EP3003600B1 - Turbine engine blade preform - Google Patents

Turbine engine blade preform Download PDF

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Publication number
EP3003600B1
EP3003600B1 EP14733252.2A EP14733252A EP3003600B1 EP 3003600 B1 EP3003600 B1 EP 3003600B1 EP 14733252 A EP14733252 A EP 14733252A EP 3003600 B1 EP3003600 B1 EP 3003600B1
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EP
European Patent Office
Prior art keywords
blade
upstream
preform
downstream
mold
Prior art date
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EP14733252.2A
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German (de)
French (fr)
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EP3003600A1 (en
Inventor
Sébastien CONGRATEL
Raphaël DUPEYRE
Guillaume KLEIN
David Mathieu
Ba-Phuc TANG
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 Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP3003600A1 publication Critical patent/EP3003600A1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/06—Permanent moulds for shaped castings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • B22D25/02—Special casting characterised by the nature of the product by its peculiarity of shape; of works of art
    • 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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining

Definitions

  • the invention relates to a turbomachine blade preform, such as in particular a turbine blade preform in a turbomachine, and a mold and a method for obtaining the blade preform.
  • the turbine blades are monoblock pieces obtained from foundry by means of a mold comprising a cavity whose three-dimensional shape makes it possible to obtain the desired shape by complementarity.
  • the part obtained after the molding step consists of a blade preform that is necessary to machine to give it the desired shapes and final dimensions.
  • a turbine blade preform comprises a stilt connecting a blade root to a platform.
  • the blade preform also comprises two transverse upstream and downstream sails formed at the upstream and downstream ends of the stilt and connecting the upstream and downstream edges of the platform to the upstream and downstream ends of the blade root, respectively.
  • upstream and downstream are to be considered with respect to a general direction of flow of an upstream fluid downstream around the blade when it is mounted in a turbomachine.
  • each blade vane Viewed in an upstream / downstream direction, each blade vane has side edges connected to the sidewalls of the blade root through concave curved walls extending towards each other and forming an area of the blade. throttling whose width measured in a transverse direction is less than that of the blade root.
  • a throttling zone at the junction between each sail and the blade root limits the time required for the final machining of the blade root.
  • the mold must also comprise corresponding throttling zones.
  • the document US6186867 discloses a method for forming a molded part with precision.
  • the document EP0290773 discloses a method of grinding profiled parts, particularly turbine blades.
  • the document EP1216770 discloses a tool having a plurality of locking blocks arranged in conjunction with at least one insert.
  • the present invention provides a simple, effective and economical solution to these problems.
  • a turbomachine blade preform comprising a stilt connecting a platform to a part of the blade root extending longitudinally along an upstream / downstream direction, two upstream and downstream sails. extending in a direction substantially perpendicular to the longitudinal direction of the blade root and being formed at the upstream and downstream ends of the stilt, these upstream and downstream sails connecting the upstream and downstream ends of the platform to the upstream and downstream ends of the blade root, characterized in that the blade root extends in a direction perpendicular to the longitudinal direction of the blade root a distance less than that of the upstream and downstream sails and in that the lateral edges of each veil are extended by walls converging towards each other up to the flanks of the foot of dawn.
  • said convergent walls are formed by flat faces inclined with respect to a median plane of the blade root extending longitudinally along an upstream / downstream direction.
  • the aforementioned faces are inclined at an angle of approximately 45 ° with respect to the median plane.
  • the invention also relates to a mold for the manufacture of a foundry blade preform as described above, comprising an internal cavity whose three-dimensional shape determines by complementarity the three-dimensional shape of the blade preform, the mold comprising at least two first and two second blocks arranged in pairs facing each other along perpendicular axes, the first two impression blocks each comprising an imprint comprising a boss intended to delimit the internal surface of a platform of the preform the dawn and defining with fingerprints of the second blocks impressed spaces for forming upstream and downstream side sails connecting upstream and downstream edges of a platform of the blade preform at the upstream and downstream ends of a dawn foot, the first impression block also comprising substantially parallel vis-à-vis faces intended to form flanks of a part of the foot of the prefo blade, characterized in that the footprint of each first block comprises first and second surfaces on either side of the boss connected to the side forming a flank of the blade root, the first and second surfaces of the blades.
  • first impression blocks converging towards each other towards
  • first and second converging surfaces avoids the formation of a throttling zone in the connection zones of the side veils at the blade root, which limits the formation of defects in these places.
  • figure 1 represents a blade preform 10 of a one-piece turbomachine according to the prior art obtained by molding in a mold and comprising, along an axis 12, a blade root portion 14 extending longitudinally along an upstream / downstream direction and having in section transverse to a substantially rectangular shape, a platform 16, a blade 18 and a blade heel 20.
  • the contour of the foot forms a U, the branches of the U being substantially parallel and being formed by the flanks 42 of the blade root.
  • Dawn represented in figure 1 more particularly represents a blade mounted in a turbine of the turbomachine.
  • the mold 22 comprises an internal cavity 24 whose three-dimensional shape is determined so that by filling the mold with liquid material the desired three-dimensional shape of the blade preform 10 is obtained.
  • the liquid material is injected into the mold. the mold 22 from a lower portion 23 of the mold 12 corresponding to that to obtain the heel 20 of the blade.
  • the liquid material progressively fills the mold (arrow A) to an upper part 25 of the mold corresponding to that making it possible to obtain a part of the blade root 14.
  • the mold 22 is shown in the inverted position relative to its position of use.
  • the figure 2 represents the dashed portion on the figure 1 , that is to say the inner part of the blade preform comprising two upstream and downstream sails 26 extending in a direction substantially perpendicular to the longitudinal direction of the blade root 14, the two upstream sails 26 and downstream 28 connecting the blade root portion 14 to the platform 16 (only the upstream web 26 is shown in FIG. figure 2 , the downstream veil 28 being visible on the figure 3 representing the invention).
  • this type of blade preform may present mechanical defects such as cracks, at the connection areas 38 of the webs 26, 28 to the flanks 42 of the foot portion 14 of the blade preform 10 of the makes the presence of a throttling zone in the mold between the two parts 34 slowing down material flow (arrow A).
  • the invention thus proposes to modify the connection areas of the lateral edges of the webs 26, 28 to the flanks 42 of the blade root by extending the lateral edges 40 of the webs by walls 44 converging towards each other until flanks 42 of the blade root 14 as shown in FIG. figure 3 .
  • the blade root 14 thus extends in a direction substantially perpendicular to the longitudinal upstream / downstream direction of the blade root for a distance less than that of the upstream and downstream sails 26.
  • the blade preform 46 no longer includes a throttling zone, which greatly reduces the risk of formation of defects at the junction of the sails 26, 28 with the blade root portion 14.
  • the walls 44 are formed by flat surfaces inclined at an angle of approximately 45 ° with respect to a median plane of the blade root extending from upstream to downstream, that is to say a plane s extending longitudinally and passing through the middle of the blade root 14.
  • the walls may be curved concave or convex while converging towards the flanks of the blade root.
  • Figures 4 to 6 representing a part of a mold 48 according to the invention making it possible to form the converging face connection zones as described with reference to FIG. figure 3 .
  • This mold comprises two first 50A, 52A and two second 54A, 56A impression blocks arranged two by two in screws along perpendicular axes 58, 60 ( figure 4 ).
  • Each impression block 50A, 52A, 54A, 56A comprises a recess 50B, 52B, 54B, 56B delimiting after assembly of the impression blocks 50A, 52A, 54A, 56A a cavity intended to complementarily form a portion of the blade preform. 46 turbine.
  • the 50B footprint of the block 50A includes a boss 50C an outer surface 50D is arranged with play vis-à-vis an outer surface 52D of a boss 52C corresponding to the cavity 52B of the block 52A so as to form the stilt of the preform 46
  • Each outer surface 50D, 52D of a boss 50C, 52C is connected to the remainder of the recess 50B, 52B by a periphery whose upper surface 50E is intended to delimit an inner face of the platform 16, two lateral surfaces.
  • 50F are intended to form with the cavities 54B, 56B second impression blocks 54A, 56A the upstream and downstream lateral sails 26 of the blade preform 46.
  • the boss 50C, 52C of each recess 50B, 52B of a first block protrudes from a surface 50G intended to form the lateral edges of the platform 16 as well as the lateral edges 40 of the upstream and downstream sails 26 of the platform 16.
  • This surface 50G is connected to a first 50H and a second 50I surfaces extending on either side of the boss 50D and intended to form the connection zones according to the invention at the foot of dawn 14.
  • the first surfaces 50H, 52H of the impressions 50B, 52B converge towards each other in an oriented direction of the blade 18 towards the blade root 14.
  • the second surfaces 50I, 52I converge towards each other in a direction oriented from the blade towards the dawn foot.
  • the first surface 50H, 52H and the second surface 50I, 52H of each impression block 50A, 52A are connected to the same surface 50J, 52J intended to form a flank 42 of a part of the blade root 14. These surfaces of the first impression blocks 50A, 52A forming the aforementioned flanks are substantially parallel.
  • the second impression blocks 54A, 56A each comprise a slot 54C intended to form a spoiler 62 extending from a lateral web 26, 28 of the blade preform 46 and opposite the platform 16 relative to in the veil.
  • a machining operation of the preform is performed so as to obtain a turbine blade 64 to the desired dimensions.
  • the machining step also involves machining the side edges of the platform.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Description

L'invention concerne une préforme d'aube de turbomachine, telle qu'en particulier une préforme d'aube de turbine dans une turbomachine, ainsi qu'un moule et un procédé pour l'obtention de la préforme d'aube.The invention relates to a turbomachine blade preform, such as in particular a turbine blade preform in a turbomachine, and a mold and a method for obtaining the blade preform.

Dans la technique actuelle, les aubes de turbine sont des pièces monoblocs obtenues de fonderie au moyen d'un moule comprenant une cavité dont la forme tridimensionnelle permet d'obtenir par complémentarité la forme souhaitée. En pratique, la pièce obtenue après l'étape de moulage consiste en une préforme d'aube qu'il est nécessaire d'usiner pour lui donner les formes et dimensions finales souhaitées.In the current technique, the turbine blades are monoblock pieces obtained from foundry by means of a mold comprising a cavity whose three-dimensional shape makes it possible to obtain the desired shape by complementarity. In practice, the part obtained after the molding step consists of a blade preform that is necessary to machine to give it the desired shapes and final dimensions.

Ainsi, une préforme d'aube de turbine comprend une échasse reliant un pied d'aube à une plate-forme. La préforme d'aube comporte également deux voiles amont et aval transverses formés aux extrémités amont et aval de l'échasse et raccordant les bords amont et aval de la plate-forme aux extrémités amont et aval du pied d'aube, respectivement. On notera que les termes « amont » et « aval » sont à considérer par rapport à une direction générale d'écoulement d'un fluide d'amont vers l'aval autour de l'aube lorsque celle-ci est montée dans une turbomachine.Thus, a turbine blade preform comprises a stilt connecting a blade root to a platform. The blade preform also comprises two transverse upstream and downstream sails formed at the upstream and downstream ends of the stilt and connecting the upstream and downstream edges of the platform to the upstream and downstream ends of the blade root, respectively. It should be noted that the terms "upstream" and "downstream" are to be considered with respect to a general direction of flow of an upstream fluid downstream around the blade when it is mounted in a turbomachine.

Vue dans une direction amont/aval, chaque voile de l'aube comprend des bords latéraux raccordés aux flancs du pied d'aube par l'intermédiaire de parois incurvées concaves s'étendant l'une vers l'autre et formant une zone d'étranglement dont la largeur mesurée dans une direction transverse est inférieure à celle du pied d'aube.Viewed in an upstream / downstream direction, each blade vane has side edges connected to the sidewalls of the blade root through concave curved walls extending towards each other and forming an area of the blade. throttling whose width measured in a transverse direction is less than that of the blade root.

La présence d'une zone d'étranglement à la jonction entre chaque voile et le pied d'aube permet de limiter le temps nécessaire à l'usinage final du pied d'aube. Pour obtenir ces zones d'étranglement précitées, le moule doit également comprendre des zones d'étranglement correspondantes.The presence of a throttling zone at the junction between each sail and the blade root limits the time required for the final machining of the blade root. To obtain these aforementioned throttling zones, the mold must also comprise corresponding throttling zones.

Toutefois, lors de l'écoulement de la matière liquide dans le moule, les zones d'étranglement du moule ralentissent l'écoulement de matière à ces endroits, ce qui peut conduire à des fins de solidification et des reprises de grain entrainant une mauvaise solidification de la matière et la formation de défauts mécaniques, tels que des criques, dans les zones de raccordement des voiles latéraux au pied de la préforme d'aube.However, during the flow of the liquid material into the mold, the throttling zones of the mold slow down the flow of material to these places, which can lead to solidification and grain recovery resulting in poor solidification of the material and the formation of mechanical defects, such as cracks, in the connection areas of the side sails at the foot of the preform 'dawn.

Le document US6186867 décrit un procédé pour former une pièce moulée avec précision. Le document EP0290773 décrit un procédé de meulage de pièces profilées, en particulier des aubes de turbine. Le document EP1216770 décrit un outil comportant plusieurs blocs de verrouillage agencés conjointement avec au moins un insert.The document US6186867 discloses a method for forming a molded part with precision. The document EP0290773 discloses a method of grinding profiled parts, particularly turbine blades. The document EP1216770 discloses a tool having a plurality of locking blocks arranged in conjunction with at least one insert.

La présente invention apporte une solution simple, efficace et économique à ces problèmes.The present invention provides a simple, effective and economical solution to these problems.

A cette fin, elle propose une préforme d'aube de turbomachine, la préforme comprenant une échasse reliant une plate-forme à une partie de pied d'aube s'étendant longitudinalement suivant une direction amont/aval, deux voiles amont et aval s'étendant suivant une direction sensiblement perpendiculaire à la direction longitudinale du pied d'aube et étant formés aux extrémités amont et aval de l'échasse, ces voiles amont et aval reliant les extrémités amont et aval de la plate-forme aux extrémités amont et aval du pied d'aube, caractérisé en ce que le pied d'aube s'étend suivant une direction perpendiculaire à la direction longitudinale du pied d'aube sur une distance inférieure à celle des voiles amont et aval et en ce que les bords latéraux de chaque voile se prolongent par des parois convergeant l'une vers l'autre jusqu'aux flancs du pied d'aube.To this end, it proposes a turbomachine blade preform, the preform comprising a stilt connecting a platform to a part of the blade root extending longitudinally along an upstream / downstream direction, two upstream and downstream sails. extending in a direction substantially perpendicular to the longitudinal direction of the blade root and being formed at the upstream and downstream ends of the stilt, these upstream and downstream sails connecting the upstream and downstream ends of the platform to the upstream and downstream ends of the blade root, characterized in that the blade root extends in a direction perpendicular to the longitudinal direction of the blade root a distance less than that of the upstream and downstream sails and in that the lateral edges of each veil are extended by walls converging towards each other up to the flanks of the foot of dawn.

La formation de bords latéraux convergeant l'un vers l'autre au niveau des zones de raccordement de chaque voile au pied d'aube permet d'obtenir en fonderie lors du coulage de la matière dans un moule adéquat des qualités métallurgiques optimales au niveau de ces zones de raccordement puisque l'écoulement de matière dans le moule se fait sans présence d'une zone d'étranglement comme dans la technique antérieure.The formation of lateral edges converging towards one another at the connection zones of each sail at the blade root makes it possible to obtain in the foundry during the casting of the material in a suitable mold optimum metallurgical qualities at the level of these connection areas since the flow of material into the mold is without the presence of a throttling area as in the prior art.

Ainsi, le taux de rebut des préformes d'aubes obtenues par moulage est fortement diminué, ce qui réduit les coûts de fabrication des aubes.Thus, the scrap rate of the blade preforms obtained by molding is greatly reduced, which reduces the costs of blade manufacture.

Préférentiellement, lesdites parois convergentes sont formées par des faces planes inclinées par rapport à un plan médian du pied d'aube s'étendant longitudinalement suivant une direction amont/aval.Preferably, said convergent walls are formed by flat faces inclined with respect to a median plane of the blade root extending longitudinally along an upstream / downstream direction.

Selon une réalisation particulière de l'invention, les faces précitées sont inclinées d'un angle d'environ 45° par rapport au plan médian.According to a particular embodiment of the invention, the aforementioned faces are inclined at an angle of approximately 45 ° with respect to the median plane.

L'invention concerne également un moule pour la fabrication d'une préforme d'aube de fonderie tel que décrit ci-dessus, comprenant une cavité interne dont la forme tridimensionnelle détermine par complémentarité la forme tridimensionnelle de la préforme d'aube, le moule comprenant au moins deux premiers et deux seconds blocs agencés deux à deux en vis-à-vis selon des axes perpendiculaires, les deux premiers blocs empreinte comprenant chacun une empreinte comportant un bossage destiné à délimiter la surface interne d'une plate-forme de la préforme l'aube et définissant avec des empreintes des seconds blocs empreintes des espaces destinés à former des voiles latéraux amont et aval de raccordement de bords amont et aval d'une plate-forme de la préforme d'aube aux extrémités amont et aval d'un pied d'aube, les premiers bloc empreinte comprenant également des faces en vis-à-vis sensiblement parallèles destinées à former des flancs d'une partie du pied de la préforme d'aube, caractérisé en ce que l'empreinte de chaque premier bloc comprend des première et seconde surfaces de part et d'autre du bossage raccordées à la face formant un flanc du pied d'aube, les premières et les secondes surfaces des premiers blocs empreintes convergeant l'une vers l'autre en direction des faces des flancs du pied d'aube.The invention also relates to a mold for the manufacture of a foundry blade preform as described above, comprising an internal cavity whose three-dimensional shape determines by complementarity the three-dimensional shape of the blade preform, the mold comprising at least two first and two second blocks arranged in pairs facing each other along perpendicular axes, the first two impression blocks each comprising an imprint comprising a boss intended to delimit the internal surface of a platform of the preform the dawn and defining with fingerprints of the second blocks impressed spaces for forming upstream and downstream side sails connecting upstream and downstream edges of a platform of the blade preform at the upstream and downstream ends of a dawn foot, the first impression block also comprising substantially parallel vis-à-vis faces intended to form flanks of a part of the foot of the prefo blade, characterized in that the footprint of each first block comprises first and second surfaces on either side of the boss connected to the side forming a flank of the blade root, the first and second surfaces of the blades. first impression blocks converging towards each other towards the faces of the flanks of the blade root.

Selon l'invention, l'intégration de premières et secondes surfaces convergentes évite la formation d'une zone d'étranglement dans les zones de raccordement des voiles latéraux au pied d'aube, ce qui limite la formation de défauts en ces endroits.According to the invention, the integration of first and second converging surfaces avoids the formation of a throttling zone in the connection zones of the side veils at the blade root, which limits the formation of defects in these places.

L'invention concerne encore un procédé de fabrication d'une aube de turbine au moyen du moule décrit ci-dessus, consistant à :

  1. a. positionner le moule de sorte que les premiers et seconds blocs empreintes soient agencées en position supérieure par rapport à une partie inférieure du moule ;
  2. b. introduire progressivement une matière liquide dans la partie inférieure du moule de manière à ce que le niveau de liquide augmente progressivement à l'intérieur du moule et forme par complémentarité de forme une préforme d'aube; puis à
  3. c. réaliser un usinage de finition de la préforme d'aube aux dimensions finales souhaitées de l'aube.
The invention further relates to a method of manufacturing a turbine blade using the mold described above, comprising:
  1. at. positioning the mold so that the first and second impression blocks are arranged in an upper position relative to a lower portion of the mold;
  2. b. gradually introducing a liquid material into the lower part of the mold so that the liquid level gradually increases inside the mold and forms by complementarity of form a dawn preform; then to
  3. vs. perform a finishing machining of the blade preform to the desired final dimensions of the blade.

L'invention sera mieux comprise et d'autres caractéristiques, détails et avantages de celle-ci apparaîtront plus clairement à la lecture de la description qui suit, faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique d'une préforme d'aube de turbomachine selon la technique antérieure ;
  • la figure 2 est une vue depuis l'amont de la zone délimitée en pointillée sur la figure 1 ;
  • la figure 3 est une vue schématique en perspective d'une préforme d'aube de turbomachine selon l'invention ;
  • les figures 4 à 6 sont des représentations schématiques en perspectives de plusieurs blocs empreintes d'un outillage pour la réalisation d'une préforme selon l'invention ;
  • la figure 7 est une vue depuis l'amont représentant simultanément et en superposition une préforme d'aube de turbine selon l'invention et une aube de turbomachine obtenu après usinage de la préforme ;
  • la figure 8 est une vue schématique en perspective représentant simultanément et en superposition une préforme d'aube de turbine selon l'invention et une aube de turbomachine obtenu après usinage de la préforme.
The invention will be better understood and other characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of nonlimiting example and with reference to the accompanying drawings in which:
  • the figure 1 is a schematic view of a turbomachine blade preform according to the prior art;
  • the figure 2 is a view from upstream of the dashed area on the figure 1 ;
  • the figure 3 is a schematic perspective view of a turbomachine blade preform according to the invention;
  • the Figures 4 to 6 are schematic representations in perspective of several blocks impressed with a tool for producing a preform according to the invention;
  • the figure 7 is a view from upstream representing simultaneously and in superposition a turbine blade preform according to the invention and a turbomachine blade obtained after machining of the preform;
  • the figure 8 is a schematic perspective view simultaneously showing and superimposed a turbine blade preform according to the invention and a turbomachine blade obtained after machining of the preform.

On se réfère tout d'abord à la figure 1 qui représente une préforme d'aube 10 de turbomachine monobloc selon l'art antérieur obtenue par moulage dans un moule et comprenant selon un axe 12 une partie de pied d'aube 14 s'étendant longitudinalement suivant une direction amont/aval et ayant en section transverse une forme sensiblement rectangulaire , une plate-forme 16, une pale 18 et un talon d'aube 20. Vue depuis l'amont ou l'aval, le contour du pied forme un U, les branches du U étant sensiblement parallèles et étant formées par les flancs 42 du pied d'aube. L'aube représentée en figure 1 représente plus particulièrement une aube montée dans une turbine de la turbomachine.We first refer to the figure 1 which represents a blade preform 10 of a one-piece turbomachine according to the prior art obtained by molding in a mold and comprising, along an axis 12, a blade root portion 14 extending longitudinally along an upstream / downstream direction and having in section transverse to a substantially rectangular shape, a platform 16, a blade 18 and a blade heel 20. Viewed from upstream or downstream, the contour of the foot forms a U, the branches of the U being substantially parallel and being formed by the flanks 42 of the blade root. Dawn represented in figure 1 more particularly represents a blade mounted in a turbine of the turbomachine.

Le moule 22 comprend une cavité interne 24 dont la forme tridimensionnelle est déterminée de manière à ce qu'en remplissant le moule de matière liquide on obtienne la forme tridimensionnelle souhaitée de la préforme d'aube 10. En pratique, la matière liquide est injectée dans le moule 22 depuis une partie inférieure 23 du moule 12 correspondant à celle permettant d'obtenir le talon 20 de l'aube. La matière liquide remplit progressivement le moule (flèche A) jusqu'à une partie supérieure 25 du moule correspondant à celle permettant d'obtenir une partie de pied d'aube 14. Ainsi, sur la figure 1, et pour une habitude de représentation de l'aube, le moule 22 est représenté en position inversée par rapport à sa position d'utilisation.The mold 22 comprises an internal cavity 24 whose three-dimensional shape is determined so that by filling the mold with liquid material the desired three-dimensional shape of the blade preform 10 is obtained. In practice, the liquid material is injected into the mold. the mold 22 from a lower portion 23 of the mold 12 corresponding to that to obtain the heel 20 of the blade. The liquid material progressively fills the mold (arrow A) to an upper part 25 of the mold corresponding to that making it possible to obtain a part of the blade root 14. Thus, on the figure 1 , and for a representation of the dawn, the mold 22 is shown in the inverted position relative to its position of use.

La figure 2 représente la partie délimitée en pointillée sur la figure 1, c'est-à-dire la partie interne de la préforme d'aube comportant deux voiles amont 26 et aval 28 s'étendant suivant une direction sensiblement perpendiculaire à la direction longitudinale du pied d'aube 14, les deux voiles amont 26 et aval 28 reliant la partie de pied d'aube 14 à la plate-forme 16 (seul le voile amont 26 est représenté en figure 2, le voile aval 28 étant visible sur la figure 3 représentant l'invention). Sur la figure 2 sont également représentés de manière schématique deux blocs empreintes 30, 32 du moule 22, agencées en vis-à-vis et comprenant chacun une partie en saillie 34 l'une vers l'autre, ces parties 34 comprenant des surfaces incurvées convexes 36 permettant de former par complémentarité de forme des parois incurvées concaves 38 raccordant les bords latéraux 40 des voiles 26, 28 à la partie de pied d'aube 14.The figure 2 represents the dashed portion on the figure 1 , that is to say the inner part of the blade preform comprising two upstream and downstream sails 26 extending in a direction substantially perpendicular to the longitudinal direction of the blade root 14, the two upstream sails 26 and downstream 28 connecting the blade root portion 14 to the platform 16 (only the upstream web 26 is shown in FIG. figure 2 , the downstream veil 28 being visible on the figure 3 representing the invention). On the figure 2 two impression blocks 30, 32 of the mold 22, arranged vis-a-vis and each comprising a projecting portion 34 towards each other, are also diagrammatically represented, these parts 34 comprising convex curved surfaces 36 making it possible to forming, by complementary shape, concave curved walls 38 connecting the lateral edges 40 of the webs 26, 28 to the blade root part 14.

Comme expliqué précédemment, ce type de préforme d'aube peut présenter des défauts mécaniques tels que des criques, au niveau des zones de raccordement 38 des voiles 26, 28 aux flancs 42 de la partie de pied 14 de la préforme d'aube 10 du fait de la présence d'une zone d'étranglement dans le moule entre les deux parties 34 ralentissant l'écoulement de matière (flèche A).As explained above, this type of blade preform may present mechanical defects such as cracks, at the connection areas 38 of the webs 26, 28 to the flanks 42 of the foot portion 14 of the blade preform 10 of the makes the presence of a throttling zone in the mold between the two parts 34 slowing down material flow (arrow A).

L'invention propose ainsi de modifier les zones de raccordement des bords latéraux des voiles 26, 28 aux flancs 42 du pied d'aube en prolongeant les bords latéraux 40 des voiles par des parois 44 convergeant l'une vers l'autre jusqu'aux flancs 42 du pied d'aube 14 comme représenté en figure 3. Le pied d'aube 14 s'étend ainsi suivant une direction sensiblement perpendiculaire à la direction longitudinale amont/aval du pied d'aube sur une distance inférieure à celle des voiles amont 26 et aval 28.Au contraire de l'art antérieur, la préforme d'aube 46 ne comprend plus de zone d'étranglement, ce qui réduit fortement les risques de formation de défauts à la jonction des voiles 26, 28 avec la partie de pied d'aube 14.The invention thus proposes to modify the connection areas of the lateral edges of the webs 26, 28 to the flanks 42 of the blade root by extending the lateral edges 40 of the webs by walls 44 converging towards each other until flanks 42 of the blade root 14 as shown in FIG. figure 3 . The blade root 14 thus extends in a direction substantially perpendicular to the longitudinal upstream / downstream direction of the blade root for a distance less than that of the upstream and downstream sails 26. In contrast to the prior art, the blade preform 46 no longer includes a throttling zone, which greatly reduces the risk of formation of defects at the junction of the sails 26, 28 with the blade root portion 14.

Dans la réalisation représentée en figure 3, les parois 44 sont formées par des surfaces planes inclinées d'un angle d'environ 45° par rapport à un plan médian du pied d'aube s'étendant d'amont en aval, c'est-à-dire un plan s'étendant longitudinalement et passant par le milieu du pied d'aube 14.In the embodiment shown in figure 3 , the walls 44 are formed by flat surfaces inclined at an angle of approximately 45 ° with respect to a median plane of the blade root extending from upstream to downstream, that is to say a plane s extending longitudinally and passing through the middle of the blade root 14.

Dans d'autres réalisations non représentées, les parois peuvent être incurvées concaves ou convexes tout en convergeant vers les flancs du pied d'aube.In other embodiments not shown, the walls may be curved concave or convex while converging towards the flanks of the blade root.

On se réfère maintenant aux figures 4 à 6 représentant une partie d'un moule 48 selon l'invention permettant de former les zones de raccordement à faces convergentes comme décrit en référence à la figure 3.We now refer to Figures 4 to 6 representing a part of a mold 48 according to the invention making it possible to form the converging face connection zones as described with reference to FIG. figure 3 .

Ce moule comprend deux premiers 50A, 52A et deux seconds 54A, 56A blocs empreintes agencés deux à deux en vis selon des axes perpendiculaires 58, 60 (figure 4). Chaque bloc empreinte 50A, 52A, 54A, 56A comprend une empreinte 50B, 52B, 54B, 56B délimitant après assemblage des blocs empreintes 50A, 52A, 54A, 56A une cavité destinée à former par complémentarité une partie de la préforme de d'aube de 46 de turbine.This mold comprises two first 50A, 52A and two second 54A, 56A impression blocks arranged two by two in screws along perpendicular axes 58, 60 ( figure 4 ). Each impression block 50A, 52A, 54A, 56A comprises a recess 50B, 52B, 54B, 56B delimiting after assembly of the impression blocks 50A, 52A, 54A, 56A a cavity intended to complementarily form a portion of the blade preform. 46 turbine.

En particulier, l'empreinte 50B du bloc 50A comprend un bossage 50C dont une surface externe 50D est agencée avec jeu en vis-à-vis d'une surface externe 52D d'un bossage 52C correspondant de l'empreinte 52B du bloc 52A de manière à former l'échasse de la préforme d'aube 46. Chaque surface externe 50D, 52D d'un bossage 50C, 52C est reliée au reste de l'empreinte 50B, 52B par un pourtour dont une surface supérieure 50E est destinée à délimiter une face interne de la plate-forme 16, deux surfaces latérales 50F sont destinées à former avec les empreintes 54B, 56B des seconds blocs empreintes 54A, 56A les voiles latéraux amont 26 et aval 28 de la préforme d'aube 46.In particular, the 50B footprint of the block 50A includes a boss 50C an outer surface 50D is arranged with play vis-à-vis an outer surface 52D of a boss 52C corresponding to the cavity 52B of the block 52A so as to form the stilt of the preform 46 Each outer surface 50D, 52D of a boss 50C, 52C is connected to the remainder of the recess 50B, 52B by a periphery whose upper surface 50E is intended to delimit an inner face of the platform 16, two lateral surfaces. 50F are intended to form with the cavities 54B, 56B second impression blocks 54A, 56A the upstream and downstream lateral sails 26 of the blade preform 46.

Le bossage 50C, 52C de chaque empreinte 50B, 52B d'un premier bloc s'étend en saillie depuis une surface 50G destinée à former les bords latéraux de la plate-forme 16 ainsi que les bords latéraux 40 des voiles amont 26 et aval 28 de la plate-forme 16. Cette surface 50G est reliée à une première 50H et une seconde 50I surfaces s'étendant de part et d'autre du bossage 50D et destinée à former les zones de raccordement selon l'invention au pied d'aube 14. Pour cela, les premières surfaces 50H, 52H des empreintes 50B, 52B convergent l'une vers l'autre dans un sens orienté de la pale 18 vers le pied d'aube 14. De même, les secondes surfaces 50I, 52I convergent l'une vers l'autre dans un sens orientée de la pale vers le pied d'aube. La première surface 50H, 52H et la seconde surface 50I, 52H de chaque bloc empreinte 50A, 52A sont reliées à une même surface 50J, 52J destinée à former un flanc 42 d'une partie du pied d'aube 14. Ces surfaces des premiers blocs empreintes 50A, 52A formant les flancs précités sont sensiblement parallèles.The boss 50C, 52C of each recess 50B, 52B of a first block protrudes from a surface 50G intended to form the lateral edges of the platform 16 as well as the lateral edges 40 of the upstream and downstream sails 26 of the platform 16. This surface 50G is connected to a first 50H and a second 50I surfaces extending on either side of the boss 50D and intended to form the connection zones according to the invention at the foot of dawn 14. For this, the first surfaces 50H, 52H of the impressions 50B, 52B converge towards each other in an oriented direction of the blade 18 towards the blade root 14. Similarly, the second surfaces 50I, 52I converge towards each other in a direction oriented from the blade towards the dawn foot. The first surface 50H, 52H and the second surface 50I, 52H of each impression block 50A, 52A are connected to the same surface 50J, 52J intended to form a flank 42 of a part of the blade root 14. These surfaces of the first impression blocks 50A, 52A forming the aforementioned flanks are substantially parallel.

La formation sur les blocs empreintes de premières et secondes faces convergentes et débouchant sur des faces parallèles 50J, 52J permet de faciliter l'écoulement de matière liquide dans le moule (flèche A).The formation on the blocks impressed with first and second converging faces and opening on parallel faces 50J, 52J makes it possible to facilitate the flow of liquid material into the mold (arrow A).

Notons que les seconds blocs empreintes 54A, 56A comprennent chacun une fente 54C destinée à former un becquet 62 s'étendant depuis un voile latéral 26, 28 de la préforme d'aube 46 et à l'opposé de la plate-forme 16 par rapport au voile.Note that the second impression blocks 54A, 56A each comprise a slot 54C intended to form a spoiler 62 extending from a lateral web 26, 28 of the blade preform 46 and opposite the platform 16 relative to in the veil.

Après moulage de la préforme 46 au moyen du moule décrit ci-dessus, on effectue une opération d'usinage de la préforme de manière à obtenir une aube de turbine 64 aux dimensions souhaitées. En particulier, on réalise un usinage de la partie du pied d'aube et des zones de raccordement des voiles latéraux à la partie du pied d'aube de manière à réaliser un pied d'aube en queue d'aronde 66 apte à être engagé axialement et retenu radialement dans un alvéole d'un disque de turbine d'une manière bien connue. L'étape d'usinage consiste également à usiner les bords latéraux de la plate-forme.After molding of the preform 46 by means of the mold described above, a machining operation of the preform is performed so as to obtain a turbine blade 64 to the desired dimensions. In particular, machining of the part of the blade root and the connection areas of the side sails to the part of the blade root so as to achieve a blade root dovetail 66 capable of being engaged axially and retained radially in a cell of a turbine disk in a well known manner. The machining step also involves machining the side edges of the platform.

Claims (5)

  1. A turbine engine blade preform (46), with the preform comprising a strut connecting a plat-form (16) to a blade root portion (14) extending longitudinally in an upstream-downstream direction, an upstream web (26) and a downstream (28) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut, with such upstream (26) and downstream (28) webs connecting the upstream and downstream ends of the plat-form (16) to the upstream and downstream ends of the blade root (14), characterized in that the blade root (14) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that over which the upstream and downstream webs (26, 28) extend in said direction and in that the upstream and downstream webs each comprise two side edges (40) which are extended by walls that converge (44) at the flanks of the blade root.
  2. A preform according to claim 1, characterized in that said converging walls (44) are formed by plane faces inclined with respect to a median plane of the blade root extending longitudinally along an upstream/downstream direction.
  3. A preform according to claim 2, characterized in that the faces (44) are inclined at an angle of approximately 45° with respect to the median plane.
  4. A mold for manufacturing a casting blade preform (14) according to claim 1, comprising an internal cavity the three-dimensional shape of which determines, in a form-fitting manner, the three-dimensional shape of the blade preform, with the mold (48) comprising at least two first (50A, 52A) and two second (54A, 56A) blocks arranged in pairs opposite each other along perpendicular axes (58, 60), with the first two cavity retainer blocks (50A, 52A) each comprising a recess (50B, 52B) having a boss (50C, 52C) intended to define the inner surface of a plat-form (16) of the preform and the blade defining, with recesses (54B, 56B) of the second cavity retainer blocks (54A, 56A), spaces intended to form upstream and downstream side webs (26, 28) for connecting upstream and downstream edges of a plat-form (16) of the blade preform to the upstream and downstream ends of a blade root, with the first cavity retainer blocks (50A, 52A) further comprising substantially parallel and opposed faces (50J, 52J) intended to form flanks of a root part (14) of the blade preform, characterized in that the recess (50B, 52B) of each first block (50A, 52A) comprises first (50H, 52H) and second surfaces (50I, 52I) on either side of the boss connected to the face (50J, 52J) forming a flank of the blade root, with the first (50H, 52H) and the second (50I, 52I) surfaces of the first cavity retainer blocks converging toward the faces of the flanks of the blade root.
  5. A method for manufacturing a turbine blade using the mold according to claim 4, characterized in that it consists in:
    a. positioning the mold (48) so that the first (50A, 52A) and second (54A, 56A) cavity retainer blocks are arranged in an upper position relative to a lower mold part;
    b. gradually introducing a liquid material into the lower part of the mold so that the liquid level gradually increases inside the mold (48) and forms a blade preform, in a form-fitting manner; then
    c. performing a finishing machining of the blade preform to the desired final dimensions of the blade.
EP14733252.2A 2013-06-05 2014-06-04 Turbine engine blade preform Active EP3003600B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1355177A FR3006616B1 (en) 2013-06-05 2013-06-05 TURBOMACHINE WAVE PREFORM
PCT/FR2014/051324 WO2014195634A1 (en) 2013-06-05 2014-06-04 Turbine engine blade preform

Publications (2)

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EP3003600A1 EP3003600A1 (en) 2016-04-13
EP3003600B1 true EP3003600B1 (en) 2017-08-02

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EP14733252.2A Active EP3003600B1 (en) 2013-06-05 2014-06-04 Turbine engine blade preform

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US (1) US9833834B2 (en)
EP (1) EP3003600B1 (en)
JP (1) JP6549103B2 (en)
CN (1) CN105263650B (en)
BR (1) BR112015029844B1 (en)
CA (1) CA2912924C (en)
FR (1) FR3006616B1 (en)
RU (1) RU2660436C2 (en)
WO (1) WO2014195634A1 (en)

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FR3052088B1 (en) * 2016-06-02 2018-06-22 Safran MOLD FOR THE MANUFACTURE OF A MONOCRYSTALLINE DARK BY FOUNDRY, INSTALLATION AND METHOD OF MANUFACTURING THE SAME
CN106077506B (en) * 2016-08-11 2019-06-07 山东豪迈机械科技股份有限公司 A kind of blade casting mould and its application and blade forming method
FR3090032B1 (en) * 2018-12-12 2021-01-29 Safran Aircraft Engines BLADE FOR TURBOMACHINE WHEEL

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Publication number Publication date
FR3006616B1 (en) 2016-03-04
JP2016526129A (en) 2016-09-01
CA2912924A1 (en) 2014-12-11
US9833834B2 (en) 2017-12-05
CN105263650B (en) 2017-07-25
JP6549103B2 (en) 2019-07-24
CN105263650A (en) 2016-01-20
US20160129497A1 (en) 2016-05-12
RU2015149780A3 (en) 2018-03-28
RU2660436C2 (en) 2018-07-06
BR112015029844A2 (en) 2017-07-25
EP3003600A1 (en) 2016-04-13
WO2014195634A1 (en) 2014-12-11
FR3006616A1 (en) 2014-12-12
BR112015029844B1 (en) 2020-01-14
RU2015149780A (en) 2017-07-13
CA2912924C (en) 2021-06-08

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