Abstract: A device for assembly of a connecting rod on the casing of a turbo-engine including: a clevis fixed to the casing and including at least two coaxially bored lugs; a shaft traversing the bores of the lugs to which the suspension member is fixed, in a manner which is mobile in radial rotation, via a ball joint surrounding the shaft; and a connecting device which holds the shaft in place in the lugs of the clevis and is capable of being driven in rotation about the axis of the bores, is disclosed. The ball joint and the connecting device are configured such that the rotation of the connecting device about the axis of the bore of the lugs causes an offset of the axis of rotation of the connecting rod in a direction perpendicular to the axis of the bores.

Abstract: A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

Abstract: Measuring the twist of a rotating shaft by means of a laser beam and polarizing filters. The measurement device includes a laser beam generator, two polarizing filters secured to the shaft and spaced apart from each other, and a laser radiation receiver receiving the laser beam after it has passed through both filters.

Abstract: A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position.

Abstract: A sealing device for passing a connecting rod of a system for controlling a pitch of fan blades of a turboprop through a partition. The device includes a tube for fastening to the partition that is to be sealed, and a frustoconical sheath through which the connecting rod is to pass, the sheath configured to slide axially inside the tube and including, at its wider end, a sealing mechanism co-operating with the tube, and, at its narrower end, a leaktight fastener fastening to a corresponding end of the connecting rod.

Abstract: A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering.

Abstract: A device for controlling orientation of fan blades of a turboprop including at least one set of fan blades having adjustable orientation attached in rotation to a rotating ring mechanically connected to a turbine rotor. Each blade of the set is coupled to a blade root support pivotably mounted on the rotating ring by a conical gear train including a first gear wheel attached to the blade root support and a second gear wheel attached to the rotating ring and bearing a counterweight that is eccentric with respect to its axis of rotation. A cylinder attached in rotation to the turbine rotor and a rod of which is connected to each counterweight through a connecting arm makes it possible to impart synchronous angular displacement to all the counterweights about the axis of rotation of their respective gear wheel.

Abstract: A mechanical transmission device to driving in rotation counter-rotating propellers of a dual-propeller turboprop, including: an epicyclic gear train having a sun gear carried on a sun gear shaft centered on a longitudinal axis and which is connected upstream to a turbine rotor of the turboprop driven in rotation; at least one planet gear meshing with the sun gear; a planet gear carrier carrying the planet gear free to rotate and which is carried by a planet carrier shaft connected downstream to a first set of propellers to drive it in rotation; and a ring gear meshing with the planet gear and which is carried on a ring gear shaft connected downstream to a second set of propellers to drive it in rotation, is disclosed.

Abstract: The invention provides a device for controlling the pitch of the fan blades of a turboprop, the device comprising: at least one set of adjustable pitch fan blades, the set being constrained to rotate with a rotary ring mechanically linked to a rotor; a synchronizing ring coupled to each blade of the set in order to adjust its pitch; an actuator centered on the longitudinal axis of the turboprop and constrained to rotate with the rotor; and control links, each connected firstly to the actuator rod and secondly to an inside end of a cylindrical shaft via a crank capable of imparting turning movement to the shaft about its axis of revolution, an outside end of the shaft being coupled to a blade in order to adjust its pitch.

Abstract: A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis.

Abstract: Device for assembly of a connecting rod (3) on the casing of a turbo-engine comprising, in addition to said suspension member, a clevis (4) fixed to the casing and comprising at least two coaxially bored lugs, and a shaft (9) traversing the bores of said lugs to which said suspension member is fixed, in a manner which is mobile in radial rotation, via a ball joint (10) surrounding the shaft, said shaft being held in place in the lugs of said clevis by connecting means (11, 12, 14) capable of being driven in rotation about the axis of said bores, characterized in that said ball joint and said connecting means are configured such that the rotation of said connecting means about the axis of the bore of the lugs causes an offset of the axis of rotation of the connecting rod (3) in a direction perpendicular to said axis of the bores.

Abstract: A turboprop having at least one propeller formed by a set of variable pitch blades. Each blade is swivel-mounted on a rotary support and carries a gearwheel meshing with an actuator annulus rotating on the rotary support and coupled to a control annulus via an epicyclic mechanism.

Abstract: The subject of the invention is a data communications cable, characterized in that it comprises: a plurality of groups (1,2,3,4) of four pairs of isolated conductors, the four pairs of isolated conductors being assembled in a helical fashion following a group assembly pitch, each pair being twisted in a helical fashion and surrounded by an electrical shield (9,10), the plurality of groups (1,2,3,4) being assembled in a helical fashion following a final assembly pitch, an external sheath (8) surrounding the plurality of groups (1,2,3,4), the final assembly pitch being variable along the cable.

Abstract: A turboprop including a rotary casing fitted with adjustable-pitch blades enabling thrust to be managed. Each blade is coupled, for the purpose of adjusting its pitch, to a control member of an annular actuator carried by the rotary casing.

Abstract: A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring centered on the longitudinal axis, and mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring centered on the longitudinal axis. An actuator is secured to rotate with the turbine rotor and is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis.

Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring. The device includes a rolling bearing including an inner cage slidably mounted on a turbine casing and connected to the rod of an actuator, and an outer cage that is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis.

Abstract: The invention relates to a sealing device for the partition penetration of a connecting rod of a turboprop fan blade orientation control system. The device includes a bellows (60) of trunconical shape designed to allow passage of the connecting rod (50a) and having, at its wider end, means (62, 64) of attachment to the partition (58) to be sealed and, at its narrower end, an O-ring through which the connecting rod is free to slide.

Abstract: The invention relates to the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.

Abstract: A rotor blade of a turbine engine comprising a body made of composite material consisting of a fibre-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement.