Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.

Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn f

Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterised in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.

Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn f

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: 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 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: 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 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 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: 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 linkage system is disclosed for releasably latching a thrust reverser to an engine casing having a longitudinal axis, the linkage system having a seat on the thrust reverser and a movable latching member on the engine casing movable between an open position in which the latching member is displaced away from the seat, and a closed position in which the latching member is located adjacent to the seat so as to prevent displacement of the thrust reverser away from the engine casing.

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 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 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: A thrust reverser is disclosed for an aircraft turbojet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having at least one reverse thrust opening and a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, wherein the thrust reverser door closes the at least one reverse thrust opening and a reverse thrust position, wherein a forward portion of the thrust reverser door moves outwardly from the cowing and a rear portion of the door moves inwardly into the gas flow duct so as to redirect a first portion of the gases flowing through the gas flow duct through the reverse thrust opening.