EP2603670B1 - Device for locking a root of a rotor blade - Google Patents

Device for locking a root of a rotor blade Download PDF

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Publication number
EP2603670B1
EP2603670B1 EP11758248.6A EP11758248A EP2603670B1 EP 2603670 B1 EP2603670 B1 EP 2603670B1 EP 11758248 A EP11758248 A EP 11758248A EP 2603670 B1 EP2603670 B1 EP 2603670B1
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EP
European Patent Office
Prior art keywords
rotor
blade
groove
root
blocking
Prior art date
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Application number
EP11758248.6A
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German (de)
French (fr)
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EP2603670A1 (en
Inventor
Jacques René Bart
Antoine Jean-Philippe Beaujard
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP2603670A1 publication Critical patent/EP2603670A1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor

Definitions

  • the invention relates to the field of turbomachine rotors and, more particularly, the maintenance of the rotor blades on a rotor disk.
  • a front-blower and double-body turbojet engine typically comprises, from upstream to downstream, a blower, a low-pressure compressor stage, a high-pressure compressor stage, a combustion chamber, a high-pressure turbine stage, and a high-pressure turbine stage. low pressure turbine stage.
  • upstream and downstream are defined with respect to the direction of air circulation in the turbojet engine.
  • inside and outside are defined radially with respect to the axis of the motor.
  • a cylinder extending along the axis of the engine has an inner face facing the axis of the motor and an outer surface opposite to its inner surface.
  • a low-pressure turbine stage for example, comprises successive rotor discs 1 each having axial or oblique grooves 11 in which blades 2 are engaged by their feet 3, the blades 2 extending radially outwards by relative to the X axis of the engine.
  • the blades 2 are retained radially in the grooves by their feet 3 in the form of fir, which also allows to provide a space between the foot 3 and the bottom of the groove to allow a flow of air which is guided in the body blades to ventilate them.
  • the blades 2 are retained axially upstream by a sealing ring 4 comprising sealing lamellae, the sealing ring 4 being known to those skilled in the art under the designation "labyrinth ring".
  • a circumferential ring sector 5 is mounted between a groove 6 of the rotor disk 1 and a downstream hook 7 of the blade root 3 2.
  • the sector ring 5 blocks the axial displacement of the blade 2 downstream, the blade 2 remaining integral with the rotor disc 1.
  • the feet 3 of the blades 2 are made of metallic material.
  • the current method of fixing a metal foot can not be transposed for the attachment of a foot composite material.
  • a traditional composite material does not allow to simply form concave areas in the blade root.
  • the manufacture of a blade root, having a fir-shaped, composite material is not preferred. Indeed, during the operation of the engine, differential expansions appear and the fir-shaped foot teeth are no longer supported in the groove of the rotor disc. The radial retention of the dawn is not satisfactory.
  • this simple mounting device allows to block radially and axially a blade with a rotor disk according to the prior art.
  • Such a monobloc device makes it possible to guarantee correct positioning of each tooth and each wedge intended to block the blade root.
  • the device is quick to mount in the rotor since each device may have several teeth and several blocking wedges.
  • the device comprises ventilation means, formed in said ring sector, arranged to allow evacuation of a flow of air flowing between the bottom of the groove and the blocking wedge.
  • the blocking wedge makes it possible to create a ventilation space between the blade root and the bottom of the groove in which circulates a flow of air that is evacuated by said ventilation means.
  • the ventilation means are aligned with the direction in which the blocking tooth extends.
  • the ventilation airflow cools the blocking wedge, the blade root and the bottom of the groove which are aligned axially with the blocking tooth.
  • the ventilation means are in the form of at least one ventilation orifice.
  • An orifice is easy to machine in the ring sector and allows evacuation of the ventilation airflow.
  • the ventilation means are in the form of at least one ventilation notch formed in the portion of the ring sector intended to be inserted into the groove of the rotor disc.
  • a ventilation notch allows to lighten the mass of the device while allowing the evacuation of the air flow.
  • the ring sector has a crenellated inner edge.
  • the ring sector has an inner radial portion, intended to be mounted in the groove of the rotor disk, and an outer radial portion, from which the blocking tooth extends, which are offset. axially with respect to each other along the ring axis.
  • this offset makes it possible to accurately position the locking device without creating significant overhang for the blocking wedge with respect to its attachment in the groove. A tilting of the locking device is then limited.
  • the invention also relates to a rotor of a turbomachine comprising a rotor disk, at least one rotor blade and at least one locking device as presented above, the rotor disk having a groove in which is housed a foot of the rotor. blade and a groove in which is mounted the locking device, the blocking wedge of the locking device extending between the blade root and the bottom of the groove.
  • the rotor disk extending axially from upstream to downstream, the groove is formed at the downstream end of the rotor disc so as to block an axial displacement downstream of the blade in the groove.
  • the root of the rotor blade comprises a casing of composite material.
  • the blade root of composite material preferably ceramic matrix, is simple to manufacture and allows to form a rotor having all the advantages of a rotor according to the prior art with metal vanes.
  • the root of the rotor blade has a dovetail shape. Thanks to the locking device according to the invention, the blade can be blocked radially which prevents any defect positioning of the blade in its housing when the rotor is stopped.
  • the invention will now be presented for a rotor of a turbomachine forming a low pressure turbine stage.
  • the rotor comprises a low-pressure turbine rotor disk 1, extending axially along an axis X as shown in FIG. figure 3 , in which are formed axial grooves or oblique 11 in which are engaged blades 2 by their feet 3, the blades 2 extending radially outwardly relative to the axis X of the motor.
  • the rotor disc 1 comprises an annular groove 6 extending radially inwards and arranged downstream of the groove 11 of the rotor disc 1.
  • the invention is here described for a downstream blocking but it goes without saying that it similarly applies for axial blocking upstream.
  • the rotor further comprises a locking device 8 of a root 3 of a rotor blade 2 in a groove 11 of the rotor disc 1 which will now be presented with reference to the Figures 2 to 6 .
  • the blocking device 8 comprises as many blocking wedges 82 as teeth 83.
  • each blade 2 of rotor disc 1 is blocked by a shim 82 and a blocking tooth 83.
  • the number of spacers 82 is equal to the number of blades 2 to be blocked.
  • the rotor disc 1 has 98 grooves 11 to receive as many blades 2.
  • the number of spacers 82 per device 8 may vary according to the number of blades of the rotor disc 1 or the number of devices 8 used to block the blades 2 of a rotor disc 1.
  • the locking device 8 generally comprises a circular ring sector 81, at least one locking wedge 82 and at least one blocking tooth 83 for axially locking the foot 3 of a rotor blade 3 housed in a groove 11 of the rotor disk 1 while allowing ventilation of the groove 11.
  • the circular ring sector 81 is intended to be mounted, transversely to the axis of the turbomachine, in a groove 6 of the rotor disc 1.
  • a circular ring sector is defined relative to to an axis which is subsequently designated ring axis S which is oriented from the rear towards the front on the figure 2 and which defines the axial direction.
  • the terms "forward” and "backward” are defined with respect to the S-ring axis.
  • the ring sector 81 extends radially with respect to the ring axis S in the radial direction of axis R, shown in FIG. figure 2 which is directed from the inside to the outside.
  • the circular ring sector 81 has a constant radius of curvature and is flattened in the axial direction S, its radial dimension being longer than its axial dimension.
  • the ring sector 81 has an open angle of the order of 30 ° but it goes without saying that this angle can be different.
  • the inner radial portion 84 of the ring sector 81 is axially offset from its outer radial portion 85 as shown in FIG. figure 2 .
  • the inner radial portion 84 is in front of the outer radial portion 85 so as to allow housing of the inner radial end 84 in the groove 6 of the rotor disc 1 while allowing the outer radial portion 85 to come to rest radially in the groove 11 of the rotor disc 1 as shown in figure 3 .
  • This characteristic will be detailed later in the example of implementation of the invention.
  • the locking wedge 82 of the blocking device 8 is integral and orthogonal to the ring sector 81, the spacer 82 extending from the rear face of the ring sector 81, parallel to the axis of FIG. ring S.
  • the blocking wedge 82 is arranged to radially support the root 3 of blade 2 in the groove 11 of the rotor disk 1.
  • the blocking wedge 82 is secured to the upper portion 85 of the ring sector 81 so as to raise the blade root 3 2 relative to the bottom of the groove 11 to allow air to flow into the groove 11 of the rotor disk 1.
  • the blocking wedge 82 of the locking device 8 is flattened in the radial direction R, its axial dimension being longer than its radial dimension.
  • the length of the blocking wedge 82 defined along the ring axis S is configured to support the blade root 3 2.
  • the length of the blocking wedge 82 corresponds to about 80% of the foot length 3 of blade 2 as shown on the figure 4 .
  • the length of the blocking wedge 82 can vary.
  • the length of the blocking wedge 82 is at least equal to half the length of the blade root 3 to distribute the forces on the blocking wedge 82.
  • the locking tooth 83 of the locking device 8 is integral and orthogonal to the blocking wedge 82.
  • the blocking tooth 83 of rectangular shape, extends from the upper part 85 of the ring sector 81 in the radial direction R outwardly, that is to say radially with respect to the axis of the ring sector S, so as to block the axial displacement of the blade root 3 in the groove 11 of the rotor disk 1.
  • the length of the tooth 83, defined along the radial axis R, is configured, in this example, to extend to the outer diameter of the rotor disk 1 when the locking device 8 is in the mounted position as shown in FIG. figure 3 .
  • the dimensions of the blocking tooth 83 are defined to resist the axial displacements of the blade root 3 during a rotation of the rotor.
  • the blocking tooth 83 is arranged to be axially aligned with the groove 11 of the rotor disc 1.
  • the rear face of the blocking tooth 83 also called the stop face, has a surface whose dimension is smaller than the section of the groove 11 of the rotor disc 1 as shown in the figure 3 .
  • Such locking tooth 83 makes it possible to fulfill its axial locking function while having a reduced mass because of its reduced dimensions.
  • the locking tooth 83 is foldable / retractable to allow a simple mounting of the locking device 8 in the groove 6, the tooth 83 being unfolded / output after assembly.
  • the locking device 8 further comprises ventilation means provided in the annular sector 81, preferably in its outer part 85, between the connecting zone of the blocking wedge 82 and the inner part 84 of the annular sector 81 as shown. on the figure 4 .
  • These ventilation means are in the form of apertures crossing in the axial direction the ring sector 81 so as to allow the evacuation of a flow of air F flowing between the bottom of the groove 11 and the shim blocking 82 as shown on the figure 4 .
  • the ventilation means are aligned radially with the blocking tooth 83, which makes it possible axially to block the blade root 3 while allowing ventilation of the groove 11.
  • the ventilation means are in the form of circular through orifices 91 as shown in FIGS. Figures 2 to 4 whose diameter is calibrated for ventilation.
  • Circular orifices 91 have the advantage of being simple to machine.
  • the ventilation means are in the form of through holes of elliptical section 92 whose small diameter preferably extends in the radial direction.
  • Elliptical section orifices 92 made for example by an inclined bore, have the advantage of offering a high air flow without affecting the mechanical strength in the radial direction of the ring sector 81. Indeed, the distance between the inner edge of the annular sector 81 and an elliptical orifice is larger than the distance between the inner edge of the annular sector 81 and a circular orifice which offers a better mechanical strength.
  • the ventilation means are in the form of notches 93 formed from the inner portion 84 of the ring sector 81 to its outer portion 85.
  • the inner end of the ring sector 81 is crenellated so
  • the notches 93 have the advantage of lightening the mass of the ring sector 81 while being simple to machine by drilling.
  • the notches 93 provide a large ventilation air flow.
  • the locking device 8 of the figure 2 is mounted in the rotor disc 1 by placing the blocking wedges 82 axially in the grooves 11 of the rotor disk 1 and inserting the inner portion 84 of the locking device 8 in the downstream groove 6 of the rotor disk 1 so as to that the upper portion 85 of the ring sector 81 is radially supported in the bottom of the groove 11 so as to provide a circulation space of an air flow F between the blocking wedge 82 and the bottom of the groove 11.
  • the axial offset also makes it possible to prevent tilting of the locking device 8 by limiting the cantilever of the locking device 8.
  • the inner portion 84 of the locking device 8 comes into contact with the downstream portion of the groove 6 which blocks the upward tilting of the shim 82.
  • the blocking wedge 82 is parallel to the bottom of the groove 11 once mounted.
  • the blocking tooth 83 extends radially with respect to the axis of the motor and is aligned axially with the groove 11.
  • the ventilation means here circular orifices 91, extend halfway up the circulation space of the air flow F between the blocking wedge 82 and the bottom of the groove 11, which makes it possible to ensure good air circulation.
  • the blade root 3 is then inserted into the groove 11 by axial displacement from upstream to downstream so that the foot 2 bears against the outer surface of the blocking wedge 82 to be retained radially. and thus avoid a defect in the positioning of the blade 2 in the disk 1, in particular when the engine is stopped. Furthermore, the blade root 3 bears against the upstream surface (stopping surface) of the locking tooth 83 to be axially locked.
  • the locking device 8 it is not necessary to use a blade at the foot of fir or to form a hook in the blade root to axially block the blade 2.
  • the root 3 of the rotor blade 2 has a simple dovetail shape whose envelope is made of a composite material. It is the locking device 8, and not the blade root 3 2, which performs the functions of axial blocking, radial blocking and ventilation of the groove 11 of the rotor disc 1.
  • Such a foot 3 is simple to manufacture and has a reduced mass.
  • the envelope of the blade root 3 is made of ceramic matrix composite material (CMC).
  • CMC ceramic matrix composite material

Description

L'invention concerne le domaine des rotors de turbomachine et, plus particulièrement, le maintien des aubes de rotor sur un disque de rotor.The invention relates to the field of turbomachine rotors and, more particularly, the maintenance of the rotor blades on a rotor disk.

Un turboréacteur à soufflante avant et à double corps, par exemple, comprend classiquement, d'amont en aval, une soufflante, un étage compresseur basse pression, un étage compresseur haute pression, une chambre de combustion, un étage de turbine haute pression et un étage de turbine basse pression.For example, a front-blower and double-body turbojet engine typically comprises, from upstream to downstream, a blower, a low-pressure compressor stage, a high-pressure compressor stage, a combustion chamber, a high-pressure turbine stage, and a high-pressure turbine stage. low pressure turbine stage.

Par convention, dans la présente demande, les termes « amont » et « aval » sont définis par rapport au sens de circulation de l'air dans le turboréacteur. De même, par convention dans la présente demande, les termes « intérieur » et « extérieur » sont définis radialement par rapport à l'axe du moteur. Ainsi, un cylindre s'étendant selon l'axe du moteur comporte une face intérieure tournée vers l'axe du moteur et une surface extérieure, opposée à sa surface intérieure.By convention, in the present application, the terms "upstream" and "downstream" are defined with respect to the direction of air circulation in the turbojet engine. Likewise, by convention in the present application, the terms "inside" and "outside" are defined radially with respect to the axis of the motor. Thus, a cylinder extending along the axis of the engine has an inner face facing the axis of the motor and an outer surface opposite to its inner surface.

De manière classique, en référence à la figure 1, un étage de turbine basse pression, par exemple, comprend des disques de rotor successifs 1 comportant chacun des rainures axiales ou obliques 11 dans lesquelles sont engagées des aubes 2 par leurs pieds 3, les aubes 2 s'étendant radialement vers l'extérieur par rapport à l'axe X du moteur.In a classical way, with reference to figure 1 a low-pressure turbine stage, for example, comprises successive rotor discs 1 each having axial or oblique grooves 11 in which blades 2 are engaged by their feet 3, the blades 2 extending radially outwards by relative to the X axis of the engine.

Les aubes 2 sont retenues radialement dans les rainures par leurs pieds 3 en forme de sapin, ce qui permet en outre de ménager un espace entre le pied 3 et le fond de la rainure pour permettre une circulation d'air qui est guidée dans le corps des aubes pour les ventiler. Les aubes 2 sont retenues axialement en amont par un anneau d'étanchéité 4 comportant des lamelles d'étanchéité, l'anneau d'étanchéité 4 étant connu de l'homme du métier sous la désignation « anneau labyrinthe ».The blades 2 are retained radially in the grooves by their feet 3 in the form of fir, which also allows to provide a space between the foot 3 and the bottom of the groove to allow a flow of air which is guided in the body blades to ventilate them. The blades 2 are retained axially upstream by a sealing ring 4 comprising sealing lamellae, the sealing ring 4 being known to those skilled in the art under the designation "labyrinth ring".

Pour retenir les aubes 2 axialement en aval, un secteur d'anneau circonférentiel 5 est monté entre une gorge 6 du disque de rotor 1 et un crochet aval 7 du pied 3 d'aube 2. Ainsi, en position d'utilisation, le secteur d'anneau 5 bloque le déplacement axial de l'aube 2 vers l'aval, l'aube 2 demeurant solidaire du disque de rotor 1.To retain the blades 2 axially downstream, a circumferential ring sector 5 is mounted between a groove 6 of the rotor disk 1 and a downstream hook 7 of the blade root 3 2. Thus, in the use position, the sector ring 5 blocks the axial displacement of the blade 2 downstream, the blade 2 remaining integral with the rotor disc 1.

Actuellement, les pieds 3 des aubes 2 sont en matériau métallique. Pour diminuer la masse du moteur, il est proposé de former des pieds 3 en matériau composite. Le mode de fixation actuel d'un pied métallique ne peut pas être transposé pour la fixation d'un pied en matériau composite. En effet, un matériau composite traditionnel ne permet pas de former simplement des zones concaves dans le pied d'aube. Ainsi, il est difficile de former un crochet aval dans le pied d'aube pour assurer la rétention axiale en aval de l'aube par un secteur d'anneau. En outre, la fabrication d'un pied d'aube, ayant une forme en sapin, en matériau composite n'est pas privilégiée. En effet, au cours du fonctionnement du moteur, des dilatations différentielles apparaissent et les dents du pied en forme de sapin ne sont plus en appui dans la rainure du disque de rotor. La rétention radiale de l'aube n'est pas satisfaisante.Currently, the feet 3 of the blades 2 are made of metallic material. To reduce the mass of the engine, it is proposed to form feet 3 of composite material. The current method of fixing a metal foot can not be transposed for the attachment of a foot composite material. Indeed, a traditional composite material does not allow to simply form concave areas in the blade root. Thus, it is difficult to form a downstream hook in the blade root to ensure the axial retention downstream of the blade by a ring sector. In addition, the manufacture of a blade root, having a fir-shaped, composite material is not preferred. Indeed, during the operation of the engine, differential expansions appear and the fir-shaped foot teeth are no longer supported in the groove of the rotor disc. The radial retention of the dawn is not satisfactory.

Des documents CA 604830 , US 4,781,534 et US 2008/0253895 A1 , on connaît des dispositifs de blocage d'un pied d'aube.Documents CA 604830 , US 4,781,534 and US 2008/0253895 A1 there are known devices for blocking a blade root.

Afin d'éliminer au moins certains de ces inconvénients, l'invention concerne un dispositif de blocage d'un pied d'une aube de rotor dans une rainure d'un disque de rotor d'une turbomachine selon la revendication 1, comportant :

  • un secteur d'anneau circulaire destiné à être monté, transversalement à l'axe de la turbomachine, dans une gorge du disque de rotor ;
  • au moins une cale de blocage, solidaire et orthogonale au secteur d'anneau, s'étendant parallèlement à l'axe du secteur d'anneau de manière à supporter radialement le pied de l'aube dans la rainure ; et
  • au moins une dent de blocage s'étendant depuis le secteur d'anneau radialement par rapport à l'axe du secteur d'anneau de manière à bloquer le déplacement axial du pied de l'aube dans la rainure.
In order to eliminate at least some of these disadvantages, the invention relates to a device for locking a root of a rotor blade in a groove of a rotor disk of a turbomachine according to claim 1, comprising:
  • a circular ring sector intended to be mounted, transversely to the axis of the turbomachine, in a groove of the rotor disc;
  • at least one blocking wedge, integral and orthogonal to the ring sector, extending parallel to the axis of the ring sector so as to radially support the root of the blade in the groove; and
  • at least one locking tooth extending from the ring sector radially relative to the axis of the ring sector so as to block the axial displacement of the root of the blade in the groove.

Grâce au dispositif, on peut avantageusement bloquer le pied d'une aube de rotor en queue d'aronde et ne comportant pas de crochet de blocage axial, en particulier, une aube en matériau composite. En outre, ce dispositif de montage simple permet de bloquer radialement et axialement une aube avec un disque de rotor selon l'art antérieur.Thanks to the device, it is advantageous to block the foot of a dovetail rotor blade and having no axial locking hook, in particular, a blade of composite material. In addition, this simple mounting device allows to block radially and axially a blade with a rotor disk according to the prior art.

Un tel dispositif monobloc permet de garantir un positionnement correct de chaque dent et de chaque cale destinée à bloquer le pied d'aube. En outre, le dispositif est rapide à monter dans le rotor étant donné que chaque dispositif peut comporter plusieurs dents et plusieurs cales de blocage. Le dispositif comporte des moyens de ventilation, ménagés dans ledit secteur d'anneau, agencés pour permettre une évacuation d'un flux d'air circulant entre le fond de la rainure et la cale de blocage. La cale de blocage permet de créer un espace de ventilation entre le pied d'aube et le fond de la rainure dans lequel circule un flux d'air qui est évacué par lesdits moyens de ventilation.Such a monobloc device makes it possible to guarantee correct positioning of each tooth and each wedge intended to block the blade root. In addition, the device is quick to mount in the rotor since each device may have several teeth and several blocking wedges. The device comprises ventilation means, formed in said ring sector, arranged to allow evacuation of a flow of air flowing between the bottom of the groove and the blocking wedge. The blocking wedge makes it possible to create a ventilation space between the blade root and the bottom of the groove in which circulates a flow of air that is evacuated by said ventilation means.

De préférence, les moyens de ventilation sont alignés avec la direction selon laquelle s'étend la dent de blocage. Ainsi, le flux d'air de ventilation refroidit la cale de blocage, le pied d'aube et le fond de la rainure qui sont alignés axialement avec la dent de blocage.Preferably, the ventilation means are aligned with the direction in which the blocking tooth extends. Thus, the ventilation airflow cools the blocking wedge, the blade root and the bottom of the groove which are aligned axially with the blocking tooth.

Selon une forme de réalisation de l'invention, les moyens de ventilation se présentent sous la forme d'au moins un orifice de ventilation. Un orifice est simple à usiner dans le secteur d'anneau et permet l'évacuation du flux d'air de ventilation.According to one embodiment of the invention, the ventilation means are in the form of at least one ventilation orifice. An orifice is easy to machine in the ring sector and allows evacuation of the ventilation airflow.

Selon une autre forme de réalisation de l'invention, les moyens de ventilation se présentent sous la forme d'au moins une encoche de ventilation ménagée dans la partie du secteur d'anneau destinée à être insérée dans la gorge du disque de rotor.According to another embodiment of the invention, the ventilation means are in the form of at least one ventilation notch formed in the portion of the ring sector intended to be inserted into the groove of the rotor disc.

Une encoche de ventilation permet d'alléger la masse du dispositif tout en permettant l'évacuation du flux d'air. De préférence, le secteur d'anneau comporte un bord intérieur crénelé.A ventilation notch allows to lighten the mass of the device while allowing the evacuation of the air flow. Preferably, the ring sector has a crenellated inner edge.

Selon un aspect de l'invention, le secteur d'anneau comporte une partie radiale intérieure, destinée à être montée dans la gorge du disque de rotor, et une partie radiale extérieure, depuis laquelle s'étend la dent de blocage, qui sont décalées axialement l'une par rapport à l'autre selon l'axe d'anneau.According to one aspect of the invention, the ring sector has an inner radial portion, intended to be mounted in the groove of the rotor disk, and an outer radial portion, from which the blocking tooth extends, which are offset. axially with respect to each other along the ring axis.

De manière avantageuse, ce décalage permet de positionner de manière précise le dispositif de blocage sans créer de porte-à-faux important pour la cale de blocage par rapport à sa fixation dans la gorge. Un basculement du dispositif de blocage est alors limité.Advantageously, this offset makes it possible to accurately position the locking device without creating significant overhang for the blocking wedge with respect to its attachment in the groove. A tilting of the locking device is then limited.

L'invention vise également un rotor d'une turbomachine comprenant un disque de rotor, au moins une aube de rotor et au moins un dispositif de blocage tel que présenté précédemment, le disque de rotor comportant une rainure dans laquelle est logé un pied de l'aube et une gorge dans laquelle est monté le dispositif de blocage, la cale de blocage du dispositif de blocage s'étendant entre le pied d'aube et le fond de la rainure.The invention also relates to a rotor of a turbomachine comprising a rotor disk, at least one rotor blade and at least one locking device as presented above, the rotor disk having a groove in which is housed a foot of the rotor. blade and a groove in which is mounted the locking device, the blocking wedge of the locking device extending between the blade root and the bottom of the groove.

De préférence, le disque de rotor s'étendant axialement de l'amont vers l'aval, la gorge est ménagée à l'extrémité aval du disque de rotor de manière à bloquer un déplacement axial vers l'aval de l'aube dans la rainure.Preferably, the rotor disk extending axially from upstream to downstream, the groove is formed at the downstream end of the rotor disc so as to block an axial displacement downstream of the blade in the groove.

Selon un aspect de l'invention, le pied de l'aube de rotor comporte une enveloppe en matériau composite.According to one aspect of the invention, the root of the rotor blade comprises a casing of composite material.

Le pied d'aube en matériau composite, de préférence à matrice céramique, est simple à fabriquer et permet de former un rotor comportant tous les avantages d'un rotor selon l'art antérieur avec des aubes métalliques.The blade root of composite material, preferably ceramic matrix, is simple to manufacture and allows to form a rotor having all the advantages of a rotor according to the prior art with metal vanes.

Selon un autre aspect de l'invention, le pied de l'aube de rotor possède une forme en queue d'aronde. Grâce au dispositif de blocage selon l'invention, l'aube peut être bloquée radialement ce qui empêche tout défaut de positionnement de l'aube dans son logement lorsque le rotor est à l'arrêt.According to another aspect of the invention, the root of the rotor blade has a dovetail shape. Thanks to the locking device according to the invention, the blade can be blocked radially which prevents any defect positioning of the blade in its housing when the rotor is stopped.

L'invention sera mieux comprise en référence au dessin annexé sur lequel :

  • la figure 1 est une vue en coupe radiale d'un disque de rotor d'une turbomachine dans lequel est monté une aube de rotor selon l'art antérieur ;
  • la figure 2 est une vue en perspective d'une première forme de réalisation d'un dispositif de blocage selon l'invention ;
  • la figure 3 est une vue en perspective d'un rotor selon l'invention comportant un dispositif de blocage selon la figure 2, le dispositif de blocage bloquant axialement une unique aube de rotor montée dans le disque de rotor ;
  • la figure 4 est une vue en coupe radiale du rotor de la figure 3 selon l'axe A-A ;
  • la figure 5 est une vue en perspective d'une deuxième forme de réalisation d'un dispositif de blocage selon l'invention ; et
  • la figure 6 est une vue en perspective d'une troisième forme de réalisation d'un dispositif de blocage selon l'invention.
The invention will be better understood with reference to the appended drawing in which:
  • the figure 1 is a radial sectional view of a rotor disk of a turbomachine in which is mounted a rotor blade according to the prior art;
  • the figure 2 is a perspective view of a first embodiment of a locking device according to the invention;
  • the figure 3 is a perspective view of a rotor according to the invention comprising a locking device according to the figure 2 , the locking device axially blocking a single rotor blade mounted in the rotor disc;
  • the figure 4 is a radial sectional view of the rotor of the figure 3 along the AA axis;
  • the figure 5 is a perspective view of a second embodiment of a locking device according to the invention; and
  • the figure 6 is a perspective view of a third embodiment of a locking device according to the invention.

L'invention va maintenant être présentée pour un rotor d'une turbomachine formant un étage de turbine basse pression. Le rotor comporte un disque de rotor de turbine basse pression 1, s'étendant axialement selon un axe X comme représenté sur la figure 3, dans lequel sont formées des rainures axiales ou obliques 11 dans lesquelles sont engagées des aubes 2 par leurs pieds 3, les aubes 2 s'étendant radialement vers l'extérieur par rapport à l'axe X du moteur. Le disque de rotor 1 comporte une gorge annulaire 6 s'étendant radialement vers l'intérieur ménagée en aval de la rainure 11 du disque de rotor 1. L'invention est ici décrite pour un blocage en aval mais il va de soi qu'elle s'applique de manière similaire pour un blocage axial en amont.The invention will now be presented for a rotor of a turbomachine forming a low pressure turbine stage. The rotor comprises a low-pressure turbine rotor disk 1, extending axially along an axis X as shown in FIG. figure 3 , in which are formed axial grooves or oblique 11 in which are engaged blades 2 by their feet 3, the blades 2 extending radially outwardly relative to the axis X of the motor. The rotor disc 1 comprises an annular groove 6 extending radially inwards and arranged downstream of the groove 11 of the rotor disc 1. The invention is here described for a downstream blocking but it goes without saying that it similarly applies for axial blocking upstream.

Le rotor comporte en outre un dispositif de blocage 8 d'un pied 3 d'une aube de rotor 2 dans une rainure 11 du disque de rotor 1 qui va être maintenant présenté en référence aux figures 2 à 6. De manière préférée, le dispositif de blocage 8 comporte autant de cales de blocage 82 que de dents 83. De préférence, chaque aube 2 de disque de rotor 1 est bloquée par une cale 82 et une dent de blocage 83.The rotor further comprises a locking device 8 of a root 3 of a rotor blade 2 in a groove 11 of the rotor disc 1 which will now be presented with reference to the Figures 2 to 6 . Preferably, the blocking device 8 comprises as many blocking wedges 82 as teeth 83. Preferably, each blade 2 of rotor disc 1 is blocked by a shim 82 and a blocking tooth 83.

Le nombre de cales 82 est égal aux nombres d'aubes 2 à bloquer. Dans cet exemple, le disque de rotor 1 comporte 98 rainures 11 pour recevoir autant d'aubes 2. Dans cet exemple, pour bloquer les aubes 2 dans les rainures 11, on dispose de 11 dispositifs de blocage 8 dont 10 comportent neuf cales 82 et dont un comporte huit cales 82, chaque dispositif 8 comportant autant de cales 82 que de dents de blocage 83.The number of spacers 82 is equal to the number of blades 2 to be blocked. In this example, the rotor disc 1 has 98 grooves 11 to receive as many blades 2. In this example, to block the blades 2 in the grooves 11, there are 11 locking devices 8 of which 10 have nine spacers 82 and one of which has eight spacers 82, each device 8 having as many spacers 82 as locking teeth 83.

Il va de soi que le nombre de cales 82 par dispositif 8 peut varier en fonction du nombre d'aubes du disque de rotor 1 ou du nombre de dispositifs 8 utilisés pour bloquer les aubes 2 d'un disque de rotor 1.It goes without saying that the number of spacers 82 per device 8 may vary according to the number of blades of the rotor disc 1 or the number of devices 8 used to block the blades 2 of a rotor disc 1.

En référence à la figure 2, le dispositif de blocage 8 comporte, de manière générale, un secteur d'anneau circulaire 81, au moins une cale de blocage 82 et au moins une dent de blocage 83 pour bloquer axialement le pied 3 d'une aube de rotor 3 logée dans une rainure 11 du disque de rotor 1 tout en permettant la ventilation de la rainure 11.With reference to the figure 2 , the locking device 8 generally comprises a circular ring sector 81, at least one locking wedge 82 and at least one blocking tooth 83 for axially locking the foot 3 of a rotor blade 3 housed in a groove 11 of the rotor disk 1 while allowing ventilation of the groove 11.

De manière plus précise, le secteur d'anneau circulaire 81 est destiné à être monté, transversalement à l'axe de la turbomachine, dans une gorge 6 du disque de rotor 1. Par définition, un secteur d'anneau circulaire est défini par rapport à un axe qui est désigné par la suite axe d'anneau S qui est orienté de l'arrière vers l'avant sur la figure 2 et qui définit la direction axiale. Par la suite, les termes « avant » et « arrière » sont définis par rapport à l'axe d'anneau S.More specifically, the circular ring sector 81 is intended to be mounted, transversely to the axis of the turbomachine, in a groove 6 of the rotor disc 1. By definition, a circular ring sector is defined relative to to an axis which is subsequently designated ring axis S which is oriented from the rear towards the front on the figure 2 and which defines the axial direction. Subsequently, the terms "forward" and "backward" are defined with respect to the S-ring axis.

Le secteur d'anneau 81 s'étend radialement par rapport à l'axe d'anneau S selon la direction radiale d'axe R, représenté sur la figure 2, qui est dirigé de l'intérieur vers l'extérieur. Le secteur d'anneau circulaire 81 possède un rayon de courbure constant et est aplati dans la direction axiale S, sa dimension radiale étant plus longue que sa dimension axiale.The ring sector 81 extends radially with respect to the ring axis S in the radial direction of axis R, shown in FIG. figure 2 which is directed from the inside to the outside. The circular ring sector 81 has a constant radius of curvature and is flattened in the axial direction S, its radial dimension being longer than its axial dimension.

Le secteur d'anneau 81 possède un angle ouvert de l'ordre de 30° mais il va de soi que cet angle peut être différent.The ring sector 81 has an open angle of the order of 30 ° but it goes without saying that this angle can be different.

La partie radiale intérieure 84 du secteur d'anneau 81 est décalée axialement par rapport à sa partie radiale extérieure 85 comme représenté sur la figure 2. Autrement dit, la partie radiale intérieure 84 est en avant de la partie radiale extérieure 85 de manière à permettre le logement de l'extrémité radiale intérieure 84 dans la gorge 6 du disque de rotor 1 tout en permettant à la partie radiale extérieure 85 de venir s'appuyer radialement dans la rainure 11 du disque de rotor 1 comme représenté sur la figure 3. Cette caractéristique sera détaillée par la suite au cours de l'exemple de mise en oeuvre de l'invention.The inner radial portion 84 of the ring sector 81 is axially offset from its outer radial portion 85 as shown in FIG. figure 2 . In other words, the inner radial portion 84 is in front of the outer radial portion 85 so as to allow housing of the inner radial end 84 in the groove 6 of the rotor disc 1 while allowing the outer radial portion 85 to come to rest radially in the groove 11 of the rotor disc 1 as shown in figure 3 . This characteristic will be detailed later in the example of implementation of the invention.

La cale de blocage 82 du dispositif de blocage 8, de forme rectangulaire, est solidaire et orthogonale au secteur d'anneau 81, la cale 82 s'étendant depuis la face arrière du secteur d'anneau 81, parallèlement à l'axe d'anneau S. La cale de blocage 82 est agencée pour supporter radialement le pied 3 d'aube 2 dans la rainure 11 du disque de rotor 1. En référence à la figure 2, la cale de blocage 82 est solidaire de la partie supérieure 85 du secteur d'anneau 81 de manière à surélever le pied 3 d'aube 2 par rapport au fond de la rainure 11 pour permettre une circulation d'air dans la rainure 11 du disque de rotor 1.The locking wedge 82 of the blocking device 8, of rectangular shape, is integral and orthogonal to the ring sector 81, the spacer 82 extending from the rear face of the ring sector 81, parallel to the axis of FIG. ring S. The blocking wedge 82 is arranged to radially support the root 3 of blade 2 in the groove 11 of the rotor disk 1. With reference to FIG. figure 2 , the blocking wedge 82 is secured to the upper portion 85 of the ring sector 81 so as to raise the blade root 3 2 relative to the bottom of the groove 11 to allow air to flow into the groove 11 of the rotor disk 1.

La cale de blocage 82 du dispositif de blocage 8 est aplatie selon la direction radiale R, sa dimension axiale étant plus longue que sa dimension radiale. La longueur de la cale de blocage 82 définie selon l'axe d'anneau S est configurée pour supporter le pied 3 d'aube 2. A titre d'exemple, la longueur de la cale de blocage 82 correspond à environ 80% de la longueur du pied 3 d'aube 2 comme représenté sur la figure 4. Il va de soi que la longueur de la cale de blocage 82 peut varier. De préférence, la longueur de la cale de blocage 82 est au moins égale à la moitié de la longueur du pied d'aube 3 pour répartir les efforts sur la cale de blocage 82.The blocking wedge 82 of the locking device 8 is flattened in the radial direction R, its axial dimension being longer than its radial dimension. The length of the blocking wedge 82 defined along the ring axis S is configured to support the blade root 3 2. For example, the length of the blocking wedge 82 corresponds to about 80% of the foot length 3 of blade 2 as shown on the figure 4 . It goes without saying that the length of the blocking wedge 82 can vary. Preferably, the length of the blocking wedge 82 is at least equal to half the length of the blade root 3 to distribute the forces on the blocking wedge 82.

La dent de blocage 83 du dispositif de blocage 8 est solidaire et orthogonale à la cale de blocage 82. La dent de blocage 83, de forme rectangulaire, s'étend depuis la partie supérieure 85 du secteur d'anneau 81 selon la direction radiale R vers l'extérieur, c'est à dire radialement par rapport à l'axe du secteur d'anneau S, de manière à bloquer le déplacement axial du pied d'aube 3 dans la rainure 11 du disque de rotor 1. La longueur de la dent 83, définie selon l'axe radial R, est configurée, dans cet exemple, pour s'étendre jusqu'au diamètre extérieur du disque de rotor 1 lorsque le dispositif de blocage 8 est en position montée comme représenté sur la figure 3.The locking tooth 83 of the locking device 8 is integral and orthogonal to the blocking wedge 82. The blocking tooth 83, of rectangular shape, extends from the upper part 85 of the ring sector 81 in the radial direction R outwardly, that is to say radially with respect to the axis of the ring sector S, so as to block the axial displacement of the blade root 3 in the groove 11 of the rotor disk 1. The length of the tooth 83, defined along the radial axis R, is configured, in this example, to extend to the outer diameter of the rotor disk 1 when the locking device 8 is in the mounted position as shown in FIG. figure 3 .

Les dimensions de la dent de blocage 83, en particulier sa longueur et sa largeur, sont définies pour résister aux déplacements axiaux du pied 3 d'aube 2 lors d'une rotation du rotor. La dent de blocage 83 est agencée pour être alignée axialement avec la rainure 11 du disque de rotor 1. De préférence, la face arrière de la dent de blocage 83, appelée aussi face d'arrêt, possède une surface dont la dimension est inférieure à la section de la rainure 11 du disque de rotor 1 comme représenté sur la figure 3. Une telle dent de blocage 83 permet de remplir sa fonction de blocage axial tout en possédant une masse réduite du fait de ses dimensions réduites. Selon une forme de réalisation particulière non représentée, la dent de blocage 83 est pliable/rétractable pour permettre un montage simple du dispositif de blocage 8 dans la gorge 6, la dent 83 n'étant dépliée/sortie qu'après montage.The dimensions of the blocking tooth 83, in particular its length and its width, are defined to resist the axial displacements of the blade root 3 during a rotation of the rotor. The blocking tooth 83 is arranged to be axially aligned with the groove 11 of the rotor disc 1. Preferably, the rear face of the blocking tooth 83, also called the stop face, has a surface whose dimension is smaller than the section of the groove 11 of the rotor disc 1 as shown in the figure 3 . Such locking tooth 83 makes it possible to fulfill its axial locking function while having a reduced mass because of its reduced dimensions. According to a particular embodiment not shown, the locking tooth 83 is foldable / retractable to allow a simple mounting of the locking device 8 in the groove 6, the tooth 83 being unfolded / output after assembly.

Le dispositif de blocage 8 comporte en outre des moyens de ventilation ménagés dans le secteur annulaire 81, de préférence, dans sa partie extérieure 85, entre la zone de liaison de la cale de blocage 82 et la partie intérieure 84 du secteur annulaire 81 comme représenté sur la figure 4. Ces moyens de ventilation se présentent sous la forme d'ouvertures traversant dans la direction axiale le secteur d'anneau 81 de manière à permettre l'évacuation d'un flux d'air F circulant entre le fond de la rainure 11 et la cale de blocage 82 comme représenté sur la figure 4.The locking device 8 further comprises ventilation means provided in the annular sector 81, preferably in its outer part 85, between the connecting zone of the blocking wedge 82 and the inner part 84 of the annular sector 81 as shown. on the figure 4 . These ventilation means are in the form of apertures crossing in the axial direction the ring sector 81 so as to allow the evacuation of a flow of air F flowing between the bottom of the groove 11 and the shim blocking 82 as shown on the figure 4 .

De manière préférée, les moyens de ventilation sont alignés radialement avec la dent de blocage 83 ce qui permet de bloquer axialement le pied 3 d'aube 2 tout en permettant la ventilation de la rainure 11.Preferably, the ventilation means are aligned radially with the blocking tooth 83, which makes it possible axially to block the blade root 3 while allowing ventilation of the groove 11.

Selon une première forme de réalisation, les moyens de ventilation se présentent sous la forme d'orifices traversant circulaires 91 comme représentés sur les figures 2 à 4 dont le diamètre est calibré pour la ventilation. Des orifices circulaires 91 présentent l'avantage d'être simples à usiner.According to a first embodiment, the ventilation means are in the form of circular through orifices 91 as shown in FIGS. Figures 2 to 4 whose diameter is calibrated for ventilation. Circular orifices 91 have the advantage of being simple to machine.

Selon une deuxième forme de réalisation, en référence à la figure 5, les moyens de ventilation se présentent sous la forme d'orifices traversant de section elliptique 92 dont le petit diamètre s'étend, de préférence, selon la direction radiale. Des orifices de section elliptique 92, réalisés par exemple par un perçage incliné, présentent l'avantage d'offrir un débit d'air important sans affecter la résistance mécanique selon la direction radiale du secteur d'anneau 81. En effet, la distance entre le bord intérieur du secteur annulaire 81 et un orifice elliptique est plus importante que la distance entre le bord intérieur du secteur annulaire 81 et un orifice circulaire ce qui offre une meilleure tenue mécanique.According to a second embodiment, with reference to the figure 5 , the ventilation means are in the form of through holes of elliptical section 92 whose small diameter preferably extends in the radial direction. Elliptical section orifices 92, made for example by an inclined bore, have the advantage of offering a high air flow without affecting the mechanical strength in the radial direction of the ring sector 81. Indeed, the distance between the inner edge of the annular sector 81 and an elliptical orifice is larger than the distance between the inner edge of the annular sector 81 and a circular orifice which offers a better mechanical strength.

Selon une troisième forme de réalisation, en référence à la figure 6, les moyens de ventilation se présentent sous la forme d'encoches 93 formées depuis la partie intérieure 84 du secteur d'anneau 81 jusque dans sa partie extérieure 85. Autrement dit, l'extrémité intérieure du secteur d'anneau 81 est crénelée de manière à permettre la ventilation des rainures 11. Des encoches 93 présentent l'avantage d'alléger la masse du secteur d'anneau 81 tout en étant simple à usiner par perçage. Par ailleurs, les encoches 93 offrent un débit d'air de ventilation important.According to a third embodiment, with reference to the figure 6 , the ventilation means are in the form of notches 93 formed from the inner portion 84 of the ring sector 81 to its outer portion 85. In other words, the inner end of the ring sector 81 is crenellated so The notches 93 have the advantage of lightening the mass of the ring sector 81 while being simple to machine by drilling. In addition, the notches 93 provide a large ventilation air flow.

Le montage d'un dispositif de blocage 8 dans le rotor va être décrit plus en avant. Ce montage est décrit en référence à un dispositif comportant des moyens de ventilation selon la première forme de réalisation (orifices circulaires). La description du procédé de montage s'applique de manière similaire aux autres formes de réalisation des moyens de ventilation.The mounting of a locking device 8 in the rotor will be described further. This arrangement is described with reference to a device comprising ventilation means according to the first embodiment (circular orifices). The description of the mounting method applies similarly to the other embodiments of the ventilation means.

En référence à la figure 3 représentant le disque de rotor 1 d'axe X, le dispositif de blocage 8 de la figure 2 est monté dans le disque de rotor 1 en plaçant les cales de blocage 82 axialement dans les rainures 11 du disque de rotor 1 et en insérant la partie intérieure 84 du dispositif de blocage 8 dans la gorge aval 6 du disque de rotor 1 de manière à ce que la partie supérieure 85 du secteur d'anneau 81 soit en appui radial dans le fond de la rainure 11 de manière à ménager un espace de circulation d'un flux d'air F entre la cale de blocage 82 et le fond de la rainure 11. Le décalage axial permet en outre d'éviter un basculement du dispositif de blocage 8 en limitant le porte-à-faux du dispositif de blocage 8. En effet, si l'aube 2 est en appui sur la cale 82, la partie intérieure 84 du dispositif de blocage 8 entre en contact avec la partie aval de la gorge 6 ce qui bloque le basculement vers l'amont de la cale 82. La cale de blocage 82 est parallèle au fond de la rainure 11 une fois montée. La dent de blocage 83 s'étend radialement par rapport à l'axe du moteur et est alignée axialement avec la rainure 11.With reference to the figure 3 representing the rotor disc 1 of X axis, the locking device 8 of the figure 2 is mounted in the rotor disc 1 by placing the blocking wedges 82 axially in the grooves 11 of the rotor disk 1 and inserting the inner portion 84 of the locking device 8 in the downstream groove 6 of the rotor disk 1 so as to that the upper portion 85 of the ring sector 81 is radially supported in the bottom of the groove 11 so as to provide a circulation space of an air flow F between the blocking wedge 82 and the bottom of the groove 11. The axial offset also makes it possible to prevent tilting of the locking device 8 by limiting the cantilever of the locking device 8. In fact, if the blade 2 bears against the spacer 82, the inner portion 84 of the locking device 8 comes into contact with the downstream portion of the groove 6 which blocks the upward tilting of the shim 82. The blocking wedge 82 is parallel to the bottom of the groove 11 once mounted. The blocking tooth 83 extends radially with respect to the axis of the motor and is aligned axially with the groove 11.

En référence à la figure 4, les moyens de ventilation, ici des orifices circulaires 91, s'étendent à mi-hauteur de l'espace de circulation du flux d'air F entre la cale de blocage 82 et le fond de la rainure 11 ce qui permet d'assurer une bonne circulation d'air.With reference to the figure 4 , the ventilation means, here circular orifices 91, extend halfway up the circulation space of the air flow F between the blocking wedge 82 and the bottom of the groove 11, which makes it possible to ensure good air circulation.

Le pied 3 d'aube 2 est ensuite inséré dans la rainure 11 par déplacement axial de l'amont vers l'aval de manière à ce que le pied 2 soit en appui sur la surface extérieure de la cale de blocage 82 pour être retenu radialement et ainsi éviter un défaut de positionnement de l'aube 2 dans le disque 1, en particulier, lorsque le moteur est à l'arrêt. Par ailleurs, le pied 3 d'aube 2 est en appui sur la surface amont (surface d'arrêt) de la dent de blocage 83 pour être bloqué axialement.The blade root 3 is then inserted into the groove 11 by axial displacement from upstream to downstream so that the foot 2 bears against the outer surface of the blocking wedge 82 to be retained radially. and thus avoid a defect in the positioning of the blade 2 in the disk 1, in particular when the engine is stopped. Furthermore, the blade root 3 bears against the upstream surface (stopping surface) of the locking tooth 83 to be axially locked.

Grâce au dispositif de blocage 8 selon l'invention, il n'est pas nécessaire de recourir à une aube en pied de sapin ou de former un crochet dans le pied d'aube pour bloquer axialement l'aube 2.Thanks to the locking device 8 according to the invention, it is not necessary to use a blade at the foot of fir or to form a hook in the blade root to axially block the blade 2.

De préférence, le pied 3 de l'aube de rotor 2 possède une forme simple en queue d'aronde dont l'enveloppe est en matériau composite. C'est le dispositif de blocage 8, et non le pied 3 d'aube 2, qui remplit les fonctions de blocage axial, de blocage radial et de ventilation de la rainure 11 du disque de rotor 1. Un tel pied 3 est simple à fabriquer et possède une masse réduite.Preferably, the root 3 of the rotor blade 2 has a simple dovetail shape whose envelope is made of a composite material. It is the locking device 8, and not the blade root 3 2, which performs the functions of axial blocking, radial blocking and ventilation of the groove 11 of the rotor disc 1. Such a foot 3 is simple to manufacture and has a reduced mass.

De manière préférée, l'enveloppe du pied 3 d'aube 2 est en matériau composite à matrice céramique (CMC).Preferably, the envelope of the blade root 3 is made of ceramic matrix composite material (CMC).

Claims (9)

  1. A device (8) for blocking a root (3) of a rotor blade (2) in a groove (11) of a rotor disk (1) of a turboengine, comprising:
    - a circular ring sector (81) which is intended to be mounted, transversely relative to the axis of the turboengine, in a recess (6) of the rotor disk (1);
    - at least one blocking wedge (82), which is fixedly joined and orthogonal relative to the ring sector (81) and which extends parallel to the axis (5) of the ring sector (81) in order to radially support the root (3) of the blade (2) in the groove (11);
    - at least one blocking tooth (83) which extends from the ring sector (81) radially relative to the axis (5) of the ring sector (81) in order to block the axial movement of the root (3) of the blade (2) in the groove (11), and
    - ventilation means (91,92,93) which are formed in the ring sector (81)and which are arranged to allow discharge of a flow of air (F) which circulates between the base of the groove (11) and the blocking wedge (82).
  2. The device as claimed in claim 1, in which the ventilation means (91,92,93) are aligned with the direction in which the blocking tooth (83) extends.
  3. The device as claimed in claim 1 or 2, in which the ventilation means are in the form of at least one ventilation hole (91,92).
  4. The device as claimed in claim 1 or 2, in which the ventilation means are in the form of at least one ventilation notch (93) which is formed in the portion (84) of the ring sector (81) which is intended to be inserted in the recess of the rotor disk (1).
  5. The device as claimed in any of the preceding claims, in which the ring sector (81) comprises an inner radial portion (84) which is intended to be mounted in the recess (6) of the rotor disk (1), and an outer radial portion (85), from which the blocking tooth (83) extends, which portions are axially offset relative to each other along the ring axis (5).
  6. A rotor of a turboengine which comprises a rotor disk (1), at least one rotor blade (2) and at least one securing device (8) as claimed in any one of claims 1 to 5, the rotor disk (1) comprising a groove (11) in which a root (3) of the blade (2) is accommodated and a recess (6) in which the securing device (8) is mounted, the blocking wedge (82) of the securing device (8) extending between the root (3) of the blade (2) and the base of the groove (11).
  7. The rotor as claimed in the preceding claim, in which, since the rotor disk (1) extends axially in a downstream direction, the recess (6) is formed at the downstream end of the rotor disk (1) in order to block an axial downstream movement of the blade (2) in the groove (11).
  8. The rotor as claimed in claim 6 or 7, in which the root of the rotor blade (2)comprises a casing of composite material.
  9. The rotor as claimed in any of claim 6 to 8, in which the root of the rotor blade (2) is of dovetail form.
EP11758248.6A 2010-08-10 2011-08-08 Device for locking a root of a rotor blade Active EP2603670B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1056528A FR2963806B1 (en) 2010-08-10 2010-08-10 DEVICE FOR LOCKING A FOOT OF A ROTOR BLADE
PCT/FR2011/051882 WO2012020195A1 (en) 2010-08-10 2011-08-08 Device for locking a root of a rotor blade

Publications (2)

Publication Number Publication Date
EP2603670A1 EP2603670A1 (en) 2013-06-19
EP2603670B1 true EP2603670B1 (en) 2018-03-07

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US (1) US9429030B2 (en)
EP (1) EP2603670B1 (en)
CN (1) CN103080479B (en)
BR (1) BR112013002996B1 (en)
CA (1) CA2807556C (en)
FR (1) FR2963806B1 (en)
RU (1) RU2572654C2 (en)
WO (1) WO2012020195A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3009608B1 (en) * 2014-10-02 2019-10-30 United Technologies Corporation Vane assembly with trapped segmented vane structures
RU2578874C1 (en) * 2014-11-27 2016-03-27 Марат Закиевич Нафиков Method of forming metal coating by simultaneous electric contact welding of steel wires
US9777586B2 (en) 2014-12-31 2017-10-03 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
US9664058B2 (en) 2014-12-31 2017-05-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
FR3093533B1 (en) * 2019-03-06 2022-04-15 Safran Aircraft Engines damping device for turbomachine rotor
CN114762968A (en) * 2021-01-14 2022-07-19 中国航发商用航空发动机有限责任公司 Blade retaining ring installation tool and blade retaining ring installation method
CN114215610B (en) * 2021-12-01 2023-06-27 东方电气集团东方汽轮机有限公司 Axial positioning structure of turbine movable blade of gas turbine and mounting and dismounting method

Family Cites Families (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA604830A (en) * 1960-09-06 Metropolitan-Vickers Electrical Company Limited Locking means for axial flow turbo-machine blading
US1873956A (en) * 1930-05-05 1932-08-30 Allis Chalmers Mfg Co Rotor structure
US3076634A (en) * 1959-06-12 1963-02-05 Ass Elect Ind Locking means for compressor and turbine blades
US3343806A (en) * 1965-05-27 1967-09-26 Gen Electric Rotor assembly for gas turbine engines
GB1291302A (en) * 1970-03-14 1972-10-04 Sec Dep For Defendence Improvements in bladed rotor assemblies
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
FR2524933B1 (en) * 1982-04-13 1987-02-20 Snecma AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
FR2586061B1 (en) * 1985-08-08 1989-06-09 Snecma MULTIFUNCTIONAL LABYRINTH DISC FOR TURBOMACHINE ROTOR
US4781534A (en) * 1987-02-27 1988-11-01 Westinghouse Electric Corp. Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
FR2694046B1 (en) * 1992-07-22 1994-09-23 Snecma Sealing and retention device for a rotor notched with pinouts receiving blade roots.
ITMI991210A1 (en) * 1999-05-31 2000-12-01 Nuovo Pignone Spa FIXING DEVICE FOR GAS TURBINE PADS
DE50209295D1 (en) 2001-07-03 2007-03-08 Abb Turbo Systems Ag SECURING SYSTEM FOR RUNNING ROLLERS AXIAL THREE-POLE TURBOMA MACHINES
FR2842828B1 (en) * 2002-07-25 2005-04-29 Snecma Moteurs MECHANICAL PIECE, AND METHOD OF MANUFACTURING SUCH A MECHANICAL PIECE
FR2867223B1 (en) 2004-03-03 2006-07-28 Snecma Moteurs TURBOMACHINE AS FOR EXAMPLE A TURBOJET AIRCRAFT
US7329101B2 (en) * 2004-12-29 2008-02-12 General Electric Company Ceramic composite with integrated compliance/wear layer
RU49905U1 (en) * 2005-06-01 2005-12-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") DEVICE FOR FIXING A WORKING BLADE INTO THE ROTOR PARTS Groove
FR2888897B1 (en) 2005-07-21 2007-10-19 Snecma DEVICE FOR DAMPING THE VIBRATION OF AN AXIAL RETAINING RING OF BLOWER BLADES OF A TURBOMACHINE
UA82235C2 (en) * 2005-12-12 2008-03-25 Государственное Предприятие «Запорожское Машиностроительное Конструкторское Бюро «Прогресс» Имени Академика О.Г. Ивченко» Device for fixation of blades of turbine wheel of axial turbo-machine
JP2007247406A (en) * 2006-03-13 2007-09-27 Ihi Corp Holding structure of fan blade
US7806662B2 (en) * 2007-04-12 2010-10-05 Pratt & Whitney Canada Corp. Blade retention system for use in a gas turbine engine
FR2918103B1 (en) * 2007-06-27 2013-09-27 Snecma DEVICE FOR COOLING ALVEOLES OF A TURBOMACHINE ROTOR DISK.
FR2918414B1 (en) * 2007-07-06 2013-04-12 Snecma VENTILATION AIR SUPPLY DEVICE FOR LOW PRESSURE TURBINE BLADES OF A GAS TURBINE ENGINE; SEGMENT FOR AXIAL STOP AND VENTILATION OF LOW PRESSURE TURBINE BLADES
FR2939834B1 (en) * 2008-12-17 2016-02-19 Turbomeca TURBINE WHEEL WITH AXIAL RETENTION SYSTEM OF AUBES

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BR112013002996B1 (en) 2020-12-08
RU2572654C2 (en) 2016-01-20
CA2807556C (en) 2018-04-17
EP2603670A1 (en) 2013-06-19
CN103080479A (en) 2013-05-01
BR112013002996A2 (en) 2016-06-14
US9429030B2 (en) 2016-08-30
CA2807556A1 (en) 2012-02-16
FR2963806A1 (en) 2012-02-17
FR2963806B1 (en) 2013-05-03
CN103080479B (en) 2015-12-09
WO2012020195A1 (en) 2012-02-16
US20130136605A1 (en) 2013-05-30

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