EP0388285B1 - Retention system for variable pitch stator blades - Google Patents

Retention system for variable pitch stator blades Download PDF

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Publication number
EP0388285B1
EP0388285B1 EP90400669A EP90400669A EP0388285B1 EP 0388285 B1 EP0388285 B1 EP 0388285B1 EP 90400669 A EP90400669 A EP 90400669A EP 90400669 A EP90400669 A EP 90400669A EP 0388285 B1 EP0388285 B1 EP 0388285B1
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EP
European Patent Office
Prior art keywords
bush
blade
blades
upstream
cotter pins
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.)
Expired - Lifetime
Application number
EP90400669A
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German (de)
French (fr)
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EP0388285A1 (en
Inventor
Daniel Jean Marey
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
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/22—Three-dimensional parallelepipedal

Definitions

  • the invention relates to turbomachine compressors and more particularly inside these means for radial retention and limitation of angular displacement of the variable pitch vanes.
  • the adaptation of the orientation of the stator fins of the different compressor stages is particularly desirable when it is desired, for example for the different stages, at a given speed, the greatest possible pressure while retaining a sufficient pumping margin.
  • stator vanes with variable setting are generally controlled in rotation by rods external to the casing and connected together by a control ring.
  • the blades generally have head and foot journals which are mounted to rotate in sockets.
  • Document FR-A 2 524 934 thus describes a blade having at its bottom a bushing pierced with a bore in which the blade root swivels, the bushing being able to comprise a diamond face whose parallel edges ensure a function of limitation of the deflection maximum angular tolerated for a blade, so that, if one of the control levers of a blade breaks, it cannot be feathered or cross the flow which would cause a probable pumping of the entire floor.
  • Document GB-A 2 159 887 shows variable-pitch vanes, the angular limitation system of which consists of the connecting screws of two adjacent casing ferrules.
  • the object of the present invention is to simplify the mounting of the stator vanes with variable setting by producing a means of pivoting the blade which also ensures the positioning and the radial retention of the blade.
  • the invention also aims in one of these variants to ensure, quite simply, the limitation of the angular displacement of the stator blades in order to limit the risks of feathering or across the flow of the blade in the event breakage of a control rod.
  • the invention also aims to achieve the retention of the blade and possibly the limitation of angular movement in an area of the engine located at the outer casing in order to simplify the implementation and positioning.
  • the invention relates to a system for retaining stator vanes with variable setting of a turbomachine compressor, said vanes being disposed between an internal ring and an external casing comprising at least one upstream ferrule and a downstream ferrule each provided with a flange, one upstream comprising housings for bushings pierced with a radial bore inside which a vane journals, the other downstream, said flanges facing each other and being joined together by longitudinal screws interposed between the housings of the upstream flange.
  • each socket has a rectangular shape with a trapezoidal section, the small base of which is located radially inwards and each blade is held radially in the socket at by means of two parallel pins arranged longitudinally, said pins passing through the sleeve and cooperating with an at least partially annular groove in the journal.
  • the stator stage with variable setting comprises vanes 1 comprising at the head a journal 2 surmounted by a threaded part intended for securing the vane with a control rod 3
  • the pin 2 has an annular groove with semi-circular section 4.
  • the pin 2 is engaged in the radial bore 5, of a sleeve 6.
  • the latter has the shape of a parallelepiped with trapezoidal section whose small base 6a is turned radially towards the inside of the engine and therefore "looks" at the top of the blade of the blade 1 while that the large base 6b is facing outwards.
  • the bore 5 of diameter D is drilled right through between the bases 6a and 6b.
  • the socket also has two holes 7 made longitudinally between the downstream face 6c, orthogonal to the bases 6a, 6b and the upstream, inclined face 6d and are symmetrical with respect to a plane containing the axis of the bore 5.
  • the two holes 7 are spaced apart by a width D equal to the diameter of bore 5 which they partially pass through at about half height of the sleeve.
  • the pins 8 are longer than the holes 7 so that, once they are in place, they protrude from the downstream face 6c of the sleeve.
  • the turbojet engine housing is separated into two facing ferrules, one upstream 9 and the other downstream 10.
  • the upstream ferrule has at its downstream edge a connecting flange 9a (called upstream by analogy with the ferrule which carries it) and has bosses 9b projecting externally from the ferrule 9.
  • bosses 9b In the bosses 9b, holes 9c are formed in the form of trapezoidal section parallelepipeds capable of receiving the sockets 6 carried by the vanes 1.
  • the housings 9c have the same dimension as the sockets 6 and therefore open freely on the rear face of the upstream flange 9a, so that once in place, the sockets 6 are flush with the rear edge of the upstream flange 9a.
  • tapped holes 9d are made for the connection with the downstream ferrule 10.
  • the downstream ferrule 10 has on its front edge a downstream flange 10a which faces the flange 9a.
  • the flange 10a has holes 10b corresponding to the internal threads 9d of the upstream flange for securing the flanges to each other by screws 11.
  • the flange 10a On its front edge, the flange 10a has blind holes 10c produced in pairs, the holes of a pair having the same spacing D as the holes 7 in the socket 6.
  • the blind holes 10c can be replaced by a simple annular groove.
  • the blades 1 fitted with their bushing 6 are mounted in the casing by positioning the bushings 6 in their housings 9c of the upstream ferrule 9.
  • the downstream ferrule 10 is brought together and the flange 10a is oriented so that the part keys 8 protruding from the faces 6c of the sockets 6, enters the blind holes 10c of the flange 10a, which locks the pivots of the blades and assumes the maintenance of the sockets 6 in the flanges.
  • FIGS. 4 and 4a a variant of the blade journal has been shown in cross section at the level of the groove, capable of ensuring the limitation of the angular amplitude of the blades.
  • the assembly according to the invention has the advantage of allowing easy positioning and radial retention of small-sized blades produced by spinning and does not require, for their radial positioning, shoulders of diameter greater than the thickness of the blade. dawn, which was the case previously.
  • this embodiment it is possible to use vanes without extra thicknesses and therefore to make savings in manufacturing costs.

Description

L'invention concerne les compresseurs de turbomachine et plus particulièrement à l'intérieur de ceux-ci les moyens de rétention radiale et de limitation de débattement angulaire des aubes à calage variable.The invention relates to turbomachine compressors and more particularly inside these means for radial retention and limitation of angular displacement of the variable pitch vanes.

L'adaptation de l'orientation des ailettes de stator des différents étages de compresseur est particulièrement souhaitable lorsqu'on désire par exemple pour les différents étages, à un régime donné, la plus grande pression possible tout en conservant une marge au pompage suffisante.The adaptation of the orientation of the stator fins of the different compressor stages is particularly desirable when it is desired, for example for the different stages, at a given speed, the greatest possible pressure while retaining a sufficient pumping margin.

Les aubes de stator à calage variable sont en général commandées en rotation par des biellettes extérieures au carter et reliées entre elles par un anneau de commande.The stator vanes with variable setting are generally controlled in rotation by rods external to the casing and connected together by a control ring.

Pour pouvoir tourner sur elles-mêmes, les aubes possèdent généralement des tourillons en tête et en pied qui sont montés tournants dans des douilles.To be able to turn on themselves, the blades generally have head and foot journals which are mounted to rotate in sockets.

Le document FR-A 2 524 934 décrit ainsi une aube possédant en pied une douille percée d'un alésage dans lequel le pied d'aube tourillonne, la douille pouvant comporter une face en losange dont les bords parallèles assurent une fonction de limitation du débattement angulaire maximal toléré pour une aube, de façon à ce que, si un des leviers de commande d'une aube venait à se rompre, celle-ci ne puisse se mettre en drapeau ou en travers de l'écoulement ce qui entraînerait un pompage probable de l'étage tout entier.Document FR-A 2 524 934 thus describes a blade having at its bottom a bushing pierced with a bore in which the blade root swivels, the bushing being able to comprise a diamond face whose parallel edges ensure a function of limitation of the deflection maximum angular tolerated for a blade, so that, if one of the control levers of a blade breaks, it cannot be feathered or cross the flow which would cause a probable pumping of the entire floor.

Le document US A-3 029 067 montre des aubes à calage variable dont le pied comporte un épaulement doté d'un fraisage contre lequel un organe d'arrêt peut venir buter pour limiter la rotation possible de l'aube. Mais ce dispositif est d'un montage assez complexe et limité à un compresseur de type centrifuge.Document US Pat. No. 3,029,067 shows blades with variable setting, the base of which has a shoulder provided with a milling against which a stop member can abut to limit the possible rotation of the blade. However, this device is of a rather complex assembly and limited to a centrifugal type compressor.

Le document GB-A 2 159 887 montre des aubes à calage variable dont le système de limitation angulaire est constitué par les vis de liaison de deux viroles adjacentes de carter.Document GB-A 2 159 887 shows variable-pitch vanes, the angular limitation system of which consists of the connecting screws of two adjacent casing ferrules.

La présente invention a pour but de simplifier le montage des aubes de stator à calage variable en réalisant un moyen de pivotement de l'aube qui assure également le positionnement et la rétention radiale de l'aube.The object of the present invention is to simplify the mounting of the stator vanes with variable setting by producing a means of pivoting the blade which also ensures the positioning and the radial retention of the blade.

L'invention a également pour but dans une de ces variantes d'assurer, tout aussi simplement la limitation du débattement angulaire des aubes de stator afin de limiter les risques de mise en drapeau ou en travers de l'écoulement de l'aube en cas de rupture d'une biellette de commande.The invention also aims in one of these variants to ensure, quite simply, the limitation of the angular displacement of the stator blades in order to limit the risks of feathering or across the flow of the blade in the event breakage of a control rod.

L'invention a également pour but de réaliser la rétention de l'aube et éventuellement la limitation de débattement angulaire dans une zone du moteur située au niveau du carter externe afin d'en simplifier la mise en oeuvre et le positionnement.The invention also aims to achieve the retention of the blade and possibly the limitation of angular movement in an area of the engine located at the outer casing in order to simplify the implementation and positioning.

L'invention concerne un système de rétention d'aubes de stator à calage variable de compresseur de turbomachine, lesdites aubes étant disposées entre un anneau interne et un carter externe comportant au moins une virole amont et une virole aval munies chacune d'une bride, l'une amont comportant des logements pour des douilles percées d'un alésage radial à l'intérieur duquel tourillonne une aube, l'autre aval, lesdites brides se faisant face et étant solidarisées entre elles par des vis longitudinales intercalées entre les logements de la bride amont.The invention relates to a system for retaining stator vanes with variable setting of a turbomachine compressor, said vanes being disposed between an internal ring and an external casing comprising at least one upstream ferrule and a downstream ferrule each provided with a flange, one upstream comprising housings for bushings pierced with a radial bore inside which a vane journals, the other downstream, said flanges facing each other and being joined together by longitudinal screws interposed between the housings of the upstream flange.

Selon la caractéristique principale de l'invention chaque douille a une forme parallélépipédique à section trapézoïdale dont la petite base est située radialement vers l'intérieur et chaque aube est maintenue radialement dans la douille au moyen de deux goupilles parallèles disposées longitudinalement, lesdites goupilles traversant la douille et coopérant avec une gorge au moins partiellement annulaire du tourillon.According to the main characteristic of the invention, each socket has a rectangular shape with a trapezoidal section, the small base of which is located radially inwards and each blade is held radially in the socket at by means of two parallel pins arranged longitudinally, said pins passing through the sleeve and cooperating with an at least partially annular groove in the journal.

D'autres caractéristiques seront précisées en regard des planches de dessins annexées et du complément de description suivant s'y rapportant.Other characteristics will be specified with reference to the accompanying drawings and the following additional description relating thereto.

Parmis les planches jointes,

  • la figure 1 montre une vue écorchée d'un stator de turbomachine incorporant l'invention avec la douille montée sur une aube et non encore installée dans son carter.
  • la figure 2 est une vue partielle d'une aube dont le tourillon comporte les moyens de rétention décrit dans l'invention.
  • la figure 3 est une vue en perspective partielle d'un étage de stator selon l'invention assemblé et dont l'anneau de commande est partiellement représenté.
  • les figures 4 et 4a sont une coupe au niveau de la gorge du tourillon d'aube de la variante apte à assurer la limitation du débattement angulaire de l'aube dans sa douille.
Among the attached boards,
  • FIG. 1 shows a cutaway view of a turbomachine stator incorporating the invention with the bush mounted on a blade and not yet installed in its casing.
  • Figure 2 is a partial view of a blade whose pin comprises the retention means described in the invention.
  • Figure 3 is a partial perspective view of a stator stage according to the invention assembled and whose control ring is partially shown.
  • Figures 4 and 4a are a section at the groove of the blade journal of the variant capable of ensuring the limitation of the angular movement of the blade in its socket.

Selon l'invention et en regard de la figure 1, l'étage de stator à calage variable comporte des aubes 1 comportant en tête un tourillon 2 surmonté d'une partie filetée destinée à la solidarisation de l'aube avec une biellette de commande 3. Environ à la moitié de sa hauteur, le tourillon 2 comporte une gorge annulaire à section semi-circulaire 4. Le tourillon 2 est engagé dans l'alésage radial 5, d'une douille 6. Celle-ci a une forme de parallélépipède à section trapézoïdale dont la petite base 6a est tournée radialement vers l'intérieur du moteur et "regarde" donc le sommet de la pale de l'aube 1 tandis que la grande base 6b est tournée vers l'extérieur. L'alésage 5 de diamètre D est percé de part en part entre les bases 6a et 6b. La douille comporte également deux perçages 7 réalisés longitudinalement entre la face 6c, aval, orthogonale aux bases 6a, 6b et la face,amont, inclinée 6d et sont symétriques par rapport à un plan contenant l'axe de l'alésage 5. Les deux perçages 7 sont espacés d'une largeur D égale au diamètre de l'alésage 5 qu'ils traversent partiellement à mi hauteur environ de la douille. Lorsque la douille 6 est installée sur le tourillon d'aube 2, deux goupilles 8 sont disposées dans les perçages 7 et viennent s'engager dans la gorge 4 du tourillon de façon à solidariser la douille et le tourillon 2 dans le sens axial de l'aube (ou radial de la turbomachine).According to the invention and with reference to FIG. 1, the stator stage with variable setting comprises vanes 1 comprising at the head a journal 2 surmounted by a threaded part intended for securing the vane with a control rod 3 About half of its height, the pin 2 has an annular groove with semi-circular section 4. The pin 2 is engaged in the radial bore 5, of a sleeve 6. The latter has the shape of a parallelepiped with trapezoidal section whose small base 6a is turned radially towards the inside of the engine and therefore "looks" at the top of the blade of the blade 1 while that the large base 6b is facing outwards. The bore 5 of diameter D is drilled right through between the bases 6a and 6b. The socket also has two holes 7 made longitudinally between the downstream face 6c, orthogonal to the bases 6a, 6b and the upstream, inclined face 6d and are symmetrical with respect to a plane containing the axis of the bore 5. The two holes 7 are spaced apart by a width D equal to the diameter of bore 5 which they partially pass through at about half height of the sleeve. When the bush 6 is installed on the blade journal 2, two pins 8 are arranged in the holes 7 and engage in the groove 4 of the journal so as to secure the bush and the journal 2 in the axial direction of the 'blade (or radial of the turbomachine).

Les goupilles 8 sont plus longues que les perçages 7 de sorte qu'une fois mises en place elles fassent saillies hors de la face aval 6c de la douille.The pins 8 are longer than the holes 7 so that, once they are in place, they protrude from the downstream face 6c of the sleeve.

Le carter du turboréacteur est séparé en deux viroles se faisant face, l'une amont 9 et l'autre aval 10.The turbojet engine housing is separated into two facing ferrules, one upstream 9 and the other downstream 10.

La virole amont comporte à son bord aval une bride de liaison 9a (dite amont par analogie avec la virole qui la porte) et comporte des bossages 9b faisant saillie extérieurement à la virole 9. Dans les bossages 9b, sont percés des logements 9c en forme de parallélépipèdes à section trapézoïdale aptes à recevoir les douilles 6 portées par les aubes 1. Les logements 9c ont la même dimension que les douilles 6 et débouchent donc librement sur la face arrière de la bride amont 9a, de telle sorte qu'une fois en place, les douilles 6 affleurent le bord arrière de la bride amont 9a. Entre les bossages 9b, des trous taraudés 9d sont réalisés pour la solidarisation avec la virole aval 10. La virole aval 10 comporte sur son bord avant une bride aval 10a qui fait face à la bride 9a. La bride 10a comporte des perçages 10b correspondant aux taraudages 9d de la bride amont pour la solidarisation des brides entre elles par des vis 11.The upstream ferrule has at its downstream edge a connecting flange 9a (called upstream by analogy with the ferrule which carries it) and has bosses 9b projecting externally from the ferrule 9. In the bosses 9b, holes 9c are formed in the form of trapezoidal section parallelepipeds capable of receiving the sockets 6 carried by the vanes 1. The housings 9c have the same dimension as the sockets 6 and therefore open freely on the rear face of the upstream flange 9a, so that once in place, the sockets 6 are flush with the rear edge of the upstream flange 9a. Between the bosses 9b, tapped holes 9d are made for the connection with the downstream ferrule 10. The downstream ferrule 10 has on its front edge a downstream flange 10a which faces the flange 9a. The flange 10a has holes 10b corresponding to the internal threads 9d of the upstream flange for securing the flanges to each other by screws 11.

Sur son bord avant, la bride 10a comporte des trous borgnes 10c réalisés par paires, les trous d'une paire ayant le même écartement D que les perçages 7 de la douille 6.On its front edge, the flange 10a has blind holes 10c produced in pairs, the holes of a pair having the same spacing D as the holes 7 in the socket 6.

En variante les trous borgnes 10c peuvent être remplacés par une simple rainure annulaire.As a variant, the blind holes 10c can be replaced by a simple annular groove.

Le montage des aubes 1 équipées de leur douille 6 dans le carter s'effectue en positionnant les douilles 6 dans leurs logements 9c de la virole amont 9. On rapproche ensuite la virole aval 10 et on oriente la bride 10a de telle façon que la partie des clavettes 8 faisant saillie hors des faces 6c des douilles 6, pénètre dans les trous borgnes 10c de la bride 10a, ce qui verrouille les pivots d'aubes et assume le maintien des douilles 6 dans les brides.The blades 1 fitted with their bushing 6 are mounted in the casing by positioning the bushings 6 in their housings 9c of the upstream ferrule 9. Next, the downstream ferrule 10 is brought together and the flange 10a is oriented so that the part keys 8 protruding from the faces 6c of the sockets 6, enters the blind holes 10c of the flange 10a, which locks the pivots of the blades and assumes the maintenance of the sockets 6 in the flanges.

Lorsque les brides 9a, 10a ont été solidarisées par les vis 11, seules dépassent de la virole 9 les extrémités filetées des aubes 1 (voir figure 3). On peut alors assembler de façon connue les biellettes 3 et l'anneau de commande 12.When the flanges 9a, 10a have been secured by the screws 11, only the threaded ends of the blades 1 protrude from the ferrule 9 (see FIG. 3). The rods 3 and the control ring 12 can then be assembled in a known manner.

Aux figures 4 et 4a, on a montré en section droite au niveau de la gorge une variante du tourillon d'aube apte à assurer la limitation d'amplitude angulaire des aubes.In FIGS. 4 and 4a, a variant of the blade journal has been shown in cross section at the level of the groove, capable of ensuring the limitation of the angular amplitude of the blades.

On a remplacé ici la gorge annulaire 4 du tourillon par deux gorges 4' symétriques d'axes parallèles séparées par deux dents 4''. Le montage s'effectue de façon identique au montage précédent mais si en fonctionnement, une biellette 12 vient à se rompre, le débattement angulaire de l'aube est limité par les dents 4'' qui viennent en butée contre les goupilles 8 logées dans les gorges 4'.
Ainsi les aubes ne peuvent se mettre ni en drapeau ni en travers de l'écoulement.We replaced here the annular groove 4 of the journal by two symmetrical grooves 4 'with parallel axes separated by two teeth 4''. The assembly is carried out in the same way as the previous assembly but if in operation, a connecting rod 12 breaks, the angular movement of the blade is limited by the teeth 4 '' which abut against the pins 8 housed in the 4 'gorges.
Thus the blades cannot be feathered or cross the flow.

Le montage selon l'invention a pour avantage de permettre le positionnement facile et la rétention radiale d'aubes de petite dimension réalisées par filage et ne nécessitent pas pour leur positionnement radial d'épaulements de diamètre supérieur à l'épaisseur de la pale d'aube, ce qui était le cas antérieurement. Ainsi par cette réalisation on peut utiliser des aubes sans surépaisseurs et donc réaliser des gains de coûts en fabrication.The assembly according to the invention has the advantage of allowing easy positioning and radial retention of small-sized blades produced by spinning and does not require, for their radial positioning, shoulders of diameter greater than the thickness of the blade. dawn, which was the case previously. Thus, by this embodiment, it is possible to use vanes without extra thicknesses and therefore to make savings in manufacturing costs.

Claims (5)

  1. System for retaining variable pitch stator blades (1) of a turboshaft engine compressor, the said blades being arranged between an inner annulus and an outer casing (9, 10), the said casing comprising at least one upstream shell (9) and a downstream shell (10) each fitted with a flange, the upstream one (9a) comprising housings (9c) for bushes (6) drilled with a radial hole (5) in which turns a blade 1, the other one, downstream (10a), the said flanges facing each other and joined together by bolts (11) oriented longitudinally and spaced in between the housings (9c) of the upstream flange (9a),
    characterised in that,
    each bush has a parallelepipedic shape of trapezoidal cross section whose smaller base (6a) is situated radially towards the interior and in that the blade (1) is held radially in the bush (6) by means of two parallel cotter pins (8) placed longitudinally, the said cotter pins passing through the bush (6) and working in conjunction with an at least partially annular throat (4, 4') on the shaft .
  2. System for retaining blades in accordance with Claim 1, characterised in that each housing (9c) is formed in a castellated part (9b) of the upstream shell (9a) the said castellations being open at the rear side in such a way that the bush (6) is flush with the rear face of the said upstream flange.
  3. System for retaining blades in accordance with Claims 1 or 2, characterised in that the cotter pins (8) are placed in two longitudinal holes (7) in the bush (6) with their axes symmetrical in relation to a plane containing the axis of the hole (5) and separated from each other by distance equal to the diameter of the hole (5).
  4. System for retaining blades in accordance with either of Claims 1 or 2, characterised in that the cotter pins (8) have a length such that once in place they project beyond the rear face (6c) of the bush and in that the downstream flange (10a) comprises blind holes (10c) to receive the downstream end of the cotter pins (8) so that the bush (6) is retained radially in its housing (9c).
  5. System for retaining blades in accordance with any of Claims 1 to 4, characterised in that the blade shaft (2) comprises two symmetrical throats (4') with parallel axes separated by two teeth (4'') capable of butting against the cotter pins (8) to limit the possible rotation of the blade.
EP90400669A 1989-03-15 1990-03-14 Retention system for variable pitch stator blades Expired - Lifetime EP0388285B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903375 1989-03-15
FR8903375A FR2644525B1 (en) 1989-03-15 1989-03-15 VARIABLE SETTING STATOR VANE RETENTION SYSTEM

Publications (2)

Publication Number Publication Date
EP0388285A1 EP0388285A1 (en) 1990-09-19
EP0388285B1 true EP0388285B1 (en) 1993-05-19

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EP90400669A Expired - Lifetime EP0388285B1 (en) 1989-03-15 1990-03-14 Retention system for variable pitch stator blades

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US (1) US5061152A (en)
EP (1) EP0388285B1 (en)
DE (1) DE69001630T2 (en)
FR (1) FR2644525B1 (en)

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GB0116675D0 (en) * 2001-07-07 2001-08-29 Lucas Industries Ltd Vane actuator
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US7278819B2 (en) * 2005-07-05 2007-10-09 General Electric Company Variable stator vane lever arm assembly and method of assembling same
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
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FR2995934B1 (en) * 2012-09-24 2018-06-01 Safran Aircraft Engines AUBE FOR TURBOMACHINE RECTIFIER
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FR2644525B1 (en) 1991-05-24
DE69001630D1 (en) 1993-06-24
US5061152A (en) 1991-10-29
DE69001630T2 (en) 1993-10-21
EP0388285A1 (en) 1990-09-19
FR2644525A1 (en) 1990-09-21

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