Abstract: A turbojet-engine thrust reverser is provided with thrust reverser door assemblies each having a pivoting thrust reverser door (7). The thrust reverser door is connected to two pivots (22, 23) that rest on a support fitting (24) to constitute a structural frame that is attached to longitudinal beam cowling portions (20, 21) and a downstream cowling portion (3) of a stationary thrust-reverser structure in order to constitute a rigid assembly between the upstream and downstream cowling portions (4, 3). At least one primary mechanical lock (26) is placed on at least one longitudinal side of the door (7) and the interface loads of the lock (26) are absorbed by the beam cowling portions (20, 21).

Abstract: A thrust reverser for a turbojet engine is provided with at least one displaceable assembly including a displaceable cowling portion and a flap. The displaceable cowling portion and the flap each subtend stationary upstream and downstream cowling portions such that the displaceable cowling portion forms a portion of the external engine cowling covering a reverse thrust opening and the flap forms a portion of the outer boundary of the gas flow in a forward thrust position. In a reverse thrust position, the reverse thrust opening is uncovered, and the displaceable cowling portion and the flap are displaced downstream such that the displaceable cowling portion extends downstream, parallel to the longitudinal engine axis and above, without interference, the downstream cowling portion.

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 method for manufacturing a hollow component made of composite materials, in particular a hot-polymerizing resin/fiber composite. The component (1) comprises enclosing walls (3) which subtend at least one cavity (2).

Abstract: A turbojet-engine cowling combined with a thrust reverser comprising a large-displacement displaceable component (7) includes an electrically grounding mechanism for the displaceable component (7) when in its forward-thrust position. The grounding mechanism comprises an elastic device (20) dedicated to shunt the electric current away from any mechanical member used in the displacement without any displaceable connecting element.

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 turbojet-engine thrust-reverser comprising pivoting hollow doors (3) which in the forward-thrust mode are integrated into the external cowling of the turbojet-engine and which in the thrust-reversal mode constitute scoop-type flow-deflecting baffles. A displaceable external cowling panel (20) covers both the fore frame (8) of the stationary structure and the cross-section of the flow exhaust of the door (3) when in the forward-thrust mode. The external cowling panel (20) is pivotable on a panel pivot (24) situated downstream of the pivot (9) of the door (3) and its upstream edge moves radially outward to simultaneously clear a space above the fore frame (8) and the exhaust cross-section for the deflected flow.

Abstract: A turbojet-engine thrust reverser comprises a displaceable sub-assembly including two internal clamshells (12) mounted on stationary pivots (18) of a stationary structure (1) and an annular, axially displaceable structure (11). The displaceable structure forms the external, downstream part (13) of a cowling. In the forward-thrust mode, the displaceable structure forms a downstream portion (15) of a radial outer wall of the flow path and forms the entire trailing edge by covering the clamshells (12) such that the clamshells form part of the radial outer wall of the flow path.

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 thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having a plurality of lateral openings and a plurality of thrust reverser doors connected to the cowling so as to be movable between forward thrust positions and reverse thrust positions. The thrust reverser also includes a plurality of linear actuators, one linear actuator connected to the cowling and to each thrust reverser door so as to move the thrust reverser doors between their forward and reverse thrust positions.

Abstract: A soundproofing panel comprises a honeycomb core sandwiched between a solid skin and a porous skin, the cells of the honeycomb being divided in the direction of its thickness into at least two resonant cavities by a least one partition which is traversed by passages interlinking the cavities. The partitions are formed by a plurality of hollow microbeads having porous walls, the microbeads being bonded to one another and to the walls of the honeycomb at their points of contact. Such a soundproofing panel combines high performance in terms of linearity as a function of the level of sound excitation, attenuation band, bulk and mechanical strength.

Abstract: A turbojet-engine thrust reverser comprising at least one pivoting hollow door (3) which in the forward-thrust mode is integrated into the external cowling and which in the thrust-reversal mode constitutes a flow-deflecting obstacle by forming a scoop. A movable deflecting cascade (23) comprising vanes is combined with each door (3). The movable cascade (23) hinges about a pivot (24) and comprises at least one upstream portion forming a deflector (26) projecting, in the thrust-reversal mode of the door (3), beyond the outer surface of an outer panel (4) of this door (3) in such manner that any interference between the exhaust flow from the door (3) and the flow deflected to the outside of the door (3) is avoided.

Abstract: A thrust reverser for a turbo-fan type turbojet-engine includes hollow, scoop-type pivoting doors (3) which, in the forward-thrust mode, are integrated into the engine and fan cowling and which, in the reversed-thrust mode, constitute scoop type flow deflecting baffles. A movable upstream visor (23), when in the forward-thrust mode, is situated between the upstream edge of the door (3) and the fixed upstream structure (6) covering the downstream structure of the forward frame (8) of the thrust reverser. The control-driven upstream visor (23) pivots about a pivot mounted on the fixed thrust reverser structure and, in the thrust-reversal mode, uncovers the downstream edge of the structure of the forward frame structure (8) and presents an aerodynamic surface to guide the reverse-thrust flow.

Abstract: A ducted fan aircraft turbojet engine having an inner engine core cowling, an outer fan shroud, an outer fan outlet cowling including a thrust reverser, a fan exhaust duct between the inner engine core cowling and the outer fan outlet cowling, at least one fan shroud brace connecting the engine and the outer fan shroud, and at least one fairing element extending into and along the fan exhaust duct and located directly adjacent and rearwardly of the at least one fan shroud brace. The at least one fairing may be connected directly to the at least one fan shroud brace, the inner engine core cowling or the outer fan outlet cowling. The invention has utility where the fan outlet cowling and thrust reverser are mounted independently of the inner engine core cowling over their respective inner areas.

Abstract: The invention relates to a bypass turbojet engine having pivoting, hollow thrust reverser doors which, in the forward thrust configuration, are integrated into the external engine cowling and which, in the reverse thrust configuration, constitute scoop baffles that deflect exhaust air flow. A movable deflector baffle cooperates with each door such that, when the door is opened towards a thrust reversing direction, the baffle moves above an outer surface of the outer panel of the door in such a way that undesired interference between the exhaust flow moving through the door and the flow deflected by the outer surface of the door is minimized or avoided.

Abstract: An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort the annular thrust-reverser structure or to break its bracing components. An emergency locking system for such thrust reverser (35) each comprises a hinging latch (38) of which one end is in the form of a hook (40) partly enclosing the lock-interfacing mechanism (43) with the latch (38) being automatically biased into closing by an elastic arrangement (47). Such a configuration allows setting up additional mechanical connections which are able to compensate for any distortion of the thrust-reverser's annular structure or for any ruptured bracing component in the event of impact by an engine piece.