• 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:
    A lubricant nozzle (172) for a turbomachine epicyclic gearbox, said nozzle having a generally elongate shape and having a longitudinal axis body B, said body having a longitudinal internal cavity (174) which is in fluid communication with a lubricant inlet located at a longitudinal end (172a) of said body and with lubricant outlet openings (176) which are formed in an annular wall of said body and which extend substantially radially with respect to said axis B, characterized in that said orifices are formed in at least one boss (176a) of said body, which protrudes radially outwardly on said wall and has an angular extent (β) about said axis less than or equal to 180 °.
    公开号:FR3069301A1
    申请号:FR1761760
    申请日:2017-12-07
    公开日:2019-01-25
    发明作者:Michel Pierre Di Giovanni Jean-Charles；Claude Michel Dombek Alexis；Pierre Marcel Morelli Boris
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    Lubricant nozzle for a planetary gearbox of a turbomachine
    Field of the invention
    The present invention relates to the field of planetary gearbox speed reducers for a turbomachine in particular of an aircraft, as well as elements which make up a reducer of this type such as sprinklers, a planet carrier, a spinning wheel, etc.
    State of the art
    The state of the art includes in particular the documents W0-A1-2010 / 092263, FR-A1 -2 987 416 and FR-A1 -3 041 054.
    Current turbomachinery, in particular turbomachinery comprising one or more propellers blowing a secondary flow, comprises a transmission system, called a reduction gear, to drive this or these propellers at the right speed of rotation from the shaft of the power turbine of the primary body of the engine.
    The operation of the reducers, in particular on turbomachines with a fan propeller with a high dilution rate, requires a particularly high oil flow rate, of the order of 6000 to 7000 liters per hour on takeoff, to ensure lubrication and cooling. of their gables and bearings.
    Among the reducers used, there are planetary and (planetary) planetary reducers which have the advantage of offering significant rates of reduction of the speed of rotation in reduced dimensions.
    Such a reducer comprises a planetary or central pinion, called a sun gear, an outer ring and planet gears, called satellites, which are engaged with the sun and with the ring, the support of one of these three components having to be blocked. in rotation for the operation of the gear train.
    When the planet carrier is fixed in rotation, the sun and the crown are driving and driven, respectively, or vice versa. The reducer is then of the “planetary” type.
    In the opposite case, the most common of a planetary gearbox, the outer ring is fixed in rotation and the sun and the planet carrier are leading and driven.
    However, this type of reducer has drawbacks. One of the issues is related to the proper lubrication of the teeth of the satellites and the sun. The oil must pass from a fixed part of the engine to a rotating part at high speed. Once in the rotating part, the oil is no longer under pressure. At high speed, it is difficult to reach the sun with the oil because of the centrifugation effect. It is therefore essential to bring the nozzle closer to the sun. Another problem is related to the complexity of the assembly.
    The present invention provides an improvement which provides a simple, effective and economical solution to at least some of these problems.
    Statement of the invention
    The invention relates to a lubricant nozzle for a speed reducer with an epicyclic train of a turbomachine, said nozzle having a generally elongated shape and comprising a body with a longitudinal axis B, said body comprising a longitudinal internal cavity which is in fluid communication with a lubricant inlet located at a longitudinal end of said body and with lubricant outlet orifices which are formed in an annular wall of said body and which extend substantially radially with respect to said axis B, characterized in that said orifices are formed in at minus a boss of said body, which projects radially outward on said wall and which has an angular extent around said axis less than or equal to 180 °.
    In contrast to the prior art, a nozzle thus has more material at the level of the oil projection orifices. This addition of material has the form of a boss at the top of which open the orifices. The orifices thus have a radial dimension greater than that of the orifices of a nozzle according to the prior art, and have their radially external ends which are at a greater radius and can be brought closer to the teeth to be lubricated. The oil passing through the orifices is guided over a longer distance and is projected as close as possible to the teeth, which significantly optimizes the lubrication of the gear unit.
    The sprinkler according to the invention may include one or more of the following characteristics, taken in isolation from each other, or in combination with each other:
    - The at least one boss has in cross section a generally rectangular, triangular or trapezoidal shape; the shape of the boss is thus optimized to convey the oil as close as possible to the teeth to be lubricated;
    - The trapezium boss comprises a small base which is defined by the radially external end of the boss on which said orifices open, and sides which form between them an angle between 0 and 90 °; the size of the bosses is thus reduced;
    - the small base has a convex curved shape, which can be obtained by turning for example;
    - Said at least one boss comprises at least one row of orifices per element to be lubricated; it comprises for example two rows each comprising several orifices; alternatively, the orifices could have another arrangement;
    - Said body comprises at least two bosses at a longitudinal distance from each other; the bosses are located in privileged areas of the nozzle body in order to optimize the lubrication of the teeth while optimizing the size and mass of the nozzle; in our case, the privileged zone is defined by the number and the width of the helices of the teeth; an extension of material can be added on these bosses; this allows us after manufacture to remove material to obtain an almost identical mass on each nozzle in order to limit the unbalance of the reducer;
    the nozzle comprises a fixing lug formed in one piece with the body, said lug extending substantially in a plane perpendicular to said axis and comprising an orifice for the passage of a fixing means of the screw-nut or screw type. threaded hole; the body of the nozzle thus has a relatively simple shape, which limits its manufacturing cost;
    - Said body comprises at least one external annular groove for housing an annular seal.
    According to another aspect, the invention relates to an assembly comprising a planet carrier and nozzles as defined above, for a speed reducer with a planetary gear train of a turbomachine, said planet carrier comprising a cage defining an internal mounting space of a central solar of axis X of rotation and of an annular row of satellites arranged around the axis X and meshed with said solar, said solar comprising means of coupling to a first shaft, said cage comprising two walls substantially parallel annulars centered on said axis X and a cylindrical wall connecting said annular walls to their outer periphery, a first of said annular walls being connected to a substantially cylindrical body comprising means for coupling to a second shaft, and a second of said annular walls having passages for mounting the nozzles, by displacement of each nozzle in a direct ion substantially parallel to said axis X, characterized in that said nozzles are configured to be mounted on said second wall from inside the cage.
    Advantageously, the nozzles each comprise a first longitudinal portion comprising said bosses and said plate and a second threaded portion, the first portion of each nozzle being configured to extend inside said cage and the threaded portion being intended to receive a nut intended to bear on an external face of said cage.
    The threaded portion of each nozzle can pass on the one hand a housing of an impeller added and fixed on said second wall of the cage, and on the other hand a housing of this second wall.
    According to another aspect, the invention relates to an aircraft turbomachine, characterized in that it comprises at least one nozzle or an assembly as described above.
    According to another aspect, the invention relates to a planet carrier and a method of assembling a planet carrier as described above, in which it comprises the steps of:
    - fixing the sprinklers to the cage, mounting the satellites and the sun in the cage, and fixing the impeller to the cage.
    Other variants of the mounting process are of course possible.
    Brief description of the figures
    Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:
    FIG. 1 is a schematic view in axial section of a turbomachine using the invention,
    FIG. 2 is a view in axial section of a planetary gear reducer,
    FIG. 3 is a schematic perspective view of an embodiment of a planetary gear reducer,
    FIG. 4 is a schematic perspective view of the reducer of FIG. 3, its impeller being dissociated from the rest of the reducer,
    FIG. 5 is a schematic perspective view of an assembly comprising a impeller, sprinklers and a cage of the reducer of FIG. 3, this cage being partially shown,
    FIG. 6 is another perspective view of the impeller of FIG. 3,
    FIG. 7 is a partial schematic view in axial section and on a larger scale of a detail of the reducer of FIG. 3, and in particular of a nozzle of the reducer, and
    - Figure 8 is a partial schematic view in cross section and on a larger scale of a detail of the reducer of Figure 3, and in particular of a nozzle of the reducer.
    Detailed description of an embodiment of the invention
    FIG. 1 shows a turbomachine 1 which conventionally comprises a fan propeller S, a low pressure compressor 1a, a high pressure compressor 1b, an annular combustion chamber 1c, a high pressure turbine 1d, a low pressure turbine 1e and an exhaust nozzle 1h. 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).
    The fan propeller S is driven by a fan shaft 4 which is coupled to the LP shaft 3 by means of a planetary gear reducer 10 shown here diagrammatically.
    The reduction gear 10 is positioned in the front part of the turbomachine. A fixed structure comprising schematically, here, an upstream part 5a and a downstream part 5b is arranged so as to form an enclosure E1 surrounding the reducer 10. This enclosure E1 is here closed upstream by seals at a level allowing the crossing of the fan shaft 4, and downstream by seals at the crossing of the LP shaft 3.
    With reference to FIG. 2, the reduction gear 10 comprises a ring 14 which is fixed by means of a ring holder (not shown) to the fixed structure 5a, 5b with flexible means arranged to enable it to follow the movements fans of the fan shaft 4, in certain cases of degraded operation for example. In a planetary architecture, the crown carrier is composed of a more or less flexible part which drives the crown and of a part held by bearings or bearings and on which the fan is mounted. These fixing means are known to those skilled in the art and are not detailed here. A brief description can be found for example in FR-A1 -2987416.
    The reduction gear 10 engages on the one hand on the shaft BP3 via splines 7 which drive a planetary or solar gear pinion 11, and on the other hand on the fan shaft 4 which is attached to a satellite carrier 13. Conventionally, the sun 11, the axis of rotation X of which coincides with that of the turbomachine, drives a series of pinions of satellites or satellites 12, which are distributed regularly over the circumference of the reduction gear 10. The number of satellites 12 is generally defined between three and seven. The satellites 12 also rotate around the axis X of the turbomachine except in the case of a planet wheel where they rotate only around their axes of revolution, meshing on internal teeth of the crown 14, which is fixed to a stator of the turbomachine by means of flanges 20 in the case of an epicycloidal or fixed to a rotor of the turbomachine in the case of a sun gear. Each of the satellites 12 rotates freely around a satellite axis / bearing 16 connected to the planet carrier 13, using a bearing which can be smooth, as shown in FIG. 2, or a rolling element bearing ( ball or roller bearings).
    The rotation of the satellites 12 around their satellite axis 16, due to the cooperation of their pinions with the teeth of the crown 14, causes the rotation of the planet carrier 13 around the axis X, and consequently that of the the fan shaft 4 which is linked to it, at a speed of rotation which is lower than that of the BP shaft 3.
    Figure 2 shows the routing of the oil to the reducer 10 and its path inside it. Arrows show in FIG. 2 the path followed by the oil from, in this example, a buffer tank linked to the fixed structure of the turbomachine, to the pinions and the bearings to be lubricated. The lubrication device conventionally comprises three parts: a first part linked to the fixed structure and delivering the oil to the rotating parts of the reduction gear 10, a spinning wheel with the planet carrier 13 receiving this oil in the case of an epicyclic and a distributor assembled with the planet carrier, which are fixed on a planetary architecture, and oil distribution circuits supplied with oil by the impeller to route it to the places to be lubricated.
    Figures 3 to 8 illustrate an embodiment of a reducer 110 according to the invention.
    The reference 130 designates the planet carrier of the reducer 110, which is here of the monobloc type comprising a part forming a cage 134 and a part forming a barrel 142. The cage comprises two annular walls 136, 138 coaxial and connected at their periphery by a cylindrical wall 140.
    The annular wall 136 is integral with the substantially cylindrical barrel 142, partially visible, this barrel comprising means of engagement with the fan shaft 4 of the turbomachine. The coupling means are for example longitudinal grooves.
    In the example shown, the cylindrical wall 140 is perforated and includes lights 143 passing through in the radial direction allowing the mounting of the satellites 150.
    The wall 138 comprises a central opening 144 (allowing the mounting of the solar) centered on the axis X and a series of orifices 146 regularly distributed around the axis X, the opening 144 and the orifices 146 being traversed in the axial direction (figure 5).
    The holes 146 are used for mounting the axes 148 of rotation of the satellites 150. The axes 148 are parallel to the axis X and are mounted in the cage
    134 by axial translation passing through the orifices 146. They are fixed at their longitudinal ends to the walls 136, 138, respectively. Each axis 148 is integral with a smooth bearing 149 around which the satellite 150 is mounted (FIG. 4). The axis 148 is hollow and includes an internal cylindrical cavity 152. The axis 148 and the bearing 149 are crossed by at least one radial duct (not visible) which opens at its radially internal end into the cavity 152, and at its end radially external in a longitudinal groove of the periphery of the bearing for its oil supply.
    As can be seen in FIG. 4, the satellites 150 mounted for rotation on the axes 148 have their external peripheries which partly pass through the slots 143 with a view to their engagement with the external ring of the reducer 110 intended to surround the cage 134.
    The satellites 150 mesh with the solar 151 which includes internal rectilinear grooves 151a for coupling to another shaft such as a turbine shaft.
    A impeller 120 is attached and fixed to the wall 138, on the side of its external face, that is to say that which is not located on the side of the satellites 150. The impeller 120 has the function of lubricating the reduction gear 110 and comprises lubrication means configured to supply lubricant to the nozzles 172 and to the axes 148 and bearings 149. The oil supply to the nozzles 172 makes it possible to lubricate the meshing teeth of the satellites 150 and of the sun 151 , as will be described in more detail in the following with reference to FIG. 8.
    The impeller 120 has a generally annular shape and includes arms 120a projecting radially outward, five in number in the example shown. The impeller 120 is intended to be mounted coaxially on the wall
    138 and has a face 120b for support and fixing on this wall.
    The impeller 120 has a central opening 120c delimited externally by an annular part defining one or more annular grooves 158a, 158b coaxial and disposed axially one next to the other. These grooves 158a, 158b extend around the axis X and open radially inward. Their radially external bottom wall comprises orifices in fluid communication with radial channels 160, on the one hand, and radial conduits 162, on the other hand (FIG. 6).
    Although not shown, oil is intended to be sprayed into the grooves 158a, 158b by means of supplying lubricant. These means generally comprise a series of injectors which are arranged around the axis X and pass through the openings 120c, 144. The injectors are carried by a stator and spray lubricant radially outwards directly into the grooves 158a, 158b , which will then flow through channels 160 and conduits 162.
    In the example shown, the number of channels 160 is equal to the number of conduits 162 which is equal to the number of axes 148 and satellites 150. This number is five here. The channels 160 are regularly distributed around the axis X and the conduits 162 are regularly distributed around the axis X, each conduit 162 being disposed between two adjacent channels 160. The conduits and channels are formed in extra thicknesses 165, 166 of the impeller (FIG. 3). The extra thicknesses 165, 166 in which the channels 160 and the conduits 162 are formed extend radially outwards from the part in which the grooves 158a, 158b are formed. The extra thicknesses 165 in which the conduits 162 are formed extend over the arms 120a of the impeller. It can be considered that the extra thicknesses 166 in which the channels 150 are formed extend over fingers 120d projecting radially towards the outside of the impeller. The fingers 120d have a radial extent smaller than that of the arms 120a and are each arranged between two adjacent arms.
    Each of the conduits 162 communicates at its radially external end with a cavity 152 of an axis 148 for the purpose of supplying lubricant to this axis 148 and the associated bearing 149 (FIG. 6). The lubricant supplied by the conduits 162 is intended to be injected into the cavities 152, then to flow through the aforementioned conduits to the periphery of the bearings 149.
    Each of the channels 160 communicates at its radially external end with a longitudinal end of a nozzle 172 visible in particular in FIGS. 5 and 7. The nozzles 172 have an elongated shape and extend parallel to the axis X. Their axes of elongation are denoted B. They are five in number and regularly distributed around the axis X, each being arranged between two adjacent axes 148. Each channel 160 communicates with cylindrical housings 160a, 160b passing through the wall 138 and the impeller, in which is engaged a longitudinal end portion 172a of the nozzle (FIG. 7). The portion 172a comprises two external annular grooves in which are mounted O-ring seals which cooperate with the wall of the housing 160a of the impeller, and which are arranged on either side of a transverse channel 173 of the portion 172a intended to be aligned with the channel 160 and therefore in fluid communication with the latter. The portion 172a has an external thread at its free end and is connected to an end portion 172b opposite by a fixing lug 175. The free end of this other portion 172b is closed.
    The lug 175 is formed in one piece with the substantially tubular body of the nozzle, and it extends in a plane substantially perpendicular to the longitudinal axis B of this body.
    As can be seen in FIGS. 5 and 8, the lug 175 is intended to be applied against the internal face of the wall 138. The lug 175 comprises an orifice for the passage of a fixing screw 175a, which is screwed into a tapped hole from wall 138.
    Each nozzle 172 comprises a longitudinal internal cavity 174 connected to the lubricant inlet formed by the channel 160a and furthermore substantially radial orifices 176, distributed over its length, which open into the cavity 174. The lubricant brought by the channels 160 to 'to the nozzles 172 is intended to be sprayed through the orifices 176 on the teeth of the satellites 150 and of the sun 151 in operation (cf. FIG. 8).
    As best seen in Figures 5 and 7, the orifices 176 are formed in at least one boss 176a of the body of the nozzle, this boss 176a projecting radially outwards.
    In the example shown, each nozzle 172 comprises two bosses 176a spaced axially from one another with respect to the longitudinal axis B of the nozzle. Each boss 176a comprises six orifices 176 distributed in two rows of three regularly spaced orifices. The number of holes and rows can naturally vary. In the example shown, there is a tooth helix boss. A row is dedicated for solar and a row is dedicated for a satellite. Furthermore, in the example shown, three jets are assigned per function, but this number can vary depending on the flow required or the need for lubrication distribution.
    Each boss 176a has an angular extent β around the extension axis B of the nozzle, which is less than or equal to 360 °, and preferably 180 ° (FIG. 8). It has here in cross section a generally rectangular, triangular or trapezoidal shape. The sides of the boss 176a are here substantially parallel. Finally, as seen in FIG. 8, the tubular wall has a wall thickness E and each boss forms an additional thickness on this wall, which is equal to E ’with E ′ greater than or equal to E in the example shown. It is present to bring the jet outlet closer to the solar and also allows the guide length to be increased.
    The orifices 176 are oriented so that the oil is oriented towards the teeth to be lubricated. In the example shown, the orifices in each row of each boss project oil onto a toothing, these orifices extending in a plane not parallel to that in which the orifices of the other row extend. In the example shown, each nozzle 172 is configured to spray oil on the solar panel 151 and one of the satellites 150.
    A dedicated tool 180 is positioned on the wall 138 (FIG. 5). A centering element 180a of the tool 180 makes it possible to center it on the wall 138.
    The longitudinal end portion 172a of each nozzle 172 is engaged in the housing 160b of the wall 138 and in the housing 180b of the tool 180. Once the nozzles 172 are positioned through the cage and the tool, each tab of fixing 175 of the nozzles 172 is supported on the wall 138 and fixed by the screw 175a. Tool 180 can then be removed.
    Next, the solar, the satellites and the impeller 120 are mounted. The impeller 120 comprises a centering element 120e which makes it possible to center the impeller 120 on the wall 180. Thanks to the centering elements 120e of the impeller and 180b of the tools, the nozzles 172 have been positioned with respect to the cage 140 and to the impeller 120 with sufficient localization precision to ensure the insertion of the longitudinal ends of the nozzles
    172 in the housings 160a of the impeller 120 despite the hyperstatism of the assembly.
    A nut 177a is then screwed onto each free end 172a of the nozzles 172, so as to keep the impeller 120 in position on the cage 140.
    In the mounted position of the nozzles 172 on the planet carrier 130 shown in FIG. 5, the bosses 176a of the nozzles are oriented rather radially inwards.
    In order to bring the orifices 176 for spraying oil carried by the sprinklers 172 closer to the teeth of the sun and the satellites, the invention thus proposes bosses 176a for lengthening the oil passages in the sprinklers up to these orifices. and therefore shortening the oil jets. In addition, the nozzles 172 are here mounted inside the cage 134 unlike the prior art. The impeller 120 can be mounted prior to assembly of the cage or at the very end of the assembly process. The nozzles 172 are inserted into the housings 160b of the wall 138 of the cage and can then be positioned with respect to each other using the tool 180 which temporarily replaces the impeller. Each nozzle 172 is then clamped using the screw 175a inside the cage and the positioning tools are removed. After this step, the solar 151, the satellites 150 and their axes 148 can be mounted. Finally, the impeller 120 is fixed to the planet carrier 130 using the nuts screwed onto the threaded parts of the sprinklers. This editing sequence is the preferred one even if there are others.
    In the context of the present invention, the inventors have sought to identify all the geometric parameters which represent the distance between a nozzle and the sun. Starting from the head diameter of the solar, and adding a mounting clearance, we obtain a centering diameter of the impeller in the planet carrier. Then, a slight clearance is left for the assembly of the nozzle. This depends on the diameter of the pipe and the thickness of the O-ring. Material is then added to the 5 nozzles, through the bosses, so as to increase the guide length of the lubricant jet.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Lubricant nozzle (172) for a planetary gearbox of a turbomachine, said nozzle having a generally elongated shape and comprising a body with a longitudinal axis B, said body having a longitudinal internal cavity (174) which is in communication fluidic with a lubricant inlet located at a longitudinal end (172a) of said body and with lubricant outlet orifices (176) which are formed in an annular wall of said body and which extend substantially radially with respect to said axis B, characterized in that said orifices are formed in at least one boss (176a) of said body, which projects radially outward on said wall and which has an angular extent (β) around said axis less than or equal to 180 °.
    [2" id="c-fr-0002]
    2. Sprinkler (172) according to the preceding claim, wherein the at least one boss (176a) has in cross section a generally rectangular, triangular or trapezoidal shape.
    [3" id="c-fr-0003]
    3. Sprinkler (172) according to the preceding claim, in which the trapezium boss (176a) comprises a small base which is defined by the radially external end of the boss (176a) on which said orifices (176) open, and flanks which form between them an angle (a) of between 0 and 90 °.
    [4" id="c-fr-0004]
    4. Sprinkler (172) according to one of the preceding claims, wherein said body comprises at least two bosses (176a) at a longitudinal distance from each other.
    [5" id="c-fr-0005]
    5. Sprinkler (172) according to one of the preceding claims, wherein said body comprises at least one external annular groove for housing an annular seal.
    [6" id="c-fr-0006]
    6. Sprinkler (172) according to one of the preceding claims, comprising a fixing lug (175) formed in one piece with the body, said lug extending substantially in a plane perpendicular to said axis and comprising a passage orifice a fixing means of the screw-nut or screw-threaded type.
    [7" id="c-fr-0007]
    7. Assembly comprising a planet carrier (130) and sprinklers (172) according to one of the preceding claims, for a speed reducer with planetary gear of a turbomachine, said planet carrier comprising a cage (134) defining an internal space for mounting a central solar (151) of axis X of rotation and an annular row of satellites (150) arranged around the axis X and meshed with said solar, said solar comprising means of coupling to a first shaft, said cage comprising two substantially parallel annular walls (136, 138) centered on said axis X and a cylindrical wall (140) connecting said annular walls to their external periphery, a first (136) of said annular walls being connected to a body (142) substantially cylindrical comprising means for coupling to a second shaft, and a second (138) of said annular walls comprising passages for mounting the nozzles, by displacement ment of each nozzle (172) in a direction substantially parallel to said axis X, characterized in that said nozzles (172) are configured to be mounted beforehand on said second wall from inside the cage.
    [8" id="c-fr-0008]
    8. Assembly according to the preceding claim, the nozzles (172) being as defined in claim 6, in which said nozzles each comprise a first longitudinal portion comprising said bosses (176a) and said tab (175) and a second threaded portion, the first portion of each nozzle being configured to extend inside said cage (134) and the threaded portion being intended to receive a nut (177a) intended to bear on an external face of said cage.
    [9" id="c-fr-0009]
    9. The assembly as claimed in claim 8, in which the threaded portion of each nozzle (172) crosses on the one hand a housing (160a) of a impeller (120) attached and fixed to said second wall (138) of the cage, and on the other hand a housing (160b) of this second wall.
    [10" id="c-fr-0010]
    10. Aircraft turbomachine, characterized in that it comprises a speed reduction gear with planetary gear comprising at least one nozzle (172) according to one of claims 1 to 6 or an assembly according to one of claims 7 to 9 .
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    同族专利:
    公开号 | 公开日
    FR3069300B1|2019-07-26|
    WO2019016463A1|2019-01-24|
    FR3069301B1|2021-11-05|
    EP3655680A1|2020-05-27|
    US11112001B2|2021-09-07|
    CN110914576A|2020-03-24|
    FR3069300A1|2019-01-25|
    EP3655679A1|2020-05-27|
    CN110869650A|2020-03-06|
    US20200132186A1|2020-04-30|
    US20210087946A1|2021-03-25|
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    FR2987416B1|2012-02-23|2015-09-04|Snecma|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.|
    FR3036763B1|2015-05-27|2017-05-26|Hispano-Suiza|EPICYCLOIDAL TRAIN REDUCER|
    FR3041054B1|2015-09-15|2017-09-15|Hispano-Suiza|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|FR3092889B1|2019-02-14|2021-12-03|Safran Trans Systems|LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AIRCRAFT|
    FR3092888B1|2019-02-14|2021-01-22|Safran Trans Systems|LUBRICATION OF A SATELLITE CARRIER FOR A MECHANICAL TURBOMACHINE REDUCER, IN PARTICULAR OF AIRCRAFT|
    FR3103243A1|2019-11-15|2021-05-21|Safran Transmission Systems|STEP WHEEL FOR THE OIL SUPPLY OF AN EPICYCLOIDAL OR PLANETARY REDUCER.|
    法律状态:
    2018-11-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-01-25| PLSC| Publication of the preliminary search report|Effective date: 20190125 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1756894|2017-07-20|
    FR1756894A|FR3069300B1|2017-07-20|2017-07-20|ASSEMBLY COMPRISING A LUBRICATING WHEEL AND LUBRICANT SPRINKLERS FOR A TURBOMACHINE EPICYCLOIDAL TRAIN SPEED REDUCER|CN201880045550.1A| CN110869650A|2017-07-20|2018-07-20|Lubricating oil nozzle for a planetary gear reducer of a turbomachine|
    PCT/FR2018/051870| WO2019016491A1|2017-07-20|2018-07-20|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine|
    US16/630,394| US20210087946A1|2017-07-20|2018-07-20|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine|
    EP18758923.9A| EP3655679A1|2017-07-20|2018-07-20|Lubricant nozzle for a planetary gear set speed reducer of a turbomachine|
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