Aircraft turbine engine assembly comprising a reduction gear and an input shaft

Abstract

The invention relates to an aircraft turbine engine assembly comprising: - a reduction gear housed in an enclosure, which includes a sun gear (5) comprising internal splines (6); - an input shaft (7) comprising external splines (8) which are rotationally connected to the internal splines (6) of the sun gear (5); characterised in that the internal and external splines (6, 8) are lubricated by immersion in an oil bath (9) which is formed at the internal periphery of the sun gear (5), the turbine engine assembly comprising a centrifugal oil separator (10) for an air / oil mixture coming from the enclosure, the oil separator (10) comprising a first outlet (11) through which the oil separated from the air / oil mixture is discharged due to the centrifugal force, the first outlet (11) being configured so that the oil separated from the air / oil mixture supplies the oil bath (9), the oil separator (10) comprising a ventilation device (12) configured to generate a flow of air / oil mixture (F) that supplies the oil separator (10).

Description

[0001] DESCRIPTION

[0002] AERON EF TU RBOMACHI NE ASSEMBLY COMPRISING A REDUCER R AND AN INPUT SHAFT

[0003] Technical field of the invention

[0004] The present invention relates to an aircraft turbomachine assembly comprising a reduction gear and an input shaft.

[0005] Technical background

[0006] A dual-flow turbomachine typically comprises a fan and a gas generator which includes at least one compressor, a combustion chamber and at least one turbine. The fan generates an airflow which is divided into a primary flow intended to supply the gas generator and a secondary flow which contributes predominantly to the thrust provided by the turbomachine.

[0007] In the case of a geared turbomachine, the fan is rotated by an input shaft via a speed reducer, the input shaft being driven by the rotor of a turbine. The reducer reduces the rotational speed of the fan relative to that of the input shaft. The reducer is conventionally placed in an enclosure (commonly called an "oil enclosure").

[0008] Such a gearbox typically includes at least one sun gear, one crown gear, two planet gears, and one planet carrier. Depending on requirements, the gearbox can be configured in various ways.

[0009] Regardless of the gearbox configuration, the gearbox sun gear is rotationally connected to the input shaft.

[0010] The sun gear can be rotationally connected to the input shaft via a splined connection. Specifically, the sun gear includes internal splines that are rotationally connected to external splines of the input shaft.

[0011] Like the bearings and the teeth of the gear wheels, the splined connection is lubricated with oil by a lubrication system which is associated with the gear, in particular to improve the contact between the splines and / or the evacuation of the heat produced by the contacts.

[0012] Traditionally, the splined joint is lubricated through a nozzle whose oil jet is directed towards the splined joint.

[0013] However, the integration of such a nozzle is not always obvious, and can prove difficult or even impossible, due in particular to the compactness of the reducer, but also to the small diameter of the grooved connection.

[0014] Engine manufacturers further note that it might be advantageous to use the air / oil mixture (also called air / oil mist) present in the enclosure to lubricate the splined connection.

[0015] The objective of the present invention is therefore to provide a simple, effective and economical solution to address the aforementioned problem.

[0016] Summary of the invention

[0017] The invention thus proposes an aircraft turbomachine assembly comprising:

[0018] - a reducer housed in an enclosure which includes a solar movable around an X axis, the solar comprising internal grooves;

[0019] - an input shaft movable about the X axis, the input shaft comprising external splines which are rotationally linked with the internal splines of the solar; characterized in that the internal and external splines are lubricated by immersion in an oil bath which is formed at the internal periphery of the solar, the turbomachine assembly comprising a centrifugal oil separator of an air / oil mixture coming from the enclosure, the oil separator comprising a first outlet through which the oil separated from the air / oil mixture is evacuated under the action of centrifugal force, the first outlet being configured so that the oil separated from the air / oil mixture feeds the oil bath, the oil separator comprising a ventilation device configured to generate a flow of air / oil mixture which feeds the oil separator.Such lubrication of the splined connection is independent, and in other words it is dissociated from the classic lubrication system which uses nozzles to lubricate elements (bearings, gear teeth) of the reducer.

[0020] In fact, the grooves are now lubricated by immersion in an oil bath which is supplied by a centrifugal oil separator.

[0021] Such independence means that you are no longer constrained by the problems of integrating a sprinkler.

[0022] In addition, such lubrication advantageously makes it possible to exploit the air / oil mixture available in the enclosure, to supply the oil bath via the oil separator.

[0023] The turbomachine assembly according to the invention may comprise one or more of the following features and / or steps, taken in isolation from one another or in combination with one another:

[0024] - the oil separator is integral with the input shaft;

[0025] - the oil separator is housed at least partly in an upstream end of the input shaft;

[0026] - the oil bath is delimited axially by an upstream element, the first outlet of the oil separator being arranged axially between the upstream element and an upstream end of the external splines of the input shaft;

[0027] - the oil separator comprises an annular chamber for de-oiling the air / oil mixture, the first outlet communicating with an external end of the chamber, the chamber being at least axially delimited by a first wall and a second wall facing each other, the first and second walls converging towards the first outlet of the oil separator, so as to concentrate the oil separated from the air / oil mixture towards the first outlet under the action of centrifugal force;

[0028] - the oil separator comprises an annular chamber for de-oiling the air / oil mixture, the first outlet communicating with an external end of the chamber, the chamber being at least axially delimited by a curved wall which has in axial half-section a curved profile with concavity facing the X axis, the curved wall having a radial dimension Dr with respect to the X axis which increases progressively along the X axis in the direction of the first outlet, so as to concentrate the oil separated from the air / oil mixture towards the first outlet under the action of centrifugal force;

[0029] - the chamber internally comprises at least one porous element, so as to increase the exchange surface between the air / oil mixture and the oil separator;

[0030] - the oil separator comprises a central tube which has an internal opening at its upstream end, the internal opening forming a second outlet of the oil separator through which the de-oiled air from the air / oil mixture is evacuated;

[0031] - the ventilation device comprises at least one annular row of fins around the X axis;

[0032] - the fins are carried externally or internally by the central tube.

[0033] The present invention also relates to an aircraft turbomachine comprising an assembly as described previously.

[0034] Brief description of the figures

[0035] 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:

[0036] [Fig.1] Figure 1 is a schematic view in axial half-section of a turbomachine according to the invention;

[0037] [Fig.2] Figure 2 is a detail view of the reducer illustrated in Figure 1;

[0038] [Fig.3] Figure 3 is a detail and perspective view of the connection between the solar and the input shaft which is illustrated in Figure 2;

[0039] [Fig.4] Figure 4 is an axial sectional view of the connection illustrated in Figure 3;

[0040] [Fig.5] Figure 5 is a view similar to Figure 3 which illustrates a first variant embodiment of the oil separator; [Fig.6] Figure 6 is an axial sectional view of the connection illustrated in Figure 5;

[0041] [Fig.7] Figure 7 is a schematic view in axial half-section which illustrates a second variant embodiment of the oil separator.

[0042] Detailed description of the invention

[0043] Figure 1 shows a turbomachine 1 of an aircraft 2 according to the invention. The aircraft 2 is for example an airplane or a drone.

[0044] 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 “propellant” mode.

[0045] According to the invention, the turbomachine 1 comprises an assembly comprising:

[0046] - a reducer 3 housed in an enclosure 4 which comprises a solar 5 movable around an axis X, the solar 5 comprising internal grooves 6;

[0047] -an input shaft 7 movable about the axis X, the input shaft 7 comprising external splines 8 which are linked in rotation with the internal splines 6 of the solar 5; the internal and external splines 6, 8 are lubricated by immersion in an oil bath 9 which is formed at the internal periphery of the solar 5, the entire turbomachine 1 comprising a centrifugal oil separator 10 of an air / oil mixture coming from the enclosure 4, the oil separator 10 comprising a first outlet 11 through which the oil separated from the air / oil mixture is evacuated under the action of centrifugal force, the first outlet 11 being configured so that the oil separated from the air / oil mixture feeds the oil bath 9, the oil separator 10 comprising a ventilation device 12 configured to generate a flow of air / oil mixture F which feeds the oil separator 10.

[0048] Such lubrication of the splined connection is independent, and in other words it is dissociated from the conventional lubrication system which uses nozzles to lubricate elements (bearings, teeth of the toothed wheels) of the reducer 3. In fact, the splines 6, 8 are now lubricated by immersion in an oil bath 9 which is supplied by a centrifugal de-oiler 10.

[0049] Such independence means that you are no longer constrained by the problems of integrating a sprinkler.

[0050] Furthermore, such lubrication advantageously makes it possible to exploit the air / oil mixture available in the enclosure 4, to supply the oil bath 9 via the oil separator 10.

[0051] The turbomachine 1 is defined along the X axis which corresponds in particular to the axis of rotation of the solar 5 and the input shaft 7.

[0052] By convention in the present application, “axial” or “axially” means any direction parallel to the X axis of the turbomachine 1, “radial” or “radially” means any direction perpendicular to the X axis of the turbomachine 1, and “circumferential” or “circumferentially” means any direction relative to the circumference of the turbomachine 1 (as opposed to the axial and radial directions explained above).

[0053] As indicated above, the reducer 3 conventionally comprises at least one sun gear 5, a crown 13, satellites 14 and a planet carrier 15. Depending on the requirements, the reducer 3 can be configured in different ways.

[0054] In a manner common to the different configurations of reducer 3 explained below, the sun gear 5 is the input element of the reducer 3, and is thus linked in rotation with the input shaft 7. The input shaft 7 is itself driven, directly or indirectly, by the rotor of a turbine (for example the rotor of the low-pressure turbine 21) of the turbomachine 1. The planet carrier 15 carries several planet gears 14 movable around their own axis of rotation. The planet gears 14 are distributed around the axis X, each planet gear 14 being meshed with both the sun gear 5 and the ring gear 13.

[0055] More specifically, the reducer 3 can be configured according to a first configuration commonly called “epicyclic”. Such an epicyclic reducer has a planet carrier movable around the X axis and a fixed ring gear. The planet carrier is thus the output element of the reducer and is rotationally connected to an output shaft (for example a fan shaft 27 or a propeller shaft).

[0056] The reducer 3 can also be configured according to a second configuration commonly called "planetary". Such a planetary reducer has a crown wheel movable around the X axis and a fixed planet carrier. The crown wheel is thus the output element of the reducer and is rotationally connected to an output shaft (for example a fan shaft 27 or a propeller shaft).

[0057] The reducer 3 can finally be configured according to a third configuration commonly called "differential". Such a differential reducer has a planet carrier and a crown wheel movable around the X axis. The planet carrier and the crown wheel are output elements of the reducer, each of them being rotationally connected to an output shaft (for example a fan shaft or a propeller shaft). The planet carrier and the crown wheel of such a differential reducer are for example each rotationally connected to a fan shaft in an engine architecture comprising two counter-rotating fans.

[0058] The reducer 3 can be single-stage or double-stage. The different gear wheels of the reducer 3 can have, for example, herringbone teeth, straight teeth or even helical teeth.

[0059] Advantageously, the oil separator 10 is integral with the input shaft 7. The oil separator 10 is thus driven in rotation by the input shaft 7.

[0060] The oil separator 10 may be fixed to an upstream end 52 of the input shaft 7, for example by shrink fitting or via fixing elements such as screws. Alternatively, the oil separator 10 could be secured to the sun 5. In this case, the oil separator would be driven in rotation by the sun.

[0061] Advantageously, the oil separator 10 is housed at least partly in an upstream end 52 of the input shaft 7. Such positioning of the oil separator 10 makes it possible to exploit the space available inside the input shaft 7, and thus to improve the compactness.

[0062] Advantageously, the oil bath 9 is delimited axially by an upstream element 41, the first outlet 11 of the oil separator 10 being arranged axially between the upstream element 41 and an upstream end 38 of the external splines 8 of the input shaft 7. Such a positioning of the first outlet 11 guarantees that the oil is discharged directly into the oil bath 9, so as to optimize the supply of the oil bath 9.

[0063] The upstream element 41 which axially delimits the oil bath 9 may be an internal rim 41 or an added element such as a seal. Such an internal rim 41 for example projects radially inwards from an internal wall 43 of the solar 5.

[0064] Advantageously, the oil separator 10 comprises an annular chamber 44 for de-oiling the air / oil mixture, the first outlet 11 communicating with an external end of the chamber 44.

[0065] The chamber 44 can be compartmentalized around the X axis, and in other words the chamber 44 can comprise several compartments 48 arranged next to each other around the X axis.

[0066] Advantageously, the chamber 44 (or each compartment of the chamber) internally comprises at least one porous element 50, so as to increase the exchange surface between the air / oil mixture and the oil separator. Increasing the exchange surface makes it possible to improve the performance of the oil separator, and in other words to increase the quantity of oil discharged through the first outlet 11.

[0067] The porous element 50 may be a metal foam or a grid.

[0068] The chamber 44 (or each compartment of the chamber) may of course internally comprise several porous elements 50 arranged next to each other. For example, the chamber (or each compartment of the chamber) may internally comprise several grids arranged axially one after the other, the grids being angularly offset from each other.

[0069] The chamber 44 may be at least axially delimited by a first wall 64 and a second wall 65 facing each other. The first and second walls 64, 65 converge towards the first outlet 11 of the oil separator 10, so as to concentrate the oil separated from the air / oil mixture towards the first outlet 11 under the action of centrifugal force.

[0070] Alternatively, the chamber 44 may be at least axially delimited by a curved wall 47 which has in axial half-section a curved profile with concavity facing the axis X. The curved wall 47 has a radial dimension Dr with respect to the axis X which increases progressively along the axis X in the direction of the first outlet 11, so as to concentrate the oil separated from the air / oil mixture towards the first outlet 11 under the action of centrifugal force.

[0071] The chamber 44 may be delimited axially by a curved upstream wall as defined above and a curved downstream wall as defined above, the upstream and downstream walls being opposite each other.

[0072] Advantageously, the oil separator 10 comprises an inlet 56 through which the oil separator 10 is supplied with an air / oil mixture.

[0073] Inlet 56 can communicate with de-oiling chamber 44.

[0074] The inlet 56 can be formed by ports 57 made in a wall of the oil separator 10.

[0075] As indicated above, the oil separator 10 comprises a first outlet 11 through which the oil separated from the air / oil mixture is discharged under the action of centrifugal force.

[0076] The first outlet 11 of the oil separator 10 may be formed by one or more annular rows of holes 58 around the axis X. Preferably, the holes 58 are radial or have at least one radial component.

[0077] The 58 holes in each row can be distributed evenly or irregularly around the X axis.

[0078] Each row of holes 58 can be defined in a radial plane (plane perpendicular to the X axis).

[0079] The rows of holes 58 may be located in the same radial plane or in different radial planes axially offset from each other.

[0080] The number of holes 58 as well as the geometric and dimensional characteristics of the holes 58 are defined according to the needs. Advantageously, the oil separator 10 comprises a second outlet 59 through which the de-oiled air from the air / oil mixture is evacuated.

[0081] The second outlet 59 may be formed by an internal opening 60 of a central tube 45 of the oil separator 10, the internal opening 60 being located at an upstream end of the central tube 45.

[0082] Advantageously, the oil separator 10 comprises a central tube 45 which has an internal opening 60 at its upstream end. The internal opening 60 forms the second outlet 59 of the oil separator 10 through which the de-oiled air from the air / oil mixture is evacuated.

[0083] Advantageously, the ventilation device 12 comprises at least one annular row of fins 61 around the axis X.

[0084] The ventilation device 12 can obviously comprise several rows of fins 61.

[0085] The fins 61 can be integral with the central tube 45.

[0086] The fins 61 can be carried externally by the central tube 45.

[0087] The fins 61 can be carried internally by the central tube 45. In this specific case, the ventilation device 12 generates the air / oil mixture flow F by creating a depression inside the oil separator.

[0088] The oil separator 10 may comprise a first row of fins carried externally by the central tube and a second row of fins carried internally by the central tube.

[0089] The number of fins 61 as well as the geometric and dimensional characteristics of the fins 61 are defined according to the needs.

[0090] According to the embodiment illustrated in Figure 1, the turbomachine 1 is a double-flow turbojet.

[0091] More specifically, the turbomachine 1 conventionally comprises, from upstream to downstream, a ducted fan 16, a low-pressure compressor 17, a high-pressure compressor 18, an annular combustion chamber 19, a high-pressure turbine 20, a low-pressure turbine 21 and an exhaust nozzle 22. The high-pressure compressor 18 and the high-pressure turbine 20 are connected to each other by a high-pressure shaft 23 and form with it a high-pressure (HP) body. The low-pressure compressor 17 and the low-pressure turbine 21 are connected to each other by different shafts and form with them a low-pressure (LP) body.

[0092] As illustrated in FIG. 1, the airflow generated by the fan 16 is divided, by a fixed structure 24 of the turbomachine 1, into a primary flow which enters a primary vein 25 to supply the low-pressure compressor 17, and into a secondary flow which flows in a secondary vein 26 around the gas generator, to provide the majority of the thrust.

[0093] As illustrated in Figure 1, the fan 16 is driven in rotation by a fan shaft 27 which is itself driven in rotation by the input shaft 7 by means of the speed reducer 3. The input shaft 7 is itself driven, directly or indirectly, by the rotor of the low pressure turbine 21.

[0094] The embodiment illustrated in Figure 1 is in no way limiting; the turbomachine 1 could, for example, be a turboprop, or even a turbomachine known by the English acronym “USF” for “Unducted Single Fan” which notably comprises a single unducted fan.

[0095] As illustrated in Figure 2, the reducer 3 is here of the “planetary” type. More precisely, the reducer 3 comprises a sun gear 5 linked in rotation with the input shaft 7, a ring gear 13 linked in rotation with the fan shaft 27, and a fixed planet carrier 15. The reducer 3 makes it possible to reduce the rotation speed of the fan shaft 27 relative to that of the input shaft 7.

[0096] As illustrated in Figure 1, the reducer 3 is housed and lubricated in an annular enclosure 4 around the axis X. The enclosure 4 is positioned in the upstream part of the turbomachine 1. The enclosure 4 is here formed by an upstream shell 28 and a downstream shell 29 of the fixed structure 24. The enclosure 4 is here closed upstream by seals at the level of a bearing allowing the fan shaft 27 to pass through, and downstream by seals at the level of the input shaft 7 to pass through.

[0097] As illustrated in Figure 2, the input shaft 7 is connected in rotation with the solar 5 via the splines 6, 8. The fan shaft 27 is flanged to the crown 13 via an annular row of screws 30 around the axis X. Each satellite 14 is carried by an axis 31 of the planet carrier 15 and guided in rotation by a plain bearing 32 arranged between the axis 31 and the satellite 14. The crown 13 here comprises two half-crowns flanged to each other. The reducer 3 here is single-stage. The different toothed wheels of the reducer 3 here have herringbone teeth.

[0098] As illustrated in Figure 2, the bearing 32 of each satellite 14 is here lubricated via a lubrication circuit 33 which conveys oil inside the corresponding axis 31, the oil reaching the bearing 32 via orifices made in the axis 31. In addition, the teeth of the sun 5 and the satellites 14 are here lubricated via different nozzles 34 whose oil jets are directed towards the meshing interface between the sun 5 and the satellites 14. As illustrated in Figures 2 to 6, the input shaft 7 is here tubular and in one piece (or monobloc). The input shaft 7 comprises a body 35 and a splined ring 36 which are connected to each other via a web 37.

[0099] More specifically, the body 35 is cylindrical and centered on the X axis. The body 35 comprises an upstream end which is connected to the grooved ring 36 via the web 37 and a downstream end which is linked in rotation, directly or indirectly, with the rotor of the low pressure turbine 21.

[0100] The ring 36 is arranged upstream of the body 35 and has an external diameter which is greater than that of the body 35. The ring 36 comprises the external grooves 8 which are linked in rotation with the internal grooves 6 of the solar 5.

[0101] The external grooves 8 extend axially over the entire axial dimension of the ring 36. Thus, the upstream end 38 of the external grooves 8 coincides with the upstream end of the ring 36, and the downstream end 39 of the external grooves 8 coincides with the downstream end of the ring 36. The web 37 widens from downstream to upstream from the upstream end of the body 35 to the grooved ring 36.

[0102] As illustrated in Figures 2 to 6, the sun gear 5 comprises an external toothing 40 which is meshed with the different satellites 14 of the reducer 3 and the internal splines 6 which are linked in rotation with the external splines 8 of the input shaft 7.

[0103] As indicated above, the internal and external grooves 6, 8 are lubricated by immersion in an oil bath 9 which is formed at the internal periphery of the solar 5. The oil bath 9 remains over time under the action of the rotation of the solar 5, and more precisely under the action of the centrifugal force which is exerted on the oil stored in the bath.

[0104] The oil bath 9 is delimited axially by an internal rim 41 upstream and by a seal 42 downstream. The seal 42 is attached to an internal groove of the solar 5.

[0105] The oil bath 9 is delimited radially by an internal wall 43 on which the internal grooves 6 are formed, the internal wall 43 being located axially between the internal rim 41 and the seal 42. The internal wall 43 forms the bottom of the oil bath 9.

[0106] As illustrated in Figures 2 to 6, the oil separator 10 is here secured to the input shaft 7. The oil separator 10 is thus driven in rotation by the input shaft 7.

[0107] The oil separator 10 is centered on the X axis and is made of a single piece (or monobloc).

[0108] The oil separator 10 comprises an annular oil separator chamber 44 which extends around a central tube 45.

[0109] The chamber 44 is delimited axially by an upstream wall 46 and a downstream wall 47 facing each other.

[0110] More precisely, as illustrated in Figures 4 and 6, the upstream wall 46 is straight and has a straight and radial profile in axial half-section.

[0111] The downstream wall 47 is curved, and has in axial half-section a curved profile with concavity facing the axis X. The downstream wall 47 has a radial dimension Dr with respect to the axis X which increases progressively along the axis X in the direction of the first outlet 11, so as to concentrate the oil separated from the air / oil mixture towards the first outlet 11 under the action of centrifugal force.

[0112] As illustrated in Figures 3 and 5, the chamber 44 is compartmentalized around the X axis. The chamber 44 here comprises six compartments 48 arranged next to each other around the X axis. The compartments 48 are defined circumferentially by partitions 49, each partition 49 connecting together the walls 46, 47 of the chamber 44 and the central tube 45.

[0113] Each compartment 48 internally comprises a porous element 50, so as to increase the exchange surface between the air / oil mixture and the oil separator 10. As indicated above, the porous element 50 is for example a metal foam or even one or more grids.

[0114] The central tube 45 is cylindrical and centered on the axis X. The tube 45 comprises a free upstream end which projects axially upstream relative to the chamber 44 and a downstream end which is connected to the downstream wall 47. The interior of the tube 45 communicates with an internal end of the chamber 44 via an annular row of orifices 51 around the axis X, the orifices 51 being made in the tube 45. The orifices 51 are here radial and oblong in shape. Each orifice is associated with a compartment 48 of the chamber 44 and makes it possible to evacuate the de-oiled air from this compartment 48.

[0115] The oil separator 10 is housed partly in the upstream end 52 of the input shaft 7. The oil separator 10 is fixed to the upstream end 52 of the input shaft 7 by shrink fitting.

[0116] More precisely, the downstream wall 47 is shrunk into a cavity 53 formed in the ring 36 of the input shaft 7. The cavity 53 has a shape complementary to that of the downstream wall 47. The oil separator 10 is stopped axially in the input shaft 7 via a collar 54 of the oil separator 10 which bears against a shoulder 55 of the input shaft 7. The collar 54 is formed on the outer periphery of the downstream wall 47 and the shoulder 55 is formed at an upstream end of the ring 36. The inlet 56 of the oil separator 10 is here axial and is formed by an annular row of openings 57 around the axis X, the openings 57 being made in the upstream wall 46. The openings 57 are here axial and of substantially triangular shape. Each light 57 is associated with a compartment 48 of the chamber 44 and makes it possible to supply this compartment 48 with an air / oil mixture.

[0117] The first outlet 11 of the oil separator 10 is here radial and is formed by an annular row of holes 58 around the axis X, the holes 58 being made in the downstream wall 47 at its outer end. The holes 58 are here radial and cylindrical in shape. The holes 58 are here upstream of the collar 54. The holes 58 communicate with an outer end of the chamber 44. Each hole 58 is associated with a compartment 48 of the chamber 44 and allows the oil separated in this compartment 48 to be evacuated, to feed the oil bath 9. The holes 58 are arranged axially between the inner rim 41 and the upstream end 38 of the outer splines 8 of the input shaft 7, so that the oil is evacuated directly into the oil bath 9.

[0118] The second outlet 59 of the oil separator 10 is here axial and is formed by an internal opening 60 arranged at the upstream end of the central tube 45. The opening 60 is here axial and circular in shape. The opening 60 communicates with the internal end of the chamber 44 via the orifices 51 and the space located inside the tube 45. The opening 60 thus makes it possible to evacuate the de-oiled air from all of the compartments 48 of the chamber 44.

[0119] As illustrated in Figures 2 to 6, the ventilation device 12 comprises an annular row of fins 61 around the axis X. The fins 61 are configured to generate a flow of air / oil mixture F which feeds the oil separator 10.

[0120] According to the embodiment illustrated in Figures 2 to 4, the fins 61 of the ventilation device 12 are carried externally by the central tube 45. The fins 61 are located axially upstream of the chamber 44. According to the embodiment variant illustrated in Figures 5 and 6, the fins 61 of the ventilation device 12 are carried internally by the central tube 45. The fins 61 are located axially between the orifices 51 and the opening

[0121] 60 of the tube 45. The fins 61 here ventilate the de-oiled air to create a depression inside the oil separator 10, and thus generate the flow of air / oil mixture F which feeds the oil separator 10.

[0122] In operation, as illustrated in Figures 4 and 6, the rotation of the vanes

[0123] 61 generates the flow of air / oil mixture F which feeds the different compartments 48 of the chamber 44 via the ports 57. In each of the compartments 48 of the chamber 44, the air / oil mixture is centrifuged so as to separate the oil which goes towards the outside and the air which goes towards the inside. The oil separated from the air / oil mixture is evacuated through the holes 58 to feed the oil bath 9. The de-oiled air from the air / oil mixture is evacuated through the opening 60 of the tube 45 to reach the enclosure 4.

[0124] According to the embodiment variant illustrated in Figure 7, the oil separator 10 comprises an annular oil separator chamber 44 which extends around a central tube 45.

[0125] Room 44 comprises an external part 62 and an internal part 63.

[0126] The external part 62 of the chamber 44 is delimited axially by an upstream wall 64 and a downstream wall 65 facing each other. The upstream and downstream walls 64, 65 converge here radially towards the first outlet 11 of the oil separator 10, so as to concentrate the oil separated from the air / oil mixture towards the first outlet 11 under the action of centrifugal force.

[0127] More precisely, as illustrated in Figure 7, the upstream and downstream walls 64, 65 of the external part 62 are each frustoconical and each have in axial half-section a straight and inclined profile which widens along the axis X in the direction of the first outlet 11.

[0128] The internal part 63 of chamber 44 is delimited axially by an upstream wall 66 and a downstream wall 67 facing each other. More precisely, as illustrated in FIG. 7, the upstream and downstream walls 66, 67 of the internal part 63 are each straight and each have a straight and radial profile in axial half-section.

[0129] The inlet 56 of the oil separator 10 is axial and is formed in the upstream wall 66 of the internal part 63 of the chamber 44.

[0130] The first outlet 11 of the oil separator 10 is radial and arranged axially between the upstream and downstream walls 64, 65 of the external part 62 of the chamber 44. The first outlet 11 communicates with an external end of the chamber 44. The second outlet 59 of the oil separator 10 is axial and is formed by the internal opening 60 arranged at the upstream end of the central tube 45.

Claims

CLAIMS 1. Aircraft (2) turbomachine assembly (1) comprising: - a reducer (3), housed in an enclosure (4), which comprises a solar (5) movable around an axis (X), the solar (5) comprising internal grooves (6); - an input shaft (7) movable around the axis (X), the input shaft (7) comprising external splines (8) which are rotationally linked with the internal splines (6) of the solar (5); characterized in that the internal and external grooves (6, 8) are lubricated by immersion in an oil bath (9) which is formed at the internal periphery of the solar (5), the turbomachine assembly (1) comprising a centrifugal oil separator (10) of an air / oil mixture coming from the enclosure (4), the oil separator (10) comprising a first outlet (11) through which the oil separated from the air / oil mixture is evacuated under the action of centrifugal force, the first outlet (11) being configured so that the oil separated from the air / oil mixture feeds the oil bath (9), the oil separator (10) comprising a ventilation device (12) configured to generate a flow of air / oil mixture (F) which feeds the oil separator (10).

2. Turbomachine assembly (1) according to claim 1, characterized in that the oil separator (10) is integral with the input shaft (7).

3. Turbomachine assembly (1) according to one of the preceding claims, characterized in that the oil separator (10) is housed at least partly in an upstream end (52) of the input shaft (7).

4. Turbomachine assembly (1) according to one of the preceding claims, characterized in that the oil bath (9) is axially delimited by an upstream element (41), the first outlet (11) of the oil separator (10) being arranged axially between the upstream element (41) and an upstream end (38) of the external splines (8) of the input shaft (7).

5. Turbomachine assembly (1) according to one of claims 1 to 4, characterized in that the oil separator (10) comprises an annular deoiling chamber (44) for the air / oil mixture, the first outlet (11) communicating with an external end of the chamber (44), the chamber (44) being at least axially delimited by a first wall (64) and a second wall (65) facing each other, the first and second walls (64, 65) converging towards the first outlet (11) of the oil separator (10), so as to concentrate the oil separated from the air / oil mixture towards the first outlet (11) under the action of centrifugal force.

6. Turbomachine assembly (1) according to one of claims 1 to 4, characterized in that the oil separator (10) comprises an annular deoiling chamber (44) for the air / oil mixture, the first outlet (11) communicating with an external end of the chamber (44), the chamber (44) being at least axially delimited by a curved wall (47) which has in axial half-section a curved profile with concavity facing the axis (X), the curved wall (47) having a radial dimension (Dr) with respect to the axis (X) which increases progressively along the axis (X) in the direction of the first outlet (11), so as to concentrate the oil separated from the air / oil mixture towards the first outlet (11) under the action of centrifugal force.

7. Turbomachine assembly (1) according to one of claims 5 or 6, characterized in that the chamber (44) internally comprises at least one porous element (50), so as to increase the exchange surface between the air / oil mixture and the oil separator (10).

8. Turbomachine assembly (1) according to one of the preceding claims, characterized in that the oil separator (10) comprises a tube central (45) which comprises an internal opening (60) at its upstream end, the internal opening (60) forming a second outlet (59) of the oil separator (10) through which the de-oiled air from the air / oil mixture is evacuated.

9. Turbomachine assembly (1) according to the preceding claim, characterized in that the ventilation device (12) comprises at least one annular row of fins (61) around the axis (X).

10. Turbomachine assembly (1) according to claim 9 when it depends on claim 8, characterized in that the fins (61) are carried externally or internally by the central tube (45).

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