GEAR MOTOR FOR AN AIRCRAFT

Abstract

Geared motor (10), particularly for an aircraft, said geared motor (10) comprising: - an electric motor (12), - a mechanical reducer (14), the reducer (14) comprising a rotating solar element (26) about an axis (A), a ring gear (28), and planet gears (30) interposed between the solar element (26) and the ring gear (28) and meshed with the solar element (26) and the ring gear (28), the planet gears (30) being carried by a planet carrier (32), - an annular housing (42) surrounding the motor (12) and the reducer (14), and - a lubrication circuit (60) for the gears of the reducer (14), characterized in that it further comprises a heat exchanger (100), this heat exchanger (100) comprising an oil network (102) which is supplied by said circuit (60) and which is formed in or on said housing (42) in order to extend around the motor (12) and the reducer (14). Figure for the abbreviation: Figure 1

Description

Title of the invention: GEAR MOTOR FOR AN AIRCRAFT Technical field of the invention

[0001] The present invention relates in particular to a geared motor, especially for an aircraft, as well as to an aircraft comprising such a geared motor. Technical Downstream Plan

[0002] The state of the art includes in particular documents FR-A1-2 987 416, FR-Al-2 853 382, ​​FR-A1-3 041 054, FR-A1-3 073 915, FR-A1-3 084 428.

[0003] The combination of an electric motor and a mechanical reducer forms a geared motor.

[0004] The role of a mechanical reducer is to modify the speed ratio and torque between the input shaft and the output shaft of a mechanism.

[0005] New generations of turbofan engines, particularly those with a high bypass ratio, include a mechanical gearbox to drive the shaft of a fan. Typically, the purpose of the gearbox is to transform the high rotational speed of the power turbine shaft into a slower rotational speed for the fan-driving shaft.

[0006] Such a reduction gear 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 a planet carrier. The sun gear, ring gear, and planet carrier are planetary gears because their axes of revolution coincide with the longitudinal axis of the turbomachine. The planet gears each have a different axis of revolution, equally spaced on the same operating diameter around the axis of the planet gears. These axes are parallel to the longitudinal axis of the turbomachine.

[0007] Several gearbox architectures exist. In the state of the art of turbofan engines, gearboxes are of the planetary or epicyclic type. In other similar applications, there are so-called differential or "compound" architectures.

[0008] - on a planetary reducer, the planet carrier is fixed and the ring constitutes the output shaft of the device which rotates in the opposite direction to the solar.

[0009] - on an epicyclic reducer, the ring gear is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the solar panel.

[0010] - on a differential reducer, no element is fixed for rotation. The ring rotates in the opposite direction to the solar panel and the satellite carrier.

[0011] Gear reducers can be composed of one or more meshing stages. This meshing is achieved in various ways, such as by contact, friction, or magnetic field. There are several types of contact meshing, such as with straight or herringbone teeth.

[0012] A gearbox requires lubrication to function correctly. It is difficult to incorporate a lubrication system external to the gearbox because the electric motor is not designed for this purpose. One solution to this problem could be to splash the rotating parts of the gearbox in oil. However, the resulting "bubbling" would not be sufficiently effective to ensure adequate lubrication of the gears.

[0013] During the lubrication of the gearbox gears, the oil absorbs thermal energy and therefore also serves to dissipate heat in addition to lubrication. This thermal energy causes the oil temperature to rise. The higher the oil temperature, the lower its viscosity and the less effective the lubrication provided by the oil. It is therefore important to limit the temperature increase of the lubricating oil and ideally to cool it.

[0014] The present invention provides a solution to this need, which is simple, effective and economical. Summary of the invention

[0015] The invention relates to a geared motor, in particular for an aircraft, this geared motor comprising:

[0016] - an electric motor,

[0017] - a mechanical reducer, the reducer comprising a rotating movable solar element around an axis, a corona, and satellites intercalated between the solar system and the corona and meshed with the solar system and the corona, the satellites being carried by a satellite carrier,

[0018] - an annular housing surrounding the motor and the reducer, and

[0019] - a lubrication circuit for the gears of the reducer,

[0020] characterized in that it further comprises a heat exchanger, this heat exchanger comprising an oil network which is supplied by said lubrication circuit and which is formed in or on said casing in order to extend around the electric motor and the reducer.

[0021] The distinctive feature of the invention lies in the fact that a heat exchanger is integrated into the geared motor to cool the gearbox's lubricating oil. The exchanger comprises a first circuit, which is an oil circuit supplied by the geared motor's lubrication circuit. The heat exchanger is preferably a surface-type or ACOC (Air-Cooled Oil-Cooled) heat exchanger, this heat exchanger having a surface intended to be cooled by an airflow. This surface can be an external surface of the geared motor, such as of a geared motor housing.

[0022] The present invention is compatible with: - of a single-stage or multi-stage reducer; - of straight, helical or chevron teeth; - of any type of one-piece satellite carrier or of the cage and cage carrier type; - of all types of satellite guidance bearings, such as rolling element bearings or hydrodynamic.

[0023] The geared motor according to the invention may comprise one or more of the following features, taken individually or in combination with each other; these features having, in particular, the advantage of optimizing the compactness of the geared motor: • the oil network has an annular shape around the axis; • The oil network includes at least one helical channel that extends around the axis; • the oil network includes at least one channel that meanders or undulates around the axis; • the satellite carrier is fixed to said housing, and the crown is mobile in rotation around the axis; • the oil network is connected to said lubrication circuit by at least one conduit formed in the planet carrier; • the geared motor further includes cooling fins which are formed on the casing or carried by the casing and which extend all around the shaft and the oil network; • the oil network has a dimension along the axis which is greater than or equal to 80% of a dimension along the axis of said casing, or of a cylindrical wall of said casing in which the oil network is formed; • the oil network has a radial thickness with respect to the axis which is greater than or equal to 30% of a radial thickness with respect to the axis of said crankcase, or of a cylindrical wall of said crankcase in which the oil network is formed; • the oil network includes an oil inlet connected to the lubrication circuit, and an oil outlet; • The lubrication circuit is self-contained and installed inside the geared motor. The lubrication circuit includes a lubricating oil reservoir, a pump located within the reservoir and designed to be immersed in the lubricating oil, and a pump with a rotor coupled to the solar array. This rotor is driven by the solar array to draw oil from the reservoir and supply it with oil. of the oil network; • the oil outlet of the oil network is in fluidic communication with the reservoir so that the oil coming out of the oil network is able to flow into the reservoir; • the pump is connected to the oil network by an annular oil distributor which extends around the axis; • the oil distributor includes an internal annular channel for oil circulation and oil supply to several nozzles which are distributed circumferentially around the axis and which are configured to lubricate at least some of the satellite gears; • the oil distributor is formed as a single piece with the nozzles; • The oil distributor is surrounded by the oil network and is connected to this network oil through a conduit formed in the satellite carrier; • The oil distributor includes mounting brackets for attaching it to the satellite carrier;

[0024] — the reservoir is located in the solar array, and in particular is formed by the solar array, in particularly when the geared motor is in a default operating position;

[0025] — in the default position, the main axis of the geared motor is oriented vertically;

[0026] — in another position, in which the main axis of the geared motor is oriented horizontally, the oil contained in the geared motor can be stored inside the planet carrier and / or the casing;

[0027] — the solar element has, in axial section, a general L or C shape and comprises a wall internal cylindrical which includes or carries an external toothing, a radial annular wall which extends outwards from the internal cylindrical wall, and an external cylindrical wall which extends around the internal cylindrical wall and is connected to the external periphery of the radial wall, at least some of these walls of the solar defining between them said reservoir;

[0028] — the solar element further comprises an internal cylindrical rib which is located between the internal and external cylindrical walls, and at a distance from the latter, and which is connected to the radial wall, this rib defining the reservoir with the radial wall and the internal cylindrical wall;

[0029] — the pump is connected to the nozzles by an annular distributor which extends around the axis;

[0030] — the pump and the nozzles are carried by the distributor;

[0031] — the nozzles extend inside the ring, parallel to the axis, and are in intercalated between the satellites;

[0032] — the number of nozzles is equal to the number of satellites, each of the satellites being associated with a sprinkler that is located between this satellite and an adjacent satellite;

[0033] — the number of nozzles is equal to twice the number of satellites, each of the sa tellites being associated with two nozzles which are located on either side of the satellite;

[0034] — the geared motor further comprises an oil control system in the mo- tore reducer;

[0035] — the control system includes a sensor or window through which a The operator can see the presence of oil, or even the oil pressure, in the geared motor;

[0036] — the window or sensor is located on a housing of the geared motor and is aligned on the projection axis of an oil spray nozzle;

[0037] — the oil spray nozzle is carried by the satellite carrier and connected to said dis tributary, preferably via an oil channel formed in the satellite carrier;

[0038] — the pump is of the gerotor type, or vane or gear type;

[0039] — the pump rotor and the satellites are driven by the same gear teeth of the solar;

[0040] — the distributor also supplies plain bearings for guiding the satellites;

[0041] — the reducer is coupled to the geared motor.

[0042] The invention further relates to an aircraft comprising a geared motor as described above, in particular for driving a propulsion propeller. Brief description of the figures

[0043] 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:

[0044] [Fig-1] [Fig.1] is a schematic exploded perspective view of a geared motor according to the invention;

[0045] [Fig.2] [Fig.2] is a schematic axial cross-sectional view of the geared motor of the [Fig.l];

[0046] [Fig.3] [Fig.3] is a schematic axial cross-sectional view of the geared motor of the [Fig.l], in a first position and illustrates the storage of the oil from the reservoir in this first position;

[0047] [Fig.4] [Fig.4] is a schematic axial cross-sectional view of the geared motor of the [Fig.l], in a second position and illustrates the storage of the oil from the reservoir in this second position;

[0048] [Fig.5] [Fig.5] is a schematic cross-sectional view of the geared motor of the [Fig.1], and shows a lubrication circuit for this geared motor;

[0049] [Fig.6] [Fig.6] is a schematic axial cross-sectional view of the geared motor of the [Fig.l], and shows a heat exchanger of the geared motor;

[0050] [Fig.7] [Fig.7] is a schematic perspective view of an embodiment of an oil network for the heat exchanger of the geared motor; and

[0051] [Fig.8] [Fig.8] is a schematic perspective view of an alternative embodiment of an oil network of the heat exchanger of the geared motor. Detailed description of the invention

[0052] Figures 1 to 6 illustrate an embodiment of a geared motor 10 according to the invention, this geared motor being particularly suitable for use in an aircraft.

[0053] The aircraft is, for example, of the VTOL type, i.e., vertical takeoff and landing. The geared motor 10 can, for example, be used to drive the propulsion propeller or one of the propulsion propellers of the aircraft.

[0054] Advantageously, the geared motor 10 is designed to drive the propeller around a vertical axis. However, it is understood from the following description that the axis of rotation of the propeller can have any orientation.

[0055] The geared motor 10 comprises an electric motor 12 and a mechanical reducer 14.

[0056] The electric motor 12 has an annular shape and is aligned on an axis A, which is a common axis with the reducer 14.

[0057] As mentioned above, this axis A can be oriented vertically, in particular during takeoff or landing of the aircraft.

[0058] The electric motor 12 comprises a rotor 16 and a stator 18. In the example shown, the rotor 16 is located inside the stator 18.

[0059] In the example shown, the rotor 16 comprises an annular row of permanent magnets 20. These magnets 20 can be separated from each other by spacers. The number of magnets 20 can be greater than 20 or 30, for example.

[0060] The stator 18 may include an annular row of windings (not shown) which are formed by winding around cores 24. The number of cores 24 is, for example, equal to the number of permanent magnets 20.

[0061] The reducer 14 can be of the planetary type, that is to say, it includes a movable ring and a fixed planet carrier.

[0062] The reducer 14 thus comprises a solar 26 movable in rotation around the axis A, a ring 28 movable in rotation around this axis A, and satellites 30 intercalated between the solar 26 and the ring 28 and meshed with the solar 26 and the ring 28.

[0063] The satellites 30 are carried by a fixed satellite carrier 32. Conventionally, each of the satellites 32 is mounted on an axis that forms a plain bearing or around which a roller bearing is mounted.

[0064] In the example shown, the solar element 26 has a general L-shaped profile in axial section or C and includes:

[0065] - an internal cylindrical wall 26a which includes or carries external teeth 33,

[0066] - a radial annular wall 26b extending from the internal cylindrical wall 26a outwards,

[0067] - and possibly an external cylindrical wall 26c which extends around the wall internal cylindrical 26a and which is connected to the external periphery of the radial wall 26b.

[0068] In the example shown, the rotor 16 is directly fixed to the outer periphery of the radial wall 26b or to the outer cylindrical wall 26c, or the stator 18 is directly carried by the outer periphery of the radial wall 26b or by the outer cylindrical wall 26c.

[0069] Advantageously, the geared motor 10 includes a first bearing 34 for guiding the solar 26, which is mounted between the solar 26 and the satellite carrier s 32, and a second bearing 36 for guiding the solar 26, which is mounted between the solar 26 and the ring 28.

[0070] The first bearing 34 preferably has a diameter greater than that D2 of the teeth 33 of the solar 26

[0071] The second bearing 36 preferably has a diameter smaller than that of the teeth 33 of the solar 26.

[0072] In the example shown, the first bearing 34 is supported by the radial wall 26b, and the second bearing 36 is located inside the internal cylindrical wall 26c.

[0073] In the example also shown, the crown 28 has a general L or C shape in axial section and comprises:

[0074] - an external cylindrical wall 28a which includes or carries internal teeth 38,

[0075] - a radial annular wall 28b extending from the external cylindrical wall 28a inward,

[0076] - and possibly an internal cylindrical wall 28c which extends inside the external cylindrical wall 28a and which is connected to the internal periphery of the radial wall 28b.

[0077] The rotor 16 can extend at least partially around the internal teeth 38 of the crown 28.

[0078] The geared motor 10 further includes an output shaft 50 in the example shown, which is coupled by splines 40 to the inner periphery of the radial wall 28b or to the inner cylindrical wall 28c.

[0079] As in the example shown, the satellite carrier 32 is fixed to a housing 42 of the geared motor 10.

[0080] The stator 18 of the motor 12 can be fixed directly to the housing 42 or carried directly by the housing 42.

[0081] The housing 42 may have a general L or C shape in axial section and comprise:

[0082] - an external cylindrical wall 42a,

[0083] - a radial annular wall 42b extending from the outer cylindrical wall towards the interior,

[0084] - and possibly an internal cylindrical wall 42c which extends inside the external cylindrical wall 42a and which is connected to the internal periphery of the radial wall 42b.

[0085] The geared motor 10 may include a bearing 44 for guiding the output shaft 50, this bearing 44 being mounted between the output shaft 50 and the inner periphery of the radial wall 42b or the inner cylindrical wall 42c of the housing 42.

[0086] The satellite carrier 32 can be fixed to the radial wall 42b of the housing 42, as in the example shown.

[0087] In the example shown, the geared motor 10 further includes a lubrication circuit 60 for the gears of the reducer 14, i.e. for the gears between the teeth of the solar 26 and the satellites 30, and between the teeth of the satellites 30 and the ring 28.

[0088] Advantageously, the lubrication circuit 60 is self-contained and is installed inside the geared motor 10. This lubrication circuit 60 includes a reservoir 62 of lubricating oil, at least one pump 64 located in the reservoir 62 and suitable for immersion in the lubricating oil 66 contained in the reservoir 62, and nozzles 68 connected to the pump 64.

[0089] The pump 64 includes a rotor 64a which is coupled to the solar 26 and which is capable of being driven in rotation by the solar 26 for the extraction of oil 66 from the reservoir 62 and the supply of oil to the nozzles 68.

[0090] Advantageously, it is the same toothing 33 of the solar 26 which drives both the satellites 32 and the rotor 64a of the pump 64.

[0091] The pump 64 is for example of the gerotor type or vane type or gear type.

[0092] Figure 3 shows the geared motor 10 in its default position in the aircraft. is oriented so that its axis A is vertical, allowing the propeller that drives it to rotate around the vertically oriented axis A. In this position, the reservoir 62 is located within the solar 26, and in particular is formed by the solar 26.

[0093] In the example shown, at least some of the walls 26a, 26b, 26c of the solar 26 define the reservoir 62 between them.

[0094] The solar 26 may include an internal cylindrical rib 26d which is located between the internal and external cylindrical walls 26a, 26c, and at a distance from them, and which is connected to the radial wall 26b.

[0095] The rib 26d can define the reservoir 62 with the radial wall 26b and the internal cylindrical wall 26a.

[0096] Figure 4 shows the geared motor 10 in another position in which it is oriented so that its axis A is horizontal. This may be the same geared motor 10. mounted in the same aircraft but with a different orientation in which its propeller rotates around the horizontally oriented axis A. In this position, the oil 66 has flowed into the geared motor 10 and is now in a new position. In the example shown, the oil is contained within the satellite carrier 32 and the housing 42.

[0097] The lubrication circuit 60 preferably includes a distributor 70 which connects the pump 64 to the nozzles 68, and which is visible in particular in Figures 1 and 5.

[0098] The distributor 70 preferably has an annular shape and extends around the axis A.

[0099] The distributor 70 includes an internal annular oil circulation channel and oil supply to the 68 nozzles.

[0100] The distributor 70 is fixed to the satellite carrier 32 and includes for this purpose fixing tabs 82 which are applied and fixed to the satellite carrier 32, by means of screws 84 or bolts for example.

[0101] The distributor 70 is preferably formed in one piece with the legs 82 and at least part of the nozzles 68.

[0102] The jets 68 can extend inside the ring 28, parallel to the axis A, and be intercalated between the satellites 30.

[0103] In a first embodiment, the number of nozzles 68 is equal to the number of satellites 30, each of the satellites 30 being associated with a nozzle 68 which is located between this satellite and a circumferentially adjacent satellite.

[0104] In one embodiment, which is illustrated in the drawings, the number of nozzles 68 is equal to twice the number of satellites 30, each satellite 30 being associated with two nozzles 68 located on either side of the satellite. This configuration is advantageous because the nozzles 68 are capable of lubricating the gears, both upstream and downstream of the satellites 30, regardless of the direction of rotation of the solar element 26.

[0105] Fig. 6 shows an oil control system 80 in the geared motor 10, this control system 80 having a window 82 through which an operator or a sensor 83 can view the presence of oil, or even the oil pressure, in the geared motor 10. Alternatively, this window 82 could be replaced by a sensor.

[0106] In the example shown, the window 82 is formed in or carried by the housing 42 of the geared motor 10.

[0107] The window 82 is aligned with an oil line 84 formed in the planet carrier 30, this oil line 84 being connected to the distributor 70 and being supplied with oil by the latter. It is therefore understood that the distributor 70 supplies both the nozzles 68 and the line 84 formed in the planet carrier 30.

[0108] The conduit 84 may have an elongated shape along an axis B parallel to the axis A, and include one end connected by a fitting 88 to the distributor 70 and an opposite end connected to an oil spray nozzle 86. This nozzle 86 is configured to spray oil onto the window 82 (or the sensor 83) to allow the operator to check the presence or even the pressure of the oil in the geared motor 10. It is thus understood that the window 82, the nozzle 86 and the pipe 84 extend on the same axis B in the example shown.

[0109] Advantageously, in addition to supplying oil to the nozzles 68 and the channel 84, the distributor 70 can be configured to supply oil to internal cavities of the plain bearings of the satellites 30. The distributor 70 is then connected to a series of nozzles 90 which are each aligned and connected to the plain bearings (Figures 1 and 5).

[0110] Integrating the lubrication circuit directly into the geared motor 10 eliminates the need for external components. Using the solar element 26 as an oil reservoir, rather than a separate reservoir, reduces the number of parts and limits the size and weight of the lubrication circuit. Furthermore, using a lubrication circuit instead of simply splashing the rotating parts of the geared motor improves the performance and efficiency of the geared motor.

[0111] According to the invention, the geared motor 10 further comprises a heat exchanger 100 (see [Fig.6]).

[0112] This heat exchanger 100 includes an oil network 102 which is supplied by the lubrication circuit 60, which is of the type described previously or of another type, and which is formed in or on the casing 42 in order to extend around the motor 12 and the reducer 14.

[0113] This oil network 102 preferably has an annular shape around the axis A.

[0114] Figures 7 and 8 illustrate embodiments of this oil network 102.

[0115] In [Fig.7], the oil network 102 includes at least one helical channel 104 which extends around the axis A.

[0116] In [Fig.8], the oil network 102 includes at least one channel 106 which meanders or undulates around the axis A.

[0117] It can be seen in these figures that the distributor 70 is surrounded by the oil network 102, and can be connected to the latter by one or more conduits 108.

[0118] The oil network 102 includes at least one oil inlet 102a connected to the circuit 60, and at least one oil outlet 102b.

[0119] The inlet 102a of the oil network 102 is preferably connected to the lubrication circuit 60 by at least one conduit 108 formed in the planet carrier 32. In the example shown in [Fig.6], this conduit 108 is at least partly formed by the channel 84 of the planet carrier 32.

[0120] It is therefore understood that, in the example shown, the exchanger 100 is connected to the lubrication circuit 60 and in particular the pump 64 by the distributor 70. The distributor 70 is connected to the exchanger 100 by a special outlet 70a, which is connected to the pipe 84 and the conduit 108 by the aforementioned fitting 88.

[0121] The oil outlet 102b of the oil network 102 is preferably in fluidic communication with the reservoir 66 so that the oil coming out of the oil network 102 is able to flow into the reservoir 66.

[0122] The oil network 102 can have a dimension L1 along the axis A which is greater than or equal to 80% of a dimension L2 along the axis A of the housing 42, or of the cylindrical wall 42a of the housing 42 in which the oil network 102 is formed.

[0123] The oil network 102 can have a radial thickness El with respect to the axis A which is greater than or equal to 30% of a radial thickness E2 with respect to the axis A of the housing 42, or of the cylindrical wall 42a of the housing 42 in which the oil network 102 is formed.

[0124] The heat exchanger 100 is preferably of the surface type or ACOC (acronym for Air-Cooled Oil-Cooled), this heat exchanger having a surface 100a intended to be cooled by an airflow.

[0125] This surface 100a is here an external surface of the geared motor 10, and in particular the external surface of the housing 42 and its wall 42a.

[0126] The geared motor 10 preferably includes cooling fins 110 on this surface 100a. These fins 110 are formed as projecting parts on the housing 42 or carried by the housing 42 and extend all around the axis A and the oil network 102.

[0127] The fins 110 may have a dimension L3 along the axis A which is greater than or equal to L1 and for example equal to L2. The fins 110 may have a radial thickness E3 with respect to the axis A which is greater than or equal to E2.

[0128] The present invention offers several advantages, including:

[0129] - integrating the heat exchanger directly into the geared motor avoids the addition of an external heat exchanger thus allows for a reduction in size and weight;

[0130] - this integration also makes it possible to contain the oil in the geared motor and This helps to reduce sealing problems since in the event of a leak the oil would flow into the reducer and not outside;

[0131] - the ability to cool the oil allows the oil's characteristics to be preserved and thus improve the performance of the geared motor compared to a splash lubrication system; etc.

Claims

Demands

1. Geared motor (10), particularly for an aircraft, said geared motor (10) comprising: - an electric motor (12), - a mechanical gearbox (14), the gearbox (14) comprising a rotating sun gear (26) about an axis (A), a ring gear (28), and planet gears (30) interposed between the sun gear (26) and the ring gear (28) and meshed with the sun gear (26) and the ring gear (28), the planet gears (30) being carried by a planet carrier (32), - an annular housing (42) surrounding the motor (12) and the gearbox (14), and - a lubrication circuit (60) for the gears of the gearbox (14), characterized in that it further comprises a heat exchanger (100), said heat exchanger (100) comprising an oil network (102) which is supplied by said lubrication circuit (60) and which formed in or on said casing (42) in order to extend around the electric motor (12) and the reducer (14).

2. Geared motor (10) according to claim 1, wherein the oil network (102) has an annular shape around the axis (A).

3. Geared motor (10) according to claim 1 or 2, wherein the oil network (102) comprises at least one helical channel (104) which extends around the axis (A).

4. Geared motor (10) according to claim 1 or 2, wherein the oil network (102) comprises at least one channel (106) which meanders or undulates around the axis (A).

5. Geared motor (10) according to any one of the preceding claims, wherein the planet carrier (32) is fixed to said housing (42), and the ring (28) is movable in rotation about the axis (A).

6. Geared motor (10) according to claim 5, in which the oil network (102) is connected to said lubrication circuit (60) by at least one conduit (108) formed in the planet carrier (32).

7. Geared motor (10) according to any one of the preceding claims, further comprising cooling fins (110) which are formed on the housing (42) or carried by the housing (42) and which extend all around the axis (A) and the oil network (102).

8. Geared motor (10) according to any one of the preceding claims, wherein the oil network (102) has a dimension (L1) along the axis (A) which is greater than or equal to 80% of a dimension (L2) along the axis (A) of said casing (42), or of a cylindrical wall of said casing (42) in which the oil network (102) is formed.

9. Geared motor (10) according to any one of the preceding claims, wherein the oil network (102) has a radial thickness (E1) with respect to the axis (A) which is greater than or equal to 30% of a radial thickness (E2) with respect to the axis (A) of said housing (42), or of a cylindrical wall of said housing (42) in which the oil network (102) is formed.

10. Geared motor (10) according to any one of the preceding claims, wherein the oil network (102) comprises an oil inlet (102a) connected to the lubrication circuit (60) and an oil outlet (102b).

11. Geared motor (10) according to any one of the preceding claims, wherein the lubrication circuit (60) is self-contained and installed inside the geared motor (10), the lubrication circuit (60) comprising a reservoir (62) of lubricating oil (66), a pump (64) located in the reservoir (62) and adapted to be immersed in the lubricating oil (66) contained in the reservoir (62), the pump (64) comprising a rotor (64a) which is coupled to the solar element (26) and adapted to be driven in rotation by the solar element (26) for drawing oil from the reservoir (62) and supplying oil to the oil network (102).

12. Geared motor (10) according to claim 11, depending on claim 10, wherein the oil outlet (102b) of the oil network (102) is in fluidic communication with the reservoir (66) so that the oil exiting the oil network (102) is able to flow into the reservoir (66).

13. Geared motor (10) according to claim 11 or 12, wherein the pump (64) is connected to the oil network (102) by an annular oil distributor (70) which extends around the axis (A).

14. Geared motor (10) according to claim 13, wherein the oil distributor (70) comprises an internal annular channel for circulating oil and supplying oil to several nozzles (68) which are distributed circumferentially around the axis (A) and which are configured to lubricate at least some of the gears of the satellites (30).

15. Geared motor (10) according to claim 14, wherein the oil distributor (70) is formed in one piece with the nozzles (68).

16. Geared motor (10) according to any one of claims 13 to 15, wherein the oil distributor (70) is surrounded by the oil network (102) and is connected to this oil network (102) by a conduit (108) formed in the planet carrier (32).

17. Geared motor (10) according to any one of claims 13 to 16, wherein the oil distributor (70) includes tabs (82) for fixing to the planet carrier (32).

18. Aircraft, comprising a geared motor (10) according to any one of the preceding claims for driving a propulsion propeller.

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