• 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:
    Crown (214) of a planetary gearbox (110) for a turbomachine, in particular an aircraft, said ring extending around an axis (X) and comprising first and second annular elements (214a, 214b) coaxial and respectively comprising two internal annular gears (250) oriented differently, said first and second annular elements further comprising respectively first and second radially outer annular flanges (214ab, 214bb) for fixing said first and second elements together, the teeth of said first and second elements; annular members being axially spaced from one another and from a joint plane (P) of said first and second flanges, and defining therebetween an annular space (266) delimited externally by two annular support flanges (214ab1, 214bb1) respective of said flanges, at least one of the flanges having at said plane of joint notches (268) substantially radial crossing oil centrifuge, characterized in that it further comprises an annular row of oil retaining walls (300) projecting on said flanges in said space.
    公开号:FR3074552A1
    申请号:FR1761732
    申请日:2017-12-06
    公开日:2019-06-07
    发明作者:Jean Charrier Mathieu；Pierre Marcel Morelli Boris；Louis Simon Adrien
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    SPEED REDUCER CROWN WITH PLANETARY DRIVE
    OF TURBOMACHINE
    Field of the invention
    The present invention relates to the field of planetary gear speed reducers for turbomachines, in particular aircraft.
    State of the art
    The state of the art includes in particular the documents FR-A1-2 853 382, FRAI -2 942 284, FR-A1 -2 987 402, FR-A1 -2 987 416, FR-A1 -2 987 417, FRAI -3 041 054, and FR-A1-3 047 279.
    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 to ensure lubrication and cooling of their pinions and bearings. The oil flow rate depends on the architecture and is for example of the order of 6000 to 7000 liters per hour on takeoff for a particular architecture.
    Among the reducers used, there are planetary and planetary gears which have the advantage of offering significant reduction rates 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 of a planetary gear reducer, the outer ring is fixed in rotation and the sun and the planet carrier are leading and driven. The present invention relates to a planetary gearbox in which the crown is movable.
    One of the problems with this type of reducer is to ensure good lubrication of the solar meshes and the satellites between them. These meshes are lubricated in operation by oil which is supplied by nozzles. Once lubricated, the meshes project the oil radially outward by centrifugation to reach the crown.
    The crown comprises two coaxial annular elements and respectively comprising two annular teeth intended to cooperate with each satellite. The teeth of the crown are of the chevron type, the teeth of the elements having substantially opposite helical angles. The annular elements of the crown have radially external annular flanges for fixing the elements together as well as to an annular crown holder intended to extend around at least part of the crown. The teeth of the annular elements are separated axially from one another and from a joint plane of the flanges. The teeth thus define between them an annular space delimited externally by two annular flanges of respective support of the flanges.
    In the current technique, centrifuged oil flows into this space and onto the edges. It is then evacuated radially outward by passing through substantially radial notches which are formed in the flanges at their joint plane.
    However, in operation, due to the rotation of the crown, the oil tends to slip on the flanges supporting the flanges and may have difficulty in being evacuated by the notches. These slippages are accentuated during the acceleration phases of the reducer and when the oil is not very viscous. This phenomenon leads to a decrease in the oil evacuation efficiency, which can have many harmful consequences such as oil recirculation, oil heating and therefore potentially entanglement, etc.
    The present invention provides an improvement which provides a simple, effective and economical solution to this problem.
    Statement of the invention
    The invention relates to a planetary reduction gear ring for a turbomachine, in particular for an aircraft, said ring extending around an axis and comprising first and second coaxial annular elements and comprising respectively two internal annular toothing differently oriented, said first and second annular elements further comprising respectively first and second radially external annular flanges for fixing said first and second elements to each other, the teeth of said first and second annular elements being axially spaced from each other and from a plane of joint of said first and second flanges, and defining between them an annular space delimited externally by two annular flanges of respective support of said flanges, at least one of the flanges comprising at said joint plane substantially radial notches for crossing the oil by centrifugation, characteristics e in that it further comprises an annular array of oil retention walls projecting from said flanges in said space.
    The invention thus proposes to limit or even prevent the sliding of the oil on the edges of the crown, by means of the retention walls. In operation, under the effect of centrifugal forces, the oil will therefore tend to be prevented from rotating with the crown and will be stored in pockets each delimited by adjacent walls. Ideally, each pocket will communicate with at least one notch crossing the flanges, for the evacuation of the oil outside the crown.
    The crown according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with each other:
    each of said flanges comprises an annular row of oil retention walls, the walls of one of said flanges being axially aligned with the walls of the other of the flanges; the walls extending between the teeth are thus each formed by a first part or half of the wall located on one of the elements, and a second part or half of the wall located on the other of the elements; this makes it possible to treat the manufacturability of the crowns independently of one another; these walls or wall parts are aligned and partition the above-mentioned space into several adjacent pockets;
    - the walls extend substantially in planes parallel to said axis; this ensures good oil retention during operation;
    - the walls of one of the flanges are spaced apart from an axial clearance from the walls of the other of the flanges; this can be useful to facilitate the assembly of the elements forming the crown and to avoid any contact in operation between the walls; alternatively, this play could be zero and therefore nonexistent;
    - The walls are attached and fixed to the first and second annular elements; this makes it easier to manufacture the elements;
    - the walls are formed in one piece with the first and second annular elements; the walls could then be obtained from foundry or produced by machining;
    - said edges are substantially cylindrical; alternatively, they could be frustoconical to promote the flow of the oil by centrifugation radially outward.
    The present invention also relates to a speed reducer with a planetary train of a turbomachine, comprising a crown as described above.
    The present invention also relates to a turbomachine, in particular an aircraft, comprising a reduction gear as described above.
    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 schematic view in axial section of a planetary gear reducer,
    - Figure 3 is a schematic perspective view of a planetary gear reducer,
    FIG. 4 is a schematic perspective view of a impeller and nozzles of the reducer of FIG. 3,
    FIG. 5 is a schematic perspective view of a planet carrier of the reducer of FIG. 3,
    FIG. 6 is a partial schematic view in axial section of a crown and of a crown holder of a reduction gear according to the prior art,
    FIG. 7 is a partial schematic perspective view of the crown of FIG. 6,
    FIG. 8 is a diagram illustrating the phenomenon of sliding of the oil in operation on the crown,
    FIG. 9 is a diagram similar to that of FIG. 9 and illustrating the solution of the invention consisting in retaining the oil on the crown by means of walls, and
    - Figure 10 is a partial schematic view in axial section of an embodiment of a reduction gear according to the invention.
    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 blower propeller S is driven by a blower shaft 4 which is coupled to the LP shaft 3 by means of a planetary gear reducer 10
    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.
    In a planetary architecture, the crown carrier (not shown) is composed of a more or less flexible part which drives the crown 14 and of a part held by bearings and on which the blower S is mounted. These means of fixing are known to those skilled in the art and are not detailed here. A brief description can be found for example in FR-A1 -2 987 416.
    The reduction gear 10 engages on the one hand on the BP shaft 3 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 Portesatellites 13. Conventionally, the sun 11, whose axis of rotation X 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 gear 10. The number of satellites 12 is generally defined between three and six. The satellites 12 rotate around their axes of revolution, meshing on internal teeth of the crown 14. Each of the satellites 12 rotates freely around a satellite axis 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 planet carrier 13 is fixed in the case of a planetary reducer.
    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 crown 14 about the axis X, and consequently that of the fan shaft 4 which is linked to it, at a speed of rotation which is lower than that of the LP 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.
    Figures 3 to 5 illustrate a more concrete example of a reducer 110. Although it is of the planetary gear type, the reducer 110 makes it possible to understand the arrangement and the cooperation of the parts of a reducer.
    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, comprising meshing means with a fan disc of the turbomachine. The coupling means are for example longitudinal grooves.
    In the example shown, the cylindrical wall 140 is perforated and comprises slots 143 passing through in the radial direction allowing the mounting of the satellites.
    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 orifices 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.
    The satellites 150 are rotatably mounted on the axes 148 and have their external peripheries which partly pass through the slots 143 with a view to their engagement with the external ring of the reducer 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 supply of oil to the nozzles makes it possible to lubricate the meshing teeth of the satellites 150 and of the sun 151.
    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 of support and fixing on this wall.
    The impeller 120 has a central opening 120c delimited on the outside by an annular part defining two annular grooves 158a, 158b coaxial and arranged axially one next to the other. These grooves 158a, 158b extend around the axis X and open radially inward. Their radially outer bottom wall comprises orifices in fluid communication with radial channels 160, on the one hand, and radial conduits 162, on the other hand.
    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.
    Each of the conduits 162 communicates at its radially outer end with a cavity of an axis 148 for the purpose of supplying lubricant to this axis 148 and the associated bearing 149. The lubricant supplied by the conduits 162 is intended to be injected into the cavities, 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 FIG. 4. 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 nozzle 172 includes orifices 176 for spraying oil onto the teeth of the satellites 150.
    The nozzles 172 are fixed to the impeller 120 by means of screwed legs 175, and the impeller 120 is attached and fixed by screws to the annular wall 138 of the planet carrier 130.
    Figures 6 and 7 show a ring 214 of a planetary reducer according to the prior art.
    The crown 214 extends around the axis X of the turbomachine, and comprises two coaxial annular elements, called first annular element 214a or upstream element and second annular element 214b or downstream element.
    Each element 214a, 214b comprises an annular body 214aa, 214ba of generally cylindrical shape and connected to an annular flange 214ab, 214bb extending radially outwards.
    Each body 214aa, 214ba comprises an internal annular toothing 250 at its internal periphery. Although this is not visible in the drawings, the teeth 250 of the two bodies or elements are complementary to the teeth of the satellites, which are they of the type shown in FIG. 3. The teeth 250 of the elements 214a, 214b are in chevron.
    The body 214aa, 214ba of each element is connected by one of its longitudinal ends to the corresponding flange 214ab, 214bb by means of an annular flange 214ab1, 214bb1. The body 214aa is connected at its downstream end, located on the side of the other body 214ba, to the flange 214ab by the flange 214ab1, and the body 214ba is connected at its upstream end, located on the side of the other body 214aa, to the flange 214bb by the flange 214bb1.
    Each flange 214ab, 214bb extends substantially in the radial direction and is supported on the other flange in a joint plane P. The flanges 214ab1, 214bb1 have here a generally frustoconical shape. The rim 214ab1 extends from upstream downstream to the outside and the rim 214bb1 extends from upstream downstream to the inside.
    The flanges 214ab, 214bb serve to fix the elements 214a, 214b together, as well as to a crown holder 254 in the example shown.
    For this, the flanges 214ab, 214bb each comprise an annular row of axial through holes 256 for the passage of fastening means 258 of the screw-nut type or the like. The orifices 256 of the flanges 214ab, 214bb are aligned and receive the fixing means 258.
    The crown holder 254 also includes an annular flange 260 for fixing to the flanges 214ab, 214bb. The flange 260 is applied axially to one of the flanges 214ab, 214bb, namely here the flange 214ab of the upstream element 214a. The flange 214ab is thus interposed axially between the flange 260 and the flange 214bb. The reverse is also possible. Conversely, we mean that the crown carrier is on the right side of the crown, which represents the rear of the engine.
    The flange 260 comprises holes aligned with the holes 256 and which also receive the fixing means 258, heads of which can be applied axially on the downstream face of the flange 214bb and nuts can be applied axially on the upstream face of the flange 260 or vice versa. In the example shown, a flange 262 of an annular oil collector is axially supported on the flange 214bb and receives the heads of the nuts on its downstream face.
    The flanges 214ab, 214bb further include a first set of axial holes 263 through and tapped allowing the disassembly of the crown holder 254 with the crown 214. A second set of axial holes 263 through and tapped allows to disassemble the element 214a from the element 214b. The flanges 214ab, 214bb also include at least one pin 265 for angular setting of the elements 214a, 214b. Each flange 214ab, 214bb can comprise one or more of these holes 263, intended to be aligned with one or more similar hole (s) 263 of the other part, and to receive a pin. wedging 265. The pin 265 here has a generally cylindrical shape and is oriented axially. It comprises an external annular bead, substantially in its middle in the axial direction, and intended to be located substantially at the surfaces 252 of the flanges.
    The flange 214bb comprises at its external periphery a cylindrical centering rim 264. This rim 264, which is carried by the element 214b is configured to cooperate by axial sliding and radial support with the external periphery of the other element 214a to ensure the centering, during assembly and in operation, of this other element 214a. Alternatively, the element 214a could include such a rim intended to cooperate with the element 214b with a view to centering it.
    The rim 264 is intended to cooperate with the external periphery of the flange 214ab of the element 214a. During assembly, the flange 264 thus extends around the flange 214ab.
    In the example shown, the rim 264 also ensures the centering of the crown holder 254. The rim 264 can cooperate as indicated in the above with the external periphery of the flange 260.
    The rim 264 extends here continuously over 360 °. It is not split or segmented. The reference surface for centering is thus uninterrupted.
    The flanges 214ab1, 214bb1 delimit an annular space 266 which here has a generally triangular section, the point of which is oriented radially outwards.
    Due to the shape of the flanges 214ab1, 214bb1 and their connection to the longitudinal ends, respectively downstream and upstream, of the bodies 214a, 214b these bodies are axially spaced from one another by a predetermined distance.
    Lubricating oil is intended to flow in operation through the inter-body space 266. Substantially radial passages are provided between the flanges 214ab, 214bb in order to allow the evacuation of the oil radially towards the outside of the crown 214.
    The oil passages are here formed on the one hand by notches 268 or substantially radial slots formed in the surfaces 252 of the flanges. Each flange includes an annular row of notches 268 aligned axially with notches 268 on the other of the flanges. The notches are made at a distance from the orifices 256 for the passage of the fixing means 258, from the pin hole 265 as well as from the holes 263. Each notch has for example in section a semi-circular (semi-oblong) or rectangular shape as in the example shown (Figure 7).
    The notches 268 are in fluid communication, at their radially internal ends, with the cavity 266, and at their axially external ends with oblong orifices 270 passing through the oil outlet formed in the centering flange 264. In other words, the oil passages open out at their radially external ends onto the external cylindrical surface of the rim 264, to form oil outlet orifices 270 therein.
    With the exception of the rim 264, the crown elements 214a, 214b are symmetrical with respect to a median plane, perpendicular to the axis and passing substantially between the elements.
    FIG. 8 very schematically shows the problem of oil slippage which occurs on the flanges 214ab1, 214bb1 for supporting the flanges due to the rotation of the crown 214 in operation. This phenomenon is accentuated during the acceleration phases of the reducer and when the oil is not very viscous, and leads to a reduction in the oil evacuation efficiency.
    The invention proposes to counter this phenomenon by providing walls 300 for retaining or retaining oil in the inter-body space 266, at the flanges 214ab1, 214bb1 for supporting the flanges, in order to prevent the oil from is driven by the crown 214 in operation. This principle is illustrated schematically in FIG. 9 which shows that the walls 300 define between them pockets having a circumferential orientation around the axis X and designed to retain the oil so as to then facilitate its flow through the notches 268 in the joint plane of the flanges 214ab, 214bb.
    Figure 10 shows a more concrete embodiment of the invention.
    The crown 214 according to the invention comprises around the aforementioned axis X an annular row of walls 300 for retaining oil projecting from the edges 214ab1, 214bb1 in the space 266. Each of the edges 214ab1, 214bb1 comprises an annular row of oil retention walls 300, the walls of one of said flanges being axially aligned with the walls of the other of the flanges.
    In the example shown, the walls 300 extend substantially in planes parallel to the axis X. The walls 300 of one of the flanges are here spaced apart by an axial clearance E from the walls of the other of the flanges.
    In a particular embodiment shown in the drawing, the walls 300 are attached and fixed to the annular elements 214a, 214b and in particular to the flanges 214ab1, 214bb1. As a variant, the walls 300 can be formed in one piece with these elements.
    Furthermore, in the example shown, the flanges 214ab1, 214bb1 have a generally substantially cylindrical shape but could have a generally frustoconical shape as shown in FIG. 6.
    The number of walls 300 per element 214a, 214b can be determined according to the number of notches 268 for discharging oil in the joint plane of the flanges 214ab, 214bb. For example, the number of walls 300 can be equal to the number of notches 268 so that a wall is associated with each notch and is positioned in an optimized manner with respect to this notch so as to facilitate the flow of l oil in operation. As shown schematically in FIG. 9, the wall will be located just downstream of the notch with respect to the direction of sliding of the oil in operation which is opposite to the direction of rotation (arrow F) of the crown 214.
    As a variant, several notches 268 could be associated with each pocket delimited between two adjacent walls 300, in order for example to accelerate the evacuation of the oil from these pockets in operation and thus reduce their storage time within the reducer.
    The invention makes it possible to facilitate the evacuation of the oil, in particular during the acceleration phases and when the oil is not very viscous. It also makes it possible to limit heating of the gearbox and therefore to increase its service life.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Planetary reduction gear (214) (110) for a turbomachine, in particular for an aircraft, said crown extending around an axis (X) and comprising first and second annular elements (214a, 214b) coaxial and comprising respectively two internal annular toothing (250) oriented differently, said first and second annular elements further comprising respectively first and second radially external annular flanges (214ab, 214bb) for fixing said first and second elements to each other, the toothing of said first and second second annular elements being axially spaced from each other and from a joint plane (P) of said first and second flanges, and defining between them an annular space (266) delimited externally by two annular flanges (214ab1, 214bb1) respective support of said flanges, at least one of the flanges comprising at said joint plane notches (268) substantially radial es of oil passage by centrifugation, characterized in that it further comprises an annular row of walls (300) of oil retention projecting from said edges in said space.
    [2" id="c-fr-0002]
    2. Crown (214) according to claim 1, in which each of said flanges (214ab1, 214bb1) comprises an annular row of oil retention walls (300), the walls of one of said flanges being axially aligned with the walls on the other side.
    [3" id="c-fr-0003]
    3. Crown (214) according to claim 1 or 2, wherein the walls (300) extend substantially in planes parallel to said axis (X).
    [4" id="c-fr-0004]
    4. Crown (214) according to one of the preceding claims, in which the walls (300) of one of the flanges (214ab1, 214bb1) are spaced from an axial clearance (E) from the walls of the other of the flanges .
    [5" id="c-fr-0005]
    5. Crown (214) according to one of the preceding claims, in which the walls (300) are attached and fixed to the first and second annular elements (214a, 214b).
    [6" id="c-fr-0006]
    6. Crown (214) according to one of the preceding claims, in
    5 which the walls (300) are formed in one piece with the first and second annular elements (214a, 214b).
    [7" id="c-fr-0007]
    7. Crown (214) according to one of the preceding claims, wherein said flanges (214a, 214b) are substantially cylindrical.
    [8" id="c-fr-0008]
    8. Speed reducer (110) with planetary gear of a turbomachine,
    10 comprising a crown (214) according to one of the preceding claims.
    [9" id="c-fr-0009]
    9. Turbomachine, in particular of an aircraft, comprising a reduction gear (110) according to the preceding claim.
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    FR3047279B1|2016-01-28|2019-06-07|Safran Transmission Systems|AXIS-DISTRIBUTED DISTRIBUTION WHEEL AND EPICYCLOIDAL TRAIN REDUCER THUS EQUIPPED|US11225912B2|2018-04-20|2022-01-18|Pratt & Whitney Canada Corp.|Gear assembly for coaxial shafts in gas turbine engine|
    FR3086341B1|2018-09-24|2020-11-27|Safran Aircraft Engines|TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT|
    US10989073B2|2019-03-05|2021-04-27|Rolls-Royce Corporation|Power gearbox with embedded oil reservoir for use in a gas turbine engine|
    US11203980B2|2020-01-17|2021-12-21|Unison Industries, Llc|Air turbine starter with lubricated bearing assembly|
    法律状态:
    2018-11-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-06-07| PLSC| Search report ready|Effective date: 20190607 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1761732|2017-12-06|
    FR1761732A|FR3074552B1|2017-12-06|2017-12-06|SPEED REDUCER CROWN WITH PLANETARY TURBOMACHINE TRAIN|FR1761732A| FR3074552B1|2017-12-06|2017-12-06|SPEED REDUCER CROWN WITH PLANETARY TURBOMACHINE TRAIN|
    EP18210087.5A| EP3495692B1|2017-12-06|2018-12-04|Turbine engine speed reduction ring gear with planetary gear|
    US16/211,133| US10704669B2|2017-12-06|2018-12-05|Planetary reduction gear ring gear for a turbine engine|
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