EP2071142A1 - Watertight assembly of a hub cavity of a turbomachine exhaust casing - Google Patents

Watertight assembly of a hub cavity of a turbomachine exhaust casing Download PDF

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Publication number
EP2071142A1
EP2071142A1 EP08168877A EP08168877A EP2071142A1 EP 2071142 A1 EP2071142 A1 EP 2071142A1 EP 08168877 A EP08168877 A EP 08168877A EP 08168877 A EP08168877 A EP 08168877A EP 2071142 A1 EP2071142 A1 EP 2071142A1
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EP
European Patent Office
Prior art keywords
radial
casing
wall
cylindrical
exhaust casing
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Granted
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EP08168877A
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German (de)
French (fr)
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EP2071142B1 (en
Inventor
Xavier Firmin Camille Jean Lescure
Aurélien René-Pierre Massot
Sebastien Jean Laurent Prestel
Christian René Schnell
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to an exhaust casing in a turbomachine, such as an aircraft turbojet, and relates more particularly to the sealing of a hub cavity in the exhaust casing.
  • the exhaust casing of a turbomachine is mounted downstream of a turbine and generally comprises two coaxial cylindrical walls, respectively radially inner and outer, which are connected by radial arms, the inner wall being surrounded by a cylindrical envelope intended to guiding an exhaust stream from the turbine.
  • the cylindrical envelope is fixed by its downstream end to the inner wall of the exhaust casing, and comprises at its upstream end a radial annular portion extending freely towards the axis of the turbomachine so that the inner wall of the casing exhaust and the cylindrical envelope delimit a cavity, commonly called hub cavity.
  • This cavity is open at the inner end of the radial annular portion of the cylindrical envelope.
  • the cylindrical envelope has vibration modes substantially corresponding to the frequencies of the rotor or rotors of the turbomachine, and is therefore likely to resonate with the rotor or rotors, thereby generating strong vibrations likely to penalize the life of the cylindrical envelope.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
  • turbomachine exhaust casing comprising two coaxial cylindrical walls, respectively radially inner and radially outer, connected by radial arms, and a cylindrical envelope integral with the downstream end of the radially inner wall and which delimits a hub cavity with the radially inner wall and an exhaust gas flow space with the radially outer wall, the cylindrical shell having at its upstream end a radial annular portion extending towards the axis of the turbomachine, characterized in that the radial annular portion of the casing has at its inner end an annular flange cooperating by substantially radially sliding radial sealing with the inner cylindrical wall of the exhaust casing.
  • the annular flange of the radial portion of the cylindrical casing makes it possible to prevent the circulation of air in the hub cavity.
  • This radially sliding connection mode makes it possible to ensure a good seal of the hub cavity while avoiding the appearance of mechanical stresses in the cylindrical envelope due to the expansions. thermal conditions that may occur at operating temperatures of the turbomachine.
  • the axial retention of the upstream end of the cylindrical envelope makes it possible to raise the frequencies of the vibration modes of the envelope and thus to avoid the resonance phenomena, for example with the rotor of the turbomachine, which are detrimental to its behavior over time.
  • the inner wall of the exhaust casing comprises two annular flanges, respectively upstream and downstream, extending radially outwards and disposed facing each other so as to form an annular groove for receiving the annular flange of the cylindrical envelope with an axial clearance for a substantially sealed connection of the cylindrical envelope to the radially inner wall allowing a radial displacement of the annular flange of the envelope.
  • the two flanges of the inner wall of the exhaust casing have a radial dimension greater than a maximum allowable amplitude of a radial displacement of the annular flange of the cylindrical envelope caused by an expansion. thermal of the latter.
  • the annular flange of the cylindrical envelope is not likely to disengage from the annular groove formed by the two flanges of the inner wall of the exhaust casing under the effect of thermal expansion, at least as long as the radial displacement of the annular flange does not exceed a maximum value corresponding to a predetermined maximum temperature that the cylindrical envelope is not likely to exceed during normal operation of the turbomachine.
  • the annular flange of the cylindrical envelope preferably extends substantially to the bottom of the annular groove of the inner wall of the exhaust casing in stopping condition of the turbomachine.
  • the cylindrical envelope is elastically preloaded, under stopping condition of the turbomachine, so as to apply the upstream face of the annular flange of its radial annular portion against the upstream annular flange of the inner wall. exhaust housing, to seal the hub cavity.
  • the cylindrical envelope is elastically prestressed, in the stopping condition of the turbomachine, so as to apply the downstream face of the annular flange of its radial annular part against the annular flange downstream of the internal wall of the exhaust casing, to seal the hub cavity.
  • the annular flange of the radial annular portion of the cylindrical envelope preferably comprises at its radially outer end a cylindrical flange extending upstream and forming a radial bearing abutment on the upstream annular flange of the inner wall of the housing. exhaust.
  • the radial annular portion of the cylindrical envelope comprises orifices for the passage of a flow of fresh air.
  • This embodiment is well suited to the case where the hub cavity requires to be ventilated.
  • the size of the orifices can then be chosen according to the level of ventilation required and allows the ventilation air flow rate to be controlled.
  • the invention also relates to a cylindrical envelope for a turbomachine of the type described above, comprising at one of its an annular flange and at the other end thereof an inwardly extending radial annular portion, characterized in that the radial annular portion has at its radially inner end a radial annular flange formed with a cylindrical flange.
  • the invention also relates to a turbomachine equipped with an exhaust casing as described above.
  • the figure 1 represents a turbomachine exhaust casing 10 comprising two coaxial cylindrical walls, respectively radially internal 12 and external 14, connected by radial structural arms 16.
  • a cylindrical casing 18 is mounted around the radially inner wall 12 of the exhaust casing 10.
  • This envelope 18 shown separately on the figure 2 , comprises a cylindrical wall 20 in which are formed cutouts 22 open downstream for the passage of the radial arms 16 of the exhaust casing 10.
  • the cylindrical casing 18 comprises at its downstream end a radial annular flange 24 for attachment to the exhaust casing 10, and to its upstream end, a radial annular portion 26 extending radially inwardly.
  • the casing 18 comprises, according to the invention, an annular flange 28 formed at the radially inner end of its radial annular portion 26.
  • the casing 18 and the radially outer wall 14 of the exhaust casing delimit an annular space for exhaust gas flow inside a turbomachine, represented partially on the figure 3 .
  • This figure 3 shows the exhaust casing 10 mounted downstream of a low-pressure turbine 30, comprising discs 32 carrying blades 34, and rotating a shaft connected to an upstream compressor (not shown), in a manner well known.
  • the exhaust casing 10 comprises a downstream radial wall 36 extending radially outwardly from the downstream end of the inner wall 12 of the casing, and to which is fixed the radial annular flange 24 of the cylindrical casing.
  • the assembly formed by the inner wall 12 and the downstream radial wall 36 of the exhaust casing 10 as well as by the cylindrical casing 18 defines a toric cavity 38 commonly called a hub cavity.
  • the radial annular portion of the cylindrical envelope is free at its radially inner end and thus provides an annular opening in the hub cavity, between the free end of this radial annular portion and the upstream end of the inner wall of the exhaust casing.
  • the cylindrical casing 18 comprises an annular flange 28 formed at the inner end of the radial annular portion 26 of the casing, and engaged, as shown in FIG. figure 3 in an annular groove 40 ( Fig. 3a ) open towards the outside and formed by two radial flanges, respectively upstream 42 and downstream 44, arranged facing each other and integral with the inner wall 12 of the exhaust casing 10, to close the hub cavity 38 substantially sealingly and thus prevent the flow of fresh air into this cavity .
  • the downstream flange 44 is for example formed at the radially outer end of a ferrule 46 extending radially outwards from the upstream end of the inner wall 12 of the exhaust casing 10.
  • the upstream flange 42 can for its part be formed for example in the extension of a radial flange 48 for fixing an inner casing 50, commonly called an oil recovery casing, to the exhaust casing 10, the inner casing 50 extending axially between the shaft of the turbine and the discs 32 of the rotor of this turbine, upstream of the exhaust casing 10.
  • an inner casing 50 commonly called an oil recovery casing
  • annular flange 28 of the cylindrical casing 18 comprises at its radially outer end a cylindrical flange 52 extending upstream and forming a radial bearing abutment on the upstream annular flange 42 of the inner wall 12 of the exhaust casing 10.
  • the axial extent of the annular groove 40 is slightly greater than the thickness of the annular flange 28 of the cylindrical envelope 18 so that the latter is engaged with an axial clearance, for example of the order of 1 mm, in the groove 40, so as to allow radial sliding of the annular flange 28 in the groove 40.
  • cylindrical envelope 18 is formed such that at room temperature, when the turbomachine is stopped, the annular flange 18 extends substantially to the bottom of the annular groove 40.
  • the radial flanges 42 and 44 of the exhaust casing have radial dimensions greater than a value of radial displacement of the annular flange 28 considered as a maximum permissible under normal operating conditions of the turbomachine, in order to avoid any risk of disengagement of the engine. ledge 28 out of the throat 40.
  • cylindrical casing 18 is prestressed axially to apply, in stopping condition of the turbomachine, the upstream face 54 of the annular flange 28 against the downstream face 56 of the upstream flange 42 of the inner wall 12 of the casing. exhaust 10, to better ensure the sealing of the connection between the cylindrical casing 18 and the inner wall 12 of the housing.
  • the thermal expansion of the cylindrical envelope then tends to further increase the pressure exerted by the flange 28 on the upstream flange 42 of the casing, so that the sealing of the hub cavity 38 is ensured permanently.
  • the cylindrical envelope 18 could be prestressed axially to apply the downstream face 58 of the annular flange 28 against the upstream face 60 of the downstream flange 44 of the inner wall 12 of the exhaust casing 10.
  • the air pressure in the hub cavity 38 becomes greater than the air pressure upstream of the exhaust casing, or if a thermal expansion of the cylindrical casing 18 causes its annular flange 28 to move towards the upstream, it is quickly pressed against the upstream flange 42 of the exhaust casing, so that the sealing of the hub cavity 38 is preserved.
  • the cylindrical envelope 18 Because of the maintenance of its upstream end, the cylindrical envelope 18 has higher frequencies of frequencies of vibration than in the prior art.
  • the sealing of the hub cavity 38 makes it possible, as explained above, to improve the service life of the radial arms 16 of the exhaust casing.

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

Abstract

The casing (10) has radial arms (16) for connecting a radial inner wall (12) and a radial outer wall (14), and a cylindrical envelope (18) connected to a downstream end of the inner wall. The envelope delimits a hub cavity (38) with the inner wall and an exhaust gas flow space with the outer wall. The envelope has an upstream end with an annular radial part (26) extending towards interior of a turbomachine. The radial part has an inner end comprising an annular edge (28) that co-operates by radial sliding with the inner wall in a sealed manner.

Description

La présente invention concerne un carter d'échappement dans une turbomachine, telle qu'un turboréacteur d'avion, et se rapporte plus particulièrement à l'étanchéité d'une cavité de moyeu dans le carter d'échappement.The present invention relates to an exhaust casing in a turbomachine, such as an aircraft turbojet, and relates more particularly to the sealing of a hub cavity in the exhaust casing.

Le carter d'échappement d'une turbomachine est monté en aval d'une turbine et comprend en général deux parois cylindriques coaxiales, respectivement radialement interne et externe, qui sont reliées par des bras radiaux, la paroi interne étant entourée par une enveloppe cylindrique destinée au guidage d'un flux de gaz d'échappement provenant de la turbine.The exhaust casing of a turbomachine is mounted downstream of a turbine and generally comprises two coaxial cylindrical walls, respectively radially inner and outer, which are connected by radial arms, the inner wall being surrounded by a cylindrical envelope intended to guiding an exhaust stream from the turbine.

L'enveloppe cylindrique est fixée par son extrémité aval à la paroi interne du carter d'échappement, et elle comprend à son extrémité amont une partie annulaire radiale s'étendant librement vers l'axe de la turbomachine de sorte que la paroi interne du carter d'échappement et l'enveloppe cylindrique délimitent une cavité, couramment appelée cavité de moyeu.The cylindrical envelope is fixed by its downstream end to the inner wall of the exhaust casing, and comprises at its upstream end a radial annular portion extending freely towards the axis of the turbomachine so that the inner wall of the casing exhaust and the cylindrical envelope delimit a cavity, commonly called hub cavity.

Cette cavité est ouverte au niveau de l'extrémité interne de la partie annulaire radiale de l'enveloppe cylindrique.This cavity is open at the inner end of the radial annular portion of the cylindrical envelope.

Il en résulte une circulation d'air provenant de l'amont dans la cavité de moyeu, cet air entrant dans la cavité par son ouverture amont et étant prélevé entre les compresseurs haute-pression et basse-pression de la turbomachine, ce qui a une influence négative sur la consommation en carburant de cette turbomachine.This results in a flow of air coming from upstream in the hub cavity, this air entering the cavity through its upstream opening and being taken between the high-pressure and low-pressure compressors of the turbomachine, which has a negative influence on the fuel consumption of this turbomachine.

La circulation d'air frais dans la cavité de moyeu tend à refroidir la paroi interne du carter d'échappement et les extrémités radialement internes des bras radiaux de ce carter, tandis que les parties radialement externes de ces bras sont maintenues à des températures relativement élevées par le flux de gaz d'échappement. Cela induit dans ces bras radiaux un gradient thermique important qui s'avère préjudiciable à leur durée de vie.The flow of fresh air into the hub cavity tends to cool the inner wall of the exhaust housing and the radially inner ends of the radial arms of this housing, while the radially outer portions of these arms are maintained at relatively high temperatures. by the flow of exhaust gas. This induces in these arms radials a significant thermal gradient that is detrimental to their service life.

En outre, du fait de sa partie annulaire radiale libre, l'enveloppe cylindrique présente des modes de vibration correspondant sensiblement aux fréquences du ou des rotors de la turbomachine, et est donc susceptible d'entrer en résonance avec le ou les rotors, générant alors de fortes vibrations de nature à pénaliser la durée de vie de l'enveloppe cylindrique.In addition, because of its free radial annular portion, the cylindrical envelope has vibration modes substantially corresponding to the frequencies of the rotor or rotors of the turbomachine, and is therefore likely to resonate with the rotor or rotors, thereby generating strong vibrations likely to penalize the life of the cylindrical envelope.

L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces problèmes, permettant d'éviter les inconvénients de la technique connue.The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.

Elle propose à cet effet un carter d'échappement de turbomachine, comprenant deux parois cylindriques coaxiales, respectivement radialement interne et radialement externe, reliées par des bras radiaux, et une enveloppe cylindrique solidaire de l'extrémité aval de la paroi radialement interne et qui délimite une cavité de moyeu avec la paroi radialement interne et un espace d'écoulement de gaz d'échappement avec la paroi radialement externe, l'enveloppe cylindrique comportant à son extrémité amont une partie annulaire radiale s'étendant vers l'axe de la turbomachine, caractérisé en ce que la partie annulaire radiale de l'enveloppe comporte à son extrémité interne un rebord annulaire coopérant par glissement radial sensiblement à étanchéité avec la paroi cylindrique interne du carter d'échappement.It proposes for this purpose a turbomachine exhaust casing, comprising two coaxial cylindrical walls, respectively radially inner and radially outer, connected by radial arms, and a cylindrical envelope integral with the downstream end of the radially inner wall and which delimits a hub cavity with the radially inner wall and an exhaust gas flow space with the radially outer wall, the cylindrical shell having at its upstream end a radial annular portion extending towards the axis of the turbomachine, characterized in that the radial annular portion of the casing has at its inner end an annular flange cooperating by substantially radially sliding radial sealing with the inner cylindrical wall of the exhaust casing.

Le rebord annulaire de la partie radiale de l'enveloppe cylindrique permet d'empêcher la circulation d'air dans la cavité de moyeu.The annular flange of the radial portion of the cylindrical casing makes it possible to prevent the circulation of air in the hub cavity.

Cela permet de minimiser le gradient thermique dans les bras radiaux du carter d'échappement, et ainsi d'accroître leur durée de vie, et cela réduit le prélèvement d'air sur les compresseurs de la turbomachine.This makes it possible to minimize the thermal gradient in the radial arms of the exhaust casing, and thus to increase their service life, and this reduces the intake of air on the compressors of the turbomachine.

Ce mode de liaison glissante radialement permet d'assurer une bonne étanchéité de la cavité de moyeu tout en évitant l'apparition de contraintes mécaniques dans l'enveloppe cylindrique du fait des dilatations thermiques susceptibles de se produire aux températures de fonctionnement de la turbomachine.This radially sliding connection mode makes it possible to ensure a good seal of the hub cavity while avoiding the appearance of mechanical stresses in the cylindrical envelope due to the expansions. thermal conditions that may occur at operating temperatures of the turbomachine.

En outre, le maintien axial de l'extrémité amont de l'enveloppe cylindrique permet d'élever les fréquences des modes de vibration de l'enveloppe et d'éviter ainsi les phénomènes de résonance, par exemple avec le rotor de la turbomachine, qui sont préjudiciables à sa tenue dans le temps.In addition, the axial retention of the upstream end of the cylindrical envelope makes it possible to raise the frequencies of the vibration modes of the envelope and thus to avoid the resonance phenomena, for example with the rotor of the turbomachine, which are detrimental to its behavior over time.

Selon une autre caractéristique de l'invention, la paroi interne du carter d'échappement comporte deux brides annulaires, respectivement amont et aval, s'étendant radialement vers l'extérieur et disposées en regard l'une de l'autre de manière à former une gorge annulaire destinée à recevoir le rebord annulaire de l'enveloppe cylindrique avec un jeu axial pour une liaison sensiblement étanche de l'enveloppe cylindrique à la paroi radialement interne autorisant un déplacement radial du rebord annulaire de l'enveloppe.According to another characteristic of the invention, the inner wall of the exhaust casing comprises two annular flanges, respectively upstream and downstream, extending radially outwards and disposed facing each other so as to form an annular groove for receiving the annular flange of the cylindrical envelope with an axial clearance for a substantially sealed connection of the cylindrical envelope to the radially inner wall allowing a radial displacement of the annular flange of the envelope.

Dans un mode de réalisation préféré de l'invention, les deux brides de la paroi interne du carter d'échappement ont une dimension radiale supérieure à une amplitude maximale admissible d'un déplacement radial du rebord annulaire de l'enveloppe cylindrique provoqué par une dilatation thermique de cette dernière.In a preferred embodiment of the invention, the two flanges of the inner wall of the exhaust casing have a radial dimension greater than a maximum allowable amplitude of a radial displacement of the annular flange of the cylindrical envelope caused by an expansion. thermal of the latter.

Ainsi, le rebord annulaire de l'enveloppe cylindrique ne risque pas de se désengager de la gorge annulaire formée par les deux brides de la paroi interne du carter d'échappement sous l'effet des dilatations thermiques, du moins tant que le déplacement radial du rebord annulaire ne dépasse pas une valeur maximale correspondant à une température maximale prédéfinie que l'enveloppe cylindrique ne risque pas de dépasser lors du fonctionnement normal de la turbomachine.Thus, the annular flange of the cylindrical envelope is not likely to disengage from the annular groove formed by the two flanges of the inner wall of the exhaust casing under the effect of thermal expansion, at least as long as the radial displacement of the annular flange does not exceed a maximum value corresponding to a predetermined maximum temperature that the cylindrical envelope is not likely to exceed during normal operation of the turbomachine.

Le rebord annulaire de l'enveloppe cylindrique s'étend de préférence sensiblement jusqu'au fond de la gorge annulaire de la paroi interne du carter d'échappement en condition d'arrêt de la turbomachine.The annular flange of the cylindrical envelope preferably extends substantially to the bottom of the annular groove of the inner wall of the exhaust casing in stopping condition of the turbomachine.

Cela permet de maximiser l'amplitude des dilatations thermiques admissibles pour l'enveloppe cylindrique.This maximizes the amplitude of the thermal expansions admissible for the cylindrical envelope.

Selon une autre caractéristique de l'invention, l'enveloppe cylindrique est précontrainte élastiquement, en condition d'arrêt de la turbomachine, de manière à appliquer la face amont du rebord annulaire de sa partie annulaire radiale contre la bride annulaire amont de la paroi interne du carter d'échappement, pour assurer l'étanchéité de la cavité de moyeu.According to another characteristic of the invention, the cylindrical envelope is elastically preloaded, under stopping condition of the turbomachine, so as to apply the upstream face of the annular flange of its radial annular portion against the upstream annular flange of the inner wall. exhaust housing, to seal the hub cavity.

En variante, l'enveloppe cylindrique est précontrainte élastiquement, en condition d'arrêt de la turbomachine, de manière à appliquer la face aval du rebord annulaire de sa partie annulaire radiale contre la bride annulaire aval de la paroi interne du carter d'échappement, pour assurer l'étanchéité de la cavité de moyeu.As a variant, the cylindrical envelope is elastically prestressed, in the stopping condition of the turbomachine, so as to apply the downstream face of the annular flange of its radial annular part against the annular flange downstream of the internal wall of the exhaust casing, to seal the hub cavity.

Les phénomènes de dilation thermique en fonctionnement tendent alors à déplacer le rebord annulaire vers l'amont de sorte que sa face amont se retrouve appliquée contre la bride annulaire amont de la paroi interne du carter d'échappement, si bien que l'étanchéité de la cavité est préservée.The phenomena of thermal expansion in operation then tend to move the annular flange upstream so that its upstream face is again applied against the upstream annular flange of the inner wall of the exhaust casing, so that the sealing of the cavity is preserved.

Le rebord annulaire de la partie annulaire radiale de l'enveloppe cylindrique comprend de préférence à son extrémité radialement externe une collerette cylindrique s'étendant vers l'amont et formant une butée radiale d'appui sur la bride annulaire amont de la paroi interne du carter d'échappement.The annular flange of the radial annular portion of the cylindrical envelope preferably comprises at its radially outer end a cylindrical flange extending upstream and forming a radial bearing abutment on the upstream annular flange of the inner wall of the housing. exhaust.

Dans un autre mode de réalisation de l'invention, la partie annulaire radiale de l'enveloppe cylindrique comprend des orifices destinés au passage d'un flux d'air frais.In another embodiment of the invention, the radial annular portion of the cylindrical envelope comprises orifices for the passage of a flow of fresh air.

Ce mode de réalisation est bien adapté au cas où la cavité de moyeu requiert d'être ventilée. La dimension des orifices peut alors être choisie en fonction du niveau de ventilation nécessaire et permet de contrôler le débit d'air de ventilation.This embodiment is well suited to the case where the hub cavity requires to be ventilated. The size of the orifices can then be chosen according to the level of ventilation required and allows the ventilation air flow rate to be controlled.

L'invention concerne également une enveloppe cylindrique pour une turbomachine du type décrit ci-dessus, comprenant à l'une de ses extrémités une bride annulaire et à l'autre de ses extrémités une partie annulaire radiale s'étendant vers l'intérieur, caractérisée en ce que la partie annulaire radiale comporte à son extrémité radialement interne un rebord annulaire radial formé avec une collerette cylindrique.The invention also relates to a cylindrical envelope for a turbomachine of the type described above, comprising at one of its an annular flange and at the other end thereof an inwardly extending radial annular portion, characterized in that the radial annular portion has at its radially inner end a radial annular flange formed with a cylindrical flange.

L'invention concerne aussi une turbomachine équipée d'un carter d'échappement tel que décrit ci-dessus.The invention also relates to a turbomachine equipped with an exhaust casing as described above.

L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de celle-ci apparaîtront plus clairement à la lecture de la description suivante faite à titre d'exemple non limitatif, en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique en perspective d'un carter d'échappement d'une turbomachine selon l'invention ;
  • la figure 2 est une vue schématique en perspective d'une enveloppe cylindrique selon l'invention, équipant le carter d'échappement de la figure 1 ;
  • la figure 3 est une vue schématique partielle en coupe axiale d'une turbomachine comprenant le carter d'échappement de la figure 1 ;
  • la figure 3a est une vue agrandie du détail IIIa de la figure 3.
The invention will be better understood and other details, advantages and characteristics thereof will appear more clearly on reading the following description given by way of non-limiting example, with reference to the accompanying drawings in which:
  • the figure 1 is a schematic perspective view of an exhaust casing of a turbomachine according to the invention;
  • the figure 2 is a schematic perspective view of a cylindrical envelope according to the invention, fitted to the exhaust casing of the figure 1 ;
  • the figure 3 is a partial schematic view in axial section of a turbomachine comprising the exhaust casing of the figure 1 ;
  • the figure 3a is an enlarged view of detail IIIa of the figure 3 .

La figure 1 représente un carter d'échappement 10 de turbomachine comprenant deux parois cylindriques coaxiales, respectivement radialement interne 12 et externe 14, reliées par des bras radiaux structuraux 16.The figure 1 represents a turbomachine exhaust casing 10 comprising two coaxial cylindrical walls, respectively radially internal 12 and external 14, connected by radial structural arms 16.

Une enveloppe cylindrique 18 est montée autour de la paroi radialement interne 12 du carter d'échappement 10.A cylindrical casing 18 is mounted around the radially inner wall 12 of the exhaust casing 10.

Cette enveloppe 18, représentée isolément sur la figure 2, comprend une paroi cylindrique 20 dans laquelle sont formées des découpes 22 ouvertes vers l'aval pour le passage des bras radiaux 16 du carter d'échappement 10.This envelope 18, shown separately on the figure 2 , comprises a cylindrical wall 20 in which are formed cutouts 22 open downstream for the passage of the radial arms 16 of the exhaust casing 10.

L'enveloppe cylindrique 18 comprend à son extrémité aval une bride annulaire radiale 24 de fixation au carter d'échappement 10, et à son extrémité amont, une partie annulaire radiale 26 s'étendant radialement vers l'intérieur.The cylindrical casing 18 comprises at its downstream end a radial annular flange 24 for attachment to the exhaust casing 10, and to its upstream end, a radial annular portion 26 extending radially inwardly.

Comme cela sera expliqué plus en détail dans ce qui suit, l'enveloppe 18 comprend, selon l'invention, un rebord annulaire 28 formé à l'extrémité radialement interne de sa partie annulaire radiale 26.As will be explained in more detail in the following, the casing 18 comprises, according to the invention, an annular flange 28 formed at the radially inner end of its radial annular portion 26.

L'enveloppe 18 et la paroi radialement externe 14 du carter d'échappement délimitent un espace annulaire d'écoulement de gaz d'échappement à l'intérieur d'une turbomachine, représentée partiellement sur la figure 3.The casing 18 and the radially outer wall 14 of the exhaust casing delimit an annular space for exhaust gas flow inside a turbomachine, represented partially on the figure 3 .

Cette figure 3 montre le carter d'échappement 10 monté en aval d'une turbine basse-pression 30, comprenant des disques 32 portant des aubes 34, et entraînant en rotation un arbre relié à un compresseur en amont (non représenté), d'une manière bien connue.This figure 3 shows the exhaust casing 10 mounted downstream of a low-pressure turbine 30, comprising discs 32 carrying blades 34, and rotating a shaft connected to an upstream compressor (not shown), in a manner well known.

Le carter d'échappement 10 comprend une paroi radiale aval 36 s'étendant radialement vers l'extérieur depuis l'extrémité aval de la paroi interne 12 du carter, et à laquelle est fixée la bride annulaire radiale 24 de l'enveloppe cylindrique.The exhaust casing 10 comprises a downstream radial wall 36 extending radially outwardly from the downstream end of the inner wall 12 of the casing, and to which is fixed the radial annular flange 24 of the cylindrical casing.

L'ensemble formé par la paroi interne 12 et la paroi radiale aval 36 du carter d'échappement 10 ainsi que par l'enveloppe cylindrique 18 délimite une cavité torique 38 couramment appelée cavité de moyeu.The assembly formed by the inner wall 12 and the downstream radial wall 36 of the exhaust casing 10 as well as by the cylindrical casing 18 defines a toric cavity 38 commonly called a hub cavity.

Dans les turbomachines selon l'art antérieur, la partie annulaire radiale de l'enveloppe cylindrique est libre à son extrémité radialement interne et ménage ainsi une ouverture annulaire dans la cavité de moyeu, entre l'extrémité libre de cette partie annulaire radiale et l'extrémité amont de la paroi interne du carter d'échappement.In the turbomachines according to the prior art, the radial annular portion of the cylindrical envelope is free at its radially inner end and thus provides an annular opening in the hub cavity, between the free end of this radial annular portion and the upstream end of the inner wall of the exhaust casing.

Pour éviter les inconvénients liés à cette configuration et comme cela a déjà été évoqué en référence à la figure 2, l'enveloppe cylindrique 18 selon l'invention comprend un rebord annulaire 28 formé à l'extrémité interne de la partie annulaire radiale 26 de l'enveloppe, et engagé, comme le montre la figure 3, dans une gorge annulaire 40 (fig. 3a) ouverte vers l'extérieur et formée par deux brides radiales, respectivement amont 42 et aval 44, disposées en regard l'une de l'autre et solidaires de la paroi interne 12 du carter d'échappement 10, pour fermer la cavité de moyeu 38 de manière sensiblement étanche et empêcher ainsi la circulation d'air frais dans cette cavité.To avoid the drawbacks associated with this configuration and as already mentioned with reference to the figure 2 , the cylindrical casing 18 according to the invention comprises an annular flange 28 formed at the inner end of the radial annular portion 26 of the casing, and engaged, as shown in FIG. figure 3 in an annular groove 40 ( Fig. 3a ) open towards the outside and formed by two radial flanges, respectively upstream 42 and downstream 44, arranged facing each other and integral with the inner wall 12 of the exhaust casing 10, to close the hub cavity 38 substantially sealingly and thus prevent the flow of fresh air into this cavity .

La bride aval 44 est par exemple formée à l'extrémité radialement externe d'une virole 46 s'étendant radialement vers l'extérieur depuis l'extrémité amont de la paroi interne 12 du carter d'échappement 10.The downstream flange 44 is for example formed at the radially outer end of a ferrule 46 extending radially outwards from the upstream end of the inner wall 12 of the exhaust casing 10.

La bride amont 42 peut quant à elle être formée par exemple dans le prolongement d'une bride radiale 48 de fixation d'un carter interne 50, couramment appelé carter de récupération d'huile, au carter d'échappement 10, le carter interne 50 s'étendant axialement entre l'arbre de la turbine et les disques 32 du rotor de cette turbine, en amont du carter d'échappement 10.The upstream flange 42 can for its part be formed for example in the extension of a radial flange 48 for fixing an inner casing 50, commonly called an oil recovery casing, to the exhaust casing 10, the inner casing 50 extending axially between the shaft of the turbine and the discs 32 of the rotor of this turbine, upstream of the exhaust casing 10.

Par ailleurs, le rebord annulaire 28 de l'enveloppe cylindrique 18 comprend à son extrémité radialement externe une collerette cylindrique 52 s'étendant vers l'amont et formant une butée radiale d'appui sur la bride annulaire amont 42 de la paroi interne 12 du carter d'échappement 10.Furthermore, the annular flange 28 of the cylindrical casing 18 comprises at its radially outer end a cylindrical flange 52 extending upstream and forming a radial bearing abutment on the upstream annular flange 42 of the inner wall 12 of the exhaust casing 10.

Comme le montre la figure 3a, l'étendue axiale de la gorge annulaire 40 est un peu supérieure à l'épaisseur du rebord annulaire 28 de l'enveloppe cylindrique 18 de sorte que ce dernier est engagé avec un jeu axial, par exemple de l'ordre de 1 mm, dans la gorge 40, de manière à autoriser un glissement radial du rebord annulaire 28 dans la gorge 40.As shown in figure 3a the axial extent of the annular groove 40 is slightly greater than the thickness of the annular flange 28 of the cylindrical envelope 18 so that the latter is engaged with an axial clearance, for example of the order of 1 mm, in the groove 40, so as to allow radial sliding of the annular flange 28 in the groove 40.

Cette possibilité de déplacement radial du rebord 28 à l'intérieur de la gorge 40 permet d'éviter l'apparition de contraintes mécaniques dans l'enveloppe cylindrique 18 du fait de phénomènes de dilatation thermique induits par l'élévation de la température au niveau du carter d'échappement 10 pendant le fonctionnement de la turbomachine.This possibility of radial displacement of the flange 28 inside the groove 40 makes it possible to avoid the appearance of mechanical stresses in the cylindrical envelope 18 due to thermal expansion phenomena induced by the rise in temperature at the level of the exhaust casing 10 during the operation of the turbomachine.

Par ailleurs, l'enveloppe cylindrique 18 est formée de telle sorte qu'à la température ambiante, lorsque la turbomachine est à l'arrêt, le rebord annulaire 18 s'étend sensiblement jusqu'au fond de la gorge annulaire 40.Moreover, the cylindrical envelope 18 is formed such that at room temperature, when the turbomachine is stopped, the annular flange 18 extends substantially to the bottom of the annular groove 40.

Cela permet de maximiser le déplacement radial vers l'extérieur admissible du rebord annulaire 28, c'est-à-dire le déplacement radial au-delà duquel le rebord 28 se désengage de la gorge annulaire 40, sous l'effet de la dilatation thermique de l'enveloppe cylindrique 18.This makes it possible to maximize the allowable radial outward movement of the annular flange 28, that is to say the radial displacement beyond which the flange 28 disengages from the annular groove 40, under the effect of thermal expansion. of the cylindrical envelope 18.

Les brides radiales 42 et 44 du carter d'échappement ont des dimensions radiales supérieures à une valeur de déplacement radial du rebord annulaire 28 considérée comme un maximum admissible dans des conditions de fonctionnement normal de la turbomachine, afin d'éviter tout risque de désengagement du rebord 28 hors de la gorge 40.The radial flanges 42 and 44 of the exhaust casing have radial dimensions greater than a value of radial displacement of the annular flange 28 considered as a maximum permissible under normal operating conditions of the turbomachine, in order to avoid any risk of disengagement of the engine. ledge 28 out of the throat 40.

En outre, l'enveloppe cylindrique 18 est précontrainte axialement pour appliquer, en condition d'arrêt de la turbomachine, la face amont 54 du rebord annulaire 28 contre la face aval 56 de la bride amont 42 de la paroi interne 12 du carter d'échappement 10, pour garantir au mieux l'étanchéité de la liaison entre l'enveloppe cylindrique 18 et la paroi interne 12 du carter.In addition, the cylindrical casing 18 is prestressed axially to apply, in stopping condition of the turbomachine, the upstream face 54 of the annular flange 28 against the downstream face 56 of the upstream flange 42 of the inner wall 12 of the casing. exhaust 10, to better ensure the sealing of the connection between the cylindrical casing 18 and the inner wall 12 of the housing.

En fonctionnement, la dilatation thermique de l'enveloppe cylindrique tend alors à accroître encore la pression exercée par le rebord 28 sur la bride amont 42 du carter, si bien que l'étanchéité de la cavité de moyeu 38 est assurée en permanence.In operation, the thermal expansion of the cylindrical envelope then tends to further increase the pressure exerted by the flange 28 on the upstream flange 42 of the casing, so that the sealing of the hub cavity 38 is ensured permanently.

En variante, l'enveloppe cylindrique 18 pourrait être précontrainte axialement pour appliquer la face aval 58 du rebord annulaire 28 contre la face amont 60 de la bride aval 44 de la paroi interne 12 du carter d'échappement 10. Dans ce cas, si la pression de l'air dans la cavité de moyeu 38 devient supérieure à la pression de l'air en amont du carter d'échappement, ou si une dilatation thermique de l'enveloppe cylindrique 18 conduit son rebord annulaire 28 à se déplacer vers l'amont, ce dernier se retrouve rapidement plaqué contre la bride amont 42 du carter d'échappement, de sorte que l'étanchéité de la cavité de moyeu 38 est préservée.As a variant, the cylindrical envelope 18 could be prestressed axially to apply the downstream face 58 of the annular flange 28 against the upstream face 60 of the downstream flange 44 of the inner wall 12 of the exhaust casing 10. In this case, if the air pressure in the hub cavity 38 becomes greater than the air pressure upstream of the exhaust casing, or if a thermal expansion of the cylindrical casing 18 causes its annular flange 28 to move towards the upstream, it is quickly pressed against the upstream flange 42 of the exhaust casing, so that the sealing of the hub cavity 38 is preserved.

Du fait du maintien de son extrémité amont, l'enveloppe cylindrique 18 présente des modes propres de vibration de fréquences plus élevées que dans l'art antérieur.Because of the maintenance of its upstream end, the cylindrical envelope 18 has higher frequencies of frequencies of vibration than in the prior art.

Cela diminue considérablement les risques de résonance entre cette enveloppe 18 et un rotor de la turbomachine, et améliore de ce fait la durée de vie de l'enveloppe 18.This considerably reduces the risks of resonance between this envelope 18 and a rotor of the turbomachine, and thereby improves the life of the envelope 18.

En outre, l'étanchéité de la cavité de moyeu 38 permet, comme cela a été expliqué ci-dessus, d'améliorer la durée de vie des bras radiaux 16 du carter d'échappement.In addition, the sealing of the hub cavity 38 makes it possible, as explained above, to improve the service life of the radial arms 16 of the exhaust casing.

Il se peut toutefois qu'un certain niveau de ventilation de la cavité de moyeu 38 soit nécessaire, auquel cas il peut être avantageux de ménager des orifices d'entrée d'air de diamètre déterminé dans la partie annulaire radiale 26 de l'enveloppe 18.It may, however, be that a certain level of ventilation of the hub cavity 38 is necessary, in which case it may be advantageous to provide air inlet orifices of a determined diameter in the radial annular portion 26 of the envelope 18. .

Claims (10)

Carter d'échappement (10) de turbomachine comprenant deux parois cylindriques coaxiales, respectivement radialement interne (12) et radialement externe (14), reliées par des bras radiaux (16), et une enveloppe cylindrique (18) solidaire de l'extrémité aval de la paroi radialement interne (12) et qui délimite une cavité de moyeu (38) avec la paroi radialement interne (12) et un espace d'écoulement de gaz d'échappement avec la paroi radialement externe (14), l'enveloppe cylindrique (18) comportant à son extrémité amont une partie annulaire radiale (26) s'étendant vers l'intérieur de la turbomachine, caractérisé en ce que la partie annulaire radiale (26) de l'enveloppe (18) comporte à son extrémité interne un rebord annulaire (28) coopérant par glissement radial sensiblement à étanchéité avec la paroi cylindrique interne (12) du carter d'échappement (10).Turbomachine exhaust casing (10) comprising two coaxial cylindrical walls, respectively radially inner (12) and radially outer (14), connected by radial arms (16), and a cylindrical casing (18) integral with the downstream end of the radially inner wall (12) and defining a hub cavity (38) with the radially inner wall (12) and an exhaust gas flow space with the radially outer wall (14), the cylindrical shell (18) having at its upstream end a radial annular portion (26) extending inwardly of the turbomachine, characterized in that the radial annular portion (26) of the casing (18) has at its inner end a annular flange (28) cooperating by radial sliding substantially sealing with the inner cylindrical wall (12) of the exhaust casing (10). Carter d'échappement (10) selon la revendication 1, caractérisé en ce que la paroi interne (12) du carter d'échappement (10) comporte deux brides annulaires, respectivement amont (42) et aval (44), s'étendant radialement vers l'extérieur et disposées en regard l'une de l'autre de manière à former une gorge annulaire (40) destinée à recevoir le rebord annulaire (28) de l'enveloppe cylindrique (18) avec un jeu axial pour une liaison étanche de l'enveloppe cylindrique (18) à la paroi radialement interne (12) autorisant un déplacement radial du rebord annulaire (28) de l'enveloppe (18).Exhaust casing (10) according to claim 1, characterized in that the inner wall (12) of the exhaust casing (10) comprises two annular flanges, respectively upstream (42) and downstream (44), extending radially outwardly and disposed facing each other so as to form an annular groove (40) for receiving the annular flange (28) of the cylindrical casing (18) with axial clearance for a tight connection from the cylindrical envelope (18) to the radially inner wall (12) allowing radial displacement of the annular flange (28) of the envelope (18). Carter d'échappement (10) selon la revendication 2, caractérisé en ce que les deux brides (42, 44) de la paroi interne (12) du carter d'échappement (10) ont une dimension radiale supérieure à une amplitude maximale admissible d'un déplacement radial du rebord annulaire (28) de l'enveloppe cylindrique (18) provoqué par une dilatation thermique de cette dernière.Exhaust casing (10) according to claim 2, characterized in that the two flanges (42, 44) of the inner wall (12) of the exhaust casing (10) have a radial dimension greater than a maximum admissible amplitude of a radial displacement of the annular rim (28) of the cylindrical envelope (18) caused by a thermal expansion of the latter. Carter d'échappement (10) selon la revendication 2 ou 3, caractérisé en ce que le rebord annulaire (28) de l'enveloppe cylindrique (18) s'étend sensiblement jusqu'au fond de la gorge annulaire (40) de la paroi interne (12) du carter d'échappement (10) en condition d'arrêt de la turbomachine.Exhaust housing (10) according to claim 2 or 3, characterized in that the annular flange (28) of the cylindrical casing (18) extends substantially to the bottom of the annular groove (40) of the inner wall (12) of the exhaust casing (10) in condition of shutdown of the turbomachine. Carter d'échappement (10) selon l'une des revendications 2 à 4, caractérisé en ce que l'enveloppe cylindrique (18) est précontrainte, en condition d'arrêt de la turbomachine, de manière à appliquer la face amont (54) du rebord annulaire (28) de sa partie annulaire radiale (26) contre la bride annulaire amont (42) de la paroi interne (12) du carter d'échappement, pour assurer l'étanchéité de la cavité de moyeu (38).Exhaust casing (10) according to one of claims 2 to 4, characterized in that the cylindrical casing (18) is prestressed in stopping condition of the turbomachine, so as to apply the upstream face (54) an annular flange (28) of its radial annular portion (26) against the upstream annular flange (42) of the inner wall (12) of the exhaust casing, for sealing the hub cavity (38). Carter d'échappement (10) selon l'une des revendications 2 à 4, caractérisé en ce que l'enveloppe cylindrique (18) est précontrainte, en condition d'arrêt de la turbomachine, de manière à appliquer la face aval (58) du rebord annulaire (28) de sa partie annulaire radiale (26) contre la bride annulaire aval (44) de la paroi interne (12) du carter d'échappement, pour assurer l'étanchéité de la cavité de moyeu (38).Exhaust casing (10) according to one of claims 2 to 4, characterized in that the cylindrical casing (18) is prestressed in stopping condition of the turbomachine, so as to apply the downstream face (58) an annular flange (28) of its radial annular portion (26) against the downstream annular flange (44) of the inner wall (12) of the exhaust casing, for sealing the hub cavity (38). Carter d'échappement (10) selon l'une des revendications 1 à 6, caractérisé en ce que le rebord annulaire (28) de la partie annulaire radiale (26) de l'enveloppe cylindrique (18) comprend à son extrémité radialement externe une collerette cylindrique (52) s'étendant vers l'amont et formant une butée radiale d'appui sur la bride annulaire amont (42) de la paroi interne (12) du carter d'échappement (10).Exhaust casing (10) according to one of claims 1 to 6, characterized in that the annular flange (28) of the radial annular portion (26) of the cylindrical casing (18) comprises at its radially outer end a cylindrical flange (52) extending upstream and forming a radial bearing abutment on the upstream annular flange (42) of the inner wall (12) of the exhaust casing (10). Carter d'échappement (10) selon l'une des revendications 1 à 7, caractérisé en ce que la partie annulaire radiale (26) de l'enveloppe cylindrique (18) comprend des orifices destinés au passage d'un flux d'air de ventilation.Exhaust casing (10) according to one of claims 1 to 7, characterized in that the radial annular portion (26) of the cylindrical casing (18) comprises orifices for the passage of an air flow of ventilation. Enveloppe cylindrique (18) pour un carter d'échappement (10) de turbomachine selon l'une des revendications précédentes, comprenant à l'une de ses extrémités une bride annulaire (24) et à l'autre de ses extrémités une partie annulaire radiale (26) s'étendant vers l'intérieur, caractérisée en ce que la partie annulaire radiale (26) comporte à son extrémité radialement interne un rebord annulaire radial (28) formé avec une collerette cylindrique.Cylindrical casing (18) for a turbomachine exhaust casing (10) according to one of the preceding claims, comprising at one of its ends an annular flange (24) and at the other end a radial annular portion Extending inwardly, characterized in that the radial annular portion (26) comprises at its radially inner end a radial annular flange (28) formed with a cylindrical collar. Turbomachine, caractérisée en ce qu'elle comprend un carter d'échappement (10) selon l'une des revendications 1 à 8.Turbomachine, characterized in that it comprises an exhaust casing (10) according to one of claims 1 to 8.
EP08168877A 2007-12-14 2008-11-12 Watertight assembly of a hub cavity of a turbomachine exhaust casing Active EP2071142B1 (en)

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FR0708713A FR2925119A1 (en) 2007-12-14 2007-12-14 SEALING A HUB CAVITY OF AN EXHAUST CASE IN A TURBOMACHINE

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EP2071142B1 (en) 2010-06-23
DE602008001592D1 (en) 2010-08-05
RU2008149138A (en) 2010-06-20
US20090155071A1 (en) 2009-06-18
CA2647058C (en) 2015-02-17
FR2925119A1 (en) 2009-06-19
US8172526B2 (en) 2012-05-08
JP2009144708A (en) 2009-07-02
JP5320046B2 (en) 2013-10-23
RU2478801C2 (en) 2013-04-10

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