Abstract: The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Abstract: The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Abstract: The invention relates to a locking device (13) that includes at least one locking system (16), intended to be placed on a first moving element (11), and a retaining member (17), intended to be placed on a second moving element (12), the locking system (16) having a first hook (18) designed to engage with the retaining member so as to lock the locking device (13). The locking system (16) includes at least a second hook (19) set back from the first hook (18) so as to engage with the retaining member in the event of the first hook (18) breaking.

Abstract: The present invention relates to a jet engine nacelle (1), of the type comprising an aft section forming an external structure (2) which, together with a concentric internal structure (4) comprising an internal panel (10) intended to surround a down-stream portion of the jet engine, defines an annular flow duct for a so-called secondary stream (3), characterized in that exhaust means (11) are formed in the internal panel such that any unwanted excess pressure is discharged into the annular duct.

Abstract: The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterized in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Abstract: The present invention relates to a jet engine nacelle (1), of the type comprising an aft section forming an external structure (2) which, together with a concentric internal structure (4) comprising an internal panel (10) intended to surround a down-stream portion of the jet engine, defines an annular flow duct for a so-called secondary stream (3), characterized in that exhaust means (11) are formed in the internal panel such that any unwanted excess pressure is discharged into the annular duct.

Abstract: The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterised in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Abstract: The invention relates to a locking device (13) that includes at least one locking system (16), intended to be placed on a first moving element (11), and a retaining member (17), intended to be placed on a second moving element (12), the locking system (16) having a first hook (18) designed to engage with the retaining member so as to lock the locking device (13). The locking system (16) includes at least a second hook (19) set back from the first hook (18) so as to engage with the retaining member in the event of the first hook (18) breaking.

Abstract: The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the movable parts (50) and tracks (62) attached to the longitudinal members (36). According to the invention, the locking system (80) comprises locks (82) located at the end (62a) of each track (62) in the opening direction (52), each lock comprising a bolt (110) capable of preventing the rail (64) moving in the opening direction (52).

Abstract: The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the movable parts (50) and tracks (62) attached to the longitudinal members (36).

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: 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.