EP3097266B1 - Mobile member of a turbomachine which comprises means for changing the resonance frequency of same - Google Patents

Mobile member of a turbomachine which comprises means for changing the resonance frequency of same Download PDF

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Publication number
EP3097266B1
EP3097266B1 EP15704057.7A EP15704057A EP3097266B1 EP 3097266 B1 EP3097266 B1 EP 3097266B1 EP 15704057 A EP15704057 A EP 15704057A EP 3097266 B1 EP3097266 B1 EP 3097266B1
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EP
European Patent Office
Prior art keywords
rotor
speed
rotational speed
critical speed
critical
Prior art date
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Active
Application number
EP15704057.7A
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German (de)
French (fr)
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EP3097266A1 (en
Inventor
Julien Michel Patrick Christian AUSTRUY
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
SNECMA Services SA
SNECMA SAS
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Publication of EP3097266A1 publication Critical patent/EP3097266A1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention proposes an aircraft turbomachine rotor which comprises means for modifying its critical speed, as a function of the operating conditions of the turbomachine.
  • the critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.
  • a movable turbomachine member such as a turbomachine rotor, has a critical speed of its own. When the rotor rotates at a speed of rotation very close to this critical speed, the vibrations of the rotor are amplified, which affects the efficiency of the turbomachine.
  • the document US 2005/152626 discloses a device for modifying the critical speed of a rotor guide bearing support having two mechanical structures bearing different stiffnesses combined to carry the bearing, whose resonance frequencies are distinct.
  • the support also comprises means for modifying the angular position of the structures relative to one another so that the critical speed of the support is equal to one or the other of two critical speeds of the structures.
  • the object of the invention is to propose a rotor which is able to rotate at a speed of rotation which is always different from the critical speed of the rotor.
  • the modification of the critical speed of the rotor of the turbomachine, in operation, makes it possible to switch from one critical speed to another, when the rotational speed of the rotor is approaching one of the critical speeds.
  • the component consists of an inverted flexible cage type system, whether or not providing flexibility to the means for modifying the critical speed of the rotor according to whether it is in one or the other of its two operating states.
  • the drive means comprise at least one actuating member which is movably mounted and is able to move radially by centrifugal action when the rotational speed of the rotor is greater than said predefined rotation speed.
  • the drive means comprise an insert movable along the main axis of the rotor and which is able to be coupled with the component to change the state of the component.
  • the drive means comprise means for transforming the radial displacement of the actuating member into an axial displacement of the insert.
  • the means for transforming the radial displacement of the actuating member comprise two portions of revolution facing each other and movable relative to one another, between which the actuating member is arranged and the bearing faces vis-à-vis the portions of revolution are inclined relative to each other.
  • the drive means comprise elastic means for driving the insert to a position corresponding to the state of the component associated with a critical speed of the rotor less than the predefined rotational speed.
  • the drive means comprise a radial main orientation wall which is axially convex, which is connected to the insert, and said wall curved is elastically deformable and is able to occupy two stable shapes distributed on each side of a radial plane passing through a radially outer edge of the curved wall.
  • the means for changing the critical speed of the rotor are made so as to reduce the critical speed of the rotor when the rotation speed of the rotor is greater than the predefined rotation speed and so as to increase the critical speed of the rotor when the rotational speed of the rotor is lower than the predefined rotation speed.
  • the invention also proposes an aircraft turbomachine comprising a rotor according to the invention, which is provided with means able to change the critical speed of the rotor when the rotational speed of the rotor is greater or less than a predefined rotational speed.
  • figure 1 a portion of an aircraft turbine engine rotor 10 such as a turboprop.
  • the invention is not limited to a rotor 10 and that the invention can also be applied to another component of the turbomachine which is rotatable, such as for example a power transmission shaft.
  • the rotor 10 comprises a shaft 12 mounted to rotate with respect to the stator (not shown) of the turbomachine about the main axis A of the rotor 10.
  • the shaft 12 carries a plurality of components (not shown) of the rotor 10 such as for example compressor blades or turbine blades.
  • the rotor 10 and the shaft 12 vibrate at a frequency corresponding to the speed of rotation.
  • the amplitude of these vibrations of the rotor 10 and of the shaft 12 depends on the speed of rotation of the rotor 10.
  • the amplitude of the vibrations increases as the speed of rotation of the rotor 10 approaches a critical speed of the rotor.
  • the critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.
  • This critical speed of the rotor 10 depends on the design of the turbomachine, it depends in particular on the mass of the components of the rotor 10, as well as the position of the guide surfaces of the shaft 12 in rotation in the stator.
  • the vibrations of the rotor 10 have a large amplitude which can damage the rotor 10 or the stator.
  • the rotor comprises means 14 making it possible to modify the critical speed of the rotor 10 when the speed of rotation of the rotor 10 approaches the critical speed of the rotor 10.
  • the means 14 for modifying the critical speed of the rotor 10 are made so as to change the critical speed of the rotor 10 in a manner that is almost instantaneous, when the speed of rotation of the rotor becomes greater than a predefined rotational speed or when the speed of rotation of the rotor 10 becomes lower than the predefined rotation speed.
  • the means 14 for modifying the critical speed then form a so-called "bistable" system, capable of occupying two stable operating states, each stable operating state being associated with a range of rotational speed of the rotor 10 greater or less than the speed predefined rotation.
  • This predefined rotation speed is between a first so-called lower critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in a first state, and a second so-called higher critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in their second state.
  • the means 14 for modifying the critical speed are designed so that when the rotor 10 rotates at a speed lower than the predefined speed of rotation, the means 14 for modifying the critical speed are in their second state, the critical speed of the rotor 10 is then the higher critical speed. The rotation speed of the rotor 10 is then always lower than the higher critical speed defined above.
  • the critical speed of the rotor 10 is then the lower critical speed.
  • the rotational speed of the rotor 10 is then always higher than its lower critical speed defined above.
  • the rotor 10 can not reach a rotational speed corresponding to its critical speed.
  • the means 14 for modifying the critical speed comprise a component 16 whose state varies according to whether the means 14 for modifying the critical speed are in their first state or in their second state.
  • the component 16 is an inverted flexible cage type system, that is to say that the flexible cage is coupled to the rotor 10.
  • the flexible cage is coupled to the stator.
  • the change of state of the flexible cage 16 is achieved by coupling it or not with an insert 40.
  • the insert 40 consists of a member integral with the rotor 10, which is axially movable relative to the rotor 10 and relative to the flexible cage 16 between a coupling position with the flexible cage 16 represented at figures 1 and 2 , and a position of non-coupling with the flexible cage 16.
  • the flexible cage 16 is designed so that when it is coupled with the insert 40, forces between the rotor 10 and the stator are transmitted at the level of the flexible cage by the flexible cage 16 and guide surfaces of the rotor 10 These two paths of effort create a stiffness of the flexible cage 16, which gives the rotor 10 its critical speed higher or lower.
  • the means 14 for modifying the critical speed are in their first state.
  • the flexible cage 16 is integral with the shaft 12, it is for example fixed to the shaft 12 by welding.
  • the means 14 for modifying the critical speed of the rotor 10 comprise a device 18 for driving the insert 40, which causes the displacement of the insert 40 between a coupling position with the flexible cage 16 and a position in which the The insert is not coupled with the flexible cage 16 when the rotational speed of the rotor 10 becomes greater or less than the predefined rotational speed.
  • the drive device 18 of the insert 40 causes the displacement of the insert 40 under the effect of the centrifugal action.
  • the drive device 18 is not connected to any control device, which makes it possible to simplify the integration of the means 14 to modify the critical speed of the rotor 10.
  • the drive device 18 comprises a cage 20 which is mounted on the shaft 12, and a cylindrical sleeve 22 which is connected to the insert 40.
  • the cylindrical sleeve 22 is mounted to move relative to the cage 20 in translation along the main axis A of the rotor 10.
  • the cage 20 and the sleeve 22 are integral with the shaft 12 in rotation and they are traversed by the axis 12.
  • the cylindrical sleeve 22 is able to occupy, with respect to the cage 20, a first position represented in FIG. figure 2 corresponding to the coupling position of the insert 40 with the flexible cage 16 and a second position shown in FIG. figure 3 , corresponding to the position in which the insert 40 is not coupled with the flexible cage 16.
  • the guiding of the cylindrical sleeve 22 in displacement relative to the cage 20 is carried out by a first bearing surface 24 integral with the cage 20.
  • the first surface 24 is connected to the rest of the cage 20 via a wall 34 which extends in a radial plane with respect to the axis A.
  • the means 14 for modifying the critical speed of the rotor 10 have a bistable character, that is to say that they have two stable operating positions.
  • the transition between each of the two stable operating positions of the means 14 for modifying the critical speed is performed by means for driving the cylindrical sleeve 22, which change the position of the sleeve 22 when the speed of rotation of the rotor 10 becomes greater or lower than the preset speed.
  • the bistable character of the means 14 for modifying the critical speed of the rotor 10 is furthermore reinforced by a wall 38 of the cage 20 which is axially curved and which is connected at its center to the cylindrical sleeve 22 via a second bearing. 26.
  • the second bearing surface 26 is integral with the cylindrical sleeve 22 in translation axially and the wall 38 is able to deform elastically during the axial displacement of its center.
  • the wall 38 is able to occupy only two stable shapes represented by Figures 2 and 3 , which are distributed on each side of a radial plane passing through the radially outer edge of the wall 38. In each of these stable shapes, the wall 38 is axially convex in one direction or the other.
  • the wall 38 causes the cylindrical sleeve 22 to move very rapidly towards one of its two positions, so that the sleeve 22, and consequently the insert 40, remain very briefly in an intermediate axial position.
  • the curved wall 38 gives the means 14 for modifying the critical speed of the rotor 10 a discontinuous character.
  • the actuating device 18 is designed to drive the cylindrical sleeve 22 in axial displacement so that the second span 26 crosses this hard point when the rotational speed of the rotor 10 becomes equal to the predefined rotation speed for which the means 14 for change the critical speed of the rotor 10 change state.
  • the securing means of the second bearing 26 with the cylindrical sleeve 22, in axial displacement relative to the cage 20 comprise a shoulder 28 of the cylindrical sleeve 22 which is supported in a first direction, here to the left, against an axial end opposite the second bearing 26.
  • the shoulder 28 is here located at one end 22a of the cylindrical sleeve located closest to the component 16.
  • the securing means of the second bearing surface 26 with the cylindrical sleeve 22 also comprise elastic means which constantly exert a bearing force of the second bearing surface 26 against the shoulder 28 in the second direction, that is to say here to the right.
  • These elastic means 30 also exert a permanent drive action of the second bearing 26 towards the stable position of the curved wall 38 shown in FIGS. figures 1 and 2 , corresponding to the second state of the means 14 for modifying the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the higher critical speed.
  • the elastic means 30 consist of a compression spring which is compressed between the two bearing surfaces 24, 26.
  • the actuating device 18 comprises means for driving the cylindrical sleeve 22 in axial displacement towards its second position shown in FIG. figure 3 when the rotational speed of the rotor 10 becomes greater than the predefined speed, corresponding to the first state of the means 14 for changing the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the lower critical speed.
  • These drive means are of the centrifugal effect type, that is to say that they comprise at least one element 32 movable radially with respect to the axis A, which moves radially away from the axis A as the speed of rotation of the rotor 10 increases, by centrifugal effect.
  • the drive means comprise several moving elements 32, which consist of balls interposed axially between the radial wall 34 which carries the first bearing surface 24, and a portion of revolution 36 carried by the second end 22b of the cylindrical sleeve 22.
  • This portion of revolution 36 extends radially outwardly from the second end 22b of the cylindrical sleeve 22 and has a bearing face 36a located opposite a support face 34a of the radial wall 34 which carries the first bearing surface 24, on which the balls 32 bear axially.
  • the facing faces 36a, 34a of the revolution portion 36 and of the radial wall 34 are inclined with respect to each other, that is to say that at least one of these two bearing faces 36a, 34a is of conical shape, and the distance between the bearing faces 36a, 34a decreases away from the main axis A.
  • the cylindrical sleeve 22 drives the second bearing 26 and causes the elastic deformation of the curved wall 38.
  • the angle defined by the bearing faces 34a, 36a, the dimensions and the mass of the balls 32, as well as the dimensions of the spring 30 are defined according to the predefined rotational speed.
  • the curved wall 38 When the curved wall 38 changes state, the elastic return force it exerts changes direction, the curved wall 38 then cooperates with the centrifugal drive means to drive the cylindrical sleeve 22, against the return force exerted by the spring 30.
  • the cylindrical sleeve 22 is driven towards its second position for which the insert 40 is not coupled with the flexible cage 16 which is in its state with games.
  • the means 14 for modifying the critical speed are in their first state, associated with the low critical speed of the rotor 10.
  • the rotor 10 rotates at a speed greater than the critical speed of the rotor 10.
  • the cylindrical sleeve 22 is driven towards its position. for which the insert 40 is coupled with the flexible cage 16 which is in its state without games.
  • the means 14 for modifying the critical speed are in their second state, associated with the higher critical speed of the rotor 10.
  • the rotor 10 rotates at a speed of rotation lower than the critical speed of the rotor 10.
  • centrifugal action drive means with the rapid deformation of the convex wall 38 makes it possible to rapidly drive the cylindrical sleeve 22 towards its position shown in FIG. figure 3 . This therefore allows for a rapid withdrawal of the insert 40 from the flexible cage 16, to change the critical speed of the rotor 10.
  • the rotor 10 also contains guide bearings 42, which are here three in number, and which rotate the shaft 12, means 14 to change the critical speed of the rotor 10, and the flexible cage 16 .
  • a first bearing 42 is arranged at an upstream portion of the shaft 12, according to the flow direction of the gas in the turbomachine, here on the right side of the figures. This first bearing 42 is located at the inlet casing of the turbomachine.
  • the two other bearings 42 are arranged on either side of a low-pressure turbine of the turbomachine.
  • the second bearing 42 which is arranged at a downstream portion of the shaft 12. Is connected to an exhaust casing of the low pressure turbine.
  • the third bearing 42 which is located between the two other bearings 42, is connected to the flexible cage 16 and is connected to an inter-turbine casing.
  • the component 16 is a mobile mass, which can be selectively coupled or not to the shaft 12 via the means 14 for modifying the critical speed or which can be moved axially by the means 14 for modifying the critical speed.
  • the change of state of the mobile mass 16 then consists of a selective coupling, or a displacement of the moving mass 16, and makes it possible to modify the critical speed of the rotor 10 as described above.

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

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention propose un rotor de turbomachine d'aéronef qui comporte des moyens pour modifier sa vitesse critique, en fonction des conditions de fonctionnement de la turbomachine. La vitesse critique étant définie comme la coïncidence entre les fréquences de rotation et de résonnance du rotor.The invention proposes an aircraft turbomachine rotor which comprises means for modifying its critical speed, as a function of the operating conditions of the turbomachine. The critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Un organe mobile de turbomachine, tel qu'un rotor de turbomachine, possède une vitesse critique qui lui est propre. Lorsque le rotor tourne à une vitesse de rotation très proche de cette vitesse critique, les vibrations du rotor sont amplifiées, ce qui nuit à l'efficacité de la turbomachine.A movable turbomachine member, such as a turbomachine rotor, has a critical speed of its own. When the rotor rotates at a speed of rotation very close to this critical speed, the vibrations of the rotor are amplified, which affects the efficiency of the turbomachine.

Pour limiter ces vibrations, il est connu de relier le rotor au stator de la turbomachine par des moyens d'amortissement.To limit these vibrations, it is known to connect the rotor to the stator of the turbomachine by damping means.

Il est aussi connu de réduire la période de temps pendant laquelle le rotor tourne à la vitesse de rotation proche de la vitesse critique. Pour cela, les accélérations ou décélérations du rotor sont mises en oeuvre rapidement, ce qui présente l'inconvénient d'appliquer au rotor, ainsi qu'à l'ensemble de la turbomachine, des contraintes mécaniques importantes.It is also known to reduce the period of time during which the rotor rotates at the speed of rotation close to the critical speed. For this, the accelerations or decelerations of the rotor are implemented quickly, which has the disadvantage of applying to the rotor, as well as to the entire turbine engine, significant mechanical stresses.

Ces solutions ne sont que partiellement efficaces, car elles soumettent quand même la turbomachine à des amplitudes de vibrations importantes lorsque le rotor tourne à une vitesse de rotation proche de la vitesse critique du rotor.These solutions are only partially effective because they still subject the turbomachine to large vibration amplitudes when the rotor rotates at a rotation speed close to the critical speed of the rotor.

Le document US-2005/152626 décrit un dispositif de modification de la vitesse critique d'un support de palier de guidage d'un rotor comportant deux structures mécaniques portantes de raideurs différentes combinées pour porter le palier, dont les fréquences de résonance propres sont distinctes. Le support comporte aussi des moyens pour modifier la position angulaire des structures l'une par rapport à l'autre pour que la vitesse critique du support soit égale à l'une ou l'autre de deux vitesses critique des structures.The document US 2005/152626 discloses a device for modifying the critical speed of a rotor guide bearing support having two mechanical structures bearing different stiffnesses combined to carry the bearing, whose resonance frequencies are distinct. The support also comprises means for modifying the angular position of the structures relative to one another so that the critical speed of the support is equal to one or the other of two critical speeds of the structures.

Ce document décrit donc des moyens qui nécessitent un organe de commande provoquant le changement de la position angulaire relative des deux structures.This document therefore describes means that require a control member causing the change of the relative angular position of the two structures.

L'invention a pour but de proposer un rotor qui est apte à tourner à une vitesse de rotation qui est toujours différente de la vitesse critique du rotor.The object of the invention is to propose a rotor which is able to rotate at a speed of rotation which is always different from the critical speed of the rotor.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention propose un rotor de turbomachine d'aéronef d'axe principal A, selon la revendication 1, qui comporte des moyens pour modifier la vitesse critique du rotor entre une première vitesse critique et une deuxième vitesse critique selon que la vitesse de rotation du rotor est inférieure ou supérieure à une vitesse de rotation prédéfinie comprise entre la première vitesse critique et la deuxième vitesse critique,
lesdits moyens pour modifier la vitesse critique du rotor (10) comportant :

  • un composant qui est apte à occuper un premier état ou un deuxième état selon que la vitesse de rotation du rotor est inférieure ou supérieure à la vitesse de rotation prédéfinie, chaque état du composant correspondant à une vitesse critique du rotor, et
  • des moyens d'entrainement du composant vers l'un ou l'autre de ses deux états en fonction de la vitesse de rotation du rotor,
caractérisé en ce que les moyens pour modifier la vitesse critique du rotor comportent en outre un composant qui coopère avec les moyens d'entrainement et qui est apte à être déformé élastiquement entre l'une ou l'autre de deux formes stables correspondant chacune à un état dudit composant.The invention proposes a main-axis aircraft turbomachine rotor A according to claim 1, which comprises means for modifying the critical speed of the rotor between a first critical speed and a second critical speed depending on whether the speed of rotation of the rotor rotor is less than or greater than a predefined rotational speed between the first critical speed and the second critical speed,
said means for changing the critical speed of the rotor (10) comprising:
  • a component which is capable of occupying a first state or a second state depending on whether the rotational speed of the rotor is lower or higher than the predefined rotational speed, each state of the component corresponding to a critical speed of the rotor, and
  • means for driving the component towards one or the other of its two states as a function of the speed of rotation of the rotor,
characterized in that the means for modifying the critical speed of the rotor further comprise a component which cooperates with the drive means and which is adapted to be elastically deformed between one or the other of two stable shapes each corresponding to a state of said component.

La modification de la vitesse critique du rotor de la turbomachine, en fonctionnement, permet de commuter d'une vitesse critique à une autre, lorsque la vitesse de rotation du rotor se rapproche de l'une des vitesses critique.The modification of the critical speed of the rotor of the turbomachine, in operation, makes it possible to switch from one critical speed to another, when the rotational speed of the rotor is approaching one of the critical speeds.

Cela permet d'éviter que le rotor ne tourne à une vitesse correspondant à sa vitesse critique, limitant par conséquent les contraintes mécaniques dans la turbomachine. Aussi, la commutation peut être effectuée rapidement.This makes it possible to prevent the rotor from rotating at a speed corresponding to its critical speed, thereby limiting the mechanical stresses in the turbomachine. Also, switching can be done quickly.

De préférence, le composant consiste en un système du type à cage souple inversée, conférant ou non une souplesse aux moyens pour modifier la vitesse critique du rotor selon qu'il est dans l'un ou l'autre de ses deux états de fonctionnement.Preferably, the component consists of an inverted flexible cage type system, whether or not providing flexibility to the means for modifying the critical speed of the rotor according to whether it is in one or the other of its two operating states.

De préférence, les moyens d'entrainement comportent au moins un organe d'actionnement qui est monté mobile et est apte à se déplacer radialement par action centrifuge lorsque la vitesse de rotation du rotor est supérieure à ladite vitesse de rotation prédéfinie.Preferably, the drive means comprise at least one actuating member which is movably mounted and is able to move radially by centrifugal action when the rotational speed of the rotor is greater than said predefined rotation speed.

De préférence, les moyens d'entrainement comportent un insert mobile le long de l'axe principal du rotor et qui est apte à être accouplé avec le composant pour changer l'état du composant.Preferably, the drive means comprise an insert movable along the main axis of the rotor and which is able to be coupled with the component to change the state of the component.

De préférence, les moyens d'entrainement comportent des moyens de transformation du déplacement radial de l'organe d'actionnement en un déplacement axial de l'insert.Preferably, the drive means comprise means for transforming the radial displacement of the actuating member into an axial displacement of the insert.

De préférence, les moyens de transformation du déplacement radial de l'organe d'actionnement comportent deux portions de révolution en vis-à-vis et mobiles l'une par rapport à l'autre, entre lesquelles l'organe d'actionnement est disposé et les faces d'appui en vis-à-vis des portions de révolution sont inclinées l'une par rapport à l'autre.Preferably, the means for transforming the radial displacement of the actuating member comprise two portions of revolution facing each other and movable relative to one another, between which the actuating member is arranged and the bearing faces vis-à-vis the portions of revolution are inclined relative to each other.

De préférence, les moyens d'entrainement comportent des moyens élastiques d'entraînement de l'insert vers une position correspondant à l'état du composant associé à une vitesse critique du rotor inférieure à la vitesse de rotation prédéfinie.
les moyens d'entrainement comportent une paroi d'orientation principale radiale qui est bombée axialement, qui est reliée à l'insert, et ladite paroi bombée est déformable élastiquement et est apte à occuper deux formes stables réparties de chaque côté d'un plan radial passant par un bord radialement externe de la paroi bombée.Preferably, the drive means comprise elastic means for driving the insert to a position corresponding to the state of the component associated with a critical speed of the rotor less than the predefined rotational speed.
the drive means comprise a radial main orientation wall which is axially convex, which is connected to the insert, and said wall curved is elastically deformable and is able to occupy two stable shapes distributed on each side of a radial plane passing through a radially outer edge of the curved wall.

De préférence, les moyens pour changer la vitesse critique du rotor sont réalisés de manière à réduire la vitesse critique du rotor lorsque la vitesse de rotation du rotor est supérieure à la vitesse de rotation prédéfinie et de manière à augmenter la vitesse critique du rotor lorsque la vitesse de rotation du rotor est inférieure à la vitesse de rotation prédéfinie.Preferably, the means for changing the critical speed of the rotor are made so as to reduce the critical speed of the rotor when the rotation speed of the rotor is greater than the predefined rotation speed and so as to increase the critical speed of the rotor when the rotational speed of the rotor is lower than the predefined rotation speed.

L'invention propose aussi une turbomachine d'aéronef comportant un rotor selon l'invention, qui est muni de moyens aptes à changer la vitesse critique du rotor lorsque la vitesse de rotation du rotor est supérieure ou inférieure à une vitesse de rotation prédéfinie.The invention also proposes an aircraft turbomachine comprising a rotor according to the invention, which is provided with means able to change the critical speed of the rotor when the rotational speed of the rotor is greater or less than a predefined rotational speed.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui va suivre pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels :

  • la figure 1 est une représentation schématique en section axiale d'une partie d'un rotor de turbomachine réalisé selon l'invention ;
  • la figure 2 est un détail à plus grande échelle des moyens d'accouplement de l'organe mobile avec l'arbre, représentés en position de séparation ;
  • la figure 3 est une vue similaire à celle de la figure 2, montrant les moyens d'accouplement en position d'accouplement.
Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:
  • the figure 1 is a schematic representation in axial section of a portion of a turbomachine rotor made according to the invention;
  • the figure 2 is a detail on a larger scale of the coupling means of the movable member with the shaft, shown in the separation position;
  • the figure 3 is a view similar to that of the figure 2 , showing the coupling means in the coupling position.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

On a représenté à la figure 1 une partie d'un rotor 10 de turbomachine d'aéronef telle qu'un turbopropulseur.We have shown figure 1 a portion of an aircraft turbine engine rotor 10 such as a turboprop.

Il sera compris que l'invention n'est pas limitée à un rotor 10 et que l'invention peut aussi s'appliquer à un autre composant de la turbomachine qui est mobile en rotation, tel que par exemple un arbre de transmission de puissance.It will be understood that the invention is not limited to a rotor 10 and that the invention can also be applied to another component of the turbomachine which is rotatable, such as for example a power transmission shaft.

Le rotor 10 comporte un arbre 12 monté mobile en rotation par rapport au stator (non représenté) de la turbomachine autour de l'axe principal A du rotor 10. L'arbre 12 porte une pluralité de composants (non représentés) du rotor 10 tels que par exemple des aubes de compresseur ou des aubes de turbine.The rotor 10 comprises a shaft 12 mounted to rotate with respect to the stator (not shown) of the turbomachine about the main axis A of the rotor 10. The shaft 12 carries a plurality of components (not shown) of the rotor 10 such as for example compressor blades or turbine blades.

Lors du fonctionnement de la turbomachine, malgré un équilibrage dynamique du rotor 10, le rotor 10, ainsi que l'arbre 12 vibrent à une fréquence correspondant à la vitesse de rotation.During operation of the turbomachine, despite dynamic balancing of the rotor 10, the rotor 10 and the shaft 12 vibrate at a frequency corresponding to the speed of rotation.

L'amplitude de ces vibrations du rotor 10 et de l'arbre 12 dépend de la vitesse de rotation du rotor 10. En particulier, l'amplitude des vibrations augmente lorsque la vitesse de rotation du rotor 10 se rapproche d'une vitesse critique du rotor 10. La vitesse critique étant définie comme la coïncidence entre les fréquences de rotation et de résonnance du rotor.The amplitude of these vibrations of the rotor 10 and of the shaft 12 depends on the speed of rotation of the rotor 10. In particular, the amplitude of the vibrations increases as the speed of rotation of the rotor 10 approaches a critical speed of the rotor. rotor 10. The critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.

Cette vitesse critique du rotor 10 dépend de la conception de la turbomachine, elle dépend notamment de la masse des composants du rotor 10, ainsi que de la position des portées de guidage de l'arbre 12 en rotation dans le stator.This critical speed of the rotor 10 depends on the design of the turbomachine, it depends in particular on the mass of the components of the rotor 10, as well as the position of the guide surfaces of the shaft 12 in rotation in the stator.

Si le rotor 10 tourne à cette vitesse critique, les vibrations du rotor 10 ont une amplitude importante pouvant endommager le rotor 10 ou le stator.If the rotor 10 rotates at this critical speed, the vibrations of the rotor 10 have a large amplitude which can damage the rotor 10 or the stator.

Pour empêcher que le rotor 10 ne tourne à une vitesse de rotation proche de sa vitesse critique, le rotor comporte des moyens 14 permettant de modifier la vitesse critique du rotor 10 lorsque la vitesse de rotation du rotor 10 se rapproche de la vitesse critique du rotor 10.To prevent the rotor 10 from rotating at a rotational speed close to its critical speed, the rotor comprises means 14 making it possible to modify the critical speed of the rotor 10 when the speed of rotation of the rotor 10 approaches the critical speed of the rotor 10.

Les moyens 14 de modification de la vitesse critique du rotor 10 sont réalisés de manière à changer la vitesse critique du rotor 10 de manière quasiment instantanée, lorsque la vitesse de rotation du rotor devient supérieure à une vitesse de rotation prédéfinie ou lorsque la vitesse de rotation du rotor 10 devient inférieure à la vitesse de rotation prédéfinie.The means 14 for modifying the critical speed of the rotor 10 are made so as to change the critical speed of the rotor 10 in a manner that is almost instantaneous, when the speed of rotation of the rotor becomes greater than a predefined rotational speed or when the speed of rotation of the rotor 10 becomes lower than the predefined rotation speed.

Les moyens 14 de modification de la vitesse critique forment alors un système dit "bistable", apte à occuper deux états stables de fonctionnement, chaque état stable de fonctionnement étant associé à une plage de vitesse de rotation du rotor 10 supérieure ou inférieure à la vitesse de rotation prédéfinie.The means 14 for modifying the critical speed then form a so-called "bistable" system, capable of occupying two stable operating states, each stable operating state being associated with a range of rotational speed of the rotor 10 greater or less than the speed predefined rotation.

Cette vitesse de rotation prédéfinie est comprise entre une première vitesse critique dite inférieure, qui est la vitesse critique du rotor 10 lorsque les moyens 14 de modification de la vitesse critique sont dans un premier état, et une deuxième vitesse critique dite supérieure, qui est la vitesse critique du rotor 10 lorsque les moyens 14 de modification de la vitesse critique sont dans leur deuxième état.This predefined rotation speed is between a first so-called lower critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in a first state, and a second so-called higher critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in their second state.

Aussi, les moyens 14 de modification de la vitesse critique sont conçus pour que lorsque le rotor 10 tourne à une vitesse inférieure à la vitesse de rotation prédéfinie, les moyens 14 de modification de la vitesse critique sont dans leur deuxième état, la vitesse critique du rotor 10 est alors la vitesse critique supérieure. La vitesse de rotation du rotor 10 est alors toujours inférieure à la vitesse critique supérieure définie ci-dessus.Also, the means 14 for modifying the critical speed are designed so that when the rotor 10 rotates at a speed lower than the predefined speed of rotation, the means 14 for modifying the critical speed are in their second state, the critical speed of the rotor 10 is then the higher critical speed. The rotation speed of the rotor 10 is then always lower than the higher critical speed defined above.

Par contre, lorsque le rotor 10 tourne à une vitesse supérieure à la vitesse de rotation prédéfinie, les moyens 14 de modification de la vitesse critique sont dans leur premier état, la vitesse critique du rotor 10 est alors la vitesse critique inférieure. La vitesse de rotation du rotor 10 est alors toujours supérieure à sa vitesse critique inférieure définie ci-dessus.On the other hand, when the rotor 10 rotates at a speed greater than the predefined speed of rotation, the means 14 for modifying the critical speed are in their first state, the critical speed of the rotor 10 is then the lower critical speed. The rotational speed of the rotor 10 is then always higher than its lower critical speed defined above.

Par conséquent, quelle que soit la vitesse de rotation du rotor 10, grâce au changement d'état des moyens 14 de modification de la vitesse critique, le rotor 10 ne peut pas atteindre une vitesse de rotation correspondant à sa vitesse critique.Therefore, regardless of the rotational speed of the rotor 10, by changing the state of the means 14 for modifying the critical speed, the rotor 10 can not reach a rotational speed corresponding to its critical speed.

Pour modifier la vitesse critique du rotor, les moyens 14 de modification de la vitesse critique comportent un composant 16 dont l'état varie selon que les moyens 14 de modification de la vitesse critique sont dans leur premier état ou dans leur deuxième état.To modify the critical speed of the rotor, the means 14 for modifying the critical speed comprise a component 16 whose state varies according to whether the means 14 for modifying the critical speed are in their first state or in their second state.

Selon un mode de réalisation préféré, le composant 16 est un système du type à cage souple inversée, c'est-à-dire que la cage souple est accouplée au rotor 10. Dans un système à cage souple classique, la cage souple est accouplée au stator.According to a preferred embodiment, the component 16 is an inverted flexible cage type system, that is to say that the flexible cage is coupled to the rotor 10. In a conventional flexible cage system, the flexible cage is coupled to the stator.

Le changement d'état de la cage souple 16 est réalisé en l'accouplant ou non avec un insert 40. Comme on peut le voir aux figures, l'insert 40 consiste en un élément solidaire du rotor 10, qui est mobile axialement par rapport au rotor 10 et par rapport à la cage souple 16 entre une position d'accouplement avec la cage souple 16 représentée aux figures 1 et 2, et une position de non accouplement avec la cage souple 16.The change of state of the flexible cage 16 is achieved by coupling it or not with an insert 40. As can be seen in the figures, the insert 40 consists of a member integral with the rotor 10, which is axially movable relative to the rotor 10 and relative to the flexible cage 16 between a coupling position with the flexible cage 16 represented at figures 1 and 2 , and a position of non-coupling with the flexible cage 16.

La cage souple 16 est conçue de manière que lorsqu'elle est accouplée avec l'insert 40, des efforts entre le rotor 10 et le stator sont transmis au niveau de la cage souple par la cage souple 16 et des portées de guidage du rotor 10. Ces deux chemins d'efforts créent une raideur de la cage souple 16, ce qui confère au rotor 10 sa vitesse critique supérieure ou inférieure.The flexible cage 16 is designed so that when it is coupled with the insert 40, forces between the rotor 10 and the stator are transmitted at the level of the flexible cage by the flexible cage 16 and guide surfaces of the rotor 10 These two paths of effort create a stiffness of the flexible cage 16, which gives the rotor 10 its critical speed higher or lower.

Ainsi, lorsque l'insert 40 est accouplé avec la cage souple 16, les moyens 14 de modification de la vitesse critique sont dans leur deuxième état.Thus, when the insert 40 is coupled with the flexible cage 16, the means 14 for modifying the critical speed are in their second state.

Par contre, lorsque l'insert 40 n'est pas accouplé avec la cage souple 16, les efforts à transmettre au niveau de la cage souple 16 ne peuvent transiter que par la cage souple 16. Ce seul chemin d'efforts créé une souplesse du système, ce qui confère au rotor 10 sa vitesse critique inférieure.On the other hand, when the insert 40 is not coupled with the flexible cage 16, the forces to be transmitted at the level of the flexible cage 16 can pass only through the flexible cage 16. This single force path creates a flexibility of the system, which gives the rotor 10 its lower critical speed.

Ainsi, lorsque l'insert 40 n'est pas accouplé avec la cage souple 16, les moyens 14 de modification de la vitesse critique sont dans leur premier état.Thus, when the insert 40 is not coupled with the flexible cage 16, the means 14 for modifying the critical speed are in their first state.

Comme on peut le voir à la figure 1, la cage souple 16 est solidaire de l'arbre 12, elle est par exemple fixée à l'arbre 12 par soudage.As can be seen at figure 1 , the flexible cage 16 is integral with the shaft 12, it is for example fixed to the shaft 12 by welding.

Les moyens 14 pour modifier la vitesse critique du rotor 10 comportent un dispositif 18 d'entrainement de l'insert 40, qui provoque le déplacement de l'insert 40 entre une position d'accouplement avec la cage souple 16 et une position dans laquelle l'insert n'est pas accouplé avec la cage souple 16 lorsque la vitesse de rotation du rotor 10 devient supérieure ou inférieure à la vitesse de rotation prédéfinie.The means 14 for modifying the critical speed of the rotor 10 comprise a device 18 for driving the insert 40, which causes the displacement of the insert 40 between a coupling position with the flexible cage 16 and a position in which the The insert is not coupled with the flexible cage 16 when the rotational speed of the rotor 10 becomes greater or less than the predefined rotational speed.

Le dispositif d'entrainement 18 de l'insert 40 provoque le déplacement de l'insert 40 sous l'effet de l'action centrifuge. Ainsi, le dispositif d'entrainement 18 n'est relié à aucun dispositif de commande, ce qui permet de simplifier l'intégration des moyens 14 pour modifier la vitesse critique du rotor 10.The drive device 18 of the insert 40 causes the displacement of the insert 40 under the effect of the centrifugal action. Thus, the drive device 18 is not connected to any control device, which makes it possible to simplify the integration of the means 14 to modify the critical speed of the rotor 10.

Comme on peut le voir aux figures, le dispositif d'entrainement 18 comporte une cage 20 qui est montée sur l'arbre 12, et un manchon cylindrique 22 qui est relié à l'insert 40.As can be seen in the figures, the drive device 18 comprises a cage 20 which is mounted on the shaft 12, and a cylindrical sleeve 22 which is connected to the insert 40.

Selon le mode de réalisation représenté aux figures, le manchon cylindrique 22 est monté mobile par rapport à la cage 20 en translation le long de l'axe principal A du rotor 10.According to the embodiment shown in the figures, the cylindrical sleeve 22 is mounted to move relative to the cage 20 in translation along the main axis A of the rotor 10.

La cage 20 et le manchon 22 sont solidaires de l'arbre 12 en rotation et ils sont traversés par l'axe 12.The cage 20 and the sleeve 22 are integral with the shaft 12 in rotation and they are traversed by the axis 12.

Le manchon cylindrique 22 est apte à occuper, par rapport à la cage 20, une première position représentée à la figure 2, correspondant à la position d'accouplement de l'insert 40 avec la cage souple 16 et une deuxième position représentée à la figure 3, correspondant à la position dans laquelle l'insert 40 n'est pas accouplé avec la cage souple 16.The cylindrical sleeve 22 is able to occupy, with respect to the cage 20, a first position represented in FIG. figure 2 corresponding to the coupling position of the insert 40 with the flexible cage 16 and a second position shown in FIG. figure 3 , corresponding to the position in which the insert 40 is not coupled with the flexible cage 16.

Le guidage du manchon cylindrique 22 en déplacement par rapport à la cage 20 est réalisé par une première portée 24 solidaire de la cage 20.The guiding of the cylindrical sleeve 22 in displacement relative to the cage 20 is carried out by a first bearing surface 24 integral with the cage 20.

La première portée 24 est reliée au reste de la cage 20 par l'intermédiaire d'une paroi 34 qui s'étend dans un plan radial par rapport à l'axe A.The first surface 24 is connected to the rest of the cage 20 via a wall 34 which extends in a radial plane with respect to the axis A.

Comme on l'a dit précédemment, les moyens 14 de modification de la vitesse critique du rotor 10 ont un caractère bistable, c'est-à-dire qu'ils possèdent deux positions stables de fonctionnement.As mentioned above, the means 14 for modifying the critical speed of the rotor 10 have a bistable character, that is to say that they have two stable operating positions.

La transition entre chacune des deux positions stables de fonctionnement des moyens 14 de modification de la vitesse critique est réalisée par des moyens d'entrainement du manchon cylindrique 22, qui changent la position du manchon 22 lorsque la vitesse de rotation du rotor 10 devient supérieure ou inférieure à la vitesse prédéfinie.The transition between each of the two stable operating positions of the means 14 for modifying the critical speed is performed by means for driving the cylindrical sleeve 22, which change the position of the sleeve 22 when the speed of rotation of the rotor 10 becomes greater or lower than the preset speed.

Le caractère bistable des moyens 14 pour modifier la vitesse critique du rotor 10 est en outre renforcé par une paroi 38 de la cage 20 qui est bombée axialement et qui est reliée en son centre au manchon cylindrique 22 par l'intermédiaire d'une deuxième portée 26.The bistable character of the means 14 for modifying the critical speed of the rotor 10 is furthermore reinforced by a wall 38 of the cage 20 which is axially curved and which is connected at its center to the cylindrical sleeve 22 via a second bearing. 26.

La deuxième portée 26 est solidaire du manchon cylindrique 22 en translation axialement et la paroi 38 est apte à se déformer élastiquement lors du déplacement axial de son centre.The second bearing surface 26 is integral with the cylindrical sleeve 22 in translation axially and the wall 38 is able to deform elastically during the axial displacement of its center.

De par sa forme bombée, la paroi 38 n'est apte à occuper que deux formes stables représentées aux figures 2 et 3, qui sont réparties de chaque côté d'un plan radial passant par le bord radialement externe de la paroi 38. Dans chacune de ces formes stables, la paroi 38 est bombée axialement dans un sens, ou dans l'autre.Because of its curved shape, the wall 38 is able to occupy only two stable shapes represented by Figures 2 and 3 , which are distributed on each side of a radial plane passing through the radially outer edge of the wall 38. In each of these stable shapes, the wall 38 is axially convex in one direction or the other.

Lorsque la paroi 38 est déformée élastiquement autrement que dans ces deux formes stables, elle a naturellement tendance à revenir vers l'une de ces deux formes, dépendant du fait qu'elle est déformée d'un côté ou de l'autre d'un point dur correspondant globalement au point lorsque son centre est à la même cote axiale que son bord radialement externe.When the wall 38 is elastically deformed otherwise than in these two stable forms, it naturally tends to return to one of these two forms, depending on whether it is deformed on one side or the other of a hard point corresponding globally to the point when its center is at the same axial dimension as its radially outer edge.

Ainsi, lorsque la vitesse de rotation du rotor 10 devient supérieure ou inférieure à la vitesse prédéfinie, la paroi 38 entraine très rapidement le manchon cylindrique 22 vers l'une de ses deux positions, de sorte que le manchon 22, et par conséquent l'insert 40, restent très brièvement dans une position axiale intermédiaire.Thus, when the rotational speed of the rotor 10 becomes greater or less than the predefined speed, the wall 38 causes the cylindrical sleeve 22 to move very rapidly towards one of its two positions, so that the sleeve 22, and consequently the insert 40, remain very briefly in an intermediate axial position.

La paroi bombée 38 confère aux moyens 14 de modification de la vitesse critique du rotor 10 un caractère discontinu.The curved wall 38 gives the means 14 for modifying the critical speed of the rotor 10 a discontinuous character.

Le dispositif d'actionnement 18 est conçu pour entraîner le manchon cylindrique 22 en déplacement axial pour que la deuxième portée 26 franchisse ce point dit dur lorsque la vitesse de rotation du rotor 10 devient égale à la vitesse de rotation prédéfinie pour laquelle les moyens 14 pour modifier la vitesse critique du rotor 10 changent d'état.The actuating device 18 is designed to drive the cylindrical sleeve 22 in axial displacement so that the second span 26 crosses this hard point when the rotational speed of the rotor 10 becomes equal to the predefined rotation speed for which the means 14 for change the critical speed of the rotor 10 change state.

Les moyens de solidarisation de la deuxième portée 26 avec le manchon cylindrique 22, en déplacement axial par rapport à la cage 20 comportent un épaulement 28 du manchon cylindrique 22 qui est en appui dans un premier sens, ici vers la gauche, contre une extrémité axiale en vis-à-vis de la deuxième portée 26. L'épaulement 28 est ici situé à une extrémité 22a du manchon cylindrique située la plus proche du composant 16.The securing means of the second bearing 26 with the cylindrical sleeve 22, in axial displacement relative to the cage 20 comprise a shoulder 28 of the cylindrical sleeve 22 which is supported in a first direction, here to the left, against an axial end opposite the second bearing 26. The shoulder 28 is here located at one end 22a of the cylindrical sleeve located closest to the component 16.

Les moyens de solidarisation de la deuxième portée 26 avec le manchon cylindrique 22 comportent aussi des moyens élastiques qui exercent en permanence un effort d'appui de la deuxième portée 26 contre l'épaulement 28 dans le deuxième sens, c'est-à-dire ici vers la droite.The securing means of the second bearing surface 26 with the cylindrical sleeve 22 also comprise elastic means which constantly exert a bearing force of the second bearing surface 26 against the shoulder 28 in the second direction, that is to say here to the right.

Ces moyens élastiques 30 exercent en outre une action permanente d'entraînement de la deuxième portée 26 vers la position stable de la paroi bombée 38 représentée aux figures 1 et 2, correspondant au deuxième état des moyens 14 pour modifier la vitesse critique du rotor 10, pour lequel la vitesse critique du rotor 10 est la vitesse critique supérieure.These elastic means 30 also exert a permanent drive action of the second bearing 26 towards the stable position of the curved wall 38 shown in FIGS. figures 1 and 2 , corresponding to the second state of the means 14 for modifying the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the higher critical speed.

Ici, les moyens élastiques 30 consistent en un ressort de compression qui est comprimé entre les deux portées 24, 26.Here, the elastic means 30 consist of a compression spring which is compressed between the two bearing surfaces 24, 26.

Le dispositif d'actionnement 18 comporte des moyens d'entraînement du manchon cylindrique 22 en déplacement axial vers sa deuxième position représentée à la figure 3, lorsque la vitesse de rotation du rotor 10 devient supérieure à la vitesse prédéfinie, correspondant au premier état des moyens 14 pour modifier la vitesse critique du rotor 10, pour lequel la vitesse critique du rotor 10 est la vitesse critique inférieure.The actuating device 18 comprises means for driving the cylindrical sleeve 22 in axial displacement towards its second position shown in FIG. figure 3 when the rotational speed of the rotor 10 becomes greater than the predefined speed, corresponding to the first state of the means 14 for changing the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the lower critical speed.

Ces moyens d'entraînement sont du type à effet centrifuge, c'est-à-dire qu'ils comportent au moins un élément 32 mobile radialement par rapport à l'axe A, qui se déplace radialement en s'éloignant de l'axe A au fur et à mesure que la vitesse de rotation du rotor 10 augmente, par effet centrifuge.These drive means are of the centrifugal effect type, that is to say that they comprise at least one element 32 movable radially with respect to the axis A, which moves radially away from the axis A as the speed of rotation of the rotor 10 increases, by centrifugal effect.

Ici, les moyens d'entraînement comportent plusieurs éléments mobiles 32, qui consistent en des billes interposées axialement entre la paroi radiale 34 qui porte la première portée 24, et une portion de révolution 36 portée par la deuxième extrémité 22b du manchon cylindrique 22.Here, the drive means comprise several moving elements 32, which consist of balls interposed axially between the radial wall 34 which carries the first bearing surface 24, and a portion of revolution 36 carried by the second end 22b of the cylindrical sleeve 22.

Cette portion de révolution 36 s'étend radialement vers l'extérieur à partir de la deuxième extrémité 22b du manchon cylindrique 22 et elle comporte une face d'appui 36a située en vis-à-vis d'une face d'appui 34a de la paroi radiale 34 qui porte la première portée 24, sur laquelle les billes 32 sont en appui axialement.This portion of revolution 36 extends radially outwardly from the second end 22b of the cylindrical sleeve 22 and has a bearing face 36a located opposite a support face 34a of the radial wall 34 which carries the first bearing surface 24, on which the balls 32 bear axially.

Les faces d'appui en vis-à-vis 36a, 34a de la portion de révolution 36 et de la paroi radiale 34 sont inclinées l'une par rapport à l'autre, c'est-à-dire qu'au moins une de ces deux faces d'appui 36a, 34a est de forme conique, et la distance entre les faces d'appui 36a, 34a diminue en s'éloignant de l'axe principal A.The facing faces 36a, 34a of the revolution portion 36 and of the radial wall 34 are inclined with respect to each other, that is to say that at least one of these two bearing faces 36a, 34a is of conical shape, and the distance between the bearing faces 36a, 34a decreases away from the main axis A.

De ce fait, lorsque les billes 32 se déplacent radialement vers l'extérieur, en s'éloignant de l'axe principal A, elles s'appuient contre les faces d'appui 34a, 36a et provoquent un déplacement du manchon cylindrique 22 par rapport à la cage 20 vers sa deuxième position.As a result, when the balls 32 move radially outwardly, away from the main axis A, they bear against the bearing faces 34a, 36a and cause the cylindrical sleeve 22 to move relative to each other. to the cage 20 to its second position.

En se déplaçant, le manchon cylindrique 22 entraîne la deuxième portée 26 et provoque la déformation élastique de la paroi bombée 38.By moving, the cylindrical sleeve 22 drives the second bearing 26 and causes the elastic deformation of the curved wall 38.

L'angle défini par les faces d'appui 34a, 36a, les dimensions et la masse des billes 32, ainsi que les dimensions du ressort 30 sont définies en fonction de la vitesse de rotation prédéfinie.The angle defined by the bearing faces 34a, 36a, the dimensions and the mass of the balls 32, as well as the dimensions of the spring 30 are defined according to the predefined rotational speed.

Lorsque le rotor 10 tourne à cette vitesse de rotation prédéfinie, ou à une vitesse de rotation supérieure, l'effort d'appui des billes 32 sur les parois 34a, 36a en vis-à-vis est supérieur à l'effort exercé par le ressort de rappel 30 et par la paroi bombée 38. Le manchon cylindrique 22 est alors entrainé axialement vers sa deuxième position, provoquant un changement d'état de la paroi bombée 38.When the rotor 10 rotates at this predefined rotational speed, or at a higher rotational speed, the bearing force of the balls 32 on the walls 34a, 36a facing each other is greater than the force exerted by the return spring 30 and the curved wall 38. The cylindrical sleeve 22 is then driven axially towards its second position, causing a change of state of the curved wall 38.

Lorsque la paroi bombée 38 change d'état, l'effort élastique de rappel qu'elle exerce change de direction, la paroi bombée 38 coopère alors avec les moyens d'entraînement centrifuge pour entraîner le manchon cylindrique 22, à l'encontre de l'effort de rappel exercé par le ressort 30.When the curved wall 38 changes state, the elastic return force it exerts changes direction, the curved wall 38 then cooperates with the centrifugal drive means to drive the cylindrical sleeve 22, against the return force exerted by the spring 30.

Ainsi, lorsque le rotor 10 tourne à une vitesse de rotation supérieure à la vitesse de rotation prédéfinie, qui est, comme on l'a dit précédemment, supérieure à la vitesse critique inférieure du rotor 10, le manchon cylindrique 22 est entrainé vers sa deuxième position pour laquelle l'insert 40 n'est pas accouplé avec la cage souple 16 qui est donc dans son état avec jeux. Les moyens 14 de modification de la vitesse critique sont dans leur premier état, associé à la vitesse critique basse du rotor 10.Thus, when the rotor 10 rotates at a speed of rotation greater than the predefined rotation speed, which is, as said above, greater than the lower critical speed of the rotor 10, the cylindrical sleeve 22 is driven towards its second position for which the insert 40 is not coupled with the flexible cage 16 which is in its state with games. The means 14 for modifying the critical speed are in their first state, associated with the low critical speed of the rotor 10.

Par conséquent, le rotor 10 tourne à une vitesse supérieure à la vitesse critique du rotor 10.Consequently, the rotor 10 rotates at a speed greater than the critical speed of the rotor 10.

Par contre, lorsque la vitesse de rotation du rotor 10 devient inférieure à cette vitesse de rotation prédéfinie, l'effort exercé par le ressort de rappel 30 est supérieur à l'effort exercé par les billes 32 sur les parois 34a, 36a en vis-à-vis et par l'effort de rappel de la paroi bombée 38. Le manchon cylindrique 22 est alors entraîné par le ressort 30 et la paroi bombée 38 vers sa position représentée aux figures 1 et 2.On the other hand, when the rotational speed of the rotor 10 becomes lower than this predefined rotational speed, the force exerted by the return spring 30 is greater than the force exerted by the balls 32 on the walls 34a, 36a facing the and by the effort return of the curved wall 38. The cylindrical sleeve 22 is then driven by the spring 30 and the curved wall 38 to its position shown in FIGS. figures 1 and 2 .

Ainsi, lorsque le rotor 10 tourne à une vitesse de rotation inférieure à la vitesse de rotation prédéfinie, qui est, comme on l'a dit précédemment, inférieure à la vitesse critique supérieure du rotor 10, le manchon cylindrique 22 est entrainé vers sa position pour laquelle l'insert 40 est accouplé avec la cage souple 16 qui est donc dans son état sans jeux. Les moyens 14 de modification de la vitesse critique sont dans leur deuxième état, associé à la vitesse critique supérieure du rotor 10.Thus, when the rotor 10 rotates at a rotational speed lower than the predefined rotational speed, which is, as previously stated, less than the upper critical speed of the rotor 10, the cylindrical sleeve 22 is driven towards its position. for which the insert 40 is coupled with the flexible cage 16 which is in its state without games. The means 14 for modifying the critical speed are in their second state, associated with the higher critical speed of the rotor 10.

Par conséquent, le rotor 10 tourne à une vitesse de rotation inférieure à la vitesse critique du rotor 10.Consequently, the rotor 10 rotates at a speed of rotation lower than the critical speed of the rotor 10.

La combinaison des moyens d'entrainement par action centrifuge avec la déformation rapide de la paroi bombée 38 permet d'entraîner rapidement le manchon cylindrique 22 vers sa position représentée à la figure 3. Cela permet par conséquent d'avoir un retrait rapide de l'insert 40 hors de la cage souple 16, pour modifier la vitesse critique du rotor 10.The combination of the centrifugal action drive means with the rapid deformation of the convex wall 38 makes it possible to rapidly drive the cylindrical sleeve 22 towards its position shown in FIG. figure 3 . This therefore allows for a rapid withdrawal of the insert 40 from the flexible cage 16, to change the critical speed of the rotor 10.

Le rotor 10 compote aussi des paliers de guidage 42, qui sont ici au nombre de trois, et qui réalisent le guidage en rotation de l'arbre 12, des moyens 14 pour modifier la vitesse critique du rotor 10, et de la cage souple 16.The rotor 10 also contains guide bearings 42, which are here three in number, and which rotate the shaft 12, means 14 to change the critical speed of the rotor 10, and the flexible cage 16 .

Un premier palier 42 est agencé au niveau d'une partie amont de l'arbre 12, selon le sens d'écoulement des gaz dans la turbomachine, ici du côté droit des figures. Ce premier palier 42 est situé au niveau du carter d'entrée de la turbomachine.A first bearing 42 is arranged at an upstream portion of the shaft 12, according to the flow direction of the gas in the turbomachine, here on the right side of the figures. This first bearing 42 is located at the inlet casing of the turbomachine.

Les deux autres paliers 42 sont agencés de part et d'autre d'une turbine basse pression de la turbomachine.The two other bearings 42 are arranged on either side of a low-pressure turbine of the turbomachine.

Le deuxième palier 42, qui est agencé au niveau d'une partie aval de l'arbre 12. Est relié à un carter d'échappement de la turbine basse pression.The second bearing 42, which is arranged at a downstream portion of the shaft 12. Is connected to an exhaust casing of the low pressure turbine.

Le troisième palier 42, qui est situé entre les deux autres paliers 42, est relié à la cage souple 16 et est relié à un carter inter-turbines.The third bearing 42, which is located between the two other bearings 42, is connected to the flexible cage 16 and is connected to an inter-turbine casing.

Selon une variante de réalisation, le composant 16 est une masse mobile, qui peut être sélectivement accouplée ou non à l'arbre 12 par l'intermédiaire des moyens 14 de modification de vitesse critique ou qui peut être déplacée axialement par les moyens 14 de modification de la vitesse critique.According to an alternative embodiment, the component 16 is a mobile mass, which can be selectively coupled or not to the shaft 12 via the means 14 for modifying the critical speed or which can be moved axially by the means 14 for modifying the critical speed.

Le changement d'état de la masse mobile 16 consiste alors en un accouplement sélectif, ou un déplacement de la masse mobile 16, et permet de modifier la vitesse critique du rotor 10 comme décrit précédemment.The change of state of the mobile mass 16 then consists of a selective coupling, or a displacement of the moving mass 16, and makes it possible to modify the critical speed of the rotor 10 as described above.

Claims (10)

  1. Rotor (10) of an aircraft turbomachine having a main axis A, which comprises means (14) for modifying a critical speed of the rotor (10) between a first critical speed and a second critical speed, depending on whether the rotational speed of the rotor (10) is lower or higher than a predefined rotational speed between the first critical speed and the second critical speed,
    said means (14) for modifying the critical speed of the rotor (10) comprising:
    - component (16) that is capable of occupying a first state or a second state depending on whether the rotational speed of the rotor (10) is lower or higher than the predefined rotational speed, each state of the component (16) corresponding to a critical speed of the rotor (10), and
    - means (18) for driving the component (16) towards one or the other of the two states thereof, depending on the rotational speed of the rotor (10),
    characterised in that the means (14) for modifying the critical speed of the rotor (10) further comprise a component (38) that engages with the drive means (18) and is capable of being deformed elastically between one or the other of two stable forms, each of which corresponding to a state of said component (16).
  2. Rotor (10) according to claim 1, characterised in that the component (16) consists of a system such as a flexible, inverted cage, providing flexibility or not to the means (14) for modifying the critical speed of the rotor (10), depending on whether it is in one or the other of the two operating states thereof.
  3. Rotor (10) according to any of the previous claims, characterised in that the drive means (18) comprise at least one actuating member (32), which is movably mounted and is capable of moving radially under a centrifugal effect when the rotational speed of the rotor (10) is higher than said predefined rotational speed.
  4. Rotor (10) according to any of the previous claims, characterised in that the drive means (18) comprise an insert (40) capable of moving along the main axis of the rotor (10) and which is capable of being coupled with the component (16) in order to change the state of the component (16).
  5. Rotor (10) according to claim 4, characterised in that the drive means (18) comprise means (34, 36) for transforming the radial movement of the actuating member (32) into an axial movement of the insert (40).
  6. Rotor (10) according to claim 5, characterised in that the means (34, 36) for transforming the radial movement of the actuating member (32) comprise two revolving portions facing each other and mobile in relation to each other, between which the actuating member (32) is positioned and in that the support surfaces (34a, 36a) of the revolving portions facing each other are inclined in relation to each other.
  7. Rotor (10) according to any of claims 4 to 6, characterised in that the drive means (18) comprise elastic means for driving the insert (40) towards a position corresponding to the state of the component (16) associated with a rotational speed of the rotor (10) that is below the predefined rotational speed.
  8. Rotor (10) according to any of claims 4 to 7, characterised in that the drive means (18) comprise a main radial orientation wall (38) that is axially convex and linked to the insert (40), and in that said convex wall (38) is elastically deformable and capable of occupying two stable forms distributed on either side of a radial plane, passing through a radially outer edge of the convex wall (38).
  9. Rotor (10) according to any of the previous claims, characterised in that the means for changing the critical speed of the rotor (10) are produced such that they reduce the critical speed of the rotor (10) when the rotational speed of the rotor (10) is higher than the predefined rotational speed and such that they increase the critical speed of the rotor (10) when the rotational speed of the rotor (10) is lower than the predefined rotational speed.
  10. Aircraft turbomachine comprising a rotor (10) according to any one of the previous claims, which is equipped with means (14) capable of modifying the critical speed of the rotor (10) when the rotational speed of the rotor (10) is higher or lower than a predefined rotational speed.
EP15704057.7A 2014-01-20 2015-01-19 Mobile member of a turbomachine which comprises means for changing the resonance frequency of same Active EP3097266B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1450424A FR3016659B1 (en) 2014-01-20 2014-01-20 MOBILE TURBOMACHINE ORGAN WHICH HAS MEANS FOR CHANGING ITS RESONANCE FREQUENCY
PCT/FR2015/050118 WO2015107310A1 (en) 2014-01-20 2015-01-19 Mobile member of a turbomachine which comprises means for changing the resonance frequency of same

Publications (2)

Publication Number Publication Date
EP3097266A1 EP3097266A1 (en) 2016-11-30
EP3097266B1 true EP3097266B1 (en) 2017-11-15

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EP15704057.7A Active EP3097266B1 (en) 2014-01-20 2015-01-19 Mobile member of a turbomachine which comprises means for changing the resonance frequency of same

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US (1) US9624777B2 (en)
EP (1) EP3097266B1 (en)
CN (1) CN105917079B (en)
BR (1) BR112016016336B1 (en)
CA (1) CA2936772C (en)
FR (1) FR3016659B1 (en)
RU (1) RU2683334C1 (en)
WO (1) WO2015107310A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3064764B1 (en) * 2017-03-28 2019-06-28 Hutchinson DYNAMIC EFFORTS GENERATOR COMPRISING AT LEAST TWO BALOURS AND ACTUATOR COMPRISING SUCH GENERATORS

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3032985A (en) * 1960-07-27 1962-05-08 Gen Motors Corp Dual rotor governor
FR2336550A1 (en) * 1975-12-24 1977-07-22 Europ Propulsion LONG SHAFT MOUNTING, ESPECIALLY FOR TURBOMACHINE
US4117742A (en) * 1977-07-29 1978-10-03 Stein Philip C Permanent automatic rotor balancer for shafts operating above critical speed
RU1828166C (en) * 1989-11-09 1995-09-10 Научно-производственное предпри тие "Завод им.В.Я.Климова" Whirling arm (its variants)
FR2864995B1 (en) * 2004-01-12 2008-01-04 Snecma Moteurs DOUBLE RAIDEUR BEARING SUPPORT
EP1892379B1 (en) * 2006-08-16 2015-11-18 Siemens Aktiengesellschaft Rotor for a turbomachine
FR2918107B1 (en) * 2007-06-26 2013-04-12 Snecma SHOCK ABSORBER DEVICE ADAPTED TO TURBOMACHINE TREES.
US8013481B2 (en) * 2009-03-27 2011-09-06 General Electric Company Detuner for tuning torsional mode of a rotating body

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
BR112016016336A2 (en) 2017-08-08
FR3016659A1 (en) 2015-07-24
EP3097266A1 (en) 2016-11-30
US9624777B2 (en) 2017-04-18
CA2936772C (en) 2023-03-14
US20160333696A1 (en) 2016-11-17
FR3016659B1 (en) 2016-03-04
CN105917079B (en) 2018-01-26
CN105917079A (en) 2016-08-31
RU2016129585A (en) 2018-01-24
BR112016016336B1 (en) 2022-08-09
CA2936772A1 (en) 2015-07-23
RU2683334C1 (en) 2019-03-28
WO2015107310A1 (en) 2015-07-23

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