• 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:
    Device for lubricating a rolling bearing (14) of a turbomachine, comprising a rolling bearing mounted between an inner part (21) and an outer part, the bearing comprising rolling elements (17) mounted between an outer ring (16) integral with the outer part and an inner ring (15) integral with the inner part, the inner part having at least one first oil passage (24) for supplying oil to the inner ring of the bearing, characterized in the inner part is a stator part and in that said at least one first conduit is connected to an oil supply source (S) configured to deliver the oil at a pressure sufficient for this oil to be conveyed to 'to the rolling elements of the bearing.
    公开号:FR3022587A1
    申请号:FR1455803
    申请日:2014-06-23
    公开日:2015-12-25
    发明作者:Catherine Pikovsky；Tewfik Boudebiza
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates in particular to a device and a method for lubricating a rolling bearing of a turbomachine. STATE OF THE ART Conventionally, a rolling bearing of a turbomachine is mounted between an inner part and an outer part, the bearing comprising rolling elements mounted between an outer ring integral with the outer part, and an inner ring secured to the internal part. A turbomachine bearing is generally lubricated by means of a nozzle which sprays oil on the bearing or in the vicinity of the bearing. In the present technique, in the case where the bearing is mounted between two rotor parts (the outer ring is secured to the outer rotor part and the inner ring is integral with the inner rotor part), or a rotor part. and a stator piece (the outer ring is integral with the outer stator piece and the inner ring is integral with the inner rotor piece), the bearing is lubricated in operation by oil which is conveyed by the inner ring. up to the landing thanks to the centrifugal forces. In this case, the inner rotor part comprises oil feed oil passages of the inner ring of the bearing, which open at their radially inner ends in an oil retention bath provided by a nozzle. Due to centrifugal forces, the oil flows from the bath to the landing, passing through the ducts of the inner room. However, this technology is not suitable in the case where the internal support part of the inner ring of the bearing is a stator piece, that is to say a stationary piece in operation. Since the stator part is not subjected to centrifugal forces, there is currently no solution for effectively lubricating the bearing by avoiding a direct supply of oil onto the bearing via a nozzle. The present invention provides a simple, effective and economical solution to this problem.
    [0002] SUMMARY OF THE INVENTION The invention proposes a device for lubricating a turbomachine rolling bearing, comprising a rolling bearing mounted between an inner part and an outer part, the bearing comprising rolling elements mounted between a solid outer ring. the outer part and an inner ring secured to the inner part, the inner part having at least a first oil passage for the oil supply of the inner ring of the bearing, characterized in that the inner part is a stator piece and in that said at least one first duct is connected to an oil supply source configured to deliver the oil at a pressure sufficient for this oil to be conveyed to the rolling elements of the bearing. The present invention thus proposes a solution to the aforementioned problem in which the technology of the prior art is adapted to allow lubrication of a bearing mounted between an inner stator part and an outer rotor part. This adaptation consists in connecting the conduits of the stator part to an oil supply source configured to deliver the oil at a pressure sufficient for this oil to be conveyed to the bearing. Unlike the prior art where the oil is delivered to the bearing through the centrifugal forces, the oil is conveyed here to the landing thanks to the pressure at which the source delivers the oil, which is subject to no centrifugal force. Preferably, the inner ring comprises substantially radial oil passage channels whose radially inner ends open into an annular cavity, such as an internal annular cavity of the inner ring.
    [0003] According to a particular embodiment of the invention, an intermediate piece, such as a sheath, is interposed between the inner piece and the inner ring, said intermediate piece comprising at least one second oil passage which is connected to said at least one first conduit. The radially inner end of said at least one second conduit may open into an annular cavity into which the radially outer end of said at least one first conduit opens. The cavity is for example an external annular cavity of the intermediate part. Said at least one first conduit may have a diameter different from that of said at least one second conduit. Advantageously, said at least one first conduit is in fluid communication with a receiving housing at one end of an oil supply pipe from said source. At least one seal may be mounted between the end of the pipe and the housing. Preferably, said at least one first conduit defines an oil passage section less than or equal to that of the pipe. Alternatively or in additional features, said at least one second conduit defines an oil passage section less than or equal to that of the pipe. The passage sections of the first and / or second ducts are thus advantageously configured so that these ducts have a calibrating function. The present invention also relates to a turbomachine, such as a turboprop engine with at least one non-faired propeller, characterized in that it comprises at least one device as described above. The present invention also relates to a method of lubricating a rolling bearing of a turbomachine, this bearing being mounted between an inner part and an outer part, the bearing comprising an outer ring integral with the outer part and an inner ring integral with the part. internal, the inner part having at least a first conduit 3022587 4 oil passage for the oil supply of the inner ring of the bearing, characterized in that, the inner part being immobile, it consists in supplying oil to said the first leads to sufficient pressure for this oil to be transported to the landing.
    [0004] DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a very diagrammatic half-view in axial section of a turbo propeller with two unducted propellers, FIG. 2 is a diagrammatic half-view in axial section of a lubrication device according to the invention, FIGS. 3 and 4 are very schematic views of members of the device 15 of Figure 2 and illustrate alternative embodiments of the invention in section perpendicular to the motor axis, by bringing all the oil passages in the same plane for FIGS. 5 and 6 are partial diagrammatic views in axial section and in perspective of the device of FIG. 2; FIG. 7 is a view corresponding to FIG. an alternative embodiment of the invention, and - Figures 8 to 10 are views corresponding to Figures 3 and 4 and illustrate other embodiments of the invention. DETAILED DESCRIPTION Reference is first made to FIG. 1 which represents a turboprop 1 for an aircraft, this turboprop being equipped with a pair of counter-rotating propulsion propellers, and designated by the expression "open rotor" or "open rotor". unducted fan ". The turboprop engine 1 comprises an upstream propeller 2 and a downstream propeller 3 rotatably mounted, in opposite directions, about the longitudinal axis A. The turboprop 1 comprises a "gas generator" portion G located inside the engine. a fixed cylindrical nacelle 4 carried by the structure of the aircraft (like the rear part of the fuselage of an airplane), and a "propulsion" part P with the pair of propellers 2, 3 arranged in radial parallel planes, perpendicular to the axis A, and constituting a non-ducted fan (open rotor). In this example of a turboprop, this part P extends the gas-generating part G and the nacelle 4. The gas-generating part G of the turboprop 1 usually comprises, from upstream to downstream in the direction of flow, with respect to the axis A, the gas flow F entering the nacelle 4, one or more compressors 5, 5 'according to the architecture of the single-gas generator, several bodies, an annular combustion chamber 6, one or more turbines 7 , 7 'at a distinct pressure according to said architecture, the shaft 8 of one of them drives, through a gear reduction device or reducer planetary gear 9 (designated by the acronym 15 English PGB for Power Gear Box) and contrarotatively, the concentric and coaxial shafts 10 and 11 of the two upstream propellers 2 and downstream 3 aligned along the axis A turboprop. A nozzle 12 usually terminates the turboprop engine 1. In operation, the flow of air F entering the turboprop 1 20 is compressed, then mixed with fuel and burned in the combustion chamber 6. The combustion gases generated then pass in the turbines 7, 7 'for driving in reverse rotation, via the epicyclic reducer 9, the propellers 2, 3 which provide most of the thrust. The combustion gases are expelled through the nozzle 12 thus increasing the thrust of the turboprop 1. As seen in FIG. 1, the radially inner shaft 11 surrounds a cylindrical stator sleeve 13 and is centered and guided in rotation around it through at least one rolling bearing 14 which must be lubricated to ensure its proper operation.
    [0005] As described in the foregoing, the prior art can not be used to lubricate this bearing 14 because the sleeve 13 is stationary in operation and the oil in contact with this sleeve 13 is not subjected to any centrifugal force. FIG. 2 represents an exemplary embodiment of a device for lubricating a rolling bearing according to the invention. In this figure, the references 13 and 14 respectively designate the sleeve and the bearing, as is the case in FIG. 1. The bearing 14 conventionally comprises two rings, respectively internal 15 and external 16, between which rolling elements are mounted. 17, such as balls or rollers, which are here kept apart from each other by an annular cage 18. The inner ring 15 comprises two annular rows, respectively upstream and downstream, of channels 19 for oil passage. These channels 19 are substantially radial, their radially outer ends opening on the raceway of the ring 15 and their radially inner ends opening into an inner annular cavity 20 of the ring 15. In the example shown, the inner ring 15 of the bearing 14 is mounted on a ring support 30 which is itself mounted on the sleeve 13 inside which is mounted an inner part 21. The inner ring 20 15, the ring holder 30, the piece 21, and the sheath 13 are coaxial and integral with each other. They are thus all motionless in operation unlike the outer ring 16 of the bearing 14 which is integral in rotation with the rotor shaft 11 of Figure 1. The ring support 30 comprises an annular row of 25 conduits 31 of passage 'oil. These ducts 31 are substantially radial. Their radially outer ends open into the cavity 20 of the ring 15 and their radially inner ends open into an outer annular cavity 32 of the sleeve 13. The sleeve 13 comprises an annular row of conduits 22 of oil passage. These ducts 22 are substantially radial. Their radially outer ends open into the cavity 32 and their radially inner ends open into an outer annular cavity 23 of the inner part 21. The part 21 comprises at least one conduit 24 for the passage of oil. This duct 24 is substantially radial. Its radially outer end 5 opens into the cavity 23 and its radially inner end opens into an inner housing 25 of the part 21. The ducts 31, 22 and 24 here extend in the same transverse plane P which passes substantially between the channels 19 , halfway between them.
    [0006] The housing 25 of the part 21 comprises an enlarged upstream portion 26 in which is fitted one end of a pipe 27 whose other end is connected, directly or indirectly, to an oil source S. The end of the pipe 27 here carries a sealing O-ring 28 which cooperates with an inner wall of the housing 25 to ensure a sealing connection between the pipe 27 and the part 21. The pipe 27 here has a substantially axial orientation. It thus extends substantially parallel to the aforementioned axis A. Two annular seal seals 29 are mounted between the sleeve 13 and the part 21, respectively upstream and downstream of the cavity 23, to ensure a tight fluid connection between the conduits 22, 24. The source S comprises for the essential a pump and an oil tank (not shown). The source S is intended to supply the device with oil at a sufficient pressure so that, by the mere fact of this pressure, the oil is conveyed from the reservoir to the bearing 14 (and in particular to the elements rolling 17), passing successively through the housing 25, the conduit 24, the cavity 23, the ducts 22, the cavity 20, and the channels 19 (see arrows). In the example shown and as also schematically shown in FIG. 3, the passage section defined by the duct 24 is smaller than that of the ducts 22 (i.e. the cumulative passage sections of these ducts 22). ), as well as that of the 3022587 8 conduits 31, 19, of the pipe 27 and the housing 25. The passage section of the conduit 24 is a calibrating passage section which is intended to calibrate the pressure of the oil supplying the bearing 14. Since the passage section of the ducts 22 and ducts 31, 19 are greater than that of the duct 24, the pressure of the oil will hardly be changed when circulating in the ducts 22 and will therefore be substantially the same in the ducts 22. cavities 20 and 23. The cavities 23 and 20 are further configured to change this pressure as little as possible. FIG. 4 illustrates an embodiment variant in which the ducts 19 provide the calibration function of the oil pressure. The passage section defined by the ducts 19 (cumulative passage sections of these ducts 19) is smaller than that of the duct 24, as well as that of the ducts 31, 22 (cumulative passage sections of these ducts 31, 22), of the duct 27 and the housing 25. The passage section of the ducts 19 is a calibrated passage section which is intended to calibrate the pressure of the oil supplying the bearing 14. The pressure of the oil will therefore be modified while circulating in the ducts. 19 and will be higher in the cavity 20 than in the cavity 23. Other configurations could exist by adding or removing parts between the inner part 21 and the inner ring 15. Indeed, it would be possible to remove the conduits 31 and the cavity 32 if the ring support 30 did not exist, as is schematically represented in FIGS. 7 to 9. Similarly, it would be possible to add parts similar to the ring support 30 comprising similar conduits 25. conduits 31 and a cavity similar to the cavity 32, that is to say with the section of the different non-calibrating elements for the system. Figure 10 illustrates an improvement of the embodiments shown in Figures 8 and 9. The parts 13, 21 and 15 may have an angular keying to have the ducts 24, 22 and 19 placed in the upper part of the engine. Advantageously, the conduit 24 will be placed at 12 o'clock (or 12 o'clock, by analogy with the dial of a clock). The ducts 22 must cover an angular perimeter greater than that of the duct 24 and centered on 12 o'clock. The ducts 19 must cover an angular perimeter greater than that of the ducts 22, centered on 12 o'clock and less than or equal to -90 °, preferably +901. 5
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. Device for lubricating a rolling bearing (14) of a turbomachine, comprising a rolling bearing mounted between an inner part (21) and an outer part (11), the bearing comprising rolling elements (17) mounted between an outer ring (16) secured to the outer part and an inner ring (15) integral with the inner part, the inner part having at least a first conduit (24) for the oil supply of the inner ring of the bearing , characterized in that the inner part is a stator part and in that said at least one first conduit is connected to an oil supply source (S) configured to deliver the oil at a pressure sufficient for this oil is conveyed to the rolling elements of the landing.
    [0002]
    2. Device according to claim 1, wherein the inner ring (15) comprises channels (19) substantially radial oil passage whose radially inner ends open into an annular cavity (20).
    [0003]
    3. Device according to claim 1 or 2, wherein an intermediate piece (13) is interposed between the inner part (21) and the inner ring (15), said intermediate piece comprising at least a second conduit (22) for passage of oil which is connected to said at least one first conduit (24).
    [0004]
    4. Device according to claim 3, wherein the radially inner end of said at least one second conduit (22) opens into an annular cavity (23) into which opens the radially outer end of said at least one first conduit (24).
    [0005]
    5. Device according to claim 3 or 4, wherein said at least one first conduit (24) has a diameter different from that of said at least one second conduit (22).
    [0006]
    6. Device according to one of claims 3 to 5, wherein said at least one first conduit (24) is in fluid communication with a housing (25) for receiving an end of a pipe (27). supplying oil from said source (S).
    [0007]
    Apparatus according to claim 6, wherein said at least one first conduit (24) defines an oil passage section smaller or equal to that of the pipe (27), and / or said at least one second conduit (22). ) defines an oil passage section that is less than or equal to that of the pipe.
    [0008]
    8. Turbomachine, such as a turboprop (1) to at least one propeller (2, 3) unducted, characterized in that it comprises at least one device according to one of the preceding claims. 10
    [0009]
    9. A method of lubricating a rolling bearing (14) of a turbomachine, this bearing being mounted between an inner part (13) and an outer part (11), the bearing comprising an outer ring (16) integral with the outer part. and an inner ring (15) integral with the inner part, the inner part comprising said at least one first oil passage duct (24) for supplying oil to the inner ring of the bearing, characterized in that, the inner part being immobile, it consists in supplying said at least one first conduit with oil at a pressure sufficient for this oil to be conveyed to the bearing. 20
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    同族专利:
    公开号 | 公开日
    CN106460556A|2017-02-22|
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    CA2952506A1|2015-12-30|
    FR3022587B1|2019-03-22|
    CN106460556B|2019-01-01|
    EP3158210A1|2017-04-26|
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    引用文献:
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    法律状态:
    2015-06-11| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-25| PLSC| Search report ready|Effective date: 20151225 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-06-16| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455803|2014-06-23|
    FR1455803A|FR3022587B1|2014-06-23|2014-06-23|DEVICE AND METHOD FOR LUBRICATING A TURBOMACHINE BEARING BEARING|FR1455803A| FR3022587B1|2014-06-23|2014-06-23|DEVICE AND METHOD FOR LUBRICATING A TURBOMACHINE BEARING BEARING|
    EP15732875.8A| EP3158210B1|2014-06-23|2015-06-15|Device and method for lubricating a turbomachine rolling bearing|
    CA2952506A| CA2952506A1|2014-06-23|2015-06-15|Device and method for lubricating a turbomachine rolling bearing|
    CN201580033169.XA| CN106460556B|2014-06-23|2015-06-15|Device and method for being lubricated to turbine rolling bearing|
    US15/320,702| US10174634B2|2014-06-23|2015-06-15|Device and method for lubricating a turbomachine rolling bearing|
    PCT/FR2015/051583| WO2015197943A1|2014-06-23|2015-06-15|Device and method for lubricating a turbomachine rolling bearing|
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