ASSEMBLY FOR AN AIRCRAFT TURBOMACHINE COMPRISING A REDUCER AND A REDUCER LUBRICATION SYSTEM

Abstract

Assembly for an aircraft turbomachine comprising: - a reducer (17) comprising a planet carrier (19) movable around an axis (X); - a lubrication system (30) comprising an impeller (31) secured to the planet carrier (19), the impeller (31) comprising an annular gutter (32) open towards the axis (X), the gutter (32) comprising an oil housing (33) delimited axially by first and second axial end walls (34, 35), the first axial end wall (34) being arranged opposite the reducer (17), characterized in that the second axial end wall (35) has, with respect to the axis (X), an internal diameter which is greater than the internal diameter of the first axial end wall (34), so that the oil can overflow from the gutter (32) beyond the radially internal free end of the second axial end wall (35) so as to prevent excess oil from flowing towards the reducer (17).Figure for abstract: Figure 2.

Description

Title of the invention: ASSEMBLY FOR AN AIRCRAFT TURBOMACHINE COMPRISING A REDUCER AND A REDUCER LUBRICATION SYSTEM Technical field of the invention

[0001] The present invention relates to an assembly for an aircraft turbomachine comprising a reducer and a lubrication system for the reducer, and to an aircraft turbomachine comprising such an assembly. Technical background

[0002] A dual-flow turbomachine conventionally comprises a fan and a gas generator which comprises at least one compressor, a combustion chamber and at least one turbine. The fan generates an air flow which is divided into a primary flow intended to supply the gas generator and into a secondary flow which contributes predominantly to the thrust provided by the turbomachine.

[0003] In the case of a turbomachine with a reduction gear, the fan shaft is driven by a turbine shaft via a speed reducer. The reduction gear makes it possible to reduce the rotational speed of the fan shaft relative to that of the turbine shaft. The reduction gear is conventionally placed in an enclosure (commonly called an “oil enclosure”).

[0004] Such a reducer conventionally comprises at least one sun gear, a crown gear, satellites and a planet carrier. Depending on the requirements, the reducer can be configured in different ways.

[0005] In the remainder of the application, we will be more particularly interested in the configurations in which the planet carrier is mobile, namely in particular the configuration commonly called “epicyclic” and the configuration commonly called “differential”.

[0006] More precisely, an epicyclic reducer has a sun gear secured to the turbine shaft, a planet carrier secured to the fan shaft and a fixed crown. Unlike the epicyclic reducer, the differential reducer has a mobile crown.

[0007] The bearings and teeth of the toothed wheels of such reducers are abundantly lubricated with oil via a lubrication system, in particular to minimize the wear of the contact surfaces of these different parts, and thus maximize the efficiency and service life of the reducer.

[0008] Document FR3041054A1 in the name of the applicant discloses a lubrication system comprising in particular a wheel (also called a distributor centrifugal) secured to the mobile planet carrier and the injectors secured to the fixed structure of the turbomachine.

[0009] More specifically, the impeller comprises an oil receiving and distribution gutter which is not only intended to receive the oil delivered by the injectors but also to distribute it to different circuits which are configured to convey the oil to the parts to be lubricated of the reducer.

[0010] The oil received by the gutter is rotated under the action of centrifugal force, then conveyed into the circuit(s) associated with it under the action of centrifugal pressure.

[0011] Engine manufacturers note that such a wheel can be improved.

[0012] Indeed, engine manufacturers note that an excess (or surplus) of oil regularly overflows from the gutter, the gutter in these cases no longer being able to distribute all of the oil received to the different circuits.

[0013] Oil overflows are in themselves inevitable because on the one hand engine manufacturers seek to maximize the quantity of oil distributed to the circuits, but on the other hand it is not possible to determine with precision the maximum distribution capacities of the gutter for all operating speeds / conditions, these capacities depending on too many parameters (oil viscosity, rotation speed of the impeller, etc.).

[0014] However, it is essential to control this oil overflow in order to prevent this excess oil from spilling into the reducer.

[0015] Indeed, an oil spill in the reducer generates additional power losses caused in particular by the transfer of movement, shearing and mixing of this excess oil.

[0016] Such additional power losses obviously lead to a direct reduction in propulsion efficiency as well as an increase in the mass of the equipment (heat exchanger(s), pump(s), etc.) of the thermal management system which is notably used to cool the oil.

[0017] The objective of the present invention is therefore to provide a simple, effective and economical solution making it possible to respond to the aforementioned problem. Summary of the invention

[0018] The invention thus proposes an assembly for an aircraft turbomachine comprising: - a reducer comprising a planet carrier movable around an X axis; - a lubrication system for the reducer comprising a wheel integral in rotation with the planet carrier, the wheel comprising an annular gutter around the X axis and open towards the X axis, the gutter comprising an annular oil housing delimited axially by a first axial end wall and by a second axial end wall, the first axial end wall being arranged opposite the reducer, characterized in that the second axial end wall has, with respect to the axis X, an internal diameter D2 which is greater than the internal diameter DI of the first axial end wall, so that the oil can overflow from the gutter beyond the radially internal free end of the second axial end wall so as to prevent excess oil from flowing towards the reducer.

[0019] Such sizing of the axial end walls of the gutter makes it possible to control oil overflow.

[0020] In fact, the oil is now forced to overflow from the gutter via the second axial end wall (and more precisely beyond its radially internal free end) to directly reach the enclosure before being evacuated there, which makes it possible to prevent excess oil from spilling into the reducer.

[0021] Such control of excess oil makes it possible to limit power losses, and consequently to improve the propulsive efficiency and the mass of the equipment (heat exchanger(s), pump(s), etc.) of the thermal management system.

[0022] The assembly according to the invention may comprise one or more of the following characteristics and / or steps, taken in isolation from one another or in combination with one another: - the inner diameter D2 of the second axial end wall is, with respect to the X axis, at least 3 mm larger than the inner diameter DI of the first axial end wall; - the annular oil housing comprises a single annular oil zone around the X axis, this single annular oil zone preferably being compartmentalized around the X axis; - the gutter comprises a partition wall which extends radially with respect to the X axis, the partition wall being arranged axially between the first axial end wall and the second axial end wall, the partition wall dividing the annular oil housing into a first and a second annular oil zone around the X axis, the first annular oil zone being axially delimited by the first axial end wall and the partition wall, and the second annular oil zone being axially delimited by the second axial end wall and the partition wall; - the dividing wall has an internal diameter D3 which is greater than the respective internal diameters D1, D2 of the first and second axial end walls; - the oil annular zones are both configured to receive the oil supplied by at least one fixed injector of the lubrication system and distribute the received oil to at least one lubrication circuit of the reducer; - the second annular oil zone is the only one of the two annular oil zones which is configured to receive the oil supplied by at least one fixed injector of the lubrication system, the first annular oil zone being supplied with oil by overflow of the second annular oil zone beyond the radially internal end of the separating wall, the second annular oil zone being the only one of the two annular oil zones which is configured to distribute the received oil to at least one lubrication circuit of the reducer; - the first annular oil zone and / or the second annular oil zone is compartmentalized around the X axis; - each lubrication circuit of the reducer is supplied by a discharge orifice of the gutter which extends radially outwards, each discharge orifice being preferably formed in a bottom wall of the gutter.

[0023] The present invention also relates to an aircraft turbomachine comprising an assembly as described previously. Brief description of the figures

[0024] The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:

[0025] [Fig-1] [Fig.l] is a schematic view in axial half-section of a turbomachine with reducer according to the invention;

[0026] [Fig.2] [Fig.2] is a detail view of [Fig.l] which illustrates the reducer and its lubrication system;

[0027] [Fig.3] [Fig.3] is a detailed and cutaway view of the reducer and its system lubrication as illustrated in [Fig.2];

[0028] [Fig.4] [Fig.4] is a detailed and half-sectional axial view of the wheel of the system lubrication as shown in Figures 2 and 3;

[0029] [Fig.5] [Fig.5] is a view similar to [Fig.4] which illustrates a first variant of making the spinning wheel;

[0030] [Fig.6] [Fig.6] is a view similar to Figures 4 and 5 which illustrates a second variant of the spinning wheel. Detailed description of the invention

[0031] In [Fig.l] a turbomachine 1 of an aircraft 2 is partially represented. The aircraft 2 is for example an airplane.

[0032] By convention in the present application, the terms “upstream” and “downstream” are defined in relation to the direction of circulation of the gases in the turbomachine 1, when the turbomachine 1 operates in “propulsor” mode.

[0033] As illustrated in [Fig.l], the turbomachine 1 conventionally comprises from upstream to downstream, a ducted fan 3, a low pressure compressor 4, a high pressure compressor 5, an annular combustion chamber 6, a high pressure turbine 7, a low pressure turbine 8 and an exhaust nozzle 9.

[0034] The high-pressure compressor 5 and the high-pressure turbine 7 are connected to each other by a high-pressure shaft 11 and form with it a high-pressure (HP) body. The low-pressure compressor 4 and the low-pressure turbine 8 are connected to each other by a low-pressure shaft 12 and form with it a low-pressure (LP) body.

[0035] As illustrated in [Fig.l], the air flow generated by the fan 3 is divided, by a fixed structure 13 of the turbomachine 1, into a primary flow which enters a primary vein 14 to supply the low pressure compressor 4, and into a secondary flow which flows in a secondary vein 15 around the gas generator, to provide the majority of the thrust.

[0036] As illustrated in [Fig.l], the blower 3 is driven in rotation by a blower shaft 16 which is itself driven in rotation by the low pressure shaft 12 by means of a speed reducer 17.

[0037] The turbomachine 1 extends around a longitudinal axis X which corresponds in particular to the axis of rotation of the fan shaft 16, of the high pressure shaft 11 and of the low pressure shaft 12.

[0038] As indicated above, the reducer 17 is here of the “epicyclic” or “differential” type, and hereinafter called reducer 17. The reducer 17 makes it possible to reduce the rotation speed of the fan shaft 16 relative to that of the low pressure shaft 12.

[0039] As illustrated in Figures 2 and 3, the reducer 17 comprises a central sun gear 18 secured to the low pressure shaft 12 and a planet carrier 19 secured to the fan shaft 16, the sun gear 18 and the planet carrier 19 being movable around the axis X. The reducer 17 also comprises a fixed ring gear 20 (for an “epicyclic” type reducer) or a movable ring gear 20 (for a “differential” type reducer). The planet carrier 19 carries several planet gears 21 distributed around the axis X, each planet gear 21 being meshed with both the sun gear 18 and the ring gear 20.

[0040] As illustrated in [Fig.l], the reducer 17 is housed and lubricated in an annular enclosure 22 around the axis X, the enclosure 22 being positioned in the upstream part of the turbomachine 1. The enclosure 22 is here formed by an upstream shell 23 and a downstream shell 24 of the fixed structure 13. The enclosure 22 is here closed upstream by seals at the level of a bearing allowing the fan shaft 16 to pass through, and downstream by seals at the level of the passage of the low pressure shaft 12.

[0041] As illustrated in Figures 2 and 3, the low pressure shaft 12 is rotatably connected with the solar 18 via splines 25. The fan shaft 16 is linked in rotation with the planet carrier 19 via a series of fingers 26 distributed around the axis X. Each satellite 21 is carried by an axis 27 which is integral with the planet carrier 19 and which is guided in rotation by a bearing 28 arranged between the axis 27 and the satellite 21. The bearing 28 is for example a plain bearing, a rolling bearing or even a hydrodynamic bearing. The crown 20 comprises two half-crowns 20a, 20b flanged to each other. The reducer 17 is here single-stage but it could be double-stage. The different toothed wheels of the reducer 17 here have a herringbone toothing 29 but they could have for example a straight toothing or a helical toothing.

[0042] The reducer 17 is lubricated via a lubrication system 30.

[0043] The lubrication system 30 comprises an impeller 31 integral in rotation with the planet carrier 19 of the reducer 17. The impeller 31 comprises an annular gutter 32 around the axis X and open towards the axis X. The gutter 32 comprises an annular oil housing 33 delimited axially by a first axial end wall 34 and by a second axial end wall 35, the first axial end wall 34 being arranged opposite (or on the side) of the reducer 17.

[0044] According to the invention, the second axial end wall 35 has, with respect to the axis X, an internal diameter D2 which is greater than the internal diameter DI of the first axial end wall 34, so that the oil can overflow from the gutter 32 beyond the radially internal free end 50 of the second axial end wall 35 so as to prevent the excess oil from flowing towards the reducer 17.

[0045] Such a dimensioning of the axial end walls 34, 35 of the gutter 32 makes it possible to control the overflow of oil.

[0046] In fact, the oil is now forced to overflow from the gutter 32 via the second axial end wall 35 (and more precisely beyond its radially internal free end 50) to directly reach the enclosure 22 before being evacuated there, which makes it possible to prevent the excess oil from flowing towards the reducer 17.

[0047] Such control of excess oil makes it possible to limit power losses, and consequently to improve the propulsive efficiency and the mass of the equipment (heat exchanger(s), pump(s), etc.) of the thermal management system.

[0048] The wheel 31 extends around the axis X which corresponds in particular to its axis of rotation.

[0049] By convention in the present application, the diameters D1-D3 (or radial dimensions) explained in this application have as reference the axis X of the impeller 31.

[0050] Furthermore, by convention in the present application, “axial” or “axially” means any direction parallel to the axis X of the turbomachine 1 or the impeller 31, “radial” or “radially” means any direction perpendicular to the axis X of the tur- turbomachine 1 or impeller 31, and by “tangent” or “tangentially” any direction relative to the circumference of the turbomachine 1 or impeller 31 (as opposed to the axial and radial directions explained above).

[0051] By definition in the present application, the first axial end wall 34 and the second axial end wall 35 of the gutter 32 are located relative to each other opposite the gutter 32. The axial end walls 34, 35 axially delimit the gutter 32 on either side.

[0052] Advantageously, the lubrication system 30 comprises several fixed injectors 36 distributed around the axis X, each injector 36 comprising a nozzle 37 which injects oil in the form of a jet towards the gutter 32.

[0053] Advantageously, the internal diameter D2 of the second axial end wall 35 is, with respect to the axis X, at least 3 mm larger than the internal diameter DI of the first axial end wall 34.

[0054] Such a dimensioning of the second axial end wall 35 ensures that the oil overflows from the gutter 32 via the second axial end wall 35 into the enclosure 22 (and not via the first axial end wall 34 into the reducer 17).

[0055] The annular oil housing 33 of the gutter 32 may comprise a single annular oil zone 38 around the axis X, this single annular oil zone 38 being compartmentalized or not compartmentalized around the axis X.

[0056] Such a zone 38 is thus configured to receive the oil supplied by the fixed injector(s) 36 of the lubrication system 30 and distribute the received oil to different lubrication circuits 39a, 39b of the reducer 17.

[0057] Advantageously, the single annular oil zone 38 is compartmentalized.

[0058] The gutter 32 may comprise a separation wall 41 (or partition) which extends radially with respect to the axis X. The partition wall 41 is arranged axially between the first axial end wall 34 and the second axial end wall 35, the partition wall 41 dividing the annular oil housing 33 into first and second annular oil zones 42a-42b, 43a-43b around the axis X. The first annular oil zone 42a, 43a is then delimited axially by the first axial end wall 34 and the partition wall 41, and the second annular oil zone 42b, 43b, is in turn delimited axially by the second axial end wall 35 and the partition wall 4L

[0059] The annular oil zones 42a, 42b may both be configured to receive the oil supplied by the fixed injector(s) 36 of the lubrication system 30 and distribute the received oil to different lubrication circuits 40a, 40b of the reducer 17. In other words, each of the two zones 42a, 42b of the housing 33 is commonly called a “reception and distribution zone”.

[0060] Advantageously, the separation wall 41 has an internal diameter D3 which is greater than the respective inner diameters D1, D2 of the first and second axial end walls 34, 35.

[0061] Such a dimensioning of the separation wall 41 allows the overflow from one zone to another, before the overflow outside the gutter 32 via the second axial end wall 35.

[0062] Alternatively, the second annular oil zone 43b may be the only one of the two annular oil zones 43a, 43b that is configured to receive the oil supplied by the fixed injector(s) 36 of the lubrication system 30. The first annular oil zone 43a is then supplied with oil by overflow of the second annular oil zone 43b beyond the radially inner end 51 of the separating wall 41, and the second annular oil zone 43b is the only one of the two annular oil zones 43a, 43b that is configured to distribute the received oil to different lubrication circuits 39a, 39b of the reducer 17. In other words, the first zone 43a is then commonly called the “distribution zone”, and the second zone 43b the “reception zone”.

[0063] The supply of the distribution zone 43a is here obtained by the overflow of the reception zone 43b, which offers advantages.

[0064] Indeed, such a supply is not subject to splashing, which makes it possible to maximize the oil level in the distribution zone 43a, and consequently to maximize the quantity of oil conveyed to the elements to be lubricated of the reducer 17, to the benefit in particular of the efficiency and the service life of the reducer 17.

[0065] Furthermore, such a supply is continuous, which makes it possible to have a centrifugal pressure of the oil which is constant over time, as is the flow rate in each of the circuits 39a, 39b and the lubrication of the elements to be lubricated, to the benefit in particular of the efficiency and the service life of the reducer 17.

[0066] Advantageously, the separation wall 41 has an internal diameter D3 which is greater than the respective internal diameters D1, D2 of the first and second axial end walls 34, 35.

[0067] Such a dimensioning of the separation wall 41 makes it possible to supply the distribution zone 43a by overflowing from the reception zone 43b.

[0068] Depending on the requirements, the first annular oil zone 42a, 43a may be compartmentalized or not compartmentalized around the X axis.

[0069] Similarly, the second annular oil zone 42b, 43b may be compartmentalized or not compartmentalized around the X axis.

[0070] Advantageously, the lubrication system 30 comprises several lubrication circuits 39a-39b, 40a-40b of the reducer 17, each circuit 39a-39b, 40a-40b being configured to convey the received oil to one or more elements to be lubricated of the reducer 17.

[0071] A circuit 39a-39b, 40a-40b may comprise a pipe provided with one or more nozzles which open at the level of the different elements to be lubricated (bearings 28, teeth 29 at the level of the meshing zones, etc.) of the reducer 17, the pipe being supplied by the or one of the annular oil zones 38, 42a-42b, 43a of the gutter 32.

[0072] Advantageously, each lubrication circuit 39a, 39b, 40a, 40b of the reducer 17 is supplied by an evacuation orifice 49 of the gutter 32 which extends radially outwards. Each evacuation orifice 49 is preferably formed in a bottom wall 46, 46a, 46b of the gutter 32.

[0073] In [Fig.2], the path of the oil is symbolized by arrows. On the Figures 4 to 6, the arrow symbolizes the overflow of oil beyond the gutter 32.

[0074] As illustrated in [Fig. 2], the lubrication system 30 here comprises several fixed injectors 36. The injectors 36 are supplied with oil by means of one or more pumps connected to an oil reservoir of the turbomachine 1. One or more lines 44 make it possible to convey the oil under pressure from the pump to an injector 36, the line or lines 44 here being associated with a buffer tank 45. Each injector 36 comprises a nozzle 37 which injects oil in the form of a jet towards the gutter 32.

[0075] As illustrated in the figures, the gutter 32 is located here axially downstream of the reducer 17, the first axial end wall 34 being arranged opposite (or on the side) of the reducer 17. The first axial end wall 34 is thus located in the immediate vicinity of the reducer 17.

[0076] As illustrated in Figures 2 to 4, the housing 33 of the gutter 32 here comprises a single annular oil zone 38 which is delimited axially by the axial end walls 34, 35, and radially by a bottom wall 46. The axial end walls 34, 35 each have a straight and radial profile in cross section while the bottom wall 46 has a straight and axial profile in cross section.

[0077] The annular oil zone 38 is here compartmentalized around the axis X, and in other words the annular zone 38 comprises several compartments 47a, 47b arranged next to each other around the axis X. The compartments 47a, 47b are defined tangentially by means of transverse walls 48, each wall 48 connecting together the axial end walls 34, 35 and the bottom wall 46.

[0078] More precisely, the annular oil zone 38 here comprises first compartments 47a which each extend tangentially over a first angular range and second compartments 47b which each extend tangentially over a second angular range, the first compartments 47a being interposed between the second compartments 47b.

[0079] The first compartments 47a are each connected to a first circuit 39a which is configured to convey the oil to the bearing 28 of a satellite 21. The second compartments 47b are each connected to a second circuit 39b which is configured to convey the oil to the teeth 29 of the toothed wheels (in particular at the meshing zones).

[0080] The discharge orifices 49 which supply the different circuits 39a, 39b are here formed in the bottom wall 46 of the gutter 32.

[0081] As illustrated in [Fig.4], the oil overflows from the gutter 32, from upstream to downstream, via the second axial end wall 35 (and more precisely beyond its radially internal free end 50), to directly reach the enclosure 22 before being evacuated there. The jet from each of the injectors 36 is here oriented towards the single annular zone 38 of the gutter 32 (see [Fig.2]).

[0082] According to the first variant embodiment illustrated in [Fig. 5], the housing 33 of the gutter 32 here comprises first and second annular receiving and distribution zones 42a, 42b, these annular zones 42a, 42b being axially attached to one another and separated from one another by the separation wall 4L.

[0083] More specifically, the first zone 42a is delimited axially by the first axial end wall 34 and the separation wall 41, and radially by a first bottom wall 46a. The second zone 42b is delimited axially by the second axial end wall 35 and the separation wall 41, and radially by a second bottom wall 46b. The axial end walls 34, 35 and the separation wall 41 each have a straight and radial profile in cross section while the bottom walls 46a, 46b each have a straight and axial profile in cross section.

[0084] The annular zones 42a, 42b are here not compartmentalized around the axis X, and in other words each annular zone 42a, 42b extends continuously around the axis X.

[0085] The first zone 42a is connected to first circuits 40a and the second zone 42b is connected to second circuits 40b.

[0086] The discharge orifices 49 which supply the different circuits 40a, 40b are here formed in the bottom walls 46a, 46b of the gutter 32.

[0087] As illustrated in [Fig.5], the oil overflows from the gutter 32, from upstream to downstream, via the second axial end wall 35 (and more precisely beyond its radially internal free end 50), to directly reach the enclosure 22 before being evacuated there. The jet from each of the injectors 36 is here oriented towards the two annular zones 42a, 42b of the gutter 32.

[0088] According to the second embodiment illustrated in [Fig.6], the housing 33 of the gutter 32 here comprises a first annular distribution zone 43a and a second annular reception zone 43b, these annular zones 43a, 43b being axially attached to each other and separated from each other by the dividing wall 41.

[0089] More specifically, the first zone 43a is delimited axially by the first axial end wall 34 and the separation wall 41, and radially by a first bottom wall 46a. The second zone 43b is delimited axially by the second axial end wall 35 and the separation wall 41, and radially by a second bottom wall 46b. The axial end walls 34, 35 and the separation wall 41 each have a straight and radial profile in cross section while the bottom walls 46a, 46b each have a straight and axial profile in cross section.

[0090] The first annular zone 43a is here compartmentalized around the axis X, and in other words the first annular zone 43a comprises several compartments 47a, 47b arranged next to each other around the axis X. The compartments 47a, 47b are defined tangentially by means of transverse walls 48, each wall 48 connecting together the first axial end wall 34, the separation wall 41 and the first bottom wall 46a.

[0091] More precisely, the first annular zone 43a comprises first compartments 47a which each extend tangentially over a first angular range and second compartments 47b which each extend tangentially over a second angular range, the first compartments 47a being interposed between the second compartments 47b.

[0092] The first compartments 47a are each connected to a first circuit 39a which is configured to convey the oil to the bearing 28 of a satellite 21. The second compartments 47b are each connected to a second circuit 39b which is configured to convey the oil to the teeth 29 of the toothed wheels (in particular at the meshing zones).

[0093] The second annular zone 43b is here not compartmentalized around the axis X, and in other words the second annular zone 43b extends continuously around the axis X.

[0094] The discharge orifices 49 which supply the different circuits 39a, 39b are here formed in the bottom wall 46a of the gutter 32.

[0095] As illustrated in [Fig.6], the oil overflows from the gutter 32, from upstream to downstream, via the second axial end wall 35 (and more precisely beyond its radially internal free end 50), to directly reach the enclosure 22 before being evacuated there. The jet from each of the injectors 36 is here oriented only in the direction of the second annular zone 43b (receiving zone) of the gutter 32. The first annular zone 43a is here supplied with oil by overflow from the second annular zone 43b beyond the radially internal end 51 of the separating wall 4L

Claims

Claims

1. Assembly for a turbomachine (1) of an aircraft (2) comprising: - a reducer (17) comprising a planet carrier (19) movable around an axis (X);- a lubrication system (30) of the reducer (17) comprising an impeller (31) integral in rotation with the planet carrier (19), the impeller (31) comprising an annular gutter (32) around the axis (X) which is open towards the axis (X), the gutter (32) comprising an annular oil housing (33) delimited axially by a first axial end wall (34) and by a second axial end wall (35), the first axial end wall (34) being arranged opposite the reducer (17), characterized in that the second axial end wall (35) has, with respect to the axis (X), an internal diameter (D2) which is greater than the internal diameter (D1) of the first axial end wall (34), so that the oil can overflow from the gutter (32) beyond the radially free end internal (50) of the second axial end wall (35) so as to prevent excess oil from flowing towards the reducer (17).;

2. Assembly according to claim 1, characterized in that the inner diameter (D2) of the second axial end wall (35) is, with respect to the axis (X), at least 3 mm larger than the inner diameter (D1) of the first axial end wall (34).

3. Assembly according to one of the preceding claims, characterized in that the annular oil housing (33) comprises a single annular oil zone around the axis (X), this single annular oil zone preferably being compartmentalized around the axis (X).

4. An assembly according to one of claims 1 or 2, characterized in that the gutter (32) comprises a separating wall (41) which extends radially with respect to the axis (X), the separating wall (41) being arranged axially between the first axial end wall (34) and the second axial end wall (35), the separating wall (41) dividing the annular oil housing (33) into a first and a second annular oil zone (42a-42b, 43a-43b) around the axis (X), the first annular oil zone (42a, 43a) being delimited axially by the first axial end wall (34) and the separating wall (41), and the second annular oil zone (42b, 43b) being delimited axially by the second axial end wall (35) and the se- wall preparation (41).

5. Assembly according to the preceding claim, characterized in that the separating wall (41) has an internal diameter (D3) which is greater than the respective internal diameters (D1, D2) of the first and second axial end walls (34, 35).

6. Assembly according to one of claims 4 or 5, characterized in that the annular oil zones (42a, 42b) are both configured to receive the oil supplied by at least one fixed injector (36) of the lubrication system (30) and distribute the received oil to at least one lubrication circuit (40a, 40b) of the reducer (17).

7. Assembly according to one of claims 4 or 5, characterized in that the second annular oil zone (43b) is the only one of the two annular oil zones (43a, 43b) which is configured to receive the oil supplied by at least one fixed injector (36) of the lubrication system (30), the first annular oil zone (43a) being supplied with oil by overflow of the second annular oil zone (43b) beyond the radially internal end (51) of the separating wall (41), the second annular oil zone (43b) being the only one of the two annular oil zones (43a, 43b) which is configured to distribute the received oil to at least one lubrication circuit (39a, 39b) of the reducer (17).

8. Assembly according to one of claims 4 to 7, characterized in that the first annular oil zone (42a, 43a) and / or the second annular oil zone (42b, 43b) is compartmentalized around the axis (X).

9. Assembly according to one of claims 6 or 7, characterized in that each lubrication circuit (39a, 39b, 40a, 40b) of the reducer (17) is supplied by an evacuation orifice (49) of the gutter (32) which extends radially outwards, each evacuation orifice (49) preferably being formed in a bottom wall (46, 46a, 46b) of the gutter (32).

10. Turbomachine (1) of aircraft (2) comprising an assembly according to one of the preceding claims.

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