• 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 present disclosure relates to a mechanical assembly of two mechanical parts rotating relative to each other to obtain a self-centering fluid bearing; it comprises a first part provided with a cylindrical cavity, a second part (34) comprising at least one cylindrical portion engaged in the cylindrical cavity of the first part, a gap separating the cylindrical portion and the wall of the cylindrical cavity in order to allow a relative rotational movement between the first and second members (34), and a lubricant distribution network (37, 38) configured to supply said gap with a fluid lubricant to form a fluid bearing; a first surface (34s) of the inner surface of the cylindrical cavity of the first part and the outer surface of the cylindrical portion of the second part is provided with at least two lubricant inlet ports (39a, 39b) distant from more than 120 ° from each other about the main axis (F) of the first surface (34s), and the first surface (34s) further has at least one circumferentially extending circumferential groove (40a) in the direction of the relative rotation of the second of said surfaces with respect to the first surface (34s) from the vicinity of a first lubricant inlet port (39a) over at least 100 °.
    公开号:FR3028903A1
    申请号:FR1461242
    申请日:2014-11-20
    公开日:2016-05-27
    发明作者:Serge Rene Morreale
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a mechanical assembly of two mechanical parts rotating relative to one another to obtain a self-centering fluid bearing.
    [0002] Such a mechanical assembly is particularly useful within a transmission member, epicyclic train type for example. In particular, such an invention may find application in the aeronautical field, in aircraft turbojet engines or helicopter turbine engines: it can in particular be applied to reducer turbojet gearboxes. STATE OF THE PRIOR ART The turbojet engines conventionally encountered today in the field of civil aviation are twin-turbojet double-flow turbojets. However, due to the ever-increasing constraints on operating costs, which are closely linked to the cost of fuel, which is currently very high, new turbojet projects with lower specific fuel consumption have been proposed. A promising option is to equip the turbojet with a speed reducer interposed between the low pressure compressor and the blower: in this way, it is possible to increase the speed of rotation of the low pressure body, thus increasing the efficiency. overall turbofan, while reducing the speed of the fan, which increases the diameter of the fan, and thus the rate of dilution of the engine (bypass ratio), retaining an edge velocity blade tip acceptable for to limit the occurrence of generating aerodynamic disturbances including noise. Such a turbofan engine with a reducer is shown in FIG. 1, in section along a vertical plane passing through its main axis A. It comprises, from upstream to downstream, a fan 2, a gearbox 3, a low pressure compressor 4, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7 and a low-pressure turbine 8. In such a turbojet engine 1, the high-pressure turbine 7 35 drives the high-pressure compressor 5 using 9. The low-pressure turbine 8, also called fast turbine, 3028903 2 drives the low-pressure compressor 4 by means of a low-pressure shaft 10. The high-speed turbine 8 also drives the fan 2 by means of the speed reducer 3. In this way, the fan 2 can be driven at a reduced speed, which is aerodynamically favorable, while the low pressure turbine 7 can evolve rapidly. e more important, which is favorable from a thermodynamic point of view. As shown in FIG 2, this reducer 3 may be an epicyclic gear provided with a ring gear 31, a sun gear 32, and planet pinions 33. The planet gears 33 are rotatably mounted on rockets 34 of FIG. a planet carrier 35: each planet pinion 33 thus rotates about the axis F of its respective rocket 34. The bearings 36 between the planet gears 33 and their respective fuses 34 may be smooth, that is to say devoid of a rolling mechanism, and then comprise a film of pressurized oil allowing the lubrication and cooling of the bearings 36. An example of an oil distribution system is given in the French patent application filed under number 13 58581. In a conventional configuration, the ring 31 is fixed to the casing 60, the planet carrier 35 is coupled to the shaft 2a blower, driving the blower 2, and the sun gear 32 is coupled to an end 10a of the low pressure shaft 10. During operation of the turbine engine, due to the rotation of the sun gear 32 and the locking of the ring 31, the planet gears 33 are driven in a race superimposing a rotation about the axis of rotation A of the epicyclic gear train and a rotation about the axis F of their respective fuses 34: s, the rockets 34 and the entire planet carrier 35 are rotated about the axis of rotation A of the epicyclic gear train.
    [0003] It will be understood therefore that the driving force of the planet gears 33, the centrifugal force and, to a lesser extent, the gravitational force cause the planet gears 33 to be off-center with respect to the rockets 34. In particular, because of the force drive, there is a pinching of the oil film behind each rocket 34. 3028903 3 This decentering then has the consequence of increasing the risk that a pinion gear 33 does not come into contact with its rocket 34 and n thus damages the bearing. To remedy this phenomenon, reduction units have been proposed in which a heterogeneous oil distribution is provided within the bearing to provide a greater amount of oil in the areas most exposed to the risk of friction. However, in general, this heterogeneous oil distribution is either a static correction, which does not take into account the true state of the system, ie a dynamic correction but requiring the installation of sensors, actuators and electronic controllers, greatly increasing the complexity and cost of the system. There is therefore a real need for a mechanical assembly which is devoid, at least in part, of the drawbacks inherent in the aforementioned known configurations. PRESENTATION OF THE INVENTION The present disclosure relates to a mechanical assembly comprising a first part provided with a cylindrical cavity, a second part 20 comprising at least one cylindrical portion engaged in the cylindrical cavity of the first part, a gap separating the cylindrical portion and the wall of the cylindrical cavity to allow relative rotational movement between the first and second parts, and a lubricant distribution network configured to supply said gap with a fluid lubricant so as to form a fluid bearing, characterized in that a first surface of the inner surface of the cylindrical cavity of the first component and the outer surface of the cylindrical portion of the second component is provided with at least two lubricant inlet ports at a distance of more than 120 °; one of the other 30 around the main axis of the first surface, and in that the first surface further comprises at least one circumferentially extending circumferential groove, in the direction of the relative rotation of the second of said surfaces with respect to the first surface, from the vicinity of a first lubricant inlet port of at least 100 ° .
    [0004] With this configuration, it is possible to automatically balance the flow of lubricant to be supplied in different areas 3028903 4 of the fluid bearing. Indeed, when the first and second parts are approaching in a given direction, there is a pinching of the fluid bearing in a corresponding zone of the gap: this nip then restricts the passage section of the lubricant at the outlet of the orifice 5 lubricant inlet located in the area of the nip, which then reduces the flow of lubricant escaping from this orifice and increases in return the flow of lubricant escaping from the other orifices. An increased amount of lubricant then travels through the circumferential groove and thereby provides excess lubricant in the area upstream of the nip. Thus, when the second surface rotates, a given point of the latter first passes into the area containing the excess lubricant, taking with it a portion of the lubricant, before reaching the pinching zone: the second surface therefore benefits from Increased lubrication in the nip area, which reduces the risk of the first and second surfaces coming into contact and participating in recentering the second surface relative to the first surface. Naturally, this lubricant dispensing system is dynamic and can automatically balance when the nip is moved. In addition, in case of refocusing of the mechanical assembly, the nip disappears and the gap then has a constant width all around the cylindrical portion of the second part: the passage sections of the lubricant inlet orifices are balanced. then as well as the feed rates of lubricant.
    [0005] Such a mechanical assembly is thus able to maintain and balance a fluid bearing, without a rolling device, between the two parts automatically and dynamically. In particular, it makes it possible to reduce the risk of contact between the two parts, whatever the decentering encountered, and contributes to refocusing the rotating part with respect to its support. This gives a mechanical assembly whose rotating part can rotate smoothly, smoothly and with minimal energy loss. In the present description, the terms "axial", "radial", "tangential", "interior", "exterior" and their derivatives are defined with respect to the main axis of the transmission member; the term "orthoradial" is defined with respect to such a radial axis; 3028903 5 "axial plane" means a plane passing through the main axis of the transmission member and "radial plane" a plane perpendicular to this main axis. In addition, the terms "upstream" and "downstream" are defined relative to the relative direction of rotation of the second surface relative to the first surface. In some embodiments, the first piece rotates around the second piece. In some embodiments, the first piece is a pinion and the second piece is a hub, said pinion rotating about said hub. In other embodiments, the first part is a bearing surface and the second part is a shaft, said shaft rotating within the bearing surface. In some embodiments, the first surface is the outer surface of the cylindrical portion of the second piece and the second surface is the inner surface of the cylindrical cavity of the first piece. This configuration is easier to implement in the context of a pinion rotating around a hub, even if the hub is itself moving in the frame of a larger mechanical member. In some embodiments, the cylindrical portion of the second member includes a lubricant receiving chamber configured to receive lubricant from a source of lubricant and fluidly connected to the lubricant inlet ports. The lubricant receiving chamber and the lubricant supply conduits to the lubricant inlet ports are part of the lubricant distribution network. This chamber allows easy distribution of the lubricant to the various lubricant inlet ports. It can be fed with lubricant using an external distributor, for example the type of dispenser described in the French patent application filed under number 13 58581. In some embodiments, the first surface comprises, in a first transverse plane, first and second diametrically opposed lubricant inlet ports. This ensures effective balancing along a first axis.
    [0006] In some embodiments, the first surface includes, in a second transverse plane distinct from the first transverse plane, third and fourth diametrically opposed lubricant inlet ports. This ensures effective balancing along a second axis. In some embodiments, the first and second lubricant inlets are disposed on a line orthogonal to the line on which the third and fourth lubricant inlets are disposed. With this arrangement, the first and second balancing axes are orthogonal, which facilitates the refocusing of the system whatever the direction of decentering.
    [0007] In some embodiments, a circumferential groove extends circumferentially, in the direction of relative rotation of the second of said surfaces relative to the first surface, from the vicinity of each lubricant inlet port to at least 100 °. . Lubricant is thus conveyed from each lubricant inlet 15 to an area upstream of the next orifice. In some embodiments, the circumferential groove extends in the same transverse plane as the first lubricant inlet port. This facilitates the passage of the lubricant from the orifice to the groove. In some embodiments, the upstream end of the circumferential groove is disjoint from the first lubricant inlet port. The orifice does not open directly into the groove, the passage section at the outlet of the orifice is effectively reduced significantly in the nip, which significantly increases the flow of oil to the other holes.
    [0008] In some embodiments, the upstream end of the circumferential groove is less than 10 °, preferably less than 5 °, from the first lubricant inlet port. This facilitates the passage of the lubricant from the orifice to the groove. In some embodiments, the circumferential groove 30 extends over at least 160 °. This brings lubricant closer to the nip. In some embodiments, the angular distance between the downstream end of the circumferential groove and a second lubricant inlet port is between 5 ° and 20 °, preferably between 10 ° and 15 °. This is a compromise between the advantage of bringing lubricant closer to the pinching zone and that lubricant coming from the second orifice does not penetrate into the circumferential groove of the first orifice to the detriment of its own circumferential groove. In some embodiments, the first surface further has at least one longitudinal groove extending longitudinally from the downstream end of a circumferential groove. This longitudinal groove makes it possible to prime an oil film over a large length of the first surface. In some embodiments, the lubricant is oil. The present disclosure also relates to a transmission member, 10 of the epicyclic gear type, comprising a mechanical assembly according to any one of the preceding claims, wherein the first part of the mechanical assembly is an epicyclic gear planet wheel and the second part is a rocket of an epicyclic gear planet carrier. This gives a transmission member, for example a gearbox, whose satellite gears can benefit from a self-centering sliding bearing. This gives the advantages of the mechanical assembly presented above. At the scale of the transmission member, it increases the energy efficiency of the transmission and reduces vibration and heating. The life of the transmission member 20 is further extended. The present disclosure also relates to a turbomachine comprising a transmission member according to any one of the preceding embodiments. In some embodiments, the turbomachine further comprises a low pressure turbine and a blower, and the epicyclic gear of the transmission member further comprises a sun gear and a ring gear. In some embodiments, the ring gear is fixed to the housing, preferably by means of a flexible connection, the sun gear is coupled with the low pressure turbine, preferably with a flexible link, and the carrier is coupled with the fan, preferably with a stiff connection. The term "flexible connection" means a more flexible connection in flexion than the so-called "stiff" connection. The foregoing and other features and advantages will be apparent from the following detailed description of exemplary embodiments of the proposed mechanical assembly and transmission member. This detailed description refers to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings are schematic and are intended primarily to illustrate the principles of the invention. In these drawings, from one figure (FIG) to the other, identical elements (or element parts) are identified by the same reference signs. In addition, elements (or element parts) belonging to different exemplary embodiments but having an analogous function are indicated in the figures by incremented numerals of 100, 200, etc. FIG 1 is an axial sectional view of an example of a turbomachine gearbox.
    [0009] FIG. 2 is a block diagram of the transmission member. FIG 3 is a perspective view of a rocket. FIG 4A is a sectional view along the plane IVA of FIG 3. FIG 4B is a sectional view along the plane IVB of FIG 3. FIGS. 5A and 5B illustrate the supply of lubricant, in the 20 planes IVA and IVB respectively, when the rocket is centered. FIGS. 6A and 6B illustrate the supply of lubricant, in the IVA and IVB planes respectively, when the fuze is off-center. FIG 7 is a sectional view illustrating a second embodiment.
    [0010] FIGS. 8A and 8B are sectional views in two different planes illustrating a third embodiment. DETAILED DESCRIPTION OF THE EMBODIMENT (S) In order to make the invention more concrete, an exemplary transmission member is described in detail below with reference to the accompanying drawings. It is recalled that the invention is not limited to this example. FIG. 1 represents a turbojet engine with a gearbox as described in an introductory manner, comprising a transmission member 3 according to the invention.
    [0011] This transmission member 3 comprises an epicyclic gear train 30 similar to that which has been described by way of introduction with reference to FIG.
    [0012] In particular, it is noted that in this example, the ring 31 is fixed to the casing 60 by flexible rings 61, the planet carrier 35 is coupled to the fan shaft 2a, driving the fan 2, by a stiff connection. and that the sun gear 32 is flexibly coupled to a fluted end 10a of the low pressure shaft 10. In this example according to the invention, as is best seen in FIGS. 3, 4A and 4B, the rockets 34 planet gears 33 each comprise an oil receiving chamber 37 fluidly connected to the gap 36 forming the sliding bearing by channels 38 passing through the rocket 34 and opening through injection orifices 39a-39d, called arrival of oil. The fuse 34 comprises first and second oil inlet orifices 39a, 39b located diametrically opposite in a first radial plane IVA extending near a first end 15 of the fuse 34; it further comprises third and fourth oil inlet orifices 39c, 39d located diametrically opposite in a second radial plane IVB extending near the second end of the rocket 34. The third and fourth orifices 39c, 39d are arranged 90 ° out of phase with the first and second ports 39a, 39b, i.e. the straight line connecting the third and fourth ports 39c, 39d is orthogonal to the straight line connecting the first and second ports 39a, 39d; orifices 39a, 39b. Thus, the orifices 39a-39d are respectively provided at 0 °, 90 °, 180 ° and 270 ° around the axis F of the rocket 34. Each orifice 39a-39d opens at the surface of the rocket 34. Circumferential grooves 40a-40d are further provided on the surface of the fuze 34. Each circumferential groove 40a-40d extends from the immediate vicinity of an oil inlet port 39a-39d in the same radial plane as this orifice: plus Specifically, the upstream end of a circumferential groove 40a is provided just downstream of the corresponding orifice 39a, less than 5 ° apart from this orifice, without the orifice 39a opening directly into the groove. 40a. In this example, the pinion 33 rotates clockwise around the rocket 34: the upstream end of the circumferential groove 40a is therefore provided just after the orifice 39a in the clockwise direction.
    [0013] The circumferential groove 40a-40d associated with a given orifice 39a-39d extends to an area upstream of the other orifice 39b, 39a, 39d, 39c of the same radial plane IVA, IVB: more precisely its downstream end is provided between 10 and 15 ° further upstream than this other orifice 39b, 39a, 39d, 39c, that is to say in this case between 10 and 15 ° traveled in the counterclockwise direction. Each circumferential groove 40a-40d therefore extends over about 160 °. In addition, each circumferential groove 40a-40d extends at its downstream end by a longitudinal groove 41a-41d: the longitudinal grooves 41a and 41b extend longitudinally from the circumferential grooves 40a and 40b in the direction of the IVB plane without, however, reach; the longitudinal grooves 41c and 41d extend longitudinally from the circumferential grooves 40c and 40d towards the IVA plane without reaching it. The transmission member 3 further comprises an oil distributor 50 for distributing lubricating oil from a supply of oil 64, provided in the stator, to the bearings 36 of the planet gears 33. oil are known: in this example, it may be a distributor similar to that described in the French patent application filed under number 13 58 581. Therefore, this distributor will not be described again in detail. It suffices to know that it comprises a rotating part, driven in rotation by the planet carrier 35, recovering oil from the stator and transferring it to the oil receiving chambers 37 of the rockets 34 with the aid of connecting ducts. The operation of the balancing system of this fluid bearing will now be described with reference to FIGS. 5A, 5B, 6A and 6B. In the case of FIGS. 5A and 5B, the pinion 33 is correctly centered around its rocket 34. No pinch zone therefore appears in the gap 36: the distance separating the surface 34s of the rocket 34 from the inner surface of the central cavity of the pinion 33 is constant all around the rocket 34.
    [0014] Under these conditions, the oil is distributed equitably in the channels 38 so that the oil flow rates 42a-42d injected through the orifices 39a-39d are equal. The oil thus escapes from each orifice 39a-39d and spreads homogeneously in the circumferential grooves 40a-40d and longitudinal 41a-41d so that the centering of the pinion 33 is not affected.
    [0015] FIGS. 6A and 6B represent a case in which the pinion 33 is off-center with respect to the rocket 34: the pinion 33 is placed too far to the right with respect to the rocket 34 so that a pinch zone P is present to the left of the rocket 34. Because of this nip, the exit passage section of the orifice 39a is reduced, which reduces the oil flow 42a escaping at this orifice 39a. Therefore, the flow of oil entering the oil receiving chamber 37 is constant, the oil flow 42b-42d escaping other 39b-39d ports increase. More particularly, the oil flow increases mainly at the orifice located opposite the pinching zone P, here the orifice 39b, insofar as the two other orifices 39c and 39d also undergo a slight reduction of their passage section caused by the decentering of the pinion 33. As a consequence, the oil flow 42b of the orifice 39b increases significantly, a greater amount of oil is provided by the circumferential groove 40b and the longitudinal groove 41b in the zone M located just upstream of the pinching zone P. Thus, an increased quantity of oil is applied to the inner surface of the pinion 33 during its passage in the upstream zone M just before its arrival. in the pinching zone P, which reduces the risk of friction. In addition, the greater amount of oil present in this zone makes it possible to widen the pinching zone P and thus tends to refocus the pinion 33 around the rocket 34. FIG. 7 illustrates a variant embodiment in which the rocket 134 comprises in a given radial plane three oil inlets 139a, 139b and 139c instead of two. These three orifices 139a-139c are located in a balanced manner about the axis A, that is to say every 120 °. Similarly to the previous example, the rocket 134 may include three other oil inlets located in a second radial plane and 60 ° out of phase with the orifices 139a-139c of the first radial plane. Similarly to the first example, circumferential grooves 140a-140c are provided on the surface of the fuse 34 and extend to an area upstream of the next orifice in the clockwise direction. In addition, similarly, each circumferential groove 140a-140c extends at its downstream end by a longitudinal groove 141a-141c.
    [0016] FIG. 8 illustrates a third exemplary embodiment in which the fixed part is a bearing surface 233 within which a shaft 234 rotates. In such an example, the fixed part being the external part, the lubricant distribution network. is planned within the latter. Despite this difference, the lubricant distribution network is quite similar to that of the first example: the inner surface of the cavity of the surface 233 is thus provided with two oil inlet orifices 239a, 239b in a first radial plane and two oil inlet ports 239c, 239d in a second radial plane with a phase shift of 90 °; each of these ports 239a-d is followed by a circumferential groove 240a-d and a longitudinal groove 241a-d. The modes or examples of embodiment described in the present description are given for illustrative and not limiting, a person skilled in the art can easily, in view of this presentation, modify these modes or embodiments, or consider others, all remaining within the scope of the invention. In addition, the various features of these modes or embodiments can be used alone or be combined with each other. When combined, these features may be as described above or differently, the invention not being limited to the specific combinations described herein. In particular, unless otherwise specified, a characteristic described in connection with a mode or example of embodiment may be applied in a similar manner to another embodiment or embodiment. 25
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Mechanical assembly comprising a first part (33) provided with a cylindrical cavity, a second part (34) comprising at least one cylindrical portion engaged in the cylindrical cavity of the first part (33), a gap (36) separating the cylindrical portion and the wall of the cylindrical cavity 10 to allow relative rotational movement between the first (33) and the second piece (34), and a lubricant distribution network (37, 38) configured to supply said gap (36) with a fluid lubricant so as to form a fluid bearing, characterized in that a first surface (34s) of the inner surface of the cylindrical cavity of the first piece and the outer surface of the cylindrical portion of the second piece is provided at least two lubricant inlets (39a, 39b) spaced more than 120 ° apart from each other about the main axis (F) of the first surface (34s), and that the first surface (34s) further has at least one circumferentially extending circumferential groove (40a) in the direction of relative rotation of the second (33) of said surfaces with respect to the first surface (34s) from the vicinity of a first lubricant inlet port (39a) over at least 100 °.
    [0002]
    2. An assembly according to claim 1, wherein the first part is a pinion (33) and the second part is a hub (44), said pinion (33) rotating around said hub (34). 30
    [0003]
    3. An assembly according to claim 1 or 2, wherein the first surface is the outer surface (34s) of the cylindrical portion of the second part (34) and the second surface is the inner surface of the cylindrical cavity of the first part ( 33). 35 3028903 14
    [0004]
    The assembly of claim 3, wherein the cylindrical portion of the second piece (34) comprises a lubricant receiving chamber (37) configured to receive lubricant from a source of lubricant and fluidly connected to the inlet ports lubricant (39a-39d).
    [0005]
    5. An assembly according to any one of claims 1 to 4, wherein the first surface (34s) comprises, in a first transverse plane (IVA), first and second lubricant inlet ports 10 (39a, 39b) diametrically opposed.
    [0006]
    An assembly according to any one of claims 1 to 5, wherein a circumferential groove (40a-40d) extends circumferentially in the direction of relative rotation of the second (33) of said surfaces with respect to the first surface (34s) from the vicinity of each lubricant inlet port (39a-39d) over at least 160 °.
    [0007]
    An assembly according to any one of claims 1 to 6, wherein the angular distance between the downstream end of the circumferential groove (40a) and a second lubricant inlet port (39b) is between 5 ° and 5 °. 20 °, preferably between 10 ° and 15 °.
    [0008]
    An assembly according to any one of claims 1 to 7, wherein the first surface (34s) further has at least one longitudinal groove (41a-41d) extending longitudinally from the downstream end of a circumferential groove. (40a-40d).
    [0009]
    9. Transmission member, of the epicyclic gear type, comprising a mechanical assembly according to any one of the preceding claims, wherein the first part of the mechanical assembly is a planet gear (33) planetary gear and the second piece is a rocket (34) of a planet carrier (35) epicyclic train. 35
    [0010]
    10. Turbomachine comprising a transmission member (30) according to claim 9.
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    同族专利:
    公开号 | 公开日
    RU2701288C2|2019-09-25|
    FR3028903B1|2017-05-05|
    RU2017121290A3|2019-04-19|
    US20170328404A1|2017-11-16|
    CA2968251A1|2016-05-26|
    EP3221603B1|2018-08-22|
    US10161446B2|2018-12-25|
    WO2016079415A1|2016-05-26|
    BR112017010458A2|2017-12-26|
    EP3221603A1|2017-09-27|
    CN107002745B|2019-09-13|
    RU2017121290A|2018-12-20|
    CN107002745A|2017-08-01|
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    FR3095252B1|2019-04-19|2021-05-14|Safran Trans Systems|AIRCRAFT TURBOMACHINE MECHANICAL REDUCER|
    DE102020122584A1|2020-08-28|2022-03-03|Rolls-Royce Deutschland Ltd & Co Kg|Plain bearing for a planetary gear, planetary gear for a gas turbine engine and gas turbine engine|
    法律状态:
    2015-11-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-27| PLSC| Publication of the preliminary search report|Effective date: 20160527 |
    2016-11-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| 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 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461242A|FR3028903B1|2014-11-20|2014-11-20|SELF-CENTER SMOOTH BEARING|FR1461242A| FR3028903B1|2014-11-20|2014-11-20|SELF-CENTER SMOOTH BEARING|
    RU2017121290A| RU2701288C2|2014-11-20|2015-11-17|Self-centering plain bearing|
    US15/528,143| US10161446B2|2014-11-20|2015-11-17|Plain self-centering bearing|
    CN201580063253.6A| CN107002745B|2014-11-20|2015-11-17|The self-centering bearing of plane|
    PCT/FR2015/053101| WO2016079415A1|2014-11-20|2015-11-17|Plain self-centring bearing|
    BR112017010458-0A| BR112017010458B1|2014-11-20|2015-11-17|MECHANICAL ASSEMBLY, TRANSMITTER MEMBER, AND TURBINE ENGINE|
    EP15805587.1A| EP3221603B1|2014-11-20|2015-11-17|Plain self-centring bearing|
    CA2968251A| CA2968251A1|2014-11-20|2015-11-17|Plain self-centring bearing|
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