EP3022405B1 - Device to assemble blades and corresponding method for assembling - Google Patents

Device to assemble blades and corresponding method for assembling Download PDF

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Publication number
EP3022405B1
EP3022405B1 EP14747094.2A EP14747094A EP3022405B1 EP 3022405 B1 EP3022405 B1 EP 3022405B1 EP 14747094 A EP14747094 A EP 14747094A EP 3022405 B1 EP3022405 B1 EP 3022405B1
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EP
European Patent Office
Prior art keywords
turbine
ring
dismantling
holding element
blades
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
EP14747094.2A
Other languages
German (de)
French (fr)
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EP3022405A1 (en
Inventor
Jean Marie FRAUCA
Yann MERSCHAERT
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 Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3022405A1 publication Critical patent/EP3022405A1/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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/12—Blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/60—Shafts
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a device for depositing at least one blade of a turbine; a system for removing at least one blade of a turbine, a method of mounting such a dispensing device and also a method of removing at least one turbine blade.
  • the invention relates more particularly to the field of aircraft engine turbines, and in particular high pressure turbines.
  • the figure 1 schematically illustrates a general section of an aircraft engine and the different parts of said engine.
  • the air entering through the air inlet of the ADMISSION part of the cold section is compressed in a compressor (COMPRESSION part on the figure 1 ) before being mixed with a fuel and burned in one of the combustion chambers of the COMBUSTION part.
  • the hot gases produced in the combustion chamber reach the vanes of the turbine and drive the turbine (or several turbines) and are ejected at the EXHAUST portion of the engine which generates a thrust causing the aircraft.
  • a turbine stage generally consists of a fixed blade followed by a moving blade.
  • a turbine may comprise one or more stages. The invention relates more particularly to the removal of the mobile blade of the turbine.
  • the axis of insertion of the vanes into the cells of the turbine in which they are received is inclined with respect to the motor axis in order to contribute to the maintenance of the vanes between them during the high speed rotation of the turbine, the removal blades are progressively and radially elliptical.
  • the inclination of the axis of insertion of the blades with respect to the motor axis can be about thirty degrees for example.
  • the figure 2 allows to visualize the inclination of an angle ⁇ of the insertion axis Xi of a blade A with respect to the shaft of the turbine Ar (turbine shaft and motor shaft are combined).
  • a sealing liner is furthermore generally inserted between two successive blades in order to reduce almost completely the clearance between the vanes.
  • the withdrawal is gradual, i.e. dawn after dawn, small distance a short distance until each dawn is maintained only a few millimeters in the cell in which his foot is inserted. These few millimeters, for example two millimeters, allow to have a sufficient clearance between the blades to extract them one by one.
  • the invention aims to remedy all or some of the disadvantages of the state of the art identified above, and in particular to propose means for to make it possible to secure the removal of the blades by limiting as much as possible the risk of falling blades during operation in the horizontal position of the engine.
  • one aspect of the invention relates to a device for depositing at least one blade of a turbine described in claim 1.
  • Such a device advantageously makes it possible to block, preferably axially, ie in a direction parallel to the shaft of the turbine, the vanes of the turbine when they are no longer retained in their respective cells by a few millimeters ie when they are are ready to be deposited.
  • a turbine blade to fall just before removal in itself (withdrawal of the blade of its alveolus).
  • the removal opening may be a notch made in the holding element.
  • the sizing of the dispensing aperture is related to the height of the portion of the blade taken in its cell to ensure its extraction from said cell.
  • the removal opening makes it possible to get rid of hazards specific to the environment where the removal of the blade of the horizontal type of the engine or module takes place, risk of contact between operators and therefore a fall of one or several blades, small shocks or repeated efforts to exit each dawn of his home, possible instability of the ground, shocks on the engine.
  • the holding element is preferably fixed to the hub / trunnion of the turbine.
  • an angular position of the holding member can be done by rotating the holding member manually around the turbine shaft due to the pivot connection.
  • the setting compared to the opening of deposit with the dawn to deposit allows an operator to access this blade which is not blocked by the blocking surface.
  • the other blades are maintained thanks to the blocking surface and are not likely to drop in the event of a jolt, mishandling or other accident.
  • the invention also relates to a system for depositing at least one blade of a turbine, said turbine comprising a set of N blades, said system comprising a dispensing device according to one of the previously described embodiments, a shaft of the turbine, the first ring being fixed to the shaft of the turbine so that it is integral in rotation with the shaft of the turbine and the holding member being free to rotate relative to the turbine shaft in the circular groove.
  • An operator to access the blades and extract them partially gradually, in ellipse of their respective cells can either help the opening of removal, and in this case rotate the holding element to put the aperture drop off each dawn little by little; either use the access opening, or the plurality of access openings.
  • the method according to the invention may have the following additional characteristic: the partial extraction step is carried out by a plurality of successive axial displacements of each of the blades of the set of vanes so as to position said vanes abutting against the blocking surface.
  • the partial extraction is done by dawn by rotating all along the turbine and by repeating this operation until the blade dimension, and more particularly the blade root, outside the corresponding cell is sufficient for the game between blades allows the removal of a blade. In this case, the blades are in abutment against the blocking surface.
  • the figure 1 illustrates a sectional view of an aircraft engine
  • the dispensing system comprises a dispensing device 1 and a turbine shaft Ar, here a journal.
  • the figure 3 illustrates the dispensing system in a vertical configuration of the turbine.
  • This type of configuration is generally adopted for the set of blades.
  • the vanes being deposited axially in their respective cells (cells not visible in the photo) along the axis X1, it is visible that in this so-called vertical configuration, no risk of falling in case of shock, shock is to be feared.
  • the blades are placed (and deposited) gradually, one after the other, elliptically millimeters by millimeters. In the vertical configuration, a blade whose foot is inserted only one or two millimeters into its cell will not fall.
  • the figure 4 illustrates the removal system of the figure 1 in a horizontal configuration of the turbine.
  • This configuration is generally used for in-situ blade removal.
  • a blade whose foot is inserted only one or two millimeters into its cell, just before removal (which is the total extraction of the blade of its cell along the axis X2) may fall without the removal device 1 whose operation will be explained in more detail with reference to the following figures.
  • the holding member is a ring.
  • the figure5A illustrates a first ring 121 attached to the shaft Ar of the turbine and thus secured in rotation with the shaft Ar of the turbine. It is fixed by means of a system 3 with screws and nuts to the shaft of the turbine Ar and more particularly to an apparent surface element 21 of the shaft Ar.
  • the first ring 121 has a shoulder 1212 on the outer surface 1211 of the first ring 121.
  • the Figure 5B is the first ring 121. It has holes 3 of the screw system and nuts for fixing the first ring to the turbine shaft. Also visible are passage holes 4 of a system for fixing a second ring to the first ring.
  • the first ring has a shoulder 1212 protruding on the outer surface 1211 of the first ring.
  • the outer surface 1211 is the surface which will be facing the locking surface of the holding member once the latter has been positioned relative to the first ring 121 and will be described with reference to the following figures.
  • the shoulder 1212 is circular and its diameter is smaller than the diameter of the first ring. Its function is to allow the positioning of the holding element and its centering.
  • the Figure 6A illustrates a holding member 11 positioned on the shoulder 1212 of the first ring 121, the first ring being fixed to the shaft Ar of the turbine.
  • the radial movements of the holding member 11 are blocked.
  • the axial movements towards the motor of the holding element 11 are blocked by the surface S of the first ring against which it bears.
  • the holding element comprises a blocking surface 111 whose function is to block the blades A in axial translation along their insertion axis in their respective cells in the direction of their removal, i.e. their extraction of the cells.
  • This axis is inclined relative to the shaft of the turbine Ar, which is the axis of rotation of the motor. This inclination has the function of allowing the maintenance of the blades during the high speed rotation of the turbine.
  • the Figure 6B is the holding member 11.
  • the locking surface 111 is constituted by the entire holding member except the dispensing opening 112, which is a notch in this embodiment.
  • the dimensions of the deposit opening 112, by which is deposited, ie totally extracted, the blade to be deposited, are a function of the geometry of the blade to be deposited.
  • the dispensing aperture 112 is here at the periphery of the holding element 11, so the dispensing opening 112 is also open towards the outside of the periphery of the holding element 11 and has this notch shape and can pass thus only the foot of dawn.
  • the holding element 11 of the Figure 6B comprises five access openings 113. These access openings 113 allow an operator to access, for example by means of his thumb, an area of the space 114 defined opposite the blocking surface (refer to FIG. the Figure 6A ) so as to catch the foot of the dawn in order to partially extract the dawn. This partial extraction can also be performed by means of the dispensing aperture 112, but in this case, it is necessary to rotate the holding element each time to put the dispensing opening 112 next to each blade, some after others.
  • the Figure 7A illustrates the removal system, once a second ring 122 attached to the first ring 121 by means of wing screws 4, chosen for their ease of tightening / loosening.
  • the superposition of the first ring 121 and the second ring 122 forms a circular groove 123 for holding and the rotational drive of the holding member 11 relative to the shaft of the turbine Ar.
  • the circular groove is formed by the shoulder 1212 of the first ring, the outer surface 1211 of the first ring facing the surface of the locking 111 of the holding member and the second ring 122.
  • the holding element 11 comprises a stop 1111 on the blocking surface 111.
  • This abutment makes it possible to adjust the axial retention of the blades and the dimensioning of this abutment is a function of the distance from which the vanes of their cells must be partially extracted before it can be deposited by the opening 112.
  • the first ring / second ring assembly forms the fastening means 12 of the holding element 11 on the shaft Ar of the turbine. Thanks to the circular groove formed by the superimposition of the first and second ring in which the holding element is located, a pivot connection is formed between the holding element and the shaft Ar of the turbine.
  • the Figure 7B illustrates the second ring 122 having passage holes 5 for thumb screws 4 for fixing the second ring to the first ring.
  • the operator rotates the holding member around the blade.
  • turbine shaft in order to bring the dispensing aperture opposite each vane to be deposited in order to extract it completely from its cell by passing it through the dispensing opening since it is no longer blocked by the surface of the locking of the holding element.
  • the holding element having several angular positions depending on the blade to be deposited.
  • the blocking surface ensures the maintenance of the blades not deposited safely.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

DOMAINE TECHNIQUE DE L'INVENTIONTECHNICAL FIELD OF THE INVENTION

L'invention se rapporte à un dispositif de dépose d'au moins une aube d'une turbine ; à un système de dépose d'au moins une aube d'une turbine, à un procédé de montage d'un tel dispositif de dépose et également à un procédé de dépose d'au moins une aube de turbine.The invention relates to a device for depositing at least one blade of a turbine; a system for removing at least one blade of a turbine, a method of mounting such a dispensing device and also a method of removing at least one turbine blade.

L'invention se rapporte plus particulièrement au domaine des turbines de moteur d'aéronefs, et en particulier des turbines haute pression.The invention relates more particularly to the field of aircraft engine turbines, and in particular high pressure turbines.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

La figure 1 illustre de façon schématique une coupe générale d'un moteur d'aéronef et les différentes parties dudit moteur. L'air entrant par l'entrée d'air de la partie ADMISSION de la section froide est comprimé dans un compresseur (partie COMPRESSION sur la figure 1) avant d'être mélangé à un carburant et brûlé dans une des chambres de combustion de la partie COMBUSTION. Les gaz chauds produits dans la chambre de combustion atteignent les aubes de la turbine et entraînent la turbine (ou plusieurs turbines) puis sont éjectés au niveau de la partie ECHAPPEMENT du moteur ce qui engendre une poussée entrainant l'aéronef. Un étage de turbine est généralement constitué d'un aubage fixe suivi d'un aubage mobile. Une turbine peut comporter un ou plusieurs étages. L'invention concerne plus particulièrement la dépose de l'aubage mobile de la turbine.The figure 1 schematically illustrates a general section of an aircraft engine and the different parts of said engine. The air entering through the air inlet of the ADMISSION part of the cold section is compressed in a compressor (COMPRESSION part on the figure 1 ) before being mixed with a fuel and burned in one of the combustion chambers of the COMBUSTION part. The hot gases produced in the combustion chamber reach the vanes of the turbine and drive the turbine (or several turbines) and are ejected at the EXHAUST portion of the engine which generates a thrust causing the aircraft. A turbine stage generally consists of a fixed blade followed by a moving blade. A turbine may comprise one or more stages. The invention relates more particularly to the removal of the mobile blade of the turbine.

Des opérations de maintenance sur ces moteurs d'aéronefs s'effectuent lorsque le moteur est à l'horizontale avec sa turbine, contrairement aux opérations initiales d'assemblage qui sont généralement réalisées à la verticale. Ainsi la dépose des aubes mobiles de la turbine HP s'effectue généralement in situ, i.e. lorsque le moteur reste à l'horizontale avec sa turbine.Maintenance operations on these aircraft engines are carried out when the engine is horizontal with its turbine, unlike the initial assembly operations that are usually performed vertically. Thus the removal of the blades of the HP turbine is generally performed in situ, i.e. when the engine remains horizontal with its turbine.

L'axe d'insertion des aubes dans les alvéoles de la turbine dans lesquelles elles sont reçues étant incliné par rapport à l'axe moteur afin de contribuer au maintien des aubes entre elles lors de la rotation à grande vitesse de la turbine, la dépose des aubes se fait progressivement et radialement en ellipse. L'inclinaison de l'axe d'insertion des aubes par rapport à l'axe moteur peut être d'une trentaine de degrés par exemple. La figure 2 permet de visualiser l'inclinaison d'un angle α de l'axe d'insertion Xi d'une aube A par rapport à l'arbre de la turbine Ar (arbre de la turbine et axe moteur sont confondus).The axis of insertion of the vanes into the cells of the turbine in which they are received is inclined with respect to the motor axis in order to contribute to the maintenance of the vanes between them during the high speed rotation of the turbine, the removal blades are progressively and radially elliptical. The inclination of the axis of insertion of the blades with respect to the motor axis can be about thirty degrees for example. The figure 2 allows to visualize the inclination of an angle α of the insertion axis Xi of a blade A with respect to the shaft of the turbine Ar (turbine shaft and motor shaft are combined).

La dépose des aubes, tout comme la pose, se fait progressivement du fait de la géométrie des pieds d'aubes (à cause de l'inclinaison par rapport à l'axe moteur mentionnée précédemment) et du jeu très faible, voire quasiment inexistant entre les aubes. Une chemise d'étanchéité est en outre généralement intercalée entre deux aubes successives afin de réduire quasiment à néant le jeu entre les aubes. Le retrait se fait progressivement, i.e. aube après aube, petite distance par petite distance jusqu'à ce que chaque aube ne soit plus maintenue que par quelques millimètres dans l'alvéole dans laquelle son pied est inséré. Ces quelques millimètres, par exemple deux millimètres, permettent d'avoir un jeu suffisant entre les aubes pour pouvoir les extraire une à une.The removal of the blades, just like the installation, is done progressively because of the geometry of the blade roots (because of the inclination with respect to the motor axis mentioned above) and the very weak or almost non-existent game between the blades. A sealing liner is furthermore generally inserted between two successive blades in order to reduce almost completely the clearance between the vanes. The withdrawal is gradual, i.e. dawn after dawn, small distance a short distance until each dawn is maintained only a few millimeters in the cell in which his foot is inserted. These few millimeters, for example two millimeters, allow to have a sufficient clearance between the blades to extract them one by one.

Lors de leur retrait progressif, il arrive un moment où toutes les aubes sont maintenues par seulement quelques millimètres dans leurs alvéoles respectives. Ce moment est critique du fait de la position horizontale de la turbine. En effet, les aubes étant retenues dans leurs alvéoles respectives par seulement quelques millimètres, la dépose finale qui consiste à extraire complètement l'une après l'autre chacune des aubes de leur alvéole respective (ou bien une seule aube si une seule aube doit être déposée) doit intervenir rapidement et avec suffisamment de sécurité de façon à maintenir l'intégrité du matériel. Il est à noter que généralement les turbines comportent plusieurs dizaines d'aubes et une voire deux personnes au maximum participent à l'opération de dépose. Il n'est donc pas possible pour une personne de maintenir toutes les aubes en même temps.During their gradual withdrawal, there comes a time when all the blades are held by only a few millimeters in their respective cells. This moment is critical because of the horizontal position of the turbine. Indeed, the blades being retained in their respective cells by only a few millimeters, the final removal which consists in completely extracting one after the other each blade of their respective cell (or a single blade if a single blade must be filed) must respond quickly and with sufficient security to maintain the integrity of the equipment. It should be noted that generally the turbines have several dozen blades and one or two people at most participate in the removal operation. It is therefore not possible for a person to maintain all the blades at the same time.

En cas de fausse manœuvre, de choc, de vibration, par exemple, une partie des aubes risque de tomber et de se détériorer ou bien encore de choquer et d'abimer d'autres pièces du moteur comme le tourillon proche des aubes. La détérioration la plus minime de ce type de pièce nécessite son changement ce qui a pour conséquence d'engendrer des coûts importants. EP0745756 montre un dispositif de montage d'aubes.In case of false maneuver, shock, vibration, for example, some of the blades may fall and deteriorate or even shock and damage other parts of the engine as the trunnion close to the blades. The slightest deterioration of this type of room necessitates its change, which results in significant costs. EP0745756 shows a blade mounting device.

EXPOSE DE L'INVENTIONSUMMARY OF THE INVENTION

L'invention vise à remédier à tout ou partie des inconvénients de l'état de la technique identifiés ci-dessus, et notamment à proposer des moyens pour permettre de sécuriser la dépose des aubes en limitant au maximum le risque de chute d'aubes lors d'opération en position horizontale du moteur.The invention aims to remedy all or some of the disadvantages of the state of the art identified above, and in particular to propose means for to make it possible to secure the removal of the blades by limiting as much as possible the risk of falling blades during operation in the horizontal position of the engine.

Dans ce dessein, un aspect de l'invention se rapporte à un dispositif de dépose d'au moins une aube d'une turbine décrit dans la revendication 1.For this purpose, one aspect of the invention relates to a device for depositing at least one blade of a turbine described in claim 1.

Un tel dispositif permet avantageusement de bloquer, de préférentiellement axialement, i.e. selon une direction parallèle à l'arbre de la turbine, les aubes de la turbine lorsque celles-ci ne sont plus retenues dans leurs alvéoles respectives que par quelques millimètres i.e. lorsqu'elles sont prêtes à être déposées. Ainsi lors de la dépose in situ, lorsque le moteur est à l'horizontale avec sa turbine, il n'y a plus de risque pour une aube de turbine de tomber juste avant la dépose en elle-même (retrait de l'aube de son alvéole).Such a device advantageously makes it possible to block, preferably axially, ie in a direction parallel to the shaft of the turbine, the vanes of the turbine when they are no longer retained in their respective cells by a few millimeters ie when they are are ready to be deposited. Thus during the in situ removal, when the engine is horizontal with its turbine, there is more risk for a turbine blade to fall just before removal in itself (withdrawal of the blade of its alveolus).

Ainsi un opérateur seul, peut travailleur sur la turbine et dégager partiellement, graduellement et en ellipse chacune des aubes sans avoir à les tenir manuellement lorsqu'elles ne sont plus retenues que par quelques millimètres dans leurs alvéoles respectives. La surface de blocage empêche les aubes de tomber.Thus a single operator can work on the turbine and partially, gradually and ellipse each of the blades without having to hold them manually when they are no longer retained by a few millimeters in their respective cells. The blocking surface prevents the blades from falling.

L'ouverture de dépose peut être une encoche pratiquée dans l'élément de maintien. Le dimensionnement de l'ouverture de dépose est lié à la hauteur de la partie de l'aube prise dans son alvéole afin d'assurer son extraction de ladite alvéole. L'ouverture de dépose permet de s'affranchir des aléas propres à l'environnement où a lieu la dépose de l'aube du type position horizontale du moteur ou module, risque de contact entre opérateurs et donc chute d'une ou plusieurs aubes, petits chocs ou efforts répétés pour sortir chaque aube de son logement, instabilité possible du sol, chocs sur le moteur.The removal opening may be a notch made in the holding element. The sizing of the dispensing aperture is related to the height of the portion of the blade taken in its cell to ensure its extraction from said cell. The removal opening makes it possible to get rid of hazards specific to the environment where the removal of the blade of the horizontal type of the engine or module takes place, risk of contact between operators and therefore a fall of one or several blades, small shocks or repeated efforts to exit each dawn of his home, possible instability of the ground, shocks on the engine.

L'élément de maintien est préférentiellement fixé au moyeu/tourillon de la turbine.The holding element is preferably fixed to the hub / trunnion of the turbine.

La définition d'une position angulaire de l'élément de maintien peut se faire en faisant tourner l'élément de maintien manuellement autour de l'arbre de la turbine du fait de la liaison pivot. Ainsi lorsque toutes les aubes ne sont plus retenues que par quelques millimètres dans leurs alvéoles respectives et que le jeu entre deux aubes est suffisant pour la dépose d'une aube, la mise en regard de l'ouverture de dépose avec l'aube à déposer permet à un opérateur d'accéder à cette aube qui n'est pas bloquée par la surface de blocage. Les autres aubes sont quant à elles maintenues grâce à la surface de blocage et ne risquent pas de chuter en cas de secousse, fausse manœuvre ou autre accident.The definition of an angular position of the holding member can be done by rotating the holding member manually around the turbine shaft due to the pivot connection. Thus when all the vanes are retained only by a few millimeters in their respective cells and that the clearance between two blades is sufficient for the removal of a blade, the setting compared to the opening of deposit with the dawn to deposit allows an operator to access this blade which is not blocked by the blocking surface. The other blades are maintained thanks to the blocking surface and are not likely to drop in the event of a jolt, mishandling or other accident.

Outre les caractéristiques principales qui viennent d'être mentionnées dans le paragraphe précédent, le dispositif selon l'invention peut présenter une ou plusieurs caractéristiques complémentaires parmi les suivantes, considérées individuellement ou selon les combinaisons techniquement possibles :

  • l'ouverture de dépose est en périphérie de l'élément de maintien. L'aube étant située en périphérie de la turbine, l'ouverture de dépose est ainsi préférentiellement située au droit du pied de l'aube à extraire et de la partie de l'élément de maintien servant de butée de maintien, i.e. la surface de blocage ;
  • l'élément de maintien comporte au moins une ouverture d'accès permettant à un opérateur d'accéder à une zone de l'espace définie en regard de la surface de blocage. L'élément de maintien peut comporter une pluralité d'ouvertures d'accès réparties sur l'élément de maintien. Elles permettent à un opérateur d'accéder manuellement aux aubes de turbine afin de faciliter leur extraction des alvéoles ;
  • l'élément de maintien est un anneau ;
  • les moyens de fixation comportent un premier anneau, un deuxième anneau, la superposition des premier et deuxième anneaux formant une rainure circulaire pour le maintien de l'élément de maintien et pour l'entrainement en rotation de l'élément de maintien par rapport à l'arbre de la turbine. L'élément de maintien est ainsi pris en sandwich entre les premier et deuxième anneaux dans la rainure circulaire ainsi formée et qui concoure à la fois à son maintien et à la réalisation de la liaison pivot entre l'élément de maintien et l'arbre de la turbine. Pour ce faire, le premier anneau peut être rendu solidaire en rotation de l'arbre de la turbine et le deuxième anneau être fixé au premier anneau ;
  • le premier anneau comporte une surface extérieure, ladite surface extérieure étant en regard de la surface de blocage et ladite surface extérieure comportant un épaulement formant saillie dont le diamètre est inférieur au diamètre du premier anneau. L'épaulement formant saillie contribue avantageusement au centrage de l'élément de maintien par rapport à l'arbre de la turbine et aux aubes. L'épaulement est préférentiellement circulaire lorsque l'élément de maintien est un anneau ;
  • la surface de blocage comporte au moins une butée permettant un ajustement du blocage des aubes. La butée permet avantageusement de régler le blocage axial des aubes. L'épaisseur de la butée, i.e. sa dimension selon l'arbre de la turbine, est préférentiellement égale à la valeur critique avant décochement. Cette valeur critique correspond à la longueur du pied d'aube nécessairement encore dans son alvéole au-delà de laquelle la moindre secousse occasionne une chute de l'aube et au-delà de laquelle le jeu entre aubes est suffisant pour pouvoir les déposer une à une. Il est à noter que généralement entre deux aubes adjacentes sont intercalées des chemises d'étanchéité pour limiter le jeu entre aubes afin de contribuer à leur maintien lors du fonctionnement de la turbine. La chemise d'étanchéité est une cale d'épaisseur amortissante entre chaque aube. ; et
  • l'ouverture de dépose est adaptée au passage d'une aube mobile d'une turbine haute pression d'un aéronef. Les dimensions de l'ouverture de dépose sont calculées pour permettre le passage d'une telle aube, et de préférence une seule.
In addition to the main features which have just been mentioned in the preceding paragraph, the device according to the invention may have one or more additional characteristics among the following, considered individually or according to the technically possible combinations:
  • the removal opening is at the periphery of the holding element. As the blade is located at the periphery of the turbine, the removal opening is thus preferably located at the right of the root of the blade to be extracted and the part of the holding element serving as a holding stop, ie the surface of blocking;
  • the holding element comprises at least one access opening allowing an operator to access an area of the defined space facing the blocking surface. The holding member may include a plurality of access openings distributed over the holding member. They allow an operator to manually access the turbine blades to facilitate their extraction of the cells;
  • the holding member is a ring;
  • the fixing means comprise a first ring, a second ring, the superposition of the first and second rings forming a circular groove for holding the holding member and for rotating the holding member with respect to the 'tree of the turbine. The holding element is thus sandwiched between the first and second rings in the circular groove thus formed and which contributes to both its maintenance and the realization of the pivot connection between the holding member and the shaft of the turbine. To do this, the first ring can be made integral in rotation with the turbine shaft and the second ring be fixed to the first ring;
  • the first ring has an outer surface, said outer surface facing the locking surface and said outer surface having a projection shoulder whose diameter is smaller than the diameter of the first ring. The protruding shoulder advantageously contributes to the centering of the holding element relative to the turbine shaft and the blades. The shoulder is preferably circular when the holding member is a ring;
  • the blocking surface comprises at least one stop allowing an adjustment of the blocking of the blades. The stop advantageously makes it possible to adjust the axial blocking of the blades. The thickness of the abutment, ie its dimension according to the shaft of the turbine, is preferably equal to the critical value before unplugging. This critical value corresponds to the length of the dawn foot necessarily still in its cell beyond which the slightest jolt causes a fall of the dawn and beyond which the play between blades is sufficient to be able to deposit them one to a. It should be noted that generally between two adjacent blades are interposed sealing sleeves to limit the clearance between blades to help maintain them during operation of the turbine. The sealing liner is a damping shim between each blade. ; and
  • the dispensing aperture is adapted to the passage of a blade of a high-pressure turbine turbine of an aircraft. The dimensions of the dispensing aperture are calculated to allow the passage of such a blade, and preferably only one.

L'invention se rapporte également à un système de dépose d'au moins une aube d'une turbine, ladite turbine comportant un ensemble de N aubes, ledit système comportant un dispositif de dépose selon l'un des modes de réalisation précédemment décrits, un arbre de la turbine, le premier anneau étant fixé à l'arbre de la turbine de sorte qu'il est solidaire en rotation de l'arbre de la turbine et l'élément de maintien étant libre en rotation par rapport à l'arbre de la turbine dans la rainure circulaire.The invention also relates to a system for depositing at least one blade of a turbine, said turbine comprising a set of N blades, said system comprising a dispensing device according to one of the previously described embodiments, a shaft of the turbine, the first ring being fixed to the shaft of the turbine so that it is integral in rotation with the shaft of the turbine and the holding member being free to rotate relative to the turbine shaft in the circular groove.

L'invention se rapporte également à un procédé de montage d'un dispositif de dépose selon l'un des modes de réalisation précédemment décrit sur un arbre de turbine, ledit procédé comportant :

  • une étape de fixation du premier anneau sur un arbre de la turbine de façon à rendre solidaire en rotation le premier anneau de l'arbre de la turbine ;
  • une étape de positionnement de l'élément de maintien sur l'épaulement du premier anneau de façon à bloquer les mouvements radiaux de l'élément de maintien ;
  • une étape de fixation du deuxième anneau au premier anneau de façon à bloquer les mouvements axiaux de l'élément de maintien.
The invention also relates to a method of mounting a dispensing device according to one of the previously described embodiments on a turbine shaft, said method comprising:
  • a step of fixing the first ring on a shaft of the turbine so as to make the first ring of the turbine shaft integral in rotation;
  • a step of positioning the holding member on the shoulder of the first ring so as to block the radial movements of the holding member;
  • a step of fixing the second ring to the first ring so as to block the axial movements of the holding member.

Outre les caractéristiques principales qui viennent d'être mentionnées dans le paragraphe précédent, le procédé selon l'invention peut présenter une ou plusieurs caractéristiques complémentaires parmi les suivantes, considérées individuellement ou selon les combinaisons techniquement possibles :

  • l'étape de fixation du premier anneau se fait sur un élément de surface apparent de l'arbre de la turbine, ledit arbre de la turbine étant un tourillon ; et
  • l'étape de fixation du deuxième anneau se fait au moyen de vis à oreilles. L'utilisation de vis à oreilles permet de faciliter l'utilisation du dispositif. En effet, il n'est pas nécessaire d'avoir des outils de serrage pour le montage/démontage. Un tel type de vis peut également être utilisé pour la fixation du premier anneau à l'arbre de la turbine.
  • Le procédé peut également comporter une étape supplémentaire consistant à placer un manchon ou cache rigide pour protéger l'arbre de la turbine et plus particulièrement son tourillon si malgré le dispositif une aube venait quand même à tomber sur le tourillon ce qui nécessiterait son remplacement.
In addition to the main features that have just been mentioned in the preceding paragraph, the method according to the invention may have one or more additional characteristics among the following, considered individually or according to the technically possible combinations:
  • the step of fixing the first ring is done on an apparent surface element of the turbine shaft, said shaft of the turbine being a trunnion; and
  • the fixing step of the second ring is by means of thumb screws. The use of thumb screws facilitates the use of the device. Indeed, it is not necessary to have clamping tools for assembly / disassembly. Such a type of screw can also be used for fixing the first ring to the shaft of the turbine.
  • The method may also include an additional step of placing a sleeve or rigid cover to protect the turbine shaft and more particularly its trunnion if despite the device a dawn was still falling on the trunnion which would require its replacement.

L'invention se rapporte également à un procédé de dépose d'au moins une aube de turbine, ladite turbine comportant un ensemble d'aubes, ledit procédé comportant :

  • une étape de montage d'un dispositif de dépose selon un des modes de réalisation précédemment décrit sur un arbre de la turbine ;
  • une étape d'extraction partielle de l'ensemble d'aubes au moyen d'un accès par l'intermédiaire soit de l'ouverture de dépose soit de l'ouverture d'accès ; et
  • une étape de positionnement de l'élément de maintien selon une première position angulaire de façon à positionner l'ouverture de dépose en regard d'au moins une aube à déposer.
The invention also relates to a method of depositing at least one turbine blade, said turbine comprising a set of blades, said method comprising:
  • a mounting step of a dispensing device according to one of the embodiments previously described on a shaft of the turbine;
  • a step of partially extracting the set of blades by means of access via either the dispensing opening or the access opening; and
  • a step of positioning the holding element in a first angular position so as to position the removal aperture facing at least one blade to be deposited.

Un opérateur, pour accéder aux aubes et les extraire partiellement graduellement, en ellipse de leurs alvéoles respectives peut soit s'aider de l'ouverture de dépose, et dans ce cas faire tourner l'élément de maintien afin de mettre en regard l'ouverture de dépose de chaque aube petit à petit ; soit utiliser l'ouverture d'accès, ou la pluralité d'ouverture d'accès. Pour la dépose d'une aube, il est nécessaire de placer l'ouverture de dépose en regard de cette aube afin de pouvoir la faire passer au travers, sinon elle est bloquée par la surface de blocage.An operator, to access the blades and extract them partially gradually, in ellipse of their respective cells can either help the opening of removal, and in this case rotate the holding element to put the aperture drop off each dawn little by little; either use the access opening, or the plurality of access openings. For the removal of a blade, it is necessary to place the removal aperture facing this blade in order to be able to pass through it, otherwise it is blocked by the blocking surface.

Outre les caractéristiques principales qui viennent d'être mentionnées dans le paragraphe précédent, le procédé selon l'invention peut présenter la caractéristique complémentaire suivante : l'étape d'extraction partielle se fait par une pluralité de déplacements axiaux successifs de chacune des aubes de l'ensemble d'aubes de façon à positionner les dites aubes en butée contre la surface de blocage. L'extraction partielle se fait aube par aube en tournant tout le long de la turbine et en recommençant cette opération jusqu'à ce que la dimension d'aube, et plus particulièrement de pied d'aube, en dehors de l'alvéole correspondante soit suffisante pour que le jeu entre aubes permette la dépose d'une aube. Dans ce cas, les aubes sont en butée contre la surface de blocage.In addition to the main features which have just been mentioned in the preceding paragraph, the method according to the invention may have the following additional characteristic: the partial extraction step is carried out by a plurality of successive axial displacements of each of the blades of the set of vanes so as to position said vanes abutting against the blocking surface. The partial extraction is done by dawn by rotating all along the turbine and by repeating this operation until the blade dimension, and more particularly the blade root, outside the corresponding cell is sufficient for the game between blades allows the removal of a blade. In this case, the blades are in abutment against the blocking surface.

BREVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF THE FIGURES

D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description qui suit, en référence aux figures annexées, qui illustrent :

  • la figure 1, une vue en coupe d'un moteur de turbine ;
  • la figure 2,
  • la figure 3, un système de dépose selon un mode de réalisation de l'invention, la turbine étant à la verticale ;
  • la figure 4, le système de dépose de la figure 1, la turbine étant à l'horizontale ;
  • la figure 5A, une vue de côté d'un arbre de turbine et d'un premier anneau rendu solidaire de l'arbre de turbine selon un mode de réalisation de l'invention ;
  • la figure 5B, une vue de face d'un premier anneau selon un mode de réalisation de l'invention ;
  • la figure 6A, une vue de côté d'un arbre de turbine, d'un premier anneau rendu solidaire de l'arbre de turbine et d'un élément de maintien positionné sur le premier anneau selon un mode de réalisation de l'invention ;
  • la figure 6B, une vue de face d'un élément de maintien selon un mode de réalisation de l'invention ;
  • la figure 7A, une vue de côté d'un système de dépose selon un mode de réalisation de l'invention ;
  • la figure 7B, une vue de face d'un deuxième anneau selon un mode de réalisation de l'invention.
Other characteristics and advantages of the invention will emerge on reading the description which follows, with reference to the appended figures, which illustrate:
  • the figure 1 a sectional view of a turbine engine;
  • the figure 2 ,
  • the figure 3 , a depositing system according to one embodiment of the invention, the turbine being vertical;
  • the figure 4 , the deposit system of the figure 1 the turbine being horizontal;
  • the Figure 5A , a side view of a turbine shaft and a first ring secured to the turbine shaft according to one embodiment of the invention;
  • the Figure 5B a front view of a first ring according to one embodiment of the invention;
  • the Figure 6A , a side view of a turbine shaft, a first ring secured to the turbine shaft and a holding member positioned on the first ring according to one embodiment of the invention;
  • the Figure 6B a front view of a holding element according to one embodiment of the invention;
  • the Figure 7A a side view of a dispensing system according to one embodiment of the invention;
  • the Figure 7B , a front view of a second ring according to one embodiment of the invention.

Pour plus de clarté, les éléments identiques ou similaires sont repérés par des signes de référence identiques sur l'ensemble des figures.For the sake of clarity, identical or similar elements are marked with identical reference signs throughout the figures.

DESCRIPTION DETAILLEE D'UN MODE DE REALISATIONDETAILED DESCRIPTION OF AN EMBODIMENT

La figure 1 illustre une vue en coupe d'un moteur d'aeronefThe figure 1 illustrates a sectional view of an aircraft engine

Aux figures 3 et 4 est illustré un système de dépose d'une aube A d'une turbine, la turbine comportant un ensemble d'aubes A. Le système de dépose comporte un dispositif de dépose 1 et un arbre de turbine Ar, ici un tourillon.To the Figures 3 and 4 is illustrated a depositing system of a blade A of a turbine, the turbine comprising a set of vanes A. The dispensing system comprises a dispensing device 1 and a turbine shaft Ar, here a journal.

La figure 3 illustre le système de dépose dans une configuration à la verticale de la turbine. Ce type de configuration est généralement adopté pour la pose des aubes. Les aubes étant déposées axialement dans leurs alvéoles respectives (alvéoles non visibles sur la photo) selon l'axe X1, il est visible que dans cette configuration dite verticale, aucun risque de chute en cas de secousse, choc n'est à craindre. Pour rappel, les aubes sont posées (et déposées) graduellement, les unes après les autres, de façon elliptique millimètres par millimètres. Dans la configuration verticale, une aube dont le pied est inséré de seulement un ou deux millimètre dans son alvéole ne risque donc pas de tomber.The figure 3 illustrates the dispensing system in a vertical configuration of the turbine. This type of configuration is generally adopted for the set of blades. The vanes being deposited axially in their respective cells (cells not visible in the photo) along the axis X1, it is visible that in this so-called vertical configuration, no risk of falling in case of shock, shock is to be feared. As a reminder, the blades are placed (and deposited) gradually, one after the other, elliptically millimeters by millimeters. In the vertical configuration, a blade whose foot is inserted only one or two millimeters into its cell will not fall.

La figure 4 illustre le système de dépose de la figure 1 dans une configuration à l'horizontale de la turbine. Cette configuration est généralement utilisée pour une dépose in-situ des aubes. Dans cette configuration, une aube dont le pied est inséré de seulement un ou deux millimètres dans son alvéole, juste avant la dépose (qui est l'extraction totale de l'aube de son alvéole selon l'axe X2) risque de tomber sans le dispositif de dépose 1 dont le fonctionnement va être expliqué plus en détail en référence aux figures suivantes.The figure 4 illustrates the removal system of the figure 1 in a horizontal configuration of the turbine. This configuration is generally used for in-situ blade removal. In this configuration, a blade whose foot is inserted only one or two millimeters into its cell, just before removal (which is the total extraction of the blade of its cell along the axis X2) may fall without the removal device 1 whose operation will be explained in more detail with reference to the following figures.

Dans les modes de réalisation décrits en référence aux figures suivantes, à savoir les figures 5A à 7B, l'élément de maintien est un anneau.In the embodiments described with reference to the following figures, namely the FIGS. 5A to 7B , the holding member is a ring.

La figure5A illustre un premier anneau 121 fixé à l'arbre Ar de la turbine et ainsi rendu solidaire en rotation de l'arbre Ar de la turbine. Il est fixé au moyen d'un système 3 à vis et écrous à l'arbre de la turbine Ar et plus particulièrement à un élément de surface apparent 21 de l'arbre Ar. Le premier anneau 121 comporte un épaulement 1212 sur la surface extérieure 1211 du premier anneau 121.The figure5A illustrates a first ring 121 attached to the shaft Ar of the turbine and thus secured in rotation with the shaft Ar of the turbine. It is fixed by means of a system 3 with screws and nuts to the shaft of the turbine Ar and more particularly to an apparent surface element 21 of the shaft Ar. The first ring 121 has a shoulder 1212 on the outer surface 1211 of the first ring 121.

La figure 5B représente le premier anneau 121. Il comporte des trous de passage 3 du système de vis et écrous pour la fixation du premier anneau à l'arbre de turbine. Sont visibles également des trous de passage 4 d'un système de fixation d'un deuxième anneau au premier anneau. Le premier anneau comporte un épaulement 1212 formant saillie sur la surface externe 1211 du premier anneau. La surface externe 1211 est la surface qui sera en regard de la surface de blocage de l'élément de maintien une fois ce dernier positionné par rapport au premier anneau 121 et sera décrite en référence aux figures suivantes.The Figure 5B is the first ring 121. It has holes 3 of the screw system and nuts for fixing the first ring to the turbine shaft. Also visible are passage holes 4 of a system for fixing a second ring to the first ring. The first ring has a shoulder 1212 protruding on the outer surface 1211 of the first ring. The outer surface 1211 is the surface which will be facing the locking surface of the holding member once the latter has been positioned relative to the first ring 121 and will be described with reference to the following figures.

L'épaulement 1212 est circulaire et son diamètre est inférieur au diamètre du premier anneau. Il a pour fonction de permettre le positionnement de l'élément de maintien et son centrage.The shoulder 1212 is circular and its diameter is smaller than the diameter of the first ring. Its function is to allow the positioning of the holding element and its centering.

La figure 6A illustre un élément de maintien 11 positionné sur l'épaulement 1212 du premier anneau 121, le premier anneau étant fixé à l'arbre Ar de la turbine. Ainsi positionné, les mouvements radiaux de l'élément de maintien 11 sont bloqués. En outre les mouvements axiaux vers le moteur de l'élément de maintien 11 sont bloqués par la surface S du premier anneau contre lequel il vient en appui.The Figure 6A illustrates a holding member 11 positioned on the shoulder 1212 of the first ring 121, the first ring being fixed to the shaft Ar of the turbine. Thus positioned, the radial movements of the holding member 11 are blocked. In addition, the axial movements towards the motor of the holding element 11 are blocked by the surface S of the first ring against which it bears.

L'élément de maintien comporte une surface de blocage 111 qui a pour fonction de bloquer les aubes A en translation axiale selon leur axe d'insertion dans leurs alvéoles respectives dans le sens de leur dépose, i.e. de leur extraction des alvéoles. Cet axe est incliné par rapport à l'arbre de la turbine Ar, qui est l'axe de rotation du moteur. Cette inclinaison a pour fonction de permettre le maintien des aubes lors de la rotation à grande vitesse de la turbine.The holding element comprises a blocking surface 111 whose function is to block the blades A in axial translation along their insertion axis in their respective cells in the direction of their removal, i.e. their extraction of the cells. This axis is inclined relative to the shaft of the turbine Ar, which is the axis of rotation of the motor. This inclination has the function of allowing the maintenance of the blades during the high speed rotation of the turbine.

La figure 6B représente l'élément de maintien 11. La surface de blocage 111 est constituée par l'ensemble de l'élément de maintien exceptée l'ouverture de dépose 112, qui est une encoche dans ce mode de réalisation. Les dimensions de l'ouverture de dépose 112, par laquelle est déposée, i.e. extraite totalement, l'aube à déposer, sont fonction de la géométrie de l'aube à déposer. L'ouverture de dépose 112 est ici en périphérie de l'élément de maintien 11, ainsi l'ouverture de dépose 112 est ouverte également vers l'extérieur de la périphérie de l'élément de maintien 11 et a cette forme d'encoche et peut laisser passer ainsi seulement le pied de l'aube.The Figure 6B is the holding member 11. The locking surface 111 is constituted by the entire holding member except the dispensing opening 112, which is a notch in this embodiment. The dimensions of the deposit opening 112, by which is deposited, ie totally extracted, the blade to be deposited, are a function of the geometry of the blade to be deposited. The dispensing aperture 112 is here at the periphery of the holding element 11, so the dispensing opening 112 is also open towards the outside of the periphery of the holding element 11 and has this notch shape and can pass thus only the foot of dawn.

L'élément de maintien 11 de la figure 6B comporte cinq ouvertures d'accès 113. Ces ouvertures d'accès 113 permettent à un opérateur d'accéder, par exemple au moyen de son pouce, à une zone de l'espace 114 définie en regard de la surface de blocage (se référer à la figure 6A) de façon à attraper le pied de l'aube afin d'extraire partiellement l'aube. Cette extraction partielle peut également être exécutée au moyen de l'ouverture de dépose 112, mais dans ce cas, il faut tourner l'élément de maintien à chaque fois pour mettre l'ouverture de dépose 112 en regard de chaque aube, les unes après les autres.The holding element 11 of the Figure 6B comprises five access openings 113. These access openings 113 allow an operator to access, for example by means of his thumb, an area of the space 114 defined opposite the blocking surface (refer to FIG. the Figure 6A ) so as to catch the foot of the dawn in order to partially extract the dawn. This partial extraction can also be performed by means of the dispensing aperture 112, but in this case, it is necessary to rotate the holding element each time to put the dispensing opening 112 next to each blade, some after others.

La figure 7A illustre le système de dépose, une fois un deuxième anneau 122 fixé au premier anneau 121 au moyen de vis à oreilles 4, choisies pour leur facilité de serrage/desserrage. La superposition du premier anneau 121 et du deuxième anneau 122 forme une rainure circulaire 123 pour le maintien et l'entrainement en rotation de l'élément de maintien 11 par rapport à l'arbre de la turbine Ar. La rainure circulaire est formée par l'épaulement 1212 du premier anneau, la surface extérieure 1211 du premier anneau en regard de la surface de blocage 111 de l'élément de maintien et le deuxième anneau 122.The Figure 7A illustrates the removal system, once a second ring 122 attached to the first ring 121 by means of wing screws 4, chosen for their ease of tightening / loosening. The superposition of the first ring 121 and the second ring 122 forms a circular groove 123 for holding and the rotational drive of the holding member 11 relative to the shaft of the turbine Ar. The circular groove is formed by the shoulder 1212 of the first ring, the outer surface 1211 of the first ring facing the surface of the locking 111 of the holding member and the second ring 122.

L'élément de maintien 11 comporte une butée 1111 sur la surface de blocage 111. Cette butée permet de régler le maintien axial des aubes et le dimensionnement de cette butée est fonction de la distance dont doivent être extraites partiellement les aubes de leurs alvéoles avant de pouvoir être déposer par l'ouverture de dépose 112.The holding element 11 comprises a stop 1111 on the blocking surface 111. This abutment makes it possible to adjust the axial retention of the blades and the dimensioning of this abutment is a function of the distance from which the vanes of their cells must be partially extracted before it can be deposited by the opening 112.

L'ensemble premier anneau/deuxième anneau forme les moyens de fixation 12 de l'élément de maintien 11 sur l'arbre Ar de la turbine. Grâce à la rainure circulaire formée par la superposition des premier et deuxième anneau dans laquelle se trouve l'élément de maintien, une liaison pivot est formée entre l'élément de maintien et l'arbre Ar de la turbine.The first ring / second ring assembly forms the fastening means 12 of the holding element 11 on the shaft Ar of the turbine. Thanks to the circular groove formed by the superimposition of the first and second ring in which the holding element is located, a pivot connection is formed between the holding element and the shaft Ar of the turbine.

La figure 7B illustre le deuxième anneau 122 comportant des trous de passage 5 pour les vis à oreille 4 permettant la fixation du deuxième anneau au premier anneau.The Figure 7B illustrates the second ring 122 having passage holes 5 for thumb screws 4 for fixing the second ring to the first ring.

Pour la dépose d'une aube, il est nécessaire dans un premier temps, une fois le dispositif de dépose installé, d'extraire partiellement chacune des aubes A :

  • soit en s'aidant des ouvertures d'accès de l'élément de maintien ;
  • soit en s'aidant de l'ouverture de dépose de l'élément de maintien, et dans ce cas, de faire tourner l'élément de maintien afin de mettre l'ouverture de dépose en regard à chaque fois de l'aube à manipuler.
For the removal of a blade, it is necessary initially, once the dispensing device installed, partially extract each blade A:
  • by using the access openings of the holding element;
  • either by using the opening for removing the holding element, and in this case, to rotate the holding element to bring the opening of deposit next to the dawn to handle .

Une fois les aubes au bord de la dépose, i.e. lorsqu'elles sont arrivées en butée contre la surface de blocage, qui les empêche de tomber en cas de secousse ou de choc, l'opérateur fait pivoter l'élément de maintien autour de l'arbre de la turbine afin d'amener l'ouverture de dépose en regard de chaque aube à déposer afin de l'extraire complètement de son alvéole en la faisant passer par l'ouverture de dépose car n'étant plus bloquée par la surface de blocage de l'élément de maintien. L'élément de maintien ayant plusieurs positions angulaires en fonction de l'aube à déposer. La surface de blocage assure le maintien des aubes non déposées en sécurité.Once the blades at the edge of removal, ie when they have come into abutment against the blocking surface, which prevents them from falling in case of shock or shock, the operator rotates the holding member around the blade. turbine shaft in order to bring the dispensing aperture opposite each vane to be deposited in order to extract it completely from its cell by passing it through the dispensing opening since it is no longer blocked by the surface of the locking of the holding element. The holding element having several angular positions depending on the blade to be deposited. The blocking surface ensures the maintenance of the blades not deposited safely.

L'invention n'est pas limitée aux modes de réalisation précédemment décrits en référence aux figures et des variantes pourraient être envisagées sans sortir du cadre de l'invention.The invention is not limited to the embodiments previously described with reference to the figures and variants could be envisaged without departing from the scope of the invention.

Claims (13)

  1. Device for dismantling (1) at least one blade (A) from a turbine, said turbine comprising a set of blades (A), each blade of said set of blades being retained in a cell of a set of turbine cells, said device comprising:
    - a holding element (11) comprising:
    - a blocking surface (111);
    - a dismantling opening (112);
    - means of attaching the holding element (11) to a shaft of the turbine, the attachment means producing a pivot connection between the holding element (11) and the shaft of the turbine (Ar),
    the defining of an angular position of the holding element (11) allowing a first function of partial extraction of at least one blade (A) of its cell facing the dismantling opening (112) and allowing a second function of blocking a set of blades (A) facing the blocking surface (111), the holding element (11) having at least one access opening (113) that allows an operator to access a zone of the space (114) defined facing the blocking surface (111).
  2. Dismantling device as claimed in any preceding claim characterised in that the dismantling opening (112) is at the periphery of the holding element (11).
  3. Dismantling device as claimed in any preceding claim characterised in that the holding element (11) is a ring.
  4. Dismantling device as claimed in any preceding claim characterised in that the attachment means comprise:
    - a first ring (121);
    - a second ring (122);
    the superposition of the first (121) and second (122) rings forming a circular groove (123) for the maintaining of the holding element (11) and for the driving in rotation of the holding element (11) with respect to the shaft of the turbine (Ar).
  5. Dismantling device as claimed in the preceding claim characterised in that the first ring (121) comprises an outer surface (1211), said outer surface (1211) facing the blocking surface (111) and said outer surface comprising a shoulder (1212) forming a projection of which the diameter is less than the diameter of the first ring.
  6. Dismantling device as claimed in any preceding claim characterised in that the blocking surface (111) comprises at least one abutment (1111) allowing for an adjustment of the blocking of the blades (A).
  7. Dismantling device as claimed in any preceding claim characterised in that the dismantling opening (112) is adapted to the passage of a mobile blade of a high pressure turbine of an aircraft.
  8. System for dismantling at least one blade (A) from a turbine, said turbine comprising a set of N blades (A), said system comprising:
    - a device for dismantling (1) according to any of claims 4 to 7;
    - a turbine shaft (Ar);
    characterised in that the first ring (121) is attached to the turbine shaft in such a way that it is integral in rotation with the turbine shaft and the holding element (11) is free in rotation with respect to the turbine shaft in the circular groove (23).
  9. Method for mounting a device for dismantling according to any of claims 5 to 7 on a turbine shaft, said method comprising:
    - a step of attaching the first ring (121) to a turbine shaft (Ar) in such a way as to make integral in rotation the first ring of the turbine shaft;
    - a step of positioning the holding element (11) on the shoulder (1212) of the first ring in such a way as to block the radial movements of the holding element (11);
    - a step of attaching the second ring (122) to the first ring (121) in such a way as to block the axial movements of the holding element.
  10. Method for mounting as claimed in the preceding claim characterised in that the step of attaching the first ring is carried out on an apparent surface element (21) of the turbine shaft, said turbine shaft being a trunnion.
  11. Method for mounting as claimed in any preceding claim characterised in that the step of attaching the second ring (122) is carried out by means of wing screws.
  12. Method for dismantling at least one turbine blade (A), said turbine comprising a set of N blades (A), said method comprising:
    - a step for mounting a device for dismantling (1) according to any of claims 1 to 7 on a turbine shaft (Ar);
    - a step of partially extracting the set of N adjacent blades (A) by means of an access by the intermediary either of the dismantling opening (112) or of the access opening (113); and
    - a step of positioning the holding element (11) according to a first angular position in such a way as to position the dismantling opening (112) facing at least one blade (A) to be dismantled.
  13. Method as claimed in the preceding claim characterised in that the step of partially extracting is carried out by a plurality of successive axial displacements of each one of the blades of the set of N blades (A) in such a way as to position said blades (A) in abutment against the blocking surface.
EP14747094.2A 2013-07-15 2014-07-10 Device to assemble blades and corresponding method for assembling Active EP3022405B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1356940A FR3008448B1 (en) 2013-07-15 2013-07-15 REMOVAL DEVICE FOR AUBES
PCT/FR2014/051774 WO2015007979A1 (en) 2013-07-15 2014-07-10 Dismantling device for blades and corresponding dismantling method

Publications (2)

Publication Number Publication Date
EP3022405A1 EP3022405A1 (en) 2016-05-25
EP3022405B1 true EP3022405B1 (en) 2019-11-13

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Application Number Title Priority Date Filing Date
EP14747094.2A Active EP3022405B1 (en) 2013-07-15 2014-07-10 Device to assemble blades and corresponding method for assembling

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US (1) US10533434B2 (en)
EP (1) EP3022405B1 (en)
CN (1) CN105452617B (en)
FR (1) FR3008448B1 (en)
WO (1) WO2015007979A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108005732B (en) * 2017-12-20 2024-04-19 华瑞（江苏）燃机服务有限公司 Dismounting mechanism of turbine stationary blade assembly of gas turbine
FR3082232B1 (en) 2018-06-12 2020-08-28 Safran Aircraft Engines HOLDING SYSTEM FOR DISMANTLING A BLADE WHEEL
CN109676562A (en) * 2018-12-19 2019-04-26 中国航发沈阳发动机研究所 A kind of aero-engine low-pressure turbine guide vane mounting device
CN113814697B (en) * 2020-06-18 2022-10-28 中国航发商用航空发动机有限责任公司 Method for decomposing low-pressure turbine shaft

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US5131814A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure
DE19520274A1 (en) * 1995-06-02 1996-12-05 Abb Management Ag Device and method for assembling rotor blades
CN100419220C (en) * 2003-05-07 2008-09-17 斯奈克玛马达公司 Mechanic stator and its mounting/dismounting method
US7648336B2 (en) * 2006-01-03 2010-01-19 General Electric Company Apparatus and method for assembling a gas turbine stator
US7971334B2 (en) * 2008-01-22 2011-07-05 United Technologies Corporation Bladed disk assembly method and roller device
US8046886B2 (en) * 2009-12-30 2011-11-01 General Electric Company Fixture for mounting articulated turbine buckets
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades

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Also Published As

Publication number Publication date
EP3022405A1 (en) 2016-05-25
CN105452617A (en) 2016-03-30
US20160169010A1 (en) 2016-06-16
WO2015007979A1 (en) 2015-01-22
CN105452617B (en) 2018-03-06
FR3008448A1 (en) 2015-01-16
FR3008448B1 (en) 2018-01-05
US10533434B2 (en) 2020-01-14

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