EP2817114A1 - Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade - Google Patents

Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade

Info

Publication number
EP2817114A1
EP2817114A1 EP13704418.6A EP13704418A EP2817114A1 EP 2817114 A1 EP2817114 A1 EP 2817114A1 EP 13704418 A EP13704418 A EP 13704418A EP 2817114 A1 EP2817114 A1 EP 2817114A1
Authority
EP
European Patent Office
Prior art keywords
cavity
core
blade
leading edge
trailing edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13704418.6A
Other languages
German (de)
French (fr)
Other versions
EP2817114B1 (en
Inventor
Huu-Thanh Tran
Michael HANSOM
Christian Bariaud
Patrice Eneau
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
Original Assignee
SNECMA Services SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2817114A1 publication Critical patent/EP2817114A1/en
Application granted granted Critical
Publication of EP2817114B1 publication Critical patent/EP2817114B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • 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
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting

Definitions

  • Foundry core assembly for the manufacture of a turbomachine blade, method of manufacturing a blade and associated blades
  • the invention relates generally to the field of turbomachines, and more particularly to the turbine blades of these turbomachines and their manufacture.
  • the turbine blades are subjected to high thermal stresses due to the heat of the gases in which they are immersed at the outlet of the combustion chamber, and need to be cooled to withstand these temperatures. They are therefore hollow and traversed by internal cavities in which circulates a cooling gas taken from the output of a stage of a compressor.
  • a turbine blade of a turbomachine comprises an aerodynamic surface (or blade) extending between a blade root and a blade head.
  • the blade has a leading edge disposed opposite the flow of the hot gases from the combustion chamber of the turbomachine, and a trailing edge opposite the leading edge and side walls intrados and extrados which connect the leading edge at the trailing edge.
  • the internal cavities extend over the height of the blade, and comprise, upstream to downstream in the flow direction of the combustion chamber gases, a leading edge cavity and an edge cavity. leak, adjacent to the leading edge and the trailing edge of the blade respectively, and at least one central cavity, extending between the leading edge cavity and the trailing edge cavity. These cavities are supplied with cooling gas by pipes connecting them to the foot of the dawn.
  • the dawn further comprises, at the level of its head, a hollow form or bathtub, which is defined by the extension of the intrados and extrados walls, as well as by a bottom wall which closes the internal cavities.
  • the blades are conventionally produced by a technique known as lost wax foundry.
  • This technique schematically consists of making a wax dawn blank in which are drowned ceramic cores which reproduce the cavities to come. The dawn wax is then embedded in a shell, for example refractory material, then the cores are removed chemically, leaving in their place the desired internal and bathtub cavities. Implementations of this method are in particular described in documents FR 2 875 425, FR 2 874 186, or FR 2 957 828 in the name of the Applicant,
  • the cores for these modern turbine blades are constituted by cavity internal cores, conventionally having the form of columns, which are positioned side by side and held together by conventional means.
  • a core generally comprises a first core member for forming the cavities and a second core member for forming the tub, the second core member being connected to the first core member by alumina or quartz connecting rods.
  • These rods are intended to maintain the parts of the core between them and to stiffen the assembly thus formed, as well as to participate in the realization of dusting holes in the upper part of the blade, These rods are stuck in the holes that they are intended to generate in the bottom of the bath.
  • the dedusting holes allow the circulation of the cooling gas in the cavities and the evacuation of various particles entering the turbomachine.
  • Such turbine blades are adapted to minimize energy losses. They include a blade that can be broken down into stacked blade sections in a stacking direction along the blade. In the case of the blade head with offset head sections, the stack of sections at the head of the blade is shifted towards the intrados wall, preferably progressively.
  • the blade may comprise a cavity at its head, open towards its free end and delimited by the bottom wall and a flange which s' extends between the leading edge and the trailing edge.
  • the stacking of blade sections of the blade at this rim then has an offset in the direction of the underside, this offset being more and more important when approaching the free end of the head of the blade. 'dawn. The dawn also includes cooling channels, inclined relative to the intrados, and connecting the internal cavities to the intrados wall.
  • the intrados wall of the blade may further have a projecting portion, the outer face is inclined relative to the remainder of the intrados of the blade and has at its end, facing the rim, an end face.
  • the bottom wall is then connected to the intrados wall at the end face of the projecting portion, and the cooling channels can be arranged in the projecting portion of the intrados wall so that they open out. on the end face of the protruding portion, the distance between the axis of the cooling channels and the outer limit of the free end of the intrados side edge being greater than zero.
  • the invention proposes a core assembly for the manufacture of a turbomachine blade cooled by circulation of fluid in internal cavities, comprising a first elongate core element for the formation of different internal cavities and a second element core for forming a bath cavity, the second core member being adapted to be disposed in the extension of the first core member.
  • the first core element comprises an internal leading edge cavity core, at least one central cavity inner core and an internal trailing edge cavity core for respectively forming, upstream to downstream in the direction of a gas flow in the turbine, a leading edge cavity, at least one central cavity and a trailing edge cavity of the blade.
  • the core of the central internal cavity adjacent to the inner core of the trailing edge cavity has, in the immediate vicinity of the second core member, a bulge extending in the direction of the core of the leading edge cavity.
  • Such a solution makes it possible to anchor at least one connecting rod at an enlarged zone of the first core element (at the level of the bulge), and consequently to make turbine blades for turbomachines having a slice offset. head in a reliable process with a low kernel scrap rate.
  • the invention also relates to a blade obtained by means of such a foundry core assembly, and a manufacturing method using such a set.
  • FIG. 1 is a general view in section and in semi-perspective of an example of turbine blade with offset of the head sections according to the invention
  • FIG. 2 is a perspective representation illustrating a foundry core according to one embodiment of the invention
  • FIG. 3 is a representation of a detail of the upper part of the foundry core of FIG. 2 and connecting rods between the different core elements.
  • FIG. 4a is a side view of an example of a blade with an offset in head cups according to the prior art
  • FIG. 4b is a top view of the blade of FIG. 4a, on which are visible the cavities along planes X1 and X2,
  • FIG. 5a is a side view of an example of blade with an offset in head sections according to the invention.
  • FIGS. 1 and 5a there is seen a turbine engine turbine blade 1 comprising a blade 10 extending between a blade root 1 1 and a blade head 12, and having a leading edge 13, a trailing edge 14 opposite to the leading edge, lateral surfaces intrados and extrados 15, and internal cavities 19a-19e separated by inter-cavity walls 20, which extend along the height of the blade 1.
  • the dawn may for example have an advanced blade tip of the type "offsets cuts at the head" in accordance with the French patent application filed November 17, 201 1 in the name of the Applicant No. FR 1 1 60465.
  • the blade 1 comprises a leading edge cavity 19a, one or more central cavities 19b, 19c, 19d, (in this case three in the case of dawn 1 shown in the figure, namely a first upstanding central cavity 19b, a downward central cavity 19c, and a second upstanding central cavity 19d, which together form an internal cavity "trombone"), and a trailing edge cavity 19th.
  • the blade 1 further comprises, at its head 1 1, a bath 18, whose bottom wall 17 closes the internal cavities 19a-19e cooling.
  • the inter-cavity wall 20 separating the central cavity 19d adjacent to the trailing edge cavity 19e and the subsequent cavity towards the leading edge 13 is shaped, in the vicinity of the bottom wall 17 of the bath 18, with an offset 16 in the direction of the leading edge 13.
  • the blade 1 when the blade 1 comprises only one central cavity 19d, it is then the inter-cavity wall 20 which separates this single central cavity 19d from the leading edge cavity 19a which can be shaped, at near the bottom wall 17 of the bath, with an offset 16 towards the leading edge 13. Because of this offset 16 relative to the remainder of the intercavity wall 20, the central cavity 19d which is adjacent to the trailing edge cavity 19e has a bulge 34 in the vicinity of the bottom wall 17, said cavity 19d being wider. at the level of the blade head 12 only at the level of the blade root 1 1. The particular shape of this central cavity 19d simplifies the manufacture of the blade 1.
  • the intercavity wall 20 is offset at the offset 16 to the bottom wall 17, to widen the entire upper part of the central cavity 19d.
  • the foundry core assembly 30 for the manufacture of such a turbomachine blade has a suitable complementary shape and comprises a first core element 31, taking the shape of the cavities 19a-19e, as well as a second core element 32, taking again the shape of the bath 18.
  • the two core elements 31 and 32 are for example ceramic.
  • the second core element 32 is connected to the first core element 31 by connecting rods 40 which may for example be made of alumina or quartz.
  • the first core element 31 is of generally elongated shape according to the height of the blade 1 and comprises a series of internal cores 31a, 31b, 31c, 31d and 31e intended to form respectively the leading edge cavities 19a, the central cavity (s) 19b, 19c and 19d, and the trailing edge cavity 19e, respectively.
  • the second core member 32 is disposed above the first core member 31, and is separated therefrom by connecting rods 40 positioned to provide dust holes 35 in the inner cores 31a through 31c. .
  • the inner core 19d defining the central cavity 31 d adjacent to the core 31 e of the trailing edge cavity has, at least in an area in the immediate vicinity of the second core member 32, a bulge 34 towards the inner core 31 a of the leading edge cavity.
  • the core internal 31 c of the corresponding central cavity is therefore wider at this level, for example from 30% to 60% wider, as visible in Figures 4a to 5b.
  • the maximum width d x of the core of the internal cavity 31 d adjacent to the core of the trailing edge cavity 31 e at the plane X 2 is of the order 3.4 mm.
  • the maximum width d y of the core of the inner cavity 31 d which is adjacent to the trailing edge internal cavity core 31 e at the plane Y 2 , for a similar blade with offset head section but including a bulge 34 according to the invention, can be of the order of 5 mm (or about 50% wider).
  • the space available for implanting a connecting rod 40 in this cavity core 31 d is therefore much greater than in the vanes of the prior art, which makes it possible to increase the depth of anchoring and the thickness of the cores around the connecting rods 40 and avoids the formation of cracks in the core elements 31, 32, and thus significantly reduce the scrap rate of the blades in the manufacture.
  • the inner core 31c of central cavity immediately adjacent towards the leading edge cavity 31a is in turn shaped with a counter-form 33 complementary so that the inter-cavity wall 20 made between these two internal cores 31c and 31d present the offset 16 described above in the direction of the leading edge 13 of the blade 1.
  • the first core 31 when the blade 1 comprises only one central cavity 19d, the first core 31 then comprises only one inner core 31c of central cavity, and it is then the inner core 31a of the cavity leading edge which is immediately adjacent to this inner core 31 d of central core. It is therefore the leading edge inner core 31a which is shaped with the complementary counterform so that the inter-cavity wall 20 formed between these two inner cores 31a and 31d has the offset 16 described below. above in the direction of the leading edge 13 of the dawn 1.
  • the bulge 34 and the counter-form 33 are local, and extend only at the level of the upper part of the internal nuclei 31 b-31 d (respectively 31 a, in the case of a blade comprising a single central cavity), the core 31 d adjacent to the core 31 e of the trailing edge cavity being wider at this bulge 34 than at its level. lower part.
  • the height of the bulge 34 is sufficient to allow anchoring of the connecting rods 40 at the bulge 34, and the realization of dust holes 35 in the wall 17 forming the bottom of the bath 18 without formation of cracks in the inner cores 31 b-31 d. Furthermore, the bulge 34 extends to the upper wall of the inner core 31 e of central cavity.
  • the diameter of the holding rods 40 may be chosen to be equal to the desired diameter for the dusting holes 35 in the final piece, in order to avoid an additional step of finishing the blade 10 (plugging the holes). after the lost wax casting step.
  • the dedusting holes 35 are oblique and may, for example, be oriented towards the leading edge 13 of the blade 1. This orientation is however not limiting, only the respect of the diameter of the holding rods 40 is important to ensure the evacuation of dust in the blade 1.
  • the connecting rods 40 are thus oriented obliquely with respect to the general direction in which the second core element 32 extends through which they pass to form the dedusting holes 35 of the second core element 32.
  • the second core element 32 may further comprise bosses 36 (FIG. 2) in the upper part in order to improve the anchoring of the connecting rods 40.
  • the foundry core assembly 30 as illustrated in Figures 2 and 3 is then used to make a wax blank, which is then embedded in a shell, and then the cores are removed to form the various cavities 19a. -19th and the bathtub 18.

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

Abstract

The invention relates to a foundry core (30) for manufacturing a blade (1) of a turbomachine (1) having a tip section offset, comprising a core element (31) for forming various internal cavities (19a-19e), said core element comprising a leading-edge cavity internal core (31a), central cavity internal cores (31b, 31c, 31d) and a trailing-edge cavity internal core (31e), characterized in that the internal core for the central cavity (31d) adjacent to the internal core (31e) for the trailing-edge cavity has a bulge (34) extending toward the core (31a) for the leading-edge cavity.

Description

Ensemble de noyau de fonderie pour la fabrication d'une aube de turbomachine, procédé de fabrication d'une aube et aube associés  Foundry core assembly for the manufacture of a turbomachine blade, method of manufacturing a blade and associated blades
L'invention concerne de manière générale le domaine des turbomachines, et plus particulièrement celui des aubes de turbines de ces turbomachines et de leur fabrication. The invention relates generally to the field of turbomachines, and more particularly to the turbine blades of these turbomachines and their manufacture.
Les aubes de turbine sont soumises à de fortes contraintes thermiques dues à la chaleur des gaz dans lesquels elles sont plongées en sortie de la chambre de combustion, et nécessitent d'être refroidies pour supporter ces températures. Elles sont pour cela creuses et traversées par des cavités internes dans lesquelles circule un gaz de refroidissement, prélevé en sortie d'un étage d'un des compresseurs.  The turbine blades are subjected to high thermal stresses due to the heat of the gases in which they are immersed at the outlet of the combustion chamber, and need to be cooled to withstand these temperatures. They are therefore hollow and traversed by internal cavities in which circulates a cooling gas taken from the output of a stage of a compressor.
Plus précisément, une aube de turbine d'une turbomachine comporte une surface aérodynamique (ou pale) s'étendant entre un pied d'aube et une tête d'aube. La pale présente un bord d'attaque disposé en regard de l'écoulement des gaz chauds issus de la chambre de combustion de la turbomachine, ainsi qu'un bord de fuite opposé au bord d'attaque et des parois latérales intrados et extrados qui relient le bord d'attaque au bord de fuite.  More specifically, a turbine blade of a turbomachine comprises an aerodynamic surface (or blade) extending between a blade root and a blade head. The blade has a leading edge disposed opposite the flow of the hot gases from the combustion chamber of the turbomachine, and a trailing edge opposite the leading edge and side walls intrados and extrados which connect the leading edge at the trailing edge.
Les cavités internes s'étendent sur la hauteur de l'aube, et comprennent, d'amont en aval dans le sens de l'écoulement des gaz de la chambre de combustion, une cavité de bord d'attaque et une cavité de bord de fuite, adjacentes au bord d'attaque et au bord de fuite de l'aube respectivement, et au moins une cavité centrale, s'étendant entre la cavité de bord d'attaque et la cavité de bord de fuite. Ces cavités sont alimentées en gaz de refroidissement par des canalisations les reliant au pied de l'aube.  The internal cavities extend over the height of the blade, and comprise, upstream to downstream in the flow direction of the combustion chamber gases, a leading edge cavity and an edge cavity. leak, adjacent to the leading edge and the trailing edge of the blade respectively, and at least one central cavity, extending between the leading edge cavity and the trailing edge cavity. These cavities are supplied with cooling gas by pipes connecting them to the foot of the dawn.
L'aube comprend en outre, au niveau de sa tête, une forme creuse ou baignoire, qui est définie par le prolongement des parois d'intrados et d'extrados, ainsi que par une paroi de fond qui ferme les cavités internes.  The dawn further comprises, at the level of its head, a hollow form or bathtub, which is defined by the extension of the intrados and extrados walls, as well as by a bottom wall which closes the internal cavities.
Pour réaliser ces différentes cavités, qui ont des formes complexes et dont la géométrie doit être respectée avec une grande précision, les aubes sont classiquement produites par une technique connue sous le nom de fonderie à la cire perdue. Cette technique consiste schématiquement à réaliser une ébauche d'aube en cire dans laquelle sont noyés des noyaux en céramique qui reproduisent les cavités à venir. L'aube en cire est ensuite noyée dans une carapace, par exemple en matériau réfractaire, puis les noyaux sont éliminés par voie chimique, laissant à leur place les cavités internes et de baignoire recherchées. Des mises en œuvre de cette méthode sont en particulier décrites dans les documents FR 2 875 425, FR 2 874 186, ou encore FR 2 957 828 au nom de la Demanderesse, To realize these different cavities, which have complex shapes and whose geometry must be respected with great precision, the blades are conventionally produced by a technique known as lost wax foundry. This technique schematically consists of making a wax dawn blank in which are drowned ceramic cores which reproduce the cavities to come. The dawn wax is then embedded in a shell, for example refractory material, then the cores are removed chemically, leaving in their place the desired internal and bathtub cavities. Implementations of this method are in particular described in documents FR 2 875 425, FR 2 874 186, or FR 2 957 828 in the name of the Applicant,
Les noyaux pour ces aubes de turbine modernes sont constitués par des noyaux internes de cavité, ayant classiquement la forme de colonnettes, qui sont positionnés côte à côte et maintenus ensemble par des moyens conventionnels.  The cores for these modern turbine blades are constituted by cavity internal cores, conventionally having the form of columns, which are positioned side by side and held together by conventional means.
Ces noyaux sont de formes de plus en plus complexes, au fur et à mesure qu'augmentent les spécifications exigées pour le refroidissement des aubes et que se diversifie les aubes. Il est alors nécessaire de les positionner avec une extrême précision dans la carapace.  These cores are of increasingly complex shapes, as the specifications required for the cooling of the blades increase and the blades become more varied. It is then necessary to position them with extreme precision in the carapace.
Un noyau comprend généralement un premier élément de noyau destiné à former les cavités et un deuxième élément de noyau destiné à former la baignoire, le deuxième élément de noyau étant relié au premier élément de noyau par des tiges de liaison en alumine ou en quartz.  A core generally comprises a first core member for forming the cavities and a second core member for forming the tub, the second core member being connected to the first core member by alumina or quartz connecting rods.
Ces tiges ont pour objectif de maintenir entre elles les parties du noyau et de rigidifier l'ensemble ainsi formé, ainsi que de participer à la réalisation de trous de dépoussiérage dans la partie supérieure de l'aube, Ces tiges sont fichées dans les trous qu'elles ont vocation à générer dans le fond de la baignoire. Les trous de dépoussiérage permettent la circulation du gaz de refroidissement dans les cavités et l'évacuation de diverses particules s'introduisant dans la turbomachine.  These rods are intended to maintain the parts of the core between them and to stiffen the assembly thus formed, as well as to participate in the realization of dusting holes in the upper part of the blade, These rods are stuck in the holes that they are intended to generate in the bottom of the bath. The dedusting holes allow the circulation of the cooling gas in the cavities and the evacuation of various particles entering the turbomachine.
Afin d'améliorer les performances aérodynamiques de l'aube et de minimiser les pertes d'énergie, il a été proposé de mettre en œuvre des aubes de turbine pour turbomachines présentant un sommet d'aube avancé du type « décalage des coupes en tête » conformément à la demande de brevet français déposée le 17 novembre 201 1 au nom de la Demanderesse n°FR 1 1 60465. In order to improve the aerodynamic performance of the blade and to minimize energy losses, it has been proposed to use turbine blades for turbomachines having an advanced blade tip of the type "shift cuts in mind" in accordance with the French patent application filed November 17, 201 1 in the name of the Applicant No. FR 1 1 60465.
De telles aubes de turbine sont adaptées pour minimiser les pertes d'énergies. Elles comprennent une pale qui peut être décomposée en sections de pale empilées selon une direction d'empilement le long de la pale. Dans le cas de la tête d'aube avec décalage des coupes de tête, l'empilement des sections au niveau de la tête de l'aube est décalé en direction de la paroi intrados, de préférence progressivement.  Such turbine blades are adapted to minimize energy losses. They include a blade that can be broken down into stacked blade sections in a stacking direction along the blade. In the case of the blade head with offset head sections, the stack of sections at the head of the blade is shifted towards the intrados wall, preferably progressively.
Pour cela, comme décrit dans la demande de brevet n°FR 1 1 60465, l'aube peut comporter une cavité au niveau de sa tête, ouverte en direction de son extrémité libre et délimitée par la paroi de fond et un rebord qui s'étend entre le bord d'attaque et le bord de fuite. L'empilement des sections de pale de l'aube au niveau de ce rebord présente alors un décalage en direction de l'intrados, ce décalage étant de plus en plus important lorsqu'on se rapproche de l'extrémité libre de la tête de l'aube. L'aube comprend également des canaux de refroidissement, inclinés par rapport à l'intrados, et reliant les cavités internes à la paroi intrados.  For this, as described in the patent application No. FR 1 1 60465, the blade may comprise a cavity at its head, open towards its free end and delimited by the bottom wall and a flange which s' extends between the leading edge and the trailing edge. The stacking of blade sections of the blade at this rim then has an offset in the direction of the underside, this offset being more and more important when approaching the free end of the head of the blade. 'dawn. The dawn also includes cooling channels, inclined relative to the intrados, and connecting the internal cavities to the intrados wall.
La paroi d'intrados de la pale peut en outre présenter une portion en saillie, dont la face extérieure est inclinée par rapport au reste de l'intrados de la pale et présente à son extrémité, tournée vers le rebord, une face terminale. La paroi de fond est alors reliée à la paroi d'intrados au niveau de la face terminale de la portion en saillie, et les canaux de refroidissement peuvent être disposés dans la portion en saillie de la paroi d'intrados de sorte qu'ils débouchent sur la face terminale de la portion en saillie, la distance entre l'axe des canaux de refroidissement et la limite extérieure de l'extrémité libre du rebord côté intrados étant supérieure à zéro.  The intrados wall of the blade may further have a projecting portion, the outer face is inclined relative to the remainder of the intrados of the blade and has at its end, facing the rim, an end face. The bottom wall is then connected to the intrados wall at the end face of the projecting portion, and the cooling channels can be arranged in the projecting portion of the intrados wall so that they open out. on the end face of the protruding portion, the distance between the axis of the cooling channels and the outer limit of the free end of the intrados side edge being greater than zero.
Néanmoins, ce décalage des coupes en tête ainsi que la faible taille de la pale, et donc des noyaux utilisés pour sa fabrication, rendent difficile le maintien par les tiges du deuxième élément de noyau qui est destiné à former la baignoire sur le premier élément de noyau. Il a donc été proposé d'orienter les tiges individuellement, avec des angles importants par rapport à la direction principale de la pale. Néanmoins, les noyaux sont complexes à réaliser en raison de la forte inclinaison des tiges de liaison par rapport à la direction principale des noyaux (et donc de l'injection de céramique), ce qui peut poser des problèmes d'usure des noyaux au niveau du fond de baignoire. Par ailleurs, la mise en œuvre de ce procédé de fabrication nécessite un savoir-faire est une expérience qui ne sont pas accessibles à tous les hommes de l'art, à savoir ici les fondeurs. Nevertheless, this offset of the cuts in the head as well as the small size of the blade, and thus the cores used for its manufacture, make it difficult for the rods to hold the second core element which is intended to form the tub on the first element of the blade. core. It has therefore been proposed to orient the rods individually, with significant angles relative to the main direction of the blade. Nevertheless, the cores are complex to achieve because of the steepness of the connecting rods with respect to the main direction of the cores (and therefore of the ceramic injection), which can cause wear problems of the cores at the level of the cores. from the bottom of the bathtub. Moreover, the implementation of this manufacturing process requires a know-how is an experience that is not accessible to all skilled in the art, namely here the founders.
Il a également été proposé d'utiliser des tiges de liaison ancrées de manière classiques dans les éléments de noyaux, avec un ancrage toutefois fortement réduit en comparaison avec les techniques conventionnelles, en raison de la faible dimension des cavités internes de l'aube. Cependant, la profondeur d'ancrage et l'épaisseur des noyaux (généralement en céramique) autour des tiges de liaison entraînent des problèmes de criques (ruptures partielles qui se produisent sous l'action d'efforts résultant d'inégalité de retrait) dans les éléments de noyaux, et donc un taux de rebut très important.  It has also been proposed to use link rods anchored conventionally in the core elements, with anchoring however greatly reduced in comparison with conventional techniques, due to the small size of the internal cavities of the blade. However, the anchoring depth and the thickness of the cores (usually ceramic) around the connecting rods cause problems of cracks (partial fractures that occur under the action of forces resulting from unequal shrinkage) in the core elements, and therefore a very important scrap rate.
L'invention propose quant à elle un ensemble formant noyau pour la fabrication d'une aube de turbomachine refroidie par circulation de fluide dans des cavités internes, comportant un premier élément de noyau de forme allongée pour la formation de différentes cavités internes et un second élément de noyau pour la formation d'une cavité de baignoire, le deuxième élément de noyau étant destiné à être disposé dans le prolongement du premier élément de noyau. Le premier élément de noyau comprend un noyau interne de cavité de bord d'attaque, au moins un noyau interne de cavité centrale et un noyau interne de cavité de bord de fuite destinés à former respectivement, d'amont en aval dans le sens d'un écoulement des gaz dans la turbine, une cavité de bord d'attaque, au moins une cavité centrale et une cavité de bord de fuite de l'aube. Le noyau de la cavité interne centrale adjacente au noyau interne de la cavité de bord de fuite présente, au voisinage immédiat du deuxième élément de noyau, un renflement qui s'étend en direction du noyau de la cavité de bord d'attaque. The invention proposes a core assembly for the manufacture of a turbomachine blade cooled by circulation of fluid in internal cavities, comprising a first elongate core element for the formation of different internal cavities and a second element core for forming a bath cavity, the second core member being adapted to be disposed in the extension of the first core member. The first core element comprises an internal leading edge cavity core, at least one central cavity inner core and an internal trailing edge cavity core for respectively forming, upstream to downstream in the direction of a gas flow in the turbine, a leading edge cavity, at least one central cavity and a trailing edge cavity of the blade. The core of the central internal cavity adjacent to the inner core of the trailing edge cavity has, in the immediate vicinity of the second core member, a bulge extending in the direction of the core of the leading edge cavity.
Une telle solution permet l'ancrage d'au moins une tige de liaison au niveau d'une zone élargie du premier élément de noyau (au niveau du renflement), et par conséquent de réaliser des aubes de turbine pour turbomachines présentant un décalage de coupes de tête selon un procédé fiable avec un taux de rebut des noyaux peu important.  Such a solution makes it possible to anchor at least one connecting rod at an enlarged zone of the first core element (at the level of the bulge), and consequently to make turbine blades for turbomachines having a slice offset. head in a reliable process with a low kernel scrap rate.
L'invention concerne également une aube obtenue au moyen d'un tel ensemble formant noyau de fonderie, ainsi qu'un procédé de fabrication utilisant un tel ensemble.  The invention also relates to a blade obtained by means of such a foundry core assembly, and a manufacturing method using such a set.
D'autres caractéristiques, buts et avantages de la présente invention apparaîtront mieux à la lecture de la description détaillée qui va suivre, faite en référence aux dessins annexés donnés à titre non limitatif et sur lesquels : Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, made with reference to the accompanying drawings given in a non-limiting manner and in which:
La figure 1 est une vue générale en coupe et en semi-perspective d'un exemple d'aube de turbine avec décalage des coupes de tête selon l'invention,  FIG. 1 is a general view in section and in semi-perspective of an example of turbine blade with offset of the head sections according to the invention,
La figure 2 est une représentation en perspective illustrant un noyau de fonderie conforme à un mode de réalisation de l'invention,  FIG. 2 is a perspective representation illustrating a foundry core according to one embodiment of the invention,
La figure 3 est une représentation d'un détail de la partie supérieure du noyau de fonderie de la figure 2 et des tiges de liaison entre les différents éléments de noyau  FIG. 3 is a representation of a detail of the upper part of the foundry core of FIG. 2 and connecting rods between the different core elements.
La figure 4a est une vue de côté d'un exemple d'aube avec un décalage en coupes de tête conforme à l'art antérieur,  FIG. 4a is a side view of an example of a blade with an offset in head cups according to the prior art,
La figure 4b est une vue du dessus de l'aube de la figure 4a, sur laquelle sont visibles les cavités selon les plans X1 et X2,  FIG. 4b is a top view of the blade of FIG. 4a, on which are visible the cavities along planes X1 and X2,
La figure 5a est une vue de côté d'un exemple d'aube avec un décalage en coupes de tête conforme à l'invention, et  FIG. 5a is a side view of an example of blade with an offset in head sections according to the invention, and
La figure 5b est une vue du dessus de l'aube de la figure 5a, sur laquelle sont visibles les cavités selon les plans Y1 et Y2. En se référant aux figures 1 et 5a, on voit une aube de turbine 1 pour turbomachine comprenant une pale 10 s'étendant entre un pied d'aube 1 1 et une tête d'aube 12, et comportant un bord d'attaque 13, un bord de fuite 14 opposé au bord d'attaque, des faces latérales intrados et extrados 15, et des cavités internes 19a-19e séparées par des parois inter-cavités 20, qui s'étendent selon la hauteur de l'aube 1 . Figure 5b is a top view of the blade of Figure 5a, on which are visible the cavities along the planes Y1 and Y2. Referring to FIGS. 1 and 5a, there is seen a turbine engine turbine blade 1 comprising a blade 10 extending between a blade root 1 1 and a blade head 12, and having a leading edge 13, a trailing edge 14 opposite to the leading edge, lateral surfaces intrados and extrados 15, and internal cavities 19a-19e separated by inter-cavity walls 20, which extend along the height of the blade 1.
L'aube peut par exemple présenter un sommet d'aube avancé du type « décalage des coupes en tête » conformément à la demande de brevet français déposée le 17 novembre 201 1 au nom de la Demanderesse n°FR 1 1 60465.  The dawn may for example have an advanced blade tip of the type "offsets cuts at the head" in accordance with the French patent application filed November 17, 201 1 in the name of the Applicant No. FR 1 1 60465.
Notamment, du bord d'attaque 13 vers le bord de fuite 14, l'aube 1 comprend une cavité de bord d'attaque 19a, une ou plusieurs cavités centrales 19b, 19c, 19d, (en l'occurrence trois dans le cas de l'aube 1 représentée sur la figure, à savoir une première cavité centrale montante 19b, une cavité centrale descendante 19c, et une deuxième cavité centrale montante 19d, qui forment ensemble une cavité interne « trombone »), et une cavité de bord de fuite 19e. L'aube 1 comprend en outre, au niveau de sa tête 1 1 , une baignoire 18, dont la paroi de fond 17 ferme les cavités internes 19a-19e de refroidissement. In particular, from the leading edge 13 to the trailing edge 14, the blade 1 comprises a leading edge cavity 19a, one or more central cavities 19b, 19c, 19d, (in this case three in the case of dawn 1 shown in the figure, namely a first upstanding central cavity 19b, a downward central cavity 19c, and a second upstanding central cavity 19d, which together form an internal cavity "trombone"), and a trailing edge cavity 19th. The blade 1 further comprises, at its head 1 1, a bath 18, whose bottom wall 17 closes the internal cavities 19a-19e cooling.
La paroi inter-cavités 20 séparant la cavité centrale 19d adjacente à la cavité 19e de bord de fuite et la cavité suivante en direction du bord d'attaque 13 (c'est-à-dire, dans le cas de l'aube de la figure 1 , la cavité centrale 19c) est conformée, au voisinage de la paroi de fond 17 de la baignoire 18, avec un décalage 16 en direction du bord d'attaque 13.  The inter-cavity wall 20 separating the central cavity 19d adjacent to the trailing edge cavity 19e and the subsequent cavity towards the leading edge 13 (that is, in the case of the dawn of the 1, the central cavity 19c) is shaped, in the vicinity of the bottom wall 17 of the bath 18, with an offset 16 in the direction of the leading edge 13.
En variante, lorsque l'aube 1 ne comprend qu'une seule cavité centrale 19d, c'est alors la paroi inter-cavités 20 qui sépare cette unique cavité centrale 19d de la cavité de bord d'attaque 19a qui peut être conformée, au voisinage de la paroi de fond 17 de la baignoire, avec un décalage 16 en direction du bord d'attaque 13. Du fait de ce décalage 16 par rapport au reste de la paroi intercavités 20, la cavité centrale 19d qui est adjacente à la cavité de bord de fuite 19e présente un renflement 34 au voisinage de la paroi de fond 17, ladite cavité 19d étant plus large au niveau de la tête d'aube 12 qu'au niveau du pied d'aube 1 1 . La forme particulière de cette cavité centrale 19d permet de simplifier la fabrication de l'aube 1 . In a variant, when the blade 1 comprises only one central cavity 19d, it is then the inter-cavity wall 20 which separates this single central cavity 19d from the leading edge cavity 19a which can be shaped, at near the bottom wall 17 of the bath, with an offset 16 towards the leading edge 13. Because of this offset 16 relative to the remainder of the intercavity wall 20, the central cavity 19d which is adjacent to the trailing edge cavity 19e has a bulge 34 in the vicinity of the bottom wall 17, said cavity 19d being wider. at the level of the blade head 12 only at the level of the blade root 1 1. The particular shape of this central cavity 19d simplifies the manufacture of the blade 1.
Par ailleurs, comme illustré sur les figures 1 et 5a, la paroi intercavité 20 est décalée au niveau du décalage 16 jusqu'à la paroi de fond 17, afin d'élargir toute la partie supérieure cette cavité centrale 19d.  Furthermore, as illustrated in Figures 1 and 5a, the intercavity wall 20 is offset at the offset 16 to the bottom wall 17, to widen the entire upper part of the central cavity 19d.
L'ensemble formant noyau de fonderie 30 pour la fabrication d'une telle aube de turbomachine (figures 2 et 3) présente une forme complémentaire adaptée et comprend un premier élément de noyau 31 , reprenant la forme des cavités 19a-19e, ainsi qu'un deuxième élément de noyau 32, reprenant quant à lui la forme de la baignoire 18. Les deux éléments de noyau 31 et 32 sont par exemple en céramique.  The foundry core assembly 30 for the manufacture of such a turbomachine blade (FIGS. 2 and 3) has a suitable complementary shape and comprises a first core element 31, taking the shape of the cavities 19a-19e, as well as a second core element 32, taking again the shape of the bath 18. The two core elements 31 and 32 are for example ceramic.
Le deuxième élément de noyau 32 est relié au premier élément de noyau 31 par des tiges de liaison 40 pouvant par exemple être en alumine ou en quartz.  The second core element 32 is connected to the first core element 31 by connecting rods 40 which may for example be made of alumina or quartz.
Le premier élément de noyau 31 est de forme globalement allongée selon la hauteur de l'aube 1 et comprend une série de noyaux internes (ou colonnettes) 31 a, 31 b, 31 c, 31 d et 31 e, destinés à former respectivement les cavités de bord d'attaque 19a, la ou les cavités centrales 19b, 19c et 19d, et la cavité de bord de fuite 19e respectivement.  The first core element 31 is of generally elongated shape according to the height of the blade 1 and comprises a series of internal cores 31a, 31b, 31c, 31d and 31e intended to form respectively the leading edge cavities 19a, the central cavity (s) 19b, 19c and 19d, and the trailing edge cavity 19e, respectively.
Le deuxième élément de noyau 32 est disposé au-dessus du premier élément de noyau 31 , et est séparé de celui-ci par des tiges de liaison 40 positionnées de façon à réaliser des trous de dépoussiérage 35 dans les noyaux internes 31 a à 31 e.  The second core member 32 is disposed above the first core member 31, and is separated therefrom by connecting rods 40 positioned to provide dust holes 35 in the inner cores 31a through 31c. .
Le noyau interne 19d définissant la cavité centrale 31 d adjacente au noyau 31 e de la cavité de bord de fuite présente, au moins dans une zone à proximité immédiate du deuxième élément de noyau 32, un renflement 34 en direction du noyau interne 31 a de la cavité de bord d'attaque. Le noyau interne 31 c de la cavité centrale correspondante est donc plus large à ce niveau, par exemple de 30% à 60% plus large, comme visible sur les figures 4a à 5b. En effet, sur une aube à décalage en coupes de tête conventionnelle, la largeur maximale dx du noyau de la cavité interne 31 d adjacent au noyau de la cavité de bord de fuite 31 e au niveau du plan X2 est de l'ordre de 3.4 mm. En comparaison, la largeur maximale dy du noyau de la cavité interne 31 d qui est adjacent au noyau de cavité interne de bord de fuite 31 e au niveau du plan Y2, pour une aube similaire avec décalage en coupe de tête mais comprenant un renflement 34 conforme à l'invention, peut être de l'ordre de 5 mm (soit environ 50% plus large). L'espace disponible pour implanter une tige de liaison 40 dans ce noyau de cavité 31 d est donc bien plus important que dans les aubes de l'art antérieur, ce qui permet d'augmenter la profondeur d'ancrage et l'épaisseur des noyaux autour des tiges de liaison 40 et permet d'éviter la formation de criques dans les éléments de noyaux 31 , 32, et donc de réduire significativement le taux de rebut des aubes à la fabrication. The inner core 19d defining the central cavity 31 d adjacent to the core 31 e of the trailing edge cavity has, at least in an area in the immediate vicinity of the second core member 32, a bulge 34 towards the inner core 31 a of the leading edge cavity. The core internal 31 c of the corresponding central cavity is therefore wider at this level, for example from 30% to 60% wider, as visible in Figures 4a to 5b. Indeed, on a blade with conventional headlamp offset, the maximum width d x of the core of the internal cavity 31 d adjacent to the core of the trailing edge cavity 31 e at the plane X 2 is of the order 3.4 mm. In comparison, the maximum width d y of the core of the inner cavity 31 d which is adjacent to the trailing edge internal cavity core 31 e at the plane Y 2 , for a similar blade with offset head section but including a bulge 34 according to the invention, can be of the order of 5 mm (or about 50% wider). The space available for implanting a connecting rod 40 in this cavity core 31 d is therefore much greater than in the vanes of the prior art, which makes it possible to increase the depth of anchoring and the thickness of the cores around the connecting rods 40 and avoids the formation of cracks in the core elements 31, 32, and thus significantly reduce the scrap rate of the blades in the manufacture.
Par ailleurs, le noyau interne 31 c de cavité centrale immédiatement adjacent en direction de la cavité 31 a de bord d'attaque est quant à lui conformé avec une contre-forme 33 complémentaire de sorte que la paroi inter-cavités 20 réalisée entre ces deux noyaux internes 31 c et 31 d présente le décalage 16 décrit ci-dessus en direction du bord d'attaque 13 de l'aube 1 .  Furthermore, the inner core 31c of central cavity immediately adjacent towards the leading edge cavity 31a is in turn shaped with a counter-form 33 complementary so that the inter-cavity wall 20 made between these two internal cores 31c and 31d present the offset 16 described above in the direction of the leading edge 13 of the blade 1.
En variante, lorsque l'aube 1 ne comprend qu'une seule cavité centrale 19d, le premier noyau 31 ne comprend alors qu'un seul noyau interne 31 c de cavité centrale, et c'est alors le noyau interne 31 a de la cavité de bord d'attaque qui se trouve immédiatement adjacent de ce noyau interne 31 d de noyau central. C'est donc le noyau interne 31 a de bord d'attaque qui est conformé avec la contre-forme complémentaire de sorte que la paroi inter-cavités 20 réalisée entre ces deux noyaux internes 31 a et 31 d présente le décalage 16 décrit ci-dessus en direction du bord d'attaque 13 de l'aube 1 .  Alternatively, when the blade 1 comprises only one central cavity 19d, the first core 31 then comprises only one inner core 31c of central cavity, and it is then the inner core 31a of the cavity leading edge which is immediately adjacent to this inner core 31 d of central core. It is therefore the leading edge inner core 31a which is shaped with the complementary counterform so that the inter-cavity wall 20 formed between these two inner cores 31a and 31d has the offset 16 described below. above in the direction of the leading edge 13 of the dawn 1.
Le renflement 34 et la contre-forme 33 sont locaux, et ne s'étendent qu'au niveau de la partie supérieure des noyaux internes 31 b-31 d (respectivement 31 a, dans le cas d'une aube comprenant une unique cavité centrale), le noyau 31 d adjacent au noyau 31 e de la cavité de bord de fuite étant plus large au niveau de ce renflement 34 qu'au niveau de sa partie inférieure. The bulge 34 and the counter-form 33 are local, and extend only at the level of the upper part of the internal nuclei 31 b-31 d (respectively 31 a, in the case of a blade comprising a single central cavity), the core 31 d adjacent to the core 31 e of the trailing edge cavity being wider at this bulge 34 than at its level. lower part.
La hauteur du renflement 34 est suffisante pour permettre l'ancrage des tiges de liaison 40 au niveau du renflement 34, et la réalisation de trous de dépoussiérage 35 dans la paroi 17 formant le fond de la baignoire 18 sans formation de criques dans les noyaux internes 31 b-31 d. Par ailleurs, le renflement 34 s'étend jusqu'à la paroi supérieure du noyau interne 31 e de cavité centrale.  The height of the bulge 34 is sufficient to allow anchoring of the connecting rods 40 at the bulge 34, and the realization of dust holes 35 in the wall 17 forming the bottom of the bath 18 without formation of cracks in the inner cores 31 b-31 d. Furthermore, the bulge 34 extends to the upper wall of the inner core 31 e of central cavity.
La réalisation de ces trous de dépoussiérage 35 est ainsi facilitée par la modification de la géométrie du noyau interne 31 d adjacent au noyau 31 e de bord de fuite et plus particulièrement par l'existence du renflement 34 dans sa partie supérieure. Notamment, du fait de la forme aérodynamique de la pale 10, laquelle présente une section transversale croissante entre le bord de fuite 14 et le bord d'attaque 13, la présence du renflement 34 permet d'ancrer les tiges de liaison 40 dans une zone du noyau 31 plus large qu'avec une configuration de noyau classique, et de limiter par conséquent l'angle formé entre les tiges de liaison 40 et l'axe principal des noyaux. La réalisation de trous 35 est donc plus favorable à la fonderie et améliore en outre les possibilités d'ancrage des tiges de liaison 40.  The realization of these dusting holes 35 is thus facilitated by the modification of the geometry of the inner core 31 d adjacent the core 31 e trailing edge and more particularly by the existence of the bulge 34 in its upper part. In particular, because of the aerodynamic shape of the blade 10, which has an increasing cross section between the trailing edge 14 and the leading edge 13, the presence of the bulge 34 makes it possible to anchor the connecting rods 40 in a zone the core 31 wider than with a conventional core configuration, and therefore limit the angle formed between the connecting rods 40 and the main axis of the cores. The production of holes 35 is therefore more favorable to the foundry and also improves the possibilities of anchoring the connecting rods 40.
Par ailleurs, le diamètre des tiges de maintien 40 peut être choisi de manière à être égal au diamètre souhaité pour les trous de dépoussiérage 35 dans la pièce finale, afin d'éviter une étape supplémentaire de finition de la pale 10 (bouchage des trous) après l'étape de fonderie à la cire perdue.  On the other hand, the diameter of the holding rods 40 may be chosen to be equal to the desired diameter for the dusting holes 35 in the final piece, in order to avoid an additional step of finishing the blade 10 (plugging the holes). after the lost wax casting step.
Comme illustré sur les figures 2 et 3, les trous de dépoussiérage 35 sont obliques et peuvent par exemple être orientés vers le bord d'attaque 13 de l'aube 1 . Cette orientation n'est cependant pas limitative, seul le respect du diamètre des tiges de maintien 40 étant important pour garantir l'évacuation des poussières dans l'aube 1 . Les tiges de liaison 40 sont de ce fait orientées de façon oblique par rapport à la direction générale selon laquelle s'étend le deuxième élément de noyau 32 qu'ils traversent pour former les trous de dépoussiérage 35 du deuxième élément de noyau 32. As illustrated in FIGS. 2 and 3, the dedusting holes 35 are oblique and may, for example, be oriented towards the leading edge 13 of the blade 1. This orientation is however not limiting, only the respect of the diameter of the holding rods 40 is important to ensure the evacuation of dust in the blade 1. The connecting rods 40 are thus oriented obliquely with respect to the general direction in which the second core element 32 extends through which they pass to form the dedusting holes 35 of the second core element 32.
Le deuxième élément de noyau 32 peut en outre comprendre des bossages 36 (Figure 2) en partie supérieure afin d'améliorer l'ancrage des tiges de liaison 40.  The second core element 32 may further comprise bosses 36 (FIG. 2) in the upper part in order to improve the anchoring of the connecting rods 40.
L'ensemble formant noyau de fonderie 30 tel qu'illustré sur les figures 2 et 3 est ensuite utilisée pour fabriquer une ébauche en cire, qui est ensuite noyée dans une carapace, puis les noyaux sont éliminés, de manière à former les différentes cavités 19a-19e et la baignoire 18.  The foundry core assembly 30 as illustrated in Figures 2 and 3 is then used to make a wax blank, which is then embedded in a shell, and then the cores are removed to form the various cavities 19a. -19th and the bathtub 18.

Claims

REVENDICATIONS
1 . Ensemble formant noyau de fonderie (30) pour la fabrication d'une aube (1 ) de turbomachine (1 ) présentant un décalage de coupe de tête refroidie par circulation de fluide dans des cavités internes (19a-19e), comportant un premier élément de noyau (31 ) de forme allongée pour la formation de différentes cavités internes (19a-19e) et un second élément de noyau (32) pour la formation d'une cavité de baignoire (18), le deuxième élément de noyau (32) étant destiné à être disposé dans le prolongement du premier élément de noyau (31 ), 1. A foundry core assembly (30) for producing a turbomachine blade (1) having a cooled fluid-cooled head cut offset in internal cavities (19a-19e), having a first fluid element an elongated core (31) for the formation of different internal cavities (19a-19e) and a second core element (32) for the formation of a bath cavity (18), the second core element (32) being intended to be arranged in the extension of the first core element (31),
dans lequel le premier élément de noyau (31 ) comprend un noyau interne (31 a) de cavité de bord d'attaque, au moins un noyau interne (31 b- 31 d) de cavité centrale et un noyau interne (31 e) de cavité de bord de fuite destinés à former respectivement, d'amont en aval dans le sens d'un écoulement des gaz dans la turbine, une cavité de bord d'attaque (19a), au moins une cavité centrale (19b-19d) et une cavité de bord de fuite (19e) de l'aube (1 ),  wherein the first core member (31) comprises an inner leading edge cavity core (31a), at least one central cavity inner core (31b-31d) and an inner core (31e) of trailing edge cavity for respectively forming, upstream to downstream in the direction of a gas flow in the turbine, a leading edge cavity (19a), at least one central cavity (19b-19d) and a trailing edge cavity (19e) of the blade (1),
caractérisé en ce que l'au moins un noyau interne de la cavité centrale (31 d) adjacent au noyau interne (31 e) de la cavité de bord de fuite présente, au voisinage immédiat du deuxième élément de noyau (32), un renflement (34) qui s'étend en direction du noyau (31 a) de la cavité de bord d'attaque.  characterized in that the at least one inner core of the central cavity (31 d) adjacent to the inner core (31 e) of the trailing edge cavity has, in the immediate vicinity of the second core member (32), a bulge (34) extending in the direction of the core (31a) of the leading edge cavity.
2. Ensemble formant noyau de fonderie (30) selon la revendication 1 , dans lequel le noyau interne (31 a, 31 b, 31 c), qui est en regard du noyau interne (31 d) de cavité centrale qui présente le renflement (34), présente une contre-forme (33) qui est complémentaire du renflement (34). The foundry core assembly (30) according to claim 1, wherein the inner core (31a, 31b, 31c), which faces the inner core (31d) of the central cavity which has the bulge ( 34), has a counter-form (33) which is complementary to the bulge (34).
3. Ensemble formant noyau de fonderie (30) selon l'une des revendications 1 et 2, comprenant en outre au moins une tige de liaison (40) qui s'étend entre le deuxième élément de noyau (32) et le renflement (34) en étant ancrée dans l'un et l'autre. The foundry core assembly (30) according to one of claims 1 and 2, further comprising at least one connecting rod (40) which extends between the second core member (32) and the bulge (34) being anchored in each other.
4. Ensemble formant noyau selon la revendication 3, dans lequel la ou les tiges de liaison (40) ancrées dans le renflement (34) s'étendent de façon oblique par rapport au deuxième élément de noyau (32). The core assembly of claim 3, wherein the one or more connecting rods (40) anchored in the bulge (34) extend obliquely with respect to the second core member (32).
5. Ensemble formant noyau selon l'une des revendications 3 ou 4, dans lequel la ou les tiges (40) sont en aluminium oxydé ou en quartz. 5. core assembly according to one of claims 3 or 4, wherein the rod or rods (40) are oxidized aluminum or quartz.
6. Ensemble formant noyau selon l'une des revendications 1 à 5, dans lequel le premier élément de noyau (31 ) comprend quatre noyaux internes (31 a, 31 b, 31 c, 31 d, 31 e). The core assembly of one of claims 1 to 5, wherein the first core member (31) comprises four inner cores (31a, 31b, 31c, 31d, 31e).
7. Procédé de fabrication d'une aube de turbomachine (1 ), dans lequel on réalise une ébauche d'aube par fonderie à la cire perdue en utilisant un ensemble de noyau de fonderie (30) selon l'une des revendications 1 à 6, A method of manufacturing a turbomachine blade (1), wherein a blade blank is made by lost-wax casting using a foundry core assembly (30) according to one of claims 1 to 6. ,
l'ébauche comportant une cavité de bord d'attaque (19a), au moins une cavité centrale (19b, 19c, 19d) et une cavité de bord de fuite (19e), chaque cavité étant séparée d'une cavité adjacente par une paroi intercavités (20), ainsi qu'une cavité de baignoire (18),  the blank having a leading edge cavity (19a), at least one central cavity (19b, 19c, 19d) and a trailing edge cavity (19e), each cavity being separated from an adjacent cavity by a wall intercavities (20) and a bathtub cavity (18),
caractérisé en ce que la paroi inter-cavités (20) de l'au moins une cavité centrale (19b, 19c) qui est adjacente à la cavité de bord d'attaque (19a) est conformée, dans un voisinage immédiat de la cavité de baignoire (18), avec un décalage en direction de la cavité de bord d'attaque (19a).  characterized in that the inter-cavity wall (20) of the at least one central cavity (19b, 19c) which is adjacent to the leading edge cavity (19a) is shaped, in an immediate vicinity of the cavity of bathtub (18) with an offset towards the leading edge cavity (19a).
8. Aube de turbomachine (1 ) comprenant un bord d'attaque (13), un bord de fuite (14), une cavité de bord d'attaque (19a), au moins une cavité centrale (19b, 19c, 19d) et une cavité de bord de fuite (19e), chaque cavité étant séparée d'une cavité adjacente par une paroi inter-cavités (20), ainsi qu'une cavité de baignoire (18), A turbomachine blade (1) comprising a leading edge (13), a trailing edge (14), a leading edge cavity (19a), at least one central cavity (19b, 19c, 19d) and a trailing edge cavity (19th), each cavity being separated from an adjacent cavity by an inter-cavity wall (20) and a bathtub cavity (18),
caractérisée en ce que la paroi inter-cavités (20) de l'au moins une cavité centrale (19d) qui est adjacente à la cavité de bord de fuite (19d) est conformée, dans un voisinage immédiat de la cavité de baignoire (18), avec un décalage (16) en direction de la cavité de bord d'attaque (19a). characterized in that the inter-cavity wall (20) of the at least one central cavity (19d) which is adjacent to the trailing edge cavity (19d) is shaped in an immediate vicinity of the bath cavity (18). ), with an offset (16) towards the leading edge cavity (19a).
9. Turbomachine comprenant une aube (1 ) selon la revendication 8. 9. Turbomachine comprising a blade (1) according to claim 8.
EP13704418.6A 2012-02-22 2013-02-12 Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade Active EP2817114B1 (en)

Applications Claiming Priority (2)

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FR1251620A FR2986982A1 (en) 2012-02-22 2012-02-22 FOUNDRY CORE ASSEMBLY FOR MANUFACTURING A TURBOMACHINE BLADE, METHOD FOR MANUFACTURING A BLADE AND AUBE ASSOCIATED
PCT/EP2013/052785 WO2013124189A1 (en) 2012-02-22 2013-02-12 Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade

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CA2864576A1 (en) 2013-08-29
CN104144757A (en) 2014-11-12
JP6170510B2 (en) 2017-07-26
EP2817114B1 (en) 2019-04-03
US20150132139A1 (en) 2015-05-14
RU2616700C2 (en) 2017-04-18
CN104144757B (en) 2017-05-10
JP2015508025A (en) 2015-03-16
FR2986982A1 (en) 2013-08-23
US9890644B2 (en) 2018-02-13
CA2864576C (en) 2019-12-31
BR112014020620B1 (en) 2019-05-14
WO2013124189A1 (en) 2013-08-29

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