EP3728794B1 - Damper device - Google Patents

Damper device 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
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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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German (de)
French (fr)
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EP3728794A1 (en
Inventor
Philippe Gérard Edmond JOLY
François Jean Comin
Charles Jean-Pierre Douguet
Laurent Jablonski
Romain Nicolas LAGARDE
Jean-Marc Claude Perrollaz
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
Priority claimed from FR1762358A external-priority patent/FR3075284B1/en
Priority claimed from FR1762545A external-priority patent/FR3075254B1/en
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3728794A1 publication Critical patent/EP3728794A1/en
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Publication of EP3728794B1 publication Critical patent/EP3728794B1/en
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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.

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention concerne un ensemble comprenant un module rotor de turbomachine.The invention relates to an assembly comprising a turbomachine rotor module.

L'invention vise plus spécifiquement un ensemble pour turbomachine comprenant deux modules rotor et un dispositif amortisseur.The invention relates more specifically to an assembly for a turbomachine comprising two rotor modules and a damping device.

ETAT DE LA TECHNIQUESTATE OF THE ART

Un module rotor de turbomachine comprend généralement un ou plusieurs étage(s), chaque étage comprenant un disque centré sur un axe longitudinal de turbomachine, correspondant à l'axe de rotation du module rotor. La mise en rotation du disque est généralement assurée par un arbre rotatif auquel il est relié solidairement, par exemple au moyen d'un tourillon de module rotor, l'arbre rotatif s'étendant selon l'axe longitudinal de la turbomachine. Des aubes sont montées à la périphérie externe du disque, et réparties circonférentiellement, de manière régulière autour de l'axe longitudinal. Chaque aube s'étend depuis le disque, et comprend en outre une pale, une plateforme, une échasse et un pied. Le pied est encastré dans un logement du disque configuré à cet effet, la pale est balayée par un flux traversant la turbomachine, et la plateforme forme une portion de la surface interne de la veine de flux.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.

Le domaine de fonctionnement d'un module rotor est limité, notamment à cause de phénomènes aéroélastiques. Les modules rotor de turbomachines modernes, qui possèdent une charge aérodynamique élevée, et un nombre réduit d'aubes, sont plus sensibles à ce type de phénomènes. En particulier, ils présentent des marges réduites entre les zones de fonctionnement sans instabilité et les zones instables. Il est néanmoins impératif de garantir une marge suffisante entre le domaine de stabilité et celui de l'instabilité, ou de démontrer que le module rotor peut fonctionner dans la zone d'instabilité sans dépasser sa limite d'endurance. Ceci permet de garantir un fonctionnement sans risque dans toute la vie et tout le domaine de fonctionnement de la turbomachine.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.

Le fonctionnement dans la zone d'instabilité se caractérise par un couplage entre le fluide et la structure, le fluide apportant l'énergie à la structure, et la structure répondant sur ses modes propres à des niveaux pouvant dépasser la limite d'endurance du matériau constituant l'aube. Ceci génère des instabilités vibratoires qui accélèrent l'usure du module rotor, et diminuent sa durée de vie.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.

Afin de limiter ces phénomènes, il est connu de mettre en place un système amortissant la réponse dynamique de l'aube, afin de garantir que celle-ci ne dépasse pas la limite d'endurance du matériau quel que soit le point de fonctionnement du module rotor. Cependant, la plupart des systèmes connus de l'art antérieur s'attachent à amortir des modes de vibration à déphasage non nul, et caractérisant une réponse asynchrone des aubes aux sollicitations aérodynamiques. De tels systèmes ont par exemple été décrits dans les documents FR 2 949 142 , EP 1 985 810 et FR 2 923 557 , au nom de la Demanderesse. Ces systèmes sont tous configurés pour être logés entre la plateforme et le pied de chaque aube, dans le logement délimité par les échasses respectives de deux aubes successives. Par ailleurs, de tels systèmes fonctionnent lorsque deux plateformes d'aubes successives se déplacent l'une par rapport à l'autre, par dissipation de l'énergie de vibration, par exemple par frottement. Un autre dispositif amortisseur est divulgué dans le document EP 3 724 455 A1 .In order to limit these phenomena, it is known to implement a system damping the dynamic response of the blade, in order to guarantee that it does not exceed the endurance limit of the material whatever the operating point of the module. rotor. However, most of the systems known from the prior art focus on damping vibration modes 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 , on behalf of the Applicant. These systems are all configured to be housed between the platform and the foot 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 vibration energy, for example by friction. Another damping device is disclosed in the document EP 3 724 455 A1 .

Cependant, ces systèmes sont totalement inefficaces pour amortir les modes de vibration présentant un déphasage nul faisant participer les aubes et la ligne rotor, c'est-à-dire son arbre rotatif. De tels modes se caractérisent par une flexion des aubes de rotor avec un déphasage inter-aube nul impliquant un moment non nul sur l'arbre rotatif. En outre, il s'agit d'un mode couplé entre l'aube, le disque, et l'arbre rotatif. Plus précisément, la torsion au sein du module rotor, résultant par exemple d'efforts inverses entre un rotor de turbine et un rotor de compresseur, aboutissent à des mouvements de flexion des aubes par rapport à leur attache avec le disque. Ces mouvements sont d'autant importants que l'aube est grande, et que l'attache est souple.However, these systems are totally ineffective in damping the vibration modes presenting a zero phase shift involving the blades and the rotor line, that is to say its rotating shaft. Such modes are characterized by bending of the rotor blades with zero inter-blade phase shift implying a non-zero moment on the rotating shaft. In addition, it is a coupled mode between the blade, the disk, and the rotating shaft. More precisely, the torsion within the rotor module, resulting for example from inverse forces between a turbine rotor and a compressor rotor, results in bending movements of the blades relative to their attachment with the disk. These movements are all the more important as the blade is large and the attachment is flexible.

Il existe donc un besoin d'un système amortisseur pour rotor de turbomachine permettant de limiter les instabilités générées par tous les modes de vibration tels que précédemment décrits.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.

RESUME DE L'INVENTIONSUMMARY OF THE INVENTION

Un but de l'invention est d'amortir les modes de vibration à déphasage nul pour tous types de modules rotor de turbomachine.An aim of the invention is to damp vibration modes with zero phase shift for all types of turbomachine rotor modules.

Un autre but de l'invention est d'influencer l'amortissement des modes de vibration à déphasage non nul, pour tous types de modules rotor de turbomachine.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.

Un autre but de l'invention est de proposer une solution d'amortissement simple et facile à mettre en oeuvre.Another aim of the invention is to propose a simple and easy to implement damping solution.

L'invention est décrite dans la revendication 1, les revendications dépendantes décrivant des aspects préférés de l'invention.The invention is described in claim 1, with the dependent claims describing preferred aspects of the invention.

Le couplage mécanique entre le premier et le deuxième module rotor permet d'augmenter la rigidité tangentielle de la liaison entre ces deux rotors, tout en autorisant une certaine souplesse axiale et radiale du dispositif amortisseur afin de maximiser le contact entre les différents éléments de l'ensemble. Ceci permet de limiter les instabilités liées au mode de vibration à déphasage nul, mais aussi de participer à l'amortissement des modes de vibration à déphasage non nul. En outre, un tel ensemble présent l'avantage d'une intégration facile au sein de turbomachines existantes, que ce soit lors de la fabrication ou lors de maintenance. En effet, le caractère annulaire du dispositif amortisseur permet de réduire son encombrement entre les deux modules motor.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. Furthermore, such an assembly has the advantage of easy integration into existing turbomachines, whether during manufacturing or during maintenance. In fact, the annular nature of the damping device makes it possible to reduce its size between the two motor modules.

DESCRIPTIF RAPIDE DES FIGURESQUICK DESCRIPTION OF FIGURES

D'autres caractéristiques, buts et avantages de la présente invention apparaitront à la lecture de la description détaillée qui va suivre et en regard des dessins annexés donnés à titre d'exemple non limitatif et sur lesquels :

  • la figure 1 est une vue en coupe schématique d'un exemple de réalisation de l'ensemble selon l'invention,
  • la figure 2 est une vue de face d'un module rotor soumis à des vibrations tangentielles dont le mode de flexion est à déphasage nul,
  • la figure 3a illustre schématiquement des déplacements tangentiels de modules rotors de turbomachine, en fonction de la position desdits modules le long d'un axe de turbomachine,
  • la figure 3b est un agrandissement en perspective schématique de l'interface entre deux modules rotor de turbomachine illustrant ses déplacements tangentiels relatifs desdits modules rotor,
  • la figure 4 illustre schématiquement un premier exemple de réalisation d'un dispositif amortisseur d'un ensemble selon l'invention,
  • la figure 5 illustre schématiquement un agrandissement d'un deuxième exemple de réalisation d'un dispositif amortisseur d'un ensemble selon l'invention,
  • la figure 6 illustre schématiquement une partie d'un autre exemple de réalisation d'un ensemble selon l'invention, et
  • la figure 7 est un organigramme détaillant un exemple de réalisation d'un procédé de montage d'un ensemble selon l'invention.
Other characteristics, aims 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:
  • there figure 1 is a schematic sectional view of an exemplary embodiment of the assembly according to the invention,
  • there figure 2 is a front view of a rotor module subjected to tangential vibrations whose bending mode is at zero phase shift,
  • there figure 3a schematically illustrates tangential movements of turbomachine rotor modules, as a function of the position of said modules along a turbomachine axis,
  • there figure 3b is a schematic perspective enlargement of the interface between two turbomachine rotor modules illustrating its relative tangential movements of said rotor modules,
  • there figure 4 schematically illustrates a first embodiment of a damping device of an assembly according to the invention,
  • there figure 5 schematically illustrates an enlargement of a second embodiment of a damping device of an assembly according to the invention,
  • there Figure 6 schematically illustrates part of another embodiment of an assembly according to the invention, and
  • there Figure 7 is a flowchart detailing an example of carrying out a method of assembling an assembly according to the invention.

DESCRIPTION DETAILLEE DE L'INVENTIONDETAILED DESCRIPTION OF THE INVENTION

Un exemple de réalisation d'un ensemble 1 selon l'invention va maintenant être décrit, en référence aux figures.An exemplary embodiment of an assembly 1 according to the invention will now be described, with reference to the figures.

Dans tout ce qui va suivre, l'amont et l'aval sont définis par rapport au sens d'écoulement normal d'air à travers la turbomachine. Par ailleurs, un axe longitudinal X-X de turbomachine est défini. De cette manière, la direction axiale correspond à la direction de l'axe longitudinal X-X de turbomachine, une direction radiale est une direction qui est perpendiculaire à cet axe longitudinal X-X de turbomachine et qui passe par ledit axe longitudinal X-X de turbomachine, et une direction circonférentielle correspond à la direction d'une ligne courbe plane et fermée, dont tous les points se trouvent à égale distance de l'axe longitudinal X-X de turbomachine. Enfin, et sauf précision contraire, les termes « interne (ou intérieur) » et « externe (ou extérieur) », respectivement, sont utilisés en référence à une direction radiale de sorte que la partie ou la face interne (i.e. radialement interne) d'un élément est plus proche de l'axe longitudinal X-X de turbomachine que la partie ou la face externe (i.e. radialement externe) du même élément.In everything that follows, 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. In this way, 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, and 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. Finally, and unless otherwise specified, 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.

En référence aux figures 1 et 3a, un tel ensemble 1 comprend :

  • un premier module rotor 2 comprenant une première aube 20,
  • un deuxième module rotor 3, relié au premier module rotor 2, et comprenant une deuxième aube 30 de longueur inférieure à la première aube 20, et
  • un dispositif amortisseur 4 qui s'étend suivant au moins une composante qui est selon un axe longitudinal X-X de turbomachine. En outre, le dispositif amortisseur 4 est annulaire en s'étendant circonférentiellement autour d'un axe longitudinal X-X de turbomachine, et comprend une première surface externe 40 en appui avec frottement contre le premier module 2 ainsi qu'une deuxième surface externe 42 en appui avec frottement contre le deuxième module 3, de sorte à coupler les modules 2, 3 en vue d'amortir leurs mouvements vibratoires respectifs en fonctionnement.
With reference to figures 1 And 3a , such a set 1 includes:
  • 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 less length than the first blade 20, and
  • a damping device 4 which extends along at least one component which is along a longitudinal axis XX of the turbomachine. In addition, the damping device 4 is annular, extending circumferentially around a longitudinal axis XX of the turbomachine, and comprises a first external surface 40 bearing with friction against the first module 2 as well as a second external surface 42 bearing with friction against the second module 3, so as to couple the modules 2, 3 with a view to damping their respective vibratory movements in operation.

Par appui « avec frottement », on comprend que le contact entre les surfaces radiales externes 41, 42 et, respectivement, le premier module rotor 2, et le deuxième module rotor 3, s'effectue avec frottement. En d'autres termes, les efforts d'appui entre les surfaces radiales externes 41, 42 et, respectivement, le premier module rotor 2, et le deuxième module rotor 3, peuvent se décomposer en des efforts de pression, qui sont dirigés normalement au contact, et des efforts de frottement, dirigés tangentiellement au contact. Cet appui garantit à la fois la cohérence mécanique de l'ensemble 1, par l'intermédiaire des efforts de pression, mais aussi le couplage entre les modules 2, 3, en vue d'amortir leurs mouvements vibratoires respectifs en fonctionnement, par l'intermédiaire des efforts de frottement.By support “with friction”, we understand that the contact between the external radial surfaces 41, 42 and, respectively, the first rotor module 2, and the second rotor module 3, takes place with friction. In other words, the support forces between the external radial surfaces 41, 42 and, respectively, the first rotor module 2, and the second rotor module 3, can be broken down into pressure forces, which are directed normally to the contact, and frictional forces, directed tangentially to the contact. This support guarantees both the mechanical coherence of assembly 1, via pressure forces, but also the coupling between modules 2, 3, with a view to damping their respective vibratory movements in operation, by intermediate friction forces.

En référence aux figures 1 et 3a, le premier module rotor est une soufflante 2, et le deuxième module rotor est un compresseur basse pression 3, situé immédiatement en aval de la soufflante 2.With reference to figures 1 And 3a , the first rotor module is a fan 2, and the second rotor module is a low pressure compressor 3, located immediately downstream of the fan 2.

La soufflante 2 et le compresseur basse pression 3 comprennent un disque 21, 31 centré sur un axe longitudinal X-X de turbomachine, la première 20 et la seconde aube 30 étant respectivement montées à la périphérie externe du disque 21, 31, et comprenant en outre une pale 23, 33, une plateforme 25, 35 une échasse 27, 37 et un pied 29, 39 encastré dans un logement 210, 310 du disque 21, 31. La distance séparant le pied 29, 39 de l'extrémité de la pale 23, 33 constitue les longueurs respectives de la première 20 et de la deuxième aube 30. La longueur de la première aube 20 et deuxième aube 30 est donc ici considérée comme sensiblement radialement par rapport à l'axe longitudinal X-X de rotation des modules rotor 2, 3. En fonctionnement, la pale 23, 33 est balayée par un flux 5 traversant la turbomachine, et la plateforme 25, 35 forme une portion de la surface interne de la veine de flux 5. De manière générale, comme visible sur les figures 2 et 3a, soufflante 2 et compresseur basse pression 3 comprennent une pluralité d'aubes 20, 30 réparties circonférentiellement autour de l'axe longitudinal X-X. Le compresseur basse pression 3 comprend en outre une virole annulaire 32 également centrée sur l'axe longitudinal X-X. La virole 32 comprend une extension circonférentielle 34, elle aussi annulaire, s'étendant vers la plateforme 25 de la première aube 20. Cette extension annulaire 34 est porteuse de léchettes radiales d'étanchéité 36 configurées pour prévenir les pertes de débit d'air depuis la veine de flux 5. De plus, la virole 32 est fixée au disque 21 de soufflante 2 au moyen d'attaches 22 réparties circonférentiellement autour de l'axe longitudinal X-X. De telles attaches peuvent par exemple être des liaisons boulonnées 22. Alternativement, de telles attaches 22 peuvent être réalisées par frettage auquel est associé un dispositif d'anti-rotation et/ou un système de verrouillage axial. Enfin, en référence à la figure 3a, l'ensemble formé de la soufflante 2 et du compresseur 3 est mis en rotation par un arbre rotatif 6, appelé arbre basse pression, auquel soufflante 2 et compresseur basse pression 3 sont solidairement reliés, au moyen d'un tourillon de rotor 60, l'arbre basse pression 6 étant également relié à une turbine basse pression 7, en aval de la turbomachine, et s'étendant selon l'axe longitudinal X-X de turbomachine.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. 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. Generally speaking, as visible in the figure 2 And 3a , 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. In addition, the ferrule 32 is fixed to the disk 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 produced by shrink fit with which is associated an anti-rotation device and/or an axial locking system. Finally, with reference to the figure 3a , 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.

En fonctionnement, la soufflante 2 aspire de l'air dont tout ou partie est compressé par le compresseur basse pression 3. L'air compressé circule ensuite dans un compresseur haute pression (non représenté) avant d'être mélangé à du carburant, puis enflammé au sein de la chambre de combustion (non représentée), pour enfin être successivement détendu dans la turbine haute (non représentée) et la turbine basse pression 7. Les efforts opposés de compression en amont, et de détente en aval, donnent lieu à des phénomènes aéroélastiques de flottement, qui couplent les efforts aérodynamiques sur les aubes 20, 30, et les mouvements de vibration en flexion et torsion dans les aubes 20, 30. Comme illustré en figure 2, ce flottement entraîne notamment des efforts de torsion intenses au sein de l'arbre basse pression 6 qui sont répercutés à la soufflante 2 et au compresseur basse pression 3. Les aubes 20, 30 sont alors soumises à des battements tangentiels, notamment selon un mode de vibration à déphasage nul. Il s'agit en effet d'un mode de flexion avec un déphasage inter-aube 20, 30 nul, impliquant un moment non nul sur l'arbre basse pression 6, dont la fréquence propre est environ une fois et demie supérieure à celle de première harmonique de vibration, et dont la déformée possède une ligne nodale à mi-hauteur de l'aube 20, 30. De telles vibrations limitent la tenue mécanique de la soufflante 2 et du compresseur basse pression 30, accélèrent l'usure de la turbomachine, et diminue sa durée de vie.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 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.

Comme visible sur la figure 3a, le déplacement tangentiel par flottement de l'aube 20 de soufflante 2 est différent de celui de la virole 32 de compresseur basse pression 3. En effet, la longueur des aubes 20 de soufflante 2 étant supérieure à celle des aubes 30 de compresseur basse pression 3, le moment de flexion tangentielle entraîné par les battements d'aube 20 de soufflante 2 est bien supérieur à celui entraîné par les battements d'aube 30 de compresseur basse pression 3. En outre, la raideur de montage au sein la de soufflante 2 est différente de celle de montage au sein du compresseur 3. En référence à la figure 3b, cet écart de battements tangentiels est notamment visible à l'interface entre la plateforme 25 d'une aube 20 de soufflante 2, et des léchettes d'étanchéité 36 de virole 32.As visible on the figure 3a , 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. In fact, 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. In addition, the mounting stiffness within the fan 2 is different from that of assembly within the compressor 3. With reference to the figure 3b , 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.

Dans un premier mode de réalisation, en référence à la figure 1, le dispositif amortisseur 4 est logé sous la plateforme 25 d'une aube 20 de soufflante 2, entre l'échasse 27 et la virole 32 de compresseur basse pression 3. En outre, le compresseur basse pression 3 comprend une virole de fixation 38 annulaire, frettée sur l'extension circonférentielle 34 de virole 32 de compresseur basse pression 3. Alternativement, la virole de fixation 38 peut être assemblée à l'extension circonférentielle 34 de virole 32 par l'intermédiaire de fixations telles que celles assurées par des doigts radiaux (non représentés) appartenant à ladite virole de fixation 38 et vissées à ladite extension 34.In a first embodiment, with reference to the figure 1 , 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. In addition, 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. Alternatively, 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.

Les léchettes 36 comprennent de manière traditionnelle des extrémités libres sensiblement radiales d'étanchéité pour être en regard d'un stator. Ici, les léchettes 36 comportent une racine annulaire qui relie ces extrémités à l'extension circonférentielle 34 de virole 32.The lips 36 traditionally comprise substantially radial free sealing ends to face a stator. Here, the lips 36 include an annular root which connects these ends to the circumferential extension 34 of the ferrule 32.

La première surface externe 40 est en appui avec frottement contre la soufflante 2 au niveau de la surface interne 250 de la plateforme 25 de l'aube 20 de soufflante 2, et la deuxième surface externe 42 est en appui avec frottement sur la virole de fixation 38. Ceci assure un couplage tangentiel de raideur importante entre soufflante 2 et compresseur basse pression 3, de sorte à réduire les vibrations tangentielles précédemment décrites. Le couplage est d'ailleurs d'autant important que la zone au sein de laquelle le dispositif amortisseur 4 est disposé présente les déplacements tangentiels relatifs les plus élevés pour le mode à déphasage nul considéré, comme illustré en figures 3a et 3b. Typiquement, ces déplacements relatifs sont de l'ordre de quelques millimètres. Pour autant, le dispositif amortisseur 4 conserve également avantageusement une efficacité sur les modes vibratoires des aubes 20 de soufflante 2 à déphasage non nul.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 . Typically, these relative displacements are of the order of a few millimeters. However, the damping device 4 also advantageously maintains effectiveness on the vibration modes of the fan blades 20 2 with non-zero phase shift.

Dans les réalisations illustrées sur les figures 1, 4 et 5, le dispositif amortisseur 4 est une languette annulaire, dont la section est en forme de V. La surface radialement externe 40 de la première branche 41 du V formant la première surface 40 en appui avec frottement contre la soufflante 2, la surface externe 42 de la deuxième branche 43 du V formant la deuxième surface externe 42 en appui avec frottement contre le compresseur basse pression 3. La structure en languette permet avantageusement de réduire l'encombrement du dispositif amortisseur 4, au sein de l'ensemble 1. En outre, la structure en V permet d'augmenter la surface de contact entre soufflante 2 et dispositif amortisseur 4 d'une part, et entre dispositif amortisseur 4 et compresseur basse pression 3 d'autre part. Cette configuration favorise donc le couplage entre ces deux éléments rotors, en vue d'amortir leurs mouvements vibratoires.In the achievements illustrated on the figures 1 , 4 And 5 , 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. In addition, 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.

En vue de faciliter le montage, la languette annulaire 4 ne constitue pas un anneau d'une seule pièce, mais est fendue de sorte à définir deux extrémités 44, 46 en regard l'une de l'autre.In order to facilitate assembly, 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.

Les sollicitations mécaniques en fonctionnement sont telles que de légers mouvements tangentiels, axiaux et radiaux du dispositif amortisseur 4 sont à prévoir. Ces mouvements sont notamment dus aux battements tangentiels à amortir, mais aussi au chargement centrifuge de l'ensemble 1. Il est nécessaire que ces mouvements n'usent pas les aubes 20 ou la virole 32, dont les revêtements sont relativement fragiles. A cet égard, les surfaces d'appui 40, 42 du dispositif amortisseur peuvent être traitées par lubrification sèche, en vue de pérenniser la valeur du coefficient de frottement entre dispositif amortisseur 4 et compresseur basse pression 3 et/ou plateforme 25 d'aube 20. Cette lubrification est par exemple de type MoS2.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. In this regard, 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.

En vue d'améliorer l'appui avec frottement, le dispositif amortisseur 4 comprend, dans un deuxième mode de réalisation, un revêtement additionnel 48, 49, comme visible sur la figure 5, définissant les surfaces d'appui 40, 42. De manière générale, un tel revêtement 48, 49 est configuré pour diminuer le frottement et/ou l'usure des pièces moteur entre le dispositif amortisseur 4 et les modules rotor 2, 3. Ce revêtement 48, 49 est par exemple de type dissipatif 48 et/ou viscoélastique et/ou amortissant. Le revêtement dissipatif 48 comprend alors un matériau choisi parmi ceux présentant des propriétés mécaniques similaires à celles du vespel, du téflon ou de toute autre matière à propriétés lubrifiantes. De manière plus générale le matériau possède un coefficient de frottement compris entre 0.3 et 0.07. Une trop grande souplesse ne permettrait pas d'amortir le mode à déphasage nul, puisque les déplacements relatifs de la soufflante 2 et du compresseur basse pression 3 aboutiraient à des frottements et/ou oscillations entre un état « collé » et un état « glissant » du dispositif amortisseur 4. En outre, le revêtement frotteur 48 constitue une alternative efficace au traitement lubrification sèche, qui nécessite d'être mise en oeuvre régulièrement.In order to improve the support with friction, 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. Generally, such 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. Too much flexibility would not allow the zero phase shift mode to be damped, since the relative movements of the fan 2 and the low pressure compressor 3 would result in friction and/or oscillations between a “stuck” state and a “sliding” state. of the damping device 4. In addition, the friction coating 48 constitutes an effective alternative to dry lubrication treatment, which needs to be implemented regularly.

Alternativement, ce revêtement 48, 49 est de type viscoélastique 49. Un tel revêtement 49 comprend alors avantageusement un matériau ayant des propriétés similaires à celles d'un matériau tel que ceux de la gamme ayant l'appellation commerciale « SMACTANEO », par exemple un matériau de type « SMACTANEO 70 ». Une autre manière d'augmenter la raideur tangentielle de l'ensemble 1 est de suffisamment précontraindre le revêtement viscoélastique 44, par exemple lors du montage de l'ensemble 1, pour que le déplacement tangentiel relatif entre aube 20 et virole 32 se transforme en cisaillement viscoélastique du revêtement 44 seul. Ces revêtements additionnels 48, 49 sont rapportés par collage au niveau des surfaces d'appui 40, 42.Alternatively, this coating 48, 49 is of the viscoelastic type 49. Such 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.

Dans un détail de réalisation comme illustré sur la figure 4, l'amortissement par couplage tangentielle peut être ajusté en contrôlant la masse du dispositif amortisseur 4, ce qui influence l'inertie de cisaillement. Ce contrôle passe par des modifications de la masse du dispositif amortisseur 4. Cette masse peut être modifiée dans tout ou partie du dispositif amortisseur 4, typiquement en pratiquant des alésages 45 pour alléger, et/ou en ajoutant un ou plusieurs inserts 47, par exemple métalliques, pour alourdir. En outre, le contrôle de la masse du dispositif amortisseur 4 permet de régler son efficacité par l'intermédiaire des forces centrifuges qu'il subit en fonctionnement. Ce détail de réalisation à alésages et/ou insert peut correspondre à un troisième mode de réalisation.In a detail of construction as illustrated on the figure 4 , 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. In addition, 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.

Avantageusement, la combinaison du deuxième et du troisième mode de réalisation permet d'ajuster les efforts de contact entre le dispositif amortisseur 4 et la soufflante 2 ainsi que le compresseur basse pression 3. En effet, des efforts de contact trop élevés entre l'aube 20 de soufflante 2 et le dispositif amortisseur 4 limiteraient les dissipations des vibrations en fonctionnement.Advantageously, 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.

Dans un quatrième mode de réalisation illustré sur la figure 6, le dispositif amortisseur 4 est un cylindre annulaire, dont la section est en forme de losange. La surface radialement externe 40 d'un premier côté du losange formant la première surface externe 40 en appui avec frottement contre la soufflante 2, la surface radialement externe 42 d'un deuxième côté du losange formant la deuxième surface externe 42 en appui avec frottement contre le compresseur basse pression 3. La section en forme de losange est en effet plus dense que la section en V, ce qui permet d'augmenter le couplage mécanique entre soufflante 2 et compresseur basse pression 3, en favorisant la raideur tangentielle de l'ensemble 1.In a fourth embodiment illustrated on the Figure 6 , the damping device 4 is an annular cylinder, the section of which is diamond-shaped. The radially external surface 40 of a first side of the diamond forming the first external surface 40 bearing with friction against the fan 2, the radially external surface 42 of a second side of the diamond forming the second external surface 42 bearing with friction against the low pressure compressor 3. 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.

En outre, la première surface externe 40 est en appui avec frottement contre la soufflante 2 au niveau de la surface interne 250 de la plateforme 25 de l'aube 20 de soufflante 2, et la deuxième surface externe 42 est également en appui avec frottement sur les léchettes radiales d'étanchéité 36. Avantageusement, les surfaces d'appui 40, 42 du dispositif amortisseur 4, et les surfaces 250, 360 de la plateforme 25 et des léchettes radiales d'étanchéité 36 sont traitées de sorte à garantir leurs appuis respectifs. De manière encore plus avantageuse, le traitement consiste en un dépôt carbone-carbone qui assure un fort coefficient de frottement, tout en limitant l'usure des surfaces 250, 360 de la plateforme 25 et des léchettes radiales d'étanchéité 36. Cet appui avec frottement est sur la racine des léchettes 36, c'est-à-dire à distance de leurs extrémités libres d'étanchéité.In addition, 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. Advantageously, 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 . Even more advantageously, 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.

En vue de faciliter le montage, le cylindre 4 ne constitue pas un anneau d'une seule pièce, mais est fendue de sorte à définir deux extrémités en regard l'une de l'autre.In order to facilitate assembly, the cylinder 4 does not constitute a single-piece ring, but is split so as to define two ends facing each other.

Avantageusement, le dispositif amortisseur 4 comprend un matériau dense, de préférence de l'acier ou un alliage à base de nickel, de sorte à maximiser la raideur tangentielle du couplage entre la soufflante 2 et le compresseur basse pression 3.Advantageously, 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.

Différents modes de réalisation de l'ensemble 1 selon l'invention ont été décrits dans le cas où le premier module rotor 2 est une soufflante, et le deuxième module rotor 3 est un compresseur basse pression.Different embodiments of assembly 1 according to the invention have been described in the case where the first rotor module 2 is a fan, and the second rotor module 3 is a low pressure compressor.

Ceci n'est cependant pas limitatif, puisque le premier module rotor 2 peut également être un premier étage de compresseur, haute ou basse pression, et le deuxième module rotor 3 un deuxième étage dudit compresseur, successif au premier étage de compresseur, en amont ou en aval de ce-dernier. Alternativement, le premier module rotor 2 est un premier étage de turbine, haute ou basse pression, et le deuxième module rotor 3 un deuxième étage de ladite turbine, successif au premier étage de turbine, en amont ou en aval de ce-dernier.This is however not 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.

Un procédé de montage d'un ensemble 1 selon l'un quelconque des modes de réalisation précédemment décrit va maintenant être détaillé, en référence à la figure 7.A method of assembling an assembly 1 according to any of the previously described embodiments will now be detailed, with reference to the Figure 7 .

Lors d'une première étape E1, le dispositif amortisseur 4 est disposé entre le premier module rotor 2 et le deuxième module rotor 3 de sorte à ce qu'une première surface externe 40 du dispositif amortisseur 4 soit en appui avec frottement contre le premier module 2, et qu'une deuxième surface externe 42 du dispositif amortisseur 4 soit en appui avec frottement contre le deuxième module 3.During a first step E1, 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.

Lors d'une deuxième étape E2, le dispositif amortisseur 4 est précontraint contre le premier 2 et le deuxième module rotor 3 de sorte à les coupler en vue d'amortir leurs mouvements vibratoires respectifs en fonctionnement.During a second step E2, 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.

Un tel procédé de montage E est avantageusement favorisé par le caractère simple issu de la forme annulaire du dispositif d'amortissement 4. En effet, le dispositif d'amortissement 4 est simplement disposé au sein d'un ensemble 1 déjà monté, sans nécessiter l'ajout de liaisons, par exemple boulonnée, qui augmenteraient à la fois la masse de l'ensemble 1, et son temps de montage et/ou de maintenance.Such an assembly method E is advantageously favored by the simple character resulting from the annular shape of the damping device 4. In fact, 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.

Claims (13)

  1. A turbomachine assembly (1) comprising:
    • a first rotor module (2) comprising a first blade (20) and a disk (21) centered on a turbomachine longitudinal axis (X-X), the first blade (20) being mounted on the external periphery of the disk (21) from which it extends, and further comprising an airfoil (23), a platform (25), a support (27) and a root (29) embedded in a housing (210) of the disk (21),
    • a second rotor module (3), connected to the first rotor module (2), and comprising a second blade (30) with a length less than the first blade (20) and a ferrule (32) comprising a circumferential extension (34) extending toward the platform (25) of the first blade (20), and
    • a damping device (4) extending with at least one component along the turbomachine longitudinal axis (X-X),
    characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first external surface (40) supported with friction against the first module (2), as well as a second external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation, the first external surface (40) of the damping device (4) being supported with friction on a radially internal surface (250) of the platform (25) of the first blade (20), the second external surface (42) of the damping device (4) being supported with friction on the ferrule (32).
  2. The assembly (1) according to claim 1, wherein the damping device is an annular tab, the cross section of which is shaped like a V, an external surface (40) of a first branch (41) of the V forming the first external surface (40) supported with friction against the first rotor module (2), an external surface (42) of a second branch (43) of the V forming the second external surface (42) supported with friction against the second rotor module (3).
  3. The assembly (1) according to one of claims 1 and 2, wherein an attachment ferrule (38) is shrink-fit to the circumferential extension (34), the second external surface (42) of the damping device being supported with friction on the attachment ferrule (38).
  4. The assembly (1) according to one of claims 1 and 2, wherein the extension (34) bears radial sealing lips (36), the second external surface (42) of the damping device (4) being supported with friction on the sealing lips (36).
  5. The assembly (1) according to claim 4, wherein the support surfaces (40, 42) of the damping device (4) and the surfaces (250, 360) of the platform (25) and of the radial sealing lips (36) are treated, for example by carbon-carbon deposit, so as to guarantee their respective supports.
  6. The assembly (1) according to one of claims 1 to 5, wherein the damping device (4) comprises a coating (48) of the dissipative type, defining the support surfaces (40, 42).
  7. The assembly (1) according to one of claims 1 to 6, wherein the damping device (4) comprises a coating (49) of the viscoelastic type.
  8. The assembly (1) according to one of claims 1 to 7, wherein the damping device (4) comprises bores (45) intended to lighten the damping device (4).
  9. The assembly (1) according to one of claims 1 to 8, wherein the damping device (4) comprises inserts (47), of the metallic type for example, intended to add weight to the damping device (4).
  10. The assembly (1) according to one of claims 1 to 9, wherein the first module (2) is a fan, and the second module (3) is a low-pressure compressor.
  11. The assembly (1) according to one of claims 1 to 10, wherein the damping device (4) is split so as to define two ends (44, 46) facing one another.
  12. A turbomachine comprising an assembly (1) according to one of claims 1 to 11.
  13. An assembly method (E) for an assembly (1) according to one of claims 1 to 11, comprising the steps of:
    • positioning (E1) the damping device (4) between the first rotor module (2) and the second rotor module (3) so that the first external surface (40) of the damping device (4) is supported with friction against the first module (2), and the second external surface (42) of the damping device (4) is supported with friction against the second module (3), and
    • preloading the damping device (4) against the modules (2, 3), so as to couple them in order to damp their respective vibrational movements during operation.
EP18833974.1A 2017-12-18 2018-12-18 Damper device Active EP3728794B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1762358A FR3075284B1 (en) 2017-12-18 2017-12-18 SHOCK ABSORBER
FR1762545A FR3075254B1 (en) 2017-12-19 2017-12-19 SHOCK ABSORBER DEVICE
PCT/FR2018/053375 WO2019122691A1 (en) 2017-12-18 2018-12-18 Damper device

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

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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3724455A1 (en) * 2017-12-14 2020-10-21 Safran Aircraft Engines Damper device

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB670665A (en) 1949-07-28 1952-04-23 Rolls Royce Improvements in or relating to compressors and turbines
US2999668A (en) 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
FR2585069B1 (en) * 1985-07-16 1989-06-09 Snecma DEVICE FOR LIMITING THE ANGULAR DEFLECTION OF BLADES MOUNTED ON A TURBOMACHINE ROTOR DISC
US5205713A (en) 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5820346A (en) * 1996-12-17 1998-10-13 General Electric Company Blade damper for a turbine engine
FR2888876B1 (en) * 2005-07-21 2011-04-01 Snecma DEVICE FOR DAMPING THE VIBRATION OF A ROTOR IN A TURBOMACHINE
FR2915510B1 (en) 2007-04-27 2009-11-06 Snecma Sa SHOCK ABSORBER FOR TURBOMACHINE BLADES
FR2918109B1 (en) 2007-06-26 2013-05-24 Snecma MOBILE WHEEL FOR A TURBOJET AND TURBOJET COMPRISING THE SAME
FR2922587B1 (en) * 2007-10-22 2010-02-26 Snecma TURBOMACHINE WHEEL
FR2923557B1 (en) 2007-11-12 2010-01-22 Snecma BLOWER DRAWER ASSEMBLY AND ITS SHOCK ABSORBER, BLOWER DAMPER AND METHOD FOR CALIBRATING THE SHOCK ABSORBER
US8371816B2 (en) * 2009-07-31 2013-02-12 General Electric Company Rotor blades for turbine engines
FR2949142B1 (en) 2009-08-11 2011-10-14 Snecma VIBRATION SHOCK ABSORBER BLOCK FOR BLOWER DAWN
US8469670B2 (en) * 2009-08-27 2013-06-25 Rolls-Royce Corporation Fan assembly
US8540488B2 (en) * 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8454303B2 (en) * 2010-01-14 2013-06-04 General Electric Company Turbine nozzle assembly
EP2803821A1 (en) * 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Blade device, blade system, and corresponding method of manufacturing a blade system
FR3021348B1 (en) 2014-05-20 2016-06-10 Snecma TURBINE ROTOR FOR A GAS TURBINE ENGINE
CA2966126C (en) 2014-10-15 2023-02-28 Safran Aircraft Engines Rotary assembly for a turbine engine comprising a self-supported rotor collar
CN204941612U (en) * 2015-09-16 2016-01-06 中国航空工业集团公司沈阳发动机设计研究所 A kind of compressible damping block
FR3047512B1 (en) 2016-02-05 2019-11-15 Safran Aircraft Engines VIBRATION DAMPING DEVICE FOR TURBOMACHINE BLADE
US10724375B2 (en) * 2016-02-12 2020-07-28 General Electric Company Gas turbine engine with ring damper

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3724455A1 (en) * 2017-12-14 2020-10-21 Safran Aircraft Engines Damper device

Also Published As

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

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