FAN MODULE EQUIPPED WITH AN OIL TRANSFER DEVICE

Description

Technical field of the invention

[0001] The present invention relates to a blower module for an aircraft turbomachine, this module comprising an oil transfer device. Technical background

[0002] The technical background includes documents EP-A1-3179044, US-A1-2004 / 037483, EP-A1-3 138 771, WO-A2-2013 / 011225, GB-A-824 332 and US-B1-8,484,942.

[0003] An aircraft turbomachine classically comprises a gas generator including, from upstream to downstream according to the direction of gas flow in operation, at least one compressor, an annular combustion chamber and at least one turbine.

[0004] The gases entering the gas generator are compressed in the compressor(s), then mixed with fuel and burned in the combustion chamber. The combustion gases flow and expand in the turbine(s) to drive its rotor(s).

[0005] In the case of a twin-body turbomachine, respectively low pressure and high pressure, the rotor of the high-pressure turbine is connected by a high-pressure shaft to the rotor of the high-pressure compressor, and the rotor of the low-pressure turbine is connected by a low-pressure shaft to the rotor of the low-pressure compressor.

[0006] The turbomachine can be equipped with one or more propellers, shrouded or unshrouded. In the case of a shrouded propeller located upstream of the gas generator, this propeller is called a fan and is driven by the low-pressure shaft of the gas generator.

[0007] The blower generates a flow of gas in operation which is divided into a first flow, called the primary flow which flows into the gas generator as mentioned above, and a second flow, called the secondary flow, which flows around the gas generator.

[0008] The dilution ratio, which is the ratio between the secondary flow rate and the primary flow rate, is increasingly important in modern turbomachinery, resulting in an increase in the diameter of the blower and a decrease in the diameter of the gas generator.

[0009] To limit the rotational speed of the fan, particularly in turbomachinery with high bypass ratios, it is common practice to drive the fan via a reduction gear, generally of the epicyclic or planetary type. The low-pressure shaft thus drives the fan through the reduction gear.

[0010] A fan, or a propeller in general, may include variable-pitch blades, meaning that each blade has an orientation around a radial axis that can be precisely adjusted. The blades are supported by a polygonal ring-shaped hub and are rotated around these axes by means of a common hydraulic actuator mounted inside the hub. This actuator is oil-supplied and can be positioned in a rotating frame of reference when it is rotationally fixed to the hub and the fan.

[0011] The turbomachine includes a lubrication system comprising an oil reservoir and a pump, which is generally located in a fixed frame. It follows, therefore, that the oil supply to the actuator from the lubrication system must be achieved via an oil transfer device from a fixed frame to a rotating frame. Such a device is commonly called an OTB, an acronym for the Anglo-Saxon term. Oil Transfer Bearing.

[0012] This type of device can be mounted in a turbomachine with a fan of the aforementioned type to supply oil to the actuator and also to supply lubricating oil to the gearbox. This type of device can also be mounted in another type of turbomachine, such as, for example, a turbomachine equipped with an unfaired, variable-pitch propeller, of the turboprop type.

[0013] In current technology, an oil transfer device comprises a stator ring having an internal cylindrical surface and internal oil channels, each opening onto this internal cylindrical surface. These channels are connected by lines to the aforementioned lubrication system.

[0014] The device further includes a shaft engaged in the ring and free to rotate about an axis inside the ring. The shaft has an external cylindrical surface extending inside the internal cylindrical surface of the ring, and internal oil channels, each opening onto this external cylindrical surface. These channels are connected by lines to the actuator for its oil supply.

[0015] In current technology, the outer cylindrical surface of the shaft has annular grooves for housing annular sealing segments. These segments are designed to move within the grooves and are configured to bear radially against the inner surface of the ring to limit and control oil leakage. The outlets of the aforementioned channels are located between two adjacent segments, thus ensuring that a maximum amount of oil supplied by each channel on the ring feeds a corresponding channel on the shaft. The number of segments is twice the number of channels. Document GB-A-824,332 describes an oil transfer device of this type. However, this technology is unsatisfactory for several reasons. Manufacturing and assembly tolerances make it difficult to precisely control these leakages. The device comprises numerous parts, which complicates assembly.The manufacturing and assembly of such a device are therefore relatively lengthy and expensive. Furthermore, the greater the number of channels in the device and the greater the number of sealing segments, the larger the axial dimension and thus the axial footprint of the device must be to accommodate these various segments. An oil transfer device can be complex to integrate into a turbomachine due to its size. Finally, the lifespan of such a device is generally limited due to potential misalignments between the shaft and the ring during operation and the wear of the sealing segments, which can be exacerbated by these misalignments as well as by the shaft's rotational speed. The larger the diameter of the device, the greater the peripheral speed of the shaft and the wear on the segments.

[0016] Another drawback of current technology is that their installation and assembly in a turbomachine is lengthy and complex. The device can be mounted upstream or downstream of the gearbox. However, the preferred location is downstream for several reasons.

[0017] Deploying the device upstream of the gearbox necessitates large-diameter rotary joints, which are sources of leakage and heat dissipation. Furthermore, the blower is generally positioned as close as possible to the turbomachine's inlet casing to minimize its overhang. Finally, the turbomachine's length must be as short as possible to minimize nacelle drag. Therefore, integrating the device downstream of the rectifier is preferable.

[0018] In this case, the oil supply to the ring's oil lines would be provided by pipes passing through the inlet casing and connected to these lines radially. Upstream access to the device would be impossible during maintenance. Attaching the device's ring to a turbomachine stator, as well as removing the ring from this stator, would have to be done from downstream of the turbomachine and the lubrication chamber containing the gearbox. This would necessitate dismantling the turbomachine's low-pressure compressor and the equipment mounted in that area, a lengthy and tedious process.

[0019] The invention thus proposes an improved oil transfer device which solves all or part of the problems of the prior art. Summary of the invention

[0020] The invention relates to a fan module for an aircraft turbomachine, this module comprising a fan which includes a fan shaft and variable-pitch fan blades, and an oil transfer device which is configured to ensure oil transfer between a stator and an actuator which is rotationally fixed to the fan shaft and which is configured to control the fan blade pitch, this device comprising: a stator ring comprising an internal cylindrical surface and internal oil channels each opening onto said internal cylindrical surface, and a shaft engaged in said ring and comprising an external cylindrical surface extending inside said internal cylindrical surface, the shaft comprising internal oil channels each opening onto said external cylindrical surface, the shaft further comprising a fastening member configured to be fixed to a rotor of the turbomachine for its rotational drive about an axis, characterized in that it further comprises: a plain bearing located between said internal and external cylindrical surfaces, and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, and in that the ring is mounted with one degree of freedom in the axial direction on the shaft and is immobilized in the circumferential direction aroundThe shaft is connected via first elements carried by the ring and configured to cooperate axially by male-female engagement with second complementary elements carried by the stator. The invention thus proposes an oil transfer device without sealing elements or segments between the opposing cylindrical surfaces of the stator ring and the shaft. Instead, a plain bearing is provided between these surfaces. Rolling bearings are mounted on either side of this plain bearing to ensure the radial thickness of the plain bearing, regardless of the turbomachine speed and the peripheral speed of the transfer device shaft. The rolling bearings are automatically lubricated by the oil leaking from the plain bearing during operation. The rolling bearings also limit oil leakage outside the plain bearing and the device.Rolling bearings also eliminate the risk of misalignment between the ring and the shaft, thus preventing contact and wear. Sealing segments are therefore no longer considered wear parts, resulting in an optimized service life compared to previous designs.

[0021] According to the invention, the device is in the form of a "cartridge" during assembly. In this application, "cartridge" means the assembly formed by the shaft and the ring of a device, which are pre-assembled one inside the other before mounting this assembly in a turbomachine.

[0022] The device is designed to be attached to a turbomachine rotor prior to the rotor and device being mounted to the rest of the turbomachine. This mounting is achieved through axial translation, from upstream to downstream, and is made possible by the "floating" mounting of the ring on the shaft, meaning the ring's axial freedom of movement on the shaft. During mounting, the first elements of the ring engage with the second elements of the stator via a male-female connection, creating a flexible, blind joint that maintains this axial movement but restricts the ring's circumferential movement relative to the shaft. This translation and interaction are sufficient to lock the ring to the turbomachine stator.The ring is thus fixed in rotation around the axis of the turbomachine but can undergo relative micro-displacements in the axial direction with respect to the shaft of the device because the ring is not fixed in the axial direction with respect to the stator.

[0023] The ring is thus connected to the stator with a certain degree of flexibility due to its non-rigid connection. This flexibility helps to limit stresses within the device and the risk of misalignment between the shaft and the ring, thereby ensuring a smooth bearing with a constant radial thickness inside the device.

[0024] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other: The ring includes first fluidic connection ports opening axially, these first ports being connected to the internal channels of the ring and being configured to cooperate by said male-female engagement with the ends of oil supply lines or bushings; these first ports can thus be considered as said first elements or a part thereof, the number of first ports being equal to the number of channels of the ring, the first ports being connected to different channels of the ring; the first ports are situated substantially in the same plane perpendicular to said axis; the ring includes a mounting hole for a temporary pin to prevent the ring from rotating on the shaft, this pin being configured to be engaged in a recess in the aforementioned rotor of the turbomachine during the assembly of the device and then to be removed after this assembly;The orifice has a substantially radial orientation and is formed on the outer periphery of the ring; one of the bearings is a roller bearing and the other is a ball bearing; the ring comprises a first axially oriented indexing member, such as a groove, configured to cooperate by said male-female engagement with a second axially oriented indexing member, such as a finger, carried by said stator of the turbomachine during said assembly; this first member or groove can thus be considered as said first elements or a part thereof; -- the support comprises at least one perforated frustoconical wall; -- a ring is mounted inside the ring and defines said plain bearing with said outer surface of the shaft; -- the bearing rings have identical internal diameters;-- the shrink ring has two cylindrical surfaces extending around each other, including a cylindrical shrink-fit surface on the ring and a cylindrical centering surface on the shaft, -- the shrink ring includes orifices which are located opposite the outlets of the ring's channels, and which cover, for example, annular grooves formed at the level of these outlets and / or the outlets of the shaft's channels, the blower is driven in rotation by a reduction gear, said device being mounted downstream of the reduction gear and being configured to supply oil to the reduction gear as well as the actuator by lines passing axially through the reduction gear, and in particular a planet carrier of the reduction gear; the shaft of the device is fixed to the planet carrier of the reduction gear, and the ring of the device is fixed to an intermediate housing by an annular support which at least partially surrounds the device;a bearing, and in particular a roller bearing, is mounted between the planet carrier and said support; the support includes an annular wall having openings for the passage of oil supply lines to the ring's piping, and preferably also for the temporary passage of a cable connected to a pin for preventing the ring from rotating on the shaft; the support includes an annular wall having second ports configured to cooperate by another male-female engagement with the ends of oil supply lines, these second ports opening radially outwards, and third ports connected to the second ports and configured to cooperate by said male-female engagement with the ends of oil supply bushings, the opposite ends of which are engaged in said first ports of the ring; the support carries said second component;-- The reducer is of the epicyclic type, i.e., with a rotating planet carrier and therefore a stationary rotating ring; -- The device supplies the reducer with lubricating oil, and in particular at least part of its bearings and gears; -- The device is configured to supply the actuator with an oil pressure between 2 and 200 bar, and preferably between 5 and 130 bar; -- The device is configured to supply the reducer with an oil pressure between 2 and 50 bar, and preferably between 5 and 20 bar.

[0025] The present invention also relates to a method for assembling a module as described above, comprising the steps of: a) mounting the ring on the shaft of the device, b) fixing the shaft of the device to the rotor of the turbomachine, c) mounting oil supply lines and / or bushings on said stator of the turbomachine, and d) translational movement of the rotor and the device towards the stator, until the first ports of the device cooperate with said lines or bushings.

[0026] The process according to the invention may comprise one or more of the following steps, taken individually or in combination with each other: The process includes, after step d), a step e) of removing the pin, this pin being connected to a cable which is pulled from outside the turbomachine; the process includes, during step d), the cooperation by engagement of said first and second elements; -- during step d), rollers carried by the planet carrier of the reducer are engaged in an outer ring carried by said support, in order to form a bearing bearing for guiding the planet carrier.

[0027] The invention also relates to an aircraft turbomachine, comprising a module as described above. Brief description of the figures

[0028] 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: [ Fig.1 ] there figure 1is a schematic half-view in axial cross-section of a turbomachine equipped with an oil transfer device, [ Fig. 2 ] there figure 2 is a larger-scale view of a part of the figure 1 , [ Fig.3 ] there figure 3 is a schematic half-view in axial cross-section of a turbomachine equipped with an oil transfer device according to the invention, [ Fig. 4 ] there figure 4 is a larger-scale view of the device of the figure 3 , [ Fig. 5 ] there figure 5 is a view similar to that of the figure 3 and illustrates a step in assembling the device according to a method of the invention, [ Fig. 6 ] there figure 6 is a larger-scale view of the device of the figure 5 , [ Fig. 7 ] there figure 7 is a schematic half-view in axial cross-section of the device of the figure 3 and illustrates a preliminary step of the process according to the invention, and [ Fig. 8 ] there figure 8is another very schematic axial cross-sectional view of the device of the figure 3 , and allows you to see the arrangement around the device of oil supply bushings and screws fixing the shaft of the device. Detailed description of the invention

[0029] There figure 1 shows a turbomachine 10 which includes, in a conventional manner, a blower 12, a low pressure (LP) compressor 14, a high pressure (HP) compressor 16, an annular combustion chamber 18, a high pressure (HP) turbine 20, a low pressure (LP) turbine 22 and an exhaust nozzle 24.

[0030] The rotors of the high-pressure compressor 16 and the high-pressure turbine 20 are connected to each other by a high-pressure shaft 26 and together form a high-pressure (HP) housing which is guided in rotation around the longitudinal axis A of the turbomachine by roller bearings 28, 30. A first bearing 28 is mounted between an upstream end of the shaft 26 and the HP housing and an inter-compressor housing 32 located between the LP compressors 14 and HP compressors 16. A second bearing 30 is mounted between a downstream end of the shaft 26 and the HP housing and an inter-turbine housing 34 located between the LP turbines 22 and HP turbines 20.

[0031] The rotors of the compressor BP 14 and the turbine BP 22 are connected by a low-pressure shaft 36 and together form a low-pressure (LP) unit which is guided in rotation around the longitudinal axis A of the turbomachine by roller bearings 38, 40. At least one bearing 38 is mounted between an upstream end of the shaft 36 of the LP unit and an inlet housing 42 located upstream of the compressor BP 14. Other bearings 40 are mounted between a downstream end of the shaft 36 of the LP unit and an exhaust housing 44 located downstream of the turbine BP 22.

[0032] The blower 12 is driven by a blower shaft 46 which is driven by the BP shaft 36 by means of a reducer 48. This reducer 48 is generally of the planetary or epicyclic type.

[0033] The following description concerns an epicycloidal type reducer, whose planet carrier and sun gear are mobile in rotation, the ring gear of the reducer being fixed in the frame of reference of the motor.

[0034] The gearbox 48 is positioned in the upstream part of the turbomachine. A fixed structure schematically comprising, here, an upstream part 50a and a downstream part 50b which make up the motor or stator housing 50 is arranged to form an enclosure E surrounding the gearbox 48. This enclosure E is closed upstream by a seal 52 at the level of a bearing 54 allowing the passage of the blower shaft 46, and downstream by a seal 55 at the level of the bearing 38 allowing the passage of the LP shaft 36.

[0035] The enclosure E is located inside the inlet casing 42 which is situated between an inlet rectifier blade 56 and the compressor BP 14.

[0036] There figure 2 shows the reducer 48 on a larger scale.

[0037] The reducer 48 includes a solar 48a centered on the axis A and coupled to the shaft BP 36 for example via splines.

[0038] The reducer 48 includes a ring 48b which is also centered on the axis A and fixed to the input housing 42.

[0039] The gearbox 48 includes satellites 48c arranged around axis A and meshed with the sun gear 48a and the ring gear 48b. These satellites 48c are carried by a satellite carrier 48d, which is rotatable around axis A and connected to the blower shaft 46 for its rotational drive. The satellite carrier 48d is guided by bearings 58 and 60 mounted on the input housing 42, these bearings 58 and 60 being located upstream and downstream of the gearbox 48, respectively.

[0040] The blower 12 of the figure 1The system comprises variable-pitch blades 12a and is associated with an actuator 62 that centrally controls the positioning of the blades 12a around their axes B, which are generally radial axes relative to the axis A of the turbomachine. Each blade 12a includes a pivot foot 12b housed in a housing of a polygonal ring-shaped hub 64, and connected by a linkage system 66 to a piston of the actuator 62. The actuator 62 extends along the axis A, and its piston is translationally movable along this axis, for example, from a first position in which the blades 12a are feathered to a second position in which the blades 12a obstruct the airflow through the fan 12.

[0041] The airflow F1 passing through the fan 12 is split into two annular and coaxial flows downstream of the fan by an annular separator 68 that extends around the blade 56. A first airflow, called the primary flow F2, flows in a primary channel, passes through this blade 56, and enters the compressors 14 and 16 to be compressed. This compressed air is then mixed with fuel and burned in the combustion chamber 18. The combustion gases are then expanded in the turbines 20 and 22 to drive their rotors and the LP 36 and HP 26 shafts, and then flow into the nozzle 24.

[0042] A second airflow, called the secondary flow F3, flows in a secondary channel defined internally by an annular engine casing 70 extending longitudinally around the compressors 14, 16, the combustion chamber 18, and the turbines 20, 22, and externally by an annular nacelle casing 72 extending longitudinally around the fan 12 and part of the engine. This nacelle casing 72 is connected to the engine by outlet guide vanes 42a of the inlet casing 42. These guide vanes 42a are structural and are configured to straighten the airflow exiting the fan 12.

[0043] The actuator 62 is hydraulic and operates with a fluid, oil, which comes from a lubrication system generally located in the nacelle or between the compressors 14, 16 and the crankcase 70 (i.e., in the engine) and therefore in a fixed frame of reference of the turbomachine. In contrast, the actuator 62 is located in a rotating frame of reference.

[0044] As can be seen in the figure 2 , the turbomachine 10 includes a device 74 for transferring oil from the fixed reference frame of the engine to the rotating reference frame in which the actuator 62 is located.

[0045] In the example shown, the device 74 is located downstream of the reducer 48 and preferably includes several oil supply routes 76 to supply the actuator 62 but also to lubricate the reducer 48. The dotted line of the figure 2symbolizes one of these paths along its entire course, from the fixed reference point to the actuator 62: crossing the primary vein to the device 74, crossing the reducer 48 (between its satellites or through the axes of these satellites), and path along the satellite carrier and then the blower shaft 46.

[0046] THE figures 3 to 8 illustrate an embodiment of an oil transfer device 174 according to the invention.

[0047] Device 174 includes: a stator ring 180 having an internal cylindrical surface 180a and internal oil channels 180b each opening onto said internal cylindrical surface 180a, and a shaft 182 engaged in the stator ring 180 and movable in rotation about the axis A inside this ring 180, the shaft 182 having an external cylindrical surface 182a extending inside the surface 180a, and internal oil channels 182b each opening onto the surface 182a.

[0048] The pipes 180b are arranged one behind the other along axis A. There are four of them in the example shown. Although the pipes 180b are shown here in the same axial plane, they could be located in different axial planes. This depends in particular on the conduits 192 to which they are connected and the arms 42b through which these conduits pass. In yet another variant, the pipes 180b could have radially external ends located in the same axial plane and ends distributed angularly around axis A and opening onto surface 180a.

[0049] Each of the 180b pipes includes a radially internal end which forms the aforementioned outlet and a radially external end which forms a first port 190 for connection to an oil supply socket 192.

[0050] Port 190 forms a female part and one end of the socket 192 forms a male part engaged in a watertight manner in port 190.

[0051] Port 190 and socket 192 have an axial orientation, therefore socket 192 and port 190 are engaged in each other by axial translation.

[0052] Among the 192 sockets connected to the 180 ring, one is shown at the figure 4 . There figure 8 This shows that the number of sockets 192 is equal to the number of pipes 180b, and therefore there are four of them. These sockets 192 are distributed on the lower half of the ring 180 and the device 174. The sockets 192 are, for example, located at 4 o'clock, 5 o'clock, 7 o'clock and 8 o'clock by analogy with the face of a clock.

[0053] The sockets 192 have their axial ends opposite the ports 190 which are axially engaged in second ports of an annular support 250, as will be described in more detail below.

[0054] In the example shown, the 192 sockets are of the "dog bone" type, meaning they have a general dog bone shape. Each has an elongated shape with enlarged longitudinal ends which here carry sealing O-rings that cooperate with the ports 190.

[0055] The ring 180 has a general cylindrical shape and includes an upstream cylindrical rim 200a and a downstream cylindrical rim 200b. These rims 200a, 200b have identical or similar diameters.

[0056] A ring 204 is fixed inside the ring 180 so as to cover its surface 180a. This ring 204 extends over most of the length of the ring 180 and includes an annular flange 204a radially external at its upstream end, which bears axially against a cylindrical bearing surface of the ring 180. As its name indicates, the ring 204 is shrink-fitted into the ring 180. The shrink-fitting, combined with the support of its flange 204a, secures the ring 204 to the ring 180.

[0057] The ring 204 comprises an annular row of radial orifices 206 at each of the channels 180b. Furthermore, an annular groove 208 is formed on the inner periphery of the ring 180 and at each of the channels 180b, this groove 208 being closed internally by the ring 204. It is therefore understood that each channel 180b supplies a groove 208 and that each groove 208 distributes oil to the orifices 206 of the ring 204.

[0058] The fret 204 includes an external cylindrical shrink-fit surface which is in contact with the internal surface 180a of the ring 180, and an internal cylindrical centering surface intended to be separated by a predetermined radial distance from the external surface 182a of the shaft 182 to define a plain bearing P.

[0059] Shaft 182 does not have a shrink sleeve. This reduces the number of tolerance stacking interfaces. Consequently, the clearances between the rotor and stator are significantly reduced by minimizing the number of interfaces.

[0060] The 182b pipes of the shaft 182 all have a radial orientation and are arranged one behind the other along the axis A. There are four of them in the example shown.

[0061] An annular groove 210 is formed at the outer periphery of the shaft 182 and at the right of each of the pipes 182b.

[0062] Each of the pipes 182b is connected to a conduit 212 which can be integrated into the shaft 182. One of these conduits 212, visible in section in the figures, includes an annular portion 212a which extends around the axis A and along a major part of the length of the shaft 182. The downstream end of this portion 212a is connected to the downstreammost pipe 182b of the shaft, and its upstream end is connected to a radial portion 212b which is formed in an upstream annular rib 214 of the shaft. This rib 214 serves to fix the shaft 182 of the device 174. In the example shown, the shaft 182 of the device 174 is fixed to the planet carrier 48d of the reducer 48. The planet carrier 48d includes a downstream cylindrical rim 48e on the outer periphery of which the bearing 60 is mounted, and on the inner periphery of which the rib 214 is engaged.This rib 214 bears axially upstream on a cylindrical bearing surface of the rim 48e and is held in axial support against this bearing surface by screws 216 screwed from downstream on the internal periphery of the rim 48e.

[0063] There figure 8 allows us to see that the screws 216 are distributed around axis A and between the sockets 192.

[0064] The bearing 60 is here a rolling bearing and includes rollers which are arranged between two rings, respectively internal and external, the internal ring being axially clamped against another cylindrical bearing surface on the external periphery of the rim 48e by a nut 218 screwed from downstream on this periphery.

[0065] The ring 180 includes a mounting hole 199' for a temporary pin 199 to prevent the ring 180 from rotating on the shaft 182. This pin 199 is configured to be engaged in a recess 199" in the aforementioned flange 48e of the turbomachine during the assembly of the device 174 and then removed after this assembly. In the example shown, the hole 199' has a substantially radial orientation and is formed on the outer periphery of the ring 180. The recess 199" is formed by a notch on the free downstream edge of the flange 48e.

[0066] The pin 199 comprises a cylindrical body oriented radially in the mounting position, and connected to a head having a through hole for attaching one end of a cable 201 (cf. figure 6This cable 201 is used by an operator to pull the pin 199, disengage it from the hole 199' and the recess 199" and remove it from the turbomachine. The head is connected to the radially external end of the body when the pin 199 is in the mounting position.

[0067] A first bearing 220 is mounted between the rim 200b of the ring 180 and the downstream end of the shaft 182.

[0068] The bearing 220 is a rolling bearing and comprises rollers arranged between two rings, an inner ring 222 and an outer ring 224. The outer ring 224 is mounted inside the flange 200b and bears axially on a cylindrical surface on the inner periphery of the flange 200b, located upstream. Downstream, the ring 224 is axially retained by a split annular ring 226 engaged in an annular groove on the inner periphery of the flange 200b.

[0069] The inner ring 222 is mounted on the downstream end of the shaft 182 and bears axially on a cylindrical bearing surface of the shaft, located upstream. Downstream, the ring 222 is axially retained by a retaining ring 228 fixed to the outer periphery of the downstream end of the shaft 182.

[0070] A second bearing 230 is mounted between the rim 200a of the ring 180 and the shaft 182.

[0071] The bearing 230 is here a rolling bearing and includes balls which are arranged between two rings, respectively internal 232 and external 234.

[0072] The outer ring 234 is mounted inside the rim 200a and bears axially on a cylindrical bearing surface on the inner periphery of the rim 200a, located downstream. Upstream, the ring 232 is axially retained by a split annular ring 236 engaged in an annular groove on the inner periphery of the rim 200a.

[0073] The inner ring 232 is mounted on a portion of the shaft 182 located between the rib 214 and the channels 182b. This ring 232 bears axially on a cylindrical bearing surface of the shaft 182, located downstream. Upstream, the ring 232 is axially retained by an annular part 182c of the shaft, which includes the rib 214 and is engaged with another part 182d of the shaft, which includes the channels 182b. The part 182c, which includes the rib 214, is axially clamped against the inner ring 232 of the bearing 230 by a nut 260 screwed onto the upstream end of the shaft 182, and in particular onto the part 182d.

[0074] In the example shown, in addition to parts 182c and 182d, the shaft 182 includes another annular part 182e which extends along the entire length of part 182d, inside it, and which defines the conduit 212 with this part 182d. Part 182e carries a sealing gasket at each of its axial ends, which is intended to cooperate with the inner periphery of part 182d.

[0075] There figure 3 allows us to see that the shaft 182 extends around the shaft BP 36 whose upstream end is coupled to the solar 48a of the reducer 48 by the aforementioned splines.

[0076] The plain bearing P is supplied with oil directly by the channels 180b of the ring 180. It is understood that the radial thickness of the space between the fret 204 and the surface 182b is calculated so that controlled leaks occur at the interfaces between the channels 180b, 182b, in order to supply the plain bearing P. The oil then spreads over the entire axial extent of the plain bearing P and up to the rolling bearings 220, 230 for the purpose of lubricating them.

[0077] The term "way" of device 174 refers to the connection between a channel 180b of the ring 180 and a channel 182b of the shaft 182. In the example shown, device 174 comprises four channels. Preferably, one of the channels is used for supplying oil to the gearbox, another for supplying oil to the actuator 62, and another for the oil return from the actuator 62. Finally, the last channel can be used for hydraulic protection of the actuator.

[0078] Device 174 is configured for example to supply actuator 62 with an oil pressure between 2 and 200 bar, and preferably between 5 and 130 bar.

[0079] The annular support 250 extends at least partially around the ring 180 and carries the fluid connection bushings 192 to the pipes 180b of the ring 180. The support 250 includes several annular walls and attachment elements to the housing 42, which are formed in the example shown by annular flanges 252, 254.

[0080] The support 250 is preferably configured to deform elastically to allow radial movement of the bearing 60. This support 250 is independent of the ring 180 insofar as they are not rigidly fixed to each other.

[0081] In the example shown, the support 250 comprises frustoconical walls 256, 258, at least one of which may be perforated, i.e., may include through perforations, so as to reduce its rigidity in the radial direction. This rigidity can also be reduced by reducing the thickness of this wall.

[0082] A first frustoconical wall 256 of the support 250 extends substantially radially and is connected at its external periphery to the flange 252 for fixing to the housing 42. At its internal periphery, this wall 256 includes integrated channels 290 having at each of its ends ports 292, 294.

[0083] The number of pipes 290 is equal to the number of pipes 180b in ring 180 and is four in the example shown. Only one of these pipes 290 is visible to the figures 3 And 4Each of the pipes 290 has an angled shape, one radially internal end of which is connected to the port 292 which extends axially upstream opposite one of the aforementioned ports 190, in order to receive by male-female engagement one end of a sleeve 192 engaged in this port 190. The radially external end of each pipe 290 is connected to the port 294 which extends radially upstream and outwards to receive by male-female engagement the radially internal end of an oil supply line 296.

[0084] The support 250 includes a second frustoconical wall 258 which extends radially outwards from upstream to downstream. This second wall 258 includes on its outer periphery the flange 254 for attachment to the housing 42. The flange 254' of the housing 42, which is attached to the flanges 252, 254, extends in a plane perpendicular to the axis A, which passes between the bearings 220, 230.

[0085] The inner periphery of wall 258 is located upstream of ring 180 and carries the outer ring of the bearing 60 mentioned above in the example shown. As mentioned above, the support 250, and in particular its wall 258, includes openings 270 for the passage of oil supply lines 296.

[0086] Each of the channels 296 extends radially, first through the openings 270, and secondly through tubular arms 42b of the inlet housing 42 which are located in the primary flow channel F2. These channels 296 then pass through the guide vanes 42a which are located in the secondary flow channel F3, to reach the lubrication system located in the nacelle (see figure 1). An alternative is to mount the lubrication system in the engine (between the primary flow - compressors 14 and 16) and the secondary flow casing 70, so that these lines 192 do not cross the secondary flow F3.

[0087] There figure 5 It also allows us to see that cable 201 follows the same path as pipes 296 and passes through one of openings 270 and arms 42a, 42b. The end of cable 251 opposite the pin is held by an operator from outside the turbomachine 10.

[0088] There figure 5It also allows us to note that the ring 180 includes at least one first axially oriented indexing member 298, such as a groove, and configured to cooperate by engagement with at least one second axially oriented indexing member 300, such as a finger, which is here carried by one of the bushings 192 or by the wall 256 of the support 250 during the assembly of the device 174 and the turbomachine 10.

[0089] The ring 180 is thus held against the support by means of this finger or similar device. The groove receiving this finger is preferably oriented axially and radially to allow axial and radial movement of the finger.

[0090] THE figures 5 to 7 show a method for assembling device 174.

[0091] Parts 182c, 182d and 182e of device 174 are assembled and fixed to each other (cf. figure 7). The device 174 is then in the form of a pre-assembled cartridge. The shaft 182 of the device 174 is then fixed to the planet carrier 48d of the reducer 48 by means of the screws 216 ( figures 5 and 6 ).

[0092] The downstream ends of the sockets 192 are engaged in the ports 292 and the pipes 296 are engaged in the ports 294 ( figure 5 ).

[0093] The pin 199 attached to the cable 201 is engaged in the orifice 199' and the recess 199", which allows the ring 180 on the shaft 182 to be temporarily immobilized in rotation. The cable 201 is passed through one of the openings 270 and then through aligned arms 42a, 42b of the housing 42 ( Figures 5 And 7 ).

[0094] The cartridge-shaped device 174, which is integral with the reducer 48, is brought closer to the rest of the turbomachine by axial translation so that the upstream ends of the bushings 192 engage in the ports 190 of the ring 180. This assembly is performed blindly and is guided by the interaction of the indexing elements 298, 300. As this translation occurs, the operator pulls on the cable 201 to keep it relatively taut at all times ( figure 5 ).

[0095] THE figures 3 And 5 allow us to see that the shaft 182 is then intercalated between the shaft BP 36, whose upstream end is coupled to the solar 48a of the reducer, and the ring 180, and that the outer ring carried by the support 250, and in particular the wall 258, covers the rollers of the bearing 60 located with the inner ring of this bearing on the rim 48e of the satellite carrier 48d.

Claims

1. A fan module for an aircraft turbine engine, this module comprising a fan (12) that comprises a fan shaft (46) and variable pitch fan vanes (12a), and an oil transfer device (174) that is configured to ensure a transfer of oil between a stator and an actuator (62) that is secured in rotation to the fan shaft (46) and that is configured to control the pitch of the fan vanes, this device comprising: - a stator annulus (180) comprising an internal cylindrical surface (180a) and internal oil pipes (180b) each opening onto said internal cylindrical surface (180a), and - a shaft (182) engaged in said annulus (180) and comprising an external cylindrical surface (182a) extending inside said internal cylindrical surface (180a), the shaft comprising internal oil pipes (182b) that each open out onto said external cylindrical surface (182a), the shaft (182) further comprising an attachment member configured to be attached to a rotor of the turbine engine to drive it in rotation about an axis (A), characterised in that it further comprises: - a plain bearing (P) located between said internal (180a) and external (182a) cylindrical surfaces, and - rolling bearings (220, 230) mounted between the annulus (180) and the shaft (182), on either side of the plain bearing (P), and in that the annulus (180) is mounted with a degree of freedom in the axial direction on the shaft (182) and is immobilised in the circumferential direction about the shaft (182) by means of first elements (190, 298) carried by the annulus (180) and configured to cooperate by male-female engagement in the axial direction with complementary second elements (192, 300) carried by said stator.

2. The module according to the preceding claim, wherein the annulus (180) comprises first fluidic connection ports (190) opening out in the axial direction, these first ports (190) being connected to the internal pipes (180b) of the annulus (180) and being configured to cooperate by said male-female engagement with ends of oil supply conduits (296) or sockets (192).

3. The module according to the preceding claim, wherein the number of first ports (190) is equal to the number of pipes (296) in the annulus (180), the first ports (190) being connected to different pipes (180b) in the annulus.

4. The module according to claim 2 or 3, wherein the first ports (190) are located substantially in the same plane perpendicular to said axis (A).

5. The module according to one of the preceding claims, wherein the annulus (180) comprises an orifice (199') for mounting a temporary pin (199) for immobilising the annulus (180) against rotation on the shaft (182), this pin (199) being configured so as to be engaged in a recess (199") of the aforementioned rotor of the turbine engine when the device (174) is mounted and then to be removed after this mounting.

6. The module according to the preceding claim, wherein the orifice (199') has a substantially radial orientation and is formed at the external periphery of the annulus (180).

7. The module according to one of the preceding claims, wherein one of the rolling bearings (220) is with roller bearing and the other of the rolling bearings (230) is ball bearing.

8. The module according to one of the preceding claims, wherein the annulus (180) comprises a first axially oriented indexing member (298), such as a groove, and configured to cooperate by said male-female engagement with a second axially oriented indexing member (300), such as a finger, carried by the stator of the turbine engine.

9. The module according to one of the preceding claims, wherein the fan (12) is driven in rotation by a gearbox (48), said device being mounted downstream of the gearbox (48) and being configured to supply oil to the gearbox (48) and to the actuator (62) via conduits passing axially through the gearbox, and in particular a planet carrier (48d) of the gearbox.

10. The module according to the preceding claim, wherein the shaft (182) of the device is attached to the planet carrier (48d) of the gearbox (48), and the annulus (180) of the device is attached to an intermediate casing (42) by an annular support (250) which at least partly surrounds the device (174).

11. The module according to the preceding claim, wherein a rolling bearing (60), in particular a roller bearing, is mounted between the planet carrier (48d) and said support (250).

12. The module according to claim 10 or 11, wherein the support (250) comprises an annular wall (258) comprising openings (270) for the passage of conduits (296) for supplying oil to the pipes (180b) of the annulus (180), and preferably also for the temporary passage of a cable (201) connected to a pin (199) for immobilising the annulus (180) in rotation on the shaft (182).

13. The module according to one of claims 10 to 12, wherein the support (250) comprises an annular wall (256) comprising: - second ports (294) configured to cooperate by further male-female engagement with ends of oil supply conduits (296), these second ports (294) opening radially outwards, and - third ports (292) connected to the second ports (294) and configured to cooperate by said male-female engagement with ends of oil supply sockets (192), opposite ends of which are engaged in said first ports (190) of the annulus (190).

14. A method for assembling a module according to one of claims 2 to 4, comprising the steps of: a) mounting the annulus (180) on the shaft (182) of the device (174), b) attaching the shaft (182) of the device (174) to the rotor of the turbine engine, c) mounting oil supply conduits (296) and / or sockets (192) on said stator of the turbine engine, and d) displacing in translation the rotor and the device (174) towards the stator, until the first ports (190) of the device cooperate with said conduits (296) or sockets (192).

15. The method according to the preceding claim, wherein: - the module being as defined in claim 12, the method comprises, after step d), a step e) of removing the pin (199), this pin being connected to a cable (201) which is pulled from outside the turbine engine, and / or - the module being as defined in claim 14, the method comprises, in step d), the cooperation by engagement of said first and second members (298, 300).