EP2531700B1 - Turbine engine air blower - Google Patents
Turbine engine air blower Download PDFInfo
- Publication number
- EP2531700B1 EP2531700B1 EP11705644.0A EP11705644A EP2531700B1 EP 2531700 B1 EP2531700 B1 EP 2531700B1 EP 11705644 A EP11705644 A EP 11705644A EP 2531700 B1 EP2531700 B1 EP 2531700B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- radial
- disc
- lug
- flanks
- clip
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 210000005069 ears Anatomy 0.000 description 15
- 230000008439 repair process Effects 0.000 description 5
- 241000272165 Charadriidae Species 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000005119 centrifugation Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000004061 bleaching Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
Definitions
- the riders can be engaged axially from upstream on the ears.
- each rider includes a transverse wall applied on a radial upstream face of an ear and having an orifice aligned with a corresponding orifice of the ear for the passage of a screw or a bolt for fixing on the compressor rotor downstream.
- each jumper is clamped on a radial ear of a disc at the attachment with the compressor rotor downstream.
- the thickness of the transverse wall is sufficiently small not to require the replacement of the screw or bolt by fixing screws or bolts of larger dimensions.
- each transverse wall of the rider comprises at least one radial tab whose free end extends upstream along a rib of the disc.
- each jumper comprises two aforementioned radial tabs which are parallel and spaced apart circumferentially from one another, which avoids a rotation of the rider during its tightening on the ear.
- the invention also relates to a jumper for protecting the flanks of a radial lug of a peripheral rib of a fan disk as described above, characterized in that it comprises two substantially parallel lateral lugs connected by a transverse wall comprising a central orifice, the transverse wall of each rider being extended by two bent legs whose free end extends in a direction opposite to the lateral flaps of the rider.
- Each radial lug 26 comprises lateral flanks comprising each a longitudinal stop 30 projecting.
- Each abutment 30 formed on the side of an ear 26 is circumferentially aligned with a stop 30 of an adjacent ear ( figure 2 ).
- jumpers 32 are mounted on the radial lugs 26 of the fan disk 10 and provide a covering of the flanks of the lugs 26 for the protection of the stops 30 ( figure 3 ).
- the lateral tabs 36, 38 of a jumper 32 each comprise a longitudinal fold 41 in U intended to fit on a longitudinal stop 30 of an ear 26 of the disc 10.
- This type of ear flange protection jumper 32 can be used both on a new blower disc 10 and on a disc in use. In the latter case, if the stops 30 have a wear, it is necessary to carry out a bleaching by surface of the abutments 30 so as to have a smooth surface in contact with the rider 32. This operation is therefore to remove between 0.2 and 0.5 millimeter of material to the flanks of a worn ear.
- jumpers 32 on the ears 26 of a fan disk 10 can be achieved when the turbomachine is in place under the wing of the aircraft, which reduces downtime and does not require complicated equipment since each jumper 32 is secured with a pre-existing fastener.
- the jumpers 32 may be made of a metallic material such as INCONEL and the blades 16 may be made of titanium. In this way the riders 32 wear out less quickly than the blades 16.
- the jumpers 32 may be made by successive folding and cutting operations of a sheet or by machining a block of material.
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
Description
La présente invention concerne une soufflante d'une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a fan of a turbomachine, such as an airplane turbojet or turboprop.
De façon connue, une soufflante de turbomachine comprend un disque de rotor comportant sur sa périphérie externe une pluralité de nervures longitudinales délimitant entre elles des alvéoles de montage axial et de retenue radiale de pieds d'aubes. L'extrémité aval de chaque nervure comprend une oreille radiale comportant un orifice de passage d'une vis ou d'un boulon pour la fixation du disque de soufflante sur une bride amont d'un compresseur basse pression agencé en aval de la soufflante. Le compresseur basse-pression est ainsi entraîné en rotation avec le rotor de la soufflante par un arbre de turbine.In known manner, a turbomachine fan comprises a rotor disk having on its outer periphery a plurality of longitudinal ribs delimiting between them axial mounting and radial retaining cells of blade roots. The downstream end of each rib comprises a radial lug having a hole for the passage of a screw or a bolt for fixing the fan disk to an upstream flange of a low-pressure compressor arranged downstream of the fan. The low-pressure compressor is thus rotated with the rotor of the fan by a turbine shaft.
Les flancs de chaque oreille forment des butées de retenue des aubes et limitent ainsi leur débattement angulaire. En cas de perte d'une aube, l'aube désolidarisée du disque impacte une aube adjacente laquelle bascule angulairement et vient en appui sur le flanc d'une oreille, ce qui permet un transfert de l'énergie libérée par le choc de l'aube désolidarisée sur l'aube adjacente vers l'ensemble du disque et évite ainsi des pertes d'aubes en cascade.The flanks of each ear form retaining stops of the blades and thus limit their angular deflection. In the event of a dawn being lost, the dawn disengaged from the disk impacts an adjacent blade which tilts angularly and bears on the side of an ear, which allows a transfer of the energy released by the shock of the dawn disengaged on the adjacent blade towards the entire disk and thus avoids cascading blade losses.
Quand l'avion est au sol et que la turbomachine est arrêtée, les parties tournantes de la turbomachine peuvent subir une autorotation (appelée « windmilling » en anglais). En effet, l'air entrant à l'intérieur de la turbomachine induit une rotation du rotor de la soufflante à une vitesse de l'ordre de 40 à 50 tours par minute. Cette faible vitesse de rotation ne permet pas une centrifugation suffisamment importante des aubes pour leur blocage en position dans les alvéoles. Il s'ensuit que les aubes de la soufflante peuvent basculer sur les flancs des oreilles des nervures du disque. Ces contacts répétés induisent des frottements entre les flancs des oreilles et les aubes conduisant à des usures prématurées des butées, ce qui impose des réparations plus fréquentes des butées.When the aircraft is on the ground and the turbomachine is stopped, the rotating parts of the turbomachine can undergo an autorotation (called "windmilling" in English). Indeed, the air entering the interior of the turbomachine induces a rotation of the rotor of the fan at a speed of the order of 40 to 50 revolutions per minute. This low rotational speed does not allow sufficiently large centrifugation of the blades for blocking in position in the cells. As a result, the blades of the blower can tilt over the flanks of the ears of the ribs of the disc. These repeated contacts induce friction between the flanks of the ears and the blades leading to premature wear of the stops, which requires more frequent repairs stops.
A l'heure actuelle, la réparation des flancs des oreilles est réalisée par dépôt par plasma d'une couche métallique. Toutefois, les oreilles du disque ainsi réparées ont une résistance à la fatigue inférieure à celle des oreilles d'un disque neuf. De plus, ces dépôts de matière ont une résistance aux chocs limitée et peuvent se désagréger progressivement au cours du temps.At present, the repair of the flanks of the ears is performed by plasma deposition of a metal layer. However, the repaired disk ears have less fatigue resistance than the ears of a new disc. In addition, these material deposits have a limited impact resistance and can break down gradually over time.
Enfin, cette opération n'est pas réalisable sous aile et nécessite un démontage et une réparation dans un atelier de maintenance, ce qui conduit à des temps d'immobilisation longs et coûteux et nécessite l'utilisation d'un outillage cher et complexe.
L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces différents problèmes.The invention aims in particular to provide a simple, economical and effective solution to these various problems.
A cette fin, elle propose une soufflante de turbomachine comprenant un disque de rotor comportant sur sa périphérie externe des alvéoles de montage de pieds d'aubes délimités par des nervures longitudinales comportant chacune une oreille radiale pour la fixation du disque sur un rotor de compresseur en aval, les flancs des oreilles formant des butées de retenue des aubes montées sur le disque, caractérisée en ce que des cavaliers en U sont montés sur les oreilles du disque et comprennent chacun deux pattes latérales recouvrant les flancs d'une oreille radiale.To this end, it proposes a turbomachine blower comprising a rotor disc having on its outer periphery mounting cells of blade roots delimited by longitudinal ribs each having a radial lug for fixing the disk to a compressor rotor. downstream, the flanks of the ears forming retaining stops of the vanes mounted on the disk, characterized in that U-shaped riders are mounted on the ears of the disc and each comprise two lateral lugs covering the flanks of a radial lug.
L'invention propose ainsi l'intégration de cavaliers de protection des oreilles du disque évitant une usure des flancs des oreilles par contact répétés des aubes lorsque la soufflante est mise en autorotation.The invention thus proposes the integration of protection riders of the ears of the disk avoiding wear of the flanks of the ears by repeated contact of the blades when the blower is put into autorotation.
Il n'est ainsi plus nécessaire de démonter la turbomachine pour réparer les oreilles des nervures du disque de soufflante. L'intégration de ces cavaliers est simple à réaliser et peut être effectuée sur une turbomachine montée sous l'aile d'un avion, évitant un démontage et un transport dans un atelier de maintenance.It is thus no longer necessary to disassemble the turbomachine to repair the ears of the ribs of the fan disk. The integration of these jumpers is simple to perform and can be performed on a turbine engine mounted under the wing of an aircraft, avoiding disassembly and transport in a maintenance workshop.
Les cavaliers peuvent être engagés axialement depuis l'amont sur les oreilles.The riders can be engaged axially from upstream on the ears.
Dans une réalisation de l'invention, chaque cavalier comprend une paroi transverse appliquée sur une face amont radiale d'une oreille et comportant un orifice aligné avec un orifice correspondant de l'oreille pour le passage d'une vis ou d'un boulon de fixation sur le rotor de compresseur en aval.In one embodiment of the invention, each rider includes a transverse wall applied on a radial upstream face of an ear and having an orifice aligned with a corresponding orifice of the ear for the passage of a screw or a bolt for fixing on the compressor rotor downstream.
Ainsi, chaque cavalier est serré sur une oreille radiale d'un disque au niveau de la fixation avec le rotor du compresseur en aval. L'épaisseur de la paroi transverse est suffisamment faible pour ne pas nécessiter le remplacement de la vis ou du boulon de fixation par des vis ou boulons de dimensions plus importantes.Thus, each jumper is clamped on a radial ear of a disc at the attachment with the compressor rotor downstream. The thickness of the transverse wall is sufficiently small not to require the replacement of the screw or bolt by fixing screws or bolts of larger dimensions.
Avantageusement, chaque patte latérale d'un cavalier comprend un pliage longitudinal en U s'emboîtant sur une butée d'un flanc de l'oreille radiale, ce qui permet d'assurer le montage axial du cavalier sur une oreille et la retenue radiale de ce cavalier sur cette oreille.Advantageously, each lateral leg of a rider comprises a longitudinal U-fold fitting on a stop of a flange of the radial lug, which makes it possible to ensure the axial mounting of the rider on one ear and the radial retention of this rider on that ear.
Selon une autre caractéristique de l'invention, chaque paroi transverse du cavalier comprend au moins une patte radiale dont l'extrémité libre s'étend vers l'amont le long d'une nervure du disque.According to another characteristic of the invention, each transverse wall of the rider comprises at least one radial tab whose free end extends upstream along a rib of the disc.
Préférentiellement, chaque cavalier comprend deux pattes radiales précitées qui sont parallèles et espacées circonférentiellement l'une de l'autre, ce qui évite une rotation du cavalier lors de son serrage sur l'oreille.Preferably, each jumper comprises two aforementioned radial tabs which are parallel and spaced apart circumferentially from one another, which avoids a rotation of the rider during its tightening on the ear.
L'invention concerne également un cavalier de protection des flancs d'une oreille radiale d'une nervure périphérique d'un disque de soufflante tel que décrit précédemment, caractérisé en ce qu'il comprend deux pattes latérales sensiblement parallèles reliées par une paroi transverse comportant un orifice central, la paroi transverse de chaque cavalier étant prolongée par deux pattes coudées dont l'extrémité libre s'étend dans un sens opposé aux pattes latérales du cavalier.The invention also relates to a jumper for protecting the flanks of a radial lug of a peripheral rib of a fan disk as described above, characterized in that it comprises two substantially parallel lateral lugs connected by a transverse wall comprising a central orifice, the transverse wall of each rider being extended by two bent legs whose free end extends in a direction opposite to the lateral flaps of the rider.
L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif, en référence aux dessins annexés dans lesquels :
- la
figure 1 est une vue schématique partielle en perspective d'un disque de soufflante selon la technique antérieure ; - la
figure 2 est une vue schématique partielle en coupe transversale d'une aube montée dans une alvéole d'un disque de soufflante selon la technique antérieure ; - la
figure 3 est une vue schématique depuis l'amont d'une partie d'un disque comprenant des moyens de protection des oreilles du disque selon l'invention ; - les
figures 4A et 4B sont des vues en perspectives de cavaliers de protection des oreilles radiales d'un disque d'une soufflante selon l'invention ; - la
figure 5 est une vue schématique en coupe axiale de la fixation du disque de soufflante selon l'invention à un rotor de compresseur basse pression agencé en aval.
- the
figure 1 is a partial schematic perspective view of a fan disk according to the prior art; - the
figure 2 is a partial schematic cross-sectional view of a blade mounted in a cavity of a fan disk according to the prior art; - the
figure 3 is a schematic view from upstream of a portion of a disk comprising means for protecting the ears of the disk according to the invention; - the
Figures 4A and 4B are perspective views of protection riders radial ears of a disc of a blower according to the invention; - the
figure 5 is a schematic view in axial section of the attachment of the fan disk according to the invention to a low pressure compressor rotor arranged downstream.
On se réfère tout d'abord à la
Chaque nervure 12 du disque 10 de soufflante comprend une oreille radiale 26 formée à son extrémité aval. Ces oreilles 26 comprennent chacune un orifice axial 28 destiné à être aligné avec un orifice correspondant formé dans une bride annulaire d'un rotor de compresseur basse pression agencé en aval (voir
Chaque oreille radiale 26 comprend des flancs latéraux comportant chacun une butée longitudinale 30 en saillie. Chaque butée 30 formée sur le flanc d'une oreille 26 est alignée circonférentiellement avec une butée 30 d'une oreille adjacente (
Lorsque les aubes 16 sont montées sur le disque 10 de soufflante, ceux sont les échasses 22 qui sont situées en regard des butées longitudinales 30.When the
En cas de perte d'aube, l'aube désolidarisée impacte une aube adjacente 16 qui bascule et dont l'échasse 22 vient en contact avec une butée 30 d'une oreille radiale 26. Ces butées 30 limitent ainsi le débattement angulaire de l'aube 16 subissant la pression de l'aube désolidarisée et permettent un transfert de l'énergie du choc vers le disque 10 de soufflante.In the event of dawn loss, the uncoupled blade impacts an
On a constaté dans la technique antérieure, que ces butées 30 étaient soumises à des usures relativement importantes dues essentiellement aux chocs des démarrages et des arrêts de la turbomachine et à son fonctionnement occasionnel en autorotation à l'arrêt au sol. En effet, l'air entrant dans la turbomachine induit une rotation de la soufflante qui n'est pas suffisamment importante pour réaliser une centrifugation des aubes 16 et un blocage en position stable des pieds d'aubes 24 dans les alvéoles 14. Il s'ensuit des basculements successifs des aubes 16 conduisant à des frottements entre les échasses 22 et les butées 30 d'où il résulte une usure des butées 30 des oreilles radiales 26.It has been found in the prior art that these
Les solutions proposées dans la technique antérieure et exposées précédemment ne sont pas pérennes et nécessitent un démontage de la turbomachine pour une effectuer une réparation dans un atelier de maintenance et un équipement coûteux.The solutions proposed in the prior art and previously exposed are not sustainable and require disassembly of the turbomachine to perform a repair in a maintenance shop and expensive equipment.
Selon l'invention, des cavaliers 32 sont montés sur les oreilles radiales 26 du disque 10 de soufflante et assurent un recouvrement des flancs des oreilles 26 pour la protection des butées 30 (
Chaque cavalier a une forme en U et comprend une paroi transverse 34 de forme sensiblement rectangulaire reliée à deux pattes latérales parallèles 36, 38. La paroi transverse 34 comprend un orifice central 40 et est prolongée par deux pattes plates radiales 42, 44 qui sont parallèles et dont les extrémités sont courbées dans un sens opposé aux pattes latérales 36, 38, ces deux pattes radiales 42, 44 étant espacées l'une de l'autre (
Les pattes latérales 36, 38 d'un cavalier 32 comprennent chacune un pliage longitudinal 41 en U destiné à s'emboîter sur une butée longitudinale 30 d'une oreille 26 du disque 10.The
Pour le montage d'un cavalier 32 sur une oreille 26 du disque 10 de soufflante, le cavalier 32 est positionné sur le disque 10 afin que les pattes radiales 42, 44 s'étendent le long d'une nervure 12 du disque 10 et vers l'amont du disque 10. Le cavalier 32 est ensuite translaté vers l'aval de manière à ce que les pliages en U 41 des pattes latérales 36, 38 s'emboîtent sur les butées longitudinales 30 de l'oreille radiale 26 du disque 10, la paroi transverse 34 du cavalier 32 venant s'appliquer sur la face radiale amont de l'oreille radiale 26. Une vis de fixation 46 est ensuite insérée depuis l'aval dans les orifices alignés du cavalier 32, de l'oreille 26 et de la bride annulaire 48 du rotor de compresseur basse pression. Un écrou de fixation 50 est serré sur la face amont du cavalier 32 (
L'insertion d'un cavalier 32 n'induit aucune modification dans les dimensions des vis de fixation 46 étant donnée l'épaisseur très faible de la paroi transverse 34 qui est de l'ordre de quelques dixièmes de millimètres.The insertion of a
Il est souhaitable de dimensionner un cavalier 32 de manière à ce que les pattes radiales 42, 44 soient montées avec un jeu radial J par rapport à une nervure 12 du disque 10 pour compenser les tolérances dans le positionnement radial d'un orifice 28 sur une oreille radiale 26 et ainsi garantir en toutes circonstances un alignement de l'orifice 40 d'un cavalier 32 avec un orifice 28 d'une oreille radiale 26.It is desirable to size a
Ce type de cavalier de protection 32 des flancs des oreilles peut être utilisé aussi bien sur un disque 10 de soufflante neuf que sur un disque en cours d'utilisation. Dans ce dernier cas, si les butées 30 présentent une usure, il est nécessaire d'effectuer un blanchiment par toilage de la surface des butées 30 de manière à avoir une surface lisse au contact du cavalier 32. Cette opération consiste donc à enlever entre 0,2 et 0,5 millimètre de matière aux flancs d'une oreille usée.This type of ear
L'intégration des cavaliers 32 sur les oreilles 26 d'un disque 10 de soufflante peut être réalisée lorsque la turbomachine est en place sous l'aile de l'avion, ce qui permet de réduire les temps d'immobilisation et ne nécessite pas d'équipements compliqués puisque chaque cavalier 32 est solidarisé à l'aide d'un élément de fixation préexistant.The integration of the
Les cavaliers 32 peuvent être réalisés dans un matériau métallique tel que de l'INCONEL et les aubes 16 peuvent être en titane. De cette manière les cavaliers 32 s'usent moins vite que les aubes 16.The
Les cavaliers 32 peuvent être réalisés par des opérations de pliage et de découpe successives d'une tôle ou bien par usinage d'un bloc de matière.The
Claims (7)
- Turbine engine fan comprising a rotor disc (10) having on its external periphery slots (14) for mounting blade roots (24) delimited by longitudinal ribs (12) each comprising a radial lug (26) for fixing the disc (10) on a compressor rotor downstream, the flanks of the lugs (26) forming stops for holding the blades (16) mounted on the disc (10), characterised in that U-shaped clips (26) are mounted on the disc lugs and each comprise two lateral tabs (36, 38) covering the flanks of a radial lug.
- A fan according to claim 1, characterised in that clips (32) are engaged axially from the upstream side on the lugs (26).
- A fan according to claim 1 or 2, characterised in that each clip (32) comprises a transverse wall (34) applied to a radial upstream face of a lug (26) and comprising an orifice (40) aligned with a corresponding orifice (28) in the lug (32) for passage of a screw or bolt for fixing on the compressor rotor downstream.
- A fan according to claim 3, characterised in that each lateral tab (36, 38) comprises a longitudinal fold (41) fitting on a stop (30) of a flank of the radial lug (26).
- A fan according to claim 3 or 4, characterised in that the transverse wall (34) of the clip (32) comprises at least one radial tab (42, 44), the end of which extends towards the upstream side along a rib (12) of the disc (10).
- A fan according to claim 5, characterised in that each clip comprises two aforementioned radial tabs (42, 44) parallel and spaced apart circumferentially from each other.
- A clip (32) intended for protecting the flanks of a radial lug (26) of a peripheral rib (12) of a fan disc (10) according to one of claims 1 to 6, characterised in that it comprises two substantially parallel lateral tabs (36, 38) connected by a transverse wall (34) comprising a central orifice (40), the transverse wall being extended by two angled tabs (42, 44) the free ends of which extend in a direction opposite to the lateral tabs (36, 38) of the clip (32).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1000456A FR2955904B1 (en) | 2010-02-04 | 2010-02-04 | TURBOMACHINE BLOWER |
PCT/FR2011/050116 WO2011095722A1 (en) | 2010-02-04 | 2011-01-21 | Turbine engine air blower |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2531700A1 EP2531700A1 (en) | 2012-12-12 |
EP2531700B1 true EP2531700B1 (en) | 2013-12-25 |
Family
ID=42733744
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11705644.0A Active EP2531700B1 (en) | 2010-02-04 | 2011-01-21 | Turbine engine air blower |
Country Status (9)
Country | Link |
---|---|
US (1) | US9376925B2 (en) |
EP (1) | EP2531700B1 (en) |
JP (1) | JP5674818B2 (en) |
CN (1) | CN102753788B (en) |
BR (1) | BR112012018267B1 (en) |
CA (1) | CA2786988C (en) |
FR (1) | FR2955904B1 (en) |
RU (1) | RU2555099C2 (en) |
WO (1) | WO2011095722A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3066780B1 (en) * | 2017-05-24 | 2019-07-19 | Safran Aircraft Engines | ANTI-WEAR REMOVABLE PIECE FOR DAWN HEEL |
Family Cites Families (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2303148A (en) * | 1941-03-24 | 1942-11-24 | Tinnerman Products Inc | Nut fastened installations |
BE499742A (en) * | 1949-03-07 | |||
US2727552A (en) * | 1953-03-12 | 1955-12-20 | Tinnerman Products Inc | Sheet metal retainer for threaded fasteners |
US3238495A (en) * | 1964-04-17 | 1966-03-01 | Illinois Tool Works | Electrical connector |
US4033705A (en) * | 1976-04-26 | 1977-07-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blade retainer assembly |
US4265595A (en) * | 1979-01-02 | 1981-05-05 | General Electric Company | Turbomachinery blade retaining assembly |
SU1078981A1 (en) * | 1982-09-17 | 2005-12-10 | С.С. Гасилин | WORKING WHEEL AXIAL TURBO MOBILE (ITS OPTIONS) |
US4887949A (en) * | 1988-03-30 | 1989-12-19 | United Technologies Corporation | Bolt retention apparatus |
US5259728A (en) * | 1992-05-08 | 1993-11-09 | General Electric Company | Bladed disk assembly |
JPH07247804A (en) * | 1993-01-07 | 1995-09-26 | General Electric Co <Ge> | Rotor and moving vane assembly for gas-turbine engine and multilayer covering shim |
US5388963A (en) * | 1993-07-02 | 1995-02-14 | United Technologies Corporation | Flange for high speed rotors |
US6290466B1 (en) * | 1999-09-17 | 2001-09-18 | General Electric Company | Composite blade root attachment |
FR2831207B1 (en) * | 2001-10-24 | 2004-06-04 | Snecma Moteurs | PLATFORMS FOR BLADES OF A ROTARY ASSEMBLY |
RU2264561C1 (en) * | 2004-06-08 | 2005-11-20 | Аверичкин Павел Алексеевич | Axial-flow compressor stage of gas-turbine engine |
FR2890105A1 (en) * | 2005-08-31 | 2007-03-02 | Snecma | Retention ring immobilization device for e.g. engine of aircraft, has stops positioned such that stops are stopped respectively against immobilization hooks, and slot covered by other hook when retention ring is placed in groove |
FR2890104A1 (en) * | 2005-08-31 | 2007-03-02 | Snecma | Rotation blocking device for use in turbomachine rotor of aircraft engine, has ring with split and set of cleat, which is arranged on ring and placed in groove of rotor disk that includes blocking hook with check face |
FR2890684B1 (en) * | 2005-09-15 | 2007-12-07 | Snecma | CLINKING FOR TURBOREACTOR BLADE |
JP2007247406A (en) * | 2006-03-13 | 2007-09-27 | Ihi Corp | Holding structure of fan blade |
FR2903154B1 (en) * | 2006-06-29 | 2011-10-28 | Snecma | ROTOR OF TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A ROTOR |
FR2911632B1 (en) * | 2007-01-18 | 2009-08-21 | Snecma Sa | ROTOR DISC OF TURBOMACHINE BLOWER |
FR2913735B1 (en) * | 2007-03-16 | 2013-04-19 | Snecma | ROTOR DISC OF A TURBOMACHINE |
FR2929660B1 (en) | 2008-04-07 | 2012-11-16 | Snecma | ANTI-WEAR DEVICE FOR TURBOMACHINE ROTOR, CAP FORMING ANTI-WEAR DEVICE AND ROTOR COMPRESSOR OF GAS TURBINE ENGINE HAVING ANTI-WEAR CAP |
FR2939836B1 (en) * | 2008-12-12 | 2015-05-15 | Snecma | SEAL FOR PLATFORM SEAL IN A TURBOMACHINE ROTOR |
-
2010
- 2010-02-04 FR FR1000456A patent/FR2955904B1/en active Active
-
2011
- 2011-01-21 BR BR112012018267-6A patent/BR112012018267B1/en active IP Right Grant
- 2011-01-21 WO PCT/FR2011/050116 patent/WO2011095722A1/en active Application Filing
- 2011-01-21 CN CN201180008540.9A patent/CN102753788B/en active Active
- 2011-01-21 JP JP2012551662A patent/JP5674818B2/en active Active
- 2011-01-21 EP EP11705644.0A patent/EP2531700B1/en active Active
- 2011-01-21 CA CA2786988A patent/CA2786988C/en active Active
- 2011-01-21 US US13/576,071 patent/US9376925B2/en active Active
- 2011-01-21 RU RU2012137508/06A patent/RU2555099C2/en active
Also Published As
Publication number | Publication date |
---|---|
FR2955904B1 (en) | 2012-07-20 |
WO2011095722A1 (en) | 2011-08-11 |
JP5674818B2 (en) | 2015-02-25 |
JP2013519030A (en) | 2013-05-23 |
EP2531700A1 (en) | 2012-12-12 |
RU2012137508A (en) | 2014-03-10 |
BR112012018267B1 (en) | 2020-10-13 |
US9376925B2 (en) | 2016-06-28 |
US20120294721A1 (en) | 2012-11-22 |
CA2786988A1 (en) | 2011-08-11 |
CN102753788A (en) | 2012-10-24 |
FR2955904A1 (en) | 2011-08-05 |
BR112012018267A2 (en) | 2017-06-27 |
CN102753788B (en) | 2015-02-11 |
CA2786988C (en) | 2017-11-14 |
RU2555099C2 (en) | 2015-07-10 |
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