• 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:
    A planet carrier (18) for an epicyclic gear reducer (10) having a torque transmitting member (24) having a longitudinal axis A and an annular cage (26) extending about the axis A and connected to a longitudinal end of the member (24). The cage (26) comprises two flanks (28, 30) extending substantially radially with respect to the axis A and connected by bridges (32), seats (36) extending axially between the flanks (28, 30). ) and being adapted to support satellites (20) rotatably mounted around the seats (36). The bridges (32) comprise bars (33, 34) which are each inclined with respect to a longitudinal plane passing through the axis A and substantially by the corresponding bar (33, 34).
    公开号:FR3058493A1
    申请号:FR1660738
    申请日:2016-11-07
    公开日:2018-05-11
    发明作者:Maxime Lefebvre；Michel Pierre Di Giovanni Jean-Charles；Emile Andre Peltier Jordane；Julien Ptaszynski Patrice
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    TECHNICAL FIELD The present invention relates to a planet carrier for planetary gear reducer, in particular for an aircraft turbomachine.
    STATE OF THE ART [0002] The purpose of a mechanical reducer is to modify the speed ratio and / or the torque between the input axis and the output axis of a mechanism.
    Conventionally, double-flow turbomachines, in particular those having a high dilution rate, comprise a mechanical reduction gear with planetary gear 10 (see FIG. 1) for driving the shaft 12 of a fan (not shown). Usually, the planetary gear reducer 10 aims to transform the so-called rapid speed of rotation of the shaft of a power turbine 14 into a slower speed of rotation for the shaft 12 driving the blower.
    Conventionally, a planetary gear reducer 10 comprises (relative to the longitudinal axis A of the turbomachine around which the shaft of the power turbine 14 in particular rotates):
    a sun gear 16, in the form of a toothed wheel which is mounted by a splined connection on the turbine shaft 14, this sun gear 16 rotating in a direction of rotation by driving the reducer 10,
    a planet carrier 18 carrying satellites 20 by means of bearings, so as to rotate around axes Y parallel to the longitudinal axis A, the satellites 20 being formed by toothed wheels meshing around the sun gear 16, and the planet carrier 18 can be fixed to a stator,
    - an external toothed ring 22, which meshes with the satellites 20 and which can be kept fixed relative to the structure of the turbomachine (a stator).
    In particular, the planet carrier 18 is one of the central parts of the reduction gear 10, supporting the bearing axes as well as the satellites 20. It has in particular the function of ensuring good support conditions for the satellites 20 of the planetary reduction gear 10. One of the major requirements linked to a planet carrier 18 is to keep the satellites 20 aligned, despite the deformations undergone by the planet carrier 18 which is highly stressed, and also not to break in the event of ultimate load. A misalignment of the satellites 20 can in particular cause premature wear of the gears and of the speed reducer 10.
    The planet carrier 18 is conventionally a solid steel piece and therefore heavy.
    Thus, the objective of this application is to provide a planet carrier 18 capable of supporting the applied loads while keeping the satellites 20 aligned, as light as possible.
    PRESENTATION OF THE INVENTION The invention proposes for this purpose a planet carrier for a speed reducer with planetary gear, comprising a torque transmission member with longitudinal axis A and an annular cage extending around the axis A and connected to a longitudinal end of the member, said cage comprising two flanks extending substantially radially with respect to axis A and connected by bridges, seats extending axially between the flanks and being intended to supporting satellites rotatably mounted around the seats, characterized in that said bridges comprise bars which are each inclined relative to a longitudinal plane passing through the axis A and substantially through the corresponding bar.
    This structure can allow a weight gain of 20% compared to the planet carriers of the state of the art. This structure can also make it possible to achieve a gain on the radial misalignment of the satellites of - 45% compared to the conventional planet carriers of the state of the art.
    This structure can also allow better accessibility for machining and for maintenance. As the architecture of the cage is more open compared to the state-of-the-art satellite carriers, this allows, among other things, simpler endoscopic controls. The maximum stresses and the tangential misalignment remain equivalent to those of the conventional satellite carriers known in the state of the art.
    The planet carrier 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:
    - each trigger guard comprises at least two crossed bars,
    - the two bars of each trigger guard intersect in an area located near one of the sides,
    said zone is located near the side situated on the side opposite to said transmission member,
    - each trigger guard has a general shape of X,
    - at least one of the sides comprises, between two adjacent seats, at least one recess,
    - each recess is aligned with a trigger guard according to a plane passing through the axis
    AT,
    - each recess has a general U or V shape, the opening of which is oriented radially outward relative to the axis A,
    - the sides and bridges are made in one piece.
    The invention also relates to a speed reduction gear with planetary gear comprising a planet carrier as mentioned above. The invention also relates to a turbomachine, in particular for an aircraft, comprising a planetary gear reducer as mentioned above.
    BRIEF DESCRIPTION OF THE FIGURES Other characteristics and advantages of the invention will appear on reading the detailed description of exemplary embodiments below, with reference to the appended figures which represent, respectively:
    Figure 1 is a perspective view of a conventional planetary gear reducer, Figure 2 is a perspective view of a planet carrier according to the invention, Figures 3 and 4 are a top view of a cage planet carrier according to the invention, FIG. 5 is a front view of a planetary gear reducer according to the invention, FIG. 6 is a rear view of a planetary gear reducer according to the invention,
    DETAILED DESCRIPTION OF AN EMBODIMENT As mentioned above, FIG. 1 illustrates the general structure of a planetary gear speed reducer 10. During the operation of the planetary gear train 10, the torque transmitted through the reducer 10 being important, this can cause deformation of the planet carrier 18 and lead to a misalignment of the axes of the satellites 20. Furthermore, the centrifugal forces can also generate a deformation of the planet carrier 20, which can again cause a misalignment of the satellites 20. As indicated above, it is essential that the planet carrier 18 maintain the correct positioning of the satellites 20, despite the deformations undergone by the satellite carriers 18 in operation.
    As shown in Figure 2, the planet carrier 18 according to the invention extends along the axis A and comprises two parts: a torque transmission member with a longitudinal axis 24 A and an annular cage 26 extending around the axis A. The annular cage 26 is connected to a longitudinal end of the torque member 24. The torque transmission member 24 is tubular and extends axially (along the axis A ). It has a generally cylindrical or frustoconical shape, one longitudinal end of which is extended by an annular connecting part and intended to make the link with the turbine shaft 14 (see FIG. 1). Thus, the front longitudinal end of the member 24 is connected to the cage 26 of the rear end which has a toothing 27 intended to be driven with the turbine shaft 14.
    The front is defined as being on the side of the fan and the rear is defined as being on the side of the exhaust nozzle of the turbomachine.
    The annular cage 26 has two sides 28, 30 extending substantially radially with respect to the axis A, respectively a front side 28 and a rear side 30. The front side 28 is defined as the side located on the opposite side of the transmission member 24 and the rear flank 30 is defined as that integral with the member 24. The two flanks 28, 30 are interconnected by bridges 32. As illustrated in Figures 2, 3 and 4, each trigger guard 32 comprises at least two intersecting bars 33, 34 and therefore has a general shape of X. Each bar 33, 34 is thus cut into two corresponding parts 33a, 33b, 34a, 34b substantially aligned and extending on both sides other of the crossing (or crossing area) of the X. In the example shown, the two corresponding bars 33, 34 of each bridge 32 intersect in an area located near one of the sides 28, 30, the side before 28 in this case.
    According to the embodiment presented, the sides 28, 30 and the bridges 32 are formed in one piece. This allows the planet carrier 18 to form a single structural unit, thereby eliminating the problems associated with the assembly of several parts by means of additional connecting members. This in particular makes it possible to avoid the problems linked to the imbalance generated by the assembly tolerances, the assembly problems or even the additional mass due to the multiplication of the parts.
    As illustrated in Figures 2 and 6, the front flanks 28 and rear 30 each have holes 36 each for mounting an end of a satellite shaft 20 and thus forming seat 36 for a satellite 20. These seats 36 thus extend axially (along axis A) between the sides 28, 30 and are intended to support the satellites 20 rotatably mounted around the seats 36.
    As shown in Figures 2 and 6, at least one of the sides 28, 30, in this case the front side 28 comprises, between two adjacent seats 36, at least one recess 38 aligned with a bridge 32 according a plane passing through axis A (see Figure 6). Each recess 38 is located between the corresponding bars 33, 34 of each bridge 32 and has a general U or V shape whose opening is oriented radially outward relative to the axis A.
    In a manner known per se, during the operation of the reduction gear 10, a first force path crosses the rear flank 30 (starting from the corresponding ends of the seats 36 of the satellites 20) then the torque transmission member 24. A second force path crosses the front flank 30 (from the corresponding ends of the seats 36 of the satellites 24 to the connection zones between the front flank 28 and the bridges 32), the bridges 32 then the torque transmission member 24 .
    The cage 26 which supports the bearing axes (along the Y axis) and therefore the satellites 20 has thus been shaped with the bars 33, 34 crisscrossed to obtain "trellis" or "braces". This allows the correct passage of the forces necessary for the operation of the reduction gear 10 with a minimum of material. The present invention therefore presents a solution which optimizes the mass of the reduction gear 10 without hampering the passage of forces between the sides 28, 30 and by limiting the misalignment of the satellites 20.
    This optimization is obtained thanks to the particular inclination of the bars 33, 34 of the bridges 32. Indeed, the bars 33, 34 of the bridges 32 are each cut into two parts: a rear part (close to the rear flank 30) and a front part (close to the front flank 28). The rear parts 33a, 34a and front 33b, 34b of each bar 33, 34 meet at the crossing of the X formed by each trigger guard 32. The particularity of the invention is that, like the corresponding bars 33, 34 between them, the rear parts 33a, 34a and front 33b, 34b of each bar 33, 34 of each trigger guard 32 do not extend in the same plane and form an angle different from 0 between them. Thus, each trigger guard 32 comprises bars 33, 34 which are each inclined relative to a first longitudinal plane passing through the axis A and substantially through the corresponding bar 33, 34 and therefore each part 33a, 34a is inclined relative to a second longitudinal plane passing through A and substantially through the corresponding bar part 33b, 34b. This difference in inclination of the bars 33, 34 between them and of the different parts 33a, 34a, 33b, 34b between them makes it possible to stiffen the planet carrier 26 in torsion around the axis A during the operation of the turbomachine.
    In addition, this structure of the train 10 makes it possible to carry out the main milling operations from outside the train 10, which is not possible on the trains 10 of the state of the art.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. planet carrier (18) for a planetary gear reducer (10), comprising a torque transmission member (24) of longitudinal axis A and an annular cage (26) extending around the axis A and connected to a longitudinal end of the member (24), said cage (26) comprising two sides (28, 30) extending substantially radially with respect to the axis A and connected by bridges (32), seats (36) extending axially between the sides (28, 30) and being intended to support satellites (20) rotatably mounted around the seats (36), characterized in that said bridges (32) comprise bars (33, 34) which are each inclined relative to a longitudinal plane passing through the axis A and substantially by the corresponding bar (33, 34).
    [2" id="c-fr-0002]
    2. planet carrier (18) according to the preceding claim, wherein each trigger guard (32) comprises at least two bars (33, 34) intersecting.
    [3" id="c-fr-0003]
    3. planet carrier (18) according to the preceding claim, wherein the two bars (33, 34) of each trigger guard (32) intersect in an area located near one of the sides (38, 30).
    [4" id="c-fr-0004]
    4. planet carrier (18) according to the preceding claim, wherein said area is located near the side (28) located on the side opposite to said transmission member (24).
    [5" id="c-fr-0005]
    5. planet carrier (18) according to one of the preceding claims, in which each trigger guard (32) has a general shape of X.
    [6" id="c-fr-0006]
    6. planet carrier (18) according to one of the preceding claims, wherein at least one of the sides (28, 30) comprises, between two adjacent seats (36), at least one recess (38).
    [7" id="c-fr-0007]
    7. planet carrier (18) according to the preceding claim, wherein each recess (38) is aligned with a trigger guard (32) along a plane passing through the axis A.
    5
    [8" id="c-fr-0008]
    8. planet carrier (18) according to claim 6 or 7, wherein each recess (38) has a general U or V shape whose opening is oriented radially outward relative to the axis A.
    [9" id="c-fr-0009]
    9. planet carrier (18) according to one of the preceding claims, in which
    [10" id="c-fr-0010]
    10 the sides (28, 30) and the bridges (32) are formed in one piece.
    10. Planetary gear speed reducer (10) comprising a planet carrier (18) according to any one of the preceding claims.
    [11" id="c-fr-0011]
    11. A turbomachine, in particular for an aircraft, comprising a planetary gear reducer (10) according to the preceding claim.
    1/2
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    同族专利:
    公开号 | 公开日
    US10816088B2|2020-10-27|
    US20200072340A1|2020-03-05|
    WO2018083410A1|2018-05-11|
    FR3058493B1|2018-11-16|
    CN109923335A|2019-06-21|
    EP3535505B1|2021-06-23|
    EP3535505A1|2019-09-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1186804A1|2000-09-01|2002-03-13|A. Friedr. Flender GmbH|Planet carrier for a planetary gearing|
    EP1482210A2|2003-05-27|2004-12-01|A. Friedr. Flender Ag|Transmission to drive a rotating tube|
    EP2677209A1|2012-06-18|2013-12-25|Robert Bosch Gmbh|Planet carrier of a planetary gear|FR3106384A1|2020-01-21|2021-07-23|Safran Transmission Systems|SATELLITE CARRIER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    EP3892895A1|2020-04-10|2021-10-13|Safran Transmission Systems|Mechanical gear for aircraft turbine engine|DE10334459A1|2003-07-29|2005-03-17|Zf Friedrichshafen Ag|Guide disc assembly of a planet carrier for a planetary gear|
    CN100389277C|2005-12-23|2008-05-21|德阳东汽表面工程技术有限公司|Assembly planetary carrier for wind power|
    US7704178B2|2006-07-05|2010-04-27|United Technologies Corporation|Oil baffle for gas turbine fan drive gear system|
    US8585536B2|2012-04-02|2013-11-19|Hamilton Sundstrand Corporation|Gear carrier frame|
    DE102012012098A1|2012-06-18|2013-12-19|Robert Bosch Gmbh|Planet bridge for connecting two planetary web cheeks|
    FR3011901B1|2013-10-10|2017-02-10|Hispano-Suiza|SATELLITE CARRIER FOR AN EPICYCLOIDAL TRAIN SPEED REDUCER|FR3052213B1|2016-06-07|2018-05-18|Safran Transmission Systems|METHOD FOR ASSEMBLING A SATELLITE HOLDER|
    FR3090061B1|2018-12-13|2021-01-29|Safran Trans Systems|SATELLITE CARRIER FOR A SPEED REDUCER|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-11| PLSC| Publication of the preliminary search report|Effective date: 20180511 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660738|2016-11-07|
    FR1660738A|FR3058493B1|2016-11-07|2016-11-07|SATELLITE CARRIER FOR AN EPICYCLOIDAL TRAIN SPEED REDUCER|FR1660738A| FR3058493B1|2016-11-07|2016-11-07|SATELLITE CARRIER FOR AN EPICYCLOIDAL TRAIN SPEED REDUCER|
    EP17804229.7A| EP3535505B1|2016-11-07|2017-10-31|Planet carrier for a speed-reducing unit with an epicyclic gear train|
    US16/347,167| US10816088B2|2016-11-07|2017-10-31|Planet carrier for a speed-reducing unit with an epicyclic gear train|
    PCT/FR2017/052989| WO2018083410A1|2016-11-07|2017-10-31|Planet carrier for a speed-reducing unit with an epicyclic gear train|
    CN201780067925.XA| CN109923335A|2016-11-07|2017-10-31|Planet carrier for the deceleration unit with planetary gear train|
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