EP1489267B1 - Adjusting device for the vanes of two stages in a turbo machine - Google Patents

Adjusting device for the vanes of two stages in a turbo machine Download PDF

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Publication number
EP1489267B1
EP1489267B1 EP04102806A EP04102806A EP1489267B1 EP 1489267 B1 EP1489267 B1 EP 1489267B1 EP 04102806 A EP04102806 A EP 04102806A EP 04102806 A EP04102806 A EP 04102806A EP 1489267 B1 EP1489267 B1 EP 1489267B1
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EP
European Patent Office
Prior art keywords
groove
stages
synchronization
casing
bellcrank
Prior art date
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Active
Application number
EP04102806A
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German (de)
French (fr)
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EP1489267A1 (en
Inventor
Florent Raine
Dominique Raulin
Alain Jean Charles Chatel
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1489267A1 publication Critical patent/EP1489267A1/en
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Classifications

    • 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
    • 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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes

Definitions

  • the invention relates to a variable setting device for two stator stages on a turbojet engine.
  • the circular blade stages mounted on the stator of the turbojet engines are often variable pitch, that is to say that the blades are capable of pivoting about their axis in order to vary the flow correction characteristics that they impose. to gases.
  • the adjusting device is mounted outside the housing and includes an actuator mechanism and a transmission mechanism to the blade pivots.
  • the actuator means is connected to the ring by means of a transmission which may comprise a synchronization bar starting from the rod of the jack, a connecting rod articulated to the ring and a bell crank joining the synchronization bar to the control rod of the the ring and articulated to them.
  • the horns are pieces pivoting about a central axis and provided with two branches forming an angle, one of which is connected to the bar of synchronization and the other to the control rod.
  • the movement of the jack moves the synchronization bar, which turns the horn.
  • the movement is communicated to the connecting rod, which pulls or pushes on the synchronization ring and rotates it around the casing, finally tilting the blade pivot control levers.
  • US 3,083,892 A discloses a device where the cylinder rod is connected to a cam which it rotates.
  • the cam carries a groove in which is engaged a pin of a rod for controlling the synchronization ring. It is thus possible to impose non-linear control laws, sinusoidal for example, between the cylinder rod and the synchronization ring.
  • a single blade stage is controlled by the aforementioned means of the rotating cam and by a few others which have nothing to do with the invention.
  • the rotating cam is added only to obtain the nonlinear control law. It should probably have a large area to accommodate a groove allowing irregular control laws or large amplitude.
  • the different control of two blade stages by a single actuator means is not solved by this patent.
  • the rotating cam is similar in shape to a horn, and the adaptation of a groove and a pin sliding in an existing horn is disadvantageous to control several floors at a time, the increase in the area of horns being problematic because of their proximity to the crankcase. Finally, the important efforts to develop in the puppet discourage weakening it with a long groove.
  • the invention relates to a device for setting a non-linear law and different of several stages of blades at a time by a device also different from that of the aforementioned prior art.
  • Document US Pat. No. 3,066,488 relates to a variable pitch assembly comprising a housing and a variable setting device with two stages of stator vanes, arranged on the housing and comprising an actuating mechanism and, for each of the stages , a horn pivoting on an axis of the housing and a control rod of the stage connected to a branch of the horn, a synchronizing bar being connected to another branch of at least one of the horns to drive, the bar of link being connected to the horn which it drives by a connection with groove and sliding pin in the groove
  • the invention is characterized in that one of the bars synchronization is connected to the housing by a connection groove and pin sliding in the groove.
  • a turbojet casing carries the reference 1; blades (only one of which is shown) 2 are mounted internally on external pivots 3 passing through the casing 1 and on unrepresented inner pivots and joined by a connecting ring; each of the blades 2 is adjusted by the device that will now be described. It comprises levers 4 mounted on the outer pivots 3, synchronization rings 5 each associated with a stage of the blades 2, extending next to them and to which the ends of the levers 4 are rotatably mounted, connecting rods 6 which are screw-type turnbuckles and which extend tangentially to the rings 5, and as shown in FIG.
  • horns 7 and 8 to which the ends of the rods 6 opposite the timing rings 5 are mounted rotary, a synchronization bar 9 and a jack 10 having a rod 11 actuating one of the horns 7 and whose body is mounted on a casing 12 of the housing 1, pivotally about a pin 13.
  • the synchronizing bar 9 unites two branches 15 and 16 horns 7 and 8 hinged thereto, said branches 15 and 16 being opposed to branches 17 and 18 to which the rods 6 are articulated; the bellcrank 7 further comprises a branch 19 to which the rod 11 is articulated to control the movement of the entire mechanism.
  • the horns 7 and 8 are rotatably mounted on the housing 12, about axes 20 and 21 parallel to each other.
  • the movements of the rod 11 cause a rotation of the horn 7, and another of the bellcrank 8 by the synchronization bar 9; the rotations of the horns 7 and 8 in turn move the connecting rods 6, the rings 5, the levers 4 and the blades 2 by turning them by the desired amount, the control law depending in particular on the lengths and angles of the branches 15 , 16, 17 and 18.
  • the synchronizing bar 9 is lined with a lug 22 which penetrates into a groove 23 hollowed out of the casing 12.
  • a second groove 26 is made in the second horn 8 to receive a lug 27 to the lug. end of the synchronization bar 9.
  • the direction of the synchronization bar 9 is imposed on all the positions of deployment of the rod 11 of the cylinder 10 by the groove 23.
  • the rotation angles of the horns 7 and 8 vary in different values.
  • the groove 23 has a shape and a direction determined to give the desired control law for the blade stage associated with the second horn 8. It is important to note that, thanks to the lever length provided by the synchronization bar 9 small deviations of the groove 23 can produce large angle variations of the second bellcrank 8.
  • the second groove 26 serves to restore the isostaticity of the mechanism while helping to define the control law. A second groove 26 short, not extending the second horn 8, will often be sufficient. FIGS.
  • 3a, 3b and 3c illustrate a situation where the end lug 27 of the synchronization bar 9 is close to the same end of the second groove 26 at the extreme positions of the rod 11 of the jack 10 (in FIGS. 3c), while it is close to the opposite end of the second groove 26 for an average deployment of the rod 11 ( Figure 3b).
  • the control law generally depends on a large number of factors, essentially on the directions and shapes of the grooves 23 and 26 and their positions relative to the horns 7 and 8. In the example considered here, two main stages can be distinguished. some movement.
  • the first groove 23 is first approximately parallel to the path of the point of articulation of the synchronization bar 9 to first horn 7, so that the synchronization bar 9 lowers without much change of inclination; but the direction of the second groove induces a greater rotation of the second horn 8 than that of the first horn 7 as the pin 27 moves in the second groove 26.
  • the invention could be implemented in other situations, and in particular to control a greater number of blade stages. It would then be implemented in a significant number of synchronization bars. These synchronization bars could, according to existing devices, be successive, that is to say, connect the neighboring horns and extend in a chain, or be parallel and extend to a common horn or even up to the actuator element itself. This is without consequence for the invention.

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

Description

L'invention a trait a un dispositif de calage variable de deux étages de stator sur un turboréacteur.The invention relates to a variable setting device for two stator stages on a turbojet engine.

Les étages circulaires d'aubes montés sur le stator des turboréacteurs sont souvent à calage variable, c'est-à-dire que les aubes sont capables de pivoter autour de leur axe afin de varier les caractéristiques de redressement d'écoulement qu'elles imposent aux gaz. Le dispositif de réglage est monté à l'extérieur du carter et comprend un mécanisme actionneur ainsi qu'un mécanisme de transmission aux pivots d'aubes. Il existe de nombreuses variantes, mais qui comprennent en général un levier de commande de chacune des aubes, un anneau de synchronisation disposé autour du carter et auquel les leviers associés aux aubes d'un même étage sont tous reliés, ainsi qu'un moyen actionneur constitué le plus souvent par un vérin dont la tige est déployée ou rétractée. Le moyen actionneur est relié à l'anneau par le truchement d'une transmission pouvant comprendre une barre de synchronisation partant de la tige du vérin, une bielle articulée à l'anneau et un guignol joignant la barre de synchronisation à la bielle de commande de l'anneau et articulé à elles. Les guignols sont des pièces pivotant autour d'un axe central et munies de deux branches formant un angle dont l'une est reliée à la barre de synchronisation et l'autre à la bielle de commande. Le mouvement du vérin déplace la barre de synchronisation, qui fait tourner le guignol. Le mouvement est communiqué à la bielle, qui tire ou pousse sur l'anneau de synchronisation et le fait tourner autour du carter, en basculant finalement les leviers de commande de pivotement des aubes.The circular blade stages mounted on the stator of the turbojet engines are often variable pitch, that is to say that the blades are capable of pivoting about their axis in order to vary the flow correction characteristics that they impose. to gases. The adjusting device is mounted outside the housing and includes an actuator mechanism and a transmission mechanism to the blade pivots. There are many variants, but generally include a control lever of each blade, a synchronization ring disposed around the housing and to which the levers associated with the blades of the same floor are all connected, and an actuator means most often constituted by a cylinder whose rod is deployed or retracted. The actuator means is connected to the ring by means of a transmission which may comprise a synchronization bar starting from the rod of the jack, a connecting rod articulated to the ring and a bell crank joining the synchronization bar to the control rod of the the ring and articulated to them. The horns are pieces pivoting about a central axis and provided with two branches forming an angle, one of which is connected to the bar of synchronization and the other to the control rod. The movement of the jack moves the synchronization bar, which turns the horn. The movement is communicated to the connecting rod, which pulls or pushes on the synchronization ring and rotates it around the casing, finally tilting the blade pivot control levers.

Quand plusieurs étages d'aubes ont le calage variable, il est fréquent qu'un seul actionneur les commande tous. Le reste du dispositif est multiplié par le nombre d'étages, les barres de synchronisation soit aboutissent toutes à l'actionneur, soit forment une chaîne passant par les guignols. Un tel dispositif n'autorise que des commandes simples des étages d'aubes, où la rotation des aubes est plus ou moins une fonction linéaire du déplacement relatif du vérin. Cela n'est pas toujours souhaitable, d'autant moins que quand plusieurs étages d'aubes sont commandés par un même moyen actionneur, il peut être souhaitable de les commander successivement, ou par des lois de commande complètement différentes, afin d'obtenir le meilleur réglage du turboréacteur pour les différents régimes considérés.When several stages of blades have the variable setting, it is common that a single actuator controls them all. The rest of the device is multiplied by the number of stages, the synchronization bars either all lead to the actuator, or form a chain passing through the horns. Such a device allows only simple controls of the blade stages, where the rotation of the blades is more or less a linear function of the relative displacement of the cylinder. This is not always desirable, especially since when several stages of blades are controlled by the same actuator means, it may be desirable to order them successively, or by completely different control laws, in order to obtain the better adjustment of the turbojet engine for the various schemes considered.

Le document US 3 083 892 A décrit un dispositif où la tige du vérin est reliée à une came qu'elle fait tourner. La came porte une rainure dans laquelle est engagé un ergot d'une tige servant à la commande de l'anneau de synchronisation. Il est ainsi possible d'imposer des lois de commande non linéaires, sinusoïdales par exemple, entre la tige du vérin et l'anneau de synchronisation. Un étage d'aubes unique est commandé par le moyen précité de la came tournante et par quelques autres qui n'ont pas de rapport avec l'invention.US 3,083,892 A discloses a device where the cylinder rod is connected to a cam which it rotates. The cam carries a groove in which is engaged a pin of a rod for controlling the synchronization ring. It is thus possible to impose non-linear control laws, sinusoidal for example, between the cylinder rod and the synchronization ring. A single blade stage is controlled by the aforementioned means of the rotating cam and by a few others which have nothing to do with the invention.

La came tournante est ajoutée seulement pour obtenir la loi de commande non linéaire. Elle devrait probablement comporter une grande superficie pour loger une rainure permettant des lois de commande irrégulière ou de grande amplitude. La commande différente de deux étages d'aubes par un moyen actionneur unique n'est pas résolue par ce brevet. La came tournante ressemble par sa forme à un guignol, et l'adaptation d'une rainure et d'un ergot y coulissant dans un guignol existant serait désavantageuse pour commander plusieurs étages à la fois, l'accroissement de la superficie des guignols étant problématique en raison de leur proximité sur le carter. Enfin, les efforts importants devant se développer dans le guignol découragent de l'affaiblir par une rainure longue. L'invention est relative à un dispositif permettant un calage à lois non linéaires et différentes de plusieurs étages d'aubes à la fois par un dispositif également différent de celui de l'art antérieur précité.The rotating cam is added only to obtain the nonlinear control law. It should probably have a large area to accommodate a groove allowing irregular control laws or large amplitude. The different control of two blade stages by a single actuator means is not solved by this patent. The rotating cam is similar in shape to a horn, and the adaptation of a groove and a pin sliding in an existing horn is disadvantageous to control several floors at a time, the increase in the area of horns being problematic because of their proximity to the crankcase. Finally, the important efforts to develop in the puppet discourage weakening it with a long groove. The invention relates to a device for setting a non-linear law and different of several stages of blades at a time by a device also different from that of the aforementioned prior art.

Le document US-A-3 066 488 est relatif à un ensemble de calage variable comprenant un carter et un dispositif de calage variable de deux étages d'aubes de stator, disposé sur le carter et comprenant un mécanisme actionneur et, pour chacun des étages, un guignol pivotant sur un axe du carter et une bielle de commande de l'étage reliée à une branche du guignol, une barre de synchronisation étant reliée à une autre branche d'au moins un des guignols pour l'entraîner, la barre de liaison étant reliée au guignol qu'elle entraîne par une liaison à rainure et ergot coulissant dans la rainure L'invention est caractérisée en ce qu'une des barres de synchronisation est reliée au carter par une liaison à rainure et ergot coulissant dans la rainure.Document US Pat. No. 3,066,488 relates to a variable pitch assembly comprising a housing and a variable setting device with two stages of stator vanes, arranged on the housing and comprising an actuating mechanism and, for each of the stages , a horn pivoting on an axis of the housing and a control rod of the stage connected to a branch of the horn, a synchronizing bar being connected to another branch of at least one of the horns to drive, the bar of link being connected to the horn which it drives by a connection with groove and sliding pin in the groove The invention is characterized in that one of the bars synchronization is connected to the housing by a connection groove and pin sliding in the groove.

L'invention sera maintenant décrite au moyen des figures suivantes :

  • la figure 1 illustre le mécanisme ;
  • la figure 2 est une vue de détail ; et
  • les figures 3a, 3b et 3c illustrent une loi de commande possible.
The invention will now be described by means of the following figures:
  • Figure 1 illustrates the mechanism;
  • Figure 2 is a detail view; and
  • Figures 3a, 3b and 3c illustrate a possible control law.

Le système considéré dans son ensemble apparaît à la figure 1. Un carter de turboréacteur porte la référence 1 ; des aubes (dont une seule est représentée) 2 sont montées à l'intérieur sur des pivots extérieurs 3 traversant le carter 1 et sur des pivots intérieurs non représentés et unis par un anneau de liaison ; chacune des aubes 2 est réglée par le dispositif qu'on va maintenant décrire. Il comprend des leviers 4 montés sur les pivots extérieurs 3, des anneaux de synchronisation 5 associés chacun à un étage des aubes 2, s'étendant à côté de ceux-ci et auxquels les extrémités des leviers 4 sont montés de façon rotative, des bielles 6 de commande qui sont des ridoirs à vis et qui s'étendent tangentiellement aux anneaux 5, et comme on le montre à la figure 2, des guignols 7 et 8 auxquels les extrémités des bielles 6 opposées aux anneaux de synchronisation 5 sont montées de façon rotative, une barre de synchronisation 9 et un vérin 10 ayant une tige 11 actionnant un des guignols 7 et dont le corps est monté sur un boîtier 12 du carter 1, de façon pivotante autour d'un tourillon 13. La barre de synchronisation 9 unit deux branches 15 et 16 des guignols 7 et 8 en leur étant articulée, lesdites branches 15 et 16 étant opposées à des branches 17 et 18 auxquelles les bielles 6 sont articulées ; le guignol 7 comprend encore une branche 19 à laquelle la tige 11 est articulée pour commander le mouvement de l'ensemble du mécanisme. Enfin, les guignols 7 et 8 sont montés tournants sur le boîtier 12, autour d'axes 20 et 21 parallèles entre eux.The system considered as a whole appears in FIG. 1. A turbojet casing carries the reference 1; blades (only one of which is shown) 2 are mounted internally on external pivots 3 passing through the casing 1 and on unrepresented inner pivots and joined by a connecting ring; each of the blades 2 is adjusted by the device that will now be described. It comprises levers 4 mounted on the outer pivots 3, synchronization rings 5 each associated with a stage of the blades 2, extending next to them and to which the ends of the levers 4 are rotatably mounted, connecting rods 6 which are screw-type turnbuckles and which extend tangentially to the rings 5, and as shown in FIG. 2, horns 7 and 8 to which the ends of the rods 6 opposite the timing rings 5 are mounted rotary, a synchronization bar 9 and a jack 10 having a rod 11 actuating one of the horns 7 and whose body is mounted on a casing 12 of the housing 1, pivotally about a pin 13. The synchronizing bar 9 unites two branches 15 and 16 horns 7 and 8 hinged thereto, said branches 15 and 16 being opposed to branches 17 and 18 to which the rods 6 are articulated; the bellcrank 7 further comprises a branch 19 to which the rod 11 is articulated to control the movement of the entire mechanism. Finally, the horns 7 and 8 are rotatably mounted on the housing 12, about axes 20 and 21 parallel to each other.

Les mouvements de la tige 11 provoquent une rotation du guignol 7, et une autre du guignol 8 par la barre de synchronisation 9 ; les rotations des guignols 7 et 8 meuvent à leur tour les bielles 6, les anneaux 5, les leviers 4 et les aubes 2 en les faisant tourner de la quantité voulue, la loi de commande dépendant en particulier des longueurs et des angles des branches 15, 16, 17 et 18.The movements of the rod 11 cause a rotation of the horn 7, and another of the bellcrank 8 by the synchronization bar 9; the rotations of the horns 7 and 8 in turn move the connecting rods 6, the rings 5, the levers 4 and the blades 2 by turning them by the desired amount, the control law depending in particular on the lengths and angles of the branches 15 , 16, 17 and 18.

Selon l'invention, la barre de synchronisation 9 est garnie d'un ergot 22 qui pénètre dans une rainure 23 creusée dans le boîtier 12. De plus, une seconde rainure 26 est opérée dans le second guignol 8 pour recevoir un ergot 27 à l'extrémité de la barre de synchronisation 9.According to the invention, the synchronizing bar 9 is lined with a lug 22 which penetrates into a groove 23 hollowed out of the casing 12. In addition, a second groove 26 is made in the second horn 8 to receive a lug 27 to the lug. end of the synchronization bar 9.

Une patte 25 fixée au boîtier 12, utilisée déjà pour soutenir les pivots des guignols 7 et 8 du côté opposé au boîtier 12 proprement dit, porte aussi une réplique 24 de la rainure 23, dans laquelle pénètre une autre portion de l'ergot 22 afin de compléter le guidage de la barre de synchronisation 9.A lug 25 fixed to the housing 12, already used to support the pivots of the horns 7 and 8 on the side opposite the housing 12 itself, also carries a replica 24 of the groove 23, into which another portion of the lug 22 penetrates so as to to complete the guidance of the synchronization bar 9.

La direction de la barre de synchronisation 9 est imposée à toutes les positions de déploiement de la tige 11 du vérin 10 par la rainure 23. Les angles de rotation des guignols 7 et 8 varient de valeurs différentes. La rainure 23 a une forme et une direction déterminées pour donner la loi de commande souhaitée pour l'étage d'aubes associé au second guignol 8. Il est important de remarquer que, grâce à la longueur de levier procurée par la barre de synchronisation 9, de petits écarts de la rainure 23 peuvent produire de grandes variations d'angle du second guignol 8. La seconde rainure 26 a pour fonction de rétablir l'isostaticité du mécanisme tout en contribuant à définir la loi de commande. Une seconde rainure 26 courte, n'étendant pas le second guignol 8, sera souvent suffisante. Les figures 3a, 3b et 3c illustrent une situation ou l'ergot 27 d'extrémité de la barre de synchronisation 9 est proche d'une même extrémité de la seconde rainure 26 aux positions extrêmes de la tige 11 du vérin 10 (aux figures 3a 3c), alors qu'il est proche de l'extrémité opposée de la seconde rainure 26 pour un déploiement moyen de la tige 11 (figure 3b).The direction of the synchronization bar 9 is imposed on all the positions of deployment of the rod 11 of the cylinder 10 by the groove 23. The rotation angles of the horns 7 and 8 vary in different values. The groove 23 has a shape and a direction determined to give the desired control law for the blade stage associated with the second horn 8. It is important to note that, thanks to the lever length provided by the synchronization bar 9 small deviations of the groove 23 can produce large angle variations of the second bellcrank 8. The second groove 26 serves to restore the isostaticity of the mechanism while helping to define the control law. A second groove 26 short, not extending the second horn 8, will often be sufficient. FIGS. 3a, 3b and 3c illustrate a situation where the end lug 27 of the synchronization bar 9 is close to the same end of the second groove 26 at the extreme positions of the rod 11 of the jack 10 (in FIGS. 3c), while it is close to the opposite end of the second groove 26 for an average deployment of the rod 11 (Figure 3b).

La loi de commande dépend en général d'un grand nombre de facteurs, essentiellement des directions et formes des rainures 23 et 26 et de leurs positions par rapport aux guignols 7 et 8. Dans l'exemple considéré ici, on peut distinguer deux étapes principales du mouvement. Dans la première, entre les états des figures 3a et 3b, la première rainure 23 est d'abord à peu près parallèle au trajet du point d'articulation de la barre de synchronisation 9 au premier guignol 7, de sorte que la barre de synchronisation 9 s'abaisse sans beaucoup changer d'inclinaison ; mais la direction de la seconde rainure induit une rotation plus importante du second guignol 8 que celle du premier guignol 7 à mesure que l'ergot 27 se déplace dans la seconde rainure 26.The control law generally depends on a large number of factors, essentially on the directions and shapes of the grooves 23 and 26 and their positions relative to the horns 7 and 8. In the example considered here, two main stages can be distinguished. some movement. In the first, between the states of Figures 3a and 3b, the first groove 23 is first approximately parallel to the path of the point of articulation of the synchronization bar 9 to first horn 7, so that the synchronization bar 9 lowers without much change of inclination; but the direction of the second groove induces a greater rotation of the second horn 8 than that of the first horn 7 as the pin 27 moves in the second groove 26.

Dans la seconde étape du mouvement, de la figure 3b à la figure 3c, l'obliquité de la première rainure 23 est insuffisante pour empêcher un redressement notable de la barre de synchronisation 9, qui s'accompagne d'un changement d'inclinaison qui diminue la rotation du second guignol 8. A l'état final de la figure 3c, le mouvement de ce second guignol 8 est moins important que celui du premier guignol 7.In the second step of the movement, from FIG. 3b to FIG. 3c, the obliqueness of the first groove 23 is insufficient to prevent a significant rectification of the synchronization bar 9, which is accompanied by a change of inclination which decreases the rotation of the second bellcrank 8. At the final state of FIG. 3c, the movement of this second bellcrank 8 is less important than that of the first bellcrank 7.

L'invention pourrait être mise en oeuvre dans d'autres situations, et notamment pour commander un nombre plus grand d'étages d'aubes. Elle serait alors mise en oeuvre en un nombre conséquent de barres de synchronisation. Ces barres de synchronisation pourraient, d'après les dispositifs existants, soit être successives, c'est-à-dire relier les guignols voisins et s'étendre en chaîne, soit être parallèles et s'étendre jusqu'à un guignol commun ou même jusqu'à l'élément actionneur lui-même. Cela est sans conséquence pour l'invention.The invention could be implemented in other situations, and in particular to control a greater number of blade stages. It would then be implemented in a significant number of synchronization bars. These synchronization bars could, according to existing devices, be successive, that is to say, connect the neighboring horns and extend in a chain, or be parallel and extend to a common horn or even up to the actuator element itself. This is without consequence for the invention.

Claims (3)

  1. Variable pitch assembly comprising the casing (1) and a variable pitch device having two stator blade stages (2) placed on a casing (1) and comprising an actuator mechanism and, for each of the stages, a bellcrank (7, 8) pivoting on an axis (20, 21) of the casing, and a control rod (6) of the stage connected to a branch of the bellcrank, a synchronization bar (9) being connected to another branch of at least one of the bellcranks in order to drive the same, the synchronization bar being connected to the bellcrank which it drives by another groove connection (26) and pin (27) sliding in the groove, characterized in that the synchronization bar is connected to the casing by a groove connection (23) and pin (22) sliding in the groove.
  2. Stator equipped with a variable pitch assembly according to claim 1.
  3. Turboshaft machine equipped with a stator according to claim 2.
EP04102806A 2003-06-20 2004-06-18 Adjusting device for the vanes of two stages in a turbo machine Active EP1489267B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350237 2003-06-20
FR0350237A FR2856424B1 (en) 2003-06-20 2003-06-20 DEVICE FOR VARIABLE SETTING OF TWO FLOORS OF BLADES FIXED ON A TURBOJETACTOR

Publications (2)

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EP1489267A1 EP1489267A1 (en) 2004-12-22
EP1489267B1 true EP1489267B1 (en) 2006-12-20

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EP04102806A Active EP1489267B1 (en) 2003-06-20 2004-06-18 Adjusting device for the vanes of two stages in a turbo machine

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US (1) US7037070B2 (en)
EP (1) EP1489267B1 (en)
JP (1) JP4050252B2 (en)
CA (1) CA2470081C (en)
DE (1) DE602004003744T2 (en)
FR (1) FR2856424B1 (en)
RU (1) RU2338932C2 (en)

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CA2470081A1 (en) 2004-12-20
RU2338932C2 (en) 2008-11-20
JP4050252B2 (en) 2008-02-20
JP2005009497A (en) 2005-01-13
FR2856424A1 (en) 2004-12-24
US7037070B2 (en) 2006-05-02
FR2856424B1 (en) 2005-09-23
DE602004003744T2 (en) 2007-10-11
DE602004003744D1 (en) 2007-02-01
EP1489267A1 (en) 2004-12-22
CA2470081C (en) 2011-08-02
RU2004118678A (en) 2006-01-10
US20050129510A1 (en) 2005-06-16

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