EP1754555B1 - Core for turbine blade - Google Patents

Core for turbine blade Download PDF

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Publication number
EP1754555B1
EP1754555B1 EP06118134A EP06118134A EP1754555B1 EP 1754555 B1 EP1754555 B1 EP 1754555B1 EP 06118134 A EP06118134 A EP 06118134A EP 06118134 A EP06118134 A EP 06118134A EP 1754555 B1 EP1754555 B1 EP 1754555B1
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EP
European Patent Office
Prior art keywords
core
squealer
main
rod
shaped
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EP06118134A
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German (de)
French (fr)
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EP1754555A1 (en
Inventor
Didier Guerche
Jean-Claude Hanny
Serge Prigent
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • B22C9/103—Multipart cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
    • 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
    • B22C9/108—Installation of cores

Definitions

  • the present invention relates to the field of turbomachine blades, in particular the blades obtained by casting a molten alloy in a mold according to the lost wax casting technique.
  • the quest for increased engine performance includes more efficient cooling of the turbine blades immediately downstream of the combustion chamber. This requirement requires formation within these more elaborate internal cooling fluid flow cavity vanes. These blades have the particularity of having several metal walls and therefore require the manufacture of ceramic cores increasingly complex.
  • a finishing step is possibly necessary to eliminate and deburr the traces of joint planes and obtain the geometry of the core. Abrasive tools are used for this purpose. It may still be necessary to strengthen the core so that it is not damaged in subsequent cycles of use. In this case, the core is impregnated with an organic resin.
  • the model is dipped in slip to form a shell of ceramic material.
  • the wax is then removed to make way for a space in the shell mold, in which the alloy is cast. After casting and cooling of the metal, the shell mold is broken and the core removed to free the part.
  • the bath is the cavity at the apex of blade open radially outwardly.
  • FIG 1 which represents a hollow blade 1.
  • the blade is hollow and comprises at its top opposite the flat -form, a cavity that is designated by the term bath 5.
  • This bath 5 is delimited laterally by the wall of the blade and the bottom is formed of a wall 6 of bath floor, perpendicular to the radial axis of the blade.
  • This bottom wall that we see in section on the figure 2 is pierced with orifices 61 which communicate with the internal cavities of the blade to evacuate a portion of the cooling fluid thereof. This fluid is itself discharged into the hot gas stream by the clearance between the top and the annular surface of the stator.
  • the patent EP 1,543,896 shows the realization of a blade with tub by means of a foundry core having a main core with a shaped member to form the bath and a shaped member to form a plurality of cavities bath.
  • a ceramic core used in the manufacture by lost-wax casting of a turbomachine blade with internal cooling cavities and tub formed by the assembly of cores comprising at least one main core, with a shaped element to form the bath and a shaped element to form at least one cavity bath, the two elements between them a space shaped to form at least in part the bottom wall of the bath characterized by the fact the core comprises a secondary core under bath connected to the main core by at least one ceramic rod integral with said shaped element to form the bath.
  • the two elements, bath and bath are interconnected also by at least one ceramic rod.
  • These rods furthermore delimit, preferably, orifices for evacuating the cooling fluid through the bath.
  • the secondary core partially cleans with the under bath portions of the main core the space for the bath bottom wall.
  • the invention also relates to the method of manufacturing a core thus characterized, this method being able to be implemented according to several variants.
  • it comprises the following steps: manufacture of said main core, drilling of at least one hole in the element shaped to constitute the bath, setting up of the secondary core with the stem. More particularly, the drilling is carried out in the core before cooking thereof.
  • This main core 10 is, here, itself consisting of a plurality of elements separated from each other by spaces constituting the walls of the cooling cavities after casting of the metal.
  • a transverse element 10B extends over the entire width of the core 10 and is separated from the other elements 10SB by a transverse space 13.
  • the space 13 is perpendicular to the spaces 14 and its width corresponds to that of a wall of the blade after casting of the alloy.
  • the element 10B, between the space 13 and the top 10S, is shaped to provide the cavity of the blade which has been designated bath, in the description of the figure 1 representing the blade.
  • the space 13 bordering the element 10B is therefore intended to contain the metal forming, at least in part, the bottom wall 6 of the bath 5 that can be seen on the figure 2 .
  • the portion 10SB to the left of the space 13 in the figure is shaped to provide cavities under bath on the blade from the casting.
  • These elements are each connected to the tubular cross member 10B by a ceramic material rod TG1, TG2, TG3, TG4. These rods support the element 10B and maintain the space 13 open.
  • notches 11 and 12 are formed parallel to the axis XX, 11 and 12. These notches 11 and 12 are visible on the figure 4 . They can be obtained by machining the core before or after firing or at the injection stage of the core by forming the mold appropriately.
  • the main core is formed at the top by the element 10B which masks the elements 10SB1 to 10SB4 which are arranged on the underside of the blade and which are shown in dashed lines.
  • a space is provided between the elements 10SB of the main core and the extrados side of the blade.
  • a secondary core 100 is shown on the figure 5 . It is shaped so as to occupy part of the space that we see on the figure 4 by providing spaces 14, 14 'with the elements 10SB of the main core. These spaces 14 and 14 'form internal partitions to the blade after casting of the metal.
  • the figure 5 we see two rods 110 and 120. These rods are shaped so as to be housed in the notches 11 and 12 respectively.
  • the figure 6 shows the secondary core 100 in perspective, with the two rods stuck in the upper face.
  • the rods 110, 120 and the rods TG are made of ceramic material of oxide, nitride, carbide or a combination of these materials for example. It may be more particularly alumina, quartz or mullite.
  • the rods may have been put in place at the time of injection of the core to form a single piece. It is also possible to machine the housings in the core 100 after its formation.
  • the number of rods depends on the geometric constraints in particular or the mechanical strength of the assembly; there is at least one.
  • the figure 7 shows the assembled primary and secondary nuclei forming a multiple 1000.
  • the secondary core was placed here on the extrados side with respect to the main core.
  • the core delimits part of the space 13 by its face 100B ( figure 5 ) and the space 14 '( figure 4 ) with the elements under the 10SB bath of the main core 10.
  • the rods 110 and 120 are engaged in the notches 11 and 12 of the element 10B of the main core 10. After placing the rods, the notches are sealed by means of a ceramic adhesive comprising a mineral filler and a mineral binder. This is for example a mixture of zircon and colloidal silica or alumina and ethyl silicate or silica and ethyl silicate. Let it dry. The secondary core is thus retained only by its attachment to the element 103.
  • the nucleus thus prepared then undergoes the successive conventional operations leading to the manufacture of the blade: molding of the model, constitution of the shell and casting of the alloy. It is observed that this core leads to the formation of a bath bottom wall corresponding to the space 13.
  • the notches are replaced by holes forming housings 21 and 22.
  • the main core 20 has the same characteristics as the main core of the figure 3 . It has a tub bottom space 23, a portion 20B forming the tub cavity, elements 20SB1, 20SB2, 20SB3, 20SB4 parallel to the axis XX, the edges 20A, 20S, 20F.
  • the figure 9 which is a sectional view across the tub element 20B perpendicular to the axis XX of the assembled core shows the two holes in the part 20B. We also see the spaces 24 and 24 'between the various core elements to form the partitions after casting of the metal.
  • the figure 10 shows the 2000 core assembled with a secondary core 200 that we see alone on the figure 12 . The latter is anchored in the bath element 20B of the main core 20 by means of the rods 210 and 220 of ceramic material.
  • the core 200 is provided with two rods 210 and 220.
  • the core 2000 is assembled by guiding the rods in the holes 21 and 22 respectively and then holding them by gluing if necessary.
  • the core is ready for subsequent dawn manufacturing operations.
  • the assembly of the cores is represented in a simplified way, to bring out the principle of the invention; this is of course applicable to multiple nuclei consisting of a plurality of elementary nuclei or the like.

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

Description

La présente invention concerne le domaine des aubages de turbomachine, celui en particulier des aubages obtenus par coulée d'un alliage en fusion dans un moule selon la technique de fonderie à la cire perdue.The present invention relates to the field of turbomachine blades, in particular the blades obtained by casting a molten alloy in a mold according to the lost wax casting technique.

La recherche de performances accrues des moteurs implique notamment un refroidissement plus efficace des aubes de turbine situées immédiatement en aval de la chambre de combustion. Cette exigence nécessite la formation à l'intérieur de ces aubes de cavités internes de circulation du fluide de refroidissement plus élaborées. Ces aubes présentent la particularité d'avoir plusieurs parois métalliques et requièrent donc la fabrication de noyaux céramiques de plus en plus complexes.The quest for increased engine performance includes more efficient cooling of the turbine blades immediately downstream of the combustion chamber. This requirement requires formation within these more elaborate internal cooling fluid flow cavity vanes. These blades have the particularity of having several metal walls and therefore require the manufacture of ceramic cores increasingly complex.

La technique de fabrication de ce type d'aubage comprend donc une première étape de formation du noyau. Le noyau est composé d'une matière céramique à structure généralement poreuse et est réalisé à partir d'un mélange constitué d'une charge réfractaire sous forme de particules et d'une fraction organique plus ou moins complexe formant un liant. Des exemples de compositions sont donnés dans les brevets EP 328 452 , FR 2 371 257 ou FR 2 785 836 . Comme cela est connu, on met en forme le noyau de fonderie par moulage en utilisant par exemple une injection à la presse. Cette mise en forme est suivie d'une opération de déliantage au cours de laquelle la fraction organique du noyau est éliminée par un moyen tel que la sublimation ou la dégradation thermique, suivant les matériaux utilisés. Une structure poreuse en résulte. Le noyau est ensuite consolidé par un traitement thermique dans un four. Une étape de finition est éventuellement nécessaire pour éliminer et ébavurer les traces de plans de joint et obtenir la géométrie du noyau. On utilise dans ce but des outils abrasifs. Il peut être encore nécessaire de renforcer le noyau afin qu'il ne soit pas endommagé dans les cycles ultérieurs d'utilisation. On imprègne dans ce cas le noyau avec une résine organique.The technique of manufacturing this type of blading therefore comprises a first stage of formation of the core. The core is composed of a ceramic material with a generally porous structure and is made from a mixture consisting of a refractory filler in the form of particles and a more or less complex organic fraction forming a binder. Examples of compositions are given in patents EP 328,452 , FR 2,371,257 or FR 2 785 836 . As is known, the casting core is shaped by molding using for example a press injection. This shaping is followed by a debinding operation during which the organic fraction of the core is removed by a means such as sublimation or thermal degradation, depending on the materials used. A porous structure results. The core is then consolidated by heat treatment in an oven. A finishing step is possibly necessary to eliminate and deburr the traces of joint planes and obtain the geometry of the core. Abrasive tools are used for this purpose. It may still be necessary to strengthen the core so that it is not damaged in subsequent cycles of use. In this case, the core is impregnated with an organic resin.

On moule ensuite à partir du noyau, un modèle en cire ou autre matériau équivalent constituant la réplique de l'aubage à couler. Dans l'étape suivante de formation du moule de coulée de l'alliage, le modèle est trempé dans des barbotines pour constituer une carapace en matériau céramique. La cire est ensuite éliminée pour laisser la place à un espace dans le moule carapace, dans lequel l'alliage est coulé. Après coulée et refroidissement du métal, le moule carapace est brisé et le noyau éliminé pour libérer la pièce.Then mold from the core, a wax model or other equivalent material constituting the replica of the flow to cast. In the next step of forming the casting mold of the alloy, the model is dipped in slip to form a shell of ceramic material. The wax is then removed to make way for a space in the shell mold, in which the alloy is cast. After casting and cooling of the metal, the shell mold is broken and the core removed to free the part.

En raison de la complexité des cavités de refroidissement à former avec leurs cloisons de séparation, et de leur agencement, on réalise le noyau en plusieurs parties que l'on assemble et colle. Les noyaux élémentaires sont généralement liés entre eux au niveau du pied et du sommet. Il s'agit en effet de maîtriser l'épaisseur des parois et des cloisons formées au moment de la coulée. L'assemblage doit permettre au noyau de supporter les contraintes subies lors des étapes d'injection de la cire, de décirage puis de la coulée.Due to the complexity of the cooling cavities to be formed with their partition walls, and their arrangement, the core is made in several parts that are assembled and glued. Elemental nuclei are usually linked together at the foot and the summit. It is in fact to control the thickness of the walls and partitions formed at the time of casting. The assembly must allow the core to withstand the stresses experienced during the steps of wax injection, dewaxing and casting.

Les techniques actuelles connues du présent déposant ne permettent cependant pas d'obtenir la baignoire en sommet d'aube directement de fonderie.Current techniques known to the present applicant, however, do not allow to get the bathtub at the top of the dawn directly foundry.

On rappelle que la baignoire est la cavité en sommet d'aube ouverte radialement vers l'extérieur. On en voit un exemple sur la figure 1 qui représente une aube creuse 1. On distingue le pied 2 de l'aube par lequel elle est montée sur un rotor de turbine, la plate-forme 3 et la pale 4. La pale est creuse et comprend en son sommet opposé à la plate-forme, une cavité que l'on désigne par le terme de baignoire 5. Cette baignoire 5 est délimitée latéralement par la paroi de la pale et le fond est formé d'une paroi 6 de fond de baignoire, perpendiculaire à l'axe radial de la pale. Cette paroi de fond que l'on voit en coupe sur la figure 2 est percée d'orifices 61 qui communiquent avec les cavités internes de la pale pour évacuer une partie du fluide de refroidissement de cette dernière. Ce fluide est lui même évacué dans la veine de gaz chaud par le jeu existant entre le sommet et la surface annulaire du stator.It is recalled that the bath is the cavity at the apex of blade open radially outwardly. We see an example on the figure 1 which represents a hollow blade 1. We distinguish the foot 2 of the blade by which it is mounted on a turbine rotor, the platform 3 and the blade 4. The blade is hollow and comprises at its top opposite the flat -form, a cavity that is designated by the term bath 5. This bath 5 is delimited laterally by the wall of the blade and the bottom is formed of a wall 6 of bath floor, perpendicular to the radial axis of the blade. This bottom wall that we see in section on the figure 2 is pierced with orifices 61 which communicate with the internal cavities of the blade to evacuate a portion of the cooling fluid thereof. This fluid is itself discharged into the hot gas stream by the clearance between the top and the annular surface of the stator.

Généralement, on réalise l'aube creuse avec ses cavités par fonderie selon la méthode présentée ci-dessus mais sans paroi de fond de baignoire. La paroi est rapportée sous la forme d'une plaquette sur l'aube venant de fonderie, et fixée par brasage. Cette opération est longue et coûteuse.Generally, the hollow dawn is made with its cavities by foundry according to the method presented above but without a bath bottom wall. The wall is reported in the form of a wafer on the dawn coming from foundry, and fixed by brazing. This operation is long and expensive.

Le brevet EP 1 543 896 montre la réalisation d'une aube avec baignoire au moyen d'un noyau de fonderie comportant un noyau principal avec un élément conformé pour constituer la baignoire et un élément conformé de manière à constituer une pluralité de cavités sous baignoire.The patent EP 1,543,896 shows the realization of a blade with tub by means of a foundry core having a main core with a shaped member to form the bath and a shaped member to form a plurality of cavities bath.

On réalise ainsi cette paroi de fond de manière industrielle avec l'opération de fonderie sans avoir à passer par l'opération de brasage.This bottom wall is thus produced industrially with the foundry operation without having to go through the brazing operation.

L'invention vise à améliorer ce type de montage de noyau pour des structures complexes.The aim of the invention is to improve this type of core assembly for complex structures.

On parvient à réaliser cet objectif conformément à l'invention avec un noyau céramique utilisé dans la fabrication par fonderie à la cire perdue d'une aube de turbomachine avec cavités internes de refroidissement et baignoire, formé par l'assemblage de noyaux comprenant au moins un noyau principal, avec un élément conformé pour constituer la baignoire et un élément conformé pour constituer au moins une cavité sous baignoire, les deux éléments ménageant entre eux un espace conformé pour constituer au moins en partie la paroi de fond de la baignoire caractérisé par le fait que le noyau comprend un noyau secondaire sous baignoire relié au noyau principal par au moins une tige céramique solidaire dudit élément conformé pour constituer la baignoire. De préférence les deux éléments, de baignoire et sous baignoire, sont reliés entre eux également par au moins une tige céramique.It is possible to achieve this objective in accordance with the invention with a ceramic core used in the manufacture by lost-wax casting of a turbomachine blade with internal cooling cavities and tub, formed by the assembly of cores comprising at least one main core, with a shaped element to form the bath and a shaped element to form at least one cavity bath, the two elements between them a space shaped to form at least in part the bottom wall of the bath characterized by the fact the core comprises a secondary core under bath connected to the main core by at least one ceramic rod integral with said shaped element to form the bath. Preferably the two elements, bath and bath, are interconnected also by at least one ceramic rod.

En fixant le noyau secondaire à l'élément conformé pour constituer la baignoire, on permet ainsi un positionnement relatif précis des éléments de noyaux assemblés qui soit reproductible de manière industrielle. Ces tiges délimitent en outre, de préférence, des orifices d'évacuation du fluide de refroidissement à travers la baignoire.By securing the secondary core to the shaped member to form the bath, accurate relative positioning of the assembled core members which is industrially reproducible is thus allowed. These rods furthermore delimit, preferably, orifices for evacuating the cooling fluid through the bath.

Plus particulièrement, le noyau secondaire ménage en partie avec les parties sous baignoires du noyau principal l'espace pour la paroi de fond de baignoire.More particularly, the secondary core partially cleans with the under bath portions of the main core the space for the bath bottom wall.

L'invention porte également sur le procédé de fabrication d'un noyau ainsi caractérisé, ce procédé pouvant être mis en oeuvre selon plusieurs variantes.The invention also relates to the method of manufacturing a core thus characterized, this method being able to be implemented according to several variants.

Selon un premier mode de fabrication d'un noyau avec noyau secondaire, le procédé comprend les étapes suivantes : fabrication dudit noyau principal, formation d'au moins une encoche dans l'élément conformé pour constituer la baignoire, mise en place du noyau secondaire avec la tige, colmatage de l'encoche. Plus particulièrement l'encoche peut être formée sur le noyau avant cuisson de celui-ci.According to a first method of manufacturing a nucleus with a secondary core, the method comprises the following steps: manufacturing of said main core, formation of at least one notch in the element shaped to constitute the bath, setting up of the secondary core with the stem, clogging the notch. More particularly, the notch may be formed on the core before cooking thereof.

Selon une variante, il comprend les étapes suivantes : fabrication dudit noyau principal, perçage d'au moins un trou dans l'élément conformé pour constituer la baignoire, mise en place du noyau secondaire avec la tige. Plus particulièrement, le perçage est effectué dans le noyau avant cuisson de celui-ci.According to a variant, it comprises the following steps: manufacture of said main core, drilling of at least one hole in the element shaped to constitute the bath, setting up of the secondary core with the stem. More particularly, the drilling is carried out in the core before cooking thereof.

Selon une autre variante, le noyau secondaire étant percé d'un logement pour la tige, le noyau secondaire est mis en position sans la tige puis la tige mise en place dans son logement.According to another variant, the secondary core being pierced with a housing for the rod, the secondary core is placed in position without the rod and the rod placed in place in its housing.

D'autres caractéristiques et avantages apparaîtront à la lecture de la description qui suit de deux modes de réalisation de l'invention, en référence aux dessins annexés sur lesquels :

  • La figure 1 représente en perspective une aube creuse, mobile, de turbine dont on voit la baignoire ;
  • La figure 2 est une vue en coupe selon II-II à travers la baignoire de la pale de figure 1 ;
  • La figure 3 représente de façon schématique et vu partiellement le long de sa hauteur dans sa plus grande largeur, un noyau principal conforme à l'invention ;
  • La figure 4 est une vue du noyau de la figure 7 selon la coupe AA ;
  • La figure 5 représente de façon schématique, vu partiellement le long de sa hauteur un noyau secondaire conformé de façon à coopérer avec le noyau principal de la figure 3 pour constituer un noyau conforme à l'invention ;
  • La figure 6 représente le noyau secondaire de la figure 5, vu en perspective ;
  • La figure 7 représente les noyaux des figures 3 et 5 après assemblage ;
  • La figure 8 représente de façon schématique une vue partielle le long de sa hauteur et dans le sens de sa plus grande largeur, un noyau principal selon une variante de réalisation ;
  • La figure 9 est une vue du noyau de la figure 10 selon la coupe BB ;
  • La figure 10 représente l'assemblage du noyau principal de la variante de la figure 8 avec un noyau secondaire ;
  • La figure 11 montre une variante de forme du noyau secondaire selon l'invention ;
  • La figure 12 représente de façon schématique, vu partiellement le long de sa hauteur, un noyau secondaire conformé de façon à coopérer avec le noyau principal de la figure 8 pour constituer un noyau selon l'invention.
Other characteristics and advantages will appear on reading the following description of two embodiments of the invention, with reference to the appended drawings in which:
  • The figure 1 represents in perspective a hollow, mobile dawn, turbine whose bath is seen;
  • The figure 2 is a sectional view along II-II through the bathtub of the blade of figure 1 ;
  • The figure 3 schematically shows and partially seen along its height in its greater width, a main core according to the invention;
  • The figure 4 is a view of the core of the figure 7 according to section AA;
  • The figure 5 represents schematically, partially seen along its height a secondary core shaped to cooperate with the main core of the figure 3 to form a core according to the invention;
  • The figure 6 represents the secondary nucleus of the figure 5 , seen in perspective;
  • The figure 7 represents the nuclei of Figures 3 and 5 after assembly;
  • The figure 8 schematically shows a partial view along its height and in the direction of its greater width, a main core according to an alternative embodiment;
  • The figure 9 is a view of the core of the figure 10 according to section BB;
  • The figure 10 represents the assembly of the main core of the variant of the figure 8 with a secondary nucleus;
  • The figure 11 shows a variant form of the secondary core according to the invention;
  • The figure 12 shows schematically, partially seen along its height, a secondary core shaped to cooperate with the main core of the figure 8 to form a core according to the invention.

En se reportant à la figure 3, on voit, selon l'axe principal XX de l'aube, la partie d'un noyau principal correspondant à la portion supérieure de la pale, le sommet étant à droite sur la figure. Le reste du noyau vers la gauche correspondant à la portion de l'aube avec le pied et la plate-forme n'est pas visible. Ce noyau principal est par exemple le noyau côté intrados d'un noyau multiple. Un noyau multiple permet la réalisation d'aubes creuses à cavités multiples séparées par des cloisons et dans lesquelles circule un fluide refroidissement. Pour ce dernier, il s'agit de l'air prélevé au compresseur, notamment, dans un moteur à turbine à gaz. La figure 4 montre un exemple de profil général de ce noyau principal.Referring to the figure 3 , we see, along the main axis XX of the blade, the portion of a main core corresponding to the upper portion of the blade, the top being on the right in the figure. The rest of the nucleus to the left corresponding to the portion of the dawn with the foot and the platform is not visible. This main core is, for example, the intrados-side core of a multiple core. A multiple core allows the realization of hollow vanes with multiple cavities separated by partitions and in which circulates a cooling fluid. For the latter, it is the air taken from the compressor, in particular in a gas turbine engine. The figure 4 shows an example of a general profile of this main kernel.

Ce noyau principal 10 est, ici, lui-même constitué d'une pluralité d'éléments séparés les uns des autres par des espaces constituant les parois des cavités de refroidissement après coulée du métal. Sur la figure schématique 3, on distingue un bord antérieur 10A du côté du bord d'attaque de la pale, un bord arrière du côté du bord de fuite de la pale et une face de sommet 10S. Il comprend les éléments 10SB1, 10SB2, 10SB3 et 10SB4 le long de son axe.This main core 10 is, here, itself consisting of a plurality of elements separated from each other by spaces constituting the walls of the cooling cavities after casting of the metal. In the schematic figure 3, there is an anterior edge 10A on the side of the leading edge of the blade, a rear edge on the side of the trailing edge of the blade and a top face 10S. It includes the elements 10SB1, 10SB2, 10SB3 and 10SB4 along its axis.

Ces éléments sont séparés par des espaces 14 définis. Un élément 10B transversal s'étend sur toute la largeur du noyau 10 et est séparé des autres éléments 10SB par un espace transversal 13. L'espace 13 est perpendiculaire aux espaces 14 et sa largeur correspond à celle d'une paroi de la pale après coulée de l'alliage. L'élément 10B, entre l'espace 13 et le sommet 10S, est conformé de manière à ménager la cavité de la pale que l'on a désignée baignoire, dans la description de la figure 1 représentant la pale. L'espace 13 bordant l'élément 10B est donc destiné à contenir le métal formant, au moins en partie, la paroi 6 de fond de baignoire 5 que l'on voit sur la figure 2.These elements are separated by defined spaces 14. A transverse element 10B extends over the entire width of the core 10 and is separated from the other elements 10SB by a transverse space 13. The space 13 is perpendicular to the spaces 14 and its width corresponds to that of a wall of the blade after casting of the alloy. The element 10B, between the space 13 and the top 10S, is shaped to provide the cavity of the blade which has been designated bath, in the description of the figure 1 representing the blade. The space 13 bordering the element 10B is therefore intended to contain the metal forming, at least in part, the bottom wall 6 of the bath 5 that can be seen on the figure 2 .

La partie 10SB à gauche de l'espace 13 sur la figure est conformée de manière à ménager des cavités sous baignoire sur l'aube issue de la coulée. Dans le mode de réalisation représenté, on a quatre éléments 10SB1, 10SB2, 10SB3, 10SB4, chacun donnant lieu à la formation d'une cavité sous baignoire. Ces éléments sont reliés chacun à l'élément transversal 10B de baignoire par une tige en matériau céramique TG1, TG2, TG3, TG4. Ces tiges supportent l'élément 10B et maintiennent l'espace 13 ouvert.The portion 10SB to the left of the space 13 in the figure is shaped to provide cavities under bath on the blade from the casting. In the embodiment shown, there are four elements 10SB1, 10SB2, 10SB3, 10SB4, each giving rise to the formation of a cavity under bath. These elements are each connected to the tubular cross member 10B by a ceramic material rod TG1, TG2, TG3, TG4. These rods support the element 10B and maintain the space 13 open.

Dans l'élément 10B on a formé deux encoches parallèles à l'axe XX, 11 et 12. Ces encoches 11 et 12 sont visibles sur la figure 4. Elles peuvent être obtenues par usinage du noyau avant ou après sa cuisson ou bien dès l'étape d'injection du noyau en conformant le moule de façon appropriée.In the element 10B two notches are formed parallel to the axis XX, 11 and 12. These notches 11 and 12 are visible on the figure 4 . They can be obtained by machining the core before or after firing or at the injection stage of the core by forming the mold appropriately.

On observe sur la figure 4 que le noyau principal est formé au sommet par l'élément 10B qui masque les éléments 10SB1 à 10SB4 qui sont disposés du côté intrados de la pale et qui sont représentés en pointillés. Un espace est ménagé entre les éléments 10SB du noyau principal et le côté extrados de l'aube.We observe on the figure 4 that the main core is formed at the top by the element 10B which masks the elements 10SB1 to 10SB4 which are arranged on the underside of the blade and which are shown in dashed lines. A space is provided between the elements 10SB of the main core and the extrados side of the blade.

Un noyau secondaire 100 est montré sur la figure 5. Il est conformé de manière à venir occuper en partie l'espace que l'on voit sur la figure 4 en ménageant des espaces 14, 14' avec les éléments 10SB du noyau principal. Ces espaces 14 et 14' forment des cloisons intérieures à la pale après coulée du métal.A secondary core 100 is shown on the figure 5 . It is shaped so as to occupy part of the space that we see on the figure 4 by providing spaces 14, 14 'with the elements 10SB of the main core. These spaces 14 and 14 'form internal partitions to the blade after casting of the metal.

Sur la figure 5, on voit deux tiges 110 et 120. Ces tiges sont conformées de manière à pouvoir venir se loger dans les encoches 11 et 12 respectivement. La figure 6 montre le noyau secondaire 100 en perspective, avec les deux tiges fichées dans la face supérieure. Les tiges 110, 120 ainsi que les tiges TG sont en matériau céramique de type oxyde, nitrure, carbure ou une combinaison de ces matériaux par exemple. Il peut s'agir plus particulièrement d'alumine, de quartz ou de mullite. Les tiges peuvent avoir été mises en place au moment de l'injection du noyau de manière à former une seule pièce. Il est possible aussi d'usiner les logements dans le noyau 100 après sa formation. Le nombre de tiges dépend des contraintes géométriques notamment ou bien de tenue mécanique de l'ensemble ; il y en a au moins une.On the figure 5 , we see two rods 110 and 120. These rods are shaped so as to be housed in the notches 11 and 12 respectively. The figure 6 shows the secondary core 100 in perspective, with the two rods stuck in the upper face. The rods 110, 120 and the rods TG are made of ceramic material of oxide, nitride, carbide or a combination of these materials for example. It may be more particularly alumina, quartz or mullite. The rods may have been put in place at the time of injection of the core to form a single piece. It is also possible to machine the housings in the core 100 after its formation. The number of rods depends on the geometric constraints in particular or the mechanical strength of the assembly; there is at least one.

La figure 7 montre les noyaux principal et secondaire assemblés formant un multiple 1000. On a placé ici le noyau secondaire du côté extrados par rapport au noyau principal. Le noyau délimite une partie de l'espace 13 par sa face 100B (figure 5) et l'espace 14' (figure 4) avec les éléments sous baignoire 10SB du noyau principal 10.The figure 7 shows the assembled primary and secondary nuclei forming a multiple 1000. The secondary core was placed here on the extrados side with respect to the main core. The core delimits part of the space 13 by its face 100B ( figure 5 ) and the space 14 '( figure 4 ) with the elements under the 10SB bath of the main core 10.

Les tiges 110 et 120 sont engagées dans les encoches 11 et 12 de l'élément 10B du noyau principal 10. Après mise en place des tiges, on colmate les encoches au moyen d'une colle céramique comprenant une charge minérale et un liant minéral. Il s'agit par exemple d'un mélange de zircon et de silice colloïdale ou bien d'alumine et de silicate d'éthyle ou encore de silice et de silicate d'éthyle. On laisse sécher. Le noyau secondaire est donc retenu seulement par son attache à l'élément 103.The rods 110 and 120 are engaged in the notches 11 and 12 of the element 10B of the main core 10. After placing the rods, the notches are sealed by means of a ceramic adhesive comprising a mineral filler and a mineral binder. This is for example a mixture of zircon and colloidal silica or alumina and ethyl silicate or silica and ethyl silicate. Let it dry. The secondary core is thus retained only by its attachment to the element 103.

Le noyau ainsi préparé subit ensuite les opérations successives conventionnelles conduisant à la fabrication de l'aube : moulage du modèle, constitution de la carapace et coulée de l'alliage. On observe que ce noyau conduit à la formation d'une paroi de fond de baignoire correspondant à l'espace 13.The nucleus thus prepared then undergoes the successive conventional operations leading to the manufacture of the blade: molding of the model, constitution of the shell and casting of the alloy. It is observed that this core leads to the formation of a bath bottom wall corresponding to the space 13.

Selon la variante représentée sur les figures 8 et 10, on remplace les encoches par des trous formant des logements 21 et 22. A part les logements 21 et 22, le noyau principal 20 présente les mêmes caractéristiques que le noyau principal de la figure 3. Il présente un espace 23 de fond de baignoire, une partie 20B formant la cavité de baignoire, des éléments 20SB1, 20SB2, 20SB3, 20SB4 parallèles à l'axe XX, les bords 20A, 20S, 20F.According to the variant represented on the Figures 8 and 10 the notches are replaced by holes forming housings 21 and 22. Apart from the housings 21 and 22, the main core 20 has the same characteristics as the main core of the figure 3 . It has a tub bottom space 23, a portion 20B forming the tub cavity, elements 20SB1, 20SB2, 20SB3, 20SB4 parallel to the axis XX, the edges 20A, 20S, 20F.

La figure 9 qui est une vue en coupe en travers de l'élément de baignoire 20B perpendiculaire à l'axe XX du noyau assemblé montre les deux trous ménagés dans la partie 20B. On voit aussi les espaces 24 et 24' entre les différents éléments de noyau pour constituer les cloisons après coulée du métal. La figure 10 montre le noyau 2000 assemblé avec un noyau secondaire 200 que l'on voit seul sur la figure 12. Ce dernier est ancré dans l'élément 20B de baignoire du noyau principal 20 au moyen des tiges 210 et 220 en matériau céramique.The figure 9 which is a sectional view across the tub element 20B perpendicular to the axis XX of the assembled core shows the two holes in the part 20B. We also see the spaces 24 and 24 'between the various core elements to form the partitions after casting of the metal. The figure 10 shows the 2000 core assembled with a secondary core 200 that we see alone on the figure 12 . The latter is anchored in the bath element 20B of the main core 20 by means of the rods 210 and 220 of ceramic material.

Comme dans le cas précédent, le noyau 200 est pourvu des deux tiges 210 et 220. On assemble le noyau 2000 en guidant les tiges dans les trous 21 et 22 respectivement puis en les maintenant par collage le cas échéant.As in the previous case, the core 200 is provided with two rods 210 and 220. The core 2000 is assembled by guiding the rods in the holes 21 and 22 respectively and then holding them by gluing if necessary.

Lorsque la géométrie est complexe, par exemple avec un noyau secondaire 300 tel que représenté sur la figure 11, et ne permet pas un montage du noyau 200 pré-assemblé avec les deux tiges, on procède différemment.When the geometry is complex, for example with a secondary core 300 as shown in FIG. figure 11 , and does not allow a mounting of the core 200 pre-assembled with the two rods, it proceeds differently.

Dans ce cas le noyau secondaire 300 est percé de deux trous 310 et 320. On présente le noyau secondaire parallèlement aux éléments 20SB du noyau principal de telle manière que les trous 310 et 320 viennent en face des trous 21 et 22. On glisse ensuite les tiges dans les trous 21 et 310 d'une part et dans les trous 22 et 320 d'autre part.In this case the secondary core 300 is pierced with two holes 310 and 320. The secondary core is presented parallel to the elements 20SB of the main core so that the holes 310 and 320 come in front of the holes 21 and 22. rods in the holes 21 and 310 on the one hand and in the holes 22 and 320 on the other hand.

Le noyau est prêt pour les opérations ultérieures de fabrication de l'aube.The core is ready for subsequent dawn manufacturing operations.

On a représenté l'assemblage des noyaux de façon simplifiée, pour faire ressortir le principe de l'invention ; celui-ci est bien sûr applicable aux noyaux multiples constitués d'une pluralité de noyaux élémentaires ou autre.The assembly of the cores is represented in a simplified way, to bring out the principle of the invention; this is of course applicable to multiple nuclei consisting of a plurality of elementary nuclei or the like.

Claims (11)

  1. A ceramic core used in the manufacture, by lost wax casting, of a turbomachine blade with cooling cavities and a squealer, comprising at least a main core (10 ; 20), wherein the main core comprises an element (10B ; 20B) shaped so as to constitute the squealer and an element (10SB ; 20SB) shaped so as to constitute at least one cavity beneath the squealer, the two elements leaving between them a space (13 ; 23) shaped so as to constitute, at least in part, the bottom wall of the squealer characterized by the fact the core includes a secondary core (100, 200) beneath the squealer, joined by at least one ceramic rod (110, 120 ; 210, 220) fastened to said element (10B ; 20B) forming the squealer.
  2. The core as claimed in the preceding claim, the two elements (10B et 10SB) of which are joined together by at least one ceramic rod (TG1 à TG4).
  3. The core as claimed in claim 1 or 2, the main core (10 ; 20) of which comprises at least two main elementary cores below the squealer (10SB1, 10SB2, 10SB3, 10SB4), each joined to the element (10B) of the main core (10 ; 20) forming the squealer.
  4. The core as claimed in claim 2 or 3, the secondary core (100) of which makes, partly with the main core (10 ; 20), the squealer bottom wall (13 ; 23).
  5. The core as claimed in one of claims 2 to 4, the ceramic rod (TG, 110, 120 ; 210, 220) of which defines, on the squealer bottom wall of the blade, an orifice for discharge of the cooling fluid.
  6. A method of manufacturing a core as claimed in one of claims 3 to 5, which comprises the following steps: manufacture of said main core (10); formation of at least one notch in the element shaped (10SB) so as to constitute the squealer; fitting of the secondary core with the rod; and plugging of the notch.
  7. The method as claimed in the preceding claim, the notch (11, 12) of which is formed on the core (10) before or after the latter is fired.
  8. The method of manufacturing a core as claimed in one of claims 1 to 5, which comprises the following steps: manufacture of said main core (20); drilling of at least one hole in the element shaped so as to constitute the squealer; and fitting of the secondary core with the rod.
  9. The method as claimed in the preceding claim, in which drilling is carried out in the main core (20) before or after the latter is fired.
  10. The method as claimed in claim 8, in which, when the secondary core (200) is drilled so as to form a housing for the rod (210, 220), the secondary core (200) is positioned without the rod (210, 220) and then the rod (210, 220) is fitted into its housing.
  11. The use of a core as claimed in one of claims 1 to 5 for the manufacture of a hollow turbomachine blade.
EP06118134A 2005-07-29 2006-07-28 Core for turbine blade Active EP1754555B1 (en)

Applications Claiming Priority (1)

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FR0508154A FR2889088B1 (en) 2005-07-29 2005-07-29 CORE FOR BLADE OF TURBOMACHINE

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EP1754555A1 EP1754555A1 (en) 2007-02-21
EP1754555B1 true EP1754555B1 (en) 2009-12-16

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US (1) US7562691B2 (en)
EP (1) EP1754555B1 (en)
DE (1) DE602006011089D1 (en)
FR (1) FR2889088B1 (en)
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RU (1) RU2404012C2 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984880A1 (en) * 2011-12-23 2013-06-28 Snecma METHOD FOR MANUFACTURING A CERAMIC CORE FOR MOBILE DREAM, CERAMIC CORE, MOBILE AUB
WO2013167847A2 (en) 2012-05-11 2013-11-14 Snecma Tool for manufacturing a foundry core for a turbine engine blade
RU2706256C2 (en) * 2014-12-17 2019-11-15 Сафран Эркрафт Энджинз Method of making gas turbine engine blade comprising vertex with complex cavity

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2923524B1 (en) * 2007-11-12 2013-12-06 Snecma MOLDED METALLIC BLADE AND METHOD OF FABRICATING THE BLADE
US20110204205A1 (en) * 2010-02-25 2011-08-25 Ahmed Kamel Casting core for turbine engine components and method of making the same
FR2957828B1 (en) * 2010-03-26 2012-10-05 Snecma EXTRACTION OF ALUMINA RODS USED TO MAINTAIN CORE DURING THE MANUFACTURE OF TURBINE BLADES.
FR2986982B1 (en) * 2012-02-22 2024-07-05 Snecma FOUNDRY CORE ASSEMBLY FOR THE MANUFACTURE OF A TURBOMACHINE BLADE, METHOD FOR MANUFACTURING A BLADE AND ASSOCIATED BLADE
CN102672102B (en) * 2012-05-04 2013-07-10 中国科学院金属研究所 Preparation method of plane thin-wall casting
US20140182809A1 (en) * 2012-12-28 2014-07-03 United Technologies Corporation Mullite-containing investment casting core
FR3000910B1 (en) * 2013-01-17 2015-05-01 Snecma PROCESS FOR MANUFACTURING A PIECE BY LOST WAX FOUNDRY AND DIRECTED COOLING
FR3023197B1 (en) * 2014-07-04 2021-07-30 Snecma PROCESS FOR MOLDING A CERAMIC TUB DAWN
FR3037829B1 (en) * 2015-06-29 2017-07-21 Snecma CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUSISHING HOLE THROUGH A CAVITY PARTLY
US10344597B2 (en) * 2015-08-17 2019-07-09 United Technologies Corporation Cupped contour for gas turbine engine blade assembly
FR3047767B1 (en) * 2016-02-12 2019-05-31 Safran METHOD FOR FORMING DEDUSTING HOLES FOR TURBINE BLADE AND CERAMIC CORE THEREFOR
FR3048374B1 (en) * 2016-03-01 2018-04-06 Snecma CORE FOR MOLDING A DAWN WITH SUPERIOR CAVITIES AND COMPRISING A DEDUSTING LINE CONDUCTING A CAVITY FROM PART TO SHARE
RU2660554C1 (en) * 2017-07-21 2018-07-06 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Method for producing foundry cores for cooled blade casting
RU2662514C1 (en) * 2017-08-07 2018-07-26 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Mixture for manufacture of foundry ceramic rods of hollow shovels from heat-resistant alloys by molding on floating models
RU2691435C1 (en) * 2018-07-23 2019-06-13 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Mixture for making cast ceramic rods of hollow blades from heat-resistant alloys by casting on molten casts
US10987727B2 (en) 2018-12-05 2021-04-27 Raytheon Technologies Corporation Investment casting core system
FR3100143B1 (en) * 2019-08-30 2021-11-12 Safran Improved method of manufacturing a ceramic core for the manufacture of turbine engine blades
US11773726B2 (en) 2019-10-16 2023-10-03 Rtx Corporation Angled tip rods
US11143035B2 (en) 2019-10-16 2021-10-12 Raytheon Technologies Corporation Angled tip rods
CN111957888A (en) * 2020-07-08 2020-11-20 中国航发北京航空材料研究院 Manufacturing method of free end of turbine blade core
FR3113255B1 (en) 2020-08-06 2022-10-07 Safran Protection against oxidation or corrosion of a hollow superalloy part
FR3113254B1 (en) 2020-08-06 2022-11-25 Safran Protection against oxidation or corrosion of a hollow superalloy part
FR3120807B1 (en) * 2021-03-16 2023-12-01 Safran Aircraft Engines Lost wax casting manufacturing process

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5599166A (en) * 1994-11-01 1997-02-04 United Technologies Corporation Core for fabrication of gas turbine engine airfoils
US5853044A (en) * 1996-04-24 1998-12-29 Pcc Airfoils, Inc. Method of casting an article
US5820774A (en) * 1996-10-28 1998-10-13 United Technologies Corporation Ceramic core for casting a turbine blade
US6637500B2 (en) * 2001-10-24 2003-10-28 United Technologies Corporation Cores for use in precision investment casting
US6915840B2 (en) * 2002-12-17 2005-07-12 General Electric Company Methods and apparatus for fabricating turbine engine airfoils
US6929054B2 (en) * 2003-12-19 2005-08-16 United Technologies Corporation Investment casting cores
US7216694B2 (en) * 2004-01-23 2007-05-15 United Technologies Corporation Apparatus and method for reducing operating stress in a turbine blade and the like

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984880A1 (en) * 2011-12-23 2013-06-28 Snecma METHOD FOR MANUFACTURING A CERAMIC CORE FOR MOBILE DREAM, CERAMIC CORE, MOBILE AUB
WO2013093352A3 (en) * 2011-12-23 2013-08-29 Snecma Method of manufacturing a ceramic core for a blade, ceramic core and blade
WO2013167847A2 (en) 2012-05-11 2013-11-14 Snecma Tool for manufacturing a foundry core for a turbine engine blade
RU2706256C2 (en) * 2014-12-17 2019-11-15 Сафран Эркрафт Энджинз Method of making gas turbine engine blade comprising vertex with complex cavity

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RU2404012C2 (en) 2010-11-20
IL177135A (en) 2010-05-17
DE602006011089D1 (en) 2010-01-28
US7562691B2 (en) 2009-07-21
FR2889088B1 (en) 2008-08-22
US20070025851A1 (en) 2007-02-01
RU2006127773A (en) 2008-02-10
IL177135A0 (en) 2006-12-10
EP1754555A1 (en) 2007-02-21
FR2889088A1 (en) 2007-02-02

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