• 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 wheel (35) for dispensing a lubricant in a turbomachine, the wheel having an axis about which extends an annular cavity open radially towards the axis and from which first and second pipes ( 43,45) lubricant supply of various organs to be lubricated. In parallel with the axis X, the annular cavity is divided into at least first and second annular sub-cavities which are separated by a substantially radial partition (38) and which communicate with the first and second pipes (43, 45), respectively.
    公开号:FR3047279A1
    申请号:FR1650696
    申请日:2016-01-28
    公开日:2017-08-04
    发明作者:Patrice Gedin；Pauline Marie Cecille Autran；Cecile Bruot；Guillaume Julien Beck；Alexis Dombek；Julie Lemoine；Jordane Peltier
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    Axially-distributing distribution wheel and planetary gear reducer
    The present invention relates in particular to a lubricant distribution wheel in a turbomachine and an epicyclic gear speed reducer, intended to equip in particular an airplane turboprop or turbofan engine.
    A speed reducer typically consists mainly of an internal sun gear (also called solar) driven by an input shaft, for example a turbine shaft, an external sun gear (also called crown), coaxial with the internal sun gear, satellites meshing both with the inner sun gear and with the outer sun gear, and a planet carrier on which the satellites are rotatably mounted.
    The variation of the reduction ratio of such a reducer is obtained by modifying the number of teeth of the solar, the satellites and the outer ring, and by the architecture of the reducer.
    In turbine engines, lubricant distribution wheels are known having an axis about which an annular cavity extends: radially open towards the axis, laterally limited by first and second walls substantially radial to said axis, to receive the lubricant, and from which at least first and second lubricant supply lines of various organs to be lubricated,
    One problem lies in the pressure supply of these bodies to be lubricated. This is particularly true when said members are located in the rotating field (such as bearings and gear teeth of the reducer), and fed from a pump located in a fixed reference. In addition, the distribution of lubricant requirements is different according to the operating phases of the gearbox. And, to limit the losses it is necessary to lubricate as close as possible to the need each of the bodies concerned, which invites to seek to adjust the distribution of the lubricant. The invention aims in particular to provide a wheel solution that promotes such an adjustment, while allowing this supply of pressure of the organs to be lubricated. To this end, it is first proposed that, parallel to said axis about which the annular cavity of the wheel extends, this cavity is split into at least a first and a second annular sub-cavities, which are separated by an internal partition. annular substantially radial to said axis, and communicate with the first and second pipes, respectively.
    Mounted on an epicyclic reduction gear or on an oil supply device as hereinafter, this impeller is intended to allow all or some of the following advantages: - to ensure lubrication without a connecting piece between the circuits connected to the fixed reference mark and those connected to the planet carrier typically provided on the gearbox, hence cost and reliability advantages, - transfer the lubricant (typically oil) from a fixed reference to the rotating mark without wear part, where again from reliability - allow a modular mounting of the gear unit in the motor, hence a gain on maintenance - distribute the lubricant between the various elements of the gear unit and vary this distribution according to the operating phases of the gear unit, where an optimization of the lubrication, an improvement of the yield, and a possible limitation of the overall mass of the engine (less lubricant used so embedded), - to ensure the lubrication ication of the gearbox in case of malfunction of one of the power supply systems (eg clogged nozzle, too high flow rate, etc ...), hence still reliability.
    In relation with the foregoing, it is also recommended that, on the wheel, radially to its axis: the first and second sub-cavities each have a bottom, and that its internal partition has, with respect to each bottom , a height lower than those of the first and second walls.
    With regard to the aforementioned device provided for an oil supply of a set of gears meshing with each other by being rotatable about a common axis of rotation (X), it is recommended that this device comprises: - a reservoir lubricating oil, at least one fixed line for supplying the oil at the level of said assembly and channels for conveying the oil at the level of the rotating gears, said conveyance ducts also being mobile in rotation around of the common axis of rotation (X), - at least one means of ejection of the oil at the end of the fixed supply line, - and the impeller above, with all or part of its characteristics. , the latter being movable in rotation about the common axis of rotation (X) and positioned opposite said ejection means, to receive the oil.
    Also concerned is an epicyclic gear speed reducer as such adapted to rotate about said common axis of rotation (X) and comprising: - the aforementioned set of gears meshing with each other, and - the aforementioned device d oil supply.
    On this reducer, it will be preferred that the internal wall of the wheel considered is farther from the axis of rotation (X) than the first and second side walls of the wheel, so that a lubricant overflow can take place, preferably from one sub-cavity to another rather than outward, parallel to said axis, of the first sub-cavity in the second, and vice versa.
    The benefits are among those already mentioned.
    All or part of the foregoing will furthermore make it possible to produce: a blower module for a turbojet engine comprising a fan shaft driven by an improved speed reducer, as before, and / or a turbomachine (engine) comprising at least less such a speed reducer.
    It is still concerned with the invention a method of operation of the aforementioned oil supply device.
    According to this method, it is intended: - to supply oil to the annular cavity of the impeller via the oil ejection means so that an initial distribution of lubricating oil is effected in the cavity of the impeller by the intermediate of the internal partition, and that one or levels (x) of oil is created (s) accordingly in said first and second sub-cavities, - then supercharge one of said first and second sub-cavities up overflowing the oil over the internal partition, in the other of said first and second sub-cavities of the wheel.
    In some operating situations, the lubricant consumption is higher than at other times. In addition, it may be desirable to avoid splashing the lubricated members by the wheel considered.
    Thus it is also possible, in a given situation, to continue a supercharging of at least one of said first and second sub-cavities until they overflow to the outside of the wheel.
    For an operating efficiency of the wheel lubrication system, it is furthermore recommended that, in order to supply and supercharge the annular cavity of the impeller with oil, this impeller is rotated and a centrifugal pressure is created in its cavity as a function of the speed of rotation of the impeller and the height of the oil column in said cavity. The invention will, if necessary, be better understood and other possible details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which: FIG. 1 shows a double flow turbojet principle, - FIG. 2 shows a speed reduction gearbox of the fan shaft, with epicyclic gear train, equipped with a lubrication system according to one possible embodiment, with details of the routing of the lubricant. to the reducer and in this one; the wheel being without the improvement of the invention, - Figure 3 is a perspective view in axial section, of the above reducer, with the refinement of the invention on the wheel, - Figure 4 is a view of side following the arrow IV, and - Figures 5-7 show three filling states of the wheel above.
    Referring to FIG. 1, a turbomachine 1 can be seen, such as a turbojet, which conventionally comprises, globally and successively along the longitudinal axis X of the turbomachine, a fan S, a low pressure compressor 1a, a high-pressure compressor 1b, a combustion chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1e and an exhaust nozzle 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 are connected by a low pressure shaft 3 and form with it a low pressure body (BP). In the configuration shown which relates to a conventional turbofan, the disk on which the blades of the fan S are mounted is driven by a fan shaft 4, or LP trunnion, which is itself driven directly by the BP shaft 3, through of an epicyclic gear reducer. The longitudinal axis X is the axis of rotation X of the turbomachine (around which the moving blades of the fan S, compressors and turbines in particular rotate). What is here "radial" is relative to this axis X.
    The blades of the blower S are carried by the fan shaft 4 which is connected to the engine structure. This fan shaft is fixed at its downstream end on the planet carrier 13 of the gearbox 10. On its side, the shaft BP 3 is connected to the sun gear 11 of the gearbox 10 by its splines 7.
    FIG. 2 shows this and, more generally, in radial half-section the upper part of the gearbox 10, the lower part being situated symmetrically with respect to the axis of rotation X.
    As illustrated, the reducer 10 is fixed, by means of closure and support flanges 20 which extend from the ring gear of the epicyclic gear train, at one end of a support housing 22, which thus ensures the maintaining the gearbox on the fan shaft 2 and its positioning relative to the LP shaft 3. The enclosure of the gearbox 10 is pressurized in a housing 24. The purpose of the pressurizing casing 24 is to create an enclosure around the gearbox which is at a pressure greater than that which surrounds it, it being put under vacuum by an oil suction pump of the gearbox 10. The housing 24 surrounds the support housing 22.
    The gearbox 10 is enclosed externally in its ring 14, which is not rotatable and which is fixed on the motor structure at the flanges 20. The gearbox engages, on the one hand, on the grooves 7 of the BP 3 shaft through the gear wheels of the sun gear 11 of the epicyclic gear train, and secondly on the fan shaft 4 which is attached to the planet carrier 13 of the same epicyclic gear train. Conventionally the sun gear 11 drives a series of planet gears 12 which are evenly distributed around the circumference of the gearbox. These satellites 12 also turn around the X axis, rolling on the ring 14 which is attached to the structure of the turbomachine by the support housing 22. In the center of each satellite is positioned a satellite axis 16 connected to a planet carrier 13, the satellite freely rotating about this axis with a bearing, as illustrated. The rotation of the satellites about their axis, because of the cooperation of their gears with those of the crown 14, causes the rotation of the planet carrier 13 around the axis X, and consequently that of the fan shaft 4 which He is bound to it. The drive of the fan shaft 4 by the planet carrier 13 is provided by a series of centering fingers 17 which extend axially from the downstream end of the fan shaft 4. The planet carrier 13 extends symmetrically on either side of the gearbox to form an enclosure in which a lubrication function can be implemented. Sockets 19 complete the closure of this enclosure by closing it at the planet axes 16, on each side of the gearbox.
    Arrows show in Figure 2 the path followed by the oil from a specific oil tank, said buffer tank 31, to the gears and bearings to lubricate. The buffer tank 31 is positioned beside the reducer at the top so that oil can flow to the center of the reducer by gravity. This tank 31 is fed by a pipe 30, from a main tank (not shown). The buffer tank 31 the oil opens into at least one injector 32 provided with at least one nozzle 33. The oil comes out of the nozzle in the form of a jet 34, which is formed under the pressure produced jointly by the pressure of the feed pump and by the weight of the oil column located above it. This jet 34 is oriented with a radial component directed towards the outside of the engine and ends in an oil distribution wheel 35.
    The wheel 35 forms an oil retaining cavity of the jet 34. This oil is rotated by the wheel 35 in the bottom of which it is pressurized under the action of the centrifugal force. From the bottom of the wheel start, respectively 430 and 450, a series of pipes for the oil supply of the various bodies to lubricate. These ducts, as represented from FIG. 2, comprise: a first series of ducts 43, in number equal to that of the planet gears 12, which after the impeller penetrate into the internal enclosure of each satellite shaft 16, which is closed by the planet carrier 13, - and a second series of pipes 45, which, like the first, are evenly distributed on the periphery of the gear and, after the wheel 35, pass into the space between two satellite gears 12 consecutive. The oil flowing in the first pipes 43 enters the internal cavity of each satellite axis 16. The centrifugal force drives it into guide channels 44 which traverse these axes radially. These channels 44 open out at the periphery of the planet axes 16, at their bearings supporting the satellites 12 and thus ensure the lubrication of these bearings. The second pipes 45 walk from the bottom of the wheel 35 between the satellites 12 and divide into several channels 45a, 45b which route the oil to the gears formed by, on the one hand, the gears of the satellites 12 and those of the sun gear. 11 and, secondly, the pinions of the satellites 12 and those of the ring 14. Each channel 45a extends axially along the planet pinion, between the planet pinion 12 and the sun gear 11. The pipe 45b, which feeds the gearing between the ring 11 and the satellites 12, projects its oil in the center of the cylinder formed by each satellite.
    Functionally, the oil will flow by gravity from the buffer tank 31 into the injector 32. Under the pressure of the feed pump and the oil column located above the nozzle (s) 33, the oil is ejected and recovered by the spinning wheel 35 in which it spreads. It then passes into the first and second pipes 43 and 45 of each satellite 12. The oil passing through the first pipe 43 enters the internal cavity of the corresponding planet pinion 12 and is then subjected simultaneously to the preceding centrifugal force field and to the field due to the rotation of the planet pinion about its satellite axis 16. It traverses the thickness of the planet gear 12 through the guide channels 44 and lubricates the bearing located between the satellite 12 and its satellite axis 16. The field centrifugal acceleration gives rise to a pressure gradient along the pipe and that this gradient is reflected in a sufficiently high pressure (about 5 bar) at the bearing to be able to feed it. For its part, the oil passing through the second pipe 45 divides between the second supply pipe 45a of the sun gear and the second supply pipe 45b of the satellite-crown gear.
    Line 45a ejects oil across the entire width of the two gears by means of its lubrication ramp. The pipe 45b rises along the pinion satellite to the level of its gear on the ring 14 and ends with a nozzle that lubricates the latter.
    Thus, the lubricating means will be able to ensure the supply of lubricant from a radially inner region of the wheel 35 to the corresponding teeth and bearings.
    The wheel 35 is here a cylindrical cup with a U-shaped radial section, the opening of the U is oriented towards the axis of rotation X. While the (each) injector 32 and its nozzle 33 are fixed, the impeller 35 is movable in rotation about the axis X. The opening of the U-shaped bottom of the impeller 35 is in front of the axis of rotation X and the nozzle, and the edges of the U are oriented in the direction of this axis. The axis of the wheel about which its inner annular cavity 37 extends is thus the axis X. And the cavity 37 is thus open radially towards the axis, X and limited laterally by a first and a second wall 39a, 39b substantially radial to said axis, to receive the lubricant.
    The first and second lubrication supply lines 43,45 of bearings and toothing start from the cavity 37, as illustrated. And, parallel to the axis X, the cavity 37 is split into annular sub-cavities 40a, 40b, here two in number. These first and second sub-cavities are separated by an annular internal partition 38 substantially radial to the X axis and communicate with the first and second pipes, respectively.
    The internal partition has, relative to the respective funds 41 a, 41 b sub-cavities (these funds being limited laterally by the first and second walls), a height h less than those (here identical, H) of the first and second walls 39a, 39b.
    In other words, the radius R 1 along which the free end of each side wall 39a or 39b extends circumferentially is smaller than the radius R2 in which the free end of the partition 38 extends circumferentially.
    Thus, a lubricant overflow will be able to take place in the wheel, parallel to the X axis, of the first sub-cavity in the second, and vice versa (arrow Figure 6).
    Furthermore, a gears speed reducer (11; 12 ...) and an oil supply device of such a set of gears meshing with each other while being rotatable about their axis will be provided. common axis X, said device comprising in particular: - the reservoir 31 of lubricating oil, - the fixed pipe 32 for supplying the oil at the pinions, - the pipes 45, 45a, 45b for routing the oil. oil at the rotating gears, these routing pipes being rotatable about the X axis so as to follow the movement of said gears, the means for ejecting the oil 33 at the end of the pipe 32, - and the wheel 35, movable in rotation about the same axis X and therefore positioned opposite said ejection means 33, to receive the oil.
    It will be noted the interest that this means 33 is oriented with a radial component directed away from the axis X, in order to favorably feed the axially stepped sub-cavities 40a, 40b.
    It will also be noted that modern turbomachines, in particular double-flow turbojets, are conventionally produced by an assembly of modules that may comprise fixed parts and moving parts. A module is defined as a subset of a turbomachine whose interfaces with adjacent modules have sufficiently precise geometric characteristics so that it can be delivered individually. The assembly of such modules makes it possible to constitute a complete engine, while minimizing the balancing and matching operations of the parts in interface.
    Such a module is here feasible, with its fan shaft 4 driven by a speed reducer of the type described.
    With the mobile wheel 35 above, it will further be possible to achieve a flow-pressure balance in the sub-cavities, nozzles and bearings being supplied with pressure and the wheel being rotated, so that a pressure is created centrifuged in the cavity 37 as a function of the rotational speed of the impeller and the height of the column (s) of oil in this cavity.
    In order to ensure the operation of the associated oil supply device, the sub-cavities 40a, 40b of the impeller are supplied with oil via the means 33 so that an initial distribution of lubricating oil takes place in the cavity 37 by means of intermediate of the partition 38, one (or a priori two) level (x) of oil 47a, 47b is created accordingly in said sub-cavities (see Figure 5).
    In a situation requiring it, such as during a climb or take-off, one will even super-feed one of these sub-cavities, such as that indicated in FIG. 6, until the oil is overflowed into the sub-cavity. adjacent cavity, parallel to the axis X, over the partition 38. The pressure necessary to evacuate the oil flow is then greater than the wheel full pressure (situation of Figure 5).
    The flow rate of the overflow sub-cavity then no longer increases. On the other hand, the flow rate of the sub-cavity 40a continues to increase. The distribution between the feed sections is therefore modified. If both sub-cavities are overflowing, the impeller protrudes outward (Figure 7).
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Wheel for dispensing a lubricant in a turbomachine, the wheel having an axis (X) around which extends an annular cavity (37): - open radially to the axis, - laterally limited by a first and a second walls (39a, 39b) substantially radial to said axis, for receiving the lubricant, and from which at least first and second lines (43, 45) supply lubricant to various members to be lubricated, characterized in that parallel to said axis, the annular cavity is divided into at least first and second annular sub-cavities (40a, 40b), which: - are separated by an annular internal partition (38) substantially radial to said axis, and communicate with the first and second pipes (43,45), respectively.
    [2" id="c-fr-0002]
    2. Wheel according to claim 1 wherein, radially to said axis: - the first and second sub-cavities (40a, 40b) each have a bottom (41a, 41b), - and the inner wall (38) has, relative at each bottom, a height less than that (s) of the first and second walls.
    [3" id="c-fr-0003]
    3. Device for supplying oil to a set of pinions (11, 12, 13) meshing with each other by being rotatable about a common axis of rotation (X), said device comprising: - a reservoir (31) for lubricating oil, - at least one fixed oil supply line (32) at said assembly and oil delivery lines at the rotating gears, said lines of also being movable in rotation about the common axis of rotation (X), at least one oil ejection means (33) at the end of the fixed supply line (32), characterized in that it further comprises a wheel (35) according to preceding claims, movable in rotation about said common axis of rotation (X) and positioned opposite said ejection means (33) for receiving the oil.
    [4" id="c-fr-0004]
    4. Epicyclic gear speed reducer adapted to rotate about an axis of rotation (X) and comprising: - a set of pinions (11, 12, 13) meshing with each other while being rotatable around a common axis of rotation (X), and - the oil supply device according to claim 3 or the wheel (35) according to claim 1 or 2.
    [5" id="c-fr-0005]
    5. A speed reducer according to claim 4, wherein the free end of the internal partition (38) is further from the axis of rotation (X) than that (s) the first and second side walls (39a, 39b). the impeller, so that a lubricant overflow can take place, parallel to said axis, the first sub-cavity in the second, and vice versa.
    [6" id="c-fr-0006]
    6. Blower module of a turbojet engine comprising a fan shaft (4) driven by a speed reducer according to claim 4 or 5.
    [7" id="c-fr-0007]
    7. Turbine engine comprising at least one speed reducer according to one of claims 4,5 or a blower module according to claim 6.
    [8" id="c-fr-0008]
    8. Operating method of the oil supply device according to claim 3, wherein: - the annular cavity of the impeller (37) is supplied with oil via the oil ejection means (33) so that initial distribution of lubricating oil takes place in the cavity of the impeller via the internal partition, and one or more levels (s) of oil are created (s) accordingly in said first and second sub-cavities ( 40a, 40b), - a supercharging of one of said first and second sub-cavities intervenes until the oil is overflowed over the internal partition (38), in the other of said first and second sub-cavities of the wheel .
    [9" id="c-fr-0009]
    9. The method of claim 8 wherein a supercharging of at least one of said first and second sub-cavities (40a, 40b) to overflow to the outside of the wheel.
    [10" id="c-fr-0010]
    10. A method according to claim 8 or 9 wherein, for supplying and supercooling oil the annular cavity (37) of the wheel, is rotated in rotation the wheel and creates a centrifugal pressure in the cavity according to the speed of rotation of the wheel (35) and the height of the oil column in said cavity.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3047279B1|2019-06-07|AXIS-DISTRIBUTED DISTRIBUTION WHEEL AND EPICYCLOIDAL TRAIN REDUCER THUS EQUIPPED
    EP2834503B1|2018-04-11|Device for recovering lubricating oil from an epicyclic reduction gear
    EP3286457B1|2020-02-12|Reduction gear having an epicyclic gear train for a turbine engine
    FR2987416A1|2013-08-30|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.
    EP3575562B1|2021-06-30|Power transmission system comprising a device for recovering lubricating oil and turbine engine equipped with such a power transmission system
    FR2987417A1|2013-08-30|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
    FR2987402A1|2013-08-30|Fan module for double-flow turbojet, has reducer carried by support casing that is able to be fixed on support of turbojet such that reducer is able to be mounted on fan module beforehand or during simultaneous assembly of fan module
    EP3283747B1|2020-09-09|Turbomachine with counter rotating propellers upstream of the gas generator
    FR3013388A1|2015-05-22|ENGINE, SUCH AS A TURBOJET, MODULAR WITH SPEED REDUCER
    EP3610176A1|2020-02-19|Assembly comprising a planetary gearset
    EP3822516A1|2021-05-19|Stage impeller for supplying oil to an epicyclic or planetary reduction gear
    WO2018189442A1|2018-10-18|Lubrication for a planetary gearset
    EP3599397A1|2020-01-29|Reducer or differential type device for a turbine engine of an aircraft
    EP3822515A1|2021-05-19|Impeller for a planet carrier of a speed reducer with epicyclic gearset of a turbomachine
    FR3046402A1|2017-07-07|STEAM CHANGE SYSTEM FOR DOUBLET TURBOPROPULSER WITH UPSTREAM CONTRAROTATIVE PROPELLERS
    EP3807507B1|2022-02-16|Device for oil distribution for a rotating planet carrier of a step-down gear of a turbomachine
    EP3726097A1|2020-10-21|Mechanical gear for aircraft turbine engine
    EP3647626A1|2020-05-06|Toothed wheel
    FR3035153A1|2016-10-21|TURBOPROPULSEUR WITH DOUBLET OF CONTRAROTATIVE PROPELLERS HAS BEFORE THE GAS GENERATOR
    WO2021116620A1|2021-06-17|Aeronautical propulsion system having a low leakage flow rate and improved propulsion efficiency
    FR3095243A1|2020-10-23|TURBOMACHINE SPEED REDUCER
    WO2021229167A1|2021-11-18|Aircraft turbomachine comprising a device for lubricating a bearing
    FR3099220A1|2021-01-29|Planetary gear reducer for a turbomachine
    WO2021116622A1|2021-06-17|Aeronautic propulsion system with low leakage rate and improved propulsion efficiency
    FR3082265A1|2019-12-13|ROTATING SATELLITE HOLDER FOR A MECHANICAL REDUCER OF A TURBOMACHINE
    同族专利:
    公开号 | 公开日
    CA3012406A1|2017-08-03|
    RU2731149C2|2020-08-31|
    CN108603414B|2021-05-14|
    EP3408504B1|2020-04-22|
    RU2018127196A|2020-03-02|
    FR3047279B1|2019-06-07|
    US20190032514A1|2019-01-31|
    CN108603414A|2018-09-28|
    US10550723B2|2020-02-04|
    EP3408504A1|2018-12-05|
    WO2017129926A1|2017-08-03|
    RU2018127196A3|2020-03-12|
    JP2019508616A|2019-03-28|
    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|
    US20130225353A1|2012-02-23|2013-08-29|Snecma|Device for lubricating an epicycloidal reduction gear|FR3087863A1|2018-10-30|2020-05-01|Safran Transmission Systems|TOOTHED WHEEL|
    EP3670966A1|2018-12-21|2020-06-24|Safran Transmission Systems|Dispenser of lubricating oil for a mechanical gear of an aircraft turbine engine|
    US10704669B2|2017-12-06|2020-07-07|Safran Transmission Systems|Planetary reduction gear ring gear for a turbine engine|
    EP3822515A1|2019-11-15|2021-05-19|Safran Transmission Systems|Impeller for a planet carrier of a speed reducer with epicyclic gearset of a turbomachine|
    EP3822516A1|2019-11-15|2021-05-19|Safran Transmission Systems|Stage impeller for supplying oil to an epicyclic or planetary reduction gear|
    WO2021094677A1|2019-11-15|2021-05-20|Safran Aircraft Engines|Impeller for a planet carrier of a planetary gear speed reducer of a turbomachine|US3744246A|1972-03-02|1973-07-10|Du Pont|Rotary closed rankine cycle engine with internal lubricating system|
    GB2234035B|1989-07-21|1993-05-12|Rolls Royce Plc|A reduction gear assembly and a gas turbine engine|
    DE4136040C1|1991-11-01|1993-01-07|Mercedes-Benz Aktiengesellschaft, 7000 Stuttgart, De|Epicyclic gear drive with disc clutch or brake - has oil guide flange between planetary gear front ends and drive path, dividing two annular chambers|
    FR2688574B1|1992-03-11|1994-05-06|Snecma|OIL FILTRATION DEVICE.|
    US6223616B1|1999-12-22|2001-05-01|United Technologies Corporation|Star gear system with lubrication circuit and lubrication method therefor|
    RU2347928C1|2007-06-04|2009-02-27|Открытое акционерное общество "Авиадвигатель"|Gas turbine engine single-row blower reduction gear drive|
    US9995174B2|2010-10-12|2018-06-12|United Technologies Corporation|Planetary gear system arrangement with auxiliary oil system|
    CN104169546B|2012-02-23|2017-05-03|斯奈克玛|Device for recovering lubricating oil from an epicyclic reduction gear|FR3066004B1|2017-05-04|2020-09-11|Safran Trans Systems|DECLUTABLE SPEED REDUCER|
    DE102017121739A1|2017-09-19|2019-03-21|Rolls-Royce Deutschland Ltd & Co Kg|Oil distribution system with at least a first rotatable area and a second area|
    DE102018106488A1|2018-03-20|2019-09-26|Rolls-Royce Deutschland Ltd & Co Kg|Gas turbine engine and method of introducing oil into a transmission assembly|
    FR3088977B1|2018-11-23|2020-11-27|Safran Trans Systems|LUBRICATING OIL DISPENSER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    US11203980B2|2020-01-17|2021-12-21|Unison Industries, Llc|Air turbine starter with lubricated bearing assembly|
    法律状态:
    2017-01-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-04| PLSC| Publication of the preliminary search report|Effective date: 20170804 |
    2017-12-21| 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 |
    2018-12-20| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650696A|FR3047279B1|2016-01-28|2016-01-28|AXIS-DISTRIBUTED DISTRIBUTION WHEEL AND EPICYCLOIDAL TRAIN REDUCER THUS EQUIPPED|
    FR1650696|2016-01-28|FR1650696A| FR3047279B1|2016-01-28|2016-01-28|AXIS-DISTRIBUTED DISTRIBUTION WHEEL AND EPICYCLOIDAL TRAIN REDUCER THUS EQUIPPED|
    JP2018539431A| JP2019508616A|2016-01-28|2017-01-27|Axially divided oil distribution wheel and planetary reduction gear provided with such a wheel|
    RU2018127196A| RU2731149C2|2016-01-28|2017-01-27|Oil-distributing ring divided by partition in axial direction, and planetary reduction gear containing such ring|
    EP17706587.7A| EP3408504B1|2016-01-28|2017-01-27|Spinning oil distributor with axial partitioning and planetary reduction gear with such a distributor|
    US16/073,197| US10550723B2|2016-01-28|2017-01-27|Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel|
    CA3012406A| CA3012406A1|2016-01-28|2017-01-27|Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel|
    PCT/FR2017/050200| WO2017129926A1|2016-01-28|2017-01-27|Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel|
    CN201780008988.8A| CN108603414B|2016-01-28|2017-01-27|Axially divided oil distribution wheel, and planetary reduction gear comprising such a wheel|
    [返回顶部]