EP1217168B1 - Axial fixation of gas turbine rotor blades - Google Patents

Axial fixation of gas turbine rotor blades Download PDF

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Publication number
EP1217168B1
EP1217168B1 EP20000870311 EP00870311A EP1217168B1 EP 1217168 B1 EP1217168 B1 EP 1217168B1 EP 20000870311 EP20000870311 EP 20000870311 EP 00870311 A EP00870311 A EP 00870311A EP 1217168 B1 EP1217168 B1 EP 1217168B1
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EP
European Patent Office
Prior art keywords
rotor
ring
boss
blades
section
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
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EP20000870311
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German (de)
French (fr)
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EP1217168A1 (en
Inventor
Yves Culot
Bruno Michel
Jean Hockers
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Safran Aero Boosters SA
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Techspace Aero SA
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Priority to EP20000870311 priority Critical patent/EP1217168B1/en
Priority to DE60029114T priority patent/DE60029114D1/en
Publication of EP1217168A1 publication Critical patent/EP1217168A1/en
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Publication of EP1217168B1 publication Critical patent/EP1217168B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—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

Definitions

  • the present invention relates to a rotor stage of a compressor or a turbine which comprises a succession of rotor blades rotating stages separated each time by rectifying stages, distributors (or stator). Said rotating blades are mounted on a rotor which is generally in the form of a disk.
  • the present invention relates more specifically to the means of retention or joining of said blades on the rotor in a rotor stage.
  • Coaxial compressors and turbines are well known per se, and are used in several types of applications. In particular, they are used in dual-body engines, turbofans or turbojet engines. We also note their presence in power plants. These low or high pressure compressors or turbines consist essentially of several stages of rotating blades or rotor stages separated by stator stages, distributors or rectifiers which are intended to reposition (distribute or straighten) the vector. velocity of the fluid leaving the previous stage before sending it to the next compartment.
  • Each of the stator stages consists of fixed vanes which are either fixed on inner concentric rings (ferrules) or assembled by segments on housings.
  • the rotor stages consist of rotating vanes mounted on a rotor usually in the form of a disk.
  • the rotating blades have at their base a part more commonly called “bulb dawn” which takes the form of a succession of excrescences and recesses and which can adapt to a complementary female cavity located in the rotor disk.
  • the succession of excrescences and recesses of the interlocking will prevent the blade from being detached radially during the setting in motion by the action of the centrifugal force.
  • the problem to be solved remains the upstream and downstream retention of said rotating blades on the rotor.
  • Several ways of securing said rotating blades can be envisaged.
  • a first possibility is the use of retaining rings and flanges.
  • a ring which is in the form of a flat ring, serves as a circlip and allows the downstream retention of said blades when they are arranged on the rotor, while the retaining flange allows the upstream retention and further anti -rotation of the flat ring. Said flange is then fixed and centered between two successive rotor discs.
  • the document FR-A-2 729 709 describes a device for sealing and retaining blades for turbomachines in which the vanes and the rotor disk have upstream side spoilers which juxtapose.
  • An elastic circular ring is housed in the groove formed by the spoilers. It comprises one or more anti-rotation cleats adapted to fit between a machined disc spoiler and a hollow blade spoiler.
  • This solution has the disadvantage of presenting an axial clearance of the blade on the disk and thus generating vibrations of the assembly.
  • the need to embed the cleats requires special machining of the rotor disk, so expensive.
  • the present invention aims to provide a solution that makes it possible to secure the rotating or mobile blades to a disk serving as a rotor.
  • the present invention aims to allow retention both upstream and downstream while using only one piece for all the blades.
  • the present invention also aims to significantly reduce the time of installation or assembly and to facilitate the maintenance of the rotor stage.
  • the slot of the ring is cut at an angle.
  • the extra material is in the form of a boss is designed in such a way that it mechanically compensates exactly the lack of material due to the presence of the slot.
  • the retention means is made of a metallic material.
  • said moving blades each have a blade and a bulb of dawn, each dawn bulb having on the one hand, on a first face, an outgrowth under beater tooth form acting as a stopper by positioning and direct contact with said rotor body and secondly on the opposite side, a protrusion in the form of a hook for the placement of the retention means against a flat flank of the rotor body.
  • FIG. 1 represents a general view of a low-pressure turbine of a turbofan in which a succession of distributor stages and rotor stages are present.
  • Figure 2 shows a sectional view of a blade provided with means for securing to the rotor.
  • Figure 3 shows a perspective view of the bulb of a blade for use according to the mounting method of the present invention.
  • FIG. 4 represents a perspective view of the securing means used according to the present invention of the rotor rotating blades.
  • Figure 5 shows a perspective view of the fastening ring according to the present invention.
  • Figures 6a to 6c show the mounting principle of the ring according to the present invention.
  • Each distributor stage 2,2 ', 2 ", ... is essentially constituted by blades 2,2', 2", ... contained between two inner platforms 4,4 ', 4 ", ... and outside 5 , 5 ', 5 ", ...
  • Each rotor stage is constituted by the rotating blades 3,3 ', 3 ", ... all connected to the rotor 1 by means of retention.
  • the gas first strikes the first distributor 2 of the first low pressure stator stage where its velocity vector is repositioned before striking the first rotor 3 to be repositioned by the second stator stage 2 'before striking again the second rotor stage 3', etc.
  • the gas thus undergoes a thrust cycle - redistribution of the speeds at the end of which its kinetic energy gradually decreases as well as its pressure, while the rotor work grows by adding from floor to floor.
  • a rotating blade 3 is conventionally in the form of a flat 30 connected to a bulb of blade 31.
  • the various bulbs 31,31 ', 31 "will be machined so that they can be arranged successively around a disk 10 which serves as a rotor, as shown in FIG.
  • the placement of the rotating blades 3 on the rotor 10 is by sliding between the teeth of the disc.
  • the blade bulbs 31, 31 ', 31 "have a male shape consisting of a succession of excrescences and recesses to which essentially corresponds a complementary female cavity made in the disc 10 serving as a rotor, these cavities creating "teeth" on the disc.
  • the blade bulbs 31,31 ', 31 are each provided, on the one hand, on a first face with a protrusion in the form of a beaver tooth. 33 which will serve as a stop virtually positioning itself directly in contact with the rotor disc 10, and secondly, on the opposite side, an excrescence in the form of hook 32 which will allow the placement of a ring 40.
  • this ring 40 will advantageously allow the joining of all the blade bulbs 31, 31 ', 31 "on the same rotor disk 10. Such a ring is shown in detail in FIG.
  • this ring 40 has a slot 41, preferably cut at an angle, so that it can perform the establishment of the ring by prescribing it and releasing it then.
  • this ring 40 has on at least one radial flank 42 an additional material in the form of a boss 45.
  • this boss 45 is present on a portion which substantially corresponds to the planned distance between two successive blades as well as represented in FIG. 4. At this distance is also said slot 41.
  • the boss also has the advantage of preventing rotation of the ring 40 with respect to the disc 10.
  • said boss 45 is drawn and calculated to exactly match the lack of material due to the presence of the slot 41.
  • the purpose of the boss 45 is therefore to provide an unbalance which must compensate exactly for the lack of material due to the slot 41. .
  • the ring 40 as shown in Figure 2, has a conical section that allows, during operation of the rotor stage, to reduce or even eliminate the axial play of the blade on the disk and therefore to reduce the vibrations that could be generated by the centrifugal force.
  • FIGS. 6a-6c show the placement of the ring 40 on the rotor disk 10.
  • the ring 40 is configured in such a way that in the free state (FIG. opening A. To allow it to be put in place, there will be a tendency to pinch during assembly so as to preload the ring (Fig. 6b). After its installation (Fig. 6c), the ring will relax so that it will fit perfectly between two rotating blades as shown in Figure 5.
  • This ring is preferably made of a metallic material that allows its use at high temperatures.

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

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte à un étage rotorique d'un compresseur ou d'une turbine qui comprend une succession d'étages rotoriques d'aubes tournantes séparés chaque fois par des étages redresseurs, distributeurs (ou statoriques). Lesdites aubes tournantes sont montées sur un rotor qui se présente en règle générale sous la forme d'un disque.The present invention relates to a rotor stage of a compressor or a turbine which comprises a succession of rotor blades rotating stages separated each time by rectifying stages, distributors (or stator). Said rotating blades are mounted on a rotor which is generally in the form of a disk.

La présente invention se rapporte plus précisément au moyen de rétention ou solidarisation desdites aubes mobiles sur le rotor dans un étage rotorique.The present invention relates more specifically to the means of retention or joining of said blades on the rotor in a rotor stage.

Etat de la techniqueState of the art

Les compresseurs et turbines coaxiaux sont bien connus en soi, et sont utilisés dans plusieurs types d'application. En particulier, ils sont utilisés dans les moteurs double corps, turbofans ou turboréacteurs. On note aussi leur présence dans les centrales électriques. Ces compresseurs ou turbines basse ou haute pression sont essentiellement constitués de plusieurs étages d'aubes tournantes ou étages rotoriques séparés par des étages statoriques, distributeurs ou redresseurs qui ont pour but de repositionner (distribuer ou redresser) le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers le compartiment suivant.Coaxial compressors and turbines are well known per se, and are used in several types of applications. In particular, they are used in dual-body engines, turbofans or turbojet engines. We also note their presence in power plants. These low or high pressure compressors or turbines consist essentially of several stages of rotating blades or rotor stages separated by stator stages, distributors or rectifiers which are intended to reposition (distribute or straighten) the vector. velocity of the fluid leaving the previous stage before sending it to the next compartment.

Chacun des étages statoriques est constitué d'aubes fixes qui sont soit fixées sur des anneaux concentriques intérieurs (viroles) soit assemblées par segments sur des carters.Each of the stator stages consists of fixed vanes which are either fixed on inner concentric rings (ferrules) or assembled by segments on housings.

Les étages rotoriques sont constitués d'aubes tournantes montées sur un rotor se présentant habituellement sous la forme d'un disque. Les aubes tournantes présentent à leur base une partie appelée plus communément "bulbe d'aube" qui prend la forme d'une succession d'excroissances et de creux et qui pourra s'adapter à une cavité femelle complémentaire située dans le disque du rotor. La succession d'excroissances et de creux de l'emboîtement empêchera l'aube de se désolidariser radialement lors de la mise en mouvement par action de la force centrifuge.The rotor stages consist of rotating vanes mounted on a rotor usually in the form of a disk. The rotating blades have at their base a part more commonly called "bulb dawn" which takes the form of a succession of excrescences and recesses and which can adapt to a complementary female cavity located in the rotor disk. The succession of excrescences and recesses of the interlocking will prevent the blade from being detached radially during the setting in motion by the action of the centrifugal force.

Le problème à résoudre reste alors la rétention amont et aval desdites aubes tournantes sur le rotor. Plusieurs manières de solidariser lesdites aubes tournantes peuvent être envisagées.The problem to be solved remains the upstream and downstream retention of said rotating blades on the rotor. Several ways of securing said rotating blades can be envisaged.

Une première possibilité est l'utilisation d'anneaux et flasques de retenue. Un anneau, qui se présente sous la forme d'un anneau plat, sert de circlip et permet la rétention aval desdites aubes lorsqu'elles sont disposées sur le rotor, tandis que le flasque de retenue permet la rétention amont et en outre l'anti-rotation de l'anneau plat. Ledit flasque est ensuite fixé et centré entre deux disques successifs du rotor.A first possibility is the use of retaining rings and flanges. A ring, which is in the form of a flat ring, serves as a circlip and allows the downstream retention of said blades when they are arranged on the rotor, while the retaining flange allows the upstream retention and further anti -rotation of the flat ring. Said flange is then fixed and centered between two successive rotor discs.

Un autre procédé de fixation des aubes mobiles ou tournantes sur ledit rotor s'effectue à l'aide de rivets qui permettent de garantir tant la rétention amont que la rétention aval. Le logement du rivet est dans ce cas usiné pour les deux tiers de sa circonférence sur l'aube, le dernier tiers restant sur le disque. Le rivetage se fait ensuite par expansion de la partie tubulaire du rivet après avoir mis en place toutes les aubes dans l'étage rotorique correspondant.
Le document FR-A-2 729 709 décrit un dispositif d'étanchéité et de rétention d'aubes pour des turbomachines dans lequel les aubes et le disque rotorique présentent côté amont des becquets qui se juxtaposent. Un anneau circulaire élastique est logé dans la gorge formée par les becquets. Celui-ci comporte un ou plusieurs taquets antirotation apte(s) à s'encastrer entre un becquet de disque usiné et un becquet d'aube évidé. Cette solution présente le désavantage de présenter un jeu axial de l'aube sur le disque et de générer par conséquent des vibrations de l'ensemble. En outre, la nécessité d'encastrer les taquets demande un usinage particulier du disque rotorique, donc coûteux.Another method of fixing the blades or rotating blades on said rotor is made using rivets which ensure both upstream retention and downstream retention. The housing of the rivet is in this case machined for two thirds of its circumference on dawn, the last remaining third on the disk. The riveting is then by expansion of the tubular part of the rivet after setting up all the blades in the corresponding rotor stage.
The document FR-A-2 729 709 describes a device for sealing and retaining blades for turbomachines in which the vanes and the rotor disk have upstream side spoilers which juxtapose. An elastic circular ring is housed in the groove formed by the spoilers. It comprises one or more anti-rotation cleats adapted to fit between a machined disc spoiler and a hollow blade spoiler. This solution has the disadvantage of presenting an axial clearance of the blade on the disk and thus generating vibrations of the assembly. In addition, the need to embed the cleats requires special machining of the rotor disk, so expensive.

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une solution qui permette de solidariser les aubes tournantes ou mobiles à un disque servant de rotor.The present invention aims to provide a solution that makes it possible to secure the rotating or mobile blades to a disk serving as a rotor.

En outre, la présente invention vise à permettre une rétention tant amont qu'aval tout en n'utilisant qu'une seule pièce pour toutes les aubes.In addition, the present invention aims to allow retention both upstream and downstream while using only one piece for all the blades.

La présente invention vise également à réduire de façon significative le temps de pose ou de montage et à faciliter la maintenance de l'étage rotorique.The present invention also aims to significantly reduce the time of installation or assembly and to facilitate the maintenance of the rotor stage.

Principaux éléments caractéristiques de l'inventionMain characteristic elements of the invention

La présente invention se rapporte à un étage rotorique d'une turbine ou d'un compresseur axial comprenant une pluralité d'aubes mobiles reliées à un corps rotorique par un moyen de rétention se présentant sous la forme d'une seule pièce correspondant à un anneau ouvert par une fente sur une section dudit anneau, ladite section présentant, sur le flanc radial défini comme le flanc tourné vers l'extérieur par rapport au corps rotorique, un surcroît de matière sous la forme d'un bossage anti-rotation s'étendant de part et d'autre de ladite fente, ledit moyen de rétention étant caractérisé en ce que :

  • la longueur du bossage le long de l'anneau correspond à la distance intercalaire prévue entre deux aubes mobiles successives ;
  • il est pourvu de moyens additionnels de réduction de jeu axial par auto-coincement dans une gorge, lesdits moyens additionnels comprenant la réalisation de l'anneau selon une section conique, à l'exception de la section présentant le bossage.
The present invention relates to a rotor stage of a turbine or axial compressor comprising a plurality of blades connected to a rotor body by a retention means in the form of a single piece corresponding to a ring open by a slot on a section of said ring, said section having, on the radial side defined as the side facing outwards with respect to the rotor body, an additional material in the form of an anti-rotation boss extending on either side of said slot, said retention means being characterized in that:
  • the length of the boss along the ring corresponds to the intermediate distance provided between two successive blades;
  • it is provided with additional means of reducing axial play by self-jamming in a groove, said additional means comprising the realization of the ring in a conical section, with the exception of the section having the boss.

De préférence, la fente de l'anneau est découpée en biais.Preferably, the slot of the ring is cut at an angle.

Avantageusement, le surcroît de matière se présentant sous la forme d'un bossage est conçu de manière telle qu'il compense mécaniquement exactement le manque de matière dû à la présence de la fente.Advantageously, the extra material is in the form of a boss is designed in such a way that it mechanically compensates exactly the lack of material due to the presence of the slot.

De préférence, le moyen de rétention est réalisé dans un matériau métallique.Preferably, the retention means is made of a metallic material.

Selon une forme d'exécution préférée de l'invention, lesdites aubes mobiles présentent chacune un plat et un bulbe d'aube, chaque bulbe d'aube présentant d'une part, sur une première face, une excroissance sous forme de dent de castor faisant fonction de butée franche par positionnement et contact direct avec ledit corps rotorique et d'autre part sur la face opposée, une excroissance sous forme de crochet pour le placement du moyen de rétention contre un flanc plat du corps rotorique.According to a preferred embodiment of the invention, said moving blades each have a blade and a bulb of dawn, each dawn bulb having on the one hand, on a first face, an outgrowth under beater tooth form acting as a stopper by positioning and direct contact with said rotor body and secondly on the opposite side, a protrusion in the form of a hook for the placement of the retention means against a flat flank of the rotor body.

Brève description des figuresBrief description of the figures

La figure 1 représente une vue générale d'une turbine basse pression d'un turbofan dans lequel sont présents une succession d'étages distributeurs et d'étages rotoriques.FIG. 1 represents a general view of a low-pressure turbine of a turbofan in which a succession of distributor stages and rotor stages are present.

La figure 2 représente une vue en coupe d'une aube munie des moyens de solidarisation au rotor.Figure 2 shows a sectional view of a blade provided with means for securing to the rotor.

La figure 3 représente une vue en perspective du bulbe d'une aube destinée à être utilisée selon le procédé de montage de la présente invention.Figure 3 shows a perspective view of the bulb of a blade for use according to the mounting method of the present invention.

La figure 4 représente une vue en perspective des moyens de solidarisation mis en oeuvre selon la présente invention des aubes tournantes au rotor.FIG. 4 represents a perspective view of the securing means used according to the present invention of the rotor rotating blades.

La figure 5 représente une vue en perspective de l'anneau de solidarisation selon la présente invention.Figure 5 shows a perspective view of the fastening ring according to the present invention.

Les figures 6a à 6c représentent le principe de montage de l'anneau selon la présente invention.Figures 6a to 6c show the mounting principle of the ring according to the present invention.

Description d'une forme d'exécution préférée de l'inventionDescription of a preferred embodiment of the invention

La figure 1 représente la turbine basse pression d'un turbofan. Cette turbine est constituée de plusieurs étages successifs, chacun composé de deux types de pièces :

  • d'une part, des pièces mobiles qui sont essentiellement constituées par le rotor 1 muni de plusieurs séries d'aubes mobiles 3,3',3",... correspondant à plusieurs étages rotoriques successifs, et
  • d'autre part des pièces fixes constituant les étages statoriques distributeurs 2,2',2",... séparant les étages rotoriques 3,3',3",...
Figure 1 shows the low pressure turbine of a turbofan. This turbine consists of several successive stages, each composed of two types of parts:
  • on the one hand, moving parts which are essentially constituted by the rotor 1 provided with several series of blades 3,3 ', 3 ", ... corresponding to several successive rotor stages, and
  • on the other hand, fixed parts constituting the stator distributor stages 2,2 ', 2 ", ... separating the rotor stages 3,3', 3", ...

Chaque étage distributeur 2,2',2",... est essentiellement constitué d'aubes 2,2',2",... contenues entre deux plateformes intérieure 4,4',4",... et extérieure 5,5',5",...Each distributor stage 2,2 ', 2 ", ... is essentially constituted by blades 2,2', 2", ... contained between two inner platforms 4,4 ', 4 ", ... and outside 5 , 5 ', 5 ", ...

Chaque étage rotorique est constitué par les aubes tournantes 3,3',3",... toutes reliées au rotor 1 par des moyens de rétention.Each rotor stage is constituted by the rotating blades 3,3 ', 3 ", ... all connected to the rotor 1 by means of retention.

Le gaz frappe d'abord le premier distributeur 2 du premier étage statorique basse pression où son vecteur vitesse est repositionné avant de frapper le premier rotor 3 pour être à nouveau repositionné par le deuxième étage statorique en 2', avant de frapper à nouveau le deuxième étage rotorique 3', etc. Le gaz subit ainsi un cycle de poussée - redistribution des vitesses à l'issue duquel son énergie cinétique diminue progressivement ainsi que sa pression, tandis que le travail rotorique croît en s'additionnant d'étage en étage.The gas first strikes the first distributor 2 of the first low pressure stator stage where its velocity vector is repositioned before striking the first rotor 3 to be repositioned by the second stator stage 2 'before striking again the second rotor stage 3', etc. The gas thus undergoes a thrust cycle - redistribution of the speeds at the end of which its kinetic energy gradually decreases as well as its pressure, while the rotor work grows by adding from floor to floor.

Aux figures 2 et 3, une aube tournante 3 se présente classiquement sous la forme d'un plat 30 lié à un bulbe d'aube 31. Les différents bulbes 31,31',31" seront usinés de telle sorte qu'ils puissent être disposés successivement autour d'un disque 10 qui sert de rotor, ainsi que représenté à la figure 4.In Figures 2 and 3, a rotating blade 3 is conventionally in the form of a flat 30 connected to a bulb of blade 31. The various bulbs 31,31 ', 31 "will be machined so that they can be arranged successively around a disk 10 which serves as a rotor, as shown in FIG.

Le placement des aubes tournantes 3 sur le rotor 10 se fait par glissement entre les dents du disque. En effet, les bulbes d'aube 31,31',31" présentent une forme mâle constituée d'une succession d'excroissances et de creux à laquelle correspond essentiellement une cavité femelle complémentaire réalisée dans le disque 10 servant de rotor, ces cavités créant des « dents » sur le disque.The placement of the rotating blades 3 on the rotor 10 is by sliding between the teeth of the disc. Indeed, the blade bulbs 31, 31 ', 31 "have a male shape consisting of a succession of excrescences and recesses to which essentially corresponds a complementary female cavity made in the disc 10 serving as a rotor, these cavities creating "teeth" on the disc.

Afin de garantir tant une rétention amont qu'une rétention aval, il est prévu que les bulbes d'aube 31,31',31" présentent chacun, d'une part, sur une première face, une excroissance sous forme de dent de castor 33 qui servira de butée franche en se positionnant directement en contact avec le disque rotorique 10, et d'autre part, sur la face opposée, une excroissance sous forme de crochet 32 qui va permettre le placement d'un anneau 40.In order to guarantee both upstream retention and downstream retention, the blade bulbs 31,31 ', 31 "are each provided, on the one hand, on a first face with a protrusion in the form of a beaver tooth. 33 which will serve as a stop frankly positioning itself directly in contact with the rotor disc 10, and secondly, on the opposite side, an excrescence in the form of hook 32 which will allow the placement of a ring 40.

La présence de cet anneau 40 va avantageusement permettre la solidarisation de tous les bulbes d'aube 31,31',31" sur le même disque rotorique 10. Un tel anneau est représenté en détail à la figure 5.The presence of this ring 40 will advantageously allow the joining of all the blade bulbs 31, 31 ', 31 "on the same rotor disk 10. Such a ring is shown in detail in FIG.

Selon une caractéristique importante de la présente invention, cet anneau 40 présente une fente 41, de préférence découpée en biais, de manière à ce que l'on puisse effectuer la mise en place de l'anneau en précontraignant celui-ci et en le relâchant ensuite.According to an important feature of the present invention, this ring 40 has a slot 41, preferably cut at an angle, so that it can perform the establishment of the ring by prescribing it and releasing it then.

En outre, cet anneau 40 présente sur au moins un flanc radial 42 un surcroît de matière sous la forme d'un bossage 45. Avantageusement, ce bossage 45 est présent sur une portion qui correspond essentiellement à la distance prévue entre deux aubes successives ainsi que représenté à la figure 4. Sur cette distance se trouve également ladite fente 41.In addition, this ring 40 has on at least one radial flank 42 an additional material in the form of a boss 45. Advantageously, this boss 45 is present on a portion which substantially corresponds to the planned distance between two successive blades as well as represented in FIG. 4. At this distance is also said slot 41.

Le bossage présente en outre l'avantage d'empêcher la rotation de l'anneau 40 par rapport au disque 10.The boss also has the advantage of preventing rotation of the ring 40 with respect to the disc 10.

De plus, ledit bossage 45 est dessiné et calculé pour correspondre exactement au manque de matière dû à la présence de la fente 41. Le bossage 45 a donc pour but de proposer un balourd qui doit compenser exactement le manque de matière dû à la fente 41.In addition, said boss 45 is drawn and calculated to exactly match the lack of material due to the presence of the slot 41. The purpose of the boss 45 is therefore to provide an unbalance which must compensate exactly for the lack of material due to the slot 41. .

En outre, l'anneau 40, ainsi que représenté à la figure 2, présente une section conique qui permet, lors du fonctionnement de l'étage rotorique, de diminuer ou même supprimer le jeu axial de l'aube sur le disque et donc de diminuer les vibrations qui pourraient être générées par la force centrifuge.In addition, the ring 40, as shown in Figure 2, has a conical section that allows, during operation of the rotor stage, to reduce or even eliminate the axial play of the blade on the disk and therefore to reduce the vibrations that could be generated by the centrifugal force.

Les figures 6a-6c représentent la mise en place de l'anneau 40 sur le disque rotorique 10. En particulier, l'anneau 40 est configuré de telle manière qu'à l'état libre (Fig. 6a), il présente une certaine ouverture A. Pour permettre sa mise en place, on aura tendance à effectuer un pincement lors du montage de manière à précontraindre l'anneau (Fig. 6b). Après sa mise en place (Fig. 6c), l'anneau se relâchera de sorte qu'il se positionnera parfaitement entre deux aubes tournantes ainsi que représenté à la figure 5.FIGS. 6a-6c show the placement of the ring 40 on the rotor disk 10. In particular, the ring 40 is configured in such a way that in the free state (FIG. opening A. To allow it to be put in place, there will be a tendency to pinch during assembly so as to preload the ring (Fig. 6b). After its installation (Fig. 6c), the ring will relax so that it will fit perfectly between two rotating blades as shown in Figure 5.

Cet anneau est de préférence réalisé en un matériau métallique qui permet son utilisation à des températures élevées.This ring is preferably made of a metallic material that allows its use at high temperatures.

De manière particulièrement avantageuse, ceci permet de réaliser la rétention à l'aide d'une seule pièce qui est l'anneau et ceci pour toutes les aubes, ce qui permet de réduire de manière significative le temps de pose et de montage et d'en faciliter la maintenance.
La présente invention présente en outre spécifiquement les différences et avantages suivants sur l'état de la technique le plus proche susmentionné (FR-A-2 729 709). Dans la présente invention :

  • la distance sur laquelle s'étend le bossage de part et d'autre de la fente correspond précisément à la distance intercalaire entre les crochets 32 de deux aubes successives ; dans l'état de la technique, les deux taquets sont équidistants de la fente et séparés par une distance correspondant à la largeur du becquet d'une seule aube ;
  • le disque rotorique est simplifié par rapport à l'état de la technique qui nécessite l'usinage d'autant de becquets de disque que d'aubes à brocher ;
  • le balourd constitué par le bossage procure l'équilibrage dynamique du rotor ;
  • l'anneau de section conique, sous l'effet de la force centrifuge, permet l'élimination du jeu axial des aubes.
In a particularly advantageous manner, this makes it possible to achieve the retention with the aid of a single piece which is the ring and this for all the blades, which makes it possible to significantly reduce the time of installation and assembly and of to facilitate maintenance.
The present invention further specifically discloses the following differences and advantages over the above-mentioned closest prior art (FR-A-2 729 709). In the present invention:
  • the distance over which the boss extends on either side of the slot corresponds precisely to the intermediate distance between the hooks 32 of two successive blades; in the state of the art, the two cleats are equidistant from the slot and separated by a distance corresponding to the width of the spoiler of a single blade;
  • the rotor disc is simplified compared to the state of the art which requires the machining of as many disk spoil as blades to broach;
  • the unbalance constituted by the boss provides the dynamic balancing of the rotor;
  • the ring of conical section, under the effect of the centrifugal force, allows the elimination of the axial play of the blades.

Claims (5)

  1. Rotor stage of an turbine or of an axial compressor comprising several mobile blades (3, 3', 3",...) connected to a rotor body (10) by a retention means having the form of a single part corresponding to a ring (40) opened by a split (41) on a section of said ring, said section having, on the radial side (42) defined as the side facing outwards relative to the rotor body (10), spare material in the form of an anti-rotation boss (45) extending on both sides of said slit (41), said retention means being characterised in that:
    - the length of the boss (45) along the ring (40) corresponds to the insertion distance provided between two successive mobile blades (3,3');
    - it is provided with an additional means for reducing the axial gap by self-jamming into a groove, said additional means comprising making the ring (40) with a tapered section, with the exception of the section with the boss (45).
  2. Rotor stage according to Claim 1, characterised in that the slit (41) of the ring (40) is cut at an angle.
  3. Rotor stage according to Claim 1 or 2, characterised in that the spare material having the form of a boss (45) is designed so that it precisely compensates mechanically for the lack of material due to the presence of the slit (41).
  4. Rotor stage according to any one of the preceding claims, characterised in that the retention means is made of a metal material.
  5. Rotor stage according to any one of the preceding claims, characterised in that said mobile blades (3, 3', 3",...) each have a flat part (30) and a blade bulb (31), each blade bulb (31) having, for one thing, on a first face, a protrusion in the form of a beaver's tooth (32) acting as an open stop by positioning and direct contact with said rotor body (10), and for another thing, on the opposite face, a protrusion in the form of a hook (33) for positioning the retention means against a flat side of the rotor body (10).
EP20000870311 2000-12-21 2000-12-21 Axial fixation of gas turbine rotor blades Expired - Lifetime EP1217168B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20000870311 EP1217168B1 (en) 2000-12-21 2000-12-21 Axial fixation of gas turbine rotor blades
DE60029114T DE60029114D1 (en) 2000-12-21 2000-12-21 Axial fixation of rotor blades of a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20000870311 EP1217168B1 (en) 2000-12-21 2000-12-21 Axial fixation of gas turbine rotor blades

Publications (2)

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EP1217168A1 EP1217168A1 (en) 2002-06-26
EP1217168B1 true EP1217168B1 (en) 2006-06-28

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EP20000870311 Expired - Lifetime EP1217168B1 (en) 2000-12-21 2000-12-21 Axial fixation of gas turbine rotor blades

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Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201404362D0 (en) 2014-03-12 2014-04-23 Rolls Royce Plc Bladed rotor
US20200131916A1 (en) * 2018-10-31 2020-04-30 United Technologies Corporation Turbine blade assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
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.
FR2729709A1 (en) * 1995-01-25 1996-07-26 Snecma Turbine rotor seal and retainer

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DE60029114D1 (en) 2006-08-10
EP1217168A1 (en) 2002-06-26

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