Planet carrier for a mechanical reduction gear of an aircraft turbine engine

Abstract

The invention relates to a planet carrier (113) for a mechanical reduction gear (110) of a turbine engine (1), comprising a cage (120), planet gears (112) and bearing shafts (113a) for the planet gears (112), the planet gears (112) being distributed around the main axis (X) and the bearing shafts (113a) passing axially through the planet gears in order to guide their rotation about secondary axes (Y) which are parallel to the main axis (X), characterised in that it further comprises lubricating sleeves (130) which are mounted respectively in the inner cavities (113b) of the bearing shafts (113a).

Description

[0001] DESCRIPTION

[0002] TITLE: SATELLITE MOUNT FOR A MECHANICAL REDUCTION GEARBOX ON AN AIRCRAFT TURBOMACHINE

[0003] Technical field of the invention

[0004] The present invention relates to the field of mechanical reducers for turbomachinery, in particular aircraft, and in particular reducers equipped with double-stage geared satellites.

[0005] Technical background

[0006] The state of the art includes in particular documents W0-A1 -2010 / 092263, FR-A1-2 987 416, FR-A1-3 011 901, FR-A1-3 041 054, FR-A1 -3 058 493, EP-A1 -4 060 174, GB-A-2 234 035, EP-B1 -3 657 0544, DE-B4-10 2010 017463 and DE-A1 -199 54 636.

[0007] The role of a mechanical reducer is to modify the speed and torque ratio between the input shaft and the output shaft of a mechanical system.

[0008] Newer generations of turbofan engines, particularly those with a high bypass ratio, incorporate a mechanical gearbox to drive the fan shaft. Typically, the gearbox's purpose is to transform the high rotational speed of the power turbine shaft into a slower rotational speed for the fan shaft.

[0009] Such a gearbox comprises a central pinion, called the sun gear, a ring gear, and pinions called planet gears, which mesh between the sun gear and the ring gear. The planet gears are held by a frame called the planet carrier. The sun gear, ring gear, and planet carrier are planetary gears because their axes of revolution coincide with the longitudinal X-axis of the turbomachine. The planet gears each have a different axis of revolution and are evenly spaced on the same operating diameter around the axis of the planet gears. These axes are parallel to the longitudinal X-axis. Several gearbox architectures exist. In state-of-the-art turbomachinery, gearboxes are of the planetary or epicyclic type. In other similar applications, there are so-called differential or compound architectures.

[0010] - On a planetary reducer, the planet carrier is fixed and the ring forms the output shaft of the device which rotates in the opposite direction to the sun.

[0011] - On an epicyclic reducer, the ring is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the sun.

[0012] - On a differential gearbox, no element is fixed in rotation. The ring rotates in the opposite direction to the solar and satellite carrier.

[0013] Gearboxes can consist of one or more meshing stages. This meshing is achieved in various ways, such as by contact, friction, or magnetic fields.

[0014] In this application, the terms "stage" or "toothing" refer to a series of teeth interlocking with a series of complementary teeth. A toothing can be internal or external.

[0015] A satellite can have one or two gear stages. A single-stage satellite has teeth that can be straight, helical, or chevron-shaped, with teeth on the same diameter. These teeth cooperate with both the sun gear and the crown gear.

[0016] A two-stage satellite comprises two sets of teeth or two series of teeth located on different diameters. One set of teeth cooperates with the sun gear and a second set of teeth cooperates with the crown gear.

[0017] One of the problems with a gearbox concerns its lubrication.

[0018] Lubrication of the various components of a gearbox is essential for the proper functioning of the system to prevent harmful events (gear seizure, pressure loss, bearing failure, etc.). A gearbox whose components are subjected to high mechanical stress, or which has a number of components requiring lubrication, has an inherently higher oil requirement. Distributing oil to all components presents a technical challenge to ensure the required flow rates for each component at all operating points, while minimizing the number of parts and mechanical interfaces, and integrating easily within the gearbox to limit the overall size of the lubrication system.

[0019] Current lubrication solutions offer a single oil inlet for the gearbox housing. Distribution occurs either from the front or upstream side, or from the rear or downstream side of the gearbox, via a wheel or ring fixed to the planet carrier. Delivering oil to the various stations is relatively easy in the case of a single-stage gearbox because the propellers of each planet are close together.

[0020] Integration becomes more complex in two-stage architectures (due to the distance between the propellers, the satellites, and the ring gear). It then becomes necessary to design a lubrication system that allows oil to flow from the front to the rear of the gearbox, through the gearbox (or from the rear to the front in the case of a single oil inlet downstream of the gearbox).

[0021] The invention offers an improvement to this technology, which is simple, efficient and economical.

[0022] Summary of the invention

[0023] The invention relates to a planet carrier for a mechanical turbomachine gearbox, particularly for aircraft, this planet carrier having a main axis and comprising a cage, planets and bearing shafts for these planets, the cage comprising two annular disks extending around the main axis, the bearing shafts being distributed around the main axis and being mounted between the disks of the cage, each of the bearing shafts having a generally elongated shape and comprising a first longitudinal end connected to a first of the disks, and a second opposite longitudinal end connected to a second of the disks, each of the bearing shafts being tubular and comprising an internal cavity which opens axially at the level of said first and second longitudinal ends, the planets being distributed around the main axis and traversed axially by the bearing shafts to guide them in rotation around secondary axes parallel to said main axis,characterized in that it further comprises lubrication sleeves which are mounted respectively in the internal cavities of the bearing shafts, each of the sleeves having a generally elongated shape and comprising at least a first lubricating oil inlet port which is located at a first longitudinal end of the sleeve and at the level of the first longitudinal end of the corresponding bearing shaft, and a first lubricating oil outlet port which is located at a second opposite longitudinal end of the sleeve and at the level of the second longitudinal end of the corresponding bearing shaft, each of the sleeves defining at least a first oil passage circuit between the inlet and outlet ports, and a second oil passage circuit around the sleeve and between the sleeve and the corresponding bearing shaft.

[0024] The invention thus proposes to circulate oil from one side of the planet carrier, and therefore of the gearbox, to the other via the planet carrier's bearing shafts. These bearing shafts are hollowed out to accommodate lubrication sleeves. This maximizes the use of the available space inside the bearing shafts to design mechanical components that supply oil both to the bearings for lubrication and to the other side of the gearbox for purposes such as lubricating gear teeth or meshing.

[0025] This invention is notably compatible with:

[0026] - of a multi-stage reducer;

[0027] - a planetary gearbox; with straight or herringbone teeth. The planet carrier according to the invention may comprise one or more of the following features, taken individually or in combination:

[0028] - the first and second circuits are independent of each other and do not communicate with each other;

[0029] - each of the sleeves includes a second oil inlet port which is independent of the first oil inlet port and which is connected to said second circuit in particular with regard to its supply;

[0030] - the first and second circuits are in fluidic communication;

[0031] - said first oil inlet port is connected to said first and second circuits in particular for the purpose of supplying them;

[0032] - said first circuit includes a straight pipeline which extends between the first oil inlet and outlet ports;

[0033] - said second circuit includes a tubular conduit which extends between the sleeve and the bearing axis, and at least one radial conduit in fluidic communication with the tubular conduit;

[0034] - said at least one radial pipeline has an internal radial end connected to said second oil inlet port, and an external radial end connected to the tubular pipeline;

[0035] - said at least one radial pipeline has an internal radial end connected to said first oil inlet port, and an external radial end connected to the tubular pipeline;

[0036] - said at least one radial pipe has a radially internal end connected to said straight pipe, and a radially external end connected to the tubular pipe;

[0037] - said radially internal end is connected to said first oil inlet port or to said straight pipeline by a flow restrictor;

[0038] - at least one annular sealing gasket is mounted between the first longitudinal end of each sleeve and the first longitudinal end of the corresponding bearing shaft, and at least one other annular sealing gasket is mounted between the second longitudinal end of each sleeve and the second longitudinal end of the corresponding bearing shaft, said second circuit extending between these gaskets;

[0039] - each of the sleeves is made from a single piece;

[0040] - each of the sleeves is formed by the assembly of at least two parts, a first tubular part of elongated shape intended to form said second circuit, and at least a second tubular part of elongated shape mounted inside the first part and intended to form said first circuit as well as at least one of said first oil inlet and outlet ports;

[0041] - the first piece is formed from a single piece with a ring which is located coaxially inside the first piece and connected to the first piece by an annular veil of material, said at least a second piece being engaged in this ring;

[0042] - said annular veil of material includes openings;

[0043] - the satellite carrier also includes an oil supply system which is located on one side of the cage and is connected to the first oil inlet ports of the sleeves,

[0044] - the satellite carrier also includes a jet lubrication system which is located on an opposite side of the cage and which is connected to the first oil outlet ports;

[0045] -- each of the bearing shafts includes radial through ports which open into the internal cavity of the bearing shaft and which are in fluidic communication with said second circuit;

[0046] -- the cage is made of a single piece.

[0047] The present invention further relates to a mechanical reducer for an aircraft turbomachine, this reducer comprising a satellite carrier as described above, a solar element which is housed in the cage and which is meshed with the satellites, and a ring which extends around the cage and which is meshed with the satellites.

[0048] The present invention further relates to an aircraft turbomachine comprising a satellite carrier or a reduction gear as described above. Brief description of the figures

[0049] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:

[0050] [Fig.1] Figure 1 is a schematic axial cross-sectional view of an aircraft turbomachine,

[0051] [Fig.2] Figure 2 is a partial and highly schematic axial section of a mechanical reducer,

[0052] [Fig.3] Figure 3 is a partial schematic axial cross-sectional view of a planet carrier according to a first embodiment of the invention, and more precisely shows a bearing shaft and a lubrication sleeve of this planet carrier,

[0053] [Fig. 4] Figure 4 is a front view of the lubrication sleeve of Figure 3.

[0054] [Fig. 5] Figure 5 is a perspective view of the lubrication sleeve of Figure 3,

[0055] [Fig. 6] Figure 6 is a partial schematic axial cross-sectional view of a planet carrier according to a second embodiment of the invention, and more precisely shows a bearing shaft and a lubrication sleeve of this planet carrier,

[0056] [Fig. 7] Figure 7 is a front view of the lubrication sleeve of Figure 6,

[0057] [Fig. 8] Figure 8 is a perspective view of the lubrication sleeve of Figure 6,

[0058] [Fig.9] Figure 9 is a partial schematic axial cross-sectional view of a planet carrier according to a third embodiment of the invention, and more precisely shows a bearing shaft and a lubrication sleeve of this planet carrier,

[0059] [Fig. 10] Figure 10 is a front view of the lubrication sleeve of Figure 9, [Fig. 11] Figure 11 is a perspective view of the lubrication sleeve of Figure 9, and

[0060] [Fig.12] Figure 12 is a partial schematic axial cross-sectional view of a reducer according to the invention.

[0061] Detailed description of the invention

[0062] Figure 1 depicts a turbomachine 1 which, in a conventional manner, comprises a rotational shaft X, a fan S, a low-pressure compressor 1a, a high-pressure compressor 1b, an annular combustion chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1e, and an exhaust nozzle 1h. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 2 and together form a high-pressure (HP) unit. The low-pressure compressor 1a and the low-pressure turbine 1e are connected by a low-pressure shaft 3 and together form a low-pressure (LP) unit.

[0063] The blower S is driven by a blower shaft 4 which is driven to the BP shaft 3 by means of a reducer 10. This reducer 10 is generally of the planetary or epicycloidal type.

[0064] The following description relates to a planetary type reducer in which the ring gear is mobile in rotation.

[0065] The gearbox 10 is positioned in the upstream part of the turbomachine. A fixed structure schematically comprising, here, an upstream part 5a and a downstream part 5b which make up the motor or stator housing 5 is arranged to form an enclosure E surrounding the gearbox 10. This enclosure E is closed upstream by seals at the level of a bearing allowing the passage of the blower shaft 4, and downstream by seals at the level of the passage of the BP shaft 3.

[0066] Figure 2 shows a gearbox 10 which can take on different forms depending on whether certain parts are fixed or rotating. At the input, the gearbox 10 is connected to the shaft BP 3, for example via internal splines 7a. Thus, the shaft BP 3 drives a planetary gear called the sun gear 11. Typically, the sun gear 11, whose axis of rotation coincides with that of the turbomachine X, drives a series of gears called sun gears 12, which are equally spaced around the same diameter around the axis of rotation X. This diameter is equal to twice the operating center distance between the sun gear 11 and the sun gears 12. The number of sun gears 12 is generally defined as between three and seven for this type of application.

[0067] The set of satellites 12 is held by a frame called the satellite carrier 13. Each satellite 12 rotates around its own Y axis, and meshes with the ring 14.

[0068] ■ In this planetary configuration, the set of satellites 12 is held by a satellite carrier 13 which is fixed to the motor or stator housing 5. Each satellite drives the ring which is brought to the blower shaft 4 via a ring carrier 15.

[0069] Each satellite 12 is mounted to rotate freely using a bearing 8, for example, a roller bearing or hydrodynamic bearing. Each bearing 8 is mounted on one of the axes 13a of the satellite carrier 13, and all the axes 13a are positioned relative to each other using a cage of the satellite carrier 13. There is a number of axes 13a and bearings 8 equal to the number of satellites 12. For reasons of operation, assembly, manufacturing, inspection, repair, or replacement, the axes 13a and cage may be separated into several parts.

[0070] In this application, an axis 13a is referred to as a bearing or support axis.

[0071] For the same reasons mentioned above, the teeth of a reduction gear can be separated into several helices, each with a median plane. In the example shown, the ring gear 14 is separated into two half-rings:

[0072] ■ An upstream half-crown 14a consisting of a rim 14aa and a mounting flange half 14ab. The upstream helix of the reduction gear teeth is located on the rim 14aa. This upstream helix meshes with that of the satellite 12, which meshes with that of the solar 11. ■ A downstream half-crown 14b consisting of a rim 14ba and a mounting flange half 14bb. The downstream helix of the reduction gear teeth is located on the rim 14ba. This downstream helix meshes with that of the satellite 12, which meshes with that of the solar 11.

[0073] The mounting half-flange 14ab of the upstream crown 14a and the mounting half-flange 14bb of the downstream crown 14b form the mounting flange 14c of the crown. The crown 14 is fixed to a crown carrier by assembling the mounting flange 14c of the crown and the mounting flange 15a of the crown carrier 15 using a bolted assembly, for example.

[0074] The arrows in Figure 2 illustrate the oil flow within the gearbox 10. The oil enters the gearbox 10 from the stator section 5 via a distributor 16 by various means, which will not be detailed in this view as they are specific to one or more types of architecture. The distributor 16 is generally divided into two parts, each typically repeated with the same number of planetary gears 12. The injectors 17a lubricate the gear teeth, and the arms 17b lubricate the bearings. The oil is supplied to the injector 17a and exits through the end 17c to lubricate the gear teeth. The oil is also supplied to the arm 17b and flows through the inlet 17d of the bearing shaft 13a. The oil then circulates in an internal cavity 13b of the shaft 13a and then exits through orifices 13c in order to lubricate the bearings 8 of the satellites 12.

[0075] Figures 3 to 5 illustrate a first embodiment of the invention and in particular of a chassis constituting a satellite carrier 113.

[0076] Within the framework of the present invention, the satellite carrier 113 is defined as essentially comprising: a cage 120, satellites 112 and bearing or support axes 113a for the satellites 112.

[0077] Cage 120 comprises two parallel disks, 120a and 120b, spaced apart and extending perpendicularly to the X-axis. Disks 120a and 120b are generally circular and centered on the X-axis. They can be connected by bridges, which are not shown in the drawings. These bridges define, for example, slots between themselves and the disks, configured to receive satellites 112.

[0078] The 120 cage is preferably of the monobloc type, with the 120a, 120b discs and the bridges forming a single piece.

[0079] In the example shown, the discs 120a, 120b include aligned mounting holes 124 for the shafts 113a.

[0080] The axes 113a are distributed around the X axis and are mounted between the disks 120a, 120b.

[0081] Each of the axes 113a has a generally elongated shape and comprises a first longitudinal end 122 connected to a first disk 120a, and a second opposite longitudinal end 126 connected to the second disk 120b. In the example shown, the first end is engaged in one of the orifices 124 of the first disk 120a, and the second end 126 is engaged in one of the orifices 124 of the second disk 120b.

[0082] Each of the axes 113a is tubular and includes an internal cavity 113b which opens axially at the ends 122, 126.

[0083] The satellites 112 are distributed around the X-axis and are traversed axially by the axes 113a to guide their rotation around the Y-axes. The satellites 112 can be mounted directly on the axes 113a if the latter define smooth bearings for guiding the satellites. Alternatively, roller bearings could be mounted between the axes 113a and the satellites 112 for their guidance.

[0084] The planet carrier 113 further includes lubrication sleeves 130 which are mounted respectively in the internal cavities 113b of the shafts 113a.

[0085] Each of the sleeves 130 has a generally elongated shape and includes at least one first lubricating oil inlet port 132 and one first lubricating oil outlet port 134. The first inlet port 132 is located at a first longitudinal end 136 of the sleeve 130 and at the first end 122 of the axis 113a.

[0086] At least one annular sealing gasket 140 is preferably mounted between the first longitudinal end 136 of each sleeve 130 and the first longitudinal end 122 of the shaft 113a. The gasket 140 surrounds the first longitudinal end 136.

[0087] At least one other annular sealing gasket 142 is mounted between the second longitudinal end 138 of each sleeve 130 and the second longitudinal end 126 of the shaft 113a. The gasket 142 surrounds the second longitudinal end 138.

[0088] The first exit port 134 is located at a second longitudinal end 138 opposite the sleeve 130 and at the level of the second end 126 of the axis 113a.

[0089] Each of the sleeves 130 defines at least one first circuit 144 for the passage of oil between the inlet and outlet ports 132, 134, and a second circuit 146 for the passage of oil around the sleeve 130 and between the sleeve 130 and the corresponding shaft 113a.

[0090] The second circuit 146 preferably extends between the joints 140, 142 and is connected to the aforementioned orifices 113c.

[0091] The first circuit 144 includes a straight conduit 148 which extends between the inlet and outlet ports 132, 134.

[0092] The second circuit 146 may include a tubular conduit 150 extending between the sleeve 130 and the axis 113a, and at least one radial conduit 152 in fluidic communication with the tubular conduit 150. The second circuit 146 may include several radial conduits 152 distributed around the Y axis.

[0093] In the embodiment shown in Figures 3 to 5, the first and second circuits 144, 146 are independent of each other and do not communicate with each other. Each of the sleeves 130 may include a second oil inlet port 148, which is independent of the first port 132 and which supplies the second circuit 146.

[0094] Each radial pipe 152 has an internal radial end connected to the second port 148, and an external radial end connected to the tubular pipe 150.

[0095] In the example shown in Figures 3 to 5, each of the sleeves 130 is formed in one piece. These figures show that the sleeve 130 is hollow and that the tubular conduit 150 is formed as a projection on an internal cylindrical surface of the sleeve body 130. It is further shown that the ports 132, 148 are located side by side and are formed within a material web 154 that extends transversely within the body of the sleeve 130 and in which the radial conduit 152 is formed. This material web 154 may include openings 156 to lighten the sleeve 130.

[0096] In figures 3 to 5, the arrows show the path of the oil from ports 132, 148 to circuits 144, 146. The oil arriving through port 132 flows through pipe 148 to reach port 134 and thus passes axially through the satellite carrier 113. The oil arriving through port 148 supplies pipes 152, 150 and the bearings 108 of the satellites 112 through ports 113c.

[0097] In the embodiments shown in Figures 6 to 8 on the one hand, and 9 to 11 on the other, the first and second circuits 144, 146 are in fluidic communication. For this purpose, the first oil inlet port 132 is configured to supply both the first and second circuits 144, 146.

[0098] In the embodiment variant of Figures 6 to 8, the radial pipe or each radial pipe 152 has an internal radial end connected to the first port 132 or to the straight pipe 144, and an external radial end connected to the tubular pipe 150. Each of the sleeves 130 can be formed by the assembly of at least two parts.

[0099] In the variant shown in Figures 6 to 8, each sleeve 130 is formed by assembling three parts. In the variant shown in Figures 9 to 11, each sleeve 130 is formed by assembling two parts.

[0100] A first tubular piece 160 of elongated shape is intended to form the second circuit 150. At least one other tubular piece 162, 164 of elongated shape is mounted inside the first piece 160 and is intended to form the first circuit 144 as well as at least one of said first ports 132, 134.

[0101] In the example shown, the first part 160 is formed in one piece with a ring 166 which is located coaxially inside the first part 160 and connected to the first part 160 by an annular veil of material 154.

[0102] In the variant shown in Figures 6 to 8, the straight pipe 144 is formed by two parts 162, 164 which are arranged coaxially end to end and are engaged in the ring 166. Part 162 has a longitudinal end engaged by male-female insertion in the ring 166 and an opposite longitudinal end forming the inlet port 132. Part 164 has a longitudinal end engaged by male-female insertion in the ring 166 and an opposite longitudinal end forming the outlet port 134.

[0103] Each radial pipe 152 can be in fluidic communication with an axial clearance provided between the ends opposite parts 162, 164, or with one or more radial passages in one of these parts. In the case of Figures 6 to 8, it is part 162 that includes this type of passage. In particular, the passage in part 162 forms a flow restrictor 168, that is to say, a small-section passage designed to reduce the flow rate of the fluid passing through it.

[0104] In the variant of figures 9 to 11, the straight channel 144 is formed by a single piece 162 which passes axially through the ring 166. The piece 162 includes a longitudinal end forming the inlet port 132, and an opposite longitudinal end forming the outlet port 134.

[0105] Each radial channel 152 can be in fluidic communication with one or more radial passages of the part, which can also be in the form of flow restrictor(s) 168.

[0106] The veil 154 which connects the ring 166 to the part 160 is preferably openwork to include openings 156.

[0107] In Figures 6 to 11, the arrows show the path of the oil from port 132 to circuits 144 and 146. The oil arriving through port 132 flows through pipe 148 to reach port 134 and thus passes axially through the planet carrier 113. Some of this oil passes through restrictor(s) 168 to supply pipes 152 and 150 and the bearings 108 of the planets 112 via ports 113c. It is therefore clear that restrictor(s) 168 is / are sized to generate a sufficient oil flow for the lubrication of the bearings 108.

[0108] Figure 12 shows a satellite carrier 113 and a reducer 110 according to the invention.

[0109] An oil supply system 170 is located on one side of the satellite carrier 113 and is connected to the ports 132 of the sleeves 130.

[0110] A lubrication system 172 equipped with nozzles 174 is located on an opposite side of the planet carrier 113 and is connected to the ports 134 of the sleeves 130.

[0111] The satellite carrier 113 is advantageously fixed, the reducer 110 then being of the planetary type as mentioned above.

[0112] The 112 satellites may be double-stage as shown and therefore include two separate gears meshed respectively with the solar (not visible) and the 114 crown.

[0113] Bearings 108 are interposed between the satellites 112 and the shafts 113a. The invention avoids axial stresses that could be caused by sealing flanges on the upstream and downstream side of the satellite carrier. The invention also allows the satellite carrier to maintain freedom of movement under load, which must not be affected by the lubrication system. Furthermore, the invention simplifies the design of the annular cage discs 120 by eliminating the need for sealing flanges.

[0114] The invention offers several other advantages, including: - reducing the number of mechanical parts in the lubrication system,

[0115] - reducing the number of mechanical interfaces in this lubrication system,

[0116] - reducing bulk,

[0117] - the reduction of mass, etc.

Claims

DEMANDS 1. Planet carrier (113) for a mechanical gearbox (110) of a turbomachine (1), particularly an aircraft, this planet carrier (113) having a main axis (X) and comprising a cage (120), planets (112) and bearing shafts (113a) of these planets (112), the cage comprising two annular disks (120a, 120b) extending around the main axis (X), the bearing shafts (113a) being distributed around the main axis (X) and being mounted between the disks (120a, 120b) of the cage (120), each of the bearing shafts (113a) having a generally elongated shape and comprising a first longitudinal end (122) connected to a first of the disks (120a), and a second opposite longitudinal end (124) connected to a second of the disks (120b), each of the bearing shafts (113a) being tubular and comprising an internal cavity (113b) which opens axially at the level of said first and second longitudinal extremities (122, 124),the satellites (112) being distributed around the main axis (X) and traversed axially by the bearing axes (113a) to guide them in rotation around secondary axes (Y) parallel to said main axis (X), characterized in that it further comprises lubrication sleeves (130) which are mounted respectively in the internal cavities (113b) of the bearing axes (113a), each of the sleeves (130) having a generally elongated shape and comprising at least a first lubricating oil inlet port (132) which is located at a first longitudinal end (136) of the sleeve (130) and at the level of the first longitudinal end (122) of the corresponding bearing axis (113a), and a first lubricating oil outlet port (134) which is located at a second opposite longitudinal end (138) of the sleeve (130) and at the level of the second longitudinal end (124) of the corresponding bearing axis (113a),each of the sleeves (130) defining at least one first circuit (144) for the passage of oil between the inlet and outlet ports (132, 134), and a second circuit, (146) of oil passage around the sleeve (130) and between the sleeve (130) and the corresponding bearing shaft (113a).

2. Satellite carrier (113) according to claim 1, wherein the first and second circuits (144, 146) are independent of each other and do not communicate with each other.

3. Satellite carrier (113) according to claim 2, in which each of the sleeves (130) includes a second oil inlet port (148) which is independent of the first oil inlet port (132) and which is connected to said second circuit (146).

4. Satellite carrier (113) according to claim 1, in which the first and second circuits (144, 146) are in fluidic communication.

5. Satellite carrier (113) according to claim 4, in which said first oil inlet port (132) is connected to said first and second circuits (144, 146).

6. Satellite carrier (113) according to any one of the preceding claims, wherein said first circuit (144) comprises a straight conduit (148) which extends between the first oil inlet and outlet ports (132, 134).

7. Satellite carrier (113) according to any one of the preceding claims, wherein said second circuit (146) comprises a tubular conduit (150) extending between the sleeve (130) and the bearing axis (113a), and at least one radial conduit (152) in fluidic communication with the tubular conduit (150).

8. Satellite carrier (113) according to claim 7, depending on claim 3, wherein said at least one radial channel (152) has a radially internal end connected to said second oil inlet port (148), and a radially external end connected to the tubular channel (150).

9. Satellite carrier (113) according to claim 7, depending on claim 5, wherein said at least one radial conduit (152) has a radially internal end connected to said first inlet port (132) of oil, and a radially external end connected to the tubular pipeline (150).

10. Satellite carrier (113) according to claim 7, depending on claim 6, wherein said at least one radial channel (152) has a radially internal end connected to said straight channel (148), and a radially external end connected to the tubular channel (150).

11. Satellite carrier (113) according to claim 10, wherein said radially internal end is connected to said first oil inlet port (132) or to said straight pipeline (148) by a flow restrictor (168).

12. Planet carrier (113) according to any one of the preceding claims, wherein at least one annular sealing seal (140) is mounted between the first longitudinal end (136) of each sleeve (130) and the first longitudinal end (122) of the corresponding bearing shaft (113a), and at least one other annular sealing seal (142) is mounted between the second longitudinal end (138) of each sleeve (130) and the second longitudinal end (124) of the corresponding bearing shaft (113a), said second circuit (146) extending between these seals (140, 142).

13. Satellite carrier (113) according to any one of claims 1 to 12, wherein each of the sleeves (130) is formed from a single piece.

14. Satellite carrier (113) according to any one of claims 1 to 12, in which each of the sleeves (130) is formed by the assembly of at least two parts (162, 164), a first tubular part (162) of elongated shape intended to form said second circuit (146), and at least a second tubular part (164) of elongated shape mounted inside the first part (162) and intended to form said first circuit (144) as well as at least one of said first ports (132, 134) for oil inlet and outlet.

15. Satellite carrier (113) according to claim 14, wherein the first part (162) is formed in one piece with a ring (166) which is located coaxially inside the first part (162) and connected to the first piece (162) by an annular veil of material (154), said at least a second piece (164) being engaged in this ring (166).

16. Planet carrier (113) according to claim 15, wherein said annular sheet of material (154) comprises openings (166).

17. Planet carrier (113) according to any one of the preceding claims, wherein it further comprises an oil supply system (170) located on one side of the cage (120) and connected to the first oil inlet ports (132) of the sleeves (130), and a nozzle lubrication system (172) (174) located on an opposite side of the cage (120) and connected to the first oil outlet ports (134).

18. Mechanical reducer (110) for an aircraft turbomachine, this reducer comprising a satellite carrier (113) according to any one of the preceding claims, a solar element (111) which is housed in the cage (120) and which is meshed with the satellites (112), and a ring gear (114) which extends around the cage (120) and which is meshed with the satellites (112).

19. Aircraft turbomachine (1), comprising a reduction gear (110) according to the preceding claim.

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