EP1717415A1 - Turbine module for a gas turbine engine - Google Patents

Turbine module for a gas turbine engine Download PDF

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Publication number
EP1717415A1
EP1717415A1 EP06113242A EP06113242A EP1717415A1 EP 1717415 A1 EP1717415 A1 EP 1717415A1 EP 06113242 A EP06113242 A EP 06113242A EP 06113242 A EP06113242 A EP 06113242A EP 1717415 A1 EP1717415 A1 EP 1717415A1
Authority
EP
European Patent Office
Prior art keywords
module
turbine
compressor
flange
bolts
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06113242A
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German (de)
French (fr)
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EP1717415B1 (en
Inventor
Michel Brault
Maurice Judet
Patrick Pasquis
Thomas Langevin
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
Original Assignee
SNECMA SAS
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Publication date
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Publication of EP1717415A1 publication Critical patent/EP1717415A1/en
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Publication of EP1717415B1 publication Critical patent/EP1717415B1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/34—Balancing of radial or axial forces on regenerative rotors

Definitions

  • the present invention relates to the field of gas turbine engines and aims in particular a turbine module, in particular the high pressure module.
  • An axial gas turbine engine includes a rotary compressor assembly, supplying a stationary combustion chamber which itself delivers hot gases to a rotating turbine assembly.
  • a turbine rotor integral with a compressor rotor forms a body and the motor may comprise one or more bodies, generally two or three rotating at different speeds.
  • a dual-body engine comprises a low pressure body LP and an HP high pressure body.
  • its architecture is often divided into modules. For example, for the high-pressure body of a double-body engine, all the parts constituting the compressor are arranged in an HP compressor module and all the parts constituting the turbine rotor into an HP turbine module.
  • This last module consists of only rotating parts, for example a turbine disk on which are bolted a labyrinth sealing assembly and a ferrule with upstream assembly flange, and a sealing assembly associated with a downstream bearing. .
  • the HP compressor and HP turbine modules are assembled via specific flanges; these flanges transmit the engine torque of the turbine to the compressor.
  • the connection by these flanges must be sufficiently resistant to fulfill this function.
  • the modules must be provided to the assembly being perfectly balanced in rotation.
  • an upstream balancing plan and a downstream balancing plan are provided.
  • the balancing plane is that in which balancing weights are available at a distance from the axis and at a given angle.
  • the flange that is at the The boundary of the module constitutes an appropriate balancing plan. Balancing weights are therefore available in the area of the boundary flange. This is particularly the case at the boundary between the HP compressor module and the HP turbine module.
  • Each module is presented to the assembly being balanced in this way.
  • the applicant has therefore set itself the goal of developing a turbine module that satisfies these constraints.
  • the gas turbine engine turbine module comprising at least one turbine disk and a disk-shaped component mounted upstream on the turbine disk with respect to the gas flow, said module comprising a means of assembly between the compressor of said engine and the turbine disk, is characterized in that the component, before assembly of the module to the compressor, is pre-assembled to the turbine disk, by bolting to a fastening flange integral with the turbine disk.
  • the means for assembling the compressor to the turbine disk comprises said fixing flange.
  • the component is disc-shaped with a web between its hub and its periphery, and is mounted to said flange by bolting through first holes in the web, second holes are formed in the web for assembly by bolting from the turbine module to the compressor.
  • the component is fixed to said flange by bolts whose number is between 2 and 8 distributed over the circumference.
  • the bolts are retained by nuts crimped on the flange, downstream side, together with nuts for assembly of the module to the compressor.
  • the fastening bolts of the component more particularly have a specific shaped head which differs from the heads of the fastening bolts of the compressor.
  • the component comprises an upstream balancing device disposed on said component independently of the assembly means to the compressor.
  • the invention applies in particular to a module whose component is a support disc of labyrinth sealing elements.
  • the invention also covers the compressor associated with the module to form a gas turbine engine, comprising a downstream flange for attachment to the module. On this flange housing or passages are formed for the heads of bolts of fixings already in place on the module.
  • FIG. 1 we see an HP turbine module half in axial section.
  • This module comprises a turbine disk 3, with a hub with axial section increasing in thickness close to the axis, and at the periphery of which are mounted the turbine blades 4. These are housed in axial recesses formed on the rim of the disc.
  • a component 5 is mounted on the disc 3 upstream, that is to say on the left in the figure. Upstream and downstream are defined with respect to the flow of gases in the engine.
  • the component is here a symmetrical disk of revolution relative to the axis of the machine.
  • This disc comprises a hub of increasing thickness towards the axis of the motor, a portion forming a web 51 towards the periphery.
  • the disc at its periphery carries radial annular blades 53 forming the rotating portion of labyrinth seals. Their counterpart is not represented.
  • the disc 5 is fixed to the disc 3 by bolting to a fastening flange 31 secured to the disc upstream thereof.
  • the bolts 7 comprise a head 71, a rod 72 passing through an orifice formed in the web 51 and a bore machined in the flange 31, and cooperate with a nut 73.
  • a disc 6 On the downstream side of the module there is a disc 6 with a journal 61 forming a support for a downstream bearing 62.
  • the disk is bolted to a downstream mounting flange 33.
  • the bolts 64 are fixed all around the disc. It also has sealing elements 63 for a labyrinth seal.
  • Disk 6 forms a downstream balancing plane. Balancing weights are fitted with the fixing bolts.
  • the module as shown in Figure 1 is pre-assembled ready to be assembled and assembled to a compressor.
  • the function of the bolts 7 is to maintain the component 5 integral with the turbine disk during handling.
  • the bolts 7 are preferably four in number and equidistant on the circumference. Their number can be between 2 and 8. In fact, you have to take into account the fastening bolts of the compressor to the disc. The bolts 7 do not come to disturb the tiering between the disc 3 and the disc 5.
  • FIGS. 2 and 3 the bolting detail is seen after the turbine module has been attached to a compressor attachment flange 9.
  • the latter is not represented.
  • the fixing flange 9 is annular and constitutes the downstream boundary of the compressor.
  • FIG. 2 shows a partial axial section taken along a bolt 7 for fastening the component 5 to the disc 3.
  • FIG. 3 shows a partial axial section taken along a bolt 8 for fixing the flange 9 to the disc 3 .
  • the heads 71 of the bolts 7 are engaged in wide scallops of the flange 9 in such a way that they engage the disc of the component 5 directly. These bolts therefore have no effect on the connection of the flange 9.
  • the bolts 8 of FIG. 3 each participate in the fixing of the flange 9 to the disc 3.
  • the heads 81 bear against the upstream surface of the flange 9 which is held tight against the disk 5 by the nut 83 applied against the downstream face of the flange 31.
  • the rod 82 of the bolt 8 passes through the disk of the component 5 and the two flanges 9 and 31.
  • annular flange 9 seen from the upstream side. It comprises notches in the form of scallops to allow it to bypass the heads 71 of the bolts 7, and abut against the disk of the component 5. It also includes holes for the passage of the rods 82 of the bolts 8, whose head 81 comes to bear on the edge of the holes.
  • FIG. 5 there is shown a variant 9 'compressor mounting flange.
  • the passage has been limited to a circular orifice of diameter slightly greater than that of the heads 71.
  • the component 5 has the same holes in the sail 51 capable of passing either the bolts 7 or the bolts 8.
  • this type of head while also providing the keying, has the further advantage of avoiding seizing, at the time of the modular disassembly of the compressor and the turbine, the bolts 8. If the bolts 8 remain blocked, the specific heads 81 of the bolts 8 are capable of withstanding a violent over-torque for shearing the shaft 82 of the head 81. In all cases, the modular disassembly is ensured.
  • FIG. 6 there is shown the flange 31 seen from the downstream side.
  • the nuts 73 and 83 are preferably mounted and crimped on site before assembling the parts. It is noted that they have a tongue 731 respectively 831 of rectangular shape so as to ensure mutual locking in rotation. This facilitates the screwing of bolts 7 and 8 during assembly.
  • the nuts 73 and 83 crimped on the flange 31 are identical.
  • fastening bolts 8 and 7 are in a concrete example of 28 and 4, respectively. It was verified that the 28 bolts could safely secure the attachment of the compressor to the disc. The difference of 4 with respect to an assembly at 32 does not affect. Calculations have demonstrated this in particular for: the passage torque, mechanical stresses, the life of parts, etc ....
  • the module comprises a flange 10 for attaching the weights on this face.
  • the flange 10 is annular with a face perpendicular to the axis of the module, and comprises a plurality of machining for assembling weights.
  • the number of machining is preferably equal to that of the number of fins mounted on the turbine disk.
  • FIG. 7 shows a flyweight 11 in place held by bolts 111.
  • the installation of these flyweights makes it possible to restore the upstream balancing plane of the HP turbine module rotor. This contributes to one of the delivery conditions of a so-called clean module.
  • a module according to the present invention does not degrade the maintenance of the surrounding modules.

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

Abstract

The module has a disk shaped component (5) pre-assembled, before assembling the module to a compressor, to a turbine disk (3) that is upstream with respect to the flow of a gas in a gas turbine engine. The component is pre-assembled by bolting to a mounting clip (31) which is integrated with the disk. The clip is fixed by bolts (7) retained by screws (73) which are tightened on the clip.

Description

La présente invention concerne le domaine des moteurs à turbine à gaz et vise en particulier un module de turbine, notamment le module haute pression.The present invention relates to the field of gas turbine engines and aims in particular a turbine module, in particular the high pressure module.

Un moteur à turbine à gaz axial comprend un ensemble rotatif formant compresseur, alimentant une chambre de combustion fixe qui elle-même délivre des gaz chauds à un ensemble rotatif formant turbine. Un rotor de turbine solidaire d'un rotor de compresseur forme un corps et le moteur peut comprendre un ou plusieurs corps, généralement deux ou trois tournant à des vitesses différentes. Ainsi un moteur à double corps, comprend un corps basse pression BP et un corps haute pression HP. Afin de rendre le montage du moteur plus aisé et de réduire les temps de montage et démontage, son architecture est souvent divisée en modules. Par exemple pour le corps haute pression d'un moteur à double corps, on dispose l'ensemble des pièces constituant le compresseur en un module de compresseur HP et l'ensemble des pièces constituant le rotor de turbine en un module de turbine HP.An axial gas turbine engine includes a rotary compressor assembly, supplying a stationary combustion chamber which itself delivers hot gases to a rotating turbine assembly. A turbine rotor integral with a compressor rotor forms a body and the motor may comprise one or more bodies, generally two or three rotating at different speeds. Thus a dual-body engine comprises a low pressure body LP and an HP high pressure body. In order to make the mounting of the engine easier and to reduce the time of assembly and disassembly, its architecture is often divided into modules. For example, for the high-pressure body of a double-body engine, all the parts constituting the compressor are arranged in an HP compressor module and all the parts constituting the turbine rotor into an HP turbine module.

Ce dernier module est constitué de seules pièces tournantes, par exemple un disque de turbine sur lequel sont boulonnés un ensemble d'étanchéité à labyrinthes et une virole avec bride d'assemblage en amont, et un ensemble d'étanchéité associé à un palier en aval.This last module consists of only rotating parts, for example a turbine disk on which are bolted a labyrinth sealing assembly and a ferrule with upstream assembly flange, and a sealing assembly associated with a downstream bearing. .

Généralement, les modules compresseur HP et turbine HP sont assemblés par l'intermédiaire de brides spécifiques ; ces brides transmettent le couple moteur de la turbine au compresseur. La liaison par ces brides doit donc être suffisamment résistante pour remplir cette fonction.Generally, the HP compressor and HP turbine modules are assembled via specific flanges; these flanges transmit the engine torque of the turbine to the compressor. The connection by these flanges must be sufficiently resistant to fulfill this function.

En outre les modules se doivent d'être fournis au montage en étant parfaitement équilibrés en rotation. Dans le cas d'un module du type de celui de la turbine HP, on prévoit un plan d'équilibrage amont et un plan d'équilibrage aval. Le plan d'équilibrage est celui dans lequel on dispose les masselottes d'équilibrage à une distance de l'axe et selon un angle déterminés. Dans la solution avec bride d'assemblage, la bride qui est à la frontière du module constitue un plan d'équilibrage approprié. On dispose donc les masselottes d'équilibrage dans la zone de la bride frontière. C'est le cas en particulier à la frontière entre le module de compresseur HP et le module de turbine HP. Chaque module est donc présenté au montage en étant équilibré de cette manière.In addition the modules must be provided to the assembly being perfectly balanced in rotation. In the case of a module of the HP turbine type, an upstream balancing plan and a downstream balancing plan are provided. The balancing plane is that in which balancing weights are available at a distance from the axis and at a given angle. In the solution with assembly flange, the flange that is at the The boundary of the module constitutes an appropriate balancing plan. Balancing weights are therefore available in the area of the boundary flange. This is particularly the case at the boundary between the HP compressor module and the HP turbine module. Each module is presented to the assembly being balanced in this way.

L'emploi de brides spécifiques d'assemblage est commode mais est pénalisant en poids. On a donc cherché à développer un module dont le montage au compresseur puisse être assuré sans bride spécifique d'assemblage. En particulier on a examiné la possibilité d'assurer l'assemblage au compresseur directement sur le disque de turbine du module.The use of specific assembly flanges is convenient but is penalizing in weight. It has therefore sought to develop a module whose assembly to the compressor can be provided without specific assembly flange. In particular, the possibility of assembling the compressor directly on the turbine disk of the module has been examined.

Il se pose alors le problème du pré-assemblage du module de turbine et de sa livraison en étant parfaitement équilibré. En effet il est important que les monteurs chargés de l'assemblage des modules n'aient pas à intervenir sur le module lui-même, sinon l'intérêt de la modularité en serait amoindri.This raises the problem of pre-assembly of the turbine module and its delivery being perfectly balanced. Indeed it is important that the assemblers responsible for assembling the modules do not have to intervene on the module itself, otherwise the interest of the modularity would be diminished.

La demanderesse s'est donc fixé comme objectif de développer un module de turbine qui satisfasse à ces contraintes.The applicant has therefore set itself the goal of developing a turbine module that satisfies these constraints.

Conformément à l'invention, le module de turbine pour moteur à turbine à gaz comprenant au moins un disque de turbine et un composant en forme de disque monté en amont sur le disque de turbine par rapport à l'écoulement des gaz, ledit module comportant un moyen d'assemblage entre le compresseur dudit moteur et le disque de turbine, est caractérisé par le fait que le composant, avant assemblage du module au compresseur, est pré-assemblé au disque de turbine, par boulonnage à une bride de fixation solidaire du disque de turbine.According to the invention, the gas turbine engine turbine module comprising at least one turbine disk and a disk-shaped component mounted upstream on the turbine disk with respect to the gas flow, said module comprising a means of assembly between the compressor of said engine and the turbine disk, is characterized in that the component, before assembly of the module to the compressor, is pre-assembled to the turbine disk, by bolting to a fastening flange integral with the turbine disk.

Ainsi par la solution de l'invention qui consiste à fixer directement le module compresseur sur le disque de turbine et à lier le composant, disposé entre le compresseur et le disque de turbine, au disque de turbine séparément, on permet une réduction de masse sans perdre en sécurité d'assemblage ainsi qu'un pré-assemblage en module pouvant être éventuellement équilibré.Thus, by the solution of the invention which consists in directly fixing the compressor module on the turbine disk and in binding the component, arranged between the compressor and the turbine disk, to the turbine disk separately, mass reduction is allowed without lose assembly security and a module pre-assembly that can be balanced if necessary.

De préférence le moyen d'assemblage du compresseur au disque de turbine comprend ladite bride de fixation.Preferably the means for assembling the compressor to the turbine disk comprises said fixing flange.

Notamment lorsque le composant est en forme de disque avec un voile entre son moyeu et sa périphérie, et est monté à ladite bride par boulonnage à travers des premiers perçages dans le voile, des deuxièmes perçages sont ménagés dans le voile pour l'assemblage par boulonnage du module de turbine au compresseur.Especially when the component is disc-shaped with a web between its hub and its periphery, and is mounted to said flange by bolting through first holes in the web, second holes are formed in the web for assembly by bolting from the turbine module to the compressor.

Conformément à une autre caractéristique le composant est fixé à ladite bride par des boulons dont le nombre est compris entre 2 et 8 répartis sur la circonférence.According to another characteristic the component is fixed to said flange by bolts whose number is between 2 and 8 distributed over the circumference.

Avantageusement, les boulons sont retenus par des écrous sertis sur la bride, côté aval, ensemble avec des écrous pour l'assemblage du module au compresseur. Les boulons de fixation du composant ont plus particulièrement une tête de forme spécifique qui se distingue des têtes des boulons de fixation du compresseur.Advantageously, the bolts are retained by nuts crimped on the flange, downstream side, together with nuts for assembly of the module to the compressor. The fastening bolts of the component more particularly have a specific shaped head which differs from the heads of the fastening bolts of the compressor.

Conformément à une autre caractéristique le composant comprend un dispositif d'équilibrage amont disposé sur ledit composant indépendamment du moyen d'assemblage au compresseur.According to another characteristic the component comprises an upstream balancing device disposed on said component independently of the assembly means to the compressor.

L'invention s'applique en particulier à un module dont le composant est un disque support d'éléments d'étanchéité à labyrinthes.The invention applies in particular to a module whose component is a support disc of labyrinth sealing elements.

L'invention couvre également le compresseur associé au module pour former un moteur à turbine à gaz, comprenant une bride aval de fixation au module. Sur cette bride des logements ou des passages sont ménagés pour les têtes des boulons de fixations déjà en place sur le module.The invention also covers the compressor associated with the module to form a gas turbine engine, comprising a downstream flange for attachment to the module. On this flange housing or passages are formed for the heads of bolts of fixings already in place on the module.

L'invention va maintenant être présentée plus en détail dans la description qui suit d'un mode de réalisation non limitatif en référence aux dessins annexés sur lesquels :

  • la figure 1 montre en coupe axiale un demi module de turbine haute pression conforme à l'invention,
  • la figure 2 montre le détail de la fixation préalable du composant au disque de turbine, vu en coupe axiale,
  • la figure 3 montre le détail de la fixation de la bride aval du compresseur au disque de turbine, vu en coupe axiale,
  • la figure 4 montre en détail l'arrangement de la bride du compresseur HP, vu du côté amont,
  • la figure 5 montre une variante de réalisation de la bride aval du compresseur HP,
  • la figure 6 est une coupe selon VI-VI de la figure 2 ou 3 et montre le détail du montage des écrous sur la bride de fixation solidaire du disque de turbine, vu du côté aval,
  • la figure 7 montre une variante du module de turbine de la figure 1, le module étant équipé d'un dispositif d'équilibrage amont.
The invention will now be presented in more detail in the following description of a non-limiting embodiment with reference to the accompanying drawings in which:
  • FIG. 1 shows in axial section a half high pressure turbine module according to the invention,
  • FIG. 2 shows the detail of the preliminary fixing of the component to the turbine disc, seen in axial section,
  • FIG. 3 shows the detail of the attachment of the downstream flange of the compressor to the turbine disk, seen in axial section,
  • FIG. 4 shows in detail the arrangement of the HP compressor flange, seen from the upstream side,
  • FIG. 5 shows an alternative embodiment of the downstream flange of the HP compressor,
  • FIG. 6 is a section along VI-VI of FIG. 2 or 3 and shows the detail of the mounting of the nuts on the integral fastening flange of the turbine disc, seen from the downstream side,
  • FIG. 7 shows a variant of the turbine module of FIG. 1, the module being equipped with an upstream balancing device.

En se reportant à la figure 1, on voit une moitié de module de turbine HP en coupe axiale. Ce module comprend un disque de turbine 3, avec un moyeu à section axiale allant en épaisseur croissante à proximité de l'axe, et à la périphérie duquel sont montées les aubes 4 de turbine. Celles-ci sont logées dans des alvéoles axiales ménagées sur la jante du disque. Un composant 5 est monté sur le disque 3 en amont, c'est-à-dire à gauche sur la figure. L'amont et l'aval étant définis par rapport à l'écoulement des gaz dans le moteur. Le composant est ici un disque à symétrie de révolution par rapport à l'axe de la machine. Ce disque comprend un moyeu allant en épaisseur croissante vers l'axe du moteur, une partie formant un voile 51 en allant vers la périphérie. Le disque à sa périphérie porte des lames 53 annulaires radiales formant la partie tournante de joints d'étanchéité à labyrinthes. Leur contrepartie n'est pas représentée.Referring to Figure 1, we see an HP turbine module half in axial section. This module comprises a turbine disk 3, with a hub with axial section increasing in thickness close to the axis, and at the periphery of which are mounted the turbine blades 4. These are housed in axial recesses formed on the rim of the disc. A component 5 is mounted on the disc 3 upstream, that is to say on the left in the figure. Upstream and downstream are defined with respect to the flow of gases in the engine. The component is here a symmetrical disk of revolution relative to the axis of the machine. This disc comprises a hub of increasing thickness towards the axis of the motor, a portion forming a web 51 towards the periphery. The disc at its periphery carries radial annular blades 53 forming the rotating portion of labyrinth seals. Their counterpart is not represented.

Le disque 5 est fixé au disque 3 par boulonnage sur une bride de fixation 31 solidaire du disque en amont de celui-ci. Les boulons 7 comprennent une tête 71, une tige 72 traversant un orifice ménagé dans le voile 51 et un perçage usiné dans la bride 31, et coopèrent avec un écrou 73.The disc 5 is fixed to the disc 3 by bolting to a fastening flange 31 secured to the disc upstream thereof. The bolts 7 comprise a head 71, a rod 72 passing through an orifice formed in the web 51 and a bore machined in the flange 31, and cooperate with a nut 73.

Sur le flanc aval du module on distingue un disque 6 avec un tourillon 61 formant support pour un palier aval 62. Le disque est boulonné sur une bride de fixation aval 33. Les boulons 64 de fixation sont répartis sur tout le pourtour du disque. Il comporte également des éléments d'étanchéité 63 pour un joint d'étanchéité à labyrinthes. Le disque 6 forme un plan d'équilibrage aval. Des masselottes d'équilibrage sont montées avec les boulons de fixation.On the downstream side of the module there is a disc 6 with a journal 61 forming a support for a downstream bearing 62. The disk is bolted to a downstream mounting flange 33. The bolts 64 are fixed all around the disc. It also has sealing elements 63 for a labyrinth seal. Disk 6 forms a downstream balancing plane. Balancing weights are fitted with the fixing bolts.

Le module tel que représenté sur la figure 1 est pré-assemblé prêt à être monté et assemblé à un compresseur. La fonction des boulons 7 est de maintenir le composant 5 solidaire du disque de turbine pendant les manipulations. Les boulons 7 sont de préférence au nombre de quatre et sont équidistants sur la circonférence. Leur nombre peut être compris entre 2 et 8. Il faut tenir compte en fait des boulons de fixation du compresseur au disque. Les boulons 7 ne viennent pas perturber le tierçage entre le disque 3 et le disque 5.The module as shown in Figure 1 is pre-assembled ready to be assembled and assembled to a compressor. The function of the bolts 7 is to maintain the component 5 integral with the turbine disk during handling. The bolts 7 are preferably four in number and equidistant on the circumference. Their number can be between 2 and 8. In fact, you have to take into account the fastening bolts of the compressor to the disc. The bolts 7 do not come to disturb the tiering between the disc 3 and the disc 5.

En se reportant aux figures 2 et 3, on voit le détail du boulonnage après que le module de turbine a été fixé à une bride 9 de fixation du compresseur. Ce dernier n'est pas représenté. La bride de fixation 9 est annulaire et constitue la frontière aval du compresseur. La figure 2 représente une coupe axiale partielle réalisée le long d'un boulon 7 de fixation du composant 5 au disque 3. La figure 3 représente une coupe axiale partielle réalisée le long d'un boulon 8 de fixation de la bride 9 au disque 3.Referring to FIGS. 2 and 3, the bolting detail is seen after the turbine module has been attached to a compressor attachment flange 9. The latter is not represented. The fixing flange 9 is annular and constitutes the downstream boundary of the compressor. FIG. 2 shows a partial axial section taken along a bolt 7 for fastening the component 5 to the disc 3. FIG. 3 shows a partial axial section taken along a bolt 8 for fixing the flange 9 to the disc 3 .

Les têtes 71 des boulons 7 sont engagées dans de larges festons de la bride 9 de telle manière qu'elles viennent en prise avec le disque du composant 5 directement. Ces boulons n'on donc aucun effet sur la liaison de la bride 9.The heads 71 of the bolts 7 are engaged in wide scallops of the flange 9 in such a way that they engage the disc of the component 5 directly. These bolts therefore have no effect on the connection of the flange 9.

Les boulons 8 de la figure 3 participent chacun à la fixation de la bride 9 au disque 3. Les têtes 81 sont en appui contre la surface amont de la bride 9 qui est maintenue serrée contre le disque 5 par l'écrou 83 appliqué contre la face aval de la bride 31. La tige 82 du boulon 8 traverse le disque du composant 5 et les deux brides 9 et 31.The bolts 8 of FIG. 3 each participate in the fixing of the flange 9 to the disc 3. The heads 81 bear against the upstream surface of the flange 9 which is held tight against the disk 5 by the nut 83 applied against the downstream face of the flange 31. The rod 82 of the bolt 8 passes through the disk of the component 5 and the two flanges 9 and 31.

Sur la figure 4 on a représenté la bride annulaire 9, vue du côté amont. Elle comprend des encoches en forme de festons pour lui permettre de contourner les têtes 71 des boulons 7, et venir en appui contre le disque du composant 5. Elle comprend également des perçages pour le passage des tiges 82 des boulons 8, dont la tête 81 vient en appui sur le bord des perçages.In Figure 4 there is shown the annular flange 9, seen from the upstream side. It comprises notches in the form of scallops to allow it to bypass the heads 71 of the bolts 7, and abut against the disk of the component 5. It also includes holes for the passage of the rods 82 of the bolts 8, whose head 81 comes to bear on the edge of the holes.

Sur la figure 5 on a représenté une variante 9' de bride de fixation du compresseur. Pour le passage des têtes 71 des boulons de fixation du disque 5, au lieu de festons on a limité le passage à un orifice circulaire de diamètre légèrement supérieur à celui des têtes 71.In Figure 5 there is shown a variant 9 'compressor mounting flange. For the passage of the heads 71 of the fixing bolts of the disk 5, instead of festoons, the passage has been limited to a circular orifice of diameter slightly greater than that of the heads 71.

Le composant 5 possède les mêmes perçages dans le voile 51 capable de laisser passer soit les boulons 7 soit les boulons 8.The component 5 has the same holes in the sail 51 capable of passing either the bolts 7 or the bolts 8.

Pour assurer la fonction de détrompeur entre les boulons 7 et 8, on peut prévoir des têtes 71 et 81 de boulons avec des formes différentes.To provide the keying function between the bolts 7 and 8, there may be heads 71 and 81 of bolts with different shapes.

Par exemple, on peut prévoir des têtes cannelées pour les uns et des têtes larges (une tête large est une tête plus large que l'opération de vissage nécessite ; elle correspond à celle d'un fût plus large) pour les autres ou inversement.For example, one can provide fluted heads for one and wide heads (a wide head is a head wider than the screwing operation requires, it corresponds to that of a wider drum) for others or vice versa.

L'emploi de ce type de têtes tout en assurant également le détrompage, présente en outre l'avantage d'éviter le grippage, au moment du démontage modulaire du compresseur et de la turbine, des boulons 8. Si les boulons 8 restent bloqués, les têtes spécifiques 81 des boulons 8 sont capables de supporter un violent sur-couple pour cisailler le fût 82 de la tête 81. Dans tous les cas, le démontage modulaire est assuré.The use of this type of head while also providing the keying, has the further advantage of avoiding seizing, at the time of the modular disassembly of the compressor and the turbine, the bolts 8. If the bolts 8 remain blocked, the specific heads 81 of the bolts 8 are capable of withstanding a violent over-torque for shearing the shaft 82 of the head 81. In all cases, the modular disassembly is ensured.

Sur la figure 6 on a représenté la bride 31 vue du côté aval. Les écrous 73 et 83 sont de préférence montés et sertis sur place avant assemblage des pièces. On note qu'ils présentent une languette 731 respectivement 831 de forme rectangulaire de manière à assurer un blocage mutuel en rotation. Cela facilite le vissage des boulons 7 et 8 lors du montage. Les écrous 73 et 83 sertis sur la bride 31 sont identiques.In Figure 6 there is shown the flange 31 seen from the downstream side. The nuts 73 and 83 are preferably mounted and crimped on site before assembling the parts. It is noted that they have a tongue 731 respectively 831 of rectangular shape so as to ensure mutual locking in rotation. This facilitates the screwing of bolts 7 and 8 during assembly. The nuts 73 and 83 crimped on the flange 31 are identical.

Les nombres de boulons de fixation 8 et 7 sont dans un exemple concret respectivement de 28 et 4. On a vérifié que les 28 boulons pouvaient assurer avec sécurité la fixation du compresseur au disque. La différence de 4 par rapport à un montage à 32 n'a pas d'incidence. Les calculs l'ont ainsi démontré notamment pour : le passage couple, les contraintes mécaniques, la durée de vie des pièces, etc....The numbers of fastening bolts 8 and 7 are in a concrete example of 28 and 4, respectively. It was verified that the 28 bolts could safely secure the attachment of the compressor to the disc. The difference of 4 with respect to an assembly at 32 does not affect. Calculations have demonstrated this in particular for: the passage torque, mechanical stresses, the life of parts, etc ....

On observe enfin que cette disposition permet le tierçage entre le module compresseur et le module de turbine.Finally, it is observed that this arrangement allows the third party between the compressor module and the turbine module.

Afin de permettre l'équilibrage du module, on prévoit de disposer des masselottes sur la face amont du disque du composant 5 qui constitue alors avantageusement le plan d'équilibrage amont. Un module comportant ce dispositif d'équilibrage est représenté sur la figure 7. Le module comprend une bride 10 d'accrochage des masselottes sur cette face. La bride 10 est annulaire avec une face perpendiculaire à l'axe du module, et comprend une pluralité d'usinages pour le montage de masselottes. Le nombre d'usinages est de préférence égal à celui du nombre d'ailettes montées sur le disque de turbine.In order to allow the balancing of the module, provision is made to have weights on the upstream face of the disk of the component 5 which then advantageously constitutes the upstream balancing plane. A module comprising this balancing device is shown in FIG. 7. The module comprises a flange 10 for attaching the weights on this face. The flange 10 is annular with a face perpendicular to the axis of the module, and comprises a plurality of machining for assembling weights. The number of machining is preferably equal to that of the number of fins mounted on the turbine disk.

La figure 7 montre une masselotte 11 en place maintenu par des boulons 111. Dans ce cas, l'installation de ces masselottes permet la restitution du plan amont d'équilibrage du rotor module turbine HP. Cela contribue à l'une des conditions de livraison d'un module dit propre.FIG. 7 shows a flyweight 11 in place held by bolts 111. In this case, the installation of these flyweights makes it possible to restore the upstream balancing plane of the HP turbine module rotor. This contributes to one of the delivery conditions of a so-called clean module.

Un module selon la présente invention ne vient pas dégrader la maintenance des modules environnants.A module according to the present invention does not degrade the maintenance of the surrounding modules.

Claims (12)

Module de turbine pour moteur à turbine à gaz comprenant au moins un disque (3) de turbine et un composant (5) en forme de disque monté sur le disque de turbine en amont par rapport à l'écoulement des gaz, ledit module comportant un moyen d'assemblage au compresseur dudit moteur, caractérisé par le fait que le composant (5) est pré-assemblé au disque (3) de turbine, avant assemblage du module au compresseur, par boulonnage à une bride (31) de fixation solidaire du disque (3) de turbine.Turbine module for a gas turbine engine comprising at least one turbine disk (3) and a disk-shaped component (5) mounted on the turbine disk upstream with respect to the gas flow, said module comprising a means for assembling the compressor of said engine, characterized in that the component (5) is pre-assembled to the turbine disk (3), before assembly of the module to the compressor, by bolting to a fastening flange (31) integral with the disc (3) of turbine. Module selon la revendication 1, dont le moyen d'assemblage au compresseur comprend ladite bride (31) de fixation.Module according to claim 1, wherein the compressor assembly means comprises said fixing flange (31). Module selon la revendication 2 dont le composant est en forme de disque avec un voile (51) entre son moyeu et sa périphérie, et est monté à ladite bride (31) par boulonnage (7) à travers des premiers perçages dans le voile (51), des deuxièmes perçages étant ménagés dans le voile pour l'assemblage par boulonnage (8) du module de turbine (3) au compresseur.Module according to claim 2, the component of which is disc-shaped with a web (51) between its hub and its periphery, and is mounted to said flange (31) by bolting (7) through first holes in the web (51). ), second holes being formed in the web for assembly by bolting (8) of the turbine module (3) to the compressor. Module selon la revendication 3 dont le composant (5) possède les mêmes perçages dans le voile (51) capable de laisser passer soit les boulons (7) soit les boulons (8).Module according to claim 3, the component (5) has the same holes in the web (51) capable of passing either bolts (7) or bolts (8). Module selon la revendication 3 ou 4 dont le composant est fixé à ladite bride (31) par des boulons (7) dont le nombre est compris entre 2 et 8 répartis sur la circonférence.Module according to claim 3 or 4 whose component is fixed to said flange (31) by bolts (7) whose number is between 2 and 8 distributed over the circumference. Module selon l'une des revendications 2 à 5 dont les boulons (7) sont retenus par des écrous (73) sertis sur la bride (31), côté aval, ensemble avec des écrous (83) pour l'assemblage du module au compresseur.Module according to one of claims 2 to 5, the bolts (7) are retained by nuts (73) crimped on the flange (31), downstream side, together with nuts (83) for assembly of the module to the compressor . Module selon la revendication 6 dont les écrous (73) et (83) sertis sur la bride (31) sont identiques.Module according to claim 6, the nuts (73) and (83) crimped on the flange (31) are identical. Module selon l'une des revendications 2 à 5 dont les boulons (7) de fixation du composant ont une tête spécifique qui se distingue des têtes des boulons (8) de fixation du compresseur.Module according to one of claims 2 to 5, wherein the bolts (7) for fixing the component have a specific head which differs from the heads of the bolts (8) for fixing the compressor. Module selon l'une des revendications 2 à 8 comprenant un dispositif d'équilibrage (10, 11) amont disposé sur ledit composant (5) indépendamment du moyen d'assemblage au compresseur.Module according to one of claims 2 to 8 comprising an upstream balancing device (10, 11) disposed on said component (5) independently of the assembly means to the compressor. Module selon l'une des revendications 2 à 9 dont le composant (5) est un disque support d'éléments d'étanchéité à labyrinthes.Module according to one of claims 2 to 9, the component (5) of which is a support disc for labyrinth sealing elements. Compresseur associé au module selon l'une des revendications précédentes pour former un moteur à turbine à gaz, comprenant une bride (9) aval de fixation au module sur laquelle des logements ou des passages sont ménagés pour les têtes des boulons (71) de fixation déjà en place sur le module.Compressor associated with the module according to one of the preceding claims to form a gas turbine engine, comprising a flange (9) downstream of attachment to the module on which housings or passages are provided for the heads of the bolts (71) fixing already in place on the module. Moteur à turbine à gaz comportant un module de turbine selon l'une des revendications 1 à 11.Gas turbine engine comprising a turbine module according to one of Claims 1 to 11.
EP06113242A 2005-04-29 2006-04-27 Turbine module for a gas turbine engine Active EP1717415B1 (en)

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FR0551124A FR2885167B1 (en) 2005-04-29 2005-04-29 TURBINE MODULE FOR GAS TURBINE ENGINE

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FR2938292A1 (en) * 2008-11-07 2010-05-14 Snecma ANNULAR FLANGE FOR FIXING A ROTOR OR STATOR ELEMENT IN A TURBOMACHINE
FR2974865A1 (en) * 2011-05-04 2012-11-09 Snecma High pressure rotor for e.g. turbojet of aircraft, has foolproofing piece to partially seal prefixing bolt passage spaces and fixed with auxiliary disk by attaching bolts to limit access to prefixing bolts by attaching bolt tightening tool
FR3002585A1 (en) * 2013-02-27 2014-08-29 Snecma Rotor for use in rotary assembly of e.g. turbojet, has fasteners, where masses of fasteners are allowed to vary circumferentially and are given according set of circumferential positions of annular supports for dynamic balancing of assembly
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FR2921422A1 (en) * 2007-09-26 2009-03-27 Snecma Sa Annular piece e.g. ring cowling, for e.g. jet engine of aircraft, has annular sheet connected on clamp and comprising rim for allowing cooperation of nuts by stopping to prevent turning of nuts in orifices of clamp
US9039351B2 (en) 2008-05-29 2015-05-26 Snecma Annular flange for fastening a rotor or stator element
WO2009144409A1 (en) * 2008-05-29 2009-12-03 Snecma Annular flange for attaching a rotor or stator element
FR2931869A1 (en) * 2008-05-29 2009-12-04 Snecma ANNULAR BRACKET FOR FIXING A ROTOR OR STATOR ELEMENT
FR2938292A1 (en) * 2008-11-07 2010-05-14 Snecma ANNULAR FLANGE FOR FIXING A ROTOR OR STATOR ELEMENT IN A TURBOMACHINE
US8727719B2 (en) 2008-11-07 2014-05-20 Snecma Annular flange for fastening a rotor or stator element in a turbomachine
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FR2974865A1 (en) * 2011-05-04 2012-11-09 Snecma High pressure rotor for e.g. turbojet of aircraft, has foolproofing piece to partially seal prefixing bolt passage spaces and fixed with auxiliary disk by attaching bolts to limit access to prefixing bolts by attaching bolt tightening tool
FR3002585A1 (en) * 2013-02-27 2014-08-29 Snecma Rotor for use in rotary assembly of e.g. turbojet, has fasteners, where masses of fasteners are allowed to vary circumferentially and are given according set of circumferential positions of annular supports for dynamic balancing of assembly
FR3021066A1 (en) * 2014-05-19 2015-11-20 Snecma BALANCED ROTOR DISC, AND BALANCING METHOD
US9920626B2 (en) 2014-05-19 2018-03-20 Snecma Balanced rotor disc, and balancing method
DE202015101878U1 (en) 2015-04-16 2015-04-30 Thilo Kraemer tester
EP3081919A1 (en) 2015-04-16 2016-10-19 Thilo Kraemer Test device for performing hardness measurements
FR3078363A1 (en) * 2018-02-23 2019-08-30 Safran Aircraft Engines MOBILE SEAL RING

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DE602006001430D1 (en) 2008-07-24
UA88281C2 (en) 2009-10-12
CA2544784A1 (en) 2006-10-29
FR2885167B1 (en) 2007-06-29
RU2403401C2 (en) 2010-11-10
EP1717415B1 (en) 2008-06-11
CN1854485A (en) 2006-11-01
RU2006114654A (en) 2007-11-10
CA2544784C (en) 2014-01-28
CN1854485B (en) 2011-05-25
ES2310887T3 (en) 2009-01-16
FR2885167A1 (en) 2006-11-03
US20070059164A1 (en) 2007-03-15
US7364402B2 (en) 2008-04-29

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