EP0069620A1 - Blade damping device for turbomachines, especially for fans - Google Patents

Blade damping device for turbomachines, especially for fans Download PDF

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Publication number
EP0069620A1
EP0069620A1 EP82401105A EP82401105A EP0069620A1 EP 0069620 A1 EP0069620 A1 EP 0069620A1 EP 82401105 A EP82401105 A EP 82401105A EP 82401105 A EP82401105 A EP 82401105A EP 0069620 A1 EP0069620 A1 EP 0069620A1
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EP
European Patent Office
Prior art keywords
torsion bar
blade
foot
cam
cell
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
EP82401105A
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German (de)
French (fr)
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EP0069620B1 (en
Inventor
Alexandre Forestier
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
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0069620A1 publication Critical patent/EP0069620A1/en
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Publication of EP0069620B1 publication Critical patent/EP0069620B1/en
Expired legal-status Critical Current

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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
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates to a device for damping blades of turbomachines, in particular blowers.
  • the feet of fan blades are mounted with clearance in cells distributed around the periphery of a support disc.
  • the centrifugal force is insufficient to press the foot of the blade on the upper part of the cell, or even on the ground, when the fan turns in a reel under the effect of the wind, the feet of the blades beat in their cell.
  • the beating of the blade root can cause erosion of the protective coating, matting of the disc teeth or blade blade and local corrosion which are all detrimental defects in the longevity of the parts and which can cause the scrap of these which are very expensive.
  • the compression means consists of a torsion bar disposed under the foot of the blade and one of the ends of which is secured to a cam bearing against the base of the blade foot , while the other end of the torsion bar is supported by a cam attached to said bar against the base of the blade root under the prior tension imparted to the bar.
  • the underside of the blade root is thus permanently subjected to compression which keeps it in abutment on the upper walls of the cell.
  • FIG. 1 there is shown a fan blade 1 whose foot 2 is engaged in a cell 3 ( Figures 3.4) of a rotor disc 4 of a turbomachine fan.
  • the underside of the foot 2 of the blade is subjected to the action of a compression means which keeps the said foot in abutment against the upper walls 3a, 3b (FIGS. 3 to 5) of the cell 3.
  • a torsion bar 5 ( Figures 1, 2) which is supported longitudinally on one side by a cylindrical part 5a against an annular member 6 fixed to the rear of the disc 4 by bolts 7 and on the other side by its end 5b against a front cone 8 fixed to the support disc 4 by bolts 9.
  • the torsion bar 5 is inserted by overmolding in a sleeve 12 of polymeric material.
  • This sleeve corresponds to the shape of the space left free between the bottom of the cell 3 and the lower part of the foot 2 of the blade.
  • a lateral recess is provided at the two ends of the sleeve to allow the travel, during assembly, of cams 10 and 16 carried by the torsion bar and which are described below.
  • the torsion bar 5 has a cam 10 (FIGS. 1, 2, 5) comprising an eccentric boss 10a which bears against the underside 11 of the blade root, so that one end of the torsion bar is immobilized in rotation against the foot of the blade.
  • the torsion bar 5 has two grooved parts 13, 14 (FIGS. 1, 2) separated by a smooth part 15 of smaller cross section.
  • a sleeve 16 having a corresponding grooved hole 16b in order to secure in rotation the sleeve 16 with the torsion bar 5, said sleeve playing the role of a second cam which has, like the cam 10, an eccentric boss 16a resting against the underside of the foot 2 of the blade under the tension imparted to the torsion bar 5 before the fitting of the bush 16.
  • a ring 17 having internal grooves corresponding to those of the torsion bar, said ring 17 being in abutment on one side against the bush 16 which it locks axially and on the other side against a split elastic ring 18 engaged in a groove 19 provided at the end of the torsion bar.
  • a latch 21 ( Figures 2 and 6) in the form of U which is mounted on a part 2a of reduced section of the foot 2 of the blade, said lock 21 having a circular cutout 21a in which is engaged the ring 17 which radially locks the lock 21 in the housing 20.
  • the assembly of the device is carried out as follows.
  • the torsion bar 5 being mounted in the space of the cell under the foot 2 of the blade with the sleeve 12 of deformable material and the cam 10 being in abutment against the lower part 11 of the blade foot, slides on the front part of the torsion bar 5 the bush 16 to the smooth part 15 of the bar.
  • a tool of the "left-turn" type is then inserted on the fluted part 14 of the torsion bar and a torsion is printed on the latter.
  • the U-bolt, 21, is then introduced through the upper face of the spoiler before the blade, into the housing 20.
  • the ring 17 is itself axially locked by a locking ring 18.
  • front cone 8 is mounted, which is fixed by bolts 9 to the disc 4 and which locks the entire area.

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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

Le pied des aubes engagé dans une alvéole d'un disque de support de rotor est maintenu contre les parois supérieures de l'alvéole sous l'action d'un moyen de compression agissant sur la face inférieure du pied de l'aube. Le moyen de compression est constitué d'une barre de torsion (5) disposée sous le pied (2) de l'aube (1) et dont l'une des extrémités est solidaire d'une came (10) en appui contre la base du pied (2) de l'aube, alors que l'autre extrémité de la barre de torsion (5) est en appui par une came (16) rapportée sur ladite barre contre la base du pied (2) de l'aube sous la tension préalable conférée à la barre. L'invention est utilisée pour le montage des aubes de turbomachines.The root of the blades engaged in a cell of a rotor support disc is held against the upper walls of the cell under the action of a compression means acting on the underside of the blade root. The compression means consists of a torsion bar (5) disposed under the foot (2) of the blade (1) and one end of which is secured to a cam (10) bearing against the base of the foot (2) of the blade, while the other end of the torsion bar (5) is supported by a cam (16) attached to said bar against the base of the foot (2) of the blade under the prior tension imparted to the bar. The invention is used for mounting the blades of turbomachinery.

Description

La présente invention a pour objet un dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes.The present invention relates to a device for damping blades of turbomachines, in particular blowers.

Dans certaines turbomachines, les pieds d'aubes de soufflante sont montés avec du jeu dans des alvéoles réparties sur le pourtour d'un disque de support. A bas régime, lorsque la force centrifuge est insuffisante pour plaquer le pied de l'aube sur la partie supérieure de l'alvéole, ou même au sol, lorsque la soufflante tourne en moulinet sous l'effet du vent, les pieds des aubes battent dans leur alvéole. Les battements du pied de l'aube peuvent entraîner une érosion du revêtement de protection, un matage des dents du disque ou du pied de l'aube et une corrosion locale qui sont autant de défauts préjudiciables à la longévité des pièces et qui peuvent entraîner le rebut de celles-ci qui sont très coûteuses.In certain turbomachinery, the feet of fan blades are mounted with clearance in cells distributed around the periphery of a support disc. At low speed, when the centrifugal force is insufficient to press the foot of the blade on the upper part of the cell, or even on the ground, when the fan turns in a reel under the effect of the wind, the feet of the blades beat in their cell. The beating of the blade root can cause erosion of the protective coating, matting of the disc teeth or blade blade and local corrosion which are all detrimental defects in the longevity of the parts and which can cause the scrap of these which are very expensive.

Divers procédés ont été proposés pour remédier à ce défaut commun à toutes les soufflantes, tels qu'une lame métallique élastique disposée sous le pied de l'aube, un garnissage des enceintes sous les platef,ormes des aubes par une mousse synthétique, des corps gonflables disposés sous ces plateformes, etc...Various methods have been proposed to remedy this defect common to all blowers, such as an elastic metal blade placed under the foot of the blade, a lining of the enclosures under the platforms, shape of the blades by synthetic foam, bodies inflatables arranged under these platforms, etc ...

Toutefois, ces procédés connus ne donnent pas entière satisfaction pour remédier à ce défaut.However, these known methods are not entirely satisfactory for remedying this defect.

Conformément à la présente invention, le moyen de compression est constitué d'une barre de torsion disposée sous le pied de l'aube et dont l'une des extrémités est solidaire d'une came en appui contre la base du pied de l'aube, alors que l'autre extrémité de la barre de torsion est en appui par une came rapportée sur ladite barre contre la base du pied de l'aube sous la tension préalable conférée à la barre.According to the present invention, the compression means consists of a torsion bar disposed under the foot of the blade and one of the ends of which is secured to a cam bearing against the base of the blade foot , while the other end of the torsion bar is supported by a cam attached to said bar against the base of the blade root under the prior tension imparted to the bar.

Dans ce dispositif, la face inférieure du pied de l'aube est ainsi soumise en permanence à une compression qui la maintient en appui sur les parois supérieures de l'alvéole.In this device, the underside of the blade root is thus permanently subjected to compression which keeps it in abutment on the upper walls of the cell.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation et en se référant aux dessins annexés, dans lesquels :

  • - la figure 1 est une vue en élévation et en coupe radiale du dispositif d'amortissement de vibrations d'aubes de soufflante, 1
  • - la figure 2 est une vue en coupe du dispositif suivant la ligne II-II.de la figure 1,
  • - la figure 3 est une vue en coupe transversale du dispositif suivant la ligne III-III de la figure 2,
  • - la figure 4 est une vue en coupe transversale du dispositif suivant la ligne IV-IV de la figure 2,
  • - la figure 5 est une vue en coupe transversale du dispositif suivant la ligne V-V de la figure 2,
  • - la figure 6 est une vue en coupe transversale du dispositif suivant la ligne VI-VI de la figure 2.
Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment and with reference to the accompanying drawings, in which:
  • - Figure 1 is an elevational view in radial section of the vibration damping device of the fan blades, 1
  • FIG. 2 is a sectional view of the device along line II-II. of FIG. 1,
  • FIG. 3 is a cross-sectional view of the device along line III-III of FIG. 2,
  • FIG. 4 is a cross-sectional view of the device along the line IV-IV of FIG. 2,
  • FIG. 5 is a cross-sectional view of the device along the line VV in FIG. 2,
  • - Figure 6 is a cross-sectional view of the device along line VI-VI of Figure 2.

A la figure 1, on a représenté une aube 1 de soufflante dont le pied 2 est engagé dans une alvéole 3 (figures 3,4) d'un disque de rotor 4 d'une soufflante de turbomachine. La face inférieure du pied 2 de l'aube est soumise à l'action d'un moyen de compression qui maintient en appui ledit pied contre les parois supérieures 3a, 3b (figures 3 à 5) de l'alvéole 3.In Figure 1, there is shown a fan blade 1 whose foot 2 is engaged in a cell 3 (Figures 3.4) of a rotor disc 4 of a turbomachine fan. The underside of the foot 2 of the blade is subjected to the action of a compression means which keeps the said foot in abutment against the upper walls 3a, 3b (FIGS. 3 to 5) of the cell 3.

Dans la partie de l'alvéole 3 située au-dessous du pied 2 de l'aube est disposée une barre de torsion 5 (figures 1, 2) qui est en appui longitudinalement d'un côté par une partie cylindrique 5a contre un organe annulaire 6 fixé à l'arrière du disque 4 par des boulons 7 et de l'autre côté par son extrémité 5b contre un cône avant 8 fixé sur le disque de support 4 par des boulons 9.In the part of the cell 3 located below the foot 2 of the blade is disposed a torsion bar 5 (Figures 1, 2) which is supported longitudinally on one side by a cylindrical part 5a against an annular member 6 fixed to the rear of the disc 4 by bolts 7 and on the other side by its end 5b against a front cone 8 fixed to the support disc 4 by bolts 9.

La barre de torsion 5 est insérée par surmoulage dans un manchon 12 en matériau polymére.The torsion bar 5 is inserted by overmolding in a sleeve 12 of polymeric material.

Le profil extérieur de ce manchon correspond à la forme de l'espace laissé libre entre le fond de l'alvéole 3 et la partie inférieure du pied 2 de l'aube.The outer profile of this sleeve corresponds to the shape of the space left free between the bottom of the cell 3 and the lower part of the foot 2 of the blade.

De plus, aux deux extrémités du manchon, est prévu un évidement latéral pour permettre le débattement, au montage, de cames 10 et 16 portées par la barre de torsion et qui sont décrites ci-après.In addition, at the two ends of the sleeve, a lateral recess is provided to allow the travel, during assembly, of cams 10 and 16 carried by the torsion bar and which are described below.

A l'une de ses extrémités, la barre de torsion 5 présente une came 10 (figures 1, 2, 5) comportant un bossage excentré 10a qui est en appui contre la face inférieure 11 du pied de l'aube, de telle sorte que l'une des extrémités de la barre de torsion est immobilisée en rotation contre le pied de l'aube. A son autre extrémité la barre de torsion 5 présente deux parties.cannelées 13, 14 (figures 1, 2) séparées par une partie lisse 15 de plus faible section. Sur la partie cannelée 13 est engagée une douille 16 présentant un trou cannelé correspondant 16b afin de solidariser en rotation la douille 16 avec la barre de torsion 5, ladite douille jouant le rôle d'une deuxième came qui présente comme la came 10 un bossage excentré 16a en appui contre la face inférieure du pied 2 de l'aube sous la tension conférée à la barre 5 de torsion avant le montage de la douille 16.At one of its ends, the torsion bar 5 has a cam 10 (FIGS. 1, 2, 5) comprising an eccentric boss 10a which bears against the underside 11 of the blade root, so that one end of the torsion bar is immobilized in rotation against the foot of the blade. At its other end, the torsion bar 5 has two grooved parts 13, 14 (FIGS. 1, 2) separated by a smooth part 15 of smaller cross section. On the grooved part 13 is engaged a sleeve 16 having a corresponding grooved hole 16b in order to secure in rotation the sleeve 16 with the torsion bar 5, said sleeve playing the role of a second cam which has, like the cam 10, an eccentric boss 16a resting against the underside of the foot 2 of the blade under the tension imparted to the torsion bar 5 before the fitting of the bush 16.

Sur les parties cannelées 13 et 14 (figures 1 et 2) est engagée une bague 17 présentant des cannelures internes correspondantes à celles de la barre de torsion, ladite bague 17 étant en appui d'un côté contre la douille 16 qu'elle verrouille axialement et de l'autre côté contre un anneau élastique fendu 18 engagé dans une gorge 19 prévue à l'extrémité de la barre de torsion. Dans le disque 4, il est prévu à l'avant un logement ou fente 20 dans lequel est engagé un verrou 21 (figures 2 et 6) en forme de U qui est monté sur une partie 2a de section réduite du pied 2 de l'aube , ledit verrou 21 présentant une découpe circulaire 21a dans laquelle est engagée la bague 17 qui verrouille radialement le verrou 21 dans le logement 20.On the grooved parts 13 and 14 (FIGS. 1 and 2) is engaged a ring 17 having internal grooves corresponding to those of the torsion bar, said ring 17 being in abutment on one side against the bush 16 which it locks axially and on the other side against a split elastic ring 18 engaged in a groove 19 provided at the end of the torsion bar. In the disc 4, there is provided at the front a housing or slot 20 in which is engaged a latch 21 (Figures 2 and 6) in the form of U which is mounted on a part 2a of reduced section of the foot 2 of the blade, said lock 21 having a circular cutout 21a in which is engaged the ring 17 which radially locks the lock 21 in the housing 20.

Le montage du dispositif s'effectue de la manière suivante.The assembly of the device is carried out as follows.

La barre de torsion 5 étant montée dans l'espace de l'alvéole sous le pied 2 de l'aube avec le manchon 12 en matière déformable et la came 10 étant en butée contre la partie inférieure 11 du pied de l'aube, on glisse sur la partie avant de la barre de torsion 5 la douille 16 jusqu'à la partie lisse 15 de la barre.The torsion bar 5 being mounted in the space of the cell under the foot 2 of the blade with the sleeve 12 of deformable material and the cam 10 being in abutment against the lower part 11 of the blade foot, slides on the front part of the torsion bar 5 the bush 16 to the smooth part 15 of the bar.

On insère alors un outil du type "tourne-à-gauche" sur la partie cannelée 14 de la barre de torsion et on imprime une torsion à cette dernière. On maintient l'outil dans cette position et on fait ensuite glisser la douille 16 de la partie lisse 15 à la partie cannelée 13, après avoir choisi la position qui assure au bossage 16a un contact glissant sur la face inférieure du pied de l'aube. La tension de la barre 5 étant réalisée, on peut alors retirer l'outil.A tool of the "left-turn" type is then inserted on the fluted part 14 of the torsion bar and a torsion is printed on the latter. We keep the tool in this position and then the sleeve 16 is made to slide from the smooth part 15 to the grooved part 13, after having chosen the position which provides the boss 16a with sliding contact on the underside of the blade root. The tension of the bar 5 being produced, the tool can then be removed.

On introduit alors par la face supérieure du becquet avant de l'aube le verrou en U, 21, dans le logement 20.The U-bolt, 21, is then introduced through the upper face of the spoiler before the blade, into the housing 20.

Ensuite, on fait glisser sur l'extrémité 5b de la barre de torsion la bague cylindrique 17 qui s'engage d'abord dans la découpe 21a du verrou.21 et le verrouille radialement, puis ladite bague 17 vient en butée contre la douille ou came rapportée 16 qu'elle verrouille axialement.Then, the cylindrical ring 17 which first engages in the cutout 21a of the bolt 21 is slid over the end 5b of the torsion bar and then locks it radially, then said ring 17 abuts against the bushing or added cam 16 which it locks axially.

La bague 17 est elle-même verrouillée axialement par un anneau de blocage 18.The ring 17 is itself axially locked by a locking ring 18.

Enfin, on monte le cône avant 8 qui est fixé par des boulons 9 sur le disque 4 et qui verrouille l'ensemble de la zone.Finally, the front cone 8 is mounted, which is fixed by bolts 9 to the disc 4 and which locks the entire area.

Bien entendu diverses modifications peuvent être apportées par l'homme de l'art aux dispositifs ou procédés qui viennent d'être décrits uniquement à titre d'exemple non limitatif, sans sortir du cadre de l'invention.Of course, various modifications can be made by those skilled in the art to the devices or methods which have just been described solely by way of non-limiting example, without departing from the scope of the invention.

Claims (7)

1. Dispositif d'amortissement des vibrations d'aubes, notamment de soufflantes, dont le pied engagé dans une alvéole d'un disque de support de rotor est maintenu contre les parois supérieures de l'alvéole sous l'action d'un moyen de compression agissant sur la face inférieure du pied de l'aube, caractérisé en ce que le moyen de compression est constitué d'une barre de torsion (5) disposée sous le pied (2) de l'aube (1) et dont l'une des extrémités est solidaire d'une came (10) en appui contre la base du pied (2) de l'aube, alors que l'autre extrémité de la barre de torsion (5) est en appui par une came (16) rapportée sur ladite barre contre la base du pied (2) de l'aube sous la tension préalable conférée à la barre.1. Device for damping the vibrations of blades, in particular of blowers, the foot of which engaged in a cell of a rotor support disc is held against the upper walls of the cell under the action of a means of compression acting on the underside of the blade root, characterized in that the compression means consists of a torsion bar (5) disposed under the blade base (2) (1) and the one end is secured to a cam (10) bearing against the base of the foot (2) of the blade, while the other end of the torsion bar (5) is supported by a cam (16) attached to said bar against the base of the foot (2) of the blade under the prior tension imparted to the bar. 2. Dispositif suivant la revendication 1, caractérisé en ce que la barre de torsion (5) est insérée dans un manchon (12) en matériau polymère qui remplit l'espace disponible de l'alvéole (3) situé sous le pied (2) de l'aube.2. Device according to claim 1, characterized in that the torsion bar (5) is inserted in a sleeve (12) of polymer material which fills the available space of the cell (3) located under the foot (2) from dawn. 3. Dispositif suivant la revendication 1, caractérisé en ce que la came rapportée sur l'une des extrémités de la barre de torsion (5) est constituée par une douille (16) présentant un trou intérieur cannelé (16b) et, extérieurement, un bossage excentré (16a) dont la face est en appui contre la face inférieure du pied (2) de l'aube.3. Device according to claim 1, characterized in that the cam attached to one of the ends of the torsion bar (5) is constituted by a bush (16) having a grooved inner hole (16b) and, externally, a eccentric boss (16a) the face of which bears against the underside of the foot (2) of the blade. 4. Dispositif suivant les revendications 1 ou 3, caractérisé en ce que, à l'une de ses extrémités, la barre (5) de torsion présente deux parties cannelées (13, 14) séparées par une partie lisse (15) de plus faible section, l'une des parties cannelées (13) recevant la douille cannelée (16) constituant la came rapportée et l'une des extrémités d'une bague cannelée (17) de verrouillage dont l'autre. extrémité est engagée sur l'autre partie cannelée (14) de la barre de torsion (5).4. Device according to claims 1 or 3, characterized in that, at one of its ends, the torsion bar (5) has two grooved parts (13, 14) separated by a smooth part (15) of lower section, one of the fluted parts (13) receiving the fluted bushing (16) constituting the added cam and one of the ends of a fluted locking ring (17) including the other. end is engaged on the other grooved part (14) of the torsion bar (5). 5. Dispositif suivant la revendication 4, caractérisé en ce que la bague de verrouillage (17) est engagée entre les deux branches d'un verrou (21) en U qui est maintenu par ladite bague dans un logement (20) ménagé à l'entrée de l'alvéole dans le disque (4) de support.5. Device according to claim 4, characterized in that the locking ring (17) is engaged between the two branches of a latch (21) in a U which is held by said ring in a housing (20) formed at entry of the cell into the support disc (4). 6. Dispositif suivant la revendication 4, caractérisé en ce que la bague de verrouillage (17) est maintenue par un anneau élastique (18) engagé dans une gorge (19) de la barre de torsion (5).6. Device according to claim 4, characterized in that the locking ring (17) is held by an elastic ring (18) engaged in a groove (19) of the torsion bar (5). 7. Dispositif suivant la revendication 1, caractérisé en ce que la barre de torsion (5) est en appui à l'arrière contre un organe annulaire (6) solidaire du disque de support (4) et à l'avant contre un cône avant (8) solidaire du disque de support (4).7. Device according to claim 1, characterized in that the torsion bar (5) is supported at the rear against an annular member (6) integral with the support disc (4) and at the front against a front cone (8) secured to the support disc (4).
EP82401105A 1981-06-25 1982-06-18 Blade damping device for turbomachines, especially for fans Expired EP0069620B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8112459A FR2508541B1 (en) 1981-06-25 1981-06-25 DEVICE FOR DAMPING BLADES OF TURBOMACHINES, ESPECIALLY BLOWERS
FR8112459 1981-06-25

Publications (2)

Publication Number Publication Date
EP0069620A1 true EP0069620A1 (en) 1983-01-12
EP0069620B1 EP0069620B1 (en) 1985-02-13

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ID=9259854

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82401105A Expired EP0069620B1 (en) 1981-06-25 1982-06-18 Blade damping device for turbomachines, especially for fans

Country Status (5)

Country Link
US (1) US4453891A (en)
EP (1) EP0069620B1 (en)
JP (1) JPS585406A (en)
DE (1) DE3262317D1 (en)
FR (1) FR2508541B1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2149677A1 (en) * 2008-07-30 2010-02-03 Siemens Aktiengesellschaft Attachment device for attaching a rotor blade to a rotor of a turbomachine
EP3191688A1 (en) * 2014-09-08 2017-07-19 Safran Aircraft Engines Vane with spoiler
FR3108664A1 (en) * 2020-03-31 2021-10-01 Safran Aircraft Engines Fan rotor with upstream center of gravity vanes
FR3108665A1 (en) * 2020-03-31 2021-10-01 Safran Aircraft Engines Fan rotor with upstream center of gravity vanes

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US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4778342A (en) * 1985-07-24 1988-10-18 Imo Delaval, Inc. Turbine blade retainer
JPS63133031U (en) * 1987-02-23 1988-08-31
US4836749A (en) * 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
JPH02249913A (en) * 1989-03-24 1990-10-05 Canon Inc Optical encoder
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
GB2287993A (en) * 1994-03-24 1995-10-04 Rolls Royce Plc Gas turbine engine fan blade retention
AU5006900A (en) 1999-05-13 2000-12-05 Rolls-Royce Corporation Method for designing a cyclic symmetric structure
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
US8485784B2 (en) * 2009-07-14 2013-07-16 General Electric Company Turbine bucket lockwire rotation prevention
US8708656B2 (en) 2010-05-25 2014-04-29 Pratt & Whitney Canada Corp. Blade fixing design for protecting against low speed rotation induced wear
US20170191366A1 (en) * 2016-01-05 2017-07-06 General Electric Company Slotted damper pin for a turbine blade
FR3107724B1 (en) * 2020-02-27 2022-06-24 Safran Aircraft Engines Fan rotor with variable pitch blades and turbomachine equipped with such a rotor

Citations (2)

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US3723023A (en) * 1971-05-05 1973-03-27 Us Air Force Independent self adjusting vibration damper
GB2021206A (en) * 1978-05-18 1979-11-28 Gen Electric Turbo machinery blade retainer

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US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3598503A (en) * 1969-09-19 1971-08-10 United Aircraft Corp Blade lock
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement

Patent Citations (2)

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US3723023A (en) * 1971-05-05 1973-03-27 Us Air Force Independent self adjusting vibration damper
GB2021206A (en) * 1978-05-18 1979-11-28 Gen Electric Turbo machinery blade retainer

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2149677A1 (en) * 2008-07-30 2010-02-03 Siemens Aktiengesellschaft Attachment device for attaching a rotor blade to a rotor of a turbomachine
EP3191688A1 (en) * 2014-09-08 2017-07-19 Safran Aircraft Engines Vane with spoiler
FR3108664A1 (en) * 2020-03-31 2021-10-01 Safran Aircraft Engines Fan rotor with upstream center of gravity vanes
FR3108665A1 (en) * 2020-03-31 2021-10-01 Safran Aircraft Engines Fan rotor with upstream center of gravity vanes

Also Published As

Publication number Publication date
EP0069620B1 (en) 1985-02-13
US4453891A (en) 1984-06-12
FR2508541A1 (en) 1982-12-31
DE3262317D1 (en) 1985-03-28
JPS585406A (en) 1983-01-12
FR2508541B1 (en) 1985-11-22
JPS6215726B2 (en) 1987-04-09

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