EP1400698A1 - Axial positioning control of a compressor blade - Google Patents

Axial positioning control of a compressor blade Download PDF

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Publication number
EP1400698A1
EP1400698A1 EP03292280A EP03292280A EP1400698A1 EP 1400698 A1 EP1400698 A1 EP 1400698A1 EP 03292280 A EP03292280 A EP 03292280A EP 03292280 A EP03292280 A EP 03292280A EP 1400698 A1 EP1400698 A1 EP 1400698A1
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EP
European Patent Office
Prior art keywords
blade
upstream
disk
blades
flange
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.)
Granted
Application number
EP03292280A
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German (de)
French (fr)
Other versions
EP1400698B1 (en
Inventor
Alain Jacques Michel Bassot
Jean-Claude Bonny
Philippe Even
Pierre Antoine Lamothe
Alain Madec
Patrick Jean-Louis Reghezza
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Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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Publication date
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Publication of EP1400698A1 publication Critical patent/EP1400698A1/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
    • 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
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber

Definitions

  • the invention relates to a control system of the position axial of the removable vanes of a blower of the turbojet engine.
  • a fan rotor having a disk whose rim has a plurality of grooves substantially axial and regularly distributed angularly, a pluralities of removable vanes that extend radially outward to the periphery of said disk, each blade having a dawn foot housing in a groove, a flange downstream secured to said disk and against which the downstream faces of the blade roots are in abutment, and an upstream flange removable integral with said disk and for retaining the blade roots in the grooves.
  • the upstream face refers to the directed face towards the front of the engine and the downstream face designates that directed towards the rear.
  • the upstream flange of a fan rotor is generally removable to allow the replacement of a blade in case of damage. This can happen if foreign bodies are swallowed, such as particularly during the take-off and approach phases of the aircraft equipped with turbojets.
  • US 4,033,705 discloses an axial retention system of vanes which has at each end of a blade root a tenon which cooperates with two oblique mortises formed in the rim of the disc of part and else of the groove receiving this foot of dawn.
  • the studs provided on each disc face are retained radially by a ring secured to the disc.
  • This document provides between each end face of the foot dawn and adjacent tenon a sheet forming spring whose role is to immobilize the tenon radially when assembling the blades, before the setting up and fixing the retaining ring. These springs create a mounting game at each end of dawn as this is shown on Figure 7 of this document, which is not controlled.
  • US 5,282,720 provides for interposing between the retaining flanges and the ends of the blade roots, honeycomb elements intended for to absorb some of the energy if you eat birds. During ingestion, the honeycomb is gradually deformed and thus dissipates a part of the energy. Honeycomb elements must retain their integrity when mounting the flanges, so there is inevitably a axial clearance after assembly, and random axial displacement is possible in operation of the blower.
  • the object of the invention is to propose a fan rotor such described in the introduction in which the axial position of the blades is controlled by a simple and inexpensive device, without creating a problem for the assembly and disassembly of the blades in case of repair possible.
  • the flange upstream is equipped on its downstream face with elastic means intended to on the upstream faces of the blade roots, after assembly, sufficient efforts to prevent axial displacement of the blades during operation normal engine.
  • the fan rotor further comprises a shim interposed between each blade root and the bottom of the groove corresponding, this wedge comprising a radial heel bearing against the upstream face of said blade root, the elastic means are advantageously bearing against said heels.
  • Figure 1 shows an X-axis fan rotor 1 which has a disc 2 and a plurality of blades 3 regularly spaced angularly around the X axis which extend radially outwards at the periphery of the disc 2.
  • Each of the blades 3 has a foot blade 4 which is retained in a groove or cell 5 substantially axial formed in the rim of the disk 2.
  • the blade roots 4 have a shape in dovetail, and the grooves 5 have a complementary shape. Under the action of the centrifugal forces, when the fan is in operation, the blade roots 4 are retained in the grooves 5 by the radially outer walls of these grooves 5.
  • a shim 6 is disposed between the base of each blade root 4 and the bottom of the groove 5.
  • This shim 6 comprises, on the side of the upstream face 7 of the disc 2, a heel 8 which bears against the upstream face 9 of the foot 4 of the dawn 3.
  • the role of the hold 6 is to prevent the dawn 3 from falling into the groove 5, when stopping the blower and cash a portion of the energy during a shock on the blade of the dawn as a result of the ingestion of a foreign body for example or the rupture of a neighboring dawn.
  • downstream face 10 of the disk 2 On the downstream face 10 of the disk 2 is fixed a downstream flange, no shown in the drawings, against which the feet 4 of the blades 3 are in stop.
  • An upstream flange 12 is also provided on the upstream face 7 of the disk 2, whose role is to prevent the feet 4 of the blades 3 of to escape from the grooves 5 by sliding after mounting the rotor 1.
  • This upstream flange 12 is fixed on flanges of the disc 2 by screws, so that to allow its dismantling, in case of need of replacement of a dawn 3.
  • the upstream flange 12 has in front of each dawn foot 4 an orifice 15 which holds the drum 16 of a pin 17 in elastomer, this pin 17 having a head 18 of larger diameter than that of the orifice 15, and having a thickness at least equal to the set J.
  • the head 18 of the pin 17 is disposed on the downstream face 13 of the upstream flange 12, and this head 18 is compressed between the downstream face 13 of the upstream flange 12 and the upstream face of the heel 8 of the hold 6.
  • the pin 17 thus exerts elastic forces on the heel 8 in an axial direction.
  • the heel 8 is in support against the dawn foot 4 adjacent, it is permanently urged to the downstream flange, against which he is in abutment.
  • This simple arrangement allows you to control the axial play of the blades 3 and to prevent random axial displacement of the blades 3.
  • FIG. 4a and 4b show in perspective views of the pawn 17 and FIG. 5 shows in perspective the downstream face 13 of the upstream flange 12.
  • the pins 17 are obviously mounted on the upstream flange 12 before mounting it on disk 2.
  • Reference 20 designates an orifice formed in the upstream flange 12 and serving for fixing this last on flanges of disc 2 by means of screws. The tightening of these screws exerts on the heads 18 of the pins 17, a sufficient compressive force to prevent further axial displacement of the blades 3, depending the difference between the thicknesses of the heads 18 at rest and the mounting clearance J of origin. This compression effort may vary from one blade to another according to the manufacturing tolerances of blades 3 and pins 17.

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

Abstract

The fan rotor, comprising a disc (2) with equally-spaced axial grooves in its rim for blade roots (4) fitted between front (12) and rear disc flanges. The front disc, which is detachable, has an elastic element (17) for each blade (3) in the form of an elastomer peg fitted in a hole in the flange and pressing against the end (8) of a blade root retaining wedge (6).

Description

L'invention concerne un système de maítrise de la position axiale des aubes amovibles d'un soufflant du turboréacteur.The invention relates to a control system of the position axial of the removable vanes of a blower of the turbojet engine.

Elle concerne plus précisément un rotor de soufflante comportant un disque dont la jante comporte une pluralité de rainures sensiblement axiales et régulièrement réparties angulairement, une pluralités d'aubes amovibles qui s'étendent radialement vers l'extérieur à la périphérie dudit disque, chaque aube comportant un pied d'aube logeant dans une rainure, un flasque aval solidaire dudit disque et contre lequel les faces aval des pieds d'aube sont en butée, et un flasque amont amovible solidaire dudit disque et destiné à retenir les pieds d'aubes dans les rainures.It relates more specifically to a fan rotor having a disk whose rim has a plurality of grooves substantially axial and regularly distributed angularly, a pluralities of removable vanes that extend radially outward to the periphery of said disk, each blade having a dawn foot housing in a groove, a flange downstream secured to said disk and against which the downstream faces of the blade roots are in abutment, and an upstream flange removable integral with said disk and for retaining the blade roots in the grooves.

Dans le présent mémoire, la face amont désigne la face dirigée vers l'avant du moteur et la face aval désigne celle dirigée vers l'arrière.In this specification, the upstream face refers to the directed face towards the front of the engine and the downstream face designates that directed towards the rear.

Le flasque amont d'un rotor de soufflante est généralement amovible afin de permettre le remplacement d'un aube en cas d'avarie. Ceci peut se produire en cas d'ingestion de corps étrangers, tels que des oiseaux, notamment lors des phases de décollage et d'approche de l'aéronef équipé de turboréacteurs.The upstream flange of a fan rotor is generally removable to allow the replacement of a blade in case of damage. This can happen if foreign bodies are swallowed, such as particularly during the take-off and approach phases of the aircraft equipped with turbojets.

Pour des raisons de montage, l'assemblage des aubes sur le disque comporte un jeu axial. Le positionnement axial aléatoire des aubes de soufflante à l'intérieur de ce jeu, déséquilibre le rotor et génère des vibrations lors du fonctionnement. Ceci est d'autant plus important que les aubes de soufflante comporte des pales à grande corde.For reasons of assembly, the assembly of the blades on the disc has axial play. Random axial positioning of blades blower inside this game, imbalance the rotor and generate vibrations during operation. This is all the more important as the Blower vanes have large rope blades.

Les forces centrifuges considérables supportées par les pales des aubes en fonctionnement peuvent également entraíner un déplacement axial aléatoire des aubes à l'intérieur de ce jeu de montage.The considerable centrifugal forces supported by the blades blades in operation can also cause a random axial displacement of the blades inside this assembly set.

US 4,033,705 dévoile un système de retenue axial des aubes qui comporte à chaque extrémité d'un pied d'aube un tenon qui coopère avec deux mortaises obliques ménagées dans la jante du disque de part et d'autre de la rainure recevant ce pied d'aube. Les tenons prévus sur chaque face de disque sont retenus radialement par un anneau solidarisé au disque. Ce document prévoit entre chaque face d'extrémité du pied d'aube et le tenon adjacent une tôle formant ressort dont le rôle est d'immobiliser radialement le tenon lors du montage des aubes, avant la mise en place et la fixation de l'anneau de retenue. Ces ressorts créent un jeu de montage à chaque extrémité d'aube, ainsi que cela est montré sur la figure 7 de ce document, qui n'est pas maítrisé.US 4,033,705 discloses an axial retention system of vanes which has at each end of a blade root a tenon which cooperates with two oblique mortises formed in the rim of the disc of part and else of the groove receiving this foot of dawn. The studs provided on each disc face are retained radially by a ring secured to the disc. This document provides between each end face of the foot dawn and adjacent tenon a sheet forming spring whose role is to immobilize the tenon radially when assembling the blades, before the setting up and fixing the retaining ring. These springs create a mounting game at each end of dawn as this is shown on Figure 7 of this document, which is not controlled.

US 5 282 720 prévoit d'intercaler entre les flasques de retenue et les extrémités des pieds d'aubes, des éléments en nid d'abeille destinés à absorber une partie de l'énergie en cas d'ingestion d'oiseaux. Lors de l'ingestion, le nid d'abeille se déforme progressivement et dissipe ainsi une partie de l'énergie. Les éléments en nid d'abeille doivent conserver leur intégrité lors du montage des flasques, aussi existe-t-il inévitablement un jeu axial après le montage, et un déplacement axial aléatoire est possible en fonctionnement de la soufflante.US 5,282,720 provides for interposing between the retaining flanges and the ends of the blade roots, honeycomb elements intended for to absorb some of the energy if you eat birds. During ingestion, the honeycomb is gradually deformed and thus dissipates a part of the energy. Honeycomb elements must retain their integrity when mounting the flanges, so there is inevitably a axial clearance after assembly, and random axial displacement is possible in operation of the blower.

Le but de l'invention est de proposer un rotor de soufflante tel que décrit en introduction dans lequel la position axiale des aubes est maítrisé par un dispositif simple et bon marché, sans créer de problème pour le montage et le démontage des aubes en cas de réparation éventuelle.The object of the invention is to propose a fan rotor such described in the introduction in which the axial position of the blades is controlled by a simple and inexpensive device, without creating a problem for the assembly and disassembly of the blades in case of repair possible.

Ce but est atteint selon l'invention par le fait que le flasque amont est équipé sur sa face aval de moyens élastiques destinés à exercer sur les faces amont des pieds d'aube, après montage, des efforts suffisant pour empêcher tout déplacement axial des aubes lors du fonctionnement normal du moteur. Par fonctionnement normal du moteur, il faut entendre qu'il s'agit du fonctionnement hors événements exceptionnels, type ingestion de corps étrangers ou perte d'aubes.This object is achieved according to the invention by the fact that the flange upstream is equipped on its downstream face with elastic means intended to on the upstream faces of the blade roots, after assembly, sufficient efforts to prevent axial displacement of the blades during operation normal engine. By normal operation of the engine, it is necessary to hear that it is the operation except exceptional events, type ingestion of foreign bodies or loss of blades.

Ainsi, ces moyens élastiques, après montage du rotor, exercent sur les pieds d'aube un effort suffisamment important pour que ces derniers soient maintenus positivement en appui contre le flasque amont, éliminant ainsi tout jeu de montage axial quelles que soient les tolérances de fabrication des aubes.Thus, these elastic means, after mounting the rotor, exert on the dawn feet an effort large enough for these the latter are positively supported against the upstream flange, eliminating any axial assembly clearance whatever the tolerances manufacturing blades.

Avantageusement, il est prévu des moyens élastiques propres pour chaque pied d'aube. Ces moyens élastiques indépendants sont constitués de préférence par des pions en élastomère retenus dans un orifice ménagé dans le flasque.Advantageously, there is provided clean elastic means for each foot of dawn. These independent elastic means are preferably constituted by elastomer pins retained in a orifice formed in the flange.

Lorsque le rotor de soufflante comporte en outre une cale interposée entre chaque pied d'aube et le fond de la rainure correspondante, cette cale comportant un talon radial en appui contre la face amont dudit pied d'aube, les moyens élastiques sont avantageusement en appui contre lesdits talons. When the fan rotor further comprises a shim interposed between each blade root and the bottom of the groove corresponding, this wedge comprising a radial heel bearing against the upstream face of said blade root, the elastic means are advantageously bearing against said heels.

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

  • la figure 1 est une coupe schématique d'un rotor de soufflante ;
  • la figure 2 est une vue détaillée de la disposition du flasque amont et d'une aube, qui montre le jeu de montage ;
  • les figures 4a et 4b sont des vues en perspective d'un pion ; et
  • la figure 5 montre en perspective la face aval du flasque amont équipé de ses pions.
Other advantages and characteristics of the invention will appear on reading the following description given by way of example and with reference to the appended drawings in which:
  • Figure 1 is a schematic section of a fan rotor;
  • Figure 2 is a detailed view of the arrangement of the upstream flange and a blade, which shows the mounting clearance;
  • Figures 4a and 4b are perspective views of a pin; and
  • FIG. 5 shows in perspective the downstream face of the upstream flange equipped with its pins.

La figure 1 montre un rotor de soufflante 1 d'axe X qui comporte un disque 2 et une pluralité d'aubes 3 régulièrement espacées angulairement autour de l'axe X qui s'étendent radialement vers l'extérieur à la périphérie du disque 2. Chacune des aubes 3 comporte un pied d'aube 4 qui est retenu dans une rainure ou alvéole 5 sensiblement axiale ménagée dans la jante du disque 2. Les pieds d'aube 4 ont une forme en queue d'aronde, et les rainures 5 ont une forme complémentaire. Sous l'action des forces centrifuges, lorsque la soufflante est en fonctionnement, les pieds d'aube 4 sont retenues dans les rainures 5 par les parois radialement externes de ces rainures 5.Figure 1 shows an X-axis fan rotor 1 which has a disc 2 and a plurality of blades 3 regularly spaced angularly around the X axis which extend radially outwards at the periphery of the disc 2. Each of the blades 3 has a foot blade 4 which is retained in a groove or cell 5 substantially axial formed in the rim of the disk 2. The blade roots 4 have a shape in dovetail, and the grooves 5 have a complementary shape. Under the action of the centrifugal forces, when the fan is in operation, the blade roots 4 are retained in the grooves 5 by the radially outer walls of these grooves 5.

Une cale 6 est disposée entre la base de chaque pied d'aube 4 et le fond de la rainure 5. Cette cale 6 comporte, du côté de la face amont 7 du disque 2, un talon 8 qui est en appui contre la face amont 9 du pied 4 de l'aube 3. Le rôle de la cale 6 est d'empêcher l'aube 3 de tomber dans la rainure 5, lors de l'arrêt de la soufflante et d'encaisser une partie de l'énergie lors d'un choc sur la pale de l'aube par suite de l'ingestion d'un corps étranger par exemple ou de la rupture d'une aube voisine.A shim 6 is disposed between the base of each blade root 4 and the bottom of the groove 5. This shim 6 comprises, on the side of the upstream face 7 of the disc 2, a heel 8 which bears against the upstream face 9 of the foot 4 of the dawn 3. The role of the hold 6 is to prevent the dawn 3 from falling into the groove 5, when stopping the blower and cash a portion of the energy during a shock on the blade of the dawn as a result of the ingestion of a foreign body for example or the rupture of a neighboring dawn.

Sur la face aval 10 du disque 2 est fixé un flasque aval, non montré sur les dessins, contre lequel les pieds 4 des aubes 3 sont en butée.On the downstream face 10 of the disk 2 is fixed a downstream flange, no shown in the drawings, against which the feet 4 of the blades 3 are in stop.

Un flasque amont 12 est également prévu sur la face amont 7 du disque 2, dont le rôle est d'empêcher les pieds 4 des aubes 3 de s'échapper des rainures 5 par coulissement après le montage du rotor 1. Ce flasque amont 12 est fixé sur des brides du disque 2 par des vis, afin de permettre son démontage, en cas de nécessité de remplacement d'une aube 3.An upstream flange 12 is also provided on the upstream face 7 of the disk 2, whose role is to prevent the feet 4 of the blades 3 of to escape from the grooves 5 by sliding after mounting the rotor 1. This upstream flange 12 is fixed on flanges of the disc 2 by screws, so that to allow its dismantling, in case of need of replacement of a dawn 3.

Sur la figure 2, on voit le jeu de montage J qui existe entre le talon 8 et la face aval 13 du flasque amont 12. Le pied 4 d'une aube 3 peut donc se déplacer d'une distance axiale J dans sa rainure 5, ce qui peut entraíner un déséquilibrage du rotor 1 et générer des vibrations lors du fonctionnement.In Figure 2, we see the assembly game J that exists between the heel 8 and the downstream face 13 of the upstream flange 12. The foot 4 of a blade 3 can therefore move an axial distance J in its groove 5, which can lead to an imbalance of the rotor 1 and generate vibrations during of operation.

Selon l'invention, le flasque amont 12 comporte devant chaque pied d'aube 4 un orifice 15 qui retient le fût 16 d'un pion 17 en élastomère, ce pion 17 comportant une tête 18 de diamètre plus grand que celui de l'orifice 15, et ayant une épaisseur au moins égale au jeu J. Ainsi que cela est montré sur la figure 3, la tête 18 du pion 17 est disposée sur la face aval 13 du flasque amont 12, et cette tête 18 est comprimée entre la face aval 13 du flasque amont 12 et la face amont du talon 8 de la cale 6.According to the invention, the upstream flange 12 has in front of each dawn foot 4 an orifice 15 which holds the drum 16 of a pin 17 in elastomer, this pin 17 having a head 18 of larger diameter than that of the orifice 15, and having a thickness at least equal to the set J. As shown in FIG. 3, the head 18 of the pin 17 is disposed on the downstream face 13 of the upstream flange 12, and this head 18 is compressed between the downstream face 13 of the upstream flange 12 and the upstream face of the heel 8 of the hold 6.

Le pion 17 exerce ainsi des forces élastiques sur le talon 8 dans une direction axiale. Comme le talon 8 est en appui contre le pied d'aube 4 adjacent, ce dernier est sollicité en permanence vers le flasque aval, contre lequel il est en butée. Cette disposition simple, permet de maítriser le jeu axial des aubes 3 et d'empêcher un déplacement axial aléatoire des aubes 3.The pin 17 thus exerts elastic forces on the heel 8 in an axial direction. As the heel 8 is in support against the dawn foot 4 adjacent, it is permanently urged to the downstream flange, against which he is in abutment. This simple arrangement allows you to control the axial play of the blades 3 and to prevent random axial displacement of the blades 3.

Les figures 4a et 4b montrent en perspective des vues du pion 17 et la figure 5 montre en perspective la face aval 13 du flasque amont 12.Figures 4a and 4b show in perspective views of the pawn 17 and FIG. 5 shows in perspective the downstream face 13 of the upstream flange 12.

Les pions 17 sont évidemment montés sur le flasque amont 12 avant le montage de ce dernier sur le disque 2. La référence 20 désigne un orifice ménagé dans le flasque amont 12 et servant à la fixation de ce dernier sur des brides du disque 2 au moyen de vis. Le serrage de ces vis exerce sur les têtes 18 des pions 17, un effort de compression suffisant pour empêcher tout déplacement axial ultérieur des aubes 3, en fonction de l'écart entre les épaisseurs des têtes 18 au repos et le jeu de montage J d'origine. Cet effort de compression pourra varier d'une aube à l'autre selon les tolérances de fabrication des aubes 3 et des pions 17.The pins 17 are obviously mounted on the upstream flange 12 before mounting it on disk 2. Reference 20 designates an orifice formed in the upstream flange 12 and serving for fixing this last on flanges of disc 2 by means of screws. The tightening of these screws exerts on the heads 18 of the pins 17, a sufficient compressive force to prevent further axial displacement of the blades 3, depending the difference between the thicknesses of the heads 18 at rest and the mounting clearance J of origin. This compression effort may vary from one blade to another according to the manufacturing tolerances of blades 3 and pins 17.

Claims (4)

Rotor de soufflante comportant un disque (2) dont la jante comporte une pluralité de rainures (5) sensiblement axiales et régulièrement réparties angulairement, une pluralité d'aubes (3) amovibles qui s'étendent radialement vers l'extérieur à la périphérie dudit disque (2), chaque aube (3) comportant un pied d'aube (4) logeant dans une rainure (5), un flasque aval solidaire dudit disque (2) et contre lequel les faces aval des pieds d'aube sont en butée, et un flasque amont (12) amovible solidaire dudit disque (2) et destiné à retenir les pieds d'aube (4) dans les rainures (5),
   caractérisé par le fait que le flasque amont (12) est équipé sur sa face aval (13) de moyens élastiques (17) destinés à exercer sur les faces amont des pieds d'aube, après montage, des efforts suffisants pour empêcher tout déplacement axial des aubes (3) lors du fonctionnement normal du moteur.Blower rotor comprising a disk (2) whose rim comprises a plurality of substantially axial grooves (5) regularly distributed angularly, a plurality of removable blades (3) which extend radially outwards at the periphery of said disk (2), each blade (3) comprising a blade root (4) housed in a groove (5), a downstream flange integral with said disk (2) and against which the downstream faces of the blade roots abut, and a removable upstream flange (12) integral with said disk (2) and intended to hold the blade roots (4) in the grooves (5),
characterized in that the upstream flange (12) is provided on its downstream face (13) with elastic means (17) intended to exert on the upstream faces of the blade roots, after assembly, sufficient forces to prevent any axial displacement. blades (3) during normal operation of the engine. Rotor de soufflante selon la revendication 1, caractérisé par le fait qu'il est prévu des moyens élastiques (17) propres à chaque pied d'aube (4).Blower rotor according to Claim 1, characterized in that resilient means (17) are provided for each blade root (4). Rotor de soufflante selon la revendication 2, caractérisé par le fait que les moyens élastiques propres à chaque pied d'aube (4) sont constitués par un pion (17) en élastomère retenu dans un orifice (15) ménagé dans le flasque amont (12).Blower rotor according to Claim 2, characterized in that the resilient means specific to each blade root (4) consist of an elastomeric pin (17) retained in an orifice (15) formed in the upstream flange (12). ). Rotor de soufflante selon l'une quelconque des revendications 1 à 3, caractérisé par le fait qu'il comporte en outre une cale (6) interposée entre chaque pied d'aube (4) et le fond de la rainure (5) correspondante, cette cale (6) comportant un talon (8) radial en appui contre la face amont (9) dudit pied d'aube (4), et par le fait que les moyens élastiques sont en appui contre lesdits talons (8).Blower rotor according to any one of claims 1 to 3, characterized in that it further comprises a spacer (6) interposed between each blade root (4) and the bottom of the corresponding groove (5), this wedge (6) comprising a radial heel (8) bearing against the upstream face (9) of said blade root (4), and in that the elastic means bear against said heels (8).
EP03292280A 2002-09-18 2003-09-16 Axial positioning control of a compressor blade Expired - Lifetime EP1400698B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0211539A FR2844562B1 (en) 2002-09-18 2002-09-18 CONTROL OF THE AXIAL POSITION OF A BLOWER ROTOR BLADE
FR0211539 2002-09-18

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Publication Number Publication Date
EP1400698A1 true EP1400698A1 (en) 2004-03-24
EP1400698B1 EP1400698B1 (en) 2008-09-03

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EP03292280A Expired - Lifetime EP1400698B1 (en) 2002-09-18 2003-09-16 Axial positioning control of a compressor blade

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US (1) US6910866B2 (en)
EP (1) EP1400698B1 (en)
JP (1) JP4059827B2 (en)
CA (1) CA2440995C (en)
DE (1) DE60323309D1 (en)
ES (1) ES2314167T3 (en)
FR (1) FR2844562B1 (en)
RU (1) RU2315206C2 (en)
UA (1) UA79088C2 (en)

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FR2929660A1 (en) * 2008-04-07 2009-10-09 Snecma Sa ANTI-WEAR DEVICE FOR TURBOMACHINE ROTOR, CAP FORMING ANTI-WEAR DEVICE AND ROTOR COMPRESSOR OF GAS TURBINE ENGINE HAVING ANTI-WEAR CAP
WO2009144401A1 (en) * 2008-05-29 2009-12-03 Snecma Turbomachine fan rotor
FR2948725A1 (en) * 2009-07-28 2011-02-04 Snecma ANTI-WEAR DEVICE FOR A TURBOMACHINE ROTOR
FR2964584A1 (en) * 2010-09-10 2012-03-16 Snecma Bracing device for bracing anti-wear pin in discharge hole of mounting flange of low pressure compressor drum of dual flow and dual body turbo jet engine, has centering head equipped with holding unit for holding pin by electromagnetism
FR3048448A1 (en) * 2016-03-02 2017-09-08 Snecma SEAL CAP FOR LOW PRESSURE COMPRESSOR DRUM, LOW PRESSURE COMPRESSOR DRUM AND TURBOMACHINE
FR3119646A1 (en) * 2021-02-11 2022-08-12 Safran Aircraft Engines turbomachine rotor
WO2022195207A1 (en) 2021-03-16 2022-09-22 Safran Aircraft Engines Method for manufacturing a fan disc with a part by additive manufacturing

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FR2933887B1 (en) * 2008-07-18 2010-09-17 Snecma PROCESS FOR REPAIRING OR RETRIEVING A TURBOMACHINE DISK AND TURBOMACHINE DISK REPAIRED OR RECOVERED
US8568102B2 (en) * 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
RU2461717C1 (en) * 2011-03-17 2012-09-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Vibration damping device of wide-chord moving blades of fans with high conicity of sleeve, and gas turbine engine fan
GB201104994D0 (en) * 2011-03-25 2011-05-11 Rolls Royce Plc a rotor having an annulus filler
FR2974864B1 (en) * 2011-05-04 2016-05-27 Snecma ROTOR OF TURBOMACHINE WITH MEANS OF AXIAL RETENTION OF AUBES
FR2974863B1 (en) * 2011-05-06 2015-10-23 Snecma TURBOMACHINE BLOWER DISK
FR2986284B1 (en) * 2012-01-31 2014-03-28 Snecma PROCESS FOR REPAIRING WEAR MARKS.
RU2494365C1 (en) * 2012-03-27 2013-09-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Loading device for investigation of end damping of oscillations of fan blades of gas-turbine engine on vibration test rig
US9410439B2 (en) * 2012-09-14 2016-08-09 United Technologies Corporation CMC blade attachment shim relief
US11220920B2 (en) * 2014-04-07 2022-01-11 Safran Aircraft Engines Turbine engine rotor lock
FR3033359B1 (en) * 2015-03-02 2017-04-07 Snecma MONOBLOC DRAWING DISK HAVING A HUB HAVING AN EVIDENCE FACED BY A BODY COMPRISING SAME
CN109488390B (en) * 2018-12-18 2021-10-01 中国航发沈阳发动机研究所 Rotor blade connecting assembly and turbine performance test assembly
FR3106615B1 (en) * 2020-01-23 2021-12-31 Safran Aircraft Engines Turbomachine Kit

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EP1873401A3 (en) * 2006-06-29 2017-04-12 Safran Aircraft Engines Turbomachine rotor and turbomachine comprising such a rotor
RU2446287C2 (en) * 2006-06-29 2012-03-27 Снекма Turbine unit rotor and turbine unit with said rotor
FR2903154A1 (en) * 2006-06-29 2008-01-04 Snecma Sa ROTOR OF TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A ROTOR
US8113785B2 (en) 2006-06-29 2012-02-14 Snecma Turbomachine rotor and turbomachine comprising such a rotor
US8985961B2 (en) 2008-04-07 2015-03-24 Snecma Turbomachine rotor comprising an anti-wear plug, and anti-wear plug
FR2929660A1 (en) * 2008-04-07 2009-10-09 Snecma Sa ANTI-WEAR DEVICE FOR TURBOMACHINE ROTOR, CAP FORMING ANTI-WEAR DEVICE AND ROTOR COMPRESSOR OF GAS TURBINE ENGINE HAVING ANTI-WEAR CAP
WO2009124949A1 (en) * 2008-04-07 2009-10-15 Carbone Lorraine Composants Turbomachine rotor comprising an anti-wear plug, and anti-wear plug
WO2009144401A1 (en) * 2008-05-29 2009-12-03 Snecma Turbomachine fan rotor
US8740568B2 (en) 2008-05-29 2014-06-03 Snecma Turbomachine fan rotor
FR2931871A1 (en) * 2008-05-29 2009-12-04 Snecma BLOWER ROTOR FOR A TURBOMACHINE.
FR2948725A1 (en) * 2009-07-28 2011-02-04 Snecma ANTI-WEAR DEVICE FOR A TURBOMACHINE ROTOR
US8573944B2 (en) 2009-07-28 2013-11-05 Snecma Anti-wear device of a turbomachine rotor
FR2964584A1 (en) * 2010-09-10 2012-03-16 Snecma Bracing device for bracing anti-wear pin in discharge hole of mounting flange of low pressure compressor drum of dual flow and dual body turbo jet engine, has centering head equipped with holding unit for holding pin by electromagnetism
FR3048448A1 (en) * 2016-03-02 2017-09-08 Snecma SEAL CAP FOR LOW PRESSURE COMPRESSOR DRUM, LOW PRESSURE COMPRESSOR DRUM AND TURBOMACHINE
FR3119646A1 (en) * 2021-02-11 2022-08-12 Safran Aircraft Engines turbomachine rotor
WO2022195207A1 (en) 2021-03-16 2022-09-22 Safran Aircraft Engines Method for manufacturing a fan disc with a part by additive manufacturing
FR3120813A1 (en) 2021-03-16 2022-09-23 Safran Aircraft Engines Process for manufacturing a fan disc with additive manufacturing part

Also Published As

Publication number Publication date
JP2004263688A (en) 2004-09-24
FR2844562A1 (en) 2004-03-19
RU2315206C2 (en) 2008-01-20
US6910866B2 (en) 2005-06-28
JP4059827B2 (en) 2008-03-12
FR2844562B1 (en) 2004-10-29
DE60323309D1 (en) 2008-10-16
CA2440995A1 (en) 2004-03-18
ES2314167T3 (en) 2009-03-16
EP1400698B1 (en) 2008-09-03
RU2003128928A (en) 2005-03-20
CA2440995C (en) 2011-02-08
US20040126240A1 (en) 2004-07-01
UA79088C2 (en) 2007-05-25

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