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: 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.

Abstract: A thrust reverser is disclosed for a turbofan type turbojet engine assembly with a cowling having an inner cowling surface forming an outer boundary of a gas flow duct, and an outer cowling surface spaced from the inner cowling surface, the inner and outer cowling surfaces joining at a rearmost edge of the cowling, the thrust reverser having a thrust reverser baffle with an outer baffle surface and an inner baffle surface, a forward linkrod pivotally connected to a forward portion of a thrust reverser baffle and to the cowling, and a rear linkrod pivotally connected to the thrust reverser baffle and to the cowling.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling with an inner cowling surface forming an outer boundary of a gas flow duct through which gases flow from a front towards a rear portion, the cowling having an outer cowling surface and at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door pivotally connected to the cowling so as to move between a forward thrust position and a reverse thrust position, the thrust reverser door having front and rear edge portions, an outer door surface and an inner door surface with at least one of the outer and inner door surfaces being flush with at least one of the corresponding outer and inner cowling surfaces when the thrust reverser door is in the forward thrust position.

Abstract: An actuating mechanism is disclosed for a thrust reverser of a turbojet engine having an engine cowling with a reverse thrust opening, a thrust reverser door pivotally connected to the engine cowling so as to pivot between forward and reverse thrust positions, and a linear actuator having a casing with an extendable and retractable piston rod. The piston rod is connected to the thrust reverser by a first connection forming a first connection point. An interface bracket is fixedly attached to the turbojet engine structure and engages a mounting flange in a connector affixed to the actuator casing at a second connection point, the mounting flange being in contact with the interface bracket at a third connection point, the first, second and third connection points lying in a straight line.

Abstract: An electric control system is disclosed for a turbojet engine thrust reverser having at least one movable component movable between a forward thrust position and a reverse thrust position, the control system having at least one electromechanical drive device mechanically connected to the moveable component such that actuation of the electromechanical drive device moves the component between the forward and reverse thrust positions, and an electronic control unit electrically connected to the electromechanical drive device and to a turbojet engine control system to transmit actuation signals to the electromechanical drive device to control the movement of the component between the forward and reverse thrust positions. The electronic control system preferably also has at least one electrically actuated locking device to hold the movable component in the forward thrust position.

Abstract: A pivot system is disclosed for pivotally connecting a movable component to a fixed component, the pivot system having a swivel device mounted on one of the movable and fixed components, a headed shaft passing through a portion of the other of the movable and fixed components and engaging the swivel device, the headed shaft having a longitudinal axis forming the pivot axis between the components, an anti-rotation device engaging the shaft so as to prevent relative rotation between the shaft and the component to which it is mounted, and an anti-axial movement device engaging the shaft as to prevent relative movement between the shaft and the component to which it is mounted along the longitudinal axis of the shaft. This structure enables the shaft to be installed having access to only one end of the pivot shaft, improving over the known systems in which it is necessary to have access to both ends of the pivot shaft.

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.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary of a gas flow duct through which pressurized gases flow, the cowling having a reverse thrust opening, in which the thrust reverser comprises a thrust reverser door assembly pivotally attached to the cowling so as to be movable between a forward thrust position in which the thrust reverser door assembly covers the reverse thrust opening through the cowling, and a reverse thrust position in which the thrust reverser door assembly directs at least a portion of the gases flowing through the gas flow duct through the reverse thrust cowling opening.

Abstract: A fail safe emergency lock for a thrust reverser is disclosed in which the thrust reverser is located on a jet engine having a cowling bounding a gas flow duct, the cowling having at least one reverse thrust opening in communication with the gas flow duct. The thrust reverser has a thrust reverser panel movably mounted on the cowling so as to be movable between a forward thrust position, in which the thrust reverser panel covers the reverse thrust opening, and a reverse thrust position in which the reverse thrust opening is uncovered.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary for a gas flow duct, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser includes a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, in which the reverse thrust opening is uncovered and the thrust reverser door covers the reverse thrust opening, and a reverse thrust position in which the thrust reverser door directs at least a portion of the gas flow from the duct through the reverse thrust opening. A panel is incorporated into the thrust reverser such that it is movable between a first position in which an inner surface of the panel forms a portion of the outer boundary of the gas flow duct and a second position wherein the entire panel is located within the gas flow duct.

Abstract: The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a flow duct through which gases flow from the front of the cowling towards a rear of the cowling, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door pivotally mounted on the cowling so as to be movable between a forward and a thrust position, wherein the thrust reverser door covers the reverse thrust opening, and a reverse thrust position wherein the thrust reverser door uncovers the reverse thrust opening and directs at least a portion of the gases flowing through the gas flow duct outwardly through the reverse thrust opening.

Abstract: A thrust reverser is disclosed for a turbofan jet engine having a fan cowling with an inner surface and a rear edge, and a jet engine cowling having an outer surface spaced from the inner surface of the fan cowling so as to form an annular gas flow duct, the engine cowling extending rearwardly of the rear edge of the fan cowling. A first thrust reverser baffle is located rearwardly of the rear edge of the fan cowling and is pivotally attached to the engine cowling so as to be movable between a forward thrust position, wherein a first surface of the first thrust reverser baffle forms a portion of the outer surface of the engine cowling, and a reverse thrust position in which a first end of the first baffle moves away from the engine cowling such that the first baffle extends into the gas flow from the gas flow duct so as to redirect at least a portion of the gas flow in a reverse thrust direction.

Abstract: A thrust reverser for a turbojet engine is disclosed having a first thrust reverser door pivotally attached to the engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the first thrust reverser door having a first inner surface forming a portion of the outer boundary of the gas flow duct when the first thrust reverser door is in the forward thrust position, a first outer surface and a rear portion which extends into the gas flow duct when the first thrust reverser door is in the reverse thrust position so as to direct at least a portion of the gases passing through the duct outwardly through an opening in the cowling, and a second thrust reverser door pivotally connected to the cowling so as to also be movable between a forward thrust position and a reverse thrust position, the second thrust reverser door having a second outer surface which, with the first inner surface of the first thrust reverser door, form opposite boundaries of a passage directing the gases i

Abstract: A thrust reverser is disclosed in which a panel is pivotally attached to the cowling downstream of the movable thrust reverser door and is connected to the door such that movement of the thrust reverser door causes the panel to pivot about its attachment to the cowling. When the door is in its forward thrust position, the inner wall of the door and an inner wall of the panel form a portion of the boundary of the duct through which pass pressurized gases. The pressurized gases exert forces on the inner wall of the door and the inner surface of the panel such that the forces urge the thrust reverser door toward its forward thrust position. Thus, the thrust reverser door is prevented from being inadvertently deployed toward its reverse thrust position even upon failure or malfunction of the door locking or latching mechanisms.

Abstract: A thrust reverser is disclosed for a turbojet engine having an outer cowling and an inner cowling forming a generally annular gas flow duct therebetween, the thrust reverser having at least one thrust reverser door pivotally attached to the outer cowling so as to pivot about a first stationary axis to move between a forward thrust position and a reverse thrust position, a thrust reverser panel pivotally attached to the inner cowling so as to pivot about a second stationary axis to move between a forward thrust position and a reverse thrust position, and a connector connecting the thrust reverser door and the thrust reverser panel such that when the thrust reverser door is in the reverse thrust position, the thrust reverser panel is in the reverse thrust position and when the thrust reverser door is in the forward thrust position, the thrust reverser panel is also in the forward thrust position.

Abstract: A thrust reverser for a turbojet engine is disclosed having a rear duct portion extending about a longitudinal axis with a rearmost edge lying in a plane extending at an oblique angle to the longitudinal axis. The thrust reverser also has a single thrust reverser baffle pivotally attached to the rear duct portion to move between a forward thrust position and a reverse thrust position. The single thrust reverser baffle has rearmost, planar edge which, in the forward thrust position, forms the downstream or rearmost end of the engine nozzle. The planar edge eliminates the aerodynamic losses of the known thrust reverser devices. The thrust reverser baffle also has an oblique edge that faces in a forward direction and is parallel to the rearmost edge of the rear duct portion when the baffle is in its forward thrust position.

Abstract: A thrust reverser for a turbojet engine is disclosed having a thrust reverser door and a thrust reverser panel pivotally attached to a housing so as to pivot in opposite directions about the same pivot axis. An epicyclic gear mechanism interconnects the housing, the thrust reverser door and the thrust reverser panel such that the thrust reverser door and the thrust reverser panels move in opposite directions about the common pivot axis when moving between their forward thrust and reverse thrust positions.

Abstract: A thrust reverser is disclosed for a turbojet engine having a central axis and an exhaust nozzle wherein the thrust reverser has a plurality of deflectors pivotally attached to the turbojet engine so as to pivot about axes extending generally traverse to the central axis between a forward thrust position, wherein the plurality of deflectors form a downstream end of the exhaust nozzle, and a reverse thrust position wherein the deflectors deflect gases emanating from the engine to generate a reverse thrust. Each of the movable deflectors has a downstream trailing edge located such that all of the trailing edges of the deflectors lie in a common plane extending substantially transverse to the central axis.