• 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:
    Turbomachine comprising two rotary shafts (3, 4) and a lubrication unit comprising at least one pump (30) comprising a housing (44) inside which is mounted a rotor (42) which is driven by one of said characterized in that the housing of the pump is rotated by the other of said shafts so that the actuation of the pump depends on the difference in rotational speeds between the shafts.
    公开号:FR3017413A1
    申请号:FR1450973
    申请日:2014-02-07
    公开日:2015-08-14
    发明作者:Benoit Jean Henri Gomanne；Michel Gilbert Roland Brault；Thomas Chauveau；Bellal Waissi
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to a turbomachine equipped with a lubricating group. STATE OF THE ART A turbomachine generally comprises several compressor stages, in particular a low pressure compressor (LP) and a high pressure compressor (HP), which belong to the primary body of the engine. Upstream of the low pressure compressor is disposed a large impeller wheel, or blower, which feeds both the primary flow that passes through the compressors BP and HP and the cold flow, or secondary flow, which is directed directly to a cold flow nozzle, said secondary nozzle. The blower is driven by the rotation shaft of the BP body and generally rotates at the same speed as it. However, it may be advantageous to rotate the fan at a lower rotational speed than that of the motor shaft or BP, especially when it is very large, in order to better adapt aerodynamically. For this we have a gearbox between the LP shaft and a fan shaft, which is carrying the fan. Among the types of reducers used are gear reducers epicyclic train, which have the advantage of offering significant rates of reduction of the rotational speed in small footprints. These reducers are characterized by satellite gears which roll on an outer ring by rotating around the axes of satellites carried by a planet carrier. For reasons of space and weight, it is advantageous to rotate the satellites on their axes by means of hydrodynamic smooth bearings. These bearings require continuous lubrication, otherwise they will deteriorate rapidly, with all the consequences that this may have on the operation of the engine and the safety of the aircraft. They thus pose difficulties in terms of operational safety, and therefore require that precautions be taken against the cases of failure, such as a blocking of the gearbox or autorotation of the blower wheel (commonly called windmilling). Indeed, the bodies HP and BP being decoupled, it is possible that the BP body and the fan rotate while the speed of rotation of the HP body is uncertain. In the present art, the gearbox is lubricated by a lubricating unit which is actuated by an Accessory Gear Box (AGB) which is generally mounted in the nacelle compartment of the propulsion unit. This accessory box comprises means of power take-off on the engine of the turbomachine, via a radial shaft which is coupled to the HP body. In case of windmilling, the HP body does not rotate and the lubrication unit is not active while the gearbox bearings must always be lubricated. There is therefore a need for pumping the oil for lubricating the gearbox, particularly when the engine is stopped. To meet this need, it has already been proposed to equip the turbomachine with a backup pump dedicated to the lubrication of the gearbox, so that the reducer can always be lubricated, even when the HP body is stopped. In this case, it is necessary to add a power take-off on the blower or a power supply circuit to actuate this pump. It can also pose problems of size, mass and life. The introduction of this pump has the disadvantage of complicating the architecture of the engine and goes against the goal of compactness and weight reduction sought.
    [0002] The present invention provides in particular a simple, effective and economical solution to at least some of the problems of the prior art. DESCRIPTION OF THE INVENTION The invention proposes a turbomachine, comprising two rotary shafts and a lubricating unit comprising at least one pump comprising a casing inside which is mounted a rotor which is driven by one of said shafts, characterized in that that the pump casing is rotated by the other of said shafts so that the operation of the pump depends on the difference in rotational speeds between the shafts. The invention thus proposes a new type of integration of a lubrication pump in a turbomachine, the casing and the rotor of which are both rotated at different non-zero speeds, the actuation of the pump resulting from the difference between these speeds. According to one characteristic of the invention, the rotary shafts are coaxial. The casing of the pump is preferably mounted coaxially with the shafts. The pump may be at least partly housed inside one of the trees which are generally tubular. The reducer generally has a ring shape. The latter can be traversed axially by the pump. Thus, the pump is relatively compact and occupies a volume that was available in the prior art. In a preferred embodiment of the invention, the shafts are respectively a drive shaft and a fan shaft, the fan shaft being driven by the drive shaft or BP via a gearbox which is lubricated by the lubrication group. The pump is thus operated with the engine stopped. For example, in case of windmilling, the fan continues to rotate and the difference in speed between the fan and the motor shaft allows to actuate the pump and thus lubricate the gearbox. Furthermore, the power to mechanically drive the pump dedicated to the lubrication of the gearbox is taken closer to the gearbox, which is advantageous for safety reasons (in case of rupture of the LP shaft between the turbine and the gearbox. compressor for example).
    [0003] The lubricating oil requirements of the gear unit in the event of windmilling are generally only around 10% of the nominal oil requirements, which can be achieved with a relatively compact pump and therefore easily implantable in the vicinity of the gearbox. . The pump casing can be coupled to the motor shaft or to the fan shaft, for example by means of splines. This coupling can be direct or through a part of the gear such as its input ring or its output shaft. Indeed, the housing of the pump may comprise splines cooperating with grooves of complementary shape of the motor shaft (or of the gearbox integral gear in rotation with the motor shaft) or the fan shaft (Or the output shaft integral with the rotation of the fan shaft). The pump may be of the pallet or gerotor type. EP-A1-0 736 691 and EP-A1-1 396 639 disclose gerotor-type positive displacement pumps. Preferably, the rotor of the pump is driven by one of said shafts via a ring gear with internal or external teeth. The use of an internally toothed crown allows the motor and fan shafts to rotate in the same direction. This solution thus makes it possible to maintain the direction of rotation of the shafts and to allow a low rotational speed between the rotor and the pump casing (a low rotational speed makes it possible to have a more reliable pump with low sliding speeds. in the case of a gerotor pump). The use of an internally toothed crown makes it possible to change the direction of rotation and to allow a higher speed of rotation between the rotor and the pump casing (with the need for equal lubrication, the high speed makes it possible to have a more compact pump). In conclusion, on the input gear for driving the pump, the technology of it can be adapted to the needs of the engine. Alternatively or additionally, the rotor of the pump may be driven by one of said shafts via a coupling system intended to ensure coupling only within a predetermined speed of rotation of the pump. tree. This makes it possible to couple the rotor of the pump to the drive shaft (such as the LP shaft) only when the speed of rotation of this shaft is low. The pump is thus used as a backup pump for the lubrication of the gearbox in case of windmilling. The pump can however be used in normal operation of the turbomachine, for the continuous lubrication of the gearbox.
    [0004] The rotor of the pump may comprise a shaft which carries at least one internal gerotor gear cooperating with an internally toothed ring which is rotatable in the pump casing. Preferably, the axis of rotation of the rotor shaft of the pump is fixed in the reference frame of the pump housing. The present invention also relates to a torque transmission system for a turbomachine, comprising two rotary shafts coupled together by an epicyclic gear reducer, characterized in that it comprises a lubrication unit comprising at least one pump comprising a casing to the inside which is mounted a rotor which is driven by one of said shafts, the housing of the pump being rotated by the other of said shafts so that the actuation of the pump depends on the difference of rotational speeds between the trees. The pump can be dedicated to gearbox lubrication and can be considered as part of the transmission system. This allows to have together transmission and pump which has a certain advantage of being autonomous with respect to its supply of lubricating oil. 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 schematic half-view of a turbomachine, FIG. 2 is a partial schematic half-view of a turbomachine according to the invention and shows the integration of a lubrication pump of a speed reducer. of rotation of the fan shaft of the turbomachine, - Figure 3 is a very schematic view of a lubrication pump for a turbomachine according to the invention, - Figure 4 is a schematic axial sectional view of a pump. lubricant for a turbomachine according to the invention, and - Figures 5 and 6 are very schematic views of gerotor lubrication pumps and pallets, respectively. DETAILED DESCRIPTION Referring to FIG. 1, a turbomachine 1 of the turbojet type which comprises, in a conventional manner, a fan S, a low-pressure compressor 1a, a high-pressure compressor 1b, a combustion chamber 1c, a high pressure turbine 1 d, a low pressure turbine le and an exhaust nozzle 1 h. The high pressure compressor 1b and the high pressure turbine 1d are connected by a high pressure shaft 2 and form with it a high pressure body (HP). The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3 and form with it a low pressure body (BP). In the configuration shown, which relates to a conventional turbojet engine, without gearbox, the disk on which the blades of the fan S are mounted is driven by a fan shaft 4, or LP journal, which is itself driven directly by the LP shaft. 3. In the case where a gearbox is positioned between the LP shaft 3 and the fan shaft 4, the latter is, in a known manner, an epicyclic gearbox.
    [0005] FIG. 2 shows the positioning that is commonly adopted for the installation of the gearbox 10 in the front part of the turbojet engine. The blades of the fan S are carried by the fan shaft 4 which is connected to the engine structure by means of a ball bearing 5 which transmits the thrust forces, and a roller bearing 6 which allows longitudinal expansion of the fan shaft. The bearings of these two bearings 5, 6 are fixed on one or more support parts 8 of the fan shaft 4, which is attached to the structure of the turbojet engine at a support flange of the fan module 9. L fan shaft 4, which belongs with the support part 8, the fan blades S and the two bearings 5 and 6 to the fan module, is fixed at its downstream end to the planet carrier 11 of the gearbox 10. On its side , the LP shaft 3 is connected to the sun gear 12 of the gearbox 10 by splines 13. The gearbox 10 is fixed, by means of closure and support flanges 14 which extend radially from the crown 15 of the gear epicyclic, at one end of a support housing 16, which thus ensures the retention of the gearbox on the fan shaft 4 and its positioning relative to the BP shaft 3. The gearbox engages, on the one hand , on the splines 13 of the BP shaft 3 through intermediary of the planetary gear pinions 12 of the epicyclic gear, and secondly on the fan shaft 4 which is attached to the planet carrier 11 of the same planetary gear train. Conventionally, the sun gear 12, whose axis of rotation coincides with that X of the turbojet, drives a series of planet gears 17, which are regularly distributed over the circumference of the gearbox. These satellites 17 also turn around the axis X of the turbojet, rolling on the ring 15 which is attached to the structure of the turbojet engine by the support housing 16. In the center of each satellite is positioned a satellite axis 18 connected to the planet carrier 11, the satellite freely rotating about this axis by means of a sliding bearing 19, the safety of operation is the subject of the invention. The rotation of the satellites around their axes 18, because of the cooperation of their gears with those of the ring gear 15, causes the planet carrier 11 to rotate about the axis X, and consequently that of the fan shaft 4 which is connected to it, at a rotation speed which is lower than that of the LP shaft 3. The drive of the fan shaft 4 by the planet carrier 11 is ensured by a series of centering fingers 20, distributed regularly over the circumference of the gear, which extend axially from the downstream end of the fan shaft 4 and which sink into holes in the planet carrier 11. The planet carrier 11 extends symmetrically on either side of the gearbox 10 to close the assembly and form an enclosure, in which is implemented a lubrication function. Sockets 21 complete the closure of this enclosure by closing it at the level of the planet shafts 18 on each side of the gearbox 10. As described above, the lubrication of the gearbox 10 is ensured by a lubrication unit which is actuated by the accessory box of the type AGB turbojet. When the engine is stopped but the fan shaft 4 continues to spin (windmilling), the lubrication of the gear 10 must be ensured to prevent degradation of its bearings 19. A supplementary emergency pump is thus used in the prior art to ensure the lubrication of the gearbox 10 in case of engine stop. The present invention proposes a new technology which facilitates in particular the integration of this type of pump in a turbojet engine. According to the invention, the emergency lubrication pump comprises a casing driven by a first shaft of the turbojet engine and a rotor mounted inside the casing and driven in rotation by a second shaft of the turbojet engine, which rotates at a different speed from the first shaft so that the actuation of the pump results from the difference in speeds between the shafts. FIG. 2 represents an example of integration of a pump 30 of this type in a turbojet engine of the aforementioned type. The pump 30 has an elongate shape, for example substantially cylindrical, its axis of elongation being substantially coincident with the axis X so that the shafts 3, 4 and the pump 30 are substantially coaxial. In the example shown, the pump 30 extends inside the fan shaft 4 and an upstream end portion of the LP shaft 3. The reducer 10 is mounted around this part of the fan. The upstream end of the LP shaft 3 is thus traversed by a portion of the pump 30. The volume occupied by the pump 30 was available in the prior art. This substantially cylindrical volume has for example a length of 480mm and a radius of 60mm in a particular case. It is therefore clearly possible to implement in this volume a lubricating oil pump. A pump whose dimensions would allow its mounting in the aforesaid volume could for example provide an oil flow of 42001 / h at 3500 rpm and 6001 / h at 800 rpm. One of the elements of the rotor and the casing of the pump 30 is coupled by means 32 appropriate to the LP shaft 3 or to a part integral in rotation with this shaft, such as the sun gear 12 of the gearbox 10, and Another element of the pump is coupled by means 34 suitable for the blower shaft 4 or a part integral with this shaft, such as an output shaft of the gearbox which is connected to the planet carrier 11. Coupling means 32, 34 may be fastening means, a pinion gear or sets of splines, for example. Each element (rotor or housing) of the pump may for example comprise splines engaged in complementary splines of a shaft or a drive part. The pump 30 comprises an oil inlet 36 and an oil outlet 38. In the example shown, oil is conveyed to the pump 30 from the downstream of the turbojet engine via a pipe 40 which passes radially. the exhaust casing then axially downstream upstream, the LP shaft and is connected via a rotary joint, of the type OTB (Oil Transfer Bearing) for example, to the oil inlet 36 pump. The oil outlet 38 of the pump could be connected to oil injection means in the gearbox 10 via an OTB type rotary joint. However, in the example shown, the pump casing is integral or recessed into the blower shaft 4. There is therefore no need for OTB to connect the oil outlet of the pump to the planet carrier 11 of the gearbox 10 A single pipe connects the outlet of the pump to the cavities in the planet carrier. The lubricating oil arrives in these cavities which are formed inside each satellite axis. The links between the satellites and the planet carrier 11 are smooth bearings lubricated by the pump. The oil is brought without OTB inside the axes of the satellites. This has the advantage of no longer having OTB. The outside of the satellite axis has grooves that create an oil film. A strong oil pressure is sent to create this carrier oil film, which allows the carrier to rotate on its axis without friction. This oil, given the amount sent, is sufficient to then lubricate and especially evacuate the calories generated by the teeth of the satellites in contact with the teeth of the ring 15 and the central sun gear 12. The oil goes to the teeth through the upstream and downstream faces of the satellites or by radial holes in the satellites. In this embodiment of the epicyclic gear lubrication, the transmission may not have an additional lubrication system because all parts are lubricated. Due to the proximity of the pump to the train and the limited number of kinematic assemblies, the lubrication of the transmission by this system alone appears to be sufficiently reliable. The pump 30 may be a vane or gerotor type pump. These types of pumps are well known to those skilled in the art. Patent applications EP-A1-0 736 691 and EP-A1-1 396 639 describe, for example, gerotor type volumetric pumps. FIG. 3 very schematically represents a pump 30 with pallets or gerotor being able to be integrated in a turbojet. With reference to FIG. 3, the pump 30 comprises a shaft 42 which is centered and guided in rotation in the pump casing 44 so as to that its axis of rotation A is stationary in the reference frame of the housing 44 (the position of the shaft 42 is thus fixed relative to the housing 44). This solution makes it possible to synchronize the movement of the casing and thus of the oil inlet and outlet with respect to the axis of the rotor which ensures the pumping of the oil, which allows a good operation of the pump.
    [0006] The shaft 42 comprises a sprocket 46 engrained with an internal toothing 48 of a ring 50 coupled by means 51 appropriate to one of the shafts, such as the BP shaft 3, and also comprises means 52 for driving at least one gerotor pinion or at least one paddle rotor, which is intended to cooperate with the pump casing 44 or with a ring mounted in this casing, for the pumping of oil, as will be described more in detail in the following.
    [0007] The use of the ring gear 50 with internal teeth 48 allows the shaft 42 of the pump to rotate in the same direction as the LP shaft. Alternatively, in the case where the pinion 46 would be engrained with an external toothing of a ring gear 50 coupled to the LP shaft 3, the shafts 42, 3 of the pump and BP would rotate in opposite directions. Moreover, the use of a pinion 46 is advantageous because the number of its teeth can be determined to optimize the relative speeds of rotation of the shafts 42, 3. The pump casing 44 is coupled by means 54 appropriate to the Another shaft, here the fan shaft 4. Figure 4 shows in more detail a lubrication pump 30 'particularly suitable for being implanted in the aforementioned environment. The elements of the pump 30 'already described in the foregoing are described by the same references. Thus, the pump 30 'of FIG. 4 comprises a shaft 42 which is centered and guided in rotation in the pump casing 44 around an axis A and whose relative position is fixed relative to this casing 44. The shaft 42 comprises a sprocket 46 engrained with the internal toothing 48 of a ring 50 coupled by coupling means 51 to the BP shaft 3.
    [0008] The shaft 42 carries at least one gerotor gear 56 or a vane rotor 57, a gerotor gear 56 being shown in FIG. 5 and a vane rotor 57 being shown in FIG. 6. The gear 56 is fixed to the shaft 42, coaxially with the latter, the pinion 56 comprising for example a notch 56a in which is engaged a pin of the shaft 42. The pinion 56 is rotatable in a ring 58 with internal teeth which is itself movable in rotation in a pump frame 59 (Figure 5). The ring 58 comprises a substantially cylindrical outer surface 60 which cooperates with an inner cylindrical surface of the pump frame 59 which itself comprises an outer cylindrical surface 61 which cooperates with an inner cylindrical surface of the pump casing 44, the reference 62 in FIG. 4 denoting this cylindrical surface of the housing 44, which defines a cavity C for receiving all the parts 56, 58, 59 of Figure 5. The ring 58 and the pump housing 59 comprise radial orifices 63a, 63b passage of oil, the pump housing 59 further comprising a longitudinal bore 64 therethrough. The pump casing 44 carries a straight rod 65 which passes through the bore 64 of the pump casing 59 to immobilize it in rotation about the axis B of the cavity C and for the radial orifices 63b to pass through. pump housing oil 59 are aligned radially with radial oil passage holes 66 of the pump housing 44. It is thus understood that, in the example shown, the pump 30 'is radially supplied and radially out of oil. Alternatively, one could use an axial feed pump and axial oil outlet. Parts 56, 58, 59 would then be interposed between two flanges which include axial openings which would communicate with axial orifices of the pump housing. The embodiment of FIG. 4 shows an eccentric pump where the eccentricity is achieved by shifting the axis A with respect to the axis B which is the axis of the gearbox formed by the pinion 46 and the ring gear 50. This embodiment makes it possible to reduce movement thanks to this small gearbox, which has the advantage of being easily adaptable to the needs. Another embodiment would be possible with the axis A aligned with the axis B of the reducer. The support frame 59 would then be formed by an eccentric. We would have a system that would take less space but without reducing the speed of rotation. The vane rotor 57 of Figure 6 is attached to the shaft 42 coaxially therewith. It comprises radial slots for housing and radial displacement of vanes 67 whose radially outer ends cooperate with the internal cylindrical surface 62 defining the cavity C of the pump frame 59 (FIGS. 4 and 6). In the example shown in Figure 6, the pump is also radially supplied and radial oil outlet.
    [0009] In the case where the pump 30 'comprises two or more gerotor pinions 56, each pinion can be separated from the other pinions by annular flanges (not shown) mounted in the cavity C and disposed on each side of the pinions 56. can then be used to immobilize in rotation all the pump frames 59 and flanges of the pump. The coupling means 54 between the pump housing 44 and the fan shaft 4 here comprise splines. Coupling means 51 of the rotor of the pump with the LP shaft 3 are here of the ossicle type and are intended to ensure a coupling between the ring 50 and the LP shaft 3 when the speed of this shaft is relatively low, this is the case during a windmilling, and do not provide this coupling when this speed is important, in normal operation of the turbojet engine. Of course, the pump 30 'could be intended to lubricate the gearbox 10 during the entire operating life of the turbojet, and not only in case of emergency or emergency type windmiling for example. In this case, the coupling means 51 could comprise splines.
    [0010] References 36 and 38 denote respectively the inlet and the oil outlet of the pump 30 '. As described above, the reference 40 designates an oil line whose upstream end is connected to the oil inlet 36 of the pump 30 '. In the example shown, the ring 50 comprises a shaft portion 70 which is centered and guided in an orifice of the pump casing 44, about the axis B, and which comprises an internal longitudinal passage 72 of oil circulation. . The downstream end of this passage 72 forms the oil inlet 36 of the pump and is connected to the pipe 40, and its upstream end opens into a chamber 74 in which are housed the ring gear 50 and the pinion 46. 68 of the pump casing 41 ensure the routing of the oil from the chamber 74 to the cavity C. The operation of the pump 30 ', because of the difference in rotation speeds between the shafts 3 and 4, forces the passage of oil from the inlet 36 to the oil outlet 38 of the pump 30 '(arrows 69).
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine comprising two rotary shafts (3, 4) and a lubrication unit comprising at least one pump (30) comprising a housing (44) inside which is mounted a rotor (42) which is driven by one of said characterized in that the housing of the pump is rotated by the other of said shafts so that the actuation of the pump depends on the difference in rotational speeds between the shafts.
    [0002]
    2. The turbomachine according to claim 1, characterized in that the rotary shafts (3, 4) are coaxial and the casing (44) of the pump (30) is mounted coaxially with the shafts.
    [0003]
    3. Turbine engine according to claim 1 or 2, characterized in that the shafts are respectively a drive shaft (3) and a fan shaft (4), the fan shaft being driven by the motor shaft via a gearbox (10) which is lubricated by the lubrication unit.
    [0004]
    4. The turbomachine according to claim 3, characterized in that the housing (44) of the pump (30) is coupled to the motor shaft or the fan shaft, for example by means of splines (54).
    [0005]
    5. Turbomachine according to claim 3 or 4, characterized in that the gear (10) has an annular shape and is traversed axially by the pump (30).
    [0006]
    6. Turbomachine according to one of the preceding claims, characterized in that the rotor (42) of the pump (30) is driven by one of said shafts via a ring (50) with internal teeth (48). ) or external and / or a coupling system (51) intended to ensure a coupling only below a predetermined speed of rotation of the shaft.
    [0007]
    7. Turbomachine according to one of the preceding claims, characterized in that the pump (30) is of the pallet or gerotor type.
    [0008]
    8. The turbomachine according to claim 7, characterized in that the rotor of the pump (30 ') comprises a shaft (42) which carries: - at least one gerotor internal gear (56) cooperating with a gear ring (58) internal which is rotatable in the housing (44) of the pump, or - at least one vane rotor (57) cooperating with the housing (44) of the pump.
    [0009]
    9. A turbomachine according to claim 8, characterized in that the axis of rotation of the shaft (42) of the rotor of the pump (30) is fixed in the reference frame of the housing (44) of the pump.
    [0010]
    Torque transmission system for a turbomachine, comprising two rotary shafts (3, 4) coupled together by an epicyclic gearbox, characterized in that it comprises a lubrication unit comprising at least one pump (30) comprising a housing (44) inside which is mounted a rotor (42) which is driven by one of said shafts, the pump housing being rotated by the other of said shafts so that the actuation of the pump depends on the difference in rotational speeds between the shafts.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3102795B1|2017-09-20|Turbine engine provided with a lubrication unit
    CA2751521C|2017-04-04|Lubrication and cooling of a reduction gear with epicyclic gear train
    EP3137741B1|2020-09-09|Aircraft turbine engine with improved drawing of mechanical power
    FR2991421A1|2013-12-06|EPICYCLOIDAL TRAIN REDUCER WITH BEARING-BASED SATELLITE AXES
    FR2987416A1|2013-08-30|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.
    EP2576995B1|2014-08-06|Gearbox in a turbomachine
    EP3495692B1|2020-10-21|Turbine engine speed reduction ring gear with planetary gear
    FR2979121A1|2013-02-22|MECHANICAL TRANSMISSION DEVICE FOR THE ROTATION DRIVE OF THE CONTRAROTATIVE PROPELLERS OF A DOUBLE PROPELLER TURBOPROPULSOR.
    EP3682141A1|2020-07-22|Pivot for a plain bearing and gearset with reduced thermal stress
    EP3137740B1|2018-07-25|Assembly for aircraft turbine engine and method for mounting same
    EP3710727B1|2022-01-26|Turbomachine speed reducer with planetary gear set
    EP3726097A1|2020-10-21|Mechanical gear for aircraft turbine engine
    EP3956555A1|2022-02-23|Speed reducer of a turbomachine
    EP3763971A1|2021-01-13|Cover for oil pipe and mechanical gear for an aircraft turbine engine comprising such a cover
    WO2021245180A1|2021-12-09|High power density radial reducer for turbofan
    FR3109801A1|2021-11-05|ARRANGEMENT FOR AN AIRCRAFT TURBOMACHINE WITH IMPROVED LUBRICATION, THE ARRANGEMENT INCLUDING A TORQUE SHAFT IN ROTATION TO A FOLLOWING ELEMENT, BY SPLINES
    WO2022049342A1|2022-03-10|Assembly for an aircraft turbine engine, comprising means for the axial and radial retention of a fan
    FR3087863A1|2020-05-01|TOOTHED WHEEL
    同族专利:
    公开号 | 公开日
    WO2015118271A1|2015-08-13|
    EP3102795A1|2016-12-14|
    EP3102795B1|2017-09-20|
    RU2016134440A3|2018-09-07|
    US20170009776A1|2017-01-12|
    CA2938385A1|2015-08-13|
    US10458422B2|2019-10-29|
    CN106460557A|2017-02-22|
    CN106460557B|2018-02-23|
    RU2694106C2|2019-07-09|
    RU2016134440A|2018-03-13|
    FR3017413B1|2018-10-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0450353A1|1990-03-15|1991-10-09|Koyo Seiko Co., Ltd.|Power transmission apparatus for four-wheel drive vehicle|
    EP1396639A1|2002-09-03|2004-03-10|Techspace Aero S.A.|Gerotor pump|
    EP2500527A2|2011-03-17|2012-09-19|Rolls-Royce plc|Rotating liquid pumping system|EP3456933A1|2017-09-15|2019-03-20|Safran Aero Boosters SA|Lubricating unit for a turbomachine, turbomachine and manufacturing method for a lubricating unit|
    EP3660276A1|2018-11-30|2020-06-03|Airbus Helicopters|A method and a system for stopping a gas turbine, and a vehicle|SE405634B|1975-11-20|1978-12-18|Stal Laval Turbin Ab|PLANE EXCHANGE LUBRICATION DEVICE|
    DE3422043A1|1984-06-14|1985-12-19|Klöckner-Humboldt-Deutz AG, 5000 Köln|PLANETARY GEARBOX|
    SU1384425A2|1986-10-11|1988-03-30|Минский автомобильный завод|Geared motor for vehicle wheel drive|
    DE69513142T2|1995-04-04|2000-08-17|Techspace Aero Milmort Soc|Internal gear pump with radial feed tubes|
    US7574854B2|2006-01-06|2009-08-18|General Electric Company|Gas turbine engine assembly and methods of assembling same|
    US8215895B2|2008-03-03|2012-07-10|Rolls-Royce Corporation|Vapor phase lubrication system|
    CN104169546B|2012-02-23|2017-05-03|斯奈克玛|Device for recovering lubricating oil from an epicyclic reduction gear|
    WO2015061011A1|2013-10-24|2015-04-30|United Technologies Corporation|Gas turbine lubrication systems|
    US10100673B2|2015-09-04|2018-10-16|Hamilton Sundstrand Corporation|Pump gear|WO2015002680A2|2013-06-06|2015-01-08|United Technologies Corporation|Manifold for gas turbine|
    US10119465B2|2015-06-23|2018-11-06|United Technologies Corporation|Geared turbofan with independent flexible ring gears and oil collectors|
    US10590854B2|2016-01-26|2020-03-17|United Technologies Corporation|Geared gas turbine engine|
    FR3049006B1|2016-03-15|2018-03-16|Safran Aircraft Engines|TURBOREACTOR HAVING A SIMPLIFIED BEARING LUBRICATION GROUP|
    GB201613029D0|2016-07-28|2016-09-14|Rolls Royce Plc|A sun gear drive arrangement|
    US10787930B2|2018-03-23|2020-09-29|Raytheon Technologies Corporation|Windmill lubrication gear train for lubricant system in a geared gas turbine engine|
    CN109578143B|2018-12-10|2020-02-04|中国航发南方工业有限公司|Transmission box oil pumping device|
    US11174916B2|2019-03-21|2021-11-16|Pratt & Whitney Canada Corp.|Aircraft engine reduction gearbox|
    FR3096742B1|2019-05-31|2021-05-14|Safran Aircraft Engines|Aircraft turbomachine comprising a disengageable pump for lubricating a fan reducer.|
    BE1027813B1|2019-12-03|2021-07-01|Safran Aero Boosters|LUBRICATION GROUP MODULAR CASING|
    US11268453B1|2021-03-17|2022-03-08|Pratt & Whitney Canada Corp.|Lubrication system for aircraft engine reduction gearbox|
    法律状态:
    2015-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-03| PLFP| Fee payment|Year of fee payment: 3 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2017-02-07| PLFP| Fee payment|Year of fee payment: 4 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 6 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 8 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450973A|FR3017413B1|2014-02-07|2014-02-07|TURBOMACHINE EQUIPPED WITH A LUBRICATION GROUP.|
    FR1450973|2014-02-07|FR1450973A| FR3017413B1|2014-02-07|2014-02-07|TURBOMACHINE EQUIPPED WITH A LUBRICATION GROUP.|
    US15/116,183| US10458422B2|2014-02-07|2015-02-05|Turbine engine provided with a lubrication unit|
    CN201580007730.7A| CN106460557B|2014-02-07|2015-02-05|It is provided with the turbogenerator of lubrication unit|
    PCT/FR2015/050282| WO2015118271A1|2014-02-07|2015-02-05|Turbine engine provided with a lubrication unit|
    EP15707702.5A| EP3102795B1|2014-02-07|2015-02-05|Turbine engine provided with a lubrication unit|
    CA2938385A| CA2938385A1|2014-02-07|2015-02-05|Turbine engine provided with a lubrication unit|
    RU2016134440A| RU2694106C2|2014-02-07|2015-02-05|Turbomachine and torque transmission system for turbomachine|
    [返回顶部]