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EP2366061B1 - Turbine wheel with an axial retention system for vanes - Google Patents

Turbine wheel with an axial retention system for vanes Download PDF

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Publication number
EP2366061B1
EP2366061B1 EP09803867.2A EP09803867A EP2366061B1 EP 2366061 B1 EP2366061 B1 EP 2366061B1 EP 09803867 A EP09803867 A EP 09803867A EP 2366061 B1 EP2366061 B1 EP 2366061B1
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EP
European Patent Office
Prior art keywords
disk
blades
turbine wheel
wheel according
teeth
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.)
Active
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EP09803867.2A
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German (de)
French (fr)
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EP2366061A1 (en
Inventor
Jean-Baptiste Arilla
Michel Beaucoueste
Denis Chanteloup
Michel Clastre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Publication date
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Priority to PL09803867T priority Critical patent/PL2366061T3/en
Publication of EP2366061A1 publication Critical patent/EP2366061A1/en
Application granted granted Critical
Publication of EP2366061B1 publication Critical patent/EP2366061B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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 invention relates generally to turbine wheels in gas turbines and more particularly to the axial retention of vanes carried by the wheels.
  • the field of application of the invention is in particular that of industrial gas turbines and aeronautical gas turbine engines.
  • the blades are mounted on the periphery of a disk, each blade having a blade with a foot secured to a fastener axially engaged in a housing or cell opening at the periphery of the disk and extending between two opposite sides of the disc.
  • Axial retention devices for the vanes are necessary to avoid axial displacement due to vibration or thermal effects despite the pressure generated by the centrifugal force between the contacting surface portions of the blade attachments and disk housings.
  • the axial support between a blade and a corresponding tooth of the disk is positioned substantially at the extrados of the blade under the blade root.
  • the retaining flange exerts an axial lateral support on lateral faces of the teeth of the disc or of the blade attachments.
  • the retaining flange advantageously has a limited radial dimension to abut only in the lower part of the teeth of the disc or the blade attachments.
  • the axial support between the blades and the rotor and the maintenance of this axial support can be advantageously provided without consumption of the radial clearance between the rotor and an adjacent stator.
  • the retaining flange may be supported on the lateral faces of the teeth of the disc or the fasteners of the blades with prestressing.
  • the retaining flange may be mounted on the rotor being immobilized axially by a retaining ring.
  • At least one opening forming a viewing window is formed in the rotor to allow a visual control of the positioning of the retaining ring.
  • the invention further relates to a turbomachine comprising a turbine wheel according to the invention.
  • the figure 1 shows a turbine rotor 10, for example a high-pressure turbine rotor (HP) in a gas turbine engine.
  • the rotor 10 is secured to a disk 12 carrying at its periphery a plurality of blades 20.
  • the blades 20 each comprise a blade 22 which extends in the annular passage 30 for the gas flow through the turbine, which passage is delimited on the outer side by a turbine ring (not shown) adjacent to the apices of the blades.
  • Each blade 20 has its foot secured to a platform 24 carrying a fastener (or stagger) 26 by which the blade is connected to the disk 12.
  • the fastener has a profile in the form of "fir ".
  • the platforms 24 of the vanes delimit the passage 30 on the inner side.
  • the fasteners 26 are engaged axially in housings (or cells) 14 of corresponding shape distributed and opening at the periphery of the disc 10.
  • the housings 14 extend axially over the entire distance between the upstream (or front) side faces 12 a and downstream (or rear) 12 b of the disk and are separated from each other by teeth 16 of the disk.
  • the upstream and downstream terms are used herein with reference to the flow direction of the gas stream in the turbine.
  • One or more reliefs 28, for example two circumferentially aligned reliefs, may be formed on the lower face of the platform 24 of a blade 20 to bear against a stop 18 in the form of a rib.
  • a rib-shaped relief 28 formed on the lower face of the platform 24 of a blade 20 may bear against a plurality of stops 18 formed on a corresponding tooth 16 of the disk, for example two abutments 18 aligned circumferentially.
  • Fasteners 26 extend along the housing 14 and the upstream side faces 26 a and 26 b downstream of the fasteners are located substantially in the same planes as, respectively, the side faces 12 has upstream and downstream 12b at the periphery of the disc 12.
  • the trailing edge BF at the base of the blades 22 is not substantially cantilevered with respect to the fasteners 26 of the blades and an overload is not generated on the fasteners 26 on the downstream side .
  • a flange 40 On the upstream side, the axial retention of the blades is provided by a flange 40.
  • the flange 40 has teeth 42 which protrude and are supported laterally on the upstream side faces 26 are fasteners 26, without contact with the upstream side face 12a of the disk 12.
  • the flange 40 has a continuous peripheral rim 46 projecting which comes into lateral contact against the upstream side face 12a of the disk 12, to the teeth 16.
  • the mounting flange 40 can then be made with axial prestressing pressure to ensure bearing teeth 42 on the teeth 16 of the rotor.
  • axial dimensions of the fasteners 26 and teeth 16 are such that the upstream side, the fasteners 26 do not protrude out of the plane of the upstream face 12 a of the disc 12, to the teeth 16.
  • the retaining flange 40 has at its periphery an extra thickness 41 forming a cantilevered mass on the side opposite to that resting on the teeth 16 or fasteners 26. This avoids an opening of the flange at its peripheral portion with loss of support on the teeth 16 or fasteners 26 under the effect of the deformation induced by the rotation.
  • flange 40 on the rotor 10 with axial locking may be adopted, for example a bayonet mount.
  • axial retention means of the blades may be reversed, with stops formed on the upstream sides of the disc teeth cooperating with the ribs formed under the platforms of the blades and a retaining flange located on the downstream side exerting a bearing on the downstream lateral faces of the teeth or blade attachments.

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

Description

L'invention concerne d'une façon générale les roues de turbine dans des turbines à gaz et vise plus particulièrement la rétention axiale des aubes portées par les roues. Le domaine d'application de l'invention est notamment celui des turbines à gaz industrielles et des moteurs aéronautiques à turbine à gaz.The invention relates generally to turbine wheels in gas turbines and more particularly to the axial retention of vanes carried by the wheels. The field of application of the invention is in particular that of industrial gas turbines and aeronautical gas turbine engines.

Dans une roue de turbine, les aubes sont montées à la périphérie d'un disque, chaque aube ayant une pale avec un pied solidaire d'une attache engagée axialement dans un logement ou alvéole s'ouvrant à la périphérie du disque et s'étendant entre deux faces opposées du disque.In a turbine wheel, the blades are mounted on the periphery of a disk, each blade having a blade with a foot secured to a fastener axially engaged in a housing or cell opening at the periphery of the disk and extending between two opposite sides of the disc.

Des dispositifs de rétention axiale des aubes sont nécessaires pour éviter un déplacement axial dû aux vibrations ou effets thermiques en dépit de la pression engendrée par la force centrifuge entre les parties de surfaces en contact des attaches des aubes et des logements du disque.Axial retention devices for the vanes are necessary to avoid axial displacement due to vibration or thermal effects despite the pressure generated by the centrifugal force between the contacting surface portions of the blade attachments and disk housings.

Des dispositifs de rétention axiale connus notamment de US 4 086 757 , utilisent des flasques portés par le rotor et venant en appui sur des faces latérales amont (avant) et aval (arrière) des attaches des aubes. Il est connu aussi des documents WO 99/50534 et WO 99/30008 d'utiliser un seul flasque venant en appui sur les attaches des aubes du côté amont et, du côté aval, une butée circonférentielle continue formée sur le disque et venant en appui sur des reliefs formés sous les plates-formes des aubes du côté aval. Pour réduire l'encombrement, la largeur des attaches (en direction axiale) pourrait être diminuée par rapport à celle des logements, la face aval des attaches étant située en retrait de celle du disque. Mais le bord de fuite de la pale de l'aube se trouvant alors en porte-à-faux par rapport à l'attache, celle-ci serait soumise à des contraintes de flexion qui peuvent la fragiliser.Axial retention devices known in particular from US 4,086,757 , use flanges carried by the rotor and bearing on the upstream (forward) and downstream (rear) side faces of the blade attachments. It is also known documents WO 99/50534 and WO 99/30008 to use a single flange bearing on the fasteners of the blades on the upstream side and, on the downstream side, a continuous circumferential stop formed on the disk and bearing on reliefs formed under the platforms of the blades on the downstream side. To reduce the size, the width of the fasteners (in the axial direction) could be reduced compared to that of the housing, the downstream face of the fasteners being set back from that of the disk. But the trailing edge of the blade of the blade being then cantilever with respect to the fastener, it would be subjected to bending stresses that can weaken it.

L'invention a pour but de proposer une roue de turbine munie d'un système de rétention axiale des aubes qui présente un encombrement minimal sans induire de surcharge des attaches des aubes.The object of the invention is to propose a turbine wheel provided with an axial retention system for the blades which has a minimal bulk without inducing overloading of the blade fasteners.

Ce but est atteint grâce à une roue de turbine comprenant :

  • une pluralité d'aubes,
  • un rotor avec un disque ayant des faces latérales opposées et à la périphérie duquel sont montées les aubes, chaque aube ayant une pale avec un pied solidaire d'une plate-forme portant une attache ayant des faces latérales opposées et engagée dans un logement s'ouvrant à la périphérie du disque, les logements étant séparés les uns des autres par des parties du disque formant des dents, et
  • des dispositifs de retenue axiale des aubes sur le disque, la retenue axiale des aubes étant réalisée sur l'un, ou premier, des côtés amont et aval du disque au moyen d'un flasque de retenue et étant réalisée, sur l'autre ou deuxième côté du disque, par appui entre un relief qui fait saillie radialement à la périphérie du disque et un relief qui est formé sous les plates-formes des aubes,
dans laquelle les logements des attaches des aubes s'étendent axialement sur toute la distance entre les faces latérales des disques et, du deuxième côté du disque, la retenue axiale des aubes est assurée par appui axial entre les reliefs formés sous les plates-formes des aubes et des reliefs formés sur les dents du disque, et les faces latérales des attaches des aubes et du disque à sa périphérie sont situées sensiblement dans un même plan sur chaque côté du disque, caractérisé en ce que l'appui axial étant en retrait par rapport aux faces latérales des attaches situées du deuxième côté du disque.This goal is achieved through a turbine wheel comprising:
  • a plurality of blades,
  • a rotor with a disc having opposite side faces and at the periphery of which the vanes are mounted, each vane having a blade with a foot secured to a platform carrying a fastener having opposite side faces and engaged in a housing; opening at the periphery of the disc, the housings being separated from each other by portions of the disc forming teeth, and
  • axial retention devices of the vanes on the disc, the axial retention of the vanes being carried out on one or first of the upstream and downstream sides of the disc by means of a retaining flange and being carried out on the other or second side of the disk, by pressing between a relief which projects radially at the periphery of the disk and a relief which is formed under the platforms of the blades,
wherein the housing of the blade fasteners extend axially over the entire distance between the lateral faces of the discs and, on the second side of the disc, the axial retention of the blades is provided by axial support between the reliefs formed under the platforms of the blades and reliefs formed on the teeth of the disc, and the lateral faces of the attachments of the blades and the disc at its periphery are located substantially in the same plane on each side of the disc, characterized in that the axial support being recessed by relative to the lateral faces of the fasteners located on the second side of the disc.

Ainsi, avantageusement, l'encombrement axial est minimisé et le bord de fuite à la base de chaque pale peut ne pas se trouver sensiblement en porte-à-faux par rapport à l'attache de la pale.Thus, advantageously, the axial size is minimized and the trailing edge at the base of each blade may not be substantially cantilever with respect to the attachment of the blade.

De préférence, l'appui axial entre une aube et une dent correspondante du disque est positionné sensiblement au niveau de l'extrados de la pale sous le pied de pale.Preferably, the axial support between a blade and a corresponding tooth of the disk is positioned substantially at the extrados of the blade under the blade root.

De préférence, le flasque de retenue exerce un appui latéral axial sur des faces latérales des dents du disque ou des attaches des aubes. Le flasque de retenue a avantageusement une dimension radiale limitée pour venir en appui uniquement dans la partie inférieure des dents du disque ou des attaches des aubes.Preferably, the retaining flange exerts an axial lateral support on lateral faces of the teeth of the disc or of the blade attachments. The retaining flange advantageously has a limited radial dimension to abut only in the lower part of the teeth of the disc or the blade attachments.

L'appui axial entre aubes et rotor et le maintien de cet appui axial peuvent être avantageusement assurés sans consommation du jeu radial entre le rotor et un stator adjacent.The axial support between the blades and the rotor and the maintenance of this axial support can be advantageously provided without consumption of the radial clearance between the rotor and an adjacent stator.

Avantageusement, le flasque de retenue présente à sa périphérie une surépaisseur formant une masse en porte-à-faux. Une ouverture du flasque entraînant une perte d'appui de celui-ci peut ainsi être évitée lors de la rotation.Advantageously, the retaining flange has at its periphery an extra thickness forming a mass cantilever. A opening of the flange causing a loss of support thereof can thus be avoided during rotation.

Le flasque de retenue peut être en appui sur les faces latérales des dents du disque ou des attaches des aubes avec précontrainte.The retaining flange may be supported on the lateral faces of the teeth of the disc or the fasteners of the blades with prestressing.

Le flasque de retenue peut être monté sur le rotor en étant immobilisé axialement par un jonc de retenue.The retaining flange may be mounted on the rotor being immobilized axially by a retaining ring.

Avantageusement, au moins une ouverture formant fenêtre de visite est formée dans le rotor pour permettre un contrôle visuel du positionnement du jonc de retenue.Advantageously, at least one opening forming a viewing window is formed in the rotor to allow a visual control of the positioning of the retaining ring.

L'invention concerne en outre une turbomachine comportant une roue de turbine selon l'invention.The invention further relates to a turbomachine comprising a turbine wheel according to the invention.

L'invention sera mieux comprise à la lecture de la description faite ci-après en référence aux dessins annexés, sur lesquels :

  • la figure 1 est une vue partielle en demi-coupe axiale d'une roue de turbine selon un mode de réalisation de l'invention ;
  • la figure 2 est une vue en perspective d'une aube de la roue de la figure 1 ;
  • les figures 3 et 4 sont des vues partielles en perspective montrant le montage d'aubes dans le disque de la roue de turbine de la figure 1 ; et
  • les figures 5 et 6 illustrent schématiquement, en perspective, deux modes de réalisation du flasque de retenue de la roue de turbine de la figure 1.
The invention will be better understood on reading the description given hereinafter with reference to the appended drawings, in which:
  • the figure 1 is a partial view in axial half-section of a turbine wheel according to one embodiment of the invention;
  • the figure 2 is a perspective view of a dawn of the wheel of the figure 1 ;
  • the Figures 3 and 4 are partial perspective views showing the blade assembly in the disk of the turbine wheel of the figure 1 ; and
  • the figures 5 and 6 schematically illustrate, in perspective, two embodiments of the retaining flange of the turbine wheel of the figure 1 .

La figure 1 montre un rotor de turbine 10, par exemple un rotor de turbine haute-pression (HP) dans un moteur à turbine à gaz. Le rotor 10 est solidaire d'un disque 12 portant à sa périphérie une pluralité d'aubes 20.The figure 1 shows a turbine rotor 10, for example a high-pressure turbine rotor (HP) in a gas turbine engine. The rotor 10 is secured to a disk 12 carrying at its periphery a plurality of blades 20.

Les aubes 20 (voir aussi figures 2-4) comportent chacune une pale 22 qui s'étend dans le passage annulaire 30 pour le flux gazeux à travers la turbine, lequel passage est délimité du côté externe par un anneau de turbine (non représenté) adjacent aux sommets des pales.The blades 20 (see also Figures 2-4 ) each comprise a blade 22 which extends in the annular passage 30 for the gas flow through the turbine, which passage is delimited on the outer side by a turbine ring (not shown) adjacent to the apices of the blades.

Chaque aube 20 a son pied solidaire d'une plate-forme 24 portant une attache (ou échasse) 26 par laquelle l'aube est reliée au disque 12. Dans l'exemple illustré, l'attache a un profil en forme de "sapin". Les plates-formes 24 des aubes délimitent le passage 30 du côté interne.Each blade 20 has its foot secured to a platform 24 carrying a fastener (or stagger) 26 by which the blade is connected to the disk 12. In the example shown, the fastener has a profile in the form of "fir ". The platforms 24 of the vanes delimit the passage 30 on the inner side.

Les attaches 26 sont engagées axialement dans des logements (ou alvéoles) 14 de forme correspondante répartis et s'ouvrant à la périphérie du disque 10. Les logements 14 s'étendent axialement sur toute la distance entre les faces latérales amont (ou avant) 12a et aval (ou arrière) 12b du disque et sont séparés les uns des autres par des dents 16 du disque. Les termes amont et aval sont utilisés ici en référence à la direction d'écoulement du flux gazeux dans la turbine.The fasteners 26 are engaged axially in housings (or cells) 14 of corresponding shape distributed and opening at the periphery of the disc 10. The housings 14 extend axially over the entire distance between the upstream (or front) side faces 12 a and downstream (or rear) 12 b of the disk and are separated from each other by teeth 16 of the disk. The upstream and downstream terms are used herein with reference to the flow direction of the gas stream in the turbine.

Du côté aval, les aubes 20 sont retenues axialement par butée entre des reliefs 28 en forme de nervures formées sur les faces inférieures des plates-formes 24 et des butées ou taquets 18 en forme de nervures faisant saillie sur les côtés aval des dents 16 du disque. Les nervures 28 s'étendent circonférentiellement à partir d'une des faces longitudinales des attaches 26 et sont situées en retrait par rapport aux faces latérales aval des attaches 26. L'appui entre reliefs 28 et butées 18 est avantageusement positionné sensiblement au niveau de l'extrados des pales 22, sous les pieds de pales. Un ou plusieurs reliefs 28, par exemple deux reliefs alignés circonférentiellement, peuvent être formés sur la face inférieure de la plate-forme 24 d'une aube 20 pour venir en appui contre une butée 18 en forme de nervure. Egalement, un relief 28 en forme de nervure formée sur la face inférieure de la plate-forme 24 d'une aube 20 peut venir en appui contre plusieurs butées 18 formées sur une dent correspondante 16 du disque, par exemple deux butées 18 alignées circonférentiellement.On the downstream side, the blades 20 are retained axially by abutment between reliefs 28 in the form of ribs formed on the lower faces of the platforms 24 and abutments or cleats 18 in the form of ribs projecting from the downstream sides of the teeth 16 of the disk. The ribs 28 extend circumferentially from one of the longitudinal faces of the fasteners 26 and are set back from the downstream lateral faces of the fasteners 26. The support between reliefs 28 and abutments 18 is advantageously positioned substantially at the level of the extrados of the blades 22, under the feet of blades. One or more reliefs 28, for example two circumferentially aligned reliefs, may be formed on the lower face of the platform 24 of a blade 20 to bear against a stop 18 in the form of a rib. Also, a rib-shaped relief 28 formed on the lower face of the platform 24 of a blade 20 may bear against a plurality of stops 18 formed on a corresponding tooth 16 of the disk, for example two abutments 18 aligned circumferentially.

Comme le montrent les figures 3 et 4, les attaches 26 s'étendent tout le long des logements 14 et les faces latérales amont 26a et aval 26b des attaches sont situées sensiblement dans des mêmes plans que, respectivement, les faces latérales amont 12a et aval 12b à la périphérie du disque 12. Ainsi, le bord de fuite BF à la base des pales 22 ne se trouve sensiblement pas en porte-à-faux par rapport aux attaches 26 des pales et une surcharge n'est pas engendrée sur les attaches 26 du côté aval.As shown by Figures 3 and 4 , Fasteners 26 extend along the housing 14 and the upstream side faces 26 a and 26 b downstream of the fasteners are located substantially in the same planes as, respectively, the side faces 12 has upstream and downstream 12b at the periphery of the disc 12. Thus, the trailing edge BF at the base of the blades 22 is not substantially cantilevered with respect to the fasteners 26 of the blades and an overload is not generated on the fasteners 26 on the downstream side .

Du côté amont, la retenue axiale des aubes est assurée par un flasque 40. Dans le mode de réalisation de la figure 5, le flasque 40 présente des dents 42 qui font saillie et viennent en appui latéral sur les faces latérales amont 26a des attaches 26, sans contact avec la face latérale amont 12a du disque 12.On the upstream side, the axial retention of the blades is provided by a flange 40. In the embodiment of the figure 5 The flange 40 has teeth 42 which protrude and are supported laterally on the upstream side faces 26 are fasteners 26, without contact with the upstream side face 12a of the disk 12.

Dans le mode de réalisation de la figure 6, le flasque 40 présente un rebord périphérique continu 46 en saillie qui vient en appui latéral sur la face latérale amont 12a du disque 12 , au niveau des dents 16. Le montage du flasque 40 peut alors être réalisé avec précontrainte axiale pour garantir une pression d'appui des dents 42 sur les dents 16 du rotor. Bien entendu, les dimensions axiales des attaches 26 et des dents 16 sont telles que, du côté amont, les attaches 26 ne font pas saillie hors du plan de la face amont 12a du disque 12, au niveau des dents 16.In the embodiment of the figure 6 , The flange 40 has a continuous peripheral rim 46 projecting which comes into lateral contact against the upstream side face 12a of the disk 12, to the teeth 16. The mounting flange 40 can then be made with axial prestressing pressure to ensure bearing teeth 42 on the teeth 16 of the rotor. Of course, axial dimensions of the fasteners 26 and teeth 16 are such that the upstream side, the fasteners 26 do not protrude out of the plane of the upstream face 12 a of the disc 12, to the teeth 16.

Avantageusement, le flasque 40 vient en appui seulement sur la partie inférieure des dents 16 ou des attaches 26. La dimension radiale du flasque 40 est ainsi limitée, ce qui permet d'éviter un contact éventuel en service avec un stator 34 portant des pales 36 de distributeur en amont de la roue de turbine.Advantageously, the flange 40 bears only on the lower part of the teeth 16 or fasteners 26. The radial dimension of the flange 40 is thus limited, which makes it possible to avoid any possible contact in service with a stator 34 carrying blades 36 distributor upstream of the turbine wheel.

Ainsi, la réalisation de l'appui axial entre aubes 20 et disque 12 et le maintien de cet appui par le flasque 40 n'entraînent aucune consommation de jeu axial entre le disque et un stator adjacent du côté amont ou du côté aval, c'est-à-dire ne conditionnent pas la dimension de ce jeu axial.Thus, the achievement of the axial support between the blades 20 and disk 12 and the maintenance of this support by the flange 40 does not cause any axial clearance consumption between the disk and an adjacent stator on the upstream side or the downstream side, that is, do not condition the size of this axial clearance.

Avantageusement encore, le flasque de retenue 40 présente à sa périphérie une surépaisseur 41 formant une masse en porte-à-faux du côté opposé à celui en appui sur les dents 16 ou attaches 26. On évite ainsi une ouverture du flasque à sa partie périphérique avec perte de l'appui sur les dents 16 ou attaches 26 sous l'effet de la déformation induite par la rotation.Advantageously, the retaining flange 40 has at its periphery an extra thickness 41 forming a cantilevered mass on the side opposite to that resting on the teeth 16 or fasteners 26. This avoids an opening of the flange at its peripheral portion with loss of support on the teeth 16 or fasteners 26 under the effect of the deformation induced by the rotation.

Dans l'exemple illustré par la figure 1, le flasque de rétention axiale 40 est monté sur le rotor 10 en étant maintenu axialement par un anneau fendu ou jonc 44 qui est engagé dans une gorge annulaire 10a formée dans le rotor et dans une gorge annulaire 40a formée dans la face interne du flasque 40. Au montage, le jonc 44 est mis en place dans la gorge 10a et est escamoté dans celle-ci pour permettre le montage du flasque 40 à la presse. En service, les efforts centrifuges maintiennent le jonc 44 dans la gorge 40a du flasque, bloquant axialement celui-ci.In the example illustrated by the figure 1 The axial retention plate 40 is mounted on the rotor 10 while being axially retained by a split ring or ring 44 which is engaged in an annular groove 10a formed in the rotor and in an annular groove 40 formed in the inner face of flange 40. in assembly, the snap ring 44 is placed in the groove 10a and is retracted therein for mounting the end plate 40 to the press. In use, the centrifugal forces keep the ring 44 in the groove 40 of the flange, axially locking the latter.

Un ou plusieurs passages ou rainures constituant des fenêtres de visite 10b sont avantageusement formés radialement dans le rotor 10 pour déboucher d'une part sur une face radiale 10c du rotor et, d'autre part, au niveau de la gorge 10a. Les fenêtres de visite 10b permettent, éventuellement à l'aide d'un endoscope, de contrôler le positionnement correct du jonc 44.One or more passages or grooves 10 b constituting viewing windows are preferably formed radially in the rotor 10 to open the one hand a radial face 10 c of the rotor and, on the other hand, at the level of the groove 10 a. The windows of visit 10b allow, possibly using an endoscope, to control the correct positioning of the ring 44.

D'autres modes de montage du flasque 40 sur le rotor 10 avec blocage axial pourront être adoptés, par exemple un montage à baïonnette.Other mounting modes of the flange 40 on the rotor 10 with axial locking may be adopted, for example a bayonet mount.

Les dispositions de moyens de rétention axiale des aubes pourront être inversées, avec des butées formées sur les côtés amont des dents du disque coopérant avec les nervures formées sous les plates-formes des aubes et un flasque de rétention situé du côté aval exerçant un appui sur les faces latérales aval des dents ou des attaches des aubes.The arrangements of axial retention means of the blades may be reversed, with stops formed on the upstream sides of the disc teeth cooperating with the ribs formed under the platforms of the blades and a retaining flange located on the downstream side exerting a bearing on the downstream lateral faces of the teeth or blade attachments.

Claims (10)

  1. A turbine wheel comprising:
    • a plurality of blades (20);
    • a rotor (10) with a disk (12) having opposite side faces and having the blades mounted at its periphery, each blade having an airfoil (22) with a foot secured to a platform (24) carrying an attachment member (26) having opposite side faces and engaged in a housing (14) opening out into the periphery of the disk, the housings being separated from one another by portions of the disk that form teeth (16); and
    • axial retaining devices for retaining the blades on the disk, the blades being retained axially at a first one of the upstream and downstream faces of the disk by means of a retaining plate and being retained axially at the other or second side of the disk by a portion in relief that projects radially from the periphery of the disk and that presses against portions in relief (28) formed under the platforms of the blades;
    wherein the housings for the attachment members (26) of the blades extend axially over the entire distance between the opposite side faces of the disk (12), and at the second side of the disk, the blades are retained axially by the portions in relief (28) formed under the platforms of the blades pressing axially against portions in relief (18) formed on the teeth (16) of the disk, and the side faces of the attachment members (26) of the blades and of the disk (12) at the periphery thereof being situated substantially in a same plane on each side of the disk, characterized in that the axial pressure is set back relative to the side faces of the attachment members situated on the second side of the disk.
  2. A turbine wheel according to claim 1, characterized in that the retaining plate (40) exerts axial pressure against the side faces of the teeth (16) of the disk (12).
  3. A turbine wheel according to claim 1 or claim 2, characterized in that the retaining plate (40) exerts axial pressure against the side faces of the attachment members (26).
  4. A turbine wheel according to claim 2 or claim 3, characterized in that the retaining plate (40) presses against the teeth (16) of the disk or the attachment members (26) of the blades with prestress.
  5. A turbine wheel according to any one of claims 2 to 4, characterized in that the retaining plate (40) has a radial dimension that is limited so as to press only against the lower portions of the teeth (16) of the disk or of the attachment members (26) of the blades.
  6. A turbine wheel according to any one of claims 1 to 5, characterized in that the axial pressure between the blades (20) and the disk (12) is provided and maintained without encroaching on the axial clearance between the rotor (10) and an adjacent stator.
  7. A turbine wheel according to any one of claims 1 to 6, characterized in that the retaining plate (40) presents extra thickness (41) at its periphery, thereby forming a cantilevered-out mass.
  8. A turbine wheel according to any one of claims 1 to 7, characterized in that the retaining plate (40) is mounted on the rotor (10) by being prevented from moving axially by a retaining split ring (44).
  9. A turbine wheel according to claim 8, characterized in that at least one opening forming an inspection window (10b) is formed in the rotor (10) to enable the positioning of the retaining split ring (44) to be inspected visually.
  10. A turbomachine including a turbine wheel according to any one of claims 1 to 9.
EP09803867.2A 2008-12-17 2009-12-16 Turbine wheel with an axial retention system for vanes Active EP2366061B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09803867T PL2366061T3 (en) 2008-12-17 2009-12-16 Turbine wheel with an axial retention system for vanes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0858689A FR2939834B1 (en) 2008-12-17 2008-12-17 TURBINE WHEEL WITH AXIAL RETENTION SYSTEM OF AUBES
PCT/FR2009/052553 WO2010076493A1 (en) 2008-12-17 2009-12-16 Turbine wheel with an axial retention system for vanes

Publications (2)

Publication Number Publication Date
EP2366061A1 EP2366061A1 (en) 2011-09-21
EP2366061B1 true EP2366061B1 (en) 2017-03-22

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Application Number Title Priority Date Filing Date
EP09803867.2A Active EP2366061B1 (en) 2008-12-17 2009-12-16 Turbine wheel with an axial retention system for vanes

Country Status (11)

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US (1) US8721293B2 (en)
EP (1) EP2366061B1 (en)
JP (1) JP5497063B2 (en)
KR (1) KR101667827B1 (en)
CN (1) CN102257245B (en)
CA (1) CA2746979C (en)
ES (1) ES2622837T3 (en)
FR (1) FR2939834B1 (en)
PL (1) PL2366061T3 (en)
RU (1) RU2511915C2 (en)
WO (1) WO2010076493A1 (en)

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Also Published As

Publication number Publication date
KR20110102908A (en) 2011-09-19
CA2746979A1 (en) 2010-07-08
CN102257245A (en) 2011-11-23
EP2366061A1 (en) 2011-09-21
PL2366061T3 (en) 2017-07-31
RU2511915C2 (en) 2014-04-10
RU2011129609A (en) 2013-01-27
US20110250071A1 (en) 2011-10-13
CA2746979C (en) 2017-01-17
KR101667827B1 (en) 2016-10-19
FR2939834B1 (en) 2016-02-19
CN102257245B (en) 2014-07-16
JP2012512360A (en) 2012-05-31
ES2622837T3 (en) 2017-07-07
FR2939834A1 (en) 2010-06-18
US8721293B2 (en) 2014-05-13
JP5497063B2 (en) 2014-05-21
WO2010076493A1 (en) 2010-07-08

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