EP0165860A1 - Axial locking device for a rotor blade of a turbo machine - Google Patents
Axial locking device for a rotor blade of a turbo machine Download PDFInfo
- Publication number
- EP0165860A1 EP0165860A1 EP85401152A EP85401152A EP0165860A1 EP 0165860 A1 EP0165860 A1 EP 0165860A1 EP 85401152 A EP85401152 A EP 85401152A EP 85401152 A EP85401152 A EP 85401152A EP 0165860 A1 EP0165860 A1 EP 0165860A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- disc
- axial
- locking
- downstream
- 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
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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
Definitions
- the present invention relates to an axial locking device for a turbomachine blade.
- Axial blade locking devices are also known in which collective locks are used, however to disassemble a blade it is necessary to unlock an entire sector. Furthermore, the sectorized rings add an additional force to the disc because the centrifugal forces are taken up by the latter.
- the object of the present invention is to remedy these drawbacks by using a device allowing unitary disassembly of the blades.
- a locking ring having regularly spaced notches in each of which is inserted an axial protuberance of each blade root projecting downstream of the disc, said protuberance being engaged in the corresponding notch by the introduction of the shim between the blade root and the bottom of the cell thus ensuring the axial locking of the blade.
- This locking device makes it possible, compared to French patent 2,507,679, to use a simplified disc and to avoid the presence of teeth both on the blades and on the disc, the realization of which is difficult.
- the device according to the invention allows unitary disassembly of the blades unlike known collective locks which require unlocking of an entire sector to disassemble a blade.
- the locking ring according to the invention which is in one piece does not add any additional force to the disc supporting it unlike sectored rings whose centrifugal forces are taken up by the disc.
- the embodiment in which the locking ring is integrated into the compressor drum has the advantage of a further reduction in the number of parts because the attachment of the disc to the drum is achieved by means of the ring of locking.
- Figure 1 there is shown a disc 1 of a turbomachine rotor having at the upper part of the upstream face a rim which is smooth, the lower part of the rim having a flange 2 on which is fixed a conical front cover 3 .
- the rim of the disc 1 On its downstream face the rim of the disc 1 has a radial flange 5 which is intended for fixing, by bolts 6 of a locking ring 7 and of a sealing ring 8.
- the sealing ring 8 comes to bear on the downstream edge of the platform 9 of the vanes 10 and its internal edge on the drum 11 of the intermediate compressor.
- a lower flange 12 is also provided on the downstream face of the rim of the disc 1 and on this flange is fixed the drum 11 of the low pressure compressor.
- Each blade 10 is mounted on the disk 1 by means of a foot 13 of dovetail-shaped section and which is slidably engaged in a cell 4 of the disk, said blade foot 13 being locked radially by a wedge 14 engaged between said foot 13 of the blade and the bottom of the cell 4.
- the wedge 14 bears on one side against a stop 15 of the front cover 3 and on the other side against a flange 16 of the drum 11.
- the rear part of the blade root 13 is extended by an axial protuberance 17 which is engaged in one of the notches 18 ( Figures 1, 3, 4 and 5) provided in the locking ring 7, said notches are regularly spaced in number equal to that of the blades.
- the notches 18 of the ring 7 are located opposite the cells 4 of the disc rim and their sides partially mask each side of the cells 4.
- the axial protuberance 17 which projects beyond the downstream face of the disc has two radial grooves 19, 19a machined on the sides of said protuberance ( Figures 3 and 5).
- the grooves 19, 19a are engaged on the edges of the notch 18 of the locking ring 7 during the lifting of the foot 13 of the blade under the action of the wedge 14 thus ensuring the axial locking of the blade 10 .
- the rear part of the foot 13 is extended by a radial protuberance 20 which can come to bear against the bottom of the notch 18, in the case of loss of a blade.
- Each blade 10 is inserted from front to back into the corresponding socket 4 of the disc, until the rear face of the stilt comes to bear on the ring.
- the front cover 3 is mounted on the flange 2 which axially locks the shims 4 in abutment against the flange 15.
- the cover 3 is removed and the shim 14 is deposited, which has the effect of allowing the blade to descend to the bottom of the cell 4 and to release the rear part and the protuberance 17 of the locking ring 7.
- the locking ring 7 is integrated into the drum 22 of the low pressure compressor and forms only one piece with it.
- the ring 7 has, as previously, indentations 18 in which is engaged by radial grooves 19, 19a the protuberance 17 of the foot 13 of the dawn.
Landscapes
- 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
Dispositif de verrouillage axial d'une aube de turbomachine, dans lequel la jante du disque de rotor présente des alvéoles à section en forme de queue d'aronde sensiblement axiales recevant les pieds d'aubes de forme correspondante qui sont verrouillés radialement par des cales placées entre le pied d'aube et le fond de l'alvéole. Sur la face aval du disque (1) est fixé un anneau de verrouillage (7) présentant des échancrures (18) régulièrement espacées dans chacune desquelles est insérée une protubérance axiale (17) de chaque pied (13) d'aube faisant saillie vers l'aval du disque (1). L'invention est utilisée pour le verrouillage axial d'une aube de turbomachine.Axial locking device of a turbomachine blade, in which the rim of the rotor disc has cells with a substantially axial dovetail-shaped section receiving the feet of correspondingly shaped blades which are locked radially by wedges placed between the blade root and the bottom of the cell. On the downstream face of the disc (1) is fixed a locking ring (7) having notches (18) regularly spaced in each of which is inserted an axial protuberance (17) of each blade root (13) projecting towards the 'downstream of the disc (1). The invention is used for axial locking of a turbomachine blade.
Description
La présente invention a pour objet un dispositif de verrouillage axial d'une aube de turbomachine.The present invention relates to an axial locking device for a turbomachine blade.
Par le brevet français 2 507 679, il est connu d'utiliser un dispositif de verrouillage axial d'une aube de turbomachine dans lequel l'aube est déplacée radialement vers l'extérieur par l'introduction d'une cale sous son pied. Par ce déplacement des butées transversales saillantes, solidaires de l'échasse ou du pied viennent en prise avec des portées sur la jante de façon à empêcher tout déplacement axial de l'aube. Ce dispositif a pour avantage de permettre un démontage unitaire des aubes, toutefois, il nécessite un assez grand nombre de pièces et la réalisation de dents sur les aubes et le disque dont la réalisation est difficile.By French patent 2,507,679, it is known to use an axial locking device for a turbomachine blade in which the blade is moved radially outward by the introduction of a wedge under its foot. By this displacement of the protruding transverse stops, integral with the stilt or the foot come into engagement with bearing surfaces on the rim so as to prevent any axial displacement of the blade. This device has the advantage of allowing a unitary disassembly of the blades, however, it requires a fairly large number of parts and the production of teeth on the blades and the disk, the production of which is difficult.
Par ailleurs, il existe un risque d'oubli au montage de l'un des verrous dont l'absence ne peut être constatée après montage.Furthermore, there is a risk of forgetting to mount one of the locks, the absence of which cannot be observed after mounting.
On connaît également des dispositifs de verrouillage axial d'aubes dans lesquels on utilise des verrous collectifs, toutefois pour démonter une aube il faut déverrouiller tout un secteur. Par ailleurs, les anneaux sectorisés ajoutent un effort supplémentaire au disque du fait que les efforts centrifuges sont repris par celui-ci.Axial blade locking devices are also known in which collective locks are used, however to disassemble a blade it is necessary to unlock an entire sector. Furthermore, the sectorized rings add an additional force to the disc because the centrifugal forces are taken up by the latter.
La présente invention a pour objet de remédier à ces inconvénients en utilisant un dispositif permettant un démontage unitaire des aubes.The object of the present invention is to remedy these drawbacks by using a device allowing unitary disassembly of the blades.
Conformément à la présente invention, sur la face aval du disque est fixé un anneau de verrouillage présentant des échancrures régulièrement espacées dans chacune desquelles est insérée une protubérance axiale de chaque pied d'aube faisant saillie vers l'aval du disque ladite protubérance étant engagée dans l'échancrure correspondante par l'introduction de la cale entre le pied d'aube et le fond de l'alvéole assurant ainsi le verrouillage axial de l'aube.According to the present invention, on the downstream face of the disc is fixed a locking ring having regularly spaced notches in each of which is inserted an axial protuberance of each blade root projecting downstream of the disc, said protuberance being engaged in the corresponding notch by the introduction of the shim between the blade root and the bottom of the cell thus ensuring the axial locking of the blade.
Ce dispositif de verrouillage permet par rapport au brevet français 2 507 679 d'utiliser un disque simplifié et d'éviter la présence de dents tant sur les aubes que sur le disque, dont la réalisation est difficile.This locking device makes it possible, compared to French patent 2,507,679, to use a simplified disc and to avoid the presence of teeth both on the blades and on the disc, the realization of which is difficult.
Il est également possible dans une variante de l'invention d'associer le verrou à la fixation du disque sur le tambour.It is also possible in a variant of the invention to associate the lock with the fixing of the disc on the drum.
Avec le dispositif suivant l'invention, il est possible de combiner sur la protubérance axiale du pied de l'aube la fonction de surface d'appui radial pour absorber les déformations des alvéoles lors de la perte d'une aube.With the device according to the invention, it is possible to combine on the axial protuberance of the root of the blade the function of a radial bearing surface to absorb the deformations of the cells when a blade is lost.
Le dispositif suivant l'invention permet un démontage unitaire des aubes contrairement aux verrous collectifs connus qui nécessitent un déverrouillage de tout un secteur pour démonter une aube.The device according to the invention allows unitary disassembly of the blades unlike known collective locks which require unlocking of an entire sector to disassemble a blade.
L'anneau de verrouillage suivant l'invention qui est en une seule pièce n'ajoute pas d'effort supplémentaire au disque le supportant contrairement aux anneaux sectorisés dont les efforts centrifuges sont repris par le disque.The locking ring according to the invention which is in one piece does not add any additional force to the disc supporting it unlike sectored rings whose centrifugal forces are taken up by the disc.
Enfin, le mode de réalisation dans lequel l'anneau de verrouillage est intégré au tambour du compresseur présente l'avantage d'une réduction supplémentaire du nombre de pièces car la solidarisation du disque au tambour est réalisée par l'intermédiaire de l'anneau de verrouillage.Finally, the embodiment in which the locking ring is integrated into the compressor drum has the advantage of a further reduction in the number of parts because the attachment of the disc to the drum is achieved by means of the ring of locking.
D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre de plusieurs modes de réalisation et en se référant aux dessins annexés sur lesquels ;
- - la figure 1 est une vue en coupe longitudinale du dispositif de fixation d'une aube sur le disque rotor d'une turbomachine,
- - la figure 2 est une vue de dessus d'un alvéole du disque incliné de 10° par rapport à l'axe du disque,
- - la figure 3 est une vue de face arrière de l'anneau de verrouillage,
- - la figure 4 est une vue en plan de l'anneau de verrouillage et de la partie en aval du pied de l'aube,
- - la figure 5 est une vue en coupe du pied de l'aube et de la protubérance engagée dans l'anneau de verrouillage,
- - la figure 6 est une vue en coupe longitudinale d'une variante de réalisation de l'anneau de verrouillage intégré au tambour du compresseur basse pression.
- FIG. 1 is a view in longitudinal section of the device for fixing a blade on the rotor disc of a turbomachine,
- FIG. 2 is a top view of a cell of the disc inclined by 10 ° relative to the axis of the disc,
- FIG. 3 is a rear front view of the locking ring,
- FIG. 4 is a plan view of the locking ring and of the part downstream from the root of the blade,
- FIG. 5 is a sectional view of the foot of the blade and of the protuberance engaged in the locking ring,
- - Figure 6 is a longitudinal sectional view of an alternative embodiment of the locking ring integrated into the drum of the low pressure compressor.
A la figure 1 on a représenté un disque 1 d'un rotor de turbomachine présentant à la partie supérieure de la face amont une jante qui est lisse, la partie inférieure de la jante comportant une bride 2 sur laquelle est fixé un capot avant cônique 3.In Figure 1 there is shown a
Dans la jante du disque 1 sont usinés par brochage des alvéoles 4 qui sont inclinés de 10" par rapport à l'axe du disque (Figure 2) ou qui sont parallèles à l'axe du disque (Figure 4). Ces alvéoles présentent en section la forme d'une queue d'aronde.In the rim of the
Sur sa face aval la jante du disque 1 comporte une bride radiale 5 qui est destinée à la fixation, par des boulons 6 d'un anneau de verrouillage 7 et d'un anneau d'étanchéité 8.On its downstream face the rim of the
L'anneau d'étanchéité 8 vient porter sur le bord aval de la plateforme 9 des aubes 10 et son bord interne sur le tambour 11 du compresseur intermédiaire.The sealing
Unebride inférieure 12 est également prévue sur la face aval de la jante du disque 1 et sur cette bride est fixé le tambour 11 du compresseur basse pression.A
Chaque aube 10 est montée sur le disque 1 au moyen d'un pied 13 à section en forme de queue d'aronde et qui est engagé par coulissement dans un alvéole 4 du disque, ledit pied 13 d'aube étant verrouillé radialement par une cale 14 engagée entre ledit pied 13 d'aube et le fond de l'alvéole 4.Each
La cale 14 est en appui d'un côté contre une butée 15 du capot avant 3 et de l'autre côté contre une bride 16 du tambour 11.The
La partie arrière du pied 13 d'aube est prolongée par une protubérance axiale 17 qui est engagée dans l'une des échancrures 18 (Figures 1, 3, 4 et 5) prévues dans l'anneau de verrouillage 7, lesdites échancrures sont régulièrement espacées en nombre égal à celui des aubes.The rear part of the
Les échancrures 18 de l'anneau 7 sont situées en face des alvéoles 4 de la jante du disque et leurs flancs masquent partiellement chaque côté des alvéoles 4.The
La protubérance axiale 17 qui fait saillie au-delà de la face aval du disque présente deux saignées radiales 19, 19a usinées sur les flancs de ladite protubérance (Figures 3 et 5). Les saignées 19, 19a sont engagées sur les bords de l'échancrure 18 de l'anneau de verrouillage 7 lors du soulèvement du pied 13 de l'aube sous l'action de la cale 14 assurant ainsi le verrouillage axial de l'aube 10.The
Par ailleurs, la partie arrière du pied 13 est prolongée par une protubérance radiale 20 qui peut venir en appui contre le fond de l'échancrure 18, dans le cas de perte d'une aube.Furthermore, the rear part of the
Pour procéder au montage des aubes 10 sur le disque 1, les anneaux de verrouillage 7 et d'étanchéité 8 sont présentés sur le disque 1 et fixés au moyen de boulons 6.To mount the
Chaque aube 10 est insérée d'avant en arrière dans l'alvéole 4 correspondant du disque, jusqu'à ce que la face arrière de l'échasse vienne en appui sur l'anneau.Each
Sous le pied 13 de l'aube on insère une cale 14, jusqu'à ce qu'elle vienne en butée contre la bride 16, ce qui a pour effet :
- - de remonter l'aube 10 radialement et de plaquer la face supérieure du
pied 13 contre la paroi supérieure de l'alvéole 4, - - de faire pénétrer les flancs de l'échancrure 18 de l'anneau 7 dans les saignées radiales 19, 19a du
pied 13 de l'aube.
- - wind the
blade 10 radially and press the upper face of thefoot 13 against the upper wall of thecell 4, - - To penetrate the sides of the
notch 18 of thering 7 in the 19, 19a of theradial grooves foot 13 of the dawn.
Enfin, le capot avant 3 est monté sur la bride 2 ce qui verrouille axialement les cales 4 en butée contre la bride 15. Pour démonter une aube 10, on enlève le capot 3 et on dépose la cale 14, ce qui a pour effet de permettre la descente de l'aube au fond de l'alvéole 4 et de libérer la partie arrière et la protubérance 17 de l'anneau de verrouillage 7.Finally, the
Il est alors possible d'extraire l'aube 10 vers l'avant du disque.It is then possible to extract the
Suivant un autre mode de réalisation représenté à la figure 6, l'anneau 7 de verrouillage est intégré au tambour 22 du compresseur basse pression et ne forme qu'une seule pièce avec celui-ci.According to another embodiment shown in FIG. 6, the
L'anneau 7 présente comme précédemment des échancrures 18 dans lesquelles est engagée par des saignées radiales 19, 19a la protubérance 17 du pied 13 de l'aube.The
Bien entendu, l'invention n'est pas limitative et l'homme de l'art pourra y apporter des modifications sans sortir du domaine de l'invention.Of course, the invention is not limiting and those skilled in the art may make modifications to it without departing from the scope of the invention.
Claims (4)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8409286 | 1984-06-14 | ||
FR8409286A FR2566061B1 (en) | 1984-06-14 | 1984-06-14 | AXIAL LOCKING DEVICE OF A TURBOMACHINE BLADE |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0165860A1 true EP0165860A1 (en) | 1985-12-27 |
EP0165860B1 EP0165860B1 (en) | 1988-03-16 |
Family
ID=9304994
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP85401152A Expired EP0165860B1 (en) | 1984-06-14 | 1985-06-12 | Axial locking device for a rotor blade of a turbo machine |
Country Status (5)
Country | Link |
---|---|
US (1) | US4604033A (en) |
EP (1) | EP0165860B1 (en) |
JP (1) | JPS6111404A (en) |
DE (1) | DE3561897D1 (en) |
FR (1) | FR2566061B1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1990446A1 (en) | 2007-04-30 | 2008-11-12 | Snecma | Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane |
WO2009124949A1 (en) | 2008-04-07 | 2009-10-15 | Carbone Lorraine Composants | Turbomachine rotor comprising an anti-wear plug, and anti-wear plug |
FR2972759A1 (en) * | 2011-03-15 | 2012-09-21 | Snecma | Wheel for rotor of low pressure turbine in e.g. turbojet of airplane, has annular part defining radial plane to axially support blades and align blades with disk, and tightly maintained against downstream faces of teeth by downstream plate |
WO2013114032A1 (en) | 2012-01-31 | 2013-08-08 | Snecma | Method for repairing wear marks on a rotor supporting the fan of a bypass engine |
US8573944B2 (en) | 2009-07-28 | 2013-11-05 | Snecma | Anti-wear device of a turbomachine rotor |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2585069B1 (en) * | 1985-07-16 | 1989-06-09 | Snecma | DEVICE FOR LIMITING THE ANGULAR DEFLECTION OF BLADES MOUNTED ON A TURBOMACHINE ROTOR DISC |
US4836750A (en) * | 1988-06-15 | 1989-06-06 | Pratt & Whitney Canada Inc. | Rotor assembly |
FR2681374B1 (en) * | 1991-09-18 | 1993-11-19 | Snecma | FIXING OF A TURBOREACTOR BLOWER BLADE. |
US5318405A (en) * | 1993-03-17 | 1994-06-07 | General Electric Company | Turbine disk interstage seal anti-rotation key through disk dovetail slot |
FR2715975B1 (en) * | 1994-02-10 | 1996-03-29 | Snecma | Turbomachine rotor with axial or inclined through blade grooves. |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
FR2841933B1 (en) * | 2002-07-04 | 2004-12-03 | Snecma Moteurs | SELF-LOCKING SHIM |
JP4807113B2 (en) * | 2006-03-14 | 2011-11-02 | 株式会社Ihi | Fan dovetail structure |
JP4911286B2 (en) * | 2006-03-14 | 2012-04-04 | 株式会社Ihi | Fan dovetail structure |
US20090053064A1 (en) * | 2006-09-01 | 2009-02-26 | Ress Jr Robert A | Fan blade retention system |
US9662721B2 (en) | 2008-02-26 | 2017-05-30 | United Technologies Corporation | Method of generating a curved blade retention slot in a turbine disk |
US8419370B2 (en) * | 2009-06-25 | 2013-04-16 | Rolls-Royce Corporation | Retaining and sealing ring assembly |
FR2965843B1 (en) * | 2010-10-06 | 2012-11-09 | Snecma | ROTOR FOR TURBOMACHINE |
FR2974863B1 (en) * | 2011-05-06 | 2015-10-23 | Snecma | TURBOMACHINE BLOWER DISK |
FR3075284B1 (en) * | 2017-12-18 | 2020-09-04 | Safran Aircraft Engines | SHOCK ABSORBER |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3378230A (en) * | 1966-12-16 | 1968-04-16 | Gen Electric | Mounting of blades in turbomachine rotors |
FR2345605A1 (en) * | 1976-03-25 | 1977-10-21 | Snecma | RETAINING DEVICE FOR BLOWER BLADES |
FR2492906A2 (en) * | 1976-03-25 | 1982-04-30 | Snecma | Retainer for movable blast vane - comprises wedge with opening to cooperate with U=shaped bolt and also cylindrical hole to which grip is fixed |
EP0068923A1 (en) * | 1981-06-12 | 1983-01-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Locking device for a rotor blade of a turbo machine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4221542A (en) * | 1977-12-27 | 1980-09-09 | General Electric Company | Segmented blade retainer |
US4265595A (en) * | 1979-01-02 | 1981-05-05 | General Electric Company | Turbomachinery blade retaining assembly |
US4453890A (en) * | 1981-06-18 | 1984-06-12 | General Electric Company | Blading system for a gas turbine engine |
FR2519072B1 (en) * | 1981-12-29 | 1986-05-30 | Snecma | DEVICE FOR AXIAL AND RADIAL RETENTION OF A TURBO JET ROTOR BLADE |
US4451205A (en) * | 1982-02-22 | 1984-05-29 | United Technologies Corporation | Rotor blade assembly |
FR2524932A1 (en) * | 1982-04-08 | 1983-10-14 | Snecma | DEVICE FOR AXIAL RETENTION OF BLADE FEET IN A TURBOMACHINE DISC |
FR2535794A1 (en) * | 1982-11-08 | 1984-05-11 | Snecma | AXIAL AND RADIAL BLADE SUPPORT DEVICE |
FR2535793B1 (en) * | 1982-11-08 | 1987-04-10 | Snecma | AXIAL LOCKING DEVICE FOR BLOWER BLADES |
-
1984
- 1984-06-14 FR FR8409286A patent/FR2566061B1/en not_active Expired
-
1985
- 1985-06-11 US US06/743,599 patent/US4604033A/en not_active Expired - Lifetime
- 1985-06-12 DE DE8585401152T patent/DE3561897D1/en not_active Expired
- 1985-06-12 JP JP60127904A patent/JPS6111404A/en active Granted
- 1985-06-12 EP EP85401152A patent/EP0165860B1/en not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3378230A (en) * | 1966-12-16 | 1968-04-16 | Gen Electric | Mounting of blades in turbomachine rotors |
FR2345605A1 (en) * | 1976-03-25 | 1977-10-21 | Snecma | RETAINING DEVICE FOR BLOWER BLADES |
FR2492906A2 (en) * | 1976-03-25 | 1982-04-30 | Snecma | Retainer for movable blast vane - comprises wedge with opening to cooperate with U=shaped bolt and also cylindrical hole to which grip is fixed |
EP0068923A1 (en) * | 1981-06-12 | 1983-01-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Locking device for a rotor blade of a turbo machine |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1990446A1 (en) | 2007-04-30 | 2008-11-12 | Snecma | Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane |
WO2009124949A1 (en) | 2008-04-07 | 2009-10-15 | Carbone Lorraine Composants | Turbomachine rotor comprising an anti-wear plug, and anti-wear plug |
US8573944B2 (en) | 2009-07-28 | 2013-11-05 | Snecma | Anti-wear device of a turbomachine rotor |
FR2972759A1 (en) * | 2011-03-15 | 2012-09-21 | Snecma | Wheel for rotor of low pressure turbine in e.g. turbojet of airplane, has annular part defining radial plane to axially support blades and align blades with disk, and tightly maintained against downstream faces of teeth by downstream plate |
WO2013114032A1 (en) | 2012-01-31 | 2013-08-08 | Snecma | Method for repairing wear marks on a rotor supporting the fan of a bypass engine |
Also Published As
Publication number | Publication date |
---|---|
DE3561897D1 (en) | 1988-04-21 |
JPH0340204B2 (en) | 1991-06-18 |
FR2566061A1 (en) | 1985-12-20 |
JPS6111404A (en) | 1986-01-18 |
EP0165860B1 (en) | 1988-03-16 |
FR2566061B1 (en) | 1988-09-02 |
US4604033A (en) | 1986-08-05 |
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