EP1489267A1 - 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
EP1489267A1
EP1489267A1 EP04102806A EP04102806A EP1489267A1 EP 1489267 A1 EP1489267 A1 EP 1489267A1 EP 04102806 A EP04102806 A EP 04102806A EP 04102806 A EP04102806 A EP 04102806A EP 1489267 A1 EP1489267 A1 EP 1489267A1
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EP
European Patent Office
Prior art keywords
groove
synchronization
stages
horn
rod
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04102806A
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German (de)
French (fr)
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EP1489267B1 (en
Inventor
Florent Raine
Dominique Raulin
Alain Jean Charles Chatel
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
SNECMA Moteurs SA
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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 device for variable setting of two stator stages on a turbojet.
  • the circular stages of blades mounted on the stator of turbojet engines are often calibrated variable, that is to say that the blades are capable of rotate around their axis to vary the flow correction features they impose on gases.
  • the adjustment device is mounted at outside the housing and includes a mechanism actuator as well as a transmission mechanism to paddle pivots.
  • a mechanism actuator as well as a transmission mechanism to paddle pivots.
  • the way actuator is connected to the ring through a transmission that may include a bar of synchronization from the cylinder rod, a connecting rod articulated to the ring and a puppet joining the bar of synchronization to the control rod of the ring and articulated to them.
  • the horns are pivoting parts around a central axis and equipped with two branches forming an angle, one of which is connected to the bar of synchronization and the other to the control rod.
  • the cylinder movement moves the synchronization bar, which turns the horn.
  • the movement is communicated to the connecting rod, which pulls or pushes on the ring synchronization and rotate it around the housing, by finally tipping the control levers of pivoting of the blades.
  • US 3,083,892 A discloses a device where the cylinder rod is connected to a cam it turns.
  • the cam carries a groove in which is engaged a pin of a rod used for the control of the synchronization ring. It is so possible to impose nonlinear 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 that have nothing to do with the invention.
  • the rotating cam is added only for obtain the nonlinear control law. She should probably have a large area to accommodate a groove allowing irregular control laws or large amplitude.
  • the different order of two blade stages by a single actuator means is not resolved by this patent.
  • the rotating cam looks like shape to a puppet, and the adaptation of a groove and a ergot y sliding in an existing puppet would disadvantageous for controlling several stages at a time, the increase in the area of the horns being problematic because of their proximity to the crankcase.
  • the important efforts to develop in the guignol discourage weakening it by a groove long.
  • the invention relates to a device allowing a calibration with nonlinear and different laws several stages of blades at a time by a device also different from that of the aforementioned prior art.
  • variable setting device of two stages of stator vanes, arranged on a housing and comprising an actuating mechanism and, for each of floors, a pivoting horn on an axle of the housing and a stage control rod connected to a branch of the horn, a synchronization bar being connected to another branch of at least one of the horns for driving it, characterized in that one of the bars synchronization is connected to the housing by a link with groove and sliding pin in the groove, and the horn that it leads by a link with groove and pin sliding in the groove.
  • a turbojet casing bears the reference 1; blades (only one of which is shown) 2 are mounted indoors on external pivots 3 passing through the housing 1 and on internal pivots not shown and united by a ring link ; each of the blades 2 is adjusted by the device that will now be described.
  • levers 4 mounted on the outer pivots 3, synchronization rings 5 each associated with a floor blades 2, extending next to them and to which the ends of the levers 4 are mounted so rotary, control rods 6 which are screw turnbuckles and which extend tangentially to rings 5, and as shown in Figure 2, horns 7 and 8 to which the ends of the rods 6 opposed to synchronization rings 5 are mounted rotatively, a synchronization bar 9 and a cylinder 10 having a rod 11 actuating one of the horns 7 and whose body is mounted on a casing 12 of the casing 1, pivotally about a pin 13.
  • the synchronization bar 9 unites two branches 15 and 16 horns 7 and 8 being hinged thereto, said branches 15 and 16 being opposed to branches 17 and 18 to which the connecting rods 6 are articulated; the guignol 7 still includes a branch 19 to which the rod 11 is hinged to control the movement of the whole mechanism.
  • the horns 7 and 8 are rotatably mounted on the housing 12, around 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 horn 8 by the synchronization bar 9; the rotations of the horns 7 and 8 move in turn the rods 6, the rings 5, the levers 4 and the blades 2 by rotating them of the desired quantity, the control law depending in particular lengths and angles of the branches 15, 16, 17 and 18.
  • the bar of synchronization 9 is lined with a pin 22 which penetrates in a groove 23 dug in the housing 12. From more, a second groove 26 is operated in the second guignol 8 to receive a lug 27 at the end of the synchronization bar 9.
  • the direction of the synchronization bar 9 is imposed on all deployment positions of the rod 11 of the cylinder 10 by the groove 23.
  • the angles of rotation of horns 7 and 8 vary in values different.
  • 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. is important to note that thanks to the length of lever provided by the synchronization bar 9, of small gaps in the groove 23 can produce large angle variations of the second hornet 8.
  • the second groove 26 has the function of restoring isostaticity of the mechanism while contributing to define the control law. A second groove 26 short, not extending the second horn 8, will be often enough.
  • Figures 3a, 3b and 3c illustrate a situation where the end pin 27 of the bar synchronization 9 is close to the same end of the second groove 26 at the extreme positions of the rod 11 of the cylinder 10 (in Figures 3a 3c), while it is close of the opposite end of the second groove 26 for a average deployment of the rod 11 ( Figure 3b).
  • the control law generally depends on a many factors, mainly directions and shapes of the grooves 23 and 26 and their positions with respect to horns 7 and 8. In the example considered here, we can distinguish two stages of the movement.
  • the first groove 23 is first roughly parallel to the path of the point of articulation of the synchronization bar 9 to first horn 7, so that the bar of synchronization 9 lowers without much change 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 especially to order a greater number of blade stages. She would be then implemented in a number of bars synchronization. These synchronization bars could, according to existing arrangements, be to be successive, that is to say to connect the horns neighbors and extend in a chain, ie be parallel and extend to a common puppet 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)

Abstract

The device has two stacks of stator blades, each with a control rod connected to a branch of each of two bell cranks. A synchronization rod of each stack is connected to another branch of each crank. The synchronization rod is connected to a casing by a connection having a groove (23) and a pin (22) sliding in the groove, and to each crank driven by another connection having groove (26) and a pin (27) sliding in the groove (26).

Description

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

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 stages of blades mounted on the stator of turbojet engines are often calibrated variable, that is to say that the blades are capable of rotate around their axis to vary the flow correction features they impose on gases. The adjustment device is mounted at outside the housing and includes a mechanism actuator as well as a transmission mechanism to paddle pivots. There are many variants, but which usually include a control lever of each of the blades, a synchronization ring arranged around the crankcase and to which the levers associated with blades of the same floor are all connected, as well as a medium actuator consisting mostly of a jack whose stem is extended or retracted. The way actuator is connected to the ring through a transmission that may include a bar of synchronization from the cylinder rod, a connecting rod articulated to the ring and a puppet joining the bar of synchronization to the control rod of the ring and articulated to them. The horns are pivoting parts around a central axis and equipped with two branches forming an angle, one of which is connected to the bar of synchronization and the other to the control rod. The cylinder movement moves the synchronization bar, which turns the horn. The movement is communicated to the connecting rod, which pulls or pushes on the ring synchronization and rotate it around the housing, by finally tipping the control levers of pivoting of the blades.

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 chaíne 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 for a single actuator order them all. The rest of the device is multiplied by the number of floors, the sync bars either all lead to the actuator, or form a chain passing by the horns. Such a device allows only simple floor commands of blades, where the rotation of the blades is more or less linear function of the relative displacement of the cylinder. it is not always desirable, especially since when several stages of blades are controlled by a same medium actuator, it may be desirable to order successively, or by order laws completely different, in order to get the best adjustment of the turbojet engine for different regimes 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 it turns. The cam carries a groove in which is engaged a pin of a rod used for the control of the synchronization ring. It is so possible to impose nonlinear 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 that 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 for obtain the nonlinear control law. She should probably have a large area to accommodate a groove allowing irregular control laws or large amplitude. The different order of two blade stages by a single actuator means is not resolved by this patent. The rotating cam looks like shape to a puppet, and the adaptation of a groove and a ergot y sliding in an existing puppet would disadvantageous for controlling several stages at a time, the increase in the area of the horns being problematic because of their proximity to the crankcase. Finally, the important efforts to develop in the guignol discourage weakening it by a groove long. The invention relates to a device allowing a calibration with nonlinear and different laws several stages of blades at a time by a device also different from that of the aforementioned prior art.

Sous sa forme la plus générale, elle est relative à un dispositif de calage variable de deux étages d'aubes de stator, disposé sur un 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'entraíner, caractérisé en ce qu'une des barres de synchronisation est reliée au carter par une liaison à rainure et ergot coulissant dans la rainure, et au guignol qu'elle entraíne par une liaison à rainure et ergot coulissant dans la rainure.In its most general form, it is relating to a variable setting device of two stages of stator vanes, arranged on a housing and comprising an actuating mechanism and, for each of floors, a pivoting horn on an axle of the housing and a stage control rod connected to a branch of the horn, a synchronization bar being connected to another branch of at least one of the horns for driving it, characterized in that one of the bars synchronization is connected to the housing by a link with groove and sliding pin in the groove, and the horn that it leads by a link with 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 apparaít 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 boítier 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 boítier 12, autour d'axes 20 et 21 parallèles entre eux.The system as a whole appears in Figure 1. A turbojet casing bears the reference 1; blades (only one of which is shown) 2 are mounted indoors on external pivots 3 passing through the housing 1 and on internal pivots not shown and united by a ring link ; each of the blades 2 is adjusted by the device that will now be described. It includes levers 4 mounted on the outer pivots 3, synchronization rings 5 each associated with a floor blades 2, extending next to them and to which the ends of the levers 4 are mounted so rotary, control rods 6 which are screw turnbuckles and which extend tangentially to rings 5, and as shown in Figure 2, horns 7 and 8 to which the ends of the rods 6 opposed to synchronization rings 5 are mounted rotatively, a synchronization bar 9 and a cylinder 10 having a rod 11 actuating one of the horns 7 and whose body is mounted on a casing 12 of the casing 1, pivotally about a pin 13. The synchronization bar 9 unites two branches 15 and 16 horns 7 and 8 being hinged thereto, said branches 15 and 16 being opposed to branches 17 and 18 to which the connecting rods 6 are articulated; the guignol 7 still includes a branch 19 to which the rod 11 is hinged to control the movement of the whole mechanism. Finally, the horns 7 and 8 are rotatably mounted on the housing 12, around 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 horn 8 by the synchronization bar 9; the rotations of the horns 7 and 8 move in turn the rods 6, the rings 5, the levers 4 and the blades 2 by rotating them of the desired quantity, the control law depending in particular 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 boítier 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 bar of synchronization 9 is lined with a pin 22 which penetrates in a groove 23 dug in the housing 12. From more, a second groove 26 is operated in the second guignol 8 to receive a lug 27 at the end of the synchronization bar 9.

Une patte 25 fixée au boítier 12, utilisée déjà pour soutenir les pivots des guignols 7 et 8 du côté opposé au boítier 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 tab 25 attached to the housing 12, used already to support the pivots of the horns 7 and 8 of the opposite side to the housing 12 itself, also door a replica 24 of the groove 23, into which penetrates another portion of the pin 22 to complete the guiding 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 deployment positions of the rod 11 of the cylinder 10 by the groove 23. The angles of rotation of horns 7 and 8 vary in values different. 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. is important to note that thanks to the length of lever provided by the synchronization bar 9, of small gaps in the groove 23 can produce large angle variations of the second hornet 8. The second groove 26 has the function of restoring isostaticity of the mechanism while contributing to define the control law. A second groove 26 short, not extending the second horn 8, will be often enough. Figures 3a, 3b and 3c illustrate a situation where the end pin 27 of the bar synchronization 9 is close to the same end of the second groove 26 at the extreme positions of the rod 11 of the cylinder 10 (in Figures 3a 3c), while it is close of the opposite end of the second groove 26 for a 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 many factors, mainly directions and shapes of the grooves 23 and 26 and their positions with respect to horns 7 and 8. In the example considered here, we can distinguish two stages of the movement. In the first, between states of FIGS. 3a and 3b, the first groove 23 is first roughly parallel to the path of the point of articulation of the synchronization bar 9 to first horn 7, so that the bar of synchronization 9 lowers without much change 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 stage of the movement, the Figure 3b in Figure 3c, the obliquity of the first groove 23 is insufficient to prevent a significant recovery of the synchronization bar 9, which is accompanied by a change of inclination which decreases the rotation of the second horn 8. In the final state of FIG. 3c, the movement of this second horn 8 is less important than that of the first horn 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 chaíne, 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 especially to order a greater number of blade stages. She would be then implemented in a number of bars synchronization. These synchronization bars could, according to existing arrangements, be to be successive, that is to say to connect the horns neighbors and extend in a chain, ie be parallel and extend to a common puppet or even up to the actuator element itself. This is without consequence for the invention.

Claims (1)

Dispositif de calage variable de deux étages d'aubes (2) de stator, disposé sur un carter (1) et comprenant un mécanisme actionneur et, pour chacun des étages, un guignol (7, 8) pivotant sur un axe (20, 21) du carter, et une bielle (6) de commande de l'étage reliée à une branche du guignol, une barre de synchronisation (9) étant reliée à une autre branche d'un au moins des guignols pour l'entraíner, caractérisé en ce que la barre de synchronisation est reliée au carter par une liaison à rainure (23) et ergot (22) coulissant dans la rainure, et au guignol qu'elle entraíne par une autre liaison à rainure (26) et ergot (27) coulissant dans la rainure.Variable setting device for two stator vane stages (2) arranged on a housing (1) and comprising an actuating mechanism and, for each of the stages, a pivoting arm (7, 8) pivoting on an axis (20, 21). ) of the casing, and a rod (6) for controlling the stage connected to a branch of the horn, a synchronization bar (9) being connected to another branch of at least one of the horns to drive, characterized in that the synchronization bar is connected to the casing by a groove connection (23) and pin (22) sliding in the groove, and it causes horn by another groove connection (26) and lug (27) sliding in the groove.
EP04102806A 2003-06-20 2004-06-18 Adjusting device for the vanes of two stages in a turbo machine Expired - Lifetime EP1489267B1 (en)

Applications Claiming Priority (2)

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

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

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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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EP1808579A2 (en) * 2006-01-17 2007-07-18 General Electric Company Actuation system for variable stator vanes
WO2010031768A2 (en) * 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Method, system, device for variable guide vanes
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WO2016034816A1 (en) * 2014-09-05 2016-03-10 Snecma Mechanism for driving members for adjusting the orientation of blades
WO2016207513A1 (en) 2015-06-25 2016-12-29 Safran Aircraft Engines System for controlling variable-setting blades for a turbine engine
WO2017203158A1 (en) 2016-05-25 2017-11-30 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
FR3133214A1 (en) 2022-03-03 2023-09-08 Safran Aircraft Engines IMPROVED SYSTEM FOR CONTROLLING RECTIFIER BLADE OF A COMPRESSOR FOR AIRCRAFT TURBOMACHINE

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FR3100272A1 (en) 2019-08-27 2021-03-05 Safran Aircraft Engines GUIGNOL FOR A VARIABLE TIMING DEVICE OF A TURBOMACHINE
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FR2885969A1 (en) * 2005-05-17 2006-11-24 Snecma Moteurs Sa TURBOMACHINE VARIABLE ROTATION ANGLE STATOR AUTONER STAGE CONTROL SYSTEM
US7322790B2 (en) 2005-05-17 2008-01-29 Snecma System for controlling stages of variable-pitch stator vanes in a turbomachine
EP1724472A3 (en) * 2005-05-17 2009-01-21 Snecma Control system for variable guide vane stages of a turbomachine
EP1724472A2 (en) * 2005-05-17 2006-11-22 Snecma Control system for variable guide vane stages of a turbomachine
EP1808579A3 (en) * 2006-01-17 2013-11-20 General Electric Company Actuation system for variable stator vanes
EP1808579A2 (en) * 2006-01-17 2007-07-18 General Electric Company Actuation system for variable stator vanes
US9890655B2 (en) 2008-09-18 2018-02-13 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
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FR2982653A1 (en) * 2011-11-14 2013-05-17 Snecma CANNELE SHAFT TRANSMISSION SYSTEM.
US10502088B2 (en) 2014-09-05 2019-12-10 Safran Aircraft Engines Mechanism for driving members for adjusting the orientation of blades
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FR3025577A1 (en) * 2014-09-05 2016-03-11 Snecma ORGAN DRIVE MECHANISM FOR ADJUSTING THE ORIENTATION OF THE BLADES
WO2016034816A1 (en) * 2014-09-05 2016-03-10 Snecma Mechanism for driving members for adjusting the orientation of blades
FR3038018A1 (en) * 2015-06-25 2016-12-30 Snecma VARIABLE TIMING AUB CONTROL SYSTEM FOR TURBOMACHINE
US10648359B2 (en) 2015-06-25 2020-05-12 Safran Aircraft Engines System for controlling variable-setting blades for a turbine engine
WO2016207513A1 (en) 2015-06-25 2016-12-29 Safran Aircraft Engines System for controlling variable-setting blades for a turbine engine
CN107771250A (en) * 2015-06-25 2018-03-06 赛峰飞机发动机公司 The system for being used to control adjustable setting blade for turbogenerator
FR3051826A1 (en) * 2016-05-25 2017-12-01 Snecma DEVICE FOR CONTROLLING VARIABLE-SETTING ELEMENTS IN A TURBOMACHINE
GB2565699A (en) * 2016-05-25 2019-02-20 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
WO2017203158A1 (en) 2016-05-25 2017-11-30 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
US10837308B2 (en) 2016-05-25 2020-11-17 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
GB2565699B (en) * 2016-05-25 2021-09-01 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
FR3133214A1 (en) 2022-03-03 2023-09-08 Safran Aircraft Engines IMPROVED SYSTEM FOR CONTROLLING RECTIFIER BLADE OF A COMPRESSOR FOR AIRCRAFT TURBOMACHINE

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Publication number Publication date
CA2470081C (en) 2011-08-02
US20050129510A1 (en) 2005-06-16
FR2856424B1 (en) 2005-09-23
CA2470081A1 (en) 2004-12-20
JP4050252B2 (en) 2008-02-20
DE602004003744D1 (en) 2007-02-01
FR2856424A1 (en) 2004-12-24
RU2004118678A (en) 2006-01-10
DE602004003744T2 (en) 2007-10-11
EP1489267B1 (en) 2006-12-20
JP2005009497A (en) 2005-01-13
US7037070B2 (en) 2006-05-02
RU2338932C2 (en) 2008-11-20

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