EP1811131B1 - Set of fixed sectorised diffuser inserts for a turbomachine compressor - Google Patents

Set of fixed sectorised diffuser inserts for a turbomachine compressor Download PDF

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Publication number
EP1811131B1
EP1811131B1 EP07290031.9A EP07290031A EP1811131B1 EP 1811131 B1 EP1811131 B1 EP 1811131B1 EP 07290031 A EP07290031 A EP 07290031A EP 1811131 B1 EP1811131 B1 EP 1811131B1
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EP
European Patent Office
Prior art keywords
rim
blades
assembly according
downstream
upstream
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EP07290031.9A
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German (de)
French (fr)
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EP1811131A2 (en
EP1811131A3 (en
Inventor
Olivier Abgrall
Yvon Cloarec
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction

Definitions

  • the present invention relates to a set of sectored fixed rectifiers for a compressor of a turbomachine, such as an airplane turbojet or turboprop.
  • a turbomachine compressor comprises a plurality of compression stages each comprising an annular row of moving blades mounted on a shaft of the turbomachine, and an annular row of fixed rectifiers carried by an outer casing.
  • Each annular row of stationary rectifiers is sectored and formed of sets of rectifiers circumferentially mounted end to end around the axis of the compressor, each set of rectifiers comprising two coaxial ferrules interconnected by radial blades, and being formed either of a single casting, either by fixing the ends of the blades on the ferrules.
  • the document EP 1 408 199 shows such a set of sectorized fixed rectifiers for a compressor.
  • a foundry assembly has a smaller axial footprint than an assembly formed by attaching the blades to the ferrules, but the leading and trailing edges of the blades of this assembly of a workpiece are connected to parts of the ferrule external which are themselves connected to annular mounting tabs on the outer casing and are therefore thick and very rigid.
  • the invention is intended to avoid this disadvantage while retaining the advantages of fixed sets of rectifiers formed of a casting.
  • a set of sectorized fixed rectifiers for a turbomachine compressor made in one piece and comprising two inner and outer shrouds extending coaxially one inside the other, radial blades s extending between the ferrules and connected by their radial ends to the ferrules, and two outer annular tabs carried by the outer ferrule and extending outside thereof, for mounting the set of rectifiers on a housing, characterized in that the leading or trailing edges of the blades are connected to areas of the outer shell less rigid than those connected to the annular mounting tabs.
  • the connection of the leading edges and / or leakage of the blades to parts of the outer shell which are less rigid than those connected to the annular mounting lugs makes it possible to better pass the forces between the edges of the ring. attack and leakage of the blades and the ferrule and thus to support the ferrule at least a portion of the stresses at which the leading and trailing edges of the blades are subjected in operation. This results in a significant increase in the life of these sets of fixed rectifiers.
  • At least one of the axial ends of the outer shell comprises a rim which extends substantially parallel to one of the annular mounting lugs and to which the leading edges or trailing edges of the blades.
  • the shapes and dimensions of the or each rim of the outer shell are determined so that this flange has sufficient flexibility to better distribute the constraints of the leading or trailing edges of the blades in operation.
  • the upstream end of the outer shell comprises a flange which is connected to the leading edges of the blades and which extends substantially parallel to the upstream annular lug.
  • downstream end of the shell comprises a flange which is connected to the trailing edges of the blades and which extends substantially parallel to the downstream annular tab.
  • each annular mounting lug which extends substantially parallel to such a rim of the outer shell is connected to a median portion of the shell, which may have a different thickness or radial dimension and for example greater than that of the rim.
  • the median portion of the outer shell may have a thickness or radial dimension optimized for the eigenfrequencies of the blades and ferrules while also improving the transmission of stresses between the blades and the outer shell.
  • the invention also relates to a turbomachine compressor, characterized in that it comprises at least one annular row of fixed rectifiers formed of sets of rectifiers as described above, mounted circumferentially end to end around the axis of the compressor , and a turbomachine, such as a turbojet engine or an airplane turboprop, comprising such a compressor.
  • the compressor 10 of the figure 1 comprises several compression stages of which only two have been shown, each stage comprising an annular row of blades 12, the radially inner ends of which are fixed on a disc 14 carried by a rotor shaft, not shown, and an annular row of fixed rectifiers 16, arranged downstream of the annular row of moving blades 12 and carried by an outer cylindrical casing 18.
  • the annular rows of stationary rectifiers 16 are sectored and formed of sets of rectifiers which are mounted circumferentially end to end around the axis of the compressor.
  • Each of these sets of rectifiers comprises two inner and outer coaxial ferrules 20 and 22, for example, in a portion of a cylinder which extend one inside the other and which are connected to one another by blades. 24.
  • These blades 24 have a concave inner surface or intrados and a convex or extrados outer surface which are connected to their upstream and downstream ends forming edges 26 and 28 of attack and leakage of the air flowing in the compressor.
  • Each set of fixed rectifiers is hooked on the outer casing 18 by means of two external annular tabs 30 formed at the axial ends of the outer shell 22, each annular tab 30 having an annular portion 32 which extends substantially radially towards the outside of the ferrule end 22, and a substantially cylindrical portion portion 34 which extends upstream or downstream respectively from the radially outer end of the annular portion 32 and which is engaged in a corresponding annular groove 36 of the housing.
  • the inner surface of the outer shell 22 is aligned with the inner surface of revolution of the casing 18.
  • a block of material 38 is fixed on the inner surface of the inner shell 20 and intended to cooperate in sealing with annular ribs 40 of the rotor shaft of the compressor, to prevent the passage of gas between the inner ring 20 and the rotor shaft.
  • the set of rectifiers of the figure 1 is formed of a single piece, in particular a casting, which makes it possible to minimize the axial dimension of the outer shell 22 and therefore the axial size of the set of rectifiers by bringing the outer tabs 30 as close to the edges as possible. attack 26 and leakage 28 radial blades.
  • the leading edges 26 and trailing edges 28 of the blades are thus connected to thick and rigid parts of the shell which are not flexible enough to partially absorb the stresses to which the leading and trailing edges of the blades are subjected. operation.
  • the set of rectifiers of the figure 2 is formed by assembling radial blades 24 on ferrules 20, 22, more precisely by interlocking and welding or soldering the ends of the blades 24 in corresponding orifices of the ferrules 20, 22.
  • the axial size of such an assembly is greater than that of the whole of the figure 1 because the attachment lugs 30 of the assembly are necessarily spaced, upstream and downstream respectively, mounting holes of the radial blades.
  • this embodiment allows the leading and trailing edges of the blades to be connected to relatively thin ferrule portions which are sufficiently flexible to absorb a portion of the stresses to which the leading edges 26 and 40 are subjected. leakage 28 blades in operation.
  • the present invention makes it possible to combine the advantages and to avoid the disadvantages of these two embodiments.
  • the outer ring 52 of the set 50 of rectifiers comprises a downstream flange 54 substantially in cylinder portion which is aligned axially with the remainder of the shell and which extends substantially parallel to the downstream annular tab 56 and inside of it.
  • This tab 56 has an annular portion 58 which extends substantially radially outwardly from the ferrule 52, and a portion 60 substantially in a portion of a cylinder or cone which extends downstream. from the radially outer end of the annular portion 58 and which is intended to be engaged in an annular groove of the housing 18.
  • the radial portion 58 of the downstream flap 56 is connected to the outer shell 52 upstream of the trailing edges 28 of the radial blades 24, which are connected to the rim 54 forming the downstream end of the outer shell 52.
  • its thickness may be reduced to give it a certain flexibility, which allows it to absorb some of the constraints applied to the trailing edges of the blades 24 in operation.
  • the thickness of the flange 54 may be substantially equal to that of the remainder of the ferrule (outside the connection zones of the external fastening tabs) or lower.
  • the portion 60 of the downstream leg 56 also comprises a radially outer annular rib 62 intended to abut on a corresponding surface of the housing when the portion 60 of the tab is engaged in the groove of the housing. On the view of the figure 1 this surface is radial and formed by a cylindrical rim of the casing 18.
  • the inner shell 20, the blades 24 and the upstream annular flange 30 are similar to those of the entire figure 1 .
  • the assembly 50 represented in figure 4 differs from that of the figure 3 in that the outer shell 52 also comprises an upstream rim 64 substantially in the form of a cylinder portion which is axially aligned with the remainder of the shell and which extends substantially parallel to the upstream annular tab 66 for fastening the assembly and to inside of it.
  • This lug 66 has an annular portion 68 that extends substantially radially outwardly from a portion of the shell located downstream of the zone of connection of the leading edges 26 of the blades, and a second portion 70 substantially in portion of cylinder which extends substantially axially upstream from the radially outer end of the annular portion 68 and which is intended to be engaged in an annular groove of the housing 18.
  • the upstream and downstream annular tabs 66 and 56 are separated from each other by a median portion of outer shell 52 which has substantially the same thickness or radial dimension as the upstream and downstream edges 64 and 54 of this ferrule. This makes it possible to optimize the eigenfrequencies of the blades 24 and the outer shell 52 while improving the transmission of stresses between the leading and trailing edges of the blades and the outer shell.
  • the upstream annular tabs 66 and downstream 56 are connected to a median portion 72 of the outer ring which has a thickness or radial dimension much greater than that of the upstream edges 64 and downstream 54 of the outer ring.
  • the first radial portions 58, 68 of the upstream and downstream lugs 66, respectively, are formed by the thick medial portion of the outer shell 52. This embodiment also makes it possible to improve the transmission of stresses between the blades and the outer shell.
  • the set of rectifiers of the figure 3 could be formed with a rim 54 at its upstream end and with an annular tab 30 at its downstream end, contrary to what is shown.

Description

La présente invention concerne un ensemble de redresseurs fixes sectorisé pour un compresseur d'une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a set of sectored fixed rectifiers for a compressor of a turbomachine, such as an airplane turbojet or turboprop.

Un compresseur de turbomachine comprend plusieurs étages de compression comportant chacun une rangée annulaire d'aubes mobiles montées sur un arbre de la turbomachine, et une rangée annulaire de redresseurs fixes portés par un carter externe.A turbomachine compressor comprises a plurality of compression stages each comprising an annular row of moving blades mounted on a shaft of the turbomachine, and an annular row of fixed rectifiers carried by an outer casing.

Chaque rangée annulaire de redresseurs fixes est sectorisée et formée d'ensembles de redresseurs montés circonférentiellement bout à bout autour de l'axe du compresseur, chaque ensemble de redresseurs comportant deux viroles coaxiales reliées entre elles par des pales radiales, et étant formé soit d'une seule pièce de fonderie, soit par fixation des extrémités des pales sur les viroles.Each annular row of stationary rectifiers is sectored and formed of sets of rectifiers circumferentially mounted end to end around the axis of the compressor, each set of rectifiers comprising two coaxial ferrules interconnected by radial blades, and being formed either of a single casting, either by fixing the ends of the blades on the ferrules.

Le document EP 1 408 199 montre un tel ensemble de redresseurs fixes sectorisés pour un compresseur. Un ensemble formé de fonderie a un encombrement axial plus faible qu'un ensemble formé par fixation des pales sur les viroles, mais les bords d'attaque et de fuite des pales de cet ensemble d'une pièce sont raccordés à des parties de la virole externe qui sont elles-mêmes raccordées à des pattes annulaires de montage sur le carter externe et qui sont donc épaisses et très rigides.The document EP 1 408 199 shows such a set of sectorized fixed rectifiers for a compressor. A foundry assembly has a smaller axial footprint than an assembly formed by attaching the blades to the ferrules, but the leading and trailing edges of the blades of this assembly of a workpiece are connected to parts of the ferrule external which are themselves connected to annular mounting tabs on the outer casing and are therefore thick and very rigid.

En conséquence, les contraintes auxquelles les bords d'attaque et de fuite des pales sont soumis en fonctionnement, sont supportées essentiellement par ces bords d'attaque et de fuite qui sont minces et peu résistants et ne sont pas amorties en partie par la virole externe, ce qui peut entraîner une détérioration ou une destruction des bords d'attaque et de fuite des pales dans leurs zones de raccordement à la virole externe.As a result, the stresses at which the leading and trailing edges of the blades are subjected to operation are essentially supported by these leading and trailing edges which are thin and weak and are not partially damped by the outer shroud. which can lead to damage or destruction of the leading and trailing edges of the blades in their areas of connection to the outer shell.

L'invention a notamment pour but d'éviter cet inconvénient tout en conservant les avantages des ensembles de redresseurs fixes formés d'une pièce de fonderie.The invention is intended to avoid this disadvantage while retaining the advantages of fixed sets of rectifiers formed of a casting.

Elle propose à cet effet un ensemble de redresseurs fixes sectorisé pour un compresseur de turbomachine, réalisé d'une seule pièce et comprenant deux viroles interne et externe s'étendant coaxialement l'une à l'intérieur de l'autre, des pales radiales s'étendant entre les viroles et raccordées par leurs extrémités radiales aux viroles, et deux pattes annulaires externes portées par la virole externe et s'étendant à l'extérieur de celle-ci, pour le montage de l'ensemble de redresseurs sur un carter, caractérisé en ce que les bords d'attaque ou de fuite des pales sont raccordés à des zones de la virole externe moins rigides que celles raccordées aux pattes annulaires de montage.It proposes for this purpose a set of sectorized fixed rectifiers for a turbomachine compressor, made in one piece and comprising two inner and outer shrouds extending coaxially one inside the other, radial blades s extending between the ferrules and connected by their radial ends to the ferrules, and two outer annular tabs carried by the outer ferrule and extending outside thereof, for mounting the set of rectifiers on a housing, characterized in that the leading or trailing edges of the blades are connected to areas of the outer shell less rigid than those connected to the annular mounting tabs.

Selon l'invention, le raccordement des bords d'attaque et/ou de fuite des pales à des parties de la virole externe qui sont moins rigides que celles raccordées aux pattes annulaires de montage, permet de mieux faire transiter les efforts entre les bords d'attaque et de fuite des pales et la virole et donc de faire supporter par la virole au moins une partie des contraintes auxquelles les bords d'attaque et de fuite des pales sont soumis en fonctionnement. Il en résulte une augmentation significative de la durée de vie de ces ensembles de redresseurs fixes.According to the invention, the connection of the leading edges and / or leakage of the blades to parts of the outer shell which are less rigid than those connected to the annular mounting lugs, makes it possible to better pass the forces between the edges of the ring. attack and leakage of the blades and the ferrule and thus to support the ferrule at least a portion of the stresses at which the leading and trailing edges of the blades are subjected in operation. This results in a significant increase in the life of these sets of fixed rectifiers.

Selon une autre caractéristique de l'invention, au moins l'une des extrémités axiales de la virole externe comporte un rebord qui s'étend sensiblement parallèlement à l'une des pattes annulaires de montage et auquel sont raccordés les bords d'attaque ou les bords de fuite des pales.According to another characteristic of the invention, at least one of the axial ends of the outer shell comprises a rim which extends substantially parallel to one of the annular mounting lugs and to which the leading edges or trailing edges of the blades.

Les formes et dimensions du ou de chaque rebord de la virole externe sont déterminées pour que ce rebord ait une flexibilité suffisante pour mieux distribuer les contraintes des bords d'attaque ou de fuite des pales en fonctionnement.The shapes and dimensions of the or each rim of the outer shell are determined so that this flange has sufficient flexibility to better distribute the constraints of the leading or trailing edges of the blades in operation.

Dans un mode de réalisation de l'invention, l'extrémité amont de la virole externe comporte un rebord qui est raccordé aux bords d'attaque des pales et qui s'étend sensiblement parallèlement à la patte annulaire amont.In one embodiment of the invention, the upstream end of the outer shell comprises a flange which is connected to the leading edges of the blades and which extends substantially parallel to the upstream annular lug.

En variante ou en caractéristique additionnelle, l'extrémité aval de la virole comporte un rebord qui est raccordé aux bords de fuite des pales et qui s'étend sensiblement parallèlement à la patte annulaire aval.As a variant or as an additional feature, the downstream end of the shell comprises a flange which is connected to the trailing edges of the blades and which extends substantially parallel to the downstream annular tab.

La ou chaque patte annulaire de montage qui s'étend sensiblement parallèlement à un tel rebord de la virole externe est raccordée à une partie médiane de cette virole, qui peut avoir une épaisseur ou dimension radiale différente et par exemple supérieure à celle du rebord.The or each annular mounting lug which extends substantially parallel to such a rim of the outer shell is connected to a median portion of the shell, which may have a different thickness or radial dimension and for example greater than that of the rim.

La partie médiane de la virole externe peut avoir une épaisseur ou dimension radiale optimisée pour les fréquences propres des pales et des viroles tout en améliorant également la transmission de contraintes entre les pales et la virole externe.The median portion of the outer shell may have a thickness or radial dimension optimized for the eigenfrequencies of the blades and ferrules while also improving the transmission of stresses between the blades and the outer shell.

L'invention concerne également un compresseur de turbomachine, caractérisé en ce qu'il comprend au moins une rangée annulaire de redresseurs fixes formée d'ensembles de redresseurs tels que décrits ci-dessus, montés circonférentiellement bout à bout autour de l'axe du compresseur, et une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, comprenant un tel compresseur.The invention also relates to a turbomachine compressor, characterized in that it comprises at least one annular row of fixed rectifiers formed of sets of rectifiers as described above, mounted circumferentially end to end around the axis of the compressor , and a turbomachine, such as a turbojet engine or an airplane turboprop, comprising such a compressor.

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

  • la figure 1 est une vue schématique partielle en coupe axiale d'un compresseur haute-pression de turbomachine, et représente un ensemble de redresseurs fixes formé de fonderie selon la technique antérieure ;
  • la figure 2 représente un autre ensemble de redresseurs fixes de la technique antérieure ;
  • la figure 3 est une vue schématique en perspective d'un ensemble de redresseurs fixes selon l'invention ;
  • les figures 4 et 5 sont des vues schématiques en perspective de variantes de réalisation de l'ensemble de redresseurs fixes selon l'invention.
The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description, given by way of non-limiting example with reference to the accompanying drawings, in which:
  • the figure 1 is a partial schematic view in axial section of a high-pressure turbomachine compressor, and shows a set of fixed rectifiers formed by casting according to the prior art;
  • the figure 2 represents another set of fixed rectifiers of the prior art;
  • the figure 3 is a schematic perspective view of a set of fixed rectifiers according to the invention;
  • the Figures 4 and 5 are schematic perspective views of alternative embodiments of the set of fixed rectifiers according to the invention.

Le compresseur 10 de la figure 1 comprend plusieurs étages de compression dont deux seulement ont été représentés, chaque étage comportant une rangée annulaire d'aubes mobiles 12, dont les extrémités radialement internes sont fixées sur un disque 14 porté par un arbre de rotor, non représenté, et une rangée annulaire de redresseurs fixes 16, agencés en aval de la rangée annulaire d'aubes mobile 12 et portés par un carter cylindrique externe 18.The compressor 10 of the figure 1 comprises several compression stages of which only two have been shown, each stage comprising an annular row of blades 12, the radially inner ends of which are fixed on a disc 14 carried by a rotor shaft, not shown, and an annular row of fixed rectifiers 16, arranged downstream of the annular row of moving blades 12 and carried by an outer cylindrical casing 18.

Les rangées annulaires de redresseurs fixes 16 sont sectorisées et formées d'ensembles de redresseurs qui sont montés circonférentiellement bout à bout autour de l'axe du compresseur. Chacun de ces ensembles de redresseurs comprend deux viroles coaxiales interne 20 et externe 22 par exemple en portion de cylindre qui s'étendent l'une à l'intérieur de l'autre et qui sont reliées l'une à l'autre par des pales radiales 24. Ces pales 24 ont une surface intérieure concave ou intrados et une surface extérieure convexe ou extrados qui sont reliées à leurs extrémités amont et aval en formant des bords 26 et 28 d'attaque et de fuite de l'air qui s'écoule dans le compresseur.The annular rows of stationary rectifiers 16 are sectored and formed of sets of rectifiers which are mounted circumferentially end to end around the axis of the compressor. Each of these sets of rectifiers comprises two inner and outer coaxial ferrules 20 and 22, for example, in a portion of a cylinder which extend one inside the other and which are connected to one another by blades. 24. These blades 24 have a concave inner surface or intrados and a convex or extrados outer surface which are connected to their upstream and downstream ends forming edges 26 and 28 of attack and leakage of the air flowing in the compressor.

Chaque ensemble de redresseurs fixes est accroché sur le carter externe 18 par l'intermédiaire de deux pattes annulaires externes 30 formées aux extrémités axiales de la virole externe 22, chaque patte annulaire 30 comportant une partie annulaire 32 qui s'étend sensiblement radialement vers l'extérieur depuis l'extrémité de la virole 22, et une partie 34 sensiblement en portion de cylindre qui s'étend vers l'amont ou vers l'aval respectivement, depuis l'extrémité radialement externe de la partie annulaire 32 et qui est engagée dans une rainure annulaire 36 correspondante du carter.Each set of fixed rectifiers is hooked on the outer casing 18 by means of two external annular tabs 30 formed at the axial ends of the outer shell 22, each annular tab 30 having an annular portion 32 which extends substantially radially towards the outside of the ferrule end 22, and a substantially cylindrical portion portion 34 which extends upstream or downstream respectively from the radially outer end of the annular portion 32 and which is engaged in a corresponding annular groove 36 of the housing.

La surface interne de la virole externe 22 est alignée avec la surface de révolution interne du carter 18. Un bloc de matière 38 est fixé sur la surface interne de la virole interne 20 et destiné à coopérer à étanchéité avec des nervures annulaires 40 de l'arbre de rotor du compresseur, pour empêcher le passage de gaz entre la virole interne 20 et l'arbre de rotor.The inner surface of the outer shell 22 is aligned with the inner surface of revolution of the casing 18. A block of material 38 is fixed on the inner surface of the inner shell 20 and intended to cooperate in sealing with annular ribs 40 of the rotor shaft of the compressor, to prevent the passage of gas between the inner ring 20 and the rotor shaft.

L'ensemble de redresseurs de la figure 1 est formé d'une seule pièce, notamment de fonderie, ce qui permet de minimiser la dimension axiale de la virole externe 22 et donc l'encombrement axial de l'ensemble de redresseur en amenant les pattes externes 30 au plus près des bords d'attaque 26 et de fuite 28 des pales radiales. Les bords d'attaque 26 et de fuite 28 des pales sont ainsi raccordés à des parties épaisses et rigides de la virole qui ne sont pas suffisamment flexibles pour absorber en partie les contraintes auxquelles sont soumis les bords d'attaque et de fuite des pales en fonctionnement.The set of rectifiers of the figure 1 is formed of a single piece, in particular a casting, which makes it possible to minimize the axial dimension of the outer shell 22 and therefore the axial size of the set of rectifiers by bringing the outer tabs 30 as close to the edges as possible. attack 26 and leakage 28 radial blades. The leading edges 26 and trailing edges 28 of the blades are thus connected to thick and rigid parts of the shell which are not flexible enough to partially absorb the stresses to which the leading and trailing edges of the blades are subjected. operation.

L'ensemble de redresseurs de la figure 2 est formé par assemblage de pales radiales 24 sur des viroles 20, 22, plus précisément par emboîtement et soudage ou brasage des extrémités des pales 24 dans des orifices correspondants des viroles 20, 22. L'encombrement axial d'un tel ensemble est supérieur à celui de l'ensemble de la figure 1 car les pattes d'accrochage 30 de l'ensemble sont nécessairement écartées, vers l'amont et vers l'aval respectivement, des orifices de montage des pales radiales. Toutefois, ce mode de réalisation permet aux bords d'attaque et de fuite des pales d'être raccordés à des parties de virole de relativement faible épaisseur qui sont suffisamment flexibles pour absorber une partie des contraintes auxquelles sont soumis les bords d'attaque 26 et de fuite 28 des pales en fonctionnement.The set of rectifiers of the figure 2 is formed by assembling radial blades 24 on ferrules 20, 22, more precisely by interlocking and welding or soldering the ends of the blades 24 in corresponding orifices of the ferrules 20, 22. The axial size of such an assembly is greater than that of the whole of the figure 1 because the attachment lugs 30 of the assembly are necessarily spaced, upstream and downstream respectively, mounting holes of the radial blades. However, this embodiment allows the leading and trailing edges of the blades to be connected to relatively thin ferrule portions which are sufficiently flexible to absorb a portion of the stresses to which the leading edges 26 and 40 are subjected. leakage 28 blades in operation.

La présente invention permet de combiner les avantages et d'éviter les inconvénients de ces deux modes de réalisation.The present invention makes it possible to combine the advantages and to avoid the disadvantages of these two embodiments.

Dans une première forme de réalisation de l'invention représentée en figure 3, la virole externe 52 de l'ensemble 50 de redresseurs comporte un rebord aval 54 sensiblement en portion de cylindre qui est aligné axialement avec le reste de la virole et qui s'étend sensiblement parallèlement à la patte annulaire aval 56 et à l'intérieur de celle-ci. Cette patte 56 comporte une partie annulaire 58 qui s'étend sensiblement radialement vers l'extérieur depuis la virole 52, et une partie 60 sensiblement en portion de cylindre ou de cône qui s'étend vers l'aval depuis l'extrémité radialement externe de la partie annulaire 58 et qui est destinée à être engagée dans une rainure annulaire du carter 18.In a first embodiment of the invention shown in figure 3 , the outer ring 52 of the set 50 of rectifiers comprises a downstream flange 54 substantially in cylinder portion which is aligned axially with the remainder of the shell and which extends substantially parallel to the downstream annular tab 56 and inside of it. This tab 56 has an annular portion 58 which extends substantially radially outwardly from the ferrule 52, and a portion 60 substantially in a portion of a cylinder or cone which extends downstream. from the radially outer end of the annular portion 58 and which is intended to be engaged in an annular groove of the housing 18.

La partie radiale 58 de la patte aval 56 est raccordée à la virole externe 52 en amont des bords de fuite 28 des pales radiales 24, qui sont raccordés au rebord 54 formant l'extrémité aval de la virole externe 52. Comme ce rebord 54 ne sert pas au raccordement de la patte externe 56 et ne participe pas à l'accrochage de l'ensemble de redresseurs su le carter, son épaisseur peut être réduite pour lui conférer une certaine flexibilité, ce qui lui permet d'absorber en partie les contraintes appliquées aux bords de fuite des pales 24 en fonctionnement. L'épaisseur du rebord 54 peut être sensiblement égale à celle du reste de la virole (en dehors des zones de raccordement des pattes externes d'accrochage) ou inférieure.The radial portion 58 of the downstream flap 56 is connected to the outer shell 52 upstream of the trailing edges 28 of the radial blades 24, which are connected to the rim 54 forming the downstream end of the outer shell 52. not used to connect the outer leg 56 and does not participate in the attachment of the set of rectifiers on the housing, its thickness may be reduced to give it a certain flexibility, which allows it to absorb some of the constraints applied to the trailing edges of the blades 24 in operation. The thickness of the flange 54 may be substantially equal to that of the remainder of the ferrule (outside the connection zones of the external fastening tabs) or lower.

La partie 60 de la patte aval 56 comprend également une nervure annulaire 62 radialement externe destinée à venir en butée sur une surface correspondante du carter lorsque la partie 60 de la patte est engagée dans la rainure du carter. Sur la vue de la figure 1, cette surface est radiale et formée par un rebord cylindrique du carter 18.The portion 60 of the downstream leg 56 also comprises a radially outer annular rib 62 intended to abut on a corresponding surface of the housing when the portion 60 of the tab is engaged in the groove of the housing. On the view of the figure 1 this surface is radial and formed by a cylindrical rim of the casing 18.

La virole interne 20, les pales 24 et la patte annulaire amont 30 sont semblables à celles de l'ensemble de la figure 1.The inner shell 20, the blades 24 and the upstream annular flange 30 are similar to those of the entire figure 1 .

L'ensemble 50 représenté en figure 4 diffère de celui de la figure 3 en ce que la virole externe 52 comporte également un rebord amont 64 sensiblement en portion de cylindre qui est aligné axialement avec le reste de la virole et qui s'étend sensiblement parallèlement à la patte annulaire amont 66 d'accrochage de l'ensemble et à l'intérieur de celle-ci. Cette patte 66 comporte une partie annulaire 68 qui s'étend sensiblement radialement vers l'extérieur depuis une partie de la virole située en aval de la zone de raccordement des bords d'attaque 26 des pales, et une seconde partie 70 sensiblement en portion de cylindre qui s'étend sensiblement axialement vers l'amont depuis l'extrémité radialement externe de la partie annulaire 68 et qui est destinée à être engagée dans une rainure annulaire du carter 18.The assembly 50 represented in figure 4 differs from that of the figure 3 in that the outer shell 52 also comprises an upstream rim 64 substantially in the form of a cylinder portion which is axially aligned with the remainder of the shell and which extends substantially parallel to the upstream annular tab 66 for fastening the assembly and to inside of it. This lug 66 has an annular portion 68 that extends substantially radially outwardly from a portion of the shell located downstream of the zone of connection of the leading edges 26 of the blades, and a second portion 70 substantially in portion of cylinder which extends substantially axially upstream from the radially outer end of the annular portion 68 and which is intended to be engaged in an annular groove of the housing 18.

Dans ce mode de réalisation, les pattes annulaires amont 66 et aval 56 sont séparées l'une de l'autre par une partie médiane de virole externe 52 qui a sensiblement la même épaisseur ou dimension radiale que les rebords amont 64 et aval 54 de cette virole. Cela permet d'optimiser les fréquences propres des pales 24 et de la virole externe 52 tout en améliorant la transmission de contraintes entre les bords d'attaque et de fuite des pales et la virole externe.In this embodiment, the upstream and downstream annular tabs 66 and 56 are separated from each other by a median portion of outer shell 52 which has substantially the same thickness or radial dimension as the upstream and downstream edges 64 and 54 of this ferrule. This makes it possible to optimize the eigenfrequencies of the blades 24 and the outer shell 52 while improving the transmission of stresses between the leading and trailing edges of the blades and the outer shell.

Dans la variante de réalisation de la figure 5, les pattes annulaires amont 66 et aval 56 d'accrochage sont raccordées à une partie médiane 72 de la virole externe qui a une épaisseur ou dimension radiale nettement supérieure à celles des rebords amont 64 et aval 54 de la virole externe. Dans l'exemple représenté, les premières parties radiales 58, 68 des pattes amont 66 et aval 56, respectivement, sont formées par la partie médiane épaisse de la virole externe 52. Ce mode de réalisation permet également d'améliorer la transmission de contraintes entre les pales et la virole externe.In the variant embodiment of the figure 5 , the upstream annular tabs 66 and downstream 56 are connected to a median portion 72 of the outer ring which has a thickness or radial dimension much greater than that of the upstream edges 64 and downstream 54 of the outer ring. In the example shown, the first radial portions 58, 68 of the upstream and downstream lugs 66, respectively, are formed by the thick medial portion of the outer shell 52. This embodiment also makes it possible to improve the transmission of stresses between the blades and the outer shell.

Bien entendu, l'invention n'est pas limitée aux modes de réalisation qui ont été décrits dans ce qui précède et représentés dans les dessins annexés. Par exemple, l'ensemble de redresseurs de la figure 3 pourrait être formé avec un rebord 54 à son extrémité amont et avec une patte annulaire 30 à son extrémité aval, à l'inverse de ce qui est représenté.Of course, the invention is not limited to the embodiments that have been described in the foregoing and shown in the accompanying drawings. For example, the set of rectifiers of the figure 3 could be formed with a rim 54 at its upstream end and with an annular tab 30 at its downstream end, contrary to what is shown.

Claims (14)

  1. An assembly of sectorized fixed stators (50) for a turbomachine compressor (10), made in one piece and comprising an inner ferrule (20) and an outer ferrule (52) extending coaxially one inside the other, and radial blades (24) extending between the ferrules (20, 52) and connected at their radial ends to the ferrules, and two outer annular lugs (30,56,66) carried by the outer ferrule (52) and extending on its outer side, for mounting the assembly of sectorized fixed stators onto the casing (18) characterized in that the leading (26) or trailing (28) edges of the blades (24) are connected to areas of the outer ferrule (52) which are less rigid than those connected to the mounting annular lugs (56, 66).
  2. An assembly according to claim 1, characterized in that at least one of the axial ends of the outer ferrule (52) has a rim (54, 64) extending substantially parallel to one of the mounting annular lugs (56, 66) and to which are connected the leading edges (26) or the trailing edges (28) of the blades (24).
  3. An assembly according to claim 2, characterized in that the rim (64) of the outer ferrule (52) is at the upstream end of the ferrule (52) and is connected to the leading edges (26) of the blades (24).
  4. An assembly according to claim 2, characterized in that the rim (54) of the outer ferrule (52) is at the downstream end of the ferrule (52).and is connected to the trailing edge (28) of the blades (24).
  5. An assembly according to claim 2, characterized in that the outer ferrule (52) comprises at its upstream end a first rim (64) to which the leading edges (26) of the blades (24) are connected and comprises at its downstream end a second rim (54) to which the trailing edges (28) of the blades (24) are connected.
  6. An assembly according to claim 3 or 5, characterized in that the upstream mounting annular lug (66) and the upstream rim (64) are connected to a middle portion of the outer ferrule (52) which has substantially the same thickness or radial dimension than the upstream rim (64).
  7. An assembly according to claim 4 or 5, characterized in that the downstream mounting annular lug (56) and the downstream rim (54) are connected to a middle portion of the outer ferrule (52) which has substantially the same thickness or radial dimension than the downstream rim(54).
  8. An assembly according to claim 3 or 5, characterized in that the upstream mounting annular lug (66) and the upstream rim (64) are connected to a middle portion (72) of the outer ferrule (52), which has a thickness or a radial dimension greater than the upstream rim (64).
  9. An assembly according to claim 4 or 5, characterized in that the downstream mounting annular lug (56) and the downstream rim (54) are connected to a middle portion (72) of the outer ferrule (52), which has a thickness or a radial dimension greater than the downstream rim (54).
  10. An assembly according to claim 3 or 4, characterized in that one of the mounting annular lugs (30) is connected to an axial end of the outer ferrule (52).
  11. Assembly according to one of the preceding claims, characterized in that one of the mounting annular lugs (56) comprises at least one radially outer annular rib (62) for abutment against a corresponding surface of the housing (18).
  12. Assembly according to one of the preceding claims, characterized in that it is made of foundry.
  13. A turbomachine compressor (10), characterized in that it comprises at least one annular row of fixed stators formed of sets of stators (50) according to one of the preceding claims, mounted circumferentially end to end about the axis of the turbomachine compressor.
  14. A turbomachine, such as an aircraft turbojet or turboprop, characterized in that it comprises a compressor (10) according to claim 13.
EP07290031.9A 2006-01-24 2007-01-10 Set of fixed sectorised diffuser inserts for a turbomachine compressor Active EP1811131B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0600616A FR2896548B1 (en) 2006-01-24 2006-01-24 SECTORIZED FIXED RECTIFIER ASSEMBLY FOR A TURBOMACHINE COMPRESSOR

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EP1811131A3 EP1811131A3 (en) 2008-09-24
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EP1811131A2 (en) 2007-07-25
US7946811B2 (en) 2011-05-24
EP1811131A3 (en) 2008-09-24
RU2439338C2 (en) 2012-01-10
US20070172349A1 (en) 2007-07-26
FR2896548B1 (en) 2011-05-27
FR2896548A1 (en) 2007-07-27
RU2007102521A (en) 2008-07-27

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