EP1739309B1 - Multi stage turbomachine compressor - Google Patents

Multi stage turbomachine compressor Download PDF

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Publication number
EP1739309B1
EP1739309B1 EP06291053.4A EP06291053A EP1739309B1 EP 1739309 B1 EP1739309 B1 EP 1739309B1 EP 06291053 A EP06291053 A EP 06291053A EP 1739309 B1 EP1739309 B1 EP 1739309B1
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EP
European Patent Office
Prior art keywords
shrouds
casing
moving blades
wall
annular
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EP06291053.4A
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German (de)
French (fr)
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EP1739309A1 (en
Inventor
Gilles Alain Marie Charier
Franck Christian Conan
Thomas Julien Roland Earith
Marc Leandri
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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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel

Definitions

  • the invention relates to a multi-stage turbomachine compressor, in particular a high-pressure compressor, and to an airplane turbojet or turboprop engine equipped with this compressor.
  • a high-pressure turbojet or turboprop compressor comprises a plurality of compression stages each comprising an annular row of rotor blades rotating inside a stationary casing and mounted on a shaft of the turbomachine, and a annular row of fixed blades for rectifying the flow of air, which are carried by the casing at their radially outer ends.
  • the document US Patent 5,630,702 describes a compressor of this type.
  • a double wall casing comprising a fixed outer wall and an inner wall which can move radially and which is connected to the outer wall by flexible suspension means or deformable, called "pins".
  • the pins are also ventilated to modify their thermal expansion and thereby adjust the radial clearances between the internal wall of the casing and the ends of the moving blades of the different compression stages.
  • the compression stages are secured to one another, at least in groups of two, via the inner wall of the casing, which limits the possibilities of adjusting the radial clearances because these games are adjusted in the same way for the compression stages which are solidary, whereas the variations of these games differ from one stage to another,
  • the present invention is intended in particular to provide a simple, effective and economical solution to this problem.
  • It relates to a multi-stage turbomachine compressor, in particular a high-pressure compressor, in which it is possible to adjust the radial clearances of the different stages or at least some of the different stages independently for each stage.
  • a multi-stage turbomachine compressor comprising annular rows of moving blades rotating inside a double-walled casing and annular rows of fixed vanes mounted on an internal wall of the casing.
  • the inner wall of the housing comprises a plurality of rings substantially aligned end to end and suspended independently of one another to an outer wall of the housing by flexible or deformable means, some of the rings each surrounding an annular row of blades. and others ferrules each carrying an annular row of fixed vanes rectification.
  • the various stages of compression are therefore, totally or at least as regards some of them, disengaged from each other, which makes it possible to adjust the radial clearances of these stages in such a way that independent for each floor, taking into account differences in mass, radial dimension and operating temperature between floors. This results in an improvement of the efficiency of the compressor and the operability of the turbomachine.
  • each annular row of blades is surrounded by a ferrule suspended from the outer wall of the casing independently of the other ferrules which surround the other annular rows of blades.
  • a first ferrule surrounding an annular row of blades is adjacent to a second ferrule carrying an annular row of fixed blades for straightening, one axial end of this second ferrule being connected to the first ferrule. by means ensuring a seal with respect to the flow of gas passing through the compressor.
  • the second axial end of the second ferrule is connected to a third ferrule surrounding a another annular row of blades by means providing a seal against the flow of gas passing through the compressor.
  • the second axial end of the second ferrule may in this case be connected to the outer wall of the housing by the suspension means of the third ferrule.
  • the second axial end of the second ferrule is spaced axially from a third ferrule surrounding another annular row of blades and is connected by its own suspension means to the outer wall of the housing.
  • an annular clearance axially separating the second ferrule and the third ferrule constitutes an air inlet passage in a cavity which is formed in the housing between the suspension means of the second ferrule and those of the third ferrule. and in which open air intake means carried by the outer wall of the housing, these air intake means being connected to other equipment of the turbomachine.
  • the invention allows, in a general manner, that the radial vibration modes of the rings surrounding the annular rows of moving blades of the compressor are set independently of one ring to the other, that is to say one floor to the other, for an optimization of the radial clearances between these ferrules and the annular rows of moving blades which turn inside these ferrules.
  • the invention also relates to an aircraft turbojet or turboprop engine, characterized in that it comprises a high-pressure compressor as described above.
  • the compressor 10 of the figure 1 which illustrates the prior art, comprises a number of compression stages of which only three have been shown, each stage comprising an annular row of blades 12, the radially inner ends of which are fixed on a disk carried by a shaft of the turbomachine, and an annular row of fixed vanes 14 of rectification, arranged downstream of the annular row of moving blades 12 and whose radially outer ends are carried by a radially inner wall 16 of a cylindrical casing 18 to double wall.
  • the inner cylindrical wall 16 of the casing 18 is suspended from the outer cylindrical wall 20 of this casing by flexible or deformable means 22, commonly known as "pins" in the art, the shapes, the masses and the rigidities of which are known to be adjusted the inner wall 16 of the casing best follows the radial vibrations of the rotor comprising the annular rows of moving blades 12.
  • the inner cylindrical wall 16 of the housing is formed of coaxial ferrules 24, which are aligned end to end and rigidly connected to each other via their annular flanges 26, which extend radially towards the outside and which are fixed to each other by appropriate means such as bolts.
  • the outer wall 20 of the housing 18 may be composed of ferrules arranged end to end and fixedly connected to each other by their outer annular flanges 28 by means of bolts or the like.
  • these radial clearances can be adjusted independently of one compression stage to another, thanks to the fact that the ferrules which constitute the internal wall of the housing and which surround the annular rows of moving blades, are suspended independently of each other to the outer wall of the casing, for all compressor stages of the compressor or for at least a majority of them.
  • the inner wall of the housing 18 is formed of a succession of ferrules 30, 32 respectively, which are suspended from the outer wall 20 of the housing independently of each other by pins 34, 36 respectively, each ferrule 30 surrounding an annular row of blades 12 and each ferrule 32 carrying an annular row of fixed vanes 14.
  • the ferrule 30 is connected to the ferrule 32 situated downstream by means 38 providing an annular seal between these two ferrules with respect to the flow of gas passing through the compressor, which makes it possible to ensure the continuity of this flow of gas in the compressor and prevents the entry of air into the space between the inner and outer walls of the housing 18.
  • the suspensions independent of the various rings 30, 32 of the inner wall of the casing make it possible to adjust independently of one another the radial clearances J1 and J2 between the radially outer ends of the blades 12 and the rings 30 in each compression stage. .
  • the order of magnitude of these radial clearances is the tenth of a millimeter, the number of compression stages of a high-pressure compressor can be between 5 and 10 approximately, depending on the engines.
  • the ferrule 30 of the compression stage E2 which surrounds the annular row of moving blades 12 of this stage, is connected at its downstream end to a shell 32 which carries the annular row of fixed vanes 14 for straightening this stage. and whose downstream end is connected by suspension means 36 to the outer wall of the casing 18.
  • the ferrule 32 of the compression stage E2 is separated from the ferrule 30 of the next compression stage E3 by an axial annular clearance 42 which forms a gas passage between the inside of the compressor and a cavity 44 defined in the crankcase. 18 between the inner and outer walls of the latter on the one hand and between the means 36 for suspending the ferrule 32 of the previous stage E2 and the means 34 for suspending the ferrule 30 of the stage E3, somewhere else.
  • One or more air intakes 46 are formed in the outer wall of the casing 18 and open into this cavity 44, to supply air to the equipment of the turbomachine.
  • the downstream end of the ferrule 30 of the compression stage E3 is sealingly connected to the upstream end of a ferrule 32 carrying the fixed vanes 14 of this compression stage.
  • the downstream end of this ferrule 32 is connected sealingly, for example by interlocking, to the upstream end of the shell 30 of the next compression stage E4 which is connected by its suspension means 34 to the outer wall of the casing 18.
  • the ferrule 32 of the compression stage E3 is thus carried by the ferrule 30 of this compression stage and by the ferrule 30 of the next compression stage E4.
  • Another air intake 46 may be formed in the outer wall of the casing 18 and opens into a cavity 48 formed between the inner and outer walls of the housing 18 downstream of the suspension means 34 of the ferrule 30 of the stage E4.
  • the radial clearances of the compression stage E2 can be regulated independently of the radial clearances of the compression stage E1 and the following compression stages E3 and E4 while the games
  • the radial blades of the compression stages E3 and E4 are set independently, the blades 12 of these two stages having the same radial dimensions, the rings 30 of the stages E3 and E4 being secured to one another by the ferrule 32. from floor E3.

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

Description

L'invention concerne un compresseur multi-étages de turbomachine, en particulier un compresseur haute-pression, ainsi qu'un turboréacteur ou un turbopropulseur d'avion équipé de ce compresseur.The invention relates to a multi-stage turbomachine compressor, in particular a high-pressure compressor, and to an airplane turbojet or turboprop engine equipped with this compressor.

Un compresseur haute-pression de turboréacteur ou de turbopropulseur comprend une pluralité d'étages de compression comportant chacun une rangée annulaire d'aubes mobiles de rotor tournant à l'intérieur d'un carter fixe et montées sur un arbre de la turbomachine, et une rangée annulaire d'aubes fixes de redressement du flux d'air, qui sont portées par le carter à leurs extrémités radialement externes. Le document US-A-5,630,702 décrit un compresseur de ce type.A high-pressure turbojet or turboprop compressor comprises a plurality of compression stages each comprising an annular row of rotor blades rotating inside a stationary casing and mounted on a shaft of the turbomachine, and a annular row of fixed blades for rectifying the flow of air, which are carried by the casing at their radially outer ends. The document US Patent 5,630,702 describes a compressor of this type.

Il est très important que les jeux radiaux entre les aubes mobiles et le carter soient optimisés, pour améliorer le rendement du compresseur et de la turbomachine et pour éviter tout frottement des extrémités des aubes mobiles sur le carter, qui se traduirait par une usure de ces extrémités et par une dégradation permanente du rendement de la turbomachine à tous les régimes de fonctionnement.It is very important that the radial clearances between the blades and the crankcase are optimized, to improve the efficiency of the compressor and the turbomachine and to avoid any friction of the ends of the blades on the crankcase, which would result in wear of these blades. extremes and by a permanent deterioration of the efficiency of the turbomachine at all operating speeds.

L'optimisation des jeux radiaux est un problème très complexe, car ces jeux dépendent de paramètres différents tels que les températures de fonctionnement, qui varient d'un étage de compression à l'autre, de la vitesse de rotation du compresseur, et des vitesses de vibration radiale du stator et du rotor, qui sont différentes et qui varient également d'un étage de compression à l'autre, en raison des différences de masse et de dimensions radiales des aubes mobiles dans les différents étages.The optimization of the radial clearances is a very complex problem, because these games depend on different parameters such as the operating temperatures, which vary from one compression stage to another, the speed of rotation of the compressor, and the speeds radial vibration of the stator and the rotor, which are different and which also vary from one compression stage to another, due to the differences in mass and radial dimensions of the blades in the different stages.

Pour apporter une solution partielle à ce problème, on a déjà proposé d'utiliser un carter à double paroi, comprenant une paroi externe fixe et une paroi interne qui peut se déplacer radialement et qui est reliée à la paroi externe par des moyens de suspension souples ou déformables, appelés « épingles ».To provide a partial solution to this problem, it has already been proposed to use a double wall casing, comprising a fixed outer wall and an inner wall which can move radially and which is connected to the outer wall by flexible suspension means or deformable, called "pins".

Par calcul, on peut connaître les vitesses de vibration radiale du carter et du rotor pour les différents régimes de fonctionnement et on détermine ensuite les formes, les masses et les rigidités des épingles pour que le comportement vibratoire de la paroi interne du carter soit adapté au mieux au comportement vibratoire du rotor. Par injection d'air dans le carter, on assure également une ventilation des épingles pour modifier leur dilatation thermique et régler par ce moyen les jeux radiaux entre la paroi interne du carter et les extrémités des aubes mobiles des différents étages de compression.By calculation, it is possible to know the radial vibration velocities of the housing and the rotor for the various operating regimes, and the shapes, the masses and the stiffnesses of the pins are then determined so that the vibratory behavior of the inner wall of the housing is adapted to the better to the vibratory behavior of the rotor. By injecting air into the casing, the pins are also ventilated to modify their thermal expansion and thereby adjust the radial clearances between the internal wall of the casing and the ends of the moving blades of the different compression stages.

Toutefois, dans la technique connue, les étages de compression sont solidarisés les uns avec les autres, au moins par groupes de deux, par l'intermédiaire de la paroi interne du carter, ce qui limite les possibilités de réglage des jeux radiaux du fait que ces jeux sont réglés de la même façon pour les étages de compression qui sont solidaires, alors que les variations de ces jeux diffèrent d'un étage à l'autre,However, in the known art, the compression stages are secured to one another, at least in groups of two, via the inner wall of the casing, which limits the possibilities of adjusting the radial clearances because these games are adjusted in the same way for the compression stages which are solidary, whereas the variations of these games differ from one stage to another,

La présente invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.The present invention is intended in particular to provide a simple, effective and economical solution to this problem.

Elle a pour objet un compresseur multi-étages de turbomachine, en particulier un compresseur haute-pression, dans lequel on peut régler les jeux radiaux des différents étages ou d'au moins certains des différents étages de façon indépendante pour chaque étage.It relates to a multi-stage turbomachine compressor, in particular a high-pressure compressor, in which it is possible to adjust the radial clearances of the different stages or at least some of the different stages independently for each stage.

Elle propose à cet effet un compresseur multi-étages de turbomachine, comprenant des rangées annulaires d'aubes mobiles tournant à l'intérieur d'un carter à double paroi et des rangées annulaires d'aubes fixes de redressement portées par une paroi interne du carter, caractérisé en ce que la paroi interne du carter comprend plusieurs viroles alignées sensiblement bout à bout et suspendues indépendamment les unes des autres à une paroi externe du carter par des moyens souples ou déformables, certaines des viroles entourant chacune une rangée annulaire d'aubes mobiles et d'autres des viroles portant chacune une rangée annulaire d'aubes fixes de redressement.To this end, it proposes a multi-stage turbomachine compressor, comprising annular rows of moving blades rotating inside a double-walled casing and annular rows of fixed vanes mounted on an internal wall of the casing. , characterized in that the inner wall of the housing comprises a plurality of rings substantially aligned end to end and suspended independently of one another to an outer wall of the housing by flexible or deformable means, some of the rings each surrounding an annular row of blades. and others ferrules each carrying an annular row of fixed vanes rectification.

Dans le compresseur selon l'invention, les différents étages de compression sont donc, en totalité ou au moins en ce qui concerne certains d'entre eux, désolidarisés les uns des autres, ce qui permet de régler les jeux radiaux de ces étages de façon indépendante pour chaque étage, en tenant compte des différences de masse, de dimension radiale et de température de fonctionnement entre les étages. Il en résulte une amélioration du rendement du compresseur et de l'opérabilité de la turbomachine.In the compressor according to the invention, the various stages of compression are therefore, totally or at least as regards some of them, disengaged from each other, which makes it possible to adjust the radial clearances of these stages in such a way that independent for each floor, taking into account differences in mass, radial dimension and operating temperature between floors. This results in an improvement of the efficiency of the compressor and the operability of the turbomachine.

Il est donc possible dans le compresseur selon l'invention que chaque rangée annulaire d'aubes mobiles soit entourée par une virole suspendue à la paroi externe du carter de façon indépendante des autres viroles qui entourent les autres rangées annulaires d'aubes mobiles.It is therefore possible in the compressor according to the invention that each annular row of blades is surrounded by a ferrule suspended from the outer wall of the casing independently of the other ferrules which surround the other annular rows of blades.

Il est également possible que deux viroles de la paroi interne du carter qui entourent deux rangées annulaires successives d'aubes mobiles, soient solidarisées l'une avec l'autre lorsque ces aubes mobiles ont les mêmes dimensions dans les deux rangées annulaires.It is also possible that two ferrules of the inner wall of the housing which surround two successive annular rows of moving blades, are secured to each other when these blades have the same dimensions in the two annular rows.

Dans ce cas en effet, le comportement vibratoire des aubes dans les deux étages de compression ne sera pas modifié par des différences de masse et de dimension radiale des aubes mobiles et il est alors acceptable que ces deux étages semblables de compression soient solidarisés l'un avec l'autre.In this case, in fact, the vibratory behavior of the blades in the two compression stages will not be modified by differences in mass and radial dimension of the blades and it is then acceptable that these two similar stages of compression are secured to one another. with the other.

Selon une autre caractéristique de l'invention, une première virole entourant une rangée annulaire d'aubes mobiles est adjacente à une seconde virole portant une rangée annulaire d'aubes fixes de redressement, une extrémité axiale de cette seconde virole étant reliée à la première virole par des moyens assurant une étanchéité par rapport au flux de gaz passant dans le compresseur.According to another characteristic of the invention, a first ferrule surrounding an annular row of blades is adjacent to a second ferrule carrying an annular row of fixed blades for straightening, one axial end of this second ferrule being connected to the first ferrule. by means ensuring a seal with respect to the flow of gas passing through the compressor.

On assure ainsi la continuité du flux de gaz passant dans le compresseur.This ensures the continuity of the flow of gas passing through the compressor.

Selon une autre caractéristique de l'invention, la seconde extrémité axiale de la seconde virole est reliée à une troisième virole entourant une autre rangée annulaire d'aubes mobiles par des moyens assurant une étanchéité par rapport au flux de gaz passant dans le compresseur.According to another characteristic of the invention, the second axial end of the second ferrule is connected to a third ferrule surrounding a another annular row of blades by means providing a seal against the flow of gas passing through the compressor.

On assure ainsi de cette façon la continuité du flux de gaz passant dans le compresseur en interdisant les sorties de gaz dans l'espace compris entre les deux parois du carter, tout en permettant une suspension indépendante de la première et de la troisième virole, pour des réglages indépendants des jeux radiaux dans ces deux étages de compression.This ensures the continuity of the flow of gas passing through the compressor by prohibiting the gas outlets in the space between the two walls of the housing, while allowing a suspension independent of the first and third ferrule, for independent adjustments of the radial clearances in these two stages of compression.

La seconde extrémité axiale de la seconde virole peut dans ce cas être reliée à la paroi externe du carter par les moyens de suspension de la troisième virole.The second axial end of the second ferrule may in this case be connected to the outer wall of the housing by the suspension means of the third ferrule.

Dans une variante possible de réalisation, la seconde extrémité axiale de la seconde virole est écartée axialement d'une troisième virole entourant une autre rangée annulaire d'aubes mobiles et est reliée par ses propres moyens de suspension à la paroi externe du carter.In a possible variant embodiment, the second axial end of the second ferrule is spaced axially from a third ferrule surrounding another annular row of blades and is connected by its own suspension means to the outer wall of the housing.

Dans ce cas, un jeu annulaire séparant axialement la seconde virole et la troisième virole, constitue un passage d'entrée d'air dans une cavité qui est formée dans le carter entre les moyens de suspension de la seconde virole et ceux de la troisième virole et dans laquelle débouchent des moyens de prélèvement d'air portés par la paroi externe du carter, ces moyens de prélèvement d'air étant reliés à d'autres équipements de la turbomachine.In this case, an annular clearance axially separating the second ferrule and the third ferrule constitutes an air inlet passage in a cavity which is formed in the housing between the suspension means of the second ferrule and those of the third ferrule. and in which open air intake means carried by the outer wall of the housing, these air intake means being connected to other equipment of the turbomachine.

On évite ainsi que le gaz qui sort du compresseur par ce jeu annulaire axial, s'accumule entre les deux parois du carter et créé une zone morte dont la température ne serait pas contrôlable, au détriment d'un réglage précis des jeux radiaux des étages de compression adjacents.This prevents the gas leaving the compressor by this axial annular clearance, accumulates between the two walls of the housing and creates a dead zone whose temperature would not be controllable, to the detriment of a precise adjustment of the radial clearances of the floors adjacent compression.

L'invention permet, de façon générale, que les modes de vibration radiale des viroles entourant les rangées annulaires d'aubes mobiles du compresseur soient réglés indépendamment d'une virole à l'autre, c'est-à-dire d'un étage à l'autre, pour une optimisation des jeux radiaux entre ces viroles et les rangées annulaires d'aubes mobiles qui tournent à l'intérieur de ces viroles.The invention allows, in a general manner, that the radial vibration modes of the rings surrounding the annular rows of moving blades of the compressor are set independently of one ring to the other, that is to say one floor to the other, for an optimization of the radial clearances between these ferrules and the annular rows of moving blades which turn inside these ferrules.

En pratique, on cherchera à ce que ces jeux radiaux soient les plus faibles possible pour un régime de fonctionnement usuel, correspondant par exemple à une vitesse de croisière, les autres régimes de fonctionnement se caractérisant par des jeux radiaux plus importants mais néanmoins acceptables.In practice, it will be sought that these radial clearances are as small as possible for a usual operating regime, corresponding for example to a cruising speed, the other operating modes being characterized by larger radial clearances but nevertheless acceptable.

L'invention concerne également un turboréacteur ou un turbopropulseur d'avion, caractérisé en ce qu'il comprend un compresseur haute-pression tel que décrit dans ce qui précède.The invention also relates to an aircraft turbojet or turboprop engine, characterized in that it comprises a high-pressure compressor as described above.

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

  • la figure 1 est une vue très schématique en coupe axiale d'une partie d'un compresseur haute-pression d'une turbomachine de la technique antérieure ;
  • la figure 2 est une vue très schématique en coupe axiale d'une partie d'un compresseur haute-pression selon l'invention ;
  • la figure 3 est une autre vue schématique en coupe axiale d'une partie d'un compresseur selon l'invention.
The invention will be better understood and other characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of example with reference to the accompanying drawings in which:
  • the figure 1 is a schematic view in axial section of a portion of a high-pressure compressor of a turbomachine of the prior art;
  • the figure 2 is a schematic view in axial section of a portion of a high-pressure compressor according to the invention;
  • the figure 3 is another schematic view in axial section of a portion of a compressor according to the invention.

Dans les figures 1 à 3, ce qui se trouve à gauche est en amont et ce qui se trouve à droite est en aval par rapport au sens d'écoulement de l'air dans le compresseur.In the Figures 1 to 3 , which is on the left is upstream and what is on the right is downstream with respect to the direction of flow of the air in the compressor.

Le compresseur 10 de la figure 1, qui illustre la technique antérieure, comprend un certain nombre d'étages de compression dont trois seulement ont été représentés, chaque étage comportant une rangée annulaire d'aubes mobiles 12, dont les extrémités radialement internes sont fixées sur un disque porté par un arbre de la turbomachine, et une rangée annulaire d'aubes fixes 14 de redressement, agencées en aval de la rangée annulaire d'aubes mobile 12 et dont les extrémités radialement externes sont portées par une paroi radialement interne 16 d'un carter cylindrique 18 à-double paroi.The compressor 10 of the figure 1 , which illustrates the prior art, comprises a number of compression stages of which only three have been shown, each stage comprising an annular row of blades 12, the radially inner ends of which are fixed on a disk carried by a shaft of the turbomachine, and an annular row of fixed vanes 14 of rectification, arranged downstream of the annular row of moving blades 12 and whose radially outer ends are carried by a radially inner wall 16 of a cylindrical casing 18 to double wall.

La paroi cylindrique interne 16 du carter 18 est suspendue à la paroi cylindrique externe 20 de ce carter par des moyens souples ou déformables 22, communément appelés « épingles » dans la technique, dont on sait régler les formes, les masses et les rigidités de façon à ce que la paroi interne 16 du carter suive au mieux les vibrations radiales du rotor comportant les rangées annulaires d'aubes mobiles 12.The inner cylindrical wall 16 of the casing 18 is suspended from the outer cylindrical wall 20 of this casing by flexible or deformable means 22, commonly known as "pins" in the art, the shapes, the masses and the rigidities of which are known to be adjusted the inner wall 16 of the casing best follows the radial vibrations of the rotor comprising the annular rows of moving blades 12.

Dans cette technique connue, la paroi cylindrique interne 16 du carter est formée de viroles 24 coaxiales, qui sont alignées bout à bout et reliées rigidement les unes aux autres par l'intermédiaire de leurs brides annulaires 26, qui s'étendent radialement vers l'extérieur et qui sont fixées les unes aux autres par des moyens appropriés tels que des boulons.In this known technique, the inner cylindrical wall 16 of the housing is formed of coaxial ferrules 24, which are aligned end to end and rigidly connected to each other via their annular flanges 26, which extend radially towards the outside and which are fixed to each other by appropriate means such as bolts.

Comme la paroi interne 16, la paroi externe 20 du carter 18 peut être composée de viroles agencées bout à bout et reliées fixement entre elles par leurs brides annulaires externes 28 au moyen de boulons ou analogues.Like the inner wall 16, the outer wall 20 of the housing 18 may be composed of ferrules arranged end to end and fixedly connected to each other by their outer annular flanges 28 by means of bolts or the like.

Les épingles de suspension 22, qui relient la paroi externe 20 du carter aux brides annulaires 26 des viroles 24 de la paroi interne 16, permettent un réglage des jeux radiaux J entre ces viroles 24 et les extrémités radialement externes des aubes mobiles 12, mais ce réglage est le même pour les trois étages de compression représentés au dessin alors que ces jeux radiaux varient de façon différente d'un étage à l'autre aux différents régimes de fonctionnement de la turbomachine.The suspension pins 22, which connect the outer wall 20 of the housing to the annular flanges 26 of the ferrules 24 of the inner wall 16, allow adjustment of the radial clearances J between these ferrules 24 and the radially outer ends of the blades 12, but this adjustment is the same for the three compression stages shown in the drawing while these radial clearances vary in a different way from one stage to another at different operating speeds of the turbomachine.

Dans le compresseur selon l'invention, et comme on le voit sur l'exemple de réalisation de la figure 2, ces jeux radiaux peuvent être réglés indépendamment d'un étage de compression à l'autre, grâce au fait que les viroles qui constituent la paroi interne du carter et qui entourent les rangées annulaires d'aubes mobiles, sont suspendues indépendamment les unes des autres à la paroi externe du carter, pour la totalité des étages de compression du compresseur ou pour au moins une majeure partie d'entre eux.In the compressor according to the invention, and as can be seen in the embodiment of the figure 2 these radial clearances can be adjusted independently of one compression stage to another, thanks to the fact that the ferrules which constitute the internal wall of the housing and which surround the annular rows of moving blades, are suspended independently of each other to the outer wall of the casing, for all compressor stages of the compressor or for at least a majority of them.

En figure 2, où deux étages de compression du compresseur selon l'invention ont été représentés schématiquement, la paroi interne du carter 18 est formée d'une succession de viroles 30, 32 respectivement, qui sont suspendues à la paroi externe 20 du carter indépendamment les unes des autres par des épingles 34, 36 respectivement, chaque virole 30 entourant une rangée annulaire d'aubes mobiles 12 et chaque virole 32 portant une rangée annulaire d'aubes fixes de redressement 14.In figure 2 where two compression stages of the compressor the invention have been shown schematically, the inner wall of the housing 18 is formed of a succession of ferrules 30, 32 respectively, which are suspended from the outer wall 20 of the housing independently of each other by pins 34, 36 respectively, each ferrule 30 surrounding an annular row of blades 12 and each ferrule 32 carrying an annular row of fixed vanes 14.

Dans chaque étage de compression, la virole 30 est raccordée à la virole 32 située en aval par des moyens 38 assurant une étanchéité annulaire entre ces deux viroles par rapport au flux de gaz passant dans le compresseur, ce qui permet d'assurer la continuité de ce flux de gaz dans le compresseur et évite l'entrée d'air dans l'espace compris entre les parois interne et externe du carter 18.In each compression stage, the ferrule 30 is connected to the ferrule 32 situated downstream by means 38 providing an annular seal between these two ferrules with respect to the flow of gas passing through the compressor, which makes it possible to ensure the continuity of this flow of gas in the compressor and prevents the entry of air into the space between the inner and outer walls of the housing 18.

Les suspensions indépendantes des diverses viroles 30, 32 de la paroi interne du carter permettent de régler indépendamment l'un de l'autre les jeux radiaux J1 et J2 entre les extrémités radialement externes des aubes mobiles 12 et les viroles 30 dans chaque étage de compression. De façon typique, l'ordre de grandeur de ces jeux radiaux est le dixième de millimètre, le nombre d'étages de compression d'un compresseur haute-pression pouvant être compris entre 5 et 10 environ, selon les moteurs.The suspensions independent of the various rings 30, 32 of the inner wall of the casing make it possible to adjust independently of one another the radial clearances J1 and J2 between the radially outer ends of the blades 12 and the rings 30 in each compression stage. . Typically, the order of magnitude of these radial clearances is the tenth of a millimeter, the number of compression stages of a high-pressure compressor can be between 5 and 10 approximately, depending on the engines.

Dans la représentation de la figure 3, qui est plus détaillée que celle de la figure 2, on voit une virole 32 de la paroi interne du carter 18, qui porte une rangée annulaire d'aubes fixes 14 de redressement d'un étage de compression E1, et qui est reliée à la paroi externe du carter par des moyens de suspension 36 et coopère à son extrémité aval avec l'extrémité amont d'une virole 30 de l'étage de compression E2 suivant, par l'intermédiaire de moyens d'étanchéité 40 de forme annulaire qui sont montés, par exemple, dans une gorge de l'extrémité amont de la virole 30 de l'étage E2 et qui sont appliqués sur l'extrémité aval de la virole 32 de l'étage E1 ou sur une face annulaire radiale des moyens 36 de suspension de cette virole 32.In the representation of the figure 3 , which is more detailed than that of the figure 2 , there is seen a shell 32 of the inner wall of the casing 18, which carries an annular row of fixed vanes 14 for rectifying a compression stage E1, and which is connected to the outer wall of the casing by suspension means 36 and cooperates at its downstream end with the upstream end of a ferrule 30 of the next compression stage E2, by means of annular sealing means 40 which are mounted, for example, in a throat of the upstream end of the ferrule 30 of the stage E2 and which are applied to the downstream end of the ferrule 32 of the stage E1 or on a radial annular face of the means 36 for suspending this ferrule 32.

La virole 30 de l'étage de compression E2, qui entoure la rangée annulaire d'aubes mobiles 12 de cet étage, est raccordée à son extrémité aval à une virole 32 qui porte la rangée annulaire d'aubes fixes 14 de redressement de cet étage et dont l'extrémité aval est raccordée par des moyens de suspension 36 à la paroi externe du carter 18.The ferrule 30 of the compression stage E2, which surrounds the annular row of moving blades 12 of this stage, is connected at its downstream end to a shell 32 which carries the annular row of fixed vanes 14 for straightening this stage. and whose downstream end is connected by suspension means 36 to the outer wall of the casing 18.

La virole 32 de l'étage de compression E2 est séparée de la virole 30 de l'étage de compression suivant E3 par un jeu annulaire axial 42 qui forme un passage de gaz entre l'intérieur du compresseur et une cavité 44 définie dans le carter 18 entre les parois interne et externe de celui-ci d'une part et entre les moyens 36 de suspension de la virole 32 de l'étage précédent E2 et les moyens 34 de suspension de la virole 30 de l'étage E3, d'autre part.The ferrule 32 of the compression stage E2 is separated from the ferrule 30 of the next compression stage E3 by an axial annular clearance 42 which forms a gas passage between the inside of the compressor and a cavity 44 defined in the crankcase. 18 between the inner and outer walls of the latter on the one hand and between the means 36 for suspending the ferrule 32 of the previous stage E2 and the means 34 for suspending the ferrule 30 of the stage E3, somewhere else.

Une ou plusieurs prises d'air 46 sont formées dans la paroi externe du carter 18 et débouchent dans cette cavité 44, pour alimenter en air des équipements de la turbomachine.One or more air intakes 46 are formed in the outer wall of the casing 18 and open into this cavity 44, to supply air to the equipment of the turbomachine.

L'extrémité aval de la virole 30 de l'étage de compression E3 est raccordée à étanchéité à l'extrémité amont d'une virole 32 portant les aubes fixes de redressement 14 de cet étage de compression. L'extrémité aval de cette virole 32 est raccordée à étanchéité, par exemple par emboîtement, à l'extrémité amont de la virole 30 de l'étage de compression suivant E4 qui est reliée par ses moyens de suspension 34 à la paroi externe du carter 18. La virole 32 de l'étage de compression E3 est ainsi portée par la virole 30 de cet étage de compression et par la virole 30 de l'étage de compression suivant E4.The downstream end of the ferrule 30 of the compression stage E3 is sealingly connected to the upstream end of a ferrule 32 carrying the fixed vanes 14 of this compression stage. The downstream end of this ferrule 32 is connected sealingly, for example by interlocking, to the upstream end of the shell 30 of the next compression stage E4 which is connected by its suspension means 34 to the outer wall of the casing 18. The ferrule 32 of the compression stage E3 is thus carried by the ferrule 30 of this compression stage and by the ferrule 30 of the next compression stage E4.

Une autre prise d'air 46 peut être formée dans la paroi externe du carter 18 et débouche dans une cavité 48 formée entre les parois interne et externe du carter 18 en aval des moyens de suspension 34 de la virole 30 de l'étage E4.Another air intake 46 may be formed in the outer wall of the casing 18 and opens into a cavity 48 formed between the inner and outer walls of the housing 18 downstream of the suspension means 34 of the ferrule 30 of the stage E4.

On voit que les jeux radiaux de l'étage de compression E2 peuvent être réglés indépendamment des jeux radiaux de l'étage de compression E1 et des étages de compression suivants E3 et E4 tandis que les jeux radiaux des étages de compression E3 et E4 sont réglés de façon non indépendante, les aubes mobiles 12 de ces deux étages ayant les mêmes dimensions radiales, les viroles 30 des étages E3 et E4 étant solidarisées l'une avec l'autre par la virole 32 de l'étage E3.It can be seen that the radial clearances of the compression stage E2 can be regulated independently of the radial clearances of the compression stage E1 and the following compression stages E3 and E4 while the games The radial blades of the compression stages E3 and E4 are set independently, the blades 12 of these two stages having the same radial dimensions, the rings 30 of the stages E3 and E4 being secured to one another by the ferrule 32. from floor E3.

Claims (11)

  1. A multistage turbomachine compressor comprising annular rows of moving blades (12) rotating inside a double-walled casing (18), and annular rows of straightening stator vanes (14) carried by an inner wall (16) of the double-walled casing, wherein the inner wall (16) of the casing comprises a plurality of shrouds (30,32) substantially in end-to-end alignment and suspended independently of one another from an outer wall (20) of the casing by means (34,36) for suspending, some of the shrouds (30) each surrounding an annular row of moving blades (12) and other of the shrouds (32) each carrying an annular row of straightening stator vanes (14), characterized in that, flexible or deformable, the means (34,36) for suspending are configured to adjust the radial clearances (J1,J2) between the radially outer-ends of the moving blades (12) and the shrouds (30), in each compression stage, independently of one another.
  2. A compressor according to claim 1, characterized in that each annular row of moving blades (12) is surrounded by one of the shrouds (30) suspended from the outer wall of the casing (18) independently from the other shrouds (30) surrounding the other annular rows of moving blades (12).
  3. A compressor according to claim 1, characterized in that two shrouds (30) of the inner wall of the casing (18), surrounding two successive annular rows of moving blades (12) are securely connected together, the moving blades (12) of these two successive rows having the same dimensions.
  4. A compressor according to claim 3, characterized in that one of the shrouds (32) carrying an annular row of straightening stator vanes (14) situated between the two shrouds (30) surrounding annular rows of moving blades (12) is carried by said two shrouds (30) and securely connects them together.
  5. A compressor according to anyone of the preceding claims, characterized in that at least one of the shrouds (30) surrounding an annular row of moving blades (12) is adjacent to a second of the shrouds (32) carrying an annular row of straightening stator vanes (14) and is connected in gastight manner to said second shroud (32).
  6. A compressor according to claim 5, characterized in that the second shroud (32) is connected to a third of the shrouds (30) surrounding an annular row of moving blades (12) by means (40) for providing sealing against the flow of gas passing through the compressor.
  7. A compressor according to claim 6, characterized in that the second shroud (32) is connected to the outer wall of the casing (18) by means (36) for suspending said second shroud, which are independent of the means for suspending the other shrouds.
  8. A compressor according to claim 5, characterized in that the second shroud (32) is axially spaced apart from a third of the shrouds (32) surrounding an annular row of moving blades (12) and is connected by means (36) for suspending said second shroud to the outer wall of the casing (18).
  9. A compressor according to claim 6, characterized in that annular clearance (42) axially separating the second shroud (32) and the third shroud (30) defines a passage allowing air to penetrate into a cavity (44) that is formed in the casing (18) between the means for suspending the second shroud (32) and the means for suspending the third shroud (30), and into which there open out means (46) for taking off air, which are carried by the outer wall (20) of the casing (18).
  10. A compressor according to anyone of the preceding claims, characterized in that the radial modes of vibration of at least some of the shrouds (30) surrounding the annular rows of moving blades (12) are adjusted independently from one shroud (30) to another, in order to optimize the radial clearances between said shrouds and the annular rows of moving blades (12) rotating inside said shrouds.
  11. An airplane turbojet or turboprop, characterized in that it comprises a compressor as defined in anyone of the preceding claims.
EP06291053.4A 2005-06-29 2006-06-26 Multi stage turbomachine compressor Revoked EP1739309B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0506610A FR2887939B1 (en) 2005-06-29 2005-06-29 TURBOMACHINE MULTI-STAGE COMPRESSOR

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EP1739309A1 EP1739309A1 (en) 2007-01-03
EP1739309B1 true EP1739309B1 (en) 2017-01-11

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US (1) US7651317B2 (en)
EP (1) EP1739309B1 (en)
FR (1) FR2887939B1 (en)
RU (1) RU2375607C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2913051B1 (en) * 2007-02-28 2011-06-10 Snecma TURBINE STAGE IN A TURBOMACHINE
US11466593B2 (en) 2020-01-07 2022-10-11 Raytheon Technologies Corporation Double walled stator housing

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GB856599A (en) 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US3314648A (en) 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
US4101242A (en) 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
EP1580404A2 (en) 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Arrangement for self adjusting the tip clearance in a two or multiple stage turbine

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US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
FR2688539A1 (en) * 1992-03-11 1993-09-17 Snecma Turbomachine stator including devices for adjusting the clearance between the stator and the blades of the rotor
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
DE4442157A1 (en) * 1994-11-26 1996-05-30 Abb Management Ag Method and device for influencing the radial clearance of the blades in compressors with axial flow
FR2794816B1 (en) * 1999-06-10 2001-07-06 Snecma HIGH PRESSURE COMPRESSOR STATOR
US6935836B2 (en) * 2002-06-05 2005-08-30 Allison Advanced Development Company Compressor casing with passive tip clearance control and endwall ovalization control

Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
GB856599A (en) 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US3314648A (en) 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
US4101242A (en) 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
EP1580404A2 (en) 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Arrangement for self adjusting the tip clearance in a two or multiple stage turbine

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Publication number Publication date
FR2887939A1 (en) 2007-01-05
EP1739309A1 (en) 2007-01-03
FR2887939B1 (en) 2016-09-30
RU2006123033A (en) 2008-01-10
US7651317B2 (en) 2010-01-26
RU2375607C2 (en) 2009-12-10
US20090304498A1 (en) 2009-12-10

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