Abstract: A planet carrier for a speed-reducing unit with an epicyclic gear train for a turbine engine, said planet carrier comprising a cage defining an internal space for assembling a central sun gear having an axis of rotation and an annular row of planet gears disposed around the axis and meshed with said sun gear, said cage comprising two substantially parallel annular walls centered on said axis and a cylindrical wall connecting said annular walls to their outer periphery, a first one of said annular walls being connected to a substantially cylindrical body, wherein a second one of said annular walls is formed as a single part with a lubrication grove, channel or duct.

Abstract: The reduction gear includes a pair of gears installed in parallel between two shafts and each provided with a mobile wheel free to move axially to engage in turn with one of the shafts and to transmit movement with different ratios. Since the gear teeth are helical, opposite forces on the reduction gear make it changeover from one reduction ratio to the other. No external control is necessary. Application to mechanical transmissions between an engine and a reversible electrical machine (starter or generator), that starts the motor with a large speed reduction and generates electricity with a smaller reduction.

Abstract: An oil jet for a turbine engine, comprising a body including a circulation pipe intended for the flow of a pressurized fluid. The jet's body comprises a first part and a second part between which a resiliently deformable membrane is inserted, said membrane being capable of deforming between a sealed position in which it prevents the circulation of the fluid in the pipe and a position in which it allows the circulation of fluid in the pipe. The second part includes bearing means configured to exert a force on the membrane positioned in the opposite direction to the circulation of fluid so as to preload the membrane when in blocked position.

Abstract: A planet carrier for a speed-reducing unit with a planetary gear set is provided. The planet carrier generally includes a torque transmission part having a longitudinal axis and an annular cage extending about the axis and connected to one longitudinal end of the part. The cage may include two sides extending radially relative to the axis and connected by bridges, and seats extending axially between the flanks and configured to support planetary gears rotatably mounted about the seats. The curved members may include at least two corresponding bars each inclined relative to a longitudinal plane passing both through the axis and substantially through the corresponding bar.

Abstract: An annular power transmission element with a longitudinal axis that has a first annular part, a second annular part with torque transmission means and a third annular part. The first, second and third annular parts are integral with each other. The first annular part and the third annular part are made of a first metallic material and the second annular part is made of a second metallic material having a density greater than the density of the first metallic material. The second annular part is locked longitudinally between the first annular part and the third annular part and radially on the first annular part, the first annular part is in contact with the third annular part and welded thereto.

Abstract: A method of chromating a part including an aluminum-based alloy, the method including the steps of providing the part including a layer based on aluminum oxide on at least one of its surfaces, of immersing the part in a chromating bath including chromium III, and of performing chemical conversion of the part in the chromating bath. The invention also provides a part obtained by the method.

Abstract: A wheel for distributing a lubricant in a turbine engine has an axis from which an annular cavity extends, open radially towards the axis and from which first and second lubricant supply lines depart for various members to be lubricated. Parallel to the axis, the annular cavity is split into at least a first and a second annular sub-cavity, which are separated by a substantially radial partition and which communicate with the first and second lines respectively.

Abstract: A device of the reduction gear type or of the differential type for a turbine engine of an aircraft is described. The device includes a central sun gear with a rotation axis X, a ring gear extending about the axis X and the sun gear, and a planetary carrier supporting an annular row of planet gears arranged between the sun gear and the ring gear. In some embodiments, the planetary carrier is engaged with the sun gear and the ring gear. The planet gears may have rotation axes Y which may be substantially parallel to said axis X. In some instances, each of the planet gears may be rotationally guided by at least one bearing extending about a tubular support with an axis Y of the planetary carrier. In some embodiments, the tubular support includes an inner cavity for receiving oil and substantially radial through-orifices for the passage of oil from the inner cavity to the at least one bearing. In some embodiments, at least two bearings may be mounted coaxially and adjacently around the support.

Abstract: A connecting rod, in particular for a turbine engine, includes an intermediate body with a general elongated shape. Connecting heads may be located at the longitudinal ends of the elongated shape, which may include holes having axes that are, for example, substantially parallel. The connecting rod is characterized in that the heads are assembled or formed as a single piece with at least one part of the body. At least one of the heads includes an alveolar annular part, about the axis of the hole, forming a vibrating filter and having a flexural and/or compressive deformation capacity greater than that of the rest of the connecting rod and, in particular, that of the body.

Abstract: A bowl for supplying oil to at least two oil-distribution circuits which are connected to a planet carrier of an epicyclic reduction gearbox, the planet carrier rotating and the oil coming from a fixed oil ejector, the bowl being designed to be secured to the planet carrier and having a substantially cylindrical shape and being open radially towards the inside with respect to an axis. The bowl is divided into a circumferential succession of separate cups each designed to communicate with one of the oil distribution circuits A reduction gearbox with its supply device and a method of operation in a turbomachine are also disclosed.

Abstract: Speed reduction gear comprising two intermediate transmission lines, in particular for a turbine engine, comprising an input line (12) and an output line that is driven by the input line via said intermediate transmission lines, said intermediate transmission lines being substantially parallel, characterized in that said reduction gear comprises means for distributing loads between said intermediate lines, said load distribution means comprising swiveling coupling means (30) for rotatably coupling one end of the input line, and oil-damping means (40, 50) for damping radial movements of an opposite end of the input line.

Abstract: The invention relates to a method for assembling (S) a planet carrier (16), comprising the following steps: separately producing (S1) the cage (20) and the cage carrier (30), providing a machining allowance at one element from among the through-holes (23, 25) in at least one upright (21) of the cage (20) or the through-hole (32) in a finger bar (31) of the cage carrier (30), and/or at one element from among a bearing seat (26) or a rolling bearing seat (41, 42); assembling (S2) the cage (20) and the cage carrier (30) and securing (S3) same to produce a one-piece assembly; determining (S4) the position of a reference axis (Y1, Y2) linked to the cage (20), to the cage carrier (30) and/or to the shaft (40); and, taking account of the position of the reference axis (Y1, Y2), machining (S5) all or part of the machining allowances.

Abstract: A device lubricates elements of an accessory drive system of an aircraft. The device includes a pinion having a pinion shank that is hollow and that has an axis of rotation, a shaft arranged inside the pinion shank and extending along the axis of rotation, a space between the shaft and the pinion shank allowing displacement of oil, an oil reservoir arranged facing the space, at a first end of the pinion shank, and an oil outlet duct arranged facing the space, at a second end of the pinion shank. The pinion shank and the shaft together form a pump and cooperate to drive the oil from the reservoir toward the oil outlet duct thanks to the rotation of the pinion shank around the shaft.

Abstract: A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.

Abstract: The invention relates to equipment (40) for disassembling a planet carrier (14), said planet carrier (14) comprising: a cage (20) comprising an inner bridge (24) and an outer bridge (26); a cage carrier (30) comprising at least one finger bar (31) to be inserted between the inner bridge (24) and the outer bridge (26); and a connection shaft (14) housed in through-holes (25, 27, 33) formed in the bridges (24, 26) and in the finger bar (31), such as to retain the cage (20) on the cage carrier (30). The equipment comprises: a jack (41) including a body and a piston (42), said piston (42) being designed to apply a force to the connection shaft (14); and a support (43) designed to bear on the finger bar (31) when the piston (42) applies a force to the connection shaft (14).

Abstract: A device for filtering a flow of gas conveying liquid or solid particles in a flow channel. According to the invention, the particles are imparted a speed that is high enough to project same by inertia into the opening of a recovery channel formed inside the flow channel, while the gas from the flow bypasses said opening due to a specific configuration of the flow conditions of a perfect fluid in the flow channel and in the collection channel.

Abstract: A reduction gear including an input shaft including an input gear, an output shaft including an output gear, and two intermediate transmission lines, each intermediate transmission line including an intermediate shaft including a first stage of teeth and a second stage of teeth, the stages rotating as one, and an additional gear for meshing respectively with the first stage of teeth and the input gear, or with the second stage of teeth and the output gear, and the reduction gear wherein the input gear or the output gear meshing with the additional gears is axially offset with respect to the stage of teeth of the intermediate shafts meshing with the additional gears.

Abstract: An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.

Abstract: The invention concerns a device (1) for hoop reinforcing of restrictors inside at least two hydraulic supply standby systems of a journal bearing. Said device is remarkable in that it comprises: a frame (2) for receiving said hearing, a syringe (3) for introducing said restrictors and a torque pick-off spindle (4), and in that said frame (2) comprises: a cradle (21), a guide plate (23) pierced with two guide openings (231), inclined at the same angle as those of said backup systems of the bearing, so as to be located in the extension of same when the bearing is in the frame, said guide openings (231) being shaped to receive said syringe (3) or said torque pick-off spindle (4).

Abstract: An aircraft drive chain including a plurality of main gears engaging with each other, a first main gear including a wall defining an inner space, an outer set of gear teeth being placed on an outer surface of the wall, the outer set of gear teeth engaging with at least one second main gear, a gear system being built into the inner space, the first main gear and the gear system being jointly configured so as to form a gearbox or reducer and ensure mechanical power transfer between a drive member and a slave member, the gear system being mounted onto the wall with a decoupling member.