EP2495399A1 - Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator - Google Patents

Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator Download PDF

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Publication number
EP2495399A1
EP2495399A1 EP11156828A EP11156828A EP2495399A1 EP 2495399 A1 EP2495399 A1 EP 2495399A1 EP 11156828 A EP11156828 A EP 11156828A EP 11156828 A EP11156828 A EP 11156828A EP 2495399 A1 EP2495399 A1 EP 2495399A1
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EP
European Patent Office
Prior art keywords
ferrule
rotor
segments
housing according
housing
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.)
Granted
Application number
EP11156828A
Other languages
German (de)
French (fr)
Other versions
EP2495399B1 (en
Inventor
Jean-François Cortequisse
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP11156828.3A priority Critical patent/EP2495399B1/en
Priority to CA2769815A priority patent/CA2769815C/en
Priority to US13/407,948 priority patent/US8939712B2/en
Priority to RU2012107669A priority patent/RU2620883C2/en
Priority to CN201210142291.9A priority patent/CN102654141B/en
Publication of EP2495399A1 publication Critical patent/EP2495399A1/en
Application granted granted Critical
Publication of EP2495399B1 publication Critical patent/EP2495399B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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 relates to a housing for wrapping the ends of a row of blades of a rotor, the housing being provided with a sealing device between the blade tips and the housing. More specifically, the invention relates to such a casing for an axial turbomachine compressor. The invention also relates to an axial turbomachine compressor comprising such a housing.
  • the patent document US 6,406,256 B1 discloses a rotating sealing device between a rotor and an axial turbomachine stator. More specifically, this teaching addresses the problem of compensating for variation of play between the blade tips and an outer shell under operating conditions covering a wide temperature range, that is to say typically for the turbine part of the turbomachine.
  • the sealing device comprises a segmented outer shroud disposed around the ends of the rotor blades. Each segment is held at the wall of the stator housing via fingers which are inclined in an opposite manner and cooperating with corresponding grooves in the housing wall. In case of increase of the temperature of the different segments, these will expand and lengthen slightly. This lengthening will have the effect of moving the fingers away.
  • the game between a row of rotor blades and its outer shell can vary in particular as a function of the speed of rotation and also as a function of a misalignment related to the operating loads (gyroscopic pairs related to a change in attitude of the turbomachine), as well as to the ingestion of foreign matter (as example of birds).
  • a misalignment between the rotor and the stator will change the mechanical play between the blade tips and the ferrule to the point that they will come into contact with the ferrule on a certain sector and the game will increase considerably on the opposite sector.
  • the patent document US 2008/0159850 A1 discloses a rotating sealing device between the rotor and the stator of the turbine part of an axial turbomachine.
  • This teaching relates to the problem of high temperatures at the ferrule and the need for cooling the ferrule.
  • the proposed solution consists essentially of a quick fixing device, facilitating the assembly and disassembly of the ferrule. More specifically, it consists in providing a segmented ferrule wherein each segment is provided with a circumferential rib with a dovetail section and directed radially outwardly of the stator. This rib cooperates with a groove of approximately corresponding section of the stator housing wall.
  • a spring may be optionally disposed in the casing wall so as to exert a force on the segments, this force being directed essentially radially towards the center of rotation of the rotor.
  • the aim of this spring is to apply a contact force between the groove surfaces and the corresponding surfaces of the dovetail section rib to ensure a certain seal.
  • Seals may also be disposed laterally of the rib, between the surface of the segments which is opposed to the inner surface of the shell and the inner surface of the housing wall. These seals are made of solid material because of the high temperatures at which a turbine works.
  • the advantage of this solution is that the different constituent segments of the shell can be easily replaced by a simple translational movement relative to the housing wall. Unlike what figure 3 of this document might suggest, the constituent segments of the ferrule are not suitable for move radially and even less to compensate for any misalignment or variation of play whatsoever.
  • the patent document FR 2 636 373 A1 relates to the problem of differential thermal expansion in a gas turbine, and more specifically to the compensation of variation of clearance between the ends of the rotor blades and the corresponding ferrule.
  • the proposed solution consists of a unitary closed ring-shaped ferrule mounted on a rotor housing via a series of pneumatic bellows compensators. Compressed air is fed into the compensators in order to exert radial forces on the ferrule and thus to control the radial clearance between the ends of the blades and the ferrule.
  • This solution although technically interesting and potentially powerful, is limited to compensate the game evenly over the entire circumference. It is therefore not suitable to compensate for variations in play in case of misalignment between the rotor and the stator.
  • it requires a device for controlling the air pressure, which makes its implementation quite expensive and likely to experience failures.
  • one of the sources of irreversible opening of the games is the misalignment of the axis of the rotor relative to that of the stator, closing the games on one side and opening the opposite.
  • At least two sources of misalignment are reversible and temporally limited during the mission: it is the misalignment related to the loads of maneuvers (gyroscopic couples related to a variation of attitude of the turbomachine) and that related to the foreign body ingestion (example: birds).
  • the misalignment related to the loads of maneuvers (gyroscopic couples related to a variation of attitude of the turbomachine) and that related to the foreign body ingestion (example: birds).
  • a slight misalignment can appear during the life of the turbomachine. It is caused by an unbalance related to the occasional deterioration, accidental or not of the rotor.
  • a friable (abradable) wear material thickness is irreversibly removed, which leads to an opening of the games. irreversible and therefore to the equally irreversible reduction of the efficiency of the turbomachine
  • the misalignment of the axis of the rotor relative to that of the stator causes the release of particles constituting the abradable in the primary vein can cause engine damage (including by causing the closure of holes ventilation in the turbine)
  • the object of the invention is to provide a sealing device between a rotor and an axial turbomachine stator that overcomes at least one of the aforementioned problems. More particularly, the invention aims to provide a sealing device between a rotor and an axial turbomachine stator compatible with misalignments between the rotor and the stator. More particularly, the invention aims to provide a solution to the aforementioned problems for an axial turbomachine compressor.
  • the invention relates to a casing for wrapping the ends of a row of blades of an axial turbomachine compressor rotor, comprising: a structural wall; a segmented ferrule for surrounding the row of blades and supported by the wall; remarkable in that it further comprises elastic means disposed between the wall and the segments of the shell so as to allow said segments to move radially in the event of contact with the ends of the rotor blades, particularly in case misalignment of the axis of rotation of the rotor relative to the axis of the housing.
  • the elastic means support the segments. These are exclusively maintained by the elastic means.
  • the radial movement of the segments can be limited to the vanes by mechanical retaining means.
  • the elastic means comprise one or more elements of deformable material (s) elastically, the elasticity of said element (s) being mainly based on the elasticity of the material (s), the or the materials being preferably elastomer.
  • the elastic means comprise a plurality of circumferentially and / or axially distributed elastic elements.
  • the elastic elements are spaced from each other so as to be able to deform freely.
  • the elastic means comprise a plurality of elastic elements each having a first end attached to the wall and a second end attached to a segment of the ferrule.
  • the first ends and / or the second ends are adhesively bonded, preferably by diffusion and / or bonding.
  • the wall has an internal groove in which the elastic means are at least partially housed.
  • the segments of the ferrule each have ends in a circumferential direction of the ferrule which are bevelled.
  • the contiguous ends of the segments are preferably engaged one to the other and bevelled so that a radial movement of a segment in the direction of an approximation of the casing caused by contact with the blades of the rotor leads to end engagement a similar movement of the next segment in the direction of rotation of the rotor.
  • the ends of the segments have a generally inclined profile between 30 ° and 60 ° relative to a tangent, said profile being preferably straight.
  • the ends in a circumferential direction of each segment of the ferrule are inclined in the same direction.
  • the segments of the shell comprise an internal surface compatible from a friction point of view with the ends of the blades.
  • the inner surface of the segments of the ferrule comprises a friable coating in case of friction with the ends of the blades.
  • the invention also relates to an axial turbomachine compressor, comprising: a rotor provided with at least one row of vanes; a stator with a casing enclosing the rotor; remarkable in that the housing is in accordance with the invention.
  • a mechanical clearance is provided between the ends of the blades and the ferrule in normal operation when the axis of rotation of the rotor is aligned with the axis of the rotor.
  • the invention has the advantage of allowing radial displacement of the segments and hence compensation in case of misalignment between the rotor and the stator, especially in case of change of attitude of the aircraft or in case of ingestion of a foreign object.
  • the state of the art identified focuses on the thermal problems associated with the turbines and does not address in any case the misalignment problem. The latter can be sudden and then disappear, as for example during a change of attitude.
  • the proposed solution by the segmentation of the ferrule and the maintenance of these segments by elastic means, allows the shell to conform to a misalignment and then return to an initial circular shape centered.
  • blocks made of elastomeric materials has the advantage of the intrinsic damping component of the elastomer.
  • the figure 1 is a diagrammatic sectional view of an axial turbomachine with a double flow, of the airplane engine type, the low-pressure compressor and / or the high-pressure compressor may be equipped with one or more sealing devices according to the invention.
  • the figure 2 is a partial sectional view of the low-pressure compressor of the turbomachine of the figure 2 , the low-pressure compressor being equipped with sealing devices according to the invention.
  • the figure 3 is a sectional view of one of the compressor sealing devices of the figure 2 .
  • the figure 4 is a detail view of an elastic element of the figure 3 this elastic element ensuring the connection between the ferrule and the housing.
  • the figure 5 is a view of the elastic element of the figure 4 in a compressed state.
  • the figure 6 is a sectional view of a compressor sector of the figure 2 , illustrating the sealing device according to the invention.
  • the figure 7 is a sectional view of a sealing device constituting an alternative to that of the figure 3 .
  • the term “external” for the ferrule refers instead to the generally annular fluid vein, “outer ferrule” denoting a ferrule on the side of the outer or outer limit of the vein fluid and “inner ferrule” designating a ferrule on the side of the inner or inner limit of the fluid vein.
  • the axial turbomachine 2 illustrated in FIG. figure 1 is a jet engine type double jet engine for aircraft. It comprises, from upstream to downstream, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and a turbine 10.
  • the low-pressure and high-pressure compressors are not subjected to the high temperatures to which they are subjected. the turbine is subjected. It is therefore possible to use lower melting point materials for the realization of different elements of these compressors.
  • the low-pressure compressor 4 of the figure 1 is illustrated at the figure 2 .
  • the rotor 20 carrying several rows of so-called rotor blades 24, the stator formed of a housing 12 and a wall 16 defining the secondary air flow.
  • the housing 12 supports a series of fixed vanes 26 called statoric.
  • Each circumferential row of stator vanes form a rectifier stage.
  • Each circumferential row of stator vanes form with a circumferential row of rotor blades a compression stage whose role is to increase the pressure of the fluid, in this case air, passing therethrough.
  • An outer shell 22 is disposed facing the outer ends of each row of rotor blades 24 to provide a seal with possibility of contact.
  • the figure 3 is a sectional view of a crankcase section provided with a housing with a sealing device according to the invention.
  • the housing wall 12 has a groove-like housing 32 on its inner surface.
  • This housing contains a series of elastically deformable elements 30 fixed to the surface of the bottom of the groove and fixed to the shell 22. The latter is at least partially housed in the groove. It is maintained and connected to the casing exclusively by the elastically deformable elements 30.
  • the ferrule is constituted by a series of segments 22 distinct so as to be able to move independently in case of misalignment between the rotor and the stator.
  • the elastically deformable elements 30 provide an elastic connection between these segments and the housing so that in case of contact of the inner surface of the shell by the ends of the blades, the segments of the shell subject to this contact can move closer to the the groove of the housing by deformation of the elastically deformable elements 30 under the force of contact blades.
  • FIGS. Figures 4 and 5 The effect of the deformation of the elements 30 is illustrated in FIGS. Figures 4 and 5 .
  • an element 30 can be observed in its normal state where the outer surface of the ferrule segment 22 is at a distance e from the bottom surface of the groove of the housing 12. This distance e corresponds to the height of the element 30.
  • the same element 30 is in a deformed state under the effect of a force generated by the blade tip contact with the inner surface of the ferrule segment 22.
  • the element 30 has a barrel shape with a shorter height e ', corresponding to the new distance between the outer surface of the ferrule segment 22 and the inner surface of the bottom of the groove of the housing 12.
  • the elastically deformable elements 30 are preferably made of elastomeric material. They are preferably glued to the housing and to the shell, respectively. They can also be linked by diffusion, screwing or any other connection method known per se to those skilled in the art.
  • the elastically deformable elements are preferably made of elastically deformable material per se, conferring exclusively their elastic deformability.
  • the elastically deformable elements may also be mechanically deformable elements whose elastic deformability is based on the combination of an elastically deformable material and a particular geometry, such as for example springs.
  • the ferrule segments are preferably connected to the housing by several elastically deformable elements arranged axially.
  • the figure 6 is a sectional view of a portion of the compressor housing of the figure 2 .
  • the bevels are inclined so that the radial displacement of a first segment in the direction of an approximation of the housing leads with it a second segment following it directly in the direction of rotation of the rotor by engagement of the beveled face of the end of the first segment with the beveled face of the contiguous end of the second segment.
  • the inner surface of the ferrule at the junctions thus remains essentially continuous.
  • the ferrule although having at rest a circular shape can thus be deformed by conforming to the misalignment between the rotor and the stator.
  • the beveled ends of the segments are preferably generally planar. They may, however, take various forms capable of ensuring engagement of the segments as described above, namely ensuring a continuity of the inner surface of the shell at the junctions between the segments when the rotating rotor exerts pressure on certain segments. .
  • the ends may for example have a stair-shaped profile in a plane perpendicular to the axis of rotation of the machine.
  • the elastically deformable elements 30 are arranged in a pointwise manner and at a distance from each other in several circumferential rows. The fact of arranging them at a distance from one another axially and / or circumferentially allows the various elements to deform freely and independently. Such an arrangement therefore does not ensure sealing between a point of the fluid stream passing through the compressor which is upstream of the blade row and another point of the fluid stream which is downstream. A minimum clearance between the upstream and downstream edges, respectively, of the ferrule and the edges corresponding to slot 32 (see figure 3 ) is provided to ensure an acceptable seal.
  • a seal 34 is fixed for example by gluing on the edges of the housing 32 corresponding to the upstream and downstream edges of the ferrule 22.
  • these joints can also provide a damping function of the movement of the different segments of the ferrule. the ferrule.
  • the shell may have on its inner surface a coating of friable material able to disintegrate during frictional contact with the blades of the rotor.
  • coatings are said to be “abradable” coatings and well known to those skilled in the art.
  • the ability of the ferrule to move and to comply in particular with a misalignment between the rotor and the stator makes it possible to provide a possibly thinner coating and / or harder, or even no coating at all. Indeed, it is quite possible to provide a ferrule of smooth metal material free of any coating of the abradable type considering the advantages of the sealing device. The use of harder materials releases little or no particles likely to damage the engine during the contacts between the "abradable" and the wheel head.
  • the sealing device which is the subject of this document is not required to ensure complete sealing, especially in view of the presence of a mechanical clearance between the ends of the blades and the inner surface of the shell.

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

Abstract

The housing (12) has a segmented shell (22) that is structured and operable to enclose a row of blades (24) and supported by a structural wall. Elastically deformable units (30) are positioned between the wall and segments of the shell so as to radially displace the segments in the event of contact with tips of the blades of a rotor and in the event of misalignment of a rotation axis of the rotor relative to an axis of the housing. The deformable units comprise elements made of elastically deformable materials e.g. elastomeric materials. An independent claim is also included for an axial turbomachine compressor.

Description

Domaine techniqueTechnical area

L'invention a trait à un carter destiné à envelopper les extrémités d'une rangée d'aubes d'un rotor, le carter étant pourvu d'un dispositif d'étanchéité entre les extrémités d'aubes et le carter. Plus précisément l'invention a trait à un tel carter pour un compresseur de turbomachine axiale. L'invention a trait également à un compresseur de turbomachine axiale comprenant un tel carter.The invention relates to a housing for wrapping the ends of a row of blades of a rotor, the housing being provided with a sealing device between the blade tips and the housing. More specifically, the invention relates to such a casing for an axial turbomachine compressor. The invention also relates to an axial turbomachine compressor comprising such a housing.

Technique antérieurePrior art

Le document de brevet US 6,406,256 B1 divulgue un dispositif d'étanchéité tournante entre un rotor et un stator de turbomachine axiale. Plus précisément cet enseignement aborde la problématique de compensation de variation de jeu entre les extrémités d'aubes et une virole externe dans des conditions de fonctionnement couvrant une large gamme de température, c'est-à-dire typiquement pour la partie turbine de la turbomachine. Le dispositif d'étanchéité comprend une virole externe segmentée disposée autour des extrémités des aubes rotoriques. Chaque segment est maintenu à la paroi du carter statorique via des doigts inclinés de manière opposée et coopérant avec des rainures correspondantes dans la paroi de carter. En cas d'augmentation de la température des différents segments, ces derniers vont se dilater et s'allonger légèrement. Cet allongement va avoir pour effet d'éloigner les doigts de maintiens. En raison de leurs inclinaisons, ces doigts vont se déplacer radialement dans le sens d'un éloignement du rotor, ce qui aura pour effet de faire légèrement remonter les segments et, partant, de compenser le rapprochement des extrémités d'aubes des segments lié à l'augmentation de température. Ce dispositif de compensation est intéressant mais manque cependant de compenser une variation du jeu causée par d'autres phénomènes que les variations de températures. En effet, le jeu entre une rangée d'aubes rotoriques et sa virole externe peuvent varier notamment en fonction de la vitesse de rotation et également en fonction d'un désalignement lié aux charges de manoeuvre (couples gyroscopiques liés à une variation d'attitude de la turbomachine), ainsi qu'à l'ingestion de corps étranger (comme exemple d'oiseaux). Un désalignement entre le rotor et le stator va modifier le jeu mécanique entrer les extrémités d'aubes et la virole au point que ces dernières vont entrer en contact avec la virole sur un certain secteur et le jeu va augmenter considérablement sur le secteur opposé.The patent document US 6,406,256 B1 discloses a rotating sealing device between a rotor and an axial turbomachine stator. More specifically, this teaching addresses the problem of compensating for variation of play between the blade tips and an outer shell under operating conditions covering a wide temperature range, that is to say typically for the turbine part of the turbomachine. . The sealing device comprises a segmented outer shroud disposed around the ends of the rotor blades. Each segment is held at the wall of the stator housing via fingers which are inclined in an opposite manner and cooperating with corresponding grooves in the housing wall. In case of increase of the temperature of the different segments, these will expand and lengthen slightly. This lengthening will have the effect of moving the fingers away. Because of their inclinations, these fingers will move radially in the direction of a distance from the rotor, which will have the effect of slightly up the segments and, therefore, to compensate for the approximation of the blade ends of the segments related to the temperature increase. This compensation device is interesting but lacks however to compensate for a variation of the game caused by other phenomena than temperature variations. Indeed, the game between a row of rotor blades and its outer shell can vary in particular as a function of the speed of rotation and also as a function of a misalignment related to the operating loads (gyroscopic pairs related to a change in attitude of the turbomachine), as well as to the ingestion of foreign matter (as example of birds). A misalignment between the rotor and the stator will change the mechanical play between the blade tips and the ferrule to the point that they will come into contact with the ferrule on a certain sector and the game will increase considerably on the opposite sector.

Le document de brevet US 2008/0159850 A1 divulgue un dispositif d'étanchéité tournante entre le rotor et le stator de la partie turbine d'une turbomachine axiale. Cet enseignement a trait au problème de températures élevées au niveau de la virole et du besoin de refroidissement de la virole. La solution proposée consiste essentiellement en un dispositif de fixation rapide, facilitant le montage et démontage de la virole. Plus précisément, elle consiste à prévoir une virole segmentée où chaque segment est pourvu d'une nervure circonférentielle à section en queue d'aronde et dirigée radialement vers l'extérieur du stator. Cette nervure coopère avec une rainure de section approximativement correspondante de la paroi de carter statorique. Un ressort peut être optionnellement disposé dans la paroi de carter de manière à exercer un effort sur les segments, cet effort étant dirigé essentiellement radialement vers le centre de rotation du rotor. Ce ressort a pour objectif d'appliquer un effort de contact entre les surfaces de la rainure et les surfaces correspondantes de la nervure à section en queue d'aronde, afin d'assurer une certaine étanchéité. Des joints peuvent être également disposés latéralement de la nervure, entre la surface des segments qui est opposée à la surface interne de la virole et la surface intérieure de la paroi de carter. Ces joints sont en matériau solide en raison des températures élevées auxquelles une turbine travaille. L'avantage de cette solution est que les différents segments constitutifs de la virole peuvent être facilement remplacés par un simple mouvement de translation par rapport à la paroi de carter. Contrairement à ce que la figure 3 de ce document pourrait laisser penser, les segments constitutifs de la virole ne sont pas aptes à se déplacer radialement et encore moins à compenser quelque désalignement ou variation de jeu que ce soit.The patent document US 2008/0159850 A1 discloses a rotating sealing device between the rotor and the stator of the turbine part of an axial turbomachine. This teaching relates to the problem of high temperatures at the ferrule and the need for cooling the ferrule. The proposed solution consists essentially of a quick fixing device, facilitating the assembly and disassembly of the ferrule. More specifically, it consists in providing a segmented ferrule wherein each segment is provided with a circumferential rib with a dovetail section and directed radially outwardly of the stator. This rib cooperates with a groove of approximately corresponding section of the stator housing wall. A spring may be optionally disposed in the casing wall so as to exert a force on the segments, this force being directed essentially radially towards the center of rotation of the rotor. The aim of this spring is to apply a contact force between the groove surfaces and the corresponding surfaces of the dovetail section rib to ensure a certain seal. Seals may also be disposed laterally of the rib, between the surface of the segments which is opposed to the inner surface of the shell and the inner surface of the housing wall. These seals are made of solid material because of the high temperatures at which a turbine works. The advantage of this solution is that the different constituent segments of the shell can be easily replaced by a simple translational movement relative to the housing wall. Unlike what figure 3 of this document might suggest, the constituent segments of the ferrule are not suitable for move radially and even less to compensate for any misalignment or variation of play whatsoever.

Le document de brevet FR 2 636 373 A1 a trait au problème de dilations thermiques différentielles dans une turbine à gaz, et plus précisément à la compensation de variation de jeu entre les extrémités des aubes rotoriques et de la virole correspondante. La solution proposée consiste en une virole en forme d'anneau fermé unitaire monté sur un carter rotorique via une série de compensateurs à soufflet pneumatiques. De l'air comprimé est amené dans les compensateurs afin d'exercer des efforts radiaux sur la virole et ainsi de contrôler le jeu radial entre les extrémités des aubes et la virole. Cette solution, bien que techniquement intéressante et potentiellement performante, se limite à compenser le jeu de manière égale sur toute la circonférence. Elle n'est par conséquent pas adaptée à compenser les variations de jeu en cas de désalignement entre le rotor et le stator. De plus, elle requiert un dispositif de contrôle de la pression d'air, ce qui rend sa mise oeuvre assez coûteuse et susceptible de connaître des pannes.The patent document FR 2 636 373 A1 relates to the problem of differential thermal expansion in a gas turbine, and more specifically to the compensation of variation of clearance between the ends of the rotor blades and the corresponding ferrule. The proposed solution consists of a unitary closed ring-shaped ferrule mounted on a rotor housing via a series of pneumatic bellows compensators. Compressed air is fed into the compensators in order to exert radial forces on the ferrule and thus to control the radial clearance between the ends of the blades and the ferrule. This solution, although technically interesting and potentially powerful, is limited to compensate the game evenly over the entire circumference. It is therefore not suitable to compensate for variations in play in case of misalignment between the rotor and the stator. In addition, it requires a device for controlling the air pressure, which makes its implementation quite expensive and likely to experience failures.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

Lors de la vie de la turbomachine, une des sources d'ouverture irréversible des jeux est le désalignement de l'axe du rotor par rapport à celui du stator, fermant les jeux d'un coté et les ouvrant à l'opposé.During the life of the turbomachine, one of the sources of irreversible opening of the games is the misalignment of the axis of the rotor relative to that of the stator, closing the games on one side and opening the opposite.

Pour les turbomachines, au moins deux sources de désalignement sont réversibles et temporellement limitées durant la mission : il s'agit du désalignement lié aux charges de manoeuvres (couples gyroscopiques liés à une variation d'attitude de la turbomachine) et de celui lié à l'ingestion de corps étranger (exemple : oiseaux). D'autre part, de manière réversible puisque réparable, un léger désalignement peut apparaître lors de la vie de la turbomachine. Il est causé par un balourd lié à la détérioration ponctuelle, accidentelle ou non du rotor. Lors de ces événements, une épaisseur de matériau d'usure friable (abradable) est enlevée de façon irréversible, ce qui conduit à une ouverture des jeux irréversible et donc à la diminution toute aussi irréversible du rendement de la turbomachineFor turbomachines, at least two sources of misalignment are reversible and temporally limited during the mission: it is the misalignment related to the loads of maneuvers (gyroscopic couples related to a variation of attitude of the turbomachine) and that related to the foreign body ingestion (example: birds). On the other hand, in a reversible manner since repairable, a slight misalignment can appear during the life of the turbomachine. It is caused by an unbalance related to the occasional deterioration, accidental or not of the rotor. During these events, a friable (abradable) wear material thickness is irreversibly removed, which leads to an opening of the games. irreversible and therefore to the equally irreversible reduction of the efficiency of the turbomachine

Indépendamment du problème de pertes de performances aérodynamiques, le désalignement de l'axe du rotor par rapport à celui du stator provoque la libération de particules constitutives de l'abradable dans la veine primaire pouvant causer des dommages moteur (notamment en provoquant le bouchage de trous de ventilation dans la turbine)Regardless of the problem of aerodynamic performance losses, the misalignment of the axis of the rotor relative to that of the stator causes the release of particles constituting the abradable in the primary vein can cause engine damage (including by causing the closure of holes ventilation in the turbine)

De plus, dans le cas d'un désalignement important accidentel, la carcasse du rotor doit pouvoir assurer la rétention des parties mobiles à haute énergie. La structure de la carcasse est ainsi dimensionnée pour ce cas ultime.In addition, in the case of accidentally significant misalignment, the rotor casing must be able to retain the moving parts at high energy. The structure of the carcass is thus dimensioned for this ultimate case.

L'invention a pour objectif de proposer un dispositif d'étanchéité entre un rotor et un stator de turbomachine axiale palliant au moins un des problèmes sus mentionnés. Plus particulièrement, l'invention a pour objectif de proposer un dispositif d'étanchéité entre un rotor et un stator de turbomachine axiale compatible avec des désalignements entre le rotor et le stator. Plus particulièrement encore, l'invention a pour objectif de proposer une solution aux problèmes sus mentionnés pour un compresseur de turbomachine axiale.The object of the invention is to provide a sealing device between a rotor and an axial turbomachine stator that overcomes at least one of the aforementioned problems. More particularly, the invention aims to provide a sealing device between a rotor and an axial turbomachine stator compatible with misalignments between the rotor and the stator. More particularly, the invention aims to provide a solution to the aforementioned problems for an axial turbomachine compressor.

Solution techniqueTechnical solution

L'invention a pour objet un carter destiné à envelopper les extrémités d'une rangée d'aubes d'un rotor de compresseur de turbomachine axiale, comprenant: une paroi structurelle; une virole segmentée destinée à entourer la rangée d'aubes et supportée par la paroi; remarquable en ce qu'il comprend, en outre, des moyens élastiques disposés entre la paroi et les segments de la virole de manière à permettre auxdits segments de se déplacer radialement en cas de contact avec les extrémités d'aubes du rotor, notamment en cas de désalignement de l'axe de rotation du rotor par rapport à l'axe du carter.The invention relates to a casing for wrapping the ends of a row of blades of an axial turbomachine compressor rotor, comprising: a structural wall; a segmented ferrule for surrounding the row of blades and supported by the wall; remarkable in that it further comprises elastic means disposed between the wall and the segments of the shell so as to allow said segments to move radially in the event of contact with the ends of the rotor blades, particularly in case misalignment of the axis of rotation of the rotor relative to the axis of the housing.

Selon un mode avantageux de l'invention, les moyens élastiques supportent les segments. Ces derniers sont exclusivement maintenus par les moyens élastiques.According to an advantageous embodiment of the invention, the elastic means support the segments. These are exclusively maintained by the elastic means.

Optionnellement, le mouvement radial des segments peut être limité vers les aubes par des moyens de retenue mécanique.Optionally, the radial movement of the segments can be limited to the vanes by mechanical retaining means.

Selon un autre mode avantageux de l'invention, les moyens élastiques comprennent un ou plusieurs éléments en matériau(x) déformable(s) élastiquement, l'élasticité dudit ou desdits éléments étant majoritairement basée sur l'élasticité du ou des matériaux, le ou les matériaux étant préférentiellement de l'élastomère.According to another advantageous embodiment of the invention, the elastic means comprise one or more elements of deformable material (s) elastically, the elasticity of said element (s) being mainly based on the elasticity of the material (s), the or the materials being preferably elastomer.

Selon un encore autre mode avantageux de l'invention, les moyens élastiques comprennent une pluralité d'éléments élastiques répartis circonférentiellement et/ou axialement.According to yet another advantageous embodiment of the invention, the elastic means comprise a plurality of circumferentially and / or axially distributed elastic elements.

Selon un encore autre mode avantageux de l'invention, les éléments élastiques sont distants les uns des autres de manière à pouvoir se déformer librement.According to yet another advantageous embodiment of the invention, the elastic elements are spaced from each other so as to be able to deform freely.

Selon un encore autre mode avantageux de l'invention, les moyens élastiques comprennent une pluralité d'éléments élastiques ayant, chacun, une première extrémité fixée à la paroi et une deuxième extrémité fixée au un segment de la virole.According to yet another advantageous embodiment of the invention, the elastic means comprise a plurality of elastic elements each having a first end attached to the wall and a second end attached to a segment of the ferrule.

Selon un encore autre mode avantageux de l'invention, les premières extrémités et/ou les deuxièmes extrémités sont fixées par adhésion, préférentiellement par diffusion et/ou par collage.According to another advantageous embodiment of the invention, the first ends and / or the second ends are adhesively bonded, preferably by diffusion and / or bonding.

Selon un encore autre mode avantageux de l'invention, la paroi comporte une gorge intérieure dans laquelle les moyens élastiques sont au moins partiellement logés.According to yet another advantageous embodiment of the invention, the wall has an internal groove in which the elastic means are at least partially housed.

Selon un encore autre mode avantageux de l'invention, les segments de la virole présentent, chacun, des extrémités selon une direction circonférentielle de la virole qui sont biseautées.According to yet another advantageous embodiment of the invention, the segments of the ferrule each have ends in a circumferential direction of the ferrule which are bevelled.

Les extrémités jointives des segments sont préférentiellement engagées l'une à l'autre et biseautés de manière à ce qu'un mouvement radial d'un segment dans le sens d'un rapprochement du carter causé par un contact avec des aubes du rotor entraine par engagement des extrémités un mouvement similaire du segment suivant dans le sens de rotation du rotor.The contiguous ends of the segments are preferably engaged one to the other and bevelled so that a radial movement of a segment in the direction of an approximation of the casing caused by contact with the blades of the rotor leads to end engagement a similar movement of the next segment in the direction of rotation of the rotor.

Selon un encore autre mode avantageux de l'invention, les extrémités des segments présentent un profil généralement incliné entre 30° et 60° par rapport à une tangente, ledit profil étant préférentiellement droit.According to another advantageous embodiment of the invention, the ends of the segments have a generally inclined profile between 30 ° and 60 ° relative to a tangent, said profile being preferably straight.

Selon un encore autre mode avantageux de l'invention, les extrémités selon une direction circonférentielle de chaque segment de la virole sont inclinées dans le même sens.According to yet another advantageous embodiment of the invention, the ends in a circumferential direction of each segment of the ferrule are inclined in the same direction.

Selon un encore autre mode avantageux de l'invention, les segments de la virole comprennent une surface interne compatible d'un point de vue frottement avec les extrémités des aubes.According to yet another advantageous embodiment of the invention, the segments of the shell comprise an internal surface compatible from a friction point of view with the ends of the blades.

Selon un encore autre mode avantageux de l'invention, la surface interne des segments de la virole comprend un revêtement friable en cas de frottement avec les extrémités des aubes.According to yet another advantageous embodiment of the invention, the inner surface of the segments of the ferrule comprises a friable coating in case of friction with the ends of the blades.

L'invention a également pour objet un compresseur de turbomachine axiale, comprenant: un rotor muni d'au moins une rangée d'aubes; un stator avec un carter renfermant le rotor; remarquable en ce que le carter est conforme à l'invention.The invention also relates to an axial turbomachine compressor, comprising: a rotor provided with at least one row of vanes; a stator with a casing enclosing the rotor; remarkable in that the housing is in accordance with the invention.

Selon un mode avantageux de l'invention, un jeu mécanique est prévu entre les extrémités des aubes et la virole en fonctionnement normal lorsque l'axe de rotation du rotor est aligné avec l'axe du rotor.According to an advantageous embodiment of the invention, a mechanical clearance is provided between the ends of the blades and the ferrule in normal operation when the axis of rotation of the rotor is aligned with the axis of the rotor.

Avantages apportésBenefits brought

Contrairement aux dispositifs connus discutés dans la partie technique antérieure, l'invention présente l'avantage de permettre un déplacement radial des segments et, partant, une compensation en cas de désalignement entre le rotor et le stator, notamment en cas de changement d'attitude de l'aéronef ou en cas d'ingestion d'un corps étranger. L'état de la technique identifié s'attache aux problèmes thermiques liés aux turbines et n'aborde en aucun cas la problématique de désalignement. Ce dernier peut être soudain et puis disparaitre, comme par exemple lors d'un changement d'attitude. La solution proposée, de par la segmentation de la virole et le maintien de ces segments par des moyens élastiques, permet à la virole de se conformer à un désalignement pour ensuite revenir à une forme circulaire centrée initiale.Unlike the known devices discussed in the prior art, the invention has the advantage of allowing radial displacement of the segments and hence compensation in case of misalignment between the rotor and the stator, especially in case of change of attitude of the aircraft or in case of ingestion of a foreign object. The state of the art identified focuses on the thermal problems associated with the turbines and does not address in any case the misalignment problem. The latter can be sudden and then disappear, as for example during a change of attitude. The proposed solution, by the segmentation of the ferrule and the maintenance of these segments by elastic means, allows the shell to conform to a misalignment and then return to an initial circular shape centered.

L'utilisation de blocs en matériaux élastomères présente l'avantage de la composante d'amortissement intrinsèque à l'élastomère.The use of blocks made of elastomeric materials has the advantage of the intrinsic damping component of the elastomer.

Brève description des dessinsBrief description of the drawings

La figure 1 est une vue en coupe schématique d'une turbomachine axiale à double flux, du type moteur d'avion dont le compresseur basse-pression et/ou le compresseur haute-pression est susceptible d'être équipé d'un ou plusieurs dispositifs d'étanchéité conformes à l'invention.The figure 1 is a diagrammatic sectional view of an axial turbomachine with a double flow, of the airplane engine type, the low-pressure compressor and / or the high-pressure compressor may be equipped with one or more sealing devices according to the invention.

La figure 2 est une vue en coupe partielle du compresseur basse-pression de la turbomachine de la figure 2, le compresseur basse-pression étant équipé de dispositifs d'étanchéité conformes à l'invention.The figure 2 is a partial sectional view of the low-pressure compressor of the turbomachine of the figure 2 , the low-pressure compressor being equipped with sealing devices according to the invention.

La figure 3 est une vue en coupe d'un des dispositifs d'étanchéité du compresseur de la figure 2.The figure 3 is a sectional view of one of the compressor sealing devices of the figure 2 .

La figure 4 est une vue de détail d'un élément élastique de la figure 3, cet élément élastique assurant la liaison entre la virole et le carter.The figure 4 is a detail view of an elastic element of the figure 3 this elastic element ensuring the connection between the ferrule and the housing.

La figure 5 est une vue de l'élément élastique de la figure 4 dans un état comprimé.The figure 5 is a view of the elastic element of the figure 4 in a compressed state.

La figure 6 est une vue en coupe d'un secteur du compresseur de la figure 2, illustrant le dispositif d'étanchéité selon l'invention.The figure 6 is a sectional view of a compressor sector of the figure 2 , illustrating the sealing device according to the invention.

La figure 7 est une vue en coupe d'un dispositif d'étanchéité constituant une alternative à celui de la figure 3.The figure 7 is a sectional view of a sealing device constituting an alternative to that of the figure 3 .

Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes « interne » et « externe » utilisés pour qualifier les surfaces de la virole et de la paroi de carter se rapportent à l'enveloppe formée par la virole et de la paroi de carter, « interne » signifiant alors à l'intérieur de cette enveloppe, et « externe » signifiant alors à l'extérieur de cette enveloppe.In the following description, the terms "internal" and "external" used to describe the surfaces of the ferrule and the casing wall refer to the casing formed by the shell and the casing wall, "internal" meaning then inside this envelope, and "external" meaning then outside of this envelope.

Il est à noter que le qualificatif « externe » pour la virole (et non pas pour sa surface) se rapporte par contre à la veine fluide généralement annulaire, « virole externe » désignant une virole du côté de la limite externe ou extérieure de la veine fluide et « virole interne » désignant une virole du côté de la limite interne ou intérieure de la veine fluide.It should be noted that the term "external" for the ferrule (and not for its surface) refers instead to the generally annular fluid vein, "outer ferrule" denoting a ferrule on the side of the outer or outer limit of the vein fluid and "inner ferrule" designating a ferrule on the side of the inner or inner limit of the fluid vein.

La turbomachine axiale 2 illustrée à la figure 1 est une machine à double flux du type moteur à réaction pour avion. Elle comprend, d'amont en aval, un compresseur basse-pression 4, un compresseur haute-pression 6, une chambre de combustion 8 et une turbine 10. Les compresseurs basse-pression et haute-pression ne sont pas soumis aux hautes températures auxquelles la turbine est soumise. Il est donc possible d'utiliser des matériaux à point de fusion plus bas pour la réalisation de différents éléments de ces compresseurs.The axial turbomachine 2 illustrated in FIG. figure 1 is a jet engine type double jet engine for aircraft. It comprises, from upstream to downstream, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and a turbine 10. The low-pressure and high-pressure compressors are not subjected to the high temperatures to which they are subjected. the turbine is subjected. It is therefore possible to use lower melting point materials for the realization of different elements of these compressors.

Le compresseur basse-pression 4 de la figure 1 est illustré à la figure 2. On peut y observer le rotor 20 portant plusieurs rangées d'aubes dite rotoriques 24, le stator formé d'un carter 12 et d'une paroi 16 délimitant le flux d'air secondaire. Le carter 12 supporte une série d'aubes fixes 26 dites statoriques. Chaque rangée circonférentielle d'aubes statoriques forme un étage redresseur. Chaque rangée circonférentielle d'aubes statoriques forme avec une rangée circonférentielle d'aubes rotoriques un étage de compression ayant pour rôle d'augmenter la pression du fluide, en l'occurrence de l'air, le traversant. Etant donné le gradient de pression selon une direction généralement axiale, il est nécessaire de prévoir des moyens d'étanchéité entre les parties tournantes et la partie fixe le long de la veine fluide. Une virole externe 22 est disposée en regard des extrémités extérieures de chaque rangée d'aubes rotoriques 24 afin d'assurer une certaine étanchéité avec possibilité de contact.The low-pressure compressor 4 of the figure 1 is illustrated at the figure 2 . There can be seen the rotor 20 carrying several rows of so-called rotor blades 24, the stator formed of a housing 12 and a wall 16 defining the secondary air flow. The housing 12 supports a series of fixed vanes 26 called statoric. Each circumferential row of stator vanes form a rectifier stage. Each circumferential row of stator vanes form with a circumferential row of rotor blades a compression stage whose role is to increase the pressure of the fluid, in this case air, passing therethrough. Given the pressure gradient in a generally axial direction, it is necessary to provide sealing means between the rotating parts and the fixed part along the fluid stream. An outer shell 22 is disposed facing the outer ends of each row of rotor blades 24 to provide a seal with possibility of contact.

La figure 3 est une vue en coupe d'une section de carter pourvue d'un carter avec un dispositif d'étanchéité selon l'invention. La paroi de carter 12 comporte un logement 32 en forme de rainure sur sa surface interne. Ce logement renferme une série d'élément déformables élastiquement 30 fixés à la surface du fond de la rainure et fixés à la virole 22. Cette dernière est au moins partiellement logée dans la rainure. Elle est maintenue et liée au carter exclusivement par les éléments déformables élastiquement 30.The figure 3 is a sectional view of a crankcase section provided with a housing with a sealing device according to the invention. The housing wall 12 has a groove-like housing 32 on its inner surface. This housing contains a series of elastically deformable elements 30 fixed to the surface of the bottom of the groove and fixed to the shell 22. The latter is at least partially housed in the groove. It is maintained and connected to the casing exclusively by the elastically deformable elements 30.

La virole est constituée d'une série de segments 22 distincts de manière à pouvoir se déplacer indépendamment en cas de désalignement entre le rotor et le stator. En effet, les éléments déformables élastiquement 30 assurent une liaison élastique entre ces différents segments et le carter de sorte à ce qu'en cas de contact de la surface interne de la virole par les extrémités des aubes, les segments de la virole sujets à ce contact puissent se déplacer en se rapprochant de la rainure du carter par déformation des éléments déformables élastiquement 30 sous l'effort du contact des aubes.The ferrule is constituted by a series of segments 22 distinct so as to be able to move independently in case of misalignment between the rotor and the stator. Indeed, the elastically deformable elements 30 provide an elastic connection between these segments and the housing so that in case of contact of the inner surface of the shell by the ends of the blades, the segments of the shell subject to this contact can move closer to the the groove of the housing by deformation of the elastically deformable elements 30 under the force of contact blades.

L'effet de la déformation des éléments 30 est illustré aux figures 4 et 5. A la figure 4, on peut observer un élément 30 à son état normal où la surface externe du segment 22 de virole est à une distance e de la surface du fond de la rainure du carter 12. Cette distance e correspond à la hauteur de l'élément 30. A la figure 5, le même élément 30 est dans un état déformé sous l'effet d'un effort généré par le contact d'extrémités d'aubes avec la surface interne du segment 22 de virole. L'élément 30 présente une forme en barillet avec une hauteur e' plus courte, correspondant à la nouvelle distance entre la surface externe du segment 22 de virole et la surface interne du fond de la rainure du carter 12.The effect of the deformation of the elements 30 is illustrated in FIGS. Figures 4 and 5 . To the figure 4 an element 30 can be observed in its normal state where the outer surface of the ferrule segment 22 is at a distance e from the bottom surface of the groove of the housing 12. This distance e corresponds to the height of the element 30. To the figure 5 the same element 30 is in a deformed state under the effect of a force generated by the blade tip contact with the inner surface of the ferrule segment 22. The element 30 has a barrel shape with a shorter height e ', corresponding to the new distance between the outer surface of the ferrule segment 22 and the inner surface of the bottom of the groove of the housing 12.

Les éléments déformables élastiquement 30 sont préférentiellement en matériau élastomère. Ils sont préférentiellement collés au carter et à la virole, respectivement. Ils peuvent être également liés par diffusion, par vissage ou toute autre méthode de liaison connue en soi de l'homme de métier. Les éléments déformables élastiquement sont préférentiellement en matériau élastiquement déformable en soi, leur conférant exclusivement leur déformabilité élastique.The elastically deformable elements 30 are preferably made of elastomeric material. They are preferably glued to the housing and to the shell, respectively. They can also be linked by diffusion, screwing or any other connection method known per se to those skilled in the art. The elastically deformable elements are preferably made of elastically deformable material per se, conferring exclusively their elastic deformability.

Les éléments déformables élastiquement peuvent également être des éléments mécaniquement déformables dont la déformabilité élastique est basée sur la combinaison d'un matériau déformable élastiquement et d'une géométrie particulière, comme par exemple des ressorts.The elastically deformable elements may also be mechanically deformable elements whose elastic deformability is based on the combination of an elastically deformable material and a particular geometry, such as for example springs.

Comme cela est visible à la figure 3, les segments de virole sont préférentiellement liés au carter par plusieurs éléments déformables élastiquement disposés axialement.As can be seen in figure 3 , the ferrule segments are preferably connected to the housing by several elastically deformable elements arranged axially.

La figure 6 est une vue en coupe d'une partie du carter du compresseur de la figure 2. On peut y observer la segmentation de la virole en une série de tronçons ou segments distincts les uns des autres. Les deux extrémités circonférentielles de chaque segment 22 sont biseautées dans le même sens de manière à assurer une continuité au niveau des jonctions entre les différents segments. Il est à noter que les biseaux sont orientés par rapport au sens de rotation du rotor de manière à éviter des ressauts au niveau des jonctions susceptibles d'entrer en contact positif avec les aubes en mouvement. Comme cela est visible à la figure 6, les biseaux sont inclinés de manière à ce que le déplacement radial d'un premier segment dans le sens d'un rapprochement du carter entraine avec lui un deuxième segment le suivant directement dans le sens de rotation du rotor par engagement de la face biseautée de l'extrémité du premier segment avec la face biseautée de l'extrémité jointive du deuxième segment. La surface interne de la virole au niveau des jonctions reste ainsi essentiellement continue. La virole bien que présentant au repos une forme circulaire pourra ainsi se déformer en se conformant au désalignement entre le rotor et le stator.The figure 6 is a sectional view of a portion of the compressor housing of the figure 2 . We can observe the segmentation of the shell in a series of segments or segments distinct from each other. Both ends circumferences of each segment 22 are bevelled in the same direction so as to ensure continuity at the junctions between the different segments. It should be noted that the bevels are oriented relative to the direction of rotation of the rotor so as to avoid projections at the junctions likely to come into positive contact with the blades in motion. As can be seen in figure 6 , the bevels are inclined so that the radial displacement of a first segment in the direction of an approximation of the housing leads with it a second segment following it directly in the direction of rotation of the rotor by engagement of the beveled face of the end of the first segment with the beveled face of the contiguous end of the second segment. The inner surface of the ferrule at the junctions thus remains essentially continuous. The ferrule although having at rest a circular shape can thus be deformed by conforming to the misalignment between the rotor and the stator.

Les extrémités biseautées des segments sont préférentiellement généralement planes. Elles peuvent cependant prendre diverses formes aptes à assurer un engagement des segments tel que décrit ci-avant, à savoir assurant une continuité de la surface interne de la virole au niveau des jonctions entre les segments lorsque le rotor en rotation exerce une pression sur certains segments. Les extrémités peuvent par exemple présenter un profil en forme d'escalier dans un plan perpendiculaire à l'axe de rotation de la machine.The beveled ends of the segments are preferably generally planar. They may, however, take various forms capable of ensuring engagement of the segments as described above, namely ensuring a continuity of the inner surface of the shell at the junctions between the segments when the rotating rotor exerts pressure on certain segments. . The ends may for example have a stair-shaped profile in a plane perpendicular to the axis of rotation of the machine.

Les éléments déformables élastiquement 30 sont disposés de manière ponctuelle et à distance les uns des autres selon plusieurs rangées circonférentielles. Le fait de les disposer à distance les uns des autres axialement et/ou de manière circonférentielle permet aux différents éléments de se déformer librement et indépendamment. Un tel agencement n'assure par conséquent pas d'étanchéité entre un point de la veine fluide traversant le compresseur qui est en amont de la rangée d'aube et un autre point de la veine fluide qui est en aval. Un jeu minimal entre les bords amont et aval, respectivement, de la virole et les bords correspondant du logement 32 (voir figure 3) est prévu afin d'assurer une étanchéité acceptable.The elastically deformable elements 30 are arranged in a pointwise manner and at a distance from each other in several circumferential rows. The fact of arranging them at a distance from one another axially and / or circumferentially allows the various elements to deform freely and independently. Such an arrangement therefore does not ensure sealing between a point of the fluid stream passing through the compressor which is upstream of the blade row and another point of the fluid stream which is downstream. A minimum clearance between the upstream and downstream edges, respectively, of the ferrule and the edges corresponding to slot 32 (see figure 3 ) is provided to ensure an acceptable seal.

Il est toutefois envisageable de prévoir des moyens d'étanchéité entre les bords amont et aval de la virole et le logement correspondant du carter. En effet, comme cela est illustré à la figure 7, un joint 34 est fixé par exemple par collage sur les bords du logement 32 correspondant aux bords amont et aval de la virole 22. Outre une fonction d'étanchéité, ces joints peuvent également assurer une fonction d'amortissement du mouvement des différents segments de la virole.However, it is conceivable to provide sealing means between the upstream and downstream edges of the shell and the corresponding housing of the housing. Indeed, as illustrated in figure 7 , a seal 34 is fixed for example by gluing on the edges of the housing 32 corresponding to the upstream and downstream edges of the ferrule 22. In addition to a sealing function, these joints can also provide a damping function of the movement of the different segments of the ferrule. the ferrule.

De manière générale, il est à noter que la virole peut comporter sur sa surface interne un revêtement en matériau friable apte à se désagréger lors de contact avec frottement avec les aubes du rotor. De tels revêtements sont dits des revêtements « abradable » et bien connus de l'homme de métier. La capacité de la virole à se déplacer et à se conformer notamment à un désalignement entre le rotor et le stator permet de prévoir un revêtement éventuellement plus mince et/ou plus dur, voire encore pas de revêtement du tout. En effet, il est tout-à-fait envisageable de prévoir une virole en matériau métallique lisse exempte de tout revêtement du type abradable compte tenu des avantages du dispositif d'étanchéité. L'utilisation de matériaux plus durs libère pas ou très peu de particules suceptibles d'endommager le moteur lors des contacts entre « l'abradable » et la tête de roue mobile.In general, it should be noted that the shell may have on its inner surface a coating of friable material able to disintegrate during frictional contact with the blades of the rotor. Such coatings are said to be "abradable" coatings and well known to those skilled in the art. The ability of the ferrule to move and to comply in particular with a misalignment between the rotor and the stator makes it possible to provide a possibly thinner coating and / or harder, or even no coating at all. Indeed, it is quite possible to provide a ferrule of smooth metal material free of any coating of the abradable type considering the advantages of the sealing device. The use of harder materials releases little or no particles likely to damage the engine during the contacts between the "abradable" and the wheel head.

De manière générale, il est également à noter que le dispositif d'étanchéité qui est le sujet de ce document n'est pas tenu d'assurer une étanchéité totale compte tenu notamment de la présence d'un jeu mécanique entre les extrémités des aubes et la surface interne de la virole.In general, it should also be noted that the sealing device which is the subject of this document is not required to ensure complete sealing, especially in view of the presence of a mechanical clearance between the ends of the blades and the inner surface of the shell.

Il est également à noter que de nombreuses alternatives aux éléments ou blocs de matériau élastiques plein 30 sont envisageables. En effet, il existe de nombreux moyens et dispositifs élastique avec une composante d'amortissement plus ou moins grande.It should also be noted that many alternatives to the elements or blocks of solid elastic material 30 are conceivable. Indeed, there are many elastic means and devices with a greater or less damping component.

Claims (15)

Carter destiné à envelopper les extrémités d'une rangée d'aubes d'un rotor de compresseur de turbomachine axiale, comprenant : une paroi structurelle (12) ; une virole segmentée (22) destinée à entourer la rangée d'aubes et supportée par la paroi ; caractérisé en ce qu'il comprend, en outre,
des moyens élastiques (30) disposés entre la paroi (12) et les segments (22) de la virole de manière à permettre auxdits segments de se déplacer en cas de contact avec les extrémités d'aubes (24) du rotor, notamment en cas de désalignement de l'axe de rotation du rotor par rapport à l'axe du carter.A casing for wrapping the ends of an array of vanes of an axial turbomachine compressor rotor, comprising: a structural wall (12); a segmented ferrule (22) for surrounding the blade array and supported by the wall; characterized in that it further comprises
elastic means (30) disposed between the wall (12) and the segments (22) of the ferrule so as to allow said segments to move in the event of contact with the blade tips (24) of the rotor, in particular in case misalignment of the axis of rotation of the rotor relative to the axis of the housing. Carter selon la revendication 1, caractérisé en ce que les moyens élastiques (30) supportent les segments (22).Housing according to claim 1, characterized in that the resilient means (30) support the segments (22). Carter selon l'une des revendications 1 et 2, caractérisé en ce que les moyens élastiques (30) comprennent un ou plusieurs éléments en matériau(x) déformable(s) élastiquement, l'élasticité dudit ou desdits éléments étant majoritairement basée sur l'élasticité du ou des matériaux, le ou les matériaux étant préférentiellement de l'élastomère.Housing according to one of claims 1 and 2, characterized in that the elastic means (30) comprise one or more elements of material (x) deformable (s) elastically, the elasticity of said element or elements being mainly based on the elasticity of the material or materials, the material or materials being preferably elastomer. Carter selon l'une des revendications 1 à 3, caractérisé en ce que les moyens élastiques (30) comprennent une pluralité d'éléments élastiques répartis circonférentiellement et/ou axialement.Housing according to one of claims 1 to 3, characterized in that the elastic means (30) comprise a plurality of circumferentially and / or axially distributed elastic elements. Carter selon la revendication 4, caractérisé en ce que les éléments élastiques (30) sont distants les uns des autres de manière à pouvoir se déformer librement.Housing according to claim 4, characterized in that the elastic elements (30) are spaced from each other so as to be able to deform freely. Carter selon l'une des revendications 1 à 5, caractérisé en ce que les moyens élastiques (30) comprennent une pluralité d'éléments élastiques ayant, chacun, une première extrémité fixée à la paroi et une deuxième extrémité fixée au un segment de la virole.Housing according to one of claims 1 to 5, characterized in that the elastic means (30) comprise a plurality of elastic elements each having a first end attached to the wall and a second end attached to a segment of the ferrule . Carter selon la revendication 6, caractérisé en ce que les premières extrémités et/ou les deuxièmes extrémités sont fixées par adhésion, préférentiellement par diffusion et/ou par collage.Housing according to claim 6, characterized in that the first ends and / or the second ends are fixed by adhesion, preferably by diffusion and / or gluing. Carter selon l'une des revendications 1 à 7, caractérisé en ce que la paroi (12) comporte une gorge intérieure (32) dans laquelle les moyens élastiques (30) sont au moins partiellement logés.Housing according to one of claims 1 to 7, characterized in that the wall (12) has an inner groove (32) in which the resilient means (30) are at least partially accommodated. Carter selon l'une des revendications 1 à 8, caractérisé en ce que les segments (22) de la virole présentent, chacun, des extrémités selon une direction circonférentielle de la virole qui sont biseautées.Housing according to one of claims 1 to 8, characterized in that the segments (22) of the ferrule each have ends in a circumferential direction of the ferrule which are beveled. Carter selon la revendication 9, caractérisé en ce que les extrémités des segments présentent un profil généralement incliné entre 30° et 60° par rapport à une tangente, ledit profil étant préférentiellement droit.Housing according to claim 9, characterized in that the ends of the segments have a generally inclined profile between 30 ° and 60 ° relative to a tangent, said profile being preferably straight. Carter selon l'une des revendications 9 et 10, caractérisé en ce que les extrémités selon une direction circonférentielle de chaque segment de la virole sont inclinées dans le même sens.Housing according to one of claims 9 and 10, characterized in that the ends in a circumferential direction of each segment of the ferrule are inclined in the same direction. Carter selon l'une des revendications 1 à 11, caractérisé en ce que les segments de la virole comprennent une surface interne compatible d'un point de vue frottement avec les extrémités des aubes.Housing according to one of claims 1 to 11, characterized in that the segments of the ferrule comprise an internal surface compatible from a friction point of view with the ends of the blades. Carter selon la revendication 12, caractérisé en ce que la surface interne des segments de la virole comprend un revêtement friable en cas de frottement avec les extrémités des aubes.Housing according to claim 12, characterized in that the inner surface of the segments of the shell comprises a friable coating in case of friction with the ends of the blades. Compresseur de turbomachine axiale, comprenant : un rotor (20) muni d'au moins une rangée d'aubes (24) ; un stator avec un carter (12) renfermant le rotor ; caractérisé en ce que le carter est conforme à l'une des revendications 1 à 11.Axial turbomachine compressor, comprising: a rotor (20) provided with at least one row of vanes (24); a stator with a housing (12) enclosing the rotor; characterized in that the casing is in accordance with one of the claims 1 to 11. Compresseur de turbomachine axiale selon la revendication 14, caractérisé en ce qu'un jeu mécanique est prévu entre les extrémités des aubes (24) et la virole (22) en fonctionnement normal lorsque l'axe de rotation du rotor est aligné avec l'axe du rotor.Axial turbomachine compressor according to Claim 14, characterized in that a mechanical clearance is provided between the ends of the vanes (24) and the ferrule (22) in normal operation when the axis of rotation of the rotor is aligned with the axis of the rotor.
EP11156828.3A 2011-03-03 2011-03-03 Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator Active EP2495399B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP11156828.3A EP2495399B1 (en) 2011-03-03 2011-03-03 Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator
CA2769815A CA2769815C (en) 2011-03-03 2012-02-28 External segmented shell capable of correcting for rotor misalignment in relation to the stator
US13/407,948 US8939712B2 (en) 2011-03-03 2012-02-29 External segmented shell capable of correcting for rotor misalignment in relation to the stator
RU2012107669A RU2620883C2 (en) 2011-03-03 2012-03-01 Outer segmented shell adapted to correct rotor offset as the stator
CN201210142291.9A CN102654141B (en) 2011-03-03 2012-03-05 Outer cover for covering end of blade rows of rotors of axial turbine motor and compressor

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EP11156828.3A EP2495399B1 (en) 2011-03-03 2011-03-03 Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator

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EP2495399A1 true EP2495399A1 (en) 2012-09-05
EP2495399B1 EP2495399B1 (en) 2016-11-23

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EP (1) EP2495399B1 (en)
CN (1) CN102654141B (en)
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CN102654141A (en) 2012-09-05
EP2495399B1 (en) 2016-11-23
US8939712B2 (en) 2015-01-27
CA2769815C (en) 2017-11-28
US20120224953A1 (en) 2012-09-06
RU2620883C2 (en) 2017-05-30
CA2769815A1 (en) 2012-09-03
CN102654141B (en) 2017-04-12
RU2012107669A (en) 2013-09-10

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