LUBRICATION IMPELLER FOR A TURBOMACHINE SPEED REDUCER

Abstract

Lubrication impeller (230) for a turbomachine speed reducer (110), comprising: - an annular oil passage cavity (238) extending around said axis (A), - an annular feed port (248) for said cavity (238), and - oil passages (143, 145) for centrifugally conveying oil from the cavity (238) into the passages (143, 145), and - a frustoconical oil collection rim (300) at the level of said port (248), the impeller (230) being formed by the assembly of at least two parts. Figure for the abbreviation: Figure 8

Description

Title of the invention: LUBRICATION WHEEL FOR A TURBOMACHINE SPEED REDUCER Technical field of the invention

[0001] The present invention relates in particular to a lubrication wheel for a turbomachine speed reducer, in particular for aircraft, as well as to a reducer and a turbomachine comprising such a wheel. Technical background

[0002] The prior art in this field includes in particular the documents FR-Al-3 036 763, FR-A1-3 047 279, FR-A1-3 041 054, FR-A1-3 065 773, W0-A1-2015 / 008000, and WO-A1-2018 / 185186.

[0003] The role of a mechanical reducer is to modify the speed and torque ratio between the input shaft and the output shaft of a mechanical system.

[0004] The new generations of double-flow turbomachinery, in particular those with a very high bypass ratio, include a mechanical reducer to drive a shaft of a blower also called a "fan".

[0005] Typically, the purpose of the reducer 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.

[0006] Such a reduction gear comprises a central pinion, called the sun gear, a ring gear, and pinions called planet gears, which mesh between the sun gear and the ring gear. The planet gears are held by a frame called a planet carrier. The sun gear, ring gear, and planet carrier are planetary gears because their axes of revolution coincide with 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 planetary gears. These axes are parallel to the longitudinal axis.

[0007] Several gearbox architectures exist. In the state of the art of turbofan engines, gearboxes are of the planetary or epicyclic type. In other similar applications, there are so-called differential or compound architectures. - 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. - 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. - On a differential gearbox, no element is fixed in rotation. The ring rotates in the opposite direction to the solar and satellite carrier.

[0008] Reducers can be composed of one or more meshing stages. This meshing is achieved in various ways such as by contact, by friction or by magnetic fields.

[0009] There are several types of contact meshing such as with straight, helical or chevron teeth.

[0010] There are several lubrication solutions for such a reducer.

[0011] Figure 1 illustrates a satellite carrier 10 as described in French patent application FR-A1-3 036 763. 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.

[0012] In the case shown, 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.

[0013] 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.

[0014] Lubricant jets, carried by a stator of the reducer or turbomachine, are arranged radially inside the impeller (they are not shown in [Fig.1]), and project lubricant radially outwards directly into the groove 24 of the impeller, to supply the lubrication means.

[0015] The lubricant is delivered to the nozzles by a pump in a turbomachine lubrication unit, which delivers a predetermined flow rate of lubricant to the nozzles. With the current technology described above, the lubricant projected into the nozzle throat is conveyed to the lubrication means solely by centrifugal force.

[0016] The wheel therefore distributes pressurized oil into the reducer using the centrifugal forces generated during operation.

[0017] In document FR-A-3 103 241, the wheel includes on its inner periphery an annular cavity which is supplied with oil by jets which project oil axially in the cavity through an annular light in the impeller. The cavity is in fluidic communication with radial channels for the centrifugal delivery of oil to the elements to be lubricated in the reducer.

[0018] This application focuses more specifically on this latter technology and proposes an improvement that notably facilitates its manufacture. The spinning wheel has a relatively complex internal periphery that is difficult to produce by casting. One solution could be to produce it by additive manufacturing, but this solution is expensive and difficult to industrialize.

[0019] Furthermore, when the rotational speed of the impeller is low, the centrifugal forces to which the oil is subjected during operation are weak, and therefore the oil can flow slowly through the radial channels of the impeller. If the oil flow rate supplied by the nozzles exceeds the oil flow rate in the channels due to centrifugal force, oil accumulates in the cavity, the treatment of which can be modified to optimize lubrication.

[0020] The present invention proposes a solution to at least some of the problems mentioned above, which is simple, effective and economical. Summary of the invention

[0021] The invention provides a lubrication wheel for a turbomachine speed reducer, particularly for aircraft, said wheel being intended to be rotated about an axis and having a generally annular shape about said axis, the wheel comprising:

[0022] - at its inner periphery an annular oil passage cavity which extends around said axis,

[0023] - at its inner periphery an annular oil supply light which extends around said axis and which opens axially into said cavity for the purpose of supplying it with oil, and

[0024] - 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 pipes,

[0025] characterized in that the internal periphery of the wheel has a frustoconical rim for collecting oil at the level of said light, and in that this frustoconical rim extends around said axis and is formed by a first annular piece attached and fixed axially in an annular body which defines at least a part of the cavity and the channels.

[0026] The frustoconical rim is configured to guide and accommodate oil, while also retaining oil, particularly when the oil flow rate feeding the impeller exceeds the oil flow rate through its channels. The rim The rim can be axially projecting on the upstream side of the oil supply relative to the light. It can also be radially projecting relative to the inner periphery of the light and cavity. The rim design improves oil supply but may require an unusual impeller design, particularly for managing assemblies and seals. Furthermore, the impeller is formed by assembling at least one annular part and an annular body, the latter incorporating the frustoconical rim. This simplifies impeller manufacturing and allows for impeller fabrication methods other than additive manufacturing.

[0027] The spinning wheel according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0028] — said frustoconical element is a surface or formed by a surface;

[0029] — said frustoconical element is formed by inclined edges of fins; these fins whose function is to ensure the oil circulates around the shaft; - said cavity includes at its internal periphery a frustoconical element which extends around said axis and of which a longitudinal end of smaller diameter is connected to a longitudinal end of smaller diameter of said frustoconical rim; - said frustoconical element is formed by said body or by said first piece; - said cavity is axially delimited by two annular lateral walls, the first of these walls having its internal periphery which internally delimits said light; this first wall can be considered as a front closing wall of the cavity, insofar as it is located on the side of the oil supply; - said first wall is located axially between the frustoconical element and the frustoconical rim; - said first wall is formed by said body or by said first piece or by a second annular piece added and fixed axially on said body; - when the first wall is formed by said first piece, the first wall and the first piece are connected together by an annular row of connecting fingers which radially cross the cavity and / or the light; - a second of the lateral walls has its internal periphery which is connected to a longitudinal end of greater diameter of said frustoconical element; this second wall can be considered as an internal dorsal wall of the cavity, insofar as it is located on the side opposite to the oil supply; - said first part includes a cylindrical centering rim which includes an external cylindrical surface capable of cooperating by centering with an internal cylindrical surface of said body; - said cylindrical surfaces are located on the inner periphery of the spinning wheel; - at least one sealing O-ring is mounted in an annular groove of one of the cylindrical surfaces to cooperate in sealing with the other of the cylindrical surfaces; - said first part is fixed to the body by welding or screwing; - the light has an internal diameter that is greater than the external diameter of the frustoconical rim; - the internal diameter of the lumen is less than an external diameter of the frustoconical element;

[0030] — at least some of the pipes communicate with axial channels of oil passage and are plugged at their radially external ends by said body or by added plugs;

[0031] — the rim flares axially on the side opposite the cavity;

[0032] — the rim has a free end of larger diameter which is located axially from the opposite side of the cavity.

[0033] 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 / or the meshings.

[0034] The present invention also relates to a turbomachine, in particular for aircraft, comprising a reducer as described above and at least one oil nozzle which is configured to project a jet of oil into said cavity, passing axially through said light and radially outside the frustoconical rim. Brief description of the figures

[0035] 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:

[0036] [Fig-1] [Fig.1] is a schematic perspective view of a satellite carrier of the previous technique,

[0037] [Fig.2] Fig.2 schematically represents an axial section of a turbomachine using the invention;

[0038] [Fig.3] Fig.3 presents a detailed cross-sectional view of an epicyclic gear reducer;

[0039] [Fig.4] The [Fig.4] is an exploded, perspective view of the reducer of the [Fig.3];

[0040] [Fig. 5] Fig. 5 shows a schematic cross-section of a gear of the reducer of the [Fig.3];

[0041] [Fig.6] [Fig.6] is a schematic axial cross-sectional view of a lubrication wheel according to a first embodiment of the invention;

[0042] [Fig.7] [Fig.7] is a schematic axial cross-sectional view of a lubrication wheel according to a second embodiment of the invention;

[0043] [Fig.8] [Fig.8] is a schematic axial cross-sectional view of a lubrication wheel according to a third embodiment of the invention;

[0044] [Fig.9] [Fig.9] is a schematic axial cross-sectional view of a lubrication wheel according to a fourth embodiment of the invention. Detailed description of the invention

[0045] The [Fig. 1] has been described above and represents the prior art to the present invention.

[0046] Figures 2 to 5 illustrate the prior art as described in document FR-A1-3 041 054.

[0047] Fig. 1 shows a turbomachine 100 comprising, in a conventional manner, a fan propeller S, a low-pressure compressor 101a, a high-pressure compressor 101b, a high-pressure turbine 101e, a low-pressure turbine 101e, and an exhaust nozzle 101h. The high-pressure compressor 101b and the high-pressure turbine 101e 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.

[0048] The blower propeller S is driven by a blower shaft 104 which is coupled to the BP shaft 103 by means of an epicyclic gear reducer 110 represented here schematically.

[0049] The reducer 110 is positioned in the upstream part of the turbomachine. In this application, the terms "upstream" and "downstream" refer to the gas flow in the turbomachine.

[0050] A fixed structure schematically comprising, here, an upstream part 105a and a downstream part 105b is arranged to form an enclosure El surrounding the reducer 110. This enclosure El is here closed upstream by seals at the level of a bearing 106a allowing passage of the blower shaft 104, and downstream by seals at the level of the passage 106b of the BP shaft 103.

[0051] With reference to Figures 2 and 3, the reducer is enclosed in a ring 114 which is fixed by means of a support housing 120 to the fixed structure 105a, 105b with flexible means 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 of them can be found, for example, in document FR-A1-2 987 416.

[0052] The reducer 110 of the example considered engages on the one hand with the BP shaft 103 via splines 107 which drive a planetary gear pinion, called a solar 111, and on the other hand with the blower shaft 104 which is attached to a planet carrier 113. Conventionally, the solar 111, whose axis of rotation A coincides with that of the turbomachine, drives a series of planet gears 112, which are regularly distributed around the circumference of the reducer 110. The number of planets 112 is generally defined between three and six. The satellite 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, via the support housing 120. Each of the satellites 112 rotates freely around a satellite shaft 116 connected to the planet carrier 113, by means of a bearing which may be plain, as shown in the [Fig.3], or a rolling element bearing (ball or roller bearings).

[0053] The rotation of the satellites 112 around their satellite axis 116, due to the cooperation of their pinions with the teeth of the crown 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.

[0054] 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, which extend axially from the downstream end of the fan shaft 104 and engage in bores 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. Closing sleeves 119, at the ends of the planet shafts 116, allow this housing to be closed at the planet bearings 112.

[0055] Fig. 3, together with Fig. 4, shows the delivery of the oil to the reducer 110 and its path within it. Arrows in Fig. 3 show the path followed by the oil from, in this example, a buffer tank 131 connected to the fixed structure of the turbomachine, up to the gears and bearings to be lubricated. The lubrication system schematically comprises three parts which will be described successively below, a first part linked to the fixed structure and delivering the oil to the rotating parts of the reducer 110, a rotating wheel with the planet carrier 113 receiving this oil, and oil distribution circuits supplied with oil by the wheel to convey it to the places to be lubricated.

[0056] The first part comprises 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 may be interposed next to the reduction gear 110 on the line, preferably in its upper part so that the oil can flow towards the center of the reduction gear 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 column of oil located above it. The nozzle 133 is positioned here radially inside the planet carrier 113 relative to axis A and the jet 134 is oriented with a radial component directed outwards from the reducer 110.

[0057] 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.

[0058] 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. In the example shown, 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.

[0059] 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 rotated 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.

[0060] The internal radial edges 140a, 140b of the side walls 139a, 139b are substantially circular. Their radius RI 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 RI 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.

[0061] 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.

[0062] 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 ([Fig.3]). .

[0063] The second series of oil distribution circuits comprises secondary channels 145 which run from the openings 142b in the bottom of the cups 137b of the second series of cups 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 hand. 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 drawn, from the middle of the cylinder to its periphery, to lubricate the gear over its entire width.

[0064] 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 cups 137a of the first series, which correspond to them, is greater than that of the cups 137b of 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 essentially reflects this ratio.

[0065] 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 be different. Similarly, the number of sets of cups with similar circumferential extensions may be different, 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, an alternative embodiment of the oil recovery wheel is conceivable with three sets of cups of different circumferential extensions.

[0066] Figures 6 to 9 illustrate several embodiments of a 230 spinning wheel according to the invention.

[0067] The wheel 230 includes features described above and designated by the same reference numerals in Figures 3 to 5. These include, in particular, the pipes 143 and the pipes 145

[0068] The spinning wheel 230 has a general annular shape around the aforementioned axis A which is not visible in figures 6 to 9.

[0069] The wheel 230 includes means for supporting the axes 116 of rotation of the satellites of the reducer, these support means being formed by cylindrical ends 260 engaged in internal cavities of these axes 116. The wheel 230 further includes means for lubricating the teeth of the satellites and the bearings of the axes 116, which include in particular the aforementioned channels 143, 145.

[0070] 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 or channels 145a, 145b such as those described above in relation to Figures 3 to 5.

[0071] The annular cavity 238 is axially delimited by two lateral annular walls 240, 242, respectively called first wall 240 and second wall 242.

[0072] The annular cavity 238 is further delimited radially by an internal peripheral wall 246 and by an external peripheral wall 244.

[0073] The wall 240 extends radially between the walls 244, 246. The radially internal ends of the pipes 143, 145 open onto the wall 244.

[0074] Unlike the prior art where the impeller 130 is fed radially for centrifugal accumulation, the cavity 238 of the impeller 230 is here closed radially internally by the wall 246. The wall 246 is connected to the wall 240 and extends radially inside the wall 242, at a radial distance from it. The inner periphery of the wall 242 and the wall 246 thus define between them an annular opening 248 for supplying lubricating oil to the cavity 238.

[0075] The wall 240 can be considered a front wall insofar as it is located on the side of the oil supply of the cavity 238. The wall 242 can be considered a back wall insofar as it is located on the opposite side of the oil supply of the cavity 238.

[0076] The cavity 238 may include an internal frustoconical element 254 which is located opposite the lumen 248.

[0077] The frustoconical element 254 can be a surface or can be formed by a surface. The frustoconical element 254 is then a frustoconical surface.

[0078] Alternatively, the frustoconical element 254 can be formed by inclined edges of fins 254a.

[0079] Each of the fins 254a has a general triangular shape and includes a first side connected to the wall 242, a second side connected to the wall 246, and a third side which is free and inclined extending from the wall 242 to the wall 246.

[0080] In the case where the cavity 238 does not include a frustoconical element 254, it is understood that the internal periphery of the wall 242 would be directly connected to the wall 246.

[0081] The element 254 can have an axial dimension L1 representing at least 25% or even 50% of the axial dimension of the wall 246 and can even represent more than 100% of the axial dimension of the wall 246 insofar as the element 254 can extend to the outside of the cavity 238 through the light 248.

[0082] The double line in figures 6 to 9 illustrates an oil jet 258 projected by a nozzle attached to a stator of the turbomachine.

[0083] The nozzle can be slightly inclined with respect to axis A to project the oil jet 258 into the cavity 238, through the opening 248 and passing around a frustoconical rim 300 on the inner periphery of the impeller 230. This oil jet 258 impacts the element 254 and / or the wall 246. When the element 254 is formed by fins 254a, the oil jet 258 impacts the wall 246 and the oil is then driven into rotation by the fins 254a in preparation for centrifugation.

[0084] The rim 300 ensures oil collection at the level of the light 248 by forming an annular basin 302 with a U or V cross-section.

[0085] The rim 300 extends around the axis A and can be formed by a first annular piece 304 which is attached and fixed axially in an annular body 306 which defines at least a part of the cavity 238 and the conduits 143, 145.

[0086] In the drawings, it is noted that the frustoconical element 254 has its longitudinal end of smaller diameter which is connected to the longitudinal end of smaller diameter of the frustoconical rim 300. The longitudinal end of larger diameter of the rim 300 is free and located on the opposite side to the cavity 238.

[0087] The wall 242 is preferably located axially between the frustoconical element 254 and the frustoconical rim 300. The connection between the aforementioned ends of the frustoconical element 254 and the rim 300 is thus preferably surrounded by the wall 242 and delimits the aforementioned light 248 with the internal periphery of this wall 242.

[0088] The light 248 preferably has an internal diameter DI which is greater than the external diameter D2 of the frustoconical rim 300.

[0089] The frustoconical rim 300 can have an axial dimension L2 representing between 10 and 50%, and for example between 20 and 30%, of the axial dimension L1 of the element 254.

[0090] The internal diameter DI of the light 248 is preferably less than the external diameter D3 of the frustoconical element 254, as seen in Figures 7 and 8. Alternatively, the internal diameter DI of the light 248 may be greater than or equal to the external diameter D3 of the frustoconical element 254, as seen in [Fig. 6].

[0091] In the embodiment of Figures 6 and 7, the frustoconical element 254 is formed by the first part 304. In the embodiment of [Fig.8], the frustoconical element 254 is formed by the body 306.

[0092] The wall 242 can be formed by the body 306, as is the case in [Fig.6], or by the first piece 304, as is the case in [Fig.9], or by a second annular piece 308 attached and fixed axially on the body 306, as is the case in figures 6 and 8. In the latter, the wheel 230 is formed by the assembly of three annular elements, the body 306 and the two pieces 304, 308.

[0093] Part 304 or parts 304, 308 can / are fixed to body 306 by welding or screwing.

[0094] In the figures, it can be seen that the channels 143 communicate with axial oil passage channels 314. In Figures 6, 7, and 9, the channels 143 are plugged at their radially external ends by the body 306 itself. In [Fig. 8], the channels 143 are plugged at their radially external ends by plugs 316 attached in a radial direction. This latter variant allows the construction of the 143 pipes by drilling the body 306, radially from the outside.

[0095] In [Fig.9] where the first wall 242 is formed by the body 304, the first wall 242 is further covered axially by a sealing ferrule associated with the body 304. Connecting fingers associate this ferrule with the frustoconical element 254, and in particular with the free edges of the aforementioned fins 254a.

[0096] The number of fingers is equal to the number of fins 254a and each finger is connected to a fin 254a. The fins 254a and the fingers can extend in radial planes passing through the X axis.

[0097] The fingers form an annular row around the X axis and radially cross the cavity 238 and / or the lumen 248.

[0098] To facilitate assembly, said first part 304 advantageously includes a cylindrical centering rim 310 which includes an external cylindrical surface 310a suitable for cooperating by centering with an internal cylindrical surface of said body 306a.

[0099] The cylindrical surfaces 310a, 306a are located on the inner periphery of the wheel 230 in the example shown.

[0100] At least one sealing O-ring can be mounted in an annular groove of one of the cylindrical surfaces, such as surface 310a, to cooperate in sealing with the other of the cylindrical surfaces, such as surface 306a.

[0101] At least one sealing O-ring can be mounted between the ferrule and the wall 242 as illustrated in [Fig.9].

[0102] The gains provided by the lubrication wheel according to the invention are in particular: - a reduced radial footprint of the technology, - an increase in oil pressure in the wheel, - better oil collection, - easier manufacturing, at isoperformance and footprint, etc.

Claims

Demands

1. A lubrication impeller (230) for a turbomachine speed reducer (110), particularly for aircraft, said impeller (230) being designed to rotate about an axis (A) and having a generally annular shape about said axis (A), the impeller comprising: - at its inner periphery an annular oil passage cavity (238) extending about said axis (A), - at its inner periphery an annular oil supply port (248) extending about said axis (A) and opening axially into said cavity (238) for the purpose of supplying it with oil, and - oil passage channels (143, 145) extending radially from said axis (A) and having radially internal ends connected to said cavity (238) for the purpose of centrifugally transferring oil from the cavity (238) into the pipes (143, 145),characterized in that the inner periphery of the wheel (230) has a frustoconical rim (300) for collecting oil at the level of said aperture (248), and in that this frustoconical rim (300) extends around said axis (A) and is formed by a first annular piece (304) attached and fixed axially in an annular body (306) which defines at least a part of the cavity (242) and the channels (143, 145).

2. A wheel (230) according to claim 1, in which said cavity (238) comprises at its inner periphery a frustoconical element (254) which extends around said axis (A) and of which a longitudinal end of smaller diameter is connected to a longitudinal end of smaller diameter of said frustoconical rim (300).

3. Spinning wheel (230) according to claim 2, wherein the frustoconical element (254) is formed by said body (306) or by said first piece (304).

4. Spinning wheel (230) according to any one of the preceding claims, in which said cavity (238) is axially delimited by two annular lateral walls (240, 242), a first (242) of these walls having its inner periphery which internally delimits said light (248).

5. Spinning wheel (230) according to claim 4 depending on claim 2 or 3, wherein said first wall (242) is located axially between the frustoconical element (254) and the frustoconical rim (300).

6. Spinning wheel (230) according to claim 4 or 5, wherein said first wall (242) is formed by said body (306) or by said first piece (304) or by a second annular piece (308) attached and fixed axially on said body (306).

7. Spinning wheel (230) according to claim 6, wherein, when the first wall (242) is formed by said first piece (304), the first wall (242) and the first piece (304) are connected together by an annular row of connecting fingers which radially pass through the cavity (238) and / or the light (248).

8. Spinning wheel (230) according to any one of claims 4 to 7 depending on claim 2 or 3, wherein a second of the side walls (240) has its inner periphery which is connected to a longitudinal end of larger diameter of said frustoconical element (254).

9. Spinning wheel (230) according to any one of the preceding claims, wherein said first part (304) comprises a cylindrical centering rim (310) which includes an external cylindrical surface (310a) capable of cooperating by centering with an internal cylindrical surface of said body (306a).

10. Spinning wheel (230) according to claim 9, wherein said cylindrical surfaces (310a, 306a) are located at the inner periphery of the spinning wheel (230).

11. Wheel (230) according to claim 9, wherein at least one sealing O-ring is mounted in an annular groove of one of the cylindrical surfaces (310a) to cooperate in sealing with the other of the cylindrical surfaces (306a).

12. Spinning wheel (230) according to any one of the preceding claims, wherein said first part (304) is fixed to the body (306) by welding or screwing.

13. Spinning wheel (230) according to any one of the preceding claims, wherein the light (248) has an internal diameter (Dl) which is greater than the external diameter (D2) of the frustoconical rim (300).

14. Wheel (230) according to claim 13 depending on claim 2 or 3, wherein the internal diameter (Dl) of the opening (248) is less than an external diameter (D3) of said frustoconical element (254).

15. 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 about 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) and / or the meshes.

16. Turbomachine (100), in particular aircraft, comprising a reducer (110) according to the preceding claim and at least one oil nozzle which is configured to project an oil jet (258) into said cavity (238), through said light (248) axially and through radially outside the frustoconical rim (300).

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