Abstract: The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.

Abstract: A hydraulic ram comprising a fixed support, a cylinder that is movable in translation relative to the support, a piston secured inside the cylinder delimiting two chambers with the cylinder and a device for supplying the chambers with hydraulic fluid upstream from the fixed support. The ram is characterised by the fact that the supply device comprises telescopic channels, each telescopic channel comprising two tubular elements sliding one into the other, a first tubular element being rigidly connected to the fixed support at one end and the second tubular element being rigidly connected to the cylinder at at least two points separated from each other along a generatrix of the cylinder. The invention is applicable to controlling the pitch of the blades of a turbine engine propeller.

Abstract: A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream 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: 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: The disclosed subject matter relates to a hydraulic and electrical interface ring for a turbine engine, characterized in that said ring comprises fluid transfer pipes which axially pass therethrough and having axial ends that form axial interlocking means, the supporting means of at least one electrical device, and at least one electrical linking connector of the device, said connector being configured to engage by axial interlocking with a complementary electrical connector of another part.

Abstract: An aircraft turbomachine including a lubricant circulation pipe and a hydraulic pipe for controlling an actuator for changing a pitch of blades of a propeller of the turbomachine. The assembly, integrated to a receiver of the turbomachine, further includes a mechanism forming a thermal bridge between the lubricant circulation pipe and the hydraulic pipe.

Abstract: Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

Abstract: The invention relates to a blower (3) including a system (1) for holding blades (2) having variable choking, the bases of which are mounted onto radial shafts (23) of a rotor (5) of the blower by means of pivots (8). Said blower is characterized in that the system (1) includes a main body (11), capable of being attached onto the rotor (5), and at least one holding arm (19, 20), mounted onto said main body (11) and capable of extending inside a pivot (8) so as to engage with same in order to lock the movement of said pivot (8) along the axis of the shaft (23) on which said holding arm is mounted. The invention also relates to a turbine engine and an assembly method.

Abstract: A balancing device including a nut having an internal thread, and a countersunk collar is disclosed. The countersunk collar has a through-hole with a diameter greater than the diameter of the internal thread of the nut. The countersunk collar includes a balancing weight.

Abstract: A method of fabricating a turbine engine drum including at least two rotor disks, the method including: positioning the two disks on a common axis spaced apart from each other and in a predetermined angular position relative to each other; placing a wall forming a body of revolution between the two disks coaxially about their common axis; driving the wall in rotation about its axis; and moving the disks axially towards the wall so as to put the disks into contact with ends of the wall and thus welding the disks to the wall by inertial friction welding.

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: A balancing device including a nut having an internal thread, and a countersunk collar is disclosed. The countersunk collar has a through-hole with a diameter greater than the diameter of the internal thread of the nut. The countersunk collar includes a balancing weight.

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 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 invention relates to a device (1) for controlling the pitch of the blades of a rotor, comprising: a radial shaft (2), the rotation of which controls the pitch of the blades, a guiding bearing (5), for guiding the radial shaft (2), characterized in that it comprises: a nut (7) which tightens the guiding bearing (5) along the radial axis (18), and comprising a circumferential rib (8) extending as a protrusion towards the outside of the nut (7), for guiding a lubrication oil towards the outside of the nut (7). The invention also relates to a turbine engine comprising such a device.

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: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.

Abstract: A cooling device for cooling the slots of a turbomachine rotor disk is provided. The turbomachine includes 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 and having a fastener flange with a periphery that is festooned; and a plurality of bolted connections passing from upstream to downstream through 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, the cavity opening out into the slots of the downstream disk at their upstream ends.

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.