Fan module provided with oil delivery equipment

Abstract

The invention relates to a fan module for an aircraft turbine engine, the module comprising a fan (12) comprising variable-pitch blades (12a) and an oil delivery device (174) configured to provide delivery of oil between a stator and a rotor, the device comprising: - a stator ring (180) comprising internal oil ducts (180b), - a shaft (182) engaged in the ring (180) and comprising internal oil ducts (182b), and - an annular support (250) of the ring (180) configured to be elastically deformed so as to enable radial movement of the ring (180), - a planar bearing (P) located between the ring (180) and the shaft (182), and - roller bearings (220, 230) mounted between the ring (180) and the shaft (182) and located on either side of the planar bearing (P).

Description

Technical Field

[0001] The present invention relates to a fan module for an aircraft turbine engine, the module including an oil delivery device. Background Technology

[0002] Background technologies include documents US-A1-2004 / 0037483, WO-A1-2020 / 074816, EP-A1-3138 771, EP-A1-3 179 044, EP-A1-3 070 377, US-B1-8,484,942 and WO-A1-2015 / 102779.

[0003] Aircraft turbine engines typically include a gas generator that comprises at least one compressor, an annular combustion chamber, and at least one turbine along the flow direction of the working gas from upstream to downstream.

[0004] The gas entering the gas generator is compressed in one or more compressors, then mixed with fuel and burned in the combustion chamber. The combustion gas flows and expands in one or more turbines to drive one or more rotors of the one or more turbines.

[0005] In the case of a turbine engine with two corps (one low-pressure corps and one high-pressure corps), the rotor of the high-pressure turbine is connected to the rotor of the high-pressure compressor via a high-pressure shaft, and the rotor of the low-pressure turbine is connected to the rotor of the low-pressure compressor via a low-pressure shaft.

[0006] The turbine engine can be equipped with one or more covered or uncovered propellers. When the covered propeller is located upstream of the gas generator, it is referred to as a fan and is driven by the low-pressure shaft of the gas generator.

[0007] During operation, the fan generates airflow, which is divided into: a first flow (called the main flow), which flows into the gas generator; and a second flow (called the secondary flow), which flows around the gas generator.

[0008] The bypass ratio (the ratio of secondary flow to main flow) is becoming increasingly important in modern turbine engines, leading to an increase in fan diameter and a decrease in gas generator diameter.

[0009] To limit the fan's rotational speed (especially in turbine engines with high bypass ratios), it is known to drive the fan via a reduction gear, typically of the planetary or planetary gear type. The low-pressure shaft then drives the fan via the reduction gear.

[0010] A fan or conventional propeller may include variable-pitch blades, meaning each blade has a precisely adjustable orientation about a radial axis. The blades are carried by a polygonal annular hub and rotated about these axes by a common hydraulic actuator mounted within the hub. This actuator is oil-supplied and can be located within a rotating reference frame when rotatably fixed to the hub and the fan.

[0011] Turbine engines include a lubrication system comprising an oil reservoir and a pump, typically located within a stationary reference frame. Therefore, it should be understood that the actuator must be supplied with oil from the lubrication system via an oil delivery device from the stationary reference frame to the rotating reference frame. This type of device is commonly referred to as OTB, an abbreviation for Oil Transfer Bearing.

[0012] This type of device can be installed in a turbine engine with a fan of the type described above to supply oil to the actuator and also to the reducer. This type of device can also be installed in another type of turbine engine, such as a turboprop-type turbine engine equipped with a shielded propeller with variable pitch blades.

[0013] In this technology, the oil delivery device includes a stator ring, which has an inner cylindrical surface and internal oil channels, with multiple internal oil channels leading to the inner cylindrical surface. These channels are connected to the aforementioned lubrication system via pipes.

[0014] The device also includes a shaft engaged in a ring and rotatable about an axis within the ring. The shaft includes: an outer cylindrical surface extending within an inner cylindrical surface of the ring; and internal oil conduits, a plurality of which lead to the outer cylindrical surface. These conduits are connected via pipes to an actuator to supply oil to the actuator.

[0015] In the prior art, the outer cylindrical surface of the shaft includes an annular groove for accommodating annular sealing sections. These sections are displaceable within the groove and are configured to radially abut against the inner surface of the ring to limit and control oil leakage. The outlet of the aforementioned conduit is located between two adjacent sections, thereby ensuring that as much oil as possible is supplied from each conduit in the ring to the corresponding conduit on the shaft. The number of sections is equal to twice the number of conduits. This type of oil conveying device is described in document GB-A-824,332.

[0016] However, this technology is not entirely satisfactory for several reasons. Manufacturing and assembly tolerances of components make it difficult to precisely control these leaks. The equipment comprises numerous parts, which complicates assembly. Consequently, the manufacturing and assembly of such equipment is relatively lengthy and costly. Furthermore, the more pipes and sealing sections in the equipment, the larger the axial dimension of the equipment used to mount these different sections, and therefore the larger the overall axial dimension. Integrating oil delivery equipment into a turbine engine can be complex due to its overall size. Finally, the service life of such equipment is generally limited by potential misalignment between the shaft and rings during operation, as well as wear on the sealing sections, which is exacerbated by the shaft's rotational speed. The larger the diameter of the equipment, the greater the circumferential speed of the shaft, and the greater the wear on the sections.

[0017] Another distinctive feature of current technology devices is that each device is typically presented as a single integral component mounted in a turbine engine as a cartouche. In this application, the term "cartouche" refers to an assembly formed by the device's shaft and ring, with one of the shaft and ring pre-installed within the other before the assembly is installed in the turbine engine.

[0018] If the conveying equipment is located downstream of the turbine engine's reducer, it is impossible to access the equipment and sleeve from upstream during maintenance operations. The equipment's rings should be attached to the turbine engine's stator and removed from the stator from downstream of the lubrication enclosure where the turbine engine and reducer are located. This would mean disassembling the turbine engine's low-pressure compressor and the equipment installed in that area, which would be time-consuming and cumbersome.

[0019] Therefore, the present invention proposes an improved oil conveying device that solves all or part of the problems of the prior art. Summary of the Invention

[0020] This invention relates to a fan module for an aircraft turbine engine, the module including a fan and an oil delivery device. The fan includes a fan shaft and variable-pitch fan blades. The oil delivery device is configured to ensure oil delivery between a stator and an actuator rotatably fixed to the fan shaft and configured to control the pitch of the fan blades. The device includes:

[0021] - Stator ring, the stator ring including an inner cylindrical surface and a plurality of internal oil channels respectively leading to the inner cylindrical surface.

[0022] A shaft, which engages in the ring and includes an outer cylindrical surface extending within the inner cylindrical surface, the shaft including a plurality of internal oil passages leading to the outer cylindrical surface, and the shaft also including attachment members configured to attach to the rotor of a turbine engine, and

[0023] - An annular support member, which extends at least partially around a ring, and the annular support member includes at least one first attachment member for attachment to the ring and at least one second attachment member configured for attachment to the stator of a turbine engine.

[0024] The device is characterized by further comprising:

[0025] - A planar bearing, located between the inner cylindrical surface and the outer cylindrical surface, and

[0026] - Roller bearings, which are mounted between a ring and a shaft and located on both sides of a planar bearing. Each of these bearings includes an outer ring and rollers carried by the ring. The ring is configured to be mounted on a shaft by engaging the shaft in the ring when the ring is pre-equipped with the outer ring and rollers of the bearing.

[0027] The support is configured to deform elastically, thereby allowing the ring to shift in the radial direction.

[0028] Therefore, the present invention proposes an oil delivery device without a sealing member or sealing section between the cylindrical surfaces facing the stator ring and the shaft. Instead, a flat bearing is provided between these surfaces. Rolling bearings are mounted on both sides of the flat bearing to ensure the radial thickness of the flat bearing, regardless of the turbine engine speed and the circumferential speed of the delivery device shaft. The rolling bearings are automatically lubricated by oil leaking from the flat bearing during operation. The rolling bearings also ensure that oil leakage to the flat bearing and the outside of the device is limited. The rolling bearings also make it possible to eliminate the risk of misalignment between the ring and the shaft, thereby eliminating the risk of contact and wear between the ring and the shaft. Therefore, the sealing section is no longer a wear component of the device, and thus has an optimized service life compared to the prior art.

[0029] According to the invention, the device is not installed in a sleeve-like form. Instead, the ring of the device is initially attached to the stator of the turbine engine via a support member. Independently, the shaft of the device can be attached to the rotor of the turbine engine, for example, to the rotating planetary carrier of a planetary gearbox. The shaft is rigidly attached to the planetary carrier and rotatably fixed to it. The ring is connected to the stator via a support member that is flexible in the radial direction. This flexibility is useful and important for two reasons. First, when the shaft is installed and inserted into the ring, the ring can be radially displaced and self-centered on the shaft. During operation, the support member also allows for relative radial displacement between the device and the stator of the turbine engine. This allows for limiting constraints within the device and the risk of misalignment between the shaft and the ring, thereby ensuring a flat bearing with a constant radial thickness within the device.

[0030] A module according to the invention may include one or more of the following features, either individually or in combination:

[0031] - The support includes at least one first truncated conical wall with perforations;

[0032] -The inner periphery of the first truncated conical wall is connected to or carries the first component, the first wall extending, for example, radially inward from upstream to downstream;

[0033] - The support includes a second truncated conical wall, the inner periphery of which is connected to the outer periphery of the first wall, the outer periphery of which is connected to or carries the second member, the second wall extending radially outward, for example, from upstream to downstream;

[0034] - The outer periphery of the first wall is connected to the outer periphery of the third truncated conical wall, the inner periphery of which is connected to the outer ring of another roller bearing or the outer ring carrying another roller bearing, the third wall extending radially outward from upstream to downstream, for example;

[0035] - The equipment includes openings for allowing tubes to pass through or connect to the ring, which supplies oil to the ring;

[0036] - A shrink ring is installed inside the ring, and the shrink ring and the outer surface of the shaft define the planar bearing;

[0037] - The shaft includes an integrated inner raceway for the rolling of the rollers;

[0038] - The inner raceway is formed by a single cylindrical surface that extends continuously within the contraction ring;

[0039] - The bearing rings have the same inner diameter;

[0040] - The shrink ring has two cylindrical surfaces that extend around each other, including a cylindrical shrink mating surface on the ring and a cylindrical central surface on the shaft;

[0041] - The shrink ring includes holes that are positioned opposite the outlet of the ring's conduit, and these holes cover, for example, an annular groove formed at the outlet of the conduit of these outlets and / or the shaft.

[0042] - The fan is driven to rotate by a speed reducer, which is mounted upstream of the speed reducer and configured to supply oil to the speed reducer and actuator via a tube that passes axially through the speed reducer (particularly the planetary carrier of the speed reducer);

[0043] -The equipment's shaft is attached to the planetary carrier of the reducer;

[0044] - Rolling bearings (especially roller bearings) are installed between the planetary carrier and the support member;

[0045] - The reducer is a planetary reducer, meaning that the reducer has a planetary carrier that can rotate, and therefore the reducer has a ring gear that cannot rotate.

[0046] - The equipment supplies lubricating oil to the reducer, particularly to at least some of the bearings and gears of the reducer;

[0047] - The device is configured to supply the actuator with an oil pressure between 2 bar and 200 bar, preferably between 5 bar and 130 bar;

[0048] The equipment is configured to supply the reducer with an oil pressure between 2 bar and 50 bar, preferably between 5 bar and 20 bar.

[0049] The present invention also relates to a method for assembling a turbine engine as described above, the method comprising the following steps:

[0050] - Attach the shaft to the planetary carrier of the reducer, and attach the ring to the stator via the support, then

[0051] - Engage the shaft in the ring.

[0052] The method according to the invention may include one or more of the following steps, either individually or in combination:

[0053] - The device's shaft engages in an annular space, which is formed between a ring on one side and the drive shaft of the reducer's sun gear on the other side.

[0054] - The shaft of the equipment comprises a single, continuous cylindrical surface, which is used to form a planar bearing and a roller bearing with rings.

[0055] - During the engagement process, the rollers carried by the planetary carrier of the reducer engage in the outer ring carried by the support to form a rolling bearing for guiding the planetary carrier.

[0056] The present invention also relates to an aircraft turbine engine comprising the modules described above. Attached Figure Description

[0057] Other features and advantages will become apparent from the following description of non-limiting embodiments of the present invention, with reference to the accompanying drawings, in which:

[0058] [ Figure 1 ] Figure 1 This is a schematic half-view of an axial cross-section of a turbine engine equipped with an oil delivery system.

[0059] [ Figure 2 ] Figure 2 yes Figure 1 A magnified view of a portion,

[0060] [ Figure 3 ] Figure 3 This is a schematic half-view of an axial cross-section of a turbine engine equipped with an oil delivery system, and it shows the assembly steps of the system.

[0061] [ Figure 4 ] Figure 4 After the equipment is assembled Figure 3 A schematic half-view of the axial cross-section of a turbine engine in the image.

[0062] [ Figure 5 ] Figure 5 This is a schematic half-view of the axial cross-section of the oil conveying device according to the present invention.

[0063] [ Figure 6 ] Figure 6 It is equipped with Figure 5 The diagram shows a schematic half-view of the turbine engine of the device, and also illustrates the assembly steps of the device.

[0064] [ Figure 7 ] Figure 7 yes Figure 6 A magnified view of the first detail.

[0065] [ Figure 8 ] Figure 8 yes Figure 6 A magnified view of the second detail.

[0066] [ Figure 9 ] Figure 9 yes Figure 5 A partial schematic perspective view of the equipment shown.

[0067] [ Figure 10 ] Figure 10 yes Figure 5 Another partial schematic perspective view of the device shown.

[0068] [ Figure 11 ] Figure 11 yes Figure 5 Another partial schematic perspective view of the device shown. Detailed Implementation

[0069] Figure 1 A turbine engine 10 is shown, which typically includes a fan 12, a low-pressure (BP) compressor 14, a high-pressure (HP) compressor 16, an annular combustion chamber 18, a high-pressure (HP) turbine 20, a low-pressure (BP) turbine 22, and an exhaust nozzle 24.

[0070] The rotors of the high-pressure compressor 16 and the high-pressure turbine 20 are connected by a high-pressure shaft 26 and together form a high-pressure (HP) body, which is guided by rolling bearings 28 and 30 to rotate about the longitudinal axis A of the turbine engine. A first bearing 28 is mounted between the upstream end of the shaft 26, the HP body, and a compressor housing 32 located between the BP compressor 14 and the HP compressor 16. A second bearing 30 is mounted between the downstream end of the shaft 26, the HP body, and a turbine housing 34 located between the BP turbine 22 and the HP turbine 24.

[0071] The rotors of the BP compressor 14 and the BP turbine 22 are connected by a low-pressure shaft 36 and together form a low-pressure (BP) body, which is guided by rolling bearings (38, 40) to rotate about the longitudinal axis A of the turbine engine. At least one bearing 38 is mounted between the upstream end of the shaft 36, the BP body, and the intake housing 42, which is located upstream of the BP compressor 14. Other bearings 40 are mounted between the downstream end of the shaft 36, the BP body, and the exhaust housing 44, which is located downstream of the BP turbine 22.

[0072] Fan 12 is driven by fan shaft 46, which is driven by BP shaft 36 via reducer 48. The reducer 48 is typically a planetary reducer or a planetary gear reducer.

[0073] The following description pertains to a planetary gearbox, in which the planet carrier and sun gear are rotatable, and the gearbox's ring gear is fixed in the engine's reference frame.

[0074] The reducer 48 is located in the upstream portion of the turbine engine. Here, a mounting structure schematically including an upstream portion 50a and a downstream portion 50b is arranged to form a containment E surrounding the reducer 48, which constitutes the engine housing or stator 50. The containment E is closed upstream by a seal 52 located at a bearing 54, and downstream by a seal 55 located at a bearing 38 through which the fan shaft 46 passes, and the BP shaft 36 passes through the bearing 38.

[0075] Enclosure E is arranged within intake housing 42, which is located between intake straightening vane 56 and BP compressor 14.

[0076] Figure 2 The reducer 48 is shown at a larger scale.

[0077] The reducer 48 includes a sun gear 48a, which is centered on axis A and connected to the BP shaft 36 via, for example, a spline.

[0078] The reducer 48 includes a ring gear 48b, which is also centered on axis A and attached to the intake housing 42.

[0079] Finally, the reducer 48 includes planetary gears 48c arranged about axis A and meshing with a sun gear 48a and a ring gear 48b. These planetary gears 48c are carried by a planet carrier 48d, which is rotatably movable about axis A and connected to the fan shaft 46 to drive the fan shaft. The planet carrier 48d is guided by bearings 58 and 60, which are carried by the intake housing 42 and are located upstream and downstream of the reducer 48, respectively.

[0080] Figure 1 The fan 12 shown includes variable pitch blades 12a and is associated with an actuator 62 that enables centralized control of the positioning of the blades 12a about their axis B, which is typically the radial axis relative to the axis A of the turbine engine.

[0081] Each of the blades 12a includes a root 12b that forms a pivot, which is received in a accommodating portion of a hub 64 in the form of a polygonal ring, and the pivot is connected by a connecting system 66 that is connected to the piston of the actuator 62.

[0082] Actuator 62 extends along axis A, and the piston of the actuator can be translated along this axis, for example, from a first position to a second position, in which blade 12a feathers, and in the second position, blade 12a obstructs airflow through fan 12.

[0083] The airflow F1 passing through fan 12 is split into two annular coaxial flows downstream of fan by an annular separator 68, which extends around blade 56. The first airflow (referred to as the main flow F2) flowing in the main bypass duct passes through this blade 56 and flows into compressors 14 and 16 to be compressed. This compressed air is then mixed with fuel and burned in combustion chamber 18. The combustion gases then expand in turbines 20 and 22 to drive the turbine rotors, as well as the BP shaft 36 and HP shaft 26, and then flow into nozzle 24.

[0084] A second airflow (referred to as secondary flow F3) flows in a secondary bypass duct, which is internally defined by an annular engine casing 70 and externally by an annular nacelle casing 72, which extends longitudinally around compressors 14, 16, combustion chamber 18, and turbines 20, 22, and which extends longitudinally around fan 12 and a portion of the engine. The nacelle casing 72 is connected to the engine via outlet guide vanes 42a of the intake casing 42. These guide vanes 42a are structural and configured to straighten the airflow exiting fan 12.

[0085] Actuator 62 is hydraulic and operates using fluid (oil) from a lubrication system typically located in the engine compartment or between the compressors 14, 16 and the housing 70 (i.e., in the engine), and thus within the fixed reference frame of the turbine engine. In contrast, actuator 62 is located within a rotating reference frame.

[0086] like Figure 2 As shown, the turbine engine 10 includes a device 74 for delivering oil from a fixed reference frame of the engine to a rotating frame where the actuator 62 is located.

[0087] In the example shown, device 74 is located downstream of reducer 48 and preferably includes multiple oil supply passages 76 for supplying oil to actuator 62 and also for lubricating reducer 48.

[0088] Figure 2 The dashed line in the diagram represents one of these pathways along the entire path from the fixed reference frame to the actuator 62: through the main duct to the device 74, through the reducer 48 (between the planetary gears of the reducer or through the axis of these planetary gears), and along the planet carrier, and then along the fan shaft 46.

[0089] Figure 3 and Figure 4 The oil conveying device 74 is shown in more detail, which includes:

[0090] - Stator ring 80, the stator ring including an inner cylindrical surface 80a and internal oil channels 80b, wherein multiple internal oil channels lead to the inner cylindrical surface 80a, and

[0091] - Shaft 82, which is engaged in stator ring 80 and rotatably movable about axis A within ring 80, shaft 82 includes: an outer cylindrical surface 82a extending within surface 80a; and internal oil conduits 82b, a plurality of internal oil conduits leading to surface 82a respectively.

[0092] from Figure 3 It can be seen from this that Figure 3 The assembly steps of device 74 are shown, device 74 being in the form of a pre-assembled sleeve. The shaft 82 of device 74 is first attached to the planetary carrier 48d of the reducer 48 by nut 83, and then fixed to the sleeve-shaped device of the reducer 48 near the rest of the turbine engine, such that the ring 80 of the device is attached to the housing 42 through the downstream portion 50b of the stator 50.

[0093] As mentioned above, this technology has many problems.

[0094] This invention enables the solution of some or all of these problems using oil conveying equipment, and embodiments of the invention include, for example... Figures 5 to 11 As shown.

[0095] In the following description and Figures 5 to 11 The reference numerals used above to indicate certain elements are used because they represent the same elements.

[0096] Figures 5 to 11 The oil conveying device 174 also includes a stator ring 180 and a shaft 182, which is engaged in the stator ring 180 and can rotate about axis A within the ring 180.

[0097] The device 174 also includes a ring support 250.

[0098] Ring 180 includes an inner cylindrical surface 180a and internal oil conduits 180b, with multiple internal oil conduits leading to surface 180a. The conduits 180b are arranged one after another along axis A. In the example shown, three of these conduits are present. Although the conduits 180b are shown here in the same axial plane, they may lie in different axial planes. This depends in particular on the pipe 192 to which they are connected and the arm 42b through which these pipes pass. In another variation, the conduits 180b may include radially outer ends located in the same axial plane and ends angled around axis A and leading to surface 180a.

[0099] Each of the pipes in pipe 180b includes a radially inner end forming the aforementioned opening and a radially outer end forming a port 190 for connection to tubing 192 or a connecting sleeve, which will be combined below. Figures 9 to 11 To describe in more detail.

[0100] Port 190 forms a recess, and the end of tube 192 or sleeve forms a protrusion that is sealed into port 190. Figure 6 and Figure 7 A tube connected to ring 180 in tube 192 is shown. These tubes 192 first extend radially through opening 270 in support 250, and then radially through tubular arms 42b of intake housing 42, which are located in the flow duct of the main flow F2. These tubes 192 then pass through guide vanes 42a located in the flow duct of secondary flow F3 to reach the lubrication system located in the nacelle (see...). Figure 1 Alternatively, the lubrication system can be installed in the engine (between the compressors 14 and 16 of the main bypass and the housing 70 of the secondary bypass), such that these pipes 192 do not pass through the secondary flow F3.

[0101] The ring 180 is typically cylindrical in shape and includes an upstream cylindrical edge 200a and a downstream cylindrical edge 200b. These edges 200a and 200b have the same or similar diameters.

[0102] A contraction ring 204 is attached within a ring 180 to cover surface 180a of the ring. The contraction ring 204 extends over a large portion of the length of the ring 180 and includes a radially outer annular edge 204a at its upstream end, which axially abuts against a cylindrical support surface of the ring 180. As its name suggests, the contraction ring 204 contracts into the ring 180. This contraction fit, associated with the support of the edge 204a of the contraction ring, ensures that the contraction ring 204 is fixed relative to the ring 180.

[0103] The contraction ring 204 includes a radial row of annular holes 206 corresponding to each pipe in the conduit 180b. Furthermore, an annular groove 208 is formed on the inner periphery of the ring 180 and corresponds to each pipe in the conduit 180b; this groove 208 is closed on its inner side by the contraction ring 204. Therefore, it should be understood that each pipe 180b is supplied with one groove 208, and each groove 208 distributes oil to the holes 206 of the contraction ring 204.

[0104] The shrink ring 204 includes an outer cylindrical shrink-fit surface and an inner cylindrical center surface. The outer cylindrical shrink-fit surface contacts the inner surface 180a of the ring 180, and the inner cylindrical center surface is designed to be separated from the outer surface 182a of the shaft 182 by a predetermined radial distance to define the planar bearing P.

[0105] Shaft 182 has no shrink ring. This allows for a reduction in the number of tolerance stacking interfaces. Therefore, by reducing the number of interfaces, the clearance between the rotor and stator is significantly reduced.

[0106] Shaft 182 includes: an outer cylindrical surface 182a extending within surface 180a; and internal oil conduits 182b, a plurality of which lead to surface 182a. The conduits 182b are radially oriented and arranged one after another along axis A. Three of these conduits are shown in the example illustrated.

[0107] An annular groove 210 is formed on the outer periphery of the shaft 182 and is provided corresponding to each pipe in the pipe 182b.

[0108] Each of the pipes in conduits 182b connects to a pipe 212, which can be integrated into the shaft 182. One of these pipes 212, visible in the cross-section of the attached figure, includes an annular segment 212a that extends around axis A and along a large portion of the length of the shaft 182. The downstream end of this segment 212a connects to the downstreammost conduit 182b of the shaft, and the upstream end of this segment connects to a radial segment 212b formed in an upstream annular rib 214 of the shaft.

[0109] The rib 214 is used to attach the shaft 182 of the device 174. In the example shown, the shaft 182 of the device 174 is attached to the planetary carrier 48d of the reducer 48. The planetary carrier 48d includes a downstream cylindrical edge 48e, on which a bearing 60 is mounted on the outer periphery, and the rib 214 engages on the inner periphery of the downstream cylindrical edge. The rib 214 axially abuts against the cylindrical support surface of the edge 48e upstream, and is held axially against the support surface by a nut 216 screwed from downstream onto the inner periphery of the edge 48e.

[0110] Bearing 60 is a rolling bearing and includes rollers arranged between two rings (an inner ring and an outer ring, respectively), the inner ring being axially clamped to another cylindrical support surface on the outer periphery of edge 48e by a nut 218 screwed from downstream to the periphery.

[0111] The first rolling bearing 220 is installed between the edge 200b of the ring 180 and the downstream end of the shaft 182.

[0112] Bearing 220 is a rolling bearing and includes rollers arranged between two raceways (an inner raceway and an outer raceway, respectively).

[0113] The inner raceway of bearing 220 is integrated into shaft 182, that is, there is no inner ring for bearing 220 mounted on shaft 182.

[0114] The outer raceway of bearing 220 is formed by an outer ring 224 mounted within edge 200b. This ring 224 rests axially against a cylindrical support surface on the inner periphery of the upstream edge 200b. Downstream, the ring 224 is axially held by a nut 226 screwed to the inner periphery of edge 200b or by a shrink ring engaged in the edge.

[0115] The inner raceway of bearing 230 is integrated into shaft 182, that is, there is no inner ring for bearing 230 mounted on shaft 182.

[0116] The outer raceway of bearing 230 is formed by an outer ring 234 mounted within edge 200a. This ring 234 rests axially against a cylindrical support surface on the inner periphery of the downstream edge 200a. Upstream, the ring 234 is axially held by a nut 228 screwed to the inner periphery of edge 200a or by a shrink ring engaged in the edge.

[0117] like Figure 5 As shown, advantageously, the outer surface 182a of the shaft 182 and the inner raceways of the bearings 220, 230 (integrated into the shaft 182) have the same diameter D1 and extend continuously along their respective extensions. Therefore, it should be understood that the shaft 182 can be mounted within the ring 180 by axial translation, the ring 180 being pre-equipped with the shrink ring 204, rings 224, 234 and rollers of the bearings 220, 230 prior to such translation.

[0118] Oil is supplied directly to the thrust bearing P via conduit 180b through ring 180. It should be understood that the radial thickness of the space between shrink ring 204 and surface 182b is calculated such that controlled leakage occurs at the interface between conduits 180b and 182b, thereby supplying the thrust bearing P. The oil then diffuses throughout the entire axial range of the thrust bearing P and extends as far as the rolling bearings 220 and 230, thereby lubricating these rolling bearings.

[0119] The “passage” of device 174 refers to the connection between pipe 180b of ring 180 and pipe 182b of shaft 182. In the example shown, device 174 includes three passages. Preferably, one passage is used to supply oil to actuator 62, another passage is used to return oil from actuator 62, and finally, the last passage is used for hydraulic protection of the actuator or to supply oil to reducer 48.

[0120] For example, device 174 is configured to supply actuator 62 with an oil pressure between 2 bar and 200 bar, preferably between 5 bar and 130 bar.

[0121] The annular support 250 extends at least partially around the ring 180 and includes at least one first attachment member for attachment to the ring 180 and at least one second attachment member for attachment to the housing 42. In the example shown, these members are formed by annular flanges 252, 254, which are designed to be attached to corresponding annular flanges by screw-nut type means.

[0122] The support 250 is configured to deform elastically, thereby enabling the ring 180 to move in the radial direction.

[0123] In the example shown, the support 250 includes truncated conical walls 256, 258, and 260, at least one of which has a perforation, i.e., at least one of the truncated conical walls includes an opening 261 therethrough, to reduce the radial stiffness of at least one of the truncated conical walls. Figures 9 to 11 This stiffness can also be reduced by decreasing the thickness of the wall.

[0124] The support member 250 includes a first truncated conical wall 256 extending radially inward from upstream to downstream, and the first truncated conical wall is connected at its inner periphery to an attachment flange 252 for attachment to a flange 252' of the ring 180. In the example shown, the flange 252' of the ring extends along a plane perpendicular to axis A, which passes between bearings 220 and 230 of the device 174.

[0125] The support member 250 includes a second truncated conical wall 258 that extends radially outward from the outer periphery of the first wall 256 from upstream to downstream. The second wall 258 includes an attachment flange 254 at its outer periphery for attachment to a flange 254' of the housing 42. Figure 7 Flange 254' extends along a plane perpendicular to axis A, which is close to the plane passing through flange 252'.

[0126] This means that walls 256 and 258 form a V-shape with the tip pointing upstream along the axial cross section.

[0127] The support member 250 includes a third truncated conical wall 260 that extends radially outward from upstream to downstream, and the outer periphery of the third truncated conical wall connects to the engagement area of ​​walls 256 and 258. Therefore, the inner periphery of the wall 260 is located on the upstream side and carries the outer ring of the bearing 60 described above in the illustrated example.

[0128] As described above, the support 250 includes an opening 270 for the passage of pipes 192, which supply oil to the conduit 180b of the ring 180.

[0129] In the example shown, these openings 270 are formed in the truncated conical wall 260, and... Figures 9 to 11 The best view is in the center. Advantageously, wall 260 includes as many openings 270 as the inner conduit 180b in ring 180, i.e., three, for example. These openings 270 are distributed around axis A and are radially aligned with one of the ports 190 of the ring as described above.

[0130] A sealed fluid connection sleeve 280 may extend into the annular space between the ring 180 and the support 250, and each sealed fluid connection sleeve may include a radially outer end engaged in one of the openings 270 and a radially inner end engaged in one of the ports 190. The aforementioned tube 192 will then include a radially inner end engaged in a sealed manner in the opening 270, which is connected via the sleeve 280 to the conduit 180b of the ring 180.

[0131] Figures 9 to 11 The sleeve 280 is shown to be straight, and the annular tubes 180b are specifically more or less bent to connect these sleeves 280 to the slots 208 and the holes 206.

[0132] For example, in Figure 10 The upstream conduit 180b of the ring 180 visible in the cross-section has a straight or linear orientation and is generally aligned with the corresponding sleeve 280 and opening 270.

[0133] For example, in Figure 11 The lower portion of the cross-sectional view shows that the downstream pipe 180b of the ring 180 has two bends, which are connected by an elongated portion extending generally parallel to axis A.

[0134] Finally, Figure 11 The top portion of the cross-sectional view shows the middle pipe 180b of the ring, which is typically S-shaped.

[0135] It can be seen that opening 270 is roughly located in the same plane perpendicular to axis A.

[0136] Figure 6 A method for assembling device 174 is shown. The first step includes attaching ring 180 to support 250 by attaching flanges 252, 252' together, and then connecting pipe 192 to pipe 180b or opening 270 in support 250 as described above.

[0137] Another step includes engaging the shaft 182 in the planet carrier 48d of the reducer 48 and attaching the shaft to the planet carrier of the reducer by tightening the nut 216.

[0138] Then, shaft 182 is engaged in ring 180 by axial translation of the assembly formed by reducer 48 and shaft 182 in ring 180.

[0139] Figure 6The diagram shows a shaft 182 inserted between a BP shaft 36 and a ring 180. The upstream end of the BP shaft is connected to the sun gear 48a of the reducer. The outer ring, carried by a support member 250, covers the rollers of a bearing 60, whose rollers and inner ring are located on the edge 48e of the planetary carrier 48d. The upstream portion 50a of the stator is then attached to the housing 42, allowing the shaft 182 to be precisely positioned axially within the ring 180.

Claims

1. A fan module for a turbine engine of an aircraft, the fan module comprising a fan (12) and an oil delivery device (174), the fan comprising a fan shaft (46) and variable-pitch fan blades (12a), the oil delivery device being configured to ensure oil delivery between a stator and an actuator (62), the actuator being rotatably fixed to the fan shaft (46), and the actuator being configured to control the pitch of the fan blades, the oil delivery device comprising: - Stator ring (180), the stator ring including an inner cylindrical surface (180a) and a plurality of first internal oil channels (180b) respectively leading to the inner cylindrical surface (180a). - A shaft (182), which engages in the stator ring (180) and includes an outer cylindrical surface (182a) extending within the inner cylindrical surface (180a), the shaft including a plurality of second internal oil passages (182b) respectively leading to the outer cylindrical surface (182a), the shaft also including attachment members configured to attach to the rotor of the turbine engine, and - An annular support (250) extending at least partially around the stator ring (180), and the annular support including at least one first attachment member for attachment to the stator ring (180) and at least one second attachment member configured for attachment to the stator of the turbine engine. The oil conveying equipment is characterized in that it further includes: - A planar bearing (P), the planar bearing being located between the inner cylindrical surface (180a) and the outer cylindrical surface (182a), and - An upstream roller bearing (230) and a downstream roller bearing (220) are mounted between the stator ring (180) and the shaft (182) and located on both sides of the planar bearing (P). Each of these upstream roller bearings (230) and downstream roller bearings (220) includes an outer ring (224, 234) and rollers carried by the stator ring (180). The stator ring is configured to be mounted on the shaft (182) by engaging the shaft (182) in the stator ring (180) when the stator ring is pre-equipped with the outer rings (224, 234) and rollers of the upstream roller bearings (230) and the downstream roller bearings (220). The annular support (250) is configured to deform elastically, thereby allowing the stator ring (180) to shift in the radial direction.

2. The fan module of claim 1, wherein, The annular support (250) includes at least one first truncated conical wall (256) with perforations.

3. The fan module according to claim 2, wherein, The inner periphery of the first truncated conical wall (256) is connected to or carries the first attachment member.

4. The fan module according to claim 3, wherein, The annular support (250) includes a second truncated conical wall (258), the inner periphery of which is connected to the outer periphery of the first truncated conical wall (256), and the outer periphery of which is connected to or carries the second attachment member.

5. The fan module according to claim 4, wherein, The outer periphery of the first truncated conical wall (256) is connected to the outer periphery of the third truncated conical wall (260), and the inner periphery of the third truncated conical wall is connected to the outer ring of another rolling bearing (60) or the outer ring carrying another rolling bearing.

6. The fan module according to any one of claims 1 to 5, wherein, The annular support (250) includes an opening (270) for a tube (192) to pass through or connect to the first internal oil conduit (180b) of the stator ring (180).

7. The fan module according to any one of claims 1 to 5, wherein, A shrink ring (204) is installed inside the stator ring (180), and the shrink ring and the outer cylindrical surface (182a) of the shaft (182) define the planar bearing (P).

8. The fan module according to any one of claims 1 to 5, wherein, The shaft (182) includes an integrated inner raceway for the rolling of the rollers.

9. The fan module according to claim 7, wherein, The shaft (182) includes an integrated inner raceway for the rolling of the roller, the inner raceway being formed by a single cylindrical surface that extends continuously within the contraction ring (204).

10. The fan module according to any one of claims 1 to 5, wherein, The fan (12) is driven to rotate by a reducer (48), and the oil delivery device is installed downstream of the reducer (48) and configured to supply oil to the reducer and the actuator (62) via a pipe that passes axially through the reducer.

11. The fan module according to claim 10, wherein, The oil delivery device is configured to supply oil to the reducer and the actuator (62) via a pipe that axially passes through the planetary carrier (48d) of the reducer.

12. The fan module according to claim 11, wherein, The shaft (182) of the oil conveying device is attached to the planetary carrier (48d) of the reducer (48).

13. The fan module according to claim 12, wherein, The rolling bearing (60) is installed between the planetary carrier (48d) and the annular support (250).

14. The fan module according to claim 3, wherein, The first truncated conical wall extends radially inland from upstream to downstream.

15. The fan module according to claim 4, wherein, The second truncated conical wall extends radially outward from upstream to downstream.

16. The fan module according to claim 5, wherein, The third truncated conical wall (260) extends radially outward from upstream to downstream.

17. The fan module according to claim 13, wherein, The rolling bearing (60) is a roller bearing.

18. A method for assembling a fan module according to claim 12 or 13, the method comprising the following steps: - The shaft (182) is attached to the planetary carrier (48d) of the reducer, and the stator ring (180) is attached to the stator via the annular support (250), then - The shaft (182) is engaged in the stator ring (180).

Images