EP3444444A1 - Variable pitch blade system for a turbomachine compressor - Google Patents

Variable pitch blade system for a turbomachine compressor Download PDF

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Publication number
EP3444444A1
EP3444444A1 EP18182843.5A EP18182843A EP3444444A1 EP 3444444 A1 EP3444444 A1 EP 3444444A1 EP 18182843 A EP18182843 A EP 18182843A EP 3444444 A1 EP3444444 A1 EP 3444444A1
Authority
EP
European Patent Office
Prior art keywords
slot
blade
compressor
control lever
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
Application number
EP18182843.5A
Other languages
German (de)
French (fr)
Other versions
EP3444444B1 (en
Inventor
Rafael Perez
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3444444A1 publication Critical patent/EP3444444A1/en
Application granted granted Critical
Publication of EP3444444B1 publication Critical patent/EP3444444B1/en
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/40—Transmission of power
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/57—Kinematic linkage, i.e. transmission of position using servos, independent actuators, etc.

Definitions

  • the invention relates to a turbomachine blade whose orientation is controlled by telescopic control lever.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • variable geometry compressor has a narrow pumping margin. Providing a variable-pitch blade system, or steerable blades, allows this margin to be extended for several regimes. This offers more security and allows the compressor to work optimally.
  • Such compressors in the context of an axial turbomachine, commonly comprise radially oriented trunnions which enable the steerable vanes to pivot on themselves.
  • Control levers connected to the journals are necessary to communicate the changes of orientation movements at each blade.
  • levers In the case where these levers are linked to an axially fixed synchronization ring, the levers must adapt geometrically. In effect such levers must also extend since the pins are also fixed axially.
  • the document US 4,978,280 A discloses a variable pitch compressor blade system for an aircraft turbojet engine.
  • the vanes comprise trunnions guiding the pivoting movements of the vanes, thus allowing piloted changes in timing.
  • the pins are capped with plates in which are fixed control levers, which themselves are connected to a synchronization ring. These levers are telescopic so that they can lengthen when the synchronizing ring is actuated.
  • this set is radially bulky.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the radial compactness of a variable pitch blade system. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, easy inspection, and improving performance.
  • the invention relates to an axially turbomachine adjustable orientation blade system, in particular an axial turbomachine compressor, the system comprising: a telescopic control lever; and a blade with a blade intended to extend radially in a flow of the turbomachine and a pin having a cylindrical portion; remarkable in that the cylindrical portion comprises a radially extending slot; and the telescopic control lever comprises a pivot link housed in the slot which is configured to impart a rotational movement to the blade around its journal.
  • the subject of the invention is also a compressor
  • Compressor comprising a system of blades with adjustable orientations, remarkable in that the system is in accordance with the invention, preferably the compressor is a low-pressure compressor.
  • the vanes and the levers are identical.
  • the system comprises one or more annular rows of blades with adjustable orientations.
  • the subject of the invention is also a turbomachine, in particular an aircraft turbojet engine, comprising a system of blades with adjustable orientations, which is remarkable in that the system is in accordance with the invention.
  • the turbomachine comprises a compressor according to the invention. 'invention.
  • each object of the invention is also applicable to the other objects of the invention.
  • Each object of the invention is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise be explicitly specified.
  • the invention allows to house the lever in the trunnion, but also to place the lever / trunnion fixing means in the grip of the latter.
  • the space around the trunnions and levers remains free, and does not confine unoccupied spaces.
  • the space around the support housing is used optimally.
  • the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation.
  • Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • a commonly designated fan or fan input fan 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • Reducing means such as an epicyclic reduction gear, can reduce the speed of rotation of the fan and / or the low-pressure compressor relative to the associated turbine.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • Flows primary 18 and secondary 20 are coaxial annular flows and fitted into one another.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4, also called a booster.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It may be a bladed one-piece drum, and / or comprise dovetail-fixed blades.
  • the low pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or a row of rotor blades to straighten the air flow, so as to convert the speed of the flow pressure, including static pressure.
  • the stator vanes 26 extend substantially radially from an outer housing 28 forming a support, and can be articulated therein by means of trunnions 30 passing through openings in the housing 28.
  • the combination of an opening and the trunnion 30 It receives a rotating mechanical connection which modulates the orientation of the blade 26.
  • Such a blade is commonly referred to as a VSV blade whose acronym corresponds to the English expression "Variable Stator Vane”.
  • the blade of the blade 26 can extend more or less through the primary flow 18.
  • the circumference of the primary vein occupied by the blade can be adjusted by adapting the orientation of the blade 26, c that is to say by modifying the inclination between the average rope of the blade 26 and the axis of rotation 14 of the turbomachine.
  • control levers 32 are connected to a timing ring 34 and journals 30 at the other ends.
  • the synchronizing rings 34 surround the axis of rotation 14, and surround the outer casing 28. These rings 34 are controlled by actuators 36 connected to a control unit 38 calculating the best orientation for the blades according to the operating conditions, of which the rotational speed of the rotor 12.
  • the inner ends of the stator vanes 26 may be rotatably connected to inner ferrules adapted to the rotation of the stator vanes 26.
  • the compressor may be mixed because it may contain one or plural rows of controllably oriented vanes, and one or more rows of stator vanes with fixed orientation 27, or single orientation, with respect to the axis of rotation 14.
  • the figure 3 sketch a system of blades with variable orientation, or blades 26.
  • the system can be similar to that introduced in relation to the figure 2 .
  • the steerable blade 26 has a blade extending through the primary flow 18.
  • the blade is extended radially by the journals 30.
  • Disks, or buttons, can form the blade-pin interfaces.
  • This blade has a leading edge BA, a trailing edge BF, a lower surface and an extrados surface which extend from the leading edge BA to the trailing edge BF. These surfaces can be concave and convex respectively. They can define aerodynamic profiles adapted to deflect the flow 18 while reducing the detachments.
  • the ring 34 may be fixed axially relative to the casing 28, which simplifies the integration of its actuator.
  • the telescopic lever 32 may comprise a sleeve 40 with a cavity 41 receiving a slide 42.
  • the slide 42 may form a rod sliding in and out of the sleeve 40.
  • the slide 42 is linked by a ball joint to the ring 34 while the sheath is attached to the trunnion 30.
  • the pin 30 has a slot 44, or a notch, in particular formed in a cylindrical portion 45 of the pin 30.
  • This slot 44 forms a central clearance in the pin 30.
  • the latter can form a fork.
  • the slot 44 is integrated in the height and the width of the pin 30. It can pass through the pin 30 according to its diameter, for example from upstream to downstream.
  • the slot 44 extends radially, or along the pin 30.
  • the diameter of the cylindrical portion 45 also called cylindrical bearing, may be equal to that of the trunnion section 30 which passes through the casing 28. This configuration provides a maximum of material while allowing the insertion of the trunnion by the inside of the casing 28. Here, the resistance is optimized while obeying an assembly constraint.
  • a pivot connection 46 connects the lever 32 to the journal. This eliminates the bending stresses when the lever is operated.
  • the pivot connection 46 is disposed in the slot 44. In particular, it can be completely housed in the body of the pin 30, and therefore of the cylindrical portion 45.
  • the radial height of the slot 44 may be greater than the radial height of the lever 32.
  • the inner bottom of the slot 44 and / or the inner face of the lever may be spaced radially from the outer surface of the casing 28.
  • the lever 32 may comprise a thinner portion 48 attached to the trunnion 30 by the pivot connection 46. This thinner portion 48 may be inserted into the slot 44.
  • the portion 48 may form a connecting lug, and / or a thinning .
  • a rod passing through the portion 48 and the pin 30 may form the pivot connection 46.
  • the figure 4 represents the adjustable-orientation blade system such as that presented in relation to the figures 2 and 3 .
  • the system is presented from the front, in the axial direction, and / or in a view oriented along the axis of sliding of the lever 32 which is partially hidden by the trunnion 30, but whose thinner portion 48 is apparent in the slot 44. Only a radial section of the blade 50 of the blade 26 is visible.
  • the thickness of the thinner portion 48 is less than or equal to the radius of the cylindrical portion 45 of the trunnion 30, or less than half of said radius. This preserves the rigidity of the trunnion 30, and increases the contact with the thinner portion 48 through which is transmitted the actuating torque of the blade 26.
  • the pin 30 has an axis of rotation 52 around which the blade 26 is hinged. This axis 52 can cut the pivot axis 54 of the pivot connection 46.
  • these axes touch at a point of intersection 55, they define a plane. Moreover, they can be orthogonal. This arrangement further improves the compactness at the same time as a reduction of actuation forces.
  • the figure 5 shows in view from above the adjustable blade system such as that presented in connection with the Figures 2 to 4 .
  • the sleeve 40 is at a distance from the pin 30. These may be separated by a portion of the thinner portion 48.
  • the smaller thickness portion 48 may have opposite surfaces 56. They may be perpendicular to the pivot axis 54. Opposite, the slot 44 may have internal surfaces 58. The latter each come into contact with one of the opposite surfaces 56, which allows a transmission of forces; and thus cause a change of direction of the blade 26.
  • the transmitted torque can increase. Torque transmission can both be effected by means of the rod passing through the portion 48, and by the surfaces (56; 58) in pairs in contact.
  • the pin 30 may have a constant diameter over most of its height, and / or on its section outside the housing, and / or over its entire height.
  • dowel blade and one lever are shown, the present teaching can be applied to a whole annular row of trunnion vanes, each connected to a control lever.
  • the blades and levers of the row may be identical.
  • Each or more rows of trunnion and lever blades may be as described above.

Abstract

L'invention se rapporte à un système d'aubes à orientations réglables (26), également appelé système d'aubes à calage variable, pour un compresseur basse-pression de turbomachine axiale. Le système comprend des aubes (26), chacune avec une pale s'étendant radialement dans un flux (18) de la turbomachine et un tourillon (30) avec une portion cylindrique (45) reliée à un levier de commande télescopique (32). La portion cylindrique (45) comprend une fente (44) s'étendant radialement; et le levier de commande (32) comprend une liaison pivot (46) logée dans la fente (44) qui est configurée pour communiquer un mouvement de rotation à l'aube (26) par rapport à son tourillon (30). L'invention propose également un compresseur et une turbomachine.The invention relates to an adjustable blade system (26), also referred to as a variable pitch vane system, for a low pressure axial turbine engine compressor. The system comprises blades (26), each with a blade extending radially in a flow (18) of the turbomachine and a pin (30) with a cylindrical portion (45) connected to a telescopic control lever (32). The cylindrical portion (45) includes a radially extending slot (44); and the control lever (32) comprises a pivot link (46) housed in the slot (44) which is configured to impart rotational movement to the blade (26) relative to its pin (30). The invention also proposes a compressor and a turbomachine.

Description

Domaine techniqueTechnical area

L'invention concerne une aube de turbomachine dont l'orientation est pilotée par levier de commande télescopique. L'invention a également trait à une turbomachine axiale, notamment un turboréacteur d'avion ou un turbopropulseur d'aéronef.The invention relates to a turbomachine blade whose orientation is controlled by telescopic control lever. The invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.

Technique antérieurePrior art

Un compresseur à géométrie variable présente une marge au pompage étroite. Y prévoir un système d'aubes à calage variable, ou aubes orientables, permet d'étendre cette marge, et ce pour plusieurs régimes. Ceci offre davantage de sécurité et permet au compresseur de travailler de manière optimale. De tels compresseurs, dans le contexte d'une turbomachine axiale, comprennent communément des tourillons orientés radialement qui permettent aux aubes orientables de pivoter sur elles-mêmes.A variable geometry compressor has a narrow pumping margin. Providing a variable-pitch blade system, or steerable blades, allows this margin to be extended for several regimes. This offers more security and allows the compressor to work optimally. Such compressors, in the context of an axial turbomachine, commonly comprise radially oriented trunnions which enable the steerable vanes to pivot on themselves.

Des leviers de commande reliés aux tourillons restent nécessaires pour communiquer les mouvements de changement d'orientation à chaque aube.Control levers connected to the journals are necessary to communicate the changes of orientation movements at each blade.

Dans le cas où ces leviers sont liés à une bague de synchronisation fixe axialement, les leviers doivent s'adapter géométriquement. En effets de tels leviers doivent également s'allonger puisque les tourillons sont également fixes axialement.In the case where these levers are linked to an axially fixed synchronization ring, the levers must adapt geometrically. In effect such levers must also extend since the pins are also fixed axially.

Le document US 4,978,280 A divulgue un système d'aubes à calage variable de compresseur pour turboréacteur d'aéronef. Dans ce système, les aubes comportent des tourillons guidant les mouvements de pivotement des aubes, autorisant ainsi des modifications de calages pilotés. Les tourillons sont coiffés de platines dans lesquelles sont fixés des leviers de commande, qui eux-mêmes sont reliés à une bague de synchronisation. Ces leviers sont télescopiques de sorte à pouvoir s'allonger lors de l'actionnement de la bague de synchronisation. Or, la fiabilité de ce système est limitée. Par ailleurs, cet ensemble est radialement encombrant.The document US 4,978,280 A discloses a variable pitch compressor blade system for an aircraft turbojet engine. In this system, the vanes comprise trunnions guiding the pivoting movements of the vanes, thus allowing piloted changes in timing. The pins are capped with plates in which are fixed control levers, which themselves are connected to a synchronization ring. These levers are telescopic so that they can lengthen when the synchronizing ring is actuated. However, the reliability of this system is limited. Moreover, this set is radially bulky.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'améliorer la compacité radiale d'un système d'aubes à calage variable. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, commode d'entretien, d'inspection aisée, et améliorant le rendement.The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the radial compactness of a variable pitch blade system. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, easy inspection, and improving performance.

Solution techniqueTechnical solution

L'invention a pour objet un système d'aubes à orientation réglable de turbomachine axiale, notamment de compresseur axial de turbomachine, le système comprenant : un levier de commande télescopique ; et une aube avec une pale destinée à s'étendre radialement dans un flux de la turbomachine et un tourillon comportant une portion cylindrique ; remarquable en ce que la portion cylindrique comprend une fente s'étendant radialement; et le levier de commande télescopique comprend une liaison pivot logée dans la fente qui est configurée pour communiquer un mouvement de rotation à l'aube autour de son tourillon.The invention relates to an axially turbomachine adjustable orientation blade system, in particular an axial turbomachine compressor, the system comprising: a telescopic control lever; and a blade with a blade intended to extend radially in a flow of the turbomachine and a pin having a cylindrical portion; remarkable in that the cylindrical portion comprises a radially extending slot; and the telescopic control lever comprises a pivot link housed in the slot which is configured to impart a rotational movement to the blade around its journal.

Selon des modes avantageux de l'invention, le système peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément ou selon toutes les combinaisons techniques possibles :

  • La fente comprend des surfaces internes en contact de la liaison pivot du levier.
  • La fente traverse diamétralement la portion cylindrique.
  • Le levier de commande télescopique comprend une portion de moindre épaisseur traversée par la liaison pivot.
  • La portion de moindre épaisseur est disposée dans la fente.
  • Le levier de commande télescopique comprend un fourreau et une coulisse glissant à l'intérieur du fourreau, la liaison pivot étant solidaire dudit fourreau.
  • Le fourreau comprend une cavité dans laquelle glisse la coulisse, la cavité étant à distance de la fente et de la liaison pivot.
  • La cavité est à distance axialement de la portion cylindrique.
  • La pale présente une épaisseur moyenne qui est supérieure à la largeur de la fente.
  • Le tourillon comprend une extrémité radiale, la liaison pivot étant disposée radialement entre la pale et ladite extrémité radiale.
  • La liaison pivot est inscrite dans le périmètre de la portion cylindrique.
  • La liaison pivot comporte un axe de pivotement, le tourillon présente un axe de rotation coupant l'axe de pivotement en un point d'intersection, lesdits axes étant optionnellement perpendiculaires.
  • Le tourillon présente un diamètre constant sur la majorité de sa hauteur, et/ou au niveau radialement de la fente.
  • Le levier de commande télescopique comprend des surfaces latérales opposées qui sont en contact de la fente.
  • Le levier de commande télescopique est intégré radialement dans la hauteur du tourillon, et éventuellement de la fente.
  • Le système comprend une bague de synchronisation qui est fixe axialement par rapport au tourillon.
  • Le système est configuré de sorte à ce que l'aube puisse pivoter sur elle-même d'un angle supérieur ou égal à 30°.
  • Le système est configuré de sorte à ce que l'aube puisse tourner sur elle-même d'un angle supérieur ou égal à : 10°, ou 20°, ou 35°.
  • La fente présente une hauteur radiale, une longueur, et une largeur inférieure à la longueur.
  • La largeur de la liaison pivot et/ou de la fente est/sont mesurée(s) le long de l'axe de pivotement de la liaison pivot.
  • Le point d'intersection est disposé dans le tourillon, notamment dans la portion cylindrique.
  • La fente est dans le prolongement radial de la pale.
  • La largeur de la liaison pivot est inférieure au diamètre du tourillon.
  • Le système comprend un carter avec un orifice traversé par le tourillon.
  • La fente comporte, éventuellement est constituée de, trois côtés ouverts et un côté fermé.
    • La largeur de la fente est ajustée à la largeur du levier de manière à ce que le levier puisse transmettre un couple au tourillon.
    • La pale et la portion cylindrique forment un ensemble venu de matière.
According to advantageous modes of the invention, the system can comprise one or more of the following characteristics, taken separately or according to all the possible technical combinations:
  • The slot includes internal surfaces in contact with the pivot link of the lever.
  • The slot diametrically crosses the cylindrical portion.
  • The telescopic control lever comprises a thinner portion traversed by the pivot connection.
  • The smaller portion is disposed in the slot.
  • The telescopic control lever comprises a sleeve and a slide sliding inside the sleeve, the pivot connection being secured to said sleeve.
  • The sheath comprises a cavity in which the slide slides, the cavity being spaced from the slot and the pivot connection.
  • The cavity is axially spaced from the cylindrical portion.
  • The blade has an average thickness which is greater than the width of the slot.
  • The journal comprises a radial end, the pivot connection being arranged radially between the blade and said radial end.
  • The pivot connection is inscribed in the perimeter of the cylindrical portion.
  • The pivot connection comprises a pivot axis, the pin has an axis of rotation intersecting the pivot axis at a point of intersection, said axes being optionally perpendicular.
  • The trunnion has a constant diameter over most of its height, and / or radially of the slot.
  • The telescopic control lever includes opposed side surfaces that are in contact with the slot.
  • The telescopic control lever is integrated radially in the height of the trunnion, and possibly the slot.
  • The system comprises a synchronizing ring which is fixed axially with respect to the journal.
  • The system is configured so that the blade can rotate on itself by an angle greater than or equal to 30 °.
  • The system is configured so that the blade can turn on itself at an angle greater than or equal to: 10 °, or 20 °, or 35 °.
  • The slot has a radial height, a length, and a width less than the length.
  • The width of the pivot connection and / or slot is / are measured along the pivot axis of the pivot connection.
  • The point of intersection is disposed in the trunnion, in particular in the cylindrical portion.
  • The slot is in the radial extension of the blade.
  • The width of the pivot connection is smaller than the diameter of the journal.
  • The system includes a housing with a hole through which the trunnion passes.
  • The slit comprises, optionally consists of, three open sides and one closed side.
    • The width of the slot is adjusted to the width of the lever so that the lever can transmit torque to the trunnion.
    • The blade and the cylindrical portion form a set of matter.

L'invention a également pour objet un compresseur,The subject of the invention is also a compressor,

Compresseur comprenant un système d'aubes à orientations réglables, remarquable en que le système est conforme à l'invention, préférentiellement le compresseur est un compresseur basse-pression.Compressor comprising a system of blades with adjustable orientations, remarkable in that the system is in accordance with the invention, preferably the compressor is a low-pressure compressor.

Selon un mode avantageux de l'invention, au sein d'une même rangée, les aubes et les leviers sont identiques.According to an advantageous embodiment of the invention, in the same row, the vanes and the levers are identical.

Selon un mode avantageux de l'invention, le système comprend une ou plusieurs rangées annulaires d'aubes à orientations réglables.According to an advantageous embodiment of the invention, the system comprises one or more annular rows of blades with adjustable orientations.

L'invention a également pour objet une turbomachine, notamment un turboréacteur d'aéronef, comprenant un système d'aubes à orientations réglables, remarquable en ce que le système est conforme à l'invention, préférentiellement, la turbomachine comprend un compresseur conforme à l'invention.The subject of the invention is also a turbomachine, in particular an aircraft turbojet engine, comprising a system of blades with adjustable orientations, which is remarkable in that the system is in accordance with the invention. Preferably, the turbomachine comprises a compressor according to the invention. 'invention.

De manière générale, les modes avantageux de chaque objet de l'invention sont également applicables aux autres objets de l'invention. Chaque objet de l'invention est combinable aux autres objets, et les objets de l'invention sont également combinables aux modes de réalisation de la description, qui en plus sont combinables entre eux, selon toutes les combinaisons techniques possibles, à moins que le contraire soit explicitement précisé.In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. Each object of the invention is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise be explicitly specified.

Avantages apportésBenefits brought

L'invention permet de loger le levier dans le tourillon, mais également de placer les moyens de fixation levier/tourillon dans l'emprise de ce dernier. Ainsi, l'espace autour des tourillons et des leviers reste libre, et ne confine pas d'espaces inoccupés. L'espace autour du carter support est utilisé de manière optimale.The invention allows to house the lever in the trunnion, but also to place the lever / trunnion fixing means in the grip of the latter. Thus, the space around the trunnions and levers remains free, and does not confine unoccupied spaces. The space around the support housing is used optimally.

L'intégration de la liaison pivot dans la hauteur radiale du tourillon permet d'abaisser le levier. Celui-ci se rapproche radialement du carter support. Il devient plus facile d'intégrer un système de dégivrage, notamment avec des conduites d'adduction de fluide chaud, au niveau des leviers.The integration of the pivot connection in the radial height of the trunnion makes it possible to lower the lever. The latter is radially closer to the support casing. It becomes easier to integrate a de-icing system, especially with hot fluid supply lines at the levers.

La transmission de couple peut à la fois s'effectuer au moyen de la tigeTorque transmission can both be done by means of the rod

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.
  • La figure 3 illustre un système d'aube à orientation réglable selon l'invention.The figure 3 illustrates a blade system with adjustable orientation according to the invention.
  • La figure 4 présente une vue axiale du système d'aube à orientation réglable selon l'invention.The figure 4 has an axial view of the blade system adjustable orientation according to the invention.
  • La figure 5 est une vue du dessus du système d'aube à orientation réglable selon l'invention.The figure 5 is a top view of the blade system adjustable orientation according to the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes « interne » et « externe » renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale.In the following description, the terms "internal" and "external" refer to a positioning relative to the axis of rotation of an axial turbomachine.

La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation.The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation.

L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine.Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8.The figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.

Un ventilateur d'entrée communément désigné fan ou soufflante 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux susmentionnés de la turbomachine, et en un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine.A commonly designated fan or fan input fan 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.

Des moyens de démultiplication, tel un réducteur épicycloïdal, peuvent réduire la vitesse de rotation de la soufflante et/ou du compresseur basse-pression par rapport à la turbine associée. Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée nécessaire au vol d'un avion. Les flux primaire 18 et secondaire 20 sont des flux annulaires coaxiaux et emmanchés l'un dans l'autre.Reducing means, such as an epicyclic reduction gear, can reduce the speed of rotation of the fan and / or the low-pressure compressor relative to the associated turbine. The secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft. Flows primary 18 and secondary 20 are coaxial annular flows and fitted into one another.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 4, également appelé booster. Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois. Il peut être un tambour monobloc aubagé, et/ou comprendre des aubes à fixation par queue d'aronde.The figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 . The compressor may be a low-pressure compressor 4, also called a booster. The rotor 12 comprises several rows of rotor blades 24, in this case three. It may be a bladed one-piece drum, and / or comprise dovetail-fixed blades.

Le compresseur basse pression 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26.The low pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.

Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression, notamment en pression statique.The rectifiers are associated with the fan 16 or a row of rotor blades to straighten the air flow, so as to convert the speed of the flow pressure, including static pressure.

Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter extérieur 28 formant un support, et peuvent y être articulées à l'aide de tourillons 30 traversant des ouvertures ménagées dans le carter 28. La combinaison d'une ouverture et du tourillon 30 qu'elle reçoit forme une liaison mécanique tournante qui permet de moduler l'orientation de l'aube 26. Une telle aube est communément désignée aube VSV dont l'acronyme correspond à l'expression anglo-saxonne « Variable Stator Vane ».The stator vanes 26 extend substantially radially from an outer housing 28 forming a support, and can be articulated therein by means of trunnions 30 passing through openings in the housing 28. The combination of an opening and the trunnion 30 It receives a rotating mechanical connection which modulates the orientation of the blade 26. Such a blade is commonly referred to as a VSV blade whose acronym corresponds to the English expression "Variable Stator Vane".

Dès lors, la pale de l'aube 26 peut s'étendre plus ou moins au travers du flux primaire 18. La circonférence de la veine primaire qu'occupe la pale peut être réglée en adaptant l'orientation de l'aube 26, c'est à dire en modifiant l'inclinaison entre la corde moyenne de l'aube 26 et l'axe de rotation 14 de la turbomachine.Therefore, the blade of the blade 26 can extend more or less through the primary flow 18. The circumference of the primary vein occupied by the blade can be adjusted by adapting the orientation of the blade 26, c that is to say by modifying the inclination between the average rope of the blade 26 and the axis of rotation 14 of the turbomachine.

Afin de transmettre un mouvement cohérent de commande aux aubes orientables 26, des leviers de commande 32 sont reliés à une bague de synchronisation 34 et aux tourillons 30 aux autres extrémités. Les bagues de synchronisation 34 entourent l'axe de rotation 14, et ceinturent le carter externe 28. Ces bagues 34 sont pilotées par des actionneurs 36 branchés à une unité de commande 38 calculant la meilleure orientation pour les aubes en fonction des conditions de fonctionnement, dont la vitesse de rotation du rotor 12.In order to transmit a consistent control movement to the steerable vanes 26, control levers 32 are connected to a timing ring 34 and journals 30 at the other ends. The synchronizing rings 34 surround the axis of rotation 14, and surround the outer casing 28. These rings 34 are controlled by actuators 36 connected to a control unit 38 calculating the best orientation for the blades according to the operating conditions, of which the rotational speed of the rotor 12.

Les extrémités internes des aubes statoriques 26 peuvent être reliées de manière tournante à des viroles internes adaptées à la rotation des aubes statoriques 26. Le compresseur peut être mixte car il peut contenir une ou plusieurs rangées d'aubes à orientation réglable, et une ou plusieurs rangées d'aubes de stator à orientation fixe 27, ou orientation unique, par rapport à l'axe de rotation 14.The inner ends of the stator vanes 26 may be rotatably connected to inner ferrules adapted to the rotation of the stator vanes 26. The compressor may be mixed because it may contain one or plural rows of controllably oriented vanes, and one or more rows of stator vanes with fixed orientation 27, or single orientation, with respect to the axis of rotation 14.

La figure 3 esquisse un système d'aubes à orientation variable, ou aubes orientables 26. Le système peut être similaire à celui introduit en relation avec la figure 2. On retrouve le carter 28, l'aube statorique orientable 26, le carter 28, le tourillon 30, le levier de commande 32 et une bague de synchronisation 34.The figure 3 sketch a system of blades with variable orientation, or blades 26. The system can be similar to that introduced in relation to the figure 2 . We find the housing 28, the stepless stator vane 26, the casing 28, the trunnion 30, the control lever 32 and a synchronizing ring 34.

L'aube orientable 26 présente une pale s'étendant au travers du flux primaire 18. La pale est prolongée radialement par les tourillons 30. Des disques, ou boutons, peuvent former les interfaces pale-tourillon. Cette pale présente un bord d'attaque BA, un bord de fuite BF, une surface intrados et une surface extrados qui s'étendent du bord d'attaque BA au bord de fuite BF. Ces surfaces peuvent être concave et convexe respectivement. Elles peuvent définir des profils aérodynamiques adaptés pour dévier le flux 18 tout en réduisant les décollements. La bague 34 peut être fixe axialement par rapport au carter 28, ce qui simplifie l'intégration de son l'actionneur.The steerable blade 26 has a blade extending through the primary flow 18. The blade is extended radially by the journals 30. Disks, or buttons, can form the blade-pin interfaces. This blade has a leading edge BA, a trailing edge BF, a lower surface and an extrados surface which extend from the leading edge BA to the trailing edge BF. These surfaces can be concave and convex respectively. They can define aerodynamic profiles adapted to deflect the flow 18 while reducing the detachments. The ring 34 may be fixed axially relative to the casing 28, which simplifies the integration of its actuator.

Puisque la rotation de l'aube orientable 26 entraîne un allongement du levier 32, ce dernier est rendu télescopique. Le levier télescopique 32 peut comprendre un fourreau 40 avec une cavité 41 recevant une coulisse 42. La coulisse 42 peut former une tige glissant dans et en dehors du fourreau 40. Par exemple, la coulisse 42 est liée par une liaison rotule à la bague 34 tandis que le fourreau est attaché au tourillon 30.Since the rotation of the steerable blade 26 causes an elongation of the lever 32, the latter is made telescopic. The telescopic lever 32 may comprise a sleeve 40 with a cavity 41 receiving a slide 42. The slide 42 may form a rod sliding in and out of the sleeve 40. For example, the slide 42 is linked by a ball joint to the ring 34 while the sheath is attached to the trunnion 30.

Le tourillon 30 présente une fente 44, ou une encoche, notamment formée dans une portion cylindrique 45 du tourillon 30. Cette fente 44 forme un dégagement central dans le tourillon 30. Ce dernier peut former une fourche. La fente 44 est intégrée dans la hauteur et la largeur du tourillon 30. Elle peut traverser le tourillon 30 suivant son diamètre, par exemple d'amont en aval. La fente 44 s'étend radialement, soit le long du tourillon 30.The pin 30 has a slot 44, or a notch, in particular formed in a cylindrical portion 45 of the pin 30. This slot 44 forms a central clearance in the pin 30. The latter can form a fork. The slot 44 is integrated in the height and the width of the pin 30. It can pass through the pin 30 according to its diameter, for example from upstream to downstream. The slot 44 extends radially, or along the pin 30.

Le diamètre de la portion cylindrique 45, également appelée portée cylindrique, peut être égal à celui du tronçon de tourillon 30 qui traverse le carter 28. Cette configuration offre un maximum de matière tout en autorisant l'insertion du tourillon par l'intérieur du carter 28. Ici, la résistance est optimisée tout en obéissant à une contrainte d'assemblage.The diameter of the cylindrical portion 45, also called cylindrical bearing, may be equal to that of the trunnion section 30 which passes through the casing 28. This configuration provides a maximum of material while allowing the insertion of the trunnion by the inside of the casing 28. Here, the resistance is optimized while obeying an assembly constraint.

Une liaison pivot 46 permet de relier le levier 32 au tourillon. Cela supprime les contraintes de flexion en cas d'actionnement du levier. La liaison pivot 46 est disposée dans la fente 44. En particulier, elle peut être totalement logée dans le corps du tourillon 30, et donc de la portion cylindrique 45.A pivot connection 46 connects the lever 32 to the journal. This eliminates the bending stresses when the lever is operated. The pivot connection 46 is disposed in the slot 44. In particular, it can be completely housed in the body of the pin 30, and therefore of the cylindrical portion 45.

La hauteur radiale de la fente 44 peut être supérieure à la hauteur radiale du levier 32. Le fond interne de la fente 44 et/ou la face interne du levier peuvent être à distance radialement de la surface externe du carter 28.The radial height of the slot 44 may be greater than the radial height of the lever 32. The inner bottom of the slot 44 and / or the inner face of the lever may be spaced radially from the outer surface of the casing 28.

Le levier 32 peut comprendre une portion de moindre épaisseur 48 attachée au tourillon 30 par la liaison pivot 46. Cette portion de moindre épaisseur 48 peut être insérée dans la fente 44. La portion 48 peut former une patte de liaison, et/ou un amincissement. Une tige traversant la portion 48 et le tourillon 30 peut former la liaison pivot 46.The lever 32 may comprise a thinner portion 48 attached to the trunnion 30 by the pivot connection 46. This thinner portion 48 may be inserted into the slot 44. The portion 48 may form a connecting lug, and / or a thinning . A rod passing through the portion 48 and the pin 30 may form the pivot connection 46.

La figure 4 représente le système d'aube à orientation réglable tel que celui présenté en relation avec les figures 2 et 3. Le système est présenté de face, selon la direction axiale, et/ou dans une vue orientée selon l'axe de coulissement du levier 32 qui est partiellement masqué par le tourillon 30, mais dont la portion de moindre épaisseur 48 est apparente dans la fente 44. Seul un tronçon radial de la pale 50 de l'aube 26 est visible.The figure 4 represents the adjustable-orientation blade system such as that presented in relation to the figures 2 and 3 . The system is presented from the front, in the axial direction, and / or in a view oriented along the axis of sliding of the lever 32 which is partially hidden by the trunnion 30, but whose thinner portion 48 is apparent in the slot 44. Only a radial section of the blade 50 of the blade 26 is visible.

L'épaisseur de la portion de moindre épaisseur 48 est inférieure ou égale au rayon de la portion cylindrique 45 du tourillon 30, ou inférieure à la moitié dudit rayon. Cela préserve la rigidité du tourillon 30, et augmente le contact avec la portion de moindre épaisseur 48 par qui est transmis le couple d'actionnement de l'aube 26.The thickness of the thinner portion 48 is less than or equal to the radius of the cylindrical portion 45 of the trunnion 30, or less than half of said radius. This preserves the rigidity of the trunnion 30, and increases the contact with the thinner portion 48 through which is transmitted the actuating torque of the blade 26.

Le tourillon 30 présente un axe de rotation 52 autour duquel l'aube 26 est articulée. Cet axe 52 peut couper l'axe de pivotement 54 de la liaison pivot 46.The pin 30 has an axis of rotation 52 around which the blade 26 is hinged. This axis 52 can cut the pivot axis 54 of the pivot connection 46.

Puisque ces axes (52 ; 54) se touchent en un point d'intersection 55, ils définissent un plan. Par ailleurs, ils peuvent être orthogonaux. Cet agencement améliore encore la compacité en même temps qu'une réduction des efforts d'actionnement.Since these axes (52; 54) touch at a point of intersection 55, they define a plane. Moreover, they can be orthogonal. This arrangement further improves the compactness at the same time as a reduction of actuation forces.

La figure 5 montre en vue du dessus le système d'aube à orientation réglable tel que celui présenté en relation avec les figures 2 à 4.The figure 5 shows in view from above the adjustable blade system such as that presented in connection with the Figures 2 to 4 .

Le fourreau 40 est à distance du tourillon 30. Ceux-là peuvent être séparés par un tronçon de la portion de moindre épaisseur 48. La portion de moindre épaisseur 48 peut présenter des surfaces opposées 56. Elles peuvent être perpendiculaires à l'axe de pivotement 54. En face, la fente 44 peut présenter des surfaces internes 58. Ces dernières viennent chacune en contact d'une des surfaces opposées 56, ce qui permet une transmission d'efforts ; et donc de provoquer un changement de direction de l'aube 26. Le couple transmis peut augmenter. La transmission de couple peut à la fois s'effectuer au moyen de la tige traversant la portion 48, et par les surfaces (56 ; 58) deux à deux en contact.The sleeve 40 is at a distance from the pin 30. These may be separated by a portion of the thinner portion 48. The smaller thickness portion 48 may have opposite surfaces 56. They may be perpendicular to the pivot axis 54. Opposite, the slot 44 may have internal surfaces 58. The latter each come into contact with one of the opposite surfaces 56, which allows a transmission of forces; and thus cause a change of direction of the blade 26. The transmitted torque can increase. Torque transmission can both be effected by means of the rod passing through the portion 48, and by the surfaces (56; 58) in pairs in contact.

Le tourillon 30 peut présenter un diamètre constant sur la majorité de sa hauteur, et/ou sur son tronçon en dehors du carter, et/ou sur toute sa hauteur.The pin 30 may have a constant diameter over most of its height, and / or on its section outside the housing, and / or over its entire height.

Cela peut correspondre à la portion cylindrique 45.This may correspond to the cylindrical portion 45.

Bien qu'une seule aube à tourillon et qu'un seul levier ne soient représentés, le présent enseignement peut s'appliquer à toute une rangée annulaire d'aubes à tourillons, chacune reliées à un levier de commande. Les aubes et les leviers de la rangée peuvent être identiques. Chaque ou plusieurs rangées d'aubes à tourillons et à leviers peuvent être tels que décrits ci-dessus.Although only one dowel blade and one lever are shown, the present teaching can be applied to a whole annular row of trunnion vanes, each connected to a control lever. The blades and levers of the row may be identical. Each or more rows of trunnion and lever blades may be as described above.

Claims (15)

Système d'aubes à orientation réglable (26) de turbomachine axiale (2), notamment de compresseur axial (4 ; 6) de turbomachine, le système comprenant : un levier de commande télescopique (32) ; et une aube (26) avec une pale (50) destinée à s'étendre radialement dans un flux (18) de la turbomachine (2) et un tourillon (30) comportant une portion cylindrique (45) ; caractérisé en ce que la portion cylindrique (45) comprend une fente (44) s'étendant radialement;
et le levier de commande télescopique (32) comprend une liaison pivot (46) logée dans la fente (44) qui est configurée pour communiquer un mouvement de rotation à l'aube (26) autour de son tourillon (30). An axially turbomachine adjustable-orientation blade system (26), in particular a turbomachine axial compressor (4; 6), the system comprising: a telescopic control lever (32); and a blade (26) with a blade (50) for extending radially in a flow (18) of the turbomachine (2) and a pin (30) having a cylindrical portion (45); characterized in that the cylindrical portion (45) comprises a radially extending slot (44);
and the telescopic control lever (32) comprises a pivot connection (46) housed in the slot (44) which is configured to impart rotational movement to the blade (26) around its trunnion (30). Système selon la revendication 1, caractérisé en ce que la fente (44) comprend des surfaces internes (58) en contact de la liaison pivot (46) du levier (32).System according to claim 1, characterized in that the slot (44) comprises internal surfaces (58) in contact with the pivot connection (46) of the lever (32). Système selon l'une des revendications 1 à 2, caractérisé en ce que la fente (44) traverse diamétralement la portion cylindrique (45).System according to one of claims 1 to 2, characterized in that the slot (44) diametrically crosses the cylindrical portion (45). Système selon l'une des revendications 1 à 3, caractérisé en ce que le levier de commande télescopique (32) comprend une portion de moindre épaisseur (48) traversée par la liaison pivot (46).System according to one of claims 1 to 3, characterized in that the telescopic control lever (32) comprises a thinner portion (48) traversed by the pivot connection (46). Système selon la revendication 4, caractérisé en ce que la portion de moindre épaisseur (48) est disposée dans la fente (44).System according to claim 4, characterized in that the thinner portion (48) is disposed in the slot (44). Système selon l'une des revendications 1 à 5, caractérisé en ce que le levier de commande télescopique (32) comprend un fourreau (40) et une coulisse (42) glissant à l'intérieur du fourreau (40), la liaison pivot (46) étant solidaire dudit fourreau (40).System according to one of claims 1 to 5, characterized in that the telescopic control lever (32) comprises a sleeve (40) and a slide (42) sliding inside the sleeve (40), the pivot connection ( 46) being integral with said sleeve (40). Système selon la revendication 6, caractérisé en ce que le fourreau (40) comprend une cavité (41) dans laquelle glisse la coulisse (42), la cavité (41) étant à distance de la fente (44) et de la liaison pivot (46).System according to Claim 6, characterized in that the sleeve (40) comprises a cavity (41) in which the slide (42) slides, the cavity (41) being at a distance from the slot (44) and the pivot connection ( 46). Système selon la revendication 7, caractérisé en ce que la cavité (41) est à distance axialement de la portion cylindrique (45).System according to claim 7, characterized in that the cavity (41) is axially spaced from the cylindrical portion (45). Système selon l'une des revendications 1 à 8, caractérisé en ce que la pale (50) présente une épaisseur moyenne qui est supérieure à la largeur de la fente (44).System according to one of claims 1 to 8, characterized in that the blade (50) has an average thickness which is greater than the width of the slot (44). Système selon l'une des revendications 1 à 9, caractérisé en ce que la liaison pivot (46) comporte un axe de pivotement (54), le tourillon (30) présente un axe de rotation (52) coupant l'axe de pivotement (54) en un point d'intersection (55), lesdits axes (52 ; 54) étant optionnellement perpendiculaires.System according to one of claims 1 to 9, characterized in that the pivot connection (46) comprises a pivot axis (54), the pin (30) has an axis of rotation (52) intersecting the pivot axis ( 54) at a point of intersection (55), said axes (52; 54) being optionally perpendicular. Système selon l'une des revendications 1 à 10, caractérisé en ce que le levier de commande télescopique (32) comprend des surfaces latérales opposées (56) qui sont en contact de la fente (44).System according to one of claims 1 to 10, characterized in that the telescopic control lever (32) comprises opposite side surfaces (56) which are in contact with the slot (44). Système selon l'une des revendications 1 à 11, caractérisé en ce que le levier de commande télescopique (32) est intégré radialement dans la hauteur du tourillon (30), et éventuellement de la fente (44).System according to one of claims 1 to 11, characterized in that the telescopic control lever (32) is radially integrated in the height of the trunnion (30), and possibly of the slot (44). Système selon l'une des revendications 1 à 12, caractérisé en ce qu'il comprend une bague de synchronisation (34) qui est fixe axialement par rapport au tourillon (30).System according to one of claims 1 to 12, characterized in that it comprises a synchronizing ring (34) which is fixed axially with respect to the pin (30). Compresseur (4; 6) comprenant un système d'aubes à orientations réglables (26), caractérisé en que le système est conforme à l'une des revendications 1 à 13, préférentiellement le compresseur est un compresseur basse-pression (4).Compressor (4; 6) comprising a system of blades with adjustable orientations (26), characterized in that the system is according to one of claims 1 to 13, preferably the compressor is a low-pressure compressor (4). Turbomachine (2), notamment un turboréacteur d'aéronef, comprenant un système d'aubes à orientations réglables (26), caractérisée en ce que le système est conforme à l'une des revendications 1 à 13, préférentiellement, la turbomachine (2) comprend un compresseur (4 ; 6) conforme à la revendication 14.Turbine engine (2), in particular an aircraft turbojet, comprising a system of blades with adjustable orientations (26), characterized in that the system complies with one of Claims 1 to 13, preferably, the turbomachine (2) comprises a compressor (4; 6) according to claim 14.
EP18182843.5A 2017-08-14 2018-07-11 Variable pitch blade system for a turbomachine compressor Active EP3444444B1 (en)

Applications Claiming Priority (1)

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BE2017/5557A BE1025470B1 (en) 2017-08-14 2017-08-14 COMPRESSOR VARIABLE SHAFT AUB SYSTEM FOR TURBOMACHINE

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EP3444444A1 true EP3444444A1 (en) 2019-02-20
EP3444444B1 EP3444444B1 (en) 2020-06-17

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EP (1) EP3444444B1 (en)
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IT201900005266A1 (en) * 2019-04-05 2020-10-05 Nuovo Pignone Tecnologie Srl Steam turbine with rotating stator blades
CN112096658B (en) * 2020-11-06 2021-01-22 中国航发上海商用航空发动机制造有限责任公司 Aircraft engine compressor and adjustable stator blade position retaining structure thereof
CN113833695A (en) * 2021-10-29 2021-12-24 中国航发沈阳发动机研究所 Stator blade angle adjusting mechanism of compressor in engine
CN114526126B (en) * 2022-04-24 2022-07-26 中国航发四川燃气涡轮研究院 Inlet variable-camber guide vane structure capable of eliminating rotary boss

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EP0532907A1 (en) * 1991-09-19 1993-03-24 Asea Brown Boveri Ag Axial turbine
EP1331403A1 (en) * 2002-01-29 2003-07-30 Snecma Moteurs Stator blade control apparatus
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US20190048738A1 (en) 2019-02-14
EP3444444B1 (en) 2020-06-17
BE1025470B1 (en) 2019-03-18
CN109386314A (en) 2019-02-26
BE1025470A1 (en) 2019-03-11
US10837307B2 (en) 2020-11-17

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