EP1936125B1 - Turbomachine compressor - Google Patents

Turbomachine compressor Download PDF

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Publication number
EP1936125B1
EP1936125B1 EP06292027A EP06292027A EP1936125B1 EP 1936125 B1 EP1936125 B1 EP 1936125B1 EP 06292027 A EP06292027 A EP 06292027A EP 06292027 A EP06292027 A EP 06292027A EP 1936125 B1 EP1936125 B1 EP 1936125B1
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EP
European Patent Office
Prior art keywords
annular
ferrules
compressor
blades
cylindrical
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EP06292027A
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German (de)
French (fr)
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EP1936125A1 (en
Inventor
Enrique Penalver Castro
Frédéric Gebbia
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Safran Aero Boosters SA
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Techspace Aero SA
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Priority to ES06292027T priority Critical patent/ES2323283T3/en
Priority to EP06292027A priority patent/EP1936125B1/en
Priority to DE602006005693T priority patent/DE602006005693D1/en
Priority to AT06292027T priority patent/ATE425346T1/en
Publication of EP1936125A1 publication Critical patent/EP1936125A1/en
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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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements

Definitions

  • the present invention relates to a turbomachine compressor, in particular a low-pressure compressor, and a turbomachine such as a turbojet engine or an airplane turboprop engine equipped with this compressor.
  • a low-pressure turbomachine compressor comprises a plurality of compression stages each comprising an upstream annular row of rotor blades rotating inside a fixed casing and driven by a shaft of the turbomachine, and a downstream annular row of fixed blades for rectifying the flow of air, which are carried by the casing at their radially outer ends.
  • the casing has a substantially cylindrical or frustoconical shape and is formed of annular rings arranged coaxially end to end, and each carrying an annular row of fixed vanes rectification.
  • the ferrules comprise at their ends cylindrical flanges each terminating in an annular flange.
  • the cylindrical upstream rim of greater axial dimension of each ferrule surrounds the annular row of upstream rotor blades, and comprises an upstream annular flange for attachment on a corresponding flange provided on the downstream cylindrical rim of smaller axial dimension of another shell located upstream.
  • the joining plane of the fastening flanges of two adjacent ferrules extends substantially upstream of the leading edges of the rotor blades located between the vanes carried by these ferrules.
  • the junction plane of these flanges may extend downstream of the trailing edges of the rotor blades located between the vanes carried by the ferrules.
  • An annular element of abradable material is fixed on the inner cylindrical surface of the upstream axial flange of each ferrule, and cooperates with the tops of the blades to limit the radial clearances between the blades and the casing.
  • the invention aims in particular to provide a simple, effective and economical solution to all of the aforementioned problems of the prior art.
  • a turbomachine compressor comprising a substantially cylindrical housing formed of annular ferrules arranged coaxially end to end and each carrying an annular row of straightening vanes, the ferrules having at their axial ends cylindrical flanges carrying annular flanges. fastening the ferrules together, these fastening flanges being in the axial direction substantially in the middle of an annular row of blades located between these ferrules, characterized in that the cylindrical edges of the ends of the adjacent ferrules form around the blades located between these ferrules an annular groove for mounting an element made of abradable material, this annular groove having an internal diameter greater than the external diameter of the theoretical vein in this part of the housing.
  • the flanges for fixing the flanges of two adjacent ferrules surround an annular array of moving blades, the flanges of these ferrules having substantially the same axial dimension.
  • the upstream and downstream cylindrical flanges of a ferrule may have the same axial dimension or different axial dimensions.
  • the fastening flanges of two adjacent ferrules surround rotor blades and are substantially equidistant from the ferrules, which makes it possible to stiffen the crankcase, which can thus withstand significant shocks such as those produced by parts of blades when rupture of the compressor rotor.
  • the axial dimensions of the upstream and downstream flanges of each shell can be optimized so as to reduce the axial size of the compressor, which was not possible in the current technique.
  • the cylindrical edges of the ends of the adjacent ferrules extend over at least the entire axial length of the blades situated between these ferrules and form an annular groove around these moving blades, this annular groove having a internal diameter greater than the outer diameter of the theoretical vein in this part of the housing.
  • An element of abradable material is mounted in the annular groove and advantageously has an axial dimension at least equal to that of the top of the blades which it surrounds, and an internal diameter equal to or greater than the external diameter of the theoretical vein in this part of the casing.
  • the outer diameter of the blades of each annular row can thus be, cold, equal to or greater than the outer diameter of the theoretical vein in the corresponding part of the housing.
  • the abradable element can be in two parts mounted end to end, each part of the abradable element being fixed on a cylindrical end rim of a ferrule.
  • the abradable element extends on either side of the junction plane between the ferrules, which limits the formation of projections within the housing. In the event of misalignment of the upstream and downstream parts of the element during clamping of the flanges, the tops of the moving blades that come into operation use by friction the abradable element make it possible to catch any unevenness or protrusion between the two parts of the element abradable.
  • the invention also relates to a turbomachine such as a turbojet engine or a turboprop engine, characterized in that it comprises a compressor as described above.
  • the compressor 10 of the figure 1 comprises a number of compression stages of which only one has been shown, each stage comprising an annular row of rotor blades 12, whose radially inner ends are fixed on a disk carried by a shaft of the turbomachine, and a 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 substantially cylindrical housing 16 of axis 18.
  • the housing 16 is formed of annular ferrules 20, 22 arranged coaxially end to end, and each carrying a row of fixed blades 14.
  • the ferrules 20, 22 each comprise an upstream cylindrical rim 26 and a downstream cylindrical rim 28 ending in annular flanges 30, 30 'for fixing ferrules together.
  • the flange 30 carried by the upstream flange of the shell 22 is applied and tightened by appropriate means of the screw-nut type on the corresponding flange 30 'carried by the downstream flange of the ferrule 20 located upstream.
  • the upstream flange 26 of the shell 22 further comprises at its free end a cylindrical surface 31 in which is engaged the downstream end of the downstream flange 28 of the shell 20.
  • junction plane J of the fastening flanges 30, 30 'of two adjacent ferrules extends substantially upstream of the leading edges (or downstream of the trailing edges) of the blades 12 situated between these ferrules. ( figure 2 ).
  • this technique has several disadvantages detailed in the foregoing.
  • the invention provides a simple and effective solution to all of these problems by moving in the axial direction of the junction plane J 'flanges 20, 20' substantially in the middle of the blades 12 and the formation of a ring groove ("Trench") in the edges of the ferrules around the blades.
  • the upstream cylindrical flange 26 of each ferrule 20, 22 has an axial dimension substantially equal to that of the downstream cylindrical flange 28 to which it is attached.
  • the flanges 26, 28 connecting two ferrules adjacent ones surround a row of moving blades 12 and define an annular groove 32 opening radially inwards.
  • each flange 26, 28 has an end portion 36 of small axial dimension and small internal diameter which is aligned axially with a shell 20.
  • Each flange 26, 28 further comprises an end portion 40 of larger axial dimension and larger internal diameter which extends around the blades 12 and internally delimits a portion of the annular groove 32 above.
  • the inside diameter of the end portion 40 of the flange is greater than the outside diameter D of the theoretical vein in the corresponding part of the casing, and the inside diameter of the end portion 36 of this flange is substantially equal to the outside diameter D of this theoretical vein.
  • a cylindrical element 34 of abradable material is fixed in the annular groove 32 and extends around the blades 12, over substantially their entire axial dimension. This element 34 is intended to cooperate with the tops of the blades to prevent the passage of air in axial direction between the tops of the blades 12 and the casing 16, as will be described in more detail in the following.
  • the element 34 is formed of two parts mounted coaxially end to end. Each of these parts is fixed by appropriate means on an end portion 40 of larger internal diameter of a flange 26, 28.
  • the internal diameter of each portion of the abradable element is substantially equal to one of its axial ends, with that of the end portion 36 of the flange to which it is attached, and at the other of its ends, with that of the other complementary part of the element.
  • the outer diameter of the blades is, in the cold, substantially equal to the external diameter D of the theoretical vein in the corresponding part of the casing, that is to say that the tops of the blades 12 are aligned axially with the cylindrical surface internal part of the housing.
  • the tops of the blades 12 define with the abradable element 34 which surrounds them a small radial clearance so as to limit the passage of air between the blades 12 and the casing 16.
  • the blades 12 expand more or less in the radial direction and this radial clearance can disappear.
  • the tops of the blades then come into contact with the abradable element 34 by friction, which makes it possible to make up any jump or difference between the two parts of the abradable element 34.
  • the invention has many other advantages detailed above.

Abstract

The compressor (10) has a cylindrical case (16) formed with annular ferrules (20, 22) that hold annular rows of straightening vanes (14). The ferrules have cylindrical edges (26, 28) to carry annular flanges (30, 30'), arranged at equal distance from the ferrules, for fixing the ferrules between the edges. The edges form an annular groove around movable vanes (12) placed between the ferrules for assembling an abradable element, where the internal diameter of the groove is higher than the external diameter of a theoretical vein in a part of the case.

Description

La présente invention concerne un compresseur de turbomachine, en particulier un compresseur basse-pression, ainsi qu'une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion équipé de ce compresseur.The present invention relates to a turbomachine compressor, in particular a low-pressure compressor, and a turbomachine such as a turbojet engine or an airplane turboprop engine equipped with this compressor.

Les documents WO-A-95025879 et GB-A-960812 décrivent des compresseurs haute-pression de turbomachine.The documents WO-A-95025879 and GB-A-960 812 describe high-pressure turbomachine compressors.

Un compresseur basse-pression de turbomachine comprend plusieurs étages de compression comportant chacun une rangée annulaire amont d'aubes mobiles de rotor tournant à l'intérieur d'un carter fixe et entraînées par un arbre de la turbomachine, et une rangée annulaire aval d'aubes fixes de redressement du flux d'air, qui sont portées par le carter à leurs extrémités radialement externes.A low-pressure turbomachine compressor comprises a plurality of compression stages each comprising an upstream annular row of rotor blades rotating inside a fixed casing and driven by a shaft of the turbomachine, and a downstream annular row of fixed blades for rectifying the flow of air, which are carried by the casing at their radially outer ends.

Le carter a une forme sensiblement cylindrique ou tronconique et est formé de viroles annulaires disposées coaxialement bout à bout, et portant chacune une rangée annulaire d'aubes fixes de redressement.The casing has a substantially cylindrical or frustoconical shape and is formed of annular rings arranged coaxially end to end, and each carrying an annular row of fixed vanes rectification.

Dans la technique actuelle, les viroles comprennent à leurs extrémités des rebords cylindriques se terminant chacun par une bride annulaire. Le rebord cylindrique amont de plus grande dimension axiale de chaque virole entoure la rangée annulaire d'aubes de rotor située en amont, et comprend une bride annulaire amont de fixation sur une bride correspondante prévue sur le rebord cylindrique aval de plus petite dimension axiale d'une autre virole située en amont. Le plan de jonction des brides de fixation de deux viroles adjacentes s'étend sensiblement en amont des bords d'attaque des aubes de rotor situées entre les aubes fixes portées par ces viroles. Selon les moteurs, le plan de jonction de ces brides peut s'étendre en aval des bords de fuite des aubes de rotor situées entre les aubes fixes portées par les viroles.In the present art, the ferrules comprise at their ends cylindrical flanges each terminating in an annular flange. The cylindrical upstream rim of greater axial dimension of each ferrule surrounds the annular row of upstream rotor blades, and comprises an upstream annular flange for attachment on a corresponding flange provided on the downstream cylindrical rim of smaller axial dimension of another shell located upstream. The joining plane of the fastening flanges of two adjacent ferrules extends substantially upstream of the leading edges of the rotor blades located between the vanes carried by these ferrules. Depending on the motors, the junction plane of these flanges may extend downstream of the trailing edges of the rotor blades located between the vanes carried by the ferrules.

Un élément annulaire en matériau abradable est fixé sur la surface cylindrique interne du rebord amont de grande dimension axiale de chaque virole, et coopère avec les sommets des aubes mobiles pour limiter les jeux radiaux entre les aubes mobiles et le carter.An annular element of abradable material is fixed on the inner cylindrical surface of the upstream axial flange of each ferrule, and cooperates with the tops of the blades to limit the radial clearances between the blades and the casing.

La technique précitée de fixation des viroles du carter présente un certain nombre d'inconvénients indiqués ci-dessous :

  • les parties des viroles situées au droit des aubes mobiles sont relativement fragiles, si bien qu'elles ne permettent pas toujours de retenir les aubes ou des parties d'aubes en cas de casse du rotor du compresseur ;
  • après le serrage des brides annulaires, il se peut que l'élément abradable ne soit pas parfaitement aligné en direction axiale avec la virole amont, ce qui crée un ressaut à l'intérieur du carter entre la virole amont et l'élément abradable qui peut provoquer des perturbations et des pertes de charge dans le flux d'air et diminuer les performances de la turbomachine ;
  • comme les aubes fixes sont rapportées et fixées par soudure sur les viroles, les rebords doivent avoir une dimension axiale suffisante pour que leurs brides, où se concentrent des contraintes importantes en fonctionnement, soient suffisamment éloignées des soudures, ce qui se traduit par un encombrement axial important du compresseur ;
  • le sens de montage et de démontage, de l'amont vers l'aval ou de l'aval vers l'amont, des étages du compresseur est en général imposé par l'inclinaison et la forme de la veine du compresseur, ce qui peut compliquer les opérations de maintenance du compresseur. A titre d'exemple, le montage/démontage des étages du compresseur est plus complexe lorsque la veine du compresseur est faiblement inclinée par rapport à l'axe de rotation des aubes mobiles, par exemple de l'ordre de 0 à 15° ;
  • au repos et à froid, les sommets des aubes mobiles ne peuvent être alignés sur le diamètre externe de la veine théorique dans la partie correspondante du carter. Cependant, dans une configuration idéale, le diamètre externe des rangées annulaires d'aubes mobiles doit être au moins égal à celui de la veine théorique, pendant les différentes phases de fonctionnement du moteur, de manière à limiter le passage d'air entre les sommets des aubes mobiles et le carter.
The aforementioned technique for fixing the casing ferrules has a certain number of drawbacks indicated below:
  • the parts of the ferrules located on the right of the blades are relatively fragile, so that they do not always allow to retain the vanes or parts of blades in case of breakage of the rotor of the compressor;
  • after tightening the annular flanges, it is possible that the abradable element is not perfectly aligned in the axial direction with the upstream shell, which creates a projection inside the casing between the upstream shell and the abradable element which can cause disturbances and pressure losses in the air flow and reduce the performance of the turbomachine;
  • since the fixed vanes are attached and fixed by welding on the shells, the flanges must have an axial dimension sufficient for their flanges, where there are important constraints in operation, to be sufficiently far from the welds, which results in an axial space requirement. important compressor;
  • the direction of assembly and disassembly, from upstream to downstream or from downstream to upstream, compressor stages is generally imposed by the inclination and shape of the compressor vein, which can complicate compressor maintenance operations. By way of example, the assembly / disassembly of the stages of the compressor is more complex when the vein of the compressor is slightly inclined with respect to the axis of rotation of the blades, for example of the order of 0 to 15 °;
  • at rest and cold, the tops of the blades can not be aligned with the outer diameter of the theoretical vein in the corresponding part of the housing. However, in an ideal configuration, the outer diameter of the annular rows of blades must be at least equal to that of the theoretical vein, during the different phases of engine operation, so as to limit the passage of air between the tops of the blades and the crankcase.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à l'ensemble des problèmes précités de la technique antérieure.The invention aims in particular to provide a simple, effective and economical solution to all of the aforementioned problems of the prior art.

Elle propose à cet effet un compresseur de turbomachine, comprenant un carter sensiblement cylindrique formé de viroles annulaires disposées coaxialement bout à bout et portant chacune une rangée annulaire d'aubes de redressement, les viroles ayant à leurs extrémités axiales des rebords cylindriques portant des brides annulaires de fixation des viroles entre elles, ces brides de fixation étant en direction axiale sensiblement au milieu d'une rangée annulaire d'aubes mobiles située entre ces viroles, caractérisé en ce que les rebords cylindriques des extrémités des viroles adjacentes forment autour des aubes mobiles situées entre ces viroles une rainure annulaire de montage d'un élément en matériau abradable, cette rainure annulaire ayant un diamètre interne supérieur au diamètre externe de la veine théorique dans cette partie du carter.It proposes for this purpose a turbomachine compressor, comprising a substantially cylindrical housing formed of annular ferrules arranged coaxially end to end and each carrying an annular row of straightening vanes, the ferrules having at their axial ends cylindrical flanges carrying annular flanges. fastening the ferrules together, these fastening flanges being in the axial direction substantially in the middle of an annular row of blades located between these ferrules, characterized in that the cylindrical edges of the ends of the adjacent ferrules form around the blades located between these ferrules an annular groove for mounting an element made of abradable material, this annular groove having an internal diameter greater than the external diameter of the theoretical vein in this part of the housing.

Selon l'invention, les brides de fixation des rebords de deux viroles adjacentes entourent une rangée annulaire d'aubes mobiles, les rebords de ces viroles ayant sensiblement la même dimension axiale. Les rebords cylindriques amont et aval d'une virole peuvent avoir une même dimension axiale ou des dimensions axiales différentes. Cette invention permet de remédier à l'ensemble des problèmes précités.According to the invention, the flanges for fixing the flanges of two adjacent ferrules surround an annular array of moving blades, the flanges of these ferrules having substantially the same axial dimension. The upstream and downstream cylindrical flanges of a ferrule may have the same axial dimension or different axial dimensions. This invention overcomes all of the aforementioned problems.

Les brides de fixation de deux viroles adjacentes entourent des aubes de rotor et sont sensiblement à égale distance des viroles, ce qui permet de rigidifier le carter qui peut ainsi résister à des chocs importants tels que ceux produits par des parties d'aubes mobiles lors de la rupture du rotor du compresseur. Les dimensions axiales des rebords amont et aval de chaque virole peuvent être optimisées de manière à diminuer l'encombrement axial du compresseur, ce qui n'était pas possible dans la technique actuelle.The fastening flanges of two adjacent ferrules surround rotor blades and are substantially equidistant from the ferrules, which makes it possible to stiffen the crankcase, which can thus withstand significant shocks such as those produced by parts of blades when rupture of the compressor rotor. The axial dimensions of the upstream and downstream flanges of each shell can be optimized so as to reduce the axial size of the compressor, which was not possible in the current technique.

Selon une autre caractéristique de l'invention, les rebords cylindriques des extrémités des viroles adjacentes s'étendent au moins sur toute la longueur axiale des aubes mobiles situées entre ces viroles et forment une rainure annulaire autour de ces aubes mobiles, cette rainure annulaire ayant un diamètre interne supérieur au diamètre externe de la veine théorique dans cette partie du carter.According to another characteristic of the invention, the cylindrical edges of the ends of the adjacent ferrules extend over at least the entire axial length of the blades situated between these ferrules and form an annular groove around these moving blades, this annular groove having a internal diameter greater than the outer diameter of the theoretical vein in this part of the housing.

Un élément en matériau abradable est monté dans la rainure annulaire et a avantageusement une dimension axiale au moins égale à celle du sommet des aubes mobiles qu'il entoure, et un diamètre interne égal ou supérieur au diamètre externe de la veine théorique dans cette partie du carter. Le diamètre externe des aubes mobiles de chaque rangée annulaire peut ainsi être, à froid, égal voire supérieur au diamètre externe de la veine théorique dans la partie correspondante du carter. L'élément abradable peut être en deux parties montées bout à bout, chaque partie de l'élément abradable étant fixé sur un rebord cylindrique d'extrémité d'une virole.An element of abradable material is mounted in the annular groove and advantageously has an axial dimension at least equal to that of the top of the blades which it surrounds, and an internal diameter equal to or greater than the external diameter of the theoretical vein in this part of the casing. The outer diameter of the blades of each annular row can thus be, cold, equal to or greater than the outer diameter of the theoretical vein in the corresponding part of the housing. The abradable element can be in two parts mounted end to end, each part of the abradable element being fixed on a cylindrical end rim of a ferrule.

L'élément abradable s'étend de part et d'autre du plan de jonction entre les viroles, ce qui limite la formation de ressauts à l'intérieur du carter. En cas de désalignement des parties amont et aval de l'élément lors du serrage des brides, les sommets des aubes mobiles qui viennent en fonctionnement user par frottement l'élément abradable permettent de rattraper tout dénivellement ou ressaut entre les deux parties de l'élément abradable.The abradable element extends on either side of the junction plane between the ferrules, which limits the formation of projections within the housing. In the event of misalignment of the upstream and downstream parts of the element during clamping of the flanges, the tops of the moving blades that come into operation use by friction the abradable element make it possible to catch any unevenness or protrusion between the two parts of the element abradable.

L'invention concerne également une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend un compresseur tel que décrit dans ce qui précède.The invention also relates to a turbomachine such as a turbojet engine or a turboprop engine, characterized in that it comprises a 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 non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi-vue très schématique en coupe axiale d'une partie d'un compresseur basse-pression d'une turbomachine selon l'invention ;
  • la figure 2 est une vue à plus grande échelle d'une partie de la figure 1.
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 non-limiting example and with reference to the accompanying drawings in which:
  • the figure 1 is a very schematic half-view in axial section of a part of a low-pressure compressor of a turbomachine according to the invention;
  • the figure 2 is a larger-scale view of some of the figure 1 .

Dans les figures, 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, what 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 comprend un certain nombre d'étages de compression dont un seul a été représenté, chaque étage comportant une rangée annulaire d'aubes mobiles 12 de rotor, 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 un carter 16 sensiblement cylindrique d'axe 18.The compressor 10 of the figure 1 comprises a number of compression stages of which only one has been shown, each stage comprising an annular row of rotor blades 12, whose radially inner ends are fixed on a disk carried by a shaft of the turbomachine, and a 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 substantially cylindrical housing 16 of axis 18.

Le carter 16 est formé de viroles annulaires 20, 22 disposées coaxialement bout à bout, et portant chacune une rangée d'aubes fixes 14. Les viroles 20, 22 comportent chacune un rebord cylindrique amont 26 et un rebord cylindrique aval 28 se terminant par des brides annulaires 30, 30' de fixation des viroles entre elles. La bride 30 portée par le rebord amont de la virole 22 est appliquée et serrée par des moyens appropriés du type vis-écrou sur la bride 30' correspondante portée par le rebord aval de la virole 20 située en amont. Le rebord amont 26 de la virole 22 comprend en outre à son extrémité libre une portée cylindrique 31 dans laquelle est engagée l'extrémité aval du rebord aval 28 de la virole 20.The housing 16 is formed of annular ferrules 20, 22 arranged coaxially end to end, and each carrying a row of fixed blades 14. The ferrules 20, 22 each comprise an upstream cylindrical rim 26 and a downstream cylindrical rim 28 ending in annular flanges 30, 30 'for fixing ferrules together. The flange 30 carried by the upstream flange of the shell 22 is applied and tightened by appropriate means of the screw-nut type on the corresponding flange 30 'carried by the downstream flange of the ferrule 20 located upstream. The upstream flange 26 of the shell 22 further comprises at its free end a cylindrical surface 31 in which is engaged the downstream end of the downstream flange 28 of the shell 20.

Dans la technique antérieure, le plan de jonction J des brides de fixation 30, 30' de deux viroles adjacentes s'étend sensiblement en amont des bords d'attaque (ou en aval des bords de fuite) des aubes mobiles 12 situées entre ces viroles (figure 2). Cependant, cette technique présente plusieurs inconvénients détaillés dans ce qui précède.In the prior art, the junction plane J of the fastening flanges 30, 30 'of two adjacent ferrules extends substantially upstream of the leading edges (or downstream of the trailing edges) of the blades 12 situated between these ferrules. ( figure 2 ). However, this technique has several disadvantages detailed in the foregoing.

L'invention apporte une solution simple et efficace à l'ensemble de ces problèmes grâce au déplacement en direction axiale du plan de jonction J' des brides 20, 20' sensiblement au milieu des aubes mobiles 12 et à la formation d'une rainure annulaire (« trench ») dans les rebords des viroles autour des aubes mobiles.The invention provides a simple and effective solution to all of these problems by moving in the axial direction of the junction plane J 'flanges 20, 20' substantially in the middle of the blades 12 and the formation of a ring groove ("Trench") in the edges of the ferrules around the blades.

Selon l'invention, le rebord cylindrique amont 26 de chaque virole 20, 22 a une dimension axiale sensiblement égale à celle du rebord cylindrique aval 28 auquel il est fixé. Les rebords 26, 28 de liaison de deux viroles adjacentes entourent une rangée d'aubes mobiles 12 et définissent une rainure annulaire 32 débouchant radialement vers l'intérieur.According to the invention, the upstream cylindrical flange 26 of each ferrule 20, 22 has an axial dimension substantially equal to that of the downstream cylindrical flange 28 to which it is attached. The flanges 26, 28 connecting two ferrules adjacent ones surround a row of moving blades 12 and define an annular groove 32 opening radially inwards.

Dans l'exemple représenté, chaque rebord 26, 28 comporte une partie d'extrémité 36 de faible dimension axiale et de faible diamètre interne qui est alignée axialement avec une virole 20. Chaque rebord 26, 28 comporte en outre une partie d'extrémité 40 de plus grande dimension axiale et de plus grand diamètre interne qui s'étend autour des aubes mobiles 12 et délimite intérieurement une partie de la rainure annulaire 32 précitée. Le diamètre interne de la partie d'extrémité 40 du rebord est supérieur au diamètre externe D de la veine théorique dans la partie correspondante du carter, et le diamètre interne de la partie d'extrémité 36 de ce rebord est sensiblement égal au diamètre externe D de cette veine théorique.In the example shown, each flange 26, 28 has an end portion 36 of small axial dimension and small internal diameter which is aligned axially with a shell 20. Each flange 26, 28 further comprises an end portion 40 of larger axial dimension and larger internal diameter which extends around the blades 12 and internally delimits a portion of the annular groove 32 above. The inside diameter of the end portion 40 of the flange is greater than the outside diameter D of the theoretical vein in the corresponding part of the casing, and the inside diameter of the end portion 36 of this flange is substantially equal to the outside diameter D of this theoretical vein.

Un élément cylindrique 34 en matériau abradable est fixé dans la rainure annulaire 32 et s'étend autour des aubes mobiles 12, sur sensiblement toute leur dimension axiale. Cet élément 34 est destiné à coopérer avec les sommets des aubes mobiles pour empêcher le passage d'air en direction axiale entre les sommets des aubes 12 et le carter 16, comme cela sera décrit plus en détail dans ce qui suit.A cylindrical element 34 of abradable material is fixed in the annular groove 32 and extends around the blades 12, over substantially their entire axial dimension. This element 34 is intended to cooperate with the tops of the blades to prevent the passage of air in axial direction between the tops of the blades 12 and the casing 16, as will be described in more detail in the following.

L'élément 34 est formé de deux parties montées coaxialement bout à bout. Chacune de ces parties est fixée par des moyens appropriés sur une partie d'extrémité 40 de plus grand diamètre interne d'un rebord 26, 28. Le diamètre interne de chaque partie de l'élément abradable est sensiblement égal, à l'une de ses extrémités axiales, avec celui de la partie d'extrémité 36 du rebord auquel elle est fixée, et à l'autre de ses extrémités, avec celui de l'autre partie complémentaire de l'élément.The element 34 is formed of two parts mounted coaxially end to end. Each of these parts is fixed by appropriate means on an end portion 40 of larger internal diameter of a flange 26, 28. The internal diameter of each portion of the abradable element is substantially equal to one of its axial ends, with that of the end portion 36 of the flange to which it is attached, and at the other of its ends, with that of the other complementary part of the element.

Comme cela est bien visible en figure 2, le diamètre externe des aubes mobiles est, à froid, sensiblement égal au diamètre externe D de la veine théorique dans la partie correspondante du carter, c'est-à-dire que les sommets des aubes mobiles 12 sont alignés axialement avec la surface cylindrique interne de cette partie du carter. Les sommets des aubes 12 définissent avec l'élément abradable 34 qui les entoure un faible jeu radial de manière à limiter le passage d'air entre les aubes 12 et le carter 16. En fonctionnement et selon le régime du moteur, les aubes mobiles 12 se dilatent plus ou moins en direction radiale et ce jeu radial peut disparaître. Les sommets des aubes viennent alors user par frottement l'élément abradable 34, ce qui permet de rattraper tout ressaut ou dénivellement entre les deux parties de l'élément abradable 34.As is clearly visible in figure 2 , the outer diameter of the blades is, in the cold, substantially equal to the external diameter D of the theoretical vein in the corresponding part of the casing, that is to say that the tops of the blades 12 are aligned axially with the cylindrical surface internal part of the housing. The tops of the blades 12 define with the abradable element 34 which surrounds them a small radial clearance so as to limit the passage of air between the blades 12 and the casing 16. In operation and according to the engine speed, the blades 12 expand more or less in the radial direction and this radial clearance can disappear. The tops of the blades then come into contact with the abradable element 34 by friction, which makes it possible to make up any jump or difference between the two parts of the abradable element 34.

L'invention présente de nombreux autres avantages détaillés ci-dessus. The invention has many other advantages detailed above.

Claims (5)

  1. Turbomachine compressor, comprising a substantially cylindrical casing (16) formed of annular shell rings (20, 22) positioned coaxially end to end and each bearing an annular row of straightening vanes (14), the shell rings having, at their axial ends, cylindrical rims (26, 28) bearing annular flanges (30, 30') for joining the shell rings together, these joining flanges lying, in the axial direction, substantially in the middle of an annular row of moving vanes (12) located between these shell rings, characterized in that the cylindrical rims (26, 28) of the ends of the adjacent shell rings form, around the moving vanes that lie between these shell rings, an annular groove, or trench, (32) for fitting an element (34) made of an abradable material, this annular groove, or trench, having an inside diameter greater than the outside diameter (D) of the theoretical stream in this part of the casing.
  2. Compressor according to Claim 1, characterized in that the element (34) made of abradable material has an axial dimension at least equal to that of the tips of the moving vanes (12) that it surrounds, and an inside diameter equal to or greater than the outside diameter (D) of the theoretical stream in this part of the casing.
  3. Compressor according to Claim 2, characterized in that the abradable element (34) is made in two parts mounted end to end, each part of the abradable element being attached to an end cylindrical rim (26, 28) of a shell ring.
  4. Compressor according to one of the preceding claims, characterized in that, when cold, the outside diameter of the moving vanes (12) of each annular row is equal to or greater than the outside diameter (D) of the theoretical stream in the corresponding part of the casing.
  5. Turbomachine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a compressor (10) according to one of the preceding claims.
EP06292027A 2006-12-22 2006-12-22 Turbomachine compressor Active EP1936125B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
ES06292027T ES2323283T3 (en) 2006-12-22 2006-12-22 TURBOMACHINE COMPRESSOR.
EP06292027A EP1936125B1 (en) 2006-12-22 2006-12-22 Turbomachine compressor
DE602006005693T DE602006005693D1 (en) 2006-12-22 2006-12-22 Turbomachinery compressor
AT06292027T ATE425346T1 (en) 2006-12-22 2006-12-22 TURBO MACHINE COMPRESSOR

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06292027A EP1936125B1 (en) 2006-12-22 2006-12-22 Turbomachine compressor

Publications (2)

Publication Number Publication Date
EP1936125A1 EP1936125A1 (en) 2008-06-25
EP1936125B1 true EP1936125B1 (en) 2009-03-11

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EP06292027A Active EP1936125B1 (en) 2006-12-22 2006-12-22 Turbomachine compressor

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EP (1) EP1936125B1 (en)
AT (1) ATE425346T1 (en)
DE (1) DE602006005693D1 (en)
ES (1) ES2323283T3 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201103583D0 (en) 2011-03-03 2011-04-13 Rolls Royce Plc Fan casing for a turbofan engine
US10100674B2 (en) 2012-11-15 2018-10-16 Safran Aero Boosters Sa Radial fixing and positioning flanges for shells of axial turbine compressor housings
EP2733314B1 (en) * 2012-11-15 2017-04-05 Safran Aero Boosters SA Radial attachment and positioning flanges for axial turbomachine casing sections
FR3098241B1 (en) * 2019-07-04 2021-06-25 Safran Aircraft Engines DRUM FOR AN AIRCRAFT TURBOMACHINE

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB960812A (en) 1963-04-08 1964-06-17 Rolls Royce Compressor for a gas turbine engine
US5462403A (en) 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly

Also Published As

Publication number Publication date
ES2323283T3 (en) 2009-07-10
DE602006005693D1 (en) 2009-04-23
EP1936125A1 (en) 2008-06-25
ATE425346T1 (en) 2009-03-15

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