EP2400160B1 - Lightened rotor of axial compressor - Google Patents

Lightened rotor of axial compressor Download PDF

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Publication number
EP2400160B1
EP2400160B1 EP20100166959 EP10166959A EP2400160B1 EP 2400160 B1 EP2400160 B1 EP 2400160B1 EP 20100166959 EP20100166959 EP 20100166959 EP 10166959 A EP10166959 A EP 10166959A EP 2400160 B1 EP2400160 B1 EP 2400160B1
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EP
European Patent Office
Prior art keywords
drum
central portion
platform
rotor
hollow body
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.)
Active
Application number
EP20100166959
Other languages
German (de)
French (fr)
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EP2400160A1 (en
Inventor
Xavier Wery
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
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP20100166959 priority Critical patent/EP2400160B1/en
Priority to RU2011125136/06A priority patent/RU2011125136A/en
Priority to CA2743817A priority patent/CA2743817C/en
Priority to US13/165,178 priority patent/US8870543B2/en
Priority to CN201110170449A priority patent/CN102297158A/en
Publication of EP2400160A1 publication Critical patent/EP2400160A1/en
Application granted granted Critical
Publication of EP2400160B1 publication Critical patent/EP2400160B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors

Definitions

  • the present invention relates, in the field of turbomachines, to a compressor rotor consisting of a drum and blades mechanically fixed thereon.
  • Axial compressors are well known per se and are used inter alia in turbomachines.
  • These low or high pressure compressors comprise several stages of rotating blades, also called rotor blades, which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next floor.
  • the rectifier stages consist essentially of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
  • a compressor drum is a symmetrical hollow body in revolution with respect to its axis of rotation which corresponds to the axis of the turbomachine.
  • the hollow body has a generally oval or ogival shape depending on the shape of the flow.
  • the drum and the rotor blades are generally made of a titanium alloy (TA6V) and the drum has circumferential cavities in which the blade roots are fixed via a system of locks.
  • T6V titanium alloy
  • Such a construction is illustrated in figure 1 of the document EP 1 111 246 B1 .
  • the document GB 1,163,752 presents an alternative to the fastening system with cavities in an axial flow machine rotor.
  • the blade comprises a blade provided with a threaded member which engages in the rotor hub to allow the blade to be fixed to the hub.
  • Document is also known US 2,685,405 an axial compressor in which the rotor stage is provided with raised zones serving to support the rotor blades. These zones comprise an opening enclosing an intermediate portion of the blade, the platform of the blade being disposed within the support area.
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the present invention is more particularly intended to provide a new drum architecture and an original attachment system of the blade to the latter.
  • the present invention also aims to provide a drum rid of its cells and thus aims to provide a new construction of the rotor to reduce consumption in radial and axial clearances.
  • the present invention also aims to achieve a new rotor construction for optimizing the choice of materials of different elements (drum, blade) and therefore a very consistent mass reduction.
  • the present invention relates to a rotor drum rotor compressor stage for axial turbomachine comprising a row of rotor blades each provided with a platform, and a generally symmetrical wall in revolution with respect to the axis of rotation of the rotor.
  • the turbomachine and forming a hollow body, said wall comprising a web and a support area raised relative to the web in a direction facing outwardly of the hollow body, said support zone comprising a central portion and side walls connecting the central portion to web of the drum, said platform of each of said blades being assembled to said central portion by means of one or more fasteners.
  • the present invention relates to a compressor drum for axial turbomachine comprising at least one rotor stage as described above.
  • the figure 1 is a partial sectional view of a conventional axial compressor drum architecture superimposed on a partial sectional view of an axial compressor drum according to a preferred embodiment of the invention (gray profile).
  • the figure 2 represents a three-dimensional view of a preferred variant of the rotor blade according to the invention and the assembly nut.
  • the figure 3 represents a profile view of the attachment of the rotor blade of the figure 2 with the drum according to the preferred embodiment of the invention.
  • FIG. 1 Two respective views in partial section (upper half) and axial of a compressor drum according to the state of the art 1 and according to the invention 2 (in gray) are superimposed on the figure 1 .
  • the respective drums are intended to fix three stages of rotor blades (not shown).
  • the drums 1.2 comprise a wall 3 generally symmetrical in rotation about an axis of rotation, the wall 3 thus forming a hollow body in the shape of an oval or ogive.
  • the wall 3 comprises a web defining the general shape of the drum.
  • the wall 3 further comprises cells 4 for receiving the roots of the rotor blades.
  • the wall 3 instead of the cells 4 support zones 5.
  • the drums 1,2 also conventionally include wipers 6 disposed between the rotor blade stages and intended to be positioned opposite the abradable inner ferrules (not shown).
  • the support zone 5 of the wall 3 visible to the figures 1 and 3 comprises two side walls 7 and a central portion 8 joining the two side walls 7 and intended to be fixed to the rotor blade 9.
  • the support zone 5 thus forms an annular cavity open towards the inside of the hollow body and raised relative to the neighboring wall 3 forming the veil.
  • the side walls 7 of the support zone 5 are preferably inclined relative to a perpendicular to the axis of rotation (radial direction) and connected to the web by rounded sections.
  • the central portion 8 has on its outer face to the hollow body, a hollow portion 10 and rounded edges 11 connecting it to the side walls 7.
  • the hollow portion 10 serves as a housing for the platform 12 of the rotor blade 9, as will be described below, and is preferably provided with a flat bottom.
  • the rounded edges 11 flanking the hollow portion 10 are at the height of the line 13 which delimits the aerodynamic vein (see figure 1 ).
  • the central portion 8 On its inner side, ie on its face facing the hollow body, the central portion 8 also has rounded edges connecting it to the side walls 7 and a projecting portion 14 directed towards the inside of the annular cavity formed by the support zone 5.
  • the projecting portion 14 may be substantially corresponding in shape to that of the hollow portion 10.
  • the projecting portion 14 comprises an area 16 of an additional piece 15, also called sector.
  • the placement area 16 and the area 15 are planar.
  • One or more openings are formed through the thickness of the central portion 8 to allow the attachment of each platform 12 to the central portion 8. According to the embodiment of the invention, or the orifices are formed through the thickness of the hollow portion 10 of the central portion 8.
  • the rotor blade 9 comprises a blade 17 and an attachment platform 12 located in a plane substantially perpendicular to that of the blade.
  • the platform and the blade of the blade are of such dimensions that the platform 12 is housed in the hollow portion 10 while the blade root of the blade partially rests on the rounded edges 11 flanking the housing (see figures 2 and 3 ).
  • the platform 12 comprises a flat surface that cooperates with the flat bottom of the hollow portion 10.
  • the platform may, however, take other forms and fit into a housing of complementary shape.
  • the platform 12 is provided with one or more rods (s) intended (s) to be inserted respectively into the or orifices formed through the thickness of the central portion 8 and allowing fixation from the support zone 5 to the platform 12 of the blade by one or more bolted fasteners, one or more lockbolts or one or more rivets.
  • the platform 12 has a threaded rod 18 at its center and is attached to the support zone 5 by a bolted fastener.
  • the platform 12 comprises one or more orifices for later receiving one or more fastening elements respectively (not shown).
  • the platform comprises one or several orifices and one or more rods (not shown).
  • the inner face of the central portion 8 comprises an investment area 16 of an additional piece 15, also called sector.
  • This piece is provided with one or more orifices intended to be placed (s) facing the orifice (s) formed through the thickness of the central portion.
  • the sector makes it possible not to damage the central part of the support zone during the assembly tensioning of the fastening element or elements.
  • the sector 15 serves to take up the compressive stresses when screwing the nut 19 on the threaded rod 18.
  • the sector is placed between the rod and the lockbolt ring and in the case a rivet, it comes to be placed between the stem and the deformed part of the rivet.
  • the rotor blades are, for example, made of a titanium alloy (TA6V) or aluminum MMC (for Metal Matrix Composite).
  • the drum according to the invention is made of an organic matrix composite material or a metallic material such as, for example, a conventional titanium alloy (TA6V).
  • the rotor according to the invention is lighter in its architecture to reduce the mass of the foot of the blade and remove the cells.
  • This new architecture also makes it possible to introduce new materials (composite drum, MMC aluminum blades) that would not be compatible with a conventional design and thus allows even more significant mass reduction.
  • This drum profile makes it possible to bring the veil of the drum closer to the inner vein, thus minimizing the mass of the blade as mentioned above, a mass that the drum must therefore no longer support.
  • This drum profile also makes it possible to free space for the feet of the stator vanes and the inner ferrules.
  • This fastening system makes it possible to guarantee blade positioning in all operating cases, even at low rotational speeds and even at standstill, in contrast to the conventional design where the blades have a positioning latitude generating, in particular, the phenomena of oscillation (rocking), consumer of axial and radial games.
  • the removal of blade rocking and, consequently, the reduction in the consumption of axial games makes it possible to improve the compactness of the booster and therefore the total mass of the engine.
  • the architecture according to the invention also makes it possible to reduce the radial clearance consumptions by the disappearance of the point masses that are the latches and balancing masses thereof used in the conventional architecture with cells and inducing ovalization of the drum.
  • the decrease of the ovalization of the rotor makes it possible to improve the aero performances via a reduction of the radial clearances as well as a reduction of the variation of these on the same floor.
  • composite materials for the drum also makes it possible to minimize the rotating mass of the drum, and consequently to reduce the amount of material required (thickness) thereon.
  • the use of composite materials for the drum also reduces manufacturing costs through a very significant reduction in material requirements, the mass ratio of the part / material purchased is particularly unfavorable in the case of a starting titanium drum a large forged and requiring a lot of machining unlike composite parts.
  • the architecture according to the invention also provides the possibility of lightening the blower system and mainly the blower disc, by reducing the forces on it from the drum, thanks to the lightening of the rotor low pressure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte, dans le domaine des turbomachines, à un rotor de compresseur constitué d'un tambour et d'aubes fixées mécaniquement sur celui-ci.The present invention relates, in the field of turbomachines, to a compressor rotor consisting of a drum and blades mechanically fixed thereon.

Etat de la techniqueState of the art

Les compresseurs axiaux sont bien connus en soi et sont utilisés entre autres dans les turbomachines.Axial compressors are well known per se and are used inter alia in turbomachines.

Ces compresseurs basse ou haute pression comportent plusieurs étages d'aubes tournantes, encore appelées aubes rotoriques, qui sont séparés par des étages redresseurs qui ont pour but de repositionner le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers l'étage suivant.These low or high pressure compressors comprise several stages of rotating blades, also called rotor blades, which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next floor.

Les étages redresseurs sont constitués essentiellement d'aubes fixes, encore appelées aubes statoriques, reliant une virole extérieure à une virole intérieure, toutes deux concentriques et délimitant la zone d'écoulement d'air ou veine aérodynamique.The rectifier stages consist essentially of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.

Les étages d'aubes rotoriques sont attachés à un tambour. D'une manière générale, un tambour de compresseur est un corps creux symétrique en révolution par rapport à son axe de rotation qui correspond à l'axe de la turbomachine. Le corps creux a une forme générale ovale ou en ogive selon la forme de l'écoulement.The rotor blade stages are attached to a drum. In general, a compressor drum is a symmetrical hollow body in revolution with respect to its axis of rotation which corresponds to the axis of the turbomachine. The hollow body has a generally oval or ogival shape depending on the shape of the flow.

De nos jours, le tambour et les aubes rotoriques sont généralement réalisés dans un alliage de titane (TA6V) et le tambour comporte des alvéoles circonférentielles dans lesquelles les pieds des aubes sont fixés via un système de verrous. Une telle construction est illustrée à la figure 1 du document EP 1 111 246 B1 .Nowadays, the drum and the rotor blades are generally made of a titanium alloy (TA6V) and the drum has circumferential cavities in which the blade roots are fixed via a system of locks. Such a construction is illustrated in figure 1 of the document EP 1 111 246 B1 .

Les architectures classiques avec alvéoles présentent cependant plusieurs inconvénients qu'on peut énumérer comme suit:

  • pour éviter l'ouverture des alvéoles et ainsi garantir la tenue des aubes et la stabilité des pieds au sein des alvéoles, ces dernières doivent appartenir à des zones massives des tambours;
  • les pieds des aubes qui viennent se loger dans ces alvéoles sont également massifs (40 à 50% de la masse de l'aube); il en résulte une masse centrifugée importante induisant des contraintes dans le tambour d'autant plus importantes;
  • la présence d'alvéoles induit des concentrations de contraintes au bord des encoches d'introduction. I1 en résulte qu'un design classique avec alvéoles embarque une quantité importante de matière dont seule une portion relativement réduite est « utile » pour la tenue mécanique;
  • les pieds des aubes ont une latitude de positionnement au sein des alvéoles engendrant notamment des phénomènes d'oscillation (rocking en anglais), consommateur de jeux axiaux et radiaux.
The classical architectures with cells, however, have several drawbacks that can be enumerated as follows:
  • to prevent the opening of the cells and thus ensure the holding of the blades and the stability of the feet within the cells, they must belong to massive areas of the drums;
  • the feet of the blades that are housed in these cells are also massive (40 to 50% of the mass of the dawn); this results in a large centrifugal mass inducing stresses in the drum all the more important;
  • the presence of cavities induces stress concentrations at the edge of the insertion notches. As a result, a conventional design with cavities embeds a large amount of material of which only a relatively small portion is "useful" for mechanical strength;
  • the feet of the blades have a positioning latitude within the cells generating in particular oscillation phenomena ( rocking in English), consumer of axial and radial games.

Le document GB 1,163,752 présente une alternative au système d'attache avec alvéoles dans un rotor de machine à flux axial. L'aube comprend une pale munie d'un membre fileté qui vient s'engager dans le moyeu de rotor pour permettre la fixation de l'aube au moyeu.The document GB 1,163,752 presents an alternative to the fastening system with cavities in an axial flow machine rotor. The blade comprises a blade provided with a threaded member which engages in the rotor hub to allow the blade to be fixed to the hub.

On connaît également du document US 2,685,405 un compresseur axial où l'étage rotorique est muni de zones surélevées servant de support aux aubes rotoriques. Ces zones comportent une ouverture enserrant une partie intermédiaire de l'aube, la plateforme de l'aube étant disposée à l'intérieur de la zone servant de support.Document is also known US 2,685,405 an axial compressor in which the rotor stage is provided with raised zones serving to support the rotor blades. These zones comprise an opening enclosing an intermediate portion of the blade, the platform of the blade being disposed within the support area.

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une solution qui permette de s'affranchir des inconvénients de l'état de la technique.The present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.

La présente invention vise plus particulièrement à fournir une nouvelle architecture de tambour et un système d'attache original de l'aube à ce dernier.The present invention is more particularly intended to provide a new drum architecture and an original attachment system of the blade to the latter.

La présente invention a aussi pour objectif de fournir un tambour débarrassé de ses alvéoles et vise ainsi à fournir une nouvelle construction du rotor permettant de réduire les consommations en jeux radiaux et axiaux.The present invention also aims to provide a drum rid of its cells and thus aims to provide a new construction of the rotor to reduce consumption in radial and axial clearances.

La présente invention a également pour objectif de réaliser une nouvelle construction de rotor permettant une optimisation du choix des matériaux des différents éléments (tambour, aube) et donc une réduction de la masse très conséquente.The present invention also aims to achieve a new rotor construction for optimizing the choice of materials of different elements (drum, blade) and therefore a very consistent mass reduction.

Résumé de l'inventionSummary of the invention

La présente invention se rapporte à un étage rotorique de tambour de compresseur pour turbomachine axiale comprenant une rangée d'aubes rotoriques munies chacune d'une plateforme, et une paroi généralement symétrique en révolution par rapport à l'axe de rotation de la turbomachine et formant un corps creux, ladite paroi comprenant un voile et une zone support surélevée par rapport au voile dans une direction orientée vers l'extérieur du corps creux, ladite zone support comportant une partie centrale et des parois latérales reliant la partie centrale au voile du tambour, ladite plateforme de chacune desdites aubes étant assemblée à ladite partie centrale au moyen d'un ou plusieurs éléments de fixation.The present invention relates to a rotor drum rotor compressor stage for axial turbomachine comprising a row of rotor blades each provided with a platform, and a generally symmetrical wall in revolution with respect to the axis of rotation of the rotor. the turbomachine and forming a hollow body, said wall comprising a web and a support area raised relative to the web in a direction facing outwardly of the hollow body, said support zone comprising a central portion and side walls connecting the central portion to web of the drum, said platform of each of said blades being assembled to said central portion by means of one or more fasteners.

Selon des modes particuliers de l'invention, l'étage rotorique comporte au moins une ou une combinaison appropriée des caractéristiques suivantes:

  • la partie centrale est munie, sur sa face extérieure au corps creux, d'un logement destiné à recevoir la plateforme de chacune desdites aubes rotoriques;
  • ladite plateforme comporte au moins un élément de fixation et/ou comporte au moins un orifice permettant le passage de l'élément de fixation;
  • la partie centrale comporte, sur sa face intérieure au corps creux, une aire de placement d'une pièce additionnelle, aussi appelée secteur;
  • la partie centrale et le secteur comportent au moins un orifice permettant chacun le passage de l'élément de fixation;
  • la partie centrale est reliée aux parois latérales par des bords arrondis, la crête des bords arrondis délimitant une veine aérodynamique, et les parois latérales sont reliées au voile du tambour par des tronçons arrondis;
  • les parois latérales sont inclinées par rapport à une perpendiculaire à l'axe de rotation;
  • l'aire de placement est disposée sur une partie saillante vers l'intérieur de la zone support;
  • le secteur et l'aire de placement sont plans;
  • le logement de la partie centrale est plan et coopère avec une surface plane de la plateforme de l'aube;
  • la plateforme est de forme complémentaire à la partie centrale;
  • l'élément de fixation est une attache boulonnée, un lockbolt ou un rivet;
  • la tige de chaque attache boulonnée ou de chaque lockbolt ou rivet fait partie intégrante de la plateforme de l'aube rotorique;
  • le secteur vient se placer en sandwich entre la partie centrale et un écrou de l'attache boulonnée ou entre la partie centrale et une bague du lockbolt ou entre la partie centrale et une partie déformée du rivet;
  • les aubes rotoriques sont réalisées en aluminium MMC, pour Metal Matrix Composite, ou dans un alliage de titane et en ce que le tambour est réalisé dans un matériau métallique ou dans un matériau composite à matrice organique.
According to particular embodiments of the invention, the rotor stage comprises at least one or a suitable combination of the following characteristics:
  • the central portion is provided on its outer face to the hollow body, a housing for receiving the platform of each of said rotor blades;
  • said platform comprises at least one fixing element and / or comprises at least one orifice allowing passage of the fixing element;
  • the central portion has, on its inner face to the hollow body, an additional part placement area, also called sector;
  • the central portion and the sector comprise at least one orifice each allowing the passage of the fastener;
  • the central part is connected to the side walls by rounded edges, the ridge of the rounded edges delimiting an aerodynamic stream, and the side walls are connected to the veil of the drum by rounded sections;
  • the side walls are inclined with respect to a perpendicular to the axis of rotation;
  • the placement area is disposed on a projecting portion towards the inside of the support area;
  • sector and placement area are plans;
  • the housing of the central portion is plane and cooperates with a flat surface of the platform of the blade;
  • the platform is of complementary shape to the central part;
  • the fastening element is a bolted fastener, a lockbolt or a rivet;
  • the stem of each bolted fastener or each lockbolt or rivet is an integral part of the rotor blade platform;
  • the sector is sandwiched between the central portion and a nut of the bolted fastener or between the central portion and a lockbolt ring or between the central portion and a deformed portion of the rivet;
  • the rotor blades are made of MMC aluminum, for Metal Matrix Composite, or in a titanium alloy and in that the drum is made of a metallic material or an organic matrix composite material.

La présente invention se rapporte à un tambour de compresseur pour turbomachine axiale comprenant au moins un étage rotorique tel que décrit ci-dessus.The present invention relates to a compressor drum for axial turbomachine comprising at least one rotor stage as described above.

Brève description des figuresBrief description of the figures

La figure 1 représente une vue en coupe partielle d'une architecture classique de tambour de compresseur axial superposée à une vue en coupe partielle d'un tambour de compresseur axial selon une forme de réalisation préférée de l'invention (profil en gris).The figure 1 is a partial sectional view of a conventional axial compressor drum architecture superimposed on a partial sectional view of an axial compressor drum according to a preferred embodiment of the invention (gray profile).

La figure 2 représente une vue tridimensionnelle d'une variante préférée de l'aube rotorique selon l'invention et de l'écrou d'assemblage.The figure 2 represents a three-dimensional view of a preferred variant of the rotor blade according to the invention and the assembly nut.

La figure 3 représente une vue de profil de la fixation de l'aube rotorique de la figure 2 au tambour selon la forme de réalisation préférée de l'invention.The figure 3 represents a profile view of the attachment of the rotor blade of the figure 2 with the drum according to the preferred embodiment of the invention.

Légende:Legend:

  1. 1. Tambour selon l'état de la techniqueDrum according to the state of the art
  2. 2. Tambour selon l'invention2. Drum according to the invention
  3. 3. Paroi du tambour3. Drum wall
  4. 4. Alvéole du tambour selon l'état de la technique4. Alveolus of the drum according to the state of the art
  5. 5. Zone support5. Support area
  6. 6. Léchette6. Lech
  7. 7. Paroi latérale de la zone support7. Side wall of the support zone
  8. 8. Partie centrale liant les parois latérales de la zone support8. Central part bonding the side walls of the support zone
  9. 9. Aube rotorique9. Rotor blade
  10. 10. Partie creuse dans la partie centrale10. Hollow part in the central part
  11. 11. Bords arrondis encadrant la partie creuse11. Rounded edges framing the hollow part
  12. 12. Plateforme de fixation12. Fixing platform
  13. 13. Ligne délimitant la veine aérodynamique13. Line delimiting the aerodynamic vein
  14. 14. Partie saillante14. projecting part
  15. 15. Pièce additionnelle, aussi appelée secteur15. Additional room, also called sector
  16. 16. Aire de placement du secteur16. Area of investment of the sector
  17. 17. Pale de l'aube17. Blade of dawn
  18. 18. Tige filetée18. Threaded rod
  19. 19. Ecrou19. Nut
Description détaillée de l'inventionDetailed description of the invention

Deux vues respectives en coupe partielle (moitié supérieure) et axiale d'un tambour de compresseur selon l'état de la technique 1 et selon l'invention 2 (en gris) sont superposées à la figure 1. Dans l'exemple illustré, les tambours respectifs sont destinés à fixer trois étages d'aubes rotoriques (non représentées).Two respective views in partial section (upper half) and axial of a compressor drum according to the state of the art 1 and according to the invention 2 (in gray) are superimposed on the figure 1 . In the illustrated example, the respective drums are intended to fix three stages of rotor blades (not shown).

Les tambours 1,2 comportent une paroi 3 généralement symétrique en rotation autour d'un axe de rotation, la paroi 3 formant ainsi un corps creux en forme d'ovale ou d'ogive. La paroi 3 comprend un voile définissant la forme générale du tambour. Selon l'architecture classique, la paroi 3 comporte en outre des alvéoles 4 destinées à recevoir les pieds des aubes rotoriques. Selon la présente invention, la paroi 3 comporte à la place des alvéoles 4 des zones supports 5. Les tambours 1,2 comportent également classiquement des léchettes 6 disposées entre les étages d'aubes rotoriques et destinées à être positionnées en regard des abradables des viroles intérieures (non représentés).The drums 1.2 comprise a wall 3 generally symmetrical in rotation about an axis of rotation, the wall 3 thus forming a hollow body in the shape of an oval or ogive. The wall 3 comprises a web defining the general shape of the drum. According to the conventional architecture, the wall 3 further comprises cells 4 for receiving the roots of the rotor blades. According to the present invention, the wall 3 instead of the cells 4 support zones 5. The drums 1,2 also conventionally include wipers 6 disposed between the rotor blade stages and intended to be positioned opposite the abradable inner ferrules (not shown).

L'architecture de rotor selon l'invention et telle que représentée partiellement à la figure 3 résulte de l'assemblage de quatre éléments principaux qui seront décrits ci-dessous:

  • une paroi 3 de tambour comportant des zones supports 5,
  • des aubes rotoriques 9 comportant chacune une plateforme 12 fixée à la zone support 5,
  • des éléments de fixation assurant la fixation entre les plateformes 12 et les zones supports 5,
  • et des pièces 15, appelées secteurs, assurant la reprise des efforts lors de la mise sous tension des éléments de fixation.
The rotor architecture according to the invention and as partially shown in FIG. figure 3 results from the assembly of four main elements which will be described below:
  • a drum wall 3 comprising support zones 5,
  • rotor blades 9 each comprising a platform 12 fixed to the support zone 5,
  • fixing elements ensuring the fixing between the platforms 12 and the support zones 5,
  • and parts 15, called sectors, ensuring the recovery of forces when powering the fasteners.

La zone support 5 de la paroi 3 visible aux figures 1 et 3 comporte deux parois latérales 7 et une partie centrale 8 joignant les deux parois latérales 7 et destinée à être fixée à l'aube rotorique 9. La zone support 5 forme ainsi une cavité annulaire ouverte vers l'intérieur du corps creux et surélevée par rapport à la paroi avoisinante 3 formant le voile. Selon la présente invention, les parois latérales 7 de la zone support 5 sont préférentiellement inclinées par rapport à une perpendiculaire à l'axe de rotation (direction radiale) et reliées au voile par des tronçons arrondis.The support zone 5 of the wall 3 visible to the figures 1 and 3 comprises two side walls 7 and a central portion 8 joining the two side walls 7 and intended to be fixed to the rotor blade 9. The support zone 5 thus forms an annular cavity open towards the inside of the hollow body and raised relative to the neighboring wall 3 forming the veil. According to the present invention, the side walls 7 of the support zone 5 are preferably inclined relative to a perpendicular to the axis of rotation (radial direction) and connected to the web by rounded sections.

Selon une forme de réalisation préférée de l'invention, la partie centrale 8 comporte sur sa face extérieure au corps creux, une partie creuse 10 et des bords arrondis 11 la reliant aux parois latérales 7. La partie creuse 10 sert de logement à la plateforme 12 de l'aube rotorique 9, comme cela sera décrit ci-dessous, et est préférentiellement munie d'un fond plat. Les bords arrondis 11 encadrant la partie creuse 10 se trouvent à hauteur de la ligne 13 qui délimite la veine aérodynamique (voir figure 1). Sur sa face intérieure, c.à.d. sur sa face en regard du corps creux, la partie centrale 8 comporte également des bords arrondis la reliant aux parois latérales 7 et une partie saillante 14 dirigée vers l'intérieur de la cavité annulaire formée par la zone support 5. Selon cette première forme de réalisation de l'invention, la partie saillante 14 peut être de forme sensiblement correspondante à celle de la partie creuse 10. Préférentiellement, la partie saillante 14 comporte une aire de placement 16 d'une pièce additionnelle 15, aussi appelée secteur. Toujours préférentiellement, l'aire de placement 16 et le secteur 15 sont plans.According to a preferred embodiment of the invention, the central portion 8 has on its outer face to the hollow body, a hollow portion 10 and rounded edges 11 connecting it to the side walls 7. The hollow portion 10 serves as a housing for the platform 12 of the rotor blade 9, as will be described below, and is preferably provided with a flat bottom. The rounded edges 11 flanking the hollow portion 10 are at the height of the line 13 which delimits the aerodynamic vein (see figure 1 ). On its inner side, ie on its face facing the hollow body, the central portion 8 also has rounded edges connecting it to the side walls 7 and a projecting portion 14 directed towards the inside of the annular cavity formed by the support zone 5. According to this first form of embodiment of the invention, the projecting portion 14 may be substantially corresponding in shape to that of the hollow portion 10. Preferably, the projecting portion 14 comprises an area 16 of an additional piece 15, also called sector. Still preferentially, the placement area 16 and the area 15 are planar.

Un ou plusieurs orifices sont ménagés au travers de l'épaisseur de la partie centrale 8 pour permettre la fixation de chaque plateforme 12 à la partie centrale 8. Selon la forme de réalisation de l'invention, le ou les orifices sont ménagés au travers de l'épaisseur de la partie creuse 10 de la partie centrale 8.One or more openings are formed through the thickness of the central portion 8 to allow the attachment of each platform 12 to the central portion 8. According to the embodiment of the invention, or the orifices are formed through the thickness of the hollow portion 10 of the central portion 8.

L'aube rotorique 9 selon l'invention comporte une pale 17 et une plateforme de fixation 12 située dans un plan sensiblement perpendiculaire à celui de la pale. La plateforme et la pale de l'aube sont de dimensions telles que la plateforme 12 vient se loger dans la partie creuse 10 tandis le pied de pale de l'aube repose partiellement sur les bords arrondis 11 encadrant le logement (voir figures 2 et 3). Préférentiellement, la plateforme 12 comporte une surface plane qui vient coopérer avec le fond plat de la partie creuse 10. La plateforme peut cependant revêtir d'autres formes et s'insérer dans un logement de forme complémentaire.The rotor blade 9 according to the invention comprises a blade 17 and an attachment platform 12 located in a plane substantially perpendicular to that of the blade. The platform and the blade of the blade are of such dimensions that the platform 12 is housed in the hollow portion 10 while the blade root of the blade partially rests on the rounded edges 11 flanking the housing (see figures 2 and 3 ). Preferably, the platform 12 comprises a flat surface that cooperates with the flat bottom of the hollow portion 10. The platform may, however, take other forms and fit into a housing of complementary shape.

Pour assurer la fixation de la plateforme 12 à la zone support 5, différentes variantes sont possibles. Selon une variante préférée, la plateforme 12 est munie d'une ou plusieurs tige(s) destinée(s) à être insérée(s) respectivement dans le ou les orifices ménagés à travers l'épaisseur de la partie centrale 8 et permettant la fixation de la zone support 5 à la plateforme 12 de l'aube par une ou plusieurs attaches boulonnées, un ou plusieurs lockbolts ou un ou plusieurs rivets. Préférentiellement et tel qu'illustré aux figures 2 et 3, la plateforme 12 comporte une tige filetée 18 en son centre et est attachée à la zone support 5 par une attache boulonnée. Selon une autre variante, la plateforme 12 comporte un ou plusieurs orifices destinés à recevoir ultérieurement un ou plusieurs éléments de fixation respectivement (non représenté). Selon encore une autre variante, la plateforme comporte un ou plusieurs orifices et une ou plusieurs tiges (non représenté).To ensure the attachment of the platform 12 to the support zone 5, different variants are possible. According to a preferred variant, the platform 12 is provided with one or more rods (s) intended (s) to be inserted respectively into the or orifices formed through the thickness of the central portion 8 and allowing fixation from the support zone 5 to the platform 12 of the blade by one or more bolted fasteners, one or more lockbolts or one or more rivets. Preferably and as illustrated in figures 2 and 3 , the platform 12 has a threaded rod 18 at its center and is attached to the support zone 5 by a bolted fastener. According to another variant, the platform 12 comprises one or more orifices for later receiving one or more fastening elements respectively (not shown). According to yet another variant, the platform comprises one or several orifices and one or more rods (not shown).

Comme susmentionné et, préférentiellement, la face intérieure de la partie centrale 8 comporte une aire de placement 16 d'une pièce additionnelle 15, aussi appelée secteur. Cette pièce est munie d'un ou de plusieurs orifices destinés à être placé(s) en regard du ou des orifices ménagés à travers l'épaisseur de la partie centrale. Le secteur permet de ne pas endommager la partie centrale de la zone support lors de la mise sous tension d'assemblage du ou des éléments de fixation. Dans l'exemple illustré à la figure 3, le secteur 15 sert à reprendre les contraintes de compression lors du vissage de l'écrou 19 sur la tige filetée 18. Dans le cas d'un lockbolt, le secteur vient se placer entre la tige et la bague du lockbolt et dans le cas d'un rivet, il vient se placer entre la tige et la partie déformée du rivet.As mentioned above, and preferentially, the inner face of the central portion 8 comprises an investment area 16 of an additional piece 15, also called sector. This piece is provided with one or more orifices intended to be placed (s) facing the orifice (s) formed through the thickness of the central portion. The sector makes it possible not to damage the central part of the support zone during the assembly tensioning of the fastening element or elements. In the example shown in figure 3 , the sector 15 serves to take up the compressive stresses when screwing the nut 19 on the threaded rod 18. In the case of a lockbolt, the sector is placed between the rod and the lockbolt ring and in the case a rivet, it comes to be placed between the stem and the deformed part of the rivet.

Selon la présente invention, les aubes rotoriques sont, par exemple, réalisées dans un alliage de titane (TA6V) ou en aluminium MMC (pour Metal Matrix Composite). Le tambour selon l'invention est réalisé dans un matériau composite à matrice organique ou dans un matériau métallique tel que, par exemple, un alliage de titane (TA6V) conventionnel.According to the present invention, the rotor blades are, for example, made of a titanium alloy (TA6V) or aluminum MMC (for Metal Matrix Composite). The drum according to the invention is made of an organic matrix composite material or a metallic material such as, for example, a conventional titanium alloy (TA6V).

Avantages de l'inventionAdvantages of the invention

Le rotor selon l'invention est plus léger de par son architecture permettant de réduire la masse du pied de l'aube et de supprimer les alvéoles. Cette nouvelle architecture permet en outre d'introduire des matériaux nouveaux (tambour en composite, aubes en aluminium MMC) qui ne seraient pas compatibles avec un design classique et permet ainsi une réduction de masse encore plus significative.The rotor according to the invention is lighter in its architecture to reduce the mass of the foot of the blade and remove the cells. This new architecture also makes it possible to introduce new materials (composite drum, MMC aluminum blades) that would not be compatible with a conventional design and thus allows even more significant mass reduction.

Ce profil de tambour permet de rapprocher au mieux le voile du tambour de la veine intérieure, réduisant ainsi au minimum la masse de l'aube comme susmentionné, masse que le tambour ne doit donc plus supporter. Ce profil de tambour permet en outre de dégager de l'espace pour les pieds des aubes statoriques et les viroles intérieures.This drum profile makes it possible to bring the veil of the drum closer to the inner vein, thus minimizing the mass of the blade as mentioned above, a mass that the drum must therefore no longer support. This drum profile also makes it possible to free space for the feet of the stator vanes and the inner ferrules.

Ce système d'attache permet de garantir un positionnement de l'aube dans tous les cas de fonctionnement y compris à faibles vitesses de rotation et même à l'arrêt, contrairement au design classique où les aubes ont une latitude de positionnement engendrant notamment les phénomènes d'oscillation (rocking), consommateur de jeux axiaux et radiaux. La suppression du rocking des aubes et, en conséquence, la diminution de la consommation de jeux axiaux permet d'améliorer la compacité du booster et donc la masse totale du moteur.This fastening system makes it possible to guarantee blade positioning in all operating cases, even at low rotational speeds and even at standstill, in contrast to the conventional design where the blades have a positioning latitude generating, in particular, the phenomena of oscillation (rocking), consumer of axial and radial games. The removal of blade rocking and, consequently, the reduction in the consumption of axial games makes it possible to improve the compactness of the booster and therefore the total mass of the engine.

L'architecture selon l'invention permet aussi de diminuer les consommations de jeux radiaux de par la disparition des masses ponctuelles que sont les verrous et les masses d'équilibrage de ceux-ci utilisées dans l'architecture classique avec alvéoles et induisant une ovalisation du tambour. La diminution de l'ovalisation du rotor permet d'améliorer les performances aéro via une réduction des jeux radiaux ainsi qu'une réduction de la variation de ceux-ci sur un même étage.The architecture according to the invention also makes it possible to reduce the radial clearance consumptions by the disappearance of the point masses that are the latches and balancing masses thereof used in the conventional architecture with cells and inducing ovalization of the drum. The decrease of the ovalization of the rotor makes it possible to improve the aero performances via a reduction of the radial clearances as well as a reduction of the variation of these on the same floor.

Elle permet également de faciliter l'assemblage et le contrôle des jeux par une fixation des aubes plus simple à mettre en ouvre et stable.It also facilitates the assembly and control of the games by a blade attachment easier to implement and stable.

Elle permet aussi d'augmenter les fréquences propres du système ce qui limite les risques de phénomènes vibratoires néfastes (mode tambour, interaction rotor-stator).It also makes it possible to increase the natural frequencies of the system which limits the risks of harmful vibration phenomena (drum mode, rotor-stator interaction).

L'utilisation de matériaux composites pour le tambour du rotor de compresseur permet d'optimiser l'orientation des fibres afin de maximiser la raideur circonférentielle. Il en résulte une augmentation de la tenue en durée de vie ainsi qu'une diminution de la consommation des jeux radiaux (moins de gonflement du tambour qu'avec un matériau métallique grâce à la maximisation de la raideur).The use of composite materials for the compressor rotor drum optimizes fiber orientation to maximize circumferential stiffness. This results in an increase in life span and a reduction in the consumption of radial clearances (less swelling of the drum with a metal material through the maximization of stiffness).

L'utilisation de matériaux composites pour le tambour permet en outre de minimiser la masse tournante du tambour, et, en conséquence, de réduire la quantité de matière nécessaire (épaisseur) sur celui-ci.The use of composite materials for the drum also makes it possible to minimize the rotating mass of the drum, and consequently to reduce the amount of material required (thickness) thereon.

L'utilisation de matériaux composites pour le tambour permet également de réduire les coûts de fabrication grâce à une diminution très importante des besoins en matière, le rapport masse de la pièce/matière achetée étant particulièrement défavorable dans le cas d'un tambour en titane partant d'un gros forgé et nécessitant beaucoup d'usinage contrairement aux pièces composites.The use of composite materials for the drum also reduces manufacturing costs through a very significant reduction in material requirements, the mass ratio of the part / material purchased is particularly unfavorable in the case of a starting titanium drum a large forged and requiring a lot of machining unlike composite parts.

La simplicité de l'assemblage permet également une réduction des temps d'assemblage et de contrôle.The simplicity of assembly also reduces assembly and control times.

Finalement, l'architecture selon l'invention donne également la possibilité d'alléger le système de la soufflante et principalement le disque de la soufflante, de par la diminution des efforts sur celui-ci provenant du tambour, grâce à l'allégement du rotor basse pression.Finally, the architecture according to the invention also provides the possibility of lightening the blower system and mainly the blower disc, by reducing the forces on it from the drum, thanks to the lightening of the rotor low pressure.

Claims (15)

  1. A compressor drum (2) for an axial turbomachine, comprising:
    - a wall (3) generally symmetrical in revolution relative to the rotation axis of the turbomachine and forming a hollow body with an oval or bullet shape, said wall (3) comprising a shroud defining the general shape of the drum (2) and a support zone (5) that is raised relative to the shroud in a direction oriented toward the outside of the hollow body; said support zone (5) comprising a central portion (8) and side walls (7) connecting the central portion (8) to the shroud of the drum (2), the support zone (5) thus forming an annular cavity that is opened toward the inside of the hollow body and raised relative to the adjacent wall (3) forming the shroud;
    - at least one rotor stage comprising a row of rotor vanes (9) each provided with a platform (12), said platform (12) of each of said vanes (9) being assembled to the central portion (8) of the support zone (5) using one or more fastening elements, the central portion (8) being provided, on its face outside the hollow body, with a housing intended to receive the platform (12) of each of said rotor vanes (9).
  2. The drum (2) according to Claim 1, characterized in that said platform (12) covers the entire central portion (8).
  3. The drum (2) according to any one of the preceding claims, characterized in that said platform (12) comprises at least one fastening element and/or comprises at least one orifice allowing the passage of the fastening element.
  4. The drum (2) according to any one of the preceding claims, characterized in that the central portion (8) comprises, on its face inside the hollow body, a placement area (16) for an additional piece (15), also called sector.
  5. The drum (2) according to Claim 4, characterized in that the central portion (8) and the sector (15) comprise at least one orifice each allowing the passage of the fastening element.
  6. The drum (2) according to any one of the preceding claims, characterized in that the central portion (8) is connected to the side walls (7) by rounded edges (11), the crest of the rounded edges (11) delimiting an aerodynamic vein, and in that the side walls (7) are connected to the shroud of the drum (2) by rounded sections.
  7. The drum (2) according to any one of the preceding claims, characterized in that the side walls (7) are slanted relative to a perpendicular to the rotation axis.
  8. The drum (2) according to Claim 4, characterized in that the placement area (16) is arranged on a portion (14) that protrudes toward the inside of the support zone (5).
  9. The drum (2) according to Claim 4, characterized in that the sector (15) and the placement area (16) are planar.
  10. The drum (2) according to Claim 1, characterized in that the housing of the central portion (8) is planar and cooperates with a planar surface of the platform (12) of the vane.
  11. The drum (2) according to Claim 2, characterized in that the shape of the platform (12) is complementary to the central portion (8).
  12. The drum (2) according to any one of the preceding claims, characterized in that the fastening element is a bolted clip, a lockbolt or a rivet.
  13. The drum (2) according to Claim 12, characterized in that the rod of each bolted clip or of each lockbolt or rivet is an integral part of the platform (12) of the rotor vane.
  14. The drum (2) according to Claim 12, characterized in that the sector (15) becomes sandwiched between the central portion (8) and a nut (19) of the bolted clip or between the central portion (8) and a ring of the lockbolt or between the central portion (8) and a deformed portion of the rivet.
  15. The drum (2) according to any one of the preceding claims, characterized in that the rotor vanes (9) are made of MMC (metal matrix composite) aluminum, or of a titanium alloy, and in that the drum (2) is made of a metal material or an organic matrix composite material.
EP20100166959 2010-06-23 2010-06-23 Lightened rotor of axial compressor Active EP2400160B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20100166959 EP2400160B1 (en) 2010-06-23 2010-06-23 Lightened rotor of axial compressor
RU2011125136/06A RU2011125136A (en) 2010-06-23 2011-06-21 LIGHTENED AXIAL COMPRESSOR ROTOR
CA2743817A CA2743817C (en) 2010-06-23 2011-06-21 Lightened axial compressor rotor
US13/165,178 US8870543B2 (en) 2010-06-23 2011-06-21 Lightened axial compressor rotor
CN201110170449A CN102297158A (en) 2010-06-23 2011-06-23 Lightened rotor of axial compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20100166959 EP2400160B1 (en) 2010-06-23 2010-06-23 Lightened rotor of axial compressor

Publications (2)

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EP2400160A1 EP2400160A1 (en) 2011-12-28
EP2400160B1 true EP2400160B1 (en) 2014-01-01

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US (1) US8870543B2 (en)
EP (1) EP2400160B1 (en)
CN (1) CN102297158A (en)
CA (1) CA2743817C (en)
RU (1) RU2011125136A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2706242A1 (en) 2012-09-11 2014-03-12 Techspace Aero S.A. Fixing of blades on an axial compressor drum
EP2762681B1 (en) * 2013-02-04 2017-09-06 Safran Aero Boosters SA Rotor drum of an axial turbomachine and corresponding turbomachine
US10422340B2 (en) 2014-05-08 2019-09-24 General Electric Company Composite booster spool with separable composite blades
BE1027359B1 (en) 2019-06-11 2021-01-21 Safran Aero Boosters Sa HYBRID ROTOR WITH EXTERNAL SHELL BUILT AGAINST COMPOSITE ANNULAR WALL

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2477954A (en) * 1947-04-01 1949-08-02 Blanc Jacques Jean Louis Gas turbine
US2685405A (en) * 1948-05-03 1954-08-03 Edward A Stalker Axial flow compressor
GB723813A (en) * 1952-05-30 1955-02-09 Power Jets Res & Dev Ltd Improvements in or relating to bladed rotors for compressors, turbines and like fluid flow machines
GB1163752A (en) 1965-11-25 1969-09-10 Edgar Allen Aerex Ltd Improvements in and relating to Axial-Flow Fluid Machines of the Rotary kind
US3609059A (en) * 1969-10-03 1971-09-28 Gen Motors Corp Isothermal wheel
US5118257A (en) * 1990-05-25 1992-06-02 Sundstrand Corporation Boot attachment for composite turbine blade, turbine blade and method of making turbine blade
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
DE69910408T2 (en) 1999-12-21 2004-06-24 Techspace Aero S.A. Rigid ring part
EP1319805A1 (en) * 2001-12-17 2003-06-18 Techspace aero Rotor or rotor element for turbocompressors

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CA2743817A1 (en) 2011-12-23
US20110318185A1 (en) 2011-12-29
CA2743817C (en) 2016-10-25
RU2011125136A (en) 2012-12-27
US8870543B2 (en) 2014-10-28
CN102297158A (en) 2011-12-28
EP2400160A1 (en) 2011-12-28

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