• 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 cup (35) for supplying oil with at least two oil distribution circuits (43-44, 45-45a-45b) connected to a planet carrier (13) of a gearbox (10). with an epicyclic gear train, said planet carrier (13) being in rotation and the oil coming from an oil ejection means (33) fixed, said cup (35) being arranged to be integral with said planet carrier ( 13) and having a substantially cylindrical shape being open radially inwardly with respect to an axis (X), characterized in that it is divided into a circumferential succession of cups (37a, 37b) separated and each arranged to communicate with one of said oil distribution circuits (43-44, 45-45a-45b). The invention also relates to the gearbox with its feed device and a method of operation in a turbomachine.
    公开号:FR3041054A1
    申请号:FR1558616
    申请日:2015-09-15
    公开日:2017-03-17
    发明作者:Patrice Gedin；Benjamin Feraud
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    Oil supply device for an epicyclic gearbox Technical field:
    The field of the present invention is that of turbomachines and more particularly that of the differential transmission systems in these turbomachines, in particular the planetary gear reducers.
    State of the art :
    Current turbomachines, in particular turbomachines comprising one or more propellers blowing a secondary flow, comprise a transmission system, called a gearbox, for driving this or these propellers at the correct rotation speed from the shaft of the power turbine. primary body of the engine.
    The operation of the gearboxes, in particular on turbomachines with fan blades with a high dilution ratio, requires a particularly high oil flow, of the order of 6000 to 7000 ü hours per hour at takeoff, to ensure lubrication and cooling. of their gears and bearings.
    Among the reducers used, there are the planetary gear reducers which have the advantage of offering significant rates of reduction of the rotational speed in small footprints. On the other hand, they have the disadvantage of having satellite gears which move by rotating about the axis of rotation of the drive shaft of the gearbox. They therefore require devices for transferring the oil from a reservoir and a pump located in a fixed reference to lubrication means which follow the rotational movement of the planet gears around the drive shaft. To solve this problem, commonly used devices include rotating joint systems.
    These systems have the disadvantage of a large size and wear that is incompatible with the lifetimes required for aircraft engines, which impacts the maintenance of said engines. Finally, these reducers are hardly compatible with a flexible assembly of the structure of the turbomachine, recommended for example to overcome a problem of loss or rupture of a blade of the fan propeller, or with a modular type of mounting, to facilitate the assembly of the motor.
    In order to remedy these drawbacks, the applicants have already proposed, in applications WO-A1-2010 / 092263 and FR-A1-2987416, lubrication devices without rotating joints, where an injector causes the oil from the fixed reference circuit to a cup integral with a planet carrier, which is rotated around the injector and confines the recovered oil by centrifugation before directing it to the lubrication means of the gears.
    These devices greatly improve the reliability of the gearbox lubrication system and its maintenance. Furthermore, the technical solution described in application WO-A1-2010 / 092263 makes it possible to adjust the flow rate of oil going to different gears according to their lubrication requirements. For this, the receiving cup is segmented into sections along the axis of rotation and separate nozzles on the injector feed these sections. The oil recovered by each axial section is then directed to a circuit dedicated to a type of gear.
    However, this solution does not make it possible to modulate the distribution of the oil flow between the sections as a function of the speed of the turbomachine. In addition, it is relatively complex with nozzles dedicated to each axial portion on the injector. In addition, the multiplication of the number of sprinklers can raise questions of reliability. The invention aims to overcome these disadvantages, while maintaining or even improving the advantages of the technical solutions proposed in the aforementioned applications.
    The invention relates, for this purpose, to a cup for supplying oil with at least two oil distribution circuits connected to a planet carrier of an epicyclic gearbox, said planet carrier being rotated. and the oil from a fixed oil ejection means, said cup being arranged to be integral with said planet carrier and having a substantially cylindrical shape being open radially inward with respect to an axis, characterized in that it is divided into a circumferential succession of separate cuvettes and each arranged to communicate with one of said oil distribution circuits.
    In other words, circumferential separations are placed between the cuvettes which succeed one another on the circumference of the cup. The fact of separating the cup into a circumferential succession of cups associated with the various oil distribution circuits makes it possible to distribute the flow rates between these circuits by varying the circumferential extension of the cuvettes. This offers an economical alternative to the previous solutions because the cup can adapt to a single injector, which does not need to be designed to distribute the flow rates. This also increases the reliability of the system by simplifying the injector. In addition, there are advantages of reliability by separating the cuvettes between the oil distribution circuits, the malfunction of one not affecting the others.
    Preferably, the cuvettes communicate with said oil distribution circuits by a bottom delimiting them radially outwards.
    Advantageously, said circumferential succession of cuvettes comprises at least two circumferentially alternating series of cuvettes, defined by circumferential extensions of the different cuvettes between each series.
    This design ensures a good rotation of the lubricant using the partition walls of these cuvettes and thus the creation of a centrifugal pressure supplying the oil distribution circuits.
    This design distributes the lubricant received by the cup between the various oil distribution circuits. In particular, it makes it possible to optimize the oil flow as required, at least for an operating speed, and therefore to minimize the mass of oil present in the turbomachine.
    Preferably, said cuvettes are circumferentially separated by circumferential separations and defined axially on both sides by transverse walls of said cup, each of the transverse walls having a substantially circular transverse inner circumferential edge and the circumferential separation between two successive cups comprising an inner radial edge further from the axis than said transverse inner peripheral edges, so as to promote a circumferential overflow of the oil retained by centrifugation in a bowl. On the one hand, this increases the reliability and minimizes the oil consumption to be expected for the case of a malfunction of the oil circuits because, in case of accidental overflow of a bowl, the oil is firstly recovered by the other cuvettes. On the other hand, this allows, by adjusting the radius of edges of the circumferential partition walls, so their height relative to the bottom, to define a second distribution of the oil flow between the circuits, by overflow of a bowl towards another, for a second mode of operation compared to the mode mentioned above.
    Preferably, the cup has an inner U-shaped section in a radial plane. The invention also relates to an oil supply device for a planetary reduction gear comprising a cup as described above, further comprising oil distribution circuits connected to said gearbox planet carrier and communicating with said cups, at the less a fixed line for supplying the oil and a means for ejecting the oil at the end of said at least one supply line, arranged to eject the oil in said cup.
    In particular, such a device adapts to a modular design of the gearbox and / or the turbomachine, because the impeller and / or the planet carrier can be assembled to the oil supply pipes by translation along the axis. The invention also relates to a reducer comprising such a device and a turbomachine comprising it. The invention also relates to a method of supplying oil to such a reducer in a turbomachine, comprising adjusting the flow of oil sent to the cup, by the means for ejecting the oil, so that the oil recovered in a bowl feeds the oil distribution circuit with which the latter communicates and forms, in this bowl, an oil bag maintained between the walls of the latter, for at least a first regime operating the turbomachine.
    Preferably, the method comprises distributing the lubricant between two oil distribution circuits according to their oil flow requirements, for at least a first operating speed of the turbomachine, by a differentiated circumferential extension of the cups. communicating with said two oil distribution circuits. Advantageously, the radially inner edges of the walls of a trough defining an inlet surface in the radial direction, the ratio of the inlet surfaces of the two troughs is proportional to the ratio between the lubricant flow requirements of the two distribution circuits. oil with which they communicate.
    Advantageously, the method comprises adjusting the flow rate of oil sent to the cup, by the means or ejection of the oil, so that the oil recovered in a bowl feeds the distribution circuit d oil with which the latter communicates and forms, for at least one bowl, an oil pocket circumferentially spun to another bowl, for at least a second operating regime of the turbomachine
    Brief description of the drawings:
    The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the following description with reference to the accompanying drawings, in which:
    Figure 1 shows schematically an axial section of a turbomachine using the invention.
    Figure 2 shows a detailed sectional view of an epicyclic gear box equipped with a wheel according to the invention.
    FIG. 3 is an exploded perspective view of the reducer of FIG. 2.
    Figure 4 shows a schematic section of a wheel according to the invention.
    Figures 5a, 5b, 5c show an enlargement of a portion of Figure 4 indicating different mode of operation of the invention.
    Description of an embodiment of the invention
    With reference to FIG. 1, the invention relates, for example, to a turbomachine 1 which comprises, in a conventional manner, a fan propeller S, a low pressure compressor 1a, a high-pressure compressor 1b, a high-pressure turbine 1d, a low pressure turbine and an exhaust nozzle lh. 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 (HP) body. The low pressure compressor la and the low pressure turbine are connected by a low pressure shaft 3 and form with it a low pressure body (BP).
    In a configuration relating to the invention, the fan propeller S is driven by a fan shaft 4 which is coupled to the LP shaft 3 by means of an epicyclic gearbox 10.
    The reducer 10 is positioned in the front part of the turbomachine. A fixed structure schematically comprising, here, an upstream portion 5a and a downstream portion 5b is arranged to form an enclosure El surrounding the gearbox 10. This enclosure E1 is here closed upstream by seals at a bearing 6a allowing the crossing of the fan shaft 4, and downstream by seals at the crossing 6b of the BP shaft 3.
    Referring to Figures 2 and 3, the gearbox is enclosed in a ring 14 which is fixed by means of a support housing 20 to said fixed structure 5a, 5b with flexible means arranged to enable it to follow the possible movements of the fan shaft 4, in some cases of degraded operation for example. These fixing means are known to those skilled in the art and are not detailed here. A brief description can be found for example in FR-A1-2987416.
    The gearbox 10 of the example considered engages on the one hand on the shaft BP3 via splines 7 which drive a sun gear 11, and on the other hand on the fan shaft 4 which is attached. To a planet carrier 13. Conventionally, the sun gear 11, whose axis of rotation X coincides with that of the turbomachine, drives a series of planet gears 12, which are regularly distributed over the circumference of the gearbox 10. number of satellites 12 is generally defined between three and six. The planet gears 12 also rotate about the axis X of the turbomachine, meshing with the internal teeth of the ring gear 14, which is fixedly mounted relative to the turbomachine, via the support housing 20. Each of the satellites 12 rotate freely about a satellite axis 16 connected to the planet carrier 13, by means of a bearing which can be smooth, as shown in FIG. 2, or a rolling element bearing (ball bearings or with rollers).
    The rotation of the satellites 12 around their satellite axis 16, because of the cooperation of their gears with the teeth of the ring gear 14, causes the planet carrier 13 to rotate about the axis X, and consequently that of the planet. fan shaft 4 which is connected thereto, at a rotation speed which is less than that of the LP shaft 3. The drive of the fan shaft 4 by the planet carrier 13 is ensured by a series of fingers 17, distributed regularly over the circumference of the gear 10, which extend axially from the downstream end of the fan shaft 4 and which sink into bores in the planet carrier 13. The planet carrier 13 extends symmetrically on either side of the satellite axes 16 and forms a chamber in which may be implemented a lubrication function of the gears. Closure sockets 19, at the ends of the planet axes 16, make it possible to close this enclosure at the level of the bearings of the satellites 12.
    Figure 2 shows, with Figure 3, the routing of the oil to the reducer 10 and its path inside it. Arrows show in Figure 2 the path followed by the oil since, in this example, a buffer tank 31 connected to the fixed structure of the turbomachine, to the gears and bearings to lubricate. The lubrication device schematically comprises three parts which will be described hereinafter successively, a first part linked to the fixed structure and delivering the oil to the rotating parts of the gearbox 10, a spinning wheel with the planet carrier 13 receiving the oil, and oil dispensing systems supplied with oil by the impeller to convey it to the areas to be lubricated.
    The first part comprises at least one injector 32 whose calibrated end is constricted to form a nozzle 33. The oil is fed to the injector via a delivery pipe 30, from the engine tank (not shown). A buffer tank 31 may be interposed adjacent the reducer 10 on the pipe, preferably in the upper part so that the oil can flow to the center of the reducer by gravity. The nozzle 33 ejects the oil in the form of a jet 34, which is formed under the pressure produced jointly by the feed pump (not shown) and by the weight of the oil column located above it . The nozzle 33 is positioned here radially inside the planet carrier 13 with respect to the axis X and the jet 34 is oriented with a radial component directed towards the outside of the gearbox 10.
    With reference to FIGS. 3 and 4, the impeller for receiving the oil connected to the planet carrier 13 essentially comprises a cylindrical cup, here having a U-shaped radial section, whose U-shaped opening is oriented in the direction of the axis of rotation X. The wheel is arranged on the planet carrier 13 so that the bottom 36 of the U of the cup 35 collects the jet of oil 34 ejected by the nozzle 33.
    According to the invention, the cup 35 of the wheel is here divided into a circumferential succession of cups 37a, 37b separated by walls 38 oriented radially and extending axially between the two side walls 39a, 39b of the U formed by the cup 35. In the example shown, the circumferential separation walls 38 delimit two alternating series of four cuvettes 37a, 37b, with an identical circumferential extension in a series but different from one series to another.
    By centrifugation, when the wheel rotates with the planet carrier 13, the oil received on the bottom 36 of the cup 35 is rotated and pressurized between the bottom 36 and the side walls 39a, 39b of the cup 35. Each bowl 35a, 35b, passing successively in front of the nozzle 33 during the rotation, collects an amount of oil proportional to its circumferential extension. Indeed, the radially inner edges of the walls 39a-39b-38 of a bowl 37a, 37b define an inlet surface of the bowl in the radial direction. This oil remains confined between the walls 38, 39a, 39b of the bowl 37a, 37b as the oil level relative to the bottom 36 remains below the minimum height h of the walls 38 thereof relative to the bottom 36.
    The inner radial edges 40a, 40b of the side walls 39a, 39b are substantially circular. Their radius R1 defines a general depth H of the cup 35 relative to the bottom 36. Preferably, the circumferential partition walls 38 have an internal radial edge 41 located at a distance R2 from the X axis slightly greater than the radius RI of the edges. internal 40a, 40b side walls 39a, 39b. The height h of the circumferential separation walls 38 with respect to the bottom 36 of the cuvettes 37a, 37b is thus slightly less than the height H of the lateral walls 39a, 39b with respect to this same bottom 36. For the invention, this difference in height d can be low, it is sufficient that it allows the oil to flow preferentially above the walls 38 of circumferential separation instead of passing through the inner edges 39a, 39b of the side walls 40a, 40b, if the level of oil rises in a bowl 37a, 37b. Typically, for a turbomachine reducer 10 of the type presented here, a difference in height d of the order of 3 millimeters could suffice.
    Furthermore the bottom 36 of each bowl 37a, 37b has an opening 42a, 42b which communicates with a pipe 43, 45 of an oil distribution circuit installed on the planet carrier 13.
    With reference to FIGS. 2 and 3, the oil distribution circuits are of two types here. A first series of oil distribution circuits corresponds to first pipes 43, which are regularly distributed over the circumference of the gear 10 and in number equal to that of the satellites 12. These pipes 43 start radially from the opening 42a of the bottom of the first series of bowls 37a and penetrate into the inner chamber of each satellite shaft 16, which is closed by the planet carrier 13. The oil flowing in the first pipes 43 enters the internal cavity of each axis of satellite 16 then passes, due to the centrifugal force, in guide channels 44, which pass through these satellite axes 16 being oriented radially. These channels 44 open out at the periphery of the planet axes 16, at the bearings supporting the pinions of the satellites 12 and thus ensure the lubrication of these bearings.
    The second series of oil distribution circuits comprises second pipes 45 which run from the openings 42b of the bottom of the cuvettes 37b of the second series of cuvettes between the satellites 12 and divide into several channels 45a, 45b. The channels 45a, 45b convey the oil to the gears formed by the pinions of the satellites 12 and the sun gear 11, on the one hand, and the pinions of the satellites 12 and the outer ring 14, on the other hand. Each channel 45a extends axially along the pinions of a satellite 12, between them and the sun gear 11, and forms a lubrication ramp over the entire width of the gears. The channel 45b, which supplies the gear between the ring gear 14 and the planet gears 12, projects its oil at the center of the cylinder formed by each satellite 12. As shown, each satellite 12 is in the form of two parallel gears. Their teeth are oriented diagonally with respect to the axis of rotation of the satellite 12, so as to give them a function of grooves in which the oil is driven from the middle of the cylinder to its periphery, to lubricate the gearing over its entire width.
    In this example, the first oil distribution circuits 43-44 that lubricate the bearings supporting the satellites need to carry a larger oil flow than the second 45-45a-45b circuits. For this reason, the circumferential extension of the cuvettes 37a of the first series, which correspond to them, is greater than that of the cuvettes 37b of the second series. Here, a ratio of two-thirds to one-third is sought in the oil flow in nominal operation; the circumferential extension of the two series of cuvettes 37a, 37b substantially takes this ratio. The assembly has been presented here with reference to a four-satellite reducer architecture 12 with two sets of different types of oil distribution circuits 43-44, 45-45a-45b. For other gear architectures, the number of cuvettes per series may be different. Likewise the number of bowl series with similar circumferential extensions may be different, depending on the types of oil distribution circuits. For example, the second oil distribution circuits could be subdivided into two, one dedicated to the gearing of the planet gears 12 with the sun gear 11 and the other dedicated to the gear with the ring gear 14. In this case, case, an alternative embodiment of the oil recovery wheel is possible with three sets of cuvettes of different circumferential extensions.
    Several modes of implementation of the lubrication device will now be described, in relation to the arrangement of the cups 37a, 37b in the cup 35.
    With reference to FIG. 5a, in a first mode of operation corresponding to a nominal speed of the turbomachine, for example a cruising flight for the aircraft on which it is installed, a first oil flow is sent by the jet 33 to the cup 35. This flow rate is adjusted to correspond to the sum of the flow rates used by all the oil distribution circuits, represented in FIGS. 5a-5c by the channels 43, 45 starting from the cup 35.
    Here, as previously presented, the first oil distribution circuits 43 require an oil flow rate higher than that of the second circuits 45 in a ratio of two-thirds to one-third. The cup 35 of the wheel was designed so that the extension of the bowls 37a of the first series is greater than that of the bowls 37b of the second series, substantially in the same ratio. During operation of the gearbox 10, each bowl 37a, 37b forms a buffer tank for the oil entering the oil distribution circuit with which it communicates. Under the influence of the centrifugation pressure and depending on the law connecting the flow rate to the pressure of each of the oil distribution circuits 43, 45, the oil forms in each bowl 37a, 37b a pocket whose level equilibrium at a certain value with respect to the bottom 38. In FIG. 5a, as in the following figures, the level of the oil pocket present in a bowl 37a, 37b is represented by a separate arc 46a, 46b. bottom 36 by a hatched area representing the oil.
    The oil level 46a, 46b is not the same according to the series of cuvettes 37a, 37b. Here the oil level 46b in the cuvettes 37b of the second series is higher than that 46a in the cuvettes 37a of the first series for the same volume of buffer oil stored because of their lower circumferential extension. In the design of the impeller, the walls 38 of circumferential separation of the cuvettes 37a, 37b were made with a height h higher than these oil levels 46a, 46b. In this way, each bowl 37a, 37b performs its function of supplying oil to the corresponding oil distribution circuit 43, 45, independently of the other cuvettes. The oil flow sent by the nozzle 33 is therefore distributed between the oil distribution circuits 43, 45 in the ratio determined according to their needs for this first mode of operation.
    With reference to FIG. 5b, in a second mode of operation corresponding to a second speed of the turbomachine, for example for the take-off of the aircraft, the lubricant needs of the gearbox 10 increase and, moreover, they may be distributed differently. between the oil distribution circuits 43, 45. For this, a second oil flow, higher than the first is sent by the nozzle 33 to the cup 35, so as to meet all the needs of the circuits oil dispenser 43, 45.
    In this case, the oil level 46a, 46b in the cuvettes 37a, 37b rises, in particular that 46b cuvettes 37b of the second series, which already had a higher value than that 46a in the cuvettes 37a of the first series. The nominal value that it should reach here is a function of the law connecting the flow rate to the pressure in each oil distribution circuit 43, 45. Moreover, during the design of the impeller, the walls 38 of circumferential separation between cuvettes 37a, 37b were made with a height h less than said nominal value. In addition, as previously stated, the circumferential separation walls 38 have a height h with respect to the bottom 36 slightly lower than that H of the side walls 39a, 39b. It follows, in this second mode of operation, that the cups 37b of the second series overflow to the bowls 37a of the first series but that the oil remains confined in the cup 35 by the side walls 39a, 39b. One consequence of this phenomenon is that the bowls 37a of the first series are supplied with oil both directly by the injector 33 and by the overflow of the bowls 37b of the second series. The ratio between the flow of oil supplying the first oil distribution circuits 43 and that feeding the second oil distribution circuits 45 therefore increases. Typically, a ratio of three quarters to a quarter is obtained in the example.
    With reference to FIG. 5c, if, for an accidental reason, the flow rate sent by the injector 33 becomes too great compared to that which passes through the oil distribution circuits 43, 45 of the gearbox 10, the oil level 46a, 46b in the cuvettes 37a, 37b reaches the inner radial edges 40a, 40b of the side walls 39a, 39b. The oil then starts to overflow the cup 35 by the side walls 39a, 39b, as in the prior art. The overflow of oil escaping from the cup 35 is then recovered in the enclosure El surrounding the gearbox 10.
    Moreover, the situation presented in FIG. 5b may also correspond to a degraded case where, here, one of the second oil distribution circuits 45 is clogged and does not absorb the nominal oil flow rate. In this case, the corresponding cup 37b overflows into the adjacent cups 37a without any oil escaping over the side walls 39a, 39b. Conversely, in one case, not shown, where one of the oil distribution circuits would not be set correctly and lets more oil pass than necessary, the oil level of the corresponding bowl may drop but this does not affect the operation of the other cuvettes and the lubrication provided by the other circuits. The invention has been presented for a type of turbomachine and for a type of reducer, but the person skilled in the art can easily transpose it, particularly in the case of epicyclic gearboxes driving two counter-rotating propellers, in which the outer ring rotates.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    claims
    1. Cup (35) for supplying oil with at least two oil distribution circuits (43-44, 45-45a-45b) connected to a planet carrier (13) of an epicyclic gearbox (10) , said planet carrier (13) being in rotation and the oil coming from an oil ejection means (33) fixed, said cup (35) being arranged to be integral with said planet carrier (13) and having a substantially cylindrical shape being open radially inward with respect to an axis (X), characterized in that it is divided into a circumferential succession of cups (37a, 37b) separated and each arranged to communicate with the one of said oil distribution circuits (43.44, 45-45a-45b).
    [2" id="c-fr-0002]
    2. Cup (35) according to the preceding claim, wherein said circumferential succession of cuvettes comprises at least two series of cuvettes (37a, 37b) alternately circumferentially, defined by circumferential extensions of the cuvettes different between each series.
    [3" id="c-fr-0003]
    3. Cup (35) according to one of the preceding claims, wherein said bowls (37a, 37b) are circumferentially separated by circumferential partitions (38) and defined axially on both sides by transverse walls (39a, 39b). ) of said cup (35), each of the transverse walls (39a, 39b) having a transverse inner circumferential peripheral edge (40a, 40b) substantially circular and the circumferential separation (38) between two successive cups (37a, 37b) having a radial edge internal (41) further from the axis (X) than said transverse inner peripheral edges (40a, 40b), so as to promote a circumferential overflow of the oil retained by centrifugation in a bowl (37a, 37b).
    [4" id="c-fr-0004]
    4. Cup (35) according to one of the preceding claims, having an inner shape of U-section in a radial plane.
    [5" id="c-fr-0005]
    5. An oil supply device for a gearbox (10 with epicyclic gear comprising a cup (35) according to one of the preceding claims, further comprising oil distribution circuits (43-44, 45-45a-45b). ) connected to said planet carrier (13) of the gearbox (10) and communicating with said cups (37a "37b), at least one fixed pipe (32) for supplying the oil and an oil ejection means (33) at the end of said at least one supply line (32), arranged to eject the oil into said cup (35)
    [6" id="c-fr-0006]
    6. Gearbox comprising a device according to the preceding claim.
    [7" id="c-fr-0007]
    7. A method of supplying oil to a gearbox (10) according to claim 6 in a turbomachine, comprising adjusting the flow of oil to the cup (35), by the or ejection means of the oil (33), so that the oil recovered in a bowl (37a, 37b) feeds the oil distribution circuit (43-44, 45-45a-45b) with which the latter communicates and forms , in this bowl, an oil pocket held between the walls (38-40a-40b) of the latter, for at least a first operating speed of the turbomachine.
    [8" id="c-fr-0008]
    The method of claim 7 comprising distributing the lubricant between two oil distribution circuits (43-44, 45-45a-45b) according to their oil flow requirements, for at least a first time. operating mode of the turbomachine, by a differentiated circumferential extension of the cuvettes (37a, 37b) communicating with said two oil distribution circuits (43-44, 45-45a-45b).
    [9" id="c-fr-0009]
    9. The method of claim 7 or 8, comprising adjusting the flow rate of oil to the cup (35), by the or the oil ejection means (33), so that the oil recovered in a bowl (37A, 37b) feeds the oil distribution circuit (43-44, 45-45a-45b) with which the latter communicates and forms, for at least one bowl (37b), a pocket of oil flowing circumferentially to another bowl (37a), for at least a second operating speed of the turbomachine.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3350482B1|2019-06-05|Oil supply device for an epicyclic reduction gear set
    EP3408504B1|2020-04-22|Spinning oil distributor with axial partitioning and planetary reduction gear with such a distributor
    CA2883999A1|2014-03-14|Speed-reducing unit having an epicyclic gear train, in particular for a turbine engine
    CA2949818C|2018-04-03|Gearbox of aircraft turbine engine
    EP3495692B1|2020-10-21|Turbine engine speed reduction ring gear with planetary gear
    FR3052522A1|2017-12-15|DEVICE FOR RECOVERING LUBRICATING OIL EJECTED BY CENTRIFUGAL EFFECT IN A TURBOMACHINE
    EP3655679A1|2020-05-27|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine
    EP3710727B1|2022-01-26|Turbomachine speed reducer with planetary gear set
    FR3065270A1|2018-10-19|ASSEMBLY COMPRISING AN EPICYCLOIDAL GEAR TRAIN
    EP3822516A1|2021-05-19|Stage impeller for supplying oil to an epicyclic or planetary reduction gear
    WO2019016491A1|2019-01-24|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine
    EP3607228A1|2020-02-12|Impeller for a planet carrier of a planetary gear speed reducer of a turbomachine
    EP3822515A1|2021-05-19|Impeller for a planet carrier of a speed reducer with epicyclic gearset of a turbomachine
    WO2018189442A1|2018-10-18|Lubrication for a planetary gearset
    FR3103240A1|2021-05-21|WHEEL FOR A TURBOMACHINE EPICYCLOIDAL GEAR REDUCER SATELLITE CARRIER
    EP3599397B1|2021-07-07|Reducer or differential type device for a turbine engine of an aircraft
    EP3807507B1|2022-02-16|Device for oil distribution for a rotating planet carrier of a step-down gear of a turbomachine
    EP3610177B1|2021-03-31|Planetary gearset
    FR3082265A1|2019-12-13|ROTATING SATELLITE HOLDER FOR A MECHANICAL REDUCER OF A TURBOMACHINE
    FR3095243A1|2020-10-23|TURBOMACHINE SPEED REDUCER
    FR3109602A1|2021-10-29|Pinion with a lubrication device
    同族专利:
    公开号 | 公开日
    CN108027039A|2018-05-11|
    RU2018109499A3|2019-10-31|
    EP3350482B1|2019-06-05|
    WO2017046481A1|2017-03-23|
    RU2709066C2|2019-12-13|
    CN108027039B|2019-12-24|
    US10458279B2|2019-10-29|
    JP6878414B2|2021-05-26|
    CA2998054A1|2017-03-23|
    FR3041054B1|2017-09-15|
    JP2018535364A|2018-11-29|
    RU2018109499A|2019-10-16|
    US20180258794A1|2018-09-13|
    EP3350482A1|2018-07-25|
    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|
    WO2015019025A1|2013-08-08|2015-02-12|Snecma|Epicyclic reduction gear with fluid transfer pipes, and propeller turbomachine for an aircraft with such a reduction gear|WO2018189476A1|2017-04-14|2018-10-18|Safran Aircraft Engines|Planetary gearset|
    WO2018189457A1|2017-04-14|2018-10-18|Safran Aircraft Engines|Assembly comprising a planetary gearset|
    WO2018189442A1|2017-04-14|2018-10-18|Safran Aircraft Engines|Lubrication for a planetary gearset|
    WO2019007742A1|2017-07-05|2019-01-10|Safran Transmission Systems|Ring gear for an epicyclic or planetary reduction gear of a turbomachine|
    WO2019007915A1|2017-07-05|2019-01-10|Safran Transmission Systems|Ring gear for an epicyclic or planetary reduction gear of a turbomachine|
    WO2019016491A1|2017-07-20|2019-01-24|Safran Transmission Systems|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine|
    WO2019016463A1|2017-07-20|2019-01-24|Safran Transmission Systems|Assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine|
    WO2019097136A1|2017-11-17|2019-05-23|Safran Transmission Systems|Cage for a turbomachine speed reducer with planetary gear set|
    FR3082266A1|2018-06-12|2019-12-13|Safran Aircraft Engines|OIL DISTRIBUTION DEVICE FOR A ROTATING SATELLITE HOLDER OF A MECHANICAL REDUCER OF A TURBOMACHINE|
    FR3082265A1|2018-06-12|2019-12-13|Safran Aircraft Engines|ROTATING SATELLITE HOLDER FOR A MECHANICAL REDUCER OF A TURBOMACHINE|
    EP3599397A1|2018-07-26|2020-01-29|Safran Transmission Systems|Reducer or differential type device for a turbine engine of an aircraft|
    EP3599396A1|2018-07-26|2020-01-29|Safran Transmission Systems|Reducer or differential type device for a turbine engine of an aircraft|
    WO2020021188A1|2018-07-26|2020-01-30|Safran Transmission Systems|Cage for a turbomachine speed reducer with planetary gear set|
    FR3084427A1|2018-07-26|2020-01-31|Safran Transmission Systems|MECHANICAL REDUCER TYPE DEVICE FOR A TURBOMACHINE|
    EP3657041A1|2018-11-23|2020-05-27|Safran Transmission Systems|Planet carrier for a mechanical gear of an aircraft turbine engine|
    EP3657046A1|2018-11-23|2020-05-27|Safran Transmission Systems|Deflector for a reducer of a aircraft's turbomachine|
    EP3657044A1|2018-11-23|2020-05-27|Safran Transmission Systems|Lubrication and cooling core for a mecanical reducer of a aircraft's turbomachine|
    EP3657045A1|2018-11-23|2020-05-27|Safran Transmission Systems|Dispenser of lubricating oil for a mechanical gear of an aircraft turbine engine|
    EP3667126A1|2018-12-13|2020-06-17|Safran Transmission Systems|Satellite carrier for a planetary reducer|
    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|
    FR3092367A1|2019-02-05|2020-08-07|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE|
    EP3696448A1|2019-02-14|2020-08-19|Safran Transmission Systems|Lubrication of a planet carrier for a mechanical gear of a turbine engine, in particular for an aircraft|
    EP3696449A1|2019-02-14|2020-08-19|Safran Transmission Systems|Lubrication of a planet carrier for a mechanical gear of a turbine engine, in particular for an aircraft|
    FR3092884A1|2019-02-20|2020-08-21|Safran Transmission Systems|PLANETARY REDUCER ASSEMBLY FOR A TURBOMACHINE|
    FR3092885A1|2019-02-20|2020-08-21|Safran Transmission Systems|SOLAR FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    EP3705705A1|2019-03-07|2020-09-09|Safran Aircraft Engines|Mechanical gear of an aircraft turbine engine|
    EP3726097A1|2019-04-19|2020-10-21|Safran Transmission Systems|Mechanical gear for aircraft turbine engine|
    EP3726031A1|2019-04-16|2020-10-21|Safran Transmission Systems|Mechanical gear for aircraft turbine engine|
    WO2020245529A1|2019-06-06|2020-12-10|Safran Aircraft Engines|Planetary reduction gear for an aircraft turbine engine|
    EP3763932A1|2019-07-08|2021-01-13|Safran Transmission Systems|Mechanical gear drive for an aircraft turbine engine|
    EP3763971A1|2019-07-08|2021-01-13|Safran Transmission Systems|Cover for oil pipe and mechanical gear for an aircraft turbine engine comprising such a cover|
    EP3767134A1|2019-07-16|2021-01-20|Safran Transmission Systems|Oil collector for a mechanical gear of an aircraft turbine engine|
    FR3099220A1|2019-07-23|2021-01-29|Safran Transmission Systems|Planetary gear reducer for a turbomachine|
    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|
    EP3825580A1|2019-11-22|2021-05-26|Safran Transmission Systems|Supply and recovery of lubricating oil in a mechanical reduction gear of an aircraft turbine engine|
    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|
    EP3922886A1|2020-06-11|2021-12-15|Safran Transmission Systems|Mechanical gear for aircraft turbine engine|
    EP3922831A1|2020-06-11|2021-12-15|Safran Transmission Systems|Mechanical gear for aircraft turbine engine|US4251987A|1979-08-22|1981-02-24|General Electric Company|Differential geared engine|
    US8939864B2|2006-08-15|2015-01-27|United Technologies Corporation|Gas turbine engine lubrication|
    US8215454B2|2006-11-22|2012-07-10|United Technologies Corporation|Lubrication system with tolerance for reduced gravity|
    WO2012026204A1|2010-08-24|2012-03-01|本田技研工業株式会社|Liquid flow path control device for drive device for vehicle|
    US8813469B2|2010-10-12|2014-08-26|United Technologies Corporation|Planetary gear system arrangement with auxiliary oil system|
    US9995174B2|2010-10-12|2018-06-12|United Technologies Corporation|Planetary gear system arrangement with auxiliary oil system|
    CN102829165B|2011-06-18|2014-03-26|南车戚墅堰机车车辆工艺研究所有限公司|Planet gear bearing forced lubricating device|
    CN104169546B|2012-02-23|2017-05-03|斯奈克玛|Device for recovering lubricating oil from an epicyclic reduction gear|
    CN203009798U|2012-11-30|2013-06-19|南车戚墅堰机车车辆工艺研究所有限公司|Outer planetary gear train engagement lubrication system|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|
    CN107725720B|2017-10-24|2020-03-03|浙江好来喜儿童用品有限公司|Differential mechanism of gearbox|
    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|
    US11009116B2|2018-04-24|2021-05-18|Bell Helicopter Textron Inc.|Passive oil system for planetary bearings|
    US11193577B2|2019-10-18|2021-12-07|Deere & Company|Epicyclic gear system having a plurality of fluid directors and method of directing a fluid in an epicyclic gear system|
    EP3964734A1|2020-09-07|2022-03-09|Airbus Helicopters|Device for separating and for collecting two flows of a lubricating liquid, epicyclic gearset, power transmission box and aircraft|
    法律状态:
    2016-09-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-17| PLSC| Search report ready|Effective date: 20170317 |
    2017-05-17| 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 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-11| ST| Notification of lapse|Effective date: 20210506 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1558616A|FR3041054B1|2015-09-15|2015-09-15|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|FR1558616A| FR3041054B1|2015-09-15|2015-09-15|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|
    EP16775281.5A| EP3350482B1|2015-09-15|2016-09-08|Oil supply device for an epicyclic reduction gear set|
    CN201680052853.7A| CN108027039B|2015-09-15|2016-09-08|Oil supply device for epicyclic gear reducer|
    JP2018513378A| JP6878414B2|2015-09-15|2016-09-08|Oil supply device for planetary deceleration gearset|
    PCT/FR2016/052238| WO2017046481A1|2015-09-15|2016-09-08|Oil supply device for an epicyclic reduction gear set|
    CA2998054A| CA2998054A1|2015-09-15|2016-09-08|Oil supply device for an epicyclic reduction gear set|
    RU2018109499A| RU2709066C2|2015-09-15|2016-09-08|Oil supply device for reduction gear with epicycloid transmission|
    US15/759,472| US10458279B2|2015-09-15|2016-09-08|Oil supply device for an epicyclic reduction gear set|
    [返回顶部]