Abstract: An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Abstract: The present invention relates to a torque-measurement device for a turbine engine shaft (1) including a proof body (7) capable of being mounted on the shaft, characterised in that the proof body (7) forms a mounting for at least one acoustic-wave strain gauge (20) and is magnetised such as to allow the torque to be measured by magnetostrictive effect.

Abstract: The invention relates to a hydraulic connection device comprising a part with an opening for the throughflow of hydraulic fluid and a tubular rod with an end fitting, the end fitting of the rod being hydraulically connected to the opening for the throughflow of the fluid, wherein the opening and the end fitting of the rod each have a portion of surface which is shaped so as to allow a certain angular movement between the part and the rod, a seal being inserted between said two surface portions.

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: The epicyclic reduction gear comprises a planetary input shaft, planet gears meshing around said shaft and supported by a planet carrier, and two transverse sides. According to the invention, the reduction gear comprises at least one fluid transfer pipe suitable for being connected to a fluid supply source and passing through the planet carrier, being linked in rotation to same, from a first of said transverse sides of the reduction gear to a second of said transverse sides of the latter in order to open on the outside of the reduction gear and dispense the fluid.

Abstract: A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.

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: The turbine engine includes respective systems for changing the pitch of the propeller blades, the system (22) for the upstream propeller including a linear actuator (23) and a transmission mechanism (24) connecting the actuator to the blades in order to transform the sliding of the actuator into a rotation of the blades, said upstream propeller (2) including a rotatable housing (19) rigidly connected to a rotatable shaft (17) supported in a static housing (27) of the turbine engine by a bearing (29) upstream of the system, and by a bearing (30) downstream of the system.

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 bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.

Abstract: Device for supplying oil under pressure to a linear actuator of a turbine engine, this actuator comprising an internal fixed portion and an external movable portion and means for regulating and supplying oil to chambers of the actuator, these regulating means being mounted radially outside the movable portion of the actuator, and the fixed portion of the actuator comprising on its upstream end portion oil passage channels of which the outlets open radially outwards, the device further comprising an oil distribution ring which is mounted on the upstream end portion of the fixed portion and which comprises internal conduits of which the inlets communicate with the outlets of the channels of the fixed portion and the outlets open axially downstream and are connected to the regulating means.

Abstract: The system comprises a linear-displacement fluidic actuator (22) coaxial with the propeller, and a transmission device (23) connecting the actuator to the blades that are to be controlled. Advantageously, the transmission device (23) comprises at least two radial arms (36) arranged symmetrically with respect to the actuator and connected, on the inside, to a translationally mobile part of the actuator and, on the outside, to a translationally movable rotary transmission ring (25) which is connected to the pivot pins (11) of the blades (6) by intermediate connecting mechanisms (26) that convert the translational movement of the rotary ring brought about by the actuator into a rotation of the blades of the propeller.

Abstract: The device (18) is intended to supply a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller, according to separate operating states, from a rotary power assembly, the device being arranged so as to be located between the power assembly and the actuator, along a longitudinal axis (A), and being connected in rotation therewith. According to the invention, the device comprises means (20) for supplying fluid interacting with said power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor (21) to which said supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by means of tubular equipment (25) connected to the distributor.

Abstract: The device (27) can be housed coaxially inside a sleeve (25) in which the supplies are situated, and comprises: a hollow cylindrical body (30) that fits inside the sleeve and accepts the mechanism (22) in the housing of the hollow body, with passages (33, 34, 36) for respectively connecting the supplies to said mechanism (22); and a cover (31) which is integrated or fixed, removably, on the front side of the cylindrical body and connects the hidden supplies to the respective passages of the body.