• 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 invention relates to a pivot (5) for an epicyclic planetary bearing, the pivot having circumferentially opposite circumferential grooves (25a), laterally open, providing flexibility to the pivot and separating radially, from two lateral parts in the door-to-door position. false (27a, 27b) of the pivot, two axially opposite end extremities of a central shaft. At least one of the cantilevered side portions is hollowed out by at least one recess (65a).
    公开号:FR3071025A1
    申请号:FR1758422
    申请日:2017-09-12
    公开日:2019-03-15
    发明作者:Marie Renee Lemoine Julie；Claude Michel Dombek Alexis；Balint Pap
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    Pivot for plain bearing and gear train with reduced thermal stresses
    The present invention relates to a pivot with a plain bearing and a gear train, in particular for a gas turbomachine for aircraft, equipped with at least one such pivot.
    In this application:
    - axial has the direction parallel to the axis (X) of rotation around which the blades of the turbomachine in question are rotatably mounted,
    - radial has the direction perpendicular to the X axis,
    - circumferential has the meaning extending around the X axis,
    - external and internal (or external and internal) have respectively radially external and radially internal directions with respect to the axis X,
    - recess has for synonym notch, notch, cutout, cavity, hollow. It is a space without matter.
    The application to a gear train, including planetary gear, is particularly intended, which includes an outer ring and planet gears engaged with a central pinion and with the outer ring and each mounted free in rotation on a planet carrier, the satellite pinions can each rotate around a satellite axis by means of a pivot.
    Among the planetary gear trains are particularly concerned:
    - those in which the outer ring is movable in rotation (assembly also called planetary reduction gear),
    - but also, those in which the planet carrier is fixed and the outer ring is mobile (mounting also called planetary reduction gear).
    The satellite carrier can therefore be fixed or pivotable around the axis of the internal and external planetary. The entry can be formed by the internal planetary, and the exit by the satellite carrier.
    In a turbomachine, planetary gears are thus used in particular to reduce the speed of rotation of the fan rotor, independently of the speed of rotation of the turbine.
    Document FR 2 991 421 describes such a planetary gear reducer, in which the toothed wheels forming the satellites are mounted on pivots of the planet carrier by means of plain bearings, which is favorable in terms of space and weight. Plain bearings have an almost infinite service life, provided that they are constantly supplied with an oil containing no abrasive particles.
    This sensitivity to lubrication involves controlling the deformation of the bearing on the pivot side and its temperature during operation.
    However, during TEHD (thermo-elasto-hydro-dynamic) calculations on a pivot for a conventional plain bearing, it has been observed that the active surface of the pivot has heated (radially outer surface forming part of the bearing once the pivot is mounted between the satellite and the satellite carrier), in particular in an area circumferentially just upstream of the passage, such as a slot, for supplying oil formed in said active surface of this pivot.
    Non-identical misalignments have also been observed between the upstream spans and the downstream spans of different pivots. Tangential displacements, due to the applied torques, and / or radial, due to the centrifugal force, and not symmetrical between upstream and downstream along the axis of rotation X, have been observed on pivots.
    All of this is damaging because it may affect the reliability of the pivot and the efficiency of the bearing.
    The object of the invention is in particular to provide a simple, effective and economical solution to at least part of these problems.
    To this end, it offers a pivot (also called a shaft) for a plain bearing of a gear train, the pivot having:
    - a part forming a central barrel, extending around an axial passage of the pivot, and
    - axially opposite circumferential grooves, open axially (therefore laterally, thus providing flexibility to the pivot) which radially separate, from two lateral parts cantilevered from the pivot, two axially opposite lateral end portions of the central shaft, the pivot being characterized in that at least one of the lateral overhangs is hollowed out by at least one recess.
    By thus providing a hollow, a void, on at least part of at least one of the flexibility zones formed by the cantilevered lateral parts, the distribution of the material in the pivot will be modified relative to a pivot with side parts in cantilever uniformly full and circumferentially identical, it being recalled that these zones of circumferential flexibility make it possible to reduce the stiffness of the pivot in order to limit the misalignment between the active surface of the pivot and its bearing surfaces.
    However, it turned out that the need for flexibility is not necessary in all directions. It is therefore possible to vary the rigidity of its flexibility zones locally, in particular in places with high temperature rise, in order to increase the conduction and thus decrease the temperature of the active zone, without however altering the quality of the aforementioned alignment. It has in fact been found that one cause of the aforementioned local temperature increase was linked to the presence of air trapped in the flexibility zone. The proposed solution remedies this. The absence of matter limits the conduction of heat and therefore the evacuation of calories.
    Tests and measurements having confirmed that it was even possible to locally suppress the predetermined deformation of the pivot provided by the aforementioned flexibility zones, it is even proposed:
    - That, on the lateral side of said at least one recess, said cantilevered lateral part is circumferential but not annular, and / or
    - That said at least one recess is present at the interface between a satellite pinion and the pivot in question, on the smooth surface of the pivot which defines the outer circumferential surface of this pivot.
    In order to further promote heat transfer and efficiency in the anti-misalignment effect even more, it is further advised that the aforementioned pivot is monobloc, with its lateral cantilevered parts and its central barrel in a single room.
    And to optimize the expected decrease in temperature of the active area, without altering the quality of the above-mentioned alignment, it is proposed that:
    - Said at least one recess has an irregular contour, and / or
    - that, on the lateral side of this recess:
    - the circumferential groove has, apart from said at least one recess, at least one depth (P) in a direction in which the circumferential groove extends towards the inside of the pivot, from a free lateral end of said part lateral cantilever, to a bottom end, and
    - that said recess then extends over at least 10% of the circumference of the pivot and / or of said depth (P) of the circumferential groove.
    Distribute this temperature control of the active area of the pivot, by providing that the pivot includes at least two recesses hollowed out respectively in one and the other of the two lateral cantilevered parts, will make it possible to widen the zone at higher temperature. low and therefore balance the constraints, even if the recesses on both sides are different.
    Now concerning the gear train, in particular for an aircraft gas turbomachine, to which the invention also relates, it is intended that it comprises an outer ring gear and planet gears, in engagement with the central gear and with the outer ring gear and each mounted freely in rotation on a planet carrier, the planet gears which can each rotate around a satellite axis (parallel to the X axis) by means of a said pivot, having all or some of its characteristics.
    It is also expected that this gear train may further comprise means for supplying oil at an interface between a said satellite pinion and the pivot in question. At least one radially outer circumferential surface of a said pivot will then preferably have a slot for supplying a lubricating liquid, said width (I) and / or depth (P) being minimum in a lateral zone of the pivot adjacent to the slot and located angularly on the opposite side to that towards which the lubricant flows (direction S below) on the outer surface when the gear train is operational, so can rotate.
    Thus, material will have been removed locally in the areas where the lubricant heats up a lot. Such a gear train is efficient in that it combines performance in the expected alignment of the parts concerned and a limitation of harmful hot spots both mechanically for the structure of the parts and for the lubricant.
    As for the aforementioned turbomachine, also concerned as such, it may include such a gear train, in particular an epicyclic gear train, the central pinion of which may surround and be fixed in rotation with a compressor shaft. the turbomachine.
    And in particular, it may be a case in which the outer ring is secured to a housing or a static annular ferrule of the low pressure compressor.
    Thus, the invention is in particular applicable to a gear train, such as a planetary gear train in which the outer ring is fixed. In this case, the gear train can be described as a reduction gear since the exit speed, i.e. that of the satellite carrier is lower than the entry speed, that is of that of the '' drive shaft in rotation of the central pinion.
    The planet carrier can for example be then connected to a fan wheel upstream of the turbomachine, the speed of which is thus lower than the speed of the compressor shaft.
    Yet another aspect on which the invention has intervened: the process for producing a pivot with a plain bearing.
    In fact, to the knowledge of the inventors so far, no method has been defined which makes it possible to obtain a good evacuation of calories, or even a favorable compromise between this evacuation and a range which is always effectively guided.
    This is how a method is proposed here for producing the aforementioned pivot with its outer circumferential surface having, as mentioned above, a slot for supplying a lubricating liquid, so that the liquid flows on a circumferential side. from said outer circumferential surface when it leaves the feed slot, in which process:
    - a TEHD model determines the temperature fields of the pivot at least at the location of at least one of the cantilevered lateral parts,
    - we identify at this location at least one area that the TEHD model indicates as the area with the highest temperature (s), then
    - A recess is created in the said zone in the said at least one cantilevered side part.
    This way of operating is fast, simple and reliable.
    It is specified that the thermo-hydrodynamic method within the framework of lubrication, noted THD, consists in determining the temperature fields in the lubricating fluid but also in the solids constituting the contact in connection with the hydrodynamic pressure field in the film which lubricates. For this, to the Reynolds equation whose main parameter is the pressure are associated two additional equations: the energy equation which will allow to determine the temperature at any point of the fluid, and the Fourrier equation which will allow to determine the temperature in solids (tree, connecting rod, bearing, etc.). The model is said to be thermo-elasto-hydrodynamic, denoted TEHD, when elastic and thermo-elastic deformations are taken into account in addition to purely thermal phenomena in the overall resolution of the problem. It goes without saying that thermal deformations of solids can only be taken into account if the temperatures in the solids are known.
    The invention will be better understood if necessary and other details, characteristics and advantages of the invention may appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which:
    - Figure 1 is a front diagram of a gear train,
    - Figure 2 is a kinematic diagram of a planetary gear train,
    FIG. 3 is a view in local section of the plain bearing,
    FIG. 4 is a longitudinal diagram of a turbomachine,
    - Figure 5 is a perspective of a pivot of the prior art,
    FIG. 6 is an axial section along VI-VI of FIG. 7,
    - Figures 7,8 are two possible embodiments of a pivot according to the invention,
    FIG. 9 is a diagram of assembly of pivots in an epicyclic configuration,
    FIG. 10 is a diagram of the mounting of pivots in a planetary configuration, and
    - In FIG. 11, two gear solutions are compared, at the epicyclic top, at the bottom planetary.
    Figures 1 and 2 schematically illustrate the structure of a gear train reducer 1 to which the invention can be applied. The reduction gear 1 conventionally comprises an internal planetary 2 (also called sun or solar) and an external planetary 3 (also called outer ring), the two planetary being coaxial. The internal sun gear, or central pinion 2 can be movable in rotation around its axis X, the external sun gear, or external ring, 3 can be fixed, or vice versa fixed. The gear train 1 further comprises satellites, or planet pinions 4 mounted so as to rotate in rotation on pivots 5 of a planet carrier 6. Each satellite 4 meshes with both the internal planetary 2 and with the planetary external 3. The planet carrier 6 is fixed or pivoting about the axis X of the internal sun gear 2 and the external sun gear 3. The input can be formed by the internal sun gear 2 and the output formed by the planet carrier 6.
    The planet carrier 6 can be coupled in rotation to a propeller (in the case of a turboprop) or to a fan wheel (in the case of a turbojet).
    In a gas turbomachine 10 for aircraft, gear trains 1 are in particular used as a speed reducer to reduce the speed of rotation of a rotor, such as a fan 12 in FIG. 4, independently of the speed of rotation at least one turbine 14 axially coupled downstream to at least one compressor 16 with which the turbomachine is also equipped. From the front air inlet 18, the blower 12 and then in particular the compressor 16 receive air.
    The central pinion, or internal sun gear, 2 surrounds and is then integral in rotation with the shaft 24 of the compressor 16; see example figures
    1.4. The gear train 1 can in particular be mounted in an annular enclosure formed radially inside a low pressure compressor 16a arranged downstream of the blower wheel 12 and upstream (AM) of a high pressure compressor 16b .
    As can be seen by considering Figures 1-3, each satellite 4 has a cylindrical internal surface 7 pivotally mounted around a cylindrical surface 8 (outer bearing surface) of the corresponding pivot 5 of the planet carrier 6, so as to form a smooth bearing.
    It is therefore necessary to supply the interface 9 with oil between these two cylindrical surfaces 7, 8. For this, as illustrated in FIG. 6, the gear train 1 comprises means 13 for supplying lubricant connected to a source of lubricant 13a and comprising a chamber 15 (51 FIG. 5), also called axial passage, extending substantially along the axis X1 of the pivot 5 concerned. At least one of the ends 17 of the chamber 15 is connected to an oil inlet channel. If only one of the ends 17 forms an oil supply, the other end is blocked. The chamber 15 is generally cylindrical and more particularly comprises two parts 15a, 15b (see FIG. 6) separated by a central partition 19 extending radially. The lateral ends 17 of the chamber 15 have axial passages of smaller diameter than the chamber 15, at least one of which forms an oil inlet, as indicated above. The central partition 19 is crossed by an orifice 21 communicating the parts 15a, 15b of the chamber 15. In FIG. 5, there is seen a conventional pivot 50 which, like those 5 according to the invention (see FIGS. 6-9) , has a (substantially) external cylindrical surface (marked 80 for pivot 50 and 8 for pivot 5) of axis X1, adapted to form a smooth bearing with the (substantially) internal cylindrical surface (7 FIG. 3) of the satellite pinion 4 of axis X1 concerned.
    Each pivot resp. (respectively) 5.50 has a part forming a radially central drum, resp. 23.53, extending around the axial passage resp. 15.51. It is around the axis X1 that the pivot is adapted to rotate, in the direction S imposed by its mounting on the reduction gear. Each pivot also has grooves resp. 25a, 25b, 55a axially opposite circumferentials, open axially (therefore laterally), providing flexibility to the pivot (FIG. 5, we cannot see the inside of the other end of the pivot, hence the only reference 55a mentioned). These circumferential grooves separate radially from two lateral parts resp. 27a, 27b, 57a, 57b in overhang, two lateral end parts resp. 230a, 230b, 55a (the other is not visible in FIG. 5), each with a peripheral bearing surface 231 a, 231 b axially opposite from the central barrel.
    For its supply of lubricating liquid, the circumferential surface, radially exterior resp. 8.80 has a passage, such as a slit, resp. 29.59 of elongated feed parallel to the X1 axis.
    This slot communicates with a radial duct (31, FIG. 8), which communicates with the aforementioned axial passage (15,51). We will consider that the liquid lubricant which leaves the passage 29,59 flows on the external surface 8,80 in the S direction of Figures 5,7,8, when the planetary gear 1 operates.
    On the pivot 50 of the prior art, it has been observed that its active surface, and therefore its outer surface 80, has heated up, in particular circumferentially upstream of the passage 59; zones 61 a, 61 b figure 5.
    It turns out that this local increase in temperature is created by the air trapped in the flexibility zone (lateral parts 57a, 57b in overhang). The absence of matter limits the conduction of heat and therefore the evacuation of calories. As a reminder, the hollow of the flexibility zone (circumferential grooves, such as 55a) makes it possible to reduce the stiffness of the pivot to reduce the misalignment between the active surface of the bearing and its bearings. However, the need for flexibility is not necessary in all directions, it is therefore possible to limit the extent of the flexibility zone in places with high heating, in order to increase the conduction and therefore decrease the temperature overall on the outer circumferential surface 8,80.
    This led the inventors to imagine the following approach methodology to which the invention moreover relates:
    First, they determined by a TEHD model and on a pivot such as that referenced 50, temperature fields such as 63a, 63b, this at least at the location of at least one of the side parts in carrier overhang 57a, 57b.
    Then, they identified at this (or each) location, at least one area that the TEHD model indicated as the area (s) of the highest temperature (s), as in 630a, 630b figure 5.
    Then they intervened on the pivot 5 of the invention so that it is manufactured with at least one of the lateral parts 27a, 27b in cantilever hollowed out by at least one recess 65a (FIGS. 6-7), 65a, 65b Figure 8;
    see part 27a interrupted locally in the common example of FIGS. 6-7 and opposite parts interrupted locally 27a, 27b in the other example of FIG. 8.
    A recess area turns out to be an area with little stress. It is therefore not or little annoying that such hollows exist. The absence of material does not (notably) affect guidance by the staves.
    Before detailing this modification, it will further be noted in FIG. 6 that, apart from the recess for the groove 25a, each circumferential groove 25a, 25b present (which could also be observed on the pivot 50 of the art anterior or that of FIG. 6) a free lateral end, resp. 250a, 250b, located at the corresponding free end of the cantilevered lateral part 27a or 27b considered.
    Each circumferential groove also has:
    - at least one depth P, in a direction (such as D in FIG. 9 for the groove 25a) in which the circumferential groove extends towards the inside of the pivot, from the free lateral end (such that therefore 250a) to at a bottom end, such as 33a (see also item 33b for the groove 25b),
    - and at least one width I (which can be considered as a section, or a diameter depending on the shape of the groove).
    Approximately, the direction (such as D) in which a circumferential groove extends is axial (parallel to the axis X1). More finely, we note a radial inclination of a few degrees inward.
    Be that as it may, the modification which leads to the solution of the invention therefore comprises a manufacture of the pivot 5 such that at least one recess 65a, 65b has been created at (the) (l) 'location ( s) indicated, via the TEHD model, as the zone (s), such as 630a and / or 630b, of the highest temperature or temperatures in said at least one cantilevered side part .
    As soon as in operation, operational planetary gear (gears able to rotate), the lubricant is supposed to flow in the direction S, out of the passage 29, on the radially external circumferential surface 8, said at least one recess 65a, 65b will be favorably adjacent to this slot and then located angularly on the side opposite to that towards which the lubricant flows (direction S) leaving the passage 29; see two examples in Figures 7 and 8.
    In order to further promote heat transfer and efficiency in the anti-misalignment effect, it is furthermore advised that the aforementioned pivot is a single piece, with its cantilevered lateral parts 27a, 27b and its central shaft 23 in one piece.
    As soon as the zone (s), such as 630a and / or 630b, of the highest temperatures are (are) likely to be located, it is foreseeable that, on the lateral side concerned with the recess 65a and / or 65b, the corresponding cantilever side portion 27a and / or 27b is circumferential but not annular, as illustrated in FIGS. 6-8. Thus, we can at best combine control of overheating and alignment.
    In this regard, the or each recess 65a, 65b will extend favorably over at least 10% of the circumference of the pivot and / or of said depth (P) of the circumferential groove 25a, 25b considered.
    In a first version, the pivot 5 may comprise a recess 65a or 65b only on one axial side of the pivot, here at the end, as in FIG. 7.
    However, it is more likely that, as in a second version shown in FIG. 8, the pivot 5 comprises at least two recesses 65a and 65b, on the two axial sides of the pivot.
    Planetary gear train of a gas turbomachine for aircraft, comprising an outer ring (3) and planet gears (4) engaged with the central pinion (2) and with the outer ring (3) and each mounted freely in rotation on a planet carrier (6), the planet gears (4) each capable of rotating about a satellite axis (X) via a pivot (5) according to any one of claims 1 to
    5.
    FIG. 9 again shows diagrammatically the case of an assembly of pivots 5 in an epicyclic configuration, therefore in a case where the central pinion 2 is movable, but the outer crown 3 fixed, integral with an outer casing, or of an annular, static ferrule 26 of the compressor 16, in particular of the low pressure compressor 16a. As illustrated, forces both tangent ET due to the applied torques, and radial ER, due to centrifugal force, are exerted on each pivot 5.
    In FIG. 10, another application case is shown diagrammatically, that of an assembly of pivots 5 in a planetary configuration, therefore in a case where both the central pinion 2 and the outer ring 3 are movable in rotation around the axis X of the compressor 16a, in particular of the low pressure compressor. As illustrated, tangential forces ET, due to the applied torques, are exerted on each pivot 5. This situation can be that of an open-rotor or of a double blower.
    In FIG. 11, solutions with planetary gear trains are compared in which:
    - at the top, we are in a solution with mobile planet carrier and fixed crown,
    - at the bottom, the gear train is such that the planet carrier 6 is fixed (opposite a casing, or an annular ferrule, static 28) and the outer ring is mobile (also called a train solution planetary reducer).
    In connection with certain previous figures, there is in common a planet carrier 6, an internal sun gear 2 and an external sun gear, here in two half-rings 3a, 3b respectively upstream and downstream with respect to the axis of rotation X. The internal sun gear 2 is engaged with the axial shaft 24, the shaft of the low pressure compressor in the example. Bearings 71, 73 support and guide the blower 12 axially.
    In the solution at the top, via an upstream axial extension 75 supported and guided by the bearings 71,73, the planet carrier 6 is engaged with the fan 12 and a fixed crown carrier 80 is attached, linked here to the half crown 3a upstream.
    In the solution at the bottom, it is the external sun gear (half-crowns 3a, 3b) which, via an upstream axial extension 77 supported and 5 guided by the bearings 71,73, is engaged with the blower 12. The satellite carriers 6 is fixed (link 79).
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Pivot (5) for plain bearing of gear train, the pivot presenting:
    - a part (23) forming a central barrel, extending around an axial passage (15) of the pivot, and
    - axially opposite circumferential grooves (25a, 25b), open laterally, which radially separate, from two cantilevered lateral parts (27a, 27b) of the pivot, two axially opposite lateral end parts (230a, 230b) of the central barrel ( 23), characterized in that at least one of the lateral cantilevered parts is hollowed out by at least one recess (65a, 65b).
    [2" id="c-fr-0002]
    2. Pivot (5) according to claim 1, which is in one piece, with its central shaft (23) and its cantilevered side parts (27a, 27b) in one piece.
    [3" id="c-fr-0003]
    3. Pivot (5) according to any one of the preceding claims, in which, on the lateral side of said at least one recess (65a, 65b), said cantilevered lateral part (27a, 27b) is circumferential but not annular .
    [4" id="c-fr-0004]
    4. Pivot (5) according to any one of the preceding claims, in which, on the lateral side of said at least one recess:
    - the circumferential groove (25a, 25b) has, at a distance from said at least one recess, at least one depth (P) in a direction in which the circumferential groove extends towards the inside of the pivot, from a lateral end free (250a, 250b) of said cantilevered side part (27a, 27b), up to a bottom end (33a) of said circumferential groove (25a, 25b), and
    - Said at least one recess (65a, 65b) extends over at least 10% of the circumference of the pivot and / or of said depth (P) of the circumferential groove (25a, 25b).
    [5" id="c-fr-0005]
    5. Pivot (5) according to any one of the preceding claims, characterized in that it comprises at least two recesses (65a, 65b) hollowed out respectively in one and the other of the two lateral parts in door-to-door false.
    [6" id="c-fr-0006]
    6. Gear train of a gas turbomachine for aircraft, comprising an outer ring (3) and planet gears (4) engaged with the central pinion (2) and with the outer ring (3) and each mounted free in rotation on a planet carrier (6), the planet gears (4) each being able to rotate around a satellite axis (X) by means of a pivot (5) according to any one of claims 1 to
    5.
    [7" id="c-fr-0007]
    7. Gear train (1) according to claim 6, further comprising means (13,14) for supplying oil at an interface (9) between one of said planet gears (4) and said pivot (5), characterized in that said pivot (5) has a radially outer circumferential surface (8) which has a passage (29) for supplying a lubricating liquid, said at least one recess being adjacent to the passage (29) and being located angularly on the side opposite to that towards which the lubricant flows (direction S) on the radially outer circumferential surface (8) when the gear train can rotate.
    [8" id="c-fr-0008]
    8. A gas turbomachine for an aircraft comprising a gear train according to claim 6 or 7, the central pinion (2) of which surrounds and is rotatably connected to a shaft (24) of the compressor of the turbomachine.
    [9" id="c-fr-0009]
    9. A turbomachine according to claim 8, in which the outer ring (3) is integral with a housing or with a static annular ferrule (26) of the low pressure compressor (16a).
    [10" id="c-fr-0010]
    10. A turbomachine according to claim 8, in which the planet carrier (6) is integral with a housing or with an annular, static ferrule (28).
    [11" id="c-fr-0011]
    11. A method of producing a pivot (5) according to any one of claims 1 to 5, an outer circumferential surface (8) of said pivot having a slot for supplying a lubricating liquid, so that the liquid flows over a circumferential side of said outer circumferential surface (8) when it leaves the feed slot, in which process:
    - a TEHD model determines the temperature fields of the pivot at least at the location of at least one of the cantilevered lateral parts,
    - we identify at this location at least one area that the TEHD model indicates 10 as the area with the highest temperature (s), then
    - A recess is created in the said zone in the said at least one cantilevered side part.
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    同族专利:
    公开号 | 公开日
    CN111094792A|2020-05-01|
    US11041562B2|2021-06-22|
    EP3682141A1|2020-07-22|
    US20200271217A1|2020-08-27|
    FR3071025B1|2021-02-12|
    WO2019053374A1|2019-03-21|
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    US9982771B2|2014-12-01|2018-05-29|United Technologies Corporation|Lightweight and compliant journal pin|
    US10494998B2|2017-01-30|2019-12-03|United Technologies Corporation|Lubrication of epicyclic gear system for gas turbine engine|
    US10851671B2|2019-03-29|2020-12-01|Pratt & Whitney Canada Corp.|Bending stiffening feature used for compliant journal bearing|
    法律状态:
    2019-03-15| PLSC| Search report ready|Effective date: 20190315 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1758422A|FR3071025B1|2017-09-12|2017-09-12|PIVOT FOR SLIDING BEARINGS AND REDUCED THERMAL STRESS GEAR TRAIN|
    FR1758422|2017-09-12|FR1758422A| FR3071025B1|2017-09-12|2017-09-12|PIVOT FOR SLIDING BEARINGS AND REDUCED THERMAL STRESS GEAR TRAIN|
    PCT/FR2018/052237| WO2019053374A1|2017-09-12|2018-09-12|Pivot for a plain bearing and gearset with reduced thermal stress|
    EP18782117.8A| EP3682141A1|2017-09-12|2018-09-12|Pivot for a plain bearing and gearset with reduced thermal stress|
    US16/646,646| US11041562B2|2017-09-12|2018-09-12|Pivot for a plain bearing and gearset with reduced thermal stress|
    CN201880059164.8A| CN111094792A|2017-09-12|2018-09-12|Pivot of sliding bearing and gear set with reduced thermal stress|
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