• 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 landing (7) of satellite (6) carried by a planet carrier (5) movable in rotation about an axis of rotation (X), said bearing comprising a central axis (9) intended to be linked. to the planet carrier, an inner ring (11) fixedly mounted on the central axis (9), an outer ring (16) rotatably mounted about said central axis (9), a lubricating circuit arranged to bring a flow of oil between said rings (11, 16), said lubrication circuit comprising a first portion (23a-23c, 24) arranged to be supplied with oil from the planet carrier (5) at the central axis (9). ) and having orifices (24) opening out of the inner ring (11) at a radially inner region (B) of the bearing relative to said axis of rotation (X), a second portion (25, 26) ) having orifices (26) opening outwardly of the inner ring (11) at a radially outer region (A) of the bearing relative to said axis of rotation (X), and an intermediate portion comprising at least one duct (27) arranged to connect the first part to the second part, characterized in that said at least one duct (27) comprises at least one loss of load singular formed by a bend (30) or a sudden narrowing of section (31) and at least one flattening of cross section over a majority portion of its length or a path forming a detour.
    公开号:FR3047284A1
    申请号:FR1650786
    申请日:2016-02-01
    公开日:2017-08-04
    发明作者:Aissa Benykhlef；Patrice Gedin；Guillaume Julien Beck；Benjamin Feraud
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    Satellite bearing for a satellite carrier, comprising lubricating means Field of the invention:
    The present invention relates to the field of bearings of rotating elements on a part itself rotated about an axis offset from said bearings, including satellite bearings in a turbomachine epicyclic gear train. It relates more particularly to lubrication devices for bearings of said bearings.
    State of the art:
    Double flow turbomachines, especially those having a high dilution ratio, can generally comprise an epicyclic gearbox to drive the fan. In a schematic manner, such a turbomachine comprises a fan placed generally in front of the engine part of the turbomachine, which successively comprises a gas generator and a power turbine. The purpose of the epicyclic gearbox is to convert the so-called rapid rotational speed of the power turbine shaft into a slower rotational speed for the shaft driving the fan.
    For this, with reference to FIG. 1, an example of a gearbox 1 with an epicyclic gear train comprises, with respect to the longitudinal axis X of the turbomachine around which the shaft 2 of the power turbine and the shaft rotate. 3 of the blower: a solar 4, in the form of a toothed wheel which is mounted by a splined connection on the turbine shaft 2, rotating in a direction of rotation by driving the gearbox, a carrier 5 secured to the shaft 3 of the fan, on which satellites 6 (three of which are shown here arranged at 60 ° from each other) are mounted by bearings 7, so as to rotate about Y axes parallel to the longitudinal axis X and linked to the planet carrier 5, the satellites 6 being formed by toothed wheels meshing around the sun 4, and an outer ring 8 toothed, which meshes with the satellites 6 and which, here, is held fixed by relation to the structure of the turbomachine e.
    Referring to Figure 2, where a single satellite 6 is schematically shown, during operation of the turbomachine, the solar 4 is driven at a determined rotational speed ωι by the shaft 2 of the turbine. By meshing both on the rotating solar 4 and on the fixed outer ring 8, the satellites 6 are rotated at a speed ω2 about the line Y at the center of their bearing 7 and drives the planet carrier 5, shown in FIG. 2 by the hub which supports the bearing 7, in a rotation at a speed 003 around the axis X. The rotation speeds ω2 of the satellites 6 and the reduction ratio between the rotation speed 0J3 of the planet carrier 5 and that ωι of the solar 4, are determined in particular by the proportions between the radius Ri of the solar 4 and the spokes R2 of the satellites 6. Generally, although the fan rotates less quickly than the turbine, the rotation speed ω2 of the carrier 5 satellites can be high, of the order of two thousand to four thousand revolutions per minute. Therefore the centrifugal acceleration field created at the level of the bearings 7 can be important, of the order of 1000 G or even higher. The bearing 7 of a satellite rotating with the planet carrier 5 is subjected to a Ntot loading, comprising a centrifugal radial component.
    Several technologies can be used for the bearings 7, such as, for example: hydrodynamic bearings or plain bearings; cylindrical roller bearings with several rows of rolling elements; or spherical bearings with one or more rows of rolling elements. The example shown in FIG. 1 corresponds to bearings 7 with two rows of spherical bearings.
    These technologies make it possible to withstand the forces applied to the bearings 7, in particular the Ntot loading. However, the lubrication of these bearings, which is essential for the performance and life of the gearbox, is affected by the centrifugal field.
    If we consider in particular bearings with rolling elements, such as those of Figure 1, the bearing contacts of the bearing 7 subjected to loading N see their maximum load in a region of the bearing 7 radially internal B, ie located radially inward with respect to the longitudinal axis X of the planet carrier 5. It is therefore essential to lubricate this zone B correctly, it is the location of the bearing 7 which requires a maximum of oil. Conversely, the centrifugal field, represented for example by the arrows G1 and G2, causes the lubricating oil present between the bearings radially outwardly relative to the longitudinal axis X, and tends to cause an accumulation of oil to a radially outer zone A of the bearing 7, opposite to the longitudinal axis X.
    There is therefore a need to define a bearing lubrication device that ensures proper lubrication at the radially inner region B of the bearing.
    However, particularly in the field of turbomachinery, it is important to achieve this result by ensuring that we have an overconsumption of oil to properly lubricate the radially internal zone B with an oil that tends to accumulate In fact, the higher the oil flow rate, the higher the volume of oil on board and the size of the tank for the lubrication circuit, which has an adverse effect on the mass of the turbomachine. .
    Moreover, especially for integration into an epicyclic reduction gear, the lubrication device must be simple and, preferably, the oil supply of the bearing on the planet carrier must be done by simplifying the arrival of oil.
    SUMMARY OF THE INVENTION: For this purpose, the invention relates to a satellite bearing carried by a planet carrier movable in rotation about an axis of rotation, said bearing comprising a central axis intended to be connected to the planet carrier, an inner ring mounted fixed on the central axis, an outer ring rotatably mounted about said central axis, a lubrication circuit arranged to bring a flow of oil between said rings, said lubrication circuit comprising a first portion arranged to be fed with oil from the planet carrier at the central axis and having orifices opening outwardly of the inner ring at a radially inner region of the bearing relative to said axis of rotation, a second portion comprising openings opening outwardly of the inner ring at a radially outer region of the bearing relative to said axis of rotation, and an intermediate portion comprising at least one pipe arranged to connect the first part to the second part, characterized in that said at least one pipe comprises at least a singular pressure loss formed by a bend or a sudden narrowing of section and at least one section flattening transverse on a majority portion of its length or a path forming a detour between two ends of said pipe.
    It is known to those skilled in the art to be able to give important values to the pressure drop of the circuit. It should be noted that the pressure drop of a circuit is composed of singular pressure drops (linked to a sudden variation such as an elbow or a restriction) and regular (or linear) pressure losses (related to the friction of the circuit). fluid on the walls of the pipe, these losses depending on the length, the roughness of the walls, the section and its shape). The detour, in the form of zigzags or loops, increases the length of the path made by the oil, the flattening increases the wet perimeter, the two characteristics increase the friction of the oil on the walls of the pipe.
    In this way, the realization of a communication pipe combining a pressure drop with an increase in friction along its path, allows to obtain significant pressure drops between the first part and the second part of the lubrication circuit. It is thus easy to adjust the distribution of lubricant flow rates sent between the radially inner and outer regions of the bearing, taking into account the centrifugal forces.
    Advantageously, a succession of several elbows makes it possible to create detours in the form of zigzags.
    Moreover, a flattening of transverse section preferably corresponds to a ratio greater than two between substantially perpendicular transverse dimensions.
    Preferably, the central axis comprises a first surface, radially external to said central axis, and the inner ring has a second surface, radially internal to said central axis, said first and second surfaces being contiguous. The bearing is then characterized in that said at least one communication pipe is formed by a groove made in the first or second surface.
    This embodiment makes it possible to form the communication pipe on one of the two elements, without touching the other. In addition, the realization of a groove on a surface can be done by a milling operation by precisely controlling the shape of this groove.
    Preferably, the first and second surfaces are cylindrical and smooth.
    Advantageously, the flattening of the transverse section of the at least one pipe is obtained by practicing in the first or second surface, a groove of transverse section substantially corresponding to an arc of a circle whose radius of curvature is greater than half the distance between the edges of the groove on said first or second surface.
    This embodiment of the groove makes it easy to maintain a constant passage section by increasing the radius of the circle to increase the wet perimeter.
    Advantageously, at least one of the first and second parts of the lubrication circuit comprises at least one pipe formed by a groove formed in the first or the second surface, communicating with a conduit passing through the inner ring.
    Even more advantageously, the first part of the lubrication circuit comprises a substantially longitudinal duct formed in said central axis and arranged to be supplied with lubricant at a first of its longitudinal ends, and at least one duct formed by a groove formed in the first or the second surface, communicating with said conduit through at least one outlet of the central axis.
    The realization of the first and second parts of the lubrication circuit at the interface between the ring and the central axis simplifies the manufacture of the bearing.
    Advantageously, the first part of the lubrication circuit comprises at least two grooves in the first or the second surface, in planes substantially perpendicular to the axis of rotation, each communicating with orifices passing through the inner ring.
    Said at least one pipe of the intermediate portion of the lubrication circuit can be connected to one of said at least two grooves of the first part of the lubrication circuit.
    In a particular embodiment, the intermediate portion of the lubrication circuit comprises a single pipe which is connected to that of said at least two grooves of the first part of the lubrication circuit which is furthest from said first longitudinal end of the longitudinal conduit of the central axis. The invention also relates to an assembly for an epicyclic gear train comprising a planet carrier, satellites and bearings as previously presented between the satellites and the planet carrier.
    Brief description of the figures:
    The present invention will be better understood and other details, characteristics and advantages of the present invention will emerge more clearly on reading the description of a nonlimiting example which follows, with reference to the appended drawings, in which: FIG. exploded perspective view of a planetary reduction gear comprising bearings according to the invention; FIG. 2 schematically represents in cross section the conditions to be reproduced for the tests of a bearing used in a gearbox such as that of FIG. 1; Figures 3a and 3b show schematically a first embodiment of a bearing according to the invention cut along a plane of symmetry in the centrifugal field; Figures 4a and 4b show schematically a cross section of an example of an oil line between the axis and the inner ring of a bearing according to the invention without and with a flattening; FIG. 5 represents a second embodiment of a bearing, according to the invention, cut along a plane of symmetry in the centrifugal field; and Figure 6 shows in perspective the skeleton of a lubrication circuit of a third embodiment of a bearing according to the invention.
    Description of an embodiment:
    A bearing 7 according to the invention is for example used in a turbomachine reducer as already presented in the foregoing, with reference to Figures 1 and 2.
    With reference to FIGS. 3a and 3b, a bearing 7 using a lubricating device according to the invention generally comprises the elements described hereinafter. Inside, an axis 9 integral with the planet carrier has a tubular portion, with a circular section centered on the Y axis. For example, this axis may be integral with a transverse portion of the planet carrier 5 linking the axes of all the bearings of the satellites. The axis 9 here comprises a smooth outer surface 10 and cylindrical diameter D1.
    An inner ring 11 of the bearing is arranged around the axis 9 so as to be secured to it and not to move in rotation. For example, the inner ring 11 has a cylindrical inner surface 12 having a diameter substantially equal to the diameter D1 of the outer surface 10 of the axis 9, so that they can be adjusted tightly.
    The outer surface of the inner ring 11 here comprises two tracks 13a and 13b for rolling elements 14, only one of which is shown schematically in FIG. 3b. The rolling elements 14 may have a spherical shape or a shape of small rolls or barrels. The tracks 13a and 13b have a shape of revolution around the central line Y of the bearing 7. Their longitudinal section is adapted to the shape of the rolling elements 14. This section may have a general direction slightly inclined relative to the axis Y. A central ring 15 separates here the two tracks 13a and 13b. In addition, flanges are formed at each longitudinal end of the inner ring 11, so as to maintain the rolling elements longitudinally.
    An outer ring 16 of the bearing is disposed around the rolling elements 14, radially opposite the inner ring 11 relative to said central axis. The inner surface of the outer ring here comprises two tracks 17a and 17b for the rolling elements 14. The tracks 17a and 17b also have a shape of revolution around the Y axis of the bearing 7. In longitudinal section, they form here a curve concave around the Y axis, centered around a radius passing longitudinally in the middle of the bearing 7.
    The two tracks 17a, 17b are here separated on this concave curve by a groove 18, positioned in front of the central ring 15.
    The tracks 17a and 17b are shaped to allow rolling of the rolling elements 14 and, thus, allow the outer ring 16 to rotate around the inner ring 11 and the axis 9 of the bearing. Furthermore, the concave shape of the tracks 17a and 17b longitudinally maintains the outer ring 16 in position facing the inner ring 11.
    Finally, the outer ring 16 is held integral by any means known to those skilled in the art to the toothed wheel 19 of the satellite 6, so as to ensure the rotation of the satellite 6 about the axis 9. The outer ring 16 can be adjusted tightened for example in this toothed wheel of the satellite 6.
    A lubrication circuit for an epicyclic gear as described has generally an oil reservoir, a first pipe system with one or more pumps for sending oil to the reducer, a recovery chamber of the invention. oil that has lubricated the gearbox and a second line system with one or more pumps to return the oil to the tank. These elements, known to those skilled in the art are not represented.
    At the level of the gearbox, a third ducting system, integral with the planet carrier 5, conveys the oil coming from the reservoir in particular to the bearings 7. In FIG. 1, this ducting system is schematically represented by a duct 20. The other parts of this third pipe circuit are not shown, nor the means for transferring oil from the first circuit to the reference frame in rotation of the planet carrier 5.
    One embodiment of the portion of the lubrication circuit specific to the bearing 7 is here detailed in three parts, with reference to FIGS. 3a and 3b.
    The first part is located at a radially internal zone B of the bearing 7 with respect to the axis X of the planet carrier. It is first formed by a substantially straight longitudinal duct 21, hollowed inside the wall of the axis 9 of the bearing 7 substantially in a median plane P with respect to the axis X of the planet carrier 5.
    The conduit 21 opens on a transverse wall so as to be connected to the conduit 20 of the third pipe system mentioned above. Note that in this example, the third pipe system has only one conduit 20 for supplying oil to bearing 7, for simplicity of integration, and that said conduit 20 opens on axis 9 to level of the radially internal area B.
    The conduit 21 is closed at its opposite longitudinal end. On the other hand, here three orifices 22a, 22b, 22c pass radially through the wall of the axis 9 toward the outside of the duct 21 towards the outer surface 10 of the axis 9. An orifice 22c opens at the level of the central crown 14 of the inner ring 11. The other orifices 22a, 22b open at the opposite longitudinal ends of the two tracks 13a, 13b of the inner ring 11.
    The first part of the circuit portion also comprises three grooves 23a, 23b, 23c dug in the inner surface 12 of the inner ring 1 in a plane perpendicular to the Y axis of the bearing 7. Each groove 23a, 23b, 23c is extends over an angular sector centered on the radially internal zone B, not going up beyond 90 degrees with respect to a plane passing through the longitudinal axis X. Each groove 23a, 23b, 23c is positioned longitudinally in front of the opening an orifice 22a, 22b, 22c on the outer surface 10 of the axis 9.
    As the outer surface 10 of the axis 9 and the inner surface 12 of the inner ring 11 are smooth and fitted, the grooves 23a, 23b, 23c form conduits at the interface between the axis 9 and the inner ring 1, which communicate with the supply of oil 20.
    Furthermore, one or more ducts 24 distributed over the circumferential extension of each groove 23a, 23b, 23c pass substantially radially through the inner ring 11. The ducts 24 corresponding to the central groove 23c open on either side of the central crown 5 to the inner longitudinal end of the tracks 13a, 13b of the ring 11. The ducts 24 corresponding to the other two grooves 23a, 23b open at the outer longitudinal ends of the tracks 13a, 13b.
    In the example shown, the groove 23b on the opposite side to the oil supply 20 extends over a very small angular sector or even zero and is positioned near the closed longitudinal end of the duct 21.
    Thus, in this first circuit part, the oil coming from the supply duct 20 is conveyed to the bearings 14 at the radially internal zone B.
    It is in the practice of those skilled in the art to size, for example with numerical simulations in fluid mechanics, the various elements of this first part, the longitudinal duct 21, the orifices 22a, 22b, 22c, the grooves 23a, 23b, 23c and the ducts 24, so that the oil is distributed in a longitudinally balanced manner in the radially internal zone B and with a flow rate sufficient to lubricate the bearings 14. The flow of oil thus arriving through this first part can be evacuate through the opening of the longitudinal ends of the volume containing the rolling elements 14, as indicated by the arrow 101 in Figure 3b.
    Part of the oil can also be driven circumferentially by the operation of the rotating bearing. It appears however that this is not sufficient to bring the oil necessary for the lubrication of the bearings at the radially outer zone A with respect to the axis X of the planet carrier or that this would correspond to an oil flow. unnecessarily high to pass at the radially internal zone B.
    For these reasons, the first circuit part which has just been described is advantageously sized to pass a flow adapted to the lubrication in the radially internal zone B and the lubrication circuit in the bearing comprises a second portion sized to let the oil flow adapted to lubricate the bearings at the radially outer region A, with an intermediate portion for supplying oil to the second portion from the first portion.
    We begin by describing the second part of the lubrication circuit in the bearing 7. In the example shown, this second part comprises a groove 25 hollowed in the inner surface 12 of the inner ring 11 in a plane perpendicular to the Y axis of the 7. The groove 25 extends over an angular sector centered around the radially outer zone A, not descending beyond 90 degrees around a plane passing through the longitudinal axis X. The groove 25 is positioned longitudinally between the two tracks 13a and 13b, at the level of the central ring 15.
    Furthermore, one or more ducts 26 distributed over the circumferential extension of the groove 25 pass substantially radially through the inner ring 11. The ducts 26 open on either side of the central crown 15 at the inner longitudinal end of the tracks 13a. , 13b of the ring 11.
    Here, this configuration has been found to be sufficient to provide the flow necessary for the lubrication of the bearings at the radially outer zone A. However, variants can be envisaged by using several grooves, in a manner comparable to that which is done at the level of the zone. radially internal B.
    In a manner comparable to that which exists at the radially internal zone B, the groove 25 forms a duct at the interface between the axis 9 and the inner ring 11, which can supply oil to the ducts 26 passing through the inner ring 11 .
    The intermediate portion of the circuit, designed to bring oil to the groove 25 in the radially outer zone A from the first part here comprises a transverse duct 27 extending over an arc connected to one end of the groove 23c farthest from the open longitudinal end of the conduit 21 for supplying oil and after the last conduit 24 on said groove 23c passing through the inner ring 11.
    The transverse duct 27 then communicates with the groove 25 of the second part by a longitudinal duct 28 extending in a median plane of the planet carrier, at the level in the radially external zone A.
    Advantageously, the transverse duct 27 and the longitudinal duct 28 are also formed at the interface between the axis 9 and the inner ring 11 by corresponding grooves 27, 28, hollowed in the inner surface 12 of the inner ring 11. The surface outer 10 of the axis 9 is smooth at this point.
    According to the invention, in a first variant embodiment, the groove 27 is hollowed out so that the corresponding conduit forms at least one, generally several, sharp elbow, as represented by the zigzag line in FIGS. and 3b.
    The elbows or bends form one or more singular pressure losses in the intermediate portion that prevent the strong centrifugal field G to which the oil is subjected in the lubrication circuit does not dry the first part of the circuit. In addition, the presence of the elbows 30 creates one or more zigzags in the route of the pipe 27, thus increasing its length and friction losses along its internal walls. By known methods, the skilled person can thus define the angles of elbows and their distribution on the conduit 27 to adapt the pressure drop to the centrifugal forces in the reducer in operation so as to balance the oil flow rates between the first and the second part of the circuit in stage 7.
    The zigzags form detours in the path of the pipe 27, in the sense that the path moves away from the shortest curve to join its two ends. In a variant not shown, a bend can be followed by one or more loops along the interface between the central axis 9 and the inner ring 11. These loops form detours that lengthen the path traveled by the oil in the pipe 27 , therefore friction losses along the walls.
    In this way, a suitable oil flow rate is delivered both at the radially inner zone B and at the radially outer zone A, in order to correctly but not excessively lubricate the bearings over the entire circumference of the bearing 7. As indicated by the arrows 101 and 102, the oil then escapes from the bearing 7 through the openings at the longitudinal ends of the volume containing the rolling elements between the inner and outer rings 11 and 16.
    According to another variant embodiment, not shown in FIGS. 3a and 3b but indicated in FIGS. 5 and 6 which are discussed below, singular pressure losses can also be created by creating one or more sudden constrictions 31 of the pipe 27 .
    In addition, to increase the friction outside singular head losses, the transverse section of the pipe 27 can be strongly flattened. This creates a wetted perimeter increase over a round section, which greatly increases the friction surface.
    With reference to FIGS. 4a and 4b, a very strong wet perimeter increase while keeping a passage section adapted to the desired flow rate can be created by acting on the shape of the groove forming the pipe 27.
    Figure 4a shows a groove section 27 having for example a semicircular shape. The area of the semicircle centered on the surface 12 here corresponds to a given passage section SP, adapted to the desired flow rate. The loss of load on a section of conduit having this section is substantially proportional to the wet perimeter, here the sum of the lengths of the semicircle and its diameter.
    By forming the groove 27, as shown in FIG. 4b, with a circle of larger diameter but with a center farther from the surface 12, thus increasing the ratio between the distance between the edges of the groove 27 and its depth to a value greater than two, one can obtain the same value of passage section SP but with a larger wet perimeter. We can therefore greatly increase the friction along the pipe by flattening it and preserving a passage section value adapted to the flow of oil to pass.
    A combination of variants, for example bends with a flattening of the passage section, is also conceivable.
    Furthermore, the longitudinal conduit 26 of the intermediate portion may also have singular pressure drops.
    At the level of the realization of the lubrication circuit in the bearing, it will be noted that the embodiment shown is easy to make. The longitudinal duct 21 and the transverse holes 22a, 22b, 22c in the axis 9, and the transverse ducts 24, 26 in the inner ring 11 may be formed by boring. The grooves 23a, 23b, 23c, 25, 26, 27, for their part, can be performed by milling. This technique allows in particular to control the shape dug to create singular pressure losses.
    It will also be noted that the example of the lubrication circuit in the bearing 7 has been presented with grooves dug in the inner wall 12 of the inner ring 11 but that a possible alternative to form conduits at the interface between the ring 11 and the axis 9 is to use grooves cut into the outer surface 10 of the axis 9, not machining the smooth inner surface 12 of the inner ring. Other embodiments of the architecture of the lubrication circuit may also incorporate the invention.
    Fig. 5 illustrates a second exemplary embodiment of the lubrication circuit. In this second example, the longitudinal duct 21 cut in the central axis 9 has a reduced longitudinal extension. It stops substantially at the level of the first transverse groove 23a of the first portion of the lubrication circuit and feeds, by a single through conduit 22, a longitudinal groove 21 'hollowed at the interface between the inner ring 11 and the axis 9. It is this longitudinal groove 21 'which supplies oil to the three transverse grooves 23a, 23b, 23c connected to the conduits 24 passing through the inner ring 11 in the radially inner zone B.
    The second part of the lubrication circuit comprises three orifices 26 passing through the inner ring 11 in the radially outer zone A with respect to the axis of the planet carrier 5, and positioned transversely substantially in front of the transverse grooves 23a, 23b, 23c of the first part.
    Here, the intermediate portion is composed of two times three grooves 27a, 27b, 27c, disposed on either side of the longitudinal groove 21 'of the first part and connecting each transverse groove 23a, 23b, 23c of the first part to an orifice 26 of the second portion passing through the inner ring.
    As indicated schematically in Figure 6, according to the invention is installed on each groove, for example, one or more abrupt narrowing 31 and it is associated with a flattened section of the groove. From an embodiment point of view, the entire circuit, after the longitudinal conduit 21, can be formed on the surface of the inner periphery of the inner ring 11, by digging a longitudinal feed groove for the first part and three circular grooves with a suitable flattening, on which section restrictions are placed between the through holes 24 of the radially inner zone B and those 26 of the radially outer zone A.
    Figure 6 illustrates a third architecture example of the lubrication circuit.
    Compared to the previous example, the first part comprises two complementary longitudinal grooves 21'a, 21'b in the radially inner zone B, connecting the transverse grooves 23a, 23b, 23c on either side of the central groove 21 .
    The second part comprises on its side a longitudinal groove 28 connecting the three through orifices 26.
    The intermediate portion has two transverse grooves 27a, 27b on each side, connecting the lateral longitudinal grooves 21'a, 21'b of the radially inner zone B to the central longitudinal groove of the radially outer zone. Here, each of the transverse grooves 27a, 27b of the intermediate portion is treated according to the invention, either by performing at least one zigzag with an elbow (variant not shown), or by placing at least one abrupt variation of section 31, associated with a flattening of transverse section on a majority portion of its length.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    claims
    1. Bearing (7) satellite (6) carried by a planet carrier (5) rotatable about an axis of rotation (X), said bearing having a central axis (9) intended to be connected to the carrier satellites, an inner ring (11) mounted fixed on the central axis (9), an outer ring (16) rotatably mounted about said central axis (9), a lubrication circuit arranged to bring an oil flow between said inner and outer rings (11, 16), said lubrication circuit comprising a first portion (23a-23c, 24) arranged to be supplied with oil from the planet carrier (5) at the central axis (9). ) and having orifices (24) opening out of the inner ring (11) at a radially inner region (B) of the bearing relative to said axis of rotation (X), a second portion (25, 26) ) comprising orifices (26) emerging outside the inner ring (11) at a radially outer region (A) of the pallet with respect to said axis of rotation (X), and an intermediate portion comprising at least one duct (27) arranged to connect the first portion (23a-23c, 24) to the second portion (25, 26), characterized in that said at least one pipe (27) comprises at least a singular pressure loss formed by a bend (30) or a sudden narrowing of section (31) and at least one transverse section flattening on a majority portion of its length or a path forming a detour.
    [2" id="c-fr-0002]
    2. Bearing (7) according to the preceding claim, wherein the central axis (9) has a first surface (10), radially external to said central axis, and the inner ring (11) has a second surface (12) , radially internal to said central axis, said first and second surfaces being contiguous, characterized in that said at least one pipe (27) is formed by a groove in the first (10) or second (12) surface.
    [3" id="c-fr-0003]
    3. Bearing (7) according to the preceding claim, wherein the first (10) and second (12) surfaces are cylindrical and smooth.
    [4" id="c-fr-0004]
    4. Bearing (7) according to claim 2 or 3, wherein the flattening of the cross section of said at least one pipe (27) is obtained by practicing in the first (10) or the second (12) surface, a groove (27) of transverse section substantially corresponding to an arc of a circle whose radius of curvature is greater than half the distance separating the edges of the groove on said first (10) or second (12) surface.
    [5" id="c-fr-0005]
    Bearing (7) according to any one of claims 2 to 4, wherein at least one of the first and second parts of the lubrication circuit comprises at least one channel formed by a groove in the first (10) or the second (12) surface, communicating with a conduit passing through the inner ring (11)
    [6" id="c-fr-0006]
    6. Bearing (7) according to the preceding claim, wherein the first part of the lubrication circuit comprises a conduit (21) substantially longitudinal, formed in said central axis (9) and arranged to be supplied with lubricant at a first end thereof longitudinal, and wherein at least one channel formed by a groove in the first (10) or second (12) surface, communicating with said conduit by at least one outlet (22a-22c) of the central axis ( 9)
    [7" id="c-fr-0007]
    7. Bearing (7) according to the preceding claim, wherein the first portion of the lubrication circuit (23a-23c, 24) comprises at least two grooves (23a-23c) in the first (10) or the second (12) surface , in planes substantially perpendicular to the axis of rotation (X), each communicating with orifices (24) passing through the inner ring (11).
    [8" id="c-fr-0008]
    8. Bearing (7) according to the preceding claim, wherein said at least one pipe (27) of the intermediate portion of the lubrication circuit is connected to one of said at least two grooves (23a-23c) of the first part of the circuit. lubrication.
    [9" id="c-fr-0009]
    9. Bearing (7) according to the preceding claim, wherein the intermediate portion of the lubrication circuit comprises a single pipe (27) which is connected to that (23c) of said at least two grooves (23a-23c) of the first part of the lubrication circuit which is furthest from said first longitudinal end of the longitudinal duct (21) of the central axis (9).
    [10" id="c-fr-0010]
    10. An assembly for an epicyclic gear train, comprising a planet carrier (5), satellites (6) and bearings (7) according to one of the preceding claims between the satellites and the planet carrier.
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    BE564660A|
    同族专利:
    公开号 | 公开日
    CA3012715A1|2017-08-10|
    CN108700121B|2020-12-01|
    RU2018127655A|2020-03-03|
    EP3411602B1|2021-10-13|
    CN108700121A|2018-10-23|
    US20190040908A1|2019-02-07|
    JP6913686B2|2021-08-04|
    US10697498B2|2020-06-30|
    JP2019503459A|2019-02-07|
    EP3411602A1|2018-12-12|
    WO2017134358A1|2017-08-10|
    RU2722151C2|2020-05-27|
    RU2018127655A3|2020-03-27|
    FR3047284B1|2018-06-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP2719927A1|2012-10-12|2014-04-16|Rolls-Royce plc|Oil scavenge arrangement|
    FR3015599A1|2013-12-23|2015-06-26|Skf Aerospace France|MECHANICAL DEVICE COMPRISING A BEARING AND A LUBRICATION SYSTEM, MACHINE AND METHOD FOR IMPLEMENTING SAID METHOD|FR3075876A1|2017-12-27|2019-06-28|Safran Transmission Systems|BEARING BEARING FOR A TURBOMACHINE COMPRISING LUBRICATION MEANS AND METHOD OF MAKING SAID BEARING BEARING|
    FR3101129A1|2019-09-24|2021-03-26|Safran Transmission Systems|OIL RESTRICTOR FOR EMERGENCY LUBRICATION OF AN AIRCRAFT TURBOMACHINE ELEMENT|SU1008565A1|1981-07-30|1983-03-30|Ivachev Leonid M|Planetary reduction gear lubrication system|
    US5106209A|1991-08-07|1992-04-21|General Electric Company|Multi-plane lubricated bearing assembly|
    JP2012163166A|2011-02-08|2012-08-30|Jtekt Corp|Conical roller bearing|
    US8343002B1|2011-06-20|2013-01-01|GM Global Technology Operations LLC|Rotating planetary gear carrier lubrication device|
    RU2472985C1|2011-07-19|2013-01-20|Андрей Михайлович Чумохвалов|Bearing assembly|
    EP2959177B1|2013-02-20|2019-10-30|United Technologies Corporation|Rolling element bearing configured with a gutter and one or more fluid passages|
    US9625028B2|2014-05-20|2017-04-18|Deere & Company|Shaft retention and lubrication system and method|FR3084429B1|2018-07-26|2020-11-13|Safran Trans Systems|REDUCER OR DIFFERENTIAL TYPE DEVICE FOR AN AIRCRAFT TURBOMACHINE|
    CN112377526A|2020-11-23|2021-02-19|浙江辛子精工机械有限公司|Gearbox bearing|
    法律状态:
    2017-02-01| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-04| PLSC| Publication of the preliminary search report|Effective date: 20170804 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-17| CD| Change of name or company name|Owner name: SAFRAN TRANSMISSION SYSTEMS, FR Effective date: 20180717 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 6 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650786A|FR3047284B1|2016-02-01|2016-02-01|SATELLITE BEARING FOR A SATELLITE CARRIER HAVING LUBRICATION MEANS|
    FR1650786|2016-02-01|FR1650786A| FR3047284B1|2016-02-01|2016-02-01|SATELLITE BEARING FOR A SATELLITE CARRIER HAVING LUBRICATION MEANS|
    RU2018127655A| RU2722151C2|2016-02-01|2017-01-20|Assembly for reduction gear with epicyclic transmission, including at least one support bearing of satellite, comprising lubrication means|
    CA3012715A| CA3012715A1|2016-02-01|2017-01-20|Assembly for an epicyclic reduction gearset comprising at least one satellite bearing comprising lubrication means|
    US16/074,039| US10697498B2|2016-02-01|2017-01-20|Assembly for an epicyclic reduction gearset comprising at least one satellite bearing comprising lubrication means|
    EP17706277.5A| EP3411602B1|2016-02-01|2017-01-20|Planetary gear reduction device with at least one planet gear bearing comprising lubrication means|
    CN201780009269.8A| CN108700121B|2016-02-01|2017-01-20|Assembly for a planetary reduction gear set comprising at least one satellite bearing comprising a lubrication device|
    PCT/FR2017/050117| WO2017134358A1|2016-02-01|2017-01-20|Assembly for an epicyclic reduction gearset comprising at least one satellite bearing comprising lubrication means|
    JP2018539271A| JP6913686B2|2016-02-01|2017-01-20|Assembly for epicyclic gear reduction gear including at least one satellite bearing including lubrication means|
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