• 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 an assembly (1) for a turbomachine comprising: A first rotor module (2) comprising a first blade (20), A second rotor module (3), connected to the first rotor module (2), and comprising a second blade of length less than the first blade (20), and • a damping device (4) comprising a first surface (41) bearing against the first module (2) as well as a second surface (42) bearing against the second module (3), so as to couple the modules (2 , 3) in order to dampen their respective vibratory movements in operation.
    公开号:FR3075282A1
    申请号:FR1762170
    申请日:2017-12-14
    公开日:2019-06-21
    发明作者:Gerard Edmond Joly Philippe；Jean Comin Francois；Jean-Pierre Douguet Charles；Laurent Jablonski；Nicolas Lagarde Romain；Claude Perrollaz Jean Marc
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The invention relates to an assembly comprising a turbomachine rotor module.
    The invention relates more specifically to an assembly for a turbomachine comprising two rotor modules and a damping device.
    STATE OF THE ART
    A turbomachine rotor module generally comprises one or more stages, each stage comprising a disc centered on a longitudinal axis of the turbomachine, corresponding to the axis of rotation of the rotor module. The rotation of the disc is generally ensured by a rotary shaft to which it is integrally connected, for example by means of a rotor module journal, the rotary shaft extending along the longitudinal axis of the turbomachine. Blades are mounted on the outer periphery of the disc, and distributed circumferentially, evenly around the longitudinal axis. Each blade extends from the disc, and further includes a blade, a platform, a stilt, and a stand. The foot is embedded in a disc housing configured for this purpose, the blade is swept by a flow passing through the turbomachine, and the platform forms a portion of the internal surface of the flow stream.
    The operating range of a rotor module is limited, in particular due to aeroelastic phenomena. The rotor modules of modern turbomachinery, which have a high aerodynamic load, and a reduced number of blades, are more sensitive to this type of phenomenon. In particular, they have reduced margins between the unstable operating zones and the unstable zones. It is nevertheless imperative to guarantee a sufficient margin between the stability and instability domains, or to demonstrate that the rotor module can operate in the instability zone without exceeding its endurance limit. This makes it possible to guarantee risk-free operation throughout the entire life and the entire operating range of the turbomachine.
    The operation in the instability zone is characterized by a coupling between the fluid and the structure, the fluid bringing energy to the structure, and the structure responding in its own modes at levels which can exceed the endurance limit of the material. constituting dawn. This generates vibrational instabilities which accelerates the wear of the rotor module, and decreases its lifespan.
    In order to limit these phenomena, it is known to set up a system damping the dynamic response of the blade, in order to guarantee that it does not exceed the limit of endurance of the material whatever the operating point of the module. rotor. However, most of the known systems of the prior art endeavor to dampen modes of vibration with non-zero phase shift, and characterizing an asynchronous response of the blades to aerodynamic stresses. Such systems have for example been described in the documents FR 2 949 142, EP 1 985 810 and FR 2 923 557, in the name of the Applicant. These systems are all configured to be housed between the platform and the base of each blade, in the housing delimited by the respective stilts of two successive blades. Furthermore, such systems operate when two successive blade platforms move relative to each other, by dissipation of the vibration energy, for example by friction.
    However, these systems are totally ineffective in damping the modes of vibration having zero phase shift involving the blades and the rotor line, that is to say its rotary shaft. Such modes are characterized by a bending of the rotor blades with a zero inter-blade phase shift involving a non-zero moment on the rotary shaft. In addition, it is a coupled mode between the blade, the disc, and the rotating shaft. More specifically, the torsion within the rotor module, resulting for example from reverse forces between a turbine rotor and a compressor rotor, result in bending movements of the blades relative to their attachment to the disc. These movements are all the more important as the dawn is large, and the attachment is flexible.
    There is therefore a need for a damping system for a turbomachine rotor making it possible to limit the instabilities generated by all the vibration modes as previously described.
    SUMMARY OF THE INVENTION
    An object of the invention is to dampen the modes of vibration having zero phase shift for all types of turbine engine rotor modules.
    Another object of the invention is to influence the damping of non-zero phase shift vibration modes, for all types of turbine engine rotor modules.
    Another object of the invention is to provide a simple and easy to implement depreciation solution.
    The invention notably proposes an assembly for a turbomachine comprising:
    • a first rotor module comprising a first blade, • a second rotor module, connected to the first rotor module, and comprising a second blade of length less than the first blade, and • a damping device comprising a first surface bearing against the first module as well as a second surface bearing against the second module, so as to couple the modules in order to dampen their respective vibratory movements in operation.
    The mechanical coupling between the first and the second rotor module makes it possible to increase the tangential rigidity of the connection between these two rotors, while allowing a certain axial and radial flexibility of the damping device in order to maximize the contact between the various elements of the together. This makes it possible to limit the instabilities linked to the zero phase shift vibration mode, but also to participate in the damping of the non-zero phase shift vibration modes. In addition, such an assembly has the advantage of easy integration into existing turbomachinery, whether during manufacture or during maintenance.
    The assembly according to the invention may also include the following characteristics taken alone or in combination:
    the first rotor module comprises a disc centered on a longitudinal axis of the turbomachine, the first blade being mounted on the external periphery of the disc from which it extends, and further comprising a blade, a platform, a stilt and a foot embedded in a disc housing, and the second module comprises a ferrule comprising a circumferential extension extending towards the platform of the first blade, the first surface of the damping device being in abutment on an internal surface of the platform of the first blade, the second surface of the damping device bearing against the circumferential extension of the shell of the second rotor module,
    - the damping device comprises a first sacrificial plate housed at the level of the first and the second surface, the first plate being configured to guarantee the support of said surfaces,
    the first plate comprises a coating configured to reduce the friction between said plate and the rotor modules, the coating comprising a material chosen from teflon and vespel,
    the first wafer comprises a viscoelastic type coating,
    the damping device comprises bores configured to lighten the mass of the damping device,
    the damping device comprises inserts, for example of the metallic type, configured to make the damping device heavier,
    - the damping device comprises two shoulders on either side of a notch formed at the internal surface of the damping device, the shoulders being in abutment against the shell,
    - It further comprises a fixing lug connected on the one hand to the damping device, and on the other hand to the connection between the first and the second rotor module, so as to ensure anti rotation, as well as the axial stop and radial of the damping device,
    the fixing lug comprises a second sacrificial plate housed at the level of the external surface of the fixing lug, the second plate being configured to increase the tangential stiffness of the damping device,
    - the fixing lug is connected to the damping device at the level of the notch,
    - the indentation includes a third sacrificial plate on which the fixing lug is supported, and
    - The first module is a blower, and the second module is a compressor, for example a low pressure compressor.
    The invention also relates to a turbomachine comprising an assembly as previously described.
    The invention further relates to a damping device comprising a first surface and a second surface configured to be respectively in abutment against a first module and a second module of an assembly as previously described, so as to couple the modules in view of '' dampen their respective vibratory movements during operation.
    The invention finally relates to a damping system comprising a damping device as previously described, and a fixing lug connected on the one hand to the damping device, and on the other hand to the connection between the first and the second rotor module of an assembly as previously described, so as to ensure the anti-rotation, as well as the axial and radial stopping of the damping device.
    QUICK DESCRIPTION OF THE FIGURES
    Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows and with reference to the appended drawings given by way of non-limiting example and in which:
    FIG. 1 is a schematic sectional view of an exemplary embodiment of the assembly according to the invention,
    FIG. 2 is a front view of a rotor module subjected to tangential vibrations, the mode of which is at zero phase shift,
    FIG. 3a diagrammatically illustrates tangential displacements of turbine engine rotor modules, as a function of the position of said modules along a turbomachine axis,
    FIG. 3b is a schematic perspective enlargement of the interface between two turbine engine rotor modules illustrating its relative tangential displacements of said rotor modules,
    FIG. 4a schematically illustrates a first exemplary embodiment of a damping device according to the invention,
    FIG. 4b schematically illustrates a second exemplary embodiment of a damping device according to the invention, and
    - Figure 4c schematically illustrates a third embodiment of a damping device according to the invention.
    DETAILED DESCRIPTION OF THE INVENTION
    An embodiment of an assembly 1 according to the invention will now be described, with reference to the figures.
    With reference to FIGS. 1 and 3a, such an assembly 1 comprises:
    a first rotor module 2 comprising a first blade 20,
    a second rotor module 3, connected to the first rotor module 2, and comprising a second blade 30 of length less than the first blade 20, and
    a damping device 4 comprising a first surface 41 bearing against the first module 2 as well as a second surface 42 bearing against the second module 3, so as to couple the modules 2, 3 with a view to damping their respective vibratory movements Operating.
    With reference to FIGS. 1 and 3a, the first rotor module is a blower 2, and the second rotor module is a low pressure compressor 3, located immediately downstream of the blower 2.
    The fan 2 and the low pressure compressor 3 comprise a disc 21, 31 centered on a longitudinal axis XX of the turbomachine, the first 20 and the second blade 30 being respectively mounted at the external periphery of the disc 21, 31, and further comprising a blade 23, 33, a platform 25, 35 a stilt 27, 37 and a foot 29, 39 embedded in a housing 210, 310 of the disc 21, 31. The distance separating the foot 29, 39 from the end of the blade 23 , 33 constitutes the respective lengths of the first 20 and of the second blade 30. The length of the first blade 20 and second blade 30 is therefore here considered to be substantially radially with respect to the longitudinal axis XX of rotation of the rotor modules 2, 3. In operation, the blade 23, 33 is swept by a flow 5 passing through the turbomachine, and the platform 25, 35 forms a portion of the internal surface of the flow stream 5. In general, as shown in FIG. 2 and 3a, blower 2 nd t low pressure compressor 3 include a plurality of vanes 20, 30 distributed circumferentially around the longitudinal axis X-X. The low pressure compressor 3 further comprises an annular ferrule 32 also centered on the longitudinal axis X-X. The ferrule 32 includes a circumferential extension 34, also annular, extending towards the platform 25 of the first blade 20. This annular extension 34 carries radial sealing wipers 36 configured to prevent losses of air flow from the flow stream 5. In addition, the ferrule 32 is fixed to the fan disc 21 of fan 2 by means of fasteners 22 distributed circumferentially around the longitudinal axis XX. Such fasteners can for example be bolted connections 22. Alternatively, such fasteners 22 can be made by shrinking with which is associated an anti-rotation device and / or an axial locking system. Finally, with reference to FIG. 3a, the assembly formed by the blower 2 and the compressor 3 is rotated by a rotary shaft 6, called a low pressure shaft, to which blower 2 and low pressure compressor 3 are integrally connected, by means a rotor journal 60, the low pressure shaft 6 also being connected to a low pressure turbine 7, downstream of the turbomachine, and extending along the longitudinal axis XX of the turbomachine.
    In operation, the blower 2 sucks in air, all or part of which is compressed by the low pressure compressor 3. The compressed air then circulates in a high pressure compressor (not shown) before being mixed with fuel, then ignited within the combustion chamber (not shown), to finally be successively expanded in the high turbine (not shown) and the low pressure turbine 7. The opposite compressive forces upstream, and expansion downstream, give rise to aeroelastic floating phenomena, which couple the aerodynamic forces on the blades 20, 30, and the vibration movements in bending and torsion in the blades 20, 30. As illustrated in FIG. 2, This floating causes in particular intense torsional forces within of the low pressure shaft 6 which are passed on to the blower 2 and to the low pressure compressor 3. The blades 20, 30 are then subjected to tangential beats, note even in a zero-phase vibration mode. It is indeed a mode of bending with an inter-blade phase shift 20, 30 zero, implying a non-zero moment on the low pressure shaft 6, the natural frequency of which is approximately one and a half times greater than that of first vibration harmonic, the deformation of which has a nodal line halfway up the blade 20, 30. Such vibrations limit the mechanical strength of the fan 2 and of the low pressure compressor 3, accelerate the wear of the turbomachine , and decreases its lifespan.
    As can be seen in FIG. 3a, the tangential displacement by floating of the blade 20 of the fan 2 is different from that of the shell 32 of the low pressure compressor 3. In fact, the length of the blades 20 of the fan 2 being greater than that of the blades 30 of low pressure compressor 3, the tangential bending moment caused by the beats of a fan 20 blade 2 is much greater than that caused by the beats of a blade 30 of low pressure compressor 3. In addition, the stiffness mounting within the blower 2 is different from that of mounting within the compressor 3. With reference to FIG. 3b, this difference in tangential beats is notably visible at the interface between the platform 25 of a blade 20 of the blower 2, and sealing wipers 36 for ferrule 32.
    In a first embodiment illustrated in FIG. 1, the damping device 4 is housed under the platform 25 of a fan blade 20, between the stilt 27 and the ferrule 32 of the low pressure compressor 3. All or part of the fan 20 blades 2 can be fitted with such a damping device 4, depending on the desired damping, but also the acceptable maintenance characteristic times.
    The first surface 41 is external to the damper device 4, and in abutment against the fan 2 at the level of the internal surface 250 of the platform 25 of the fan blade 2, and the second face 42 is also external to the damper device 4, and in abutment against the circumferential extension 34 of the shell 32. This ensures a tangential coupling of considerable stiffness between the fan 2 and the low pressure compressor 3, so as to reduce the tangential vibrations described above. The coupling is moreover all the more important as the zone within which the damping device 4 is arranged has the highest relative tangential displacements for the zero phase shift mode considered, as illustrated in FIGS. 3a and 3b. Typically, these relative displacements are of the order of a few millimeters. However, the damping device 4 also advantageously retains an effectiveness on the vibratory modes of the fan blades 2 with non-zero phase shift.
    In a second embodiment, still with reference to FIG. 1, the assembly 1 comprises a fixing lug 8 connected on the one hand to the damping device 4, and on the other hand to the connection between the blower 2 and the compressor low pressure 3, so as to ensure anti-rotation, as well as the axial and radial stopping of the damping device 4. Taking into account the mechanical stresses already described, it is indeed necessary to ensure stability, in particular axial and radial , of the damping device 4 within the assembly 1 in operation.
    Advantageously, the fixing lug 8 is fixed to the connection between blower 2 and low pressure compressor 3 at the level of the bolted connection 22 between disc and ferrule 32.
    The fixing lug 8 can also be interposed between two circumferentially adjacent damping devices 4, and fixed to the latter, for example by screwing. Alternatively, the fixing lug 8 can be fixed to the damping devices 4 by any other fixing means known to those skilled in the art.
    The assembly 1 may also include two fixing lugs 8, fixed on each side of the damping device 4, for example by screwing. Alternatively, the fixing lugs 8 can be fixed to the damping devices 4 by any other fixing means known to those skilled in the art.
    As the fixing lug 8 may prove to be too flexible tangentially, the assembly 1 may also comprise a second sacrificial plate 80 housed at the level of the external surface 81 of the fixing lug 8, the second plate 80 being configured to increase the tangential stiffness of the damping device 4. The second sacrificial plate 80 also has the same characteristics as the first sacrificial plate 40, in particular as regards the composition, lubrication and additional coatings.
    In a third embodiment illustrated in FIGS. 4a to 4c, the damping device 4 comprises a first sacrificial plate 40 housed at the level of the first 41 and the second 42 bearing surface. This first plate 40 is configured to guarantee the support of the surfaces 41, 42 of the damping device 4 on the fan 2 and the low pressure compressor 3. In fact, the mechanical stresses in operation are such that slight tangential, axial and radial movements of the damping device 4 are to be expected. These movements are notably due to the tangential beats to be damped, but also to the centrifugal loading of the assembly 1. It is necessary that these movements do not wear the blades 20 or the ferrule 32, the coatings of which are relatively fragile. In this regard, the first sacrificial plate 40 comprises an anti-wear material, for example of the Teflon type or any specific composite material known to those skilled in the art. In addition, the first sacrificial plate 40 can be treated by dry lubrication, in order to perpetuate the value of the coefficient of friction between damping device 4 and ferrule 32 and / or blade platform 2. This material with lubricating properties is MoS2 type example.
    In order to improve the support of the damping device 4, the first sacrificial plate 40 may also include an additional coating 44, as visible in FIG. 4b. Generally, such a coating 44 is configured to reduce the friction and / or wear of the engine parts between the first plate 40 and the rotor modules 2, 3.
    This coating 44 is for example of the viscoelastic type. Such a coating 44 then advantageously comprises a material having properties similar to those of a material such as those of the range having the trade name "SMACTANE®", for example a material of the "SMACTANE® 70" type. Another way to increase the tangential stiffness of the assembly 1 is to sufficiently prestress the viscoelastic coating 44 so that the relative tangential displacement between blade 20 and ferrule 32 is transformed into viscoelastic shear of the coating 44 alone.
    Alternatively, this coating 44 is of the dissipative and / or viscoelastic and / or damping type. The dissipative coating 44 then comprises a material chosen from those having mechanical properties similar to those of vespel, teflon or any other material with lubricating properties. More generally, the material has a coefficient of friction between 0.3 and 0.07. Too much flexibility would not dampen the zero phase shift mode, since the relative displacements of the fan 2 and of the low pressure compressor 3 would lead to friction and / or oscillations between a “glued” state and a “slippery” state of the damping device 4.
    These additional coatings 44 are added by bonding to the first sacrificial plate 40.
    In a fourth embodiment illustrated in FIG. 4c, the damping by tangential coupling can be adjusted by controlling the mass of the damping device 4, which influences the inertia in shear. This control involves modifications of the mass of the damping device 4. This mass can be modified in all or part of the damping device 4, typically by making bores 45 to lighten, and / or by adding one or more inserts 46, for example metallic, to weigh down.
    Advantageously, the combination of the second and the third embodiment makes it possible to adjust the contact forces between the damping device 4 and the fan 2 as well as the low pressure compressor 3. Indeed, too high contact forces between the blade 20 of fan 2 and the damping device 4 would limit the dissipation of vibrations during operation.
    In a fifth embodiment illustrated in FIGS. 4a to 4c, the damping device 4 comprises two shoulders 47 on either side of a notch 48 formed at the internal surface 49 of the damping device
    4, the shoulders 47 being in abutment against the ferrule 32 or, where appropriate against the shank 27. This internal abutment of the damping device 4 on the ferrule 32 notably guarantees radial stability.
    In addition to the second embodiment, the fixing lug 8 can then be connected to the damping device 4 at the level of the notch 48 separating the two shoulders 47. In this case, as visible in FIG. 4c, the notch 48 can comprise a third sacrificial plate 480 on which the fixing lug 8 is supported, ensuring functions equivalent to those of the first sacrificial plate 40, and having the same characteristics, in particular with regard to the composition, the lubrication and the additional coatings .
    Different embodiments of the assembly 1 according to the invention have been described in the case where the first rotor module 2 is a blower, and the second rotor module 3 is a low pressure compressor.
    This is not, however, limiting, since the first rotor module 2 can also be a first compressor stage, high or low pressure, and the second rotor module 3 a second stage of said compressor, successive to the first compressor stage, upstream or downstream of the latter. Alternatively, the first rotor module 2 is a first turbine stage, high or low pressure, and the second rotor module 3 a second stage of said turbine, successive to the first turbine stage, upstream or downstream of the latter.
    权利要求:
    Claims (16)
    [1" id="c-fr-0001]
    1. Assembly (1) for a turbomachine comprising:
    • a first rotor module (2) comprising a first blade (20), • a second rotor module (3), connected to the first rotor module (2), and comprising a second blade (30) of length less than the first blade ( 20), and • a damping device (4) comprising a first surface (41) bearing against the first module (2) and a second surface (42) bearing against the second module (3), so as to couple the modules (2, 3) in order to dampen their respective vibratory movements in operation.
    [2" id="c-fr-0002]
    2. An assembly (1) according to claim 1, in which:
    • the first rotor module (2) comprises a disc (21) centered on a longitudinal axis (XX) of the turbomachine, the first blade (20) being mounted on the external periphery of the disc (21) from which it extends, and comprising furthermore a blade (23), a platform (25), a stilt (27) and a foot (29) embedded in a housing (210) of the disc (21), and • the second module (3) comprises a ferrule ( 32) comprising a circumferential extension (34) extending towards the platform (25) of the first blade (20), the first surface (41) of the damping device (4) being in abutment on an internal surface (250) of the platform (25) of the first blade (20), the second surface (42) of the damping device (4) being in abutment against the circumferential extension (34) of the ferrule (32) of the second rotor module (3).
    [3" id="c-fr-0003]
    3. An assembly (1) according to claim 1 or 2, in which the damping device (4) comprises a first sacrificial plate (40) housed at the level of the first (41) and of the second (42) surface, the first plate (40) being configured to guarantee the support of said surfaces (41, 42).
    [4" id="c-fr-0004]
    4. An assembly (1) according to claim 3, in which the first plate (40) comprises a coating (44) configured to reduce the friction between said first plate (40) and the rotor modules (2, 3), the coating ( 44) comprising a material chosen from teflon and vespel.
    [5" id="c-fr-0005]
    5. The assembly (1) according to claim 3, wherein the first plate (40) comprises a coating (44) of viscoelastic type.
    [6" id="c-fr-0006]
    6. An assembly (1) according to one of claims 1 to 5, in which the damping device (4) comprises bores (45) configured to lighten the mass of the damping device (4).
    [7" id="c-fr-0007]
    7. An assembly (1) according to one of claims 1 to 6, in which the damping device (4) comprises inserts (46), for example of metallic type, configured to make the damping device (4) heavier.
    [8" id="c-fr-0008]
    8. An assembly (1) according to one of claims 1 to 7, wherein the damping device (4) comprises two shoulders (47) on either side of a notch (48) formed at a surface internal (49) of the damping device (4), the shoulders (47) being in abutment against the ferrule (32).
    [9" id="c-fr-0009]
    9. Assembly (1) according to one of claims 1 to 8, further comprising a fixing lug (8) connected on the one hand to the damping device (4), and on the other hand to the connection between the first ( 2) and the second rotor module (3), so as to ensure anti-rotation, as well as the axial and radial stopping of the damping device (4).
    [10" id="c-fr-0010]
    10. The assembly (1) according to claim 9, wherein the fixing lug (8) comprises a second sacrificial plate (80) housed at an external surface (81) of the fixing lug (8), the second plate (80) being configured to increase the tangential stiffness of the damping device (4).
    [11" id="c-fr-0011]
    11. Assembly (1) according to one of claims 9 or 10, taken in combination with claim 8, in which the fixing lug (8) is connected to the damping device (4) at the level of the notch (48) .
    [12" id="c-fr-0012]
    12. The assembly (1) according to claim 11, wherein the notch (48) comprises a third sacrificial plate (480) on which the fixing lug (8) is supported.
    [13" id="c-fr-0013]
    13. An assembly (1) according to one of claims 1 to 12, wherein the first module (2) is a blower, and the second module (3) is a low pressure compressor.
    [14" id="c-fr-0014]
    14. Turbomachine comprising an assembly (1) according to one of claims 1 to 13.
    [15" id="c-fr-0015]
    15. Damping device (4) comprising a first surface (41) and a second surface (42) configured to be respectively in abutment against a first module (2) and a second module (3) of an assembly (1) according to l 'one of claims 1 to 13, so as to couple the modules (2, 3) in order to dampen their respective vibratory movements in operation.
    [16" id="c-fr-0016]
    16. damping system comprising a damping device (4) according to claim 15, and a fixing lug (8) connected on the one hand to the damping device (4), and on the other hand to the connection between the first (2) and the second rotor module (3) of an assembly (1) according to one of claims 1 to 13, so as to ensure anti-rotation, as well as the axial and radial stopping of the damping device
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    同族专利:
    公开号 | 公开日
    WO2019115977A1|2019-06-20|
    EP3724455A1|2020-10-21|
    FR3075282B1|2021-01-08|
    CN111630249A|2020-09-04|
    US20210079794A1|2021-03-18|
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    法律状态:
    2018-11-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-06-21| PLSC| Publication of the preliminary search report|Effective date: 20190621 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1762170|2017-12-14|
    FR1762170A|FR3075282B1|2017-12-14|2017-12-14|SHOCK ABSORBER|FR1762170A| FR3075282B1|2017-12-14|2017-12-14|SHOCK ABSORBER|
    GB1820365.3A| GB2571176A|2017-12-14|2018-12-13|Damping device|
    US16/219,823| US10927683B2|2017-12-14|2018-12-13|Damping device|
    EP18836279.2A| EP3724455A1|2017-12-14|2018-12-14|Damper device|
    PCT/FR2018/053302| WO2019115977A1|2017-12-14|2018-12-14|Damper device|
    CN201880086692.2A| CN111630249A|2017-12-14|2018-12-14|Damping device|
    US16/954,007| US20210079794A1|2017-12-14|2018-12-14|Damping device|
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