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    • 专利摘要:
    Distributor (13) of lubricating oil for a mechanical reducer of a turbomachine, in particular of an aircraft, characterized in that it has a generally annular shape around an axis X and is formed in one piece, this distributor comprising first and second independent oil circuits (20, 21), said first oil circuit (20) comprising a first oil inlet (20a) connected by a first annular chamber (20b) to several oil outlets (20c) distributed over a first circumference C1 around said axis X, and said second oil circuit (21) comprising a second oil inlet (21a) connected by a second annular chamber (21b) to several oil outlets ( 21c) distributed over a second circumference C2 around said axis X, the first and second circumferences having different diameters. Figure for the abstract: Figure 5
    公开号:FR3088977A1
    申请号:FR1871757
    申请日:2018-11-23
    公开日:2020-05-29
    发明作者:Michel Pierre Di Giovanni Jean-Charles
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    Description
    Title of the invention: LUBRICATING OIL DISTRIBUTOR FOR A MECHANICAL REDUCER OF AIRCRAFT TURBOMACHINE
    Technical Field [0001] The present invention relates to the field of mechanical reducers for turbomachinery in particular of aircraft.
    PRIOR ART [0002] The state of the art includes in particular documents WO-A1-2010 / 092263, LR-A1-2 987 416 and LR-A1-3 041 054.
    The role of a mechanical reducer is to modify the speed and torque ratio between the input axis and the output axis of a mechanical system.
    The new generations of turbofans with double flow, in particular those having a high dilution rate, include a mechanical reducer to drive the shaft of a fan (also called "fan"). The usual purpose of the reduction gear is to transform the so-called rapid rotation speed of the shaft of a power turbine into a slower rotation speed for the shaft driving the fan.
    Such a reducer comprises a central pinion, called a sun gear, a crown and pinions called satellites, which are engaged between the sun and the crown. The satellites are held by a chassis called the planet carrier s. The sun, the crown and the planet carrier are planetary because their axes of revolution coincide with the longitudinal axis X of the turbomachine. The satellites each have a different axis of revolution distributed equally over the same operating diameter around the axis of the planets. These axes are parallel to the longitudinal axis X.
    There are several reducer architectures. In the state of the art of double-flow turbomachines, the reducers are of the planetary or planetary type. In other similar applications, so-called differential or "compound" architectures exist.
    - On a planetary gearbox, the planet carrier is fixed and the crown constitutes the output shaft of the device which rotates in the opposite direction to the sun.
    - On a planetary reduction gear, the crown is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the sun.
    - On a differential gearbox, no element is fixed in rotation. The crown rotates in the opposite direction to the sun and the planet carrier.
    The reducers can be composed of one or more meshing stages. This meshing is ensured in different ways such as by contact, by friction or by magnetic fields.
    There are several types of contact meshing such as with straight or chevron teeth.
    The present invention provides an improvement of a reducer with a simple, effective and economical solution to improve the circulation and / or the evacuation of the oil in a turbomachine.
    Summary of the invention The invention has several aspects.
    According to a first aspect, the invention relates to a deflector for a mechanical reduction gear of a turbomachine, in particular of an aircraft, this deflector being intended to be interposed between two adjacent satellites of said reduction gear, this deflector comprising a block comprising a first surface lateral which is cylindrical and concave and which has a radius of curvature RI measured from an axis Gl, the block comprising a second lateral surface, opposite said first surface, which is cylindrical and concave and which has a radius of curvature RI measured from a axis G2 which is parallel to Gl, characterized in that it comprises on each of said first and second surfaces at least one protruding tongue which has a generally elongated shape around the axis Gl, G2 of the surface considered and whose periphery internal is concave curved and has a radius of curvature R2 measured from this axis Gl, G2 which is less than RI.
    The deflector thus comprises tabs on these cylindrical surfaces surrounding the satellites. Each of these tabs is configured to be engaged in an inter-helix groove of the teeth of a satellite, and to extend along this groove. A satellite indeed comprises a toothing with at least two helices (respectively front and rear), that is to say a toothing comprising two adjacent serrated annular bands. These two propellers are separated from each other by an annular groove. It is therefore understood that the propellers of a satellite are separated by the tongue of a deflector, in the location of this deflector. The tab has a function of "inter-helix deflector" which is added to the main function of the "inter-satellite deflector".
    This first aspect of the invention makes it possible to prevent the recirculation of oil and particles between the front and rear propellers of the satellites. The gains brought by this deflector are numerous: no oil recirculation between the propellers therefore better evacuation of the calories generated in operation, limitation of particle transitions, stiffening of the deflector structure, etc.
    This first aspect of the invention is compatible with any type of reducer (planetary, planetary, etc.). It is also compatible with any type of toothing (straight, chevron) provided that this toothing has at least two propellers. It is also compatible with any type of planet carrier, whether monobloc or cage-cage type. Finally, it is compatible with any type of satellite bearing, whether it is composed of rolling elements, a hydrodynamic bearing, etc.
    The deflector according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with each other:
    - The deflector comprises a single tongue projecting from each of said surfaces, preferably substantially in the middle of the surface; functionally, it is preferably facing the groove or groove of the satellites which is between their two propellers,
    the deflector comprises several tabs projecting from each of said surfaces,
    - each tab has a circumferential extent which is less than or equal to the circumferential extent of the surface on which it is located,
    - each tab has a circumferential extent which is greater than the circumferential extent of the surface on which it is located; end portions of the tabs can thus extend projecting from the deflector,
    the deflector comprises tapped holes for receiving the screws for fixing the deflector to a planet carrier of said reduction gear,
    - the deflector includes an integrated lubrication circuit,
    - said circuit comprises an oil inlet connected by holes to at least one oil outlet,
    - said oil inlet comprises a connection tube by male-female fitting,
    - the deflector comprises an oil outlet intended to receive a sealed fluid connection socket,
    - The deflector comprises an oil outlet formed by a nozzle formed in one piece with said block, this nozzle preferably having a generally elongated shape and extending in a median plane of symmetry of said block.
    This makes the nozzle more rigid in the cantilever lubrication of the solar grooves, and limit the number of parts and interfaces by merging the known functions of the deflector and the nozzle while retaining facilitating assembly. of the deflector. The gains made include: a shorter nozzle (less subject to vibrations), fewer parts and therefore fewer references, less machining and less assembly, etc.
    The invention also relates to a planet carrier for a mechanical reducer of a turbomachine, in particular of an aircraft, comprising a cage defining a housing for receiving a central solar unit of axis X of rotation, of satellites arranged around the solar and each comprising a double helical toothing, as well as deflectors as described above which are each fixed to the cage and interposed between two adjacent satellites so that their tongues are engaged in inter-helical grooves of the teeth of the satellites .
    Advantageously, one of the deflectors of the planet carrier comprises a nozzle which is oriented in the radial direction relative to said axis X and inwardly so as to be able to spray oil on internal grooves of said solar .
    Advantageously, the cage has a radial wall comprising a central orifice, a radially internal peripheral edge comprises one or more notches to facilitate the mounting of the deflectors and in particular of that comprising the nozzle.
    According to a second aspect, the invention relates to a lubrication and cooling core for a mechanical reduction gear of a turbomachine, in particular of an aircraft, characterized in that it is intended to be mounted in an axis of a satellite of said reducer, and comprises first and second coaxial and substantially frustoconical flanges each comprising a first end of larger diameter and a second opposite end of smaller diameter, the flanges being fixed together by their second ends and being intended to extend to inside said axis and to cover at least one radially internal surface of this axis to define therewith at least one annular cavity for circulation of lubricating and cooling oil of this axis, said second ends of said first and second flanges comprising means for fluidly connecting said at least one cavity to a source of lubricating and cooling oil.
    The core has the function of receiving lubricating oil then distributing it and routing it to different elements of the reducer. The core has two separate circuits, which is advantageous since the circuits can circulate oil at different flow rates and / or temperatures and limit the transfer of pollution. The one-piece design of this core makes it easier to mount it in the gearbox, to optimize its mass, and to limit vibration phenomena. The diameter of this core is advantageously chosen to facilitate its integration into the reducer. The diameter of the reducer and in particular of its chambers is for example less than the external diameter of the planet carrier (or of the cage or the cage holder of the planet carrier) and greater than the external diameter of an input shaft of the reducer which is engaged in solar and coupled to solar. This input shaft may include a bellows section giving the shaft some flexibility in order to best take advantage of misalignments of the motor shaft.
    The gains provided by this aspect are: better integration of the core in the motor, a significant release of space to increase the size of the flexibility of the motor shaft (which allows better recovery of the misalignments of the reducer) , a potentially more rigid structure (and therefore less subject to vibration phenomena), the same connection interface possible for the different oil outlets, a shorter oil path with less pressure drop, etc.
    This second aspect of the invention is mainly designed for a planetary type reducer but could be compatible with an epicyclic reducer with a few adjustments. It is compatible with all types of teeth (straight, chevron), as well as any type of planet carrier, whether it is monobloc or cage and portecage type. Finally, this aspect is compatible with any type of satellite bearing, whether it is composed of rolling elements, a hydrodynamic bearing, etc.
    The core according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with one another:
    - each of said first ends, or also each of said second ends, has an outer cylindrical centering surface comprising an annular groove for receiving a seal,
    - one of said flanges comprises an internal chamber centered on an axis Y common to the flanges, this chamber being connected on the one hand by radial passages formed in this flange or between the two flanges at said at least one annular cavity, and d on the other hand to a connection tube centered on the Y axis,
    - said tubing is configured to cooperate by male-female fitting, in particular with a fluid connection socket which can be used to connect the tubing to a lubricating oil distributor,
    - Said chamber has a generally cylindrical shape centered on the Y axis and comprises a longitudinal end connected to the tubing and an opposite longitudinal end which is either closed or open and which opens into another chamber, this other chamber being formed in the other flange and being connected by other radial passages to said at least one annular cavity,
    - said flanges are configured to be fixed to each other and only to one another,
    - said flanges are configured to be fixed to each other as well as to an annular flange for fixing said satellite axis,
    - The flanges are supported on either side of said flange; as there is no more play, the kernel cannot translate along the Y axis; the assembly is therefore less hyperstatic,
    - the flanges are fixed by one or more screws distributed around the Y axis; as the fixing means do not coincide with the axis of the bearing and it passes through a passage hole of the latter, this prevents the core from rotating on itself; the nucleus therefore has its last degree of freedom blocked,
    - the core has an internal chamber which is dimensioned to ensure a distribution of the oil by its slowing down, making it possible to reduce the kinetic effects of the fluids.
    The invention also relates to a satellite axis for a mechanical reduction gear of a turbomachine, in particular of an aircraft, this axis having a generally tubular shape and comprising substantially radial orifices extending between at least one radially internal surface of this axis and the outer periphery of this axis, a core as described above being mounted in this axis and covering said at least one surface.
    The axis according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with each other:
    - the outer periphery of the axis is configured to define at least one, and preferably two, bearing race track (s),
    - The internal periphery of the axis is of the biconical type and comprises in particular two coaxial frustoconical surfaces and flaring in opposite directions, these two frustoconical surfaces being covered by said flanges and defining with these flanges one or two annular cavity (ies) (s) for oil circulation.
    According to a third aspect, the invention relates to a lubricating oil distributor for a mechanical reducer of a turbomachine, in particular of an aircraft, characterized in that it has a generally annular shape around an axis X and is formed in one piece, this distributor comprising first and second independent oil circuits, said first oil circuit comprising a first oil inlet connected by a first annular chamber to several oil outlets distributed over a first circumference C1 around said axis X, and said second oil circuit comprising a second oil inlet connected by a second annular chamber to several oil outlets distributed over a second circumference C2 around said axis X, the first and second circumferences having different diameters.
    The axis of a reduction gear satellite is guided by at least one bearing. The heat generated by the passage of the moving parts of the bearing must be removed. The bearing is supplied with oil through orifices passing radially through the axis of the satellite. The circulation of this oil inside the satellite axis and in particular on the internal periphery of the axis, makes it possible to absorb the calories generated by the bearing in operation. These calories are transmitted by conduction from the inner ring of the bearing, which can be integrated into the outer periphery of the axis of the satellite, up to the inner periphery of this axis. The invention applies to various forms of the internal periphery of the satellite axis, and for example a biconical internal periphery. The use of two independent flanges makes it possible to marry all forms of the internal periphery of an axis, and in particular a biconical form, in order to form one or more oil circulation cavities for the lubrication and the cooling of the axis.
    The proposed solution is compatible with any type of reducer (planetary, planetary, etc.). This solution is compatible with all types of teeth (straight, chevron), and all types of planet carrier, whether monobloc or cage-cage type. Finally, the solution is only compatible with satellite bearings composed of rolling elements (ball bearings, roller bearings, tapered rollers, etc.).
    The distributor according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with one another:
    - said first and second inputs are oriented in the radial direction relative to said axis X,
    - said first and second entrances are located in the same plane perpendicular to said axis X and are inclined with respect to one another by a determined angle,
    said first and second chambers have an generally circular shape in axial section,
    said first and second chambers are formed by two coaxial tubular rings which are intimately linked,
    the diameter of said first circumference C1 is less than those of said rings, and the diameter of said second circumference C2 is greater than those of said rings,
    - said outlets are oriented axially in the same direction,
    the distributor comprises fixing lugs comprising orifices for the passage of screws,
    - Said first and second chambers each have a diameter greater than the external diameter of a portion of a shaft intended to pass axially through the distributor; this shaft is an input shaft of the reducer,
    - The diameter and the orientation of said first and second chambers are arranged so that the oil outlet conduits are of similar length; this arrangement also makes it possible to have oil inlet conduits of the shortest length, of the most linear shape while having a comfortable radius of curvature; this also allows the circular section conduits to open fully and tangentially to their respective chambers; it is thus possible to fulfill all these conditions while having the axes of the oil inlets on the same median plane; on the one hand, it is advantageous to have short oil inlets in order to be able to mount the distributor which is diametrically smaller than the diameter of the cage holder; on the other hand, it is advantageous to have linear conduits which open completely and tangentially into the chambers to reduce the pressure drops to a minimum;
    - all the oil outlets, whether connected to said first chamber or to said second chamber, are identical; this allows to have the same machining tools, the same controls and the same O-rings on the deflectors as those of the core,
    - at least some of the oil outlets are advanced so as to enter inside the axle and inside the rear flange of the core; this reduces the length of the oil duct and increases the rigidity of the assembly.
    The invention also relates to a planet carrier for a mechanical reduction gear for a turbomachine, in particular an aircraft, comprising a cage defining a housing for receiving a central solar unit of axis X of rotation and satellites arranged around the solar, a distributor as described above being attached and fixed on the cage.
    Advantageously, the cage comprises at its periphery axial housings intended to receive axial fingers secured to a cage holder of said reducer, each housing being traversed by a substantially radial pin which is intended to guide in rotation a connecting means , such as a ball joint or a bearing, carried by one of said fingers, said first and second inputs of said distributor being oriented respectively in first and second directions which each pass through a sector of free space axially delimited by the cage and the holder cage and extending circumferentially between two adjacent fingers.
    The invention further relates to a mechanical gearbox for a turbomachine, in particular an aircraft, comprising at least one of the elements (deflector, core, distributor, planet carrier, axis, etc., described in the foregoing, as well that a turbomachine comprising such a reducer.
    The characteristics of the different aspects of the invention can be combined with one another.
    Brief Description of the Drawings Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the attached drawings in which:
    [Fig.l] Figure 1 is a schematic view in axial section of a turbomachine using the invention, [fig.2] Figure 2 is an axial section in partial view of a mechanical reducer , [FIG. 3] FIG. 3 is a view in axial section of a mechanical reducer incorporating several aspects of the invention, [FIG. 4] [FIG. 4] is a perspective view of the reducer Figure 3, [fig.5] Figure 5 is a perspective view of a lubricating oil distributor of the reducer of Figure 3, [0048] [fig.6] Figure 6 is a view in section of a detail of the reducer of Figure 3 and shows an oil inlet of the distributor of Figure 5, [0049] [fig.7] Figure 7 is a sectional view of a detail of the reducer of the Figure 3 and shows an oil inlet of the dispenser of Figure 5, [Figure 8] Figure 8 is a sectional view of a detail of Figure 3 and shows a satellite axis in which is mounted a lubrication and cooling core ssement, [0051] [fig.9] Figure 9 is an exploded perspective view of the axis and the core of Figure 8, [0052] [fig. 10] Figure 10 is a sectional view along line X-X of Figure 8, [0053] [fig. 11] FIG. 11 is a view similar to that in FIG. 8 and shows the flow of lubricating and cooling oil, [0054] [fig. 12] Figure 12 is a view similar to that of Figure 8 and illustrating an alternative embodiment of the core, [0055] [fig. 13] FIG. 13 is a view similar to that in FIG. 12 and shows the path of lubricating and cooling oil, [0056] [fig. 14a] Figure 14a is a perspective view of a deflector, [0057] [fig. 14b] Figure 14b is a view similar to that of Figure 14a and illustrating an alternative embodiment of a deflector, [0058] [fig. 15] Figure 15 is a partial view in radial section of the reducer of Figure 3 and shows the position of the deflector of Figure 14 in this reducer, [fig. 16] Figure 16 is a sectional view along line XVI-XVI of Figure 15, [0060] [fig. 17] Figure 17 is a partial perspective view of a front face of the reducer of Figure 3, [0061] [fig. 18] Figure 18 is a view of the front face of the reducer of Figure 3, [0062] [fig. 19] Figure 19 is a schematic perspective view of the reducer of Figure 3, and shows a step of assembling this reducer, [fig. 20] Figure 20 is a schematic perspective view of the reducer of the FIG. 3, and shows a step of assembling this reducer, [FIG. 21] FIG. 21 is a schematic perspective view of the reducer of FIG. 3, and shows a step of assembling this reducer, [ [Fig.22] Figure 22 is a schematic perspective view of the reducer of Figure 3, and shows a step of assembling this reducer.
    Description of the embodiments FIG. 1 describes a turbomachine 1 which conventionally comprises a blower S, a low pressure compressor 1a, a high pressure compressor 1b, an annular combustion chamber 1c, a high pressure turbine Id , a low pressure turbine le and an exhaust nozzle Ih. The high pressure compressor 1b and the high pressure turbine Id are connected by a high pressure shaft 2 and form with it a high pressure body (HP). The low pressure compressor 1a and the low pressure turbine are connected by a low pressure shaft 3 and form with it a low pressure body (BP).
    The fan S is driven by a fan shaft 4 which is driven to the shaft BP 3 by means of a reducer 6. This reducer 6 is generally of the planetary or planetary type.
    Although the following description relates to a planetary or planetary type reducer, it also applies to a mechanical differential in which the three components, which are the planet carrier, the crown and the sun, are movable in rotation , the speed of rotation of one of these components depending in particular on the difference in speeds of the other two components.
    The reducer 6 is positioned in the front part of the turbomachine. A fixed structure schematically comprising, here, an upstream part 5a and a downstream part 5b which composes the motor casing or stator 5 is arranged so as to form an enclosure E surrounding the reduction gear 6. This enclosure E is here closed upstream by seals at a level allowing the crossing of the fan shaft 4, and downstream by seals at the level of the crossing of the BP shaft 3.
    Figure 2 shows a reducer 6 which can take the form of different architectures depending on whether certain parts are fixed or in rotation. At the input, the reduction gear 6 is connected to the BP shaft 3, for example by means of internal splines 7a. Thus the BP shaft 3 drives a planetary gear called the sun 7. Conventionally, the sun 7, whose axis of rotation coincides with that of the turbomachine X, drives a series of gears called satellites 8, which are equally distributed over the same diameter around the axis of rotation X. This diameter is equal to twice the operating distance between the solar 7 and the satellites 8. The number of satellites 8 is generally defined between three and seven for this type of application .
    The set of satellites 8 is held by a chassis called planet carrier 10. Each satellite 8 rotates around its own axis Y, and meshes with the crown 9.
    At the output we have:
    · In an epicyclic configuration, the set of satellites 8 rotates the planet carrier 10 around the axis X of the turbomachine. The crown is fixed to the crankcase or stator 5 via a crown holder 12 and the planet carrier 10 is fixed to the fan shaft 4.
    • In a planetary configuration, all of the satellites 8 are held by a planet carrier 10 which is fixed to the motor housing or stator 5. Each satellite drives the crown which is attached to the fan shaft 4 via a crown carrier 12.
    Each satellite 8 is mounted to rotate freely using a bearing 11, for example of the rolling or hydrostatic bearing type. Each bearing 11 is mounted on one of the axes 10b of the planet carrier 10 and all the axes are positioned relative to each other using one or more structural frames 10a of the planet carrier 10. There are a number of 'axes 10b and levels 11 equal to the number of satellites. For reasons of operation, assembly, manufacture, control, repair or replacement, the axes 10b and the chassis 10a can be separated into several parts.
    For the same reasons mentioned above, the teeth of a reduction gear can be separated into several helices each having a median plane P. In our example, we detail the operation of a reduction gear with several propellers with a crown separated in two half crowns:
    · A front half-crown 9a consisting of a rim 9aa and a half-fixing flange 9ab. On rim 9aa is the front propeller of the gear teeth. This forward propeller meshes with that of the satellite 8 which meshes with that of the solar 7.
    • A rear half-crown 9b consisting of a rim 9ba and a half-fixing flange 9bb. On the 9ba rim is the rear propeller of the gear teeth. This rear propeller meshes with that of the satellite 8 which meshes with that of the solar 7.
    If the helix widths vary between the sun 7, the satellites 8 and the crown 9 because of the toothing overlaps, they are all centered on a median plane P for the front propellers and on another median plane P for the rear propellers. In the other figures, in the case of a bearing with two rows of rollers, each row of rolling elements is also centered on two median planes.
    The fixing half-flange 9ab of the front ring 9a and the fixing half-flange 9bb of the rear ring 9b form the fixing flange 9c of the ring. The crown 9 is fixed to a crown holder by assembling the fixing flange 9c of the crown and the fixing flange 12a of the crown holder using a bolted mounting for example.
    The arrows in FIG. 2 describe the routing of the oil in the reducer 6. The oil arrives in the reducer 6 from the stator part 5 in the distributor 13 by various means which will not be specified in this view because they are specific to one or more types of architecture. The distributor is divided into 2 parts in general each repeated with the same number of satellites. The injectors 13a have the function of lubricating the teeth and the arms 13b have the function of lubricating the bearings. The oil is brought to the injector 13a to come out through the end 13c in order to lubricate the teeth. The oil is also brought to the arm 13b and circulates via the supply mouth 13d of the bearing. The oil then circulates through the axis in one or more buffer zones 10c and then exits through the orifices 10d in order to lubricate the bearings of the satellites.
    Figures 3 and 4 show an embodiment of a reducer 6 comprising several aspects of the invention.
    One of these aspects relates to a lubricating oil distributor and will be described in the following with reference to FIGS. 5 to 7. Another aspect of the invention relates to a lubrication and cooling core and will be described in what follows with reference to FIGS. 8 to 13, and finally a last aspect of the invention relates to a deflector and will be described in what follows with reference to FIGS. 14 to 22.
    The reducer 6 of Figures 3 and 4 comprises a planet carrier 10 of the cage type 14 and cage holder 15, the cage 14 and the cage holder 15 being connected by ball joints.
    The cage 14 comprises two radial annular walls 14a, 14b extending around the axis X, these walls 14a, 14b being parallel and being respectively a front radial wall 14a and a rear radial wall 14b. The walls 14a, 14b are connected to each other at their external peripheries by pairs of bridges 14c, 14d, regularly distributed around the axis X. These pairs of bridges provide a structural connection between the walls 14a, 14b. Each pair of bridges comprises two bridges, respectively radially external 14c and radially internal 14d, which extend substantially parallel along the axis X at a radial distance from each other.
    The pairs of bridges 14c, 14d define between them slots 16 which extend circumferentially around the axis X and are axially delimited by the external peripheral edges of the walls 14a, 14b. The pairs of jumpers are 5 in number in the example shown.
    Each pair of bridges form a yoke to accommodate a finger 15a of the cage holder 15. In other words, the bridges of each couple define between them a housing for receiving a finger 15a of the cage holder 15. Openings 14th oblong are made in the rear wall 14b so as to allow the fingers 15a to pass between the bridges 14c, 14d. The wall 14a may have similar openings axially aligned with the openings 14e of the wall 14b.
    The number of fingers 15a is equal to the number of pairs of bridges 14c, 14d and is 5 in the example shown. These fingers 15a extend axially projecting upstream from a ring 15b of the cage carrier 15 extending around the axis X. The fingers 15a of the cage carrier 15 are engaged in the inter-bridge housings by translation axial from the rear, through the openings 14e of the wall 14b.
    Each finger 15a comprises, substantially in the middle, a mounting recess of a bearing (not shown) intended to be crossed by a cylindrical pin 17 carried by each pair of bridges 14c, 14d. Each pin 17 passes through the inter-bridge housing and has a substantially radial orientation relative to the axis X. Each pin 17 comprises a cylindrical body 17a connected at one end, here radially external, to a flange 17b. The pin 17 is here engaged by radial translation from the outside through the radial orifices of the bridges 14c, 14d, its flange 17b being intended to come into radial abutment on a flat face 14ca of the external bridge 14c. After insertion of the pin 17 into the holes of the bridges, until the collar 17b is supported on the external bridge, the collar 17b is fixed to this bridge, for example by screwing.
    As can be seen in the drawings, in the assembled position, the ring 15b of the portage 15 is axially spaced apart by a predetermined distance L1 from the rear wall 14b opposite the cage 14 (FIG. 3). The annular space extending between the external periphery of the cage 14 and the external periphery of the cage holder 15 is sectorized by the fingers 15a which thus define between them sectors of space SI (FIG. 4).
    The cage 14 defines an internal housing for receiving the solar 7 of axis X, satellites 8 arranged around the solar 7 and meshed with it, as well as deflectors 18 which will be described in detail in the following with reference in Figures 14 and following.
    As described in the above in relation to Figure 2, the solar 7 includes internal splines 7a for coupling to external splines 3a complementary to the BP shaft 3 (Figure 3). It can be seen that the grooves 3a are located at the front end of the BP shaft 3 which includes a downstream section 3b in the form of a bellows. This section 3b is here located in a plane PI perpendicular to the axis X which is spaced axially from the cage 14 of the planet carrier 10 and which passes substantially through the ring 15b of the cage carrier 15 in our example. This section 3b gives the BP shaft 3 a certain flexibility limiting the transmission of the forces from the engine in operation to the reduction gear. The grooves 3a are here situated on a circumference C3 of axis X and of diameter D3, and the section 3b has an external diameter D3 ’which is greater than D3 and less than the internal diameter D5 of the ring 15b.
    The reducer 6 comprises a distributor 13 of improved lubricating oil which is better visible in FIG. 5.
    The dispenser 13 has a generally annular shape around the axis X and is formed in one piece. Here it is attached and fixed to the planet carrier 10 and for this includes lugs 19a for fixing to the cage 14 of the planet carrier and in particular on its rear wall 14b, as shown in FIG. 4. The lugs 19a are regularly distributed around the X axis and include portions applied to the downstream radial face of the wall 14b and comprising screw passage holes 19b screwed into tapped holes in the wall 14b.
    The dispenser 13 comprises first and second independent oil circuits 20, 21, the first oil circuit 20 comprising a first oil inlet 20a connected by a first annular chamber 20b to several oil outlets 20c distributed on a first circumference C1 around the axis X, and the second oil circuit 21 comprises a second oil inlet 21a connected by a second annular chamber 21b to several oil outlets 21c distributed over a second circumference C2 around the X axis (Figures 3 and 5).
    The circumference C1 has a diameter DI and the circumference C2 has a diameter D2, D2 being greater than Dl. The oil outlets 20c are on DI or Cl and the outlets 21c are on D2 or C2. In the example shown, DI and D2 are each greater than D3 and less than D5.
    The distributor 13 is diametrically smaller than D5 which allows its assembly / disassembly without the need to touch the rest. Because of the pins 17 and the deflectors 18, the cage and the cage holder are mounted first, then the solar 7, the satellites 8, the axes 10b and finally the distributor 13, as will be described in more detail in what follows.
    The external diameter of the distributor 13 corresponds to the end of the inlets 20a, 21a (which end at the same circumference).
    The chambers 20b, 21b are formed by two coaxial tubular rings and intimately linked, that is to say that their tubular walls are fused. The chambers have an generally circular axial section and the passage sections of the chambers are substantially constant over their entire angular extent and substantially identical to one another.
    The first chamber 20b extends substantially over a circumference C4 of diameter D4 between DI and D2. The second chamber 21b extends substantially over another circumference C4 'of diameter D4' between DI and D2. D4 ’is greater than D4. The circumferences C4 and C4 ’are centered on the X axis. DI is less than D4 and D4’ while D2 is greater than D4 and D4 ’. It is advantageous for C4 and C4 ’to be located substantially mid-way (radial) from C1 and C2, as this stiffens the distributor 13.
    The chamber 21b of larger diameter is located in front of that 20b of smaller diameter. As can be seen in FIG. 4, the chambers extending in planes P2, P3 perpendicular to the axis X, which pass between the cage 14, on the one hand, and the ring 15b of the cage carrier 15, on the other hand. It can also be seen in this figure that the plane P3 which passes through the second chamber 20b or rear chamber is close to the section 3b of the shaft BP 3 and its diameter D4 'is greater than that D3' of the section 3b to avoid any risk of contact in operation.
    The inputs 20a, 21a are oriented in the radial direction relative to the X axis. They are preferably located in the same plane P4 perpendicular to the X axis and are inclined relative to each other in this plane P4 of an angle determined (Figures 5 to 7). This angle a is for example between 30 and 60 °. As can be seen in FIG. 4, the inputs 20a, 21a are oriented respectively in directions which each pass through one of the above-mentioned sectors of space S. A finger 15a of the cage carrier passes between the two inputs 20a, 21a.
    The planes P2, P3 and P4 are located between the cage 14 and the ring 15b of the cage holder 15 (Figures 6 and 7).
    The distributor 13 is advantageously configured to be fluidly connected, at its inputs and these outputs, by sockets of the male-female type, that is to say by fittings requiring only an interlocking by axial translation of a male fitting into a female fitting. Even if a connector is presented in the following as male and intended to cooperate with a female connector, it may alternatively be replaced by a female connector therefore intended to cooperate with a male connector, and vice versa.
    Regarding the inputs 20a, 21a, they each comprise a female connector 20aa, 21aa in the example shown which is intended to receive the male connector of a supply pipe 20f, 21f (Figures 4, 6 and 7). The pipes 20f, 21f are rectilinear and pass through the abovementioned space sectors S and are intended also to pass through tubular arms of an intermediate casing of the turbomachine 1, for the purpose of connecting the distributor 13 to a source of lubricating oil . The number of arms of the intermediate casing can be greater than 5 and therefore the number of space sectors S. The sealing of the male-female connections can be ensured by O-rings or the like.
    The female connectors 20aa, 21aa of the inputs 20a, 21a are connected to the respective chambers by pipes 20d, 21d. The connector 20aa of the inlet 20a is connected to the chamber 20b furthest from the plane P4 by a pipe 20ab which has a general shape of S (FIG. 6). The connector 21aa of the inlet 21a is connected to the chamber 21b closest to the plane P4 by a pipe 21ab which has a rectilinear or slightly bent shape (FIG. 7).
    Regarding the outputs 20c, they each comprise a female connector 20ca in the example shown which is intended to receive the male connector of one of the deflectors 18. These outputs 20c are oriented axially, all in the same direction here forward. The connections 20ca of these outputs are connected to the chamber 20b by channels 20d substantially in L or V shape (FIG. 5).
    Regarding the outputs 21c, they each comprise a female connector 21ca in the example shown which is intended to receive the male connector of one of the lubrication and cooling cores 22 which will be described in detail in this which follows with reference to Figures 8 to 13. These outputs 21c are oriented axially, all in the same direction here forward. The connections 21ca of these outputs are connected to the chamber 21b by conduits 21d substantially in L or V.
    As seen in Figure 3, the lengths or axial dimensions of the channels 20d and the conduits 21d are different, the outputs 21c being located in a plane P5 perpendicular to the axis X which is more forward than that P6 which goes through the outputs 20c. The planes P5 and P6 are located in the cage 14.
    Finally, as can be seen in FIG. 5, the channels 20d are connected to the ring forming the chamber 20b by nozzles 20e situated on the internal periphery of this ring, while the conduits 21d are connected to the ring forming the chamber 21b by nozzles 21e located on the outer periphery of this ring (Figure 5).
    As mentioned in the foregoing, the outputs 21c of the distributor 13 are connected to cores 22 which will now be described with reference to FIGS. 8 to 13.
    The cores 22 have the function of lubricating and cooling the axes 10b of the satellites 8 which are here centered and guided by the bearings 11 with rollers 11a.
    In the embodiments shown, each axis 10b is guided by a bearing 11 with double rolling, that is to say with double row of rollers 11a. The two rows extend around the same axis which coincides with that, denoted Y, of the axis 10b of the satellite 8.
    Conventionally, the rollers are guided in tracks defined by internal and external rings. In the examples shown, a feature is linked to the fact that the internal guide rings of the rollers 1a are integrated into the axis 10b. The outer periphery of the axis 10b thus comprises cylindrical tracks 11b for rolling the rollers 11a, each track 11b being delimited axially by annular ribs 1c which serve to guide cages 1 Id for holding the rollers 11a. Furthermore, FIG. 3 shows that the outer rings are integrated into the internal periphery of the satellites 8. The internal periphery of the satellites 8 thus comprises cylindrical tracks 8a for rolling the rollers 11a, the tracks 8a being separated from one the other by an annular groove 8b opening radially inward and at the bottom of which are formed radial holes 8c for oil passage.
    The external periphery of each satellite 8 comprises a toothing 8d with a double helix, that is to say two coaxial and adjacent helices which are here separated from each other by an annular groove 8e opening radially towards the outside and at the bottom of which open the holes 8c.
    The internal periphery of the axis 10b of each satellite 8 has a generally biconical shape and includes two internal frustoconical surfaces 10e, lOf flared in opposite axial directions. The front frustoconical surface 10e is thus flared towards the front and the rear internal frustoconical surface lOf is flared towards the rear. In the example shown, a cylindrical surface 10g is located between the frustoconical surfaces 10e, 10f, an internal cylindrical surface before 10h extends between the front end of the axis 10b and the front end of the surface 10e, and a rear internal cylindrical surface 10i extends between the rear end of the axis 10b and the rear end of this axis 10b.
    Oil flow orifices lOd cross the axes 10b in the radial direction, and therefore extend between their internal and external peripheries. In the example shown, they extend between the frustoconical surfaces 10e, lOf, on the one hand, and the tracks 11b and the external peripheries of the ribs binds, on the other hand.
    An annular flange lOga for fixing the core 22 extends radially inwards from the cylindrical surface 10g. This flange lOga comprises axial holes for the passage of screws 30.
    In the first embodiment of the core 22 shown in Figures 8 to 11, this core 22 comprises two annular flanges 22a, 22b coaxial and substantially frustoconical each having a first end of larger diameter and a second opposite end of smaller diameter. The flanges, respectively front 22a and rear 22b, are fixed together by their second ends. Like the surfaces 10e, lOf, the flanges 22a, 22b therefore widen in opposite axial directions.
    The flanges 22a, 22b are mounted adjusted inside the axis 10b and are intended to cover the frustoconical surfaces 10e, lOf to define therewith at least one annular cavity 24 for circulation of lubricating oil and cooling the axis 10b. In the example shown, these cavities 24 are two in number which are separated from each other by the lOga flange.
    The ends of the flanges 22a, 22b each have an outer cylindrical centering surface comprising an annular groove for receiving a seal 25a. The front flange 22a has an upstream end mounted adjusted by its external cylindrical surface on the surface 10h, and a downstream end mounted adjusted by its external cylindrical surface on the surface 10g, in front of the flange lOga. The rear flange 22b has an upstream end mounted adjusted by its external cylindrical surface on the surface 10h, behind the flange lOga, and a downstream end mounted adjusted by its external cylindrical surface on the surface 10O.
    It can be seen in FIG. 8 that the orifices 10d open out radially inside into the cavities 24. It is also noted that the flanges 22a, 22b comprise means for fluid connection of the cavities 24 to the distributor 13 described in the foregoing .
    The rear flange 22b here comprises an internal chamber 26 centered on the axis Y and connected on the one hand by radial passages 27 formed in this flange to the cavity 24 delimited by this flange and the surface 10f. This flange 22b further comprises a connection tube 25 centered on the axis Y, one end of which opens into the chamber 26 and the opposite end of which faces backwards forms a male connector intended to receive by fitting one of the female connectors 21ca. of an outlet 21c of the distributor 13. As a variant, the tubing 25 could form a female connector.
    The rear flange 22b is mounted adjusted in the axis 10b by axial translation from the rear until its front end is in axial support on the lOga flange. The flange 22b comprises at its front end another connection tube 23 centered on the axis Y, which defines a front end part of the chamber 26 and which is intended to pass axially through the flange lOga, in its middle, in view of the connection of the chamber 26 to an internal chamber 28 of the front flange 22a. The chamber 26 thus extends between the tube 25 and the chamber 28, the latter being connected to the cavity 24 formed between the flange 22a and the surface 10e by holes 29 formed in this flange.
    The holes 27, 29 of each flange 22a, 22b are three in number (this number can vary between 1 and more) and regularly distributed around the Y axis (Figure 10). In the example, they have the same number of fixing screws. The number depends mainly on the radial place that remains after or before implantation of the screws. The flanges 22a, 22b further comprise each of the holes for passing or screwing screws 30 for fixing between them and to the flange lOga. The orifices of the flanges are aligned together and those of the lOga flange and the screws 30 are screwed from the rear through, in order, an orifice of the flange 22b, an aligned orifice of the lOga flange and an orifice of the flange 22a (see Figure 8).
    Figure 11 shows the flow of oil from the distributor 13 to the rollers 1a and to the cage 1 Id, for the lubrication of the rollers and the cage but also the cooling of the axis 10b. The oil enters the distributor 13 through its inlet 21a and feeds the chamber 21b then circulates to the outlets 21c. The oil enters the chamber 26 through the tubing 25 and then into the chamber 28 through the tubing 23. The chambers 26 and 28 make it possible to slow down the flow of oil (and to avoid a Venturi effect in line with the holes 27, 29 ) and better distribute the oil between the front and rear flanges. The oil then circulates in the holes 27, 29 to supply the cavities 24. The oil flows axially along the surfaces, from the rear to the upstream on the surface 10e, owing to the fact that the holes 29 open at the rear end of the front cavity 24, and from front to rear on the surface 10f, because the holes 27 open at the front end of the rear cavity 24. The oil then circulates in the orifices lOd to reach the tracks 11b and the ribs 1c for the lubrication of the rollers 1c and the cages 1 Id. The oil is brought "cold" by the distributor 13. It circulates in the axis 10b which is hot and is therefore warmed up. It thus reaches a good temperature for optimal lubrication performance at the bearing level while having dissipated the heat generated. The amount of heat taken up by the oil depends in particular on the shape of the flanges 22a, 22b.
    The thickness or the radial dimension of the cavity 24 is chosen as a function of the expected increase in temperature of the oil intended to circulate in this cavity, for example between 10 ° C and 60 ° C. The temperature of the oil leaving the orifices lOd is also a function of the angle of inclination of the frustoconical surfaces 10e, lOf and the flanges 22a, 22b, relative to the axis Y.
    Figures 12 and 13 show an alternative embodiment of the core which is designated by the reference 122. Its characteristics are designated by the same reference numbers as those of the core 22, increased by a hundred. The above description in relation to the core 22 applies to this variant insofar as it does not contradict the following.
    The core 122 differs from the previous embodiment in particular in that the flanges 122a, 122b define a single annular cavity 124 with the internal periphery of the axis 110b. This axis 110b does not include here an internal cylindrical surface between its frustoconical surfaces 110e, HOf. The smaller diameter ends of the tapered surfaces 110e, HOf are thus directly connected to each other. The internal periphery of the axis 110b does not include a lOga flange of the aforementioned type. The cavity 124 has a general form of "diabolo". It can also be seen that the radial thickness of this cavity 124 is less than that in the previous embodiment. The oil passage openings 110d are distributed in annular rows and each row of openings opens into the cavity 124, in the bottom of a radially internal annular groove formed on the surface 110e, 11f.
    The chamber 126 of the rear flange 122b is in fluid communication with the tube 125 and with radial bores 127 which open into the cavity 124. This chamber 126 is here closed at its front end. The chamber 126 is therefore only formed in the rear flange 122b. The holes 127 can also be formed only in the rear flange 122b or else formed in this flange 122b and closed axially by the front flange 122a.
    The rear flange 122b comprises a central cylindrical extension 131 towards the front which has an external thread and which passes through a central orifice in the front flange 122a. This extension 131 receives a nut 132 screwed from the front which bears axially on the front flange, for the purpose of tightening the assembly. Due to the absence of the lOga flange of the previous embodiment, the flanges 122a, 122b are fixed only to one another and its held in position inside the axis 110b by the only fitting assembly flanges on the internal periphery of the axis 110b. The tightening of the nut 132 generates an axial tightening of the internal periphery of the axis 110b between the flanges 122a, 122b due to the complementarity of shapes.
    As can be seen in the drawings, the ends of the larger diameter of the flanges can also be clamped axially against cylindrical shoulders 133 of the internal periphery of the axis 110b, when tightening the nut 132.
    FIG. 13 shows the path of the oil from the distributor 113 to the rollers 11a, for the lubrication of the rollers but also for the cooling of the axis 110b. The oil enters the distributor 113 as indicated in the above and then enters the chamber 126 through a sleeve 137 engaged in the tubing
    125. The socket 137 is a connection socket similar to the sockets 37 and the length of which is adjusted according to need. The number of sockets 137 is equal to the number of lines 21d and makes it possible to resume the misalignment and to have a less hyperstatic mounting of the distributor 113 on the reducer. The oil then circulates in the holes 127 to supply the cavity 124, substantially in the middle. The oil flows axially along the 110th surfaces, IlOf, from the center of the cavity backwards and forwards. The oil then circulates in the orifices HOd to reach the tracks 111b and the ribs 11 le for the lubrication of the rollers 11 la and the cage 11 Id.
    Figures 14 to 17 illustrate an embodiment of a deflector 18. As mentioned in the foregoing, the reduction gear 6 comprises several deflectors 18 which are housed in the cage 14 and are each disposed between two adjacent satellites 8. The number of deflectors 18 of the reduction gear 6 is therefore equal to the number of satellites 8 of this reduction gear.
    The first function of a deflector 18 is to guide the lubricating oil of the teeth of the satellites 8 and to avoid the recirculation of oil between satellites, hence the concept of "inter-satellite deflector". The deflectors 18 are thus shaped to match the peripheral shape of the satellites 8.
    As seen in Figures 4 and 15, in addition to extending between two adjacent satellites 8, each deflector 18 is located between the sun 7 on the one hand, located radially inside, and a couple of bridges 14c, 14d, on the other hand, located radially outside.
    Each deflector 18 comprises a block comprising a first lateral surface 18a which is cylindrical and concave and which has a radius of curvature RI measured from an axis Gl, which coincides with the axis Y of rotation of a satellite 8 ( figure 15). The block comprises a second lateral surface 18b, opposite the first surface 18a, which is cylindrical and concave and which has a radius of curvature RI measured from an axis G2 which is parallel to Gl, and which is coincident with the axis Y of rotation of another satellite 8.
    Each of the first and second surfaces 18a, 18b has a protruding tongue 34 which has a generally elongated shape around the axis G1, G2 of the surface considered and whose internal periphery is concave curved and has a radius of curvature R2 measured from this axis Gl, G2 which is less than RI. The tongues 34 of a deflector 18 extend substantially in the same plane perpendicular to the axis X and are preferably located in the middle of the respective surfaces 18a, 18b (in the axial direction).
    The surfaces 18a, 18b and the tongues 34 extend around the respective axes Gl, G2 over an angular range between 30 and 80 ° in our example, and preferably as large as possible.
    In the example shown and as can be seen in FIGS. 14 and 15, the ex22 longitudinal hoppers of the tongues 34 are set back with respect to planes passing respectively through the faces 18e, 18f of the deflector 18.
    In the variant shown in Figure 23, the longitudinal ends 34a of the tongues 34 could pass through such planes and thus protrude for the purpose in particular of lengthening the length of the tongues and therefore the circumferential dimension for guiding the oil around the satellites 8. In the latter case, the tongue 34 would protrude from the side of the face 18f where the jets 36cb are located (solar side) and from the other side of the bridges 14c, 14d and the finger 15a. On the solution of Figures 14a and 15, the tongue covers approximately 2x45 ° of the circumference of a satellite (twice, because there are two deflectors on either side). If the tongue is extended as shown in Figure 14b, outside the deflector so that it does not touch the sun on mounting and it does not come out of the circumference of the cage, the tongue could cover about 2x75 ° 360 ° overlap of the satellite.
    The block of each deflector 18 further comprises a front planar face 18c, which is substantially radial when the deflector is mounted in the cage 14 of the reduction gear, and a rear planar face 18d, which is also substantially radial. The block further comprises an upper planar face 18e (or radially outer), which is intended to be oriented on the side of the pair of bridges 14c, 14d, and a lower face 18f (or radially inner), which is intended to be oriented from the side of the solar 7. This face 18f is cylindrical and concave and has a radius of curvature R3 measured from an axis G3, which coincides with the axis X of the solar. This face 18f therefore has the function of guiding the lubricating oil of the teeth of the sun.
    The deflectors 18 extend between the radial walls 14a, 14b of the cage 14 and have their faces 18a, 18b which are supported on the internal faces opposite these walls 14a, 14b. The deflectors 18 are fixed to the cage 14 by screws 35 for example. Each block may include, for example on its rear face 18d, tapped holes for receiving screws 35 for fixing the deflector to the rear wall 14b of the cage 14. An identical configuration on the wall 14a is also possible.
    As seen in Figure 4, the threaded holes of each deflector 18 are located substantially in the middle of the height or radial dimension of the deflector, and the screws 35 screwed into these holes pass through holes in the wall 14b which are located near the radially internal peripheral edge 14ba of this wall 14b (Figures 3 and 4). It is thus understood that in the mounted position each deflector 18 has a lower part which extends radially inwards from the peripheral edge 14ba, between this peripheral edge 14ba and the sun 7.
    We also note in Figure 16 that in the mounted position, the tongues 34 of each deflector 18 extend in the middle and inside the inter-helix grooves 8e of the two satellites 8 between which this deflector is mounted . A predetermined clearance J is left between the top of each tongue 34 and the bottom opposite the groove 8e in which the tongue is inserted. The tongue 34 has a thickness Ep or axial dimension which represents approximately 10 to 90% of the axial dimension of the groove 8e. The groove 8e of a satellite has a radius R4 measured from the axis Y of the satellite and its teeth have an external radius R5 measured from the same axis. The radius R2 is between R4 and R5 and the above-mentioned clearance J is equal to the difference between R2 and R4 (Figures 15 and 16). This clearance J must be as small as possible to optimize the function of the tongue 34 of "inter-helix deflector". The tongues 34 have the function of limiting the passage of oil from one toothing to another toothing of the same satellite 8.
    Each deflector 18 includes an integrated lubrication circuit, which includes an oil inlet 36a connected by holes 36b to at least one oil outlet 36c. In the example shown, the oil inlet 36a is located on the rear face 18d and comprises a tube intended to form a male connector and to cooperate by malefemale fitting with an outlet 20c from the distributor 13 described in the above. Even if a connector is presented in the following as male and intended to cooperate with a female connector, it may alternatively be replaced by a female connector therefore intended to cooperate with a male connector, and vice versa (FIG. 3).
    Each deflector 18 comprises at least one outlet 36c which is in the form of an orifice 36ca forming a female connector which is intended to receive a socket 37 for sealing fluid connection (FIG. 3). Like the inlet 36a, the socket 37 can be removed and replaced by a male connector. This 36ca orifice is here located on the upper face 18th of each deflector. Figure 3 shows that one half of the socket 37 is engaged by male-female fitting in the 36ca orifice and that the other half is engaged by male-female fitting in a female orifice provided at the radially inner end of the body 17a of the pin 17 carried by a pair of bridges 14c, 14d. This same figure shows that the inlet 36a is connected by two holes 36b 1, 36b2 to the outlet 36c. These holes are perpendicular, a first 36bl extending along the axis X, from the inlet 36a, and a second 36b2 extending radially from the first bore to the orifice 36ca.
    The surfaces 18a, 18b are each connected to the face 18f by a truncated edge on which are formed orifices 36cb for spraying oil onto the meshing zones of the solar 7 with the satellites 8. These orifices 36cb are connected by channels 36b4 internal to the block, with axial bore 36bl (Figures 3 and 14). FIG. 15 shows the trajectories 36cbl of the oil jets projected by the orifices 36cb of a deflector 18.
    One of the deflectors 18 comprises a nozzle 38 intended to project lubricating oil onto the splines 7a of the solar 7. This deflector 18 is that shown in FIG. 14 and in the center in FIG. 15. The nozzle 38 is formed in one piece with the deflector block 18 and here has a general L-shape, one branch 38a of which has a radial orientation and one branch 38b of which extends axially and connects the front face 18c of the block to the radially outer end of the branch 38a. The nozzle 38 extends in a median plane of symmetry of the block. The deflectors 18 which do not comprise a nozzle 38 also have a median plane of symmetry, which corresponds to a plane passing through the axis X of the reducer 6.
    The branch 38a extends radially inwards from the branch 38b and its radially internal free end includes a 36cc orifice oriented towards the rear for spraying oil onto the grooves 7a. FIG. 17 shows the jet of oil 39 projected by this nozzle 38.
    The oil supply to the nozzle 38 is achieved by extending the axial bore 36bl visible in Figure 3 to the front face 18c of the deflector block 18, and in the axial branch 38b (Figure 14). An additional radial bore 36b3 is produced in the branch 38 to connect this axial bore 36b to the orifice 36cc for spraying oil from the nozzle. The radially outer end of the bore 36b3 of the nozzle, which is therefore opposite to the oil spraying opening 36cc, can be closed by an attached plug 36d (FIG. 14). As seen in Figure 3, the deflectors 18 which do not include a nozzle 38 have a shorter axial bore 36b, that is to say not opening on the front face 18c of the deflector block.
    Figures 17 and 18 show that the radially internal peripheral edge 14aa of the front radial wall 14a includes notches 40 regularly distributed around the axis X to facilitate the mounting of the deflectors and in particular that comprising the nozzle 38. This peripheral edge 14aa thus has a general star shape. The number of notches 40 is equal to the number of deflectors 18 and therefore to the number of satellites 8. The minimum number of notches 40 is equal to the number of nozzles 38, ie only one in the example shown. But, in order to gain mass and to have a more regular / periodic form, it is more advantageous to have the maximum number, ie the number of satellites 8 or deflectors 18. The advantage of making a single notch would be need to unmute the assembly so that the deflector-nozzle cannot be mounted in one of the five positions which would not be intended for it for several reasons.
    Figures 19 to 22 illustrate mounting steps of the reducer 6 and in particular of the deflectors 18, the solar 7, the satellites 8 and their axes 10b. A first step consists in placing the deflectors 18 in the cage 14 which is already fixed to the carrier 15. The deflectors are inserted one after the other in the cage, through the central orifice of the front wall 14a and then are moved radially towards one after the other to be positioned so that their tapped holes are aligned with the screw holes 35 of the rear wall 14b (Figure 19). Mount them by sliding them through the lights 16 is also possible. These screws 35 are then screwed and tightened to fix the deflectors 18 to the cage 14 (FIG. 20). The sun 7 is then inserted into the cage 14 by axial translation from the rear, through the central opening of the rear wall 14b (Figure 20). The satellites 8 are then engaged one after the other in the cage 14, by translation in a radial direction through the mounting holes 16 located between the pairs of bridges 14c, 14d (FIG. 21). The axes 10b of the satellites 8 are then inserted into their respective satellites by axial translation from upstream, through openings provided for this purpose on the front radial wall 14a (Figure 22). A nut 41 is screwed onto the rear end of each axis 10b and bears axially on the rear wall 14b in order to maintain the axes of the satellites in the cage 14 (Figures 3, 4 and 22).
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    Claims [Claim 1] Distributor (13) of lubricating oil for a mechanical reducer (6) of a turbomachine (1), in particular of an aircraft, characterized in that it has a generally annular shape around an axis X and is formed of a single piece, this distributor comprising first and second independent oil circuits (20, 21), said first oil circuit (20) comprising a first oil inlet (20a) connected by a first annular chamber (20b) with several oil outlets (20c) distributed over a first circumference C1 around said axis X, and said second oil circuit (21) comprising a second oil inlet (21a) connected by a second annular chamber (21b) to several oil outlets (21c) distributed over a second circumference C2 around said axis X, the first and second circumferences having different diameters. [Claim 2] Distributor (13) according to claim 1, wherein said first and second inlets (20a, 21a) are oriented in the radial direction relative to said X axis. [Claim 3] Distributor (13) according to claim 1 or 2, wherein said first and second inlets (20a, 21a) are located in the same plane (P4) perpendicular to said axis X and are inclined relative to each other by a determined angle (a). [Claim 4] Distributor (13) according to one of the preceding claims, in which said first and second chambers (20b, 21b) have in axial section a generally circular shape. [Claim 5] Distributor (13) according to one of the preceding claims, in which said first and second chambers (20b, 21b) are formed by two coaxial and intimately linked tubular rings. [Claim 6] Distributor (13) according to the preceding claim, wherein the diameter of said first circumference C1 is less than those of said rings, and the diameter of said second circumference C2 is greater than those of said rings. [Claim 7] Distributor (13) according to one of the preceding claims, in which said outlets (20c, 21c) are oriented axially in the same direction. [Claim 8] Distributor (13) according to one of the preceding claims, in which it comprises fixing lugs (19a) having screw passage holes (20). [Claim 9] Planet carrier (10) for a mechanical reducer (6) of a turbomachine
    (1), in particular an aircraft, comprising a cage (14) defining a housing for receiving a central solar (7) of axis X of rotation and satellites (8) arranged around the solar, a distributor (13 ) according to one of the preceding claims being attached and fixed to the cage. [Claim 10] Satellite carrier (10) according to the preceding claim, in which the cage (14) comprises at its periphery housings intended to receive axial fingers (15a) integral with a cage carrier (15) of said reducer, each housing being traversed by a substantially radial pin (17) which is intended to guide in rotation a connecting means, such as a ball joint or a bearing, carried by one of said fingers, said first and second inlets (20a, 21a) of said distributor (13) being oriented respectively in first and second directions which each pass through a sector of free space (S) delimited axially by the cage and the cage holder and extending circumferentially between two adjacent fingers (15a).
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    同族专利:
    公开号 | 公开日
    US20200165980A1|2020-05-28|
    FR3088977B1|2020-11-27|
    EP3657045A1|2020-05-27|
    US11268451B2|2022-03-08|
    CN111219256A|2020-06-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2010092263A1|2009-02-16|2010-08-19|Snecma|Lubrication and cooling of a reduction gear with epicyclic gear train|
    FR2987416A1|2012-02-23|2013-08-30|Snecma|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.|
    FR3041054A1|2015-09-15|2017-03-17|Hispano-Suiza|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|
    WO2017129926A1|2016-01-28|2017-08-03|Safran Transmission Systems|Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel|
    US9163717B2|2012-04-30|2015-10-20|United Technologies Corporation|Multi-piece fluid manifold for gas turbine engine|
    US9476321B2|2012-09-20|2016-10-25|United Technologies Corporation|Turbomachine fluid delivery manifold and system|
    FR3088980B1|2018-11-23|2021-01-08|Safran Trans Systems|LUBRICATION AND COOLING CORE FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    FR3088978B1|2018-11-23|2020-12-18|Safran Trans Systems|DEFLECTOR FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    FR3090061B1|2018-12-13|2021-01-29|Safran Trans Systems|SATELLITE CARRIER FOR A SPEED REDUCER|
    FR3090786B1|2018-12-21|2020-12-04|Safran Trans Systems|LUBRICATING OIL DISPENSER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|FR3088979B1|2018-11-23|2021-06-18|Safran Trans Systems|SATELLITE CARRIER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    FR3095252B1|2019-04-19|2021-05-14|Safran Trans Systems|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    法律状态:
    2019-10-22| PLFP| Fee payment|Year of fee payment: 2 |
    2020-05-29| PLSC| Publication of the preliminary search report|Effective date: 20200529 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 3 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1871757A|FR3088977B1|2018-11-23|2018-11-23|LUBRICATING OIL DISPENSER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|FR1871757A| FR3088977B1|2018-11-23|2018-11-23|LUBRICATING OIL DISPENSER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    EP19210523.7A| EP3657045A1|2018-11-23|2019-11-21|Dispenser of lubricating oil for a mechanical gear of an aircraft turbine engine|
    US16/691,481| US11268451B2|2018-11-23|2019-11-21|Lubricating oil distributor for a mechanical reduction gear of aircraft turbine engine|
    CN201911155827.9A| CN111219256A|2018-11-23|2019-11-22|Lubricating oil distributor for mechanical reducers of turbine engines of aircraft|
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