EP0263002B1 - Sealing and locking device for the vanes of a turbo machine - Google Patents

Sealing and locking device for the vanes of a turbo machine Download PDF

Info

Publication number
EP0263002B1
EP0263002B1 EP87401958A EP87401958A EP0263002B1 EP 0263002 B1 EP0263002 B1 EP 0263002B1 EP 87401958 A EP87401958 A EP 87401958A EP 87401958 A EP87401958 A EP 87401958A EP 0263002 B1 EP0263002 B1 EP 0263002B1
Authority
EP
European Patent Office
Prior art keywords
disc
segment
blades
blade
throat
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.)
Expired - Lifetime
Application number
EP87401958A
Other languages
German (de)
French (fr)
Other versions
EP0263002A1 (en
Inventor
Jean-Louis Bertrand
Jacky Naudet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0263002A1 publication Critical patent/EP0263002A1/en
Application granted granted Critical
Publication of EP0263002B1 publication Critical patent/EP0263002B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
  • a first problem consists in ensuring the axial locking of each of the blades in the simplest possible but also the safest way possible and so that the easy disassembly of a blade or of the entire stage is also simplified.
  • the second problem is that of the seal between the upstream and the downstream of a disc and arises crucially in the compressors of the turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
  • the pinned blades are locked axially, on one side by a spoiler at the foot of the blade, which ensures locking in one direction, and on the other side by a split elastic segment which is clamped during assembly. to reduce its diameter and introduce it into the bore formed by the teeth of the disc in order to then allow it to relax inside an annular groove formed in the teeth of the disc and in the feet of the blades.
  • the segment is notched so as to enter jointly into a circular slot of the disc and into slots of the spoilers of the blades, then is turned by a half-step so that the full part of the segment comes to lock in said slots. If it provides locking, such a segment has the disadvantage of poorly sealing at the feet of the blades.
  • the object of the invention is to remedy the aforementioned problems by means of a simple device comprising a very small number of parts which simultaneously ensure sealing at the level of the blade roots and the axial locking of the blades on the disc.
  • Another object is to provide a device adaptable to rotor discs of compressors or small diameter turbines such as those existing in aircraft turbomachines such as turbojet engines, turbojet engines with non-faired counter-rotating propellers, called propane, or faired, or in other aviation turbomachines.
  • the subject of the invention is therefore a turbomachine rotor, in particular for an aviation turbomachine comprising at least one disc carrying a set of vanes, the feet of which are mounted in stapled cells on the periphery of the disc along a parallel or slightly inclined axis. relative to a parallel to the longitudinal axis of the engine, the blade roots comprising a means of wedging the blades on the upstream face of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery.
  • the rotor comprises a means of axial locking downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the cells of the disc, said means for locking downstream of the blades on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the blades and the circular groove of the disc, the first segment having a rectangular notch on its radially external part and the second segment inserted by radial compression having a radial width at least equal to that "1" of the notch of the first segment.
  • Figure 1 are shown by way of example in longitudinal section the first two stages of a high pressure compressor rotor of a turbojet engine.
  • the first stage of the rotor comprises a disc 1 connected by an upstream flange 2 to a medium or low pressure compressor and by a downstream flange 3 from the second stage of the rotor, generally referenced 4, of the HP compressor.
  • Blades 5 having under their platform 6 a foot 7 are slid axially in cells 8 of the disc in a conventional manner.
  • Figure 1 shows that the longitudinal axis of the cells is here slightly inclined relative to a parallel to the longitudinal axis 9 of the engine in a radial plane and this axis could also be slightly inclined relative to the axis 9 in a plane tangential to the periphery of the disc 1.
  • the blade roots 7 have upstream an axial wedging means formed by an upstream spoiler 10 radially oriented towards the axis of symmetry 9, said spoiler coming to bear against the upstream face 11 of the disc 1.
  • the blade also has downstream a spoiler 12 defining between it and the blade root a circular groove 13 whose opening is radially oriented towards the axis of symmetry of the disc.
  • the disc 1 Facing this groove 13 of the blade set up, the disc 1 has a circular groove 14 facing it, that is to say having its opening oriented radially towards the periphery of the disc and machined to a diameter smaller than the diameter machining the bottom of the cells 8.
  • the blade locking and sealing device comprises a first split segment 15 whose radial width "1" is equal to the distance separating the bottoms of the grooves 12 from the blade spoilers and 14 from the disc.
  • the first segment 15 can undergo a slight radial deformation as well as an axial deformation so that the slats of the slot are no longer in the plane containing the segment and when the segment is in this deformed position, it can be put in place in the groove 14 by introducing one of its ends into the groove and then "screwing" circular.
  • the segment 15 completely masks the downstream openings of the cells 8.
  • the segment 15 has a rectangular notch 16 allowing the passage of the downstream spoiler 12 of a blade until the upstream spoiler 10 comes into abutment on the upstream face of the disc.
  • the segment 15 is engaged in the groove 13 of the already mounted blade and the notch 16 is brought in front of the cell 8 of the next blade to be put in place.
  • the same mounting operation is carried out successively for each of the following blades until all the blades are completely installed.
  • the locking device also comprises a second split segment 17 dimensioned in such a way, firstly that its external diameter is equal to that of the bottom of the groove 13 of the blades, secondly that the sum of its thickness and of that of the first segment allows it to be inserted into the groove 13 downstream of the first segment 15 and thirdly that its radial height is at least equal to that "1 '" of the notch 16 of the first segment in order to hide completely this opening, once the second segment 17 in place.
  • the positioning of the second segment is carried out by radial compression, which makes it possible to slide it radially under the downstream spoilers 12 of the blades then by letting it relax to its nominal diameter, to engage it at the bottom of the groove 13.
  • the centrifugation effect of segment 17 during operation of the turbomachine ensures that the segment is held correctly in place.
  • the disassembly of the locking device is carried out by carrying out all the operations in the reverse order to what has just been described.
  • the first segment 15 completely masks the trailing lunules, which without its presence would exist between the feet of the blade 7 and the bottom of the cells 8.
  • the disc shown has on the teeth 18 separating the cells downstream also a spoiler 19 defining a groove which provides continuity between the grooves 13 of the blade spoilers.
  • these teeth 19 spoilers are no longer necessary with the device according to the invention and can be eliminated, which greatly simplifies the machining of the discs and reduces the manufacturing cost.
  • the invention provides a simple solution to the problem of interlocking padded rotor blades, which makes it applicable in particular to small motor rotors.

Landscapes

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

Description

La présente invention concerne les rotors de turbomachine et plus particulièrement les moyens de verrouillage axial d'aubes montées dans des brochages axiaux de la périphérie du disque.The present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.

Lorsque les aubes de rotors des turbomachines sont fixées dans des brochages axiaux, c'est-à-dire parallèles à l'axe de la turbomachine ou faiblement écartés d'une parallèle à l'axe de la turbomachine, deux problèmes se posent au montage.When the rotor blades of turbomachinery are fixed in axial pinouts, that is to say parallel to the axis of the turbomachine or slightly spaced from a parallel to the axis of the turbomachine, two problems arise in mounting. .

Un premier problème consiste à assurer le verrouillage axial de chacune des aubes de la façon la plus simple possible mais aussi la plus sûre possible et de sorte que le démontage facile d'une aube ou de l'étage entier soit également simplifié.A first problem consists in ensuring the axial locking of each of the blades in the simplest possible but also the safest way possible and so that the easy disassembly of a blade or of the entire stage is also simplified.

Le second problème est celui de l'étanchéité entre l'amont et l'aval d'un disque et se pose de façon cruciale dans les compresseurs du turbomachines. En effet, si les espaces situés entre les fonds d'alvéoles du disque et les pieds d'aubes ne sont pas masqués convenablement, des volumes importants d'air aval peuvent passer sous les pieds d'aubes et recirculer vers l'amont du compresseur, ce qui diminue le taux de compression de celui-ci et fait chuter de façon prohibitive le rendement global de la turbomachine.The second problem is that of the seal between the upstream and the downstream of a disc and arises crucially in the compressors of the turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.

Généralement, les aubes brochées sont verrouillées axialement, d'un côté par un becquet du pied de l'aube, lequel assure le verrouillage dans un sens, et de l'autre côté par un segment élastique fendu que l'on pince au montage afin de diminuer son diamètre et l'introduire dans l'alésage constitué par les dents du disque pour le laisser ensuite se détendre à l'intérieur d'une gorge annulaire ménagée dans les dents du disque et dans les pieds des aubes.Generally, the pinned blades are locked axially, on one side by a spoiler at the foot of the blade, which ensures locking in one direction, and on the other side by a split elastic segment which is clamped during assembly. to reduce its diameter and introduce it into the bore formed by the teeth of the disc in order to then allow it to relax inside an annular groove formed in the teeth of the disc and in the feet of the blades.

Dans un autre cas, tel que représenté au brevet FR 2 501 283 le segment est échancré de façon à pénétrer conjointement dans une fente circulaire du disque et dans des fentes des becquets d'aubes puis est tourné d'un demi-pas afin que la partie pleine du segment vienne se verrouiller dans lesdites fentes. S'il assure le verouillage, un tel segment a pour inconvénient de mal assurer l'étanchéité au niveau des pieds des aubes.In another case, as shown in patent FR 2 501 283, the segment is notched so as to enter jointly into a circular slot of the disc and into slots of the spoilers of the blades, then is turned by a half-step so that the full part of the segment comes to lock in said slots. If it provides locking, such a segment has the disadvantage of poorly sealing at the feet of the blades.

Pour résoudre ce problème on a proposé dans le brevet GB 1 512 882 à propos d'une roue de turbine d'utiliser des plaques segmentées coopérant avec une rainure circulaire du disque et des rainures des plates-formes des aubes, un joint torique disposé dans la rainure du disque coopérant avec une face tronconique des plaques pour les comprimer par centrifugation contre les rainures des plates-formes. Une telle disposition, qui permet d'assurer une certaine étanchéité au niveau des brochages de pieds d'aubes n'est toutefois pas facilement utilisable pour des disques de compresseur de faible diamètre et d'autre part nécessite un grand nombre de pièces, ce qui en complique la mise en place et la maintenance.To solve this problem, it has been proposed in the patent GB 1 512 882 about a turbine wheel to use segmented plates cooperating with a circular groove of the disc and grooves of the platforms of the blades, an O-ring arranged in the groove of the disc cooperating with a frustoconical face of the plates to compress them by centrifugation against the grooves of the platforms. Such an arrangement, which makes it possible to ensure a certain tightness at the level of blade pin assignments, is however not easily usable for compressor discs of small diameter and on the other hand requires a large number of parts, which complicates installation and maintenance.

Le but de l'invention est de remédier aux problèmes précités au moyen d'un dispositif simple comportant un très faible nombre de pièces qui assurent simultanément l'étanchéité au niveau des pieds d'aubes et le verrouillage axial des aubes sur le disque.The object of the invention is to remedy the aforementioned problems by means of a simple device comprising a very small number of parts which simultaneously ensure sealing at the level of the blade roots and the axial locking of the blades on the disc.

Un autre but est de prévoir un dispositif adaptable à des disques de rotor de compresseurs ou de turbines de faible diamètre tels que ceux existant dans des turbomachines d'avion comme les turboréacteurs, les turboréacteurs à hélices contrarotatives non carénées, dits propfans, ou carénées, ou dans d'autres turbomachines d'aviation.Another object is to provide a device adaptable to rotor discs of compressors or small diameter turbines such as those existing in aircraft turbomachines such as turbojet engines, turbojet engines with non-faired counter-rotating propellers, called propane, or faired, or in other aviation turbomachines.

L'invention a donc pour objet un rotor de turbomachine, notamment pour turbomachine d'aviation comportant au moins un disque portant un ensemble d'aubes dont les pieds sont montés dans des alvéoles brochés sur la périphérie du disque selon un axe parallèle ou faiblement incliné par rapport à une parallèle à l'axe longitudinal du moteur, les pieds d'aubes comportant un moyen de calage des aubes sur la face amont du disque et un becquet arrière possédant une gorge transversale radialement orientée vers l'axe du disque tandis que le disque comporte une gorge circulaire radialement orientée vers sa périphérie.The subject of the invention is therefore a turbomachine rotor, in particular for an aviation turbomachine comprising at least one disc carrying a set of vanes, the feet of which are mounted in stapled cells on the periphery of the disc along a parallel or slightly inclined axis. relative to a parallel to the longitudinal axis of the engine, the blade roots comprising a means of wedging the blades on the upstream face of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery.

Selon l'invention, le rotor comporte un moyen de verrouillage axial aval des aubes sur le disque, assurant simultanément l'étanchéité entre les pieds d'aube et le fond des alvéoles du disque, ledit moyen de verrouillage aval des aubes sur le disque etant constitué par deux segments fendus dont le premier au moins coopère simultanément avec les gorges des becquets des aubes et la gorge circulaire du disque, le premier segment possédant une échancrure rectangulaire sur sa partie radialement externe et le second segment inséré par compression radiale ayant une largeur radiale au moins égale à celle "1" de l'échancrure du premier segment.According to the invention, the rotor comprises a means of axial locking downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the cells of the disc, said means for locking downstream of the blades on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the blades and the circular groove of the disc, the first segment having a rectangular notch on its radially external part and the second segment inserted by radial compression having a radial width at least equal to that "1" of the notch of the first segment.

L'invention a également pour objet un procédé de montage des aubes sur un disque de rotor de turbomachine selon lequel:

  • a) on insère un premier segment fendu dans une gorge de la face aval du disque par déformation axiale des deux becs de la fente du segment et mise en rotation dudit premier segment dans la gorge ;
  • b) on amène une échancrure du premier segment en face d'un alvéole du disque ;
  • c) on insère une aube dans l'alvéole jusqu'à la mise en butée sur le disque de son moyen de calage amont et au chevauchement de la gorge du becquet de l'aube sur le premier segment ;
  • d) on fait tourner le premier segment d'un pas et on monte l'aube suivant, les opérations (c) et (d) étant recommencées jusqu'au montage de toutes les aubes ;
  • e) on comprime radialement un second segment et on le met en place par extension radiale dans la gorge formée par les becquets entre le premier segment et la partie aval des becquets d'aubes.
The subject of the invention is also a method of mounting the blades on a turbomachine rotor disc according to which:
  • a) a first split segment is inserted into a groove in the downstream face of the disc by axial deformation of the two nozzles of the segment slot and rotation of said first segment in the groove;
  • b) a notch of the first segment is brought in front of a disc socket;
  • c) inserting a blade into the cell until the abutment on the disc of its upstream wedging means and overlapping the groove of the spoiler of the blade on the first segment;
  • d) the first segment is rotated by one step and the next blade is mounted, operations (c) and (d) being repeated until the assembly of all the blades;
  • e) a second segment is radially compressed and it is put in place by radial extension in the groove formed by the spoilers between the first segment and the downstream part of the spoilers of blades.

D'autres caractéristiques et des détails de l'invention seront décrites à la lumière du complément qui va suivre de la description et des planches de dessins annexées, lesquels représentent de façon non limitative l'application de l'invention au montage des aubes sur un disque de compresseur de turboréacteur.Other characteristics and details of the invention will be described in the light of the complement which will follow from the description and from the accompanying drawing plates, which represent in a nonlimiting manner the application of the invention to the mounting of the blades on a turbojet compressor disc.

Parmi ces planches :

  • - la figure 1 montre en demi-coupe longitudinale un disque de compresseur et une aube montée sur le disque et verrouillée au moyen du dispositif de verrouillage et d'étanchéité selon l'invention ;
  • - la figure 2 montre en vue aval partielle le montage d'une aube sur le disque de la figure 1 et les deux segments fendus assurant l'étanchéité et le verrouillage des aubes.
Among these boards:
  • - Figure 1 shows in longitudinal half-section a compressor disc and a blade mounted on the disc and locked by means of the locking and sealing device according to the invention;
  • - Figure 2 shows in partial downstream view the mounting of a blade on the disk of Figure 1 and the two split segments ensuring the sealing and locking of the blades.

Sur la figure 1 ont été représentés à titre exemplatif en coupe longitudinale les deux premiers étages d'un rotor de compresseur haute pression de turboréacteur. Le premier étage du rotor comporte un disque 1 relié par une bride amont 2 à un compresseur moyenne ou basse pression et par une bride aval 3 du deuxième étage du rotor, globalement référencé 4, du compresseur HP.In Figure 1 are shown by way of example in longitudinal section the first two stages of a high pressure compressor rotor of a turbojet engine. The first stage of the rotor comprises a disc 1 connected by an upstream flange 2 to a medium or low pressure compressor and by a downstream flange 3 from the second stage of the rotor, generally referenced 4, of the HP compressor.

Des aubes 5 comportant sous leur plate-forme 6 un pied 7 sont glissées axialement dans des alvéoles 8 du disque de façon classique. La figure 1 montre que l'axe longitudinal des alvéoles est ici faiblement incliné par rapport à une parallèle à l'axe longitudinal 9 du moteur dans un plan radial et cet axe pourrait également être faiblement incliné par rapport à l'axe 9 dans un plan tangentiel à la périphérie du disque 1. Ces faibles variations angulaires n'ont aucun effet sur l'invention proprement dite et quelles que soient ces faibles variations, on les englobera dans la suite du texte dans le terme général "montage axial" des aubes sur le disque.Blades 5 having under their platform 6 a foot 7 are slid axially in cells 8 of the disc in a conventional manner. Figure 1 shows that the longitudinal axis of the cells is here slightly inclined relative to a parallel to the longitudinal axis 9 of the engine in a radial plane and this axis could also be slightly inclined relative to the axis 9 in a plane tangential to the periphery of the disc 1. These slight angular variations have no effect on the invention proper and whatever these slight variations, they will be included in the rest of the text in the general term "axial mounting" of the blades on the disc.

Les pieds d'aube 7 possèdent en amont un moyen de calage axial formé d'un becquet amont 10 radialement orienté vers l'axe de symétrie 9, ledit becquet venant en appui contre la face amont 11 du disque 1.The blade roots 7 have upstream an axial wedging means formed by an upstream spoiler 10 radially oriented towards the axis of symmetry 9, said spoiler coming to bear against the upstream face 11 of the disc 1.

L'aube possède également en aval un becquet 12 définissant entre lui et le pied d'aube une gorge circulaire 13 dont l'ouver ture est radialement orientée vers l'axe de symétrie du disque.The blade also has downstream a spoiler 12 defining between it and the blade root a circular groove 13 whose opening is radially oriented towards the axis of symmetry of the disc.

Face à cette gorge 13 de l'aube mise en place, le disque 1 possède une gorge 14 circulaire lui faisant face, c'est à dire ayant son ouverture orientée radialement vers la périphérie du disque et usinée à un diamètre plus faible que le diamètre d'usinage du fond des alvéoles 8.Facing this groove 13 of the blade set up, the disc 1 has a circular groove 14 facing it, that is to say having its opening oriented radially towards the periphery of the disc and machined to a diameter smaller than the diameter machining the bottom of the cells 8.

Le dispositif de verrouillage des aubes et d'étanchéité selon l'invention comporte un premier segment fendu 15 dont la largeur radiale "1" est égale à la distance séparant les fonds des gorges 12 des becquets d'aubes et 14 du disque.The blade locking and sealing device according to the invention comprises a first split segment 15 whose radial width "1" is equal to the distance separating the bottoms of the grooves 12 from the blade spoilers and 14 from the disc.

Le premier segment 15 peur subir une faible déformation radiale ainsi qu'une déformation axiale de telle sorte que les becs de la fente ne soient plus dans le plan contenant le segment et lorsque le segment est dans cette position déformée, il peut être mis en place dans la gorge 14 par introduction d'une de ses extrémités dans la gorge puis "vissage" circulaire.The first segment 15 can undergo a slight radial deformation as well as an axial deformation so that the slats of the slot are no longer in the plane containing the segment and when the segment is in this deformed position, it can be put in place in the groove 14 by introducing one of its ends into the groove and then "screwing" circular.

Une fois mis en place, le segment 15 masque totalement les ouvertures aval des alvéoles 8. Pour permettre l'introduction successives des aubes 5 dans leur alvéole 8, le segment 15 possède une échancrure rectangulaire 16 permettant le passage du becquet aval 12 d'une aube jusqu'à la mise en butée du becquet amont 10 sur la face amont du disque. Par rotation d'un pas on engage le segment 15 dans la gorge 13 de l'aube déjà montée et on amène l'échancrure 16 devant l'alvéole 8 de l'aube suivante à mettre en place. On effectue la même opération de montage successivement pour chacune des aubes suivantes jusqu'à installation complète de toutes les aubes.Once in place, the segment 15 completely masks the downstream openings of the cells 8. To allow the successive introduction of the blades 5 into their cell 8, the segment 15 has a rectangular notch 16 allowing the passage of the downstream spoiler 12 of a blade until the upstream spoiler 10 comes into abutment on the upstream face of the disc. By rotation of a step, the segment 15 is engaged in the groove 13 of the already mounted blade and the notch 16 is brought in front of the cell 8 of the next blade to be put in place. The same mounting operation is carried out successively for each of the following blades until all the blades are completely installed.

Selon l'invention le dispositif de verrouillage comporte également un second segment fendu 17 dimensionné de telle sorte, en premier lieu que son diamètre externe soit égal à celui du fond de la gorge 13 des aubes, en second lieu que la somme de son épaissuer et de celle du premier segment lui permet d'être inséré dans la gorge 13 en aval du premier segment 15 et en troisième lieu que sa hauteur radiale soit au moins égale à celle "1'" de l'échancrure 16 du premier segment afin de masquer complètement cette ouverture, une fois le second segment 17 en place.According to the invention, the locking device also comprises a second split segment 17 dimensioned in such a way, firstly that its external diameter is equal to that of the bottom of the groove 13 of the blades, secondly that the sum of its thickness and of that of the first segment allows it to be inserted into the groove 13 downstream of the first segment 15 and thirdly that its radial height is at least equal to that "1 '" of the notch 16 of the first segment in order to hide completely this opening, once the second segment 17 in place.

La mise en place du second segment s'effectue par compression radiale, ce qui permet de le glisser radialement sous les becquets aval 12 des aubes puis en le laissant se détendre à son diamètre nominal, de l'engager au fond de la gorge 13. L'effet de centrifugation du segment 17 lors du fonctionnement de la turbomachine permet d'assurer le maintien correct en place dudit segment.The positioning of the second segment is carried out by radial compression, which makes it possible to slide it radially under the downstream spoilers 12 of the blades then by letting it relax to its nominal diameter, to engage it at the bottom of the groove 13. The centrifugation effect of segment 17 during operation of the turbomachine ensures that the segment is held correctly in place.

Le démontage du dispositif de verrouillage s'effectue en réalisant toutes les opérations dans l'ordre inverse de ce qui vient d'être décrit.The disassembly of the locking device is carried out by carrying out all the operations in the reverse order to what has just been described.

On voit sur les figures 1 et 2 que le premier segment 15 masque totalement les lunules de fuite, qui sans sa présence existeraient entre les pieds d'aube 7 et les fonds d'alvéoles 8. On voit également sur la figure 2 que le disque représenté possède sur les dents 18 séparant les alvéoles en aval également un becquet 19 délimitant une gorge qui assure une continuité entre les gorges 13 des becquets d'aube. Toutefois ces becquets 19 des dents, indispensables avec les systèmes de verrouillage actuels ne le sont plus avec le dispositif selon l'invention et peuvent être supprimés, ce qui simplifie grandement l'usinage des disques et en réduit le coût de fabrication.It can be seen in FIGS. 1 and 2 that the first segment 15 completely masks the trailing lunules, which without its presence would exist between the feet of the blade 7 and the bottom of the cells 8. We also see in FIG. 2 that the disc shown has on the teeth 18 separating the cells downstream also a spoiler 19 defining a groove which provides continuity between the grooves 13 of the blade spoilers. However, these teeth 19 spoilers, essential with current locking systems, are no longer necessary with the device according to the invention and can be eliminated, which greatly simplifies the machining of the discs and reduces the manufacturing cost.

On voit d'autre part que l'étanchéité est parfaitement assurée et si on empêche le déplacement circulaire du premier segment 15 (par un pion de verrouillage par exemple) de telle sorte que l'échancrure 16 soit disposée dans le prolongement axial d'une des dents 18, l'échancrure étant elle-même masquée complètement par le second segment 17, on voit que les possibilités de fuites sont totalement supprimées.We see on the other hand that the seal is perfectly ensured and if circular movement of the first segment 15 is prevented (by a locking pin for example) so that the notch 16 is disposed in the axial extension of a teeth 18, the notch being itself completely masked by the second segment 17, it can be seen that the possibilities of leaks are completely eliminated.

L'invention apporte une solution simple au problème du verrouillage d'aubes brochées de rotor, qui la rend applicable notamment aux rotors de moteur de faible dimension.The invention provides a simple solution to the problem of interlocking padded rotor blades, which makes it applicable in particular to small motor rotors.

Claims (3)

1. Gas turbine rotor, notably for aircraft gas turbines comprising at least one disc carrying a blade assembly of which the blade roots are fitted into recesses formed around the priphery of the disc with their axes parallel or slightly inclined to the longitudinal axis of the engine, the roots (7) of the blades comprising a means of wedging (10) the blades against the upstream face of the disc (1) and a downstream nib (12) having a transverse throat (13) radially facing the axis of the disc whilst the disc has a circular throat (14) radially facing outwards towards the periphery of the disc characterised in that it comprises a means of axially locking the blades to the disc and of ensuring simultaneously the gas- tightness of the joint between the blade roots (7) and the bottoms of the recesses (8) in the disc, the said means of locking the blades on the downstream side being constituted by two split segments (15, 17) of which the first (15) works in conjunction simultaneously with the throats (13) of the nibs of the blades and the circular throat (14) on the disc, and in that the said first split segment (15) fitted into the throat on the disc comprises a rectangular cut out (16) on its radially outer edge to allow the successive longitudinal insertion of the blades (5) on the said segment and in that the second split segment (17) is sufficiently radially elastic to enable it, by radial compression and extension, into the circular throat (13) formed by the nibs (12) of the blade roots, and in that it is of radial width at least equal to that "1" of the cut out (16) in the first segment (15).
2. Gas turbine rotor in accordance with Claim 1 of which the circular throat (14) on the disc has a lesser diameter than that machined at the bottom of the blade recesses (8), characterised in that the radial width "1" of the first split segment (15) is equal to the distance separating the bottoms of the throats (14, 13) of the disc and the blade root nibs, and in that the sum of the thicknesses of the first and second segments (15, 17) is equal to the width of the throats (13) of the blade root nibs.
3. Procedure for fitting the blades to the rotor disc of the gas turbine accordance with Claims 1 or 2, characterised in that:
a) the first split segment (15) is inserted in the throat (14) on the downstream face of the disc (1) by the axial distortion of the two ends of the segment, at the point where this is split and by rotating the said first segment (15) in the throat (14).
b) the cut out (16) in the first segment (15) is brought in front of a recess (8) in the disc (1).
c) the blade (5, 7) is slid into the recess (8) until its stop butts up against the disc (1).
d) the first segment (15) is rotated by one step and the next blade (5) is fitted, the operations (c) and (d) being repeated until all the blades are fitted.
e) the second segment (17) is radially compressed and it is allowed to expand into place in the throat (13) formed by the nibs (12) between the first segment (15) and the downstream part of the blade root nibs (12).
EP87401958A 1986-09-03 1987-09-02 Sealing and locking device for the vanes of a turbo machine Expired - Lifetime EP0263002B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8612357A FR2603333B1 (en) 1986-09-03 1986-09-03 TURBOMACHINE ROTOR COMPRISING A MEANS OF AXIAL LOCKING AND SEALING OF BLADES MOUNTED IN AXIAL PINS OF THE DISC AND MOUNTING METHOD
FR8612357 1986-09-03

Publications (2)

Publication Number Publication Date
EP0263002A1 EP0263002A1 (en) 1988-04-06
EP0263002B1 true EP0263002B1 (en) 1990-04-04

Family

ID=9338657

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401958A Expired - Lifetime EP0263002B1 (en) 1986-09-03 1987-09-02 Sealing and locking device for the vanes of a turbo machine

Country Status (4)

Country Link
US (1) US4730983A (en)
EP (1) EP0263002B1 (en)
DE (1) DE3762142D1 (en)
FR (1) FR2603333B1 (en)

Families Citing this family (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS61501321A (en) * 1984-01-23 1986-07-03 インスティテュト・フォ−・エネジテクニク Technetium-99m composition for labeling protein-like substances and method of using the same
FR2639063A1 (en) * 1988-11-17 1990-05-18 Snecma STOP AND SEGMENT SEGMENT OF A SET OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
US5256035A (en) * 1992-06-01 1993-10-26 United Technologies Corporation Rotor blade retention and sealing construction
FR2694046B1 (en) * 1992-07-22 1994-09-23 Snecma Sealing and retention device for a rotor notched with pinouts receiving blade roots.
US5302086A (en) * 1992-08-18 1994-04-12 General Electric Company Apparatus for retaining rotor blades
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
FR2729709A1 (en) * 1995-01-25 1996-07-26 Snecma Turbine rotor seal and retainer
US5501575A (en) * 1995-03-01 1996-03-26 United Technologies Corporation Fan blade attachment for gas turbine engine
GB9517369D0 (en) * 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor
GB2311826B (en) * 1996-04-02 2000-05-10 Europ Gas Turbines Ltd Turbomachines
US6234756B1 (en) 1998-10-26 2001-05-22 Allison Advanced Development Company Segmented ring blade retainer
US6109877A (en) * 1998-11-23 2000-08-29 Pratt & Whitney Canada Corp. Turbine blade-to-disk retention device
CA2372875A1 (en) 1999-05-14 2000-11-23 Siemens Aktiengesellschaft Turbomachine with a sealing system for a rotor
WO2000070191A1 (en) * 1999-05-14 2000-11-23 Siemens Aktiengesellschaft Sealing system for a rotor of a turbo engine
DE19960896A1 (en) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Retaining device for rotor blades of axial turbine engine, with recesses in outer circumference of retainer corresponding to sections of blade receivers
EP1371814A1 (en) * 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
GB0302116D0 (en) * 2003-01-30 2003-03-05 Rolls Royce Plc A rotor
DE10348198A1 (en) * 2003-10-16 2005-05-12 Rolls Royce Deutschland Scoop restraint
FR2890104A1 (en) * 2005-08-31 2007-03-02 Snecma Rotation blocking device for use in turbomachine rotor of aircraft engine, has ring with split and set of cleat, which is arranged on ring and placed in groove of rotor disk that includes blocking hook with check face
FR2890105A1 (en) * 2005-08-31 2007-03-02 Snecma Retention ring immobilization device for e.g. engine of aircraft, has stops positioned such that stops are stopped respectively against immobilization hooks, and slot covered by other hook when retention ring is placed in groove
US7484936B2 (en) * 2005-09-26 2009-02-03 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US20080273982A1 (en) * 2007-03-12 2008-11-06 Honeywell International, Inc. Blade attachment retention device
EP2128450B1 (en) * 2007-03-27 2018-05-16 IHI Corporation Fan rotor blade support structure and turbofan engine having the same
FR2918106B1 (en) * 2007-06-27 2011-05-06 Snecma AXIS RETAINING DEVICE OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISC.
MX2010001538A (en) * 2007-08-08 2010-03-15 Alstom Technology Ltd Rotor arrangement of a turbine.
FR2930603B1 (en) 2008-04-24 2010-04-30 Snecma AXIAL RETAINING DEVICE FOR MOBILE AUBES ON A ROTOR DISC
FR2939832B1 (en) * 2008-12-11 2011-01-07 Turbomeca TURBINE WHEEL EQUIPPED WITH AXIAL HOLDING DEVICE LOCKING BLADES WITH RESPECT TO A DISK.
US8459954B2 (en) * 2010-01-19 2013-06-11 United Technologies Corporation Torsional flexing energy absorbing blade lock
FR2958322B1 (en) * 2010-04-01 2013-03-15 Snecma GAS TURBINE ENGINE ROTOR COMPRISING A ROTOR DRUM AND ROTOR CROWN
US8562301B2 (en) 2010-04-20 2013-10-22 Hamilton Sundstrand Corporation Turbine blade retention device
US8651820B2 (en) * 2010-07-14 2014-02-18 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US8491267B2 (en) 2010-08-27 2013-07-23 Pratt & Whitney Canada Corp. Retaining ring arrangement for a rotary assembly
RU2548226C2 (en) 2010-12-09 2015-04-20 Альстом Текнолоджи Лтд Fluid medium flow unit, in particular, turbine with axially passing heated gas flow
DE102011077501A1 (en) * 2011-06-14 2012-12-20 Rolls-Royce Deutschland Ltd & Co Kg Rotor device for a jet engine with a disc wheel and a plurality of blades
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US9790803B2 (en) 2013-03-08 2017-10-17 United Technologies Corporation Double split blade lock ring
US9618002B1 (en) * 2013-09-27 2017-04-11 University Of South Florida Mini notched turbine generator
FR3026429B1 (en) * 2014-09-30 2016-12-09 Snecma MOBILE TURBINE DRAWING, COMPRISING AN ERGOT ENGAGING A ROTOR DISK BLOCKING DETAIL
US9777593B2 (en) 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
FR3086328B1 (en) 2018-09-20 2021-01-01 Safran Aircraft Engines IMPELLER WITH AXIALLY RETAINED BLADES, FOR TURBOMACHINE
US10704400B2 (en) * 2018-10-17 2020-07-07 Pratt & Whitney Canada Corp. Rotor assembly with rotor disc lip
US20200131916A1 (en) * 2018-10-31 2020-04-30 United Technologies Corporation Turbine blade assembly
IT201900014724A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Elements for retaining blades for turbomachinery.
IT201900014739A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Elements for retaining blades for turbomachinery.
IT201900014736A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Integral sealing elements for blades held in a rotatable annular outer drum rotor in a turbomachinery.
US11168615B1 (en) * 2020-08-25 2021-11-09 Raytheon Technologies Corporation Double ring axial sealing design

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB712112A (en) * 1951-07-13 1954-07-21 Bristol Aeroplane Co Ltd Improvements in or relating to blade-locking means for turbine and the like rotor assemblies
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
GB928349A (en) * 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
GB988541A (en) * 1962-03-06 1965-04-07 Ruston & Hornsby Ltd Gas turbine rotor cooling
GB954323A (en) * 1962-03-17 1964-04-02 Rolls Royce Improvements in or relating to bladed rotors for fluid flow machines such as turbines
GB987839A (en) * 1963-12-04 1965-03-31 Rolls Royce A bladed rotor for an axial fluid flow machine
US3300179A (en) * 1966-04-22 1967-01-24 Gen Motors Corp Blade stalk cover plate
GB1095830A (en) * 1966-09-13 1967-12-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
GB1291302A (en) * 1970-03-14 1972-10-04 Sec Dep For Defendence Improvements in bladed rotor assemblies
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
GB1295003A (en) * 1971-06-15 1972-11-01
SU533738A1 (en) * 1974-04-29 1976-10-30 Предприятие П/Я Г-4561 Device for fixing the blades in the turbomachine disk
GB1479332A (en) * 1974-11-06 1977-07-13 Rolls Royce Means for retaining blades to a disc or like structure
GB1512882A (en) * 1976-02-11 1978-06-01 Rolls Royce Bladed rotor assembly for a gas turbine engine
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
GB2010404B (en) * 1977-12-17 1982-02-10 Rolls Royce Gas turbine engines
US4389161A (en) * 1980-12-19 1983-06-21 United Technologies Corporation Locking of rotor blades on a rotor disk
FR2524933B1 (en) * 1982-04-13 1987-02-20 Snecma AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
EP0236337B1 (en) * 1985-09-12 1989-03-01 Solar Turbines Incorporated Seal ring means for a bladed rotor assembly

Also Published As

Publication number Publication date
EP0263002A1 (en) 1988-04-06
FR2603333B1 (en) 1990-07-20
DE3762142D1 (en) 1990-05-10
FR2603333A1 (en) 1988-03-04
US4730983A (en) 1988-03-15

Similar Documents

Publication Publication Date Title
EP0263002B1 (en) Sealing and locking device for the vanes of a turbo machine
EP0396726B1 (en) Segment for locking and sealing a set of vanes mounted on a turbo-engine rotary disk
EP2366061B1 (en) Turbine wheel with an axial retention system for vanes
EP1972757A1 (en) Rotor assembly of a turbomachine fan
EP2603670B1 (en) Device for locking a root of a rotor blade
CA2520069C (en) Turbine module for gas turbine engine with rotor that includes a monobloc body
CA2598532A1 (en) Turbomachine rotor blade
CA2831522C (en) Sealing ring for a turbine stage of an aircraft turbomachine, comprising slotted anti-rotation pegs
EP3201438B1 (en) Rotor blade of a turbomachine comprising a flange which abuts a blocking notch of a rotor disc
FR3001759A1 (en) ROUGE AUBAGEE OF TURBOMACHINE
EP3797212A1 (en) Turbomachine blading angular sector with seal between sectors
FR3068070B1 (en) TURBINE FOR TURBOMACHINE
FR3099520A1 (en) Turbomachine wheel
FR2972482A1 (en) Sealing sleeve for rotor of e.g. single-stage high pressure turbine of ducted-fan twin-spool turbojet of aircraft, has main body comprising strip cooperating with groove of pin of downstream flange to axially retain flange towards upstream
WO2019224464A1 (en) Improved turbmachine fan disc
FR3100836A1 (en) MOBILE BLADES FOR TURBINE
FR3107082A1 (en) Turbomachine wheel
FR3109795A1 (en) STRAIGHTENING INTERMEDIATE HOUSING WITH MONOBLOC STRUCTURAL ARM
FR3049645B1 (en) ROTARY ASSEMBLY FOR TURBOMACHINE WITH ROUND JUNCTION IN U
FR3098844A1 (en) Turbomachine wheel
WO2024194575A1 (en) Bladed wheel for an aircraft turbomachine, and aircraft turbomachine
FR3111677A1 (en) TURBOMACHINE COMPRESSOR, PROCESS FOR ASSEMBLING THE COMPRESSOR
EP4208626A1 (en) Turbine for a turbine engine comprising heat-shielding foils
WO2024156955A1 (en) Turbomachine rotor, turbomachine turbine and turbomachine for an aircraft
FR3137411A1 (en) ROTOR EQUIPPED WITH BLADE WITH AXIAL STOP AND AIRCRAFT TURBOMACHINE

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19870912

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT

17Q First examination report despatched

Effective date: 19890124

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MO

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

ITF It: translation for a ep patent filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3762142

Country of ref document: DE

Date of ref document: 19900510

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20050824

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20050825

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20050926

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20060930

Year of fee payment: 20

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070403

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20060902

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20070531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060902

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20061002