Abstract: A turbomachine rotor disk including inter-blade platforms fixed to ribs delimited by cavities in which blade roots are retained, and protective liners mounted between the flanks of the cavities of the disk and the blade roots is disclosed. The protective liners have a C-shaped cross section so that they can be fitted translationally and retained radially on the ribs of the disk and constitute a locking device which locks the platforms on the ribs of the disk.

Abstract: A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X.

Abstract: The present invention relates to the field of blades, particularly fan blades, intended for turbojets, particularly of the aeronautical type. Its objective is to provide a fan blade the features of which will enable the number of fan blades to be reduced while at the same time providing satisfactory performance. According to the invention, the fan blade comprises a plurality of aerodynamic parts which are superposed in a radial direction Z and the number of aerodynamic profiles varies from one aerodynamic part to the other.

Abstract: An aircraft turbomachine fan is disclosed. The fan includes a turbomachine inlet cone that has an exterior surface intended to be closely followed by a flow section of the turbomachine, and an annular balancing flange that rotates as one with a fan disk about an axis of rotation and is equipped with a plurality of weight-fixing holes. The fan also includes one or more balancing weights mounted fixedly on the annular balancing flange. The annular balancing flange is positioned inside the inlet cone in such a way that its weight-fixing holes are isolated from the flow section. The flange is produced as a single piece with a fan blade retaining ring.

Abstract: A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines.

Abstract: A deoiler including a hub mounted on the vent shaft and a cover mounted on the hub between two stop faces which fix the cover avoiding the need to weld or bolt the cover.

Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.

Abstract: A turbomachine fan including blades and inter-blade platforms having radial flanges fastened to flanges of a rotor disk by threaded rods inserted into bushes mounted in orifices in the flanges of the platforms is disclosed. Each bush includes at least one deformable part interposed transversely between the threaded rod and an edge of the orifice in which the bush is mounted. The deformable part is intended to allow the platform to pivot in the event of an impact of a blade against the platform and to absorb some of the energy of the impact.

Abstract: A turbomachine including at least one unducted propeller with variable pitch blades, the blades being carried by respective plates mounted to pivot in radial housings of a rotor element and connected to a control ring that is driven in rotation about the axis of the turbomachine together with the rotor element, and that is movable in translation along the axis to pivot the plates about their axes, the control ring being centered and guided in rotation about the axis on a mechanism that is stationary in rotation and movable in translation along the axis by an actuator carried by the stator of the turbomachine.

Abstract: The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade.

Abstract: A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

Abstract: The invention relates to a cooling device for cooling the slots of a turbomachine rotor disk, the turbomachine comprising an upstream rotor disk having a fastener flange with a periphery that is festooned, a downstream rotor disk, an endplate for holding blades and arranged around the ring of the downstream disk and co-operating therewith to form an air diffusion cavity, a cone for driving disks in rotation, the cone having a fastener flange with a periphery that is festooned, and a plurality of bolted connections passing from upstream to downstream through the solid portions of the fastener flanges of the upstream disk and of the cone, the fastener flange of the endplate, and the fastener flange of the downstream disk. The fastener flange of the endplate is pierced by ventilation orifices opening out into the air diffusion cavity in order to feed it with cooling air, said cavity opening out into the slots of the downstream disk at their upstream ends in order to cool them.

Abstract: A radial annular flange including in inner or outer periphery alternating solid portions including orifices for passing fastener bolts, and hollow portions having bottoms that are substantially flat. The bottom of at least one keying hollow portion is situated radially inside, or outside, respectively, a circle centered on the axis of the flange and externally, or respectively internally, tangential to the orifices. Two hollow portions are situated on either side of the keying hollow portion having bottoms of concave curved shapes situated radially on the outside, or respectively on the inside, relative to the flat bottoms of the other hollow portions.

Abstract: The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base (5) on the rim of a turbine engine compressor hub (3), said rim comprising a peripheral groove (4) on the outer surface thereof for receiving the bases (5) of the blades of said set and two shoulders (7) framing said groove with surfaces which form bearings for holding said blades, said rim also comprising a cut-out (8) provided in at least one of said shoulders (7) to enable the bases (5) of the blades to be inserted in said groove (4), said device comprising a means (10) for translatably immobilising the blades in said groove, suitable for being positioned in said groove (4) between two consecutive blades and in turn translatably held in said groove by an attachment means, characterised in that said carrier is shaped so as to fit into said cut-out (8) and to rest circumferentially on at least one engagement surface (9a, 9b) of said shoulder (7).

Abstract: A one-piece rotor spool (20) for a gas turbine engine extending along the axis of the engine, the spool comprising an upstream portion (20A) and a downstream portion (20B) that are radially offset relative to one another, the radially outer portion (20B) comprising a plurality of housings (24) for rotor blades formed in the outer surface of said radially outer portion (20B), the spool (20) being characterized in that the radially inner portion (20A) comprises attachment means (23) designed to interact with a rotor ring (30) in order to prevent a tangential movement of the rotor ring (30) relative to the radially inner portion (20A).

Abstract: A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone.

Abstract: The present invention relates to a device for attaching a turbomachine stator vane in an annular casing (20) of the turbomachine, the vane comprising a tip formed of a platform (14) with two edges (141, 142), one of them forming an upstream edge (141) and the other forming a downstream edge (142), an airfoil (11) and a root (13), the annular casing (20) comprising a circumferential groove (23) formed in its interior wall with an upstream flank (21) and a downstream flank (22), the vane being held by engagement of the platform (14) in the groove (23), the upstream edge against the upstream flank (21) and the downstream edge (142) against the downstream flank (22) of the groove (23), the downstream flank (22) of the groove (23) being in the form of a slot (22) opening axially in the upstream direction, the downstream edge of the platform (23) being engaged in said downstream flank (22) and a fastening means (40) being attached in order to hold the platform (14) in the groove on the upstream side, wherein the va

Abstract: A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.

Abstract: A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.

Abstract: The invention relates to a balancing device comprising a nut 15 having an internal thread, and a countersunk collar 17 integral with said nut 15, said countersunk collar 17 having a through-hole 23 with a diameter greater than the diameter of the internal thread of the nut 15. Said countersunk collar comprises a balancing weight 19. The invention also relates to a method for balancing a rotating part 1 with such a device, and a rotating part 1 balanced by such a device.