Safran Nacelles

Patrick André Boileau

Gina Ferrier

Patrick Gonidec

Fabien Jourdan

Vincent Jean-François Peyron

Julien Chandelier

Loïc Chapelain

Jean-Philippe Joret

Laurent Georges Valleroy

Sébastien Laurent Marie Pascal

Xavier Cazuc

François Bellet

Vincent Dutot

Stephane Riquier

Edouard Marie Gabriel Ramstein

A propulsion assembly for an aircraft equipped with a thrust reverser comprising an actuator for moving a movable structure between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device equipped with a first connecting part for connecting it to the deflection edge and/or to the outer shell of the intermediate casing, with a second connecting part for connecting it to a body of the actuator, and with a central part running axially between the shell and the actuator. Moreover, the actuator support device forms a guide for a set of cascades of the movable structure.

Propulsion assembly for an aircraft comprising a thrust reverser with movable cascades and with an actuator mounted in an optimized manner

A propulsion assembly including an actuator connected to an outer casing of a turbomachine by a connecting structure. The connecting structure is fastened in line with a structural arm connecting the outer casing to a hub of the turbomachine, with a common fastening device, with the result that the arm can withstand loading forces of the actuator while relieving the outer casing.

Aircraft propulsion assembly comprising an actuator connected to a structural arm such as an outlet guide vane

A thrust reverser including a sealing membrane designed to deflect at least one portion of a secondary flow towards a deflection cascade when a movable structure of the reverser is in the retracted reverse-thrust position, the reverser including a rear frame for supporting the deflection cascade. The reverser further includes an interface device between the sealing membrane and a rear cascade structure including the rear cascade support frame, the vanes located furthest back on the deflection cascade, and a bearing member via which the cascade bears against the rear cascade support frame. Moreover, the device forms an elastic clip mounted around the rear structure, and a rear clip portion whereof is arranged behind the structure.

Thrust reverser comprising means facilitating the mounting of a membrane for sealing off the secondary flow path

A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

Thrust reverser comprising fixed cascades and a sealing membrane

A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.

Thrust reverser comprising movable cascades and a sealing membrane

A thrust reverser includes a jack for translational actuation of a movable part, the jack being a screw jack without an extension tube.

Actuating system for a cascade thrust reverser

A thrust reverser for a propulsion unit, incudes movable grids, two half-assemblies forming part of a secondary stream and, at the six o'clock position, a connecting beam intended to be mounted in cantilever with a fan housing. The half-assemblies are hinged at the twelve o'clock position so as to enable their 'butterfly' movement between a flight configuration and a maintenance configuration. The connecting beam includes a connecting member configured to cooperate, in the form of a tenon and groove connection, with the half-assemblies when these are in flight configuration. The reverser also includes, downstream of the connecting member, locks capable of locking the half-assemblies in flight configuration.

Thrust reverser comprising pivoting half-assemblies and a connecting beam for the half-assemblies at the six o'clock position

A thrust reverser for an aircraft propulsion unit, including a movable system with cascade vanes and an actuator allowing moving a movable system between an advanced direct thrust position and a backward thrust reversal position, the system also including an inter-cascade structure for limiting buckling of the actuator, forming a channel crossed by the actuator and delimited by a cylindrical internal surface extending along a first closed directrix curve, the fixed portion of the actuator including an end equipped with an external ring for limiting buckling of the actuator, the ring having a cylindrical external surface extending along a second closed directrix curve, the first and second closed directrix curves preferably having the same shapes and being concentric while being spaced apart from one another with the same spacing.

Reverser with movable cascades for an aircraft propulsion assembly, comprising a system for limiting the buckling of an actuator of the reverser

A thrust reverser with movable grids, includes structure for connecting, by recessing, a front frame of an outer cowl and a rear frame of the grids. The reverser includes loading structure configured to exert a stress pressing against the connecting structure, under the action of a circumferential pull of the front frame of the outer cowl or of a tightening band supported by the front frame.

Thrust reverser comprising movable grids and cowls assembled by recessing

A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Thrust reverser with anti-buckling actuating system

A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.

Growing community of inventors

Moissy-Cramayel, France

Patrick André Boileau