Classified impellers for oil supply to epicyclic or planetary gear reducers

Abstract

The invention relates to an oil supply device for supplying oil to an epicyclic or planetary gear reducer. The oil comes from at least one oil injection member fixed relative to the gear reducer, the oil supply device comprising at least one cup-shaped member integral with the planetary carrier of the gear reducer and opening substantially annularly and radially relative to the axis of the gear reducer; and the wall of the cup-shaped member delimiting a chamber supplied by the at least one oil injection member and supplying one of the oil distribution circuits of the gear reducer, the oil supply device being graded and comprising at least two independent stages, each stage being provided with a coaxial cup-shaped member of different diameter, each cup-shaped member supplying an associated oil circuit and being configured to receive oil axially, centripetally or tangentially or according to an oblique direction combining the two directions.

Description

Technical Field

[0001] The field of the invention is turbomachinery, and more particularly differential drive systems in these turbomachinery, in particular epicyclic or planetary gear reducers. Background Art

[0002] Current turbomachines, in particular those comprising one or more blown secondary air propellers, comprise a transmission system, known as a gear reducer, for driving the propeller(s) at a suitable rotational speed from the shaft of the power turbine of the main body of the engine.

[0003] The function of a mechanical gear reducer is to change the speed ratio and torque between the input and output shafts of a mechanism.

[0004] The new generation of twin-flow turbines, in particular those with a high bypass ratio, include a mechanical gear reducer for the shaft driving the fan. Typically, the purpose of the gear reducer is to convert the so-called fast rotational speed of the shaft of the power turbine into a slower rotational speed of the shaft driving the fan.

[0005] This gear reducer consists of a central pinion gear, known as the sun gear, a ring gear, and pinions, known as planet gears, meshing between the sun and ring gears. The planet gears are held in place by a frame, known as the planet carrier. The sun gear, ring gear, and planet carrier all function as planetary transmissions because their axes of rotation coincide with the turbine's longitudinal axis, X. Each planet gear has a different axis of rotation and is evenly spaced around the axis of the planetary transmission, with the same working diameter. These axes are parallel to the longitudinal axis, X.

[0006] There are various gear reducer architectures. In the prior art for twin-flow turbines, the gear reducers are epicyclic or planetary. In other similar applications, there are so-called differential or compound architectures.

[0007] -On a planetary gear reducer, the planet carrier is fixed and the ring gear forms the output shaft of the device, which rotates in the opposite direction of the sun gear.

[0008] -On an epicyclic gear reducer, the ring gear is fixed and the planetary carrier forms the output shaft of the device, which rotates in the same direction as the sun gear.

[0009] -In a differential gear reducer, no element is fixed in rotation. The ring gear rotates in the opposite direction to the sun gear and planet carrier.

[0010] A gear reducer can consist of one or more meshing stages. This meshing can be ensured in various ways, such as by contact, friction or magnetic fields.

[0011] There are various types of contact toothing, such as spur toothing or chevron toothing.

[0012] Epicyclic gear reducers, in particular, offer the advantage of providing a high reduction ratio within a compact space. On the other hand, like differential gear reducers, they have the disadvantage of having planetary gear pinions that rotate around the gear reducer's drive shaft via a rotation axis coaxial with the planetary gears. Consequently, epicyclic gear reducers require a device for transferring oil from a fixed-point oil reservoir and pump to a lubricating member that rotates around the drive shaft, following the axes of the planetary gear pinions. This problem is typically addressed using a device that incorporates a rotary motion pair system.

[0013] The drawbacks of these systems are that they are bulky and prone to wear, which is incompatible with the lifespan required of aircraft engines, thus affecting the maintenance of these engines. Finally, these gear reducers are difficult to assemble with flexible components of the turbine structure, which is recommended, for example, to compensate for the loss or damage of fan propeller blades or to adopt modular components to facilitate the assembly of the engine.

[0014] To remedy these drawbacks, the applicant has proposed, in patent applications WO-A1-2010 / 092263, FR-A1-2987416, WO-2019 / 16463-A1 and WO-2019 / 16491-A1, a lubricating device without a rotating kinematic pair, in which an oil injection system is provided, comprising a supply member with a nozzle, which injects oil from a fixedly marked connection circuit onto an oil supply device (called an "impeller" or "distributor"), which comprises a cup-shaped element integral with the planetary carrier. The cup-shaped element, which rotates around the injection member together with the oil supply device (called an "impeller" or "distributor"), limits the oil recovered by centrifugal separation before directing it to a member that lubricates the pinion.

[0015] Therefore, these devices greatly improve the reliability of the lubrication system of the gear reducer and its maintenance.

[0016] Furthermore, the technical solution described in patent application FR-3.047.279-A1 attempts to adjust the oil flow rate to different gears according to their lubrication needs. To this end, the receiving cup of the oil supply device is divided into multiple sections along the axis of rotation, and axially offset supply members include axially offset nozzles that feed these sections. These sections define chambers associated with different circuits, which are interconnected by overflows. The oil recovered in each axial section is then directed to a circuit dedicated to a specific type of meshing or other component to be lubricated.

[0017] However, this solution does not allow for the oil flow distribution between the segments to be adjusted according to the turbine speed. Furthermore, placing nozzles on the same diameter and dedicated to each axial segment is quite complex. Furthermore, the increased number of nozzles and their proximity can cause reliability issues.

[0018] The technical solution described in patent application FR-3.041.054-A1 also seeks to adjust the oil flow rate to different lubrication points (such as gears) according to their lubrication needs. To this end, the receiving cup of the oil supply device (called an "impeller" or "distributor") is divided into an annular series of bowls arranged around the axis of rotation, and the nozzles of the injection member of the oil injection system supply these segments. The oil recovered by each bowl is then directed to a circuit dedicated to a specific lubrication point.

[0019] However, this solution does not allow, beyond regulating the oil flow rate supplied by each bowl to the circuit associated with it, to regulate the oil flow distribution between the lubricating points being supplied, since the bowls are supplied with oil from the same nozzles of the same supply member and therefore have the same flow rate. This solution also does not allow differentiation of the type of lubricant used, particularly with regard to viscosity, temperature, or filtration, so as to adapt lubricants with different properties to the needs of the components or gears being lubricated. Furthermore, the supply of the bowls is significantly irregular, as it relates to their passage before the nozzles.

[0020] Furthermore, in both designs, since the oil circuits are fed by axial cup sections or reservoirs, which are placed at approximately the same diameter, the circuit placed on the larger diameter suffers a significant pressure drop.

[0021] To overcome these shortcomings, US-2016 / 377167-A1 proposes an oil supply device comprising two coaxial, graded, annular lubrication cups. Each cup supplies a different oil distribution circuit of the gear reducer and is configured to receive oil from two oil spray members, forming two independent lubrication stages. The oil spray members are injection manifolds that provide centrifugal oil injection. Consequently, the injection manifolds are located close to the axis of the gear reducer and are difficult to install.

[0022] The present invention aims to overcome this shortcoming while improving the advantages of the technical solutions proposed in the above patent application. Summary of the Invention

[0023] To this end, the invention relates to an oil supply device extending about an axis X, the oil supply device being intended to supply oil to two different oil distribution circuits of a gear reducer comprising at least one sun pinion, a planetary carrier and a ring gear, which are capable of relative rotational movement relative to one another, the oil coming from at least one oil injection member fixed relative to the gear reducer, the device being fixed to the planetary carrier and comprising an annular lubrication cup configured to receive oil from the at least one oil injection member and capable of supplying oil to one of the oil distribution circuits, the device comprising at least one further Lubricating cups so as to be capable of being graded into at least two independent lubrication stages, said further cups being configured to receive oil from further oil injection members and being capable of supplying oil to further oil distribution circuits, each cup supplying a different oil circuit associated therewith, the cups being coaxial and having different diameters, characterised in that said cups are configured to receive oil axially in a direction parallel to the axis X and facing the cup associated therewith, or to receive oil centripetally in a radial direction facing the axis X, or to receive oil tangentially, or to receive oil according to an oblique direction combining the two said directions.

[0024] According to other characteristics of the supply device:

[0025] -The device comprises at least:

[0026] a first annular cup, the oil distribution circuit of which is associated therewith comprising a plurality of nozzles distributed angularly about the axis X, which supply oil to the sun pinion and / or the planetary gears, and

[0027] a second annular cup, the oil distribution circuit of which is associated with it, supplies oil to the bearings of the planetary gears on the planet carrier,

[0028] at least one annular cup having an outer part and an inner part, the outer part having a substantially U-shaped cross section open in a radial direction to the axis X, the inner part extending to the outer part from a branch of the U-shaped cross section, the inner part defining J-shaped or V-shaped grooves configured to receive an oil jet inclined according to a direction having at least one radial centripetal component and an axial component facing the axis X, or an axial and tangential component facing the cup, or a direction of the L-shaped groove opening opposite the cup fed by a purely axial oil jet or an axial and tangential oil jet,

[0029] - the annular cup is angularly divided into adjacent compartments defining a plurality of reservoirs supplying the oil distribution circuit, said reservoirs being separated by axial walls arranged at the angular ends of said compartments, the free ends of said axial walls being inclined towards the axis of the gear reducer so as to enable the oil to flow from the reservoirs of one compartment to the reservoirs of an adjacent compartment,

[0030] - the grooves comprise fins extending substantially in radial direction, arranged in the inner part to drive the oil at the bottom of the reservoir by centrifugal action,

[0031] - the vanes are radial or inclined relative to the radial direction and / or have a blade profile,

[0032] - Each cup is connected to the adjacent cup by a structural arm,

[0033] - at least one cup comprises an extra thickness which can be machined locally to enable said cup to balance,

[0034] At least one cup comprises a region capable of receiving at least one weight for balancing said cup.

[0035] The invention also relates to an oil injection system for supplying oil to an oil supply device of the above type, characterized in that the oil injection system is staged and comprises at least two different oil injection members, each supplying a corresponding cup of the device.

[0036] According to other characteristics of the injection system:

[0037] - each oil injection member of the cup comprises an annular tubular injection manifold, or a plurality of angled segments of annular tubular manifolds, the diameter of which is substantially slightly larger than the diameter of the corresponding cup, these segments comprising holes distributed in the circumferential direction, the holes being directed towards the opening of the groove of the corresponding cup, and at least one main radial duct for supplying oil to said annular manifold or said angled segments of said annular manifold,

[0038] Each oil injection member is supplied with oil adapted to the requirements of the components of the gear reducer lubricated by the corresponding cup.

[0039] Finally, the invention relates to a lubrication assembly for an epicyclic or differential gear reducer, characterized in that it comprises an oil supply device according to one of the claims and an oil injection system of the type described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Other features and advantages of the present invention will become apparent during reading the following detailed description, for which reference will be made to the accompanying drawings, in which:

[0041] [ Figure 1 ] Figure 1 is a schematic axial cross-sectional view of a turbine using the present invention;

[0042] [ Figure 2 ] Figure 2 It is a partial axial cross-sectional view of a mechanical gear reducer;

[0043] [ Figure 3 ] Figure 3 is an axial cross-sectional view of an epicyclic gear reducer equipped with an oil supply device according to the present invention;

[0044] [ Figure 4 ] Figure 4 The epicyclic gear reducer equipped with the oil supply device according to the present invention is along Figure 3 A cross-sectional view of plane 4-4;

[0045] [ Figure 5 ] Figure 5 yes Figure 3 An enlarged view showing a second cup-shaped member of the oil supply device;

[0046] [ Figure 6 ] Figure 6 yes Figure 4 An enlarged view showing a second cup-shaped member of the oil supply device;

[0047] [ Figure 7 ] Figure 7 yes Figure 3 An enlarged view showing a first cup-shaped member of the oil supply device;

[0048] [ Figure 8 ] Figure 8 yes Figure 4 An enlarged view showing a first cup-shaped member of the oil supply device;

[0049] [ Figure 9 ] Figure 9 is a perspective view of an oil injection system of an oil supply device according to the present invention;

[0050] [ Figure 10 ] Figure 10 is a block diagram illustrating the steps of a method for assembling an epicyclic gear reducer and a lubrication assembly according to the present invention. DETAILED DESCRIPTION

[0051] Figure 1A turbomachine 10 is depicted, which, in conventional fashion, includes a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, an annular combustion chamber 18, a high-pressure turbine 20, a low-pressure turbine 22, and an exhaust duct 24. 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. The low-pressure compressor 14 and the low-pressure turbine 20 are connected by a low-pressure shaft 28 and together form a low-pressure (LP) body.

[0052] The fan 12 is driven by a fan shaft 30 which is driven by the LP shaft 28 through a gear reducer 32. The gear reducer 32 is typically of the planetary or epicyclic type.

[0053] Although the following description relates to planetary or epicyclic gear reducers, it also applies to mechanical differential gear reducers in which three components (i.e., the planet carrier, the ring gear, and the sun gear) are rotatably movable, and in particular, the speed of one component depends on the speed difference between the other two components.

[0054] A gear reducer 32 is placed in the upstream part of the turbine. To form a housing E around the gear reducer 32, a fixed structure is arranged, schematically comprising an upstream part 34 and a downstream part 36, which form the engine housing or stator 38. This housing E is sealed upstream by seals at the same level as the bearings that allow the passage of the fan shaft 30, and downstream by seals at the same level as the passage of the LP shaft 28.

[0055] Figure 2 A gear reducer 32 is shown, which can take different structural forms depending on whether some components are fixed or rotating. On the input side, the gear reducer 32 is connected to the LP shaft 28, for example, via internal splines 40a. The LP shaft 28 thus drives planetary pinions, known as sun gears 40. Traditionally, the rotation axis of the sun gear 40 is the same as the turbine's rotation axis X, which drives a series of pinions, known as planet gears 42, which are evenly distributed around the rotation axis X and have the same diameter. This diameter is equal to twice the running center distance between the sun gear 40 and the planet gears 42. For this type of application, the number of planet gears 42 is usually limited to between three and seven.

[0056] A set of planetary gears 42 are held by a frame called a planet carrier 44. Each planetary gear 42 rotates about its own axis and meshes with a ring gear 46.

[0057] In epicyclic configuration, a set of planetary gears 42 drives a planet carrier 44 about the turbine axis X. A ring gear 46 is fixed to the casing or stator 38 of the engine via a ring gear carrier 48 , and the planet carrier 44 is fixed to the fan shaft 30 .

[0058] In a planetary configuration, a set of planet gears 42 are held by a planet carrier 44 attached to the engine or stator housing 38. Each planet gear 42 drives a ring gear 46, which is attached to the fan shaft 30 via a ring gear carrier 48.

[0059] Each planet gear 42 is mounted so as to rotate freely using a bearing 50 (e.g., a bearing or hydrodynamic bearing type). Each bearing 50 is mounted on one of the shafts 44b of the planet carrier 44, and all the shafts are positioned relative to each other using one or more structural frames 44a of the planet carrier 44. The number of shafts 44b and bearings 50 is equal to the number of planet gears 42. The shafts 44b and frames 44a may be divided into multiple parts for handling, assembly, manufacturing, inspection, repair, or replacement.

[0060] For the same reasons as above, the gear reducer teeth can be divided into a plurality of propellers, in particular upstream and downstream propellers, relative to the so-called symmetry plane of the gear reducer and relative to the direction from upstream to downstream according to the engine. In the embodiment of the present application, we have detailed the operation of a gear reducer with multiple propellers, in which the ring gear 46 of the gear reducer is divided into two half ring gears 46a and 46b.

[0061] The upstream half ring gear 46a comprises a backing ring 46aa and a mounting half flange 46ab. The upstream propeller of the gear reducer is located on the backing ring 46aa. The upstream propeller meshes with the planetary gears 42, which in turn mesh with the sun gear 40.

[0062] The downstream half ring gear 46b comprises a backing ring 46ba and a mounting half flange 46bb. The rear propeller of the gear reducer is located on the backing ring 46ba. The downstream propeller meshes with the planetary gears 42, which in turn mesh with the sun gear 40.

[0063] Mounting half flange 46ab of upstream ring gear 46a and mounting half flange 46bb of downstream ring gear 46 form mounting flange 46c of ring gear 46. Ring gear 46 is attached to the ring gear carrier by assembling ring gear mounting flange 46c and mounting flange 48a of ring gear carrier 48 together using, for example, bolted connections.

[0064] Figure 2 The arrows in FIG. 3 depict the oil flow in the gear reducer 32. Oil is supplied from the stator assembly 38 to the gear reducer 32 via various components (which will not be described in detail in this figure as they are specific to the type of gear reducer construction) into the oil supply, in this case into the flow divider 52.

[0065] The splitter 52 is divided into two sections, each typically consisting of an equal number of overlapping planetary gears. The nozzle 52a of the splitter 52 lubricates the teeth, while the arm 52b of the splitter 52 lubricates the bearings. Oil is supplied to the nozzle 52a and exits at the nozzle end 52c to lubricate the teeth.

[0066] Oil is also supplied to the arm 52b and circulates through the bearing supply port 52d. The oil then flows through the shaft into one or more buffer areas 44c and out through the orifice 44d to lubricate the bearings of the planetary gear 42.

[0067] Conventional designs use a single cup-shaped piece ( Figure 2 Under these conditions, since the nozzle 52a and the arm 52b are supplied by the same cup and the injectors of the same injection system, the distribution of the oil flow between the locations to be lubricated cannot be adjusted.

[0068] These conventional designs also do not differentiate between the type of lubricant used, particularly with respect to viscosity, temperature or filtration, so that lubricants with different properties can be used to suit the needs of the component or gear being lubricated.

[0069] Additionally, in these common designs, the nozzle 52a and arm 52b are centrifugally fed by a single cup placed at a specific diameter, resulting in the end of the arm 52b (which has a larger diameter than the nozzle 52a) experiencing significant pressure losses.

[0070] Another oil supply device features two coaxial, stepped, annular lubrication cups. Each cup feeds a different oil distribution circuit of the gear reducer and is configured to receive oil from two oil spray members, thereby creating two independent lubrication stages. The oil spray members are spray manifolds that provide centrifugal oil spray. Consequently, the spray manifolds are located close to the gear reducer's axis and are difficult to install.

[0071] The present invention overcomes this drawback by proposing a classifying impeller with a separate cup, which can be fed centripetally by an injection manifold further from the axis X and is therefore easier to install.

[0072] Similar to the above design, Figure 3 An oil supply device 54 is shown, which is intended to supply oil to at least two oil distribution circuits 54a, 54b connected to the planet carrier 44 of an epicyclic gear reducer, which includes at least one sun pinion 40, a planet carrier, and a ring gear (not shown) that rotate relative to each other. It should be noted that this oil supply device 54 can also be adapted to supply oil to a differential gear reducer.

[0073] The oil comes from an oil injection system 58 comprising at least one oil injection member fixed relative to the gear reducer 32. The oil supply device 54 comprises at least one lubricating annular cup 56a integral with said planet carrier 44 and having a substantially annular shape and radially open relative to the axis X of the gear reducer 32. The wall of the cup 56a delimits a chamber 59a which receives the oil coming from the oil injection member 58 and supplies it to at least one oil distribution circuit 54a.

[0074] The present invention is innovative with respect to the prior art in that the oil supply device 54 further comprises a lubricating annular cup 56b so as to be staged into at least two independent stages, each stage comprising cups 56a, 56b.

[0075] A lubricating annular cup 56b is also integral with the planet carrier 44 and is substantially annular and radially open with respect to the axis X of the gear reducer 32. The wall of the cup 56b delimits a chamber 59b which receives oil from the oil injection member 58 and supplies it to the further oil distribution circuit 54b.

[0076] The cups 56 a , 56 b are coaxial along the axis X of the gear reducer 32 , have different diameters, and are each able to advantageously receive oil delivered with a centripetal and / or axial component to supply each independently the associated oil circuit 54 a , 54 b .

[0077] In the remainder of this specification, the oil supply device 54 is considered to include two cup-shaped members 56 a, 56 b, but it should be understood that this structure does not limit the present invention, and the oil supply device 54 may include more cup-shaped members.

[0078] In any case, the oil supply device 54 includes at least one first annular cup 56a, an oil distribution circuit 54a associated with the first annular cup, the oil distribution circuit including a plurality of nozzles 60a, which are angled and evenly distributed around the axis X of the gear reducer, which nozzles are arranged close to the sun pinion and / or the planetary gears and spray the sun pinion 40 and / or the planetary gears 42.

[0079] like Figure 7 As shown in detail, the first cup 56a comprises a first substantially annular wall 62a facing the planet carrier 44, and a second substantially annular wall 64a opposite thereto, both transverse to the axis X of the gear reducer and connected by a third peripheral wall 66a. The walls 62a, 64a and 66a delimit at least one oil reservoir 59a corresponding to the chamber delimited thereby and supplying the oil distribution circuit 54a.

[0080] The nozzle 60a is shown here as being flanged on the first cup 56a, but this configuration is not limiting of the present invention. The nozzle 60a is shown as being flanged on the first wall 62a and, for this purpose, includes a cylindrical bearing 68a that engages in a borehole 70a formed in the first wall 62a, as well as a shoulder 71a located on the wall and traversed by a screw 73a received in the first wall 62a to secure the flanged nozzle 60a. The borehole 70a forms a conduit connecting the oil reservoir 59a to the nozzle 60a.

[0081] Alternatively, the nozzle 60a may be integrally integrated into the cup 56a.

[0082] Similarly, the oil supply device 54 comprises a second annular cup 56 b , the oil distribution circuit 54 b of which supplies the bearings (not shown) of the planetary gears 42 on the planetary carrier 42 .

[0083] For example, Figure 5 As shown in detail, cup-shaped member 56b includes a first, generally annular wall 62b facing the planet carrier and an opposing, generally annular second wall 64b, both of which are transverse to the axis of the gear reducer and connected by a third peripheral wall 66b. Walls 62b, 64b, and 66b define at least one oil reservoir 59b, which corresponds to the chamber defined thereby and supplies oil to oil distribution circuit 54b. First wall 62b includes a conduit 70b connecting reservoir 59b to the bearings of planetary gears 42. This connection is achieved via an externally threaded adapter 75b. Adapter 75b is integral with the shaft of the bearing of planetary gear 42 and connects to the internally threaded interface formed by conduit 70b, within which the adapter is housed.

[0084] The novelty of the present invention lies in the fact that the chambers of the oil reservoirs 59 a, 59 b are supplied with oil by axial jets along the axis X and / or centrifugal and / or tangential jets rotating in the direction of the gear reducer axis X, unlike known prior art designs that use centrifugal jets rotating away from the gear reducer axis X. The oil jets are directed axially in a direction parallel to the axis X and facing the cups 56 a, 56 b associated therewith, or centripetally in a radial direction facing the axis X, or tangentially or according to an oblique direction combining these two directions.

[0085] As long as the jet direction includes at least one centripetal radial component facing the axis X, this configuration can use an oil injection system 58 that is not very close to the LP shaft 28 and is therefore easier to install. Figure 3 and Figure 5As shown, this LP shaft 28 is intended to compensate for the effects of misalignment within the turbine, which is usually equipped with a large radially flexible device 29 of the bellows type, which is located near the gear reducer 32. The use of an oil injection system 58 with a centripetal component makes it possible to install this system around the flexible device 29 without affecting the overall axial dimensions when coupling the gear reducer 32 to the LP shaft 28.

[0086] In general, each cup-shaped member 56a, 56b has an outer part having a substantially U-shaped cross-section that opens radially toward the axis, which cross-section corresponds to the first wall 62a, 62b, the second wall 64a, 64b and the third wall 66a, 66b that delimit the oil reservoir 59a, 59b, and each cup-shaped member also has an inner part that delimits the groove and extends from the branches of the U-shaped cross-section to the outer part, that is, starting from the first wall 62a, 62b.

[0087] The third walls 66a, 66b of the cups 56a, 56b are arranged on the opposite side of the axis of the gear reducer with respect to the chamber forming the oil reservoir 59a, 59b that they define. Each first wall 62a, 62b is extended by an annular groove 72a, 72b that extends axially beyond the second wall 64a, 64b and is configured to receive the oil injected by the injection member of the oil injection system 58.

[0088] In the accompanying figures, without limitation, the grooves 72a, 72b are substantially J-shaped, and the recesses 74a, 74b of the grooves are directed away from the axis X of the gear reducer 32, thereby receiving an oil jet inclined according to a direction having at least one radial centripetal component and an axial component facing the axis X or an axial and tangential component facing the cup-shaped members 56a, 56b.

[0089] Alternatively, the grooves 72a, 72b may be V-shaped and fed in the same way, or may be L-shaped openings opposite the cups and, in this case, may be fed with oil by purely axial oil jets or axial and tangential oil jets.

[0090] The structure also allows the oil supply device 54 to be supplied by a staged oil injection system 58 , which includes at least two independent oil injection members 58 a , 58 b , each of which supplies a corresponding cup 56 a , 56 b of the oil supply device 54 .

[0091] This configuration is particularly advantageous because it avoids the inherent pressure drop problem of supplying oil from a single cup and because it allows for differential oil supply to cups 56a, 56b. Thus, the type of lubricant used can be differentiated, particularly with respect to viscosity, temperature, or filtration, so that lubricants with different properties can be used to suit the needs of the components or gears being lubricated. For example, the bearings of planetary gears 42 can be supplied with oil that is different from the oil used to lubricate the gears between sun gear 40 and planetary gears 42. Thus, each oil injection member 58a, 58b is supplied with oil adapted to the needs of the components of gear reducer 32, thereby lubricating the components of the gear reducer through the corresponding cups 56a, 56b.

[0092] Therefore, the oil used may be different oils filtered in different ways to obtain oils comprising different minimum particle sizes in order to meet different and specific lubrication needs.

[0093] like Figure 3 、 Figure 5 、 Figure 7 and Figure 9 As shown, each oil injection member 58a, 58b has an annular tubular manifold 76a, 76b, the diameter of which is substantially slightly larger than the diameter of the groove 72a, 72b of the corresponding cup-shaped member 56a, 56b, and the manifold includes evenly distributed holes 78a, 78b. Figure 5 and Figure 7 As shown, these holes 78a, 78b are turned towards the grooves 72a, 72b of the cups 56a, 56b at an angle relative to the axis X in order to improve the oil supply. Preferably, this angle is chosen so that the jet has a radial component towards the axis X, an axial component towards the cups 56a, 56b and possibly a tangential component, i.e. perpendicular to the axis X. Figure 3 、 Figure 5 and Figure 7 plane.

[0094] In addition, if Figure 9 As shown, each oil injection member 58a, 58b includes at least one integral radial oil supply pipe 80a, 80b leading to the annular manifold 76a, 76b. Preferably, each oil injection member 58a, 58b includes a plurality of evenly distributed pipes 80a, 80b to ensure uniform oil supply to the manifold 76a, 76b in terms of flow rate and velocity.

[0095] It should be noted that the manifolds 76a, 76b need not be continuous. For example, each oil injection member 58a, 58b may include multiple angled segments of an annular manifold 76a, 76b, each segment being supplied with oil by at least one conduit 80a, 80b.

[0096] The oil injection components are carried by the turbine housing (not shown). Therefore, they do not need to be connected to each other. If the oil injection components are separated from each other, the jet of one oil injection component will not interfere with the jet of another oil injection component, which is another advantage of the present invention.

[0097] The same is true for the cup-shaped members 56a, 56b, which may or may not be connected together by structural arms, depending on the coaxiality, stiffness and statically indeterminate constraints during assembly.

[0098] In the non-limiting embodiment described in detail herein, cup 56a is connected to cup 56b by structural arms 57, such as Figure 4 The cup-shaped pieces 56a, 56b then form the impeller 54.

[0099] The oil supply device is mounted on the planet carrier in a flange manner by means of axial elements (e.g. screws passing through holes 55), as shown in FIG. Figure 4 、 Figure 6 and Figure 8 shown.

[0100] Various components are provided to balance the impeller 54 .

[0101] For example, at least one cup-shaped member may include extra thickness that may be locally machined to balance the cup-shaped member.

[0102] Here, if Figure 5 As shown, the second wall 64b of the cup 56b includes additional thickness in a region 65b that may be locally machined to balance the cup 56b.

[0103] Alternatively, at least one cup may include a region capable of receiving at least one balancing weight therefrom.

[0104] Here, if Figure 5 and Figure 7 As shown, the second wall 64a of the cup 56a includes a region 65a that is capable of receiving at least one balancing weight (not shown) from the cup 56a.

[0105] Additionally, a means is provided to improve the collection of oil by the grooves 72a, 72b of the cups 56a, 56b and its delivery to the oil reservoirs 59a, 59b.

[0106] For this reason, Figure 4 、 Figure 6 and Figure 8As shown, the outer part of each cup-shaped element 56a, 56b, i.e., the part corresponding to the first wall 62a, 62b, the second wall 64a, 64b and the third wall 66a, 66b, delimits the oil reservoir 59a, 59b, which is angularly divided between the first wall 62a, the second wall 64b and the first wall 62b, the second wall 64b, respectively, into adjacent compartments 82a, 82b, which define a plurality of oil reservoirs 59a, 59b. This delimitation is ensured by axial walls 84a, 84b arranged at the angular ends of these compartments 82a, 82b.

[0107] As shown in the non-limiting exemplary embodiment illustrated herein, each cup 56a, 56b includes five compartments 82a, 82b, but it should be understood that this number is not limiting of the present invention.

[0108] Advantageously, as Figure 6 and Figure 8 As shown, the free ends 86a, 86b of the walls 84a, 84b are inclined and slope towards the axis X of the gear reducer, thereby allowing oil to flow from the reservoir 59a, 59b of one compartment 82a, 82b to the reservoir 59a, 59b of an adjacent compartment.

[0109] Walls 84a and 84b may be sloped to help direct the oil.

[0110] The annular grooves 72a, 72b are continuous along the entire periphery of the respective cup-shaped members 56a, 56b.

[0111] This structure improves the oil distribution between the compartments.If all oil reservoirs 59a, 59b are full, the oil will overflow to the axis X of the gear reducer 32.

[0112] In addition, the channel-shaped inner portion of each cup-shaped member 56a, 56b includes fins 88a, 88b that extend generally radially between the channel 72a, 72b and at least the second wall 62a, 62b. These fins 88a, 88b are configured to centrifugally drive oil to the bottom of the corresponding oil reservoir 59a, 59b. Note that the fins 88a, 88b may extend beyond the second wall 62a, 62b and to the bottom of the corresponding oil reservoir, i.e., to the third peripheral wall 66a, 66b.

[0113] exist Figures 4 to 8 In the drawings, radial fins 88a, 88b have been shown, but these fins may also be inclined with respect to the radial direction and / or have a blade profile.

[0114] exist Figure 4 、 Figure 6 and Figure 8In the embodiment shown, each cup 56a, 56b comprises an inner part associated only with a series of coaxial reservoirs 59a, 59b and an associated inner part, these inner and outer parts occupying the entire radial footprint of the cup.

[0115] It is entirely conceivable that the cup-shaped member comprises a plurality of series of coaxial outer and inner members separated by different angles, thereby forming an angular continuous pattern forming reservoirs placed on different diameters and delivery nozzles placed on different diameters.

[0116] The present invention also provides a method of assembling an epicyclic or planetary gear reducer, which includes a lubrication assembly including an oil supply device 54 and an oil injection system 58 .

[0117] like Figure 10 As shown, the method comprises a first step ET1 of assembly of the gear reducer 32 , in which the sun pinion 40 , the planet carrier 44 with its planetary gears 42 and the ring gear 46 are assembled together.

[0118] Then, in a second step ET2 , the oil supply device 54 is introduced into the gear reducer 32 .

[0119] Then, in a third step ET3 , the turbine is mounted, the LP turbine shaft 28 of which is configured to be inserted into the sun gear 40 , and the oil injection system 58 is attached to the casing (not shown) of said turbine.

[0120] Finally, in a fourth step ET4, the gear reducer is inserted into the engine frame by inserting the LP turbine shaft 28 into the sun gear. Once the gear reducer is installed, the oil injection system 58 is naturally in the ideal position to supply oil to the impeller 54.

[0121] The present invention can provide differentiated, simple, reliable and effective lubrication to various components of a gear reducer of a turbine.

Claims

1. An oil supply device (54), extending about an axis (X), for supplying oil to two different oil distribution circuits (54a, 54b) of a gear reducer (32), the gear reducer (32) comprising at least one sun pinion (40), a planet carrier (44) and a ring gear (46) which are capable of relative rotational movement relative to each other, the oil coming from at least one oil injection member (58a) fixed relative to the gear reducer (32), the oil supply device (54) being fixed to the planet carrier (44) and comprising an annular lubricating cup (56a), the annular lubricating cup being configured to receive oil from the at least one oil injection member (58a) and capable of supplying oil to one of the oil distribution circuits (54a, 54b), The oil supply device (54) comprises at least one further annular lubrication cup (56b) so as to be able to be graded into at least two independent lubrication stages, the further annular lubrication cup (56b) being configured to receive oil from a further oil injection member (58b) and to be able to supply oil to a further oil distribution circuit (54b), each annular lubrication cup supplying a different oil circuit (54a, 54b) associated therewith, the annular lubrication cups (56a, 56b) being coaxial and having different diameters, The annular lubrication cup is configured to receive oil axially in a direction parallel to the axis (X) and facing the annular lubrication cup (56a, 56b) associated therewith, or centripetally in a radial direction facing the axis (X), or tangentially, or according to an oblique direction combining the two said directions, At least one annular lubricating cup (56a, 56b) has an outer part and an inner part, the outer part having a substantially U-shaped cross section, the U-shaped cross section opening in a radial direction toward the axis (X), the inner part extending from a branch of the U-shaped cross section to the outer part, the inner part defining a J-shaped or V-shaped groove (72a, 72b), the J-shaped or V-shaped groove being configured to receive an oil jet inclined according to a direction having at least one radial centripetal component facing the axis (X) and an axial component or an axial and tangential component facing the annular lubricating cup (56a, 56b); or the inner part defining an L-shaped groove opening opposite the annular lubricating cup (56a, 56b), the L-shaped groove opening being fed by a purely axial oil jet or an axial and tangential oil jet, It is characterized by: The annular lubrication cup (56a, 56b) is circumferentially divided into adjacent compartments (82a, 82b) defining a plurality of oil reservoirs (59a, 59b) supplying the oil distribution circuit (54a, 54b), the plurality of oil reservoirs being separated by axial walls (84a, 84b) arranged at the angular ends of the compartments (82a, 82b), the free ends (86a, 86b) of the axial walls (84a, 84b) being inclined toward the axis (X) of the gear reducer (32) so as to enable oil to flow from the oil reservoir (59a, 59b) of one compartment (82a, 82b) to the oil reservoir (59a, 59b) of an adjacent compartment (82a, 82b).

2. The oil supply device (54) according to claim 1, characterized in that The oil supply device (54) at least comprises: - a first annular lubricating cup (56a), the oil distribution circuit (54a) associated with said first annular lubricating cup comprising a plurality of nozzles distributed circumferentially around said axis (X), said nozzles supplying oil to said sun pinion (40) and / or planetary gears (42), and - a second annular lubrication cup (56b), the oil distribution circuit (54b) of which is associated therewith, supplies oil to the bearings of the planetary gears (42) of the planetary carrier (44).

3. The oil supply device (54) according to claim 1, characterized in that The grooves (72a, 72b) include fins (88a, 88b) extending substantially in radial direction, the fins being arranged to drive the oil at the bottom of the oil reservoir (59a, 59b) by centrifugal action.

4. The oil supply device according to claim 3, characterized in that: The fins (88a, 88b) are radial or inclined relative to the radial direction and / or have a blade profile.

5. The oil supply device according to claim 1 or 2, characterized in that: Each annular lubrication cup (56a) is connected to an adjacent annular lubrication cup (56b) by a structural arm (57).

6. The oil supply device (54) according to claim 1, characterized in that At least one annular lubrication cup (56b) includes extra thickness that can be locally machined to enable balancing of the annular lubrication cup (56b).

7. The oil supply device (54) according to claim 1, characterized in that At least one annular lubrication cup (56a) comprises a region (65a) capable of receiving at least one weight for balancing the annular lubrication cup (56a).

8. An oil injection system (58) for supplying oil to an oil supply device (54) according to one of claims 1 to 7, characterized in that: The oil injection system is staged and comprises at least two different oil injection members (58a, 58b), each oil injection member feeding a corresponding annular lubricating cup (56a, 56b) of the oil supply device (54).

9. The fuel injection system (58) according to claim 8, characterized in that Each oil injection member (58a, 58b) of the annular lubricating cup comprises an annular tubular injection manifold (76a, 76b), or a plurality of angled segments of the annular tubular injection manifold, the diameter of the segments being substantially slightly larger than the diameter of the corresponding annular lubricating cup (56a, 56b), the segments comprising circumferentially distributed holes (78a, 78b) intended to be oriented towards the opening of the groove of the corresponding annular lubricating cup (56a, 56b), and at least one main radial duct (80a, 80b) for supplying oil to the annular tubular injection manifold (76a, 76b) or the angled segments of the annular tubular injection manifold.

10. The fuel injection system (58) according to claim 8 or 9, characterized in that Each of the oil spraying members (58a, 58b) is supplied with oil adapted to the requirements of the components of the gear reducer (32) lubricated by the corresponding annular lubricating cup (56a, 56b).

11. A lubrication assembly for an epicyclic gear reducer, characterized in that: The lubrication assembly comprises an oil supply device (54) according to any one of claims 1 to 7 or an oil injection system (58) according to any one of claims 8 to 10.

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