and therewith forms a fixed structure of the nacelle. Guide means are entirely attached to the central structure for guiding the outer panel or panels and allowing substantially rectilinear movement of the outer panel towards the upstream end of the nacelle so that the air intake structure can be opened.

Abstract: The present invention relates to a nacelle rear assembly (1) including a pod-shaped internal structure (11), said internal structure comprising at least one downstream portion (15) and one upstream portion (13) that are each movably mounted between an operative position, in which said portions are connected, and at least one maintenance position, in which said portions are separate from each other, the downstream portion being movably mounted by means of sliding while the upstream portion is movable by opening at least one door. The downstream portion and upstream portion are provided with a connection means that is capable of engaging therebetween. Said assembly is characterized in that at least one of the downstream and upstream portions is provided with a hinging means (131, 151) having a range of movement in at least one direction so as to enable stress-free control and operation of the portion in question.

Abstract: The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterised in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.

Abstract: The invention relates to an assembly for holding the interface of a stationary outer structure (15) of a nacelle (3) and housing (27) of a jet engine (5), said assembly including: a first raised element belonging to the upstream end of the stationary outer structure (15); a second raised element belonging to the downstream end of the housing (27), said first and second raised elements being formed so as to be placed in contact with each other; two half-rings (109) formed by a wall defining a recess that is formed so as to receive the first and second raised elements when the housing (27) and the stationary outer structure (15) are mounted edge to edge; and an abutment means formed so as to keep the first and second raised elements in the recess.

Abstract: The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.

Abstract: The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) including 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 includes at least one electric heating element (14) situated between the inner skin and the outer skin and capable of being connected to an electric supply (15, 16), and the 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 present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure (5) comprising a casing (9) designed to encircle said fan, with the air inlet structure attached to it, said structure having a peripheral inside surface at least partly equipped with a sound-attenuating structure (13) extending without geometrical interruption around at least part of the casing, said structure being characterized in that a gap (14) is provided between the sound-attenuating structure and the casing.

Abstract: The invention relates to a structuring assembly (13) for an exhaust nozzle, including the following main elements: (a) an outer skin (22) including a non-acoustic portion (33); (b) an inner structuring skin (23); (c) an acoustic structure (21) including cells (27) having a cellular core, said acoustic structure being arranged between the outer skin (22) and the inner structuring skin (23), at least one of said main elements being made of a composite material, and the acoustic structure (21) being supported between the outer skin (22) and inner structuring skin (23) by linking means (31; 41) attached to the inner structuring skin (23) and to the non-acoustic portion (33) of the outer skin (22) so as to transfer the stresses onto the inner structuring skin (23) and the non-acoustic portion (33) of the outer skin (22). The invention also relates to an exhaust nozzle for a nacelle, comprising such a structuring assembly (13), as well as to a nacelle.

Abstract: The present invention relates to a thrust reversal device (1) for a turbojet engine nacelle, characterized in that: (i) the movable cowl (3) is provided with at least one driving lead screw (30) having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means (31) of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting (32, 35, 36) the rotational movement thereof towards at least one drive system (33, 34, 25) of the flap.

Abstract: The invention relates to a device (50) for centering a movable structure (4) on a stationary structure (5) of a nacelle, comprising: a centering pin (52) mounted on a pin holder (54) attached onto the movable structure (4) or onto the stationary structure (5), the centering pin (52) having a central axis (56) and a receiving bore (60) mounted onto a bore holder (62) attached onto the stationary structure (5) or onto the movable structure (4), said receiving bore (60) being capable of receiving at least the centering pin (52), characterized in that the centering device (50) also comprises a movable interface system, capable of overlapping the central axis (56) of the centering pin (52) and the central axis of said interface system or of the receiving bore (60) and capable of receiving said centering pin (52) in a central opening, and a locking means capable of locking said interface system. The invention also relates to a nacelle including such a device (50).

Abstract: The invention relates to a thrust reversing device (20) that includes at least one mobile cowling (30) mounted in translation in a direction substantially parallel to a longitudinal axis of a nacelle, capable of moving alternatively from a closing position on which it enables the aerodynamic continuity of the nacelle into an opening position in which it opens a passage in the nacelle for the bypassed flow, wherein said mobile cowling (30) also includes as an extension at least one variable nozzle section (40) including at least one panel (41) mounted so as to be capable of rotation, the panel (41) being adapted for pivoting towards at least one position entailing a variation in the nozzle section (40) on the one hand, and pivoting towards a position in which it blocks a cold flow jet (13) formed between a fixed structure of a turbojet fairing (12 and the nacelle on the other hand, wherein the mobile cowling (30) and the panel (41) are associated with actuation means (50) capable of activating the respective t

Abstract: The invention relates to a thrust reverser (1) for the nacelle of a dual-flow turbine engine, in which the bypass means (4) and the actuation jacks (22) of the sliding cowling (2) and of the reverse flaps (20) are arranged in two substantially parallel planes arranged above one another in the radial direction of the nacelle. The invention also relates to a nacelle for a dual-flow turbine engine that comprises such a thrust reverser.

Abstract: The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).

Abstract: The present invention relates to an attachment structure (1) for attaching a turbojet engine (2) to a fixed structure of an airplane via an attachment pylon, characterized in that it comprises a one-piece box section intended to extend at least partially on each side of a fan casing (3) of the turbojet engine about a substantially longitudinal axis thereof and comprising, on the one hand, means of attachment to the pylon and, on the other hand, means of attachment of the engine (4) which are positioned on the box section on each side of a substantially longitudinal axis of the turbojet engine and are intended to be connected to part of the turbojet engine in such a way as to react the forces applied thereto.

Abstract: The present invention relates to a locking system (20) for a movable lateral cowl (8) of a turbine engine nacelle intended to be connected to a pylon (4) of an aircraft, comprising, on the one hand, a clevis (21) intended to be connected to the pylon, and, on the other hand, a rod (22) intended to be mounted on the movable cowl and capable of engaging with the clevis when the movable cowl is in the closed position, characterized in that the rod is mounted so that it can move translationally along a substantially longitudinal axis of the movable cowl so as to form a slider which can shift between a locked position, in which it is engaged with the clevis and provides a structural connection between the pylon and the movable cowl, and an unlocked position, in which it is disengaged from the clevis and allows the movable cowl to be opened.

Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai

Abstract: The invention relates to a suspension assembly for an aircraft turbojet engine (3), including a pylon (1) up and connected to the pylon (1), and connecting rods (13a, 13b) for taking up the thrust of the turbojet engine (3) remarkable in that the assembly includes means (19a, 19b; 25) separate from said pylon for thermally insulating the connecting rods (13a, 13b) from the turbojet engine (3).

Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.

Abstract: The invention relates to a method for making an acoustic attenuation panel, comprising using at least one foam block (1), coating at least the acoustic surface of said foam block (1) with a fresh composite material (9), and making perforations (27; 27a, 27b, 27c, 27d, 27e) in the resulting coating.