WO2013088078A1 - Flow straightener sector for a turbomachine compressor which is produced by brazing a platform of its vanes to a shell ring - Google Patents

Flow straightener sector for a turbomachine compressor which is produced by brazing a platform of its vanes to a shell ring Download PDF

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Publication number
WO2013088078A1
WO2013088078A1 PCT/FR2012/052920 FR2012052920W WO2013088078A1 WO 2013088078 A1 WO2013088078 A1 WO 2013088078A1 FR 2012052920 W FR2012052920 W FR 2012052920W WO 2013088078 A1 WO2013088078 A1 WO 2013088078A1
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WO
WIPO (PCT)
Prior art keywords
platform
blade
blades
sector
platforms
Prior art date
Application number
PCT/FR2012/052920
Other languages
French (fr)
Inventor
Patrick Edmond Kapala
Original Assignee
Snecma
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Publication date
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Publication of WO2013088078A1 publication Critical patent/WO2013088078A1/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
    • 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
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing

Definitions

  • the field of the present invention is that of turbomachines and, more particularly, that of the manufacture of parts that constitute them, such as compressor rectifiers.
  • a turbomachine for an aircraft generally comprises, from upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more stages of turbines, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
  • Each compressor may correspond to a turbine, both being connected by a shaft, thus forming, for example, a high pressure body and a low pressure body.
  • the compressors consist of a plurality of stages themselves composed of a wheel of moving blades, driven in rotation by the rotation shaft of the corresponding body, which circulate in front of a fixed rotor wheel, called rectifiers.
  • These rectifiers are generally made in the form of sectors which contain a certain number of blades and which are assembled to each other along a circumference of the turbomachine. They are generally attached to the housings by hook type connections.
  • these rectifiers are manufactured either by assembling blades manufactured individually on ferrules (mechanically-brazed process), or directly by casting (monobloc process molded in the foundry), or finally by machining from massive pieces (monobloc process machined in the mass ).
  • the rectifier sectors consist of blades, an outer ferrule sector, and an inner ferrule sector.
  • the rectifier also comprises a honeycomb sector, positioned inside the inner ferrule, to form an abradable element which seals inside the body between the fixed parts and the moving parts of the body. this same body. All these components are soldered together.
  • the brazed connections between the blades and the inner and outer ferrule sectors are at the level of cuts previously made in the ferrule sectors.
  • the sectors being pre-assembled the solder is deposited at the bonds to be created, in the form of paste or in the form of a strip.
  • the part is then heated to about 1000 ° C in an oven for the brazing operation itself. After cooling, the sector then constitutes a rigid assembly.
  • the end of the range includes surface machining operations whose tolerances are the tightest.
  • the sectors are cast in the foundry by the lost wax process.
  • the intrados and extrados surfaces of the blades and the internal ones of the platforms, which form the internal and external veins of the flow, remain gross of foundry with the finished dimensions and undergo only a polishing making it possible to obtain the low level of roughness specified.
  • the honeycomb is either brazed on the rectifier sector or brazed on a ring sector reported in final assembly. As for mechanically-braked sectors, finishing machining is necessary.
  • the sectors are machined from forged blanks.
  • the material of the inter-blade channels can be removed either by milling, by electro-erosion, or by electrochemical machining.
  • a particular difficulty here lies in the accessibility of the tools of these confined and highly three-dimensional zones.
  • the high machining time contributes to the high cost of this type of manufacture.
  • the operations of polishing, soldering of the honeycomb and machining finish are the same as for the integrally cast molded process.
  • the advantages are the level of the mechanical characteristics of the forged material, which is greater than that of the cast material.
  • the mechano-brazed process is characterized, in particular, by a brittleness of the brazed joint, a poor knowledge of the radius of the brazing fillet, a difficult mastery of it and lastly problems of quality.
  • the rectifying blades of modern compressors are often the seat of vibrations that can lead to their damage in fatigue, with the appearance of cracks, or cracks, may, in the worst case, lead to the rupture of blades.
  • the parts of these rectifiers most requested are the blades, in the connection areas with the inner and outer rings, where is made the transition between the low thickness of the blade and the more rigid portion formed by the ferrules. Initiation of the cracks is in all cases at the trailing edge, at the outlet of the outer blade / ferrule connecting radius formed by the solder which is installed between the two components.
  • This vibration fatigue damage is explained by high dynamic stresses in an area that is already heavily stressed in static stress.
  • the mechanical characteristics of the material constituting the brazed joint are indeed lower than those of the base material and are not very well known. In addition, they depend on parameters that are difficult to control in manufacturing, such as the amount of solder deposited or the clearance between the assembled parts. Consequently, for design, empirical coefficients of reduction of the order of 40% must be applied to the characteristics of the basic material.
  • the radius must be as small as possible in order not to degrade the aerodynamics, but, mechanically, a large radius has a favorable effect thanks to the reduction of the local stress peaks. ; it has, on the other hand, an adverse effect by a decrease in the strength of the brazed joint.
  • a brazed joint thus constitutes a weak point in the manufacture of a mechanically brazed rectifier, both with respect to its mechanical strength and the industrial problems that it generates.
  • the integrally molded casting process is characterized by relatively low mechanical characteristics which are very dependent on the metallurgy and the manufacturing processes used (feeding, cooling, heat treatment). In addition, few founders have the necessary know-how while these parts have demanding specifications. The intervention of a machinist is also necessary for finishing machining, as well as that of a polishing specialist. In the end, the industrialization is very long and not flexible with respect to design changes.
  • the machined monobloc process has the disadvantage that few suppliers have the necessary know-how (namely milling or machining by electroerosion or electrochemical) and the accessibility of the tools in the inter-blade channels is not always possible. In addition, it is characterized by a very high production cost.
  • the present invention aims to overcome these disadvantages by providing compressor rectifiers that offer better mechanical strength in use than those of the prior art and a method for producing these rectifiers which is a reasonable cost.
  • the subject of the invention is a rectifier sector of a turbomachine comprising at least two blades positioned side by side and forming between them a circulation channel for the air passing through the compressor, and held together by their attachment, at one of their radial ends, at a circumferential shroud, each of said vanes comprising at least a first platform integrally formed with its blade and said blade being fixed by soldering of said first platform to said ferrule, characterized in that said blades are positioned circumferentially on said shell leaving their said first non-contiguous platforms, said solder filling the gap left empty between the first platforms of adjacent blades.
  • the invention applies, inter alia, to a rectifier sector of a compressor of a turbomachine.
  • the blades comprise a second platform located on the blade at the end opposite the first platform, said second platforms of at least two adjacent blades being contiguous, without assembly, between them. .
  • This configuration makes it possible to remove the outer shell and, with it, the problems related to its connection with the blades.
  • the second platforms are joined without implying that there is a connection between them.
  • the circumferential shroud is the inner shroud of the straightener.
  • said ferrule has the shape of a cylindrical sheet with straight generatrices. This greatly facilitates the realization of this ferrule and the brazing of the blades on it.
  • the invention also relates to a compressor rectifier of a turbomachine constituted by the assembly of sectors as described above and on a turbomachine characterized in that at least one stage of one of its compressors comprises such a rectifier. .
  • the invention finally relates to a method of producing a rectifier sector intended to be mounted on a stage of a turbomachine compressor, comprising the individual embodiment of blades and their attachment to at least one cylindrical shell whose extension circumferential corresponds to the extension sought for said sector, characterized in that the realization of said blades comprises: a) manufacturing a blade, at least one first platform integral with said blade, located at one end of said blade, and at least one second platform located on the blade at the end; opposed to the first platform, the circumferential extension of said second platforms being such that they are, after assembly, contiguous, without assembly, between them.
  • the blade is manufactured with a circumferential extension of its first platforms such that a gap is positioned between them after assembly.
  • brazing is performed by positioning a solder strip between the face of said first platform opposite said blade and said ferrule.
  • a radially oriented pressure is applied between said first platform and said ferrule during said brazing, so as to compress said solder strip.
  • an abradable ring is brazed to said cylindrical shell, prior to the attachment of said blades to said shell.
  • FIG. 1 is a sectional view of a portion of a turbomachine compressor
  • FIG. 2 is a perspective view of a rectifier sector of a compressor produced according to the prior art, by a mechano-brazed process;
  • FIG. 3 is a sectional view of the sector of Figure 2;
  • FIG. 4 is a sectional view of a rectifier sector according to one embodiment of the invention.
  • FIG. 5 is a sectional view of a stator blade and an inner ferrule of the sector of FIG. 4, before their assembly, and
  • FIG. 6 is a perspective view of the blade of Figure 5, after its assembly on the inner ring.
  • a turbomachine comprises a high-pressure rotor 1 on which are mounted blades 2 which flow upstream of fixed vanes 3 or stator vanes. These have the function of reducing the flow of compressed air in a substantially axial direction after its exit from the blade wheel which is located immediately upstream.
  • the fixed blades 3 are assembled side by side on inner cylindrical inner and outer rings 5 and form with them a rectifier for the stage in question.
  • the outer shell 5 comprises, on the upstream side and the downstream side, hooks 6 whose purpose is to ensure the attachment of the rectifier on the structure of the turbomachine.
  • the inner ferrule 4 carries a support piece 7 (visible in Figure 3) on which is brazed a ring 8 honeycomb. On this ring are rubbed wipers 9, that is to say, thin ribs extending radially from the rotor 1 to penetrate the honeycomb and provide inter-stage sealing in the compressor.
  • Figure 2 shows a rectifier of the prior art in progress according to the mechano-brazed process.
  • the inner and outer rings 5 and 5 are pierced regularly at their center, along their circumference, by cutouts reproducing the profile of the blades forming the blades 3. These cuts have the function of passing the upper and lower ends of the blades, which radially overflow ferrules on which they can be soldered.
  • the rectifier is, for reasons of ease of manufacture, made in the form of circular sectors which are assembled to each other to form a circular ring 360 °.
  • Figure 3 shows in section the relative positioning of a fixed vane blade 3 and the inner and outer shells 5 and 5 on which it is brazed.
  • the upper part of the blade 3 protrudes from the outer shell 5 and weld beads are arranged around the blade at each of the faces of the shell. Brazing is carried out by heating the assembly in an oven at around 1000 ° C. It is the same for the junction between the lower part of the blade 3 and the inner shell 4.
  • At the lower part of the inner shell is fixed by crimping a support 7 which is carrying the honeycomb ring 8 on which will come to rub the wipers 9 of the rotor.
  • a rectifier sector 10 made according to the method of the invention. It is constituted by the assembly of 8 fixed blades 3 monoblocs, each comprising a blade and two platforms, the latter extending axially at both ends of the blade.
  • the blades are positioned side by side and form between them a circulation channel for the air that passes through the compressor. They are assembled at their lower platforms 11 by brazing on an inner ferrule sector 14, while their upper platforms 12 are simply juxtaposed, without assembly between them (the upper and lower words are taken in connection with their away from the axis of rotation of the turbomachine, when mounted on it).
  • the upper platforms have a circumferential extension such that they are in simple support against each other, without physical connection at this level. Such a configuration allows the vibration damping of these platforms by the flexibility it provides.
  • the blades 3 are machined by a cut in the mass and placed on the sector 14 of inner shell which has, here, the shape of a simple cylindrical sheet with straight generatrices.
  • the lower platforms 11 which are fixed by a solder bead 13.
  • the circumferential extension of the lower platforms 11 is such, unlike that of the upper platforms 12, that they are not contiguous and that there is a gap 15 in which may interfere with the solder during the soldering operation of the blade 3 on the ferrule, as will be explained later.
  • the planes of joint between the blades, which form the gap 15, are represented here with an axial direction (with reference to the axis of rotation of the turbomachine) but they can, just as well, present an angle of inclination by report to that direction.
  • the brazing cord thus extends, on the one hand, under the lower platform 11 of the vanes, between these and the lower ferrule 14 and, on the other hand, on the two lateral faces of these platforms. lower in the interstices 15 left between two adjacent blades 3.
  • an abradable honeycomb ring 8 On the inner face of the inner ferrule sector 14 is fixed, also by soldering, an abradable honeycomb ring 8, in the same way as in the prior art, with the difference however that there is no here, an intermediate support piece.
  • FIG. 5 shows, in section, the two constituent parts of a rectifier sector 10.
  • blade 3 has a blade surrounded by its lower platform 4 and its upper platform. 5, and second, the inner ferrule 14 on which was brazed the honeycomb ring 8.
  • These two elements being presented opposite each other, in the position they have after assembly; a space is left free between the lower face of the lower platform 11 and the upper face of the inner shell 14, so that solder can be provided, preferably in the form of a strip, to ensure their mutual attachment.
  • FIG. 6 shows, in perspective, these two elements of FIG. 5, after their assembly.
  • the weld bead 13 has filled the space left free between the lower platform 11 and the inner shell 14 and the gap 15 between the blade presented and an adjacent blade, not shown.
  • the lateral face of the lower platform 14 is embedded by the weld bead 13, which ensures a joining of the adjacent blades at the edge of their lower platforms.
  • the blades 3 are manufactured directly, with their lower 11 and upper 12 platforms, by a conventional machining process, such as a forging or a foundry.
  • a blade blank is produced, which is then machined electrochemically at its blade and the faces of its platforms which form the vein for the air that passes through. the compressor. It then undergoes a polishing operation by tribo finishing.
  • This blade is then lengthened to its length by machining, particularly at the circumferential extension of its platforms, so that the upper platforms 12 of the same sector are perfectly joined and that the lower platforms 11 have between them a clearance corresponding to the desired width for the gap 15.
  • the inner ferrule sector 14 is cut in a sheet, in dimensions chosen according to the circumferential length sought for the sector 10.
  • a honeycomb sector 8 is brazed on the lower face of the sector of inner ferrule 14, to serve as abradable wipers 9 of the rotor 1. This brazing is carried out in a conventional manner, with, for example, a solder NiSiB heated to 1060 ° C.
  • the realization of a rectifier sector 10 then consists of assembling a predetermined number of blades (8 in the case shown in FIG. 4, without this number being imperative) on the inner ferrule sector 14.
  • the number of blades by sector is generally chosen around a dozen, the angle covered by each sector being then from about 30 to 50 °.
  • the notion of sector can move away from this value and go from a few blades to the half-crown or even to a whole crown over 360 °. In the latter case, it is appropriate to manage the problem of the cumulation of tolerances on the width of the platforms, for example by playing on the span of a wheel closure game, whose platform size is then adjustable by machining.
  • the blades To assemble the blades, they are positioned above the inner ferrule sector 14, leaving a space between their lower platforms and the inner ferrule, in which will take place the solder. They are positioned on the circumference of the inner ferrule sector so that their upper platforms are in contact with each other. Being thus positioned the lower platforms 11 are not contiguous and a gap 15, calibrated due to the size of the lower platforms, appears between them.
  • the blades are assembled on the inner ferrule 14 by soldering, by positioning a solder strip of the NiPdCrB 980 or NiCrBSi 1000 type in the space left free between the lower platforms and the inner ferrule, and bearing the all at a temperature respectively of 1010 ° or 1030 ° C depending on the type of solder chosen.
  • This assembly is carried out under a pressure of the blades against the ferrule during soldering.
  • the solder by liquefying, fills the space left between the lower platforms 11 and the inner ferrule sector 14 and migrates, under the effect of applied pressure, to fill the interstices 15 between two consecutive platforms on the ferrule.
  • the solder bead thus has the shape of a cylindrical belt which extends radial extensions which surround the lower platforms, as can be seen in Figure 6.
  • a conventional heat treatment completes the realization of the rectifier sectors 10 , which are then assembled together to form a complete stator wheel.
  • the invention thus has the advantage of combining the mechano-brazed and machined processes in the mass, choosing for each part of the rectifier the most suitable method.
  • Brazed connections at the foot and head of the profiles which were the seat of departures of creeks, no longer exist. They are transferred to a single cylindrical brazed joint between the blade platforms and the ferrule, which is common practice in the trade and is much more easily achievable.
  • the stresses are better distributed than in the case of a more punctual blade / ferrule connection.
  • the proposed method provides, in particular, the following advantages:
  • the outer portion of the rectifier sector 10 is, contrary to what is commonly practiced in the field of turbomachines, sectorized between the blades and that the vanes are not held together at their upper platform 12.
  • This feature which has already been tested on projects of the plaintiff however the introduction of intermediate damping parts, which are not retained in the method of the present invention (see patent applications FR2902843, FR0955439 and FR0955440) does not pose any particular problem because, on the one hand the assembly is held at the inner ferrule and secondly, the stator grooves of the turbomachine maintain the assembly by the hooks 6. It is even a advantage vis-à-vis the reduction of vibratory stresses by the provision of flexibility and damping it provides.

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Abstract

Flow straightener sector of a compressor of a turbomachine comprising at least two vanes (3) positioned side by side and between them forming a circulation duct for the air passing through the compressor, and which are held together by being attached, at one of their radial ends, to a circumferential shell ring (14), each of said vanes comprising at least one first platform (11) produced as one piece with its blade and said vane being attached by brazing of said first platform to said shell ring, characterized in that said vanes (3) are positioned circumferentially on said shell ring (14), leaving their said first platforms (11) non-contiguous, said braze material (13) filling the gap (15) left between the first platforms of adjacent vanes.

Description

SECTEUR DE REDRESSEUR POUR UN COMPRESSEUR DE TURBOMACHINE RÉALISÉ PAR BRASAGE D'UNE PLATE-FORME DE SES AUBES SUR UNE  RECTIFIER AREA FOR A TURBOMACHINE COMPRESSOR MADE BY BRATING A PLATFORM OF ITS AUBES ON A
VIROLE Le domaine de la présente invention est celui des turbomachines et, plus particulièrement celui de la fabrication des pièces qui les constituent, telles que les redresseurs de compresseur.  The field of the present invention is that of turbomachines and, more particularly, that of the manufacture of parts that constitute them, such as compressor rectifiers.
Une turbomachine pour un aéronef comprend généralement, d'amont en aval dans le sens de l'écoulement des gaz, une soufflante, un ou plusieurs étages de compresseurs, par exemple un compresseur basse pression et un compresseur haute pression, une chambre de combustion, un ou plusieurs étages de turbines, par exemple une turbine haute pression et une turbine basse pression, et une tuyère d'échappement des gaz. A chaque compresseur peut correspondre une turbine, les deux étant reliés par un arbre, formant ainsi, par exemple, un corps haute pression et un corps basse pression. A turbomachine for an aircraft generally comprises, from upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more stages of turbines, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle. Each compressor may correspond to a turbine, both being connected by a shaft, thus forming, for example, a high pressure body and a low pressure body.
Les compresseurs sont constitués d'une pluralité d'étages composés eux-mêmes d'une roue d'aubes mobiles, entraînées en rotation par l'arbre de rotation du corps correspondant, qui circulent devant une roue d'aubages fixes, dénommés redresseurs. Ces redresseurs sont généralement réalisés sous la forme de secteurs qui contiennent un certain nombre d'aubes et qui sont assemblés les uns aux autres le long d'une circonférence de la turbomachine. Ils sont généralement fixés aux carters par des liaisons de type crochet. The compressors consist of a plurality of stages themselves composed of a wheel of moving blades, driven in rotation by the rotation shaft of the corresponding body, which circulate in front of a fixed rotor wheel, called rectifiers. These rectifiers are generally made in the form of sectors which contain a certain number of blades and which are assembled to each other along a circumference of the turbomachine. They are generally attached to the housings by hook type connections.
Traditionnellement ces redresseurs sont fabriqués soit en assemblant des pales fabriquées individuellement sur des viroles (procédé mécano -brasé), soit directement par fonderie (procédé monobloc moulé en fonderie), soit enfin par usinage à partir de pièces massives (procédé monobloc usiné dans la masse).  Traditionally, these rectifiers are manufactured either by assembling blades manufactured individually on ferrules (mechanically-brazed process), or directly by casting (monobloc process molded in the foundry), or finally by machining from massive pieces (monobloc process machined in the mass ).
Dans le cas du procédé mécano-brasé les secteurs de redresseur sont constitués des pales, d'un secteur de virole extérieure, et d'un secteur de virole intérieure. En général le redresseur comprend également un secteur en nid d'abeille, positionné à l'intérieur de la virole intérieure, pour former un élément abradable qui, assure l'étanchéité à l'intérieur du corps entre les parties fixes et les parties mobiles de ce même corps. Tous ces composants sont assemblés par brasage. In the case of the mechano-brazed process the rectifier sectors consist of blades, an outer ferrule sector, and an inner ferrule sector. In general, the rectifier also comprises a honeycomb sector, positioned inside the inner ferrule, to form an abradable element which seals inside the body between the fixed parts and the moving parts of the body. this same body. All these components are soldered together.
Les liaisons brasées entre les pales et les secteurs de virole intérieure et extérieure se font au niveau de découpes préalablement pratiquées dans les secteurs de virole. Les secteurs étant pré-assemblés, la brasure est déposée au niveau des liaisons à créer, sous forme de pâte ou sous forme d'un feuillard. La pièce est ensuite chauffée à environ 1000°C dans un four pour l'opération de brasage proprement dite. Après refroidissement, le secteur constitue alors un ensemble rigide. La fin de gamme comporte des opérations d'usinage des surfaces dont les tolérances sont les plus serrées. The brazed connections between the blades and the inner and outer ferrule sectors are at the level of cuts previously made in the ferrule sectors. The sectors being pre-assembled, the solder is deposited at the bonds to be created, in the form of paste or in the form of a strip. The part is then heated to about 1000 ° C in an oven for the brazing operation itself. After cooling, the sector then constitutes a rigid assembly. The end of the range includes surface machining operations whose tolerances are the tightest.
Dans le cas du procédé monobloc moulé en fonderie, les secteurs sont coulés en fonderie par le procédé de la cire perdue. Les surfaces intrados et extrados des pales et celles internes des plates-formes, qui forment les veines intérieure et extérieure de l'écoulement, restent brutes de fonderie aux cotes finies et ne subissent qu'un polissage permettant d'obtenir le faible niveau de rugosité spécifié. Le nid d'abeille est soit brasé sur le secteur redresseur, soit brasé sur un secteur d'anneau rapporté en assemblage final. Comme pour les secteurs mécano -brasés, des usinages de finition sont nécessaires. In the case of the integrally cast molded process, the sectors are cast in the foundry by the lost wax process. The intrados and extrados surfaces of the blades and the internal ones of the platforms, which form the internal and external veins of the flow, remain gross of foundry with the finished dimensions and undergo only a polishing making it possible to obtain the low level of roughness specified. The honeycomb is either brazed on the rectifier sector or brazed on a ring sector reported in final assembly. As for mechanically-braked sectors, finishing machining is necessary.
Enfin dans le cas du procédé monobloc usiné dans la masse, les secteurs sont usinés à partir de pièces brutes forgées. La matière des canaux inter-pales peut être enlevée soit par fraisage, soit par électroérosion, soit encore par usinage électrochimique. Une difficulté particulière réside ici dans l'accessibilité aux outils de ces zones confinées et fortement tridimensionnelles. Le temps d'usinage élevé contribue au coût important de ce type de fabrication. Les opérations de polissage, brasage du nid d'abeille et d'usinage finition sont les mêmes que pour le procédé monobloc moulé en fonderie. Par rapport au procédé précédent, les avantages sont le niveau des caractéristiques mécaniques du matériau forgé, qui est supérieur à celui du matériau coulé.  Finally, in the case of the one-piece process machined in the mass, the sectors are machined from forged blanks. The material of the inter-blade channels can be removed either by milling, by electro-erosion, or by electrochemical machining. A particular difficulty here lies in the accessibility of the tools of these confined and highly three-dimensional zones. The high machining time contributes to the high cost of this type of manufacture. The operations of polishing, soldering of the honeycomb and machining finish are the same as for the integrally cast molded process. Compared to the previous method, the advantages are the level of the mechanical characteristics of the forged material, which is greater than that of the cast material.
Ces différents procédés présentent en revanche plusieurs inconvénients :  These different processes, however, have several disadvantages:
Le procédé mécano-brasé se caractérise, tout particulièrement, par une fragilité du joint brasé, une mauvaise connaissance du rayon du congé de brasure, une maîtrise difficile de celui-ci et enfin des problèmes de qualité. En effet, les aubages redresseurs des compresseurs modernes sont souvent le siège de vibrations pouvant conduire à leur endommagement en fatigue, avec l'apparition de fissurations, ou criques, pouvant, dans le pire des cas, conduire à la rupture de pales. Ces problèmes sont connus particulièrement sur les compresseurs HP modernes à charge aérodynamique élevée. The mechano-brazed process is characterized, in particular, by a brittleness of the brazed joint, a poor knowledge of the radius of the brazing fillet, a difficult mastery of it and lastly problems of quality. Indeed, the rectifying blades of modern compressors are often the seat of vibrations that can lead to their damage in fatigue, with the appearance of cracks, or cracks, may, in the worst case, lead to the rupture of blades. These problems are particularly known on modern HP compressors with high aerodynamic load.
Les parties de ces redresseurs les plus sollicitées sont les pales, dans les zones de raccordement avec les viroles intérieure et extérieure, là où se fait la transition entre l'épaisseur faible de la pale et la partie plus rigide formée par les viroles. L'initiation des criques se situe dans tous les cas au bord de fuite, à la sortie du rayon de raccordement pale/virole extérieure formé par la brasure qui est installée entre les deux composants. Ces dommages de fatigue vibratoire s'expliquent par des contraintes dynamiques élevées dans une zone qui est déjà fortement sollicitée en contrainte statique. Les caractéristiques mécaniques du matériau qui constitue le joint brasé sont en effet plus faibles que celles du matériau de base et ne sont pas très bien connues. De plus, elles dépendent de paramètres qui sont difficiles à maîtriser en fabrication, comme la quantité de brasure déposée ou le jeu entre les pièces assemblées. En conséquence, pour le dimensionnement, des coefficients d'abattement empiriques de l'ordre de 40% doivent être appliqués aux caractéristiques du matériau de base. The parts of these rectifiers most requested are the blades, in the connection areas with the inner and outer rings, where is made the transition between the low thickness of the blade and the more rigid portion formed by the ferrules. Initiation of the cracks is in all cases at the trailing edge, at the outlet of the outer blade / ferrule connecting radius formed by the solder which is installed between the two components. This vibration fatigue damage is explained by high dynamic stresses in an area that is already heavily stressed in static stress. The mechanical characteristics of the material constituting the brazed joint are indeed lower than those of the base material and are not very well known. In addition, they depend on parameters that are difficult to control in manufacturing, such as the amount of solder deposited or the clearance between the assembled parts. Consequently, for design, empirical coefficients of reduction of the order of 40% must be applied to the characteristics of the basic material.
En ce qui concerne le rayon du congé de brasure, le rayon doit être le plus petit possible pour ne pas dégrader l'aérodynamique, mais, sur le plan mécanique, un grand rayon a un effet favorable grâce à la réduction des pics de contrainte locale ; il a, en revanche, un effet défavorable par une diminution de la résistance du joint brasé. Enfin, en production de série, il est difficile de maîtriser le rayon du congé de brasure, à cause de la dispersion de la quantité de brasure déposée, qui est fonction de l'opérateur, de l'accessibilité de la zone et de la viscosité de la pâte. Un joint brasé constitue ainsi un point faible de la fabrication d'un redresseur mécano-brasé, tant vis à vis de sa tenue mécanique que des problèmes industriels qu'il engendre.  As far as the solder radius is concerned, the radius must be as small as possible in order not to degrade the aerodynamics, but, mechanically, a large radius has a favorable effect thanks to the reduction of the local stress peaks. ; it has, on the other hand, an adverse effect by a decrease in the strength of the brazed joint. Finally, in series production, it is difficult to control the radius of the brazing fillet, because of the dispersion of the amount of solder deposited, which is a function of the operator, the accessibility of the zone and the viscosity dough. A brazed joint thus constitutes a weak point in the manufacture of a mechanically brazed rectifier, both with respect to its mechanical strength and the industrial problems that it generates.
Le procédé monobloc moulé en fonderie se caractérise par des caractéristiques mécaniques relativement faibles qui sont très dépendantes de la métallurgie et des processus de fabrication mis en œuvre (alimentation, refroidissement, traitement thermique). En outre, peu de fondeurs possèdent le savoir-faire nécessaire alors que ces pièces ont des spécifications exigeantes. L'intervention d'un usineur est également nécessaire pour l'usinage de finition, de même que celle d'un spécialiste du polissage. Au final, l'industrialisation est très longue et peu souple vis à vis des modifications de conception.  The integrally molded casting process is characterized by relatively low mechanical characteristics which are very dependent on the metallurgy and the manufacturing processes used (feeding, cooling, heat treatment). In addition, few founders have the necessary know-how while these parts have demanding specifications. The intervention of a machinist is also necessary for finishing machining, as well as that of a polishing specialist. In the end, the industrialization is very long and not flexible with respect to design changes.
Enfin le procédé monobloc usiné a pour inconvénient que peu de fournisseurs possèdent le savoir-faire nécessaire (à savoir un fraisage ou un usinage par électroérosion ou électrochimique) et l'accessibilité des outils dans les canaux inter-pales n'est pas toujours possible. Par ailleurs il se caractérise par un coût de production très élevé. Finally, the machined monobloc process has the disadvantage that few suppliers have the necessary know-how (namely milling or machining by electroerosion or electrochemical) and the accessibility of the tools in the inter-blade channels is not always possible. In addition, it is characterized by a very high production cost.
La présente invention a pour but de remédier à ces inconvénients en proposant des redresseurs de compresseur qui offrent une meilleure tenue mécanique en utilisation que ceux de l'art antérieur et un procédé de réalisation de ces redresseurs qui soit d'un coût raisonnable. A cet effet, l'invention a pour objet un secteur de redresseur d'une turbomachine comprenant au moins deux aubes positionnées côte à côte et formant entre elles un canal de circulation pour l'air traversant le compresseur, et maintenues ensemble par leur rattachement, au niveau d'une de leurs extrémités radiales, à une virole circonférentielle, chacune desdites aubes comportant au moins une première plate-forme réalisée de façon monobloc avec sa pale et ladite aube étant fixée par brasure de ladite première plate-forme sur ladite virole, caractérisé en ce que lesdites aubes sont positionnées circonférentiellement sur ladite virole en laissant leurs dites premières plates-formes non-jointives, ladite brasure remplissant l'interstice laissé vide entre les premières plates-formes d'aubes adjacentes. L'invention s'applique, entre autres, à un secteur de redresseur d'un compresseur d'une turbomachine. The present invention aims to overcome these disadvantages by providing compressor rectifiers that offer better mechanical strength in use than those of the prior art and a method for producing these rectifiers which is a reasonable cost. For this purpose, the subject of the invention is a rectifier sector of a turbomachine comprising at least two blades positioned side by side and forming between them a circulation channel for the air passing through the compressor, and held together by their attachment, at one of their radial ends, at a circumferential shroud, each of said vanes comprising at least a first platform integrally formed with its blade and said blade being fixed by soldering of said first platform to said ferrule, characterized in that said blades are positioned circumferentially on said shell leaving their said first non-contiguous platforms, said solder filling the gap left empty between the first platforms of adjacent blades. The invention applies, inter alia, to a rectifier sector of a compressor of a turbomachine.
Le report de la zone brasée en dessous de la plate-forme inférieure de l'aube permet de supprimer la liaison brasée entre la pale et la plate-forme, qui était un point faible dans la tenue en service des redresseurs mécano-brasés de l'art antérieur. Et le fait que ladite brasure remplisse l'interstice laissé vide entre les premières plates-formes d'aubes adjacentes permet d'obtenir une meilleure tenue des aubes sur la virole intérieure en augmentant la surface brasée.  The postponement of the brazed zone below the lower platform of the blade makes it possible to eliminate the brazed connection between the blade and the platform, which was a weak point in the service life of the mechanically-brazed rectifiers of the blade. prior art. And the fact that said solder fills the gap left empty between the first adjacent blade platforms allows to obtain a better holding of the blades on the inner ring by increasing the soldered surface.
Dans un mode particulier de réalisation les aubes comportent une seconde plate-forme située sur la pale à l'extrémité opposée à la première plate-forme, lesdites secondes plates-formes d'au moins deux aubes adjacentes étant jointives, sans assemblage, entre elles. Cette configuration permet de supprimer la virole extérieure et, avec elle, les problèmes liés à sa liaison avec les pales. Les secondes plates-formes sont jointives sans que cela implique qu'il y ait une liaison entre elles.  In a particular embodiment, the blades comprise a second platform located on the blade at the end opposite the first platform, said second platforms of at least two adjacent blades being contiguous, without assembly, between them. . This configuration makes it possible to remove the outer shell and, with it, the problems related to its connection with the blades. The second platforms are joined without implying that there is a connection between them.
Avantageusement la virole circonférentielle est la virole intérieure du redresseur.  Advantageously, the circumferential shroud is the inner shroud of the straightener.
Préférentiellement ladite virole a la forme d'une tôle cylindrique à génératrices rectilignes. Cela facilite grandement la réalisation, de cette virole et le brasage des aubes sur elle. Preferably said ferrule has the shape of a cylindrical sheet with straight generatrices. This greatly facilitates the realization of this ferrule and the brazing of the blades on it.
L'invention porte également sur un redresseur de compresseur d'une turbomachine constitué par l'assemblage de secteurs tels que décrits ci-dessus et sur une turbomachine caractérisée en ce qu'au moins un étage d'un de ses compresseurs comporte un tel redresseur.  The invention also relates to a compressor rectifier of a turbomachine constituted by the assembly of sectors as described above and on a turbomachine characterized in that at least one stage of one of its compressors comprises such a rectifier. .
L'invention porte enfin sur une procédé de réalisation d'un secteur de redresseur destiné à être monté sur un étage d'un compresseur de turbomachine, comprenant la réalisation individuelles d'aubes et leur fixation sur au moins une virole cylindrique dont l'extension circonférentielle correspond à l'extension recherchée pour ledit secteur, caractérisé en ce que la réalisation desdites aubes comprend : a) la fabrication d'une pale, d'au moins une première plate-forme monobloc avec ladite pale, située à une des extrémités de ladite pale, et d'au moins une seconde plate-forme située sur la pale à l'extrémité opposée à la première plate-forme, l'extension circonférentielle desdites secondes plates-formes étant telle qu'elles sont, après montage, jointives, sans assemblage, entre elles. The invention finally relates to a method of producing a rectifier sector intended to be mounted on a stage of a turbomachine compressor, comprising the individual embodiment of blades and their attachment to at least one cylindrical shell whose extension circumferential corresponds to the extension sought for said sector, characterized in that the realization of said blades comprises: a) manufacturing a blade, at least one first platform integral with said blade, located at one end of said blade, and at least one second platform located on the blade at the end; opposed to the first platform, the circumferential extension of said second platforms being such that they are, after assembly, contiguous, without assembly, between them.
b) la fixation desdites aubes par brasage de ladite première plate-forme sur ladite virole cylindrique.  b) fixing said blades by brazing said first platform on said cylindrical shell.
De façon préférentielle l'aube est fabriquée avec une extension circonférentielle de ses premières plates-formes telle qu'un interstice se trouve positionné entre elles après montage. Avantageusement le brasage est effectué en positionnant un feuillard de brasure entre la face de ladite première plate-forme opposée à ladite pale et ladite virole.  Preferably the blade is manufactured with a circumferential extension of its first platforms such that a gap is positioned between them after assembly. Advantageously brazing is performed by positioning a solder strip between the face of said first platform opposite said blade and said ferrule.
De façon préférentielle une pression orientée radialement est appliquée entre ladite première plate-forme et ladite virole au cours dudit brasage, de façon à comprimer ledit feuillard de brasure.  Preferably a radially oriented pressure is applied between said first platform and said ferrule during said brazing, so as to compress said solder strip.
Dans un mode particulier de réalisation un anneau abradable est brasé sur ladite virole cylindrique, antérieurement à la fixation desdites aubes sur ladite virole.  In a particular embodiment an abradable ring is brazed to said cylindrical shell, prior to the attachment of said blades to said shell.
L'invention sera mieux comprise, et d'autres buts, détails, caractéristiques et avantages de celle-ci apparaîtront plus clairement au cours de la description explicative détaillée qui va suivre, d'un mode de réalisation de l'invention donné à titre d'exemple purement illustratif et non limitatif, en référence aux dessins schématiques annexés. The invention will be better understood, and other objects, details, features and advantages thereof will appear more clearly in the following detailed explanatory description of an embodiment of the invention given as a purely illustrative and non-limiting example, with reference to the accompanying schematic drawings.
Sur ces dessins : On these drawings:
- la figure 1 est une vue en coupe d'une partie d'un compresseur de turbomachine ;  - Figure 1 is a sectional view of a portion of a turbomachine compressor;
- la figure 2 est une vue en perspective d'un secteur de redresseur d'un compresseur réalisé selon l'art antérieur, par un procédé mécano-brasé ;  FIG. 2 is a perspective view of a rectifier sector of a compressor produced according to the prior art, by a mechano-brazed process;
- la figure 3 est une vue en coupe du secteur de la figure 2 ;  - Figure 3 is a sectional view of the sector of Figure 2;
- la figure 4 est une vue en coupe d'un secteur de redresseur selon un mode de réalisation de l'invention ;  - Figure 4 is a sectional view of a rectifier sector according to one embodiment of the invention;
- la figure 5 est une vue en coupe d'une aube de redresseur et d'une virole intérieure du secteur de la figure 4, avant leur assemblage, et  FIG. 5 is a sectional view of a stator blade and an inner ferrule of the sector of FIG. 4, before their assembly, and
- la figure 6 est une vue en perspective de l'aube de la figure 5, après son assemblage sur l'anneau intérieur. En se référant à la figure 1, on voit les derniers étages du compresseur haute pression d'une turbomachine. Celle-ci comporte un rotor haute pression 1 sur lequel sont montées des aubes mobiles 2 qui circulent en amont d'aubes fixes 3 ou aubes de redresseur. Celles-ci ont pour fonction de ramener l'écoulement de l'air comprimé dans une direction sensiblement axiale après sa sortie de la roue d'aubes mobiles qui est située immédiatement en amont. Les aubes fixes 3 sont assemblées côte à côte sur des viroles intérieure 4 et extérieure 5 cylindriques et forment avec celles-ci un redresseur pour l'étage en question. La virole extérieure 5 comporte, du côté amont et du coté aval, des crochets 6 dont le but est d'assurer l'accrochage du redresseur sur la structure de la turbomachine. La virole intérieure 4 porte une pièce de support 7 (visible sur la figure 3) sur laquelle est brasé un anneau 8 en nid d'abeille. Sur cet anneau viennent frotter des léchettes 9, c'est-à-dire des nervures fines s'étendant radialement à partir du rotor 1 pour pénétrer dans le nid d'abeille et assurer une étanchéité inter-étages dans le compresseur. - Figure 6 is a perspective view of the blade of Figure 5, after its assembly on the inner ring. Referring to Figure 1, we see the last stages of the high pressure compressor of a turbomachine. It comprises a high-pressure rotor 1 on which are mounted blades 2 which flow upstream of fixed vanes 3 or stator vanes. These have the function of reducing the flow of compressed air in a substantially axial direction after its exit from the blade wheel which is located immediately upstream. The fixed blades 3 are assembled side by side on inner cylindrical inner and outer rings 5 and form with them a rectifier for the stage in question. The outer shell 5 comprises, on the upstream side and the downstream side, hooks 6 whose purpose is to ensure the attachment of the rectifier on the structure of the turbomachine. The inner ferrule 4 carries a support piece 7 (visible in Figure 3) on which is brazed a ring 8 honeycomb. On this ring are rubbed wipers 9, that is to say, thin ribs extending radially from the rotor 1 to penetrate the honeycomb and provide inter-stage sealing in the compressor.
La figure 2 montre un redresseur de l'art antérieur en cours de réalisation selon le procédé mécano-brasé. Les viroles intérieure 4 et extérieure 5 sont percées régulièrement en leur centre, le long de leur circonférence, par des découpes reproduisant le profil des pales formant les aubes fixes 3. Ces découpes ont pour fonction de laisser passer les extrémités hautes et basses des pales, qui débordent ainsi radialement des viroles sur lesquelles elles peuvent être brasées. Le redresseur est, pour des raisons de facilité de fabrication, réalisé sous la forme de secteurs circulaires qui sont assemblés les uns aux autres pour former une couronne circulaire sur 360°.  Figure 2 shows a rectifier of the prior art in progress according to the mechano-brazed process. The inner and outer rings 5 and 5 are pierced regularly at their center, along their circumference, by cutouts reproducing the profile of the blades forming the blades 3. These cuts have the function of passing the upper and lower ends of the blades, which radially overflow ferrules on which they can be soldered. The rectifier is, for reasons of ease of manufacture, made in the form of circular sectors which are assembled to each other to form a circular ring 360 °.
La figure 3 montre en coupe le positionnement relatif d'une pale d'aube fixe 3 et des viroles intérieur 4 et extérieure 5 sur lesquelles elle est brasée. La partie supérieure de l'aube 3 dépasse de la virole extérieure 5 et des cordons de soudure sont disposés autour de la pale au niveau de chacune des faces de la virole. Le brasage s'effectue par chauffage de l'ensemble dans un four aux alentours de 1000°C. Il en est de même pour la jonction entre la partie inférieure de l'aube 3 et la virole intérieure 4. A la partie inférieure de la virole intérieure est fixé par sertissage un support 7 qui est porteur de l'anneau en nid d'abeille 8 sur lequel viendront frotter les léchettes 9 du rotor.  Figure 3 shows in section the relative positioning of a fixed vane blade 3 and the inner and outer shells 5 and 5 on which it is brazed. The upper part of the blade 3 protrudes from the outer shell 5 and weld beads are arranged around the blade at each of the faces of the shell. Brazing is carried out by heating the assembly in an oven at around 1000 ° C. It is the same for the junction between the lower part of the blade 3 and the inner shell 4. At the lower part of the inner shell is fixed by crimping a support 7 which is carrying the honeycomb ring 8 on which will come to rub the wipers 9 of the rotor.
En se référant maintenant à la figure 4 on voit, en coupe transversale, un secteur de redresseur 10 réalisé selon le procédé de l'invention. Il est constitué par l'assemblage de 8 aubes fixes 3 monoblocs, comprenant chacune une pale et deux plates-formes, celles-ci s'étendant axialement aux deux extrémités de la pale. Les aubes sont positionnées côte à côte et forment entre elles un canal de circulation pour l'air qui traverse le compresseur. Elles sont assemblées au niveau de leurs plates-formes inférieures 11 par brasage sur un secteur de virole intérieure 14, alors que leurs plates-formes supérieures 12 sont simplement juxtaposées, sans assemblage entre elles (les mentions supérieure et inférieure sont prises en relation avec leur éloignement de l'axe de rotation de la turbomachine, lorsqu'elles sont montées sur elle). Les plates-formes supérieures ont une extension circonférentielle telle qu'elles sont en appui simple l'une contre l'autre, sans liaison physique à ce niveau. Une telle configuration permet l'amortissement des vibrations de ces plates-formes par la souplesse qu'elle apporte. Referring now to Figure 4 is seen in cross section, a rectifier sector 10 made according to the method of the invention. It is constituted by the assembly of 8 fixed blades 3 monoblocs, each comprising a blade and two platforms, the latter extending axially at both ends of the blade. The blades are positioned side by side and form between them a circulation channel for the air that passes through the compressor. They are assembled at their lower platforms 11 by brazing on an inner ferrule sector 14, while their upper platforms 12 are simply juxtaposed, without assembly between them (the upper and lower words are taken in connection with their away from the axis of rotation of the turbomachine, when mounted on it). The upper platforms have a circumferential extension such that they are in simple support against each other, without physical connection at this level. Such a configuration allows the vibration damping of these platforms by the flexibility it provides.
Les aubes 3 sont usinées par un taillage dans la masse et posées sur le secteur 14 de virole intérieure qui a, ici, la forme d'une simple tôle cylindrique à génératrices rectilignes. Sur cette virole sont disposées les plates-formes inférieures 11 qui sont fixées par un cordon de brasure 13. L'extension circonférentielle des plates-formes inférieures 11 est telle, à la différence de celle des plates-formes supérieures 12, qu'elles ne sont pas jointives et qu'il existe un interstice 15 dans lequel peut s'immiscer de la brasure lors de l'opération de brasage de l'aube 3 sur la virole, comme cela sera expliqué plus loin. Les plans de joint entre les pales, qui forment l'interstice 15, sont représentés ici avec une direction axiale (en référence à l'axe de rotation de la turbomachine) mais ils peuvent, tout aussi bien, présenter un angle d'inclinaison par rapport à cette direction. Le cordon de brasure s'étend ainsi, d'une part, sous la plate-forme inférieure 11 des aubes, entre celles-ci et la virole inférieure 14 et, d'autre part, sur les deux faces latérales de ces plates-formes inférieures dans les interstices 15 laissés entre deux aubes adjacentes 3. The blades 3 are machined by a cut in the mass and placed on the sector 14 of inner shell which has, here, the shape of a simple cylindrical sheet with straight generatrices. On this ferrule are arranged the lower platforms 11 which are fixed by a solder bead 13. The circumferential extension of the lower platforms 11 is such, unlike that of the upper platforms 12, that they are not contiguous and that there is a gap 15 in which may interfere with the solder during the soldering operation of the blade 3 on the ferrule, as will be explained later. The planes of joint between the blades, which form the gap 15, are represented here with an axial direction (with reference to the axis of rotation of the turbomachine) but they can, just as well, present an angle of inclination by report to that direction. The brazing cord thus extends, on the one hand, under the lower platform 11 of the vanes, between these and the lower ferrule 14 and, on the other hand, on the two lateral faces of these platforms. lower in the interstices 15 left between two adjacent blades 3.
Sur la face intérieure du secteur de virole intérieure 14 est fixé, également par brasage, un anneau abradable en nid d'abeille 8, de la même façon que dans l'art antérieur, à la différence toutefois qu'il n'y a pas, ici, de pièce intermédiaire de support. Le décalage radial de l'anneau abradable 8 par rapport à la veine, qui était nécessaire dans l'art antérieur, est remplacé, ici, par l'épaisseur de la plate-forme inférieure 11. La fixation du nid d'abeille sur les secteurs de redresseurs selon l'invention est ainsi facilitée par le fait qu'il est fixé directement sur la virole intérieure et, par ailleurs, que celle-ci a une forme cylindrique simple, à génératrices rectilignes.  On the inner face of the inner ferrule sector 14 is fixed, also by soldering, an abradable honeycomb ring 8, in the same way as in the prior art, with the difference however that there is no here, an intermediate support piece. The radial offset of the abradable ring 8 with respect to the vein, which was necessary in the prior art, is here replaced by the thickness of the lower platform 11. The fixing of the honeycomb on the Rectifier sectors according to the invention is thus facilitated by the fact that it is fixed directly on the inner shell and, moreover, that it has a simple cylindrical shape with straight generatrices.
La figure 5 montre, en coupe, les deux parties constitutives d'un secteur de redresseur 10. On trouve, en premier lieu l'aube 3, qui comporte une pale entourée de sa plate-forme inférieure 4 et de sa plate-forme supérieure 5, et en second lieu, la virole intérieure 14 sur laquelle a été brasé l'anneau en nid d'abeille 8. Ces deux éléments étant présentés l'un en face de l'autre, dans la position qu'ils ont après assemblage ; un espace est laissé libre entre la face inférieure de la plate-forme inférieure 11 et la face supérieure de la virole intérieure 14, de sorte que de la brasure peut être apportée, préférentiellement sous forme d'un feuillard, pour assurer leur fixation réciproque. FIG. 5 shows, in section, the two constituent parts of a rectifier sector 10. First of all, blade 3 has a blade surrounded by its lower platform 4 and its upper platform. 5, and second, the inner ferrule 14 on which was brazed the honeycomb ring 8. These two elements being presented opposite each other, in the position they have after assembly; a space is left free between the lower face of the lower platform 11 and the upper face of the inner shell 14, so that solder can be provided, preferably in the form of a strip, to ensure their mutual attachment.
Enfin, la figure 6 montre, en perspective, ces deux éléments de la figure 5, après leur assemblage. Le cordon de soudure 13 a rempli l'espace laissé libre entre la plate-forme inférieure 11 et la virole intérieure 14 ainsi que l'interstice 15 entre l'aube présentée et une aube adjacente, non représentée. Ce faisant, la face latérale de la plate-forme inférieure 14 est noyée par le cordon de soudure 13, ce qui assure une solidarisation des aubes adjacentes au niveau de la tranche de leurs plates-formes inférieures. Finally, FIG. 6 shows, in perspective, these two elements of FIG. 5, after their assembly. The weld bead 13 has filled the space left free between the lower platform 11 and the inner shell 14 and the gap 15 between the blade presented and an adjacent blade, not shown. In doing so, the lateral face of the lower platform 14 is embedded by the weld bead 13, which ensures a joining of the adjacent blades at the edge of their lower platforms.
On va maintenant décrire le déroulement du procédé de réalisation d'un redresseur de compresseur selon l'invention. We will now describe the progress of the method of producing a compressor rectifier according to the invention.
D'une part, les aubes 3 sont fabriquées directement, avec leurs plates-formes inférieure 11 et supérieure 12, par un procédé d'usinage classique, tel qu'un forgeage ou une fonderie. Dans le cas, préféré, d'un forgeage, une ébauche de l'aube est réalisée, qui est ensuite usinée de façon électrochimique au niveau de sa pale et des faces de ses plates-formes qui forment la veine pour l'air qui traverse le compresseur. Elle subit ensuite une opération de polissage par tribo finition.  On the one hand, the blades 3 are manufactured directly, with their lower 11 and upper 12 platforms, by a conventional machining process, such as a forging or a foundry. In the preferred case of a forging, a blade blank is produced, which is then machined electrochemically at its blade and the faces of its platforms which form the vein for the air that passes through. the compressor. It then undergoes a polishing operation by tribo finishing.
Cette aube fait alors l'objet d'une mise à longueur de ses dimensions par usinage, notamment au niveau de l'extension circonférentielle de ses plates-formes, afin que les plates-formes supérieures 12 d'un même secteur soient parfaitement jointives et que les plates-formes inférieures 11 présentent entre elles un jeu correspondant à la largeur souhaitée pour l'interstice 15. This blade is then lengthened to its length by machining, particularly at the circumferential extension of its platforms, so that the upper platforms 12 of the same sector are perfectly joined and that the lower platforms 11 have between them a clearance corresponding to the desired width for the gap 15.
D'autre part, le secteur 14 de virole intérieure est découpé dans une tôle, dans des dimensions choisies en fonction de la longueur circonférentielle recherchée pour le secteur 10. Un secteur de nid d'abeille 8 est brasé sur la face inférieure du secteur de virole intérieure 14, pour servir d'abradable aux léchettes 9 du rotor 1. Ce brasage s'effectue de façon classique, avec, par exemple, une brasure NiSiB chauffée à 1060°C. On the other hand, the inner ferrule sector 14 is cut in a sheet, in dimensions chosen according to the circumferential length sought for the sector 10. A honeycomb sector 8 is brazed on the lower face of the sector of inner ferrule 14, to serve as abradable wipers 9 of the rotor 1. This brazing is carried out in a conventional manner, with, for example, a solder NiSiB heated to 1060 ° C.
La réalisation d'un secteur de redresseur 10 consiste ensuite à assembler un nombre prédéterminé d'aubes (8 dans le cas présenté sur la figure 4, sans que ce nombre soit impératif) sur le secteur de virole intérieure 14. Le nombre de pales par secteur est généralement choisi autour d'une dizaine, l'angle couvert par chaque secteur étant alors d'environ 30 à 50°. Dans certains cas la notion de secteur peut s'éloigner de cette valeur et aller de quelques pales jusqu'à la demi-couronne ou même jusqu'à une couronne entière sur 360°. Dans ce dernier cas, il convient de gérer le problème du cumul des tolérances sur la largeur des plates-formes, par exemple en jouant sur l'envergure d'un jeu de fermeture de la roue, dont la taille des plates-formes est alors ajustable par usinage. The realization of a rectifier sector 10 then consists of assembling a predetermined number of blades (8 in the case shown in FIG. 4, without this number being imperative) on the inner ferrule sector 14. The number of blades by sector is generally chosen around a dozen, the angle covered by each sector being then from about 30 to 50 °. In some cases the notion of sector can move away from this value and go from a few blades to the half-crown or even to a whole crown over 360 °. In the latter case, it is appropriate to manage the problem of the cumulation of tolerances on the width of the platforms, for example by playing on the span of a wheel closure game, whose platform size is then adjustable by machining.
Pour effectuer l'assemblage des aubes, celles-ci sont positionnées au dessus du secteur 14 de virole intérieure, en laissant un espace entre leurs plates-formes inférieures et la virole intérieure, dans lequel prendra place la brasure. Elles sont positionnées sur la circonférence du secteur de virole intérieure de façon que leurs plates-formes supérieures soient en contact les unes avec les autres. Étant ainsi positionnées les plates-formes inférieures 11 ne sont pas jointives et un interstice 15, calibré du fait de la mise aux dimensions des plates-formes inférieures, apparaît entre elles.  To assemble the blades, they are positioned above the inner ferrule sector 14, leaving a space between their lower platforms and the inner ferrule, in which will take place the solder. They are positioned on the circumference of the inner ferrule sector so that their upper platforms are in contact with each other. Being thus positioned the lower platforms 11 are not contiguous and a gap 15, calibrated due to the size of the lower platforms, appears between them.
L'assemblage des aubes sur la virole intérieure 14 s'effectue par brasage, en positionnant un feuillard de brasure du type NiPdCrB 980 ou NiCrBSi 1000 dans l'espace laissé libre entre les plates-formes inférieures et la virole intérieure, et en portant le tout à une température respectivement de 1010° ou 1030°C selon le type de brasure choisi. Cet assemblage s'effectue sous une mise en pression des aubes contre la virole au cours du brasage. La brasure, en se liquéfiant remplit l'espace laissé entre les plates-formes inférieures 11 et le secteur de virole intérieure 14 et migre, sous l'effet de la pression appliquée, pour remplir les interstices 15 existant entre deux plates-formes consécutives sur la virole.  The blades are assembled on the inner ferrule 14 by soldering, by positioning a solder strip of the NiPdCrB 980 or NiCrBSi 1000 type in the space left free between the lower platforms and the inner ferrule, and bearing the all at a temperature respectively of 1010 ° or 1030 ° C depending on the type of solder chosen. This assembly is carried out under a pressure of the blades against the ferrule during soldering. The solder, by liquefying, fills the space left between the lower platforms 11 and the inner ferrule sector 14 and migrates, under the effect of applied pressure, to fill the interstices 15 between two consecutive platforms on the ferrule.
Le cordon de brasure a ainsi la forme d'un tapis cylindrique duquel s'étendent des extensions radiales qui entourent les plates-formes inférieures, comme on peut le voir sur la figure 6. Un traitement thermique classique complète la réalisation des secteurs de redresseur 10, qui sont ensuite assemblés entre eux pour former une roue complète de redresseur.  The solder bead thus has the shape of a cylindrical belt which extends radial extensions which surround the lower platforms, as can be seen in Figure 6. A conventional heat treatment completes the realization of the rectifier sectors 10 , which are then assembled together to form a complete stator wheel.
Un usinage final, du type rectification, est enfin réalisé pour parfaire les dimensions des crochets 6 de la plate-forme supérieure complète 5, des différentes extrémités et du diamètre intérieur du nid d'abeille 8. Final machining, of the grinding type, is finally performed to perfect the dimensions of the hooks 6 of the complete upper platform 5, the different ends and the inner diameter of the honeycomb 8.
L'invention a ainsi pour intérêt de combiner les procédés mécano-brasé et usiné dans la masse, en choisissant pour chaque partie du redresseur le procédé le mieux adapté. Les liaisons brasées en pied et tête des profils, qui étaient le siège de départs de criques, n'existent plus. Elles sont reportées vers un seul joint brasé de forme cylindrique entre les plates-formes des aubes et la virole, ce qui est d'une pratique courante dans le métier et qui est bien plus facilement réalisable. Enfin les contraintes sont mieux réparties que dans le cas d'une liaison pale/virole plus ponctuelle. The invention thus has the advantage of combining the mechano-brazed and machined processes in the mass, choosing for each part of the rectifier the most suitable method. Brazed connections at the foot and head of the profiles, which were the seat of departures of creeks, no longer exist. They are transferred to a single cylindrical brazed joint between the blade platforms and the ferrule, which is common practice in the trade and is much more easily achievable. Finally, the stresses are better distributed than in the case of a more punctual blade / ferrule connection.
Le procédé proposé procure, en particulier, les avantages suivants :  The proposed method provides, in particular, the following advantages:
- un joint brasé 13 qui est peu sollicité, puisqu'il est reporté en dessous des plates-formes de l'aube,  a brazed joint 13 which is not very stressed, since it is carried below the platforms of the dawn,
- une géométrie des zones critiques bien maîtrisée ; leur géométrie est faite non plus par les congés de brasure, à la forme aléatoire, mais par les rayons obtenus lors de la fabrication des pales unitaires par des procédés classiques et bien connus,  - a geometry of critical areas well controlled; their geometry is made no longer by the brazing fades, in the random form, but by the rays obtained during the manufacture of the unit blades by conventional and well-known methods,
- l'apport, dans les zones critiques, de bonnes caractéristiques mécaniques dues à l'utilisation d'un matériau forgé,  - the contribution, in the critical zones, of good mechanical characteristics due to the use of a forged material,
- un secteur de virole extérieure souple et naturellement amorti, du fait de la liberté laissée aux plates-formes supérieures 12 et à leur positionnement en appui les unes contre les autres,  a flexible and naturally dampened outer shell sector, due to the freedom left to the upper platforms 12 and to their positioning in support against each other,
- la suppression du besoin d'une virole extérieure, qui est remplacée par les plates-formes supérieures 12 jointives,  the elimination of the need for an outer shell, which is replaced by the upper platforms 12 joined,
- et la suppression de la réalisation d'ouvertures dans les secteurs des viroles intérieure 4 et extérieur 5.  and the suppression of the production of openings in the sectors of the inner and outer rings 5 and 5.
On peut noter que la partie extérieure du secteur de redresseur 10 est, contrairement à ce qui est pratiqué couramment dans le domaine des turbomachines, sectorisée entre les pales et que les aubes ne sont pas maintenues ensemble au niveau de leur plate-forme supérieure 12. Cette caractéristique, qui a déjà été expérimentée sur des projets de la demanderesse moyennant toutefois l'introduction de pièces intermédiaires d'amortissement, qui ne sont pas retenu dans le procédé de la présente invention (voir les demandes de brevet FR2902843, FR0955439 et FR0955440), ne pose pas de problème particulier car, d'une part l'ensemble est tenu au niveau de la virole intérieure et d'autre part, les gorges du stator de la turbomachine maintiennent l'ensemble par les crochets 6. Elle constitue même un avantage vis à vis de la réduction des contraintes vibratoires par l'apport de souplesse et l'amortissement qu'elle procure.  It may be noted that the outer portion of the rectifier sector 10 is, contrary to what is commonly practiced in the field of turbomachines, sectorized between the blades and that the vanes are not held together at their upper platform 12. This feature, which has already been tested on projects of the plaintiff however the introduction of intermediate damping parts, which are not retained in the method of the present invention (see patent applications FR2902843, FR0955439 and FR0955440) does not pose any particular problem because, on the one hand the assembly is held at the inner ferrule and secondly, the stator grooves of the turbomachine maintain the assembly by the hooks 6. It is even a advantage vis-à-vis the reduction of vibratory stresses by the provision of flexibility and damping it provides.

Claims

REVENDICATIONS
1. Secteur de redresseur d'une turbomachine comprenant au moins deux aubes (3) positionnées côte à côte et formant entre elles un canal de circulation pour l'air traversant le compresseur, et maintenues ensemble par leur rattachement, au niveau d'une de leurs extrémités radiales, à une virole circonférentielle (14), chacune desdites aubes comportant au moins une première plate-forme (11) réalisée de façon monobloc avec sa pale et ladite aube étant fixée par brasure de ladite première plate-forme sur ladite virole, 1. Rectifier sector of a turbomachine comprising at least two blades (3) positioned side by side and forming between them a circulation channel for the air passing through the compressor, and held together by their attachment, at one of their radial ends, to a circumferential shroud (14), each of said blades comprising at least a first platform (11) integrally formed with its blade and said blade being fixed by brazing said first platform on said shell,
caractérisé en ce que lesdites aubes (3) sont positionnées circonférentiellement sur ladite virole (14) en laissant leurs dites premières plates-formes (11) non-jointives, ladite brasure (13) remplissant l'interstice (15) laissé vide entre les premières plates-formes d'aubes adjacentes. characterized in that said blades (3) are positioned circumferentially on said ferrule (14) leaving their said first platforms (11) non-contiguous, said solder (13) filling the gap (15) left empty between the first adjacent blade platforms.
2. Secteur de redresseur selon la revendication 1 dans lequel les aubes (3) comportent une seconde plate-forme (12) située sur la pale à l'extrémité opposée à la première plate-forme (11), lesdites secondes plates-formes d'au moins deux aubes adjacentes étant jointives, sans assemblage entre elles.  2. rectifier sector according to claim 1 wherein the blades (3) comprise a second platform (12) located on the blade at the end opposite the first platform (11), said second platforms of at least two adjacent blades being contiguous, without assembly between them.
3. Secteur de redresseur selon la revendication 2 dans lequel la virole circonférentielle (14) est la virole intérieure du redresseur.  The rectifier sector of claim 2 wherein the circumferential collar (14) is the inner ferrule of the rectifier.
4. Secteur de redresseur selon l'une des revendications 1 à 3 dans lequel ladite virole (14) a la forme d'une tôle cylindrique à génératrices rectilignes.  4. rectifier sector according to one of claims 1 to 3 wherein said ferrule (14) has the shape of a cylindrical sheet with straight generatrices.
5. Redresseur de compresseur d'une turbomachine constitué par l'assemblage de secteurs selon l'une des revendications 1 à 4.  5. Rectifier compressor of a turbomachine constituted by the sector assembly according to one of claims 1 to 4.
6. Turbomachine caractérisée en ce qu'au moins un étage d'un de ses compresseurs comporte un redresseur selon la revendication 5.  6. Turbomachine characterized in that at least one stage of one of its compressors comprises a rectifier according to claim 5.
7. Procédé de réalisation d'un secteur de redresseur destiné à être monté sur un étage d'un compresseur de turbomachine, comprenant la réalisation individuelles d'aubes (3) et leur fixation sur au moins une virole cylindrique dont l'extension circonférentielle correspond à l'extension recherchée pour ledit secteur (10),  7. A method of producing a rectifier sector intended to be mounted on a stage of a turbomachine compressor, comprising the individual embodiment of blades (3) and their attachment to at least one cylindrical shell whose circumferential extension corresponds to the desired extension for said sector (10),
caractérisé en ce que la réalisation desdites aubes (3) comprend : characterized in that the production of said vanes (3) comprises:
c) la fabrication d'une pale, d'au moins une première plate-forme (1 1) monobloc avec ladite pale, située à une des extrémités de ladite pale, et d'au moins une seconde plateforme (12) située sur la pale à l'extrémité opposée à la première plate-forme (11), l'extension circonférentielle desdites secondes plates-formes étant telle qu'elles sont, après montage, jointives, sans assemblage, entre elles, c) the manufacture of a blade, at least a first platform (1 1) integral with said blade, located at one end of said blade, and at least one second platform (12) located on the blade at the end opposite the first platform (11), the circumferential extension of said second platforms being such that they are, after assembly, contiguous, without assembly, between them,
d) la fixation desdites aubes par brasage de ladite première plate-forme (11) sur ladite virole cylindrique (14).  d) fixing said blades by brazing said first platform (11) on said cylindrical shell (14).
8. Procédé selon la revendication 7 dans lequel l'aube est fabriquée avec une extension circonférentielle de ses premières plates-formes telle qu'un interstice (15) se trouve positionné entre elles après montage.  8. The method of claim 7 wherein the blade is manufactured with a circumferential extension of its first platforms such that a gap (15) is positioned between them after assembly.
9. Procédé selon l'une des revendications 7 ou 8 dans lequel le brasage est effectué en positionnant un feuillard de brasure (13) entre la face de ladite première plate-forme (11) opposée à ladite pale et ladite virole (14).  9. Method according to one of claims 7 or 8 wherein the brazing is performed by positioning a solder strip (13) between the face of said first platform (11) opposite said blade and said ferrule (14).
10. Procédé selon la revendication 9 dans lequel une pression orientée radialement est appliquée entre ladite première plate-forme et ladite virole au cours dudit brasage, de façon à comprimer le feuillard de brasure (13).  The method of claim 9 wherein a radially oriented pressure is applied between said first platform and said ferrule during said brazing, thereby compressing the solder strip (13).
11. Procédé selon l'une des revendications 7 à 10 dans lequel un anneau abradable (8) est brasé sur ladite virole cylindrique, antérieurement à la fixation desdites aubes sur ladite virole.  11. Method according to one of claims 7 to 10 wherein an abradable ring (8) is brazed to said cylindrical shell, prior to the attachment of said blades on said ferrule.
PCT/FR2012/052920 2011-12-15 2012-12-13 Flow straightener sector for a turbomachine compressor which is produced by brazing a platform of its vanes to a shell ring WO2013088078A1 (en)

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FR1161660A FR2984427B1 (en) 2011-12-15 2011-12-15 RECTIFIER AREA FOR A TURBOMACHINE COMPRESSOR MADE BY BRATING A PLATFORM OF ITS AUBES ON A VIROLE.
FR1161660 2011-12-15

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WO2015088834A1 (en) * 2013-12-13 2015-06-18 United Technologies Corporation Integral part wear indicator system for stator
FR3049000A1 (en) * 2016-03-18 2017-09-22 Snecma TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN
CN110686508A (en) * 2018-07-04 2020-01-14 中国二十冶集团有限公司 Method for mounting lower frame of annular heating furnace
US10731660B2 (en) 2018-08-17 2020-08-04 Rolls-Royce Corporation Diffuser having platform vanes

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FR2942638A1 (en) * 2009-02-27 2010-09-03 Snecma Angular sector for rectifier in compressor of e.g. turbojet engine, of airplane, has angular locking flange arranged coaxially around outer shell and including shoulder that is radially supported against outer shell

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US6508630B2 (en) * 2001-03-30 2003-01-21 General Electric Company Twisted stator vane
FR2950116B1 (en) * 2009-09-15 2011-12-09 Snecma COMPRESSOR RECTIFIER FOR TURBOMACHINE, COMPRISING AUB HEADS MOUNTED USING A VIBRATION SHOCK ABSORBER MATERIAL ON THE EXTERNAL VIROLE

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EP2031255A1 (en) * 2007-08-30 2009-03-04 Techspace Aero Vane, collar and assembly for synchronising ring stage of a compressor, turbomachine comprising such a compressor and method of assembly by welding between a collar and a vane.
FR2942638A1 (en) * 2009-02-27 2010-09-03 Snecma Angular sector for rectifier in compressor of e.g. turbojet engine, of airplane, has angular locking flange arranged coaxially around outer shell and including shoulder that is radially supported against outer shell

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015088834A1 (en) * 2013-12-13 2015-06-18 United Technologies Corporation Integral part wear indicator system for stator
US10213893B2 (en) 2013-12-13 2019-02-26 United Technologies Corporation Integral part wear indicator system, method and apparatus
US10688618B2 (en) 2013-12-13 2020-06-23 Raytheon Technologies Corporation Integral part wear indicator system, method and apparatus
FR3049000A1 (en) * 2016-03-18 2017-09-22 Snecma TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN
CN110686508A (en) * 2018-07-04 2020-01-14 中国二十冶集团有限公司 Method for mounting lower frame of annular heating furnace
CN110686508B (en) * 2018-07-04 2023-11-21 中国二十冶集团有限公司 Method for installing lower frame of annular heating furnace
US10731660B2 (en) 2018-08-17 2020-08-04 Rolls-Royce Corporation Diffuser having platform vanes

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