EP1724471A2 - Control system for variable stator vane stages of a turbomachine - Google Patents

Control system for variable stator vane stages of a turbomachine Download PDF

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Publication number
EP1724471A2
EP1724471A2 EP06112920A EP06112920A EP1724471A2 EP 1724471 A2 EP1724471 A2 EP 1724471A2 EP 06112920 A EP06112920 A EP 06112920A EP 06112920 A EP06112920 A EP 06112920A EP 1724471 A2 EP1724471 A2 EP 1724471A2
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EP
European Patent Office
Prior art keywords
follower
ring
control system
control
arm
Prior art date
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Granted
Application number
EP06112920A
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German (de)
French (fr)
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EP1724471A3 (en
EP1724471B1 (en
Inventor
Michel Bouru
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F04D29/52—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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics
    • 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
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • 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
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams

Definitions

  • the present invention relates to the general field of the blade stage control variable pitch angle of a turbomachine.
  • stator vane stages each include a plurality of vanes (referred to as variable pitch vanes) that are pivotable about their stator connection axis so that their stall angle can be varied according to the operating regime. of the turbomachine.
  • Known devices for controlling a stage of variable pitch vanes usually comprise a control member in the form of a ring surrounding the casing of the turbomachine and a plurality of rods or levers, each rod having a first end connected to the control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • An actuating jack is connected to the control ring in order to rotate the latter around the axis of the turbomachine. The rotation of the ring around the axis of the turbomachine causes a synchronized modification of the angular position of the blades of the stage.
  • This control system generates movements on the various ordered stages represented in the form of curves which show the angle of wedging of the vanes of the follower stage as a function of the wedging angle of the vanes of the pilot stage.
  • these curves called correlation curves, have a progressive slope evolution. Also, this type of control system allows only simple commands of the blade stages.
  • each rod of the pilot stage is connected to the corresponding control ring by a groove connection and pin sliding in the groove.
  • This control system is however not satisfactory because it does not reproduce all kinds of control laws.
  • the main purpose of the present invention is thus to overcome such disadvantages by proposing a control system which makes it possible to produce any type of law for setting the blades, whatever its complexity.
  • a control system of two stator vane stages with a variable turbine engine pitch angle each stage being formed of a plurality of vanes which are each mounted pivotally on a casing of the turbine engine.
  • the control system comprising an actuating element for rotating the control ring of the one stages by means of a pilot member pivotally mounted on the housing, and a synchronization bar for transmitting the rotational movement of the ring driven by the operating element to the control ring of the other floor by via a follower member pivotally mounted on the housing, characterized in that it further comprises an additional pivoting member interposed between the follower member and the follower ring, said additional pivoting member being pivotally mounted on the follower member and connected to the housing by a roller sliding in a groove secured to the housing.
  • follower ring is meant the control ring which is rotated through the follower member.
  • the groove has a shape and a direction determined to compensate for deviations in trajectory between a desired clamping law and a nominal clamping law.
  • nominal stall law it is understood a stall law whose gradual slope correlation curve would be obtained by a conventional control system without additional pivoting member.
  • the additional pivoting member constitutes a differential guide element integrating only the deviations of trajectory with respect to the nominal clamping law.
  • the roller of the system according to the invention has to absorb as a difference in altitude the difference between the desired clamping law and the nominal clamping law. In this way, the control system makes it possible to obtain blade setting laws that would be unachievable with traditional control systems.
  • the additional pivoting member comprises a first arm connected to the follower ring via a first control rod and a second arm connected to the casing by the roller.
  • the follower member comprises a first arm pivotally connected to the additional member and a second arm connected to one end of the synchronization bar.
  • the pilot member comprises a first arm connected to the ring of the pilot stage via a second control rod, a second arm connected to the end of the synchronization bar opposite to that connected to the follower member and a third arm connected to the actuating member.
  • FIG. 1 partially shows two stages 10, 10 'of variable pitch vanes belonging, for example, to a turbomachine compressor.
  • the compressor comprises an annular stator envelope 12 (or casing) which is centered on the X-X axis of the turbomachine.
  • the stages 10, 10 'of blades are offset axially relative to each other.
  • Each stage consists of a plurality of vanes 14, 14 'arranged radially around the X-X axis of the turbomachine.
  • the blades 14, 14 ' are pivotable about an axis 16, 16' (or pivot) which passes through the housing 12.
  • Each pivot 16, 16 'of the variable pitch vanes 14, 14' is connected to one end of a rod or control lever 18, 18 'whose other end is articulated around pins 20, 20' arranged radially on a control ring 22, 22 '.
  • the control rings surround the casing 12 and are centered on the X-X axis of the turbomachine.
  • the synchronized modification of the angular position of the blades 14, 14 ' is thus achieved by rotation of the respective control rings 22, 22' around the axis X-X of the turbomachine.
  • the system according to the invention makes it possible to synchronously control the rotation of the control rings 22, 22 'around the axis XX of the turbomachine. It comprises a actuating element 24 of the jack type fixed to the casing 12 for rotating the control ring 22 of one of the stages 10 by means of a pilot member 26 of type return which is pivotally mounted on a housing 28 of the casing 12 of the turbomachine.
  • a synchronization bar 30 makes it possible to transmit the rotational movement of the ring 22 driven by the jack 24 (called the pilot ring) to the ring 22 'of the other stage 10' (called the follower ring) via a follower member 26 'which is also pivotally mounted on the housing 28 of the housing 12.
  • Control rods 32, 32 'of screw-type turnbuckles provide transmission of the movement of the pilot 26 and follower 26' to the rings 22, 22 '. These rods extend tangentially to the rings on which they are fixed by means of connecting yokes 27, 27 '. At their opposite end, the connecting rods 32, 32 'are attached to respective arms (or branches) 34, 36 of the pilot 26 and follower 26' references hinged thereto.
  • the synchronization bar 30 of the control system unites two other respective arms 38, 40 of the pilot 26 and follower 26 'references hinged thereto. As for the jack 24, it is articulated to a third arm 42 of the pilot gear 26 opposite the arm 34 on which is fixed the connecting rod 32.
  • the control system according to the invention further comprises an additional pivoting member 44 (or additional reference) which is interposed between the follower member 26 'and the follower ring 22'.
  • This additional reference is pivotally mounted on the follower 26 'and connected to the housing 12 by a roller 46 sliding in a groove 48 integral with the housing.
  • the additional return 44 comprises a first arm 50, one end of which is connected to the link rod 32 'for controlling the follower ring 22' by being articulated to it and the other end is pivotally mounted on the follower member. 26.
  • the additional return also comprises a second arm 52, one end of which is pivotally mounted on the follower member 26 ', the opposite end being provided with the roller 46.
  • the first 50 and the second arm 52 of the additional return are fixed to the one compared to the other. In other words, the angle between these two arms 50, 52 is fixed and constant.
  • the roller 46 slides in a groove 48 having a predetermined path and formed in a support 54 which is fixed on the casing 12 of the turbomachine.
  • the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot return 26, and another of the follower 24 'via the synchronization bar 30.
  • the rotation of the references 26, 26 'around their point of pivoting on the housing 12 in turn drives the respective rods 32, 32' which then rotate in one direction or the other the rings 22, 22 'around of the axis XX of the turbomachine.
  • the rotation of the rings causes a synchronized change in the angular position of the blades 14, 14 'of each stage 10, 10' by means of the control levers 18, 18 '.
  • the predetermined path of the groove 48 in which the roller 46 slides depends on the displacement of the follower ring 22 ', and therefore the law of wedging of the blades 14' of the follower stage 10 '.
  • the shape and the direction of the groove modify the law of setting of the vanes of the follower stage, and thus the correlation curve giving the angle of wedging of the vanes 14 'of the follower stage 10' according to the wedging angle of the blades 14 of the pilot stage 10.
  • This figure represents correlation curves 100, 102, that is to say curves giving the wedging angle of the vanes 14 'of the follower stage 10' (in degree) as a function of the wedging angle of the blades 14 of the pilot stage 10 (in degree).
  • the correlation curve 100 (in solid lines) is that which must be applied to the setting of the blades of the two stages in order to meet the aerodynamic requirements.
  • This curve is complex; it comprises in particular portions of curves similar to sinusoids.
  • the nominal gradient correlation curve 102 (in dashed lines) which is the closest to the correlation curve 100 to be applied.
  • the calibration law based on such a nominal curve can be easily obtained by a known control system of the prior art including follower and pilot referrals and a synchronization bar connecting these references and wherein the control rod of the ring. follower is connected directly to one of the arms of the follower.
  • this type of control system gives known calibration laws whose correlation curves are more or less progressive (sometimes linear).
  • the choice of the closest curve is then made by a simple calculation (graphical or numerical) of means, the curve having the smallest deviations with the curve to be applied over the whole angular range being considered like the closest.
  • the shape and direction of the groove of the additional return are then calculated as a function of the gaps e existing over the entire angular range between the correlation curve 100 to be applied and the nominal correlation curve 102 so that the roller compensates for these deviations.
  • This calculation can be done by a graphical or numerical method. It will be noted that a groove having a simple circular arc shape corresponds to a correlation curve to be applied coinciding with the chosen nominal correlation curve.
  • the shape and the direction of the groove of the additional return must be such as to prevent the roller carried by the additional return being on a circular arc so as to avoid any unstable position of the roller, and therefore of the wedging of the blades.
  • the control system according to the invention therefore comprises a differential guiding element integrating only the path deviations between the correlation curve to be applied and a nominal correlation curve. It is thus easy to reproduce any type of calibration law, whatever its complexity.
  • the advantage of the invention resides in particular in the fact that it is not sought to obtain a correlation curve by the direct use of a cam guide but by the use of a roller which reproduces only the deviations of trajectory with respect to a nominal correlation curve.
  • the invention could also be implemented for controlling a greater number of blade stages with so many synchronization bars. Depending on the devices chosen, these bars would be either successive, that is to say connect adjacent referrals or parallel to each other to extend to a common referral.

Abstract

The system has an actuator (24) for turning a control ring (22) of one of variable-pitch stator stages via a control unit (26) that is pivotally mounted on a stator casing (12). A synchronization bar (30) transmits the turning movement of the ring to a control ring (22`) of the other stage via a follower unit (26). An additional crank (44) interposed between the follower unit and the follower ring has a differential guide unit. The unit (44) is pivotally mounted on the follower unit and connected to the casing by a wheel (46) sliding in a slot (48) secured to the casing.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général de la commande d'étages d'aubes à angle de calage variable d'une turbomachine.The present invention relates to the general field of the blade stage control variable pitch angle of a turbomachine.

Dans une turbomachine, il est connu d'utiliser un ou plusieurs étages d'aubes de stator pour ajuster le flux et la direction d'écoulement des gaz traversant la section de compression en fonction du régime de fonctionnement de la turbomachine. Ces étages d'aubes de stator comportent chacun une pluralité d'aubes (appelées aubes à calage variable) qui peuvent pivoter autour de leur axe de liaison au stator de manière à ce que leur angle de calage puisse être modifié en fonction du régime de fonctionnement de la turbomachine.In a turbomachine, it is known to use one or more stages of stator vanes for adjusting the flow and the flow direction of the gases passing through the compression section as a function of the operating speed of the turbomachine. These stator vane stages each include a plurality of vanes (referred to as variable pitch vanes) that are pivotable about their stator connection axis so that their stall angle can be varied according to the operating regime. of the turbomachine.

Les dispositifs connus pour la commande d'un étage d'aubes à calage variable comportent habituellement un organe de commande sous forme d'un anneau entourant le carter de la turbomachine et une pluralité de biellettes ou leviers, chaque biellette ayant une première extrémité reliée à l'anneau de commande par une articulation et une deuxième extrémité montée sur le pivot d'une aube respective. Un vérin de manoeuvre est relié à l'anneau de commande afin d'entraîner en rotation ce dernier autour de l'axe de la turbomachine. La rotation de l'anneau autour de l'axe de la turbomachine entraîne une modification synchronisée de la position angulaire des aubes de l'étage.Known devices for controlling a stage of variable pitch vanes usually comprise a control member in the form of a ring surrounding the casing of the turbomachine and a plurality of rods or levers, each rod having a first end connected to the control ring by a hinge and a second end mounted on the pivot of a respective blade. An actuating jack is connected to the control ring in order to rotate the latter around the axis of the turbomachine. The rotation of the ring around the axis of the turbomachine causes a synchronized modification of the angular position of the blades of the stage.

Lorsqu'il s'agit de commander de façon synchronisée deux étages d'aubes à calage variable qui sont décalés axialement, il est également connu d'utiliser une barre de synchronisation pour transmettre le mouvement de rotation de l'anneau entraîné par le vérin de manoeuvre à l'anneau de commande de l'autre étage. Cette transmission de mouvement s'effectue par l'intermédiaire de renvois montés de façon pivotante sur le carter de la turbomachine et reliés d'une part à la barre de synchronisation et d'autre part aux anneaux de commande.When it comes to synchronously controlling two stages of variable-pitch vanes which are axially offset, it is also known to use a synchronization bar to transmit the rotational movement of the ring driven by the actuator cylinder. maneuver to the control ring of the other floor. This transmission of movement is effected by means of references pivotally mounted on the casing of the turbomachine and connected on the one hand to the synchronization bar and on the other hand to the control rings.

Ce système de commande génère des mouvements sur les différents étages commandés représentables sous la forme de courbes qui montrent l'angle de calage des aubes de l'étage suiveur en fonction de l'angle de calage des aubes de l'étage pilote. Avec le type de système de commande précédemment décrit, ces courbes, appelées courbes de corrélation, présentent une évolution à pente progressive. Aussi, ce type de système de commande n'autorise que des commandes simples des étages d'aubes.This control system generates movements on the various ordered stages represented in the form of curves which show the angle of wedging of the vanes of the follower stage as a function of the wedging angle of the vanes of the pilot stage. With the type of control system previously described, these curves, called correlation curves, have a progressive slope evolution. Also, this type of control system allows only simple commands of the blade stages.

Or, il est devenu de plus en plus fréquent que les exigences aérodynamiques pour la commande des calages d'aubes nécessitent des lois de commande plus complexes. Ces commandes se traduisent notamment par des courbes de corrélation dont l'évolution n'est pas simplement à pente progressive mais comporte également des portions de courbes s'apparentant à des sinusoïdes.Now, it has become more and more common that the aerodynamic requirements for the control of blade wedges require more complex control laws. These commands are reflected in particular by correlation curves whose evolution is not simply progressive slope but also includes portions of curves similar to sinusoids.

Le document EP 0 909 880 décrit un dispositif de calage variable permettant d'obtenir des lois de commande non linéaires. Dans ce dispositif, chaque biellette de l'étage pilote est reliée à l'anneau de commande correspondant par une liaison à rainure et ergot coulissant dans la rainure. Ce système de commande n'est cependant pas satisfaisant car il ne permet pas de reproduire toutes sortes de lois de commande.The document EP 0 909 880 describes a variable setting device for obtaining nonlinear control laws. In this device, each rod of the pilot stage is connected to the corresponding control ring by a groove connection and pin sliding in the groove. This control system is however not satisfactory because it does not reproduce all kinds of control laws.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant un système de commande qui permet de réaliser tout type de loi de calage des aubes, quelle que soit sa complexité.The main purpose of the present invention is thus to overcome such disadvantages by proposing a control system which makes it possible to produce any type of law for setting the blades, whatever its complexity.

A cet effet, il est prévu un système de commande de deux étages d'aubes de stator à angle de calage variable de turbomachine, chaque étage étant formé d'une pluralité d'aubes qui sont montées chacune de façon pivotante sur un carter de la turbomachine et d'un anneau de commande entourant le carter et relié à chacune des aubes de l'étage par l'intermédiaire de leviers, le système de commande comportant un élément de manoeuvre pour entraîner en rotation l'anneau de commande de l'un des étages par l'intermédiaire d'un organe pilote monté de façon pivotante sur le carter, et une barre de synchronisation pour transmettre le mouvement de rotation de l'anneau entraîné par l'élément de manoeuvre à l'anneau de commande de l'autre étage par l'intermédiaire d'un organe suiveur monté de façon pivotante sur le carter, caractérisé en ce qu'il comporte en outre un organe pivotant supplémentaire intercalé entre l'organe suiveur et l'anneau suiveur, ledit organe pivotant supplémentaire étant monté de façon pivotante sur l'organe suiveur et relié au carter par un galet coulissant dans une rainure solidaire du carter.For this purpose, there is provided a control system of two stator vane stages with a variable turbine engine pitch angle, each stage being formed of a plurality of vanes which are each mounted pivotally on a casing of the turbine engine. turbomachine and a control ring surrounding the housing and connected to each of the blades of the stage by means of levers, the control system comprising an actuating element for rotating the control ring of the one stages by means of a pilot member pivotally mounted on the housing, and a synchronization bar for transmitting the rotational movement of the ring driven by the operating element to the control ring of the other floor by via a follower member pivotally mounted on the housing, characterized in that it further comprises an additional pivoting member interposed between the follower member and the follower ring, said additional pivoting member being pivotally mounted on the follower member and connected to the housing by a roller sliding in a groove secured to the housing.

Par anneau suiveur, on entend l'anneau de commande qui est entraîné en rotation par l'intermédiaire de l'organe suiveur.By follower ring is meant the control ring which is rotated through the follower member.

Selon une disposition avantageuse de l'invention, la rainure présente une forme et une direction déterminée pour compenser des écarts de trajectoire entre une loi de calage souhaitée et une loi de calage nominale. Par loi de calage nominale, on entendu une loi de calage dont la courbe de corrélation à pente progressive serait obtenue par un système de commande conventionnel dépourvu d'organe pivotant supplémentaire.According to an advantageous arrangement of the invention, the groove has a shape and a direction determined to compensate for deviations in trajectory between a desired clamping law and a nominal clamping law. By nominal stall law, it is understood a stall law whose gradual slope correlation curve would be obtained by a conventional control system without additional pivoting member.

L'organe pivotant supplémentaire constitue un élément de guidage différentiel n'intégrant que les écarts de trajectoire par rapport à la loi de calage nominale. En d'autres termes, le galet du système selon l'invention n'a à absorber comme dénivelé que la différence existant entre la loi de calage souhaitée et la loi de calage nominale. De la sorte, le système de commande permet d'obtenir des lois de calage des aubes qui seraient irréalisables avec les systèmes de commande traditionnels.The additional pivoting member constitutes a differential guide element integrating only the deviations of trajectory with respect to the nominal clamping law. In other words, the roller of the system according to the invention has to absorb as a difference in altitude the difference between the desired clamping law and the nominal clamping law. In this way, the control system makes it possible to obtain blade setting laws that would be unachievable with traditional control systems.

Selon une autre disposition avantageuse de l'invention, l'organe pivotant supplémentaire comporte un premier bras relié à l'anneau suiveur par l'intermédiaire d'une première bielle de commande et un second bras relié au carter par le galet.According to another advantageous arrangement of the invention, the additional pivoting member comprises a first arm connected to the follower ring via a first control rod and a second arm connected to the casing by the roller.

Selon encore une autre disposition avantageuse, l'organe suiveur comporte un premier bras relié de façon pivotante à l'organe supplémentaire et un second bras relié à une extrémité de la barre de synchronisation. Dans ce cas, l'organe pilote comporte un premier bras relié à l'anneau de l'étage pilote par l'intermédiaire d'une seconde bielle de commande, un deuxième bras relié à l'extrémité de la barre de synchronisation opposée à celle reliée à l'organe suiveur et un troisième bras relié à l'élément de manoeuvre.According to yet another advantageous arrangement, the follower member comprises a first arm pivotally connected to the additional member and a second arm connected to one end of the synchronization bar. In this case, the pilot member comprises a first arm connected to the ring of the pilot stage via a second control rod, a second arm connected to the end of the synchronization bar opposite to that connected to the follower member and a third arm connected to the actuating member.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue partielle et en perspective du système de commande selon un mode de réalisation de l'invention ;
  • les figures 2A et 2B montrent le système de commande de la figure 1 selon deux positions différentes ; et
  • la figure 3 est une courbe de corrélation montrant une loi de calage possible obtenue par le système de commande de l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • Figure 1 is a partial view in perspective of the control system according to one embodiment of the invention;
  • Figures 2A and 2B show the control system of Figure 1 in two different positions; and
  • FIG. 3 is a correlation curve showing a possible calibration law obtained by the control system of the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

Sur la figure 1 sont représentés partiellement deux étages 10, 10' d'aubes à calage variable appartenant, par exemple, à un compresseur de turbomachine. Le compresseur comporte une enveloppe annulaire de stator 12 (ou carter) qui est centrée sur l'axe X-X de la turbomachine. Les étages 10, 10' d'aubes sont décalés axialement l'un par rapport à l'autre.FIG. 1 partially shows two stages 10, 10 'of variable pitch vanes belonging, for example, to a turbomachine compressor. The compressor comprises an annular stator envelope 12 (or casing) which is centered on the X-X axis of the turbomachine. The stages 10, 10 'of blades are offset axially relative to each other.

Chaque étage se compose d'une pluralité d'aubes 14, 14' disposées radialement autour de l'axe X-X de la turbomachine. Les aubes 14, 14' sont pivotantes autour d'un axe 16, 16' (ou pivot) qui traverse le carter 12.Each stage consists of a plurality of vanes 14, 14 'arranged radially around the X-X axis of the turbomachine. The blades 14, 14 'are pivotable about an axis 16, 16' (or pivot) which passes through the housing 12.

Chaque pivot 16, 16' des aubes à calage variable 14, 14' est relié à une extrémité d'une biellette ou levier de commande 18, 18' dont l'autre extrémité est articulée autour de tourillons 20, 20' disposés radialement sur un anneau de commande 22, 22'.Each pivot 16, 16 'of the variable pitch vanes 14, 14' is connected to one end of a rod or control lever 18, 18 'whose other end is articulated around pins 20, 20' arranged radially on a control ring 22, 22 '.

Les anneaux de commande entourent le carter 12 et sont centrés sur l'axe X-X de la turbomachine. La modification synchronisée de la position angulaire des aubes 14, 14' est ainsi réalisée par rotation des anneaux de commande respectifs 22, 22' autour de l'axe X-X de la turbomachine.The control rings surround the casing 12 and are centered on the X-X axis of the turbomachine. The synchronized modification of the angular position of the blades 14, 14 'is thus achieved by rotation of the respective control rings 22, 22' around the axis X-X of the turbomachine.

Le système selon l'invention permet de commander de façon synchronisée la rotation des anneaux de commande 22, 22' autour de l'axe X-X de la turbomachine. Il comporte un élément de manoeuvre 24 de type vérin fixé au carter 12 pour entraîner en rotation l'anneau de commande 22 de l'un des étages 10 par l'intermédiaire d'un organe pilote 26 de type renvoi qui est monté de façon pivotante sur un boîtier 28 du carter 12 de la turbomachine.The system according to the invention makes it possible to synchronously control the rotation of the control rings 22, 22 'around the axis XX of the turbomachine. It comprises a actuating element 24 of the jack type fixed to the casing 12 for rotating the control ring 22 of one of the stages 10 by means of a pilot member 26 of type return which is pivotally mounted on a housing 28 of the casing 12 of the turbomachine.

Une barre de synchronisation 30 permet de transmettre le mouvement de rotation de l'anneau 22 entraîné par le vérin 24 (appelé anneau pilote) à l'anneau 22' de l'autre étage 10' (appelé anneau suiveur) par l'intermédiaire d'un organe suiveur 26' de type renvoi qui est monté également de façon pivotante sur le boîtier 28 du carter 12.A synchronization bar 30 makes it possible to transmit the rotational movement of the ring 22 driven by the jack 24 (called the pilot ring) to the ring 22 'of the other stage 10' (called the follower ring) via a follower member 26 'which is also pivotally mounted on the housing 28 of the housing 12.

Des bielles de commande 32, 32' de type ridoirs à vis assurent la transmission du mouvement des renvois pilote 26 et suiveur 26' aux anneaux 22, 22'. Ces bielles s'étendent tangentiellement aux anneaux sur lesquels elles sont fixées par l'intermédiaire de chapes de liaison 27, 27'. A leur extrémité opposée, les bielles 32, 32' sont fixées à des bras (ou branches) respectifs 34, 36 des renvois pilote 26 et suiveur 26' en leur étant articulées.Control rods 32, 32 'of screw-type turnbuckles provide transmission of the movement of the pilot 26 and follower 26' to the rings 22, 22 '. These rods extend tangentially to the rings on which they are fixed by means of connecting yokes 27, 27 '. At their opposite end, the connecting rods 32, 32 'are attached to respective arms (or branches) 34, 36 of the pilot 26 and follower 26' references hinged thereto.

La barre de synchronisation 30 du système de commande unit deux autres bras respectifs 38, 40 des renvois pilote 26 et suiveur 26' en leur étant articulée. Quant au vérin 24, il est articulé à un troisième bras 42 du renvoi pilote 26 opposé au bras 34 sur lequel est fixée la bielle 32.The synchronization bar 30 of the control system unites two other respective arms 38, 40 of the pilot 26 and follower 26 'references hinged thereto. As for the jack 24, it is articulated to a third arm 42 of the pilot gear 26 opposite the arm 34 on which is fixed the connecting rod 32.

Le système de commande selon l'invention comporte en outre un organe pivotant supplémentaire 44 (ou renvoi supplémentaire) qui est intercalé entre l'organe suiveur 26' et l'anneau suiveur 22'. Ce renvoi supplémentaire est monté de façon pivotante sur le renvoi suiveur 26' et relié au carter 12 par un galet 46 coulissant dans une rainure 48 solidaire du carter.The control system according to the invention further comprises an additional pivoting member 44 (or additional reference) which is interposed between the follower member 26 'and the follower ring 22'. This additional reference is pivotally mounted on the follower 26 'and connected to the housing 12 by a roller 46 sliding in a groove 48 integral with the housing.

Plus précisément, le renvoi supplémentaire 44 comporte un premier bras 50 dont une extrémité est reliée à la bielle 32' de commande de l'anneau suiveur 22' en lui étant articulée et l'autre extrémité est montée de façon pivotante sur l'organe suiveur 26'. Le renvoi supplémentaire comporte également un second bras 52 dont une extrémité est montée de façon pivotante sur l'organe suiveur 26', l'extrémité opposée étant muni du galet 46. Le premier 50 et le second bras 52 du renvoi supplémentaire sont fixes l'un par rapport à l'autre. En d'autres termes, l'angle existant entre ces deux bras 50, 52 est fixe et constant. Le galet 46 coulisse dans une rainure 48 ayant un trajet prédéterminé et formé dans un support 54 qui est fixé sur le carter 12 de la turbomachine.More specifically, the additional return 44 comprises a first arm 50, one end of which is connected to the link rod 32 'for controlling the follower ring 22' by being articulated to it and the other end is pivotally mounted on the follower member. 26. The additional return also comprises a second arm 52, one end of which is pivotally mounted on the follower member 26 ', the opposite end being provided with the roller 46. The first 50 and the second arm 52 of the additional return are fixed to the one compared to the other. In other words, the angle between these two arms 50, 52 is fixed and constant. The roller 46 slides in a groove 48 having a predetermined path and formed in a support 54 which is fixed on the casing 12 of the turbomachine.

Comme illustré sur les figures 2A et 2B, le mouvement du système de commande est le suivant : l'actionnement du vérin 24 provoque une rotation du renvoi pilote 26, et une autre du renvoi suiveur 26' par l'intermédiaire de la barre de synchronisation 30. La rotation des renvois 26, 26' autour de leur point de pivotement sur le carter 12 entraîne à leur tour les bielles 32, 32' respectives qui font alors tourner dans un sens ou dans l'autre les anneaux 22, 22' autour de l'axe X-X de la turbomachine. Comme indiqué précédemment, la rotation des anneaux provoque une modification synchronisée de la position angulaire des aubes 14, 14' de chaque étage 10, 10' par l'intermédiaire des leviers de commande 18, 18'.As illustrated in FIGS. 2A and 2B, the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot return 26, and another of the follower 24 'via the synchronization bar 30. The rotation of the references 26, 26 'around their point of pivoting on the housing 12 in turn drives the respective rods 32, 32' which then rotate in one direction or the other the rings 22, 22 'around of the axis XX of the turbomachine. As indicated above, the rotation of the rings causes a synchronized change in the angular position of the blades 14, 14 'of each stage 10, 10' by means of the control levers 18, 18 '.

Par ailleurs, la rotation du renvoi suiveur 26' entraîne une rotation du renvoi supplémentaire 44 autour de son axe de pivotement sur le renvoi suiveur. Cette rotation a pour effet que le galet 46 coulisse dans la rainure 48, provoquant ainsi un déplacement du bras 52 du renvoi supplémentaire 44 sur lequel est monté le galet. Le déplacement de ce dernier meut alors l'autre bras 50 du renvoi supplémentaire auquel est reliée la bielle 32'.Furthermore, the rotation of the follower 26 'causes a rotation of the additional return 44 about its pivot axis on the follower. This rotation has the effect that the roller 46 slides in the groove 48, causing a displacement of the arm 52 of the additional return 44 on which is mounted the roller. The displacement of the latter then moves the other arm 50 of the additional return which is connected to the connecting rod 32 '.

On comprend ainsi que du trajet prédéterminé de la rainure 48 dans laquelle coulisse le galet 46 dépend le déplacement de l'anneau suiveur 22', et donc la loi de calage des aubes 14' de l'étage suiveur 10'. En d'autres termes, la forme et la direction de la rainure modifient la loi de calage des aubes de l'étage suiveur, et donc la courbe de corrélation donnant l'angle de calage des aubes 14' de l'étage suiveur 10' en fonction de l'angle de calage des aubes 14 de l'étage pilote 10.It is thus understood that the predetermined path of the groove 48 in which the roller 46 slides depends on the displacement of the follower ring 22 ', and therefore the law of wedging of the blades 14' of the follower stage 10 '. In other words, the shape and the direction of the groove modify the law of setting of the vanes of the follower stage, and thus the correlation curve giving the angle of wedging of the vanes 14 'of the follower stage 10' according to the wedging angle of the blades 14 of the pilot stage 10.

En se référant à la figure 3, on décrira maintenant la façon dont la forme et la direction de la rainure 48 sont prédéterminées. Cette figure représente des courbes de corrélation 100, 102, c'est-à-dire des courbes donnant l'angle de calage des aubes 14' de l'étage suiveur 10' (en degré) en fonction de l'angle de calage des aubes 14 de l'étage pilote 10 (en degré).Referring to Figure 3, the manner in which the shape and direction of the groove 48 are predetermined will now be described. This figure represents correlation curves 100, 102, that is to say curves giving the wedging angle of the vanes 14 'of the follower stage 10' (in degree) as a function of the wedging angle of the blades 14 of the pilot stage 10 (in degree).

La courbe de corrélation 100 (en traits pleins) est celle qui doit être appliquée au calage des aubes des deux étages afin de répondre aux exigences aérodynamiques. Cette courbe est complexe ; elle comporte notamment des portions de courbes s'apparentant à des sinusoïdes.The correlation curve 100 (in solid lines) is that which must be applied to the setting of the blades of the two stages in order to meet the aerodynamic requirements. This curve is complex; it comprises in particular portions of curves similar to sinusoids.

A partir de cette courbe de corrélation, il est possible de choisir la courbe de corrélation nominale 102 (en traits discontinus) à pente progressive qui est la plus proche de la courbe de corrélation 100 à appliquer. La loi de calage basée sur une telle courbe nominale peut être facilement obtenue par un système de commande connu de l'art antérieur comportant des renvois suiveur et pilote et une barre de synchronisation reliant ces renvois et dans lequel la bielle de commande de l'anneau suiveur est reliée directement à l'un des bras du renvoi suiveur. En fonction de la position relative des renvois pilote et suiveur, ce type de système de commande donne des lois de calage connues dont les courbes de corrélation sont plus ou moins progressives (parfois linéaires). Parmi ces courbes nominales connues, le choix de la courbe la plus proche s'effectue alors par un simple calcul (graphique ou numérique) de moyennes, la courbe ayant les écarts les plus faibles avec la courbe à appliquer sur toute la plage angulaire étant considérée comme la plus proche.From this correlation curve, it is possible to choose the nominal gradient correlation curve 102 (in dashed lines) which is the closest to the correlation curve 100 to be applied. The calibration law based on such a nominal curve can be easily obtained by a known control system of the prior art including follower and pilot referrals and a synchronization bar connecting these references and wherein the control rod of the ring. follower is connected directly to one of the arms of the follower. Depending on the relative position of the pilot and follower references, this type of control system gives known calibration laws whose correlation curves are more or less progressive (sometimes linear). Among these known nominal curves, the choice of the closest curve is then made by a simple calculation (graphical or numerical) of means, the curve having the smallest deviations with the curve to be applied over the whole angular range being considered like the closest.

La forme et la direction de la rainure du renvoi supplémentaire sont alors calculées en fonction des écarts e existant sur toute la plage angulaire entre la courbe de corrélation 100 à appliquer et la courbe de corrélation nominale 102 de sorte que le galet compense ces écarts. Ce calcul peut être réalisé par une méthode graphique ou numérique. On notera qu'à une rainure ayant une forme simple en arc de cercle correspond une courbe de corrélation à appliquer confondue avec la courbe de corrélation nominale choisie.The shape and direction of the groove of the additional return are then calculated as a function of the gaps e existing over the entire angular range between the correlation curve 100 to be applied and the nominal correlation curve 102 so that the roller compensates for these deviations. This calculation can be done by a graphical or numerical method. It will be noted that a groove having a simple circular arc shape corresponds to a correlation curve to be applied coinciding with the chosen nominal correlation curve.

De préférence, la forme et la direction de la rainure du renvoi supplémentaire devront être telles qu'elles empêcheront que le galet porté par le renvoi supplémentaire ne se trouve sur un arc de cercle de façon à éviter toute position instable du galet, et donc du calage des aubes.Preferably, the shape and the direction of the groove of the additional return must be such as to prevent the roller carried by the additional return being on a circular arc so as to avoid any unstable position of the roller, and therefore of the wedging of the blades.

Le système de commande selon l'invention comporte donc un élément de guidage différentiel n'intégrant que les écarts de trajectoire entre la courbe de corrélation à appliquer et une courbe de corrélation nominale. Il est ainsi aisé de reproduire tout type de loi de calage, quelle que soit sa complexité. L'avantage de l'invention réside notamment dans le fait que l'on ne cherche pas à obtenir une courbe de corrélation par l'utilisation directe d'un guidage par came mais par l'utilisation d'un galet qui ne reproduit que les écarts de trajectoire par rapport à une courbe de corrélation nominale.The control system according to the invention therefore comprises a differential guiding element integrating only the path deviations between the correlation curve to be applied and a nominal correlation curve. It is thus easy to reproduce any type of calibration law, whatever its complexity. The advantage of the invention resides in particular in the fact that it is not sought to obtain a correlation curve by the direct use of a cam guide but by the use of a roller which reproduces only the deviations of trajectory with respect to a nominal correlation curve.

On notera que l'invention pourrait également être mise en oeuvre pour la commande d'un plus grand nombre d'étages d'aubes grâce à autant de barres de synchronisation. Suivant les dispositifs choisis, ces barres seraient soit successives, c'est-à-dire relier des renvois adjacents, soit parallèles entre elles pour s'étendre jusqu'à un renvoi commun.Note that the invention could also be implemented for controlling a greater number of blade stages with so many synchronization bars. Depending on the devices chosen, these bars would be either successive, that is to say connect adjacent referrals or parallel to each other to extend to a common referral.

Claims (5)

Système de commande de deux étages (10, 10') d'aubes de stator (14, 14') à angle de calage variable de turbomachine, chaque étage (10, 10') étant formé d'une pluralité d'aubes (14, 14') qui sont montées chacune de façon pivotante sur un carter (12) de la turbomachine et d'un anneau de commande (22, 22') entourant le carter et relié à chacune des aubes (14, 14') de l'étage par l'intermédiaire de leviers (18, 18'), le système de commande comportant un élément de manoeuvre (24) pour entraîner en rotation l'anneau de commande (22) de l'un des étages (10) par l'intermédiaire d'un organe pilote (26) monté de façon pivotante sur le carter (12), et une barre de synchronisation (30) pour transmettre le mouvement de rotation de l'anneau entraîné (22) par l'élément de manoeuvre (24) à l'anneau de commande (22') de l'autre étage (10') par l'intermédiaire d'un organe suiveur (26') monté de façon pivotante sur le carter, caractérisé en ce qu'il comporte en outre un organe pivotant supplémentaire (44) intercalé entre l'organe suiveur (26') et l'anneau suiveur (22'), ledit organe pivotant supplémentaire étant monté de façon pivotante sur l'organe suiveur (26') et relié au carter (12) par un galet (46) coulissant dans une rainure (48) solidaire du carter.A two-stage control system (10, 10 ') of stator vanes (14, 14') with variable turbine engine pitch angle, each stage (10, 10 ') being formed of a plurality of vanes (14 , 14 ') which are each pivotally mounted on a casing (12) of the turbomachine and a control ring (22, 22') surrounding the housing and connected to each of the blades (14, 14 ') of the the stage by means of levers (18, 18 '), the control system comprising an operating element (24) for rotating the control ring (22) of one of the stages (10) by means of intermediate of a pilot member (26) pivotally mounted on the housing (12), and a synchronizing bar (30) for transmitting the rotational movement of the driven ring (22) by the operating element ( 24) to the control ring (22 ') of the other stage (10') via a follower member (26 ') pivotally mounted on the housing, characterized in that it comprises besides an o an additional pivoting member (44) interposed between the follower member (26 ') and the follower ring (22'), said additional pivot member being pivotally mounted on the follower member (26 ') and connected to the housing (12); ) by a roller (46) sliding in a groove (48) integral with the housing. Système de commande selon la revendication 1, dans lequel la rainure (48) présente une forme et une direction déterminée pour compenser des écarts de trajectoire entre une loi de calage souhaitée et une loi de calage nominale.A control system according to claim 1, wherein the groove (48) has a shape and a direction determined to compensate for deviations in trajectory between a desired stall law and a nominal stall law. Système de commande selon l'une des revendications 1 et 2, dans lequel l'organe pivotant supplémentaire (44) comporte un premier bras (50) relié à l'anneau suiveur (22') par l'intermédiaire d'une première bielle de commande (32') et un second bras (52) relié au carter (12) par ledit galet (46).Control system according to one of claims 1 and 2, wherein the additional pivoting member (44) comprises a first arm (50) connected to the follower ring (22 ') via a first connecting rod of control (32 ') and a second arm (52) connected to the housing (12) by said roller (46). Système de commande selon l'une quelconque des revendications 1 à 3, dans lequel l'organe suiveur (26') comporte un premier bras (36) relié de façon pivotante à l'organe pivotant supplémentaire (44) et un second bras (40) relié à une extrémité de la barre de synchronisation (30).Control system according to any one of claims 1 to 3, wherein the follower member (26 ') comprises a first arm (36) pivotally connected to the pivoting member an additional arm (40) connected to one end of the synchronization bar (30). Système de commande selon la revendication 4, dans lequel l'organe pilote (26) comporte un premier bras (34) relié à l'anneau (22) de l'étage pilote (10) par l'intermédiaire d'une seconde bielle de commande (32), un deuxième bras (38) relié à l'extrémité de la barre de synchronisation (30) opposée à celle reliée à l'organe suiveur (26') et un troisième bras (42) relié à l'élément de manoeuvre (24).Control system according to claim 4, wherein the pilot member (26) comprises a first arm (34) connected to the ring (22) of the pilot stage (10) via a second connecting rod of control (32), a second arm (38) connected to the end of the synchronizer bar (30) opposite to that connected to the follower member (26 ') and a third arm (42) connected to the maneuver (24).
EP06112920A 2005-05-17 2006-04-21 Control system for variable stator vane stages of a turbomachine Active EP1724471B1 (en)

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FR2885968B1 (en) 2007-08-10
CA2547025C (en) 2012-10-02
DE602006015740D1 (en) 2010-09-09
CA2547025A1 (en) 2006-11-17
US20060260307A1 (en) 2006-11-23
EP1724471A3 (en) 2009-01-21
JP4653013B2 (en) 2011-03-16
RU2396439C2 (en) 2010-08-10
EP1724471B1 (en) 2010-07-28
JP2006322456A (en) 2006-11-30
FR2885968A1 (en) 2006-11-24
US7273346B2 (en) 2007-09-25
RU2006116818A (en) 2007-11-27

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