EP1637742A2 - Actuator lever for setting the angular position of guide vanes in a turbo machine. - Google Patents
Actuator lever for setting the angular position of guide vanes in a turbo machine. Download PDFInfo
- Publication number
- EP1637742A2 EP1637742A2 EP05291889A EP05291889A EP1637742A2 EP 1637742 A2 EP1637742 A2 EP 1637742A2 EP 05291889 A EP05291889 A EP 05291889A EP 05291889 A EP05291889 A EP 05291889A EP 1637742 A2 EP1637742 A2 EP 1637742A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- lever
- intermediate portion
- control lever
- thickness
- turbomachine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 238000005452 bending Methods 0.000 claims description 5
- 238000005422 blasting Methods 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 2
- 229910052719 titanium Inorganic materials 0.000 claims description 2
- 239000010936 titanium Substances 0.000 claims description 2
- 238000002788 crimping Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- 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
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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
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- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
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- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
Definitions
- the present invention relates to a lever for controlling the angular setting of a stator blade in a turbomachine and a turbomachine compressor comprising a plurality of stator vanes with variable pitch angle equipped with these control levers.
- Adjusting the angular setting of the stator vanes in a turbomachine such as a turbojet engine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the various flight configurations.
- This adjustment is effected by means of a lever which comprises a first end fixedly mounted on a pivot of the blade to drive it in rotation about its longitudinal axis, a second end comprising a cylindrical pin for mounting on a control ring which externally surrounds the stator of the turbomachine and which is rotatable about the longitudinal axis of the stator by a motor means such as a cylinder or an electric motor, and a flat intermediate portion connecting the first and second ends of the lever.
- a lever which comprises a first end fixedly mounted on a pivot of the blade to drive it in rotation about its longitudinal axis, a second end comprising a cylindrical pin for mounting on a control ring which externally surrounds the stator of the turbomachine and which is rotatable about the longitudinal axis of the stator by a motor means such as a cylinder or an electric motor, and a flat intermediate portion connecting the first and second ends of the lever.
- the control lever which is rotated by the control ring and which is fixed on the pivot of the blade, is subjected to bending and torsion forces which are exerted mainly at its intermediate portion and its second end.
- these control levers are subjected to vibrations due in particular to the passages of the rotor blades in front of the stator vanes, the frequencies of these vibrations varying with the speed of rotation of the rotor.
- the present invention aims to prevent the occurrence of cracks or cracks in a lever of the aforementioned type, without significantly modifying the stiffness of the lever.
- a lever for controlling the angular setting of a stator blade in particular in a turbomachine compressor, comprising a first end intended to be fixedly mounted on a blade pivot, a second end comprising a cylindrical pin. on a drive means, and a flat intermediate portion connecting the first and second ends, said first end having a thickness and a width greater than those of the intermediate portion and the second end of the lever, characterized in that the shapes and dimensions of the intermediate portion and the second end are determined to increase the natural frequencies of the lever in bending and torsion above the vibratory frequencies of the turbomachine upstream of the lever and to maintain the stiffness of the lever.
- the second end of the control lever has a thickness greater than that of the intermediate portion, and the intermediate portion locally has a width less than that of the second end of the lever.
- Increasing the thickness of the second end of the control lever makes it possible to better withstand the stresses during crimping of the cylindrical pin, and to limit the appearance and propagation of cracks or cracks. It causes an increase in the overall stiffness of the lever, which is compensated by a local decrease in the width of the intermediate portion so that the control lever retains the same stiffness and requires the same operating power as before.
- the intermediate portion of the lever is of constant thickness and is connected to the ends of the lever by areas of progressively increasing thickness.
- the intermediate portion of the lever has curved longitudinal edges of concave shape which allow progressive transitions between portions of different widths by avoiding stress concentrations in parts of the lever whose width varies abruptly and discontinuously.
- control lever shape and dimensions of the control lever are dynamically optimized to increase the eigenfrequencies of the lever in bending and torsion beyond the vibratory frequencies of the turbomachine upstream, and statically by reducing the local concentrations of stresses.
- control lever according to the invention is advantageously subjected at least partially to shot blasting, this treatment making it possible to harden the surface of the lever and thus to protect it against shocks or possible blows during its handling and its mounting on the blade pivot and on the control ring, these shocks and blows can be the cause of cracks or microcracks.
- the invention also proposes a turbomachine compressor, for example a turbojet engine comprising a plurality of variable-pitch vanes equipped with control levers of the aforementioned type.
- FIG. 1 shows a portion of a high-pressure compressor 10 of a turbomachine, in which each stage of the compressor comprises a row of guide vanes 12 mounted on the stator and a row of vanes 14 carried by the rotor.
- the blades 12 of the stator are rectifiers whose orientation or angular setting is adjustable using control levers 16 driven by a control ring 18 actuated by motor means (not shown) of the type jack or electric motor.
- Each control lever 16 comprises a first end 20 fixed on a radial pin 22 of a blade 12, guided in rotation in a bearing 24 mounted in a radial chimney of an outer casing 26, a second end 28 and a flat intermediate portion Connecting the ends 20 and 28.
- the second end 28 of the control lever 16 carries a cylindrical pin 32 which is crimped on this end 28 and is guided in rotation in a cylindrical sleeve 34 of the control ring 18.
- the first end 20 of the lever 16 has a thickness and a width greater than those of the intermediate portion 34 and the second end 28 of the lever 16.
- the thickness of the first end 20 is about 10 mm and its width is about 22 mm.
- the second end 28 of the lever 16 which carries the cylindrical mounting pin 32 on the control ring 18 has a circular edge extending about 180 ° around the crimped head of the cylindrical pin 32.
- the thickness of the second end is about 1.1 mm and its width is about 10 mm.
- the intermediate portion 34 which connects the first and second ends 20 and 28 has the same thickness as the second end 28 and a triangular shape and is connected to the first end 20 by a connecting zone 38 of gradually increasing thickness.
- the thickness of the intermediate portion 34 is about 1.1 mm and its width varies between about 10 and 22 mm.
- the eigenfrequencies of the levers 16 in flexion and torsion may coincide with the vibratory frequencies of the upstream part of the compressor and then cause significant vibrations of the levers 16 resulting in the formation of cracks or cracks , in particular at the crimping zones of the cylindrical pins 32 on the second ends 28 of the levers 16.
- This vibratory frequency depends on the speed of rotation of the rotor and is about 6500 Hz for a particular example of a high-pressure compressor considered.
- the shapes and dimensions of the intermediate portion 34 and the second end 28 are modified so that the frequencies of the lever 16 in flexion and in torsion are greater than the vibratory frequencies of the upstream part of the compressor, without appreciably increasing the stiffness of the lever.
- Figure 3 shows schematically and in perspective an embodiment of a control lever 40 according to the invention.
- the second end 42 of the lever 40 has a thickness greater than that of the second end 28 of the lever 16 of the prior art to better withstand the stresses due to the crimping of the cylindrical pin 32 and delay the propagation of cracks or fissures. For example, this thickness is about 1.8 mm.
- the shape of the second end 42 has also been modified by increasing the angular extent of its rounded edge which extends over more than 180 °.
- This rounded edge may have one or more radii of curvature varying for example between 6 and 15 mm.
- the intermediate portion 44 of the lever 40 is of constant thickness, greater than that of the intermediate portion 34 of the lever 16 of the prior art but lower than that of the second end 42 of the lever 40.
- the thickness of the part intermediate 44 of the lever 40 is about 1.4 mm.
- the increase in stiffness of the lever 40 due to the increase in the thickness of the intermediate portion 44 and the second end 42 is compensated by a decrease in the width of at least a portion 46 of the intermediate portion 44 of the lever 40, which allows to maintain the same overall stiffness as in the prior art, this portion 46 being connected to the second end 42 of the lever.
- the portion 46 has a width of about 8 mm, less than that of the second end 42 and is delimited by substantially parallel longitudinal edges.
- the intermediate portion 44 of the lever 40 is connected to the first end 48 by a connecting zone 50 of short length and gradually increasing thickness which is substantially identical to the connecting zone 38 of the lever 16 of the prior art and whose thickness varies between that of the intermediate portion 44 of the lever 40 and that of its first end 48.
- Another zone 52 of progressively increasing thickness connects the portion 46 of the intermediate portion 44 to the second end 42 of the lever 40.
- edges 54, 56 of the connecting zones 50 and 52 and the intermediate portion 44 are curved and concave and connected to the straight edges of the portion 46 mentioned above.
- the edges 54 may have one or more radii of curvature which are typically between 6 and 15 mm for example, and the edges 56 may also have one or more radii of curvature which are typically between 15 and 30 mm for example.
- the radii of curvature of the edges 54, 56 thus increase from the second end 42 of the lever 40 towards the first end 48.
- the control lever 40 according to the invention is preferably treated at least partially by shot-blasting, for example on the intermediate portion 44 and / or on the second end 42 of the lever 40.
- This treatment makes it possible to harden the surface of the lever and therefore of improve its protection against shocks or blows that may occur during the mounting of the control lever 40 and may cause crack initiation or cracking.
- control lever 40 according to the invention is advantageously made of titanium.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
La présente invention concerne un levier de commande du calage angulaire d'une aube de stator dans une turbomachine et un compresseur de turbomachine comprenant une pluralité d'aubes de stator à angle de calage variable équipées de ces leviers de commande.The present invention relates to a lever for controlling the angular setting of a stator blade in a turbomachine and a turbomachine compressor comprising a plurality of stator vanes with variable pitch angle equipped with these control levers.
Le réglage du calage angulaire des aubes de stator dans une turbomachine telle qu'un turboréacteur est destiné à optimiser le rendement de cette turbomachine et à réduire sa consommation en carburant dans les différentes configurations de vol.Adjusting the angular setting of the stator vanes in a turbomachine such as a turbojet engine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the various flight configurations.
Ce réglage est effectué au moyen d'un levier qui comprend une première extrémité montée fixement sur un pivot de l'aube pour l'entraîner en rotation autour de son axe longitudinal, une deuxième extrémité comportant un pion cylindrique de montage sur un anneau de commande qui entoure extérieurement le stator de la turbomachine et qui est déplaçable en rotation autour de l'axe longitudinal du stator par un moyen moteur tel qu'un vérin ou un moteur électrique, et une partie intermédiaire plate reliant les première et deuxième extrémités du levier.This adjustment is effected by means of a lever which comprises a first end fixedly mounted on a pivot of the blade to drive it in rotation about its longitudinal axis, a second end comprising a cylindrical pin for mounting on a control ring which externally surrounds the stator of the turbomachine and which is rotatable about the longitudinal axis of the stator by a motor means such as a cylinder or an electric motor, and a flat intermediate portion connecting the first and second ends of the lever.
Le levier de commande qui est entraîné en rotation par l'anneau de commande et qui est fixé sur le pivot de l'aube, est soumis à des forces de flexion et de torsion qui s'exercent principalement au niveau de sa partie intermédiaire et de sa deuxième extrémité.The control lever which is rotated by the control ring and which is fixed on the pivot of the blade, is subjected to bending and torsion forces which are exerted mainly at its intermediate portion and its second end.
En fonctionnement de la turbomachine, ces leviers de commande sont soumis à des vibrations dues notamment aux passages des aubes de rotor devant les aubes de stator, les fréquences de ces vibrations variant avec la vitesse de rotation du rotor.In operation of the turbomachine, these control levers are subjected to vibrations due in particular to the passages of the rotor blades in front of the stator vanes, the frequencies of these vibrations varying with the speed of rotation of the rotor.
On a constaté que ces fréquences pouvaient coïncider avec un mode vibratoire des leviers précités, et que les contraintes résultantes subies par les leviers pouvaient provoquer l'apparition de criques ou de fissures dans ces leviers, notamment dans la zone reliant leur partie intermédiaire à leur deuxième extrémité reliée à l'anneau de commande, avec un risque de rupture des leviers.It has been found that these frequencies could coincide with a vibratory mode of the aforementioned levers, and that the resulting constraints on the levers could cause the appearance of cracks or cracks in these levers, especially in the zone connecting their part. intermediate at their second end connected to the control ring, with a risk of breaking levers.
Une solution permettant d'éviter cet inconvénient grave consisterait à surdimensionner chaque levier pour éviter toute apparition de criques ou fissures et donc éviter tout risque de rupture du levier. Cela conduirait cependant à augmenter de façon correspondante la raideur du levier, ainsi que la puissance nécessaire pour déplacer le levier puisque tout déplacement du levier se traduit par une déformation du levier en flexion et en torsion. Comme l'énergie consommée par l'actionnement des leviers est prélevée sur l'énergie fournie par la turbomachine, une telle solution serait très désavantageuse.One solution to avoid this serious drawback would be to oversize each lever to prevent any occurrence of cracks or fissures and thus avoid any risk of rupture of the lever. This would however lead to correspondingly increase the stiffness of the lever, as well as the power required to move the lever since any movement of the lever results in a deformation of the lever flexion and torsion. As the energy consumed by the operation of the levers is taken from the energy supplied by the turbomachine, such a solution would be very disadvantageous.
La présente invention a pour but d'éviter l'apparition de criques ou fissures dans un levier du type précité, sans modifier de façon sensible la raideur de ce levier.The present invention aims to prevent the occurrence of cracks or cracks in a lever of the aforementioned type, without significantly modifying the stiffness of the lever.
Elle propose à cet effet un levier de commande du calage angulaire d'une aube de stator, en particulier dans un compresseur de turbomachine, comprenant une première extrémité destinée à être montée fixement sur un pivot d'aube, une deuxième extrémité comportant un pion cylindrique de montage sur un moyen d'entraînement, et une partie intermédiaire plate reliant les première et deuxième extrémités, ladite première extrémité ayant une épaisseur et une largeur supérieures à celles de la partie intermédiaire et de la deuxième extrémité du levier, caractérisé en ce que les formes et dimensions de la partie intermédiaire et de la deuxième extrémité sont déterminées pour augmenter les fréquences propres du levier en flexion et en torsion au-dessus des fréquences vibratoires de la turbomachine en amont du levier et pour conserver la raideur du levier.It proposes for this purpose a lever for controlling the angular setting of a stator blade, in particular in a turbomachine compressor, comprising a first end intended to be fixedly mounted on a blade pivot, a second end comprising a cylindrical pin. on a drive means, and a flat intermediate portion connecting the first and second ends, said first end having a thickness and a width greater than those of the intermediate portion and the second end of the lever, characterized in that the shapes and dimensions of the intermediate portion and the second end are determined to increase the natural frequencies of the lever in bending and torsion above the vibratory frequencies of the turbomachine upstream of the lever and to maintain the stiffness of the lever.
En augmentant les fréquences propres du levier en flexion et en torsion au-delà des fréquences vibratoires de la turbomachine en amont du levier, on évite que le levier puisse entrer en résonance pendant le fonctionnement de la turbomachine, et en conservant sa raideur, on n'augmente pas la puissance nécessaire à son actionnement et on ne dégrade pas le fonctionnement de la turbomachine.By increasing the eigenfrequencies of the lever in flexion and in torsion beyond the vibratory frequencies of the turbomachine upstream of the lever, it is avoided that the lever can come into resonance during the operation of the turbomachine, and while maintaining its stiffness, no does not increase the power required for its actuation and does not degrade the operation of the turbomachine.
On évite ainsi tout risque d'apparition de criques ou de fissures dans le levier de commande en fatigue vibratoire.This avoids any risk of occurrence of cracks or cracks in the control lever vibratory fatigue.
Dans un mode préféré de réalisation de l'invention, la deuxième extrémité du levier de commande a une épaisseur supérieure à celle de la partie intermédiaire, et la partie intermédiaire a localement une largeur inférieure à celle de la deuxième extrémité du levier.In a preferred embodiment of the invention, the second end of the control lever has a thickness greater than that of the intermediate portion, and the intermediate portion locally has a width less than that of the second end of the lever.
L'augmentation de l'épaisseur de la deuxième extrémité du levier de commande permet de mieux supporter les contraintes lors du sertissage du pion cylindrique, et de limiter l'apparition et la propagation de criques ou de fissures. Elle entraîne une augmentation de la raideur globale du levier, qui est compensée par une diminution locale de la largeur de la partie intermédiaire de sorte que le levier de commande conserve la même raideur et nécessite la même puissance d'actionnement qu'auparavant.Increasing the thickness of the second end of the control lever makes it possible to better withstand the stresses during crimping of the cylindrical pin, and to limit the appearance and propagation of cracks or cracks. It causes an increase in the overall stiffness of the lever, which is compensated by a local decrease in the width of the intermediate portion so that the control lever retains the same stiffness and requires the same operating power as before.
Dans ce mode de réalisation, la partie intermédiaire du levier est d'épaisseur constante et est reliée aux extrémités du levier par des zones d'épaisseur progressivement croissante.In this embodiment, the intermediate portion of the lever is of constant thickness and is connected to the ends of the lever by areas of progressively increasing thickness.
L'augmentation progressive de l'épaisseur des zones de liaison aux extrémités du levier permet de réduire les concentrations locales de contraintes.The gradual increase in the thickness of the connection zones at the ends of the lever makes it possible to reduce the local concentrations of stresses.
La partie intermédiaire du levier a des bords longitudinaux incurvés de forme concave qui permettent des transitions progressives entre des portions de largeurs différentes en évitant des concentrations de contraintes dans des parties du levier dont la largeur varierait brutalement et de façon discontinue.The intermediate portion of the lever has curved longitudinal edges of concave shape which allow progressive transitions between portions of different widths by avoiding stress concentrations in parts of the lever whose width varies abruptly and discontinuously.
La forme et les dimensions du levier de commande sont donc optimisées dynamiquement pour augmenter les fréquences propres du levier en flexion et en torsion au-delà des fréquences vibratoires de la turbomachine en amont, et statiquement en réduisant les concentrations locales de contraintes.The shape and dimensions of the control lever are dynamically optimized to increase the eigenfrequencies of the lever in bending and torsion beyond the vibratory frequencies of the turbomachine upstream, and statically by reducing the local concentrations of stresses.
Par ailleurs, le levier de commande selon l'invention est avantageusement soumis au moins partiellement à un grenaillage, ce traitement permettant de durcir la surface du levier et ainsi de le protéger contre des chocs ou des coups éventuels pendant sa manipulation et son montage sur le pivot d'aube et sur l'anneau de commande, ces chocs et ces coups pouvant être à l'origine de criques ou de microfissures.Moreover, the control lever according to the invention is advantageously subjected at least partially to shot blasting, this treatment making it possible to harden the surface of the lever and thus to protect it against shocks or possible blows during its handling and its mounting on the blade pivot and on the control ring, these shocks and blows can be the cause of cracks or microcracks.
L'invention propose également un compresseur de turbomachine, par exemple de turboréacteur comprenant une pluralité d'aubes à calage variable équipées de leviers de commande du type précité.The invention also proposes a turbomachine compressor, for example a turbojet engine comprising a plurality of variable-pitch vanes equipped with control levers of the aforementioned type.
D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif en référence aux dessins annexés dans lesquels :
- la figure 1 est une vue schématique en coupe partielle d'un levier de commande du calage angulaire d'une aube de stator dans un étage de compresseur d'une turbomachine ;
- la figure 2 est une vue schématique en perspective d'un levier de commande selon la technique antérieure ;
- la figure 3 est une vue schématique en perspective d'un levier de commande selon l'invention.
- Figure 1 is a schematic partial sectional view of a lever for controlling the angular setting of a stator blade in a compressor stage of a turbomachine;
- Figure 2 is a schematic perspective view of a control lever according to the prior art;
- Figure 3 is a schematic perspective view of a control lever according to the invention.
En figure 1, on a représenté une partie d'un compresseur haute-pression 10 d'une turbomachine, dans laquelle chaque étage du compresseur comprend une rangée d'aubes directrices 12 montées sur le stator et une rangée d'aubes 14 portées par le rotor.FIG. 1 shows a portion of a high-
Les aubes 12 du stator sont des redresseurs dont l'orientation ou calage angulaire est réglable à l'aide de leviers de commande 16 entraînés par un anneau de commande 18 actionné par des moyens moteurs (non représentés) du type vérin ou moteur électrique.The
Chaque levier de commande 16 comprend une première extrémité 20 fixée sur un pivot radial 22 d'une aube 12, guidé en rotation dans un palier 24 monté dans une cheminée radiale d'un carter externe 26, une deuxième extrémité 28 et une partie intermédiaire plate 30 reliant les extrémités 20 et 28.Each
La deuxième extrémité 28 du levier de commande 16 porte un pion cylindrique 32 qui est serti sur cette extrémité 28 et est guidé en rotation dans une douille cylindrique 34 de l'anneau de commande 18.The
Un déplacement angulaire de l'anneau de commande 18 autour de l'axe du carter 26 se traduit par une rotation des leviers 16 autour des axes 36 des pivots 22 et par l'entraînement en rotation des aubes 12 autour de ces axes 36, ainsi que par des déformations en flexion et en torsion des leviers 16.An angular displacement of the
Comme on le voit mieux en figure 2, la première extrémité 20 du levier 16 a une épaisseur et une largeur supérieures à celles de la partie intermédiaire 34 et de la deuxième extrémité 28 du levier 16. Par exemple, l'épaisseur de la première extrémité 20 est d'environ 10 mm et sa largeur est d'environ 22 mm.As best seen in Figure 2, the
La deuxième extrémité 28 du levier 16 qui porte le pion cylindrique 32 de montage sur l'anneau de commande 18 présente un bord circulaire s'étendant sur environ 180° autour de la tête sertie du pion cylindrique 32. Par exemple, l'épaisseur de la deuxième extrémité est d'environ 1,1 mm et sa largeur est d'environ 10 mm.The
La partie intermédiaire 34 qui relie les première et deuxième extrémités 20 et 28 a la même épaisseur que la deuxième extrémité 28 et une forme triangulaire et est reliée à la première extrémité 20 par une zone de liaison 38 d'épaisseur progressivement croissante. Par exemple, l'épaisseur de la partie intermédiaire 34 est d'environ 1,1 mm et sa largeur varie entre environ 10 et 22 mm.The
En fonctionnement du compresseur haute-pression, les fréquences propres des leviers 16 en flexion et en torsion peuvent coïncider avec les fréquences vibratoires de la partie amont du compresseur et provoquer alors des vibrations importantes des leviers 16 se traduisant par la formation de criques ou de fissures, en particulier au niveau des zones de sertissage des pions cylindriques 32 sur les secondes extrémités 28 des leviers 16. Cette fréquence vibratoire dépend de la vitesse de rotation du rotor et est de 6500 Hz environ pour un exemple particulier de compresseur haute-pression considéré.In operation of the high-pressure compressor, the eigenfrequencies of the
Selon l'invention, les formes et dimensions de la partie intermédiaire 34 et de la deuxième extrémité 28 sont modifiées pour que les fréquences propres du levier 16 en flexion et en torsion soient supérieures aux fréquences vibratoires de la partie amont du compresseur, sans augmenter de façon sensible la raideur du levier.According to the invention, the shapes and dimensions of the
La figure 3 représente schématiquement et en perspective un exemple de réalisation d'un levier de commande 40 selon l'invention.Figure 3 shows schematically and in perspective an embodiment of a
La deuxième extrémité 42 du levier 40 a une épaisseur supérieure à celle de la deuxième extrémité 28 du levier 16 de la technique antérieure afin de mieux supporter les contraintes dues au sertissage du pion cylindrique 32 et retarder la propagation de criques ou de fissures. Par exemple, cette épaisseur est de 1,8 mm environ.The
La forme de la deuxième extrémité 42 a également été modifiée par augmentation de l'étendue angulaire de son bord arrondi qui s'étend sur plus de 180°. Ce bord arrondi peut présenter un ou plusieurs rayons de courbure variant par exemple entre 6 et 15 mm.The shape of the
La partie intermédiaire 44 du levier 40 est d'épaisseur constante, supérieure à celle de la partie intermédiaire 34 du levier 16 de la technique antérieure mais inférieure à celle de la deuxième extrémité 42 du levier 40. Par exemple, l'épaisseur de la partie intermédiaire 44 du levier 40 est de 1,4 mm environ.The
L'augmentation de raideur du levier 40 due à l'augmentation de l'épaisseur de la partie intermédiaire 44 et de la deuxième extrémité 42 est compensée par une diminution de la largeur d'au moins une portion 46 de la partie intermédiaire 44 du levier 40, ce qui permet de conserver la même raideur globale que dans la technique antérieure, cette portion 46 étant reliée à la deuxième extrémité 42 du levier.The increase in stiffness of the
Dans l'exemple de réalisation de la figure 3, la portion 46 a une largeur de 8 mm environ, inférieure à celle de la deuxième extrémité 42 et est délimitée par des bords longitudinaux sensiblement parallèles.In the embodiment of Figure 3, the
La partie intermédiaire 44 du levier 40 est reliée à la première extrémité 48 par une zone de liaison 50 de faible longueur et d'épaisseur progressivement croissante qui est pour l'essentiel identique à la zone de liaison 38 du levier 16 de la technique antérieure et dont l'épaisseur varie entre celle de la partie intermédiaire 44 du levier 40 et celle de sa première extrémité 48.The
Une autre zone 52 d'épaisseur progressivement croissante relie la portion 46 de la partie intermédiaire 44 à la deuxième extrémité 42 du levier 40.Another
Les bords 54, 56 des zones de liaison 50 et 52 et de la partie intermédiaire 44 sont incurvés et concaves et reliés aux bords rectilignes de la portion 46 précitée. Les bords 54 peuvent présenter un ou plusieurs rayons de courbure qui sont typiquement compris entre 6 et 15 mm par exemple, et les bords 56 peuvent également présenter un ou plusieurs rayons de courbure qui sont typiquement compris entre 15 et 30 mm par exemple. Les rayons de courbure des bords 54, 56 augmentent donc de la deuxième extrémité 42 du levier 40 vers la première extrémité 48.The
Le levier de commande 40 selon l'invention est de préférence traité au moins partiellement par grenaillage, par exemple sur la partie intermédiaire 44 et/ou sur la deuxième extrémité 42 du levier 40. Ce traitement permet de durcir la surface du levier et donc d'améliorer sa protection contre des chocs ou des coups qui peuvent notamment intervenir pendant le montage du levier de commande 40 et qui peuvent provoquer des amorces de criques ou de fissures.The
Le levier de commande 40 selon l'invention est réalisé avantageusement en titane.The
Claims (9)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0409945A FR2875559B1 (en) | 2004-09-21 | 2004-09-21 | LEVER FOR CONTROLLING THE ANGULAR SETTING OF A STATOR BLADE IN A TURBOMACHINE |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1637742A2 true EP1637742A2 (en) | 2006-03-22 |
EP1637742A3 EP1637742A3 (en) | 2014-03-12 |
EP1637742B1 EP1637742B1 (en) | 2016-11-23 |
Family
ID=34949015
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05291889.3A Active EP1637742B1 (en) | 2004-09-21 | 2005-09-13 | Actuator lever for setting the angular position of guide vanes in a turbo machine. |
Country Status (7)
Country | Link |
---|---|
US (1) | US7524165B2 (en) |
EP (1) | EP1637742B1 (en) |
JP (1) | JP4832839B2 (en) |
CN (1) | CN1789673B (en) |
CA (1) | CA2520078C (en) |
FR (1) | FR2875559B1 (en) |
RU (1) | RU2311541C2 (en) |
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EP2481891A2 (en) * | 2011-02-01 | 2012-08-01 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
DE102016224523A1 (en) * | 2016-12-08 | 2018-06-14 | MTU Aero Engines AG | Guide vane adjustment with laterally mounted adjustment lever |
EP3431718A1 (en) * | 2017-07-19 | 2019-01-23 | Rolls-Royce plc | Unison ring assembly |
DE102017222209A1 (en) * | 2017-12-07 | 2019-06-13 | MTU Aero Engines AG | Guide vane connection and turbomachine |
FR3097007A1 (en) * | 2019-06-06 | 2020-12-11 | Safran Aircraft Engines | Device for actuating variable-pitch turbomachine blades, turbomachine provided with it |
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FR2921100B1 (en) * | 2007-09-13 | 2009-12-04 | Snecma | ROTATIONAL DRIVE LEVER AROUND A VARIABLE TURBOMACHINE STATOR VANE PIVOT |
US8215902B2 (en) * | 2008-10-15 | 2012-07-10 | United Technologies Corporation | Scalable high pressure compressor variable vane actuation arm |
US8714916B2 (en) * | 2010-09-28 | 2014-05-06 | General Electric Company | Variable vane assembly for a turbine compressor |
US8668444B2 (en) * | 2010-09-28 | 2014-03-11 | General Electric Company | Attachment stud for a variable vane assembly of a turbine compressor |
KR102106888B1 (en) | 2015-01-13 | 2020-05-06 | 한화에어로스페이스 주식회사 | Lever arm assembly for driving variable vane |
DE102015004649A1 (en) * | 2015-04-15 | 2016-10-20 | Man Diesel & Turbo Se | Guide vane adjusting device and turbomachine |
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FR3055374B1 (en) * | 2016-08-23 | 2018-08-03 | Safran Aircraft Engines | INTERFACE PIECE FOR RECONDITIONING A CONTROL RING OF A MOTOR COMPRESSOR, AND ASSOCIATED RECONDITIONING METHOD |
US10753224B2 (en) * | 2017-04-27 | 2020-08-25 | General Electric Company | Variable stator vane actuator overload indicating bushing |
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FR3100272A1 (en) * | 2019-08-27 | 2021-03-05 | Safran Aircraft Engines | GUIGNOL FOR A VARIABLE TIMING DEVICE OF A TURBOMACHINE |
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CN114109916B (en) * | 2021-08-19 | 2024-03-01 | 鑫磊压缩机股份有限公司 | Inlet guide vane regulator convenient to maintain and replace |
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DE102016224523A1 (en) * | 2016-12-08 | 2018-06-14 | MTU Aero Engines AG | Guide vane adjustment with laterally mounted adjustment lever |
US10830090B2 (en) | 2016-12-08 | 2020-11-10 | MTU Aero Engines AG | Vane actuating mechanism having a laterally mounted actuating lever |
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Also Published As
Publication number | Publication date |
---|---|
RU2005129352A (en) | 2007-03-27 |
US20060062667A1 (en) | 2006-03-23 |
FR2875559B1 (en) | 2007-02-23 |
CA2520078C (en) | 2011-04-19 |
RU2311541C2 (en) | 2007-11-27 |
CN1789673B (en) | 2010-09-15 |
EP1637742B1 (en) | 2016-11-23 |
CN1789673A (en) | 2006-06-21 |
JP4832839B2 (en) | 2011-12-07 |
EP1637742A3 (en) | 2014-03-12 |
CA2520078A1 (en) | 2006-03-21 |
JP2006090319A (en) | 2006-04-06 |
FR2875559A1 (en) | 2006-03-24 |
US7524165B2 (en) | 2009-04-28 |
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