WO2011012679A2 - Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks - Google Patents

Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks Download PDF

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Publication number
WO2011012679A2
WO2011012679A2 PCT/EP2010/061037 EP2010061037W WO2011012679A2 WO 2011012679 A2 WO2011012679 A2 WO 2011012679A2 EP 2010061037 W EP2010061037 W EP 2010061037W WO 2011012679 A2 WO2011012679 A2 WO 2011012679A2
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WO
WIPO (PCT)
Prior art keywords
sector
assembly
elementary sectors
damping
sectors
Prior art date
Application number
PCT/EP2010/061037
Other languages
French (fr)
Other versions
WO2011012679A3 (en
Inventor
Laurent Gilles Dezouche
Patrick Edmond Kapala
Samir Zaidi
Original Assignee
Snecma
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 Snecma filed Critical Snecma
Priority to CA2769217A priority Critical patent/CA2769217A1/en
Priority to BR112012002304A priority patent/BR112012002304A2/en
Priority to US13/386,496 priority patent/US20120128482A1/en
Priority to EP10739591.5A priority patent/EP2459884B1/en
Priority to JP2012522172A priority patent/JP5697667B2/en
Priority to CN2010800340319A priority patent/CN102472297A/en
Priority to RU2012107522/06A priority patent/RU2537997C2/en
Publication of WO2011012679A2 publication Critical patent/WO2011012679A2/en
Publication of WO2011012679A3 publication Critical patent/WO2011012679A3/en

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Classifications

    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates generally to an aircraft turbomachine, preferably of the turbojet or turboprop type.
  • the invention relates to the compressor or turbine stator of such a turbomachine, and more specifically to a bladed crown sector comprising a plurality of stator vanes as well as two concentric ferrules carrying the vanes and intended to delimit radially a primary flow through the turbomachine, respectively inwardly and outwardly.
  • a bladed crown generally made using several sectors arranged end to end, is generally used in the compressor or the turbine as a rectifier or distributor.
  • Turbomachines generally comprise in series a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
  • the compressors and the turbines comprise several rows of circumferentially spaced apart blades, these rows being separated by rows of blades that are also circumferentially spaced apart.
  • rectifiers and distributors are subject to high dynamic loads. Indeed, the technological evolution leads to a reduction of the number of floors for equal or higher performances, which results in a higher load for each floor.
  • the evolution of production technologies leads to reducing the number of parts, which leads to the reduction of the damping effect of the connections between the parts. This is the case, in particular, when adopting an abradable cartridge soldering technology that eliminates a significant source of dissipation of vibration energy.
  • the object of the invention is therefore to remedy at least partially the problems mentioned above, relating to the embodiments of the prior art.
  • the invention firstly relates to an assembly forming an outer ring sector, for blown crown sector intended to equip an aircraft turbomachine compressor or turbine stator, said outer shell sector comprising: on the one hand a plurality of elementary sectors spaced apart from each other in a tangential direction of said assembly, and on the other hand damping damping wedges each interposed between two elementary sectors associated with it, positioned directly following said tangential direction.
  • each vibration damping wedge has a substantially identical profile to that of the elementary sectors.
  • a support shims against the friction surfaces of the elementary sectors allows a perfect seal between these elements, independent of the pressure differential between the aerodynamic stream and the outside of the compressor or the turbine. Indeed, this seal is obtained by construction, with shims exerting substantially oriented efforts in the tangential direction against the friction surfaces of the elementary sectors. It is noted that this seal is further enhanced in operation, since the plating forces between the friction surfaces and the wedges are accentuated by the application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the vanes. of stator.
  • said wedge is in abutment against two plane parallel friction surfaces and facing each other in said tangential direction and respectively provided on said two elementary sectors associated with said wedge, and said wedge has two friction surfaces. complementary planes parallel to each other and cooperating respectively with the two friction surfaces of the elementary sectors.
  • the planar contacts between the friction surfaces and the complementary friction surfaces make it possible to ensure a satisfactory damping of the vibrations by friction.
  • the manufacture of the assembly according to the invention is greatly simplified, which provides a significant gain in terms of cost and time.
  • said wedge has hooks for its maintenance on the stator of compressor or turbine, these hooks thus having the same profile than those of the brackets worn by the elementary sectors.
  • the elementary sectors are spaced from each other by radial slots fully filled by said damping damping wedges.
  • said damping damping wedges extend substantially in an axial or oblique direction of said assembly.
  • Another object of the present invention relates to a bladed crown sector intended to equip an aircraft turbomachine compressor or turbine stator, comprising an outer ferrule sector assembly as described above, an inner ferrule sector, and a plurality of blades spaced tangentially from each other and interposed between the outer ferrule sector assembly and the inner ferrule sector.
  • each elementary sector carries a single stator vane, or possibly several blades, without departing from the scope of the invention.
  • the bladed crown can constitute a compressor rectifier, or a turbine distributor.
  • the ring sector preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
  • the subject of the invention is also an aircraft turbine engine comprising a stator of compressor or turbine equipped with at least one sector of bladed crown as described above.
  • FIG. 1 represents a schematic sectional view of a turbomachine intended to be equipped with one or more sectors of bladed crown according to the present invention
  • FIG. 2 shows a sectional view showing a portion of the high pressure compressor of the turbomachine shown in Figure 1, and incorporating a bladed crown sector according to the present invention
  • Fig. 3 is a perspective view of the bladed crown sector shown in the preceding figure, the sector being in the form of a preferred embodiment of the present invention
  • Figure 4 shows an axial view of a portion of the bladed crown sector shown in the previous figure
  • FIG. 5 represents a view of the profiles of the wedges and of the elementary sectors of the bladed crown sector shown in the preceding figures, taken along the line V-V of FIG. 4;
  • FIGS. 6a to 6c show diagrammatic views of different steps of a method of manufacture of the bladed crown sector shown in the preceding figures.
  • an aircraft turbojet 100 to which the invention is applicable. It comprises, from upstream to downstream, a low-pressure compressor 2, a high-pressure compressor 4, an annular combustion chamber 6, a high-pressure turbine 8 and a low-pressure turbine 10.
  • FIG. 2 represents a portion of the high-pressure compressor 4.
  • the compressor alternately presents in an axial direction parallel to the axis 12 of the compressor rows 14 of stator vanes and rows 16 of vanes. rotor.
  • a sector of bladed crown 20 it being understood that this sector 20 preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
  • the sector 20 thus forming all or part of a turbine distributor or a compressor rectifier, comprises an inner ferrule sector 24 of inner radial delimitation of a primary annular flow 26 passing through the turbomachine, this ferrule sector 24 laying the feet of In addition to these vanes 18, the sector 20 also incorporates an outer ferrule sector assembly 28, radially outer of the primary annular flow 26, which fixes the heads of the vanes 18.
  • the sector 20 also comprises known additional elements equipping the ferrule sector 24, such as an abradable radially inner coating 29 forming an annular sealing track, contacted by a sealing device 31 carried by the rotor stage 16 carrying the rotating vanes and arranged downstream of the sector 20 concerned.
  • the rotating sealing device 31 is in a known manner of labyrinth or wipe type.
  • the bladed crown sector 20 can be seen.
  • the entire turbine distributor or compressor straightener is obtained by the end-to-end placement of a plurality of these sectors 20, each constituting an angular or circumferential portion of the crown aubagée.
  • the angular sectors 20 are preferably devoid of direct rigid mechanical connections connecting them to each other, their adjacent ends being in fact simply placed opposite each other, with or without play.
  • the inner ferrule sector 24 is made in one piece, and is not segmented.
  • the assembly 28 forming outer shell sector 28 is segmented into elementary sectors 30 spaced from each other in the tangential direction 22, by radial or slightly oblique straight slots 32, thus creating gaps between the directly consecutive sectors 30.
  • Each slot 32 is made along a median straight line between two directly consecutive blades 18, so that each elementary sector 30 fixedly carries a single stator blade 18.
  • One of the two elementary sectors 30 located at the ends of the sector 20 carries an anti-rotation stop 33 protruding radially outwardly, and intended to cooperate, in a known manner, with another part of the stator of the compressor.
  • the assembly 28 also comprises, housed between the elementary sectors 30 directly consecutive vibration damping wedges 34.
  • each vibration damping wedge 34 is housed between two parallel flat friction surfaces 38 facing one another in the tangential direction 22, and respectively provided on the tangential ends facing each other of the two associated elementary sectors. at the hold.
  • each shim 34 has two complementary flat friction surfaces 40, parallel to each other, and also parallel and in contact with the two flat friction surfaces 38 with which they cooperate, respectively.
  • Each shim 34 is thus sandwiched between two directly consecutive elementary sectors 30, in having a complementarity of shape with that of the friction surfaces 38.
  • the contact between the two friction surfaces 38, 40 of each pair is obtained preferably as soon as the wedge 34 is placed between its two associated elementary sectors 30.
  • the wedges 34 thus exert, with their complementary flat friction surfaces 40, substantially oriented efforts in the tangential direction against the friction surfaces 38 of the elementary sectors. These efforts are moreover reinforced in operation by the additional application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the stator vanes.
  • profile of shims 34 is substantially identical to the profile of the elementary sectors, this same profile corresponding to that of the outer shell sector.
  • profile here means the overall shape of the element seen in the tangential direction 22, although a sectional view has been shown in Figure 5.
  • each shim 34 has, like the elementary sectors 30, a lower surface 46 serving as external radial delineation of the vein.
  • the annular overall surface of delimitation of the vein, composed of the succession of these surfaces 46 provided on the wedges 34 and the sectors 30, is therefore substantially continuous from a point of view aerodynamic, since there is no step between the successive surfaces 46.
  • each shim 34 and sector 30 includes hooks for its retention on another part of the compressor stator, and more specifically a holding hook 48 projecting forwards, and a holding hook 50 protruding towards the rear.
  • the hooks 48, 50 are respectively housed in annular slots 52, 54 provided in another part of the stator of the compressor, to ensure the attachment of the sector 20 on the other part of the stator.
  • each shim 34 allows the transmission of tangential forces between the two elementary sectors 30 between which it is interposed.
  • the material used for the elementary sectors 30 and the material used for the wedges 34 are substantially of the same nature, preferably metallic, and chosen so that the wedges are used primarily with respect to the elementary sectors 30.
  • the ratio between the extent in the tangential direction of each shim, and the extent in the tangential direction of each elementary sector, these extents also corresponding to the thicknesses is between 0.5 and 1.
  • FIGS. 6a to 6c schematize a method of manufacturing the bladed crown sector 20.
  • a one-piece assembly 100 is produced by casting or by machining, forming the inner ferrule sector 24, the outer ferrule sector 28, and the stator vanes 18.
  • By simple and inexpensive machining it is then proceeded to the realization of the radial straight slots 32 on the outer ferrule sector 28, so as to obtain the elementary sectors 30, such as that this has been schematized in Figure 6b.
  • these slots 32 can be obtained by simply cutting the sector 28.
  • Figure 6c shows the final step of placing the vibration damping wedges 34 in the slots 32 forming the friction surfaces, by simply sliding the wedges in their respective holes.

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

Abstract

The invention relates to an assembly forming an outer shell sector (28) for a bladed ring sector (20) intended for a turbine or compressor stator of an aircraft turbine engine, comprising a plurality of elementary sectors (30) and vibration-damping blocks (34) disposed between the two elementary sectors associated therewith. According to the invention, the profile of each vibration-damping block (34) is substantially identical to that of the elementary sectors (30).

Description

SECTEUR DE VIROLE EXTERIEURE POUR COURONNE AUBAGEE DE EXTERNAL VIROLE SECTOR FOR AUBAGEE CROWN
STATOR DE TURBOMACHINE D'AERONEF, COMPRENANT DES CALES AIRCRAFT TURBOMACHINE STATOR, COMPRISING SHIMS
AMORTISSEUSES DE VIBRATIONS  SHOCK ABSORBERS
DESCRIPTION DESCRIPTION
La présente invention se rapporte de façon générale à une turbomachine d'aéronef, de préférence du type turboréacteur ou turbopropulseur . The present invention relates generally to an aircraft turbomachine, preferably of the turbojet or turboprop type.
Plus particulièrement, l'invention concerne le stator de compresseur ou de turbine d'une telle turbomachine, et plus précisément un secteur de couronne aubagée comprenant une pluralité d'aubes de stator ainsi que deux viroles concentriques portant les aubes et destinées à délimiter radialement un flux primaire traversant la turbomachine, respectivement vers l'intérieur et vers l'extérieur. Une telle couronne aubagée, généralement réalisée à l'aide de plusieurs secteurs agencés bout à bout, est généralement utilisée dans le compresseur ou la turbine en tant que redresseur ou distributeur.  More particularly, the invention relates to the compressor or turbine stator of such a turbomachine, and more specifically to a bladed crown sector comprising a plurality of stator vanes as well as two concentric ferrules carrying the vanes and intended to delimit radially a primary flow through the turbomachine, respectively inwardly and outwardly. Such a bladed crown, generally made using several sectors arranged end to end, is generally used in the compressor or the turbine as a rectifier or distributor.
Les turbomachines comportent généralement en série un compresseur basse pression, un compresseur haute pression, une chambre de combustion, une turbine haute pression et une turbine basse pression. Les compresseurs et les turbines comportent plusieurs rangées d'aubes mobiles espacées circonférentiellement, ces rangées étant séparées par des rangées d'aubes fixes aussi espacées circonférentiellement . Dans les turbomachines modernes, les redresseurs et les distributeurs sont soumis à des sollicitations dynamiques élevées. En effet, l'évolution technologique conduit à une réduction du nombre des étages pour des performances égales ou supérieures, ce qui se traduit par une charge plus élevée pour chaque étage. D'autre part, l'évolution des technologies de production conduit à réduire le nombre de pièces, ce qui conduit à la diminution de l'effet amortisseur des liaisons entre les pièces. C'est le cas, notamment, lorsque l'on adopte une technologie de brasage de la cartouche d' abradable qui supprime une source importante de dissipation de l'énergie vibratoire. Turbomachines generally comprise in series a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The compressors and the turbines comprise several rows of circumferentially spaced apart blades, these rows being separated by rows of blades that are also circumferentially spaced apart. In the Modern turbomachines, rectifiers and distributors are subject to high dynamic loads. Indeed, the technological evolution leads to a reduction of the number of floors for equal or higher performances, which results in a higher load for each floor. On the other hand, the evolution of production technologies leads to reducing the number of parts, which leads to the reduction of the damping effect of the connections between the parts. This is the case, in particular, when adopting an abradable cartridge soldering technology that eliminates a significant source of dissipation of vibration energy.
Pour résoudre ce problème de vibrations, il a été proposé, dans le document FR-A-2 902 843, de segmenter le secteur de virole extérieure en secteurs élémentaires espacés les uns des autres selon la direction tangentielle par des fentes ou découpes radiales, obliques ou autres, chaque secteur élémentaire portant une unique aube du secteur de couronne aubagée . De plus, des plaquettes d'amortissement en forme de languettes sont interposées entre les secteurs élémentaires. Le principe de fonctionnement repose sur l'introduction d'une non linéarité de raideur dans le comportement dynamique de la structure. Cette non linéarité est activée à partir d'un niveau vibratoire seuil du système. Cette activité vibratoire provoque un mouvement relatif entre les secteurs élémentaires des pales et les plaquettes amortissantes. Ce mouvement relatif provoque des pertes d'adhérence et des recollements successifs des plaquettes amortissantes. Ils se traduisent par une variation continuelle de la raideur locale du système. De ce fait, le ou les modes responsables de l'activité vibratoire sont désorganisés par la variation permanente de leurs fréquences propres associées. Les résonances du système ne peuvent s'installer du fait de la variation continuelle de l'état du système dynamique. Il s'en suit une réduction des niveaux vibratoires du système. To solve this vibration problem, it has been proposed in document FR-A-2 902 843 to segment the outer shell sector into elementary sectors spaced from each other in the tangential direction by oblique radial slits or cuts. or other, each elemental area bearing a single dawn of the bladed crown area. In addition, tab-shaped damping plates are interposed between the elementary sectors. The operating principle is based on the introduction of a nonlinearity of stiffness in the dynamic behavior of the structure. This non-linearity is activated from a threshold vibratory level of the system. This vibratory activity causes a relative movement between the elementary sectors of the blades and the damping pads. This relative movement causes adhesion losses and successive gluing of damping pads. They result in a continual variation of the local stiffness of the system. As a result, the mode or modes responsible for the vibratory activity are disorganized by the permanent variation of their associated natural frequencies. The resonances of the system can not be installed because of the continual variation of the state of the dynamic system. This results in a reduction of the vibratory levels of the system.
Néanmoins, même si cette solution s'avère satisfaisante en termes d'amortissement des vibrations, elle reste perfectible. Surtout, dans cette solution proposée par le document FR-A-2 902 843, les plaquettes amortissantes sont maintenues plaquées contre les surfaces de friction des secteurs élémentaires par effet de gradient de pression entre la veine aérodynamique et l'extérieur du compresseur, appliquant à ces plaquettes un effort orienté radialement vers l'intérieur. L'inconvénient est que ce gradient de pression peut ne pas être suffisant pour assurer un plaquage adéquate des plaquettes contre les surfaces de friction. Dans un tel cas, il en découle non seulement une diminution des performances d'amortissement des vibrations, mais également une possible rupture d'étanchéité de la veine.  Nevertheless, even if this solution is satisfactory in terms of vibration damping, it remains perfectible. Above all, in this solution proposed by the document FR-A-2 902 843, the damping plates are held pressed against the friction surfaces of the elementary sectors by pressure gradient effect between the aerodynamic stream and the outside of the compressor, applying to these plates a force directed radially inwards. The disadvantage is that this pressure gradient may not be sufficient to ensure proper plating of the pads against the friction surfaces. In such a case, it results not only a decrease in vibration damping performance, but also a possible breakage of the vein.
En outre, un autre inconvénient relatif à cette solution réside dans la sur-sollicitation de l'une des aubes du secteur de couronne aubagée . En effet, les efforts aérodynamiques appliqués sur les aubes intègrent une composante tangentielle qui ne peut être reprise dans le secteur de virole extérieure, en raison de sa segmentation en secteurs élémentaires espacés tangentiellement . Ainsi, ces composantes tangentielles se cumulent et transitent par le secteur de virole intérieure du secteur de couronne aubagée, avant de transiter par l'aube située au droit de la butée anti-rotation équipant le secteur de couronne. C'est donc cette aube qui est extrêmement sollicitée en raison de l'incapacité du secteur de virole extérieure à transmettre les efforts statiques selon la direction tangentielle . In addition, another drawback relating to this solution lies in the over-stressing of one of the blades of the bladed crown sector. Indeed, the aerodynamic forces applied on the blades incorporate a tangential component that can not be taken up in the outer shell sector, because of its segmentation in elementary sectors spaced tangentially. Thus, these tangential components accumulate and transit through the inner ferrule sector of the bladed crown sector, before passing through the blade located at the right of the anti-rotation stop equipping the crown sector. It is therefore this dawn which is extremely solicited because of the inability of the outer shell sector to transmit the static forces in the tangential direction.
L' invention a donc pour but de remédier au moins partiellement aux problèmes mentionnés ci-dessus, relatifs aux réalisations de l'art antérieur.  The object of the invention is therefore to remedy at least partially the problems mentioned above, relating to the embodiments of the prior art.
Pour ce faire, l'invention a tout d'abord pour objet un ensemble formant secteur de virole extérieure, pour secteur de couronne aubagée destiné à équiper un stator de compresseur ou de turbine de turbomachine d'aéronef, ledit secteur de virole extérieure comprenant d'une part une pluralité de secteurs élémentaires espacés les uns des autres selon une direction tangentielle dudit ensemble, et d'autre part des cales amortisseuses de vibrations chacune interposée entre deux secteurs élémentaires lui étant associés, positionnés de façon directement consécutive selon ladite direction tangentielle.  To do this, the invention firstly relates to an assembly forming an outer ring sector, for blown crown sector intended to equip an aircraft turbomachine compressor or turbine stator, said outer shell sector comprising: on the one hand a plurality of elementary sectors spaced apart from each other in a tangential direction of said assembly, and on the other hand damping damping wedges each interposed between two elementary sectors associated with it, positioned directly following said tangential direction.
Selon l'invention, chaque cale amortisseuse de vibrations présente un profil sensiblement identique à celui des secteurs élémentaires.  According to the invention, each vibration damping wedge has a substantially identical profile to that of the elementary sectors.
De par le profil particulier des cales, l'interface de friction entre celles-ci et les secteurs élémentaires est de grande dimension, qui se traduit par un effet d'amortissement amélioré. Due to the particular profile of the wedges, the friction interface between these and the sectors elementary is large, which results in an improved damping effect.
De plus, un appui des cales contre les surfaces de friction des secteurs élémentaires permet l'obtention d'une parfaite étanchéité entre ces éléments, indépendante du différentiel de pression entre la veine aérodynamique et l'extérieur du compresseur ou de la turbine. En effet, cette étanchéité est obtenue par construction, avec les cales exerçant des efforts sensiblement orientés selon la direction tangentielle contre les surfaces de friction des secteurs élémentaires. Il est noté que cette étanchéité est davantage renforcée en fonctionnement, puisque les efforts de plaquage entre les surfaces de friction et les cales sont accentués par l'application, sur les secteurs élémentaires, de la composante tangentielle des efforts aérodynamiques s' exerçant sur les aubes de stator.  In addition, a support shims against the friction surfaces of the elementary sectors allows a perfect seal between these elements, independent of the pressure differential between the aerodynamic stream and the outside of the compressor or the turbine. Indeed, this seal is obtained by construction, with shims exerting substantially oriented efforts in the tangential direction against the friction surfaces of the elementary sectors. It is noted that this seal is further enhanced in operation, since the plating forces between the friction surfaces and the wedges are accentuated by the application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the vanes. of stator.
Pour ce qui concerne la composante tangentielle des efforts aérodynamiques s' exerçant sur les aubes, il est noté que l'un des avantages essentiels de la présente invention réside dans le fait que cette composante peut transiter par l'ensemble formant secteur de virole extérieure, puisque ce dernier, bien qu'il soit sectorisé selon la direction tangentielle, est fortement rigidifié dans cette même direction par l'emplacement particulier des cales amortisseuses de vibrations. Il n'en résulte aucune sur-sollicitation des aubes, qui sont donc chargées de façon sensiblement uniforme. Enfin, il est indiqué qu'un adoptant un profil sensiblement identique à celui des secteurs élémentaires, la délimitation radiale extérieure du flux annulaire primaire, également dénommé veine, est parfaitement reconstituée entre les secteurs élémentaires espacés les uns des autres. With regard to the tangential component of the aerodynamic forces exerted on the blades, it is noted that one of the essential advantages of the present invention lies in the fact that this component can pass through the outer shell sector assembly, since the latter, although it is sectorized in the tangential direction, is strongly stiffened in this same direction by the particular location of vibration damping wedges. This results in no over-stressing of the vanes, which are therefore loaded substantially uniformly. Finally, it is stated that since a adopter has a substantially identical profile to that of the elementary sectors, the outer radial delimitation of the primary annular flow, also called vein, is perfectly reconstituted between the elementary sectors spaced apart from one another.
De préférence, ladite cale est en appui contre deux surfaces de friction planes parallèles et en regard l'une de l'autre selon ladite direction tangentielle et respectivement prévues sur lesdits deux secteurs élémentaires associés à ladite cale, et ladite cale présente deux surfaces de friction planes complémentaires, parallèles entre-elles et coopérant respectivement avec les deux surfaces de friction des secteurs élémentaires. Les contacts plans entre les surfaces de friction et les surfaces de friction complémentaires permettent d'assurer un amortissement satisfaisant des vibrations par frottement. De plus, il est possible de réaliser simultanément les deux surfaces de friction au cours d'une unique opération d'usinage, par exemple un simple tronçonnage, afin d'obtenir des fentes droites, c'est-à-dire suivant un plan déterminé, fentes dans lesquelles sont ensuite logées les cales correspondantes. La fabrication de l'ensemble selon l'invention s'en trouve fortement simplifiée, ce qui procure un gain sensible en termes de coût et de temps .  Preferably, said wedge is in abutment against two plane parallel friction surfaces and facing each other in said tangential direction and respectively provided on said two elementary sectors associated with said wedge, and said wedge has two friction surfaces. complementary planes parallel to each other and cooperating respectively with the two friction surfaces of the elementary sectors. The planar contacts between the friction surfaces and the complementary friction surfaces make it possible to ensure a satisfactory damping of the vibrations by friction. In addition, it is possible to simultaneously perform the two friction surfaces during a single machining operation, for example a simple cutting, in order to obtain straight slots, that is to say according to a specific plane , slots in which are then housed the corresponding shims. The manufacture of the assembly according to the invention is greatly simplified, which provides a significant gain in terms of cost and time.
De préférence, ladite cale présente des crochets pour son maintien sur le stator de compresseur ou de turbine, ces crochets disposant donc d'un même profil que ceux des crochets portés par les secteurs élémentaires . Preferably, said wedge has hooks for its maintenance on the stator of compressor or turbine, these hooks thus having the same profile than those of the brackets worn by the elementary sectors.
De préférence, les secteurs élémentaires sont espacés les uns des autres par des fentes radiales entièrement comblées par lesdites cales amortisseuses de vibrations.  Preferably, the elementary sectors are spaced from each other by radial slots fully filled by said damping damping wedges.
Préférentiellement, lesdites cales amortisseuses de vibrations s'étendent sensiblement selon une direction axiale ou oblique dudit ensemble.  Preferably, said damping damping wedges extend substantially in an axial or oblique direction of said assembly.
Un autre objet de la présente invention concerne un secteur de couronne aubagée destiné à équiper un stator de compresseur ou de turbine de turbomachine d'aéronef, comprenant un ensemble formant secteur de virole extérieure tel que décrit ci-dessus, un secteur de virole intérieure, ainsi qu'une pluralité d'aubes espacées tangentiellement les unes des autres et interposées entre l'ensemble formant secteur de virole extérieure et le secteur de virole intérieure. Ici, il est prévu que chaque secteur élémentaire porte une unique aube de stator, ou bien éventuellement plusieurs aubes, sans sortir du cadre de l'invention.  Another object of the present invention relates to a bladed crown sector intended to equip an aircraft turbomachine compressor or turbine stator, comprising an outer ferrule sector assembly as described above, an inner ferrule sector, and a plurality of blades spaced tangentially from each other and interposed between the outer ferrule sector assembly and the inner ferrule sector. Here, it is expected that each elementary sector carries a single stator vane, or possibly several blades, without departing from the scope of the invention.
La couronne aubagée peut constituer un redresseur de compresseur, ou bien un distributeur de turbine .  The bladed crown can constitute a compressor rectifier, or a turbine distributor.
En outre, le secteur de couronne s'étend préférentiellement sur une étendue angulaire comprise entre 5 et 60°, mais pouvant aller jusqu'à 360° afin de constituer la totalité de la couronne aubagée.  In addition, the ring sector preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
L'invention a également pour objet une turbomachine d'aéronef comprenant un stator de compresseur ou de turbine équipé d'au moins un secteur de couronne aubagée tel que décrit ci-dessus. The subject of the invention is also an aircraft turbine engine comprising a stator of compressor or turbine equipped with at least one sector of bladed crown as described above.
D'autres avantages et caractéristiques de l'invention apparaîtront dans la description détaillée non limitative ci-dessous.  Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
Cette description sera faite au regard des dessins annexés parmi lesquels ;  This description will be made with reference to the appended drawings among which;
la figure 1 représente une vue schématique en coupe d'une turbomachine destinée à être équipée d'un ou plusieurs secteurs de couronne aubagée selon la présente invention ;  FIG. 1 represents a schematic sectional view of a turbomachine intended to be equipped with one or more sectors of bladed crown according to the present invention;
- la figure 2 représente une vue en coupe représentant une partie du compresseur haute pression de la turbomachine montrée sur la figure 1, et intégrant un secteur de couronne aubagée selon la présente invention ;  - Figure 2 shows a sectional view showing a portion of the high pressure compressor of the turbomachine shown in Figure 1, and incorporating a bladed crown sector according to the present invention;
la figure 3 représente une vue en perspective du secteur de couronne aubagée montré sur la figure précédente, le secteur se présentant sous la forme d'un mode de réalisation préféré de la présente invention ;  Fig. 3 is a perspective view of the bladed crown sector shown in the preceding figure, the sector being in the form of a preferred embodiment of the present invention;
la figure 4 représente une vue axiale d'une partie du secteur de couronne aubagée montré sur la figure précédente ;  Figure 4 shows an axial view of a portion of the bladed crown sector shown in the previous figure;
- la figure 5 représente une vue des profils des cales et des secteurs élémentaires du secteur de couronne aubagée montré sur les figures précédentes, prise selon la ligne V-V de la figure 4 ; et  FIG. 5 represents a view of the profiles of the wedges and of the elementary sectors of the bladed crown sector shown in the preceding figures, taken along the line V-V of FIG. 4; and
- les figures 6a à 6c représentent des vues schématisant différentes étapes d'un procédé de fabrication du secteur de couronne aubagée montré sur les figures précédentes. FIGS. 6a to 6c show diagrammatic views of different steps of a method of manufacture of the bladed crown sector shown in the preceding figures.
En référence tout d'abord à la figure 1, on peut apercevoir un turboréacteur d'aéronef 100 auquel l'invention s'applique. Il comporte, d'amont en aval, un compresseur basse pression 2, un compresseur haute pression 4, une chambre annulaire de combustion 6, une turbine haute pression 8 et une turbine basse pression 10.  Referring firstly to Figure 1, one can see an aircraft turbojet 100 to which the invention is applicable. It comprises, from upstream to downstream, a low-pressure compressor 2, a high-pressure compressor 4, an annular combustion chamber 6, a high-pressure turbine 8 and a low-pressure turbine 10.
La figure 2 représente une partie du compresseur haute pression 4. De façon connue, le compresseur présente, en alternance selon une direction axiale parallèle à l'axe 12 du compresseur, des rangées 14 d'aubes de stator et des rangées 16 d'aubes de rotor. Les aubes de stator 18, réparties circonférentiellement/tangentiellement autour de l'axe 12, s'intègrent dans une partie de stator dénommée couronne aubagée 20, préférentiellement réalisée de manière sectorisée dans la direction circonférentielle 22. Ainsi, par la suite, il sera fait référence à un secteur de couronne aubagée 20, étant entendu que ce secteur 20 s'étend préférentiellement sur une étendue angulaire comprise entre 5 et 60°, mais pouvant aller jusqu'à 360° afin de constituer la totalité de la couronne aubagée.  FIG. 2 represents a portion of the high-pressure compressor 4. In a known manner, the compressor alternately presents in an axial direction parallel to the axis 12 of the compressor rows 14 of stator vanes and rows 16 of vanes. rotor. The stator vanes 18, distributed circumferentially / tangentially about the axis 12, fit into a stator portion called a bladed crown 20, preferably made in a sectorized manner in the circumferential direction 22. Thus, subsequently, it will be done reference to a sector of bladed crown 20, it being understood that this sector 20 preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
Le secteur 20, formant donc tout ou partie d'un distributeur de turbine ou d'un redresseur de compresseur, comprend un secteur de virole intérieure 24 de délimitation radiale intérieure d'un flux annulaire primaire 26 traversant la turbomachine, ce secteur de virole 24 portant fixement les pieds des aubes de stator 18. Le secteur 20 intègre également, en plus de ces aubes 18, un ensemble formant secteur de virole extérieure 28, de délimitation radiale extérieure du flux annulaire primaire 26, qui porte fixement les têtes des aubes 18. The sector 20, thus forming all or part of a turbine distributor or a compressor rectifier, comprises an inner ferrule sector 24 of inner radial delimitation of a primary annular flow 26 passing through the turbomachine, this ferrule sector 24 laying the feet of In addition to these vanes 18, the sector 20 also incorporates an outer ferrule sector assembly 28, radially outer of the primary annular flow 26, which fixes the heads of the vanes 18.
A cet égard, il est noté que le secteur 20 comprend également des éléments additionnels connus équipant le secteur de virole 24, tel qu'un revêtement radialement intérieur abradable 29 formant piste d'étanchéité annulaire, contactée par un dispositif d'étanchéité 31 porté par l'étage de rotor 16 portant les aubes tournantes et agencé en aval du secteur 20 concerné. Le dispositif d'étanchéité tournant 31 est de façon connue du type à labyrinthe ou à léchettes.  In this regard, it is noted that the sector 20 also comprises known additional elements equipping the ferrule sector 24, such as an abradable radially inner coating 29 forming an annular sealing track, contacted by a sealing device 31 carried by the rotor stage 16 carrying the rotating vanes and arranged downstream of the sector 20 concerned. The rotating sealing device 31 is in a known manner of labyrinth or wipe type.
Sur la figure 3, on peut apercevoir le secteur de couronne aubagée 20. Dans le mode de réalisation préféré décrit, la totalité du distributeur de turbine ou du redresseur de compresseur est obtenue par la mise en place bout à bout d'une pluralité de ces secteurs 20, constituant donc chacun une portion angulaire ou circonférentielle de cette couronne aubagée. Les secteurs angulaires 20 (un seul visible sur la figure 3) sont de préférence dépourvus de liaisons mécaniques rigides directes les reliant les uns aux autres, leurs extrémités adjacentes étant en effet simplement placées en regard les unes les autres, avec ou sans jeu.  In FIG. 3, the bladed crown sector 20 can be seen. In the preferred embodiment described, the entire turbine distributor or compressor straightener is obtained by the end-to-end placement of a plurality of these sectors 20, each constituting an angular or circumferential portion of the crown aubagée. The angular sectors 20 (only one visible in FIG. 3) are preferably devoid of direct rigid mechanical connections connecting them to each other, their adjacent ends being in fact simply placed opposite each other, with or without play.
Plus spécifiquement en référence aux figures 3 et 4, on peut apercevoir que le secteur de virole intérieure 24 est réalisé d'une seule pièce, et n'est pas segmenté. En revanche, l'ensemble 28 formant secteur de virole extérieure 28 est segmenté en secteurs élémentaires 30 espacés les uns des autres selon la direction tangentielle 22, par des fentes droites radiales ou légèrement oblique 32, créant donc des jeux entre les secteurs 30 directement consécutifs. Chaque fente 32 est réalisée le long d'une ligne droite médiane entre deux aubes 18 directement consécutives, de sorte que chaque secteur élémentaire 30 porte fixement une unique aube de stator 18. L'un des deux secteurs élémentaires 30 situés aux extrémités du secteur 20 porte une butée anti-rotation 33 faisant saillie radialement vers l'extérieur, et destinée à coopérer, de façon connue, avec une autre partie du stator du compresseur. More specifically with reference to Figures 3 and 4, it can be seen that the inner ferrule sector 24 is made in one piece, and is not segmented. In contrast, the assembly 28 forming outer shell sector 28 is segmented into elementary sectors 30 spaced from each other in the tangential direction 22, by radial or slightly oblique straight slots 32, thus creating gaps between the directly consecutive sectors 30. Each slot 32 is made along a median straight line between two directly consecutive blades 18, so that each elementary sector 30 fixedly carries a single stator blade 18. One of the two elementary sectors 30 located at the ends of the sector 20 carries an anti-rotation stop 33 protruding radially outwardly, and intended to cooperate, in a known manner, with another part of the stator of the compressor.
L'ensemble 28 comporte également, logées entre les secteurs élémentaires 30 directement consécutifs, des cales amortisseuses de vibrations 34.  The assembly 28 also comprises, housed between the elementary sectors 30 directly consecutive vibration damping wedges 34.
Plus précisément, chaque cale amortisseuse de vibrations 34 est logée entre deux surfaces de friction planes 38 parallèles et en regard l'une de l'autre selon la direction tangentielle 22, et respectivement prévues sur les extrémités tangentielles se faisant face des deux secteurs élémentaires associés à la cale. De manière analogue, chaque cale 34 présente deux surfaces de friction planes complémentaires 40, parallèles entre-elles, et également parallèles et au contact des deux surfaces de friction planes 38 avec lesquelles elles coopèrent, respectivement.  More specifically, each vibration damping wedge 34 is housed between two parallel flat friction surfaces 38 facing one another in the tangential direction 22, and respectively provided on the tangential ends facing each other of the two associated elementary sectors. at the hold. Similarly, each shim 34 has two complementary flat friction surfaces 40, parallel to each other, and also parallel and in contact with the two flat friction surfaces 38 with which they cooperate, respectively.
Chaque cale 34 est donc enserrée entre deux secteurs élémentaires directement consécutifs 30, en présentant une complémentarité de forme avec celle des surfaces de friction 38. Each shim 34 is thus sandwiched between two directly consecutive elementary sectors 30, in having a complementarity of shape with that of the friction surfaces 38.
Le contact entre les deux surfaces de friction 38, 40 de chaque couple est obtenu de préférence dès la mise en place de la cale 34 entre ses deux secteurs élémentaires associés 30. Les cales 34 exercent ainsi, avec leurs surfaces de friction planes complémentaires 40, des efforts sensiblement orientés selon la direction tangentielle contre les surfaces de friction 38 des secteurs élémentaires. Ces efforts sont d'ailleurs davantage renforcés en fonctionnement par l'application supplémentaire, sur les secteurs élémentaires, de la composante tangentielle des efforts aérodynamiques s' exerçant sur les aubes de stator.  The contact between the two friction surfaces 38, 40 of each pair is obtained preferably as soon as the wedge 34 is placed between its two associated elementary sectors 30. The wedges 34 thus exert, with their complementary flat friction surfaces 40, substantially oriented efforts in the tangential direction against the friction surfaces 38 of the elementary sectors. These efforts are moreover reinforced in operation by the additional application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the stator vanes.
Comme cela a été schématisé sur la figure As has been schematized in the figure
5, l'une des particularités de la présente invention réside dans le fait que le profil des cales 34 est sensiblement identique au profil des secteurs élémentaires, ce même profil correspondant à celui du secteur de virole extérieure. Par profil, on entend ici la forme globale de l'élément vu selon la direction tangentielle 22, même si une vue en section a été représentée en figure 5. 5, one of the peculiarities of the present invention lies in the fact that the profile of shims 34 is substantially identical to the profile of the elementary sectors, this same profile corresponding to that of the outer shell sector. By profile, here means the overall shape of the element seen in the tangential direction 22, although a sectional view has been shown in Figure 5.
Ainsi, chaque cale 34 présente, tout comme les secteurs élémentaires 30, une surface inférieure 46 servant de délimitation radiale extérieure de la veine. La surface globale annulaire de délimitation de la veine, composée de la succession de ces surfaces 46 prévues sur les cales 34 et les secteurs 30, est par conséquent sensiblement continue d'une point de vue aérodynamique, puisqu'il n'existe aucune marche entre les surfaces successives 46. Thus, each shim 34 has, like the elementary sectors 30, a lower surface 46 serving as external radial delineation of the vein. The annular overall surface of delimitation of the vein, composed of the succession of these surfaces 46 provided on the wedges 34 and the sectors 30, is therefore substantially continuous from a point of view aerodynamic, since there is no step between the successive surfaces 46.
De plus, chaque cale 34 et secteur 30 comprend des crochets pour son maintien sur une autre partie du stator de compresseur, et plus précisément un crochet de maintien 48 faisant saillie vers l'avant, ainsi qu'un crochet de maintien 50 faisant saillie vers l'arrière. Comme cela est montré sur la figure 2, les crochets 48, 50 sont respectivement logés dans des fentes annulaires 52, 54 prévues dans une autre partie du stator du compresseur, afin d'assurer la fixation du secteur 20 sur cette autre partie de stator.  In addition, each shim 34 and sector 30 includes hooks for its retention on another part of the compressor stator, and more specifically a holding hook 48 projecting forwards, and a holding hook 50 protruding towards the rear. As shown in Figure 2, the hooks 48, 50 are respectively housed in annular slots 52, 54 provided in another part of the stator of the compressor, to ensure the attachment of the sector 20 on the other part of the stator.
Les cales 34, comblant entièrement les fentes 32, permettent d'assurer une fonction d'amortissement des vibrations par frottement contre les surfaces de friction 38, selon le principe physique rappelé ci-dessus relatif aux cales divulguées dans le document FR-A-2 902 843. Elles assurent également une fonction d' étanchéité, ainsi qu'une fonction de passage de la composante tangentielle des efforts aérodynamiques s' exerçant sur les aubes de stator. Concernant ce dernier point, d'une façon plus générale, chaque cale 34 permet la transmission d'efforts tangentiels entre les deux secteurs élémentaires 30 entre lesquels elle est interposée.  The shims 34, completely filling the slots 32, make it possible to ensure a damping function of the vibrations by friction against the friction surfaces 38, according to the physical principle mentioned above relating to the shims disclosed in document FR-A-2. 902 843. They also provide a sealing function, as well as a function of passage of the tangential component of the aerodynamic forces exerted on the stator vanes. Regarding this last point, more generally, each shim 34 allows the transmission of tangential forces between the two elementary sectors 30 between which it is interposed.
Le matériau utilisé pour les secteurs élémentaires 30 et le matériau utilisé pour les cales 34 sont sensiblement de même nature, de préférence métalliques, et choisis de manière à ce que les cales s'usent prioritairement par rapport aux secteurs élémentaires 30. En outre, il est indiqué que le rapport entre l'étendue selon la direction tangentielle de chaque cale, et l'étendue selon la direction tangentielle de chaque secteur élémentaire, ces étendues correspondant également aux épaisseurs, est compris entre 0,5 et 1. The material used for the elementary sectors 30 and the material used for the wedges 34 are substantially of the same nature, preferably metallic, and chosen so that the wedges are used primarily with respect to the elementary sectors 30. In addition, it is indicated that the ratio between the extent in the tangential direction of each shim, and the extent in the tangential direction of each elementary sector, these extents also corresponding to the thicknesses, is between 0.5 and 1.
Les figures 6a à 6c schématisent un procédé de fabrication du secteur de couronne aubagée 20. Tout d'abord, comme le montre la figure 6a, en ensemble monobloc 100 est réalisé par coulée ou par usinage, formant le secteur de virole intérieure 24, le secteur de virole extérieure 28, et les aubes de stator 18. Par usinage simple et peu coûteux, il est ensuite procédé à la réalisation des fentes droite radiale 32 sur le secteur de virole extérieure 28, de manière à obtenir les secteurs élémentaires 30, tel que cela a été schématisé sur la figure 6b. A titre d'exemple, ces fentes 32 peuvent être obtenues par simple tronçonnage du secteur 28.  FIGS. 6a to 6c schematize a method of manufacturing the bladed crown sector 20. First, as shown in FIG. 6a, as a one-piece assembly 100 is produced by casting or by machining, forming the inner ferrule sector 24, the outer ferrule sector 28, and the stator vanes 18. By simple and inexpensive machining, it is then proceeded to the realization of the radial straight slots 32 on the outer ferrule sector 28, so as to obtain the elementary sectors 30, such as that this has been schematized in Figure 6b. For example, these slots 32 can be obtained by simply cutting the sector 28.
Enfin, la figure 6c montre l'étape finale consistant à mettre en place les cales amortisseuses de vibrations 34 dans les fentes 32 formant les surfaces de friction, par simple coulissement des cales dans leurs trous respectifs.  Finally, Figure 6c shows the final step of placing the vibration damping wedges 34 in the slots 32 forming the friction surfaces, by simply sliding the wedges in their respective holes.
II est noté que pour obtenir une relative facilité d' insertion de chaque cale dans sa fente associée, tout en permettant un maintien de cette cale dans sa fente par le seul pincement entre les deux surfaces de friction 38, un jeu d'ajustement glissant juste est préférentiellement retenu. Bien entendu, diverses modifications peuvent être apportées par l'homme du métier à l'invention qui vient d'être décrite, uniquement à titre d'exemples non limitatifs. It is noted that to obtain relative ease of insertion of each shim in its associated slot, while allowing a hold of this shim in its slot by the only pinch between the two friction surfaces 38, a sliding fit game just is preferentially retained. Of course, various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples.

Claims

REVENDICATIONS
1. Ensemble formant secteur de virole extérieure (28), pour secteur de couronne aubagée (20) destiné à équiper un stator de compresseur de turbomachine d'aéronef, ledit secteur de virole extérieure comprenant d'une part une pluralité de secteurs élémentaires (30) espacés les uns des autres selon une direction tangentielle (22) dudit ensemble, et d'autre part des cales amortisseuses de vibrations (34) chacune interposée entre deux secteurs élémentaires lui étant associés, positionnés de façon directement consécutive selon ladite direction tangentielle, An outer ferrule sector assembly (28), for a bladed crown sector (20) for equipping an aircraft turbomachine compressor stator, said outer ferrule sector comprising on the one hand a plurality of elementary sectors (30). ) spaced apart from each other in a tangential direction (22) of said assembly, and on the other hand damping damping wedges (34) each interposed between two elementary sectors associated therewith, positioned directly consecutive in said tangential direction,
caractérisé en ce que chaque cale amortisseuse de vibrations (34) présente un profil sensiblement identique à celui des secteurs élémentaires (30).  characterized in that each vibration damping wedge (34) has a profile substantially identical to that of the elementary sectors (30).
2. Ensemble selon la revendication 1, caractérisé en ce que ladite cale est en appui contre deux surfaces de friction planes (38) parallèles et en regard l'une de l'autre selon ladite direction tangentielle (22) et respectivement prévues sur lesdits deux secteurs élémentaires (30) associés à ladite cale, et en ce que ladite cale (34) présente deux surfaces de friction planes complémentaires (40), parallèles entre- elles et coopérant respectivement avec les deux surfaces de friction des secteurs élémentaires. 2. An assembly according to claim 1, characterized in that said shim is in abutment against two plane friction surfaces (38) parallel and facing each other in said tangential direction (22) and respectively provided on said two elementary sectors (30) associated with said wedge, and in that said wedge (34) has two complementary flat friction surfaces (40) parallel to each other and cooperating respectively with the two friction surfaces of the elementary sectors.
3. Ensemble selon la revendication 1 ou la revendication 2, caractérisé en ce que ladite cale (34) présente des crochets (48, 50) pour son maintien sur le stator de compresseur ou de turbine. 3. An assembly according to claim 1 or claim 2, characterized in that said shim (34) has hooks (48, 50) for its maintenance on the stator compressor or turbine.
4. Ensemble selon l'une quelconque des revendications précédentes, caractérisé en ce que les secteurs élémentaires (30) sont espacés les uns des autres par des fentes radiales (32) entièrement comblées par lesdites cales amortisseuses de vibrations (34) . 4. An assembly according to any one of the preceding claims, characterized in that the elementary sectors (30) are spaced from each other by radial slots (32) fully filled by said vibration damping wedges (34).
5. Ensemble selon l'une quelconque des revendications précédentes, caractérisé en ce que lesdites cales amortisseuses de vibrations (34) s'étendent sensiblement selon une direction axiale ou oblique dudit ensemble. 5. An assembly according to any one of the preceding claims, characterized in that said damping damping wedges (34) extend substantially in an axial or oblique direction of said assembly.
6. Secteur de couronne aubagée (20) destiné à équiper un stator de compresseur de turbomachine d'aéronef, comprenant un ensemble formant secteur de virole extérieure (28) selon l'une quelconque des revendications précédentes, un secteur de virole intérieure (24), ainsi qu'une pluralité d'aubes (18) espacées tangentiellement les unes des autres et interposées entre l'ensemble formant secteur de virole extérieure et le secteur de virole intérieure. A bladed crown sector (20) for equipping an aircraft turbomachine compressor stator, comprising an outer ferrule sector assembly (28) according to any one of the preceding claims, an inner ferrule sector (24). and a plurality of blades (18) spaced tangentially from each other and interposed between the outer ferrule sector assembly and the inner ferrule sector.
7. Turbomachine d' aéronef comprenant un stator de compresseur équipé d'au moins un secteur de couronne aubagée selon la revendication 6. 7. An aircraft turbomachine comprising a compressor stator equipped with at least one bladed crown sector according to claim 6.
PCT/EP2010/061037 2009-07-31 2010-07-29 Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks WO2011012679A2 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
CA2769217A CA2769217A1 (en) 2009-07-31 2010-07-29 Outer shell sector for a bladed ring for an aircraft turbomachine stator, including vibration damping shims
BR112012002304A BR112012002304A2 (en) 2009-07-31 2010-07-29 crowned blade sector intended to equip an aircraft turbocharger compressor stator, and aircraft turbocharger
US13/386,496 US20120128482A1 (en) 2009-07-31 2010-07-29 Outer shell sector for a bladed ring for an aircraft turbomachine stator, including vibration damping shims
EP10739591.5A EP2459884B1 (en) 2009-07-31 2010-07-29 Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks
JP2012522172A JP5697667B2 (en) 2009-07-31 2010-07-29 Outer shell sector for winged rings for aircraft turbomachine stators, including damping shims
CN2010800340319A CN102472297A (en) 2009-07-31 2010-07-29 Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks
RU2012107522/06A RU2537997C2 (en) 2009-07-31 2010-07-29 Turbomachine stator blade circular sector and aircraft turbomachine

Applications Claiming Priority (2)

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FR0955439 2009-07-31
FR0955439A FR2948736B1 (en) 2009-07-31 2009-07-31 EXTERNAL VIROLE SECTOR FOR AIRBORNE TURBOMACHINE AIRBORNE STATOR CROWN, COMPRISING SHOCK ABSORBING MOUNTS

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WO2011012679A2 true WO2011012679A2 (en) 2011-02-03
WO2011012679A3 WO2011012679A3 (en) 2011-04-21

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EP (1) EP2459884B1 (en)
JP (1) JP5697667B2 (en)
CN (1) CN102472297A (en)
BR (1) BR112012002304A2 (en)
CA (1) CA2769217A1 (en)
FR (1) FR2948736B1 (en)
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CA2769217A1 (en) 2011-02-03
EP2459884B1 (en) 2018-06-27
JP2013501181A (en) 2013-01-10
FR2948736A1 (en) 2011-02-04
BR112012002304A2 (en) 2016-05-31
JP5697667B2 (en) 2015-04-08
FR2948736B1 (en) 2011-09-23
WO2011012679A3 (en) 2011-04-21
EP2459884A2 (en) 2012-06-06
US20120128482A1 (en) 2012-05-24
RU2012107522A (en) 2013-09-10
CN102472297A (en) 2012-05-23
RU2537997C2 (en) 2015-01-10

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