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 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 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 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.

Abstract: A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to an engine cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse thrust position.

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 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.

Abstract: A locking system is disclosed for an aircraft jet engine thrust reverser door that is movably connected to an engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the cowling having a reverse thrust opening that is covered by the thrust reverser door when in the forward thrust position and uncovered when the thrust reverser door is in the reverse thrust position. The locking system has a plurality of locking devices attached to the cowling at the forward side of the reverse thrust opening with at least one locking device located on opposite sides of a longitudinal line equidistantly spaced from opposite lateral sides of the thrust reverser door such that the locking devices simultaneously lock the thrust reverser door in the forward thrust position.

Abstract: A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to a cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse thrust position.

Abstract: A thrust reverser is disclosed for an aircraft jet engine having a bypass duct enclosing a cowling with an outer cowling surface and a reverse thrust opening extending through the cowling. The thrust reverser has a thrust reverser door in the opening 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 thrust reverser door is moved within the thrust reverser opening, which is then uncovered, into a gas deflecting position at which position a portion of the door extends into the bypass duct. The thrust reverser door has an inner panel defining a part of the gas duct and an outer panel having an outer surface substantially flush with the outer cowling surface when the thrust reverser door is in the forward thrust position. The inner panel is sealed against the cowling.

Abstract: A security hydraulic coupling system includes at least two hydraulic connector fittings (4, 5) which may be connected to adjacent fluid ports (1, 2) of a hydraulic unit (12) and which are linked to each other by means of a base plate (3) which is also shaped to cooperate with at least one projection (10) on the hydraulic unit (12) to thereby physically prescribe the positions of the various elements during the steps of fitting connection and disconnection. An interlock system comprises a security pin (6) which is housed in the base plate (3) and is mounted between the fittings (4, 5) and cooperates with grooves (7, 8) provided in the fittings (4, 5) to prescribe the possible sequence of steps in connecting/disconnecting the fittings (4, 5) from the ports of the hydraulic unit (12).

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary of a gas flow duct through which gases flow from a front to a rear, the cowling having at least one reverse thrust opening communicating with the gas flow duct and a thrust reverser door pivotally connected to the cowling so as to move between a forward thrust position wherein the thrust reverser door covers the reverse thrust opening, and a reverse thrust position wherein the reverse thrust opening is uncovered and the thrust reverser door directs at least a portion of the gases flowing through the duct through the reverse thrust opening.

Abstract: A device for closing and locking the shutters of an aircraft thrust reverser includes a lock having a latch which is motorized so as to complete the closure of a shutter utilizing energy supplied by the motor, thereby relieving the jack which is the prime mover of the shutter. The device includes a stop which opposes the latch and interacts with a counter-stop so as to immobilize the shutter in the closed position and thus reduce vibration and flapping of the shutter.

Abstract: A variable turbofan bypass cowling includes a movable cowling assembly (12) with pivoting door type thrust reversers (20) connected to a fixed upstream cowling structure (11). The movable assembly may be translated between an upstream position whereat an upstream portion of the reverser and cowling assembly (12) is housed inside an enclosure formed by the upstream cowling structure (11) and a downstream position whereat the assembly (12) effects a variation in the exhaust duct (17) cross-section between an inner primary turbojet-engine cowling (15) and a radially inner wall of the assembly (12). The reverser doors (20) in their closed position are integrated into the cowling wall and contain at least part of the exhaust flow. When pivoted to thrust reversed positions following translation of the assembly (12) to a downstream rearward position, thrust reversal is provided in the usual manner.

Abstract: A thrust reverser is disclosed for an aircraft jet engine having a cowling with an outer surface and at least one reverse thrust opening, the thrust reverser including a thrust reverser door assembly movable with respect to the cowling between a forward thrust position, in which the reverse thrust opening is uncovered, and a reverse thrust position in which the thrust reverser door uncovers the reverse thrust opening. The thrust reverser door assembly includes an inner structure, an external panel movably connected to the inner structure and one or more resilient devices acting on the inner structure and the external panel to bias the external panel toward the inner structure such that, when the thrust reverser door is in the forward thrust position the external panel is displaced away from the inner structure by contact with the cowling such that an outer surface of the external panel is substantially flush with the outer surface of the cowling.

Abstract: The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a gas flow duct, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door with forward and rear portions, a first opening in the forward portion, a second opening in the rear portion and a passage communicating with the first and second openings.