EP2948640B1 - Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method - Google Patents

Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method Download PDF

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Publication number
EP2948640B1
EP2948640B1 EP14704842.5A EP14704842A EP2948640B1 EP 2948640 B1 EP2948640 B1 EP 2948640B1 EP 14704842 A EP14704842 A EP 14704842A EP 2948640 B1 EP2948640 B1 EP 2948640B1
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EP
European Patent Office
Prior art keywords
ring
vane assembly
partition
radial
tongue
Prior art date
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EP14704842.5A
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German (de)
French (fr)
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EP2948640A1 (en
Inventor
Sébastien CONGRATEL
Marion CHAMBRE
Bruno Richard
Romain ROULLET
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Safran Aircraft Engines SAS
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SNECMA Services SA
SNECMA SAS
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Publication of EP2948640A1 publication Critical patent/EP2948640A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the field of the invention is that of fixed vanes for distribution of the air flow in a turbomachine.
  • a turbomachine generally comprises, from upstream to downstream in the direction of the gas flow, a blower, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
  • These turbines comprise a distributor of the air flow in the turbomachine, composed of a plurality of fixed blade stages each comprising a plurality of blades extending generally radially with respect to an axis of the turbomachine, and disposed between an inner annular platform and an outer annular platform by which said vanes are attached to the turbomachine.
  • the blades are conventionally produced by a technique known as the foundry lost wax. Nuclei are inserted in the mold before injection of the wax, these cores being held in position by sockets, the association between the cores and the sockets being carried out manually.
  • the invention aims to remedy this problem by proposing a fixed blade of flow distribution in a turbomachine, comprising an inner annular platform and a plurality of fixed vanes mounted on it, the inner platform comprising a support plate forming the base of said blades, a radial annular partition extending from the support plate towards an axis of the blade, and an inner ring attached to the radial annular partition, and having an inner surface on which is disposed a material abradable, the blade being characterized in that the inner ring comprises at least one cutout defining a tongue, the tongue being folded to bear against the radial annular partition.
  • the invention also proposes a turbomachine comprising at least one such blade.
  • the distribution vane according to the invention is lighter but as robust as before since the reinforcement function in support against the partition radial is made by the inner crown of the vane itself, without adding material.
  • FIG. 1 there is shown a partial view of a fixed blade 10 distribution of the flow of air flowing in a turbomachine, the direction of flow of the air flow being represented by an arrow F, the blade forming a stage of a distributor of a turbomachine turbine, for example a low-pressure turbine.
  • Blading 10 comprises a plurality of fixed blades 11 arranged radially with respect to an axis of the turbomachine (not shown), which is also the axis of the blade, said blades being mounted on an inner annular platform 12 .
  • the platform 12 comprises an annular partition 120 extending radially with respect to the axis of the turbomachine, as well as an annular plate 121 for supporting the blades 11, extending on either side of the annular partition. at a radially outer end thereof.
  • the platform 12 also comprises an inner ring 122 extending on either side of the radial annular partition 120, at its radially inner end, and on which a layer of abradable material 123 is attached.
  • the inner ring 122 has a median annular section 1220 extending substantially axially with respect to the axis of the blading, and two end annular tabs 1221, 1222 extending respectively upstream and downstream.
  • the blading relative to the airflow being radially offset from the center section 1220, said sections being inclined relative to the axis of the blading.
  • These sections are shaped to cooperate with rotor blade spoilers placed upstream and downstream with respect to the blade 10, in order to form labyrinth type seals, to avoid recirculation of air in one direction. radial between the vein of the blade 10 (that is to say between the blades 11) and the gap between the platform of the fixed blade and the adjacent rotor.
  • the inner ring 122 comprises, on its median section 1220, at least one, and preferably a plurality of U-shaped cutouts 1223, each cutout thus comprising two preferably but non-limitatively parallel portions 1224 (forming the branches of the "U"") Joined at one end by a transverse portion 1225 (forming the base of the" U ").
  • the portions 1224 are oriented substantially parallel to the axis of the blade and the transverse portion 1225 and disposed on the downstream side of the blank with respect to the air flow.
  • Each cutout 1223 thus delimits a tongue 1226 detached from the rest of the median section by the three portions of the cutout. Because of the shape of the cutouts, each tab extends over a ring sector.
  • At least one end portion 1227 of each cutout is bent at right angles to the middle section of the ring 122 so as to extend substantially radially.
  • each tongue can also be bent at right angles to the crown.
  • Each tongue thus folded releases an opening 1228 in ring sector in the ring 122.
  • the cuts 1123, and therefore the tabs 1226 and the openings 1228 are distributed regularly, that is to say at constant angular interval relative to the axis of the blade, along the circumference of the crown.
  • the ring 122 has, on an annular zone of its median section of the width of the openings, an alternation of solid areas and openings 1228.
  • the ring 122 is attached to the radial partition 120 at the annular zone comprising the alternation of openings and solid areas, the end 1227 of the tabs at right angles to the ring bearing against the wall radial.
  • the tongues cut in the crown constitute the surface to be soldered on the radial partition, thus making it possible to assemble the crown to the radial partition without adding additional elements (for example sheets, tabs on a radial partition ).
  • the blading is thus lightened.
  • the layer of abradable material 123 attached to the ring can also be reported on the radial wall through each opening 1228 of said ring.
  • the layer of abradable material 123 is brazed firstly on the radial wall through each opening, and secondly on the radially inner surface of the middle section 1220 of the inner ring.
  • the ring 122 may comprise only a cutout 1223 U, it thus occupies a smaller space. Other types of attachment can nevertheless be integrated in the crown in addition to this single cut.
  • a plurality of U-shaped cutouts 1223 are produced on the circumference of an annular ring 122, in accordance with the cuts described above, the cuts being preferably evenly distributed over said circumference.
  • each cutout 1223 is folded at right angles outwardly of the ring, so that the end 1227 of each tongue is oriented substantially radially with respect to the axis of the crown.
  • the crown 122 is reported on the radial partition 120 of an internal platform with a fixed blade, the blades 11 and the outer platform of the blade may also be already mounted on the internal platform.
  • the crown is attached so that the folded ends of each tongue bear against the radial partition, and the radial annular partition is disposed at the openings 1228 made in the ring.
  • the ends of the tongues 1226 bearing against the radial partition, as well as the zones of the ring between two consecutive openings are brazed to the radial wall.
  • a layer of abradable material 123 on the assembly obtained in the previous step preferably by brazing the layer on the radially inner surface of the median portion 1220 of the ring, and at the openings 1228, brazing the layer 123 to the radial wall (also on its radially inner surface).
  • brazing operations 300 and 400 can be performed simultaneously, which makes the process faster to implement.

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

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

Le domaine de l'invention est celui des aubages fixes de distribution du flux d'air dans une turbomachine.The field of the invention is that of fixed vanes for distribution of the air flow in a turbomachine.

ETAT DE LA TECHNIQUESTATE OF THE ART

Une turbomachine 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 turbomachine generally comprises, from upstream to downstream in the direction of the gas flow, a blower, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.

Ces turbines comprennent un distributeur du flux d'air dans la turbomachine, composé d'une pluralité d'étages d'aubages fixes comprenant chacun une pluralité d'aubes s'étendant généralement radialement par rapport à un axe de la turbomachine, et disposées entre une plate-forme annulaire intérieure et une plate-forme annulaire extérieure par lesquelles lesdites aubes sont fixées à la turbomachine.These turbines comprise a distributor of the air flow in the turbomachine, composed of a plurality of fixed blade stages each comprising a plurality of blades extending generally radially with respect to an axis of the turbomachine, and disposed between an inner annular platform and an outer annular platform by which said vanes are attached to the turbomachine.

Afin notamment de minimiser la masse globale du moteur, tout ou partie de ces aubes sont creuses.In particular to minimize the overall mass of the engine, all or part of these blades are hollow.

Pour réaliser ces différentes cavités, qui ont des formes complexes et dont la géométrie doit être respectée avec une grande précision, les aubes sont classiquement produites par une technique connue sous le nom de fonderie à la cire perdue. Des noyaux sont donc insérés dans le moule avant injection de la cire, ces noyaux étant maintenus en position par des douilles, l'association entre les noyaux et les douilles étant réalisée manuellement.To achieve these different cavities, which have complex shapes and whose geometry must be respected with great precision, the blades are conventionally produced by a technique known as the foundry lost wax. Nuclei are inserted in the mold before injection of the wax, these cores being held in position by sockets, the association between the cores and the sockets being carried out manually.

Cependant, la géométrie actuelle des aubages ne présente pas un espace suffisant pour permettre le positionnement des douilles, et par conséquent de réaliser des aubages creux avec un tolérancement et des dimensions donnés.However, the current geometry of the blades does not have sufficient space to allow the positioning of the bushings, and therefore to achieve hollow vanes with tolerancing and given dimensions.

Il a été proposé à cet égard un aubage fixe dont la plate-forme annulaire interne comprend une platine annulaire de support formant la base des aubes et une cloison radiale s'étendant de ladite platine vers l'axe de la turbomachine, ladite cloison radiale étant associée à une couronne interne présentant une surface externe au niveau de laquelle ladite couronne est fixée à la cloison radiale, la couronne et la cloison radiale étant en outre solidarisées entre elles par des éléments de renforts.It has been proposed in this respect a fixed blade whose inner annular platform comprises an annular support plate forming the base of the blades and a radial partition extending from said plate towards the axis of the turbomachine, said radial partition being associated with an inner ring having an external surface at which said ring is fixed to the radial wall, the ring and the radial wall being further secured to each other by reinforcing elements.

Or pour diminuer la masse de la turbomachine il est nécessaire de minimiser le nombre de pièces. Le document FR 2 930 592 A1 divulgue l'art antérieur.But to reduce the mass of the turbomachine it is necessary to minimize the number of parts. The document FR 2 930 592 A1 discloses the prior art.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

L'invention vise à remédier à cette problématique, en proposant un aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme annulaire interne et une pluralité d'aubes fixes montées sur celle-ci, la plate-forme interne comprenant une platine de support formant base desdites aubes, une cloison annulaire radiale s'étendant depuis la platine de support vers un axe de l'aubage, et une couronne interne rapportée sur la cloison annulaire radiale, et présentant une surface interne sur laquelle est disposé un matériau abradable, l'aubage étant caractérisé en ce que la couronne interne comporte au moins une découpe délimitant une languette, la languette étant repliée pour venir en appui sur la cloison annulaire radiale.The invention aims to remedy this problem by proposing a fixed blade of flow distribution in a turbomachine, comprising an inner annular platform and a plurality of fixed vanes mounted on it, the inner platform comprising a support plate forming the base of said blades, a radial annular partition extending from the support plate towards an axis of the blade, and an inner ring attached to the radial annular partition, and having an inner surface on which is disposed a material abradable, the blade being characterized in that the inner ring comprises at least one cutout defining a tongue, the tongue being folded to bear against the radial annular partition.

Avantageusement, mais facultativement, l'aubage selon l'invention peut en outre comprendre au moins l'une des caractéristiques suivantes :

  • la ou chaque languette vient en appui par au moins une portion d'extrémité sur la cloison radiale, ce qui permet de ne réaliser qu'un seul pliage de languette et ainsi de simplifier la fabrication de l'aubage.
  • Si l'aubage présente plusieurs languettes, celles-ci peuvent être disposées selon une répartition angulaire régulière sur la circonférence de la couronne, de façon répartir de façon équilibrée les contacts en butée et ainsi à conférer une meilleure stabilité à l'aubage.
  • la portion d'extrémité de chaque languette est brasée sur la cloison radiale.
  • la couronne interne est rapportée sur la cloison annulaire radiale au niveau des ouvertures traversantes résultant chacune du pliage d'une languette correspondante.
  • le matériau abradable est rapporté sur la cloison radiale au travers de chaque ouverture.
  • le matériau abradable est brasé sur la surface interne de la couronne, et sur la cloison radiale au travers de chaque ouverture de la couronne.
  • la couronne interne comprend en outre une patte annulaire s'étendant vers l'amont et une patte annulaire s'étendant vers l'aval par rapport à un flux d'air dans l'aubage.
Advantageously, but optionally, the blading according to the invention may further comprise at least one of the following characteristics:
  • the or each tab is supported by at least one end portion on the radial wall, which allows to achieve only one tab fold and thus simplify the manufacture of the blade.
  • If the blade has several tabs, they can be arranged in a regular angular distribution on the circumference of the ring, so as to distribute equitably the abutting contacts and thus to confer a better stability to the blading.
  • the end portion of each tongue is brazed to the radial wall.
  • the inner ring is attached to the radial annular partition at the through openings resulting each folding a corresponding tab.
  • the abradable material is attached to the radial septum through each opening.
  • the abradable material is brazed to the inner surface of the crown, and to the radial septum through each opening of the crown.
  • the inner ring further comprises an annular tab extending upstream and an annular tab extending downstream relative to a stream of air in the vane.

L'invention propose également une turbomachine comportant au moins un tel aubage.The invention also proposes a turbomachine comprising at least one such blade.

L'invention propose enfin un procédé de fabrication d'un aubage fixe de distribution de flux selon l'invention, comprenant les étapes consistant à :

  • former au moins une découpe en U dans une couronne pour délimiter une pluralité de languettes,
  • replier une portion de la languette à angle droit par rapport à la couronne, et
  • fixer la couronne sur la cloison radiale d'une plate-forme annulaire interne d'aubage, de sorte que la cloison radiale soit en contact avec une surface annulaire externe de la couronne, et que la portion de la languette à angle droit par rapport à la couronne soit en appui sur ladite cloison.
The invention finally proposes a method of manufacturing a fixed blade of flow distribution according to the invention, comprising the steps of:
  • forming at least one U-shaped cutout in a crown to delimit a plurality of tongues,
  • fold a portion of the tongue at right angles to the crown, and
  • fixing the crown on the radial wall of an inner annular platform of vane, so that the radial wall is in contact with an outer annular surface of the crown, and the portion of the tongue at right angles to the crown is supported on said partition.

Avantageusement, mais facultativement, le procédé selon l'invention peut en outre comprendre au moins l'une des caractéristiques suivantes :

  • l'étape de fixation de la couronne sur la cloison radiale comporte le brasage de la portion de chaque languette à angle droit par rapport à la couronne sur la cloison.
  • Le procédé comprend en outre une étape consistant à braser une couche de matériau abradable sur une surface interne de la couronne, et sur la cloison radiale au travers d'une pluralité d'ouvertures de la couronne résultant du pliage de chaque languette.
Advantageously, but optionally, the method according to the invention may further comprise at least one of the following characteristics:
  • the step of fixing the crown on the radial wall comprises brazing the portion of each tongue at right angles to the crown on the wall.
  • The method further comprises a step of brazing a layer of abradable material on an inner surface of the ring, and on the radial wall through a plurality of openings of the ring resulting from the folding of each tab.

Ainsi, l'aubage de distribution selon l'invention est plus léger mais aussi robuste qu'auparavant puisque la fonction de renfort en appui contre la cloison radiale est réalisée par la couronne interne de l'aubage elle-même, sans ajout de matériel.Thus, the distribution vane according to the invention is lighter but as robust as before since the reinforcement function in support against the partition radial is made by the inner crown of the vane itself, without adding material.

DESCRIPTION DES FIGURESDESCRIPTION OF THE FIGURES

D'autres caractéristiques, buts et avantages de l'invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard des dessins annexés, sur lesquels :

  • La figure 1 représente une vue en coupe partielle d'un aubage de distribution de flux selon un mode de réalisation de l'invention.
  • Les figures 2a et 2b représentent respectivement une vue en coupe partielle et une vue de dessus d'une couronne interne de plate-forme annulaire interne d'un aubage de distribution de flux de la figure 1.
  • La figure 3 représente schématiquement les principales étapes du procédé de fabrication d'un aubage de distribution de flux selon un mode de réalisation de l'invention.
Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings, in which:
  • The figure 1 represents a partial sectional view of a flow distribution vane according to one embodiment of the invention.
  • The Figures 2a and 2b respectively represent a partial sectional view and a top view of an internal annular platform inner ring of a flow distribution vane of the figure 1 .
  • The figure 3 schematically represents the main steps of the method of manufacturing a flux distribution vane according to one embodiment of the invention.

DESCRIPTION DETAILLEE D'AU MOINS UN MODE DE REALISATIONDETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT

En référence à la figure 1, on a représenté une vue partielle d'un aubage 10 fixe de distribution du flux d'air s'écoulant dans une turbomachine, le sens de l'écoulement du flux d'air étant représenté par une flèche F, l'aubage formant un étage d'un distributeur d'une turbine de turbomachine, par exemple de turbine basse-pression.With reference to the figure 1 , there is shown a partial view of a fixed blade 10 distribution of the flow of air flowing in a turbomachine, the direction of flow of the air flow being represented by an arrow F, the blade forming a stage of a distributor of a turbomachine turbine, for example a low-pressure turbine.

L'aubage 10 comporte une pluralité d'aubes 11 fixes disposées radialement par rapport à un axe de la turbomachine (non représenté), qui est également l'axe de l'aubage, lesdites aubes étant montées sur une plate-forme annulaire interne 12.Blading 10 comprises a plurality of fixed blades 11 arranged radially with respect to an axis of the turbomachine (not shown), which is also the axis of the blade, said blades being mounted on an inner annular platform 12 .

La plate-forme 12 comporte une cloison annulaire 120 s'étendant radialement par rapport à l'axe de la turbomachine, ainsi qu'une platine 121 annulaire de support des aubes 11, s'étendant de part et d'autre de la cloison annulaire au niveau d'une extrémité radialement externe de celle-ci.The platform 12 comprises an annular partition 120 extending radially with respect to the axis of the turbomachine, as well as an annular plate 121 for supporting the blades 11, extending on either side of the annular partition. at a radially outer end thereof.

La plate-forme 12 comporte également une couronne interne 122 s'étendant de part et d'autre de la cloison annulaire radiale 120, au niveau de son extrémité radialement interne, et sur laquelle est rapportée une couche de matériau abradable 123.The platform 12 also comprises an inner ring 122 extending on either side of the radial annular partition 120, at its radially inner end, and on which a layer of abradable material 123 is attached.

En référence aux figures 2a et 2b, la couronne interne 122 présente une section annulaire 1220 médiane s'étendant sensiblement axialement par rapport à l'axe de l'aubage, et deux pattes annulaires d'extrémité 1221,1222 s'étendant respectivement vers l'amont et vers l'aval de l'aubage par rapport au flux d'air, en étant décalée radialement par rapport à la section médiane 1220, lesdites sections pouvant être inclinées par rapport à l'axe de l'aubage.With reference to Figures 2a and 2b , the inner ring 122 has a median annular section 1220 extending substantially axially with respect to the axis of the blading, and two end annular tabs 1221, 1222 extending respectively upstream and downstream. the blading relative to the airflow, being radially offset from the center section 1220, said sections being inclined relative to the axis of the blading.

Ces sections sont conformées pour coopérer avec des becquets d'aubage de rotor placés en amont et en aval par rapport à l'aubage 10, afin de former des joints d'étanchéité de type labyrinthe, pour éviter une recirculation d'air dans une direction radiale entre la veine de l'aubage 10 (c'est-à-dire entre les pales 11) et l'interstice entre la plate-forme de l'aubage fixe et du rotor adjacent.These sections are shaped to cooperate with rotor blade spoilers placed upstream and downstream with respect to the blade 10, in order to form labyrinth type seals, to avoid recirculation of air in one direction. radial between the vein of the blade 10 (that is to say between the blades 11) and the gap between the platform of the fixed blade and the adjacent rotor.

En outre, la couronne interne 122 comprend, sur sa section médiane 1220, au moins une, et de préférence une pluralité de découpes 1223 en U, chaque découpe comprenant donc deux portions de préférence mais non limitativement parallèles 1224 (formant les branches du « U ») réunies en une extrémité par une portion transversale 1225 (formant la base du « U »). Avantageusement, comme sur la figure 2a, les portions 1224 sont orientées sensiblement parallèlement à l'axe de l'aubage et la portion transversale 1225 et disposée du coté aval de la découpe par rapport au flux d'air.In addition, the inner ring 122 comprises, on its median section 1220, at least one, and preferably a plurality of U-shaped cutouts 1223, each cutout thus comprising two preferably but non-limitatively parallel portions 1224 (forming the branches of the "U"") Joined at one end by a transverse portion 1225 (forming the base of the" U "). Advantageously, as on the figure 2a , the portions 1224 are oriented substantially parallel to the axis of the blade and the transverse portion 1225 and disposed on the downstream side of the blank with respect to the air flow.

Chaque découpe 1223 délimite ainsi une languette 1226 détachée du reste de la section médiane par les trois portions de la découpe. Du fait de la forme des découpes, chaque languette s'étend sur un secteur d'anneau.Each cutout 1223 thus delimits a tongue 1226 detached from the rest of the median section by the three portions of the cutout. Because of the shape of the cutouts, each tab extends over a ring sector.

Au moins une partie d'extrémité 1227 de chaque découpe est repliée à angle droit par rapport à la section médiane de la couronne 122 de manière à s'étendre sensiblement radialement.At least one end portion 1227 of each cutout is bent at right angles to the middle section of the ring 122 so as to extend substantially radially.

La totalité de chaque languette peut également être repliée à angle droit par rapport à la couronne.The whole of each tongue can also be bent at right angles to the crown.

Chaque languette ainsi repliée libère une ouverture 1228 en secteur d'anneau dans la couronne 122.Each tongue thus folded releases an opening 1228 in ring sector in the ring 122.

De préférence, les découpes 1123, et donc les languettes 1226 et les ouvertures 1228 sont réparties régulièrement, c'est-à-dire à intervalle angulaire constant par rapport à l'axe de l'aubage, le long de la circonférence de la couronne. Ainsi, la couronne 122 présente, sur une zone annulaire de sa section médiane de la largeur des ouvertures, une alternance de zones pleines et d'ouvertures 1228.Preferably, the cuts 1123, and therefore the tabs 1226 and the openings 1228 are distributed regularly, that is to say at constant angular interval relative to the axis of the blade, along the circumference of the crown. . Thus, the ring 122 has, on an annular zone of its median section of the width of the openings, an alternation of solid areas and openings 1228.

Enfin, la couronne 122 est rapportée sur la cloison radiale 120 au niveau de la zone annulaire comprenant l'alternance d'ouvertures et de zones pleines, l'extrémité 1227 des languettes à angle droit par rapport à la couronne venant en appui contre la cloison radiale.Finally, the ring 122 is attached to the radial partition 120 at the annular zone comprising the alternation of openings and solid areas, the end 1227 of the tabs at right angles to the ring bearing against the wall radial.

De cette manière, les languettes découpées dans la couronne constituent la surface à braser sur la cloison radiale, permettant ainsi d'assurer l'assemblage de la couronne à la cloison radiale sans ajout d'éléments supplémentaires (par exemple tôles, pattes sur cloison radiale...). L'aubage est donc allégé.In this way, the tongues cut in the crown constitute the surface to be soldered on the radial partition, thus making it possible to assemble the crown to the radial partition without adding additional elements (for example sheets, tabs on a radial partition ...). The blading is thus lightened.

D'autre part, la couche de matériau abradable 123 rapportée sur la couronne peut donc être également rapportée sur la cloison radiale au travers de chaque ouverture 1228 de ladite couronne. De préférence, la couche de matériau abradable 123 est brasée d'une part sur la cloison radiale au travers de chaque ouverture, et d'autre part sur la surface radialement interne de la section médiane 1220 de la couronne interne.On the other hand, the layer of abradable material 123 attached to the ring can also be reported on the radial wall through each opening 1228 of said ring. Preferably, the layer of abradable material 123 is brazed firstly on the radial wall through each opening, and secondly on the radially inner surface of the middle section 1220 of the inner ring.

La couronne 122 peut ne comprendre qu'une découpe 1223 en U, elle occupe ainsi un espace plus réduit. D'autres types de fixation peuvent néanmoins être intégrés à la couronne en complément de cette découpe unique.The ring 122 may comprise only a cutout 1223 U, it thus occupies a smaller space. Other types of attachment can nevertheless be integrated in the crown in addition to this single cut.

On va maintenant décrire, en référence à la figure 3, un procédé de fabrication de l'aubage présenté ci-avant.We will now describe, with reference to the figure 3 , a method of manufacturing the blading presented above.

Au cours d'une étape 100, on réalise une pluralité de découpes 1223 en U sur la circonférence d'une couronne annulaire 122, conformes aux découpes décrites ci-avant, les découpes étant de préférence réparties régulièrement sur ladite circonférence.During a step 100, a plurality of U-shaped cutouts 1223 are produced on the circumference of an annular ring 122, in accordance with the cuts described above, the cuts being preferably evenly distributed over said circumference.

Au cours d'une étape 200, on replie la languette 1226 délimitée par chaque découpe 1223 à angle droit vers l'extérieur de la couronne, de sorte que l'extrémité 1227 de chaque languette soit orientée sensiblement radialement par rapport à l'axe de la couronne.During a step 200, the tongue 1226 delimited by each cutout 1223 is folded at right angles outwardly of the ring, so that the end 1227 of each tongue is oriented substantially radially with respect to the axis of the crown.

Au cours d'une étape 300, on rapporte la couronne 122 sur la cloison radiale 120 d'une plate-forme interne d'un aubage fixe, les pales 11 et la plate-forme externe de l'aubage pouvant également être déjà montées sur la plate-forme interne. La couronne est rapportée de sorte que les extrémités repliées de chaque languette viennent en appui contre la cloison radiale, et que la cloison annulaire radiale soit disposée au niveau des ouvertures 1228 réalisées dans la couronne.During a step 300, the crown 122 is reported on the radial partition 120 of an internal platform with a fixed blade, the blades 11 and the outer platform of the blade may also be already mounted on the internal platform. The crown is attached so that the folded ends of each tongue bear against the radial partition, and the radial annular partition is disposed at the openings 1228 made in the ring.

De préférence, les extrémités des languettes 1226 en appui contre la cloison radiale, ainsi que les zones de la couronne entre deux ouvertures consécutives sont brasées à la cloison radiale.Preferably, the ends of the tongues 1226 bearing against the radial partition, as well as the zones of the ring between two consecutive openings are brazed to the radial wall.

Enfin, au cours d'une étape 400, on rapporte une couche de matériau abradable 123 sur l'ensemble obtenu à la précédente étape, de préférence en brasant la couche à la surface radialement interne de la portion médiane 1220 de la couronne, et, au niveau des ouvertures 1228, en brasant la couche 123 à la cloison radiale (également sur sa surface radialement interne).Finally, during a step 400, there is reported a layer of abradable material 123 on the assembly obtained in the previous step, preferably by brazing the layer on the radially inner surface of the median portion 1220 of the ring, and at the openings 1228, brazing the layer 123 to the radial wall (also on its radially inner surface).

Avantageusement, mais facultativement, les opérations de brasage 300 et 400 peuvent être réalisées simultanément, ce qui rend le procédé plus rapide à mettre en oeuvre.Advantageously, but optionally, brazing operations 300 and 400 can be performed simultaneously, which makes the process faster to implement.

Claims (11)

  1. A fixed vane assembly (10) for distributing flow within a turbomachine, comprising an inner annular platform (12) and a plurality of fixed vanes (11) mounted thereon, the inner platform including a support plate (121) forming the base of said vanes, an annular radial partition (120) extending from the support plate toward an axis of the vane assembly, and an inner ring (122) applied to the radial annular partition (120) and having an inner surface on which is positioned an abradable material (123),
    the vane assembly being characterized in that the inner ring includes at least one U-shape cut (1223) delimiting a tongue (1226), the tongue being folded to bear against the radial annular partition (120).
  2. The vane assembly (10) according to claim 1, wherein the tongue (1226) bears, with at least one end portion (1227), on the radial partition (120).
  3. The vane assembly (10) according to claim 2, wherein the end portion (1227) of each tongue is brazed onto the radial partition (120).
  4. The vane assembly (10) according to one of claims 1 to 3, wherein the inner ring (122) is applied to the radial annular partition (120) at through openings (1228) each resulting from folding the corresponding tongue (1226).
  5. The vane assembly (10) according to claim 4, wherein the abradable material (123) is applied to the radial partition (120) through each opening (1228).
  6. The vane assembly (10) according to one of claims 4 or 5, wherein the abradable material (123) is brazed to the inner surface of the ring (122) and to the radial partition (120) through each opening (1228) of the ring (122).
  7. The vane assembly (10) according to one of the preceding claims, wherein the inner ring (122) further includes an annular tab (1221) extending upstream and an annular tab (1222) extending downstream with respect to an air flow in the vane assembly.
  8. A turbomachine including at least one fixed vane assembly (10) for distributing flow according to one of the preceding claims.
  9. A method for manufacturing a fixed vane assembly (10) for distributing flow according to one of claims 1 to 8, including the steps consisting of:
    - forming at least one U-shape cut (1223) in a ring (122) to delimit at least one tongue (1226),
    - folding one portion (1227) of the right-angled tongue (1226) with respect to the ring, and
    - attaching the ring (122) to the radial partition (120) of an inner annular platform (12) of vane assembly (10), so that the radial partition is in contact with an outer annular surface of the ring, and the portion (1227) of the right-angled tongue with respect to the ring bears on said partition.
  10. The method for manufacturing a vane assembly (10) according to the preceding claim, wherein step (300) of attaching the ring (122) to the radial partition (120) includes brazing the portion (1227) of each right-angled tongue with respect to the ring (122) onto the partition (120).
  11. The method for manufacturing a vane assembly (10) according to one of claims 9 or 10, further comprising a step consisting of brazing a layer of abradable material (123) onto an inner surface of the ring (122), and onto the radial partition through a plurality of openings (1228) of the ring resulting from the folding of each tongue (1226).
EP14704842.5A 2013-01-23 2014-01-22 Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method Active EP2948640B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1350582A FR3001252B1 (en) 2013-01-23 2013-01-23 FIXED FLOW DISTRIBUTION AUBING COMPRISING AN INTEGRATED REINFORCED INTERNAL PLATFORM
PCT/FR2014/050113 WO2014114873A1 (en) 2013-01-23 2014-01-22 Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method

Publications (2)

Publication Number Publication Date
EP2948640A1 EP2948640A1 (en) 2015-12-02
EP2948640B1 true EP2948640B1 (en) 2017-04-19

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EP14704842.5A Active EP2948640B1 (en) 2013-01-23 2014-01-22 Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method

Country Status (8)

Country Link
US (1) US10024179B2 (en)
EP (1) EP2948640B1 (en)
CN (1) CN104937216B (en)
BR (1) BR112015017351B1 (en)
CA (1) CA2898864C (en)
FR (1) FR3001252B1 (en)
RU (1) RU2651919C2 (en)
WO (1) WO2014114873A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3082233B1 (en) * 2018-06-12 2020-07-17 Safran Aircraft Engines TURBINE SET
FR3100838B1 (en) * 2019-09-13 2021-10-01 Safran Aircraft Engines TURBOMACHINE SEALING RING
FR3103012B1 (en) * 2019-11-12 2021-11-19 Safran Aircraft Engines Sectoral annular row of fixed vanes
DE102020200073A1 (en) * 2020-01-07 2021-07-08 Siemens Aktiengesellschaft Guide vane ring
FR3113298B1 (en) * 2020-08-10 2023-09-01 Safran Aircraft Engines Abradable holder for a low pressure distributor comprising a single sheet
FR3146931A1 (en) * 2023-03-23 2024-09-27 Safran Aircraft Engines Stator assembly for an aircraft turbomachine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB807231A (en) * 1955-05-20 1959-01-14 Gen Electric Securing means for blading of compressors or turbines
US3018085A (en) * 1957-03-25 1962-01-23 Gen Motors Corp Floating labyrinth seal
DE3003469C2 (en) * 1980-01-31 1987-03-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for connecting rotationally symmetrically arranged components for turbomachines, in particular gas turbine engines, which are exposed to different thermal influences
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
RU2171380C2 (en) * 1999-04-27 2001-07-27 Открытое акционерное общество "Авиадвигатель" Nozzle block of turbine
FR2928961B1 (en) * 2008-03-19 2015-11-13 Snecma SECTORIZED DISPENSER FOR A TURBOMACHINE.
FR2930592B1 (en) * 2008-04-24 2010-04-30 Snecma TURBINE DISPENSER FOR A TURBOMACHINE

Non-Patent Citations (1)

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

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US20150377044A1 (en) 2015-12-31
RU2015135580A (en) 2017-03-02
EP2948640A1 (en) 2015-12-02
BR112015017351B1 (en) 2021-12-14
CN104937216B (en) 2016-08-10
US10024179B2 (en) 2018-07-17
CA2898864C (en) 2020-08-25
FR3001252B1 (en) 2015-02-13
CN104937216A (en) 2015-09-23
BR112015017351A2 (en) 2017-07-11
WO2014114873A1 (en) 2014-07-31
CA2898864A1 (en) 2014-07-31
RU2651919C2 (en) 2018-04-24
FR3001252A1 (en) 2014-07-25

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