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: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Abstract: A locking device includes a bolt capable of engaging with a corresponding hook, the bolt being mounted against a resilient return spring that tends to return the bolt into a spaced apart position. The locking device further includes a detection linkage, which is moveable between a first position and a second position. In the first position, the linkage enables unlocking of the bolt and the hook. In the second position, the linkage engages with a portion of the locking pair so as to block the unlocking.

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 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: The invention concerns a fixing system for at least one component of a pod of a turbojet on an engine strut to which the pod is attached and comprising at least one coupling zone provided by the component capable of co-operating with at least one complimentary coupling zone provided by the strut, and fixing means for providing with complementary fixing means a rigid and detachable connection between said component and the strut. The invention is wherein the fixing means and the complementary fixing means are capable of slightly pivoting relative to each other, as well as relative to a corresponding pod.

Abstract: An air intake of a turbofan engine, capable of being fixed at the front of an engine casing enclosing the fan. The air intake includes an annular inner wall, an annular outer cowl radially spaced apart from the inner wall and of the outer cowl, a front annular partition linking downstream ends of the inner wall and of the outer cowl, a rear annular flange located in an extension of the inner wall to fix the air intake in front of the engine casing, and a front annular lip that forms with the front partition an annular de-icing chamber capable of being connected to a defrosting system. The air intake is made in at least two separable parts. The separation plane of the two parts passes outside the de-icing chamber, the inner wall, and the rear flange, and cuts out a dome in the outer cowl and a crescent with rectilinear edge in the rear partition.

Abstract: A backup locking system for a thrust reverser door comprises a catch pivotally mounted by a pivot pin to a fixed structure of the thrust reverser. A hook with a self-locking profile is provided at the free end of said catch for cooperation with a locking interface on the door in the event of failure of the normal locking systems. At its other end remote from said hook, the catch has a heel ending in a part-cylindrical surface which is concentric with said pivot pin. The catch is urged against the locking interface by a piston rod which presses against a front face of said heel under the force of a spring acting on a piston to which said piston rod is attached. When the rod is retracted, a double lever positively moves the catch toward a minimum opening angle, at which point the door can be opened. An unlocking spring causes the full opening of the catch to maximum open position when an opening lever is released.

Abstract: The invention concerns an air intake of a turbofan engine, capable of being fixed at the front of an engine casing enclosing said fan, and comprising an annular inner wall (6), an annular outer cowl (5) radially spaced apart from the inner wall (6), an annular rear wall (2) linking the upstream ends of the inner wall (6) and of the outer cowl (5), a front annular partition linking the downstream ends of the inner wall (6) and of the outer cowl (5), a rear annular flange (1) located in the extension of the inner wall (6) and designed to fix said air intake in front of the engine casing and a front annular lip (4) which forms with the front partition an annular de-icing chamber capable of being connected to a defrosting system, said air intake being made in at least two separable parts.

Abstract: In a turbojet thrust reverser comprising, in an annular section of an outer cowling of the turbojet, a number of movable doors which, in an inactive position during operation in a forward thrust configuration, close off passages separating rigid spars of a fixed structure, there is provided, between two adjacent doors, a locking system which allows substantially simultaneous opening of the two doors. The locking system comprises, for each door, at least one hook mounted on the fixed structure so that it can be pivoted by an olive secured to the door between a door locking position and an unlocked position during opening or closing movement of the door. The two hooks of the locking system are rotationally interlinked by a mechanical linkage device, for example link rods, so as to prevent the unlocking of one door if the other door is closed.

Abstract: In a turbojet thrust reverser comprising, in an annular section of an outer cowling of the turbojet, a number of movable doors which, in an inactive position during operation in a forward thrust configuration, close off passages separating rigid spars of a fixed structure, there is provided, between two adjacent doors, a locking system which allows substantially simultaneous opening of said two doors. The locking system comprises, for each door, at least one hook mounted on said fixed structure so that it can be pivoted by an olive secured to said door between a door locking position and an unlocked position during opening or closing movement of the door. The two hooks of the locking system are rotationally interlinked by a mechanical linkage device, for example link rods, so as to prevent the unlocking of one door if the other door is closed.

Abstract: A conventional honeycomb structure is strengthened by intermediate membranes (13), which compartmentalize the cells (5) in the height-wise direction. Such a structure more particularly has an increased mechanical strength and high damping properties for Helmholtz resonators intended to trap sound waves arriving on the structure by a perforated face (1).

Abstract: A system is disclosed for closing a pivoting door thrust reverser pivotally attached to a jet engine cowling including a latch mechanism that is movably connected to the jet engine cowling and movable between a first position in which the latch grips a forward portion of the thrust reverser door when the forward portion of the thrust reverser door is a predetermined distance from the fully closed position and a second position in which the latch mechanism exerts a force on the thrust reverser door to urge the thrust reverser door to the fully closed position. In this manner, a relatively large closing torque is exerted on a forward portion of the thrust reverser door by the movable latch mechanism. Since the force is applied a relatively large distance from the pivot axis of the thrust reverser door, the requisite torque may be generated by actuator having a relatively low force.

Abstract: A thrust reverser for a turbojet engine comprising displaceable downstream baffles (2) which are integrated into the outer wall of the annular bypass-flow duct so as to form the downstream end of the exhaust nozzle of the turbojet engine during the operation of the turbojet engine in a forward-thrust mode is provided. When in a thrust-reversal mode, the downstream baffles (2) are positioned so as to deflect the bypass flow and obtain thrust reversal. The baffles (2) are pivotably mounted on stationary pivots (10) and have at least one associated displacement mechanism (6, 7) for driving the baffles (2). Each downstream baffle (2) has an associated displaceable inner panel (13). Each baffle (2) and the associated inner panel (13) are driven through different angular displacements by the at least one associated displacement mechanism (6, 7), which is common to the baffle (2) and the associated inner panel (13), to change between the forward-thrust mode and the thrust-reversal mode.

Abstract: A bypass turbojet-engine thrust reverser comprises at least one hollow, pivoting door (3) with an inner conduit (10), defined between an outer structure (4) of the door (3) and an inner structure (5) of the door (3), which guides flow through the door (3) when the door (3) is in a reverse thrust position. At least a downstream part of the outer structure (4) of the door (3) is independent of and displaceable relative to the inner structure (5) of the door (3) and is driven in a centrifugal direction relative to the inner structure (5) by a mechanical drive system such that a downstream exhaust cross-section (S2) of the inner conduit (10), which is less than an intake cross-section (S1) of the inner conduit (10) when the door (3) is in a forward thrust position, is at least equal to the intake cross-section (S1) when the door (3) is in the reverse thrust position.

Abstract: A bypass turbo-fan type turbojet-engine having a thrust reverser utilizing pivotally mounted bypass flow deflecting doors, each door having a movable, retractable spoiler at its upstream edge. A control actuator for driving each movable spoiler relative to a door is arranged to cause the spoiler to remain in a stowed retracted position during the initial motion of the door toward its open thrust reversed position and to begin to positively move the spoiler to its extended position into the deflected flow stream as the door nears its fully opened position, the spoiler being fully extended when the door is fully opened at its thrust reversed position.

Abstract: A thrust reverser for aircraft gas-turbine engines includes latch devices that display a tell-tale visible indication when thrust reverser shutters (doors, etc.) are ajar. A latch of the lock at least partly projects from a wall (13, 14) radially bounding the annular structure (12) of the thrust reverser (10) when the latch (37) is in the open mode.

Abstract: A turbojet-engine thrust reverser includes bypass flow deflectors (3) which in a forward thrust mode are retracted into a wall of the primary cowling (4) of the engine and which are driven by linear actuator (6) mounted inside the primary cowling (4) to form an annular flow-deflecting assembly aft of the outlet of the bypass flow duct for producing thrust reversal. Each deflector (3) is independently driven by an actuator (6) and a linkage element (9) into rotation about one or more displaceable pivots (12) which in turn is or are translated by at least one linear actuator along one or more longitudinal guide elements (10). Each actuator (6) is connected to a deflector at the downstream end of the deflector and drives the associated deflector downstream end in an upstream or forward direction, the guide elements extending in a fore and aft direction.

Abstract: A latching mechanism is disclosed for a jet engine thrust reverser having a thrust reverser door movably connected to an engine cowling with a reverse thrust opening, the thrust reverser door being movable between a forward thrust position, in which the thrust reverser door covers the reverse thrust opening, and a reverse thrust position, in which the reverse thrust opening is uncovered. The latching mechanism has a lock bar mounted on the thrust reverser door, the lock bar having a distal end, and a latch member pivotally located on the cowling, the latch member having a slot engaged by the distal end of the lock bar when the thrust reverser door is in the forward thrust position. The latch member is movable between a latched position, in which the latch member prevents disengagement of the distal end of the lock bar from the slot, so as to lock the thrust reverser door in the forward thrust position, and an unlatched position which permits disengagement of the distal end of the lock bar from the slot.

Abstract: A cell panel for thermal ventilation including a first wall having raised portions which define openings; a second wall; partition walls connected to the first and second walls and that define cells. The openings in the first wall are located upstream of an air flow flowing outside the first wall. The first wall may further include raised portions which define other openings located downstream of the air flow. The second wall may also include raised portions which define openings located downstream of the air flow. The partition walls may define communication holes between adjacent cells.