Abstract: A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile.

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 reduction gear with epicyclic gear train including an annulus gear, and at least one planet gear rolling on the annulus gear and able to rotate about a planet spindle borne by a planet carrier is provided. The planet spindle is mounted such that it can itself rotate about its axis relative to the planet carrier. The reduction gear is suitable for mounting in a high bypass ratio jet engine for driving the fan thereof.

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: 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 rotor blade of a turbine engine comprising a body made of composite material consisting of a fiber-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.

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: 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 reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field.

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: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

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: A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop, the device including: a fluid manifold secured to a rotor of the turboprop and including a cylindrical portion including at least two fluid-circulation grooves, each presenting an outlet orifice; a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion including at least two distinct fluid passages opening to fluid-admission tubes and each leading radially into one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and including a cylindrical portion including at least two fluid-flow channels, each fed with fluid by a respective one of the outlet orifices of the fluid dispenser, each fluid-flow channel leading to a respective chamber of a control actuator.

Abstract: A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.

Abstract: Turbine blade for a turbojet engine, made of a ceramic matrix composite material and comprising a vane that extends above a platform and a root that extends below said platform, the pressure face and suction face of said vane being formed by sheets of a composite material, said sheets meeting at the leading edge and trailing edge of said vane, characterised in that the pressure face and suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge.

Abstract: A feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades with adjustable orientation is provided. The assembly is attached in rotation to a rotating cowling connected to a turbine rotor. 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 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. A device to cause a rise in the temperature of the mechanical parts so as to expand them is also provided.

Abstract: A bypass aeronautical engine including a fan, an LP compressor, an HP compressor, a combustion chamber, an HP turbine, and at least one LP turbine stage is disclosed. The LP turbine stage includes a first movable bladed wheel carried by a first turbine shaft and a second movable bladed wheel turning in the opposite direction to the first wheel. The fan is driven by the second wheel via a second turbine shaft and by the first shaft via a module for reversing its direction of rotation. The reversing module includes two bevel pinions carried respectively by the first and second LP turbine shafts, and a reversing pinion.

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 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 reduction gear with epicyclic gear train comprising an annulus gear (14), at least one planet gear (12) rolling on said annulus gear and able to rotate about a planet spindle (16) borne by a planet carrier (13), wherein said planet spindle is mounted such that it can itself rotate about its axis relative to said planet carrier. The invention is suited to a reduction gear mounted in a high bypass ratio jet engine for driving the fan thereof.