EP0466602A1 - Statorranes for turbines made from thermostructural composite material - Google Patents

Statorranes for turbines made from thermostructural composite material Download PDF

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Publication number
EP0466602A1
EP0466602A1 EP19910401948 EP91401948A EP0466602A1 EP 0466602 A1 EP0466602 A1 EP 0466602A1 EP 19910401948 EP19910401948 EP 19910401948 EP 91401948 A EP91401948 A EP 91401948A EP 0466602 A1 EP0466602 A1 EP 0466602A1
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EP
European Patent Office
Prior art keywords
blade
heels
blades
distributor according
casing
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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
EP19910401948
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German (de)
French (fr)
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EP0466602B1 (en
Inventor
Jean-Pierre Ciais
Jacques G. Fouillot
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Societe Europeenne de Propulsion SEP SA
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Societe Europeenne de Propulsion SEP SA
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Publication of EP0466602A1 publication Critical patent/EP0466602A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates to a fixed vane of a turbine distributor or gas compressor.
  • a turbine distributor includes a set of fixed blades arranged between an inner casing and an outer casing.
  • FIGS. 1 and 2 illustrate a one-piece distributor with vanes 1 between interior 2 and exterior 3 casings.
  • the inventors have envisaged the production of the blades in a thermostructural composite material.
  • Thermostructural composite materials are well known. They consist of a refractory fibrous reinforcement, for example made of carbon fibers or ceramic fibers, densified by a refractory matrix, for example also made of carbon or ceramic. These materials, due to the presence of a fibrous reinforcing texture and their refractory nature, have good mechanical strength, which makes them capable of constituting structural elements, and retain their mechanical characteristics up to high temperatures, and do not have the brittle nature of solid ceramics.
  • the present invention aims to propose an architecture for a turbine distributor or a gas compressor which is particularly suitable for producing fixed vanes made of thermostructural composite material.
  • each blade with asymmetrical heels, that is to say with heels each extending on one side of the airfoil, allows a relatively easy development of the fiber reinforcement of the blades, for example by forming a preform consisting of tissue layers or a three-dimensional texture such as a needle texture.
  • FIGS. 3 to 5 A first embodiment of a turbine distributor provided with fixed blades and in accordance with the present invention is illustrated by FIGS. 3 to 5.
  • the fixed vanes 10 are mounted between an inner annular casing 20 and an outer annular casing 22.
  • Each vane 10 has a substantially C shape with a central part 12 forming an aerodynamic profile extended by two asymmetrical heels, interior 14 and exterior 16. Heels 14 and 16 extend on one and the same side of the part 12, in this case on the side of the lower surface 12a.
  • the heels 14, 16 of a blade rest by their end edges 14a, 16a on the upper surface 12b of a neighboring blade and consequently define the distance or not between the blades, the edges 14a, 16a of the blades. heels having a shape which matches that of the upper surface 12b.
  • Pawns 16 are housed in holes formed in the internal faces of housings 20 and 22 and protrude in the interval between them.
  • the pins 18 form stops against which the heels of at least one blade 10 bear, notches receiving the pins 18 being formed for this purpose in the end edges of the heels.
  • the pins 18 determine the orientation of the blades 10 in the gap between the housings, that is to say essentially the orientation of the aerodynamic profiles 12.
  • the pins 18 ensure a rotation lock of the blades 10 after their mounting.
  • the heels 14 and 16 have external surfaces 14b, 16b which are not exactly cylindrical so that they do not match the internal faces of the casings 20, 22. More precisely, each heel 14, 16 is supported on the corresponding casing by a only part of its external surface, in the vicinity of its end 14a, 16a. Thus, from the bearing zone of each heel, a clearance J is formed between the heel and the surface of the adjacent casing, clearance which can gradually increase up to the level of the central part 12.
  • the blades 10 are made of a thermostructural composite material which, by its nature, has a certain elasticity in bending. Therefore, and thanks to the games J, the blades 10 can accommodate without damage differential expansions between themselves and the housings 20, 22, these can be in the same material as the blades, or in a material different, for example metallic. During assembly, at room temperature, the heels of the blades 10 are at least slightly prestressed in bending to ensure effective support on the internal faces of the casings.
  • the blades may have a C shape with asymmetrical heels which both extend on the side of the upper surface.
  • FIGS. 6A to 6C A method of manufacturing blades 10 such as that of FIG. 4 will now be described with reference to FIGS. 6A to 6C.
  • a fiber preform 30, intended to constitute the reinforcement of the composite material constituting the blades, is for example produced by stacking layers of fabric 32 and molding the layers in a tool 34.
  • the fabric from which the layers 32 are cut is made of refractory fibers, for example carbon fibers or ceramic fibers, such as silicon carbide fibers.
  • the tool 34 comprises a punch 34a whose shape is that of the lower surface 12a and of the internal profile of the heels 14, 16.
  • the punch 34a defines, with the complementary part 34b of the tool 34, a volume of constant thickness and of C section in which the C shape of a blade 10 is inscribed.
  • the preform 30 may be produced other than by stacking layers of fabric, for example by shaping a three-dimensional texture having the desired thickness, such as a needled texture or a texture obtained by three-dimensional weaving.
  • the preform 30, held in the tooling is introduced into an enclosure to be densified by chemical vapor infiltration of a material constituting the matrix of the composite material, for example carbon or a ceramic, such as silicon carbide.
  • the infiltration can be carried out in several phases, including a first phase during which the infiltration is carried out only until a bond between the fibers of the preform is sufficient so that the latter retains its shape after removal of the tools.
  • a first phase during which the infiltration is carried out only until a bond between the fibers of the preform is sufficient so that the latter retains its shape after removal of the tools.
  • chemical vapor infiltration can be continued on the preform leaving the tooling until obtaining a densified part 40 (FIG. 6B).
  • machining is necessary at least to form the upper surface, as shown in section, FIG. 6C, as well as to form the external surfaces of the heels, in order to spare the clearance J, and to form the extreme edges of the heels, in order to give them a shape corresponding to that of the upper surface on which they are intended to rest.
  • the blades can thus be manufactured one by one from the development of the preform to densification and final machining.
  • the definition of the blades with asymmetrical heels allows an easy realization of the fibrous preform to form a profile of constant thickness, with a continuity of the layers of fabric forming the reinforcement.
  • FIGS. 7 and B Another embodiment of a turbine distributor according to the invention is illustrated in FIGS. 7 and B.
  • the same references designate the elements of this distributor similar to those of the distributor in FIGS. 3 to 5.
  • the turbine distributor of FIGS. 7 and 8 differs from that of FIGS. 3 to 5 by the shape of the blades 50. These have in fact a Z shape with a central part 52 constituting the aerodynamic profile similar to the central part 12 vanes 10 and two internal and external asymmetrical heels 54, 56 which extend respectively from the side of the upper surface 52b and from the side of the lower surface 52a.
  • the heels 54 and 56 of a blade 50 bear by their end edges 54a and 56a against, respectively, the lower surface of one of the neighboring blades and the upper surface of the other neighboring blade, and define the distance between the blades.
  • Pawns 18 determine the orientation of the blades 50 and block them in rotation.
  • the external faces 54b, 56b of the heels 54, 56 are in contact with the internal surfaces of the casings 20, 22 over only part of their surface, in order to provide clearance J ′.
  • the contact between the heels and the casings can in this case be located slightly behind the ends of the heels so that the compensation for differential expansion is effected at least in part by tilting the heels, and not only by bending them. this.
  • the blades 50 are produced by preparing a fiber preform, densifying it and final machining.
  • the preform is, as before, prepared by draping layers of fabric and molding in a tool of suitable shape.

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

Abstract

The vanes (10) are of thermostructural composite material and have asymmetrical internal (14) and external (16) projections, such that at least one of the projections of a vane rests on the outer face (12; 52b) or the inner face (12a) of an adjacent vane. In addition each of the projections (14, 16) of each vane rests on the adjacent housing solely by way of part of its external surface so as to permit bending of the projection under the effect of any differential expansion between vane and housing. <IMAGE>

Description

La présente invention concerne un aubage fixe de distributeur de turbine ou de compresseur à gaz.The present invention relates to a fixed vane of a turbine distributor or gas compressor.

Un distributeur de turbine comprend un ensemble d'aubes fixes disposées entre un carter intérieur et un carter extérieur. Les figures 1 et 2 illustrent un distributeur monobloc avec des aubes 1 entre des carters intérieur 2 et extérieur 3.A turbine distributor includes a set of fixed blades arranged between an inner casing and an outer casing. FIGS. 1 and 2 illustrate a one-piece distributor with vanes 1 between interior 2 and exterior 3 casings.

Habituellement, les technologies utilisées pour la fabrication d'un distributeur de turbine sont la fonderie et la forge de précision, que ce soit pour fabriquer une pièce monobloc, ou pour fabriquer un distributeur à aubes rapportées.Usually, the technologies used for the manufacture of a turbine distributor are foundry and precision forging, whether it is to manufacture a single piece, or to manufacture a distributor with added blades.

Pour assurer un fonctionnement à des températures élevées, il peut être envisagé de remplacer les aubages traditionnels en métal ou alliage métallique par des aubages en matériau réfractaire.To ensure operation at high temperatures, it can be envisaged to replace traditional metal or metal alloy blades with blades made of refractory material.

La réalisation des aubes en céramique massive, notamment en céramique frittée est difficile à envisager. En effet, en raison de leur nature fragile, les céramiques frittées ont généralement des tenues aux chocs thermiques et des caractéristiques mécaniques limitées. Par conséquent, des problèmes difficiles à résoudre seraient en particulier rencontrés pour réaliser un montage des aubes entre les carters intérieur et extérieur évitant l'application sur les aubes de toute contrainte due à une dilatation différentielle.The production of blades in solid ceramic, in particular in sintered ceramic, is difficult to envisage. Indeed, due to their fragile nature, sintered ceramics generally have resistance to thermal shock and limited mechanical characteristics. Consequently, problems which are difficult to solve would in particular be encountered in mounting the blades between the inner and outer casings avoiding the application to the blades of any stress due to differential expansion.

Aussi, les inventeurs ont envisagé la réalisation des aubes en un matériau composite thermostructural.Also, the inventors have envisaged the production of the blades in a thermostructural composite material.

Les matériaux composites thermostructuraux sont bien connus. Ils sont constitués par un renfort fibreux réfractaire, par exemple en fibres de carbone ou en fibres céramiques, densifié par une matrice réfractaire, par exemple également en carbone ou céramique. Ces matériaux, en raison de la présence d'une texture de renfort fibreux et de leur nature réfractaire, ont une bonne tenue mécanique, qui les rend aptes à constituer des éléments de structure, et conservent leurs caractéristiques mécaniques jusqu'à des températures élevées, et ne présentent pas le caractère fragile des céramiques massives.Thermostructural composite materials are well known. They consist of a refractory fibrous reinforcement, for example made of carbon fibers or ceramic fibers, densified by a refractory matrix, for example also made of carbon or ceramic. These materials, due to the presence of a fibrous reinforcing texture and their refractory nature, have good mechanical strength, which makes them capable of constituting structural elements, and retain their mechanical characteristics up to high temperatures, and do not have the brittle nature of solid ceramics.

C'est pourquoi la présente invention a pour but de proposer une architecture de distributeur de turbine ou de compresseur à gaz particulièrement adaptée à la réalisation des aubes fixes en matériau composite thermostructural.This is why the present invention aims to propose an architecture for a turbine distributor or a gas compressor which is particularly suitable for producing fixed vanes made of thermostructural composite material.

Ce but est atteint grâce à un distributeur formé d'aubes fixes rapportées disposées entre un carter intérieur et un carter extérieur, chaque aube ayant une partie formant profil aérodynamique et de talons intérieur et extérieur qui définissent les distances entre aubes voisines, aubage dans lequel, conformément à l'invention :

  • le aubes sont en matériau composite thermostructural,
  • les talons intérieur et extérieur de chaque aube sont asymétriques, de sorte que l'un au moins des talons d'une aube s'appuie sur l'extrados ou l'intrados d'une aube voisine, et
  • l'un au moins des talons de chaque aube est en appui sur le carter adjacent par une partie seulement de sa surface externe, de manière à autoriser une flexion sous l'effet d'une dilatation différentielle entre l'aube et le carter.
This object is achieved thanks to a distributor formed of fixed fixed blades arranged between an inner casing and an outer casing, each blade having an aerodynamic profile portion and internal and external heels which define the distances between neighboring blades, blade in which, in accordance with the invention:
  • the blades are made of thermostructural composite material,
  • the inner and outer heels of each blade are asymmetrical, so that at least one of the heels of a blade rests on the upper surface or the lower surface of a neighboring blade, and
  • at least one of the heels of each blade is resting on the adjacent casing by only part of its external surface, so as to allow bending under the effect of differential expansion between the blade and the casing.

Comme expliqué plus loin, le fait de prévoir chaque aube avec des talons asymétriques, c'est-à-dire avec des talons s'étendant chacun d'un seul côté du profil aérodynamique, permet une élaboration relativement aisée du renfort fibreux des aubes, par exemple par formage d'une préforme constituée de strates de tissus ou d'une texture tridimensionnelle telle qu'une texture aiguilletée.As explained below, the fact of providing each blade with asymmetrical heels, that is to say with heels each extending on one side of the airfoil, allows a relatively easy development of the fiber reinforcement of the blades, for example by forming a preform consisting of tissue layers or a three-dimensional texture such as a needle texture.

En outre, le montage particulier des aubes entre les carters et le comportement élastique en flexion du matériau composite autorisent des dilatations différentielles sans dommage pour l'aubage.In addition, the particular mounting of the blades between the casings and the elastic bending behavior of the composite material allow differential expansions without damage to the blading.

L'invention sera mieux comprise à la lecture de la description faite ci-après, à titre indicatif mais non limitatif, en référence aux dessin annexés sur lesquels :

  • la figure 1 illustre très schématiquement une partie d'un distributeur de turbine monobloc de l'art antérieur,
  • la figure 2 est une vue en coupe d'une aube du distributeur de la figure 1,
  • la figure 3 illustre très schématiquement une partie d'un distributeur de turbine selon un mode de réalisation de l'invention,
  • la figure 4 est une vue schématique en perspective d'une aube du distributeur de la figure 3,
  • la figure 5 est une vue en coupe suivant le plan V de la figure 4 montrant le profil aérodynamique formé par la partie centrale de l'aube de la figure 4,
  • les figures 6A à 6C illustrent différentes phases du processus de réalisation d'une aube en matériau composite thermostructural telle que celle de la figure 4,
  • la figure 7 illustre très schématiquement une partie d'un distributeur de turbine selon un autre mode de réalisation de l'invention, et
  • la figure 8 est une vue schématique en perspective d'une aube du distributeur de la figure 7.
The invention will be better understood on reading the description given below, by way of indication but not limitation, with reference to the appended drawings in which:
  • Figure 1 illustrates very schematically a part a one-piece turbine distributor of the prior art,
  • FIG. 2 is a sectional view of a blade of the distributor of FIG. 1,
  • FIG. 3 very schematically illustrates part of a turbine distributor according to an embodiment of the invention,
  • FIG. 4 is a schematic perspective view of a blade of the distributor of FIG. 3,
  • FIG. 5 is a sectional view along the plane V of FIG. 4 showing the aerodynamic profile formed by the central part of the blade of FIG. 4,
  • FIGS. 6A to 6C illustrate different phases of the process for producing a blade made of thermostructural composite material such as that of FIG. 4,
  • FIG. 7 very schematically illustrates part of a turbine distributor according to another embodiment of the invention, and
  • FIG. 8 is a schematic perspective view of a blade of the distributor of FIG. 7.

Un premier mode de réalisation d'un distributeur de turbine muni d'aubes fixes et conformes à la présente invention est illustré par les figures 3 à 5.A first embodiment of a turbine distributor provided with fixed blades and in accordance with the present invention is illustrated by FIGS. 3 to 5.

Les aubes fixes 10 sont montées entre un carter annulaire intérieur 20 et un carter annulaire extérieur 22. Chaque aube 10 a sensiblement une forme de C avec une partie centrale 12 formant profil aérodynamique prolongée par deux talons asymétriques intérieur 14 et extérieur 16. Les talons 14 et 16 s'étendent d'un seul et même côté de la partie 12, en l'espèce du côté de l'intrados 12a.The fixed vanes 10 are mounted between an inner annular casing 20 and an outer annular casing 22. Each vane 10 has a substantially C shape with a central part 12 forming an aerodynamic profile extended by two asymmetrical heels, interior 14 and exterior 16. Heels 14 and 16 extend on one and the same side of the part 12, in this case on the side of the lower surface 12a.

Les talons 14, 16, d'une aube s'appuient par leurs bords d'extrémité 14a, 16a sur l'extrados 12b d'une aube voisine et définissent par conséquent la distance ou pas entre les aubes, les bords 14a, 16a des talons ayant une forme qui épouse celle de l'extrados 12b.The heels 14, 16 of a blade rest by their end edges 14a, 16a on the upper surface 12b of a neighboring blade and consequently define the distance or not between the blades, the edges 14a, 16a of the blades. heels having a shape which matches that of the upper surface 12b.

Des pions 16 sont logés dans des trous formés dans les faces internes des carters 20 et 22 et font saillie dans l'intervalle entre ceux-ci. Les pions 18 forment des butées contre lesquelles s'appuient les talons d'au moins une aube 10, des encoches recevant les pions 18 étant formées à cet effet dans les bords d'extrémité des talons. Les pions 18 déterminent l'orientation des aubes 10 dans l'intervalle entre les carters, c'est-à-dire essentiellement l'orientation des profils aérodynamiques 12. En outre, les pions 18 assurent un blocage en rotation des aubes 10 après leur montage.Pawns 16 are housed in holes formed in the internal faces of housings 20 and 22 and protrude in the interval between them. The pins 18 form stops against which the heels of at least one blade 10 bear, notches receiving the pins 18 being formed for this purpose in the end edges of the heels. The pins 18 determine the orientation of the blades 10 in the gap between the housings, that is to say essentially the orientation of the aerodynamic profiles 12. In addition, the pins 18 ensure a rotation lock of the blades 10 after their mounting.

Les talons 14 et 16 ont des surfaces externes 14b, 16b non exactement cylindriques de sorte qu'elles n'épousent pas les faces internes des carters 20, 22. Plus précisément, chaque talon 14, 16 s'appuie sur le carter correspondant par une partie seulement de sa surface externe, au voisinage de son extrémité 14a, 16a. Ainsi, à partir de la zone d'appui de chaque talon, un jeu J est ménagé entre le talon et la surface du carter adjacent, jeu qui peut croître progressivement jusqu'au niveau de la partie centrale 12.The heels 14 and 16 have external surfaces 14b, 16b which are not exactly cylindrical so that they do not match the internal faces of the casings 20, 22. More precisely, each heel 14, 16 is supported on the corresponding casing by a only part of its external surface, in the vicinity of its end 14a, 16a. Thus, from the bearing zone of each heel, a clearance J is formed between the heel and the surface of the adjacent casing, clearance which can gradually increase up to the level of the central part 12.

Les aubes 10 sont réalisées en un matériau composite thermostructural qui, par sa nature, présente une certaine élasticité en flexion. De ce fait, et grâce aux jeux J, les aubes 10 peuvent s'accomoder sans dommage de dilatations différentielles entre elles-mêmes et les carters 20, 22, ceux-ci pouvant être dans le même matériau que les aubes, ou dans un matériau différent, par exemple métallique. Au montage, à température ambiante, les talons des aubes 10 sont au mois légèrement précontraints en flexion pour assurer un appui effectif sur les faces internes des carters.The blades 10 are made of a thermostructural composite material which, by its nature, has a certain elasticity in bending. Therefore, and thanks to the games J, the blades 10 can accommodate without damage differential expansions between themselves and the housings 20, 22, these can be in the same material as the blades, or in a material different, for example metallic. During assembly, at room temperature, the heels of the blades 10 are at least slightly prestressed in bending to ensure effective support on the internal faces of the casings.

En variante, il est possible de ménager un jeu J entre seulement l'un des talons de chaque aube et le carter adjacent, l'autre talon épousant la face interne du carter contre laquelle il est en appui.As a variant, it is possible to provide a clearance J between only one of the heels of each blade and the adjacent casing, the other heel conforming to the internal face of the casing against which it is supported.

Toujours en variante, les aubes pourront présenter une forme en C avec des talons asymétriques qui s'étendent tous deux du côté de l'extrados.Also alternatively, the blades may have a C shape with asymmetrical heels which both extend on the side of the upper surface.

Un procédé de fabrication d'aubes 10 telles que celle de la figure 4 sera maintenant décrit en référence aux figures 6A à 6C.A method of manufacturing blades 10 such as that of FIG. 4 will now be described with reference to FIGS. 6A to 6C.

Une préforme fibreuse 30, destinée à constituer le renfort du matériau composite constitutif des aubes, est par exemple élaborée par empilement de strates de tissu 32 et moulage des strates dans un outillage 34.A fiber preform 30, intended to constitute the reinforcement of the composite material constituting the blades, is for example produced by stacking layers of fabric 32 and molding the layers in a tool 34.

Le tissu dans lequel sont découpées les strates 32 est en fibres réfractaires, par exemple en fibres de carbone ou en fibres céramiques, telles que des fibres de carbure de silicium.The fabric from which the layers 32 are cut is made of refractory fibers, for example carbon fibers or ceramic fibers, such as silicon carbide fibers.

L'outillage 34 comprend un poinçon 34a dont la forme est celle de l'intrados 12a et du profil interne des talons 14, 16. Le poinçon 34a définit, avec la partie complémentaire 34b de l'outillage 34 un volume d'épaisseur constante et de section en C dans laquelle s'inscrit la forme en C d'une aube 10.The tool 34 comprises a punch 34a whose shape is that of the lower surface 12a and of the internal profile of the heels 14, 16. The punch 34a defines, with the complementary part 34b of the tool 34, a volume of constant thickness and of C section in which the C shape of a blade 10 is inscribed.

La préforme 30 pourra être réalisée autrement que par empilement de strates de tissu, par exemple par mise en forme d'une texture tridimensionnelle ayant l'épaisseur désirée, telle qu'une texture aiguilletée ou une texture obtenue par tissage tridimensionnel.The preform 30 may be produced other than by stacking layers of fabric, for example by shaping a three-dimensional texture having the desired thickness, such as a needled texture or a texture obtained by three-dimensional weaving.

La préforme 30, maintenue dans l'outillage est introduite dans une enceinte pour être densifiée par infiltration chimique en phase vapeur d'une matière constituant la matrice du matériau composite, par exemple du carbone ou une céramique, telle que du carbure de silicium.The preform 30, held in the tooling, is introduced into an enclosure to be densified by chemical vapor infiltration of a material constituting the matrix of the composite material, for example carbon or a ceramic, such as silicon carbide.

Les procédés d'infiltration chimique en phase vapeur de carbone ou de carbure de silicium sont bien connus de sorte qu'il n'est pas nécessaire de les décrire ici en détail.The methods of chemical vapor infiltration of carbon or silicon carbide are well known so that it is not necessary to describe them here in detail.

L'infiltration peut être réalisée en plusieurs phases, dont une première phase au cours de laquelle l'infiltration est réalisée seulement jusqu'à obtenir une liaison entre les fibres de la préforme qui soit suffisante pour que celle-ci conserve sa forme après retrait de l'outillage. Après cette première phase de consolidation, l'infiltration chimique en phase vapeur peut être poursuivie sur la préforme sortie de l'outillage jusqu'à obtenir une pièce densifiée 40 (figure 6B).The infiltration can be carried out in several phases, including a first phase during which the infiltration is carried out only until a bond between the fibers of the preform is sufficient so that the latter retains its shape after removal of the tools. After this first consolidation phase, chemical vapor infiltration can be continued on the preform leaving the tooling until obtaining a densified part 40 (FIG. 6B).

Après densification, un usinage est nécessaire au moins pour former l'extrados, comme le montre, en coupe, la figure 6C, ainsi que pour former les surfaces externes des talons, afin de ménager le jeu J, et pour former les bords extrêmes des talons, afin de leur donner une forme correspondant à celle de l'extrados sur lequel ils sont destinés à s'appuyer.After densification, machining is necessary at least to form the upper surface, as shown in section, FIG. 6C, as well as to form the external surfaces of the heels, in order to spare the clearance J, and to form the extreme edges of the heels, in order to give them a shape corresponding to that of the upper surface on which they are intended to rest.

Les aubes peuvent ainsi être fabriquées une par une depuis l'élaboration de la préforme jusqu'à la densification et l'usinage final.The blades can thus be manufactured one by one from the development of the preform to densification and final machining.

En variante, il est possible de réaliser un profilé densifié de longueur correspondant à plusieurs aubes. Le profilé est alors découpé avant usinage des aubes.As a variant, it is possible to produce a densified profile of length corresponding to several blades. The profile is then cut before machining the blades.

La définition des aubes avec des talons asymétriques permet une réalisation aisée de la préforme fibreuse pour former un profilé d'épaisseur constante, avec une continuité des strates de tissu formant le renfort.The definition of the blades with asymmetrical heels allows an easy realization of the fibrous preform to form a profile of constant thickness, with a continuity of the layers of fabric forming the reinforcement.

Il en serait différemment pour des aubes ayant des talons symétriques, par exemple des aubes en forme de I, pour lesquelles la réalisation de la préforme serait notablement plus complexe.It would be different for blades having symmetrical heels, for example I-shaped blades, for which the production of the preform would be notably more complex.

Un autre mode de réalisation d'un distributeur de turbine selon l'invention est illustré par les figures 7 et B. Des mêmes références désignent les éléments de ce distributeur semblables à ceux du distributeur des figures 3 à 5.Another embodiment of a turbine distributor according to the invention is illustrated in FIGS. 7 and B. The same references designate the elements of this distributor similar to those of the distributor in FIGS. 3 to 5.

Le distributeur de turbine des figures 7 et 8 se distingue de celui des figures 3 à 5 par la forme des aubes 50. Celles-ci ont en effet une forme en Z avec une partie centrale 52 constituant le profil aérodynamique semblable à la partie centrale 12 des aubes 10 et deux talons asymétriques intérieur et extérieur 54, 56 qui s'étendent respectivement du côté de l'extrados 52b et du côté de l'intrados 52a.The turbine distributor of FIGS. 7 and 8 differs from that of FIGS. 3 to 5 by the shape of the blades 50. These have in fact a Z shape with a central part 52 constituting the aerodynamic profile similar to the central part 12 vanes 10 and two internal and external asymmetrical heels 54, 56 which extend respectively from the side of the upper surface 52b and from the side of the lower surface 52a.

Bien entendu, les dispositions des talons 54 et 56 pourraient être inversées.Of course, the arrangements of the heels 54 and 56 could be reversed.

Les talons 54 et 56 d'une aube 50 s'appuient par leurs bords d'extrémité 54a et 56a contre, respectivement, l'intrados d'une des aubes voisines et l'extrados de l'autre aube voisine, et définissent la distance entre les aubes.The heels 54 and 56 of a blade 50 bear by their end edges 54a and 56a against, respectively, the lower surface of one of the neighboring blades and the upper surface of the other neighboring blade, and define the distance between the blades.

Des pions 18 déterminent l'orientation des aubes 50 et bloquent celles-ci en rotation.Pawns 18 determine the orientation of the blades 50 and block them in rotation.

Comme le montre la figure 7, les faces externes 54b, 56b des talons 54, 56 sont en contact avec les surfaces internes des carters 20, 22 sur une partie seulement de leur surface, afin de ménager des jeux J′. Le contact entre les talons et les carters peut dans ce cas être situé quelque peu en retrait des extrémités des talons de sorte que la compensation de dilatation différentielle se fasse au moins en partie par basculement des talons, et non pas seulement par flexion de ceux-ci.As shown in FIG. 7, the external faces 54b, 56b of the heels 54, 56 are in contact with the internal surfaces of the casings 20, 22 over only part of their surface, in order to provide clearance J ′. The contact between the heels and the casings can in this case be located slightly behind the ends of the heels so that the compensation for differential expansion is effected at least in part by tilting the heels, and not only by bending them. this.

La fabrication des aubes 50 est réalisée par élaboration d'une préforme fibreuse, densification de celle-ci et usinage final. La préforme est, comme précédemment, élaborée par drapage de strates de tissu et moulage dans un outillage de forme appropriée.The blades 50 are produced by preparing a fiber preform, densifying it and final machining. The preform is, as before, prepared by draping layers of fabric and molding in a tool of suitable shape.

Claims (8)

Distributeur, notamment de turbine, formé d'aubes fixes (10 ; 50) rapportées disposées entre un carter intérieur (20) et un carter extérieur (22), chaque aube ayant une partie (12 ; 52) formant profil aérodynamique et de talons intérieur (14 ; 54) et extérieur (16 ; 56) qui définissent les distances entre aubes voisines,
caractérisé en ce que : - les aubes (10 ; 50) sont en matériau composite thermostructural, - les talons intérieur (14 ; 54) et extérieur (16 ; 56) de chaque aube sont asymétriques, de sorte que l'un au moins des talons d'une aube s'appuie sur l'extrados (12 ; 52b) ou l'intrados (12a ; 52a) d'une aube voisine, et - l'un au moins des talons (14, 16 ; 54, 56) de chaque aube est en appui sur le carter adjacent par une partie seulement de sa surface externe, de manière à autoriser une flexion sous l'effet d'une dilatation différentielle entre l'aube et le carter. Distributor, in particular of a turbine, formed from fixed vanes (10; 50) attached arranged between an inner casing (20) and an outer casing (22), each vane having a part (12; 52) forming an aerodynamic profile and inner heels (14; 54) and outside (16; 56) which define the distances between neighboring blades,
characterized in that: - the blades (10; 50) are made of thermostructural composite material, - the inner (14; 54) and outer (16; 56) heels of each blade are asymmetrical, so that at least one of the heels of a blade rests on the upper surface (12; 52b) or l '' intrados (12a; 52a) of a neighboring dawn, and - at least one of the heels (14, 16; 54, 56) of each blade is in abutment on the adjacent casing by only part of its external surface, so as to allow bending under the effect of expansion differential between the blade and the casing. Distributeur selon la revendication 1, caractérisé en ce que l'appui partiel entre un talon (14, 16) d'une aube (10) et le carter adjacent (20, 22) est réalisé au voisinage de l'extrémité du talon.Distributor according to claim 1, characterized in that the partial support between a heel (14, 16) of a blade (10) and the adjacent casing (20, 22) is produced in the vicinity of the end of the heel. Distributeur selon l'une quelconque des revendications 1 et 2, caractérisé en ce que les talons intérieur (14) et extérieur (16) de chaque aube (10) sont situés d'un même côté de la partie (12) formant profil aérodynamique.Distributor according to either of Claims 1 and 2, characterized in that the internal (14) and external (16) heels of each blade (10) are located on the same side of the part (12) forming an aerodynamic profile. Distributeur selon l'une quelconque des revendications 1 et 2, caractérisé en ce que les talons intérieur (54) et extérieur (56) de chaque aube (50) sont situés respectivement d'un côté et de l'autre côté de la partie (52) formant profil aérodynamique.Distributor according to either of Claims 1 and 2, characterized in that the internal (54) and external (56) heels of each blade (50) are located respectively on one side and on the other side of the part ( 52) forming an aerodynamic profile. Distributeur selon l'une quelconque des revendications 1 à 4, caractérisé en ce que chaque talon (14, 16 ; 54, 56) d'une aube (10 ; 50) est en appui sur le carter adjacent (20, 22) par une partie seulement de sa surface externe.Distributor according to any one of claims 1 to 4, characterized in that each heel (14, 16; 54, 56) of a blade (10; 50) is supported on the adjacent casing (20, 22) by a only part of its external surface. Distributeur selon l'une quelconque des revendications 1 à 5, caractérisé en ce qu'il comprend des pions (18) solidaires des carters intérieur (20) et extérieur (22) et sur lesquels s'appuient les bords des talons (14, 16 ; 54, 56) d'au moins une aube (10 ; 50) afin d'immobiliser les aubes entre les carters intérieur et extérieur dans des positions voulues.Distributor according to any one of claims 1 to 5, characterized in that it comprises pins (18) integral with the inner (20) and outer (22) casings and on which the edges of the heels (14, 16 are supported) ; 54, 56) of at least one blade (10; 50) in order to immobilize the blades between the inner and outer casings in desired positions. Distributeur selon l'une quelconque des revendications 1 à 6, caractérisé en ce que les aubes (10 ; 50) sont réalisées en matériau composite à matrice céramique.Distributor according to any one of Claims 1 to 6, characterized in that the blades (10; 50) are made of composite material with a ceramic matrix. Procédé de fabrication d'aubes fixes pour un distributeur selon l'une quelconque des revendications 1 à 7, caractérisé en ce qu'il comprend les étapes qui consistent à : - élaborer une préforme fibreuse en fibres réfractaires dont le profil correspond sensiblement à celui d'une aube à réaliser, - densifier la préforme fibreuse par infiltration chimique en phase vapeur d'une matière réfractaire, et - usiner la pièce obtenue au moins dans sa partie destinée à former profil aérodynamique. Method of manufacturing stationary vanes for a distributor according to any one of Claims 1 to 7, characterized in that it comprises the steps which consist in: - develop a fibrous preform of refractory fibers whose profile corresponds substantially to that of a blade to be produced, densifying the fibrous preform by chemical vapor infiltration of a refractory material, and - machine the part obtained at least in its part intended to form an aerodynamic profile.
EP91401948A 1990-07-12 1991-07-12 Statorranes for turbines made from thermostructural composite material Expired - Lifetime EP0466602B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9008903A FR2664647B1 (en) 1990-07-12 1990-07-12 DISPENSER, PARTICULARLY FOR TURBINE, WITH FIXED BLADES OF THERMOSTRUCTURAL COMPOSITE MATERIAL, AND MANUFACTURING METHOD.
FR9008903 1990-07-12

Publications (2)

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EP0466602A1 true EP0466602A1 (en) 1992-01-15
EP0466602B1 EP0466602B1 (en) 1995-06-28

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EP91401948A Expired - Lifetime EP0466602B1 (en) 1990-07-12 1991-07-12 Statorranes for turbines made from thermostructural composite material

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US (1) US5131808A (en)
EP (1) EP0466602B1 (en)
JP (1) JP3053125B2 (en)
CA (1) CA2046173C (en)
DE (1) DE69110777T2 (en)
FR (1) FR2664647B1 (en)

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WO1996015356A1 (en) * 1994-11-15 1996-05-23 Solar Turbines Incorporated An improved airfoil structure
WO2010146288A1 (en) 2009-06-18 2010-12-23 Snecma Turbine distributor element made of cmc, method for making same, distributor and gas turbine including same
US20140064956A1 (en) * 2012-09-06 2014-03-06 Rolls-Royce Plc Guide vane assembly
WO2018057086A1 (en) * 2016-09-21 2018-03-29 General Electric Company Composite airfoil singlet and corresponding assembly of singlets
CN109695480A (en) * 2017-10-23 2019-04-30 赛峰航空器发动机 Turbogenerator comprising aligning component
WO2023198979A1 (en) * 2022-04-15 2023-10-19 Safran Aircraft Engines Turbine engine motor having an unducted fan

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US9334743B2 (en) 2011-05-26 2016-05-10 United Technologies Corporation Ceramic matrix composite airfoil for a gas turbine engine
JP6372210B2 (en) 2014-07-14 2018-08-15 株式会社Ihi Turbine vane made of ceramic matrix composite
US9845692B2 (en) * 2015-05-05 2017-12-19 General Electric Company Turbine component connection with thermally stress-free fastener
JP6763157B2 (en) * 2016-03-11 2020-09-30 株式会社Ihi Turbine nozzle
FR3050759B1 (en) * 2016-04-27 2020-02-07 Safran Aircraft Engines AIR FLOW STRAIGHTENING ASSEMBLY AND TURBOMACHINE COMPRISING SUCH AN ASSEMBLY
US11603765B1 (en) * 2021-07-16 2023-03-14 Raytheon Technologies Corporation Airfoil assembly with fiber-reinforced composite rings and toothed exit slot
US12000306B2 (en) * 2022-06-03 2024-06-04 Rtx Corporation Vane arc segment with single-sided platforms

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Cited By (12)

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Publication number Priority date Publication date Assignee Title
WO1996015356A1 (en) * 1994-11-15 1996-05-23 Solar Turbines Incorporated An improved airfoil structure
WO2010146288A1 (en) 2009-06-18 2010-12-23 Snecma Turbine distributor element made of cmc, method for making same, distributor and gas turbine including same
FR2946999A1 (en) * 2009-06-18 2010-12-24 Snecma CMC TURBINE DISPENSER ELEMENT, PROCESS FOR MANUFACTURING SAME, AND DISPENSER AND GAS TURBINE INCORPORATING SAME.
US9022733B2 (en) 2009-06-18 2015-05-05 Snecma Turbine distributor element made of CMC, method for making same, distributor and gas turbine including same
US20140064956A1 (en) * 2012-09-06 2014-03-06 Rolls-Royce Plc Guide vane assembly
US9777585B2 (en) * 2012-09-06 2017-10-03 Rolls-Royce Plc Guide vane assembly
WO2018057086A1 (en) * 2016-09-21 2018-03-29 General Electric Company Composite airfoil singlet and corresponding assembly of singlets
US10443625B2 (en) 2016-09-21 2019-10-15 General Electric Company Airfoil singlets
CN109695480A (en) * 2017-10-23 2019-04-30 赛峰航空器发动机 Turbogenerator comprising aligning component
CN109695480B (en) * 2017-10-23 2024-03-29 赛峰航空器发动机 Turbine engine including straightening assembly
WO2023198979A1 (en) * 2022-04-15 2023-10-19 Safran Aircraft Engines Turbine engine motor having an unducted fan
FR3134598A1 (en) * 2022-04-15 2023-10-20 Safran Aircraft Engines Fixed blade made of composite materials fixed radially on a fixed structure of a turbomachine

Also Published As

Publication number Publication date
DE69110777T2 (en) 1996-03-21
EP0466602B1 (en) 1995-06-28
JPH04232306A (en) 1992-08-20
FR2664647A1 (en) 1992-01-17
US5131808A (en) 1992-07-21
DE69110777D1 (en) 1995-08-03
CA2046173A1 (en) 1992-01-13
JP3053125B2 (en) 2000-06-19
FR2664647B1 (en) 1994-08-26
CA2046173C (en) 2000-11-21

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