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    • 专利摘要:
    LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AN AIRCRAFT The invention relates to the lubrication of a planet carrier (10) for a mechanical reduction gear (6) of a turbomachine, in particular of an aircraft, this planet carrier comprising a cage (14) defining an internal housing intended to receive a central solar (7) of axis X of rotation, and an annular row of satellites (8) arranged around the solar, this cage comprising two annular walls radial (14a, 14b) with respect to said X axis and connected together at their outer periphery by a cylindrical wall (14c) of axis X, at least one of the radial walls comprising holes (14aa) for mounting the axes (10b) of said planet gears, and the cylindrical wall comprising openings (14ca) for passing the gears of the gears for their engagement with a toothing of a ring gear (9) intended to extend around the gears and the cage. Figure for the abstract: Figure 6
    公开号:FR3092889A1
    申请号:FR1901524
    申请日:2019-02-14
    公开日:2020-08-21
    发明作者:Louis Simon Adrien；Jean Charrier Mathieu；Michel Pierre Di Giovanni Jean-Charles；Loïc Clément LEFEBVRE Simon；Jean Pierre Robinet Guillaume
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    [0001] Technical field of the invention
    [0002] The present invention relates to the field of mechanical reduction gears for turbomachines, in particular aircraft.
    [0003] Technical background
    [0004] The state of the art includes in particular the documents WO-A1-2010/092263, FR-A1-2 987 416 and FR-A1-3 041 054.
    [0005] The role of a mechanical gearbox is to modify the speed and torque ratio between the input axis and the output axis of a mechanical system.
    [0006] New generations of dual-flow turbomachines, particularly those with a high bypass ratio, include a mechanical reduction gear to drive the shaft of a fan (also called a “fan”). Usually, the purpose of the reduction gear is to transform the so-called fast rotation speed of the shaft of a power turbine into a slower rotation speed for the shaft driving the fan.
    [0007] Such a reducer comprises a central pinion, called sun gear, a crown and pinions called satellites, which are engaged between the sun gear and the crown. The satellites are held by a frame called the planet carrier. The solar, the crown and the planet carrier are planetary because their axes of revolution coincide with the longitudinal axis X of the turbomachine. The satellites each have a different axis of revolution evenly distributed over the same operating diameter around the axis of the planetary gears. These axes are parallel to the longitudinal axis X.
    [0008] There are several reducer architectures. In the state of the art of turbofan engines, the reduction gears are of the planetary or planetary type. In other similar applications, there are so-called differential or “compound” architectures.
    [0009] - On a planetary gearbox, the planet carrier is fixed and the crown constitutes the output shaft of the device which rotates in the opposite direction to the sun.
    [0010] - On an epicyclic reduction gear, the crown is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the sun gear.
    [0011] - On a differential gearbox, no element is fixed in rotation. The crown rotates in the opposite direction to the sun and the planet carrier.
    [0012] Reducers can be composed of one or more meshing stages. This meshing is ensured in different ways such as by contact, by friction or even by magnetic fields.
    [0013] There are several types of contact meshing such as straight, helical or chevron gears.
    [0014] The present invention proposes an improvement of a reduction gear with a simple, efficient and economical solution for improving the lubrication of its planet carrier.
    [0015] The invention has several aspects.
    [0016] According to a first aspect, the invention relates to a planet carrier for a mechanical reduction gear of a turbomachine, in particular an aircraft, this planet carrier comprising a cage defining an internal housing intended to receive a central sun gear of axis X of rotation, and an annular row of satellites arranged around the solar, this cage comprising two radial annular walls with respect to said axis X and connected together at their outer periphery by a cylindrical wall of axis X, at least one of the radial walls comprising mounting holes of axes of the said satellites, and the cylindrical wall comprising openings for the passage of the toothings of the satellites for their meshing with a toothing of a crown intended to extend around the satellites and the cage, characterized in that it comprises first and second independent lubrication circuits, the first circuit comprising a first dedicated oil inlet connected by a first annular oil chamber entant around the axis X to oil supply lines to said axes of the satellites, and the second circuit comprising a second dedicated oil inlet connected by a second annular oil chamber extending around the axis X to oil supply channels up to the meshes of the teeth of the satellites with the ring gear, and in that said first and second inlets, said pipes, said channels, and at least a part of said first and second chambers are integrated into said cage.
    [0017] The invention thus proposes to integrate a major part of the lubrication circuits in the cage of the planet carrier, which makes it possible to reduce the number of parts and simplifies the assembly of the reducer. The risk of oil leakage is also significantly reduced.
    [0018] The planet carrier according to the invention may comprise one or more of the following characteristics, taken separately from each other, or in combination with each other:
    [0019] - said first and second inlets are oriented radially with respect to said axis X and emerge radially outwards; they are thus easily accessible for connection to oil supply means,
    [0020] - said first and second inlets are located in the same plane perpendicular to said axis X and are inclined relative to each other; they are therefore close to each other and can pass through the same arm or different arms of a casing of the turbomachine in which the reduction gear is integrated with this planet carrier,
    [0021] - said first and second chambers are arranged adjacently, one behind the other, along said X axis; this makes it possible to optimize the compactness and therefore the size of the lubrication circuits,
    [0022] - one of said first and second chambers is located in said plane and connected to one of said inlets by a radial and straight bore, and the other of said first and second chambers is located outside of said plane and connected to the other said inlets by two holes including a first hole located in said plane and a second hole of which extends in an inclined manner between the first hole and this other chamber; this also makes it possible to optimize the compactness and therefore the size of the lubrication circuits; these opening holes are preferably plugged by sealed plugs which can be screwed and/or glued.
    [0023] - said conduits are formed in one of said radial walls and extend straight between said first chamber and lubricating cores of the axes of the satellites; the ducts are thus formed in the thickness of the radial walls, or in extra thicknesses of these walls,
    [0024] - said channels are formed in one of said radial walls as well as in said cylindrical wall and each have a general L-shape extending between said second chamber and oil projection orifices towards said gears; the channels are thus formed in the thickness of the radial and cylindrical walls, or in the extra thicknesses of these walls,
    [0025] - said first and second chambers are located at the inner periphery of one of said radial walls, and are delimited partly by this radial wall and partly by an attached annular distributor comprising a cylindrical wall internally delimiting said chambers and at least one partition annular axially closing one of said chambers, and
    [0026] - one of said chambers is connected to at least one oil nozzle towards said solar, said nozzle being integrated into said distributor; the nozzle is preferably configured to spray oil towards the coupling between the solar and its drive shaft.
    [0027] According to a second aspect, the invention relates to a planet carrier for a mechanical reduction gear of a turbomachine, in particular an aircraft, this planet carrier comprising a cage defining an internal housing intended to receive a central sun gear with axis X of rotation, and an annular row of satellites arranged around the solar, this cage comprising two radial annular walls with respect to said axis X and connected together at their outer periphery by a cylindrical wall of axis X, at least one of the radial walls comprising mounting holes of axes of the said satellites, and the cylindrical wall comprising openings for the passage of the toothings of the satellites for their meshing with a toothing of a crown intended to extend around the satellites and the cage, characterized in that it comprises in in addition to an annular lubricating oil distributor which is formed in one piece and which is configured to be attached and fixed to the internal periphery of one of said radial walls so as to define with this radial wall two independent and closed annular oil circulation chambers.
    [0028] The realization of the oil chambers is thus simplified because they are delimited between the cage, on the one hand, and by the added distributor, on the other hand. It is in fact simpler and more economical to manufacture the distributor from a foundry or to machine a part to manufacture the distributor, rather than to produce the chambers entirely in situ on the cage. The distributor has a simple general shape and is formed from a single piece, which facilitates its mounting on the cage.
    [0029] The planet carrier according to the invention may comprise one or more of the following characteristics, taken separately from each other, or in combination with each other:
    [0030] - said distributor comprises a cylindrical wall internally delimiting said chambers and at least one annular partition axially closing one of said chambers; the dispenser of simple shape can therefore be inexpensive to produce,
    [0031] - said distributor comprises two annular partitions extending radially outwards from said cylindrical wall and delimiting between them one of said chambers, the other of said chambers being delimited between one of these partitions and an annular surface opposite the radial wall on which the distributor is attached,
    [0032] - the or each partition comprises at its outer periphery an outer cylindrical centering surface on which is formed an annular groove for receiving an annular seal intended to cooperate with the inner periphery of the radial wall on which the distributor is attached ; the cylindrical surfaces therefore have a dual function of centering but also of sealing because they are equipped with seals ensuring the sealing of the chambers and therefore of the lubrication circuits,
    [0033] - said cylindrical wall comprises a cylindrical centering surface on which is formed an annular groove for receiving an annular seal intended to cooperate with the internal periphery of the radial wall on which the distributor is attached; this cylindrical surface also has a dual function of centering and sealing,
    [0034] - said first and second chambers are arranged adjacently, one behind the other, along said X axis,
    [0035] - said first and second chambers each have a general parallelepiped shape in section, and
    [0036] - the distributor comprises a flange or fixing lugs on said cage, by means of screws.
    [0037] The present invention also relates to an aircraft turbomachine, characterized in that it comprises a mechanical reduction gear comprising a planet carrier as described above.
    [0038] The features of the different aspects of the invention can be combined with each other.
    [0039] Brief description of figures
    [0040] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:
    [0041] Figure 1 is a schematic view in axial section of a turbomachine using the invention,
    [0042] Figure 2 is an axial section in partial view of a mechanical reducer,
    [0043] Figure 3 is a schematic perspective view of a mechanical reducer according to the invention,
    [0044] Figure 4 is a schematic view in axial section of the reducer of Figure 3,
    [0045] Figure 5 is a partial schematic perspective view of an annular lubricating oil distributor,
    [0046] Figure 6 is a schematic perspective view of the volumes of the lubricating oil circuits of the reducer of Figure 3,
    [0047] Figure 7a is a schematic view in axial section of the reducer of Figure 3, the section being made in one plane,
    [0048] Figure 7b is another schematic view in axial section of the reducer of Figure 3, the section being made in a different plane, and
    [0049] Figure 7c is another schematic view in axial section of the reducer of Figure 3, the section being made in a different plane.
    [0050] Detailed description of the invention
    [0051] FIG. 1 describes a turbomachine 1 which comprises, in a conventional manner, 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 a exhaust pipe 1h. The high pressure compressor 1b and the high pressure turbine 1d are connected by a high pressure shaft 2 and form with it a high pressure body (HP). The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3 and form with it a low pressure body (LP).
    [0052] The fan S is driven by a fan shaft 4 which is driven to the LP shaft 3 by means of a reducer 6. This reducer 6 is generally of the planetary or planetary type.
    [0053] Although the following description relates to a reduction gear of the planetary or epicyclic type, it also applies to a mechanical differential in which the three components, which are the planet carrier, the crown and the sun gear, are mobile in rotation, the speed rotation of one of these components depending in particular on the speed difference of the other two components.
    [0054] The reducer 6 is positioned in the front part of the turbomachine. A fixed structure comprising schematically, here, an upstream part 5a and a downstream part 5b which makes up the motor casing or stator 5 is arranged so as to form an enclosure E surrounding the reducer 6. This enclosure E is here closed upstream by seals at the level of a bearing allowing the crossing of the fan shaft 4, and downstream by seals at the level of the crossing of the LP shaft 3.
    [0055] Figure 2 shows a reducer 6 which can take the form of different architectures depending on whether certain parts are fixed or rotating. At the input, the reducer 6 is connected to the BP shaft 3, for example via internal splines 7a. Thus the BP shaft 3 drives a planet gear called the sun gear 7. Conventionally, the sun gear 7, whose axis of rotation coincides with that of the turbomachine X, drives a series of gears called satellites 8, which are evenly distributed on the same diameter around the axis of rotation X. This diameter is equal to twice the operating center distance between the solar 7 and the satellites 8. The number of satellites 8 is generally defined between three and seven for this type of application .
    [0056] All of the satellites 8 are held by a frame called the planet carrier 10. Each satellite 8 rotates around its own Y axis, and meshes with the ring gear 9.
    [0057] dans une configuration épicycloïdale, l’ensemble des satellites 8 entraine en rotation le porte-satellite 10 autour de l’axe X de la turbomachine. La couronne est fixée au carter moteur ou stator 5 via un porte-couronne 12 et le porte-satellites 10 est fixé à l’arbre de soufflante 4. dans une configuration planétaire, l’ensemble des satellites 8 est maintenu par un porte-satellites 10 qui est fixé au carter moteur ou stator 5. Chaque satellite entraine la couronne qui est rapportée à l’arbre de soufflante 4 via un porte-couronne 12. As output, we have: in an epicyclic configuration, the set of satellites 8 drives the planet carrier 10 in rotation around the axis X of the turbomachine. The ring gear is fixed to the motor casing or stator 5 via a ring gear carrier 12 and the planet gear carrier 10 is fixed to the fan shaft 4. in a planetary configuration, the set of satellites 8 is held by a planet carrier 10 which is fixed to the motor casing or stator 5. Each satellite drives the crown which is attached to the fan shaft 4 via a crown carrier 12 .
    [0058] Each satellite 8 is mounted free to rotate using a bearing 11, for example of the bearing or hydrodynamic bearing type. Each bearing 11 is mounted on one of the axes 10b of the planet carrier 10 and all the axes are positioned relative to each other using one or more structural frames 10a of the planet carrier 10. There are a number of axes 10b and bearings 11 equal to the number of satellites. For operational, assembly, manufacturing, control, repair or replacement reasons, the axles 10b and the frame 10a can be separated into several parts.
    [0059] une demi-couronne avant 9a constituée d’une jante 9aa et d’une demi-bride de fixation 9ab. Sur la jante 9aa se trouve l’hélice avant de la denture du réducteur. Cette hélice avant engrène avec celle du satellite 8 qui engrène avec celle du solaire 7. une demi-couronne arrière 9b constituée d’une jante 9ba et d’une demi-bride de fixation 9bb. Sur la jante 9ba se trouve l’hélice arrière de la denture du réducteur. Cette hélice arrière engrène avec celle du satellite 8 qui engrène avec celle du solaire 7. For the same reasons mentioned above, the teeth of a reducer can be separated into several helices each having a median plane P. In our example, we detail the operation of a reducer with several helices with a crown separated into two half-crowns : a front half-crown 9a consisting of a rim 9aa and a fixing half-flange 9ab. On the rim 9aa is the front helix of the reduction gear. This forward propeller meshes with that of satellite 8 which meshes with that of solar 7. a rear half-crown 9b consisting of a rim 9ba and a fixing half-flange 9bb. On the rim 9ba is the rear propeller of the reduction gear. This rear propeller meshes with that of satellite 8 which meshes with that of solar 7.
    [0060] In the case of herringbone gears, if the propeller widths vary between the solar 7, the satellites 8 and the crown 9 because of the toothing overlaps, they are all centered on a median plane P1 for the front propellers and on another median plane P2 for the rear propellers. In the other figures, in the case of a bearing with two rows of rollers.
    [0061] The fixing half-flange 9ab of the front half-crown 9a and the fixing half-flange 9bb of the rear half-crown 9b form the fixing flange 9c of the crown. The crown 9 is fixed to the crown holder 12 by assembling the fixing flange 9c of the crown and the fixing flange 12a of the crown holder using a bolted assembly for example.
    [0062] The arrows in Figure 2 describe the routing of the oil in the reducer 6. The oil arrives in the reducer 6 from the stator part 5 in a distributor 13 by various means which will not be specified in this view because they are specific to one or more types of architecture. The distributor 13 is separated into two parts, each generally repeated by the same number of satellites. The injectors 13a have the function of lubricating the teeth and the arms 13b have the function of lubricating the bearings. The oil is brought to the injector 13a to come out through the end 13c in order to lubricate the teeth. The oil is also brought to the arm 13b and circulates via the supply port 13d of the bearing. The oil then circulates through the shaft 10b in one or more buffer zones 10c and then exits through the orifices 10d in order to lubricate the bearings 11 of the satellites 8.
    [0063] Figures 3 to 7 represent an embodiment of a reducer 6 comprising several aspects of the invention.
    [0064] One of these aspects concerns the lubricating oil distributor 13' and another concerns the lubricating oil circuits 15a, 15b of the reducer 6.
    [0065] The reducer 6 of Figures 5 and following is similar to those described in the foregoing and comprises a planet carrier 10 with cage 14.
    [0066] The cage 14 comprises two radial annular walls 14a, 14b extending around the axis X, these walls 14a, 14b being parallel and being respectively a front radial wall 14a and a rear radial wall 14b. The walls 14a, 14b are interconnected at their outer peripheries by a cylindrical wall 14c. The walls 14a, 14b and 14c are better visible in Figures 7a to 7c.
    [0067] The cage 14 defines an internal housing intended to receive the central solar 7 of axis X of rotation, and the annular row of satellites 8 arranged around the solar 7.
    [0068] At least one of the radial walls 14a, 14b (this is the front wall 14a in the example represented in FIGS. 7a to 7c) comprises orifices 14aa for mounting the axes 10b of the satellites 8, and the cylindrical wall 14c comprises slots 14ca for the passage of the toothings of the satellites 8 for their meshing with the toothing of the crown 9 intended to extend around the satellites 8 and the cage 14.
    [0069] The orifices 14aa are regularly distributed around the axis X. The walls 14a, 14b each further comprise a central orifice 14ab, 14ba aligned on the axis X. The walls 14a, 14b can also be connected to each other by another cylindrical wall 14d extending over the internal periphery of the walls 14a, 14b, around their orifices 14ab, 14ba. This wall 14d is visible in Figure 7b.
    [0070] The reducer 6 comprises two independent lubrication circuits 15a, 15b, the volumes of oil of these circuits being visible in figure 6.
    [0071] The first circuit 15a comprises a first dedicated oil inlet 15aa connected by a first annular oil chamber 15ab extending around the axis X to lines 15ac for supplying oil to the axes 10b of the satellites 8 .
    [0072] The second circuit 15b comprises a second dedicated oil inlet 15ba connected by a second annular oil chamber 15bb extending around the X axis to channels 15bc for supplying oil to the meshes of the satellite teeth. 8 with the crown 9. The second circuit 15b can further comprise channels 15bd for supplying oil to the meshes of the teeth of the satellites 8 with the sun gear 7.
    [0073] As can be seen in the drawings, the inlets 15aa, 15ba, the pipes 15ac, the channels 15bc, 15bd, and at least part of the chambers 15ab, 15bb are integrated into the cage 15, i.e. they are not formed by or in parts added to the cage but are an integral part of the cage.
    [0074] The inlets 15aa, 15ba are oriented radially with respect to the axis X and emerge radially outward for their connection to oil supply means. These inputs 15aa, 15ba are located in the same plane P3 perpendicular to the axis X and are inclined relative to each other in this plane P3, around the axis X (FIGS. 7a and 7b).
    [0075] The chambers 15ab, 15bb are arranged adjacently, one behind the other, along the axis X. They each have in section a generally parallelepipedal shape in the example shown. One of these chambers, namely the front chamber 15bb in the example shown, is located in the aforementioned plane P3 and is connected to the inlet 15ba by a radial and rectilinear bore 16a formed in the rear radial wall 14b (figures 7b and 7c). The other chamber 15ab is located outside the plane P3 (here behind this plane) and is connected to the other inlet 15aa by two holes including a first hole 16b located in the plane P3 and a second hole 16c extends in an inclined manner between the first bore 16b and the chamber 15ab (FIG. 7a).
    [0076] The pipes 15ac are formed in the rear radial wall 14b and extend straight and slightly inclined between the chamber 15ab and the oil supply cores 17 of the satellites 8 (FIG. 7a).
    [0077] The channels 15bc are formed in the rear radial wall 14b as well as in the cylindrical wall 14c (FIG. 7c). They each have a general L-shape and each comprise a rectilinear and radial branch extending in the wall 14b, from the chamber 15bb, and an axial rectilinear branch extending in the wall 14c, up to projection orifices 15bc1 of oil towards the meshes of the teeth of the satellites 8 and of the crown 9 (FIGS. 7c and 6).
    [0078] The channels 15bd are formed in the wall 14d and extend from the chamber 15bb to the oil projection orifices 15bd1 towards the meshes of the teeth of the satellites 8 with the sun gear 7 (FIGS. 6 and 7b).
    [0079] The chambers 15ab, 15bb are located at the internal periphery of the wall 14b, and are delimited in part by this radial wall and in part by the distributor 13' which is attached to this wall and fixed thereto by screws 18 ( figures 3 and 4).
    [0080] The internal periphery of the wall 14b comprises a cylindrical rim 19 directed towards the rear and comprising an internal cylindrical surface 19a on which the radially internal ends of the bores 16a, 16c, of the conduits 15ac and of the channels 15bc open (FIGS. 7a to 7c) . A rear radial surface 19b of wall 14b extends between the central hole 14bb of wall 14b and surface 19a. Channels 15bd lie axially downstream on surface 19b (Figure 7b).
    [0081] Distributor 13' has a generally annular shape and is formed from a single piece. It comprises a cylindrical wall 13a internally delimiting the chambers 15ab, 15bb, the chambers being intended to be delimited externally by the surface 19a of the wall 14b when the distributor 13' is mounted coaxially on the wall 14b by engaging it to the inside the flange and the orifice 14bb of the wall 14b.
    [0082] The distributor 13' comprises two annular partitions 13b, 13c that are substantially radial in the example shown. One of the partitions 13c extends radially outwards from the rear end of the wall 13a and is in sealed radial support on the surface 19a, here at the rear end of the rim 19.
    [0083] The cylindrical wall 13a of the distributor 13' has its front end which is in leaktight radial support on the peripheral edge of the orifice 14bb. The partition 13b extends radially outwards, at a distance from the upstream end of the wall 13a and of the partition 13b, and is also in leaktight radial support on the surface 19a.
    [0084] Each sealed support is obtained in the example shown by an O-ring which is arranged in an annular groove 20 of the outer periphery of the partition 13b, 13c, or of the front end of the wall 13a, and which cooperates by pressing and elastic deformation with the radial wall 14b or its rim 19.
    [0085] To facilitate the centering of the distributor 13 'and the realization of the grooves 20 on the partitions 13b, 13c, the latter can be oversized at their outer peripheries and each comprise a cylindrical centering surface on which is formed the groove 20 for receiving a joint. Furthermore, to facilitate the assembly of the distributor 13 'by axial translation in the orifice 14bb and the rim 19, the seal carried by the partition 13b can cooperate with an annular rib 19d projecting from the surface 19a, as is visible in the figures 7b and 7c.
    [0086] It is understood that the chamber 15bb is closed by the distributor 13' and delimited between a front annular portion of the surface 19a, the surface 19b, a front annular portion of the wall 13a and the partition 13c. Chamber 15ab is closed by distributor 13' and delimited between a rear annular portion of surface 19a, a rear annular portion of wall 13a and partitions 13b, 13c.
    [0087] The chambers 15ab, 15bb are thus independent insofar as they do not communicate with each other.
    [0088] The distributor 13', and in particular its partition 13b, comprises an annular flange 21 extending radially outwards and comprising holes 22 for the passage of the screws 18 which are screwed into threaded holes in the wall 14b of the cage.
    [0089] The distributor 13' further comprises, projecting from the internal cylindrical surface of its wall 13a, an oil nozzle 23 which is connected to the front chamber 15bb (FIGS. 5 and 7a). This nozzle 23 is configured to project oil on the coupling between the solar 7 and the low pressure shaft 3 of figure 2.
    [0090] The nozzle 23 is advantageously also integrated into the distributor 13', as is the case in the example shown.
    [0091] The oil circuits 15a, 15b are advantageously configured to be fluidically connected, at their inlets and at their possible outlets, by fittings of the male-female type, that is to say by fittings requiring only an interlocking by axial translation of a male connector in a female connector. Even if a connector is presented in the following as male and intended to cooperate with a female connector, it can alternatively be replaced by a female connector therefore intended to cooperate with a male connector, and vice versa. The tightness of the male-female connections can be ensured by O-rings or the like.
    [0092] As regards the inputs 15aa, 15ba, they each comprise a female connector in the example shown which is intended to receive the male connector of an oil supply pipe (FIGS. 6 to 7c).
    [0093] As regards the oil outlets and apart from the oil projection orifices 15bc1, 15bd1, they are located at the radially outer ends of the ducts 15ac (FIGS. 6 and 7a).
    [0094] As can be seen in FIG. 7a, the outlets of the ducts 15ac each comprise a female connector 15ac1 in the example shown, which is intended to receive the male connector of one of the cores 17. These connectors 15ac1 are oriented axially, all in the same direction here forward.
    [0095] The cores 17 have the function of lubricating and cooling the axes 10b of the satellites 8.
    [0096] In the embodiment shown, each axis 10b is guided by a bearing 11 with double bearings, that is to say with a double row of rollers 11a. The two rows extend around the same axis which coincides with that, denoted Y, of the axis 10b of the satellite 8. The application could comprise more than two rows.
    [0097] Conventionally, the rollers are guided in tracks defined by internal and external rings. A special feature here is linked to the fact that the internal roller guide rings 11a are integrated into the axis 10b. The outer periphery of shaft 10b thus comprises cylindrical tracks 11b for rolling rollers 11a, each track 11b being delimited axially by annular ribs 11c which themselves serve to guide cages 11d for holding rollers 11a. Furthermore, FIGS. 7a to 7c show that the outer rings are integrated into the inner periphery of the planet wheels 8. The inner periphery of the planet wheels 8 thus comprises cylindrical tracks 8a for rolling the rollers 11a.
    [0098] The internal periphery of the axis 10b comprises an internal cylindrical surface 10e which is intended to be covered by the core 17.
    [0099] This core 17 essentially comprises three parts, namely a cylindrical portion 17a, a disc 17b and a ring 17c. The core 17 is here formed in one piece although this feature is not limiting.
    [0100] The portion 17a extends along the Y axis and includes an internal pipe, called the first pipe 17a1, which extends along the Y axis over almost the entire length of the portion 17a in the example shown.
    [0101] Portion 17a has an axial end (rear) forming the aforementioned male connector, and an opposite end (front) connected to the center of disc 17b, the outer periphery of which is connected to ring 17c. Disc 17b extends in a plane substantially perpendicular to axis Y and includes an internal duct, called second duct 17b1, which extends radially from first duct 17a1 to the outer annular surface of disc 17b.
    [0102] The disc 17b is connected substantially in the middle of the ring 17c (along the Y axis) so that the second pipe opens out substantially in the middle of the ring 17c. The disc 17b could comprise several second radial conduits 17b1 regularly spaced around the Y axis.
    [0103] The ring 17c extends around the axis Y and delimits with the internal cylindrical surface of the axis 10b an annular cavity 22 for the circulation of oil and for the supply of the orifices 10d for conveying the oil to the bearing 11 and to the cages 11d, these orifices being visible in figure 2.
    [0104] In operation, the oil reaches the chambers 15ab, 15bb through the inlets 15aa, 15ba and the bores 16a, 16b and 16c. The oil in the chamber 15ab feeds the cores 17 through the conduits 15ac for the lubrication of the bearing 11. The oil in the chamber 15bb feeds the channels 15bc, 15bd for the lubrication of the gears. Oil is also sprayed by the nozzle 23 on the coupling between the solar 7 and the BP shaft 3.
    权利要求:
    Claims (10)
    [0001]
    Planetary carrier (10) for a mechanical reduction gear (6) of a turbomachine, in particular an aircraft, this planetary carrier comprising a cage (14) defining an internal housing intended to receive a central sun gear (7) of axis X of rotation, and an annular row of satellites (8) arranged around the solar, this cage comprising two radial annular walls (14a, 14b) with respect to said axis X and connected together at their outer periphery by a cylindrical wall (14c) of axis X, at least one of the radial walls comprising orifices (14aa) for mounting axles (10b) of said satellites, and the cylindrical wall comprising openings (14ca) for the passage of toothings of the satellites for their meshing with a toothing of a crown (9) intended to extend around the satellites and the cage, characterized in that it comprises first and second independent lubrication circuits (15a, 15b), the first circuit (15a) comprising a first inlet (15aa ) dedicated oil connected by a p first annular oil chamber (15ab) extending around the axis X to pipes (15ac) for supplying oil to the said axes of the satellites, and the second circuit (15b) comprising a second inlet (15ba ) dedicated oil connected by a second annular oil chamber (15bb) extending around the X axis to channels (15bc) for supplying oil to the meshes of the teeth of the satellites with the crown, and in that said first and second inlets, said pipes, said channels, and at least part of said first and second chambers are integrated in said cage.
    [0002]
    Planet carrier (10) according to claim 1, in which said first and second inlets (15aa, 15ba) are oriented radially with respect to said axis X and open radially outwards.
    [0003]
    Planet carrier (10) according to Claim 2, in which the said first and second inputs (15aa, 15ba) are located in the same plane (P3) perpendicular to the said axis X and are inclined with respect to each other.
    [0004]
    Planet carrier (10) according to one of the preceding claims, in which said first and second chambers (15ab, 15bb) are arranged adjacently, one behind the other, along said X axis.
    [0005]
    Planet carrier (10) according to both of Claims 3 and 4, in which one of the said first and second chambers (15bb) is located in the said plane (P3) and connected to one of the said inlets (15ba) by a radial and rectilinear bore (16a), and the other of said first and second chambers (15aa) is located outside of said plane and connected to the other of said inlets (15aa) by two bores (16b, 16c) including a first bore located in said plane and of which a second bore extends in an inclined manner between the first bore and this other chamber.
    [0006]
    Planet carrier (10) according to one of the preceding claims, in which the said conduits (15ac) are formed in one of the said radial walls (14b) and extend in a rectilinear manner between the said first chamber (15ab) and cores (17) for lubricating said axes (10b) of the satellites.
    [0007]
    Planet carrier (10) according to one of the preceding claims, in which the said channels (15bc) are formed in one of the said radial walls (14b) as well as in the said cylindrical wall (14c) and each have a generally L-shaped extending between said second chamber (15bb) and orifices (15bc1) for spraying oil towards said gears.
    [0008]
    Planet carrier (10) according to one of the preceding claims, in which the said first and second chambers (15ab, 15bb) are located at the internal periphery of one of the said radial walls (14b), and are delimited in part by this radial wall and partly by an attached annular distributor (13') comprising a cylindrical wall (13a) internally delimiting said chambers and at least one annular partition (13b, 13c) axially closing one of said chambers.
    [0009]
    Planet carrier (10) according to Claim 8, in which one of the said chambers (15bb) is connected to at least one oil nozzle (23) towards the said solar, the said nozzle also being integrated with the said distributor (13').
    [0010]
    Aircraft turbomachine, characterized in that it comprises a mechanical reduction gear (6) comprising a planet carrier (10) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    CN111561559A|2020-08-21|
    EP3696449A1|2020-08-19|
    US20200300173A1|2020-09-24|
    FR3092889B1|2021-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1114949A2|1999-12-22|2001-07-11|United Technologies Corporation|Epicyclic gear train|
    WO2010092263A1|2009-02-16|2010-08-19|Snecma|Lubrication and cooling of a reduction gear with epicyclic gear train|
    EP2615335A1|2012-01-16|2013-07-17|Hamilton Sundstrand Corporation|Carrier for planetary gear system|
    FR2987416A1|2012-02-23|2013-08-30|Snecma|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.|
    EP2844855A2|2012-04-30|2015-03-11|United Technologies Corporation|Manifold for gas turbine engine|
    EP3109514A2|2015-06-25|2016-12-28|United Technologies Corporation|Rolling element cage for geared turbofan|
    FR3041054A1|2015-09-15|2017-03-17|Hispano-Suiza|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|
    WO2019016463A1|2017-07-20|2019-01-24|Safran Transmission Systems|Assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine|
    FR3065773B1|2017-04-27|2020-03-06|Safran Transmission Systems|CAGE SATELLITE HOLDER FOR AN EPICYCLOIDAL SPEED REDUCER|
    FR3092888B1|2019-02-14|2021-01-22|Safran Trans Systems|LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AIRCRAFT|
    法律状态:
    2020-01-21| PLFP| Fee payment|Year of fee payment: 2 |
    2020-08-21| PLSC| Publication of the preliminary search report|Effective date: 20200821 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 3 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1901524A|FR3092889B1|2019-02-14|2019-02-14|LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AIRCRAFT|
    FR1901524|2019-02-14|FR1901524A| FR3092889B1|2019-02-14|2019-02-14|LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AIRCRAFT|
    EP20157152.8A| EP3696449A1|2019-02-14|2020-02-13|Lubrication of a planet carrier for a mechanical gear of a turbine engine, in particular for an aircraft|
    CN202010090915.1A| CN111561559A|2019-02-14|2020-02-13|Lubrication of a planet carrier of a mechanical reducer, in particular for an aircraft turbine engine|
    US16/790,360| US20200300173A1|2019-02-14|2020-02-13|Lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft|
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