• 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:
    Aircraft turbomachine gearbox (10), comprising a housing (14) defining an oil-lubricated rotating member housing, and at least one tubular sleeve (30) coupled to the rotating members and configured for rotating a shaft (18), said sleeve having splines (26) configured to cooperate with complementary splines (24) of said shaft, characterized in that it further comprises means (42, 44) for recovering lubricating oil of the rotating elements and run-off of recovered oil to the grooves for lubrication.
    公开号:FR3021358A1
    申请号:FR1454679
    申请日:2014-05-23
    公开日:2015-11-27
    发明作者:Jean-Baptiste Etienne Bernard Lepretre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to a turbomachine gearbox. STATE OF THE ART An aircraft turbomachine gearbox, in particular for an airplane or helicopter turbojet or turboprop, may consist of an accessory box (also known as AGB, acronym for the English language). Accessory Gear Box) used to drive turbomachine equipment, such as pumps, electricity generators, etc. The accessory box transmits mechanical power originating from the turbomachine to the equipment via a kinematic chain composed of rotating elements such as pinions or bearings. An aircraft turbomachine gearbox may also consist of a transfer case (also called TGB), for example to kinematically connect an accessory box to a turbine shaft of the aircraft. turbomachine using two transfer shafts optionally forming an angle and interconnected by the transfer box. Such a gearbox, in particular an accessory box and a transfer case, comprises a casing defining a housing housing rotating elements which are lubricated with oil, this oil can also serve to cool the housing. The gearbox comprises at least one tubular sleeve meshing with at least one rotating element and configured to be coupled and to rotate a shaft, for example a transfer shaft or the shaft of a turbine engine equipment. This sleeve comprises a female interlocking portion comprising splines configured to cooperate with splines of a male interlocking portion of the shaft.
    [0002] The splines of the female socket portion of the sleeve and those of the male interlocking portion of the shaft must be lubricated. This lubrication however requires very little oil. It is sufficient to ensure a level of oil in the splines to lubricate the coupling. In the present art, a continuously operating nozzle is generally used to lubricate these flutes. The diameter of the nozzle can not be too small, so that the grooves are often over-lubricated. This results in unnecessary consumption of oil.
    [0003] US-A-5,119,905 illustrates a particular prior art relating to an accessory box in which a nozzle is used intermittently. The jet of oil projected by the nozzle passes through a hole in the sleeve, when the engine stops. This technology has a disadvantage related to the fact that the filling of an annular tank supplying oil splines only occurs when the engine stops. The renewal of the oil assigned to the lubrication of the grooves is therefore carried out only in a particularly discontinuous manner over time. The present invention aims in particular to provide a simple, effective and economical solution to at least some of the aforementioned problems. SUMMARY OF THE INVENTION The invention proposes an aircraft turbomachine gearbox, comprising a casing defining an enclosure for housing rotary elements lubricated with oil, and at least one tubular sleeve coupled to the rotating elements. and configured to rotate a shaft, said sleeve having female splines configured to cooperate with male splines of said shaft, characterized in that it further comprises means for recovering lubricating oil from the rotating and conveying elements by flushing the recovered oil to the flutes for lubrication.
    [0004] The splines are thus lubricated by oil recovered from rotating element lubrication and not by oil dedicated exclusively to the lubrication of the splines. At least a portion of the lubricating oil of the rotating elements is thus recovered and conveyed to the flutes without direct oil supply from a nozzle. This limits the lubricating oil consumption of the gearbox. Moreover, the recovery and the routing of the oil can be carried out continuously during the operation of the engine, which is advantageous over the prior art.
    [0005] Preferably, the recovery and routing means are carried by the housing. Advantageously, the recovery and routing means comprise at least one internal oil collecting wall of said casing, the gearbox being configured to run off oil on said at least one collecting inner wall during operation of the turbine engine. The recovery and routing means may comprise a ducting member which extends at least partially inside said sleeve.
    [0006] The recovery and conveying means may comprise at least one gutter configured to convey the oil flowing over said at least one collecting internal wall to the channeling member. The channeling member and said at least one gutter are preferably carried by or formed with a flange of the housing. The flange may define said at least one collector inner wall and serve as support for a rolling bearing of the sleeve. According to one embodiment of the invention, the flange has a flat portion and a hollow cylindrical portion which extends substantially perpendicularly to the flat portion and which supports the rolling bearing, said channeling member extending inside the the cylindrical portion from the planar portion, and at least one radial opening being formed in the cylindrical portion at the junction with the planar portion so that runoff oil passes through said at least one radial opening to be collected in said at least one gutter.
    [0007] Preferably, the splines extend in a longitudinal annular cavity of the sleeve which is delimited at one longitudinal end by an annular seal configured to cooperate with said shaft, and at an opposite longitudinal end by an annular barrier preferably formed by a seal. a level whose outer periphery defines a maximum oil level in said annular cavity. Advantageously, the annular barrier extends in a transverse plane which is traversed by the recovery and routing means. The present invention also relates to a turbomachine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a gearbox as described above. 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 with reference to the accompanying drawings in which: FIG. 1 is a schematic perspective view of an example of a turbomachine accessories box; - Figure 2 is a very schematic sectional view of an accessory box according to the invention; FIG. 3 is a diagrammatic sectional view of an accessory box according to an exemplary embodiment of the invention, and FIG. 4 is a partial perspective view of a casing flange of the accessory box. of Figure 3.
    [0008] DETAILED DESCRIPTION Reference is first made to FIG. 1 which represents an example of an accessory box 10 for driving equipment 12 of a turbomachine such as an aircraft turbojet or turboprop engine. Such an accessory box is described in particular in document FR-A1-2 941 744. This accessory box 10 is intended to take a mechanical power originating from the turbomachine and to transmit it to the equipment which are pumps, generators electricity, etc. The transmission is performed by a kinematic chain composed of rotating elements geared to each other to form gear lines or accessories. The accessory box 10 comprises a casing 14 defining a housing for housing the rotating elements which comprise, for example, gears and bearings. The kinematic chain is connected to a drive shaft 16 which is a radial shaft of the turbomachine or an intermediate shaft, the chain being also connected to shafts 18 of power take-off equipment. The accessory box 10 is attached to the turbomachine and the equipment is in general itself attached to the accessory box 10.
    [0009] Figure 2 shows an embodiment of the invention. The reference numerals 10, 14 and 18 are also used to designate the accessory box, its housing and the shaft of an equipment, respectively. The example gearbox according to the invention described with reference to Figures 2 to 4 relates to an accessory box, but it is understood that the embodiment described herein is also applicable to a transfer case. The coupling of the shaft 18 to the kinematic chain of the accessory box 10 is achieved by means of splines 24, 26. The shaft 18 comprises a male end portion 28 intended to be engaged in a sleeve 30 constituting a tubular portion of a rotating element or pinion of the accessory box, this end portion 28 having external or male grooves 24 which are preferably straight grooves extending substantially parallel to the axis A of rotation of the shaft 18. The accessory box 10 comprises one or more pinion sleeves 30, each sleeve serving to rotate a shaft 18 of equipment and to transmit the power of the driveline to that shaft. The sleeve 30 comprises a female end portion 32 intended to receive the end portion 28 of the shaft 18, this end portion 32 having internal or female grooves 26 substantially complementary to the grooves 24. rectilinearly extending substantially parallel to the axis A of rotation of the shaft 18. The grooves 24, 26 here extend in an internal longitudinal cavity 34 of the sleeve 30 which is delimited at one end, located on the side of the shaft 18, by an annular seal 36 and at the opposite end by an annular dam 38. The annular seal 36 is carried by the sleeve 30 and is intended to cooperate with the shaft 18 to ensure a seal at the As an alternative, the seal 36 could be carried by the shaft 18 and cooperate with the sleeve 30. The annular barrier 38 is preferably formed by a level annular seal. The cavity 34 makes it possible to store a determined volume of oil in which the grooves 24, 26 are immersed. The level seal (dam 38) is configured to define a maximum level of oil 40 in the cavity 34, the surplus oil being then discharged from the cavity 34 flowing through the level seal. The sleeve 30 is rotatable and rotated by at least one rotating element of the accessory box, for example another pinion. For this, the sleeve may comprise at its outer periphery a toothed wheel adapted to be engaged with the toothed wheel of another pinion. The sleeve 30 and its gear wheel constitute a pinion.
    [0010] The rotating elements of the accessory box 10 are lubricated by oil which can be brought into the inner chamber of the housing 14 by nozzles for example. According to the invention, the accessory box 10 comprises means for recovering the lubricating oil from the rotating elements and the trickling of the recovered oil to the flutes 24, 26. These means here comprise a wall or a flange 42 of the housing 14 on which flows at least a portion of the oil which was used to lubricate the rotating elements. This flange 42, which serves as a sealing cover for the housing, comprises or carries at least one inner wall 48 for collecting lubricating oil from the rotating elements and a channeling member 44 which has an elongated shape and extends in part. inside the sleeve 30 so that its free longitudinal end is located closest to the cavity 34 of the sleeve 30 and that the oil can be routed and simply poured by runoff and gravity to this cavity 34 (arrows 46). The level seal (annular barrier 38) thus extends in a transverse plane P which is traversed by the channeling member 44. Advantageously, the run-off by the member 44 is provided sufficient to compensate for any minor oil leakage. at the joint 36. Figures 3 and 4 show a more concrete embodiment of the accessory box 10 according to the invention and in particular of its flange 42 carrying the oil recovery and conveying means.
    [0011] The flange 42 is here formed in one piece and comprises in particular a flat portion on the inner face of which is formed at least one recess defining a collector inner wall 48 as described above. The flange 42 also comprises a hollow cylindrical portion 54 which extends substantially perpendicular to the flat portion and which supports a rolling bearing 52 of the sleeve. The internal collecting wall 48 is substantially perpendicular to the axis of this cylindrical portion 54. The rolling bearing 52 comprises an outer ring mounted in a free end portion of the cylindrical portion 54 and an inner ring mounted around a portion end of the sleeve 30, opposite the grooves 26. The sleeve 50 is thus partly engaged by an end portion in the cylindrical portion 54 of the flange 42. This end portion is however at axial distance from the portion plane flange 42 to allow an oil flow between them (arrow 46), as will be described in the following.
    [0012] The cylindrical portion 54 is here formed by a boss of the flange which comprises external radial extensions in which are provided threaded orifices 49 for screwing screws for fixing the outer ring of the bearing 52 to the flange 42. The cylindrical portion 54 comprises an opening radial 56 at the junction with the wall 48 of the flat portion of the flange 42. Oil can flow on the wall 48 to the inside of the cylindrical portion 54, through the opening 56. The flange 42 further comprises, radially inside the cylindrical portion 54, the aforesaid channel member 44 and two gutters 50 which serve to collect the oil passing through the radial opening 56 and to route it to the longitudinal end of the member 44 connected to the flat portion of the flange 42. Each gutter 50 has a substantially U-shaped cross section and extends substantially radially relative to the axis of the cylindrical portion 54, sensitive from the axis to the cylindrical portion 54. The gutters 50 together form a V with an angle of the order of 120-160 °. The gutters 50 are located substantially in the axial space extending between the flat portion of the flange 42 and the end of the sleeve 30 guided by the bearing 52.
    [0013] The duct member 44 has a substantially U-shaped section and extends partially inside the sleeve 30 to be able to discharge the recovered oil into the inner cavity 34 of the sleeve. The cavity 34 is delimited by the level seal (dam 38) and by the aforementioned seal (seal 36 in Figure 2) which is here carried by the shaft and which is not shown. This seal is intended to cooperate with an inner cylindrical surface of the sleeve 30. The end portion of the sleeve 30 comprising the splines 26 is guided by another bearing 60 and is further surrounded by a dynamic seal 62 , the bearing 60 and the seal 62 being mounted in a cylindrical wall 64 of the casing 14.
    [0014] The sleeve 30 is further secured to a wheel 66 with external teeth so as to form a pinion. The flange 42 of Figures 3 and 4 can be made of casting for example, or by machining. As is schematically represented by the arrow 46 in FIG. 3, the oil which is projected or discharges during operation on the collecting wall 48 flows to the opening 56 and penetrates into the cylindrical wall 54 to be collected in the gutters 50 which conveys this oil to the channeling member 44. This oil then flows into the internal cavity 34 of the sleeve 30 for the lubrication of the grooves 26 and those of the corresponding equipment shaft. Since the channeling member 44 passes through the transverse plane in which the level seal extends (annular barrier 38), the oil which flows by gravitation at the free end of this channeling member necessarily falls into the cavity. internal 34 of the sleeve 30.
    [0015] It is thus ensured a continuous renewal of the oil contained in the internal cavity 34. Indeed, during operation of the turbomachine, the entire annular space of the internal cavity 34 fills with oil under the effect of the force centrifugal due to the rotation of the sleeve 30. The oil flowing into the sleeve 30 from the duct member 44 mixes with the oil of the internal cavity 34. The excess oil in the internal cavity 34 overflows by above the level gasket 38 to return to the housing, or even to participate in the lubrication of the bearing 52. The duct member 44 is advantageously arranged to extend substantially horizontally once the accessory box installed in the turbomachine, or to form a slight slope relative to the horizontal in most flight attitudes so as to promote the flow of oil by gravitation. The flow of the oil into the internal cavity 34 is not interrupted, except in exceptional flight attitudes and short duration. It may be provided for example that the opening of the sleeve 30 on the side of the gasket 38 is oriented towards the front of the aircraft, so that during flight the flow of the oil into the internal cavity 34 from the channeling member 44 can be interrupted only during a possible flight phase in steep downward inclination (especially in case of acceleration dive).
    [0016] Moreover, the level gasket 38 advantageously has a radial height sufficient for stopping the turbomachine, that is to say when the rotating elements of the accessory box are no longer in rotation, a part of the grooves of the sleeve and the barbote shaft in the oil retained in the bottom of the internal cavity 34. At restart of the turbomachine, all the grooves are found quickly lubricated by the retained oil.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Aircraft turbomachine gearbox (10), comprising a housing (14) defining an oil-lubricated rotating member housing, and at least one tubular sleeve (30) coupled to the rotating members and configured for rotating a shaft (18), said sleeve having splines (26) configured to cooperate with complementary splines (24) of said shaft, characterized in that it further comprises means (42, 44, 48, 50 ) of lubricating oil recovery of the rotating elements and run-off of recovered oil to the grooves for lubrication.
    [0002]
    The gearbox (10) of claim 1, wherein said recovery and routing means (42,44,48,50) is carried by said housing (14).
    [0003]
    The gearbox (10) according to claim 1 or 2, wherein said recovery and conveying means (42, 44, 48, 50) comprises at least one inner oil collecting wall (48) of said crankcase (14), the gearbox being configured to run off oil on said at least one collector inner wall during operation of the turbomachine.
    [0004]
    The gearbox (10) according to one of the preceding claims, wherein said recovery and conveying means (42, 44, 48, 50) comprises a channeling member (44) which extends at least part inside said sleeve (30).
    [0005]
    The gearbox (10) according to claim 4, in dependence on claim 3, wherein said recovery and routing means (42, 44, 48, 50) comprise at least one gutter (50) configured to routing the runoff oil on said at least one collecting inner wall (48) to the channeling member (44).
    [0006]
    The gearbox (10) according to claim 5, wherein said channeling member (44) and said at least one gutter (50) are carried by or formed with a flange (42) of the housing, said flange defining said less a collector inner wall (48) and serving as a support for a rolling bearing (52) of the sleeve (30).
    [0007]
    Gearbox (10) according to claim 6, wherein the flange (42) has a flat portion and a hollow cylindrical portion (54) which extends substantially perpendicular to the flat portion and which supports the rolling bearing. (52), said channeling member (44) extending within the cylindrical portion from the planar portion, and at least one radial opening (56) being formed in the cylindrical portion at the junction with the planar portion thereof; said runoff oil passes through said at least one radial opening to be collected in said at least one gutter (50).
    [0008]
    Gearbox (10) according to one of the preceding claims, wherein said splines (26) extend in a longitudinal annular cavity (34) of the sleeve (30) which is delimited at one longitudinal end by a joint ring (36) configured to cooperate with said shaft (18), and at an opposite longitudinal end by an annular dam (38) preferably formed by a level seal whose outer periphery defines a maximum oil level in said annular cavity (34).
    [0009]
    The gearbox (10) according to claim 8, wherein said annular barrier (38) extends in a transverse plane (P) which is traversed by the recovery and conveying means (42, 44, 48). , 50).
    [0010]
    10. Aircraft turbomachine, such as a turbojet engine or a turboprop aircraft or helicopter, characterized in that it comprises at least one gearbox (10) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    CN106460668B|2018-05-22|
    FR3021358B1|2018-07-20|
    WO2015177487A1|2015-11-26|
    EP3146183A1|2017-03-29|
    EP3146183B1|2018-02-14|
    CA2949818C|2018-04-03|
    CA2949818A1|2015-11-26|
    CN106460668A|2017-02-22|
    RU2651004C1|2018-04-18|
    US9790804B2|2017-10-17|
    US20170138214A1|2017-05-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    法律状态:
    2015-05-12| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-27| PLSC| Publication of the preliminary search report|Effective date: 20151127 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-05-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| 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 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454679A|FR3021358B1|2014-05-23|2014-05-23|AIRCRAFT TURBINE ENGINE GEAR BOX|
    FR1454679|2014-05-23|FR1454679A| FR3021358B1|2014-05-23|2014-05-23|AIRCRAFT TURBINE ENGINE GEAR BOX|
    RU2016148457A| RU2651004C1|2014-05-23|2015-05-22|Drive box for aviation gas turbine engine|
    PCT/FR2015/051374| WO2015177487A1|2014-05-23|2015-05-22|Gearbox of aircraft turbine engine|
    CA2949818A| CA2949818C|2014-05-23|2015-05-22|Gearbox of aircraft turbine engine|
    CN201580026913.3A| CN106460668B|2014-05-23|2015-05-22|The gear-box of aircraft turbine engine|
    EP15732796.6A| EP3146183B1|2014-05-23|2015-05-22|Gearbox of aircraft turbine engine|
    US15/313,036| US9790804B2|2014-05-23|2015-05-22|Gearbox of aircraft turbine engine|
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