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 device for controlling the pitch of the blades of a rotor is provided. The device includes a radial shaft, the rotation of which controls the pitch of the blades; a guiding bearing for guiding the radial shaft; a nut which tightens the guiding bearing along the radial axis; and a circumferential rib extending as a protrusion towards the outside of the nut, for guiding a lubrication oil towards the outside of the nut.

Abstract: A device for guiding variable pitch diffuser vanes of a turbine engine is provided. The device includes a first ring having an axial portion at its periphery that is extended by a collar extending radially outwards; a second ring mounted around the axial portion of the first ring so as to cooperate therewith to define a plurality of outwardly open sockets; a plurality of cylindrical bushings, each mounted in a respective socket for the purpose of receiving a guide pivot of a diffuser vane; and a resilient clamping ring for cooperating with one of the rings in order to clamp the two rings axially one against the other.

Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Abstract: A fan including a system for holding blades having variable pitch, in which the bases of the blades are mounted onto radial shafts of a rotor of the fan by pivots, is provided. The system includes a main body capable of being attached onto the rotor; and at least one holding arm mounted onto the main body and capable of extending inside a pivot so as to engage with the pivot in order to lock the movement of the pivot along the axis of the shaft on which the holding arm is mounted.

Abstract: A system includes a linear-displacement fluidic actuator coaxial with the propeller, and a transmission device connecting the actuator to the blades that are to be controlled. The transmission device includes at least two radial arms 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 which is connected to the pivot pins of the blades by intermediate connecting mechanisms that convert the translational movement of the rotary ring brought about by the actuator into a rotation of the blades of the propeller.

Abstract: A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from the opening, and a second part forming a substantially toroidal chamber, radially open outward at a low point, so as to allow oil to escape, a passage being arranged between the basin and the chamber substantially over the entire circumference around the axis so as to cause the oil recovered by the basin to enter the chamber, wherein a rim is arranged between a radially inner bottom of the chamber and the passage, so as to contain the oil accumulating in this radially inner bottom of the chamber, and in some embodiments, at a high point.

Abstract: A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.

Abstract: A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.

Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.

Abstract: A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

Abstract: A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds and being secured thereto. The part is made of composite material and is obtained by densifying a fiber preform with a matrix. The fiber preform includes a set of yarns extending continuously along a path passing longitudinally along the preform portions of at least two consecutive vanes by passing through the inner shroud preform portion and the outer shroud preform portion, and the woven fiber reinforcement yarns extends continuously in the circumferential direction along an inner shroud segment and along an outer shroud segment between which the consecutive vanes extend.

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 an assembly (60) for an aircraft turbine machine comprising a receiver for a pair of open rotor contra-rotating propellers, the assembly comprising a duct (52), ancillaries routed inside the duct, an attachment case (54), attachment means (62) of the duct on an annular installation portion (64) of the case (54). According to the invention, the attachment means (62) in an assembled configuration include: a split ring (66) fitted with internal projections (71) housed inside orifices (72) in the duct; a radial loading surface (68) of the ring made on the portion (64) the surface (68) being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface (70) of the complementary shaped tapered split ring; means (80) of axially loading the ring along the first direction, these means (80) being blocked in the axial direction on the portion (64).

Abstract: A turbine engine including a power gear box shaft, a turbine shaft, a connecting part of annular shape by which one end of the power gear box shaft and one end of the turbine shaft are connected in a rotationally fixed manner, a structural housing, and a guide bearing for guiding the connecting part relative to the housing, is provided. The guide bearing is mounted between the connecting part and the housing and includes an external ring mounted on the housing, an internal ring mounted on the connecting part, and at least one rolling element configured to enable the external ring to roll around the internal ring. The guide bearing is configured to form a ball joint link enabling a relative angular displacement of its external ring with respect to its internal ring.

Abstract: The device 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, and being connected in rotation therewith. According to the invention, the device comprises supplies for supplying fluid interacting with the power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor to which the supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by a tubular equipment connected to the distributor.

Abstract: The invention relates to a device for guiding variable pitch diffuser vanes of a turbine engine, the device comprising a first ring (26) having an axial portion (32) at its periphery that is extended by a collar (34) extending radially outwards, a second ring (28) mounted around the axial portion of the first ring so as to co-operate therewith to define a plurality of outwardly open sockets (36), a plurality of cylindrical bushings (22), each mounted in a respective socket for the purpose of receiving a guide pivot (12) of a diffuser vane (4), and a resilient clamping ring (30) for cooperating with one of the rings in order to clamp the two rings axially one against the other.

Abstract: A device can be housed coaxially inside a sleeve in which the supplies are situated, and includes: a hollow cylindrical body that fits inside the sleeve and accepts the mechanism in the housing of the hollow body, with passages for respectively connecting the supplies to said mechanism; and a cover 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.

Abstract: A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.

Abstract: The invention relates to a radial control shaft (48) for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, the shaft comprising an external portion (52) that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade (26) in order to adjust its pitch, and an internal portion (50), independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing (40) in order to pivot the shaft about a radial axis (Z-Z), and to close an oil enclosure in which said bearing is housed, the external and internal portions of the shaft being coupled to each other. The invention also relates to a method of mounting such a shaft and to a control device including such a shaft.