Lubrication wheel for a turbomachine speed reduction gear

Abstract

The invention relates to a lubrication wheel (230) for a turbomachine speed reduction gear (110), in particular of an aircraft, said wheel (230) being intended to be rotated about an axis (A) and having a generally annular shape about said axis (A), the wheel comprising: - at the inner periphery thereof, an annular oil-receiving cavity (238) which extends around said axis (A) and which opens radially inwards, and - first oil passage pipes (143) which extend radially with respect to said axis (A) and radially inner ends of which are connected to said cavity (238), and - lubrication chambers (250) which are distributed around the axis (A) and which are respectively connected to the radially outer ends of the first pipes (143) by filtration strainers (256).

Description

[0001]

[0002] Technical field of the invention

[0003] The present invention relates in particular to a lubrication wheel for a turbomachine speed reducer, especially for aircraft, as well as to a reducer and a turbomachine comprising such a wheel. Such a lubrication wheel is commonly called an oil supply device or a rotary-seal-free lubrication device.

[0004] Technical background

[0005] The state of the art in this field includes in particular documents FR-A1-3 036 763, FR-A1-3 047 279, FR-A1-3 041 054, FR-A1-3 065 773, W0-A1 -2015 / 008000, WO-A1 -2018 / 185186, FR-A1 -3 103 241, FR-A1 -3 065 046, US-A1 -2023 / 069754, JP-A1 -2005 351294, FR-A1 -3 075 868, USAI -2019 / 085972 and FR-A1 -3 740 657.

[0006] The role of a mechanical reducer is to modify the speed and torque ratio between the input and output shafts of a mechanical system.

[0007] Newer generations of dual-flow turbomachinery, especially those with a very high bypass ratio, include a mechanical reducer to drive a blower shaft also called a "fan".

[0008] Typically, the purpose of the gearbox is to transform the so-called high rotational speed of the shaft of a power turbine into a slower rotational speed for the shaft driving the blower.

[0009] Such a reduction gear comprises a central pinion, called the sun gear, a ring gear, and pinions called planet gears, which mesh between the sun gear and the ring gear. The planet gears are held by a frame called the planet carrier. The sun gear, ring gear, and planet carrier are planetary gears because their axes of revolution coincide with a longitudinal axis of the turbomachine. The planet gears each have a different axis of revolution, equally spaced on the same operating diameter around the axis of the planet gears. These axes are parallel to the longitudinal axis.

[0010] Several gearbox architectures exist. In state-of-the-art turbomachinery, gearboxes are of the planetary or epicyclic type. In other similar applications, differential or compound architectures exist.

[0011] - On a planetary reducer, the planet carrier is fixed and the ring forms the output shaft of the device which rotates in the opposite direction to the sun.

[0012] - On an epicyclic reducer, the ring is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the solar.

[0013] - On a differential gearbox, no element is fixed in rotation. The ring rotates in the opposite direction to the solar and satellite carrier.

[0014] Gearboxes can consist of one or more meshing stages. This meshing is achieved in various ways, such as by contact, friction, or magnetic fields.

[0015] There are several types of contact meshing such as with straight, helical or herringbone teeth.

[0016] There are several lubrication solutions for such a reducer.

[0017] Figure 1 illustrates a satellite carrier 10 as described in FRAI-3 036 763. This satellite carrier 10 comprises a cylindrical body 12 connected at one longitudinal end to an annular wall 14 supporting parallel axes 16 of rotation of the satellites 18. The axes 16 are evenly distributed around the axis A of rotation of the satellite carrier and are fixed at one of their longitudinal ends to the aforementioned annular wall 14. A lubrication wheel 20 is attached to and fixed at opposite longitudinal ends of the axes 16.

[0018] The lubrication wheel 20 is fixed to the planet carrier 10 by virtue of its connection to the axes 16 of support of the planets 18. The lubrication wheel 20 is therefore intended to be rotated in operation around the axis A by being fixed to the rotor of the reducer.

[0019] The lubrication wheel 20 has a general annular shape around the axis A and has hydraulic connections on its external periphery to the axes 16 of rotation of the satellites 18. The wheel 20 includes lubrication means, on the one hand, bearings mounted between the axes 16 and the satellites 18, and, on the other hand, meshing teeth of the satellites 18 and the solar element 22. These lubrication means include an annular groove 24 located on the internal periphery of the wheel 20 and opening radially inwards, i.e. towards the axis A.

[0020] Lubricant jets, carried by a stator of the reducer or turbomachine, are arranged radially inside the impeller (they are not shown in Figure 1), and project lubricant radially outwards directly into the groove 24 of the impeller, to supply the lubrication means.

[0021] The lubricant is delivered to the nozzles by a pump in the turbomachine's lubrication unit, which delivers a predetermined flow rate of lubricant to the nozzles. With the current technology described above, the lubricant sprayed into the nozzle throat is delivered to the lubrication system solely by centrifugal force.

[0022] The impeller therefore distributes pressurized oil into the reducer using the centrifugal forces generated during operation.

[0023] Solid particles (from worn parts, for example) can enter the impeller or come into contact with the oil and can wear down the components supplied with oil by the impeller (satellite bearings, gears, etc.). The present invention offers a simple, effective, and economical solution to this problem.

[0024] Summary of the invention

[0025] The invention provides a lubrication wheel for a turbomachine speed reducer, particularly for aircraft, said wheel being designed to rotate about an axis and having a generally annular shape about said axis, the wheel comprising:

[0026] - on its inner periphery an annular oil-receiving cavity extending around said axis and opening radially inwards, and

[0027] - the first oil passage channels which extend radially with respect to said axis and whose radially internal ends are connected to said cavity for the purpose of passing oil by centrifugation from the cavity into the first channels,

[0028] - lubrication chambers which are distributed around the axis and which are connected respectively to the radially external ends of the first pipes, each of these chambers having an axial end which is open and an opposite axial end which is closed by a bottom and which includes an orifice for fluid communication of the chamber with the radially external end of the corresponding first pipe, characterized in that the impeller includes oil filter screens which circulate in the first pipes, as well as particle evacuation holes, these holes being located upstream of the screens with respect to the circulation of the oil in the pipes, and these holes extending between the pipes and the outside of the impeller in order to evacuate particles and prevent them from clogging the screens.

[0029] The impeller is thus equipped with an oil filtration system, which takes the form of filter screens. For the purposes of this application, a filter screen is a component configured to filter the oil passing through it. The screen may, for example, be made of a cellular or mesh material that allows the oil to pass through while retaining impurities or particles contained in the oil. These screens are advantageously located in the impeller's channels that supply the gearbox's satellites. The screens are advantageously in the form of inserts. The impeller according to the invention may comprise one or more of the following features, taken individually or in combination:

[0030] - the strainers are mounted in the aforementioned orifices for fluidic communication of the chambers with the radially external ends of the first pipes;

[0031] - the strainers are oriented parallel to the axis;

[0032] - the holes extend radially with respect to said axis;

[0033] - the holes extend parallel to said axis;

[0034] - the holes are inclined relative to said axis;

[0035] - the strainers are fitted in the first pipes;

[0036] - the strainers are oriented radially with respect to the axis;

[0037] - the holes extend parallel to said axis;

[0038] - the holes are inclined relative to said axis;

[0039] - the holes are formed on the outer periphery of the wheel and / or open at the radially external ends of the first pipes;

[0040] - the first pipes are blocked at their radially external ends by added plugs;

[0041] - the wheel includes second oil passage channels which extend radially with respect to said axis and whose radially internal ends are connected to said cavity for the purpose of passing oil by centrifugation from the cavity into the second channels, the second channels having a radial dimension smaller than that of the first channels;

[0042] -- each of the strainers comprises a mounting portion and a filtration portion projecting longitudinally from said mounting portion, said mounting portion being received in one of said orifices;

[0043] -- said filtration portion is located upstream of said mounting portion with respect to the oil flow; -- said filtration portion comprises a curved filtration wall whose convexity is turned towards the side opposite the mounting portion;

[0044] -- said filtration portion extends at least partially into one of the said first pipes;

[0045] -- each of the said perforations opens opposite the filtration portion of one of the said strainers;

[0046] -- each of said pipes has a blind terminal section extending beyond the junction between that pipe and the corresponding chamber

[0047] -- the holes have a diameter that is at least 25% smaller than the diameter of the strainers.

[0048] The present invention also relates to a speed reducer for a turbomachine, this reducer comprising a rotating solar element about an axis, a ring extending around the axis and the solar element, and satellites located between the solar element and the ring and meshed with the solar element and the ring, the satellites being carried by a satellite carrier centered on the axis and rotating about this axis, in which a wheel as described above is fixed coaxially to the satellite carrier for the purpose of lubricating the satellites, and in particular the bearings of the satellites, via said lubrication chambers.

[0049] Brief description of the figures

[0050] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:

[0051] [Fig.1] Figure 1 is a schematic perspective view of a satellite carrier of prior art,

[0052] [Fig.2] Figure 2 schematically represents an axial section of a turbomachine using the invention;

[0053] [Fig.3] Figure 3 shows a detailed cross-sectional view of an epicyclic gear reducer; [Fig.4] Figure 4 is an exploded, perspective view of the reducer in Figure 3;

[0054] [Fig.5] Figure 5 shows a schematic cross-section of a gear from the reducer in Figure 3;

[0055] [Fig.6] Figure 6 is a schematic half-view in axial section of a lubrication wheel according to an embodiment of the invention;

[0056] [Fig.7] Figure 7 is a partial schematic axial cross-section and perspective view of the lubrication wheel of Figure 6;

[0057] [Fig.8a-8c] Figures 8a-8c are views similar to that of Figure 6 and representing variant embodiments of the invention;

[0058] [Fig.9] Figure 9 is a view similar to that of Figure 6 and representing another variant embodiment of the invention.

[0059] Detailed description of the invention

[0060] Figure 1 has been described above and represents the technique prior to the present invention.

[0061] Figures 2 to 5 illustrate the earlier technique as described in document FR-A1-3 041 054.

[0062] Figure 1 shows a turbomachine 100 which conventionally comprises a fan propeller S, a low-pressure compressor 101a, a high-pressure compressor 101b, a high-pressure turbine 101d, a low-pressure turbine 101e, and an exhaust nozzle 101h. The high-pressure compressor 101b and the high-pressure turbine 101d are connected by a high-pressure shaft 102 and together form a high-pressure (HP) housing. The low-pressure compressor 101a and the low-pressure turbine 101e are connected by a low-pressure shaft 103 and together form a low-pressure (LP) housing.

[0063] The fan propeller S is driven by a fan shaft 104, which is coupled to the BP shaft 103 by means of an epicyclic gear reducer 110, shown schematically here. The reducer 110 is located in the upstream section of the turbomachine. In this application, the terms "upstream" and "downstream" refer to the gas flow within the turbomachine.

[0064] A fixed structure schematically comprising here an upstream part 105a and a downstream part 105b is arranged to form an enclosure E1 surrounding the reducer 110. This enclosure E1 is here closed upstream by seals at the level of a bearing 106a allowing the passage of the blower shaft 104, and downstream by seals at the level of the passage 106b of the BP shaft 103.

[0065] With reference to Figures 2 and 3, the gearbox is enclosed in a ring 114 which is fixed, via a support housing 120, to the fixed structure 105a, 105b. Flexible means are arranged to allow it to follow any movements of the blower shaft 104, for example, in certain degraded operating conditions. These fastening means are known to those skilled in the art and are not detailed here. A brief description can be found, for example, in document FRAI-2 987 416.

[0066] The gearbox 110 in the example under consideration engages, on the one hand, with the BP shaft 103 via splines 107 which drive a planetary gear, called the sun gear 111, and on the other hand, with the fan shaft 104 which is attached to a planet carrier 113. Typically, the sun gear 111, whose axis of rotation A coincides with that of the turbomachine, drives a series of planet gears 112, which are evenly distributed around the circumference of the gearbox 110. The number of planet gears 112 is generally defined as between three and six. The planet gears 112 also rotate around the axis A of the turbomachine, meshing with internal teeth of the ring gear 114, which is fixed relative to the turbomachine by means of the support housing 120.Each of the satellites 112 rotates freely around a satellite axis 116 connected to the satellite carrier 113, using a bearing which can be smooth, as shown in Figure 3, or a rolling element bearing (ball or roller bearings).

[0067] The rotation of the satellites 112 around their satellite axis 116, due to the cooperation of their pinions with the teeth of the ring 114, causes the rotation of the satellite carrier 113 around the axis A, and consequently that of the blower shaft 104 which is linked to it, at a rotational speed which is lower than that of the BP shaft 103.

[0068] The fan shaft 104 is driven by the planet carrier 113 by a series of centering fingers 117, evenly distributed around the circumference of the gearbox 110. These fingers extend axially from the downstream end of the fan shaft 104 and engage in bores machined in the planet carrier 113. The planet carrier 113 extends symmetrically on either side of the planet shafts 116 and forms a housing in which a gear lubrication function can be implemented. Sealing sleeves 119, at the ends of the planet shafts 116, allow this housing to be closed at the planet bearings 112.

[0069] Figure 3, along with Figure 4, shows the oil supply to the gearbox 110 and its path within it. Arrows in Figure 3 indicate the path followed by the oil from, in this example, a buffer reservoir 131 connected to the fixed structure of the turbomachine, to the gears and bearings to be lubricated. The lubrication system schematically comprises three parts, which will be described successively below: a first part connected to the fixed structure that delivers the oil to the rotating parts of the gearbox 110; a rotating impeller with a planet carrier 113 that receives this oil; and oil distribution circuits supplied with oil by the impeller to deliver it to the areas to be lubricated. The first part includes at least one injector 132, the calibrated end of which is constricted to form a nozzle 133.Oil is supplied to the injector via a delivery line 129 from the engine reservoir (not shown). A buffer tank 131 can be placed next to the gearbox 110 on the line, preferably at the top so that the oil can flow towards the center of the gearbox by gravity. The nozzle 133 ejects the oil in the form of a jet 134, which is formed under the pressure produced jointly by the supply pump (not shown) and by the weight of the oil column above it. The nozzle 133 is positioned radially inside the planet carrier 113 with respect to axis A, and the jet 134 is oriented with a radial component directed outwards from the gearbox 110.

[0070] With reference to figures 4 and 5, the oil receiving wheel 130 linked to the planet carrier 113 essentially comprises a cylindrical cup 135, here with a radial U-shaped cross-section, the U-shaped opening of which is oriented in the direction of the axis of rotation A. The wheel 130 is arranged on the planet carrier 113 so that the bottom 136 of the U of the cup 135 collects the jet of oil 134 ejected by the nozzle 133.

[0071] The cup 135 of the wheel 130 is here divided into a circumferential succession of bowls 137a, 137b separated by walls 138 oriented radially and extending axially between the two lateral walls 139a, 139b of the U formed by the cup 135. On the example presented, the circumferential separating walls 138 delimit two alternating series of four bowls 137a, 137b, with an identical circumferential extension in one series but different from one series to the other.

[0072] By centrifugal force, when the impeller 130 rotates with the planet carrier 113, the oil collected on the bottom 136 of the cup 135 is driven into rotation and pressurized between the bottom 136 and the side walls 139a, 139b of the cup 135. Each cup 135a, 135b, as it passes successively in front of the nozzle 133 during rotation, collects a quantity of oil proportional to its circumferential extent. Indeed, the radially inner edges of the walls 139a-139b-138 of a cup 137a, 137b define an inlet surface of the cup along the radial direction. This oil remains confined between the walls 138, 139a, 139b of the basin 137a, 137b as long as the oil level relative to the bottom 136 remains below the minimum height h of the walls 138 of it relative to the bottom 136. The internal radial edges 140a, 140b of the lateral walls 139a, 139b are substantially circular.Their radius R1 defines a general depth H of the cup 135 relative to the bottom 136. Preferably, the circumferential separating walls 138 have an internal radial edge 141 located at a distance R2 from the axis A slightly greater than the radius R1 of the internal edges 140a, 140b of the side walls 139a, 139b. The height h of the circumferential separating walls 138 relative to the bottom 136 of the cups 137a, 137b is therefore slightly less than the height H of the side walls 139a, 139b relative to the same bottom 136.

[0073] Furthermore, the bottom 136 of each bowl 137a, 137b has an opening 142a, 142b which communicates with a pipe 143, 145 of an oil distribution circuit installed on the satellite carrier 113.

[0074] With reference to Figures 4 and 5, the oil distribution circuits are of two types. A first series of oil distribution circuits corresponds to first channels 143, which are regularly distributed around the circumference of the reducer 110 and in a number equal to that of the satellites 112. These channels 143 originate radially from the opening 142a in the bottom of the first series of cups 137a and enter the internal housing of each satellite shaft 116, which is closed by the satellite carrier 113. The oil flowing in the first channels 143 enters the internal cavity of each satellite shaft 116 and then passes, due to centrifugal force, into guide channels 144, which pass through these satellite shafts 116 while being radially oriented. These channels 144 open at the periphery of the satellite axes 116, at the level of the bearings supporting the pinions of the satellites 112 and thus ensure the lubrication of these bearings (figure 3).

[0075] The second series of oil distribution circuits comprises secondary channels 145 which run from the openings 142b in the bottom of the basins 137b of the second series of basins between the satellites 112 and divide into several channels 145a, 145b. The channels 145a, 145b carry the oil to the gears formed by the pinions of the satellites 112 and the sun gear 111, on the one hand, and the pinions of the satellites 112 and the outer ring 114, on the other. Each channel 145a extends axially along the pinions of a satellite 112, between them and the sun gear 111, and forms a lubrication ramp across the entire width of the pinions. The channel 145b, which supplies the gearing between the crown 114 and the pinions of the satellites 112, projects its oil into the center of the cylinder formed by each satellite 112. As shown, each satellite 112 is made in the form of two parallel pinions.Their teeth are oriented diagonally with respect to the axis of rotation of the satellite 112, so as to give them a function of grooves in which the oil is driven, from the middle of the cylinder to its periphery, to lubricate the gear over its entire width.

[0076] The first oil distribution circuits 143-144, which lubricate the bearings supporting the satellites, require a higher oil flow rate than the second circuits 145-145a-145b. For this reason, the circumferential extent of the corresponding cups 137a in the first series is greater than that of the cups 137b in the second series. Here, a two-thirds to one-third ratio is sought in the oil flow rate during nominal operation; the circumferential extent of the two series of cups 137a and 137b closely reflects this ratio.

[0077] The assembly has been presented here with reference to a four-satellite gearbox 110 with two sets of oil distribution circuits 143-144, 145-145a-145b of different types. For other gearbox architectures, the number of cups per set may differ. Similarly, the number of cup sets with similar circumferential extensions may vary, depending on the types of oil distribution circuits. For example, the second oil distribution circuit could be subdivided into two: one dedicated to the gearing of the satellite pinions 112 with the sun gear 111, and the other dedicated to the gearing with the ring gear 114. In this case, a variant embodiment of the oil recovery wheel is conceivable with three sets of cups of different circumferential extensions.

[0078] Figures 6 to 9 illustrate several embodiments of a 230 spinning wheel according to the invention.

[0079] The wheel 230 includes features described above and designated by the same references in figures 3 to 5. These include the pipes 143, and also the pipes 145. The wheel 230 has a general annular shape around the aforementioned axis A.

[0080] The wheel 230 includes fluidic connection means to the axes 116 of rotation of the reducer satellites, these connection means being formed by cylindrical ends 260 engaged in internal cavities of these axes 116. The wheel 230 may also include means for lubricating the teeth of the satellites and the bearings of the axes 116, which include in particular the aforementioned channels 143, 145.

[0081] The lubrication means further comprise an annular cavity 238 located on the inner periphery of the impeller 230 and connected to the channels 143, 145. The channels 143 extend substantially radially between the cavity 238 and the shafts 116 for the purpose of supplying them with oil. The channels 145 may extend substantially radially between the cavity 238 and nozzle mounting ports 262 or channels 145a, 145b such as those described above in relation to Figures 3 to 5.

[0082] The annular cavity 238 is axially delimited by two lateral annular walls 240, 242, respectively called first wall 240 and second wall 242.

[0083] The annular cavity 238 is further delimited radially by an external peripheral wall 246. The inner periphery of the cavity 238 is open. The channels 143, 145 extend radially outwards from the external wall 246 and open into the cavity 238 through their radially internal ends. The radially external ends of the channels 143 are connected to lubrication chambers 250 which are distributed around the axis A. These chambers 250 are formed in the aforementioned end caps 260 and are therefore intended to supply oil to the internal cavities of the axes 116.

[0084] Each chamber 250 has an axial end 250a which is open and an opposite axial end 250b which is closed by a bottom 252 and which includes an orifice 254 for fluidic communication of the chamber 250 with the radially external end of the corresponding first pipe 143.

[0085] The distinctive feature of the wheel 230 according to the invention is that it includes strainers 256 for filtering the oil which circulates in the first pipes 143.

[0086] The impeller 230 further includes particle evacuation holes 258. These holes 258 are located upstream of the strainers 256 with respect to the oil flow in the pipes 143, and these holes 258 extend between the pipes 143 and the outside of the impeller 230 in order to evacuate particles and prevent them from clogging the strainers 256.

[0087] In the embodiments of figures 6, 7 and 8a-8c, the strainers 256 are mounted in the aforementioned orifices 254 for fluidic communication of the chambers 250 with the radially external ends of the first pipes 143.

[0088] In the embodiments of figures 6, 7 and 8a-8c, the strainers 256 are oriented parallel to axis A and allow the oil to pass in directions parallel to axis A (see arrow).

[0089] In the embodiment of figures 6 and 7, the holes 258 extend radially with respect to axis A.

[0090] In the embodiment of figures 8a and 9, the holes 258 extend parallel to axis A.

[0091] In the embodiment of figures 8b and 8c, the holes 258 are inclined with respect to axis A.

[0092] In the embodiment shown in Figure 9, the strainers 256 are mounted in the first channels 143, specifically at their radially external ends. The strainers 256 are oriented radially with respect to axis A and allow oil to pass through in radial directions with respect to axis A.

[0093] The holes 258 are preferably formed on the outer periphery of the wheel 230 and / or preferably open at the radially external ends of the first pipes 143.

[0094] In the embodiments shown in Figures 6, 7, and 8a-8c, the radially external ends of the first channels 143 of the impeller 230 are plugged by the main body 264 of the impeller, which is formed in one piece. In the variant shown in Figure 9, the first channels 143 are plugged at their radially external ends by plugs 266 attached to and fixed onto the body 264 of the impeller. The plugs 266 are oriented radially with respect to axis A and are aligned with the strainers 256. It is understood that the receiving orifices of the plugs 266 can be used for mounting the strainers 256 in the channels 143.

[0095] In the case of the other embodiments of figures 6 to 8c, the strainers 256 can be mounted in the orifices 254 through the open axial end 250a of each of the chambers 250.

[0096] As in figures 3 to 5, the wheel 230 may also include second channels 145 for lubricating the teeth and gears of the reducer.

[0097] The second pipes 145 may have a radial dimension smaller than that of the first pipes 143.

[0098] Each of the strainers 256 may include a mounting portion and a filtration portion projecting longitudinally from said mounting portion, said mounting portion being received in one of said orifices 254.

[0099] The filtration portion is preferably located upstream of the assembly portion with respect to the oil circulation.

[0100] The filtration portion may include a curved filter wall with its convexity facing away from the mounting portion. The filtration portion may extend at least partially into one of the first 143 pipes.

[0101] Each of the bores 258 can open opposite the filtration portion of one of the said strainers 256. Each of the pipes 143 can have a blind terminal section extending beyond the junction between the pipe and the corresponding chamber 250.

[0102] The holes 258 may have a diameter that is at least 25% smaller than the diameter of the strainers 256.

Claims

DEMANDS 1. Lubrication impeller (230) for a turbomachine speed reducer (110), in particular for aircraft, said impeller (230) being intended to be rotated about an axis (A) and having a generally annular shape about said axis (A), the impeller comprising: - at its inner periphery an annular oil-receiving cavity (238) extending around said axis (A) and opening radially inwards, and - of the first oil passage channels (143) which extend radially with respect to said axis (A) and whose radially internal ends are connected to said cavity (238) for the purpose of passing oil by centrifugation from the cavity (238) into the first channels (143), - lubrication chambers (250) which are distributed around the axis (A) and which are connected respectively to the radially external ends of the first pipes (143), each of these chambers (250) having an axial end (250a) which is open and an opposite axial end (250b) which is closed by a bottom (252) and which includes an orifice (254) for fluidic communication of the chamber (250) with the radially external end of the corresponding first pipe (143), characterized in that the impeller (230) includes strainers (256) for filtering the oil which flows in the first pipes (143), as well as perforations (258) for particle evacuation, these perforations (258) being located upstream of the strainers (256) with respect to the flow of the oil in the pipes (143),and these perforations (258) extending between the pipes (143) and the outside of the impeller (230) in order to evacuate particles and prevent them from clogging the strainers (256).

2. Impeller (230) according to claim 1, in which the strainers (256) are mounted in the aforementioned orifices (254) for fluidic communication of the chambers (250) with the radially external ends of the first pipes (143).

3. Spinning wheel (230) according to claim 1 or 2, in which the strainers (256) are oriented parallel to the axis (A).

4. Wheel (230) according to claim 2 or 3, in which the holes (258) extend radially with respect to said axis (A).

5. Wheel (230) according to claim 2 or 3, in which the holes (258) extend parallel to said axis (A).

6. Wheel (230) according to claim 2 or 3, in which the holes (258) are inclined with respect to said axis (A).

7. Spinning wheel (230) according to claim 1, in which the strainers (256) are mounted in the first pipes (143).

8. Wheel (230) according to claim 1 or 7, in which the strainers (256) are oriented radially with respect to the axis (A).

9. Wheel (230) according to claim 7 or 8, in which the holes (258) extend parallel to said axis (A).

10. Wheel (230) according to claim 7 or 8, in which the holes (258) are inclined with respect to said axis (A).

11. Wheel (230) according to any one of claims 2 to 10, wherein the bores (258) are formed at the outer periphery of the wheel (230) and / or open out at the radially external ends of the first channels (143).

12. Wheel (230) according to any one of the preceding claims, wherein the first channels (143) are plugged at their radially external ends by attached plugs (266).

13. A wheel (230) according to any one of the preceding claims, wherein it comprises second oil passage channels (145) extending radially from said axis (A) and whose radially internal ends are connected to said cavity (238) for the purpose of passing oil by centrifugation from the cavity (238) into the second channels (145), the second channels (145) having a radial dimension smaller than that of the first channels (143).

14. Speed ​​reducer (110) for a turbomachine (100), said reducer (110) comprising a sun (111) movable in rotation about an axis (A), a ring (114) which extends around the axis (A) and the sun (111), and satellites (112) which are located between the sun (111) and the ring (114) and meshed with the sun (111) and the ring (114), the satellites (112) being carried by a satellite carrier (113) which is centered on the axis (A) and which is movable in rotation about this axis (A), in which a wheel (230) according to one of the preceding claims is fixed coaxially to the satellite carrier (113) for the purpose of lubricating the satellites (112) via said lubrication chambers (250).

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