EP0607082A1 - Turbomachine rotor with blade attachment by pins - Google Patents

Turbomachine rotor with blade attachment by pins Download PDF

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Publication number
EP0607082A1
EP0607082A1 EP94400066A EP94400066A EP0607082A1 EP 0607082 A1 EP0607082 A1 EP 0607082A1 EP 94400066 A EP94400066 A EP 94400066A EP 94400066 A EP94400066 A EP 94400066A EP 0607082 A1 EP0607082 A1 EP 0607082A1
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EP
European Patent Office
Prior art keywords
heels
disc
blade
blades
pins
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
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EP94400066A
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German (de)
French (fr)
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EP0607082B1 (en
Inventor
Jean-Francois Imbault
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion

Definitions

  • the present invention relates to a turbomachine rotor of the type comprising: a disc having a plurality of annular ribs which extend outwards from the periphery of said disc and which define a plurality of annular grooves, a plurality of blades, regularly disposed at the periphery of said disc and extending radially outward, each blade comprising a notched foot so as to define heels each of which lodges in a corresponding groove on said disc, and means for fixing said blades to the disc.
  • blower rotor provided with blades of large rope made of composite material without incorporated platform and the base of which has comb-type fasteners.
  • US Pat. No. 3,694,104 describes a blade made of composite material, the foot of which is notched and has heels each having a bore delimited by a metal sleeve intended to cooperate with a spindle.
  • the blade root is fixed on the disc ribs by two axially offset pins, one located on the upstream side of the blade and the other on the downstream side respectively in the plane of the leading edge and in the plane from the trailing edge.
  • the object of the present invention is to overcome these drawbacks, and to propose a turbomachine rotor of the type mentioned in which the means for fixing the blades on the disc allow all the forces exerted on the blades to be taken up.
  • the rotor is characterized in that the heels of each blade root are divided into two groups of heels, the heels of one of said groups being offset on the side of the the lower surface of said blade and the heels of the other group being offset towards the upper surface, in that the heels of a group of heels of any dawn form an alignment of vanes with the heels of the other group of heels of the neighboring dawn, and in that the means for fixing said blades comprise, for each alignment of blades, a pin arranged in corresponding bores passing right through the plurality of annular ribs and the heels of said alignment of heels.
  • each blade is retained by two parallel pins regularly spaced at the periphery of the disc and each pin retains two blades, which makes it possible to reduce the mass of the assembly.
  • the pins are parallel to the axis of the disc and introduced by the same face of the disc.
  • the blades are made of composite material and the heel bores are delimited by sockets which are contoumed at their lower part by the fibers of the composite which then leave towards the external end of the corresponding blade.
  • the heels of the group of heels offset on the extrados side are arranged in the middle part of the blade root.
  • the turbomachine rotor 1 shown in the drawings, comprises a rotor disc 10, having the shape of a rim, on the circumference of which is fixed, in a regularly distributed manner, a plurality of blades 11, each comprising a fixing foot 12 to the disc 10 and a blade 13 which extends radially outward from the periphery of the disc 10.
  • Reported platforms 14, intended to delimit, on the side of the axis of the rotor 1, the flow of gas flowing from upstream to downstream through the blades 11 of the rotor 1 when the latter is in operation, are arranged between the blades 11.
  • the invention relates more particularly to the fixing of blades 11 made of composite material of the long cord type, and fitted to blowers.
  • the latter comprises a plurality of annular ribs 15 which extend radially outward from its periphery, and which delimit a plurality of annular grooves 16.
  • the blade root 12 has, at its end, radial notches adapted to the annular ribs 15, so as to have heels 17 interposed alternately between the annular ribs 15.
  • the heels 17 of a blade 11 represented five in number in the drawings and referenced respectively by the letters A, B, C, D, E upstream downstream of the turbomachine, are divided into two heel groups.
  • the heels of the first group of heels are offset on the side of the lower surface of the blade 11 and are aligned, while the heels of the second group of heels are offset on the side of the upper surface and are also aligned.
  • each blade 11 is offset so that the heels of a group of heels of a blade 11 form an alignment of blades 18 with the heels of the other group of heels of the neighboring blade. .
  • the second group of heels has only one heel which is the heel located in the middle part of the blade root 12 and referenced C, but it could include several heels 17 consecutive or not consecutive.
  • the heel C of the blade 11a is disposed between the heels B and D of the blade 11b.
  • the blades 11 are fixed to the disc 10 by a plurality of pins 19.
  • Each pin 19 is arranged in aligned bores which pass right through the annular ribs 15 and the heels of a heel alignment 18.
  • each blade 11 is fixed to the disc 10 by two adjacent pins 19 and each pin 19 retains two consecutive blades 11a and 11b.
  • all of the pins 19 are mounted on the same side of the disc 10 and are parallel to the axis of the rotor.
  • the two neighboring spindles 19 which retain a blade 11 are angularly spaced and take up the radial and tangential components of the forces exerted on the blade 11.
  • each heel 17 has a socket 20 through which the spindle 19 passes.
  • the fibers 21 of the composite constituting the blade 13 bypass the sockets 20 at their lower part in the direction of the lower surface towards the upper surface and ensure the continuity of the loads centrifugal.
  • the fibers 21 are arranged crosswise over the entire height of the blade 13. Some fibers travel from the leading edge side of the blade to the other trailing edge side and return to the other face of the blade 13 by crossing with other fibers having followed a reverse symmetrical path. All of the fibers 21 form a bag which, combined with excellent fastening behavior, provides better security against deterioration of the profile after an impact, by the fact that this arrangement of the fibers 21 allows, in most shocks , the retention of the pieces of blades linked by this crossed mesh and ensures positive security.
  • the profile of the vein is reconstituted by platforms 14 which are supported by a central rib 22 on the junction of the two blades 11a and 11b.
  • Each platform 14 has a wall 22a which is inclined relative to the axis of the rotor, which extends between the opposite faces of the two consecutive blades 11a and 11b and which is extended at its front and rear ends by two plates 23 and 24 which extend radially towards the axis of the rotor 1.
  • the inner ends of these plates 23 and 24 have axial flanges 25 and 26 which are retained by ferrules 27 and 28 fixed to the disc 10.
  • the ferrule front 27 also serves as a means of retaining the heads 29 of the pins 19.
  • the mounting of the rotor 1 is done as follows: a first blade 11b is placed on the disk 10, so that the bores of the ribs 15 are aligned with the bushings 20 of the heels 12. Then, the central heel C is embedded of the neighboring blade 11a between the heels B and C of the blade 11b, and a pin 19 is threaded in the alignment of heels. The same procedure is followed for all of the blades 11. The platforms 14 are then placed, then the ferrules 27 and 28 are fixed so as to maintain the platforms 14 and the pins 19. The disassembly of the rotor is done in reverse order of the previous operations.

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

Abstract

The present invention relates to a turbomachine rotor (1) comprising a disc (10) exhibiting a plurality of annular ribs (15) extending outwards, a plurality of radial blades (11) distributed at the periphery of the disc (10), made of composite material and with a notched root fitting onto the ribs (15), and pins (19) for fastening the blades (11) onto the disc (10). Each blade (11) is fastened by two pins (19), and each pin (19) fastens two neighbouring blades (11a, 11b). The butt ends (17) of a blade root (12) are distributed in two groups of butt ends which are offset towards the pressure face side and towards the suction face side. <IMAGE>

Description

La présente invention concerne un rotor de turbomachine du type comprenant :
   un disque présentant une pluralité de nervures annulaires qui s'étendent vers l'extérieur à partir de la périphérie dudit disque et qui définissent une pluralité de rainures annulaires,
   une pluralité d'aubes, régulièrement disposées à la périphérie dudit disque et s'étendant radialement vers l'extérieur, chaque aube comportant un pied encoché de manière à définir des talons dont chacun loge dans une rainure correspondante dudit disque, et
   des moyens de fixation desdites aubes sur le disque.The present invention relates to a turbomachine rotor of the type comprising:
a disc having a plurality of annular ribs which extend outwards from the periphery of said disc and which define a plurality of annular grooves,
a plurality of blades, regularly disposed at the periphery of said disc and extending radially outward, each blade comprising a notched foot so as to define heels each of which lodges in a corresponding groove on said disc, and
means for fixing said blades to the disc.

Elle conceme plus précisément un rotor de soufflante muni de pales à grande corde en matériau composite sans plate-forme incorporée et dont le pied comporte des attaches du type peigne.More precisely, it relates to a blower rotor provided with blades of large rope made of composite material without incorporated platform and the base of which has comb-type fasteners.

Le brevet US-3 694 104 décrit une aube en matériau composite dont le pied est encoché et présente des talons comportant chacun un alésage délimité par une douille métallique destinée à coopérer avec une broche. Le pied de l'aube est fixé sur les nervures du disque par deux broches décalées axialement, l'une située du côté amont de l'aube et l'autre du côté aval respectivement dans le plan du bord d'attaque et dans le plan du bord de fuite.US Pat. No. 3,694,104 describes a blade made of composite material, the foot of which is notched and has heels each having a bore delimited by a metal sleeve intended to cooperate with a spindle. The blade root is fixed on the disc ribs by two axially offset pins, one located on the upstream side of the blade and the other on the downstream side respectively in the plane of the leading edge and in the plane from the trailing edge.

Cette disposition ne permet pas aux broches de reprendre la totalité des forces appliquées sur les aubes. Aussi, les plates-formes rapportées interposées entre les aubes sont sollicitées pour la reprise des composantes tangentielles des forces, et elles doivent être rigides et solidement fixées au disque par des vis de fixation, ce qui se traduit par une augmentation du poids du rotor. De plus, le décalage angulaire existant entre l'axe de la broche amont et l'axe de la broche aval crée des difficultés dans la construction de l'aube et du disque. Enfin, certaines broches et vis de fixation sont montées par la face avant du disque et d'autres par la face arrière. Ceci entraîne une dépose du rotor en cas de démontage des pales.This arrangement does not allow the spindles to take up all the forces applied to the blades. Also, the added platforms interposed between the blades are stressed for the recovery of the tangential components of the forces, and they must be rigid and firmly fixed to the disc by fixing screws, which results in an increase in the weight of the rotor. In addition, the angular offset existing between the axis of the upstream spindle and the axis of the downstream spindle creates difficulties in the construction of the blade and the disc. Finally, some pins and fixing screws are mounted on the front of the disc and others on the rear. This results in removal of the rotor if the blades are removed.

Le but de la présente invention est de pallier ces inconvénients, et de proposer un rotor de turbomachine du type mentionné dans lequel les moyens de fixation des aubes sur le disque permettent de reprendre l'ensemble des forces exercées sur les aubes.The object of the present invention is to overcome these drawbacks, and to propose a turbomachine rotor of the type mentioned in which the means for fixing the blades on the disc allow all the forces exerted on the blades to be taken up.

Le but est atteint selon l'invention par le fait que le rotor est caractérisé en ce que les talons de chaque pied d'aube sont répartis en deux groupes de talons, les talons de l'un desdits groupes étant décalés du côté de l'intrados de ladite aube et les talons de l'autre groupe étant décalés du côté de l'extrados,
   en ce que les talons d'un groupe de talons d'une aube quelconque forment un alignement d'aubes avec les talons de l'autre groupe de talons de l'aube voisine, et
   en ce que les moyens de fixation desdites aubes comportent, pour chaque alignement d'aubes, une broche disposée dans des alésages en correspondance traversant de part en part la pluralité des nervures annulaires et les talons dudit alignement de talons.The object is achieved according to the invention by the fact that the rotor is characterized in that the heels of each blade root are divided into two groups of heels, the heels of one of said groups being offset on the side of the the lower surface of said blade and the heels of the other group being offset towards the upper surface,
in that the heels of a group of heels of any dawn form an alignment of vanes with the heels of the other group of heels of the neighboring dawn, and
in that the means for fixing said blades comprise, for each alignment of blades, a pin arranged in corresponding bores passing right through the plurality of annular ribs and the heels of said alignment of heels.

Grâce à cette disposition, chaque aube est retenue par deux broches parallèles régulièrement espacées à la périphérie du disque et chaque broche retient deux aubes, ce qui permet de réduire la masse de l'ensemble.Thanks to this arrangement, each blade is retained by two parallel pins regularly spaced at the periphery of the disc and each pin retains two blades, which makes it possible to reduce the mass of the assembly.

De façon avantageuse, les broches sont parallèles à l'axe du disque et introduites par la même face du disque.Advantageously, the pins are parallel to the axis of the disc and introduced by the same face of the disc.

Avantageusement, les aubes sont réalisées en matériau composite et les alésages des talons sont délimités par des douilles qui sont contoumées à leur partie inférieure par les fibres du composite qui partent ensuite vers l'extrémité externe de l'aube correspondante.Advantageously, the blades are made of composite material and the heel bores are delimited by sockets which are contoumed at their lower part by the fibers of the composite which then leave towards the external end of the corresponding blade.

De préférence, les talons du groupe de talons décalés du côté de l'extrados sont disposés dans la partie médiane du pied d'aube.Preferably, the heels of the group of heels offset on the extrados side are arranged in the middle part of the blade root.

D'autre avantages et caractéristiques de l'invention apparaitront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une coupe axiale d'un rotor de turbomachine selon l'invention selon un plan passant par une broche de fixation,
  • la figure 2 est une coupe selon un plan perpendiculaire à l'axe de la turbomachine prise selon la ligne II II de la figure 1,
  • la figure 3 est une coupe selon la ligne III III de la figure 2,
  • la figure 4 est une coupe axiale d'une variante de réalisation de la figure 1, dans laquelle on montre les moyens de fixation des plates-formes rapportées,
  • la figure 5 est une coupe selon la ligne V V de la figure 4,
  • la figure 6 est une coupe transversale d'un pied d'aube,
  • la figure 7 est une coupe selon la ligne VII VII de la figure 6, et
  • la figure 8 est une vue latérale d'une aube.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • FIG. 1 is an axial section of a turbomachine rotor according to the invention along a plane passing through a fixing pin,
  • FIG. 2 is a section on a plane perpendicular to the axis of the turbomachine taken along line II II of FIG. 1,
  • FIG. 3 is a section along line III III of FIG. 2,
  • FIG. 4 is an axial section of an alternative embodiment of FIG. 1, in which the means for fixing the added platforms are shown,
  • FIG. 5 is a section along the line VV in FIG. 4,
  • FIG. 6 is a cross section of a blade root,
  • FIG. 7 is a section along line VII VII of FIG. 6, and
  • Figure 8 is a side view of a blade.

Le rotor de turbomachine 1, montré sur les dessins, comporte un disque de rotor 10, ayant la forme d'une jante, sur la circonférence duquel est fixée, de façon régulièrement réparties, une pluralité d'aubes 11, comportant, chacune, un pied de fixation 12 au disque 10 et une pale 13 qui s'étend radialement vers l'extérieur à partir de la périphérie du disque 10. Des plates-formes rapportées 14, destinées à délimiter, du côté de l'axe du rotor 1, la veine du flux gazeux circulant d'amont en aval à travers les aubes 11 du rotor 1 lorsque celui ci est en fonctionnement, sont disposées entre les aubes 11.The turbomachine rotor 1, shown in the drawings, comprises a rotor disc 10, having the shape of a rim, on the circumference of which is fixed, in a regularly distributed manner, a plurality of blades 11, each comprising a fixing foot 12 to the disc 10 and a blade 13 which extends radially outward from the periphery of the disc 10. Reported platforms 14, intended to delimit, on the side of the axis of the rotor 1, the flow of gas flowing from upstream to downstream through the blades 11 of the rotor 1 when the latter is in operation, are arranged between the blades 11.

L'invention concerne plus particulièrement la fixation d'aubes 11 réalisées en matériau composite du type à grande corde, et équipant des soufflantes.The invention relates more particularly to the fixing of blades 11 made of composite material of the long cord type, and fitted to blowers.

Pour assurer l'attache des aubes 11 sur le disque 10, celui-ci comprend une pluralité de nervures annulaires 15 qui s'étendent radialement vers l'extérieur à partir de sa périphérie, et qui délimitent une pluralité de rainures annulaires 16.To secure the blades 11 on the disc 10, the latter comprises a plurality of annular ribs 15 which extend radially outward from its periphery, and which delimit a plurality of annular grooves 16.

Le pied d'aube 12 comporte, à son extrémité, des encoches radiales adaptées aux nervures annulaires 15, de manière à présenter des talons 17 interposés en alternance entre les nervures annulaires 15.The blade root 12 has, at its end, radial notches adapted to the annular ribs 15, so as to have heels 17 interposed alternately between the annular ribs 15.

Selon l'invention, les talons 17 d'une aube 11, représentés au nombre de cinq sur les dessins et référencés respectivement par les lettres A, B, C, D, E d'amont en aval de la turbomachine, sont répartis en deux groupes de talons. Les talons du premier groupe de talons sont décalés du côté de l'intrados de l'aube 11 et sont alignés, tandis que les talons du deuxième groupe de talons sont décalés du côté de l'extrados et sont également alignés.According to the invention, the heels 17 of a blade 11, represented five in number in the drawings and referenced respectively by the letters A, B, C, D, E upstream downstream of the turbomachine, are divided into two heel groups. The heels of the first group of heels are offset on the side of the lower surface of the blade 11 and are aligned, while the heels of the second group of heels are offset on the side of the upper surface and are also aligned.

De plus, les talons de chaque aube 11 sont décalés de telle manière que les talons d'un groupe de talons d'une aube 11 forment un alignement d'aubes 18 avec les talons de l'autre groupe de talons de l'aube voisine.In addition, the heels of each blade 11 are offset so that the heels of a group of heels of a blade 11 form an alignment of blades 18 with the heels of the other group of heels of the neighboring blade. .

Dans les modes de réalisation représentés sur les dessins, le deuxième groupe de talons ne comporte qu'un seul talon qui est le talon situé dans la partie médiane du pied d'aube 12 et référencé C, mais il pourrait comporter plusieurs talons 17 consécutifs ou non consécutifs. Comme on le voit clairement sur la figure 3, le talon C de l'aube 11a est disposé entre les talons B et D de l'aube 11b.In the embodiments shown in the drawings, the second group of heels has only one heel which is the heel located in the middle part of the blade root 12 and referenced C, but it could include several heels 17 consecutive or not consecutive. As can be clearly seen in Figure 3, the heel C of the blade 11a is disposed between the heels B and D of the blade 11b.

Les aubes 11 sont fixées au disque 10 par une pluralité de broches 19. Chaque broche 19 est disposée dans les alésages alignés qui traversent de part en part les nervures annulaires 15 et les talons d'un alignement de talons 18.The blades 11 are fixed to the disc 10 by a plurality of pins 19. Each pin 19 is arranged in aligned bores which pass right through the annular ribs 15 and the heels of a heel alignment 18.

Grâce à cette disposition des talons 12, chaque aube 11 est fixée au disque 10 par deux broches voisines 19 et chaque broche 19 retient deux aubes consécutives 11a et 11b. De préférence, toutes les broches 19 sont montées du même côté du disque 10 et sont parallèles à l'axe du rotor.Thanks to this arrangement of the heels 12, each blade 11 is fixed to the disc 10 by two adjacent pins 19 and each pin 19 retains two consecutive blades 11a and 11b. Preferably, all of the pins 19 are mounted on the same side of the disc 10 and are parallel to the axis of the rotor.

Les deux broches voisines 19 qui retiennent une aube 11, sont espacées angulairement et reprennent les composantes radiales et tangentielles des forces qui s'exercent sur l'aube 11.The two neighboring spindles 19 which retain a blade 11 are angularly spaced and take up the radial and tangential components of the forces exerted on the blade 11.

De préférence, chaque talon 17 comporte une douille 20 traversée par la broche 19. Les fibres 21 du composite constituant la pale 13 contoument les douilles 20 à leur partie inférieure dans le sens de l'intrados vers l'extrados et assurent la continuité des charges centrifuges.Preferably, each heel 17 has a socket 20 through which the spindle 19 passes. The fibers 21 of the composite constituting the blade 13 bypass the sockets 20 at their lower part in the direction of the lower surface towards the upper surface and ensure the continuity of the loads centrifugal.

Comme on le voit sur la figure 8, les fibres 21 sont disposées de façon croisée sur toute la hauteur de la pale 13. Certaines fibres cheminent du côté bord d'attaque de l'aube à l'autre côté bord de fuite et reviennent sur l'autre face de la pale 13 en se croisant avec d'autres fibres ayant suivi un chemin symétrique inverse. L'ensemble des fibres 21 forme un sac qui, allié à une excellente tenue à l'attache, procure une meilleure sécurité à la détérioration du profil après un choc, par le fait que cette disposition des fibres 21 permet, dans la majorité des chocs, la retenue des morceaux d'aubes liées par ce maillage croisé et assure une sécurité positive.As can be seen in FIG. 8, the fibers 21 are arranged crosswise over the entire height of the blade 13. Some fibers travel from the leading edge side of the blade to the other trailing edge side and return to the other face of the blade 13 by crossing with other fibers having followed a reverse symmetrical path. All of the fibers 21 form a bag which, combined with excellent fastening behavior, provides better security against deterioration of the profile after an impact, by the fact that this arrangement of the fibers 21 allows, in most shocks , the retention of the pieces of blades linked by this crossed mesh and ensures positive security.

Entre deux aubes consécutives 11a et 11b, le profil de la veine est reconstitué par des plates-formes 14 qui prennent appui par une nervure centrale 22 sur la jonction des deux aubes 11a et 11b. Chaque plate-forme 14 présente une paroi 22a qui est inclinée par rapport à l'axe du rotor, qui s'étend entre les faces en vis à vis des deux aubes consécutives 11a et 11b et qui est prolongée à ses extrémités avant et arrière par deux plaques 23 et 24 qui s'étendent radialement vers l'axe du rotor 1. Les extrémités intemes de ces plaques 23 et 24 présentent des rebords axiaux 25 et 26 qui sont retenus par des viroles 27 et 28 fixées au disque 10. La virole avant 27 sert de plus de moyen de retenue des têtes 29 des broches 19.Between two consecutive blades 11a and 11b, the profile of the vein is reconstituted by platforms 14 which are supported by a central rib 22 on the junction of the two blades 11a and 11b. Each platform 14 has a wall 22a which is inclined relative to the axis of the rotor, which extends between the opposite faces of the two consecutive blades 11a and 11b and which is extended at its front and rear ends by two plates 23 and 24 which extend radially towards the axis of the rotor 1. The inner ends of these plates 23 and 24 have axial flanges 25 and 26 which are retained by ferrules 27 and 28 fixed to the disc 10. The ferrule front 27 also serves as a means of retaining the heads 29 of the pins 19.

Le montage du rotor 1 se fait de la manière suivante : on dispose une première aube 11b sur le disque 10, de telle manière que les alésages des nervures 15 soient alignés avec les douilles 20 des talons 12. Puis, on encastre le talon central C de l'aube voisine 11a entre les talons B et C de l'aube 11b, et on enfile une broche 19 dans l'alignement de talons. On poursuit de la même manière pour l'ensemble des aubes 11. On place ensuite les plates-formes 14, puis on fixe les viroles 27 et 28 de manière à maintenir les plates-formes 14 et les broches 19. Le démontage du rotor se fait dans l'ordre inverse des opérations précédentes.The mounting of the rotor 1 is done as follows: a first blade 11b is placed on the disk 10, so that the bores of the ribs 15 are aligned with the bushings 20 of the heels 12. Then, the central heel C is embedded of the neighboring blade 11a between the heels B and C of the blade 11b, and a pin 19 is threaded in the alignment of heels. The same procedure is followed for all of the blades 11. The platforms 14 are then placed, then the ferrules 27 and 28 are fixed so as to maintain the platforms 14 and the pins 19. The disassembly of the rotor is done in reverse order of the previous operations.

Claims (5)

Rotor de turbomachine du type comprenant :
   un disque (10) présentant une pluralité de nervures annulaires (15) qui s'étendent vers l'extérieur à partir de la périphérie dudit disque (10) et qui définissent une pluralité de rainures annulaires (16),
   une pluralité d'aubes (11), régulièrement disposées à la périphérie dudit disque (10) et s'étendant radialement vers l'extérieur, chaque aube (11) comportant un pied encoché (12) de manière à définir des talons (17) dont chacun loge dans une rainure (16) correspondante dudit disque (10), et
   des moyens de fixation desdites aubes (11) sur le disque (10),
   caractérisé en ce que les talons (17) de chaque pied d'aube (12) sont répartis en deux groupes de talons, les talons (A, B, D, E) de l'un desdits groupes étant décalés du côté de l'intrados de ladite aube (17) et les talons (C) de l'autre groupe étant décalés du côté de l'extrados,
   en ce que les talons (A, B, D, E) d'un groupe de talons d'une aube (11b) quelconque forment un alignement d'aubes (18) avec les talons (C) de l'autre groupe de talons d'une aube voisine (11a) et
   en ce que les moyens de fixation desdites aubes (11) comportent, pour chaque alignement d'aubes (18), une broche (19) disposée dans des alésages en correspondance traversant de part en part la pluralité des nervures annulaires (15) et les talons (A, B, C, D, E) dudit alignement de talons (18).Turbomachine rotor of the type comprising:
a disc (10) having a plurality of annular ribs (15) which extend outwards from the periphery of said disc (10) and which define a plurality of annular grooves (16),
a plurality of blades (11), regularly arranged at the periphery of said disc (10) and extending radially outward, each blade (11) comprising a notched foot (12) so as to define heels (17) each of which is housed in a corresponding groove (16) of said disc (10), and
means for fixing said blades (11) to the disc (10),
characterized in that the heels (17) of each blade root (12) are divided into two groups of heels, the heels (A, B, D, E) of one of said groups being offset on the side of the lower surface of said blade (17) and heels (C) of the other group being offset towards the upper surface,
in that the heels (A, B, D, E) of a group of heels of any blade (11b) form an alignment of blades (18) with the heels (C) of the other group of heels from a neighboring blade (11a) and
in that the means for fixing said blades (11) comprise, for each alignment of blades (18), a spindle (19) disposed in corresponding bores passing right through the plurality of annular ribs (15) and the heels (A, B, C, D, E) of said alignment of heels (18). Rotor selon la revendication 1, caractérisé en ce que les broches (19) sont introduites par la même face du disque (10).Rotor according to claim 1, characterized in that the pins (19) are introduced through the same face of the disc (10). Rotor selon la revendication 2, caractérisé en ce que les broches (19) sont parallèles à l'axe du disque (10);Rotor according to claim 2, characterized in that the pins (19) are parallel to the axis of the disc (10); Rotor selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les aubes (11) sont réalisées en matériau composite et en ce que les alésages des talons sont délimités par des douilles (20) qui sont contournées à leur partie inférieure par les fibres (21) du composite qui partent ensuite vers l'extrémité externe de l'aube correspondante;Rotor according to any one of claims 1 to 3, characterized in that the blades (11) are made of composite material and in that the bores of the heels are delimited by bushings (20) which are bypassed at their lower part by the fibers (21) of the composite which then leave towards the external end of the corresponding blade; Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que les talons (C) du groupe de talons décalés du côté de l'extrados sont disposés dans la partie médiane du pied d'aube (12).Rotor according to any one of the preceding claims, characterized in that the heels (C) of the group of heels offset from the upper surface side are arranged in the middle part of the blade root (12).
EP94400066A 1993-01-14 1994-01-12 Turbomachine rotor with blade attachment by pins Expired - Lifetime EP0607082B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9300276 1993-01-14
FR9300276A FR2700362B1 (en) 1993-01-14 1993-01-14 Turbomachine rotor with blade attachments by pins.

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EP0607082A1 true EP0607082A1 (en) 1994-07-20
EP0607082B1 EP0607082B1 (en) 1996-03-06

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US (1) US5409353A (en)
EP (1) EP0607082B1 (en)
JP (1) JP2807624B2 (en)
DE (1) DE69400079T2 (en)
FR (1) FR2700362B1 (en)

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FR2963055A1 (en) * 2010-07-21 2012-01-27 Snecma ROTOR BLADE OF A COMPOSITE MATERIAL GAS TURBOMOTOR COMPRISING A CONNECTING HAT, A METHOD OF MANUFACTURING THE BLADE
FR2995004A1 (en) * 2012-09-03 2014-03-07 Snecma High pressure turbine blade for rotor of double flow type turbojet in aeronautical field, has foot mounted on rotor disk, where foot of blade is provided as lengthened band that is rolled up around two cylindrical supports
EP3643882A3 (en) * 2018-10-18 2020-07-01 United Technologies Corporation Rotor assembly for gas turbine engines

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FR2990462B1 (en) * 2012-05-14 2014-05-30 Snecma DEVICE FOR ATTACHING AUBES TO A TURBOMACHINE ROTOR DISC
US9470092B2 (en) * 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine
EP3034783B1 (en) * 2014-12-17 2019-11-20 Rolls-Royce Deutschland Ltd & Co KG A blade arrangement of a jet engine or an aircraft propeller and corresponding engine
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EP3643882A3 (en) * 2018-10-18 2020-07-01 United Technologies Corporation Rotor assembly for gas turbine engines
US11092020B2 (en) 2018-10-18 2021-08-17 Raytheon Technologies Corporation Rotor assembly for gas turbine engines
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Also Published As

Publication number Publication date
JP2807624B2 (en) 1998-10-08
FR2700362B1 (en) 1995-02-10
DE69400079T2 (en) 1996-09-12
EP0607082B1 (en) 1996-03-06
FR2700362A1 (en) 1994-07-13
US5409353A (en) 1995-04-25
JPH06241002A (en) 1994-08-30
DE69400079D1 (en) 1996-04-11

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