• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a gearbox (11) with an epicyclic gear train for a turbomachine (1), in particular an aircraft, comprising a planetary shaft (15) of rotation axis A, a ring (19) of axis A s' extending around said planet shaft (15), satellites (18) distributed about said axis A, which are meshing with said ring gear (19) and the sun gear shaft (15), and a satellite carrier comprising, on the one hand, support members (21) for bearings (23a, 23b) of the satellites (18a, 18b), axes of rotation B, which are uniformly distributed around the axis A, and, on the other hand, a workpiece (38). ) now each support member (21) substantially by its middle along its axis B, characterized in that said support members (21) are formed in one piece with means (45, 46, 41) for feeding lubricating oil of said bearings (23a, 23b). It also relates to a method of assembling said gear.
    公开号:FR3035375A1
    申请号:FR1553675
    申请日:2015-04-23
    公开日:2016-10-28
    发明作者:Jeremy Phorla Lao；Olivier Belmonte；Clementine Charlotte Marie Mouton；Van Thomas Julien Nguyen；Emmanuel Pierre Dimitri Patsouris
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the field of epicyclic gearboxes and, in particular, though not exclusively, to turbomachine gearboxes with a pair of counter-rotating propeller propellers. The invention more particularly relates to the integration of lubricating means in an epicyclic gear train gearbox. STATE OF THE ART: The architecture of turbomachines with twin blades of counter-rotating propellers, designated by the English expression "open rotor", differs from that of conventional turbojet engines in that the blower is, no longer internal, but external and that it consists of two coaxial and counter-rotating propellers that may be located upstream or downstream of the gas generator. Such an architecture generates lower fuel consumption compared to multi-stream turbofan engines operating on commercial aircraft. As shown diagrammatically in FIG. 1, a turbine engine 1 with a doublet of counter-rotating propellers upstream 2 and downstream 3 mainly comprises, along a central longitudinal axis A, two distinct parts: a gas generating part G and a propelling portion P. The part P extends, in this example of a turbine engine, the gas generator part G and the nacelle 4. The gas generator part G of the turbine engine 1 usually comprises, from upstream to downstream in the direction of flow, with respect to the axis A, the gas flow F entering the nacelle 4 of the turbine engine, one or two compressors 7 according to the architecture of the single or double-body gas generator, an annular combustion chamber 8, one or more turbines 9 linked to separate bodies according to said architecture. The propulsion part comprises a power turbine whose shaft 10 drives, via a gear reduction device or reduction gear with epicyclic gear train 11 (designated by the acronym PGB for Power Gear Box) and in a contrarotative manner, the concentric and coaxial shafts 12 and 13 of the two upstream propellers 2 and downstream 3 aligned along the axis A of the turbine engine. A nozzle 14 terminates in the usual manner 303 5 3 75 2 the turbine engine 1. Such an architecture is presented, for example, in the patent FR-A-2 955 085 and the patent applications FR-A1-2 962 109 and FR-A1- 2 940 247. In operation and briefly, the air flow F entering the turbine engine 1 is compressed, then mixed with fuel and burned in the combustion chamber 8. The generated combustion gases then pass into the turbine part 9 to drive in reverse rotation, via the epicyclic reduction gear 11, the propellers 2, 3 which provide the bulk of the thrust. The combustion gases are expelled through the nozzle 14 thus increasing the thrust of the turbine engine 1. The gearbox (PGB) 11 of an open rotor is intended to transform the so-called rapid rotation speed of the power turbine 9, whose FIG. 2 shows the power shaft 10 cooperating with the sun gear 15 of the gearbox 11, at two different slow speeds of the two counter-rotating propellers 3, 4. For this, with reference to FIG. 2, the differential gearbox 11 The planetary gear train 15 comprises, with respect to the longitudinal axis A: The sun gear 15 in the form of a toothed wheel, which is mounted by a splined connection on the turbine shaft 10 rotating in a direction of rotation. by driving the gearbox 11, satellites 18, here three in number, arranged at 120 ° from each other (only one of them being represented in the figure), which are formed by toothed wheels 18a, 18b, meshing around the sun gear 15 and which are connected to a planet carrier 16 rotating, accordingly, in a direction of rotation identical to the input shaft, and an outer ring gear 19, which meshes with the satellites 18 and which rotates in one direction reverse rotation of the sun gear 15, therefore in the opposite direction 25 of the planet carrier 16. The example of FIG. 2 shows an inverted reduction gear 11, for which the shaft 12 of the upstream propeller 2 ends, in the example presented, by an annular bulb, to be integral in rotation with the planet carrier 16, and the shaft 13 of the downstream propeller 3, is integral in rotation with the outer ring gear 19.
    [0002] With reference to FIGS. 2 and 3, a known epicyclic gearbox comprises a satellite support 17 with three individual support members 21 (only one being shown in FIG. 2), held together by an annular piece 20. Each individual support member 21 here has substantially the shape of a cylindrical tube. These cylindrical tubes 21, three in number (three satellites), are parallel and each serve for the rotation of the wheels 18a, 18b of a satellite 18 about an axis B connected to the individual support 20. The outer surface of each cylindrical tube 21 has an extra thickness in its center, separating the tube in two parts. These parts here support two inner rings of rolling bearings 23a, 23b identical. These bearings 23a, 23b allow the rotation of the gears 18a, 18b, of the satellite 18 around the axis B.
    [0003] Furthermore, the cylindrical tubes are monobloc, connected by an annular piece 20, substantially in their middle along the axis B. This annular piece 20 not shown in Figure 2 is bolted to the fingers 47 of the planet carrier 16, so to rotate it about the axis A. The gear 11 has the particularity of having no static component and is considered a differential gear with epicyclic gear train with, at its input, a speed of initial rotation (that of the turbine) and, at its output, two different rotational speeds of opposite direction (those of the two stages of blower). Also, to ensure optimum and reliable operation of the gear 11, it is essential to route oil to lubricate and cool the rolling components 20 that constitute it, given that the gearbox is subjected to the different forces of the input shafts (turbine) and output (propellers) undergoing significant mechanical and thermal external stress generated by the turbomachine. For this, the two cylindrical tube portions 21 described above are pierced radially with holes regularly spaced on their circumference opposite each bearing 23a, 23b, to allow circulation of oil, denoted by the arrows T in FIG. to these levels. Within each support member 21, an axis axis 24 axisymmetric and frustoconical with respect to the axis B, begins upstream by a cylindrical portion of radius significantly less than that of the cylindrical tube 21 and joins the outer periphery of 30 the support member 21 downstream. This piece 24 terminates downstream by a flange which extends radially beyond the cylinder 21 and which blocks axially downstream the bearing 23b. Upstream, a plate 25, having substantially the shape of a disc, closes the space between the cylindrical tube 21 and the satellite axis 24. It also allows, radially exceeding the cylinder 21, to lock axially towards the upstream the bearing 23a. Furthermore, the plate 25 has a hole-type opening in its innermost part radially relative to the axis A of the gear 11 to allow the oil to flow to the bearings 23a and 23b (arrow T). The plate 25 and the satellite axis 24 form with the cylinder 21, a cavity 26 putting in communication the opening of the plate 25 with the holes of the cylinder 21. During operation of the gearbox, the lubricating oil, whose path is indicated by arrows T, passes through the opening of the upstream plate 25 and leaves the cavity 26 through the holes of the cylindrical tube 21, to lubricate the bearings before distributing in the gears and then be removed by centrifugation. The particular shape of the inner part 24 allows the oil to be distributed to the holes furthest from the inlet opening in the cavity 26. The three plates (a satellite plate 18), associated with the cylindrical part 30, form the lower cover of an oil transfer device 28, provided for transferring oil from an oil supply source 27 located in the fixed nacelle 4 to the rotating reference frame of the planet carrier 17. This oil transfer device 28 rests directly on the outer surface of the cylindrical part 31, called the upper cover of the device 28. This upper cover 31 is fixed directly to the lower cover formed by the three plates 25 and the cylinder 30. The upper and lower covers then form a cavity 29 in which 25 flows the oil from the device 28. The set of parts 30, 31, 21, 25 and 24 make it possible to route the oil of the device 28 at the bearings 23a and 23b according to the arrows T. The presence of several parts, including the internal frustoconical piece 24 in each individual support 20 weighs down the gear 11, which goes against the goal of reducing mass, in particular for open rotors. The volume of the pipes, in particular that of the cavity 26, also implies the presence of an unnecessary mass of oil entrained in the rotation of the satellite support 17. Moreover, in this design, parts dedicated to the oil routing are involved in the recovery of efforts and must therefore be oversized with respect to their oil transfer function. Finally, the assembly of the planet carrier 17 and satellites on the planet carrier is complex because of the number of parts. With reference to FIG. 7, in this example, this assembly is done in six steps with a large number of parts. A first step a) consists in installing, axially upstream and downstream, the inner rings 10 of the bearings 23a, 23b on each cylindrical portion 21 of the satellite support 17. In a second step b), the lower cover (Monobloc part consisting of parts 30 and 25) is assembled to the satellite support 17, thus axially locking the lower bearing rings 23a on all satellites. In a third step c), the frustoconical parts 24 are placed downstream in axial abutment against the inner race rings 23b. In a fourth step d), the frustoconical pieces 24 are bolted to the circular portion 25 of the lower cover for each satellite. In fifth e) and sixth f) steps, the outer cover 31 of the oil circulation cavity 29 is mounted and bolted to the assembly obtained in step d). The present invention aims to provide a solution to the disadvantages mentioned above, in particular by simplifying the design of the assembly. It is particularly adapted to an epicyclic gear train gearbox for a contra-rotating propeller turbine engine, but can be used for other types of epicyclic gear train gearboxes, used for example to drive the blower of a twin-engine turbomachine. flux, regardless of the number of satellites in the gearbox. SUMMARY OF THE INVENTION For this purpose, the invention relates to a planetary reduction gearbox for a turbomachine, in particular an aircraft, comprising a rotating planet shaft A, an axle ring A extending around said planet shaft, satellites distributed about said axis A, which are meshed with said ring gear and the sun shaft, and a satellite support comprising, on the one hand, satellite bearing support members, axes of rotation B, which are regularly distributed around the axis A, and secondly, a part holding each support member substantially by its middle along its axis B, characterized in that said support members are formed 5 one piece with lubricating oil supply means of said bearings. By realizing in one piece the support members of the bearings with their oil supply means, gaining simplicity of assembly. In addition, by removing the piece which formed, in the prior art, the radially inner wall of the supply chamber 10, it is possible to gain mass and bulk within each member. Advantageously, said support members each have a hollow tubular shape, preferably of substantially circular cross section on its outer periphery. The oil supply means of the bearings in the members are therefore integrated into the thickness of the tube and release the inner space of the tube. Preferably, said lubricating oil supply means of said bearings comprise at least one external lubrication oil circulation channel around the axis B in communication with the outer periphery of said support members. The outer channel, can supply lubricating oil bearings of satellites 20 over their entire circumference, by feeding oil to the track on a portion of this circumference, through the through holes. Therefore, it is no longer necessary to provide an internal chamber arranged to supply lubricating oil throughout the circumference and occupying a large part of the internal space to the cylindrical tube of the support member. We gain mass and simplicity of assembly compared to the prior art. Preferably, the outer channels are substantially in a plane perpendicular to the B axis and have a circular section. On the circumference of these channels are equitably distributed holes oriented towards the bearing tracks so that the lubricating oil can be injected.
    [0004] Advantageously, said members each comprise at least one integrated duct arranged to place said at least one external channel in communication with a lubricating oil distribution member to the support members. Advantageously, said support members are formed of a single a piece between them and with a tubular lubricating oil dispensing element, which extends about said axis A and which comprises an annular oil distribution pipe to the support members. Advantageously, said tubular lubricant oil distribution element comprises an interface for an oil transfer device between a fixed source of oil 10 with respect to the turbomachine and the satellite support, in rotation about the axis A Preferably, said interface is arranged to bring the oil radially into the inner pipe of said tubular lubricating oil dispensing element.
    [0005] Advantageously, said duct communicates with said integrated chamber of each of said members. Advantageously, said tubular element is connected by one of its longitudinal ends to one of the longitudinal ends of each of said support members.
    [0006] This allows, in particular, to locate the arrival of the internal pipe of said tubular lubricating oil distribution element at the part of each member closest to the axis A. Preferably, each support member supports two bearings, respectively associated with two wheels of satellites.
    [0007] Advantageously, each support member comprises two tracks, each arranged to support at least one satellite bearing, and having different diameters. This makes it possible to axially mount two bearings on the member by the same longitudinal end of said member, in particular for mounting two spaced gears constituting the satellite corresponding to said member.
    [0008] Advantageously, the holding piece is a separate part of the support members.
    [0009] Preferably, this holding piece comprises comprises for each support member, a ring surrounding the latter between the two tracks. The reported crown of each support member, to secure together said bodies of the satellite support so as to transmit a torque to an output shaft, including propeller or blower. In addition, the fact that the ring is reported allows a simple mounting of the satellite by installing axially, successively, the upstream bearing, the ring, and the downstream bearing. The invention also relates to a turbomachine comprising a gear as described above.
    [0010] The invention also relates to a method of producing a gear as described above, characterized in that the bearings and the holding piece are mounted on the support members by translations having all the same direction along the axes B. Thanks to the characteristics of said reducer thus gaining simplicity of assembly 15 and accessibility for maintenance. BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the description of a non-limiting example which follows, with reference to the accompanying drawings in which: - Figure 1 is a schematic longitudinal half-sectional view of a turbomachine doublet contra-rotating propellers, such as an "open rotor"; FIG. 2 shows, according to a detailed longitudinal half-section of part I of FIG. 1, an exemplary embodiment of an epicyclic gear train gearbox according to the prior art; - Figure 3 shows in perspective, a schematic view of a carrier-satellites according to the prior art used in the gear reducer epicyclic gear of Figure 2; FIG. 4 represents, according to a detailed longitudinal half-section of part I of FIG. 1, an exemplary embodiment of an epicyclic gear train reducer according to the invention; FIG. 5 shows, in partial perspective, the main elements of an epicyclic gear train gearbox according to the invention; FIG. 6 is a perspective view of a schematic view of a satellite carrier used in the epicyclic gear train gearbox of FIG. 4; FIG. 7 schematically shows the mounting steps of a satellite carrier for an epicyclic gear train gearbox according to the prior art; and FIG. 8 schematically shows the mounting steps of a planet carrier for an epicyclic gear train gearbox according to the invention.
    [0011] It should be noted that the elements fulfilling identical functions are referenced with the same numbers in the different figures. DESCRIPTION OF THE PREFERRED EMBODIMENT The invention relates in particular to an epicyclic gear reducer in a turbomachine with a pair of counter-rotating propellers, "open rotor", such as that presented above, with reference to FIG. Although this example is not limiting, the following description of the invention can easily be adapted by those skilled in the art, for example in the case of an epicyclic gear train gearbox for driving a blower in a machine. A turbomachine with a double flow. Here, the general architecture of the reducer is similar to that which has been described above. With reference to FIG. 4, the differential gear unit 11 with epicyclic gear train comprises, with respect to the longitudinal axis A of the turbomachine: a planetary input shaft 15 of axis A of rotation, in the form of a toothed wheel, which is mounted by a splined connection on the turbine shaft 10 rotating in a direction of rotation by driving the gearbox 11, 3035375 10 satellites 18, here the number of three arranged at 1200 some of others (two being shown in FIG. 5), which are each formed by two toothed wheels 18a, 18b meshing around the input shaft 15 and which are supported by a satellite carrier 17 rotating, accordingly, in a direction of rotation identical to the input shaft 15, and an outer ring gear 19, which meshes with the gears 18a, 18b, satellites 18 and which rotates in the opposite direction of rotation of the input shaft 15, so in the opposite direction of the planet carrier 16. The side downstream of the gearbox 11 being turned towards the propellers 2, 3, the shaft 12 of the upstream propeller 2 terminates in an annular bulb, to be rotationally integral with the planet carrier 16 connected to the planet carrier 17, while that the shaft 13 of the downstream propeller 3, is integral in rotation with the outer ring gear 19. With reference to FIGS. 5 and 6, the satellite support 17 here comprises three support members 21of the satellites 18, each defining an axis B rotation of said satellites 18 18, parallel to the axis A and regularly distributed at 120 ° from each other, about said axis A. These support members 21 are constituted by substantially cylindrical hollow tubes 21 around each axis A The annular flange 20 has a connecting ring 38 associated with each cylindrical tube 21 arranged to hold the latter substantially at its center along the axis B. The annular flange 20 has a connecting ring 38 associated therewith. e connection 38 surrounds the outer surface of each cylindrical tube 21, so as to be placed between the upstream wheels 18a and downstream 18b of the satellite. In an embodiment illustrated in FIG. 5, fingers 47 connect the planet carrier 16 to the annular flange 20 of the planet carrier 17, between the cylindrical tubes 21. The fingers 47 are preferably fixed to the annular flange 20 by ball joints 48 to form an isostatic mounting. In an alternative embodiment, not shown, the fingers 47 can pass inside the cylindrical tubes and be fixed, preferably also by a ball joint connection substantially in the middle of the cylindrical tubes 21, at the connecting rings 38. Indeed, as is apparent from the following description, the inside of the cylindrical tubes 21 is clear and leaves a passage for the fingers 47, in the gear 11 according to the invention, by the way, the surface radially inner of each cylindrical tube 21 may have a rib 44, substantially in the middle along the axis B, promoting its mechanical strength and can be used as an attachment for fixing the fingers 47.
    [0012] Each tubular support member 21 serves as support for bearings 23a, 23b of corresponding satellites 18. Here, an upstream bearing 23a and a downstream bearing 23b respectively allow the rotation of upstream gears 18a and 18b downstream of each satellite 18 about the axis B. In the example shown, it is bearings 23a, 23b comprising each an internal ring 10 centered on the cylindrical tube 21, an outer ring centered on a toothed wheel 18a, 18b, allowing the rotation of the gears around the cylindrical tube 21 The radially outer surface of each cylindrical tube 21 here comprises an upstream cylindrical track 22a, having a first diameter D1, and a downstream cylindrical track 22b, having a second diameter D2 slightly smaller than D1. The upstream cylindrical track 22a supports the inner ring of the upstream bearing 23a, while the downstream cylindrical track 22b supports the inner ring of the downstream bearing 23b. Note in this connection that the connecting ring 38 has an internal diameter corresponding to the internal diameter D2 of the downstream track 22a. When the satellite support 17 is assembled, the connecting ring 38 is thus positioned in abutment with the interface between the upstream tracks 22a and the downstream tracks 22b, between the two bearings 23a and 23b. In this way, the flange 20 can pass between the upstream bearings 23a and downstream 23b, and between the upstream gears 18a and 18b downstream, to secure the connecting rings 38. The satellite support 17 according to the invention, illustrated in detail with reference to FIGS. 4 and 5, it is possible to bring the lubricating oil to the rotating elements 23a, 23b, 18a, 18b at the periphery of the cylindrical tubes 21. The path of the oil has been symbolized by As in the state of the art previously described, an oil transfer device 28 is here provided for transferring the oil from an oil supply source 27 located in the fixed nacelle 4 The device 28 is located in an annular internal space of the turbine engine 1, located around the turbine shaft 10 and delimited between a stationary housing 32 and the upstream side of the gearbox 11. epicyclic train. With reference to FIG. 4, the transfer device 28 mainly comprises two concentric outer 33 and inner 34 rings spaced radially from one another, the outer ring 33 being fixed to a static casing 32 of the turbomachine and the ring internal mounting 34 being fixed to the carrier-satellites 17 of the gearbox 11. To pass the rotation between the fixed outer ring 33 connected to the static housing 32 (fixed reference) and the inner rotating ring 34 connected to the satellite carrier 17 (rotary reference), Bearings, plain or with bearings, are arranged between the rings.
    [0013] Advantageously, bearings with rolling elements are used. In general spherical rollers are chosen in cooperation with straight teeth or cylindrical rollers in cooperation with chevron or helical gears in order to maintain the planetary position of the planet in the axial position relative to the planet gear and to the crown, but without making the system hyperstatic. .
    [0014] The outer ring 33 is connected to a supply line exiting the oil source 27 and has an opening for radial passage of the oil therethrough. Means, not forming part of the invention, connect the outer and inner rings 33 and 34 to each other and are arranged to allow the oil to pass to the inner ring 34. The inner ring 34 is itself pierced with openings. radial to let the oil pass. An intermediate tubular piece 37 around the axis A of the gearbox 11, or oil distribution box, integral with the rotary satellite support 17, is intended to convey the oil exiting the inner ring 34 of the transfer device 28. to each cylindrical tube 21. The oil distribution housing 37 has an upstream portion 35 of substantially cylindrical shape about the axis A, which supports the inner ring 34 on its outer periphery. A downstream portion 36 forms the connection with each cylindrical tube 21.
    [0015] In the thickness of the oil distribution housing 37, a cavity 29 is provided to form a pipe carrying the oil from downstream to upstream. This duct 29 is annular at least in the upstream portion 35 of the casing 37. The duct 29 opens out onto the outer periphery of the upstream portion 35 so as to be in communication with the orifices of the inner ring 34 of the transfer device. 28. The pipe 29 also opens at the free ends of the downstream part 36, inside each cylindrical tube 21. Preferably, the whole of the oil distribution box 37 remains radially close to the shaft 15. The pipe 29 thus opens downstream at the portion of the cylindrical tubes 21 closest to the axis A of the reducer 11. Each cylindrical tube 21 has a substantially constant thickness over its circumference, except in its the portion closest to the axis A of the gearbox 11. At this portion, an inner conduit 45 is formed in the thickness of the cylindrical tube 21 and communicates, at its upstream end, with the corresponding downstream opening e of the inner pipe 29 of the distribution housing 37. The inner pipe 45 is located in a limited angular sector of the cylindrical tube, on either side of the plane passing through the axis B of the cylindrical tube 21 and the axis A of the reducer 11. It presents here a symmetry around this plane. In a variant, this inner duct 45 can be multiple to distribute the oil more evenly over an angular sector. The conduit 45 extends axially substantially over the entire length of the cylindrical tube 21, in particular it extends in front of the two bearings 23a, 23b. It is closed laterally and downstream. The radially inner wall of the duct 45 with respect to the axis B has substantially the same thickness as that of the cylindrical tube 21, outside the duct 45, and contributes to the mechanical strength of the cylindrical tube, as well as to the connection with the distribution box 37.
    [0016] Here, the radial extension of the inner duct 45 has a value substantially equal to that of the thickness of the cylindrical tube 21. As a result, the cylindrical tube 21 forms a tubular piece whose internal space is largely clear. The radially outer wall of the inner conduit 45 relative to the axis B is, in turn, in the continuity of the outer surface of the cylindrical tube. Its thickness 30 is adapted to support the bearings 23a, 23b.
    [0017] The radially outer wall of the inner duct 45 is traversed by substantially radial orifices 46, placing the inner duct 45 in communication with the external surface of the cylindrical tube 21, at the upstream and downstream tracks 22a and 22b of the rolling bearings 23a. 23b.
    [0018] As a result, the oil from the distribution housing 37, whose path is symbolized by the arrows T, enters the upstream in the conduit 45 and exits on the outer surface of the cylindrical tube through the orifices 46. part of the experience of those skilled in the art to adjust the shape of the conduit 45 and / or orifices 46 to distribute the flow of oil arriving at the surface of the cylindrical tube substantially uniformly in front of the bearings 23a, 23b. The upstream tracks 22a and downstream 22b of the cylindrical tube 21 comprise several circumferential channels 41 spaced axially and arranged such that there are several in front of each bearing 23a, 23b, for example at least three. These channels 41 are here in planes substantially perpendicular to the axis A. In addition, they are arranged to communicate with the oil outlet orifices 46 of the inner conduit 45. In the example shown, the orifices 46 may be radial slots on which arrive the channels 41. In a variant, the channels 41 can make the complete turn of the cylinder 21 and the orifices 46 open at the bottom of the channels 41, the latter having, for example, a secant shape to the duct 45.
    [0019] In this way, the oil leaving each orifice 46, for one part goes directly into the part of the bearing 23a, 23b situated in front of the orifice 46 and, for another part, flows into the channel 41 which communicates with said orifice 46. The channels 41 have, for example, a transverse section 0, punctually open or a U-shaped cross section continuously open on the outer surface of the cylindrical tube 21. This section is adapted to promote the circumferential circulation of the oil around the cylindrical tube in the channel 41, while allowing the oil to escape, evenly substantially on the circumference, to the bearings 23a, 23b by opening the channel on the outer surface. This phenomenon is favored by the combined effects of the centrifugation resulting from the rotation of the satellite support 17 and the driving of the bearings around the cylindrical tube 21.
    [0020] According to known methods and means, not forming part of the invention, the oil reaching the bearings 23a, 23b passes through them to lubricate the gears between each satellite 18 and the toothed wheel 19, and is then removed from the gearbox. 11. It will furthermore be noted that, in the example presented, the cylindrical tube 21 comprises in part an integral part, an upstream flange 39 at the end of the upstream part of the external surface, and that a nut 40 is fixed in downstream of the downstream part of the outer surface. This upstream flange 39 and this downstream nut 40 form axial abutments which hold the bearings 23a, 23b and the connecting ring 38 in position. Preferably, the distribution box 29 and the cylindrical tubes 21 can be made of a alone holding, for example by forging. In all cases, the assembly forms a part making it easier to mount the satellite support 17. With reference to FIG. 8, this assembly is done in four steps, all corresponding to a mounting of the parts on the cylindrical tubes 21 by a translation along the axis B, from downstream to upstream, preferably using an integrated assembly formed of the oil distribution housing 37 and, here, the three cylindrical tubes 21 for supporting the satellites. A first step a) consists in installing the upstream bearings 23a on the upstream track 22a of each cylindrical tube 21, by introducing them via the downstream side of the cylindrical tubes 21, which is free whereas the upstream side is blocked by the presence of the distribution box 37.
    [0021] In a second step b), the flange 20 is installed by introducing the connecting rings 38 by the downstream side of the cylindrical tubes 21, then sliding them so as to position them at the interface between the upstream track 22a and the downstream track 22b of each cylindrical tube 21. In a third step c), the downstream bearings 23b are installed on the downstream track 22b of each cylindrical tube 21, still passing through the downstream end. In a fourth step d), a nut 40, axial stop for the bearings 23a, 23b and the connecting ring 38, is clamped to the downstream end of each cylindrical tube 21. Thus, thanks to the tracks of the bearings which have not not the same diameter and thanks to the space cleared in the cylindrical tubes 21, we can assemble the satellite carrier 30 of the gearbox with fewer parts and only one side. The holding flange 20 and its crowns 38 are easily accessible. Not having to access both sides facilitates the maintenance of the reducer because, in this case we can leave part of the support-satellites and satellites mounted on the rest of the module to change only certain parts. 5
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Gear unit (11) with epicyclic gear train for a turbomachine (1), in particular an aircraft, comprising a planetary shaft (15) of axis A of rotation, a ring (19) of axis A extending around said planetary shaft (15), satellites (18) distributed around said axis A, which are meshing with said ring gear (19) and the sun gear shaft (15), and a satellite support (17) comprising, on the one hand, bearing support (21) of bearings (23a, 23b) of the satellites (18a, 18b), axes of rotation B, which are regularly distributed around the axis A, and secondly, a part (20-38 ) now each support member (21) substantially by its middle along its axis B, characterized in that said support members (21) are formed in one piece with means (45, 46, 41) for feeding lubricating oil of said bearings (23a, 23b).
    [0002]
    2. Gearbox (11) according to claim 1, wherein said support members (21) each have a hollow tubular shape, preferably of substantially circular cross section on its outer periphery.
    [0003]
    3. gearbox (11) according to one of the preceding claims, wherein said means (45, 46, 41) lubricating oil supply of said bearings (23a, 23b) comprise at least one external channel (41) circulation lubricating oil about the axis B in communication with the outer periphery of said support members (21).
    [0004]
    4. Gearbox (11) according to one of the preceding claims, wherein said support members (21) are formed integrally therebetween and with a tubular lubricating oil distribution member (29), which extends around said axis A and which comprises an annular pipe (37) for dispensing oil to the support members (21). 3035375 18
    [0005]
    5. Gearbox (11) according to the preceding claim, wherein said tubular element (29) is connected by one of its longitudinal ends to one of the longitudinal ends of each of said support members (21). 5
    [0006]
    6. gearbox (11) according to one of the preceding claims, wherein each support member (21) comprises two tracks (22a, 22b), each arranged to support at least one satellite bearing (23a, 23b), and having diameters (D2, D1) different. 10
    [0007]
    7. gearbox (11) according to one of the preceding claims, wherein the holding member (20, 38) is a separate part of the support members (21).
    [0008]
    8. gearbox (11) according to claims 6 and 7, wherein the holding piece (20, 38) comprises for each support member (21), a ring (38) 15 surrounding the latter between the two tracks (22a, 22b).
    [0009]
    9. Turbomachine (1), characterized in that it comprises at least one gear (11) according to one of the preceding claims. 20
    [0010]
    10. A method of producing a gearbox (11) according to claim 8, characterized in that the bearings (23a, 23b) and the holding piece (20, 38) are mounted on the support members (21) by means of translations having all the same meaning along the axes B. 25
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    同族专利:
    公开号 | 公开日
    BR112017022476A2|2018-07-10|
    EP3286457A2|2018-02-28|
    JP6768699B2|2020-10-14|
    CA2982888A1|2017-01-12|
    CN107532518A|2018-01-02|
    RU2704516C2|2019-10-29|
    WO2017005997A2|2017-01-12|
    JP2018516331A|2018-06-21|
    US20180163850A1|2018-06-14|
    RU2017136708A|2019-05-23|
    FR3035375B1|2018-07-27|
    RU2017136708A3|2019-09-30|
    CN107532518B|2019-09-10|
    WO2017005997A3|2017-03-23|
    EP3286457B1|2020-02-12|
    US10302187B2|2019-05-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2493834A|2011-08-18|2013-02-20|Snecma|Transmission arrangement for counter-rotating propellers of a dual-propeller turboprop|
    WO2013124590A1|2012-02-23|2013-08-29|Snecma|Device for recovering lubricating oil from an epicyclic reduction gear|
    FR2987417A1|2012-02-23|2013-08-30|Snecma|Epicyclic gear reducer for blower module of turbojet i.e. double-flow turbojet, has set of planetary carriers comprising positioned radial extension, and oil guided or ejected towards radial end of reducer by centrifugal force|FR3074552A1|2017-12-06|2019-06-07|Safran Transmission Systems|SPEED REDUCER CROWN WITH PLANETARY TURBOMACHINE TRAIN|
    FR3081959A1|2018-06-05|2019-12-06|Safran Transmission Systems|METHOD FOR ASSEMBLING A REDUCER AND INSTALLATION FOR IMPLEMENTING THE METHOD|
    FR3104193A1|2019-12-10|2021-06-11|Safran Aircraft Engines|RECOVERING LUBRICATING OIL FROM AN AIRCRAFT TURBOMACHINE REDUCER|FR2940247B1|2008-12-19|2011-01-21|Snecma|SYSTEM OF CONTRAROTATIVE PROPELLERS DRAWN BY AN EPICYCLOIDAL TRAIN PROVIDING A BALANCED TORQUE DISTRIBUTION BETWEEN THE TWO PROPELLERS|
    FR2962109B1|2010-07-05|2013-04-12|Snecma|TURBOMOTEUR WITH NON CARINEES PROPELLERS|
    ITBO20100109U1|2010-10-29|2012-04-30|Bonfiglioli Riduttori Spa|PLANETARY REDUCER|
    GB201210146D0|2012-06-08|2012-07-25|Rolls Royce Plc|Oil scavenge arrangement|
    JP6334535B2|2012-09-04|2018-05-30|イスパノ・シユイザ|Planetary gear reducer especially for turbomachinery|
    FR3009594B1|2013-08-08|2016-12-09|Snecma|EPICYCLOIDAL TRAIN REDUCER WITH FLUID TRANSFER PIPES, AND AIRCRAFT TURBOMACHINE FOR AN AIRCRAFT WITH SUCH REDUCER|
    RU2528236C1|2013-08-27|2014-09-10|Открытое акционерное общество "Научно-производственное объединение "Сатурн"|Planetary differential reduction gearbox|
    US9038779B2|2013-08-30|2015-05-26|United Technologies Corporation|Geared architecture gas turbine engine with oil scavenge|US10227928B2|2013-01-18|2019-03-12|General Electric Company|Engine architecture with reverse rotation integral drive and vaneless turbine|
    US10801442B2|2017-02-08|2020-10-13|General Electric Company|Counter rotating turbine with reversing reduction gear assembly|
    DE102017108332A1|2017-04-19|2018-10-25|Rolls-Royce Deutschland Ltd & Co Kg|Transmission device with at least one with respect to a housing device rotating component|
    CN107178426B|2017-06-07|2019-04-26|南昌航空大学|A kind of storage function governor gear transmission turbogenerator|
    DE102018101723A1|2018-01-25|2019-07-25|Rolls-Royce Deutschland Ltd & Co Kg|Device and aircraft engine with a device|
    FR3084429B1|2018-07-26|2020-11-13|Safran Trans Systems|REDUCER OR DIFFERENTIAL TYPE DEVICE FOR AN AIRCRAFT TURBOMACHINE|
    FR3088979B1|2018-11-23|2021-06-18|Safran Trans Systems|SATELLITE CARRIER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    CN113123871A|2021-04-21|2021-07-16|南京航空航天大学|Jet self-driven and blade tip turbine driven contra-rotating propeller fan engine with hoop|
    法律状态:
    2016-04-12| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-28| PLSC| Publication of the preliminary search report|Effective date: 20161028 |
    2017-04-06| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2022-01-07| ST| Notification of lapse|Effective date: 20211205 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1553675A|FR3035375B1|2015-04-23|2015-04-23|EPICYCLOIDAL GEAR TRAIN REDUCER FOR A TURBOMACHINE.|
    FR1553675|2015-04-23|FR1553675A| FR3035375B1|2015-04-23|2015-04-23|EPICYCLOIDAL GEAR TRAIN REDUCER FOR A TURBOMACHINE.|
    US15/567,493| US10302187B2|2015-04-23|2016-04-21|Reduction gear having an epicyclic gear train for a turbine engine|
    PCT/FR2016/050943| WO2017005997A2|2015-04-23|2016-04-21|Reduction gear having an epicyclic gear train for a turbine engine|
    RU2017136708A| RU2704516C2|2015-04-23|2016-04-21|Reduction gear with epicycloid transmission for gas turbine engine|
    CA2982888A| CA2982888A1|2015-04-23|2016-04-21|Reduction gear having an epicyclic gear train for a turbine engine|
    EP16725185.9A| EP3286457B1|2015-04-23|2016-04-21|Reduction gear having an epicyclic gear train for a turbine engine|
    BR112017022476-3A| BR112017022476A2|2015-04-23|2016-04-21|gearbox with epicyclic gear train for a turbomachine|
    CN201680022665.XA| CN107532518B|2015-04-23|2016-04-21|The reduction gearing with epicyclic train of gears for turbogenerator|
    JP2017554569A| JP6768699B2|2015-04-23|2016-04-21|Reducer with epicyclic gear train for turbine engine|
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