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: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

Abstract: A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, is provided. The system includes a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism. The connection mechanism allows movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.

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 turbine blade for a turbojet engine, made of a ceramic matrix composite material and including a vane that extends above a platform and a root that extends below the platform is provided. The pressure face and the suction face of the vane is formed by sheets of a composite material, the sheets meeting at the leading edge and trailing edge of the vane. 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 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: An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

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: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

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: An open rotor type aircraft turbine engine including a contrarotating propeller receiver and a dual-body gas generator having a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, in which the gas generator is arranged upstream from the receiver is provided. The turbine engine includes a structural casing for supporting the receiver, surrounding the gas generator and having a downstream end attached to the receiver and an upstream end attached to the intermediate housing; and a connection device between the structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing.

Abstract: A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.

Abstract: An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.

Abstract: An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.

Abstract: The invention relates to a turbine blade having an airfoil (31) extending above a platform (32) and a root (33) extending below said platform, the root of said blade having the form of a radially extending arm (34), being produced from composite material and having at least one cylindrical face (34), the direction of the generatrices of which is oriented in the direction of said platform so as to allow a clamping piece (5) to slide towards the latter on said cylindrical face under the action of centrifugal force, characterized in that said arm has, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1), and in that the root (33) is located entirely on the side of said protuberance with respect to said face.

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: A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, including a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism, the connection mechanism configured to allow movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.

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 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.