Planet gear provided with a lubricant discharge device for a speed reducer of a turbomachine

Abstract

The invention relates to a planet gear (4) for a speed reducer of a turbomachine, comprising: - a planet gear rim (43) internally defining an internal orifice (44); - an external toothing comprising a series of upstream teeth (41) and a series of downstream teeth (42) in a double helical gear configuration, these series of teeth being axially spaced apart along a planet gear axis (40) on either side of a planet gear groove (45); and - a lubricant discharge device (46) for discharging a lubricant from the series of upstream teeth and the series of downstream teeth towards the internal orifice, comprising a plurality of scoops (47) which are mounted securely on the planet gear rim inside the planet gear groove and project radially beyond the external toothing, each of the scoops facing a hole (48) which passes radially through the planet gear groove so as to open out into the internal orifice.

Description

[0001] DESCRIPTION

[0002] TITLE: Satellite equipped with a lubricant evacuation device for a turbomachine speed reducer

[0003] [Technical field]

[0004] The invention relates to a satellite for a speed reducer of a turbomachine, and more particularly a satellite equipped with two sets of chevron teeth and a lubricant evacuation device.

[0005] It also relates to a speed reducer equipped with several of these satellites, as well as to a turbomachine, such as a turbojet or turboprop of an aircraft, equipped with such a speed reducer.

[0006] [State of the art]

[0007] A turbofan engine, such as a turbojet or turboprop, comprises at least one propeller or fan generating a primary and a secondary flow, and a speed reducer to drive the propeller or fan shaft (called the fan shaft) at a slow speed from a high-speed rotating power shaft of a turbine.

[0008] Such a speed reducer comprises a central pinion, called the sun gear, and a ring gear, both coaxial with a central axis (corresponding to the axis of the power shaft), as well as peripheral pinions, called planet gears, which mesh between the sun gear and the ring gear. The planet gears are held by a frame called a planet carrier, and they have axes of revolution, called planet axes, which are parallel to the central axis and evenly spaced around the same operating diameter around the central axis.

[0009] There are several reduction gear architectures, including the planetary architecture in which the planet carrier is fixed and the ring gear is coupled to the blower shaft which rotates in the opposite direction to the sun, and the epicycloidal architecture in which the ring gear is fixed and the planet carrier is coupled to the blower shaft which rotates in the same direction as the sun.

[0010] The satellites of a reduction gear can comprise one or two gear stages. A "stage" is understood to mean a set of teeth configured to mesh with a complementary set of teeth. This set of teeth can consist of a single series of teeth (for example, a series of straight or helical teeth) or two series of teeth spaced axially along the satellite's axis, i.e., at an axial distance from each other (for example, two series of teeth arranged in a herringbone pattern, in which case it is called a herringbone gear). A single-stage satellite comprises a single set of teeth whose teeth are located on the same diameter and which meshes with both the sun gear and the ring gear. A double-stage satellite comprises two sets of teeth whose teeth are located on different diameters, with one set meshing with the sun gear and the other with the ring gear.

[0011] The operation of a speed reducer, particularly on a turbojet with a high bypass ratio fan, requires a particularly high flow rate of lubricant (classically a lubricating oil) to ensure the lubrication and cooling of the various components, such as the gears and bearings, as well as the dissipation of a large amount of power.

[0012] One of the problems with these speed reducers is therefore related to the recovery and evacuation of lubricant to obtain the desired flow rate, while integrating into a cluttered and restricted environment, as is the case within a turbomachine.

[0013] [Summary of the invention]

[0014] One object of the invention is to facilitate the recovery and evacuation of lubricant within a satellite of a speed reducer, and in particular of a single-stage satellite comprising a single herringbone toothing, i.e. two series of teeth spaced axially along the axis of the satellite and arranged in a herringbone pattern.

[0015] Another aim of the invention is to avoid increasing the radial size of the satellite and therefore of the speed reducer.

[0016] Thus, the invention proposes a satellite for a speed reducer of a turbomachine, this satellite comprising:

[0017] - a satellite rim of annular shape around a satellite axis and defining internally an internal orifice;

[0018] - an external toothing system projecting outwards from the satellite rim and comprising a series of upstream teeth and a series of downstream teeth arranged in a chevron pattern, spaced axially along the satellite axis on either side of a satellite groove; and

[0019] - a lubricant evacuation device for evacuating lubricant from the upstream set of teeth and the downstream set of teeth towards the internal orifice, this lubricant evacuation device comprising several scoops which are mounted integrally on the satellite rim inside the satellite groove and which extend radially beyond the external teeth, each of the scoops facing a hole which passes radially through the satellite groove to open into the internal orifice.

[0020] The invention relates to a single-stage satellite comprising a single external herringbone gear set, incorporating scoops that collect the lubricant flowing between the teeth of each of the two sets of teeth, towards the satellite groove, to be directed towards the inside of the satellite rim (into its internal orifice), and finally to be expelled to the sides of the satellite by centrifugal force. The scoops extend radially above the teeth so that they can engage inside the crown groove (described later), thus capturing more lubricant and guiding it through the holes without interruption of the flow.

[0021] According to one characteristic, each scoop includes a wall that protrudes from the satellite throat and has an inner face facing the corresponding hole and an outer face opposite the inner face.

[0022] Thus, like a paddle wheel, the walls of the scoops form blades that bend and guide the lubricant towards the holes and therefore towards the internal orifice of the satellite rim.

[0023] According to one possibility, the wall of each of the scoops is curved in shape so that its inner face is concave.

[0024] Thus, in a cutting plane orthogonal to the satellite axis, the walls of the scoops are curved to guide the lubricant without interruption of flow.

[0025] According to another possibility, the wall of each of the scoops comprises two folded edges directed towards the inner face and extending orthogonally to the satellite axis.

[0026] The presence of these two folded edges allows the lubricant to be channeled inwards, thus preventing used lubricant from re-entering the teeth.

[0027] According to another possibility, the scoops are regularly distributed around the satellite's axis.

[0028] Thus, these scoops are evenly distributed around the perimeter of the satellite to promote its balance.

[0029] Depending on the possibility, the scoops are made in the form of a single monobloc piece or are made in the form of an assembly.

[0030] In a particular design, each of the scoops is mounted in the corresponding hole, or in the extension of the corresponding hole.

[0031] This shape facilitates the guidance of the lubricant towards the hole, and therefore towards the internal orifice.

[0032] Advantageously, each scoop is attached to a ring arranged inside the internal orifice, so that the scoops protrude from this ring to pass through the corresponding holes.

[0033] The advantage of this configuration is that the scoops are held in place by the ring located inside the satellite rim, which improves their resistance to centrifugal force; however, it should be noted that these scoops can alternatively be mounted on a ring outside the satellite rim. The invention also relates to a speed reducer for a turbomachine, for example, a turbojet or turboprop engine of an aircraft, comprising:

[0034] - a mobile solar panel rotating around a central axis;

[0035] - a crown mounted coaxially to the central axis and extending around the solar, and the crown comprises a series of upstream crown teeth, a series of downstream crown teeth and a crown groove extending circumferentially between the series of upstream crown teeth and the series of downstream crown teeth;

[0036] - satellites in mesh with the solar and with the crown which is arranged around the satellites, each of the satellites conforming to the description made above and its upstream series of teeth and its downstream series of teeth are in mesh respectively with the upstream series of crown teeth and the downstream series of crown teeth, and the crown groove extends in front of the satellite groove so that each of its scoops can engage inside the crown groove;

[0037] - a satellite carrier on which the satellites are mounted, mobile and rotating around their respective satellite axes which are parallel to the central axis.

[0038] According to one possibility, the speed reducer includes a lubrication distributor to distribute lubricant at least to the sets of teeth of the satellites.

[0039] The satellite design allows lubricant to be evacuated from a single-stage herringbone gearbox without passing through the ring gear mounting flange, thus avoiding any impact on the radial dimensions of the speed reducer. Furthermore, each scoop is designed to engage within the ring gear groove, thereby collecting and guiding the lubricant present there.

[0040] The crown may comprise an upstream half-crown and a downstream half-crown assembled together, the upstream half-crown comprising an upstream rim and an upstream half-flange and the downstream half-crown comprising a downstream rim and a downstream half-flange, the upstream rim being provided with the upstream crown tooth series and the downstream rim being provided with the downstream crown tooth series, the upstream half-flange and the downstream half-flange being assembled to form a crown fixing flange.

[0041] In a particular embodiment, for each of the satellites, each of the scoops has a shape complementary to the crown groove in order to be able to follow its contour.

[0042] Thus, in an axial cross-sectional plane containing the satellite axis, the scoops have an external shape that conforms to the shape of the crown groove in order to capture a maximum of lubricant. In one possibility, the solar element has teeth consisting of an upstream series of solar teeth and a downstream series of solar teeth, and the upstream and downstream series of teeth of each satellite mesh with the upstream and downstream series of solar teeth, respectively.

[0043] According to another possibility, the solar exhibits a solar throat extending circumferentially between the upstream solar tooth series and the downstream solar tooth series, this solar throat extending opposite the satellite throat of each of the satellites so that each of the scoops can engage inside the solar throat.

[0044] Thus, each scoop is adapted to be able to engage inside the solar groove and thus recover and guide the lubricant present in this solar groove.

[0045] In a particular embodiment, for each of the satellites, each of the scoops has a shape complementary to the solar throat in order to be able to follow its contour.

[0046] Thus, in an axial cutting plane containing the satellite axis, the scoops have an external shape that follows the shape of the solar throat in order to capture a maximum of lubricant.

[0047] The invention also relates to a turbomachine, for example a turbojet or turboprop of an aircraft, comprising a speed reducer as described above, and comprising a power shaft on which the solar element of the speed reducer is mounted in rotation, and a fan shaft coupled to the ring or the planet carrier of the speed reducer.

[0048] [Brief description of the figures]

[0049] Other features and advantages of the present invention will become apparent from the following detailed description, of a non-limiting example of implementation, made with reference to the accompanying figures in which:

[0050] [Fig 1] is a schematic axial cross-sectional view of a turbomachine incorporating a speed reducer;

[0051] [Fig 2] is a partial schematic axial cross-sectional view of a speed reducer according to the invention;

[0052] [Fig 3] is a schematic perspective view of a satellite according to the invention, as present in the speed reducer of Figure 2;

[0053] [Fig 4] is a schematic view of a lubricant evacuation device used in the satellite in Figure 3.

[0054] [Detailed description of an embodiment of the invention]

[0055] Referring to Figure 1, a turbomachine 1 comprises a fan 10, a low-pressure compressor 110, a high-pressure compressor 111, an annular combustion chamber 112, a high-pressure turbine 113, a low-pressure turbine 114, and an exhaust nozzle 115. The high-pressure compressor 111 and the high-pressure turbine 113 are connected by a high-pressure shaft 12 and together form a high-pressure housing. The low-pressure compressor 110 and the low-pressure turbine 114 are connected by a low-pressure shaft 13 and together form a low-pressure housing.

[0056] The blower 10 is driven by a blower shaft 14 which is driven by the low pressure shaft 13 by means of a speed reducer 2. This speed reducer 2 is generally of the planetary or epicyclic type.

[0057] The speed reducer 2 is positioned in an upstream part 15 of the turbomachine 1 which comprises a fixed structure schematically including the upstream part 15 and a downstream part 16 which makes up the motor or stator housing 17 and which is arranged to form a housing 18 surrounding the speed reducer 2. This housing 18 is here closed upstream by seals at the level of a bearing allowing the passage of the blower shaft 14, and downstream by seals at the level of the passage of the low pressure shaft 13.

[0058] Figure 2 illustrates schematically and in more detail the speed reducer 2 which is a single-stage reducer.

[0059] The speed reducer 2 includes a solar element 3 that rotates about a central axis 100, which here coincides with the axis of the turbomachine 10. At the input, the solar element 3 is mounted to rotate fixedly on the low-pressure shaft 13, for example by means of internal splines 130. Thus, the low-pressure shaft 13 drives the solar element 3 in rotation about the central axis 100, and this low-pressure shaft 13 thus constitutes a power shaft at the input of the speed reducer 2.

[0060] The speed reducer 2 includes satellites 4 which are driven in rotation by the solar 3 and which are equidistant on the same diameter around the central axis 100. This diameter is equal to twice the operating center distance between the solar 3 and the satellites 4. The number of satellites 4 is defined between three and seven for this type of application.

[0061] The speed reducer 2 includes a planet carrier 5 which forms a frame holding all the satellites 4 and each satellite 4 is rotatably mounted on the planet carrier 5 around its own axis of rotation 40, called the satellite axis, which is parallel to the central axis 100.

[0062] The speed reducer 2 also includes a ring gear 6 mounted coaxially to the central shaft 100 and extending around the solar element 3 and the satellite elements 4, so that the satellite elements 4 are meshed with the solar element 3 and with the ring gear 6. The ring gear 6 is fixed to a ring carrier 7. In an epicyclic configuration architecture, the set of satellite elements 4 drives the planet carrier 5 in rotation around the central shaft 100, the ring gear 6 is fixed to the motor housing or stator 17 via the ring carrier 7 and the planet carrier 5 is fixed to the blower shaft 14.

[0063] In a planetary architecture, the set of satellites 4 is held by the satellite carrier 5 which is fixed to the motor housing or stator 5. Each satellite 4 drives the ring 6 which is connected to the blower shaft 14 via the ring carrier 7.

[0064] Each satellite 4 is mounted to rotate freely by means of a bearing 50, for example, a roller bearing or hydrodynamic bearing. Each bearing 50 is mounted on one of the axes 51 of the satellite carrier 5, and all the axes are positioned relative to each other by means of one or more structural frames 52 of the satellite carrier 5; with the number of axes 51 and bearings 50 equal to the number of satellites 4. For reasons of operation, assembly, manufacturing, inspection, repair, or replacement, the axes 51 and the frame 52 may be separated into several parts.

[0065] For the same reasons mentioned above, the teeth of a satellite 4 can be separated into several teeth, each having a median plane, respectively an upstream median plane 81 and a downstream median plane 82, which are parallel and orthogonal. In the illustrated example, each satellite 4 comprises an external herringbone tooth arrangement, which is composed of two sets of herringbone teeth 41 and 42, and more precisely, an upstream set of teeth 41 and a downstream set of teeth 42.

[0066] The crown 6 is composed of two half-crowns 61, 62 assembled together, and more precisely of an upstream half-crown 61 and a downstream half-crown 62 assembled together.

[0067] The upstream half-crown 61 consists of an upstream rim 610 and an upstream half-flange 611, and the downstream half-crown 62 consists of a downstream rim 620 and a downstream half-flange 621.

[0068] The upstream rim 610 is provided with a series of upstream crown teeth 613 meshed with the upstream tooth series 41 of each satellite 4, and the downstream rim 620 is provided with a series of downstream crown teeth 623 meshed with the downstream tooth series 42 of each satellite 4. Furthermore, the crown 6 has a crown groove 64 extending circumferentially between the upstream crown tooth series 613 and the downstream crown tooth series 623.

[0069] The solar 3 also includes a toothing system composed of two sets of teeth 31, 32, and more specifically an upstream solar tooth set 31 and a downstream solar tooth set 32. Furthermore, the solar 3 has a solar groove 33 extending circumferentially between the upstream solar tooth set 31 and the downstream solar tooth set 32. The upstream tooth set 41 of each satellite 4 meshes with the upstream solar tooth set 31, and the downstream tooth set 42 of each satellite 4 meshes with the downstream solar tooth set 32.

[0070] It is conceivable that the tooth widths vary between the solar 3, the satellites 4 and the crown 6 because of the tooth overlaps, but they are all centered on the upstream median plane 81 for the upstream teeth 41, 613, 31 and on the downstream median plane 82 for the downstream teeth 42, 623, 32.

[0071] As can be seen in Figure 2, the speed reducer 2 is a single-stage mesh reducer, that is to say, the same tooth set of each satellite 4 cooperates with both the solar 3 and the ring gear 6. Although the tooth set of each satellite 4 comprises two sets of teeth 41, 42, these teeth 41, 42 have the same average diameter and form a single set of teeth called a chevron.

[0072] The upstream half-flange 611 of the upstream half-crown 61 and the downstream half-flange 621 of the downstream half-crown 62 form a fixing flange 63 of the crown 6. The crown 6 is thus fixed to the crown carrier 7 by assembling the fixing flange 63 of the crown 6 and a fixing flange 73 of the crown carrier 7 using a bolted assembly for example.

[0073] The speed reducer 2 also includes a lubrication distributor 9 to distribute a lubricant 90 (such as a lubricating oil) at least to the tooth sets 41, 42 of the satellites 4. In Figure 2, the arrows schematically illustrate the routing of the lubricant 90 in the speed reducer 2. The lubricant 90 arrives in the speed reducer 2 from the stator part 17 in the lubrication distributor 9 by various means which will not be specified in this view as they are specific to one or more types of architecture.

[0074] The lubrication distributor 9 includes injectors 91 and distribution arms 92. The injectors 91 are used to lubricate the gear teeth and the distribution arms 92 are used to lubricate the bearings 50.

[0075] The lubricant 90 is brought to the injectors 91 to exit through their respective ends 93 in order to lubricate the teeth, and in particular the sets of teeth 41, 42 of the satellites.

[0076] The lubricant 90 is also supplied to the distribution arms 92 and circulates, via supply ports 94 mounted on the shafts 51 of the planet carrier 5, to the bearings 50. The lubricant 90 circulates through the shafts 51 in one or more buffer zones 53 and then exits through ports 54 to lubricate the bearings 50 of the planets 4.

[0077] With reference to Figure 3, each satellite 4 comprises:

[0078] - a satellite rim 43 of annular shape around the satellite axis 40 and internally defining an internal orifice 44;

[0079] - the external chevron teeth described above, which protrude externally from the satellite rim 43 and comprises the upstream tooth series 41 and the downstream tooth series 42 arranged in a chevron pattern, spaced axially along the satellite axis 40 on either side of a satellite groove 45.

[0080] The upstream tooth series 41 and the downstream tooth series 42 have the same maximum diameter (also called tooth diameter), the same tooth height (which corresponds to the height of the teeth) and the same minimum diameter (which corresponds to the maximum diameter from which the tooth height is deduced).

[0081] The satellite throat 45 of each satellite 4, the coronal throat 64 and the solar throat 33 extend in the same median plane, orthogonal to the central axis 100, and thus the coronal throat 64 and the solar throat 33 extend opposite the satellite throat 45 of each satellite 4.

[0082] The satellite groove 45 has a bottom diameter that is less than or equal to the minimum diameter, so that the lubricant flowing between the teeth of the upstream tooth series 41 and the downstream tooth series 42 is guided inside the satellite groove 45, which thus forms a kind of channel or trough receiving the lubricant that has been injected by the lubrication distributor 9 at the level of the external chevron teeth of the satellite 4.

[0083] The satellite 4 further includes a lubricant evacuation device 46 to evacuate the lubricant from the upstream tooth set 41 and the downstream tooth set 42 towards the internal orifice 44. In other words, this lubricant evacuation device 46 recovers the lubricant which has been injected by the lubrication distributor 9 at the level of the external chevron teeth of the satellite 4, to guide it and transfer it into the internal orifice 44 after passing through the satellite rim 43.

[0084] This lubricant evacuation device 46 includes several scoops 47 which are fixedly mounted on the satellite rim 43 inside the satellite groove 45 and which radially extend beyond the external teeth, in other words, which radially extend beyond the teeth of the upstream and downstream tooth sets 41, 42. The scoops 47 are regularly distributed around the axis of the satellite 40.

[0085] Each scoop 47 faces a hole 48 which passes radially through the satellite groove 45 to open into the internal orifice 43. Thus, each scoop 47 guides the lubricant through the hole 48 to the internal orifice 44.

[0086] The crown groove 64, the solar groove 33, and the scoops 47 are shaped so that the scoops 47 can engage within the crown groove 64 and the solar groove 33. As shown in Figure 2, each of the scoops 47 has a shape complementary to the crown groove 64 to fit its contour and also has a shape complementary to the solar groove 33 to fit its contour. Thus, each scoop 47 has a width (distance measured along the central axis 100) that is substantially equivalent to the width of the crown groove 64 and the solar groove 33.

[0087] In the version illustrated in Figures 3 and 4, each of the scoops 47 is attached to a ring 49 arranged inside the internal orifice 44, so that the scoops 47 protrude from this ring 49 to pass through the corresponding holes 48, and thus each of the scoops 47 is mounted in the corresponding hole 48, and even in the extension of the corresponding hole 48.

[0088] The ring 49 has openings 490 around which the scoops 47 protrude. Each scoop 47 includes a wall 470 which protrudes from the ring 49; so that, once in place on the satellite rim 43, the openings 490 coincide with the holes 48 and the scoops 47 protrude from the satellite groove 45.

[0089] The wall 470 has an inner face facing the corresponding hole 48 and an outer face opposite the inner face. This wall 470 is curved such that its inner face is concave. Furthermore, the wall 470 includes two folded edges 471 directed towards the inner face and extending orthogonally to the axis of the satellite 40.

[0090] In Figure 3, the dashed arrows schematically represent the path of the lubricant from the upstream tooth series 41 and downstream 4 to the satellite groove 45, then through the holes 48 with the guidance by the scoops 47 to pass into the internal orifice 44, and the unbroken arrows schematically represent the evacuation of the lubricant on the sides of the internal orifice 44 by centrifugal force.

Claims

DEMANDS 1. Satellite (4) for a speed reducer (2) of a turbomachine (1), said satellite (4) comprising: - a satellite rim (43) of annular shape around a satellite axis (40) and internally defining an internal orifice (44); - an external toothing projecting outwards from the satellite rim (43) and comprising a series of upstream teeth (41) and a series of downstream teeth (42) arranged in a chevron pattern, spaced axially along the satellite axis (40) on either side of a satellite groove (45); and - a lubricant evacuation device (46) for evacuating lubricant from the upstream set of teeth (41) and the downstream set of teeth (42) towards the internal orifice (44), this lubricant evacuation device (46) comprising several scoops (47) which are mounted integrally on the satellite rim (43) inside the satellite groove (45) and which extend radially beyond the external teeth, each of the scoops (47) facing a hole (48) which passes radially through the satellite groove (45) to open into the internal orifice (44).

2. Satellite (4) according to claim 1, wherein each of the scoops (47) comprises a wall (470) which protrudes from the satellite groove (45) and which has an inner face facing the corresponding hole (48) and an outer face opposite the inner face.

3. Satellite (4) according to claim 2, wherein the wall (470) of each of the scoops (47) is curved in shape so that its inner face is concave.

4. Satellite (4) according to claim 2 or 3, wherein the wall (470) of each of the scoops (47) comprises two folded edges (471) directed towards the inner face and extending orthogonally to the axis of satellite (40).

5. Satellite (4) according to any one of the preceding claims, wherein the scoops (47) are regularly distributed around the axis of satellite (40).

6. Satellite (4) according to any one of the preceding claims, wherein the scoops (47) are made in the form of a single monobloc piece or are made in the form of an assembly.

7. Satellite (4) according to any one of the preceding claims, in which each of the scoops (47) is mounted in the corresponding hole (48), or in the extension of the corresponding hole (48).

8. Satellite (4) according to claim 7, wherein each of the scoops (47) is integral with a ring (49) disposed inside the internal orifice (44), such that the scoops (47) protrude from this ring (49) to pass through the corresponding holes (48).

9. Speed ​​reducer (2) for a turbomachine (1), for example a turbojet or turboprop engine of an aircraft, comprising: - a solar (3) mobile in rotation around a central axis (100); - a crown (6) mounted coaxially to the central axis (100) and extending around the solar (3), and the crown (6) comprises a series of upstream crown teeth (613), a series of downstream crown teeth (623) and a crown groove (64) extending circumferentially between the series of upstream crown teeth (613) and the series of downstream crown teeth (623); - satellites (4) meshing with the solar element (3) and with the crown (6) which is arranged around the satellites (4), each of the satellites (4) conforming to any one of the preceding claims and its upstream set of teeth (41) and its downstream set of teeth (42) meshing respectively with the upstream crown set of teeth (613) and the downstream crown set of teeth (623), and the crown groove (64) extends opposite the satellite groove (45) so that each of its scoops (47) can engage inside the crown groove (64). - a satellite carrier (5) on which the satellites (4) are mounted mobilely in rotation around their respective satellite axes (40) which are parallel to the central axis (100).

10. Speed ​​reducer (2) according to claim 9, in which, for each of the satellites (4), each of the scoops (47) has a shape complementary to the crown groove (64) to follow its contour.

11. Speed ​​reducer (2) according to claim 9 or 10, wherein the solar (3) has a toothing which is composed of a series of upstream solar teeth (31) and a series of downstream solar teeth (32), and the series of upstream teeth (41) and the series of downstream teeth (42) of each of the satellites (4) are meshed respectively with the series of upstream solar teeth (31) and the series of downstream solar teeth (32).

12. Speed ​​reducer (2) according to claim 11, wherein the solar element (3) has a solar element groove (33) extending circumferentially between the upstream solar tooth series (31) and downstream solar tooth series (32), this solar groove (33) extending opposite the satellite groove (45) of each of the satellites (4) so ​​that each of the scoops (47) can engage inside the solar groove (33).

13. Speed ​​reducer (2) according to claim 12, wherein, for each of the satellites (4), each of the scoops (47) has a shape complementary to the solar groove (33) so as to be able to conform to its contour.

14. Turbomachine (1), for example turbojet or turboprop of an aircraft, comprising a speed reducer (2) according to any one of claims 9 to 13 and comprising a power shaft (13) on which is mounted in rotational solidarity the solar (3) of the speed reducer (2), and a fan shaft (14) coupled to the ring (6) or the planet carrier (5) of the speed reducer (2).

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