EP0765992B1 - Actuating system for variable stator vanes - Google Patents

Actuating system for variable stator vanes Download PDF

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Publication number
EP0765992B1
EP0765992B1 EP96402040A EP96402040A EP0765992B1 EP 0765992 B1 EP0765992 B1 EP 0765992B1 EP 96402040 A EP96402040 A EP 96402040A EP 96402040 A EP96402040 A EP 96402040A EP 0765992 B1 EP0765992 B1 EP 0765992B1
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EP
European Patent Office
Prior art keywords
articulated
cams
stationary pivot
cam
crank
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Expired - Lifetime
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EP96402040A
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German (de)
French (fr)
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EP0765992A1 (en
Inventor
Jean-Louis Charbonnel
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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    • 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

Definitions

  • the invention relates to a device for control of a stage of pivoting or stalling vanes variable.
  • EP-A-0 094 296 a particular device for setting a blade stage regulating the pressure drop in a secondary turbojet channel.
  • the control ring is articulated to levers by means of rods and bent levers which control half of the blades so as to impose angular movements opposite two adjacent blades.
  • coping mechanisms command which involve the use of an organ actuator such as a cylinder and a mechanism transmission composed of levers, connecting rods, etc.
  • organ actuator such as a cylinder
  • mechanism transmission composed of levers, connecting rods, etc.
  • the characteristics of these transmissions are pretty varied and some allow orders not vane linear, that is to say that the rotation of the these are not proportional to the displacement of the actuator.
  • the invention belongs to this kind of control devices and its essential advantage is that the transmission is particularly simple.
  • control device is characterized in that the control ring is connected to the cam by an articulated transmission rod.
  • the control device can also concern several stages of blades and several rings order at a time.
  • it is then possible to have other cams articulated by pivoting around other first axes fixed to other control rings of other stages variable pitch vanes, the cams being connected between them by an articulated synchronization bar cams at identical positions relative to first fixed axes.
  • there are other cams articulated in pivoting around other first axes fixed to others control rings for other stages of wedge blades variable the other cams being interconnected and with the crank turning by a bar of synchronization articulated to the other cams and to the crank in identical positions with respect to other first fixed axes and the second fixed axis.
  • Figure 1 shows the entrance to a turbomachine with in particular a compressor section at low pressure 1 and a compressor section at high pressure 2. It is on this that the invention is established.
  • Each compressor is above all composed of stages of fixed blades 3 and movable blades 4 which alternate, some attached to a stator 5 which surrounds the annular vein 6 for gas circulation and the others fixed to a rotor 7 delimiting the vein 6, and turning with him.
  • a pin 17 fixed on the stator is established at cam 15 elbow to allow it to rotate, and its other arm 18 extends opposite the rod of transmission 12 and carries at its end another articulation 19 intended to support a bar of synchronization 20 perpendicular to the ring of control 10, that is to say arranged in the axial direction of the machine.
  • Synchronization bar 20 is similarly articulated to other cams 15 assigned to the control of other stages of fixed blades 3 by transmissions similar to the one just described and which include in particular a control ring 10 for each of the floors.
  • the only difference is what the other cams, denoted 15a, 15b, 15c, etc., have arms 16a, 16b or 16c, etc.
  • the control mechanism unlike a solution previously adopted by the plaintiff, does not not a lever attached to the fixed axis 17 of the cam 15 considered first, and whose purpose is to rotate it to pull or push on control rods 12 through all the cams 15 and timing bar 20. Instead from that, we have a crank 21 rotating around a second fixed axis 26 parallel to the first axes fixed 17, 17a, 17b, 17c, etc., and a connecting rod 22 of which the ends are articulated, for the first 23 to the end of the crank 21, and for the second 24 to a part of the second arm 18 remote from the fixed axis 17.
  • the angle ⁇ is therefore a sinusoidal function of the angle ⁇ .
  • Crank 21 can be turned by the rod 27 of a jack 28 articulated at a fixed point 29, according to a usual design.
  • angles ⁇ of rotation imposed on the levers 9 and the blades 3 are different for the various stages, and more specifically, they are proportional to lengths l, la, lb, lc, etc. of the arms 16 between the axis fixed 17 and articulation 14 of the transmission rod 12, that is to say that the rotation laws are all sinusoidal.
  • cam 15 and 15a are not connected to synchronization bar 20 and its second arm 18 is replaced by arm 118 of another shape intended to receive a joint 123 uniting it with one end of a connecting rod 122 similar or similar to the connecting rod 22 and the other end of which is joined by a joint 124 to a protrusion 125 formed on a cam 115a moreover similar to cam 15a and located in the same place.
  • the fixed axis 117a of articulation of the cam 115a is not an inert axis but a control axis dependent on the actuator member.
  • the crank 21 of the previous embodiment is deleted and the cam 115a is a motor lever.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Transmission Devices (AREA)

Description

L'invention se rapporte à un dispositif de commande d'un étage d'aubes pivotantes ou à calage variable.The invention relates to a device for control of a stage of pivoting or stalling vanes variable.

On rencontre de telles aubes sur les stators de certains moteurs d'avions : selon les régimes de la machine, on éprouve le besoin de redresser plus ou moins le flux du gaz qui passe par ces étages d'aubes, qu'on fait donc pivoter autour de leur axe sous l'action d'un mécanisme de commande situé de l'autre côté du stator.We meet such blades on the stators of certain aircraft engines: according to the regimes of the machine, we feel the need to straighten more or minus the flow of gas passing through these stages of blades, that we therefore rotate around their axis under the action of a control mechanism located on the other side of the stator.

Les pivots des aubes, qui traversent le stator, sont unis à des leviers de commande tous reliés à un anneau de commande qui entoure le stator et qu'un mécanisme de commande fait tourner. Un exemple de ces dispositions est donné par US-A-2 999 630.The pivots of the blades, which cross the stator, are linked to control levers all connected to a control ring that surrounds the stator and that a control mechanism rotates. An example of these provisions is given by US-A-2,999,630.

On connaít par ailleurs par EP-A-0 094 296 un dispositif particulier du calage d'un étage d'aubes réglant la perte de charge dans un canal secondaire de turboréacteur. L'anneau de commande est articulé à des leviers par l'intermédiaire de biellettes et de leviers coudés qui commandent la moitié des aubes de manière à imposer des mouvements angulaires opposés à deux aubes adjacentes.We also know from EP-A-0 094 296 a particular device for setting a blade stage regulating the pressure drop in a secondary turbojet channel. The control ring is articulated to levers by means of rods and bent levers which control half of the blades so as to impose angular movements opposite two adjacent blades.

Il existe de nombreux genres de mécanismes de commande, qui impliquent l'emploi d'un organe actionneur tel qu'un vérin et d'un mécanisme de transmission composé de leviers, de bielles, etc. Les caractéristiques de ces transmissions sont assez variées et certaines permettent des commandes non linéaires des aubes, c'est-à-dire que la rotation du celles-ci n'est pas proportionnelle au déplacement de l'actionneur. L'invention appartient à ce genre de dispositifs de commande et son avantage essentiel est que la transmission est particulièrement simple.There are many kinds of coping mechanisms command, which involve the use of an organ actuator such as a cylinder and a mechanism transmission composed of levers, connecting rods, etc. The characteristics of these transmissions are pretty varied and some allow orders not vane linear, that is to say that the rotation of the these are not proportional to the displacement of the actuator. The invention belongs to this kind of control devices and its essential advantage is that the transmission is particularly simple.

Par DE-A-1 601 625, on connaít en outre un dispositif de commande d'un étage d'aubes à calage variable munies de leviers réunis à un anneau de commande, l'anneau de commande étant articulé à une came pivotant autour d'un premier axe fixe, la came étant unie à une manivelle de commande tournant autour d'un second axe fixe parallèle au premier axe par une biellette articulée à la came et à la manivelle tournante en des points distincts des axes fixes.By DE-A-1 601 625, we also know a device for controlling a stage of blades at variable timing fitted with levers joined to a ring control, the control ring being articulated to a cam pivoting around a first fixed axis, the cam being joined to a control crank rotating around a second fixed axis parallel to the first axis by a link articulated to the cam and to the rotating crank at points distinct from the axes fixed.

Selon l'invention, le dispositif de commande est caractérisé en ce que l'anneau de commande est relié à la came par une tige de transmission articulée.According to the invention, the control device is characterized in that the control ring is connected to the cam by an articulated transmission rod.

Le dispositif de commande peut d'ailleurs concerner plusieurs étages d'aubes et plusieurs anneaux de commande à la fois. Pour appliquer l'invention, il est alors possible de disposer d'autres cames articulées en pivotant autour d'autres premiers axes fixes à d'autres anneaux de commande d'autres étages d'aubes à calage variable, les cames étant reliées entre elles par une barre de synchronisation articulée aux cames à des positions identiques par rapport aux premiers axes fixes. Ou encore, dans une conception différente, on dispose d'autres cames articulées en pivotant autour d'autres premiers axes fixes à d'autres anneaux de commande d'autres étages d'aubes à calage variable, les autres cames étant reliées entre elles et à la manivelle tournante par une barre de synchronisation articulée aux autres cames et à la manivelle à des positions identiques par rapport aux autres premiers axes fixes et au second axe fixe.The control device can also concern several stages of blades and several rings order at a time. To apply the invention, it it is then possible to have other cams articulated by pivoting around other first axes fixed to other control rings of other stages variable pitch vanes, the cams being connected between them by an articulated synchronization bar cams at identical positions relative to first fixed axes. Or, in a design different, there are other cams articulated in pivoting around other first axes fixed to others control rings for other stages of wedge blades variable, the other cams being interconnected and with the crank turning by a bar of synchronization articulated to the other cams and to the crank in identical positions with respect to other first fixed axes and the second fixed axis.

L'invention va maintenant être décrite plus en détail à l'aide des figures suivantes, qui sont annexées à titre illustratif et non limitatif :

  • la figure 1 représente une vue générale d'implantation de l'invention,
  • les figures 2 et 3 représentent une première réalisation de l'invention, et
  • la figure 4 représente une autre réalisation de l'invention.
The invention will now be described in more detail with the aid of the following figures, which are annexed by way of illustration and not limitation:
  • FIG. 1 represents a general view of the implantation of the invention,
  • FIGS. 2 and 3 represent a first embodiment of the invention, and
  • Figure 4 shows another embodiment of the invention.

La figure 1 représente l'entrée d'une turbomachine avec notamment une section de compresseur à basse pression 1 et une section de compresseur à haute pression 2. C'est sur celle-ci que l'invention est établie. Chacun des compresseurs est avant tout composé d'étages d'aubes fixes 3 et d'aubes mobiles 4 qui alternent, les unes attachées à un stator 5 qui entoure la veine 6 annulaire de circulation des gaz et les autres fixées à un rotor 7 délimitant la veine 6, et tournant avec lui.Figure 1 shows the entrance to a turbomachine with in particular a compressor section at low pressure 1 and a compressor section at high pressure 2. It is on this that the invention is established. Each compressor is above all composed of stages of fixed blades 3 and movable blades 4 which alternate, some attached to a stator 5 which surrounds the annular vein 6 for gas circulation and the others fixed to a rotor 7 delimiting the vein 6, and turning with him.

Les aubes fixes 3 peuvent en réalité pivoter autour d'un pivot 8 traversant le stator 5. Le pivot 8 de chacune des aubes 3 est terminé par un levier 9. Les leviers 9 de chacun des étages d'aubes sont unis à un anneau de commande 10 commun.Fixed vanes 3 can actually rotate around a pivot 8 passing through the stator 5. The pivot 8 of each of the blades 3 is terminated by a lever 9. The levers 9 of each of the blade stages are joined to a control ring 10 common.

On voit aux figure 2 et 3 que la réunion des leviers 9 d'un étage à l'anneau de commande 10 associé est faite par des articulations 11 qui maintiennent l'anneau de commande 10 tout en lui permettant cependant de tourner sur lui-même. Cela peut être accompli en munissant l'anneau de commande d'une tige de transmission 12 dont une extrémité 13 est articulée à lui, de façon à permettre des déplacements angulaires de la tige de transmission 12, et dont l'autre extrémité 14 est articulée à une came 15 en forme de levier coudé et plus précisément au bout d'un des bras 16 de ce levier coudé.We see in Figures 2 and 3 that the meeting of levers 9 from one stage to the associated control ring 10 is made by joints 11 which hold the control ring 10 while allowing it however to turn on itself. This may be accomplished by providing the control ring with a rod transmission 12 of which one end 13 is articulated to him, so as to allow angular displacements of the transmission rod 12, and of which the other end 14 is articulated to a cam 15 in the form of bent lever and more precisely at the end of one of the arms 16 of this bent lever.

Un axe 17 fixe sur le stator est établi au coude de la came 15 pour lui permettre de tourner, et son autre bras 18 s'étend à l'opposé de la tige de transmission 12 et porte à son extrémité une autre articulation 19 destinée à soutenir une barre de synchronisation 20 perpendiculaire à l'anneau de commande 10, c'est-à-dire disposée dans le sens axial de la machine. La barre de synchronisation 20 est pareillement articulée à d'autres cames 15 affectées à la commande d'autres étages d'aubes fixes 3 par des transmissions semblables à celle qu'on vient de décrire et qui comprennent notamment un anneau de commande 10 pour chacun des étages. La seule différence consiste en ce que les autres cames, notées 15a, 15b, 15c, etc., ont des bras 16a, 16b ou 16c, etc. articulés aux tiges de transmission 12 de longueurs différentes ℓ, ℓa, ℓb, ℓc, etc. Cela permettra, comme on le verra clairement d'ici peu, de commander différemment les étages d'aubes fixes 3, c'est-à-dire de leur imposer des rotations différentes. Mais les seconds bras 18 ont tous la même longueur et sont parallèles, si bien que la barre de synchronisation 20 est articulée aux cames 15, 15a, 15b, 15c, etc., à une position identique des axes fixes 17, 17a, 17b, 17c, etc.A pin 17 fixed on the stator is established at cam 15 elbow to allow it to rotate, and its other arm 18 extends opposite the rod of transmission 12 and carries at its end another articulation 19 intended to support a bar of synchronization 20 perpendicular to the ring of control 10, that is to say arranged in the axial direction of the machine. Synchronization bar 20 is similarly articulated to other cams 15 assigned to the control of other stages of fixed blades 3 by transmissions similar to the one just described and which include in particular a control ring 10 for each of the floors. The only difference is what the other cams, denoted 15a, 15b, 15c, etc., have arms 16a, 16b or 16c, etc. articulated to the rods transmission 12 of different lengths ℓ, ℓa, ℓb, ℓc, etc. This will allow, as we will clearly see soon, order the blade stages differently fixed 3, that is to say to impose rotations on them different. But the second arms 18 all have the same length and are parallel, so that the bar synchronization 20 is articulated to the cams 15, 15a, 15b, 15c, etc., at an identical position of the fixed axes 17, 17a, 17b, 17c, etc.

Le mécanisme de commande, contrairement à une solution précédemment adoptée par la demanderesse, ne consiste pas en un levier fixé à l'axe fixe 17 de la came 15 considérée en premier, et dont le but est de faire tourner celui-ci pour tirer ou pousser sur les tiges de commande 12 par l'intermédiaire de toutes les cames 15 et de la barre de synchronisation 20. Au lieu de cela, on dispose une manivelle 21 tournante autour d'un second axe fixe 26 parallèle aux premiers axes fixes 17, 17a, 17b, 17c, etc., et une bielle 22 dont les extrémités sont articulées, pour la première 23 à l'extrémité de la manivelle 21, et pour la seconde 24 à une partie du second bras 18 éloignée de l'axe fixe 17.The control mechanism, unlike a solution previously adopted by the plaintiff, does not not a lever attached to the fixed axis 17 of the cam 15 considered first, and whose purpose is to rotate it to pull or push on control rods 12 through all the cams 15 and timing bar 20. Instead from that, we have a crank 21 rotating around a second fixed axis 26 parallel to the first axes fixed 17, 17a, 17b, 17c, etc., and a connecting rod 22 of which the ends are articulated, for the first 23 to the end of the crank 21, and for the second 24 to a part of the second arm 18 remote from the fixed axis 17.

Les lois de commande de l'angle β de rotation des aubes 3 en fonction de l'angle α de rotation de la manivelle 21 dépendent essentiellement de la longueur L de la bielle 22 entre les articulations 23 et 24 et de rayons R1 et R2 mesurés sur les cames 15 entre l'axe fixe 17 et les articulations 14 et 24. On obtient finalement, avec ce mécanisme où la manivelle 21, la bielle 22, les cames 15, 15a, 15b, 15c, etc., la barre de synchronisation 20 et les tiges de commande 12 s'étendent sensiblement dans un plan perpendiculaire aux axes fixes 17, 17a, 17b, 17c, etc. et 26, la formule suivante à partir de positions angulaires d'origine α0 et β0 : β + β0 2 = Arc tg t, où t est une racine de l'équation t2(Z-K)+2tT-Z-K=0, avec T=[R2sin(α0-α)-x], E=[-R2cos(α0-α)+y]' et

Figure 00060001
x et y étant les mesures de la distance entre l'axe fixe 26 et l'axe fixe 17, projetée sur les axes parallèles respectivement à la barre de synchronisation 20 et aux anneaux de commande 10 une fois projetés dans le plan des figures 2 et 3.The laws controlling the angle β of rotation of the blades 3 as a function of the angle α of rotation of the crank 21 essentially depend on the length L of the connecting rod 22 between the joints 23 and 24 and of radii R 1 and R 2 measured on the cams 15 between the fixed axis 17 and the joints 14 and 24. Finally, with this mechanism, the crank 21, the connecting rod 22, the cams 15, 15a, 15b, 15c, etc., are obtained. synchronization 20 and the control rods 12 extend substantially in a plane perpendicular to the fixed axes 17, 17a, 17b, 17c, etc. and 26, the following formula from angular positions of origin α 0 and β 0 : β + β 0 2 = Arc tg t, where t is a root of the equation t 2 (ZK) + 2tT-ZK = 0, with T = [R 2 sin (α 0 -α) -x], E = [- R 2 cos (α 0 -α ) + y] 'and
Figure 00060001
x and y being the measurements of the distance between the fixed axis 26 and the fixed axis 17, projected onto the axes parallel respectively to the synchronization bar 20 and to the control rings 10 once projected in the plane of FIGS. 2 and 3.

L'angle β est donc une fonction sinusoïdale de l'angle α.The angle β is therefore a sinusoidal function of the angle α.

La manivelle 21 peut être tournée par la tige 27 d'un vérin 28 articulé à un point fixe 29, selon une conception usuelle.Crank 21 can be turned by the rod 27 of a jack 28 articulated at a fixed point 29, according to a usual design.

Les angles β de rotation infligés aux leviers 9 et aux aubes 3 sont différents pour les divers étages, et plus précisément, ils sont proportionnels aux longueurs ℓ, ℓa, ℓb, ℓc, etc., des bras 16 entre l'axe fixe 17 et l'articulation 14 de la tige de transmission 12, c'est-à-dire que les lois de rotation sont toutes sinusoïdales.The angles β of rotation imposed on the levers 9 and the blades 3 are different for the various stages, and more specifically, they are proportional to lengths ℓ, ℓa, ℓb, ℓc, etc. of the arms 16 between the axis fixed 17 and articulation 14 of the transmission rod 12, that is to say that the rotation laws are all sinusoidal.

Dans la conception de la figure 4, un des étages d'aubes fixes 3, celui de gauche sur la figure, est de même déplacé selon suivant une loi non linéaire, mais les autres obéissent à une loi proportionnelle avec les déplacements de l'actionneur. Avec les notations des figures 2 et 3, on retrouve la barre de synchronisation 20 à laquelle sont articulés les cames 15b, 15c, etc. Les modifications concernent les cames 15 et 15a : la came 15, notée désormais 115, n'est pas reliée à la barre de synchronisation 20 et son second bras 18 est remplacé par un bras 118 d'une autre forme destiné à recevoir une articulation 123 l'unissant à une extrémité d'une bielle 122 analogue ou semblable à la bielle 22 et dont l'autre extrémité est réunie par une articulation 124 à une excroissance 125 ménagée sur une came 115a par ailleurs semblable à la came 15a et située au même endroit. Une autre différence consiste en ce que l'axe 117a fixe d'articulation de la came 115a n'est pas un axe inerte mais un axe de commande dépendant de l'organe actionneur. En un mot, la manivelle 21 de la réalisation précédente est supprimée et la came 115a est un levier moteur.In the design of Figure 4, one of fixed blade stages 3, the one on the left in the figure, is likewise moved according to a nonlinear law, but the others obey a proportional law with the movements of the actuator. With the notations of Figures 2 and 3, we find the bar synchronization 20 to which the cams are articulated 15b, 15c, etc. The modifications concern the cams 15 and 15a: cam 15, now denoted 115, is not connected to synchronization bar 20 and its second arm 18 is replaced by arm 118 of another shape intended to receive a joint 123 uniting it with one end of a connecting rod 122 similar or similar to the connecting rod 22 and the other end of which is joined by a joint 124 to a protrusion 125 formed on a cam 115a moreover similar to cam 15a and located in the same place. Another difference is in that the fixed axis 117a of articulation of the cam 115a is not an inert axis but a control axis dependent on the actuator member. In a word, the crank 21 of the previous embodiment is deleted and the cam 115a is a motor lever.

Claims (3)

  1. An actuating device for a stage of adjustable vanes (3) having levers (9) connected to an actuator ring (10) which is articulated to a cam (15, 115) pivotable about a first stationary pivot pin (17), the cam (15, 115) being connected to an actuating crank (21, 115a), rotatable about a second stationary pivot pin (26, 117a) parallel to the first stationary pivot pin (17), by a link (22, 122) articulated to the cant and to the rotatable crank at points distinct from the stationary pivot pins, characterised in that the actuator ring (10) is connected to the cam (15, 115) by an articulated transmission rod (12).
  2. An actuating device according to claim 1, characterised in that it comprises further cams (15a, 15b, 15c, ...) articulated, by pivoting about further first stationary pivot pins (17a, 17b, 17c, ...), to further actuator rings (10) of further adjustable vane stages (3), the cams being interconnected by a synchronising rod (20) articulated to the cams at identical positions relative to the first stationary pivot pins.
  3. An actuating device according to claim 1, characterised in that it comprises further cams (15b, 15c, ...) anticulated, by pivoting about further first stationary pivot pins (17b, 17c, ...), to further actuator rings of further adjustable vane stages, the further cams being connected to one another and to the adjustable crank (115a) by a synchronising rod (20) articulated to the further cams and to the rotatable link at positions which are identical relative to the further first stationary pivot pins and to the second stationary pivot pin (117a).
EP96402040A 1995-09-27 1996-09-26 Actuating system for variable stator vanes Expired - Lifetime EP0765992B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9511301 1995-09-27
FR9511301A FR2739137B1 (en) 1995-09-27 1995-09-27 DEVICE FOR CONTROLLING A VARIABLE SETTING BLADE STAGE

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EP0765992A1 EP0765992A1 (en) 1997-04-02
EP0765992B1 true EP0765992B1 (en) 2001-08-29

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EP (1) EP0765992B1 (en)
DE (1) DE69614794T2 (en)
FR (1) FR2739137B1 (en)

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US8915703B2 (en) 2011-07-28 2014-12-23 United Technologies Corporation Internally actuated inlet guide vane for fan section
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FR2739137A1 (en) 1997-03-28
EP0765992A1 (en) 1997-04-02
FR2739137B1 (en) 1997-10-31
US5692879A (en) 1997-12-02
DE69614794D1 (en) 2001-10-04
DE69614794T2 (en) 2002-05-23

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