EP2009244A1 - Device for axial retention of vanes mounted on a turbomachine rotor disc - Google Patents

Device for axial retention of vanes mounted on a turbomachine rotor disc Download PDF

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Publication number
EP2009244A1
EP2009244A1 EP08158843A EP08158843A EP2009244A1 EP 2009244 A1 EP2009244 A1 EP 2009244A1 EP 08158843 A EP08158843 A EP 08158843A EP 08158843 A EP08158843 A EP 08158843A EP 2009244 A1 EP2009244 A1 EP 2009244A1
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EP
European Patent Office
Prior art keywords
retaining ring
segments
disk
bearing face
rotor
Prior art date
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Granted
Application number
EP08158843A
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German (de)
French (fr)
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EP2009244B1 (en
Inventor
Claude Gérard René Dejaune
Valérie Annie Gros
Gaël Loro
Jean-Luc Soupizon
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2009244A1 publication Critical patent/EP2009244A1/en
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Publication of EP2009244B1 publication Critical patent/EP2009244B1/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
    • F01D5/3007—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 device for axially retaining blades mounted on a turbomachine rotor disk such as the rotor of the last stage of the low-pressure turbine.
  • the low-pressure turbine of a turbomachine is composed of a plurality of stages of moving blades alternating with fixed vanes. For each stage of the turbine, the blades are fixed on two concentric rings and the blades are fixed by their foot on a rotor disk. All the rotor disks of the turbine are fixed to each other by bolted connections and are secured to the low-pressure shaft of the turbomachine via a trunnion.
  • the disc of the last stage of such a low-pressure turbine comprises at its periphery a plurality of axial cells in each of which is mounted the foot of a blade of the turbine.
  • the gas stream passes through the turbine exerting an axial force on the moving blades, it is necessary to prevent any axial displacement of the vanes with the aid of retaining devices.
  • One of these devices is to immobilize the blade roots with an annular flange pressed against a radial bearing surface of the disc and the blade root, the flange being held in this position by an annular ring.
  • EP 1,180,580 and EP 1,498,579 we can refer to publications EP 1,180,580 and EP 1,498,579 .
  • such a device is usually quite complex to make and assemble since it requires the use of several parts (namely the flange and the retaining ring of the flange).
  • the present invention aims to overcome the aforementioned drawbacks by proposing an axial retaining device blades whose realization and assembly are simple and which is likely to contribute to the balancing of the rotor disk.
  • an axial retention device for vanes mounted on a turbomachine rotor disk characterized in that it comprises a rotor disk comprising at its periphery a plurality of substantially axial cells and open towards the outside. outside, and at a radial bearing face, a flange extending radially outwardly to define with said bearing face an annular groove open towards the outside, the device further comprising a plurality of blades each comprising a foot mounted in a corresponding cell of the rotor disc, each blade root being provided at a radial bearing surface corresponding to that of the rotor disc of at least one radially extending spoiler inwardly to delimit with said bearing face an annular slot open towards the inside, and a retaining ring mounted against the bearing face of the rotor disc and the blade roots, said retaining ring etan t housed in the groove of the disk, held outside in the notches of the blade roots, and consists of a plurality of angular segments placed
  • the device according to the invention comprises only one piece (namely the retaining ring which is segmented) so that it is easy to make and easy to mount on the rotor disc.
  • the retaining ring consists of a plurality of angular segments placed end to end, it is possible to vary the mass of each of these segments individually in order to correct the unbalance phenomenon encountered by the rotor disks. . In this way, the unbalance correction can be obtained without having to disassemble before binding structural.
  • At least one of the segments of the retaining ring has a greater mass than the other segments.
  • each segment of the retaining ring comprises notches open towards the outside to allow the passage of the spoilers of the blade roots during assembly of the retaining ring in the groove of the disc of rotor.
  • the retaining ring comprises means for making it possible to stop its rotation in the groove of the rotor disk.
  • at least one of the segments of the retaining ring may comprise a foldable tongue that is adapted to be folded between two adjacent lugs of blade roots to stop the rotation of the retaining ring in the groove of the rotor disk.
  • the invention also relates to a turbomachine comprising at least one axial retention device blades mounted on a rotor disk as defined above.
  • FIGS. 1 and 1A partially represent in longitudinal section a low-pressure turbine of an aviation turbine engine equipped with a device according to one embodiment of the invention.
  • turbomachine assembly (aeronautical or terrestrial) provided with a rotor disk on which are mounted axially blades.
  • the low-pressure turbine is centered on the longitudinal axis X-X of the turbomachine.
  • the last stage of the turbine consists of a distributor formed of a plurality of blades 2 and a movable wheel placed behind the distributor and formed of a plurality of blades 4 mounted axially on a rotor disk 6.
  • the penultimate stage of the turbine also consists of a distributor (not shown) and a movable wheel formed of a plurality of blades 4 'mounted on a rotor disk 6'.
  • the discs 6, 6 'of the last and the penultimate stages of the turbine are fixed to each other by means of bolted connections 8 and are secured to the low-pressure shaft of the turbomachine (no shown) by an annular journal 10. The latter is also fixed on the discs 6, 6 'by means of the same bolted connections 8.
  • the disk 6 of the last stage of the turbine comprises at its periphery a plurality of substantially axial cells 12, open towards the outside of the disk (that is to say in the direction opposite to the longitudinal axis XX) and intended each axially receive the foot 4a (for example fir-shaped) of a blade 4 of the turbine (for example by fitting).
  • the disk 6 also comprises, at its downstream radial face 14 (hereinafter referred to as the bearing face), a flange 16 extending radially outwards of the disk to delimit with the bearing face an annular groove 18 open. outwards.
  • each blade root 4a is provided at its downstream radial face corresponding to that of the rotor disc 6 of at least one spoiler 20 extending radially towards the inside of the disk (ie say towards the longitudinal axis XX) to delimit with said downstream face an annular notch 22 which is open towards the inside.
  • the device according to the invention comprises a retaining ring 24 which is mounted against the bearing face 14 of the rotor disc 6 and the blade roots 4a.
  • This retaining ring 24 is housed in the groove 18 of the disc and is held outside in the notches 22 of the blade roots 4a.
  • the retaining ring 24 consists of a plurality of angular segments (or sectors) 24a placed end to end, each ring segment 24a being able to extend circumferentially over the same angular distance.
  • a turbomachine low-pressure turbine whose last stage comprises 98 blades, it can be provided 14 ring segments 24a which therefore each extend over 25 °.
  • each ring segment 24a comprises notches 26 which are open towards the outside. As illustrated by Figure 2A these notches are dimensioned to allow the passage of the spoilers 20 of the blade roots 4a when mounting the retaining ring in the groove of the disc. In this position, the ring segments are not maintained outside in the notches 22 of the blade roots.
  • the number of notches 26 per segment can be 7.
  • the ring segments 24a are pivoted about the longitudinal axis XX of the turbomachine so that the spoilers 20 of the blade roots are no longer arranged opposite the notches 26 ( Figure 2B ). In this position, the ring segments are then held outside in the notches of the blade roots.
  • the rotor disc 6 comprises 98 blades 4 and the retaining ring 24 consists of 14 segments 24a, each segment having 7 notches 26, a rotation (in one direction or the other ) 1.8 ° of the retaining ring allows to move from the position of the Figure 2A at the position of the Figure 2B .
  • the disassembly of the retaining ring is performed in the same manner by pivoting the latter by an angle sufficient to ensure that the spoilers of the blade roots are again arranged opposite the notches of the segments of the Ring.
  • At least one of the ring segments 24a comprises a foldable tongue 28 which is adapted to be folded between two adjacent spoilers 20 of blade roots 4a to stop the rotation of the retaining ring. in the groove 18 of the rotor disk 6 once it is correctly positioned ( Figure 2B ).
  • the tongue 28 is disposed at one of the indentations 26 of the ring segment 24a and is bendable to take two extreme positions: a position in which it extends in a plane inclined with respect to the radial plane of the segment ring to allow rotation of said segment ( Figure 2A ), and another position in which it is arranged in the same radial plane as the spoilers 20 of the blade roots and extends circumferentially between two adjacent spoilers 20 in order to lock in rotation said segment and therefore the entire ring restraint ( Figure 2B ).
  • At least one of the ring segments 24a has a larger mass than the other segments.
  • Such an arrangement makes it possible to easily correct the unbalance phenomenon observed in a low-pressure turbine. Indeed, as the retaining ring 24 is segmented, it is possible to assign to some of the ring segments an individual mass which is different from that of the others and thus ensure that the center of gravity of the rotor disc is found well on the longitudinal axis XX of the turbomachine. It should be noted that the higher the number of ring segments, the better the balance of the masses on the entire disk.
  • This arrangement is particularly advantageous when, as represented on the figure 1 the annular space between the inner end of the disk 6 of the last stage of the turbine and the pin 10 does not allow direct access to the bolted connections 8 so that it is impossible to fix balancing masses on these bolted connections without first removing the last stage of the turbine.
  • a balancing control of the rotor disk is performed once the turbine assembly and an unbalance correction is optionally applied.
  • one or more ring segments are replaced by modified mass segments adapted to the required correction.
  • the modified mass segments are ring segments whose mass is greater than that of the other segments.
  • FIGS. 3A to 3C which represent in longitudinal section different alternative embodiments of the device according to the invention, illustrate various ways of varying the mass of a ring segment 24a.
  • the ring segment 24a has an excess thickness 30 with respect to the segment shown in FIG. figure 3A .
  • the ring segment 24a of the figure 3C has a boss 32 which is present neither on the ring segment of the figure 3A nor on that of the figure 3B .
  • This extra thickness 30 and this boss 32 may extend circumferentially over all or only part of the ring segment. They correspond to mass additions.
  • the depth of the indentations 26, as well as the height and / or the thickness of the inter-indent regions may vary in order to increase or decrease the mass of the ring segments.
  • the ring segments can be pre-machined with range classes (for example from gram to gram) to provide a wide choice of segments adapted to the unbalance correction required.
  • the ring segments can be machined on demand.
  • the axial blade retainer according to the invention has many advantages.
  • it consists of only one main piece (ie the retaining ring) which makes its inexpensive manufacture and assembly / disassembly against the bearing surface of the easy disc.
  • ring segments it is possible to vary the mass of each of these segments and thus easily correct the phenomenon of unbalance observed with this type of technology.

Abstract

The device has a set of axial slots (12) outwardly opened at periphery of a rotor disk (6). A flange (16) extends radially outwards to co-operate with a bearing face (14) of the disk. A set of blades (4) has roots (4a) mounted in the slot and on a radial bearing face corresponding to the bearing face of the disk. A retaining ring (24) is placed in a groove (18) of the disk and hold in notches (22) of the roots. A set of angular segments (24a) is placed at ends of the ring such that weight of one of the segments of the retaining ring is greater than other segments.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention concerne un dispositif de retenue axiale d'aubes montées sur un disque de rotor de turbomachine tel que le rotor du dernier étage de la turbine basse-pression.The present invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk such as the rotor of the last stage of the low-pressure turbine.

De façon connue en soi, la turbine basse-pression d'une turbomachine se compose d'une pluralité d'étages d'aubes mobiles alternant avec des aubes fixes. Pour chaque étage de la turbine, les aubes fixes sont fixées sur deux viroles concentriques et les aubes mobiles sont fixées par leur pied sur un disque de rotor. Tous les disques de rotor de la turbine sont fixés les uns aux autres par des liaisons boulonnées et sont rendus solidaires de l'arbre basse-pression de la turbomachine par l'intermédiaire d'un tourillon.In a manner known per se, the low-pressure turbine of a turbomachine is composed of a plurality of stages of moving blades alternating with fixed vanes. For each stage of the turbine, the blades are fixed on two concentric rings and the blades are fixed by their foot on a rotor disk. All the rotor disks of the turbine are fixed to each other by bolted connections and are secured to the low-pressure shaft of the turbomachine via a trunnion.

Il est également connu que le disque du dernier étage d'une telle turbine basse-pression comprend à sa périphérie une pluralité d'alvéoles axiales dans chacune desquelles est monté le pied d'une aube mobile de la turbine. Le flux gazeux qui traverse la turbine exerçant un effort axial sur les aubes mobiles, il est nécessaire d'empêcher tout déplacement axial des aubes à l'aide de dispositifs de retenue. L'un de ces dispositifs consiste à immobiliser les pieds des aubes à l'aide d'un flasque annulaire plaqué contre une face radiale d'appui du disque et du pied des aubes, le flasque étant maintenu dans cette position par un jonc annulaire. On pourra se référer par exemple aux publications EP 1,180,580 et EP 1,498,579 . Or, bien qu'efficace, un tel dispositif est le plus souvent assez complexe à réaliser et à monter puisqu'il nécessite de se servir de plusieurs pièces (à savoir le flasque et le jonc de retenue du flasque).It is also known that the disc of the last stage of such a low-pressure turbine comprises at its periphery a plurality of axial cells in each of which is mounted the foot of a blade of the turbine. As the gas stream passes through the turbine exerting an axial force on the moving blades, it is necessary to prevent any axial displacement of the vanes with the aid of retaining devices. One of these devices is to immobilize the blade roots with an annular flange pressed against a radial bearing surface of the disc and the blade root, the flange being held in this position by an annular ring. For example, we can refer to publications EP 1,180,580 and EP 1,498,579 . However, although effective, such a device is usually quite complex to make and assemble since it requires the use of several parts (namely the flange and the retaining ring of the flange).

Il est encore connu que les disques de rotor de la turbine basse-pression d'une turbomachine sont sujets à une mauvaise répartition des masses qui fait que leur centre de gravité n'est pas sur leur axe de rotation. Afin de corriger un tel phénomène de balourd, des masses d'équilibrage sont positionnées à certains endroits des disques, notamment au niveau des liaisons boulonnées entre les différents disques de la turbine et au niveau de brides rajoutées spécifiquement dans ce but. Or, certaines configurations de turbine basse-pression rendent impossible l'accès à ces liaisons boulonnées sans avoir à démonter au préalable certains étages de la turbine. Par ailleurs, l'ajout de brides spécifiques à la fixation des masses d'équilibrage alourdit la masse totale de la turbine.It is still known that the rotor discs of the low-pressure turbine of a turbomachine are subject to a poor distribution of masses that makes their center of gravity is not on their axis of rotation. In order to correct such an unbalance phenomenon, balancing masses are positioned at certain locations of the disks, in particular at the level of the links bolted between the different disks. turbine and at the flanges added specifically for this purpose. However, some low-pressure turbine configurations make it impossible to access these bolted connections without having to dismantle some stages of the turbine beforehand. Furthermore, the addition of specific flanges for fixing balancing masses increases the total mass of the turbine.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention vise à remédier aux inconvénients précités en proposant un dispositif de retenue axiale des aubes dont la réalisation et le montage sont simples et qui est susceptible de contribuer à l'équilibrage du disque de rotor.The present invention aims to overcome the aforementioned drawbacks by proposing an axial retaining device blades whose realization and assembly are simple and which is likely to contribute to the balancing of the rotor disk.

Ce but est atteint grâce à un dispositif de retenue axiale d'aubes montées sur un disque de rotor de turbomachine, caractérisé en ce qu'il comprend un disque de rotor comprenant à sa périphérie, une pluralité d'alvéoles sensiblement axiales et ouvertes vers l'extérieur, et au niveau d'une face radiale d'appui, une bride s'étendant radialement vers l'extérieur pour délimiter avec ladite face d'appui une rainure annulaire ouverte vers l'extérieur, le dispositif comprenant en outre une pluralité d'aubes comprenant chacune un pied monté dans une alvéole correspondante du disque de rotor, chaque pied d'aube étant muni au niveau d'une face radiale d'appui correspondant à celle du disque de rotor d'au moins un becquet s'étendant radialement vers l'intérieur pour délimiter avec ladite face d'appui une encoche annulaire ouverte vers l'intérieur, et une bague de retenue montée contre la face d'appui du disque de rotor et des pieds des aubes, ladite bague de retenue étant logée dans la rainure du disque, maintenue à l'extérieur dans les encoches des pieds des aubes, et constituée d'une pluralité de segments angulaires mis bout à bout.This object is achieved by means of an axial retention device for vanes mounted on a turbomachine rotor disk, characterized in that it comprises a rotor disk comprising at its periphery a plurality of substantially axial cells and open towards the outside. outside, and at a radial bearing face, a flange extending radially outwardly to define with said bearing face an annular groove open towards the outside, the device further comprising a plurality of blades each comprising a foot mounted in a corresponding cell of the rotor disc, each blade root being provided at a radial bearing surface corresponding to that of the rotor disc of at least one radially extending spoiler inwardly to delimit with said bearing face an annular slot open towards the inside, and a retaining ring mounted against the bearing face of the rotor disc and the blade roots, said retaining ring etan t housed in the groove of the disk, held outside in the notches of the blade roots, and consists of a plurality of angular segments placed end to end.

Le dispositif selon l'invention ne comprend qu'une seule pièce (à savoir la bague de retenue qui est segmentée) de sorte qu'il est aisé à réaliser et facile à monter sur le disque de rotor. Par ailleurs, la bague de retenue étant constituée d'une pluralité de segments angulaires mis bout à bout, il est possible de faire varier de façon individuelle la masse de chacun de ces segments afin de corriger le phénomène de balourd rencontré par les disques de rotor. De la sorte, la correction du balourd peut être obtenue sans avoir à démonter au préalable de liaison structurale. De plus, il n'est pas nécessaire d'avoir à rajouter des brides dédiées à la fixation de masses d'équilibrage et dont la présence alourdit l'ensemble.The device according to the invention comprises only one piece (namely the retaining ring which is segmented) so that it is easy to make and easy to mount on the rotor disc. Moreover, since the retaining ring consists of a plurality of angular segments placed end to end, it is possible to vary the mass of each of these segments individually in order to correct the unbalance phenomenon encountered by the rotor disks. . In this way, the unbalance correction can be obtained without having to disassemble before binding structural. In addition, it is not necessary to have to add flanges dedicated to the fixing of balancing masses and whose presence weighs the whole.

Selon une caractéristique avantageuse de l'invention, au moins l'un des segments de la bague de retenue possède une masse plus importante que les autres segments.According to an advantageous characteristic of the invention, at least one of the segments of the retaining ring has a greater mass than the other segments.

Selon une autre caractéristique avantageuse de l'invention, chaque segment de la bague de retenue comprend des échancrures ouvertes vers l'extérieur pour permettre le passage des becquets des pieds d'aubes lors du montage de la bague de retenue dans la rainure du disque de rotor.According to another advantageous characteristic of the invention, each segment of the retaining ring comprises notches open towards the outside to allow the passage of the spoilers of the blade roots during assembly of the retaining ring in the groove of the disc of rotor.

Selon encore une autre caractéristique avantageuse de l'invention, la bague de retenue comprend des moyens pour permettre d'arrêter sa rotation dans la rainure du disque de rotor. Ainsi, au moins l'un des segments de la bague de retenue peut comprendre une languette pliable qui est apte à être rabattue entre deux becquets adjacents de pieds d'aubes pour arrêter la rotation de la bague de retenue dans la rainure du disque de rotor.According to yet another advantageous characteristic of the invention, the retaining ring comprises means for making it possible to stop its rotation in the groove of the rotor disk. Thus, at least one of the segments of the retaining ring may comprise a foldable tongue that is adapted to be folded between two adjacent lugs of blade roots to stop the rotation of the retaining ring in the groove of the rotor disk. .

L'invention a également pour objet une turbomachine comprenant au moins un dispositif de retenue axiale d'aubes montées sur un disque de rotor tel que défini précédemment.The invention also relates to a turbomachine comprising at least one axial retention device blades mounted on a rotor disk as defined above.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue partielle et en coupe longitudinale d'une turbine basse-pression de turbomachine équipée d'un dispositif selon un mode de réalisation de l'invention ;
  • la figure 1A est une loupe de la figure 1 ;
  • les figures 2A et 2B sont des vues partielles de devant du dispositif de la figure 1 montrant le montage de la bague de retenue ; et
  • les figures 3A à 3C sont des vues en coupe longitudinale de dispositifs selon d'autres modes de réalisation de l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a partial view in longitudinal section of a turbomachine low-pressure turbine equipped with a device according to one embodiment of the invention;
  • the Figure 1A is a magnifying glass of the figure 1 ;
  • the Figures 2A and 2B are partial front views of the device from the figure 1 showing the mounting of the retaining ring; and
  • the FIGS. 3A to 3C are longitudinal sectional views of devices according to other embodiments of the invention.

Description détaillée de modes de réalisationDetailed description of embodiments

Les figures 1 et 1A représentent partiellement en coupe longitudinale une turbine basse-pression d'une turbomachine aéronautique équipée d'un dispositif selon un mode de réalisation de l'invention.The Figures 1 and 1A partially represent in longitudinal section a low-pressure turbine of an aviation turbine engine equipped with a device according to one embodiment of the invention.

Bien entendu, la présente invention s'applique à tout autre ensemble de turbomachine (aéronautique ou terrestre) muni d'un disque de rotor sur lequel sont montées axialement des aubes.Of course, the present invention applies to any other turbomachine assembly (aeronautical or terrestrial) provided with a rotor disk on which are mounted axially blades.

La turbine basse-pression est centrée sur l'axe longitudinal X-X de la turbomachine. Le dernier étage de la turbine se compose d'un distributeur formé d'une pluralité d'aubes fixes 2 et d'une roue mobile placée derrière le distributeur et formée d'une pluralité d'aubes mobiles 4 montées axialement sur un disque de rotor 6. L'avant-dernier étage de la turbine se compose également d'un distributeur (non représenté) et d'une roue mobile formée d'une pluralité d'aubes mobiles 4' montées sur un disque de rotor 6'.The low-pressure turbine is centered on the longitudinal axis X-X of the turbomachine. The last stage of the turbine consists of a distributor formed of a plurality of blades 2 and a movable wheel placed behind the distributor and formed of a plurality of blades 4 mounted axially on a rotor disk 6. The penultimate stage of the turbine also consists of a distributor (not shown) and a movable wheel formed of a plurality of blades 4 'mounted on a rotor disk 6'.

Les disques 6, 6' du dernier et de l'avant-dernier étages de la turbine sont fixés l'un à l'autre au moyen de liaisons boulonnées 8 et sont rendus solidaire de l'arbre basse-pression de la turbomachine (non représenté) par un tourillon annulaire 10. Ce dernier est également fixé sur les disques 6, 6' au moyen des mêmes liaisons boulonnées 8.The discs 6, 6 'of the last and the penultimate stages of the turbine are fixed to each other by means of bolted connections 8 and are secured to the low-pressure shaft of the turbomachine (no shown) by an annular journal 10. The latter is also fixed on the discs 6, 6 'by means of the same bolted connections 8.

Comme représenté à la figure 1A, le disque 6 du dernier étage de la turbine comporte à sa périphérie une pluralité d'alvéoles 12 sensiblement axiales, ouvertes vers l'extérieur du disque (c'est-à-dire en direction opposée à l'axe longitudinal X-X) et destinées à recevoir chacune axialement le pied 4a (par exemple en forme de sapin) d'une aube mobile 4 de la turbine (par exemple par emmanchement).As represented in Figure 1A , the disk 6 of the last stage of the turbine comprises at its periphery a plurality of substantially axial cells 12, open towards the outside of the disk (that is to say in the direction opposite to the longitudinal axis XX) and intended each axially receive the foot 4a (for example fir-shaped) of a blade 4 of the turbine (for example by fitting).

Le disque 6 comporte également au niveau de sa face radiale aval 14 (appelée ci-après face d'appui), une bride 16 s'étendant radialement vers l'extérieur du disque pour délimiter avec la face d'appui une rainure annulaire 18 ouverte vers l'extérieur.The disk 6 also comprises, at its downstream radial face 14 (hereinafter referred to as the bearing face), a flange 16 extending radially outwards of the disk to delimit with the bearing face an annular groove 18 open. outwards.

Par ailleurs, chaque pied d'aube 4a est muni au niveau de sa face radiale aval correspondant à celle du disque de rotor 6 d'au moins un becquet 20 s'étendant radialement vers l'intérieur du disque (c'est-à-dire vers l'axe longitudinal X-X) pour délimiter avec ladite face aval une encoche annulaire 22 qui est ouverte vers l'intérieur.Furthermore, each blade root 4a is provided at its downstream radial face corresponding to that of the rotor disc 6 of at least one spoiler 20 extending radially towards the inside of the disk (ie say towards the longitudinal axis XX) to delimit with said downstream face an annular notch 22 which is open towards the inside.

Le dispositif selon l'invention comprend une bague de retenue 24 qui est montée contre la face d'appui 14 du disque de rotor 6 et des pieds d'aubes 4a. Cette bague de retenue 24 est logée dans la rainure 18 du disque et elle est maintenue à l'extérieur dans les encoches 22 des pieds d'aubes 4a.The device according to the invention comprises a retaining ring 24 which is mounted against the bearing face 14 of the rotor disc 6 and the blade roots 4a. This retaining ring 24 is housed in the groove 18 of the disc and is held outside in the notches 22 of the blade roots 4a.

En outre, la bague de retenue 24 est constituée d'une pluralité de segments (ou secteurs) angulaires 24a mis bout à bout, chaque segment de bague 24a pouvant s'étendre circonférentiellement sur une même distance angulaire.In addition, the retaining ring 24 consists of a plurality of angular segments (or sectors) 24a placed end to end, each ring segment 24a being able to extend circumferentially over the same angular distance.

A titre d'exemple, pour une turbine basse-pression de turbomachine dont le dernier étage comprend 98 aubes mobiles, il peut être prévu 14 segments de bague 24a qui s'étendent donc chacun sur 25°.For example, for a turbomachine low-pressure turbine whose last stage comprises 98 blades, it can be provided 14 ring segments 24a which therefore each extend over 25 °.

Pour permettre leur montage dans la rainure 18 du disque 6, chaque segment de bague 24a comprend des échancrures 26 qui sont ouvertes vers l'extérieur. Comme illustré par la figure 2A, ces échancrures sont dimensionnées pour permettre le passage des becquets 20 des pieds d'aubes 4a lors du montage de la bague de retenue dans la rainure du disque. Dans cette position, les segments de bague ne sont donc pas maintenus à l'extérieur dans les encoches 22 des pieds d'aubes.To allow their mounting in the groove 18 of the disk 6, each ring segment 24a comprises notches 26 which are open towards the outside. As illustrated by Figure 2A these notches are dimensioned to allow the passage of the spoilers 20 of the blade roots 4a when mounting the retaining ring in the groove of the disc. In this position, the ring segments are not maintained outside in the notches 22 of the blade roots.

Encore à titre d'exemple, lorsque le disque de rotor 6 comprend 98 aubes mobiles 4 et que la bague de retenue 24 est constituée de 14 segments 24a, le nombre d'échancrures 26 par segment peut être de 7.Still for example, when the rotor disc 6 comprises 98 blades 4 and the retaining ring 24 consists of 14 segments 24a, the number of notches 26 per segment can be 7.

Une fois montées dans la rainure 18 du disque, les segments de bague 24a sont pivotés autour de l'axe longitudinal X-X de la turbomachine de façon à ce que les becquets 20 des pieds d'aubes ne soient plus disposés en regard des échancrures 26 (figure 2B). Dans cette position, les segments de bague sont alors maintenus à l'extérieur dans les encoches des pieds d'aubes.Once mounted in the groove 18 of the disc, the ring segments 24a are pivoted about the longitudinal axis XX of the turbomachine so that the spoilers 20 of the blade roots are no longer arranged opposite the notches 26 ( Figure 2B ). In this position, the ring segments are then held outside in the notches of the blade roots.

Toujours à titre d'exemple, lorsque le disque de rotor 6 comprend 98 aubes mobiles 4 et que la bague de retenue 24 est constituée de 14 segments 24a, chaque segment ayant 7 échancrures 26, une rotation (dans un sens ou dans l'autre) de 1,8° de la bague de retenue permet de passer de la position de la figure 2A à la position de la figure 2B.Still as an example, when the rotor disc 6 comprises 98 blades 4 and the retaining ring 24 consists of 14 segments 24a, each segment having 7 notches 26, a rotation (in one direction or the other ) 1.8 ° of the retaining ring allows to move from the position of the Figure 2A at the position of the Figure 2B .

Bien entendu, le démontage de la bague de retenue s'effectue de la même manière en pivotant celle-ci d'un angle suffisant pour faire en sorte que les becquets des pieds d'aubes soient à nouveau disposés en regard des échancrures des segments de bague.Of course, the disassembly of the retaining ring is performed in the same manner by pivoting the latter by an angle sufficient to ensure that the spoilers of the blade roots are again arranged opposite the notches of the segments of the Ring.

Selon une disposition avantageuse de l'invention, au moins l'un des segments de bague 24a comprend une languette pliable 28 qui est apte à être rabattue entre deux becquets adjacents 20 de pieds d'aubes 4a pour arrêter la rotation de la bague de retenue dans la rainure 18 du disque de rotor 6 une fois que celle-ci est correctement positionnée (figure 2B).According to an advantageous arrangement of the invention, at least one of the ring segments 24a comprises a foldable tongue 28 which is adapted to be folded between two adjacent spoilers 20 of blade roots 4a to stop the rotation of the retaining ring. in the groove 18 of the rotor disk 6 once it is correctly positioned ( Figure 2B ).

Ainsi, dans l'exemple de réalisation des figures 2A et 2B, la languette 28 est disposée au niveau de l'une des échancrures 26 du segment de bague 24a et est apte par pliage à prendre deux positions extrêmes : une position dans laquelle elle s'étend dans un plan incliné par rapport au plan radial du segment de bague afin de permettre une rotation dudit segment (figure 2A), et une autre position dans laquelle elle est disposée dans le même plan radial que les becquets 20 des pieds d'aubes et s'étend circonférentiellement entre deux becquets adjacents 20 afin de bloquer en rotation ledit segment et donc l'ensemble de la bague de retenue (figure 2B).Thus, in the exemplary embodiment of Figures 2A and 2B , the tongue 28 is disposed at one of the indentations 26 of the ring segment 24a and is bendable to take two extreme positions: a position in which it extends in a plane inclined with respect to the radial plane of the segment ring to allow rotation of said segment ( Figure 2A ), and another position in which it is arranged in the same radial plane as the spoilers 20 of the blade roots and extends circumferentially between two adjacent spoilers 20 in order to lock in rotation said segment and therefore the entire ring restraint ( Figure 2B ).

Il est à noter qu'il n'est pas nécessaire que tous les segments de bague soient équipés d'une telle languette, une seule languette pour l'ensemble des segments pouvant suffire à bloquer en rotation ladite bague.It should be noted that it is not necessary for all the ring segments to be equipped with such a tongue, a single tongue for all the segments being sufficient to lock said ring in rotation.

Selon une autre disposition avantageuse de l'invention, au moins l'un des segments de bague 24a possède une masse plus importante que les autres segments.According to another advantageous arrangement of the invention, at least one of the ring segments 24a has a larger mass than the other segments.

Une telle disposition permet de corriger aisément le phénomène de balourd observé dans une turbine basse-pression. En effet, comme la bague de retenue 24 est segmentée, il est possible d'affecter à certains des segments de bague une masse individuelle qui est différente de celle des autres et ainsi faire en sorte que le centre de gravité du disque de rotor se retrouve bien sur l'axe longitudinal X-X de la turbomachine. Il est à noter que plus le nombre de segments de bague sera élevé, plus l'équilibrage des masses sur l'ensemble du disque pourra être précis.Such an arrangement makes it possible to easily correct the unbalance phenomenon observed in a low-pressure turbine. Indeed, as the retaining ring 24 is segmented, it is possible to assign to some of the ring segments an individual mass which is different from that of the others and thus ensure that the center of gravity of the rotor disc is found well on the longitudinal axis XX of the turbomachine. It should be noted that the higher the number of ring segments, the better the balance of the masses on the entire disk.

Cette disposition est particulièrement avantageuse lorsque, comme représenté sur la figure 1, l'espace annulaire entre l'extrémité interne du disque 6 du dernier étage de la turbine et le tourillon 10 ne permet pas d'avoir un accès direct aux liaisons boulonnées 8 de sorte qu'il est impossible de fixer des masses d'équilibrage sur ces liaisons boulonnées sans avoir à démonter au préalable le dernier étage de la turbine.This arrangement is particularly advantageous when, as represented on the figure 1 the annular space between the inner end of the disk 6 of the last stage of the turbine and the pin 10 does not allow direct access to the bolted connections 8 so that it is impossible to fix balancing masses on these bolted connections without first removing the last stage of the turbine.

En pratique, un contrôle d'équilibrage du disque de rotor est réalisé une fois la turbine assemblée et une correction de balourd est éventuellement appliquée. Lors de l'opération de correction de balourd, un ou plusieurs segments de bague sont remplacés par des segments de masse modifiée et adaptée à la correction nécessaire. Les segments de masse modifiée sont des segments de bague dont la masse est supérieure à celle des autres segments.In practice, a balancing control of the rotor disk is performed once the turbine assembly and an unbalance correction is optionally applied. During the unbalance correction operation, one or more ring segments are replaced by modified mass segments adapted to the required correction. The modified mass segments are ring segments whose mass is greater than that of the other segments.

Les figures 3A à 3C, qui représentent en coupe longitudinale différents variantes de réalisation du dispositif conforme à l'invention, illustrent diverses manières de faire varier la masse d'un segment de bague 24a.The FIGS. 3A to 3C , which represent in longitudinal section different alternative embodiments of the device according to the invention, illustrate various ways of varying the mass of a ring segment 24a.

Ainsi, sur l'exemple de réalisation de la figure 3B, le segment de bague 24a présente une surépaisseur 30 par rapport au segment représenté à la figure 3A. En plus d'une telle surépaisseur, le segment de bague 24a de la figure 3C présente un bossage 32 qui n'est présent ni sur le segment de bague de la figure 3A ni sur celui de la figure 3B. Cette surépaisseur 30 et ce bossage 32 peuvent s'étendre circonférentiellement sur toute ou partie seulement du segment de bague. Ils correspondent à des ajouts de masse.So, on the embodiment of the figure 3B , the ring segment 24a has an excess thickness 30 with respect to the segment shown in FIG. figure 3A . In addition to such an extra thickness, the ring segment 24a of the figure 3C has a boss 32 which is present neither on the ring segment of the figure 3A nor on that of the figure 3B . This extra thickness 30 and this boss 32 may extend circumferentially over all or only part of the ring segment. They correspond to mass additions.

D'autres manières de faire varier la masse des segments de bague sont encore possibles. Ainsi, la profondeur des échancrures 26, de même que la hauteur et/ou l'épaisseur des zones inter-échancrures peuvent varier afin d'augmenter ou de diminuer la masse des segments de bague.Other ways of varying the mass of the ring segments are still possible. Thus, the depth of the indentations 26, as well as the height and / or the thickness of the inter-indent regions may vary in order to increase or decrease the mass of the ring segments.

Il est à noter que les segments de bague peuvent être usinés au préalable avec des classes de gamme (par exemple de gramme en gramme) pour offrir un large choix de segment adapté à la correction de balourd nécessaire. Alternativement, les segments de bague peuvent être usinés à la demande.It should be noted that the ring segments can be pre-machined with range classes (for example from gram to gram) to provide a wide choice of segments adapted to the unbalance correction required. Alternatively, the ring segments can be machined on demand.

Le dispositif de retenue axiale d'aubes selon l'invention présente de nombreux avantages. En particulier, celui-ci n'est constitué que d'une seule pièce principale (à savoir la bague de retenue) ce qui rend sa fabrication peu onéreuse et son montage/démontage contre la face d'appui du disque aisé. En outre, grâce à l'utilisation de segments de bague, il est possible de faire varier la masse de chacun de ces segments et ainsi de corriger aisément le phénomène de balourd observé avec ce type de technologie.The axial blade retainer according to the invention has many advantages. In particular, it consists of only one main piece (ie the retaining ring) which makes its inexpensive manufacture and assembly / disassembly against the bearing surface of the easy disc. In addition, through the use of ring segments, it is possible to vary the mass of each of these segments and thus easily correct the phenomenon of unbalance observed with this type of technology.

Claims (5)

Dispositif de retenue axiale d'aubes montées sur un disque de rotor de turbomachine, comprenant : un disque de rotor (6) comprenant ; à sa périphérie, une pluralité d'alvéoles (12) sensiblement axiales et ouvertes vers l'extérieur ; et au niveau d'une face radiale d'appui (14), une bride (16) s'étendant radialement vers l'extérieur pour délimiter avec ladite face d'appui une rainure annulaire (18) ouverte vers l'extérieur ; une pluralité d'aubes (4) comprenant chacune un pied (4a) monté dans une alvéole correspondante du disque de rotor, chaque pied d'aube étant muni au niveau d'une face radiale d'appui correspondant à celle du disque de rotor d'au moins un becquet (20) s'étendant radialement vers l'intérieur pour délimiter avec ladite face d'appui une encoche annulaire (22) ouverte vers l'intérieur ; et caractérisé en ce qu'il comporte en outre une bague de retenue (24) montée contre la face d'appui (14) du disque de rotor et des pieds des aubes, ladite bague de retenue étant logée dans la rainure (18) du disque, maintenue à l'extérieur dans les encoches (22) des pieds des aubes, et constituée d'une pluralité de segments angulaires (24a) mis bout à bout, la masse d'au moins l'un des segments de la bague de retenue étant plus importante que celle des autres. An axial retention device for vanes mounted on a turbomachine rotor disk, comprising: a rotor disk (6) comprising; at its periphery, a plurality of cells (12) substantially axial and open towards the outside; and at a radial bearing face (14), a flange (16) extending radially outwards for delimiting with said bearing face an annular groove (18) open towards the outside; a plurality of vanes (4) each comprising a foot (4a) mounted in a corresponding cell of the rotor disc, each blade root being provided at a radial bearing face corresponding to that of the rotor disk; at least one spoiler (20) extending radially inwardly to define with said bearing face an annular notch (22) open towards the inside; and characterized in that it further comprises a retaining ring (24) mounted against the bearing face (14) of the rotor disk and the blade roots, said retaining ring being housed in the groove (18) of the disk , held outside in the notches (22) of the blade roots, and consisting of a plurality of angular segments (24a) placed end to end, the mass of at least one of the segments of the retaining ring being more important than the others. Dispositif selon la revendication 1, dans lequel chaque segment (24a) de la bague de retenue comprend des échancrures (26) ouvertes vers l'extérieur pour permettre le passage des becquets (20) des pieds d'aubes (4a) lors du montage de la bague de retenue (24) dans la rainure (18) du disque de rotor.Device according to claim 1, wherein each segment (24a) of the retaining ring comprises notches (26) open outwards to allow the passage of the spoilers (20) of the blade roots (4a) during assembly of the retaining ring (24) in the groove (18) of the rotor disc. Dispositif selon l'une des revendications 1 et 2, dans lequel la bague de retenue (24) comprend des moyens (28) pour permettre d'arrêter sa rotation dans la rainure du disque de rotor.Device according to one of claims 1 and 2, wherein the retaining ring (24) comprises means (28) for allowing to stop its rotation in the groove of the rotor disk. Dispositif selon la revendication 3, dans lequel au moins l'un des segments (24a) de la bague de retenue comprend une languette pliable (28) qui est apte à être rabattue entre deux becquets adjacents (20) de pieds d'aubes (4a) pour arrêter la rotation de la bague de retenue (24) dans la rainure (18) du disque de rotor.Device according to claim 3, wherein at least one of the segments (24a) of the retaining ring comprises a tongue collapsible (28) which is adapted to be folded between two adjacent spoilers (20) of blade roots (4a) to stop the rotation of the retaining ring (24) in the groove (18) of the rotor disc. Turbomachine caractérisée en ce qu'elle comporte au moins un dispositif de retenue axiale d'aubes montées sur un disque de rotor selon l'une quelconque des revendications 1 à 4.Turbomachine characterized in that it comprises at least one axial retaining device for blades mounted on a rotor disc according to any one of claims 1 to 4.
EP08158843A 2007-06-27 2008-06-24 Device for axial retention of vanes mounted on a turbomachine rotor disc Active EP2009244B1 (en)

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FR0756062A FR2918106B1 (en) 2007-06-27 2007-06-27 AXIS RETAINING DEVICE OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISC.

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933442A1 (en) * 2008-07-04 2010-01-08 Snecma Flange for maintaining blade retainer ring of rotor disk of low pressure gas turbine engine, has intermediate part comprising wider portion towards fixing edge and radial upstream portion connected to edge and wider portion

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010015404B4 (en) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Method for repairing a rotor assembly of a turbomachine, ring element for a rotor assembly of a turbomachine and rotor assembly for a turbomachine
US8936440B2 (en) 2011-05-26 2015-01-20 United Technologies Corporation Hybrid rotor disk assembly with ceramic matrix composites platform for a gas turbine engine
US8834125B2 (en) 2011-05-26 2014-09-16 United Technologies Corporation Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine
US8851853B2 (en) * 2011-05-26 2014-10-07 United Technologies Corporation Hybrid rotor disk assembly for a gas turbine engine
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
US8979502B2 (en) * 2011-12-15 2015-03-17 Pratt & Whitney Canada Corp. Turbine rotor retaining system
FR2988128A1 (en) * 2012-03-19 2013-09-20 Alstom Technology Ltd TURBINE ROTOR FOR A THERMOELECTRIC POWER PLANT
US9803485B2 (en) 2013-03-05 2017-10-31 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
GB2506712B (en) * 2013-05-14 2018-05-02 Rolls Royce Plc Balancing method
US9624775B2 (en) * 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing
US10392951B2 (en) 2014-10-02 2019-08-27 United Technologies Corporation Vane assembly with trapped segmented vane structures
JP2017028674A (en) * 2016-02-12 2017-02-02 Ｎｅｃプラットフォームズ株式会社 Management device, management method and management program
US10724384B2 (en) 2016-09-01 2020-07-28 Raytheon Technologies Corporation Intermittent tab configuration for retaining ring retention
US10415401B2 (en) 2016-09-08 2019-09-17 United Technologies Corporation Airfoil retention assembly for a gas turbine engine
IT201600130088A1 (en) 2016-12-22 2018-06-22 Nuovo Pignone Tecnologie Srl Turbine blade and fastening set
CN108808905B (en) * 2017-05-04 2020-07-28 东元电机股份有限公司 Method for producing a segmented rotor structure
US10458244B2 (en) 2017-10-18 2019-10-29 United Technologies Corporation Tuned retention ring for rotor disk
FR3082232B1 (en) * 2018-06-12 2020-08-28 Safran Aircraft Engines HOLDING SYSTEM FOR DISMANTLING A BLADE WHEEL
IT201900014739A1 (en) * 2019-08-13 2021-02-13 Ge Avio Srl Elements for retaining blades for turbomachinery.

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
US4648799A (en) * 1981-09-22 1987-03-10 Westinghouse Electric Corp. Cooled combustion turbine blade with retrofit blade seal
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
EP1180580A1 (en) 2000-08-10 2002-02-20 Snecma Moteurs Device for mounting an annular flask at a radial side of a bladed rotor
EP1498579A1 (en) 2003-07-17 2005-01-19 Snecma Moteurs Retaining device for mounting a flask onto a rotor
EP1703081A1 (en) * 2005-02-23 2006-09-20 Rolls-Royce Plc Side plate
WO2007014543A1 (en) * 2005-07-30 2007-02-08 Mtu Aero Engines Gmbh Securing element for fastening moving blades
US20080008593A1 (en) * 2006-07-06 2008-01-10 Siemens Power Generation, Inc. Turbine blade self locking seal plate system

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
GB1479332A (en) * 1974-11-06 1977-07-13 Rolls Royce Means for retaining blades to a disc or like structure
FR2524933B1 (en) * 1982-04-13 1987-02-20 Snecma AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES
US4645425A (en) * 1984-12-19 1987-02-24 United Technologies Corporation Turbine or compressor blade mounting
FR2603333B1 (en) * 1986-09-03 1990-07-20 Snecma TURBOMACHINE ROTOR COMPRISING A MEANS OF AXIAL LOCKING AND SEALING OF BLADES MOUNTED IN AXIAL PINS OF THE DISC AND MOUNTING METHOD
FR2663997B1 (en) * 1990-06-27 1993-12-24 Snecma DEVICE FOR FIXING A REVOLUTION CROWN ON A TURBOMACHINE DISC.
US5244348A (en) * 1991-12-18 1993-09-14 Brunswick Corporation Propeller drive sleeve
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
GB9302064D0 (en) * 1993-02-03 1993-03-24 Rolls Royce Plc Balanced rotor
FR2728299B1 (en) * 1994-12-14 1997-01-24 Snecma DEVICE FOR AXIAL FIXING OF TURBO-SPINDLE ROTOR BLADES
US6951448B2 (en) * 2002-04-16 2005-10-04 United Technologies Corporation Axial retention system and components thereof for a bladed rotor
RU2238412C1 (en) * 2003-04-28 2004-10-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Turbine wheel
FR2861128B1 (en) * 2003-10-16 2007-06-08 Snecma Moteurs DEVICE FOR ATTACHING A MOBILE DARK TO A TURBINE ROTOR DISK IN A TURBOMACHINE
ATE391835T1 (en) * 2004-07-22 2008-04-15 Siemens Ag SAFETY DEVICE FOR A ROTATING BLADE OF A FLOW MACHINE ARRANGED ON A ROTATING ROTOR DISC, FLOW MACHINE AND METHOD FOR MOUNTING AND DISASSEMBLING A ROTOR BLADE ON A ROTOR DISC OF A FLOW MACHINE
ES2321862T3 (en) * 2006-09-25 2009-06-12 Siemens Aktiengesellschaft TURBINE ROTOR WITH LOCK PLATES AND CORRESPONDING ASSEMBLY PROCEDURE.
US8128371B2 (en) * 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
US4648799A (en) * 1981-09-22 1987-03-10 Westinghouse Electric Corp. Cooled combustion turbine blade with retrofit blade seal
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
EP1180580A1 (en) 2000-08-10 2002-02-20 Snecma Moteurs Device for mounting an annular flask at a radial side of a bladed rotor
EP1498579A1 (en) 2003-07-17 2005-01-19 Snecma Moteurs Retaining device for mounting a flask onto a rotor
EP1703081A1 (en) * 2005-02-23 2006-09-20 Rolls-Royce Plc Side plate
WO2007014543A1 (en) * 2005-07-30 2007-02-08 Mtu Aero Engines Gmbh Securing element for fastening moving blades
US20080008593A1 (en) * 2006-07-06 2008-01-10 Siemens Power Generation, Inc. Turbine blade self locking seal plate system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933442A1 (en) * 2008-07-04 2010-01-08 Snecma Flange for maintaining blade retainer ring of rotor disk of low pressure gas turbine engine, has intermediate part comprising wider portion towards fixing edge and radial upstream portion connected to edge and wider portion

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EP2009244B1 (en) 2010-08-11
US20090004018A1 (en) 2009-01-01
FR2918106A1 (en) 2009-01-02
CN101333942A (en) 2008-12-31
US8348620B2 (en) 2013-01-08
CN101333942B (en) 2013-07-24
CA2635635C (en) 2013-01-22
RU2008126092A (en) 2010-01-10
RU2471999C2 (en) 2013-01-10
FR2918106B1 (en) 2011-05-06
DE602008002103D1 (en) 2010-09-23
JP2009008085A (en) 2009-01-15
CA2635635A1 (en) 2008-12-27
JP5306721B2 (en) 2013-10-02

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