EP2264284A1 - Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method - Google Patents

Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method Download PDF

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Publication number
EP2264284A1
EP2264284A1 EP09163148A EP09163148A EP2264284A1 EP 2264284 A1 EP2264284 A1 EP 2264284A1 EP 09163148 A EP09163148 A EP 09163148A EP 09163148 A EP09163148 A EP 09163148A EP 2264284 A1 EP2264284 A1 EP 2264284A1
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EP
European Patent Office
Prior art keywords
blades
folds
preform
rectifier
resin
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP09163148A
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German (de)
French (fr)
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EP2264284B1 (en
Inventor
Benoit Baldewijns
Enrique Penalver Castro
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP09163148.1A priority Critical patent/EP2264284B1/en
Priority to CA2705631A priority patent/CA2705631C/en
Priority to US12/791,270 priority patent/US8414259B2/en
Publication of EP2264284A1 publication Critical patent/EP2264284A1/en
Application granted granted Critical
Publication of EP2264284B1 publication Critical patent/EP2264284B1/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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to a method of manufacturing a rectifier in a turbomachine.
  • It relates more particularly to a method of manufacturing composite outer rings with integrated vanes.
  • Axial compressors are well known per se and are used inter alia in turbomachines.
  • These low or high pressure compressors comprise several stages of rotating blades which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next stage.
  • rectifier stages consist essentially of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
  • stator vanes also called stator vanes
  • the stator vanes generally include a platform which is attached to the outer shell by riveting, welding, bolting, gluing, etc.
  • Examples of rivet assembly ( US 6,543,995 A ) and bolts ( EP 1 936 121 A ) are respectively illustrated Figures 2a and 2b .
  • Assembly by rivets, bolts, etc. has the disadvantage of requiring the drilling of openings in the ferrule for the passage of the fasteners, which causes a reduction in the structural strength of the ferrule.
  • Welding assembly (eg by electron beam or laser beam) also has drawbacks. It is known that welding generates, in the thermally affected zone (ZAT), a degradation of the mechanical properties. It is therefore necessary to avoid placing in these weakened zones any element generating stress concentrations. In the particular case of a low-pressure compressor (or booster), it is necessary to avoid placing in these zones the assembly flanges of the outer rings (cf. fig.1 and fig.2b ). Practically, it is therefore necessary to move the flanges away from these zones, resulting in an extension of the length of the low pressure compressor.
  • ZAT thermally affected zone
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the present invention aims in particular to achieve an assembly between blades and ferrules not weakening the mechanical strength of the ferrule.
  • the present invention also relates to a turbomachine rectifier obtained by means of the method as described above.
  • the figure 1 represents a sectional view of a portion of a turbomachine compressor.
  • FIGS. 2a and 2b respectively represent a three-dimensional view and a sectional view of examples of assembly between stator blades and outer ring according to the state of the art.
  • the figure 3 represents a three-dimensional view of the insertion of the stator vanes during the draping of the outer ferrule according to the invention.
  • the figure 4 represents a sectional view corresponding to the assembly of the figure 3 .
  • the present invention relates to a method of manufacturing a turbomachine rectifier and, more particularly, to a method of manufacturing a composite outer shell with integrated vanes.
  • the outer shell is obtained by the draping method and the blades or blade preforms are inserted during the layup between the folds.
  • the method according to the invention comprises at least six steps (see fig.3 and fig.4 ).
  • a first step a) consists of draping the first folds 7 on a core having openings and having the shape of the aerodynamic vein (not shown).
  • the first folds are incised according to an incision 8 placed opposite the opening of the core.
  • the first folds 7 may also be pre-incised, in which case step b) is absent.
  • the plies may consist of carbon fiber fabric.
  • the blades and, more particularly, the blades 12 of blades are inserted through the incisions 8 of the first plies 7 and openings of the core in the direction of the arrow represented in FIG. figure 4 .
  • the incisions and openings are spaced so as to arrange side by side, that is to say in a contiguous manner, the platforms as illustrated by the dotted lines in the figure 3 .
  • the blades may be dry preforms intended later to be injected by a resin, or composite blades or metal blades.
  • the last plies 10 are draped over the blade platforms 9 for complete the preform of the rectifier.
  • a resin is injected into a closed mold containing the preform and the impregnated preform is polymerized.
  • the inserted blade is a dry preform, the latter is also injected by the resin.
  • a final step f) then consists in opening the mold and demolding the rectifier thus produced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The method involves draping a set of folds (7) over a core comprising perforations, and optionally cutting the folds along incisions (8) formed opposite to the perforations. Blades (12) of vanes or vane preforms are inserted via the incisions and perforations, where the vanes are made of composite or metal material. Another set of folds (10) is draped over vane platforms (9) forming a rectifier preform. Resin is injected into a closed mold with the preform, and the resin-impregnated preform is polymerized. Molded piece having shape and dimensions of a rectifier is retrieved from the mold.

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte à un procédé de fabrication d'un redresseur dans une turbomachine.The present invention relates to a method of manufacturing a rectifier in a turbomachine.

Elle se rapporte plus particulièrement à un procédé de fabrication de viroles extérieures composites avec aubes intégrées.It relates more particularly to a method of manufacturing composite outer rings with integrated vanes.

Elle se rapporte également au redresseur obtenu selon le procédé.It also relates to the rectifier obtained according to the method.

Etat de la techniqueState of the art

Les compresseurs axiaux sont bien connus en soi et sont utilisés entre autres dans les turbomachines.Axial compressors are well known per se and are used inter alia in turbomachines.

Ces compresseurs basse ou haute pression comportent plusieurs étages d'aubes tournantes qui sont séparés par des étages redresseurs qui ont pour but de repositionner le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers l'étage suivant.These low or high pressure compressors comprise several stages of rotating blades which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next stage.

Ces étages redresseurs sont constitués essentiellement d'aubes fixes, encore appelées aubes statoriques, reliant une virole extérieure à une virole intérieure, toutes deux concentriques et délimitant la zone d'écoulement d'air ou veine aérodynamique. A titre explicatif, la figure 1 montre une coupe d'une partie d'un compresseur de turbomachine où l'on peut voir les aubes statoriques fixées aux viroles intérieures et extérieures (cf. légende).These rectifier stages consist essentially of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein. As an explanation, the figure 1 shows a section of a part of a turbomachine compressor where we can see the blades stator fixed to the inner and outer rings (see legend).

Les aubes statoriques comportent généralement une plate-forme qui est fixée à la virole extérieure par rivetage, soudage, boulonnage, collage, etc. Des exemples d'assemblage par rivets ( US 6,543,995 A ) et boulons ( EP 1 936 121 A ) sont respectivement illustrés aux figures 2a et 2b.The stator vanes generally include a platform which is attached to the outer shell by riveting, welding, bolting, gluing, etc. Examples of rivet assembly ( US 6,543,995 A ) and bolts ( EP 1 936 121 A ) are respectively illustrated Figures 2a and 2b .

L'assemblage par rivets, boulons, etc. a pour inconvénient de nécessiter le perçage d'ouvertures dans la virole pour le passage des éléments de fixation, ce qui entraine une diminution de la résistance structurelle de la virole.Assembly by rivets, bolts, etc. has the disadvantage of requiring the drilling of openings in the ferrule for the passage of the fasteners, which causes a reduction in the structural strength of the ferrule.

L'assemblage par soudage (par ex. par faisceau d'électrons ou par faisceau laser) présente également des inconvénients. Il est connu que le soudage engendre, dans la zone affectée thermiquement (ZAT), une dégradation des propriétés mécaniques. Il faut en conséquence éviter de placer dans ces zones fragilisées tout élément engendrant des concentrations de contraintes. Dans le cas particulier d'un compresseur basse pression (ou booster), il faut éviter de placer dans ces zones les brides d'assemblage des viroles extérieures (cf.1 dans fig.1 et fig.2b). Pratiquement, il est donc nécessaire d'éloigner les brides de ces zones, il en résulte un allongement de la longueur du compresseur basse pression.Welding assembly (eg by electron beam or laser beam) also has drawbacks. It is known that welding generates, in the thermally affected zone (ZAT), a degradation of the mechanical properties. It is therefore necessary to avoid placing in these weakened zones any element generating stress concentrations. In the particular case of a low-pressure compressor (or booster), it is necessary to avoid placing in these zones the assembly flanges of the outer rings (cf. fig.1 and fig.2b ). Practically, it is therefore necessary to move the flanges away from these zones, resulting in an extension of the length of the low pressure compressor.

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une solution qui permette de s'affranchir des inconvénients de l'état de la technique.The present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.

La présente invention vise en particulier à réaliser un assemblage entre aubes et viroles n'affaiblissant pas la résistance mécanique de la virole.The present invention aims in particular to achieve an assembly between blades and ferrules not weakening the mechanical strength of the ferrule.

Principaux éléments caractéristiques de l'inventionMain characteristic elements of the invention

La présente invention se rapporte à un procédé de fabrication d'un redresseur de turbomachine comportant une virole extérieure et une pluralité d'aubes statoriques, lesdites aubes comportant une plate-forme et une pale, caractérisé en ce que ledit procédé comporte au moins les étapes suivantes :

  1. a) on drape des premiers plis sur un noyau comportant des ajours et ayant la forme de la veine aérodynamique ;
  2. b) optionnellement, on incise les premiers plis selon des incisions placées en regard des ajours du noyau ;
  3. c) on insère les pales des aubes ou, alternativement, les pales des préformes d'aubes, à travers les incisions des premiers plis et les ajours du noyau ;
  4. d) on drape des derniers plis au-dessus des plate-formes formant ainsi une préforme de redresseur ;
  5. e) on injecte une résine dans un moule fermé contenant la préforme et on polymérise la préforme imprégnée de résine ;
  6. f) on sort du moule une pièce moulée présentant sensiblement la forme et les dimensions dudit redresseur.
The present invention relates to a method for manufacturing a turbomachine rectifier comprising an outer shell and a plurality of stator blades, said blades comprising a platform and a blade, characterized in that said method comprises at least the steps following:
  1. a) drapes first folds on a core having openings and having the shape of the aerodynamic vein;
  2. b) optionally, the first folds are incised according to incisions placed opposite the openings of the core;
  3. c) the blades of the blades or, alternatively, the blades of the blade preforms, are inserted through the incisions of the first folds and the openings of the core;
  4. d) drapes last folds above the platforms thus forming a preform of rectifier;
  5. e) injecting a resin into a closed mold containing the preform and polymerizing the preform impregnated with resin;
  6. f) a molding is produced from the mold having substantially the shape and dimensions of said rectifier.

Selon des modes particuliers de l'invention, le procédé comporte au moins une ou une combinaison appropriée des caractéristiques suivantes :

  • les premiers plis sont pré-incisés, auquel cas, l'étape b) est absente ;
  • l'aube est en matériau composite ou métallique ;
  • la préforme d'aube est également injectée par la résine dans l'étape e) ;
  • on dispose côte à côte les plate-formes des aubes dans l'étape c) ;
  • les premiers et derniers plis comprennent du tissu en fibres de carbone.
According to particular embodiments of the invention, the method comprises at least one or a suitable combination of the following characteristics:
  • the first folds are pre-incised, in which case step b) is absent;
  • the dawn is made of composite or metallic material;
  • the blade preform is also injected by the resin in step e);
  • the platforms of the blades are arranged side by side in step c);
  • the first and last folds comprise carbon fiber fabric.

La présente invention se rapporte également à un redresseur de turbomachine obtenu au moyen du procédé tel que décrit ci-dessus.The present invention also relates to a turbomachine rectifier obtained by means of the method as described above.

Brève description des figuresBrief description of the figures

La figure 1, déjà mentionnée, représente une vue en coupe d'une partie d'un compresseur de turbomachine.The figure 1 , already mentioned, represents a sectional view of a portion of a turbomachine compressor.

Les figures 2a et 2b, déjà mentionnées, représentent respectivement une vue tridimensionnelle et une vue en coupe d'exemples d'assemblage entre aubes statoriques et virole extérieure selon l'état de l'art.The Figures 2a and 2b , already mentioned, respectively represent a three-dimensional view and a sectional view of examples of assembly between stator blades and outer ring according to the state of the art.

La figure 3 représente une vue tridimensionnelle de l'insertion des aubes statoriques lors du drapage de la virole extérieure selon l'invention.The figure 3 represents a three-dimensional view of the insertion of the stator vanes during the draping of the outer ferrule according to the invention.

La figure 4 représente une vue en coupe correspondant à l'assemblage de la figure 3.The figure 4 represents a sectional view corresponding to the assembly of the figure 3 .

Légende :Legend:

  1. (1) Bride d'assemblage entre viroles extérieures(1) Mounting flange between outer ferrules
  2. (2) Aubes fixes ou statoriques(2) Fixed or statoric blades
  3. (3) Aubes rotoriques(3) Rotor blades
  4. (4) Virole intérieure(4) Inner ferrule
  5. (5) Virole extérieure(5) outer shell
  6. (6) Abradable(6) Abradable
  7. (7) Premiers plis drapés(7) First draping folds
  8. (8) Incision dans les premiers plis(8) Incision in the first folds
  9. (9) Plate-forme de l'aube statorique(9) Platform of the statoric dawn
  10. (10) Derniers plis drapés(10) Last draped folds
  11. (11) Rayon de raccordement entre la pale et la plate-forme de l'aube statorique(11) Connection radius between the blade and the platform of the stator blade
  12. (12) Pale de l'aube statorique(12) Pale of stator dawn
Description détaillée de l'inventionDetailed description of the invention

La présente invention concerne un procédé de fabrication d'un redresseur de turbomachine et, plus particulièrement, un procédé de fabrication d'une virole extérieure composite avec aubes intégrées. Dans la présente invention, la virole extérieure est obtenue par la méthode de drapage et les aubes ou préformes d'aubes sont insérées lors du drapage entre les plis.The present invention relates to a method of manufacturing a turbomachine rectifier and, more particularly, to a method of manufacturing a composite outer shell with integrated vanes. In the present invention, the outer shell is obtained by the draping method and the blades or blade preforms are inserted during the layup between the folds.

Le procédé selon l'invention comporte au moins six étapes (voir fig.3 et fig.4). Une première étape a) consiste à draper les premiers plis 7 sur un noyau comportant des ajours et ayant la forme de la veine aérodynamique (non représenté). Dans une seconde étape b), les premiers plis sont incisés selon une incision 8 placée en regard de l'ajour du noyau. Les premiers plis 7 peuvent également être pré-incisés, auquel cas, l'étape b) est absente. A titre d'exemple, les plis peuvent être constitués de tissu en fibres de carbone. Dans une troisième étape c), les aubes et, plus particulièrement, les pales 12 d'aubes sont insérées au travers des incisions 8 des premiers plis 7 et des ajours du noyau dans le sens de la flèche représentée à la figure 4. Selon la présente invention, les incisions et ajours sont espacés de façon à disposer côte à côte, c'est-à-dire de manière jointive, les plate-formes comme illustré par les pointillés dans la figure 3. Les aubes peuvent être des préformes sèches destinées ultérieurement à être injectées par une résine, ou bien des aubes composites ou encore des aubes métalliques. Ensuite, dans l'étape d), les derniers plis 10 sont drapés au-dessus des plate-formes 9 d'aubes pour compléter la préforme du redresseur. Dans l'étape e), une résine est injectée dans un moule fermé contenant la préforme et la préforme imprégnée est polymérisée. Dans le cas où l'aube insérée est une préforme sèche, cette dernière est également injectée par la résine. Une dernière étape f) consiste ensuite à ouvrir le moule et démouler le redresseur ainsi réalisé.The method according to the invention comprises at least six steps (see fig.3 and fig.4 ). A first step a) consists of draping the first folds 7 on a core having openings and having the shape of the aerodynamic vein (not shown). In a second step b), the first folds are incised according to an incision 8 placed opposite the opening of the core. The first folds 7 may also be pre-incised, in which case step b) is absent. By way of example, the plies may consist of carbon fiber fabric. In a third step c) , the blades and, more particularly, the blades 12 of blades are inserted through the incisions 8 of the first plies 7 and openings of the core in the direction of the arrow represented in FIG. figure 4 . According to the present invention, the incisions and openings are spaced so as to arrange side by side, that is to say in a contiguous manner, the platforms as illustrated by the dotted lines in the figure 3 . The blades may be dry preforms intended later to be injected by a resin, or composite blades or metal blades. Then, in step d), the last plies 10 are draped over the blade platforms 9 for complete the preform of the rectifier. In step e), a resin is injected into a closed mold containing the preform and the impregnated preform is polymerized. In the case where the inserted blade is a dry preform, the latter is also injected by the resin. A final step f) then consists in opening the mold and demolding the rectifier thus produced.

Avantages du procédé selon l'inventionAdvantages of the process according to the invention

  • La veine aérodynamique ne présente aucun défaut car une grande partie du rayon de raccordement pale/plate-forme 11 se trouve dans l'épaisseur de la virole ; cela permet de minimiser les perturbations au niveau aérodynamique.The aerodynamic vein has no defect because a large part of the blade / platform connection radius 11 is in the thickness of the ferrule; this minimizes aerodynamic disturbances.
  • Les plate-formes sont jointives entre elles pour assurer le calage angulaire ainsi qu'une meilleure tenue mécanique.The platforms are contiguous to each other to ensure angular setting and better mechanical strength.
  • Le montage est simplifié car il n'y a pas besoin d'éléments de fixation tels que rivets, boulons, etc.Mounting is simplified because there is no need for fasteners such as rivets, bolts, etc.
  • L'absence de soudure ne demande pas l'éloignement des brides de la zone d'assemblage plate-forme/virole et, par conséquent, permet de réduire la longueur du compresseur basse pression.The absence of welding does not require the distance of the flanges from the platform / ferrule assembly area and, therefore, reduces the length of the low pressure compressor.
  • Le procédé selon l'invention permet la réalisation de viroles extérieures et aubes en composite ce qui engendre un gain de masse d'environ 13% par rapport à un assemblage soudé entre viroles extérieures et aubes réalisées respectivement en titane.The method according to the invention allows the production of outer rings and composite blades which generates a weight saving of about 13% compared to a welded joint between outer rings and vanes respectively made of titanium.

Claims (7)

Procédé de fabrication d'un redresseur de turbomachine comportant une virole extérieure (5) et une pluralité d'aubes statoriques (2), lesdites aubes comportant une plate-forme (9) et une pale (12), caractérisé en ce que ledit procédé comporte au moins les étapes suivantes : a) on drape des premiers plis (7) sur un noyau comportant des ajours et ayant la forme de la veine aérodynamique ; b) optionnellement, on incise les premiers plis (7) selon des incisions (8) placées en regard des ajours du noyau ; c) on insère les pales (12) des aubes ou, alternativement, les pales (12) des préformes d'aubes, à travers les incisions (8) des premiers plis (7) et les ajours du noyau ; d) on drape des derniers plis (10) au-dessus des plate-formes (9) formant ainsi une préforme de redresseur ; e) on injecte une résine dans un moule fermé contenant la préforme et on polymérise la préforme imprégnée de résine ; f) on sort du moule une pièce moulée présentant sensiblement la forme et les dimensions dudit redresseur. A method of manufacturing a turbomachine rectifier comprising an outer shell (5) and a plurality of stator vanes (2), said blades having a platform (9) and a blade (12), characterized in that said method has at least the following steps: a) drapes first folds (7) on a core having openings and having the shape of the aerodynamic vein; b) optionally, the first folds (7) are incised according to incisions (8) placed opposite the openings of the core; c) inserting the blades (12) of the blades or, alternatively, the blades (12) of the blade preforms, through the incisions (8) of the first plies (7) and the openings of the core; d) drapes last folds (10) above the platforms (9) thereby forming a rectifier preform; e) injecting a resin into a closed mold containing the preform and polymerizing the preform impregnated with resin; f) a molding is produced from the mold having substantially the shape and dimensions of said rectifier. Procédé selon la revendication 1, caractérisé en ce que les premiers plis (7) sont pré-incisés, auquel cas, l'étape b) est absente.Method according to claim 1, characterized in that the first folds (7) are pre-incised, in which case step b) is absent. Procédé selon la revendication 1 ou 2, caractérisé en ce que l'aube est en matériau composite ou métallique.Process according to Claim 1 or 2, characterized in that the blade is made of composite or metallic material. Procédé selon la revendication 1 ou 2 caractérisé en ce que la préforme d'aube est également injectée par la résine dans l'étape e).Process according to claim 1 or 2, characterized in that the blade preform is also injected by the resin in step e). Procédé selon l'une quelconque des revendications précédentes caractérisé en ce qu'on dispose côte à côte les plate-formes (9) des aubes dans l'étape c).Method according to any one of the preceding claims, characterized in that the platforms (9) of the blades are arranged side by side in step c). Procédé selon l'une quelconque des revendications précédentes caractérisé en ce que, les premiers (7) et derniers plis (10) comprennent du tissu en fibres de carbone.Process according to any one of the preceding claims, characterized in that the first (7) and last plies (10) comprise carbon fiber fabric. Redresseur de turbomachine obtenu au moyen du procédé selon l'une quelconque des revendications précédentes.A turbomachine rectifier obtained by the method according to any of the preceding claims.
EP09163148.1A 2009-06-18 2009-06-18 Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method Active EP2264284B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP09163148.1A EP2264284B1 (en) 2009-06-18 2009-06-18 Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method
CA2705631A CA2705631C (en) 2009-06-18 2010-05-27 Method for manufacturing vanes integrated into a ring and rectifier obtained by the method
US12/791,270 US8414259B2 (en) 2009-06-18 2010-06-01 Method for manufacturing vanes integrated into a ring and rectifier obtained by the method

Applications Claiming Priority (1)

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EP09163148.1A EP2264284B1 (en) 2009-06-18 2009-06-18 Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method

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EP2264284A1 true EP2264284A1 (en) 2010-12-22
EP2264284B1 EP2264284B1 (en) 2015-01-28

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CA (1) CA2705631C (en)

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CN107762568A (en) * 2017-09-30 2018-03-06 中国航发沈阳发动机研究所 Weld the fancase formed
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Also Published As

Publication number Publication date
US8414259B2 (en) 2013-04-09
US20100322763A1 (en) 2010-12-23
CA2705631A1 (en) 2010-12-18
EP2264284B1 (en) 2015-01-28
CA2705631C (en) 2017-02-28

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