EP1724472B1 - Control system for variable guide vane stages of a turbomachine - Google Patents

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

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Publication number
EP1724472B1
EP1724472B1 EP06112991A EP06112991A EP1724472B1 EP 1724472 B1 EP1724472 B1 EP 1724472B1 EP 06112991 A EP06112991 A EP 06112991A EP 06112991 A EP06112991 A EP 06112991A EP 1724472 B1 EP1724472 B1 EP 1724472B1
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EP
European Patent Office
Prior art keywords
ring
follower
arm
casing
control
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EP06112991A
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German (de)
French (fr)
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EP1724472A3 (en
EP1724472A2 (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
    • 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
    • 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
    • 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 fully satisfactory because it does not allow in particular to reproduce a correlation curve having a sudden acceleration or deceleration of the slope.
  • the document EP 1 489 267 also describes a variable setting device for obtaining nonlinear control laws. This system has the same drawback.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a control system which makes it possible to produce a law for setting the blades having an acceleration (or deceleration) on a localized zone of the control trajectory.
  • 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 casing, 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 having an arm pivotally mounted on a control rod connected to the follower ring and a guide rod sliding in a ring pivotally mounted on the housing.
  • follower ring is meant the control ring which is rotated through the follower member.
  • the follower member comprises a first arm pivotally connected to the additional pivoting member and a second arm connected to one end of the synchronization bar.
  • the point of pivoting on the casing of the additional pivoting member may be arranged inside a circle having as a center the point of pivoting on the housing of the follower member and for radius the first arm of the follower member. . In this case, it is then an acceleration of the control path.
  • the point of pivoting on the casing of the additional pivoting member may be arranged outside a circle having the center of the pivot point on the housing of the follower member and for radius the first arm of the follower organ. In this case, it is then a deceleration of the control path.
  • the pilot member comprises a first arm connected to the ring of the pilot stage by means of a second control rod, a second arm connected to the end of the synchronizing bar opposed to that connected to the follower member and a third arm connected to the actuating element.
  • FIG. 1 On the figure 1 are partially represented 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 axis XX 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 in order to drive in rotation the ring of control 22 of one of the stages 10 by means of a pilot member 26 of return type which is pivotally mounted on a housing 28 of the housing 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 both the housing 12 and the follower member 26 '.
  • the additional return 44 comprises a first arm 46, one end of which is connected to the control rod 32 'of the follower ring 22' by being hinged to it and the other end is pivotally mounted on the follower 26 .
  • the additional return also includes a second arm 48 extending perpendicularly to the first arm 46 along the axis of pivoting of the additional return on the follower.
  • a guide rod 50 is attached to one end of the second arm 48.
  • the guide rod 50 of the additional return wheel 44 is able to slide in a ring 52 pivotally mounted on the casing 12.
  • the sliding ring 52 is for example a recirculation ring of rolling elements. It is pivotally attached to the housing 12, for example by means of a pivoting support 54 brazed to the housing.
  • the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot referral 26, and another of the follower 26 'via the synchronization bar 30.
  • the rotation of the referrals 26, 26 'around their point of pivoting on the housing 12 in turn drives the rods 32, 32' respectively which then rotate in one direction or the other the rings 22, 22 'about 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 Figure 2C more precisely represents the movement of the additional return 44.
  • this figure only shows the follower 26 'and the additional return 44 in two extreme positions of the control system of the figure 1 : in dashed lines, the system in the position in opening of setting and in solid lines, the system in the position in closing of rigging.
  • the guide rod 50 From a certain position of the pivot point 44a of the additional return 44, hereinafter referred to as the tilting position, the guide rod 50 will cause, by leverage, an accelerated rotation of the first arm 46 of the additional return wheel 44 around its pivot point 44a in the direction of rotation of the follower 26 '. This accelerated rotation of the first arm of the additional reference thereby, via the rod, an acceleration of the rotation of the follower ring in wedging closure.
  • the angle e schematized on the Figure 2C represents the angular acceleration experienced by the additional return 44 with respect to a control system devoid of such a device.
  • the tilting position of the pivot point 44a of the additional return 44 can be defined as the position from which more than half the length of the guide rod 50 has slid into the ring 52. Also, this tilting position can be adjusted by changing the position of the pivoting support 54 of the ring 52 and / or the length of the guide rod to choose the area of the control path to be accelerated. This zone can be as well at the beginning, middle or at the end of the trajectory.
  • the figure 3 illustrates the effect on the law of wedging of the blades of such an acceleration.
  • Dotted line is represented a correlation curve 100 (that is to say the curve giving 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) for a control system without additional return and in solid lines is shown schematically the correlation curve 102 established for the control system according to the invention.
  • the correlation curve 100 established for a control system devoid of additional reference is gradual slope.
  • the correlation curve 102 has a clear acceleration of the angle of wedging of the blades of the follower stage in an angular zone 104.
  • the acceleration zone 104 is at the end of its trajectory, that is to say, in locking closure. As previously explained, it could be localized differently.
  • the pivoting support 54 of the ring 52 (which corresponds to the point of pivoting on the housing of the additional return 44) is disposed inside a circle C having the center of the pivot point 26'a on the housing of the housing of the follower member 26 'and for radius the arm 36 of the follower member on which is mounted the additional return 44.
  • Such a configuration has the consequence of accelerating the control path.
  • a deceleration is indeed obtained by arranging the pivoting support 54 of the ring 52 outside the circle C as defined above.
  • the pivoting support 54 of the ring 52 outside the circle C and / or the length of the guide rod 50, it is also possible to choose the zone of the control path which must be decelerated (beginning, middle or end).

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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)

Description

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 d'organes 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 members 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 se traduisant par des courbes de corrélation qui comportent, notamment en partie terminale, des portions de courbes présentant une accélération ou une décélération brusque de la pente.However, it has become more and more frequent that the aerodynamic requirements for the control of the blade wedges require control laws resulting in correlation curves which comprise, particularly in the terminal part, portions of curves having an acceleration or a sudden deceleration of the slope.

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 pleinement satisfaisant car il ne permet notamment pas de reproduire une courbe de corrélation ayant une accélération ou une décélération brusque de la pente.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 fully satisfactory because it does not allow in particular to reproduce a correlation curve having a sudden acceleration or deceleration of the slope.

Le document EP 1 489 267 décrit également un dispositif de calage variable permettant d'obtenir des lois de commande non linéaires. Ce système présente le même inconvénient.The document EP 1 489 267 also describes a variable setting device for obtaining nonlinear control laws. This system has the same drawback.

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 une loi de calage des aubes ayant une accélération (ou décélération) sur une zone localisée de la trajectoire de commande.The main purpose of the present invention is therefore to overcome such drawbacks by proposing a control system which makes it possible to produce a law for setting the blades having an acceleration (or deceleration) on a localized zone of the control trajectory.

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 comportant un bras monté de façon pivotante sur une bielle de commande reliée à l'anneau suiveur et une tige de guidage coulissant dans une bague montée de façon pivotante sur le 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 casing, 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 having an arm pivotally mounted on a control rod connected to the follower ring and a guide rod sliding in a ring pivotally mounted on 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.

Par l'intermédiaire d'un tel organe pivotant supplémentaire, il est possible de provoquer une accélération ou une décélération des mouvements sur les étages commandés sur une zone localisée de la trajectoire de commande. De la disposition du point de pivotement sur le carter de l'organe pivotant supplémentaire dépend la localisation de cette accélération (ou décélération) sur la trajectoire de commande.Through such an additional pivoting member, it is possible to cause an acceleration or deceleration of the movements on the stages controlled on a localized area of the control path. The provision of the pivot point on the casing of the additional pivoting member depends on the location of this acceleration (or deceleration) on the control path.

Selon une disposition avantageuse de l'invention, l'organe suiveur comporte un premier bras relié de façon pivotante à l'organe pivotant supplémentaire et un second bras relié à une extrémité de la barre de synchronisation.According to an advantageous arrangement of the invention, the follower member comprises a first arm pivotally connected to the additional pivoting member and a second arm connected to one end of the synchronization bar.

Le point de pivotement sur le carter de l'organe pivotant supplémentaire peut être disposé à l'intérieur d'un cercle ayant pour centre le point de pivotement sur le carter de l'organe suiveur et pour rayon le premier bras de l'organe suiveur. Dans ce cas, il s'agit alors d'une accélération de la trajectoire de commande.The point of pivoting on the casing of the additional pivoting member may be arranged inside a circle having as a center the point of pivoting on the housing of the follower member and for radius the first arm of the follower member. . In this case, it is then an acceleration of the control path.

Alternativement, le point de pivotement sur le carter de l'organe pivotant supplémentaire peut être disposé à l'extérieur d'un cercle ayant pour centre le point de pivotement sur le carter de l'organe suiveur et pour rayon le premier bras de l'organe suiveur. Dans ce cas, il s'agit alors d'une décélération de la trajectoire de commande.Alternatively, the point of pivoting on the casing of the additional pivoting member may be arranged outside a circle having the center of the pivot point on the housing of the follower member and for radius the first arm of the follower organ. In this case, it is then a deceleration of the control path.

Selon une autre disposition avantageuse de l'invention, 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 another advantageous arrangement of the invention, the pilot member comprises a first arm connected to the ring of the pilot stage by means of a second control rod, a second arm connected to the end of the synchronizing bar opposed to that connected to the follower member and a third arm connected to the actuating element.

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, 2B et 2C montrent le système de commande de la figure 1 dans des 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:
  • the figure 1 is a partial perspective view of the control system according to one embodiment of the invention;
  • the Figures 2A , 2B and 2C show the control system of the figure 1 in different positions; and
  • the figure 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.On the figure 1 are partially represented 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 axis XX 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 in order to drive in rotation the ring of control 22 of one of the stages 10 by means of a pilot member 26 of return type which is pivotally mounted on a housing 28 of the housing 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 à la fois sur le carter 12 et sur l'organe suiveur 26'.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 both the housing 12 and the follower member 26 '.

Plus précisément, le renvoi supplémentaire 44 comporte un premier bras 46 dont une extrémité est reliée à la bielle de commande 32' de l'anneau suiveur 22' en lui étant articulée et l'autre extrémité est montée de façon pivotante sur le renvoi suiveur 26'. Le renvoi supplémentaire comporte également un second bras 48 s'étendant perpendiculairement au premier bras 46 selon l'axe de pivotement du renvoi supplémentaire sur le renvoi suiveur. Une tige de guidage 50 est fixée à une extrémité du second bras 48.More specifically, the additional return 44 comprises a first arm 46, one end of which is connected to the control rod 32 'of the follower ring 22' by being hinged to it and the other end is pivotally mounted on the follower 26 . The additional return also includes a second arm 48 extending perpendicularly to the first arm 46 along the axis of pivoting of the additional return on the follower. A guide rod 50 is attached to one end of the second arm 48.

La tige de guidage 50 du renvoi supplémentaire 44 est apte à coulisser dans une bague 52 montée de façon pivotante sur le carter 12. La bague de coulissement 52 est par exemple une bague à re-circulation d'éléments de roulement. Elle est fixée de façon pivotante sur le carter 12, par exemple à l'aide d'un support pivotant 54 brasé sur le carter.The guide rod 50 of the additional return wheel 44 is able to slide in a ring 52 pivotally mounted on the casing 12. The sliding ring 52 is for example a recirculation ring of rolling elements. It is pivotally attached to the housing 12, for example by means of a pivoting support 54 brazed to the housing.

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 on Figures 2A and 2B , the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot referral 26, and another of the follower 26 'via the synchronization bar 30. The rotation of the referrals 26, 26 'around their point of pivoting on the housing 12 in turn drives the rods 32, 32' respectively which then rotate in one direction or the other the rings 22, 22 'about 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 '.

La figure 2C représente plus précisément le mouvement du renvoi supplémentaire 44. Pour des raisons de clarté, sont illustrés sur cette figure uniquement le renvoi suiveur 26' et le renvoi supplémentaire 44 dans deux positions extrêmes du système de commande de la figure 1 : en traits pointillés, le système dans la position en ouverture de calage et en traits pleins, le système dans la position en fermeture de calage.The Figure 2C more precisely represents the movement of the additional return 44. For the sake of clarity, this figure only shows the follower 26 'and the additional return 44 in two extreme positions of the control system of the figure 1 : in dashed lines, the system in the position in opening of setting and in solid lines, the system in the position in closing of rigging.

La rotation du renvoi suiveur 26' autour de son point de pivotement 26'a sur le boîtier du carter a pour effet que la tige de guidage 50 du renvoi supplémentaire 44 coulisse dans la bague 52. Le fait que la bague 52 soit montée de façon pivotante sur le carter permet à la tige de guidage 50 de rester en permanence alignée avec l'axe de coulissement de la bague. Au fur et à mesure que la tige de guidage coulisse dans la bague, le point de pivotement 44a du renvoi supplémentaire 44 sur le renvoi suiveur 26' se rapproche du support 54 de la bague. Dans un premier temps, il s'ensuit que le premier bras 46 du renvoi supplémentaire 44 reste aligné avec le bras 36 du renvoi suiveur 26' sur lequel est monté le renvoi supplémentaire.The rotation of the follower 26 'about its pivot point 26'a on the casing of the housing causes the guide rod 50 of the additional return 44 to slide in the ring 52. The fact that the ring 52 is mounted so that pivoting on the housing allows the guide rod 50 to remain permanently aligned with the sliding axis of the ring. As the guide rod slides in the ring, the pivot point 44a of the additional return 44 on the follower 26 'approaches the support 54 of the ring. At first, it follows that the first arm 46 of the additional return 44 remains aligned with the arm 36 of the follower 26 'on which is mounted the additional return.

A partir d'une certaine position du point de pivotement 44a du renvoi supplémentaire 44, appelée ci-après position de basculement, la tige de guidage 50 va provoquer, par effet de levier, une rotation accélérée du premier bras 46 du renvoi supplémentaire 44 autour de son point de pivotement 44a dans le sens de rotation du renvoi suiveur 26'. Cette rotation accélérée du premier bras du renvoi supplémentaire entraîne ainsi, par l'intermédiaire de la bielle, une accélération de la rotation de l'anneau suiveur en fermeture de calage. L'angle e schématisé sur la figure 2C représente l'accélération angulaire subie par le renvoi supplémentaire 44 par rapport à un système de commande dépourvu d'un tel dispositif.From a certain position of the pivot point 44a of the additional return 44, hereinafter referred to as the tilting position, the guide rod 50 will cause, by leverage, an accelerated rotation of the first arm 46 of the additional return wheel 44 around its pivot point 44a in the direction of rotation of the follower 26 '. This accelerated rotation of the first arm of the additional reference thereby, via the rod, an acceleration of the rotation of the follower ring in wedging closure. The angle e schematized on the Figure 2C represents the angular acceleration experienced by the additional return 44 with respect to a control system devoid of such a device.

A titre d'exemple, la position de basculement du point de pivotement 44a du renvoi supplémentaire 44 peut être définie comme étant la position à partir de laquelle plus de la moitié de la longueur de la tige de guidage 50 a coulissé dans la bague 52. Aussi, cette position de basculement peut être réglée en modifiant la position du support pivotant 54 de la bague 52 et/ou la longueur de la tige de guidage afin de choisir la zone de la trajectoire de commande qui doit être accélérée. Cette zone peut être aussi bien en début, milieu ou en fin de trajectoire.By way of example, the tilting position of the pivot point 44a of the additional return 44 can be defined as the position from which more than half the length of the guide rod 50 has slid into the ring 52. Also, this tilting position can be adjusted by changing the position of the pivoting support 54 of the ring 52 and / or the length of the guide rod to choose the area of the control path to be accelerated. This zone can be as well at the beginning, middle or at the end of the trajectory.

La figure 3 illustre l'effet sur la loi de calage des aubes d'une telle accélération. En pointillée est représentée une courbe de corrélation 100 (c'est-à-dire la courbe donnant l'angle de calage des aubes de l'étage suiveur en fonction de l'angle de calage des aubes de l'étage pilote) pour un système de commande dépourvu de renvoi supplémentaire et en traits pleins est schématisée la courbe de corrélation 102 établie pour le système de commande selon l'invention.The figure 3 illustrates the effect on the law of wedging of the blades of such an acceleration. Dotted line is represented a correlation curve 100 (that is to say the curve giving 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) for a control system without additional return and in solid lines is shown schematically the correlation curve 102 established for the control system according to the invention.

La courbe de corrélation 100 établie pour un système de commande dépourvu de renvoi supplémentaire est à pente progressive. Par rapport à cette courbe, la courbe de corrélation 102 présente une nette accélération de l'angle de calage des aubes de l'étage suiveur dans une zone angulaire 104. Sur cet exemple, la zone d'accélération 104 est en fin de trajectoire, c'est-à-dire en fermeture de calage. Comme expliqué précédemment, elle pourrait être localisée différemment.The correlation curve 100 established for a control system devoid of additional reference is gradual slope. With respect to this curve, the correlation curve 102 has a clear acceleration of the angle of wedging of the blades of the follower stage in an angular zone 104. In this example, the acceleration zone 104 is at the end of its trajectory, that is to say, in locking closure. As previously explained, it could be localized differently.

On notera que sur l'exemple de réalisation de la figure 2C, le support pivotant 54 de la bague 52 (qui correspond au point de pivotement sur le carter du renvoi supplémentaire 44) est disposé à l'intérieur d'un cercle C ayant pour centre le point de pivotement 26'a sur le boîtier du carter de l'organe suiveur 26' et pour rayon le bras 36 de l'organe suiveur sur lequel est monté le renvoi supplémentaire 44. Une telle configuration a pour conséquence d'accélérer la trajectoire de commande.It will be noted that on the embodiment of the Figure 2C , the pivoting support 54 of the ring 52 (which corresponds to the point of pivoting on the housing of the additional return 44) is disposed inside a circle C having the center of the pivot point 26'a on the housing of the housing of the follower member 26 'and for radius the arm 36 of the follower member on which is mounted the additional return 44. Such a configuration has the consequence of accelerating the control path.

Selon une autre configuration non représentée sur les figures, il est également possible de provoquer une décélération de la trajectoire de commande. Une décélération est en effet obtenue en disposant le support pivotant 54 de la bague 52 à l'extérieur du cercle C tel que défini précédemment. Bien entendu, en modifiant la position du support pivotant 54 de la bague 52 à l'extérieur du cercle C et/ou la longueur de la tige de guidage 50, il est aussi possible de choisir la zone de la trajectoire de commande qui doit être décélérée (début, milieu ou fin).According to another configuration not shown in the figures, it is also possible to cause a deceleration of the control path. A deceleration is indeed obtained by arranging the pivoting support 54 of the ring 52 outside the circle C as defined above. Of course, by modifying the position of the pivoting support 54 of the ring 52 outside the circle C and / or the length of the guide rod 50, it is also possible to choose the zone of the control path which must be decelerated (beginning, middle or end).

On notera enfin 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.Finally, 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)

  1. A system for controlling two stages (10, 10') of variable-pitch stator vanes (14, 14') of a turbomachine, each stage (10, 10') being formed by a plurality of vanes (14, 14') each of which is pivotally mounted on a casing (12) of the turbomachine, and by a control ring (22, 22') surrounding the casing and connected to each of the vanes (14, 14') of the stage via levers (18, 18'), the control system comprising a drive element (24) for turning the control ring (22) of one of the stages (10) via a leader member (26) pivotally mounted on the casing (12), and a synchronization bar (30) for transmitting the turning movement of the ring (22) driven by the drive element (24) to the control ring (22') of the other stage (10') via a follower member (26') pivotally mounted on the casing, the system being characterized in that it further comprises an additional pivot member (44) interposed between the follower member (26') and the follower ring (22'), said additional pivot member (44) being pivotally mounted on the follower member (26')and comprising an arm (46) pivotally mounted on a control rod (32') connected to the follower ring (22'), and a guide rod (50) slidably received in a bushing (52) pivotally mounted on the casing (12).
  2. A control system according to claim 1, in which the follower member (26') comprises a first arm (36) pivotally connected to the additional pivot member (44), and a second arm (40) connected to one end of the synchronization bar (30).
  3. A control system according to claim 2, in which the pivot point on the casing (12) of the additional pivot member (44) is disposed inside a circle (C) centered on the pivot point (26'a) on the casing of the follower member (26'), and has as its radius the first arm (36) of said follower member.
  4. A control system according to claim 2, in which the pivot point on the casing (12) of the additional pivot member (44) is disposed outside a circle (C) centered on the pivot point (26'a) on the casing of the follower member (26'), and has as its radius the first arm (36) of said follower member.
  5. A control system according to any one of claims 2 to 4, in which the leader member (26) comprises a first arm (34) connected to the ring (22) of the leader stage (10) via a second control rod (32), a second arm (38) connected to the end of the synchronization bar (30) opposite from its end connected to the follower member (26'), and a third arm (42) connected to the drive element (24).
EP06112991A 2005-05-17 2006-04-24 Control system for variable guide vane stages of a turbomachine Active EP1724472B1 (en)

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FR0504918A FR2885969B1 (en) 2005-05-17 2005-05-17 TURBOMACHINE VARIABLE ROTATION ANGLE STATOR AUTONER STAGE CONTROL SYSTEM

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RU2501957C2 (en) * 2008-09-30 2013-12-20 Снекма System to control equipment of gas turbine engine with variable geometry, in particular, by means of control levers

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CA2547026A1 (en) 2006-11-17
EP1724472A3 (en) 2009-01-21
FR2885969A1 (en) 2006-11-24
RU2396438C2 (en) 2010-08-10
JP4773876B2 (en) 2011-09-14
EP1724472A2 (en) 2006-11-22
CA2547026C (en) 2013-09-17
DE602006014902D1 (en) 2010-07-29
US20060263206A1 (en) 2006-11-23
RU2006116817A (en) 2007-11-27
JP2006322457A (en) 2006-11-30
US7322790B2 (en) 2008-01-29
FR2885969B1 (en) 2007-08-10

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