EP0429353A1 - Axial turbomachine - Google Patents

Axial turbomachine Download PDF

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Publication number
EP0429353A1
EP0429353A1 EP90403275A EP90403275A EP0429353A1 EP 0429353 A1 EP0429353 A1 EP 0429353A1 EP 90403275 A EP90403275 A EP 90403275A EP 90403275 A EP90403275 A EP 90403275A EP 0429353 A1 EP0429353 A1 EP 0429353A1
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EP
European Patent Office
Prior art keywords
disc
blade
pins
rotor
platform
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Granted
Application number
EP90403275A
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German (de)
French (fr)
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EP0429353B1 (en
Inventor
Pierre Antoine Glowacki
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0429353A1 publication Critical patent/EP0429353A1/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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins

Definitions

  • the present invention relates to a turbomachine rotor with axial flow of the type comprising a disc having a plurality of ribs extending radially outward from its periphery, so as to delimit a plurality of annular grooves between the front annular rib located on the upstream side of the flow and the rear annular rib located on the downstream side flow, a plurality of blades, regularly arranged at the periphery of the disc and extending radially outward, each blade having a foot notched at its end adjacent to the disc so as to define heels, each being received by a corresponding groove and each blade being fixed to the disc by fixing means, and a plurality of added platforms fixed to the disc so as to be, each, arranged between two adjacent blades to delimit, on the side of the disc, the vein of the fluid circulating from upstream to downstream through said plurality of blades during operation of said rotor.
  • 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 foot of dawn 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 of the trailing edge.
  • This arrangement does not allow the spindles to take up all the forces applied to the blades.
  • the added platforms interposed between the blades are requested 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.
  • 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 blade on the disc allow all the forces exerted on the blades to be taken up.
  • the fixing means comprise, for each blade, two substantially parallel pins, equidistant from the periphery of the disc and arranged in corresponding bores passing right through the plurality of annular ribs and the heels of the blade, said pins extending at least between the front annular rib and the rear annular rib and each comprising at one of their ends a spindle head fixed to the disc, and in that each platform is extended at its front and rear ends by plates extending towards the axis of the disc and provided with openings for the passage of the two adjacent pins each retaining a neighboring blade.
  • the parallel and circumferentially offset pins ensure the recovery of forces in all directions.
  • the added platforms are no longer subjected to tangential forces and they can be lighter.
  • the number of parts for fixing the blades and the added platforms is limited compared to the prior art.
  • the bores of the heels of the blade root and of the annular ribs are parallel to the axis of the disc. This facilitates the drilling of the annular ribs.
  • the annular ribs advantageously include notches between two adjacent blade roots.
  • the blades are made of composite material and the bores of each heel are delimited by sockets which are bypassed at their lower part by the fibers of the composite which then leave towards the outer end of the blade.
  • the axial flow turbomachine rotor 1 shown in the drawing, 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 comprising, each , a foot 12 for fixing to the disk 10 and a payroll 13 which extends radially outwards from the periphery of the disk 10.
  • Reported platforms 14, intended to delimit, on the side of the axis of the rotor 1, the vein of the gas flow 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 latter comprises a plurality of annular ribs 15 which extend radially outward from its periphery.
  • the blade root 12 has, at its end, radial notches adapted to the annular ribs 15, so as to have heels 16 interposed in correspondence between the annular ribs 15.
  • the number of annular ribs 15 is equal to the number of heels 16 blades 11 increased by one, such that the blade roots 12 are arranged between a front rib 15a located on the upstream side of the flow and a rear rib 15b located on the downstream side.
  • each heel 16 is equal to the distance separating the adjacent annular ribs so as to prevent axial displacement of the blades 11.
  • a space 17 is provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b.
  • Each attached platform 14 has a wall 20 which is inclined relative to the axis of the rotor 1, which extends between the facing faces of two consecutive blades 11a and 11b, and which is extended at its front and rear ends by plates 21 and 22 which extend radially towards the axis of the rotor 1.
  • the front plate 21 is disposed against the front face 23 of the rib annular front 14a and the rear plate 22 has its end portion which accommodates in the space 17 provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b, so as to prevent any axial movement of the platform 14.
  • the wall 20 rests by its longitudinal edges on support fins 20a and 20b provided on the faces of the blade 11 and which extend in the direction of the flow of gas.
  • Each blade 11 is fixed to the disc 10 by two pins 25a and 25b which are introduced by the front face of the rotor 1 into two conduits 26a and 26b parallel and equidistant from the axis of the rotor 1.
  • the conduits 26a and 26b are delimited by aligned bores provided in correspondence in the annular ribs 15 and the heels 16 of the blade root 12.
  • the front plates 21 and rear 22 of each platform also have openings for the passage of the two adjacent pins 25a and 25b which fix , each one of the two neighboring blades 11a and 11b.
  • the pins 25a and 25b for fixing a blade 11 thus hold the blade 11 on the disc 10 and take up the radial and tangential components of the forces exerted on the blade 11.
  • the blade 11 is produced in a composite material, and each heel 16 has two parallel sockets 27a and 27b partially delimiting the conduits 26a and 26b.
  • the fibers of the composite constituting the pay 13 bypass the sockets 27a and 27b at their lower part in the direction of the lower surface towards the upper surface and ensure the continuity of the centrifugal loads.
  • the pins 25a and 25b extend at least between the front rib 15a and the rear rib 15b and they respectively comprise pin heads 32a and 32b which are in abutment against the front face of the front plate 21 of the attached platform 14.
  • the openings of the front plate 21 of the platform 14 through which the pins 25a and 25b pass are replaced by parallel notches 28a and 28h opening onto the end edge 29 of the front plate 21 situated on the side of the axis of the rotor, and this end edge 29 is extended towards the front of the rotor 1 by a flange 30 whose external radial face 31 is intended to cooperate with the edges of the heads 32a and 32b of the pins 25a and 25b, located on the side of the axis of the rotor 1 so as to radially lock the platform 14.
  • the heads 32a and 32b of the two consecutive pins 25a and 25b fixing a platform 14 have a 'trapezoidal shape and each have, on the side of the other pin, a lateral protrusion 33 comprising a notch intended to accommodate the lateral protrusion 33 of the other spindle, so that said protuberances 33 are superimposed on the right of the median zone of the front plate 21 of the platform 14.
  • the two pins 25a and 25b are fixed together and fixed to the platform. form 14 using a fixing screw 34 accommodating in a bore passing through the superimposed lateral protrusions 33 and there the front plate 21 and cooperating with a nut 35 previously fixed on the rear face of the front plate 21.
  • notches 36 are advantageously provided on the annular ribs 15 in the vicinity of the median planes of the platforms 14 between two adjacent blade roots 12.
  • each blade 11 is first placed on the disc 10 so that the bores of the blade roots 12 are aligned with the bores of the annular ribs 15 and the pins 25a and 25b through the front face of the disc 10 in the holes 26a and 26b to immobilize the blade 11.
  • each platform 14 is positioned and fixed by completely introducing the corresponding pins 25a and 25b in the holes 26a and 26b so that the pin heads 32a, 32b cooperate with the flange 30 to radially hold the platform 14.
  • the two pin heads 32a, 32b of the two pins 25a and are then fixed 25b retaining each platform 14, between them and to the front plate 21 of the corresponding platform, using the fixing screw 34.

Abstract

The present invention relates to a rotor of an axial flow turbo-engine comprising a disc (10) having a plurality of annular ribs (15) extending outwards, a plurality of vanes (11) extending radially outwards and a plurality of attached platforms (14) fixed to the disc and defining the jet of gaseous fluid circulating from upstream downwards across the plurality of vanes. The vanes (11) are fixed on the disc (10) by means of two parallel pins (25a, 25b), equidistant from the axis of the disc (10), housed in corresponding bores (26a, 26b) passing through the annular ribs (15) and projections (16) provided on the end of the vane feet (12). The platforms (14) are firmly attached to the disc (10) by the pins (25a, 25b) for fixing the vanes (11). …<IMAGE>…

Description

La présente invention concerne un rotor de turbomachine à flux axial du type comprenant
un disque présentant une pluralité de nervures s'étendant radialement vers l'extérieur à partir de sa périphérie, de manière à délimiter une pluralité de rainures annulaires entre la nervure annulaire avant située du côté amont du flux et la nervure annulaire arrière située du côté aval du flux,
une pluralité d'aubes, régulièrement disposées à la périphérie du disque et s'étendant radialement vers l'extérieur, chaque aube comportant un pied encoché à son extrémité voisine du disque de manière à définir des talons, chacun étant reçu par une rainure correspondante et chaque aube étant fixée au disque par des moyens de fixation, et
une pluralité de plates-formes rapportées fixées au disque de façon à être, chacune, disposée entre deux aubes voisines pour délimiter, du côté du disque, la veine du fluide circulant d'amont en aval à travers ladite pluralité d'aubes lors du fonctionnement dudit rotor.The present invention relates to a turbomachine rotor with axial flow of the type comprising
a disc having a plurality of ribs extending radially outward from its periphery, so as to delimit a plurality of annular grooves between the front annular rib located on the upstream side of the flow and the rear annular rib located on the downstream side flow,
a plurality of blades, regularly arranged at the periphery of the disc and extending radially outward, each blade having a foot notched at its end adjacent to the disc so as to define heels, each being received by a corresponding groove and each blade being fixed to the disc by fixing means, and
a plurality of added platforms fixed to the disc so as to be, each, arranged between two adjacent blades to delimit, on the side of the disc, the vein of the fluid circulating from upstream to downstream through said plurality of blades during operation of said rotor.

Il est connu d'utiliser dans la fabrication des rotors de turbomachine à flux axial des aubes sans plate-forme incorporée et dont le pied comporte une attache du type peigne et qui est fixé par une broche axiale sur les nervures annulaires du disque. Ce type d'attache d'aube simplifie la fabrication du disque par rapport au disque portant des aubes non encochées qui nécessite des alvéoles axiales sur sa périphérie. Le problème qui se pose, en particulier pour les aubes à grande corde utilisées dans les soufflantes et les compresseurs, est la reprise des efforts dans toutes les directions et, en particulier, la reprise des composantes tangentielles des forces appliquées sur les aubes.It is known to use in the manufacture of turbomachine rotors with axial flow vanes without an incorporated platform and the base of which has a comb-type attachment and which is fixed by an axial pin to the annular ribs of the disc. This type of blade attachment simplifies the manufacture of the disc relative to the disc carrying non-notched blades which requires axial cells on its periphery. The problem which arises, in particular for the long cord blades used in blowers and compressors, is the resumption of forces in all directions and, in particular, the resumption of the tangential components of the forces applied to the blades.

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. 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. 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.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 foot of dawn 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 of the trailing edge. 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 requested 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. 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 in the event of disassembly.

Dans d'autres types de constructions de rotors, les forces tangentielles sont reprises par la broche de fixation du pied d'aube grâce à des surfaces curvilignes de l'extrémité du pied qui s'appliquent parfaitement sur les surfaces cylindriques du disque. Le brevet US-4.361.416 montre une telle disposition des aubes qui se traduit inévitablement par une augmentation de masse du pied d'aube.In other types of rotor construction, the tangential forces are taken up by the fixing pin of the blade root thanks to curvilinear surfaces of the end of the foot which are applied perfectly to the cylindrical surfaces of the disc. US Patent 4,361,416 shows such an arrangement of the blades which inevitably results in an increase in mass of the blade root.

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 de l'aube 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 blade 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 les moyens de fixation comportent, pour chaque aube, deux broches sensiblement parallèles, équidistantes de la périphérie du disque et disposées dans des alésages en correspondance traversant de part en part la pluralité de nervures annulaires et les talons de l'aube, lesdites broches s'étendant au moins entre la nervure annulaire avant et la nervure annulaire arrière et comportant chacune à l'une de leurs extrémités une tête de broche fixée au disque, et en ce que chaque plate-forme est prolongée à ses extrémités avant et arrière par des plaques s'étendant vers l'axe du disque et munies d'ouvertures pour le passage des deux broches adjacentes retenant chacune une aube voisine. Grâce à cette disposition, les broches parallèles et circonférentiellement décalées assurent la reprise des efforts dans toutes les directions. Les plates-formes rapportées ne sont plus soumises à des efforts tangentiels et elles peuvent être plus légères. Enfin, le nombre de pièces pour fixer les aubes et les plates-formes rapportées est limité par rapport à l'art antérieur.The object is achieved according to the invention by the fact that the fixing means comprise, for each blade, two substantially parallel pins, equidistant from the periphery of the disc and arranged in corresponding bores passing right through the plurality of annular ribs and the heels of the blade, said pins extending at least between the front annular rib and the rear annular rib and each comprising at one of their ends a spindle head fixed to the disc, and in that each platform is extended at its front and rear ends by plates extending towards the axis of the disc and provided with openings for the passage of the two adjacent pins each retaining a neighboring blade. Thanks to this arrangement, the parallel and circumferentially offset pins ensure the recovery of forces in all directions. The added platforms are no longer subjected to tangential forces and they can be lighter. Finally, the number of parts for fixing the blades and the added platforms is limited compared to the prior art.

De façon avantageuse, les alésages des talons du pied d'aube et des nervures annulaires sont parallèles à l'axe du disque. Ceci facilite le perçage des nervures annulaires.Advantageously, the bores of the heels of the blade root and of the annular ribs are parallel to the axis of the disc. This facilitates the drilling of the annular ribs.

De façon à alléger le disque, les nervures annulaires comportent avantageusement des échancrures entre deux pieds d'aube adjacents.In order to lighten the disc, the annular ribs advantageously include notches between two adjacent blade roots.

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

D'autres avantages et caractéristiques de l'invention apparaîtront 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 vue frontale, partiellement coupée, montrant la disposition de deux aubes voisines et de la plate-forme rapportée disposée entre celles-ci, les aubes étant respectivement représentées selon leur section par deux plans perpendiculaires à l'axe du rotor et axialement décalés.
  • La figure 2 est une coupe axiale du rotor selon la ligne II II de la figure 1,
  • La figure 3 est une vue de la face avant du disque seul,
  • La figure 4 est une vue de la face avant du rotor sans les têtes de broches,
  • La figure 5 est une vue partielle de la face avant du rotor montrant la fixation des têtes de broches, et
  • La figure 6 est une vue en perspective 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 a front view, partially cut away, showing the arrangement of two neighboring blades and of the attached platform arranged between them, the blades being respectively represented according to their section by two planes perpendicular to the axis of the rotor and axially offset.
  • FIG. 2 is an axial section of the rotor along line II II of FIG. 1,
  • FIG. 3 is a view of the front face of the disc alone,
  • FIG. 4 is a view of the front face of the rotor without the pin heads,
  • FIG. 5 is a partial view of the front face of the rotor showing the fixing of the pin heads, and
  • Figure 6 is a perspective view of a blade.

Le rotor de turbomachine à flux axial 1, montré sur le dessin, 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 paie 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 axial flow turbomachine rotor 1, shown in the drawing, 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 comprising, each , a foot 12 for fixing to the disk 10 and a payroll 13 which extends radially outwards from the periphery of the disk 10. Reported platforms 14, intended to delimit, on the side of the axis of the rotor 1, the vein of the gas flow 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.

Pour assurer l'attache des aubes 11 sur le disque 10, celui-ci comprend une pluralité de nervures annulaires 15 qui s'étend radialement vers l'extérieur à partir de sa périphérie. Le pied d'aube 12 comporte, à son extrémité, des encoches radiales adaptées aux nervures annulaires 15, de manière à présenter des talons 16 interposés en concordance entre les nervures annulaires 15. Le nombre de nervures annulaires 15 est égal au nombre de talons 16 des aubes 11 augmenté de un, de telle manière que les pieds d'aubes 12 sont disposés entre une nervure avant 15a située du côté amont du flux et une nervure arrière 15b située du côté aval.To ensure the attachment of the blades 11 on the disc 10, the latter comprises a plurality of annular ribs 15 which extend radially outward from its periphery. The blade root 12 has, at its end, radial notches adapted to the annular ribs 15, so as to have heels 16 interposed in correspondence between the annular ribs 15. The number of annular ribs 15 is equal to the number of heels 16 blades 11 increased by one, such that the blade roots 12 are arranged between a front rib 15a located on the upstream side of the flow and a rear rib 15b located on the downstream side.

La longueur axiale de chaque talon 16 est égale à la distance séparant les nervures annulaires voisines de manière à empêcher un déplacement axial des aubes 11. Toutefois, un espace 17 est prévu entre la face arrière 18 du pied d'aube 12 et la face avant 19 de la nervure annulaire arrière 15b.The axial length of each heel 16 is equal to the distance separating the adjacent annular ribs so as to prevent axial displacement of the blades 11. However, a space 17 is provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b.

Chaque plate-forme rapportée 14 présente une paroi 20 qui est inclinée par rapport à l'axe du rotor 1, qui s'étend entre les faces en vis-à-vis de deux aubes consécutives 11a et 11b, et qui est prolongée à ses extrémités avant et arrière par des plaques 21 et 22 qui s'étendent radialement vers l'axe du rotor 1. La plaque avant 21 est disposée contre la face avant 23 de la nervure annulaire avant 14a et la plaque arrière 22 a sa partie d'extrémité qui loge dans l'espace 17 prévu entre la face arrière 18 du pied d'aube 12 et la face avant 19 de la nervure annulaire arrière 15b, de manière à empêcher tout déplacement axial de la plate-forme 14. La paroi 20 repose par ses bords longitudinaux sur des ailettes de support 20a et 20b prévues sur les faces de l'aube 11 et qui s'étendent dans le sens de la veine du flux gazeux.Each attached platform 14 has a wall 20 which is inclined relative to the axis of the rotor 1, which extends between the facing faces of two consecutive blades 11a and 11b, and which is extended at its front and rear ends by plates 21 and 22 which extend radially towards the axis of the rotor 1. The front plate 21 is disposed against the front face 23 of the rib annular front 14a and the rear plate 22 has its end portion which accommodates in the space 17 provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b, so as to prevent any axial movement of the platform 14. The wall 20 rests by its longitudinal edges on support fins 20a and 20b provided on the faces of the blade 11 and which extend in the direction of the flow of gas.

Chaque aube 11 est fixée sur le disque 10 par deux broches 25a et 25b qui sont introduites par la face avant du rotor 1 dans deux conduits 26a et 26b parallèles et équidistants de l'axe du rotor 1. Les conduits 26a et 26b sont délimités par des alésages alignés prévus en correspondance dans les nervures annulaires 15 et les talons 16 du pied d'aube 12. Les plaques avant 21 et arrière 22 de chaque plate-forme comportent également des ouvertures pour le passage des deux broches 25a et 25b adjacentes qui fixent, chacune, l'une des deux aubes voisines 11a et 11b.Each blade 11 is fixed to the disc 10 by two pins 25a and 25b which are introduced by the front face of the rotor 1 into two conduits 26a and 26b parallel and equidistant from the axis of the rotor 1. The conduits 26a and 26b are delimited by aligned bores provided in correspondence in the annular ribs 15 and the heels 16 of the blade root 12. The front plates 21 and rear 22 of each platform also have openings for the passage of the two adjacent pins 25a and 25b which fix , each one of the two neighboring blades 11a and 11b.

Les broches 25a et 25b de fixation d'une aube 11 maintiennent ainsi l'aube 11 sur le disque 10 et reprennent les composantes radiales et tangentielles des forces qui s'exercent sur l'aube 11. De préférence, l'aube 11 est réalisée dans un maté­riau composite, et chaque talon 16 comporte deux douilles paral­lèles 27a et 27b délimitant partiellement les conduits 26a et 26b.The pins 25a and 25b for fixing a blade 11 thus hold the blade 11 on the disc 10 and take up the radial and tangential components of the forces exerted on the blade 11. Preferably, the blade 11 is produced in a composite material, and each heel 16 has two parallel sockets 27a and 27b partially delimiting the conduits 26a and 26b.

Les fibres du composite constituant la paie 13 contournent les douilles 27a et 27b à leur partie inférieure dans le sens de l'intrados vers l'extrados et assurent la continuité des charges centrifuges.The fibers of the composite constituting the pay 13 bypass the sockets 27a and 27b at their lower part in the direction of the lower surface towards the upper surface and ensure the continuity of the centrifugal loads.

Les broches 25a et 25b s'étendent au moins entre la nervure avant 15a et la nervure arrière 15b et elles comportent respectivement des têtes de broches 32a et 32b qui sont en butée contre la face avant de la plaque avant 21 de la plate-forme rapportée 14.The pins 25a and 25b extend at least between the front rib 15a and the rear rib 15b and they respectively comprise pin heads 32a and 32b which are in abutment against the front face of the front plate 21 of the attached platform 14.

De préférence, les ouvertures de la plaque avant 21 de la plate-forme 14 par lesquelles passent les broches 25a et 25b sont remplacées par des échancrures 28a et 28h parallèles débouchant sur le bord d'extrémité 29 de la plaque avant 21 situé du côté de l'axe du rotor, et ce bord d'extrémité 29 est prolongé vers l'avant du rotor 1 par un rebord 30 dont la face radiale externe 31 est destinée à coopérer avec les bords des têtes 32a et 32b des broches 25a et 25b, situés du côté de l'axe du rotor 1 de façon à verrouiller radialement la plate-forme 14.Preferably, the openings of the front plate 21 of the platform 14 through which the pins 25a and 25b pass are replaced by parallel notches 28a and 28h opening onto the end edge 29 of the front plate 21 situated on the side of the axis of the rotor, and this end edge 29 is extended towards the front of the rotor 1 by a flange 30 whose external radial face 31 is intended to cooperate with the edges of the heads 32a and 32b of the pins 25a and 25b, located on the side of the axis of the rotor 1 so as to radially lock the platform 14.

Les têtes 32a et 32b des deux broches 25a et 25b consécutives fixant une plate-forme 14 ont une forme' trapézoïdale et présentent, chacune, du côté de l'autre broche, une excroissance latérale 33 comportant une échancrure destinée à loger l'excroissance latérale 33 de l'autre broche, de telle manière que lesdites excroissances 33 se superposent au droit de la zone médiane de la plaque avant 21 de la plate-forme 14. Les deux broches 25a et 25b sont fixées entre elles et fixées à la plate-forme 14 à l'aide d'une vis de fixation 34 logeant dans un alésage traversant les excroissances latérales superposées 33 et là plaque avant 21 et coopérant avec un écrou 35 préalablement fixé sur la face arrière de la plaque avant 21.The heads 32a and 32b of the two consecutive pins 25a and 25b fixing a platform 14 have a 'trapezoidal shape and each have, on the side of the other pin, a lateral protrusion 33 comprising a notch intended to accommodate the lateral protrusion 33 of the other spindle, so that said protuberances 33 are superimposed on the right of the median zone of the front plate 21 of the platform 14. The two pins 25a and 25b are fixed together and fixed to the platform. form 14 using a fixing screw 34 accommodating in a bore passing through the superimposed lateral protrusions 33 and there the front plate 21 and cooperating with a nut 35 previously fixed on the rear face of the front plate 21.

De manière à alléger le disque 10, des échancrures 36 sont avantageusement prévues sur les nervures annulaires 15 au voisinage des plans médians des plates-formes 14 entre deux pieds d'aube 12 adjacents.In order to lighten the disc 10, notches 36 are advantageously provided on the annular ribs 15 in the vicinity of the median planes of the platforms 14 between two adjacent blade roots 12.

Le montage du rotor 1 se fait de la façon suivante : on dispose d'abord chaque aube 11 sur le disque 10 de telle manière que les alésages des pieds d'aube 12 soient alignés avec les alésa­ges des nervures annulaires 15 et on introduit partiellement les broches 25a et 25b par la face avant du disque 10 dans les orifices 26a et 26b pour immobiliser l'aube 11. Après avoir ainsi immobilisé toutes les aubes 11, on positionne chaque plate-forme 14 et on la fixe en introduisant complètement les broches corres­pondantes 25a et 25b dans les orifices 26a et 26b de telle manière que les têtes de broches 32a, 32b coopèrent avec le rebord 30 pour maintenir radialement la plate-forme 14. On fixe ensuite les deux têtes de broches 32a, 32b des deux broches 25a et 25b retenant chaque plate-forme 14, entre elles et à la plaque avant 21 de la plate-forme correspondante, à l'aide de la vis de fixation 34.The mounting of the rotor 1 is carried out as follows: each blade 11 is first placed on the disc 10 so that the bores of the blade roots 12 are aligned with the bores of the annular ribs 15 and the pins 25a and 25b through the front face of the disc 10 in the holes 26a and 26b to immobilize the blade 11. After having thus immobilized all the blades 11, each platform 14 is positioned and fixed by completely introducing the corresponding pins 25a and 25b in the holes 26a and 26b so that the pin heads 32a, 32b cooperate with the flange 30 to radially hold the platform 14. The two pin heads 32a, 32b of the two pins 25a and are then fixed 25b retaining each platform 14, between them and to the front plate 21 of the corresponding platform, using the fixing screw 34.

Claims (9)

1. Rotor de turbomachine à flux axial du type comprenant
un disque (10) présentant une pluralité de nervures annulaires (15) s'étendant vers l'extérieur à partir de sa périphérie de manière à délimiter une pluralité de rainures annulaires entre la nervure annulaire avant (15a) située du côté amont du flux et la nervure annulaire arrière (15b) située du côté aval du flux,
une pluralité d'aubes (11), régulièrement disposées à la périphérie du disque (10) et s'étendant radialement vers l'extérieur, chaque aube (11) comportant un pied (12) encoché à son extrémité voisine du disque (10) de manière à définir des talons (16) chacun étant reçu par une rainure correspondante et chaque aube étant fixée au disque (10) par des moyens de fixation (25a, 25b) et
une pluralité de plates-formes rapportées (14) fixées au disque (10), de façon à être, chacune, disposée entre deux aubes voisines (11a, 11b) pour délimiter, du côté du disque (10), la veine du fluide circulant d'amont en aval à travers ladite pluralité d'aubes lors du fonctionnement dudit rotor,
caractérisé en ce que les moyens de fixation comportent pour chaque aube (11) deux broches (25a, 25b) sensiblement parallèles, équidistantes de la périphérie du disque (10) et disposées dans des alésages en correspondance (26a, 26b) traversant de part en part la pluralité des nervures annulaires (15) et les talons (16) de l'aube (11), lesdites broches s'étendant au moins entre la nervure annulaire avant (15a) et la nervure annulaire arrière (15b) et comportant, chacune, à l'une de leurs extrémités, une tête de broche (32a, 32b) fixée au disque, et en ce que chaque plate-forme (14) est prolongée à ses extrémités avant et arrière par des plaques (21, 22) s'étendant radialement vers l'axe du disque (10) et munies d'ouvertures pour le passage de deux broches adjacentes (25a, 25b) retenant chacune une aube voisine (11a, 11b).1. Axial-flow turbomachine rotor of the type comprising
a disc (10) having a plurality of annular ribs (15) extending outwards from its periphery so as to delimit a plurality of annular grooves between the front annular rib (15a) situated on the upstream side of the flow and the rear annular rib (15b) located on the downstream side of the flow,
a plurality of blades (11), regularly arranged at the periphery of the disc (10) and extending radially outward, each blade (11) comprising a foot (12) notched at its end close to the disc (10) so as to define heels (16) each being received by a corresponding groove and each blade being fixed to the disc (10) by fixing means (25a, 25b) and
a plurality of attached platforms (14) fixed to the disc (10), so as to be, each, arranged between two adjacent blades (11a, 11b) to delimit, on the side of the disc (10), the vein of the circulating fluid from upstream to downstream through said plurality of blades during operation of said rotor,
characterized in that the fixing means comprise for each blade (11) two pins (25a, 25b) substantially parallel, equidistant from the periphery of the disc (10) and arranged in corresponding bores (26a, 26b) passing right through share the plurality of annular ribs (15) and the heels (16) of the blade (11), said pins extending at least between the front annular rib (15a) and the rear annular rib (15b) and comprising, each , at one of their ends, a spindle head (32a, 32b) fixed to the disc, and in that each platform (14) is extended at its front and rear ends by plates (21, 22) s 'extending radially towards the axis of the disc (10) and provided with openings for the passage of two adjacent pins (25a, 25b) each retaining a neighboring blade (11a, 11b). 2. Rotor selon la revendication 1 caractérisé en ce que les alésages (26a, 26b) des talons (16) du pied d'aube (12) et des nervures annulaires (15) sont parallèles à l'axe du disque (10).2. Rotor according to claim 1 characterized in that the bores (26a, 26b) of the heels (16) of the blade root (12) and of the annular ribs (15) are parallel to the axis of the disc (10). 3. Rotor selon l'une quelconque des revendications 1 et 2, caractérisé en ce que les nervures annulaires (15) comportent des échancrures (36) entre deux pieds d'aube adjacents (12).3. Rotor according to any one of claims 1 and 2, characterized in that the annular ribs (15) have notches (36) between two adjacent blade roots (12). 4. Rotor selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les aubes sont réalisées en matériau composite et en ce que les alésages (26a, 26b) de chaque talon (16) sont délimités par des douilles (27a, 27b) qui sont contournées à leur partie inférieure par les fibres du composite qui partent ensuite vers l'extrémité externe de l'aube.4. Rotor according to any one of claims 1 to 3, characterized in that the blades are made of composite material and in that the bores (26a, 26b) of each heel (16) are delimited by sockets (27a, 27b) which are bypassed at their lower part by the fibers of the composite which then leave towards the outer end of the blade. 5. Rotor selon l'une quelconque des revendications 1 à 4, caractérisé en ce que la plaque arrière (22) de la plate-forme (14) est disposée entre les faces arrières (18) des deux pieds d'aube adjacents (12) et la face avant (19) de la nervure annulaire arrière (15b).5. Rotor according to any one of claims 1 to 4, characterized in that the rear plate (22) of the platform (14) is disposed between the rear faces (18) of the two adjacent blade feet (12 ) and the front face (19) of the rear annular rib (15b). 6. Rotor selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la plaque avant (21) est disposée contre la face avant (23) de la nervure annulaire avant (15e) et présente deux échancrures parallèles (28a, 28b) ouvertes du côté de l'axe du rotor pour le passage des broches (25a et 25b) et un rebord d'extrémité (30) s'étendent vers l'avant et formant verrou avec les têtes (32a, 32b) des broches (25a, 25b).6. Rotor according to any one of claims 1 to 5, characterized in that the front plate (21) is disposed against the front face (23) of the front annular rib (15e) and has two parallel notches (28a, 28b ) open on the side of the rotor axis for the passage of the pins (25a and 25b) and an end flange (30) extend forward and forming a lock with the heads (32a, 32b) of the pins ( 25a, 25b). 7. Rotor selon la revendication 6, caractérisé en ce que les têtes de broches (32a, 32b) présentent, chacune, du côté de l'autre bro­che, une excroissance latérale (33) comportant une échancrure des­tinée à loger l'excroissance latérale (33) de l'autre broche, de telle manière que lesdites excroissances (33) se superposent au droit de la zone médiane de la plaque avant (21) de la plate-forme (14).7. Rotor according to claim 6, characterized in that the spindle heads (32a, 32b) each have, on the side of the other spindle, a lateral protuberance (33) comprising a notch intended to accommodate the lateral protrusion ( 33) of the other spindle, so that said protuberances (33) are superimposed on the right of the central zone of the front plate (21) of the platform (14). 8. Rotor selon la revendication 7, caractérisé en ce que les deux broches (25a, 25b) sont fixées entre elles et à la plate-forme (14) à l'aide d'une vis de fixation (34) logeant dans un alésage traversant les excroissances superposées (33) et la plaque avant (21) de la plate-forme (14) et coopèrent avec un écrou fixé sur la face arrière de ladite plaque avant (21).8. Rotor according to claim 7, characterized in that the two pins (25a, 25b) are fixed to each other and to the platform (14) using a fixing screw (34) accommodating in a bore passing through the superimposed projections (33) and the front plate (21) of the platform (14) and cooperate with a nut fixed on the rear face of said front plate (21). 9. Rotor selon l'une quelconque des revendications 1 à 8, caractérisé en ce que chaque plate-forme (14) repose par ses bords longitudinaux sur des ailettes de support (20a, 20b) prévues sur les faces de l'aube et qui s'étendent dans le sens de la veine du flux gazeux.9. Rotor according to any one of claims 1 to 8, characterized in that each platform (14) rests by its longitudinal edges on support fins (20a, 20b) provided on the faces of the blade and which extend in the direction of the gas flow.
EP90403275A 1989-11-22 1990-11-21 Axial turbomachine Expired - Lifetime EP0429353B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8915301A FR2654773B1 (en) 1989-11-22 1989-11-22 AXIAL FLOW TURBOMACHINE ROTOR.
FR8915301 1989-11-22

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EP0429353A1 true EP0429353A1 (en) 1991-05-29
EP0429353B1 EP0429353B1 (en) 1993-05-26

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EP90403275A Expired - Lifetime EP0429353B1 (en) 1989-11-22 1990-11-21 Axial turbomachine

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US (1) US5145319A (en)
EP (1) EP0429353B1 (en)
DE (1) DE69001745T2 (en)
FR (1) FR2654773B1 (en)

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FR2700362A1 (en) * 1993-01-14 1994-07-13 Snecma Turbomachine rotor with blade attachments by pins.
EP2070819A1 (en) 2007-12-14 2009-06-17 Eurocopter Rotorcraft blade, rotorcraft rotor equipped with said blade and method of manufacturing this blade

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US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US9470092B2 (en) * 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine
US10557361B1 (en) 2018-10-16 2020-02-11 United Technologies Corporation Platform for an airfoil of a gas turbine engine
US11306601B2 (en) * 2018-10-18 2022-04-19 Raytheon Technologies Corporation Pinned airfoil for gas turbine engines

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US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
FR2700362A1 (en) * 1993-01-14 1994-07-13 Snecma Turbomachine rotor with blade attachments by pins.
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Also Published As

Publication number Publication date
FR2654773B1 (en) 1992-02-14
DE69001745T2 (en) 1993-10-07
US5145319A (en) 1992-09-08
DE69001745D1 (en) 1993-07-01
FR2654773A1 (en) 1991-05-24
EP0429353B1 (en) 1993-05-26

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