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EP3728794B1 - Dämpfervorrichtung - Google Patents

Dämpfervorrichtung Download PDF

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Publication number
EP3728794B1
EP3728794B1 EP18833974.1A EP18833974A EP3728794B1 EP 3728794 B1 EP3728794 B1 EP 3728794B1 EP 18833974 A EP18833974 A EP 18833974A EP 3728794 B1 EP3728794 B1 EP 3728794B1
Authority
EP
European Patent Office
Prior art keywords
damping device
assembly
external surface
module
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP18833974.1A
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English (en)
French (fr)
Other versions
EP3728794A1 (de
Inventor
Philippe Gérard Edmond JOLY
François Jean Comin
Charles Jean-Pierre Douguet
Laurent Jablonski
Romain Nicolas LAGARDE
Jean-Marc Claude Perrollaz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from FR1762358A external-priority patent/FR3075284B1/fr
Priority claimed from FR1762545A external-priority patent/FR3075254B1/fr
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3728794A1 publication Critical patent/EP3728794A1/de
Application granted granted Critical
Publication of EP3728794B1 publication Critical patent/EP3728794B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • 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.
  • a turbomachine rotor module generally comprises one or more stage(s), each stage comprising a disk centered on a longitudinal axis of the turbomachine, corresponding to the axis of rotation of the rotor module.
  • the disk is generally rotated by a rotating shaft to which it is integrally connected, for example by means of a rotor module pin, the rotating shaft extending along the longitudinal axis of the turbomachine.
  • Vanes are mounted on the outer periphery of the disk, and distributed circumferentially, regularly around the longitudinal axis.
  • Each blade extends from the disc, and further includes a blade, a platform, a stilt and a foot. The foot is embedded in a housing of the disk 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 vein.
  • the operating range of a rotor module is limited, in particular because of aeroelastic phenomena.
  • the rotor modules of modern turbomachines which have a high aerodynamic load and a reduced number of blades, are more sensitive to this type of phenomena. In particular, they have reduced margins between operating zones without instability and unstable zones. It is nevertheless imperative to guarantee a sufficient margin between the stability domain and that of instability, 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 life and entire operating range of the turbomachine.
  • Operation in the instability zone is characterized by coupling between the fluid and the structure, the fluid providing energy to the structure, and the structure responding in its own modes to levels which may exceed the endurance limit of the material constituting the blade. This generates vibrational instabilities which accelerate the wear of the rotor module and shorten its lifespan.
  • An aim of the invention is to damp vibration modes with zero phase shift for all types of turbomachine rotor modules.
  • Another aim of the invention is to influence the damping of vibration modes with non-zero phase shift, for all types of turbomachine rotor modules.
  • Another aim of the invention is to propose a simple and easy to implement damping solution.
  • 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 different elements of the together.
  • This makes it possible to limit the instabilities linked to the vibration mode with zero phase shift, but also to participate in the damping of the vibration modes with non-zero phase shift.
  • such an assembly has the advantage of easy integration into existing turbomachines, whether during manufacturing or during maintenance.
  • the annular nature of the damping device makes it possible to reduce its size between the two motor modules.
  • the upstream and downstream are defined in relation to the direction of normal air flow through the turbomachine. Furthermore, a longitudinal axis X-X of the turbomachine is defined.
  • the axial direction corresponds to the direction of the longitudinal axis XX of the turbomachine
  • a radial direction is a direction which is perpendicular to this longitudinal axis XX of the turbomachine and which passes through said longitudinal axis XX of the turbomachine
  • a direction circumferential corresponds to the direction of a flat and closed curved line, all the points of which are equidistant from the longitudinal axis X-X of the turbomachine.
  • the terms “internal (or interior)” and “external (or exterior)”, respectively, are used in reference to a radial direction so that the internal part or face (i.e. radially internal) of 'an element is closer to the longitudinal axis X-X of the turbomachine than the part or the external face (i.e. radially external) of the same element.
  • the first rotor module is a fan 2
  • the second rotor module is a low pressure compressor 3, located immediately downstream of the fan 2.
  • the fan 2 and the low pressure compressor 3 comprise a disk 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 disk 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 the second blade 30.
  • the length of the first blade 20 and second blade 30 is therefore considered here as substantially radially relative to the longitudinal axis XX of rotation of the rotor modules 2, 3.
  • fan 2 and low pressure compressor 3 comprise a plurality of blades 20, 30 distributed circumferentially around the longitudinal axis XX.
  • the low pressure compressor 3 further comprises an annular shroud 32 also centered on the longitudinal axis XX.
  • the ferrule 32 comprises a circumferential extension 34, also annular, extending towards the platform 25 of the first blade 20. This annular extension 34 carries radial sealing lips 36 configured to prevent losses of air flow from the flow stream 5.
  • ferrule 32 is fixed to the disk 21 of fan 2 by means of fasteners 22 distributed circumferentially around the longitudinal axis XX.
  • fasteners 22 can for example be bolted connections 22.
  • fasteners 22 can be produced by shrink fit with which is associated an anti-rotation device and/or an axial locking system.
  • the assembly formed by the blower 2 and the compressor 3 is rotated by a rotating shaft 6, called a low pressure shaft, to which the blower 2 and the low pressure compressor 3 are integrally connected, by means of a rotor pin 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.
  • 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 opposing forces of compression 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 flexion and torsion in the blades 20, 30. As illustrated in figure 2 , this floating leads in particular to intense torsional forces within the low pressure shaft 6 which are passed on to the fan 2 and the low pressure compressor 3.
  • the blades 20, 30 are then subjected to tangential beating, in particular in a mode vibration with zero phase shift. It is in fact a bending mode with a zero inter-blade phase shift 20, 30, 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 harmonic of vibration, and whose deformation has a nodal line halfway up the blade 20, 30.
  • Such vibrations limit the mechanical strength of the fan 2 and the low pressure compressor 30, accelerate the wear of the turbomachine, and reduce its lifespan.
  • the tangential movement by floating of the blade 20 of the fan 2 is different from that of the shroud 32 of the low pressure compressor 3.
  • the length of the blades 20 of the fan 2 being greater than that of the blades 30 of the low pressure compressor 3
  • the tangential bending moment caused by the beating of blade 20 of fan 2 is much greater than that caused by the beating of blade 30 of low pressure compressor 3.
  • the mounting stiffness within the fan 2 is different from that of assembly within the compressor 3.
  • this difference in tangential beats is particularly visible at the interface between the platform 25 of a blade 20 of fan 2, and sealing lips 36 of ferrule 32.
  • the damping device 4 is housed under the platform 25 of a blade 20 of fan 2, between the stilt 27 and the shroud 32 of low pressure compressor 3.
  • the low pressure compressor 3 comprises an annular fixing shroud 38 , hooped onto the circumferential extension 34 of the ferrule 32 of the low pressure compressor 3.
  • the fixing ferrule 38 can be assembled to the circumferential extension 34 of the ferrule 32 via fixings such as those provided by radial fingers (not shown) belonging to said fixing ferrule 38 and screwed to said extension 34.
  • the lips 36 traditionally comprise substantially radial free sealing ends to face a stator.
  • the lips 36 include an annular root which connects these ends to the circumferential extension 34 of the ferrule 32.
  • the first external surface 40 bears with friction against the fan 2 at the level of the internal surface 250 of the platform 25 of the blade 20 of the fan 2, and the second external surface 42 bears with friction on the fixing shroud 38.
  • This ensures a tangential coupling of significant stiffness between blower 2 and low pressure compressor 3, so as to reduce the tangential vibrations previously described.
  • 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 figures 3a And 3b .
  • these relative displacements are of the order of a few millimeters.
  • the damping device 4 also advantageously maintains effectiveness on the vibration modes of the fan blades 20 2 with non-zero phase shift.
  • the damping device 4 is an annular tongue, the section of which is V-shaped.
  • the radially external surface 40 of the first branch 41 of the V forming the first surface 40 bearing with friction against the fan 2, the external surface 42 of the second branch 43 of the V forming the second external surface 42 bearing with friction against the low pressure compressor 3.
  • the tongue structure advantageously makes it possible to reduce the bulk of the damping device 4, within the assembly 1.
  • the V-shaped structure makes it possible to increase the contact surface between blower 2 and damper device 4 on the one hand, and between damper device 4 and low pressure compressor 3 on the other hand. This configuration therefore promotes the coupling between these two rotor elements, with a view to damping their vibratory movements.
  • the annular tongue 4 does not constitute a single-piece ring, but is split so as to define two ends 44, 46 facing each other.
  • 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 out the blades 20 or the shroud 32, the coverings of which are relatively fragile.
  • the bearing surfaces 40, 42 of the damping device can be treated by dry lubrication, with a view to perpetuating the value of the coefficient of friction between damping device 4 and low pressure compressor 3 and/or platform 25 of blade 20 This lubrication is for example of the MoS2 type.
  • the damping device 4 comprises, in a second embodiment, an additional coating 48, 49, as visible on the figure 5 , defining the support surfaces 40, 42.
  • a coating 48, 49 is configured to reduce friction and/or wear of the engine parts between the damping device 4 and the rotor modules 2, 3.
  • This coating 48, 49 is for example of the dissipative 48 and/or viscoelastic and/or damping type.
  • the dissipative coating 48 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 friction coefficient of between 0.3 and 0.07.
  • this coating 48, 49 is of the viscoelastic type 49.
  • a coating 49 then advantageously comprises a material having properties similar to those of a material such as those of the range having the commercial name "SMACTANEO", for example a “SMACTANEO 70” type material.
  • Another way of increasing the tangential stiffness of assembly 1 is to sufficiently prestress the viscoelastic coating 44, for example during assembly of assembly 1, so that the relative tangential displacement between blade 20 and shroud 32 transforms into shear. viscoelastic coating 44 alone.
  • These additional coverings 48, 49 are attached by gluing at the level of the bearing surfaces 40, 42.
  • the damping by tangential coupling can be adjusted by controlling the mass of the damping device 4, which influences the shear inertia.
  • This control involves modifications to 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 47, for example metal, to add weight.
  • controlling the mass of the damping device 4 makes it possible to adjust its effectiveness via the centrifugal forces that it experiences in operation.
  • This detail of construction with bores and/or insert can correspond to a third embodiment.
  • the combination of the second and 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 the fan 2 and the damping device 4 would limit the dissipation of vibrations in operation.
  • the damping device 4 is an annular cylinder, the section of which is diamond-shaped.
  • the diamond-shaped section is in fact denser than the V-shaped section, which makes it possible to increase the mechanical coupling between blower 2 and low pressure compressor 3, by promoting the tangential stiffness of the assembly 1.
  • the first external surface 40 bears with friction against the fan 2 at the level of the internal surface 250 of the platform 25 of the blade 20 of the fan 2, and the second external surface 42 also bears with friction on the radial sealing lips 36.
  • the bearing surfaces 40, 42 of the damping device 4, and the surfaces 250, 360 of the platform 25 and the radial sealing lips 36 are treated so as to guarantee their respective supports .
  • the treatment consists of a carbon-carbon deposit which ensures a high coefficient of friction, while limiting the wear of the surfaces 250, 360 of the platform 25 and the radial sealing lips 36. This support with friction is on the root of the wipers 36, that is to say at a distance from their free sealing ends.
  • the cylinder 4 does not constitute a single-piece ring, but is split so as to define two ends facing each other.
  • the damping device 4 comprises a dense material, preferably steel or a nickel-based alloy, so as to maximize the tangential stiffness of the coupling between the fan 2 and the low pressure compressor 3.
  • first rotor module 2 is a fan
  • second rotor module 3 is a low pressure compressor
  • 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.
  • 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.
  • the damper device 4 is arranged between the first rotor module 2 and the second rotor module 3 so that a first external surface 40 of the damper device 4 bears with friction against the first module 2, and that a second external surface 42 of the damping device 4 bears with friction against the second module 3.
  • the damping device 4 is pre-stressed against the first 2 and the second rotor module 3 so as to couple them with a view to damping their respective vibratory movements in operation.
  • Such an assembly method E is advantageously favored by the simple character resulting from the annular shape of the damping device 4.
  • the damping device 4 is simply arranged within an assembly 1 already mounted, without requiring the the addition of connections, for example bolted, which would increase both the mass of assembly 1, and its assembly and/or maintenance time.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Anordnung (1) für Turbomaschine, umfassend:
    • ein erstes Rotormodul (2), das eine erste Schaufel (20) und eine Scheibe (21) umfasst, die auf einer Turbomaschinen-Längsachse (X-X) zentriert ist, wobei die erste Schaufel (20) am äußeren Umfang der Scheibe (21) angebracht ist, ab der sich erstreckt und ferner ein Blatt (23), eine Plattform (25), einen Stab (27) und einen Fuß (29) umfasst, der in eine Aufnahme (210) der Scheibe (21) eingesetzt ist,
    • ein zweites Rotormodul (3), das mit dem ersten Rotormodul (2) verbunden ist und eine zweite Schaufel (30) kürzerer Länge als die erste Schaufel (20) sowie einen Ring (32) umfasst, der eine Umfangserweiterung (34) umfasst, die sich zur Plattform (25) der ersten Schaufel (20) erstreckt, und
    • eine Dämpfungsvorrichtung (4), die sich entlang mindestens einer Komponente gemäß der Turbomaschinen-Längsachse (X-X) erstreckt,
    dadurch gekennzeichnet, dass die Dämpfungsvorrichtung (4) ringförmig ist, indem sie sich umfangmäßig um die Turbomaschinen-Längsachse (X-X) erstreckt und dass die Dämpfungsvorrichtung (4) eine erste äußere Oberfläche (40) umfasst, die sich mit Reibung auf dem ersten Modul (2) abstützt, sowie eine zweite äußere Oberfläche (42), die sich mit Reibung auf dem zweiten Modul (3) abstützt, so dass die Module (2, 3) gekoppelt werden, um ihre jeweiligen Vibrationsbewegungen im Betrieb zu dämpfen, wobei sich die erste äußere Oberfläche (40) der Dämpfungsvorrichtung (4) mit Reibung auf einer radial inneren Oberfläche (250) der Plattform (25) der ersten Schaufel (20) abstützt, wobei sich die zweite äußere Oberfläche (42) der Dämpfungsvorrichtung (4) mit Reibung auf dem Ring (32) abstützt.
  2. Anordnung (1) nach Anspruch 1, wobei die Dämpfungsvorrichtung (4) eine ringförmige Zunge ist, deren Querschnitt V-förmig ist, wobei eine äußere Oberfläche (40) eines ersten Schenkels (41) des V die erste äußere Oberfläche (40) bildet, die sich mit Reibung auf dem ersten Rotormodul (2) abstützt, wobei eine äußere Oberfläche (42) eines zweiten Schenkels (43) des V die zweite äußere Oberfläche (42) bildet, die sich mit Reibung auf dem zweiten Rotormodul (3) abstützt.
  3. Anordnung (1) nach einem der Ansprüche 1 und 2, wobei ein Befestigungsring (38) auf der Umfangserweiterung (34) aufgeschrumpft ist, wobei sich die zweite äußere Oberfläche (42) der Dämpfungsvorrichtung (4) mit Reibung auf dem Befestigungsring (38) abstützt.
  4. Anordnung (1) nach einem der Ansprüche 1 und 2, wobei die Erweiterung (34) radiale Schneidendichtungen (36) trägt, wobei sich die zweite äußere Oberfläche (42) der Dämpfungsvorrichtung (4) mit Reibung auf den Schneidendichtungen (36) abstützt.
  5. Anordnung (1) nach Anspruch 4, wobei die Abstützoberflächen (40, 42) der Dämpfungsvorrichtung (4) und die Oberflächen (250, 360) der Plattform (25) und der radialen Schneidendichtungen (36) beispielsweise durch eine Carbon-Carbon-Ablagerung behandelt sind, um deren jeweilige Abstützungen zu garantieren.
  6. Anordnung (1) nach einem der Ansprüche 1 bis 5, wobei die Dämpfungsvorrichtung (4) eine Beschichtung (48) des ableitfähigen Typs umfasst, die die Abstützoberflächen (40, 42) definiert.
  7. Anordnung (1) nach einem der Ansprüche 1 bis 6, wobei die Dämpfungsvorrichtung (4) eine Beschichtung (49) des viskoelastischen Typs umfasst.
  8. Anordnung (1) nach einem der Ansprüche 1 bis 7, wobei die Dämpfungsvorrichtung (4) Bohrungen (45) zur Erleichterung der Dämpfungsvorrichtung (4) umfasst.
  9. Anordnung (1) nach einem der Ansprüche 1 bis 8, wobei die Dämpfungsvorrichtung (4) Einsätze (47) beispielsweise des metallischen Typs zur Beschwerung der Dämpfungsvorrichtung (4) umfasst.
  10. Anordnung (1) nach einem der Ansprüche 1 bis 9, wobei das erste Modul (2) ein Gebläse ist und das zweite Modul (3) ein Niederdruckkompressor ist.
  11. Anordnung (1) nach einem der Ansprüche 1 bis 10, wobei die Dämpfungsvorrichtung (4) derart geschlitzt ist, dass zwei einander zugewandte Enden (44, 46) definiert werden.
  12. Turbomaschine, umfassend eine Anordnung (1) nach einem der Ansprüche 1 bis 11.
  13. Verfahren zur Montage (E) einer Anordnung (1) nach einem der Ansprüche 1 bis 11, das die folgenden Schritte umfasst:
    • Anordnen (E1) der Dämpfungsvorrichtung (4) zwischen dem ersten Rotormodul (2) und dem zweiten Rotormodul (3), so dass sich die erste äußere Oberfläche (40) der Dämpfungsvorrichtung (4) mit Reibung auf dem ersten Modul (2) abstützt, und sich die zweite äußere Oberfläche (42) der Dämpfungsvorrichtung (4) mit Reibung auf dem zweiten Modul (3) abstützt, und
    • Vorspannen der Dämpfungsvorrichtung (4) an den Modulen (2, 3), so dass sie gekoppelt werden, um ihre jeweiligen Vibrationsbewegungen im Betrieb zu dämpfen.
EP18833974.1A 2017-12-18 2018-12-18 Dämpfervorrichtung Active EP3728794B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1762358A FR3075284B1 (fr) 2017-12-18 2017-12-18 Dispositif amortisseur
FR1762545A FR3075254B1 (fr) 2017-12-19 2017-12-19 Dispositif amortisseur
PCT/FR2018/053375 WO2019122691A1 (fr) 2017-12-18 2018-12-18 Dispositif amortisseur

Publications (2)

Publication Number Publication Date
EP3728794A1 EP3728794A1 (de) 2020-10-28
EP3728794B1 true EP3728794B1 (de) 2024-02-28

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US (1) US11536157B2 (de)
EP (1) EP3728794B1 (de)
CN (1) CN111615584B (de)
WO (1) WO2019122691A1 (de)

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CN111615584B (zh) 2022-08-16
CN111615584A (zh) 2020-09-01
US20210010391A1 (en) 2021-01-14
EP3728794A1 (de) 2020-10-28
US11536157B2 (en) 2022-12-27
WO2019122691A1 (fr) 2019-06-27
WO2019122691A9 (fr) 2020-04-09

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