Sun gear for a mechanical reduction gear of an aircraft turbine engine
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- Filing Date
- 2026-01-29
- Publication Date
- 2026-08-13
Smart Images
Figure FR2026050092_13082026_PF_FP_ABST
Abstract
Description
[0001] DESCRIPTION
[0002] TITLE: SOLAR POWER FOR A MECHANICAL REDUCER OF AN AIRCRAFT TURBOVISION ENGINE
[0003] Technical field of the invention
[0004] The present invention relates to the field of mechanical reducers for turbomachinery, particularly aircraft turbomachinery, and in particular the lubrication of these reducers.
[0005] Technical background
[0006] The state of the art includes in particular documents WO-A1-2010 / 092263, FR-A1-2 987416, FR-A1-3 011 901, FR-A1-3 041 054, FR-A1-3 058 493, CA-A1-2 640 040, DE-A1-10 2016 102096 and FR-A1-3 120 657.
[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 cycloidal 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 solar.
[0012] - In a differential gearbox, no element is fixed for rotation. The ring gear rotates in the opposite direction to the sun and the satellite carrier. Gearboxes can consist of one or more meshing stages. This meshing is achieved in various ways, such as by contact, friction, or magnetic fields.
[0013] 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.
[0014] 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.
[0015] 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.
[0016] One of the problems with a gearbox concerns its lubrication.
[0017] 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.
[0018] In current technology, the lubrication of the teeth or gears of a solar array is achieved by oil jets that project oil directly onto them. However, this solution is not always effective or even feasible, particularly because a gearbox is very bulky, and it is not easy to integrate jets and position them so that the teeth and gears are effectively lubricated. Furthermore, these jets are relatively complex and expensive to manufacture, resulting in a significant increase in the gearbox's cost.
[0019] The invention offers a solution to this problem that is simple, effective, and economical.
[0020] Summary of the invention
[0021] The invention relates to a solar element for a mechanical gearbox of a turbomachine, in particular an aircraft, the solar element comprising:
[0022] - a tubular shaft centered on a first axis,
[0023] - an external toothing system located at the outer periphery of the shaft and comprising two annular rows of teeth which are axially spaced from each other, - an external annular groove located at the outer periphery of the shaft and between the rows of teeth, the groove comprising an external cylindrical surface extending between two lateral annular faces extending radially outwards from the external cylindrical surface, and
[0024] - orifices formed in the drum to allow the passage of lubricating oil, the orifices extending from the inner periphery of the drum to the outer periphery of the drum,
[0025] characterized in that it further comprises: - an oil distributor which is brought and fixed in said groove and which includes oil projection holes on the lateral faces and / or the rows of teeth, the oil distributor being in fluid communication with at least a part of said orifices for the purpose of supplying oil to said holes.
[0026] The invention proposes replacing the nozzles of the prior art with an oil distributor that is directly mounted on the solar panel and can therefore be considered integrated into the panel. The distributor is located between the two rows of teeth of the solar panel, in the annular groove that separates these two rows of teeth. The distributor can therefore be mounted on existing solar panels without substantial modification. The distributor is supplied with oil from inside the solar panel and its function is to distribute oil to each side of the panel and thus to each row of teeth for lubrication.
[0027] The invention is notably compatible with a multi-stage reducer, a planetary or epicyclic reducer, straight or herringbone gears, etc.
[0028] The solar device according to the invention may comprise one or more of the following features, taken individually or in combination with each other:
[0029] - the oil distributor has an annular shape and extends around the first axis,
[0030] - the oil distributor comprises an annular cavity, possibly sectored, which is in fluid communication with at least a part of said orifices, and into which said oil spray holes open, - the oil distributor has, at least in part in axial section, a general U-shaped shape and comprises a central annular wall extending between two lateral walls extending radially inwards from the central annular wall,
[0031] - the inner periphery of each of the lateral walls rests on the external cylindrical surface of the groove, - your lateral walls are at an axial distance from the lateral faces of the groove, - your oil projection holes are located at the outer periphery of the lateral walls with respect to said first axis,
[0032] - The oil distributor has an external diameter that is equal to the external diameter of the teeth, to within + / -10%.
[0033] - Your oil spray holes are oriented parallel to the first axis, - Your oil spray holes are inclined relative to the first axis, with the oil spray holes oriented towards one of the rows of teeth having an angle of inclination equal to that of the teeth in that row within + / -20%, and the oil spray holes oriented towards the other row of teeth having an angle of inclination equal to that of the teeth in that row within + / -20%,
[0034] - the oil distributor is formed by the assembly of two half-shells, each having a circumferential extent around the first axis of approximately 180°, the half-shells being fixed to each other, and also to the barrel, at their circumferential ends,
[0035] - each of the half-shells has at one circumferential end a first leg resting on the external cylindrical surface of the throat, and at a second circumferential end a second leg superimposed radially on the first leg of the other half-shell,
[0036] - the first leg of each half-shell has a first opening, and the second leg of each half-shell has a second opening, the first openings of the first legs being radially aligned with the second openings of the superimposed second legs, and two diametrically opposed fixing pins passing through respectively the first and second aligned openings,
[0037] - the fixing pins have radial orientations with respect to the first axis and are mounted in housings in the barrel,
[0038] - the fixing pins are mounted by shrink fitting in the housings from inside the barrel, - the fixing pins are mounted sliding in the housings of the barrel, preferably by elastic elements which on the one hand allow a radial movement towards the inside of each of the pins in its housing, and which on the other hand stress each of the pins radially outwards; - the fixing pins are preferably of the captive type.
[0039] The present invention also relates to a mechanical gearbox for a turbomachine, in particular for aircraft, the gearbox comprising:
[0040] - a solar panel according to one of the previous claims,
[0041] - a crown centered on the first axis,
[0042] - satellites intercalated between the solar system and the corona and meshed with the solar system and the corona, and
[0043] - a satellite carrier centered on the first axis and carrying the satellites.
[0044] The reducer may include at least one oil nozzle suitable for projecting oil inside the solar barrel.
[0045] The present invention also relates to an aircraft turbomachine comprising a reducer as described above.
[0046] Brief description of the figures
[0047] 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:
[0048] Figure 1 is a schematic axial cross-sectional view of an aircraft turbomachine.
[0049] Figure 2 is a partial and highly schematic axial section of a mechanical reducer.
[0050] Figure 3 is a schematic perspective view of a solar panel according to one embodiment of the invention.
[0051] Figure 4a is a schematic axial cross-sectional view of the solar array in Figure 3, and Figure 4b is a larger-scale view of a portion of the solar array. Figures 5a and 5b are larger-scale schematic views of a portion of the solar array in Figure 3 and show two embodiment variants.
[0052] Figure 6 is a larger-scale view of part of Figure 3, and shows the solar oil dispenser.
[0053] Figure 7 is a schematic cross-sectional view of the solar panel in Figure 3, and shows the distributor mounting pins, and
[0054] Figure 8a is another schematic axial cross-sectional view of the solar in Figure 3, and Figure 8b is a larger scale view of part of Figure 8a.
[0055] Tax-free description of the invention
[0056] Figure 1 depicts a turbomachine 1 which, in a conventional manner, comprises a rotation 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.
[0057] 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 epicyclic type.
[0058] The following description relates to a planetary type reducer in which the ring gear is mobile in rotation.
[0059] 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.
[0060] 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. The shaft BP 3 thus 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 planet gears 12, which are evenly 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 planet gears 12. The number of planet gears 12 is generally between three and seven for this type of application. The set of planet gears 12 is held by a frame called the planet carrier 13. Each planet gear 12 rotates around its own Y-axis and meshes with the ring gear 14.
[0061] ▪ 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.
[0062] 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.
[0063] For the same reasons mentioned previously, 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: ▪ An upstream half-ring gear 14a consisting of a rim 14aa and a mounting flange half 14ab. The upstream helix of the reduction gear's teeth is located on the rim 14aa. This upstream helix meshes with that of the satellite gear 12, which meshes with that of the solar gear 11.
[0064] ▪ A downstream half-crown 14b consisting of a rim 14ba and a mounting half-flange 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 element 11.
[0065] 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.
[0066] 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.
[0067] The invention relates essentially to an improved solar system and in particular to the lubrication of a solar system for a reducer as described above.
[0068] Figures 3 and following illustrate an embodiment of a solar panel 111 according to the invention. The solar panel 111 comprises:
[0069] - a tubular shaft 120 centered on a first axis, which is the aforementioned X axis, - an external toothing 122 located at the external periphery of the shaft 120 and comprising two annular rows of teeth 122a, 122b which are axially spaced from each other,
[0070] - an external annular groove 124 located at the external periphery of the shaft 120 and between the rows of teeth 122a, 122b, and
[0071] - orifices 126 formed in the barrel 120 to allow the passage of lubricating oil
[0072] In the example shown, the groove 124 has an external cylindrical surface 128 extending between two lateral annular faces 130, 132 which extend radially outwards from the external cylindrical surface 128 (Figure 4b). It is understood that these faces 130, 132 are formed by the longitudinal ends of the rows of teeth 122a, 122b, as can be seen in Figures 3 and 4a.
[0073] The orifices 126 extend from the inner periphery of the barrel 120 to the outer periphery of the barrel 120.
[0074] In the example shown, the orifices 126 are located in a plane P perpendicular to the first axis X and passing through the middle of the groove 124 (Figures 4a-4b). The orifices 126 open into the groove 124, and in particular onto the external cylindrical surface 128.
[0075] The distinctive feature of the solar element 111 is that it also includes an oil distributor 134, which is attached and fixed in the groove 124 and which has oil spray holes 136 on its lateral faces 130, 132 and / or the rows of teeth 122a, 122b (Figures 4a-4b). The distributor 134 is in fluidic communication with at least some of the orifices 126 for the purpose of supplying oil to these holes 136.
[0076] The distributor 134 preferably has an annular shape and extends around the first axis X (figure 3). The distributor 134 may include an annular cavity 138 which is in fluidic communication with at least part of the orifices 126, and into which the oil spray holes 136 open (figure 4b).
[0077] Cavity 138 can be continuous over 360° or be sectorized as we will see later.
[0078] The distributor 134 may have at least in part in axial section a general U-shape, as can be seen in figure 4b. The distributor 134 then comprises a median annular wall 140 extending between two lateral walls 142, 144 which extend radially inwards from the median annular wall 140 (figure 4b).
[0079] The inner periphery of each of the side walls 142, 144 is preferably in contact with the external cylindrical surface 128 of the groove 124 (figure 4b).
[0080] The side walls 142, 144 are preferably at an axial distance from the side faces 130, 132 of the groove 124 so that the oil can be projected and impact the rows of teeth 122a, 122b. The side walls 142, 144 may be parallel to the side faces 130, 132 of the groove 124. The wall 142 is located opposite the face 130, and the wall 144 is located opposite the face 132, in the example shown.
[0081] The oil projection holes 136 can be located at the outer periphery of the side walls 142, 144 so that the oil can be projected at the outer periphery of the teeth.
[0082] The distributor 124 preferably has an external diameter D1 that is equal to the external diameter D2 of the teeth 122, within + / -10% (Figure 4b). In other embodiments, the distributor 124 may have an external diameter that is significantly larger than the external diameter of the teeth 122; the distributor 124 could therefore, for example, be 15% or, where applicable, 20% radially taller than the teeth of the solar element. Given that there is typically a gap between the teeth of the satellite elements, this gap being radially aligned with the groove of the solar element and determining the available radial volume for the distributor, Figure 5a shows a first variant in which the oil spray holes 136 are oriented parallel to the first X-axis. The oil is then sprayed in directions parallel to the X-axis, respectively onto the two rows of teeth 122a and 122b.
[0083] Figure 5b shows a second variant in which the oil spray holes 136 are inclined with respect to the first X-axis. The holes 136 facing the tooth row 122a have an inclination angle α equal to that of the teeth in that row to within ±20%, and the holes 136 facing the tooth row 122b have an inclination angle β equal to that of the teeth in that row to within ±20%. The angles α and β can be identical in absolute value.
[0084] Advantageously, as can be seen in Figures 6 and following, the distributor 134 is formed by the assembly of two half-shells 134a, 134b which each have a circumferential extent around the first axis X of the order of 180°.
[0085] The half-shells 134a, 134b are fixed to each other, and preferably also to the shaft 120, at their circumferential ends.
[0086] Each of the half-shells 134a, 134b has at a first circumferential end a first leg 146 able to bear on the external cylindrical surface 128 of the throat 124, and at a second circumferential end a second leg 148 able to be superimposed radially on the first leg 146 of the other half-shell.
[0087] The first leg 146 of each of the half-shells 134a, 134b has a first orifice 146a, and the second leg 148 of each of the half-shells 134a, 134b has a second orifice 148a.
[0088] The first orifices 146a of the first legs 146 are radially aligned with the second orifices 148a of the superimposed second legs 148, as can be seen in figures 8a and 8b.
[0089] Two diametrically opposed fixing pins 150 pass through the first and second aligned orifices 146a, 148a respectively. These pins are advantageously mounted so that they cannot be lost and cannot escape during operation of the reducer.
[0090] The mounting pins 150 preferably have radial orientations with respect to the first X-axis and are mounted in recesses 152 of the shaft 120. The mounting pins 150 can be press-fitted into the recesses 152, for example from inside the shaft (Figure 8a). In this case, it is understood that the recesses 152 open into the inside of the shaft and that the pins are engaged in the holes 146a, 148a of the tabs 146, 148 by first passing through the recesses 152.
[0091] Alternatively, the fixing pins 150 could be mounted sliding in the housings 152 of the barrel 120, as illustrated in figure 8b.
[0092] In this case, elastic elements 154, such as springs, could be mounted in the housings 152 to, on the one hand, allow radial inward movement of each of the pins 150 within its housing 152, and on the other hand, apply radial force to each of the pins 150 outward through the openings 146a, 148a in the tabs 146, 148. The distributor 134, as illustrated in Figures 6 and following, can be assembled as follows. The half-shells 134a, 134b are positioned in the groove 124 so that their tabs 146, 148 are radially overlapped. The pins 150 are then engaged by shrink fitting into the openings 146a, 148a in the tabs 146, 148 from inside the barrel 120.Alternatively, the pins 150 are pressed radially into their respective housings 152 before the assembly of the half-shells 134a, 134b and return to their original position by elastic return of the springs 152 once the half-shells 134a, 134b are positioned in the groove 124 and the openings 146a, 148a of the tabs 146, 148 are aligned with the housings 152. The pins 150 then engage in these openings 146a, 146b. The pins are preferably captive.
[0093] During operation, oil is conveyed radially from the inside of the drum 120 to the outside through the orifices 126. This oil supplies the distributor 134, and in particular its cavity 138, which then supplies the holes 136. The oil is sprayed through these holes 136 onto the faces 130, 132, and in particular the rows of teeth 122a, 122b, for lubrication. The oil flow rate can be determined so that the annular oil pockets located on either side of the distributor 134, between the distributor 134 and the rows of teeth 122a, 122b, are completely filled during operation.
[0094] The present invention further relates to a mechanical reducer 10 as described above with reference to figures 1 and 2, comprising a solar 111 according to the invention.
[0095] The reducer 10 can include at least one oil jet 160 suitable for projecting oil inside the barrel 120 of the solar 111, as illustrated very schematically in figure 3.
[0096] The invention offers several advantages, including:
[0097] - a reduction in the number of mechanical parts in the solar lubrication system,
[0098] - a reduction in the number of mechanical interfaces in the solar lubrication system,
[0099] - a reduction in bulk,
[0100] - a reduction in mass,
[0101] - improved lubrication of the teeth,
[0102] - lubrication of each row of teeth, etc.
Claims
DEMANDS 1. Solar (111) for a mechanical reducer (10) of a turbomachine (1), in particular an aircraft, the solar (111) comprising: - a tubular shaft (120) centered on a first axis (X), - an external toothing (122) located at the external periphery of the shaft (120) and comprising two annular rows of teeth (122a, 122b) which are axially spaced from each other, - an external annular groove (124) located at the outer periphery of the shaft (120) and between the rows of teeth (122a, 122b), the groove (124) comprising an external cylindrical surface (128) extending between two lateral annular faces (130, 132) extending radially outwards from the external cylindrical surface (128), and - orifices (126) formed in the barrel (120) to allow the passage of lubricating oil, the orifices (126) extending from the inner periphery of the barrel (120) to the outer periphery of the barrel (120), characterized in that it further comprises: - an oil distributor (134) which is attached and fixed in said groove (124) and which includes oil projection holes (136) on the lateral faces (130, 132) and / or the rows of teeth (122a, 122b), the oil distributor (134) being in fluidic communication with at least a part of said orifices (126) for the purpose of supplying oil to said holes (136).
2. Solar (111) according to claim 1, wherein the oil distributor (134) has an annular shape and extends around the first axis (X).
3. Solar (111) according to claim 1 or 2, wherein the oil distributor (134) comprises an annular cavity (138), optionally sectorized, which is in fluidic communication with at least a portion of said orifices (126), and into which said oil spray holes (136) open.
4. Solar (111) according to any one of the preceding claims, wherein the oil distributor (134) has at least partly in axial section a general U-shaped shape and comprises a median annular wall (140) extending between two lateral walls (142, 144) extending radially inwards from the median annular wall (140).
5. Solar (111) according to claim 4, wherein the inner periphery of each of the side walls (142, 144) is in contact with the external cylindrical surface (128) of the groove (124).
6. Solar (111) according to claim 4 or 5, wherein the side walls (142, 144) are at an axial distance from the side faces (130, 132) of the throat (124).
7. Solar (111) according to any one of claims 4 to 6, wherein the oil spray holes (136) are located at the outer periphery of the side walls (142, 144) opposite said first axis (X).
8. Solar (111) according to any one of the preceding claims, wherein the oil distributor (134) has an external diameter (D1) which is equal to the external diameter (D2) of the teeth (122), to + / -10%.
9. Solar (111) according to any one of claims 1 to 8, wherein the oil projection holes (136) are oriented parallel to the first axis (X).
10. Solar (111) according to any one of claims 1 to 8, wherein the oil spray holes (136) are inclined with respect to the first axis (X), the oil spray holes (136) oriented towards one of the rows of teeth (122a) having an angle of inclination (a) equal to that of the teeth of that row to within + / -20%, and the oil spray holes (136) oriented towards the other of the rows of teeth (122b) having an angle of inclination (P) equal to that of the teeth of that row to within + / -20%.
11. Solar (111) according to any one of the preceding claims, wherein the oil distributor (134) is formed by the assembly of two half-shells (134a, 134b) each having a circumferential extent around the first axis of approximately 180°, the half-shells (134a, 134b) being fixed to each other, and preferably also to the barrel (120), at their circumferential ends.
12. Solar (111) according to claim 11, wherein each of the half-shells (134a, 134b) has at a first circumferential end a first tab (146) bearing on the external cylindrical surface (128) of the groove (124), and at a second circumferential end a second tab (148) radially superimposed on the first tab (146) of the other of the half-shells.
13. Solar (111) according to claim 12, wherein the first leg (146) of each of the half-shells (134a, 134b) has a first orifice (146a), and the second leg (148) of each of the half-shells (134a, 134b) has a second orifice (148a), the first orifices (146a) of the first legs (146) being aligned radially with the second orifices (148a) of the superimposed second legs (148), and two diametrically opposed fixing pins (150) passing respectively through the first and second aligned orifices (146a, 148a).
14. Solar (111) according to claim 13, wherein the fixing pins (150) have radial orientations with respect to the first axis (X) and are mounted in housings (152) of the shaft (120).
15. Solar (111) according to claim 14, wherein the fixing pins (150) are mounted by shrink fitting into the housings (152) from inside the shaft (120).
16. Solar (111) according to claim 14, wherein the fixing pins (150) are mounted to slide in the housings (152) of the shaft (52), preferably by elastic elements (154) which on the one hand allow a radial displacement inwards of each of the pins (150) in its housing (152), and which on the other hand stress each of the pins (150) radially outwards.
17. Mechanical reducer (10) for a turbomachine (1), in particular for aircraft, the reducer (10) comprising: - a solar (111) according to one of the preceding claims, - a ring (14) centered on the first axis (X), - satellites (12) interposed between the solar element (111) and the ring (14) and meshed with the solar element (111) and the ring (14), and - a satellite carrier (13) centered on the first axis (X) and carrying the satellites (12).
18. Reducer (10) according to the preceding claim, wherein it comprises at least one oil jet (160) capable of projecting oil into the inside of the barrel (120) of the solar (111).
19. Turbomachine (1), in particular for aircraft, comprising a reduction gear (10) according to claim 17 or 18.