Abstract: A turboprop having a set of variable-pitch rotary blades constrained to rotate with a rotary support. In order to vary its pitch, each blade of said set is coupled to a specific hydraulic actuator carried by the rotary support.

Abstract: A system of contra-rotating propellers for an aircraft jet engine, including: a free power turbine; a first and second propeller, contra-rotating, the first propeller being placed in a predetermined direction relative to the second propeller, each including a hub, an outer ferrule, and coupling arms linking the two; and a casing inserted between the free turbine and the propellers, the propellers arranged in the predetermined direction relative to the casing and the free turbine arranged in the opposite direction relative to the casing, the casing including a casing extension in the given direction, rotatably supporting the hub of the propeller. The coupling arms extend in the opposite direction, radially towards the outside.

Abstract: A device including a pair of counter rotating propellers with variable pitch which may be modified by an actuator located in a central cavity of the shafts. A system for transporting energy to the actuator includes a conduit passing into a static case in proximity to an epicycloidal gear train, and then control conduits leading to the actuator and crossing the planet carrier of an epicycloidal gear train. The junction is affected by a dynamic joint with a collector. This transport path avoids a high temperature turbine.

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 system of contra-rotating propellers for an aircraft turbomachine, including: a free power turbine including a first rotor; first and second propellers; and a mechanical transmission system including a planetary gear train fitted with a sun gear driven by the rotor, at least one planet gear driving the first propeller, and a ring driving the second propeller. The free power turbine also includes a second rotor that is contra-rotating relative to the first rotor, and rotating the ring.

Abstract: The invention concerns a feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades (14) with adjustable orientation. The assembly is attached in rotation to a rotating cowling (16) connected to a turbine rotor (18). Each blade is coupled, for the adjustment of its orientation, to a control ring that is movable between two extreme positions, one of which corresponds to feathering of the blades. Mechanical parts (32) are able to extend elastically as a result of a rise in their temperature, these mechanical parts being positioned facing the control ring so as to be able to exert a thrust force on the ring in order to put it in a position to feather the blades when they expand. Means are provided to cause a rise in the temperature of the mechanical parts so as to expand them.

Abstract: A sealing plug for a hollow shaft used to impart a rotational speed, the hollow shaft including a first end adapted to be located in a chamber containing lubricant, and a second end adapted to be located outside the chamber. The sealing plug has a substantially cylindrical surface, a first face and a second face for insertion into the first end of the hollow shaft. The plug also includes a cavity that is open at the second face and a first radial duct opening, at one of its ends, at the cavity and, at its opposite end, at the substantially cylindrical surface of the sealing plug. The device is applied particularly in the field of turbomachines equipped with an open rotor.

Abstract: A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.

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: A system for controlling propeller blade pitch in a turboshaft engine, including: a first track connected to a propeller blade, of which the rotation provides for the setting of the incidence of this blade; a second track; a member actuating the first track, arranged between the first and second tracks, and having a recessed angular portion; and at least one locking member provided between the first and second tracks, housed in the recessed angular portion and in the notch. The locking member can occupy a normal over-center position rendering the first and second tracks integral in rotation, and a release position authorizing the displacement in rotation of a unit including the first track, the locking member, and the actuating member.

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: Bypass aeronautical engine comprising a fan (1), an LP compressor (3) and an HP compressor (4), a combustion chamber (5), an HP turbine and at least one LP turbine stage, said LP stage comprising a first movable bladed wheel (9a, 10a) carried by a first turbine shaft and a second movable bladed wheel (9b, 10b, 11b) turning in the opposite direction to said first wheel, said fan being driven by said second wheel via a second turbine shaft (2b) and by said first shaft (2a) via a module for reversing its direction of rotation, wherein the reversing module is produced with the aid of two bevel pinions (19, 21) of the same size, carried respectively by the first and second LP turbine shafts, and with the aid of a reversing pinion (20), the two turbine shafts (2a, 2b) turning in absolute value at the same speed of rotation.

Abstract: The invention relates to a device for controlling the pitch of fan blades of a turboprop. The device includes at least at least one set of adjustable pitch fan blades secured to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor. Each blade of the set is coupled for pitch-adjustment purposes with a synchronization ring centered on the longitudinal axis, the synchronization ring being suitable for pivoting about the longitudinal axis relative to the rotary ring under drive from actuators carried by the rotary ring and each having a respective axis extending in a direction that is substantially tangential to the synchronization ring.

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 turboprop having a set of variable-pitch rotary blades constrained to rotate with a rotary support. In order to vary its pitch, each blade of said set is coupled to a specific hydraulic actuator carried by the rotary support.

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

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.