EP1970538B1 - Turbomachine rotor disc - Google Patents

Turbomachine rotor disc Download PDF

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Publication number
EP1970538B1
EP1970538B1 EP08152232A EP08152232A EP1970538B1 EP 1970538 B1 EP1970538 B1 EP 1970538B1 EP 08152232 A EP08152232 A EP 08152232A EP 08152232 A EP08152232 A EP 08152232A EP 1970538 B1 EP1970538 B1 EP 1970538B1
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EP
European Patent Office
Prior art keywords
disk
blade
roots
ribs
platforms
Prior art date
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Active
Application number
EP08152232A
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German (de)
French (fr)
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EP1970538A1 (en
Inventor
Olivier Belmonte
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP1970538A1 publication Critical patent/EP1970538A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • the present invention relates to a fan rotor disk of a turbomachine, such as an airplane turbojet engine.
  • a rotor disk is formed at its periphery with an alternation of cells and ribs and carries a plurality of blades, each formed of a blade connected to a foot engaged axially and radially retained in a cell of the disk. Platforms are fixed between the blades by means of radial flanges connected to corresponding radial flanges formed on the ribs of the disc.
  • the kinematics of mounting and dismounting of the platforms on the ribs of the disk requires the platform to translate on the rib so that the holes of the flanges of the platform are engaged with pins or rods provided on the ribs. flanges of the disc.
  • the lateral edges of the platforms must be sufficiently close to the blades of the blade to avoid parasitic air circulation to the disk.
  • the blades of a fan have a curved profile, which requires that the lateral edges of the platforms are also curved.
  • clearance is required between the edges of the platforms and the blades and induces air leaks to the disk. This game is particularly important at the axial ends of the platform.
  • the accumulation of blade / platform games on the entire disk causes a decrease in the efficiency of the turbomachine.
  • the invention aims in particular to provide a simple, economical and effective solution to these various problems.
  • turbomachine blower rotor disc having at its periphery blades whose feet are retained in disk cavities, and inter-blade platforms fixed on ribs delimited by the mounting cavities of the blades. blade roots, protective linings being mounted between the sides of the disc cavities and the blade roots, characterized in that the protective linings have a C-shaped section enabling them to be engaged in translation and to retain them radially on the flanges. ribs of the disk and constitute locking means of the platforms on the ribs of the disk.
  • the linings are used to protect the blade roots against friction on the inner walls of the cell.
  • the lining is usually made of a material having a greater wear resistance than the blade root and the disc.
  • EP 1 085 172 is considered the document describing the closest state of the art.
  • the linings exert an additional function by allowing the inter-blade platforms to be held radially in position on the ribs of the rotor disk by locking means.
  • the invention therefore reduces the clearance between the blade and the platform since the platform no longer has to be inserted axially, the locking being provided by the linings.
  • the lateral edges of the platform can thus perfectly correspond to the curvature of the blade of the blade.
  • the platforms on the disc comprise feet applied to the ribs of the disk, these feet being engaged and retained in cutouts or windows of the linings.
  • the packings can be moved in translation on the ribs between a release position and a position for retaining the feet of the platforms, and are immobilized in their retaining position by an annular piece mounted on the upstream face. of the disc for the axial retention of the blade roots in the cavities of the disc.
  • This locking system by translation of the protective lining allows mounting of the platform with a minimum of play on a rib of the disc.
  • the feet of the platforms comprise radial uprights and axial flanges extending upstream from the radial uprights.
  • the axial flanges are inside the protective lining and thus allow the platform to be held on the rib of the disk.
  • the cells and ribs of the disk, and the protective linings have a helical profile.
  • the blades of the moving blades are mounted in cavities of the disk which form an angle with the axis of the disk.
  • there is a disproportion of rib thicknesses ensuring the radial retention of the blades on each side of the blade root which is the source of premature wear of the feet of the blade. blades.
  • the use of helical profiles for the cavities and ribs of the disk allows to maintain constant thicknesses on each side of the blade roots over the entire length of the disk, the linings having a helical profile to be engaged on the ribs.
  • the platforms are advantageously mounted on the disk by radial translation.
  • the invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises a disk of the type described above.
  • the invention also relates to a protection pad for blade roots in a turbomachine, characterized in that it has a section C and comprises cutouts or windows formed in its wall connecting the wings of the C, these cuts allowing to engage and hold feet of an inter-blade platform.
  • the protective lining may have a helical profile.
  • FIG 1 represents a portion of a disk 10 of a turbine engine carrying a blade 12 according to the prior art.
  • the disk 10 comprises at its periphery an alternation of cells 14 and ribs 16 extending longitudinally over the entire length of the disk 10.
  • the blade 12 is formed by a blade 18 connected to a blade root 20 is engaged and held radially in a cavity 14 of the disk 10.
  • a platform 22 is positioned on a rib 16 of the disk 10, the edges 24 of the platform 22 being placed sufficiently close to the blade 18 of the adjoining blade 12 for avoid the air flows to the disc 10.
  • the platform 22 is fixed by radial flanges extending inwardly on radial flanges 26 extending outwardly of a rib 16 of the disc 10.
  • Stems 28 inserted in the flanges 26 of the disc 10 and the flanges of the platform 22 provide the radial retention of the platform 22 on the rib 16.
  • the kinematics of mounting and dismounting of the platform 22 requires that its flanges are engaged in the rods 28 by a displacement movement of the platform 22 along the median axis of the rib 16.
  • the blade 18 being bent, it is necessary to have a clearance between the edges 24 of the platform 22 and the blade 18 to allow movement along the median axis of the rib 16 of the platform 22.
  • This game is of the order of 3 mm and is most important at the axial ends of the platform 22. An air flow can thus take place between the platform 22 and the blade 12 reducing the performance of the turbomachine.
  • the invention makes it possible to reduce the clearance between the edges 24 of the platform and the blade 18 of the blade 12 by modifying the kinematics for mounting the platforms on the ribs 16 of the disk 10 and by using protective gaskets. to lock the platforms on the disk.
  • gaskets are used to protect the blade roots 20 engaged in the cells 14 against the friction thereof on the sides of the cavities 14 of the disc.
  • FIG 2 is schematically shown a protective lining 30 according to the invention, engaged in translation on a rib 16 of a disk 32 according to the invention of which only a portion is visible.
  • the protective lining 30 has a C-shaped transverse section enabling it to be axially engaged and retained radially on the rib 16.
  • the central portion 34 of the protective lining 30 extends over a portion of the rib 16 of the disk and is connected by substantially radial uprights 36 to the lateral edges 38 of the gasket 30 and extend over the entire length of the disk 32.
  • the lateral edges 38 disposed inside the cell 14, bear against a part of the rib and provide the radial retention of the protective lining 30.
  • the central portion 34 is substantially parallel to the outer peripheral surface of the rib 16 of the disk 32 and its axial ends 40 are substantially parallel to a plane perpendicular to the axis of the disk 32.
  • the protective lining 30 not only makes it possible to prevent the blade roots 20 from being damaged, but also to keep the platform on the rib 16 of the disk 32 by forming locking means for the platform. form.
  • the central portion 34 of the liner 30 comprises a window 42 and cutouts 40 at its axial ends.
  • FIG 3 there is shown a platform 44 according to the invention comprising radially inwardly extending legs 46 which are formed of radial uprights 48 and axial flanges 50.
  • the locking of a platform 44 placed on a rib 16 of the disc 32 is made by translationally inserting the protective lining 30 on a rib 16 of the disc 32.
  • the lining 30 is moved on the rib 16 of the disc 32 until at a position such that the feet 46 of the platform 44 can be inserted by radial translation along the arrow A in a cutout 40 and the window 42 of the protective lining 30.
  • the platform 44 shown in FIG. figure 3 comprises two feet 46 offset axially and which rest after insertion through the protective lining 30 on the rib 16 of the disc 32.
  • the protective lining 30 is then translated according to the arrow B on the rib 16 so that the axial flanges 50 are retained radially by the central portion 34 of the protective lining 30, which ensures a radial locking of the platform 44 on the disk 32.
  • the platform 44 undergoes the effect of the centrifugal force and performs a movement of radial displacement stopped by the axial flanges 50 which abut against the central portion 34 of the protective lining.
  • the radial insertion of the platform 44 allows the curvature of the edges of the platform 44 coincides perfectly with the curvature of the blade 18 and the clearance between the platform 44 and the blade 12 is reduced.
  • the lateral upstream ends of the lining 30 form projections 52 with respect to the upstream face of the disk 32 when the lining 30 is in the locking position of the platform 44. These projections 52 are intended to cooperate with a annular piece not shown, mounted on the upstream face of the disk 32 for the axial retention of the blade roots 20 and the protective liners 30.
  • the cells 14 and the ribs 16 and the protective liners 30 have a helical profile.
  • This profile makes it possible, in the case where the cells 14 make an angle with the axis of the disk 32, to keep a thickness e1 constant over the entire length of the disk 32 and substantially equal to the thickness e2 since the cells 14 and ribs 16 follow the cylindrical profile of the disc 32. This type of profile thus reduces the wear of the blade roots 20.
  • the protective lining 30 may also serve as a stop or be deformed to avoid contact between the platform 44 and the blade 12 disengaged which can lead to the ejection of the platform 44.
  • the protective liner 30 may comprise a variable number of cutouts 42 and openings according to the number of feet 46 required for the platform 44.
  • the protective seals are metallic and have a thickness of between 0.1 and a few millimeters.

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

Description

La présente invention concerne un disque de rotor de soufflante d'une turbomachine, telle qu'un turboréacteur d'avion.The present invention relates to a fan rotor disk of a turbomachine, such as an airplane turbojet engine.

Dans la technique connue, un disque de rotor est formé à sa périphérie avec une alternance d'alvéoles et de nervures et porte une pluralité d'aubes, chacune formée d'une pale raccordée à un pied engagé axialement et retenu radialement dans une alvéole du disque. Des plates-formes sont fixées entre les aubes par l'intermédiaire de brides radiales reliées à des brides radiales correspondantes formées sur les nervures du disque.In the known art, a rotor disk is formed at its periphery with an alternation of cells and ribs and carries a plurality of blades, each formed of a blade connected to a foot engaged axially and radially retained in a cell of the disk. Platforms are fixed between the blades by means of radial flanges connected to corresponding radial flanges formed on the ribs of the disc.

La cinématique de montage et démontage des plates-formes sur les nervures du disque impose que la plate-forme effectue une translation sur la nervure afin que des orifices des brides de la plate-forme viennent s'engager avec des pions ou tiges prévues sur les brides du disque.The kinematics of mounting and dismounting of the platforms on the ribs of the disk requires the platform to translate on the rib so that the holes of the flanges of the platform are engaged with pins or rods provided on the ribs. flanges of the disc.

Dans une turbomachine, les bords latéraux des plates-formes doivent être suffisamment proches des pales de l'aube afin d'éviter les circulations d'air parasites vers le disque. Les pales d'une soufflante ont un profil courbe, ce qui nécessite que les bords latéraux des plates-formes soient également courbes. Cependant, du fait de la cinématique de montage et de démontage, un jeu est nécessaire entre les bords des plates-formes et les pales et induit des fuites d'air vers le disque. Ce jeu est particulièrement important aux extrémités axiales de la plate-forme. Ainsi, le cumul des jeux aubes / plates-formes sur l'ensemble du disque entraîne une diminution du rendement de la turbomachine.In a turbomachine, the lateral edges of the platforms must be sufficiently close to the blades of the blade to avoid parasitic air circulation to the disk. The blades of a fan have a curved profile, which requires that the lateral edges of the platforms are also curved. However, because of the kinematics of assembly and disassembly, clearance is required between the edges of the platforms and the blades and induces air leaks to the disk. This game is particularly important at the axial ends of the platform. Thus, the accumulation of blade / platform games on the entire disk causes a decrease in the efficiency of the turbomachine.

Dans la technique antérieure, les solutions se sont focalisées sur la restauration de l'étanchéité entre la plate-forme et l'aube. Cependant ces techniques nécessitent l'incorporation de pièces supplémentaires, ce qui conduit à un alourdissement de la turbomachine.In the prior art, the solutions have focused on restoring the seal between the platform and the blade. However, these techniques require the incorporation of additional parts, which leads to an increase of the turbomachine.

L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces différents problèmes.The invention aims in particular to provide a simple, economical and effective solution to these various problems.

Elle propose à cet effet un disque de rotor de soufflante de turbomachine, comportant à sa périphérie des aubes dont les pieds sont retenus dans des alvéoles du disque, et des plates-formes inter-aubes fixées sur des nervures délimitées par les alvéoles de montage des pieds d'aubes, des garnitures de protection étant montées entre les flancs des alvéoles du disque et les pieds des aubes, caractérisé en ce que les garnitures de protection ont une section en C permettant de les engager en translation et de les retenir radialement sur les nervures du disque et constituent des moyens de verrouillage des plates-formes sur les nervures du disque.It proposes for this purpose a turbomachine blower rotor disc, having at its periphery blades whose feet are retained in disk cavities, and inter-blade platforms fixed on ribs delimited by the mounting cavities of the blades. blade roots, protective linings being mounted between the sides of the disc cavities and the blade roots, characterized in that the protective linings have a C-shaped section enabling them to be engaged in translation and to retain them radially on the flanges. ribs of the disk and constitute locking means of the platforms on the ribs of the disk.

Dans la technique connue, les garnitures sont utilisées pour protéger les pieds des aubes contre des frottements sur les parois internes de l'alvéole. La garniture est habituellement réalisée dans un matériau présentant une résistance à l'usure plus importante que le pied d'aube et que le disque.In the known art, the linings are used to protect the blade roots against friction on the inner walls of the cell. The lining is usually made of a material having a greater wear resistance than the blade root and the disc.

EP 1 085 172 est considéré comme le document décrivant l'état de la technique le plus proche. EP 1 085 172 is considered the document describing the closest state of the art.

Selon l'invention, les garnitures exercent une fonction supplémentaire en permettant de retenir radialement les plates-formes inter-aubes en position sur les nervures du disque de rotor par des moyens de verrouillage. L'invention permet donc de réduire le jeu entre l'aube et la plate-forme puisque la plate-forme n'a plus à être insérée axialement, le verrouillage étant assuré par les garnitures. Les bords latéraux de la plate-forme peuvent ainsi parfaitement correspondre à la courbure de la pale de l'aube.According to the invention, the linings exert an additional function by allowing the inter-blade platforms to be held radially in position on the ribs of the rotor disk by locking means. The invention therefore reduces the clearance between the blade and the platform since the platform no longer has to be inserted axially, the locking being provided by the linings. The lateral edges of the platform can thus perfectly correspond to the curvature of the blade of the blade.

Selon une autre caractéristique de l'invention, les plates-formes sur le disque comprennent des pieds appliqués sur les nervures du disque, ces pieds étant engagés et retenus dans des découpes ou fenêtres des garnitures.According to another characteristic of the invention, the platforms on the disc comprise feet applied to the ribs of the disk, these feet being engaged and retained in cutouts or windows of the linings.

Dans un mode de réalisation préféré, les garnitures sont déplaçables en translation sur les nervures entre une position de libération et une position de retenue des pieds des plates-formes, et sont immobilisées dans leur position de retenue par une pièce annulaire montée sur la face amont du disque pour la retenue axiale des pieds d'aubes dans les alvéoles du disque.In a preferred embodiment, the packings can be moved in translation on the ribs between a release position and a position for retaining the feet of the platforms, and are immobilized in their retaining position by an annular piece mounted on the upstream face. of the disc for the axial retention of the blade roots in the cavities of the disc.

Ce système de verrouillage par translation de la garniture de protection permet un montage de la plate-forme avec un minimum de jeu sur une nervure du disque.This locking system by translation of the protective lining allows mounting of the platform with a minimum of play on a rib of the disc.

Selon une autre caractéristique de l'invention, les pieds des plates-formes comprennent des montants radiaux et des rebords axiaux s'étendant vers l'amont depuis les montants radiaux. Lorsque la garniture de protection est en position de verrouillage, les rebords axiaux sont à l'intérieur de la garniture de protection et permettent ainsi le maintien de la plate-forme sur la nervure du disque.According to another characteristic of the invention, the feet of the platforms comprise radial uprights and axial flanges extending upstream from the radial uprights. When the protective lining is in the locking position, the axial flanges are inside the protective lining and thus allow the platform to be held on the rib of the disk.

Avantageusement, les alvéoles et nervures du disque, et les garnitures de protection ont un profil hélicoïdal.Advantageously, the cells and ribs of the disk, and the protective linings have a helical profile.

Dans certaines configurations de turbomachine, les pieds des aubes mobiles sont montés dans des alvéoles du disque qui forment un angle avec l'axe du disque. Ainsi, lorsque les aubes sont montées dans les alvéoles du disque, il existe une disproportion d'épaisseurs de nervure assurant la retenue radiale des aubes de chaque côté du pied d'aube ce qui est la source d'une usure prématurée des pieds d'aubes. L'utilisation de profils hélicoïdaux pour les alvéoles et nervures du disque permet de conserver des épaisseurs constantes de chaque côté des pieds d'aubes sur toute la longueur du disque, les garnitures ayant un profil hélicoïdal pour pouvoir être engagées sur les nervures.In certain turbomachine configurations, the blades of the moving blades are mounted in cavities of the disk which form an angle with the axis of the disk. Thus, when the blades are mounted in the cavities of the disk, there is a disproportion of rib thicknesses ensuring the radial retention of the blades on each side of the blade root which is the source of premature wear of the feet of the blade. blades. The use of helical profiles for the cavities and ribs of the disk allows to maintain constant thicknesses on each side of the blade roots over the entire length of the disk, the linings having a helical profile to be engaged on the ribs.

Les plates-formes sont avantageusement montées sur le disque par translation radiale.The platforms are advantageously mounted on the disk by radial translation.

L'invention concerne également une turbomachine, telle qu'un turboréacteur d'avion, caractérisée en ce qu'elle comprend un disque du type décrit ci-dessus.The invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises a disk of the type described above.

L'invention concerne encore une garniture de protection de pieds d'aube dans une turbomachine, caractérisée en ce qu'elle a une section en C et comprend des découpes ou fenêtres formées dans sa paroi reliant les ailes du C, ces découpes permettant d'y engager et d'y retenir des pieds d'une plate-forme inter-aubes. La garniture de protection peut avoir un profil hélicoïdal.The invention also relates to a protection pad for blade roots in a turbomachine, characterized in that it has a section C and comprises cutouts or windows formed in its wall connecting the wings of the C, these cuts allowing to engage and hold feet of an inter-blade platform. The protective lining may have a helical profile.

D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue partielle en perspective d'un disque portant une aube et une plate-forme selon la technique antérieure ;
  • la figure 2 est une vue schématique en perspective d'une garniture de protection engagée sur une nervure du disque selon l'invention ;
  • la figure 3 est une vue schématique de côté d'une plate-forme inter-aubes selon l'invention verrouillée sur une nervure du disque ;
  • la figure 4 est une vue schématique de gauche du disque de la figure 3.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial perspective view of a disc carrying a blade and a platform according to the prior art;
  • the figure 2 is a schematic perspective view of a protective lining engaged on a rib of the disk according to the invention;
  • the figure 3 is a schematic side view of an inter-blade platform according to the invention locked on a rib of the disc;
  • the figure 4 is a schematic left view of the disk of the figure 3 .

On se réfère tout d'abord à la figure 1 qui représente une partie d'un disque 10 d'une turbomachine portant une aube 12 selon la technique antérieure. Le disque 10 comprend à sa périphérie une alternance d'alvéoles 14 et de nervures 16 s'étendant longitudinalement sur toute la longueur du disque 10. L'aube mobile 12 formée d'une pale 18 raccordée à un pied d'aube 20 est engagée et retenue radialement dans une alvéole 14 du disque 10. Une plate-forme 22 est positionnée sur une nervure 16 du disque 10, les bords 24 de la plate-forme 22 étant placés suffisamment proche de la pale 18 de l'aube 12 attenante pour éviter les circulations d'air vers le disque 10. La plate-forme 22 est fixée par des brides radiales s'étendant vers l'intérieur sur des brides 26 radiales s'étendant vers l'extérieur d'une nervure 16 du disque 10. Des tiges 28 insérées dans les brides 26 du disque 10 et les brides de la plate-forme 22 assurent la retenue radiale de la plate-forme 22 sur la nervure 16. La cinématique de montage et de démontage de la plate-forme 22 impose que ses brides soient engagées dans les tiges 28 par un mouvement de déplacement de la plate-forme 22 selon l'axe médian de la nervure 16. Or la pale 18 étant courbée, il est nécessaire d'avoir un jeu entre les bords 24 de la plate-forme 22 et la pale 18 pour permettre le déplacement selon l'axe médian de la nervure 16 de la plate-forme 22. Ce jeu est de l'ordre de 3 mm et est le plus important aux extrémités axiales de la plate-forme 22. Une circulation d'air peut ainsi avoir lieu entre la plate-forme 22 et l'aube 12 réduisant les performances de la turbomachine.We first refer to the figure 1 which represents a portion of a disk 10 of a turbine engine carrying a blade 12 according to the prior art. The disk 10 comprises at its periphery an alternation of cells 14 and ribs 16 extending longitudinally over the entire length of the disk 10. The blade 12 is formed by a blade 18 connected to a blade root 20 is engaged and held radially in a cavity 14 of the disk 10. A platform 22 is positioned on a rib 16 of the disk 10, the edges 24 of the platform 22 being placed sufficiently close to the blade 18 of the adjoining blade 12 for avoid the air flows to the disc 10. The platform 22 is fixed by radial flanges extending inwardly on radial flanges 26 extending outwardly of a rib 16 of the disc 10. Stems 28 inserted in the flanges 26 of the disc 10 and the flanges of the platform 22 provide the radial retention of the platform 22 on the rib 16. The kinematics of mounting and dismounting of the platform 22 requires that its flanges are engaged in the rods 28 by a displacement movement of the platform 22 along the median axis of the rib 16. However, the blade 18 being bent, it is necessary to have a clearance between the edges 24 of the platform 22 and the blade 18 to allow movement along the median axis of the rib 16 of the platform 22. This game is of the order of 3 mm and is most important at the axial ends of the platform 22. An air flow can thus take place between the platform 22 and the blade 12 reducing the performance of the turbomachine.

L'invention permet de réduire le jeu entre les bords 24 de la plate-forme et la pale 18 de l'aube 12 en modifiant la cinématique de montage des plates-formes sur les nervures 16 du disque 10 et en utilisant des garnitures de protection pour verrouiller les plates-formes sur le disque.The invention makes it possible to reduce the clearance between the edges 24 of the platform and the blade 18 of the blade 12 by modifying the kinematics for mounting the platforms on the ribs 16 of the disk 10 and by using protective gaskets. to lock the platforms on the disk.

Dans la technique antérieure, on utilise des garnitures pour protéger les pieds d'aubes 20 engagés dans les alvéoles 14 contre les frottements de ceux-ci sur les flancs des alvéoles 14 du disque. L'interposition d'un élément tel qu'une garniture de protection entre la nervure 16 et le pied d'aube 20, dont la résistance à l'usure est plus faible que celles du pied d'aube 20 et du disque 10, permet de préserver le pied d'aube 20.In the prior art, gaskets are used to protect the blade roots 20 engaged in the cells 14 against the friction thereof on the sides of the cavities 14 of the disc. The interposition of an element such as a protective lining between the rib 16 and the blade root 20, whose wear resistance is lower than that of the blade root 20 and the disk 10, allows to preserve the dawn foot 20.

En figure 2 est représenté schématiquement une garniture de protection 30 selon l'invention, engagée en translation sur une nervure 16 d'un disque 32 selon l'invention dont seule une partie est visible. La garniture de protection 30 à une section transverse en forme de C lui permettant d'être engagée axialement et retenue radialement sur la nervure 16. La partie centrale 34 de la garniture de protection 30 s'étend sur une partie de la nervure 16 du disque et est raccordée par des montants 36 sensiblement radiaux aux bords 38 latéraux de la garniture 30 et s'étendent sur toute la longueur du disque 32. Les bords 38 latéraux disposés à l'intérieur de l'alvéole 14, sont en appui contre une partie de la nervure et assurent la retenue radiale de la garniture de protection 30. La partie centrale 34 est sensiblement parallèle à la surface externe périphérique de la nervure 16 du disque 32 et ses extrémités axiales 40 sont sensiblement parallèles à un plan perpendiculaire à l'axe du disque 32.In figure 2 is schematically shown a protective lining 30 according to the invention, engaged in translation on a rib 16 of a disk 32 according to the invention of which only a portion is visible. The protective lining 30 has a C-shaped transverse section enabling it to be axially engaged and retained radially on the rib 16. The central portion 34 of the protective lining 30 extends over a portion of the rib 16 of the disk and is connected by substantially radial uprights 36 to the lateral edges 38 of the gasket 30 and extend over the entire length of the disk 32. The lateral edges 38 disposed inside the cell 14, bear against a part of the rib and provide the radial retention of the protective lining 30. The central portion 34 is substantially parallel to the outer peripheral surface of the rib 16 of the disk 32 and its axial ends 40 are substantially parallel to a plane perpendicular to the axis of the disk 32.

La garniture de protection 30 selon l'invention permet non seulement d'éviter l'endommagement des pieds d'aubes 20, mais également de maintenir la plate-forme sur la nervure 16 du disque 32 en formant des moyens de verrouillage de la plate-forme. Pour cela, la partie centrale 34 de la garniture 30 comprend une fenêtre 42 et des découpes 40 à ses extrémités axiales.The protective lining 30 according to the invention not only makes it possible to prevent the blade roots 20 from being damaged, but also to keep the platform on the rib 16 of the disk 32 by forming locking means for the platform. form. For this, the central portion 34 of the liner 30 comprises a window 42 and cutouts 40 at its axial ends.

En figure 3 est représentée une plate-forme 44 selon l'invention comprenant des pieds 46 s'étendant radialement vers l'intérieur, lesquels sont formés de montants radiaux 48 et de rebords axiaux 50.In figure 3 there is shown a platform 44 according to the invention comprising radially inwardly extending legs 46 which are formed of radial uprights 48 and axial flanges 50.

Le verrouillage d'une plate-forme 44 posée sur une nervure 16 du disque 32 est réalisé en insérant par translation la garniture de protection 30 sur une nervure 16 du disque 32. La garniture 30 est déplacée sur la nervure 16 du disque 32 jusqu'à une position telle que les pieds 46 de la plate-forme 44 puissent être insérés par translation radiale selon la flèche A dans une découpe 40 et la fenêtre 42 de la garniture de protection 30. La plate-forme 44 représentée en figure 3 comprend deux pieds 46 décalés axialement et qui reposent après insertion à travers la garniture de protection 30 sur la nervure 16 du disque 32. La garniture de protection 30 est ensuite translatée selon la flèche B sur la nervure 16 de manière à ce que les rebords axiaux 50 soient retenus radialement par la partie centrale 34 de la garniture de protection 30, ce qui assure un verrouillage radial de la plate-forme 44 sur le disque 32. En effet, en fonctionnement, la plate-forme 44 subit l'effet de la force centrifuge et effectue un mouvement de déplacement radial stoppé par les rebords axiaux 50 qui viennent buter contre la partie centrale 34 de la garniture de protection.The locking of a platform 44 placed on a rib 16 of the disc 32 is made by translationally inserting the protective lining 30 on a rib 16 of the disc 32. The lining 30 is moved on the rib 16 of the disc 32 until at a position such that the feet 46 of the platform 44 can be inserted by radial translation along the arrow A in a cutout 40 and the window 42 of the protective lining 30. The platform 44 shown in FIG. figure 3 comprises two feet 46 offset axially and which rest after insertion through the protective lining 30 on the rib 16 of the disc 32. The protective lining 30 is then translated according to the arrow B on the rib 16 so that the axial flanges 50 are retained radially by the central portion 34 of the protective lining 30, which ensures a radial locking of the platform 44 on the disk 32. In effect, in operation, the platform 44 undergoes the effect of the centrifugal force and performs a movement of radial displacement stopped by the axial flanges 50 which abut against the central portion 34 of the protective lining.

L'insertion radiale de la plate-forme 44 permet que la courbure des bords de la plate-forme 44 coïncide parfaitement avec la courbure de la pale 18 et le jeu entre la plate-forme 44 et l'aube 12 est ainsi réduit.The radial insertion of the platform 44 allows the curvature of the edges of the platform 44 coincides perfectly with the curvature of the blade 18 and the clearance between the platform 44 and the blade 12 is reduced.

Dans le mode de réalisation de la garniture de protection 30 représenté aux dessins, les extrémités amont latérales de la garniture 30 forment des saillies 52 par rapport à la face amont du disque 32 lorsque la garniture 30 est en position de verrouillage de la plate-forme 44. Ces saillies 52 sont destinées à coopérer avec une pièce annulaire non représentée, montée sur la face amont du disque 32 pour la retenue axiale des pieds d'aubes 20 et des garnitures de protection 30.In the embodiment of the protective lining 30 shown in the drawings, the lateral upstream ends of the lining 30 form projections 52 with respect to the upstream face of the disk 32 when the lining 30 is in the locking position of the platform 44. These projections 52 are intended to cooperate with a annular piece not shown, mounted on the upstream face of the disk 32 for the axial retention of the blade roots 20 and the protective liners 30.

Dans un mode de réalisation préféré de l'invention représenté en figure 4, les alvéoles 14 et les nervures 16 ainsi que les garnitures de protection 30 ont un profil hélicoïdal. Ce profil permet dans le cas où les alvéoles 14 font un angle avec l'axe du disque 32 de conserver une épaisseur e1 constante sur toute la longueur du disque 32 et sensiblement égale à l'épaisseur e2 puisque les alvéoles 14 et nervures 16 suivent le profil cylindrique du disque 32. Ce type de profil permet ainsi de réduire l'usure des pieds d'aubes 20.In a preferred embodiment of the invention shown in figure 4 , the cells 14 and the ribs 16 and the protective liners 30 have a helical profile. This profile makes it possible, in the case where the cells 14 make an angle with the axis of the disk 32, to keep a thickness e1 constant over the entire length of the disk 32 and substantially equal to the thickness e2 since the cells 14 and ribs 16 follow the cylindrical profile of the disc 32. This type of profile thus reduces the wear of the blade roots 20.

En cas de perte d'aube, la garniture de protection 30 peut également servir de butée ou bien se déformer pour éviter le contact entre la plate-forme 44 et l'aube 12 désolidarisée qui peut conduire à l'éjection de la plate-forme 44.In case of dawn loss, the protective lining 30 may also serve as a stop or be deformed to avoid contact between the platform 44 and the blade 12 disengaged which can lead to the ejection of the platform 44.

La garniture de protection 30 peut comprendre un nombre variable de découpes 42 et d'ajours en fonction du nombre de pieds 46 requis pour la plate-forme 44.The protective liner 30 may comprise a variable number of cutouts 42 and openings according to the number of feet 46 required for the platform 44.

Les garnitures de protection sont métalliques et ont une épaisseur comprise entre 0,1 et quelques millimètres.The protective seals are metallic and have a thickness of between 0.1 and a few millimeters.

Claims (9)

  1. A turbomachine fan rotor disk (32) comprising, at its periphery, blades (12) having roots (20) that are retained in cavities (14) of the disk (32), protective liners (30) being mounted between the flanks of the cavities (14) of the disk (32) and the blade roots (20), the protective liners (30) have a C-shaped cross section so that they can be fitted translationally and retained radially on the ribs (16) of the disk (32), characterized in that the disk comprises inter-blade platforms (44) fixed to ribs (16) delimited by the cavities (14) in which the blade roots (20) are mounted, and said protective liners (30) form means of locking the platforms (44) onto the ribs (16) of the disk (32).
  2. The disk as claimed in claim 1, characterized in that the platforms (44) comprise roots (46) pressed against the ribs (16) of the disk (32), these roots (46) being engaged and retained in cutouts or openings (40, 42) in the liners.
  3. The disk as claimed in claim 2, characterized in that the liners (30) can be moved translationally on the ribs (16) between a position in which they free and a position in which they retain the roots (46) of the platforms (44) and are immobilized in their retaining position by an annular component mounted on the upstream face of the disk (32) for axially retaining the blade roots (20) in the cavities (14) of the disk (32).
  4. The disk as claimed in claim 2, characterized in that the roots (46) of the platforms (44) comprise radial uprights (48) and axial rims (50) extending in the upstream direction from the radial uprights (48).
  5. The disk as claimed in claim 1, characterized in that the cavities (14) and ribs (16) of the disk (32) and the protective liners (30) have a helicoidal profile.
  6. The disk as claimed in claim 1, characterized in that the platforms (44) are mounted on the disk (32) by radial translation.
  7. A turbomachine such as an airplane turbojet or turboprop engine and which comprises a fan rotor disk (32) as claimed in claim 1.
  8. A protective liner (30) for a blade root (20) in a fan, this liner has a C-shaped cross section and comprises cutouts or openings (40, 42) formed in its wall connecting the legs of the C, characterized in that these cutouts allow fitting and retaining of the roots of an inter-blade platform therein.
  9. The liner as claimed in claim 8, characterized in that the liner has a helicoidal profile.
EP08152232A 2007-03-16 2008-03-04 Turbomachine rotor disc Active EP1970538B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0701906A FR2913735B1 (en) 2007-03-16 2007-03-16 ROTOR DISC OF A TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP1970538A1 EP1970538A1 (en) 2008-09-17
EP1970538B1 true EP1970538B1 (en) 2010-05-19

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US (1) US8277188B2 (en)
EP (1) EP1970538B1 (en)
JP (1) JP5152755B2 (en)
CA (1) CA2625317C (en)
DE (1) DE602008001269D1 (en)
FR (1) FR2913735B1 (en)
RU (1) RU2487249C2 (en)

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US8277188B2 (en) 2012-10-02
US20080226457A1 (en) 2008-09-18
FR2913735A1 (en) 2008-09-19
FR2913735B1 (en) 2013-04-19
EP1970538A1 (en) 2008-09-17
RU2008109760A (en) 2009-09-20
DE602008001269D1 (en) 2010-07-01
CA2625317C (en) 2015-04-28
JP2008232146A (en) 2008-10-02
JP5152755B2 (en) 2013-02-27
CA2625317A1 (en) 2008-09-16
RU2487249C2 (en) 2013-07-10

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