阅读说明：本技术 飞行器涡轮机的机械减速器中的润滑油的供给和回收 (Supply and recovery of lubricating oil in mechanical reducers of aircraft turbines ) 是由 阿德瑞安·路易斯·西蒙 于 2020-11-20 设计创作，主要内容包括：本发明涉及在飞行器涡轮机的机械减速器中润滑油的供给和回收。本发明还涉及用于特别是飞行器的涡轮机的机械减速器的润滑油分配器、减速器以及飞行器涡轮机。该分配器具有围绕轴线X的大致环状形状的主体,并且包括第一和第二独立的油回路,第一油回路包括第一油入口,该第一油入口通过第一腔室连接到围绕轴线X分布在主体上的多个油出口,并且第二油回路包括第二油入口,该第二油入口通过第二腔室连接到围绕轴线X分布在主体上的多个油出口,第一腔室和第二腔室以不同的直径围绕轴线X沿圆周延伸,其特征在于,第一油回路和第二油回路在主体中形成,并且分别是回收回路和用于减速器的齿的油供给回路。(The invention relates to the supply and recovery of lubricating oil in mechanical reducers of aircraft turbines. The invention also relates to a lubricating oil distributor for a mechanical retarder of a turbomachine, in particular of an aircraft, to a retarder and to an aircraft turbomachine. The distributor has a body of substantially annular shape about an axis X and comprises a first and a second independent oil circuit, the first oil circuit comprising a first oil inlet connected by a first chamber to a plurality of oil outlets distributed on the body about the axis X, and the second oil circuit comprising a second oil inlet connected by a second chamber to a plurality of oil outlets distributed on the body about the axis X, the first and second chambers extending circumferentially about the axis X with different diameters, characterized in that the first and second oil circuits are formed in the body and are respectively a recovery circuit and an oil feed circuit for the teeth of the reducer.)

1. A lubricant distributor (13) for a mechanical reducer (6) of a turbomachine (1), in particular of an aircraft, the distributor having a body of substantially annular shape about an axis X and comprising an independent oil circuit (23, 20) formed in the body, characterized in that it comprises:

-an oil recovery circuit (23) configured to recover oil and comprising a plurality of first oil inlets (23a) distributed on the body around the axis X and connected to at least one first oil outlet (23c) by a first annular chamber (23b), and

-an oil feed circuit (20) configured to feed the teeth of the reducer in particular with oil and comprising a second oil inlet (20a) connected by a second annular chamber (20b) to a plurality of second oil outlets (20c) distributed on the body around the axis X, the first and second chambers extending circumferentially around the axis X with different diameters.

2. Distributor (13) according to claim 1, wherein said circuit comprises a further oil feeding circuit (21) which is independent and configured to feed oil in particular to the bearings of the reducer, said further feeding circuit (21) comprising at least one third oil inlet (21a) connected by a third annular chamber (21b) to a plurality of third oil outlets (21c) distributed on the body around the axis X.

3. Distributor (13) according to the preceding claim, wherein the first oil outlet (23c) of the recovery circuit (23), the second oil inlet (20a) of the feeding circuit (20) and the third oil inlet (21a) of the further feeding circuit (21) are oriented in a radial direction with respect to the axis X.

4. Distributor (13) according to claim 2 or 3, wherein the first outlet (23c) of the recovery circuit (23), the second outlet (20c) of the feeding circuit and the third outlet (21c) of the further feeding circuit (21) are axially oriented in the same direction.

5. Distributor (13) according to any one of claims 2 to 4, wherein it comprises bosses (25) distributed on the body around the axis X, each of these bosses comprising one of the first outlets (23a) of the recovery circuit (23) and one of the second outlets (20c) of the feed circuit (20).

6. Distributor (13) according to any one of claims 2 to 5, wherein the diameter of the chamber (21b) of the further feeding circuit (21) is greater than the diameter of the chamber (20b) of the feeding circuit (20), which itself is preferably greater than the diameter of the chamber (23b) of the recovery circuit (23).

7. The dispenser (13) according to any one of the preceding claims, wherein the body is made in one piece.

8. A mechanical retarder (6) for an aircraft turbine, the retarder comprising: a cage (14) defining a housing for housing a central sun gear (7) having an axis of rotation X; a planetary gear (8) arranged around the sun gear; a deflector (18) fixed to the cage and arranged between the planet gears; and a distributor (13) according to any one of the preceding claims, attached and fixed to the cage and connected to the deflector (18), the distributor being configured to supply lubricating oil to the teeth of the sun and planet gears, or even to the planet gear bearings (11), and to recover at least part of the oil through the deflector (18).

9. A reducer (6) according to the preceding claim, wherein each of the deflectors (18) comprises a block comprising two opposite sides (18a, 18b) of substantially curved shape, which extend around the planet gears and on which are located oil inlet holes (35a) in fluid communication with the oil recovery circuit (23) for recovering oil from the teeth of the reducer.

10. A reducer according to the preceding claim in which the oil inlet hole (35a) is connected to an oil outlet port (35b) of the block of the deflector through an internal passage of the block shaped to convey the recovered oil to said port by means of the centrifugal force exerted on the projected oil by the planet gears arranged on either side of the deflector.

11. An aircraft turbine comprising a mechanical reducer (6) equipped with a planet carrier (10) according to the preceding claim.

Technical Field

The present invention relates to the field of mechanical reducers for turbomachines, in particular aircraft turbomachines, and in particular to the supply and recovery of lubricating oil in these reducers.

Background

The prior art includes in particular the documents WO-A1-2010/092263, FR-A1-2987416, EP-A1-2317181, US-A1-2011/124461 and FR-A1-3041054.

The function of a mechanical reducer is to change the speed-to-torque ratio between the input and output shafts of a mechanical system.

A new generation of double-flow turbines, in particular those with high bypass ratio, comprises a mechanical reducer to drive the shaft of the fan. Generally, the purpose of the speed reducer is to convert the so-called fast rotational speed of the shaft of the power turbine into a slower rotational speed of the shaft for driving the fan.

Such a reducer comprises a central pinion, called 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 carrier. The sun gear, the ring gear and the planet carrier are planet gears, since their axes of rotation coincide with the longitudinal axis X of the turbine. The planet gears each have a different axis of rotation, equally distributed about the axis of the planet gears on the same running diameter. These axes are parallel to the longitudinal axis X.

There are a variety of retarder architectures. In the prior art of double flow turbines, the speed reducer is of the planetary or epicyclic type. In other similar applications, there are so-called differential architectures or composite architectures.

On a planetary reducer, the planet carrier is fixed and the ring gear constitutes the output shaft of the plant, which rotates in the opposite direction to the sun gear.

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

On a differential reducer, no element is rotationally fixed. The ring gear rotates in the opposite direction to the sun gear and the carrier.

The reduction gear may be constituted by one or more meshing stages. The engagement is ensured in different ways, for example by contact, friction or a magnetic field.

There are various types of contacting engagement, such as straight teeth, helical teeth, or herringbone teeth.

The present invention provides an improved retarder by means of a simple, effective and economical solution to improve the supply and recovery of lubricating oil in the retarder.

Disclosure of Invention

The invention relates to a lubricating oil distributor for a mechanical reducer, in particular of an aircraft turbomachine, having a body of substantially annular shape about an axis X and comprising an independent oil circuit formed in the body, characterized in that said circuit comprises:

-an oil recovery circuit configured to recover oil and comprising a plurality of first oil inlets distributed on the body around said axis X and connected to at least one first oil outlet by a first annular chamber, and

-an oil feed circuit configured to feed the teeth of the reducer in particular with oil and comprising a second oil inlet connected by a second annular chamber to a plurality of second oil outlets distributed on the body around said axis X, the first and second chambers extending circumferentially around the axis X with different diameters.

Therefore, the distributor is designed to perform various functions of oil supply and recovery of lubricating oil from the decelerator. These functions are provided by separate oil circuits. One oil circuit is dedicated to feeding the reducer to lubricate it. The other oil circuit is dedicated to recovering the oil that has lubricated the retarder and to draining it for recirculation. The circuits are independent so that oil recovery is not hampered by oil supply and vice versa. This also limits or even prevents the risk of heating the lubricating oil by means of recovered oil, which may be hot due to the heat absorbed during lubrication of the retarder.

The rapid draining of oil from the cavity of the retarder improves its efficiency. In fact, the faster the heat generated by the power transmission is removed, the lower the operating temperature, and the shorter the time the oil has to be heated.

In the case of a planetary type operation, i.e. with a fixed planet carrier and a rotating ring gear, it is not possible to centrifuge the oil around the sun gear. This may lead to so-called stirring or even vigorous agitation, which corresponds to an accumulation of hot oil in the decelerator.

The invention is therefore compatible with planetary gear reducers having a fixed planet carrier and a rotating ring gear. The invention is also compatible with any type of teeth (straight, helical, herringbone). The invention is also compatible with any type of planet carrier, whether monolithic or cage/and cage type. Finally, the invention is compatible with any type of planet bearing, whether or not it is constituted by rolling elements, hydrodynamic bearings, etc.

The dispenser according to the invention may comprise one or more of the following features, taken independently of each other or taken in combination with each other:

said circuit comprises a further oil feed circuit, which is independent and is configured to feed the bearings of the reducer in particular, with oil, said further feed circuit comprising at least one third oil inlet connected by a third annular chamber to a plurality of third oil outlets distributed on the body around said axis X,

the body of the dispenser is made in one piece.

-the first oil outlet of the recovery circuit, the second oil inlet of the feed circuit and the third oil inlet of the other feed circuit are oriented in a radial direction with respect to said axis X.

Each chamber is of the closed type, as opposed to for example a groove, the inner or outer periphery of which is open.

-the first, second and/or third chambers are formed by coaxial and tightly connected tubular rings.

-the first outlet of the recovery circuit, the second outlet of the feed circuit and the third outlet of the further feed circuit are axially oriented in the same direction.

-the inlet of the third circuit is located close to the outlet of the first circuit.

The dispenser comprises bosses distributed on the body about said axis X, each of these bosses comprising: a first inlet of the recovery loop; and one of the second outlets of the feed circuit.

The diameter of the chamber of the further feed circuit is greater than the diameter of the chamber of the feed circuit, which itself is preferably greater than the diameter of the chamber of the recovery circuit.

The invention also relates to a mechanical reducer for an aircraft turbine, comprising: a cage defining a housing for housing a central sun gear having an axis of rotation X; a planetary gear disposed around the sun gear; a deflector fixed to the cage and disposed between the planet gears; a distributor as described above, attached and fixed to the cage and connected to a deflector configured to supply lubricating oil to the teeth of the sun gear and the planet gears, or even to the planet gear bearings, and to recover at least part of this oil through said deflector.

Advantageously, each of the deflectors comprises a block comprising two opposite sides with a substantially curved shape, which extend around said planet gears and on which there are positioned oil inlet holes in fluid communication with an oil recovery circuit for recovering oil from the teeth of the reducer.

Preferably, said oil inlet hole is connected to an oil outlet port of the block of the deflector through an internal passage of the block shaped to convey the recovered oil to the port by means of the centrifugal force exerted on the projected oil by the planetary gears arranged on either side of the deflector.

The invention also relates to a deflector for a mechanical reducer, in particular of an aircraft turbine, intended to be interposed between two adjacent planetary gears of said reducer, comprising a block comprising a first lubricating oil circuit comprising at least one oil inlet port and at least one oil outlet hole or port for lubricating the reducer, characterized in that it further comprises a second independent lubricating oil circuit comprising at least an oil inlet hole and at least one oil outlet port for oil recirculation.

Thus, the deflector combines multiple functions, including lubrication supply and recovery for the retarder. Each of these functions is provided by an oil circuit. The first oil circuit is dedicated to feeding the reducer to lubricate it. The second oil circuit is dedicated to recovering the oil that has lubricated the speed reducer and discharging it for recycling. The circuits are independent so that oil recovery is not hampered by oil supply and vice versa. This also limits or even prevents the risk of heating the lubricating oil by means of recovered oil, which may be hot due to the heat absorbed during lubrication of the retarder.

The invention is compatible with planetary gear reducers having a fixed planet carrier and a rotating ring gear. The invention is also compatible with any type of gear (spur, herringbone). The invention is also compatible with any type of planet carrier, whether of the one-piece or cage/cage type. Finally, the invention is compatible with any type of planet bearing, whether or not it is constituted by rolling elements, hydrodynamic bearings, etc.

The deflector according to the invention may comprise one or more of the following features, taken independently of each other or taken in combination with each other:

-the oil inlet port of the first circuit and the oil outlet port of the second circuit are positioned close to each other and on the same face of said block,

-the oil inlet port of the first circuit and the oil outlet port of the second circuit are oriented in substantially parallel directions,

the deflector comprises a radially inner end for orientation towards the main rotation axis of the reducer and a radially outer end for radial orientation opposite to this axis, at which are located the oil inlet port of the first circuit and the oil outlet port of the second circuit,

-the first circuit comprises an outlet and oil projection holes, the outlet and oil projection holes being located at the radially inner end,

the first circuit may comprise an oil outlet port or bore located at said radially outer end,

the block comprises two opposite sides having a substantially curved shape and on which the oil inlet holes of said second circuit are positioned,

-an oil inlet hole is located at the radially inner end,

-each of said ports comprises a tubular water seal and a fluid connection nozzle.

The invention also relates to a planet carrier of a mechanical reducer of a turbomachine, in particular of an aircraft, comprising: a cage defining a housing for housing a central sun gear having an axis of rotation X; a planetary gear disposed around the sun gear; and deflectors as described above, each fixed to the cage and interposed between two adjacent planetary gears.

Furthermore, the invention relates to a mechanical reducer of a turbomachine, in particular of an aircraft, comprising at least one element (deflector, distributor, planet carrier, etc.) as described above.

Finally, the invention relates to a turbine comprising at least one element (deflector, distributor, planet carrier, reducer, etc.) as described above.

The features of the different aspects of the invention may be combined with each other.

Drawings

Further features and advantages will appear from the following description of a non-exhaustive embodiment of the invention, with reference to the accompanying drawings, in which:

figure 1 is a schematic cross-sectional view of a turbine employing the present invention,

figure 2 is a partial cross-sectional view of a mechanical reducer,

figure 3 is a cross-sectional view of a mechanical reducer incorporating aspects of the present invention,

figure 4 is a perspective view of a lubricant distributor for the retarder of figure 3,

fig. 5 is a partial cross-sectional perspective view of the reducer of fig. 3, and illustrates the connection of the distributor of fig. 4 to a deflector,

figure 6 is a perspective view of the deflector of the reducer of figure 3,

figure 7 is another perspective view of the deflector of figure 6,

FIG. 8 is a partial cross-sectional view of the reducer of FIG. 3, an

Fig. 9 is a view similar to fig. 3 and on a larger scale.

Detailed Description

Fig. 1 depicts a turbine 1, which turbine 1 comprises in a conventional manner a rotation axis X, a fan S, a low-pressure compressor 1a, a high-pressure compressor 1b, a combustion annular chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1e and an exhaust nozzle 1 h. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 2, and form a high-pressure (HP) body together with the high-pressure shaft 2. The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3, and form a Low Pressure (LP) body together with the low pressure shaft 3.

The fan S is driven by a fan shaft 4, which fan shaft 4 is driven by the LP shaft 3 by means of a speed reducer 6. The reducer 6 is generally of the planetary or epicyclic type.

The following description relates to a planetary type reducer in which a ring gear is rotatably movable.

The speed reducer 6 is positioned in the upstream portion of the turbine. A fixed structure, here schematically comprising an upstream portion 5a and a downstream portion 5b, constituting the engine casing or stator 5, is arranged to form a casing E around the reducer 6. Here, the casing E is closed upstream by a seal at a position of a bearing that allows passage of the fan shaft 4, and closed downstream by a seal at a position that allows passage of the LP shaft 3.

Fig. 2 shows a reducer 6, which reducer 6 may take the form of different architectures depending on whether some parts are stationary or rotating. On the inlet side, a speed reducer 6 is connected to the LP shaft 3, for example by internal splines 7 a. Thus, the LP shaft 3 drives a planetary pinion called sun gear 7. Conventionally, the rotation axis of the sun gear 7 is identical to the rotation axis X of the turbine, this sun gear 7 driving a series of pinions, called planet gears 8, which are equally distributed on the same diameter around the rotation axis X. This diameter is equal to twice the distance of the running center between the sun gear 7 and the planet gears 8. For this type of application, the number of planet gears 8 is usually limited to between three and seven.

A set of planet gears 8 is held by a frame called a planet carrier 10. Each planet gear 8 rotates about the axis Y of the planet gear 8 itself and meshes with the ring gear 9.

In the planetary configuration, the set of planet gears 8 is held by a planet carrier 10 fixed to the engine housing or stator 5. Each planet gear drives a ring gear which is connected to the fan shaft 4 via a ring gear carrier 12.

Each planet gear 8 is mounted freely rotatably by means of a bearing 11 (for example of the rolling bearing type or hydrodynamic bearing type). Each bearing 11 is mounted on one of the wheel axles (axles)10b of the planet carrier 10 and all the axles are positioned relative to each other by means of one or more structural frames 10a of the planet carrier 10. There are a plurality of axles 10b and bearings 11, the number of axles 10b and bearings 11 being equal to the number of planet gears. The axle 10b and frame 10a may be divided into multiple parts for operational, assembly, manufacturing, inspection, maintenance or spare part reasons.

For the same reasons as above, the teeth of the reducer may be divided into a plurality of spirals, each having a median plane P. In the example shown, the ring gear is divided into two ring gear halves:

an upstream ring gear half 9a, which consists of a rim 9aa and a mounting flange half 9 ab. On the rim 9aa is the upstream helix of the teeth of the reducer. The upstream spiral portion meshes with the spiral portion of the planetary gear 8, and the spiral portion of the planetary gear 8 meshes with the spiral portion of the sun gear 7.

A rear ring gear half 9b, which is made up of a rim 9ba and a mounting flange half 9 bb. On the rim 9ba is the downstream helix of the teeth of the reducer. The downstream spiral portion meshes with the spiral portion of the planetary gear 8, and the spiral portion of the planetary gear 8 meshes with the spiral portion of the sun gear 7.

The mounting flange half 9ab of the upstream ring gear 9a and the mounting flange half 9bb of the downstream ring gear 9b form a ring gear mounting flange 9 c. The ring gear 9 is attached to the ring gear carrier by assembling the mounting flange 9c of the ring gear and the mounting flange 12a of the ring gear carrier using, for example, a bolt assembly.

The arrows in fig. 2 depict the oil flow in the retarder 6. The oil enters the distributor 13 from the stator part 5 to enter the reducer 6 through various means, which will not be specified in this view, as they are specific to one or more types of architecture. The distributor is divided into two parts, each of which is generally repeated by the same number of planet gears. The injector 13a has a function of lubricating the teeth, and the arm 13b has a function of lubricating the bearings. Oil is supplied to the injectors 13a to come out through the end portions 13c to lubricate the teeth. Oil is also supplied to the arm 13b and flows through the supply port 13d of the bearing. The oil then flows through the shaft into the buffer zone 10c and out through the holes 10d to lubricate the bearings of the planet gears.

FIG. 3 illustrates an embodiment of a retarder 6 incorporating aspects of the present invention.

One of these aspects relates to a lubricant distributor and will be described below with particular reference to fig. 4, 5 and 9. Another aspect of the present invention relates to the deflector, and will be described below with reference to fig. 5 to 8.

The speed reducer 6 includes a carrier 10 of the type having a cage 14 and a cage 15, the cage 14 and the cage 15 being connected by a ball joint.

The cage 14 comprises two radial annular walls 14a, 14b extending around the axis X, these walls 14a, 14b being parallel and being an upstream radial wall 14a and a downstream radial wall 14b, respectively. The walls 14a, 14b are connected to each other at the outer periphery of the walls 14a, 14b by pairs of bridges 14c, 14d, evenly distributed around the axis X. These pairs of bridges provide a structural connection between the walls 14a, 14 b. Each pair of bridges comprises two bridges, respectively a radially outer bridge 14c and a radially inner bridge 14d, which radially outer and inner bridges 14c, 14d extend substantially parallel along the axis X at a radial distance from each other.

Each pair of bridges forms a clevis to receive a finger 15a of a cage 15. In other words, each pair of bridges defines between them a housing for the fingers 15a of the cage 15. An oblong opening 14e is formed in the rear wall 14b so that the finger 15a can pass between the bridges 14c, 14 d. Wall 14a may include a similar opening that is axially aligned with opening 14e of wall 14 b.

The number of fingers 15a is equal to the number of pairs of bridges 14c, 14d, and in the example shown is 5. These fingers 15a project axially upstream from a ring 15b of the cage 15 extending about the axis X. The fingers 15a of the cage 15 engage in the inter-bridge housing by translating axially from the rear through the openings 14e in the wall 14 b.

Each finger 15a comprises, substantially in the middle of the finger, a mounting recess for a bearing (not shown) intended to be traversed by a cylindrical pin 17 carried by each pair of bridges 14c, 14 d. Each pin 17 passes through the interstrance housing and has a substantially radial orientation with respect to the axis X. Each pin 17 comprises a cylindrical body 17a connected at one end (here the radially outer end) to a collar 17 b. The pin 17 is here engaged by radial translation from the outside through a radial hole in the bridge 14c, 14d, the collar 17b of the pin 17 being intended to come into radial contact with the flat face 14ca of the outer bridge 14 c. After the pin 17 has been inserted into the bore of the bridge until the collar 17b is placed on the outer bridge, the collar 17b is fixed to the bridge, for example by a screw connection.

As shown, in the assembled position, the ring 15b of the cage 15 is axially spaced from the downstream wall 14b facing the cage 14 by a predetermined distance L1 (fig. 3).

The cage 14 defines an internal housing for housing a sun gear 7 having an axis X, planet gears 8, the planet gears 8 being arranged around the sun gear 7 and meshing with the sun gear 7, and a deflector 18, the deflector 18 being described in detail below with reference to fig. 5 to 9.

The retarder 6 comprises an improved lubricant distributor 13, which lubricant distributor 13 is clearly shown in fig. 4.

The distributor 13 is substantially annular in shape about the axis X and is made in a single piece. The distributor 13 is attached to the planet carrier 10 and may for this purpose comprise a bracket (not shown) on the cage 14 of the planet carrier.

The distributor 13 comprises an independent oil circuit 20, 21, 23, which oil circuit 20, 21, 23 comprises:

a first oil circuit 20, the first oil circuit 20 comprising a first oil inlet 20a, the first oil inlet 20a being connected by a first annular chamber 20b to a plurality of oil outlets 20C distributed over a first circumference C1 around the axis X,

a second oil circuit 21, the second oil circuit 21 comprising a second oil inlet 21a, the second oil inlet 21a being connected by a second annular chamber 21b to a plurality of oil outlets 21C distributed over a second circumference C2 about the axis X, and

a third independent oil circuit 23, the third independent oil circuit 23 being intended to recover oil from the retarder, the third oil circuit comprising a plurality of oil inlets 23a, the plurality of oil inlets 23a being distributed over a third circumference C6 around the axis X and being connected to at least one oil outlet 23C through a third annular chamber 23 b.

As shown in fig. 4, the inlet 23a and the outlet 20c are preferably formed in a boss 25 of the distributor 13. These bosses 25 are evenly distributed on the same axial side (here the upstream axial side) of the distributor 13 about the axis X.

Circumference C1 has a diameter D1, circumference C2 has a diameter D2, and circumference C6 has a diameter D6.

D2 is greater than D1. D6 is here similar or even identical to D1, but may differ from D1.

In the example shown, D1, D2, and D6 are each larger than D5, which D5 is the inner diameter of ring 15 b. The dispenser 13 is smaller in diameter than D5, which allows assembly/disassembly of the dispenser without touching the rest. Due to the pins 17 and the deflectors 18, the cage 14 and the cage 15 are installed first, then the sun gear 7, the planet gears 8, the axles 10b and finally the distributor 13.

The chambers 20b, 21b, 23b are formed by coaxial and tightly connected tubular rings, i.e. the tubular walls of the chambers are fused together. The chambers have an axial cross-section of any overall shape and the passage cross-section of the chamber is substantially constant over the angular extent of the chamber. In the example shown, the chambers 21b, 23b have a semicircular overall shape in cross section and the chamber 20b has a rectangular overall shape in cross section. We also see that these chambers are arranged in a radially stepped manner, with chamber 21b extending around chamber 20b, which chamber 20b extends around chamber 23b (see fig. 5).

The first chamber 20b extends substantially over a circumference C4 having a diameter D4, the diameter D4 being between D1 and D2. The second chamber 21b extends over another circumference C4 ' having substantially a diameter D4 ', D4 ' ranging between D1 and D2. The third chamber 23b extends substantially over another circumference C4 "having a diameter D4", with a diameter D4 "ranging between D1 and D2. D4 ' is less than D4 ', D4 ' is less than D4. The circumferences C4, C4' and C4 "are centered on the axis X.

As shown in fig. 3 and 5, the chambers 20b, 21b, 23b extend in a plane P2 perpendicular to the axis X, this plane P2 passing between the cage 14 on the one hand and the ring 15b of the cage 15 on the other hand. It can also be seen that the diameter D4 "is greater than the diameter D3' of the section 3b, in order to avoid any risk of contact during operation.

The inlets 20a, 21a and the outlets 23c may be oriented in a radial direction with respect to the axis X. Preferably, the outlet 23c is located at the dial 6 o' clock, analogous to a clock, so that oil flows by gravity from the distributor 13 to the recirculation system.

Preferably, the plane P3 is located between the cage 14 and the ring 15b of the cage 15.

Advantageously, the dispenser 13 is configured to be fluidly connected at the inlet and outlet of the dispenser 13 by male-female plug members (i.e., connectors that merely require axial translation of a male connector to a female connector). Even though the coupling is denoted below as male coupling and is intended to cooperate with a female coupling, the coupling may alternatively be replaced by a female coupling intended to cooperate with a male coupling, or vice versa. The male-female connection may be sealed with an O-ring or the like.

The inlets 20a, 21a and the outlet 23c may each comprise a female connector to receive a male connector of a hose connected to a source of lubricating oil.

For the outlets 20c, as shown in the example, the outlets 20c each include a female connector 20ca for receiving a male connector of one of the deflectors 18. These outlets 20c are here all oriented axially in the same direction towards the front.

With regard to the outlets 21c, in the example shown, the outlets 21c each comprise a female connector for receiving a male connector from one of the lubricating and cooling cores 22.

The function of the core 22 is to lubricate and cool the axles 10b of the planetary gears 8, where the axles 10b are centered and guided by the bearings 11 of the rollers 11 a.

In the example of embodiment shown, each axle 10b is guided by a double-roller bearing 11 (i.e. with a double row of rollers 11 a). Two rows of rollers extend around the same axis: this axis is identical to the axis marked Y of the hub 10b of the planet gear 8.

The outlets 21c are here all oriented axially in the same direction towards the front. The connection of these outlets is connected to the chamber 21b by an approximately L-shaped conduit 21 d.

As far as the inlets 23a are concerned, in the example shown, the inlets 23a each comprise a female connector for receiving a male connector from one of the deflectors 18. These inlets 23a are here all oriented axially in the same direction towards the front.

Finally, as shown in fig. 5, the passage 21d is connected to the ring forming the chamber 21b by a screw thread on the outer periphery of the ring, while the inlet 23a and the outlet 20c are formed directly on the ring forming the chamber.

Fig. 5 to 9 show an embodiment of the deflector 18. As mentioned above, the reducer 6 comprises a plurality of deflectors 18, which deflectors 18 are housed in the cage 14 and are each arranged between two adjacent planet gears 8. The number of deflectors 18 in the reducer 6 is therefore equal to the number of planet gears 8 in the reducer.

The primary function of the deflector 18 is to direct lubricating oil onto the teeth and prevent oil recirculation between the planet gears, and is therefore referred to as an "inter-planet gear deflector". Thus, the deflector 18 is shaped to match the peripheral shape of the planet gear 8.

As shown, each deflector 18 is located between the sun gear 7, which is located radially on the one hand, and a pair of bridges 14c, 14d, which are located radially on the other hand, in addition to extending between two adjacent planet gears 8.

Each deflector 18 comprises a block comprising a first lateral surface 18a, the first lateral surface 18a being cylindrical and concave and having a radius of curvature R1 measured from an axis G1, the axis G1 coinciding with the axis of rotation Y of the planet gears 8 (fig. 8). The block comprises a second lateral surface 18b opposite the first surface 18a, the second lateral surface 18b being cylindrical and concave and having a radius of curvature R1 measured from an axis G2 parallel to G1, the axis G2 coinciding with the axis of rotation Y of the other planet gear 8.

The block of each deflector 18 further comprises an upstream flat face 18c, which is substantially radial when the deflector is mounted in the cage 14 of the reducer, and a downstream flat face 18d, which is also substantially radial 18 d. The block further comprises a radially outward flat face 18e intended to be oriented on the side of the pair of bridges 14c, 14d and a radially inward face 18f intended to be oriented on the side of the sun gear 7. This face 18f is cylindrical and concave and has a radius of curvature R3 measured from the axis: which coincides with the axis X of the sun gear. Therefore, the surface 18f has a function of guiding the lubricating oil of the teeth of the sun gear.

The deflector 18 extends between the radial walls 14a, 14b of the cage 14 and has faces 18c, 18d, which faces 18c, 18d are supported on an inner face opposite these walls 14a, 14 b. The deflector 18 is fixed to the cage 14, for example by screws.

Each deflector 18 has two independent integrated oil circuits 35, 36, the oil circuits 35, 36 comprising:

a first lubricating oil circuit 36, which first lubricating oil circuit 36 comprises at least one oil inlet port 36a and at least one oil outlet hole 36b or port, for lubricating the retarder,

a second oil recovery circuit 35, the second oil recovery circuit 35 being independent of the first circuit 36, and the second oil recovery circuit 35 comprising at least one oil inlet hole 35a and at least one oil outlet port 35b for oil recirculation.

The first circuit 36 includes an oil inlet 36a connected to at least one oil outlet hole 36b by drilling. In the example shown, the oil inlet 36a is located on the downstream side 18d and comprises a pipe designed to form a male connector and to cooperate with the outlet 20c of the distributor 13 described above by means of a male-female plug. Although the connector is shown below as a male connector and is intended to mate with a female connector, the connector may alternatively be replaced by a female connector intended to mate with a male connector, and vice versa (fig. 3). Here, the hole 36b is positioned close to the face 18f of the deflector and is oriented towards the teeth of at least the planet gears 8 and the sun gear 7.

Each deflector 18 may include at least one oil outlet port 36c forming, for example, a female connector for receiving a sealed fluid coupling sleeve 37 (fig. 3 and 5). Like the inlet 36a, the sleeve 37 may be removed and replaced with a male connector. Here, the ports 36c are located on the radially outer face 18e of each deflector. Fig. 3 shows that half of the sleeve 37 engages by means of male-female plugs into the port 36c and the other half engages by means of male-female plugs into female holes located on the radially inner ends of the main body 17a of the pin 17 carried by the pair of bridge pieces 14c, 14 d.

The second circuit 35 comprises an oil inlet hole 35a, which oil inlet hole 35a is located on the faces 18a, 18b in the example shown. Thus, during operation, the oil flowing on these faces 18a, 18b is recovered for recirculation, which avoids the oil from projecting again on the adjacent planet gears 8.

The second circuit 35 also comprises an oil outlet port 35b located on the downstream face 18d and a tube designed to form a male connector and to cooperate with the inlet 23a of the distributor 13 described above by means of a male-female plug. Even though the connector is denoted as male connector below and is intended to mate with a female connector, the connector may alternatively be replaced by a female connector intended to mate with a male connector, or vice versa.

As can be seen from the figure, the oil inlet port 36a of the first circuit 36 and the oil outlet port 35b of the second circuit 35 are positioned close to each other and on the same face 18d of the block of the deflector 18. Here, the ports 36a, 35b are positioned close to the side 18f of the deflector and are oriented in a substantially parallel direction.

Fig. 8 shows the direction of rotation of the sun gear 7 (arrow F1) and of the planet gears 8 (arrow F2), the orientation of the oil projection from the holes 36b of the first circuit 36 of the deflector 18 (arrow F3), and the oil flow after lubrication and recovery of this oil in the second circuit 35 of the deflector 18 (arrow F4). Fig. 8 and 9 show that the circuit 35 is preferably configured to take advantage of the direction of the centrifugal oil around the planet gears to save energy of the oil during oil recovery.

Thus, during operation it can be understood that lubricating oil is first supplied by the distributor 13 to a portion of the core 22 and to the axles 10b of the planet gears 8 for lubricating the bearings 11, and to the first circuit 36 of the deflector 18 for lubricating the teeth of the sun gear 7 and of the planet gears 8. The lubricating oil from the reducer 6 is projected onto the faces 18a, 18b of the deflector 18 and flows into the second circuit 35 of the deflector through the hole 35 a. The oil is delivered to port 35b where it is discharged through distributor 13 for recirculation.

The aim here is to collect and drain the oil as quickly as possible after the oil has been used in the gear.

For a planetary-type reduction gear, the object of the invention is to provide an oil distributor which supplies oil to the teeth of the planet gears and the bearings of the planet gears and also enables oil to be recovered for efficient emptying of the oil.

For this purpose, the distributor comprises an oil feed circuit separate from the oil discharge circuit.

It will be appreciated that this enables more efficient drainage of oil than prior art architectures, where oil is recovered after flowing through the crankcase and transitioning to a low point (6 o' clock).