• 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:
    Mechanical reduction gear (6) of a turbomachine, in particular of an aircraft, this reduction gear comprising: - a sun gear having an axis of rotation, - a ring (9) which extends around the sun and which is configured to be stationary in rotation around of said axis, - satellites which are meshed with the sun and the crown and which are held by a planet carrier which is configured to be movable in rotation about said axis, - at least one lubricating oil distributor which comprises a part stator (15) stationary in rotation and a rotor part (14) integral in rotation with said planet carrier, and - an annular oil deflector (26) which is integral with the crown, characterized in that said stator part is integral with said deflector. Figure for the abstract: Figure 4
    公开号:FR3093550A1
    申请号:FR1902311
    申请日:2019-03-07
    公开日:2020-09-11
    发明作者:Louis Simon Adrien；Bruno François FOGLIA Matthieu
    申请人:Safran Aircraft Engines SAS；Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    [0001] Technical field of the invention
    [0002] The present invention relates to the field of mechanical reduction gears for turbomachines, in particular aircraft.
    [0003] Technical background
    [0004] The state of the art includes in particular the documents WO-A1-2010/092263, FR-A1-2 987 416 and FR-A1-3 041 054.
    [0005] The role of a mechanical gearbox is to modify the speed and torque ratio between the input axis and the output axis of a mechanical system.
    [0006] New generations of dual-flow turbomachines, particularly those with a high bypass ratio, include a mechanical reduction gear to drive the shaft of a fan (also called a “fan”). Usually, the purpose of the reduction gear is to transform the so-called fast rotation speed of the shaft of a power turbine into a slower rotation speed for the shaft driving the fan.
    [0007] Such a reducer comprises a central pinion, called sun gear, a crown and pinions called satellites, which are engaged between the sun gear and the crown. The satellites are held by a frame called the planet carrier. The solar, the crown and the planet carrier are planetary because their axes of revolution coincide with the longitudinal axis X of the turbomachine. The satellites each have a different axis of revolution, they are evenly distributed over the same operating diameter around the axis of the planetary gears. These axes are parallel to the longitudinal axis X.
    [0008] There are several reducer architectures. In the state of the art of turbofan engines, the reduction gears are of the planetary or planetary type. In other similar applications, there are so-called differential or “compound” architectures.
    [0009] - On a planetary gearbox, the planet carrier is fixed and the crown constitutes the output shaft of the device which rotates in the opposite direction to the sun.
    [0010] - On an epicyclic reduction gear, the crown is fixed and the planet carrier constitutes the output shaft of the device which rotates in the same direction as the sun gear.
    [0011] - On a differential gearbox, no element is fixed in rotation. The crown rotates in the opposite direction to the sun and the planet carrier.
    [0012] Reducers can include one or more meshing stages. This meshing is ensured in different ways such as by contact, by friction or even by magnetic fields. There are several types of meshing by contact such as with straight or chevron teeth.
    [0013] A gearbox must be lubricated and the supply of lubricating oil to the rotating components of a gearbox can be problematic. The oil is brought to the reduction gear by a distributor which comprises a stationary stator part in rotation and a rotor part integral in rotation with the planet carrier when the reduction gear is of the epicyclic type. The stator part of the distributor cooperates in sealing with the rotor part, this sealing having to be guaranteed whereas the stator part must in operation move and tilt relative to the reduction gear and follow the movements of the rotor part. In the current technique, the stator part is immobilized in rotation by connecting rod to a stator casing of the turbomachine.
    [0014] The present invention proposes a simple, effective and economical improvement to this technology.
    [0015] The invention relates to a planet carrier for a mechanical gearbox of a turbomachine, in particular an aircraft, this gearbox comprising:
    [0016] - a solar having an axis of rotation,
    [0017] - a crown which extends around the sun and which is configured to be stationary in rotation around said axis,
    [0018] - satellites which are meshed with the sun and the crown and which are held by a planet carrier which is configured to be mobile in rotation around said axis,
    [0019] - a lubricating oil distributor which comprises a stationary stator part in rotation and a rotor part fixed in rotation to said planet carrier, and
    [0020] - at least one annular oil deflector which is integral with the ring gear,
    [0021] characterized in that said stator part of the distributor is integral with said deflector.
    [0022] In the state of the art, the deflector has a single function of capturing and guiding the oil projected radially outwards, with a view to its evacuation and recycling. In the present invention, the deflector has this function and also has another function of maintaining the stator part of the distributor in order to limit the relative displacements and the relative rocking between the stator and rotor parts of the distributor in operation, which makes it possible to guarantee a good seal between these parts in particular.
    [0023] The solution proposed below is compatible with an epicyclic reduction gear whose ring gear is fixed in the motor reference. It is compatible with any type of toothing (straight, chevron), any type of planet carrier, whether one-piece or of the cage-carrier/cage type, and it is compatible with planet bearings made up of rolling elements. (ball bearings, roller bearings, tapered roller bearings, etc.) or hydrodynamic bearings.
    [0024] The reducer according to the invention may comprise one or more of the following characteristics, taken separately from each other, or in combination with each other:
    [0025] - the deflector comprises an annular flange for fixing to an annular flange of the crown,
    [0026] - the crown comprises two half-crowns each comprising a rim equipped with a toothing and a fixing half-flange, the fixing half-flanges being fixed together and to the flange of the deflector,
    [0027] - the crown comprises two half-crowns each comprising a rim equipped with a toothing and a fixing half-flange, the ferrule being fixed to the rim of one of the half-crowns or being formed in one piece with the one of the half-crowns,
    [0028] - the deflector comprises an outer peripheral part extending around a half-crown.
    [0029] - the deflector comprises an internal peripheral part extending mainly radially to said axis,
    [0030] - the deflector may comprise an annular row of through lights,
    [0031] - the deflector comprises a tapered portion in which said slots are formed,
    [0032] - said stator part of the distributor comprises:
    [0033] - an outer cylindrical surface comprising oil outlet orifices and configured to cooperate in sealing with said rotor part of the distributor, and
    [0034] - an internal oil circuit comprising an annular cavity connected on the one hand to pipes extending mainly axially and connecting said cavity to said orifices, and on the other hand to at least one supply channel extending mainly radially from said cavity.
    [0035] The invention further relates to a turbomachine, in particular for an aircraft, comprising a mechanical reduction gear as described above.
    [0036] Brief description of figures
    [0037] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:
    [0038] Figure 1 is a schematic view in axial section of a turbomachine using the invention,
    [0039] Figure 2 is a partial view in axial section of a mechanical reducer,
    [0040] Figure 3 is another partial view in axial section of a mechanical reducer, and illustrates the technique prior to the present invention,
    [0041] Figure 4 is another partial view in axial section of a mechanical reducer, and illustrates the present invention,
    [0042] Figure 5 is a perspective view of the reducer of Figure 4, and
    [0043] FIG. 6 is a view similar to that of FIG. 4 and illustrating an alternative embodiment of the invention.
    [0044] Detailed description of the invention
    [0045] FIG. 1 describes a turbomachine 1 which comprises, in a conventional manner, a fan S, a low pressure compressor 1a, a high pressure compressor 1b, an annular combustion chamber 1c, a high pressure turbine 1d, a low pressure turbine 1e and a exhaust pipe 1h. The high pressure compressor 1b and the high pressure turbine 1d are connected by a high pressure shaft 2 and form with it a high pressure body (HP). The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3 and form with it a low pressure body (LP).
    [0046] The fan S is driven by a fan shaft 4 which is driven to the LP shaft 3 by means of a reducer 6. This reducer 6 is generally of the planetary or planetary type.
    [0047] The description which follows relates to a reducer of the planetary type, of which the planet carrier and the solar are mobile in rotation, the crown of the reducer being fixed in the frame of the motor.
    [0048] The reducer 6 is positioned in the upstream part of the turbomachine. In the present application, the expressions upstream and downstream refer to the general flow of gases in the turbomachine, along its axis of elongation or rotation of its rotors. A fixed structure comprising schematically, here, an upstream part 5a and a downstream part 5b which makes up the motor casing or stator 5 is arranged so as to form an enclosure E surrounding the reducer 6. This enclosure E is here closed upstream by seals at the level of a bearing allowing the crossing of the fan shaft 4, and downstream by seals at the level of the crossing of the LP shaft 3.
    [0049] Figure 2 shows an epicyclic reducer 6. At the input, the reducer 6 is connected to the BP shaft 3, for example via internal splines 7a. Thus, the BP shaft 3 drives a planet gear called the sun gear 7. Conventionally, the sun gear 7, whose axis of rotation coincides with that of the turbomachine X, drives a series of gears called satellites 8, which are evenly distributed over the same diameter around the axis of rotation X. This diameter is equal to twice the operating center distance between the solar 7 and the satellites 8. The number of satellites 8 is generally defined between three and seven for this type of application.
    [0050] All of the satellites 8 are held by a frame called the planet carrier 10. Each satellite 8 rotates around its own Y axis, and meshes with the ring gear 9.
    [0051] Dans cette configuration épicycloïdale, l’ensemble des satellites 8 entraine en rotation le porte-satellite 10 autour de l’axe X de la turbomachine. La couronne est fixée au carter moteur ou stator 5 via un porte-couronne 12 et le porte-satellites 10 est fixé à l’arbre de soufflante 4. Dans une autre configuration planétaire, l’ensemble des satellites 8 est maintenu par un porte-satellites 10 qui est fixé au carter moteur ou stator 5. Chaque satellite entraine la couronne qui est rapportée à l’arbre de soufflante 4 via un porte-couronne 12. As output we have: In this epicyclic configuration, all of the planet wheels 8 rotate the planet carrier 10 about the axis X of the turbomachine. The ring gear is fixed to the motor casing or stator 5 via a ring gear carrier 12 and the planet gear carrier 10 is fixed to the fan shaft 4. In another planetary configuration, the set of satellites 8 is held by a planet carrier 10 which is fixed to the motor casing or stator 5. Each satellite drives the crown which is attached to the fan shaft 4 via a crown carrier 12.
    [0052] Each satellite 8 is mounted free to rotate using a bearing 11, for example of the bearing or hydrodynamic bearing type. Each bearing 11 is mounted on one of the axes 10b of the planet carrier 10 and all the axes are positioned relative to each other using one or more structural frames 10a of the planet carrier 10. There are a number of axes 10b and bearings 11 equal to the number of satellites. For reasons of operation, assembly, manufacture, control, repair or replacement, the axles 10b and the frame 10a can be separated into several parts.
    [0053] Une demi-couronne amont 9a constituée d’une jante 9aa et d’une demi-bride de fixation 9ab. Sur la jante 9aa se trouve l’hélice amont de la denture du réducteur. Cette hélice amont engrène avec celle du satellite 8 qui engrène avec celle du solaire 7. Une demi-couronne aval 9b constituée d’une jante 9ba et d’une demi-bride de fixation 9bb. Sur la jante 9ba se trouve l’hélice aval de la denture du réducteur. Cette hélice aval engrène avec celle du satellite 8 qui engrène avec celle du solaire 7. For the same reasons mentioned above, the teeth of a reducer can be separated into several helices each having a median plane P. In our example, we detail the operation of a reducer with several helices with a crown separated into two half-crowns : An upstream half-ring 9a consisting of a rim 9aa and a fixing half-flange 9ab. On the rim 9aa is the upstream helix of the reduction gear teeth. This upstream helix meshes with that of satellite 8 which meshes with that of solar 7. A downstream half-ring 9b consisting of a rim 9ba and a fixing half-flange 9bb. On the rim 9ba is the downstream helix of the gear teeth. This downstream propeller meshes with that of satellite 8 which meshes with that of solar 7.
    [0054] If the helix widths vary between solar 7, satellites 8 and crown 9 because of tooth overlaps, they are all centered on a median plane P for the upstream helices and on another median plane P for the downstream helices . In the case of a bearing with two rows of rollers, each row of rolling elements is also preferably, but not necessarily, centered on two median planes.
    [0055] The fixing half-flange 9ab of the upstream crown 9a and the fixing half-flange 9bb of the downstream crown 9b form the fixing flange 9c of the crown. The crown 9 is fixed to a crown holder by assembling the fixing flange 9c of the crown and the fixing flange 12a of the crown holder using a bolted assembly for example.
    [0056] The arrows in Figure 2 describe the routing of the oil in the reducer 6. The oil arrives in the reducer 6 from the stator part 5 in a distributor 13 by various means which will not be specified in this view because they are specific to one or more types of architecture. Distributor 13 includes injectors 13a and arms 13b. The injectors 13a have the function of lubricating the teeth and the arms 13b have the function of lubricating the bearings. The oil is brought to the injector 13a to come out through the end 13c in order to lubricate the teeth. The oil is also brought to the arm 13b and circulates via the supply port 13d of the bearing. The oil then circulates through the shaft in one or more buffer zones 10c and then exits through the holes 10d in order to lubricate the bearings of the satellites.
    [0057] Figure 3 shows a more concrete embodiment of an oil distributor 13 which comprises a rotor part 14 and a stator part 15.
    [0058] The rotor part 14 is integral in rotation with the planet carrier 10 and has a generally annular shape around the axis X. This part 14 comprises end pieces 14a engaged in the supply mouths 13d of the bearings 11 of the planet wheels 8 and comprising orifices 16 of oil outlet for the oil supply of the buffer zones 10c.
    [0059] The rotor part 14 comprises at its internal periphery an internal cylindrical surface 14b comprising orifices 17 for oil inlets. The rotor part 14 further comprises an annular chamber 18 which is connected on the one hand by first channels 19 substantially radial to the orifices 17, and by second channels 20 substantially L-shaped to the orifices 16.
    [0060] The stator part 15 of the distributor 13 is secured to a casing of the turbomachine which is not shown. In practice, part 15 is connected to the casing by an arm which serves to prevent the swiveling of the reducer 6.
    [0061] The stator part 15 has a generally annular shape around the axis X and comprises a cylindrical body engaged in the rotor part 14 and comprising an outer cylindrical surface 15a comprising orifices 21 for oil outlet. The surfaces 14b and 15a cooperate together in operation to guarantee sealing between the internal oil circuits of the distributor 13.
    [0062] The internal oil circuit of the stator part 15 comprises an annular cavity 22 connected on the one hand to pipes 23 extending substantially axially and connecting the cavity 22 to the orifices 21, and on the other hand to at least one channel of supply 24 extending substantially radially from the cavity 22. The channel 24 opens radially outwards on an outer surface of the stator part 15 to form an orifice 25 for the oil inlet.
    [0063] The reducer 6 in FIG. 3 also comprises an annular oil deflector 26. This deflector 26 is integral with the crown 9 and forms part of the stator of the reducer because the crown 9 is fixed. The deflector 26 is in the form of a thin annular shell. The deflector 26 comprises a radially outer peripheral edge which is fixed to the crown 9 and which in particular comprises an annular flange 27 for fixing to the flange 9c of the crown. The deflector 26 extends around a half-ring 9b, here downstream, and comprises a radially internal peripheral edge which is free.
    [0064] In axial section, the deflector 26 has a generally curved shape. It is configured to capture the oil centrifuged and expelled radially outwards during operation and to route this oil to the flange 9c of the ring gear 9 where this oil can be evacuated and recycled.
    [0065] However, as mentioned above, to guarantee the seal between the rotor 14 and stator 15 parts of the distributor 13, it is necessary to limit or even prevent any relative movement (apart from the rotation of the rotor part 14 around the stator part 15) and any relative tilting of these parts.
    [0066] The invention makes it possible to remedy this problem and proposes a first embodiment in FIGS. 4 and 5, in which the deflector 26 is modified to assign it an additional function of maintaining the stator part 15 of the deflector 26. Maintaining the stator part 15 by a stator element of the reducer, in this case crown 9, makes it possible to limit or even prevent the aforementioned relative displacements and tiltings.
    [0067] For this, the deflector 26 is elongated and now extends from the crown 9 to the stator part 15. The deflector 26 comprises a radially outer peripheral part 26a similar to that in FIG. 3 (and comprises a flange 27 for fixing to the crown 9), and also comprises two additional parts, namely a radially inner peripheral part 26c and an intermediate part 26b (located between the parts 26a, 26c).
    [0068] The intermediate part 26b has a generally frustoconical shape and comprises, in the example shown, an annular row of crossing slots 28 serving to adjust the mass and the flexibility of the part 26. These slots are not necessary for the proper functioning of the part 26.
    [0069] The internal part 26c extends substantially radially with respect to the axis X and can be fixed to the stator part 15 by any appropriate means and for example by welding or shrinking. Alternatively, the deflector 26 could be formed in one piece with the stator part 15.
    [0070] In the example shown where the stator part 15 is engaged in the rotor part 14 from downstream and its inlet 25 is located downstream of the reducer 6, the connection of the deflector 26 to this stator part 15 can be located just upstream of this orifice 25.
    [0071] In the embodiment variant of figure 6, the deflector 26 of the prior art is retained and an additional deflector 26' equips the reducer 6.
    [0072] The deflector 26 'comprises parts 26b', 26c' similar to those of the deflector 26 of Figures 4 and 5. The outer peripheral edge of the deflector 26' is here not fixed to the flange of the crown but is connected directly to a rim 9ba of one of the half-crowns, here downstream 9b. The deflector 26 'can be fixed to the rim 9ba by welding or can be formed in one piece with this rim, as in the example shown.
    [0073] The free inner peripheral edge of deflector 26 surrounds the outer periphery of deflector 26' and is spaced from deflector 26' by a small radial clearance 29.
    [0074] Thus, the solution proposed by the invention consists in integrating two functions in the same room, which makes the design of the architecture simpler. In addition, the deflector is a more effective means than the aforementioned arm of the state of the art to prevent the gearbox from rotating.
    权利要求:
    Claims (10)
    [0001]
    Mechanical reduction gear (6) for a turbomachine (1), in particular for an aircraft, this reduction gear comprising: - a solar (7) having an axis of rotation (X), - a crown (9) which extends around the solar (7) and which is configured to be stationary in rotation around said axis (X), - satellites (8) which are meshed with the sun gear (7) and the crown (9) and which are held by a planet carrier which is configured to be able to rotate around said axis (X), - a distributor (13) of lubricating oil which comprises a stator part (15) immobile in rotation and a rotor part (14) integral in rotation with said planet carrier, and - at least one annular oil deflector (26, 26') which is integral with the crown (9), characterized in that said stator part (15) of the distributor (13) is integral with said deflector (26, 26').
    [0002]
    Mechanical reducer (6) according to Claim 1, in which the deflector (26) comprises an annular flange (27) for fixing to an annular flange (9c) of the crown (9).
    [0003]
    Mechanical reduction gear (6) according to Claim 2, in which the crown (9) comprises two half-crowns (9a, 9b) each comprising a rim (9aa, 9ba) equipped with a set of teeth and a fixing half-flange (9ab , 9ab), the fixing half-flanges being fixed together and to the flange (27) of the deflector (26).
    [0004]
    Mechanical reduction gear (6) according to Claim 1, in which the crown (9) comprises two half-crowns (9a, 9b) each comprising a rim (9aa, 9ba) equipped with a toothing and a half-flange (9ab, 9ab ) for fixing, the deflector (26) being fixed to the rim of one of the half-rings or being formed in one piece with one of the half-rings.
    [0005]
    Mechanical reducer (6) according to Claim 3 or 4, in which the deflector (26) comprises an outer peripheral part (26a) extending around a half-ring (9b).
    [0006]
    Mechanical reducer (6) according to one of the preceding claims, in which the deflector (26) comprises an internal peripheral part (26c) extending mainly radially to said axis (X).
    [0007]
    Mechanical reduction gear (6) according to one of the preceding claims, in which the deflector (26) comprises an annular row of through-holes (28).
    [0008]
    Mechanical reducer (6) according to the preceding claim, in which the deflector (26) comprises a frustoconical portion (26b) in which the said slots (28) are formed.
    [0009]
    Mechanical reduction gear (6) according to one of the preceding claims, in which the said stator part (15) of the distributor (13) comprises: - an external cylindrical surface (15a) comprising oil outlet orifices (21) and configured to cooperate in sealing with said rotor part (14) of the distributor (13), and - an internal oil circuit comprising an annular cavity (22) connected on the one hand to pipes (23) extending mainly axially and connecting said cavity to said orifices (21), and on the other hand to at least one channel supply (24) extending primarily radially from said cavity (22).
    [0010]
    Turbomachine (1), in particular for an aircraft, comprising a mechanical reduction gear (6) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    EP3705705A1|2020-09-09|
    CN111664225A|2020-09-15|
    US20200284203A1|2020-09-10|
    FR3093550B1|2021-02-19|
    EP3705705B1|2021-08-25|
    JP2020143669A|2020-09-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2010092263A1|2009-02-16|2010-08-19|Snecma|Lubrication and cooling of a reduction gear with epicyclic gear train|
    EP2518279A2|2011-04-27|2012-10-31|United Technologies Corporation|Fan drive planetary gear system integrated carrier and torque frame|
    EP2554874A2|2011-08-02|2013-02-06|United Technologies Corporation|Journal pin oil supply for gear system|
    US20130225353A1|2012-02-23|2013-08-29|Snecma|Device for lubricating an epicycloidal reduction gear|
    FR2987416A1|2012-02-23|2013-08-30|Snecma|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.|
    FR3041054A1|2015-09-15|2017-03-17|Hispano-Suiza|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|
    FR3088979B1|2018-11-23|2021-06-18|Safran Trans Systems|SATELLITE CARRIER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    CN113531103B|2021-09-13|2021-12-07|中车戚墅堰机车车辆工艺研究所有限公司|Lubricating structure and gear box|
    法律状态:
    2020-02-20| PLFP| Fee payment|Year of fee payment: 2 |
    2020-09-11| PLSC| Publication of the preliminary search report|Effective date: 20200911 |
    2021-02-18| PLFP| Fee payment|Year of fee payment: 3 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1902311|2019-03-07|
    FR1902311A|FR3093550B1|2019-03-07|2019-03-07|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|FR1902311A| FR3093550B1|2019-03-07|2019-03-07|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    JP2020011527A| JP2020143669A|2019-03-07|2020-01-28|Aircraft turbine engine mechanical reduction gear|
    CN202010141652.2A| CN111664225A|2019-03-07|2020-03-04|Mechanical speed reducer for aircraft turbine engine|
    EP20161331.2A| EP3705705B1|2019-03-07|2020-03-05|Mechanical gear of an aircraft turbine engine|
    US16/810,158| US20200284203A1|2019-03-07|2020-03-05|Aircraft turbine engine mechanical reduction gear|
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