Abstract: The invention concerns an epicycloidal gear train (10) comprising a central pinion (26), an outer crown (28) and satellite pinions (32) in engagement with the central pinion (26) and the outer crown (28) and each mounted freely rotatable on a satellite carrier (32), the gear train (10) comprising an annular cup (56) being integral with the satellite carrier (36) and open radially inward. According to the invention, the cup (56) is divided into a circumferential succession of first basins (60) of the first oil circuit and second basins (62) of the second oil circuit, the first basins (60) being fluidly separated from the second cells (62) and characterised in that the cup (56) comprises two annular walls (56a, 56b) axially facing, the annular wall (56b) of which is furthest from a median transverse plane (74) of the gear train (10) has openings (76) opening into the second basins (62).

Abstract: The invention concerns an epicycloidal gear train comprising a central pinion (26), an outer crown (28) and satellite pinions (32) in engagement with the central pinion (26) and the outer crown (28) and each mounted freely rotatable on a satellite carrier (36), the gear train (10) comprising means for lubricating the teeth and axes (34) of the satellite pinions (32), these means including an annular cup (56) integral with the satellite carrier (36) opened radially inward. According to the invention, an annular bailer (64) is arranged radially inside the cup (56) and applied annularly sealingly to it, the annular bailer (64) being fixed in rotation to the central pinion (26).

Abstract: An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover.

Abstract: The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor (2) carrying blades (3), a stationary housing (7), a mechanism (11, 12, 13, 14, 20) for regulating the pitch of the blades (3), which is connected to the rotor, and a control means (16, 17) mounted on the stationary housing (7) and comprising a control part (18) that can be moved in translation according to an axis (X) of rotation of the rotor (2), and a bearing (19) for load transfer between the control part (18) and said mechanism, characterised in that it also comprises a stationary track (23) supporting the elastic restoring means (26, 27) which are arranged so as to exert an axial restoring force on the control part (18) towards a determined position, preferably corresponding to the blade (3) feathering.

Abstract: An annular cap for collecting lubricating oil for turbomachine equipment is configured to extend around the equipment and to rotate about an axis. The cap includes through-orifices through which the oil can pass radially under the effect of spinning. The cap further includes means of deflecting the oil leaving the orifices in a direction substantially transverse to the axis and substantially tangential to the cap.

Abstract: The present disclosure describes a lubrication oil piping gutter of an aircraft turbomachine. The lubrication oil piping gutter can be used for a sun gear train reducer of the turbomachine. The gutter may include two lateral annular walls connected at their outer periphery by an annular bottom wall. In some embodiments, the annular bottom wall may include at least one oil evacuation opening in which is located a deflector configured to facilitate the flow of oil radially from the inside to the outside of the gutter.

Abstract: A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured to regulate the flow of oil in the cooling circuit as a function of an oil temperature at output of the enclosure and a pressure difference at the level of the jet.

Abstract: A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.

Abstract: A system for measuring an oil retention volume of a first member of an engine lubricating system, the injected oil flowing inside the first member mixed with a first air volume, the mixture forming a first fluid, the measuring system including an oil injector at the inlet of the lubricating system; a first flowmeter to measure a first oil flow rate at the inlet of the lubricating system; a second flowmeter at the outlet of the first member to measure a second flow rate of the first fluid at the outlet of the first member; a measuring device to calculate a first value representing a quantity of oil in a volume of the first fluid flowing inside the first member; a calculator to calculate a third oil flow rate at the outlet from the second flow rate of the first fluid measured and the first value calculated and the instantaneous oil retention volume in the first member from the comparison of the first oil flow rate with the third oil flow rate.

Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing and a pitch changing and control system for adjusting and controlling the setting of the blades. The rotor includes a central shaft and a blade support ring surrounding the central shaft, a front end of the ring that is connected to a front end of the central shaft, so as to create a rearward-opening annular space between the ring and the shaft. The annular space of the rotor housing the blade changing and control system and the central shaft are guided by a first bearing mounted in a stationary casing behind the ring. The fan has a tubular part connected to the stationary casing and extending into the annular space in front of the first bearing and carrying at least a first complementary bearing for guiding the shaft.

Abstract: The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).

Abstract: A mechanical assembly includes two mechanical parts rotatable relative to each other. A first part is provided with a cylindrical cavity, a second part (34) has at least one cylindrical portion engaged in the cylindrical cavity of the first part, and a gap separates the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement in rotation between the first part and the second part (34). A lubricant distribution network (37, 38) is configured for feeding the gap with a fluid lubricant so as to form a fluid bearing. A first surface (34s) selected from the inside surface of the cylindrical cavity of the first part and the outside surface of the cylindrical portion of the second part is provided with at least two lubricant admission orifices.

Abstract: An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover.

Abstract: A device for sealing the coaxial shafts of a turbomachine includes an annular seal able to perform sealing by contact with the outer shaft, and a lubricating device to lubricate the region of contact between the annular seal and the outer shaft.

Abstract: A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.

Abstract: The present disclosure relates to a mechanical assembly of two mechanical parts rotatable relative to each other and enabling a self-centering fluid bearing to be obtained; it comprises a first part provided with a cylindrical cavity, a second part (34) having at least one cylindrical portion engaged in the cylindrical cavity of the first part, a gap separating the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement in rotation between the first part and the second part (34), and a lubricant distribution network (37, 38) configured for feeding said gap with a fluid lubricant so as to form a fluid bearing; a first surface (34s) selected from the inside surface of the cylindrical cavity of the first part and the outside surface of the cylindrical portion of the second part is provided with at least two lubricant admission orifices (39a, 39b) that are spaced apart from each other by not less than 120° about the main axis (F) of the first surface (34s), and the first surfac

Abstract: A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.

Abstract: A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured to regulate the flow of oil in the cooling circuit as a function of an oil temperature at output of the enclosure and a pressure difference at the level of the jet.

Abstract: An annular cap for collecting lubricating oil for turbomachine equipment is configured to extend around the equipment and to rotate about an axis. The cap includes through-orifices through which the oil can pass radially under the effect of spinning. The cap further includes means of deflecting the oil leaving the orifices in a direction substantially transverse to the axis and substantially tangential to the cap.

Abstract: A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.