EP3351736B1 - Internal ferrule of an axial turbine-engine compressor - Google Patents

Internal ferrule of an axial turbine-engine compressor Download PDF

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Publication number
EP3351736B1
EP3351736B1 EP18159641.2A EP18159641A EP3351736B1 EP 3351736 B1 EP3351736 B1 EP 3351736B1 EP 18159641 A EP18159641 A EP 18159641A EP 3351736 B1 EP3351736 B1 EP 3351736B1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
shroud
rotor
ferrule
roughness
Prior art date
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Active
Application number
EP18159641.2A
Other languages
German (de)
French (fr)
Other versions
EP3351736A1 (en
Inventor
Jean-François Cortequisse
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
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Safran Aero Boosters SA
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Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3351736A1 publication Critical patent/EP3351736A1/en
Application granted granted Critical
Publication of EP3351736B1 publication Critical patent/EP3351736B1/en
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Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the field of the present invention is that of axial turbomachines. More particularly, the invention addresses the internal ferrules connected to a row of stator vanes.
  • An internal ferrule is known for making it possible to delimit the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid stream. Thanks to its external surface, it helps guide the flow during its expansion in a turbine, or its compression in a compressor.
  • an internal ferrule can be mounted on the internal ends of vanes arranged in an annular row, themselves linked to an external casing.
  • the ferrule has recesses for the introduction of the ferrule fixing ends.
  • the internal ferrule is also intended to ensure a seal with the rotor around which it is placed. To this end, it has a layer of abradable material cooperating by abrasion with wipers formed outside the rotor. In operation, the wipers come close to the abradable, possibly creating circular notches there, so that a dynamic seal is ensured.
  • each internal ferrule comprises a tubular wall in which are provided rows of openings. These allow the introduction of the blade roots used for fixing between the ferrule and the blades.
  • Each opening has a lip which extends radially around it, ribs join the lips of the neighboring openings, the assembly making it possible to stiffen the ferrule.
  • the bending stiffness of the shell; in particular of its segments remains limited.
  • the main efforts are taken up by the branches of the U shape of the ferrule.
  • the openings can open further around the seals surrounding the blades, which degrades the seal.
  • the document EP1419849A1 discloses a method of repairing a turbine segment.
  • the segment comprises a pair of blades, the ends of which are linked to an internal ferrule.
  • the latter has two openings linked to the blades, the opposite edges of the openings being joined by a flange.
  • the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the sealing of a ferrule or a segment of a ferrule. The invention also aims to improve the rigidity of an assembly comprising a ferrule and vanes linked in openings formed in the ferrule. Another object of the invention is to stiffen an internal ferrule or an internal ferrule segment linked to stator vanes.
  • the subject of the invention is a turbomachine comprising a rotor and an internal ferrule around the rotor or an internal ferrule segment matching the rotor, the ferrule or the ferrule segment comprising a circular or semi-circular wall whose profile mainly extends axially, and a circular or semi-circular radial flange extend radially from the wall towards the inside, the flange having a circular or semi-circular surface whose profile extends mainly radially, said surface having asperities.
  • the rotor has annular ribs cooperating sealingly with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced from each radial flange of the ferrule or the ferrule segment. Furthermore, at least one or each radial flange comprises asperities which are formed over the majority of the radial height of the profile of revolution of one of the annular ribs of the rotor disposed opposite the associated radial flange.
  • At least one or each radial flange comprises at least one surface with asperities, said surface being generally perpendicular to the axis of revolution of the ferrule or of the ferrule segment.
  • the asperities form a pattern repeated on substantially an entire face of the corresponding radial flange.
  • the radial flange makes it possible to form a bridge which spans each opening.
  • the flange thus makes it possible to link the opposite edges of the openings so as to connect the edges.
  • This mechanical seal makes it possible to link the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the material vacuum of the openings.
  • the invention makes it possible to improve the seal between a ferrule or a segment of a ferrule with openings in which stator vanes are fixed.
  • the invention thus provides a ferrule or a segment of ferrule which is both light, rigid, and economical to produce.
  • the terms internal or internal and external or external refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the lateral direction is according to the circumference.
  • the figure 1 represents in a simplified manner an axial turbomachine.
  • the turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 5, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first level of compression called a low-pressure compressor 5
  • a second level of compression called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.
  • Reduction means can increase the speed of rotation transmitted to the compressors.
  • An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the outlet of the turbine.
  • the secondary flow can be accelerated so as to generate a thrust reaction.
  • the primary 18 and secondary 20 flows are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical or ferrule walls which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 5.
  • the rotor 12 comprises a drum with an external annular wall which supports several rows of rotor blades 24, in this case three rows.
  • the low-pressure compressor 5 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.
  • the rectifiers are associated with the fan or with a row of rotor vanes to straighten the air flow, so as to convert the velocity of the flow into static pressure.
  • the stator vanes 26 extend essentially radially from an external casing 22, and can be fixed to it using a pin.
  • the casing 22 then forms an external support for the different rows.
  • the compressor 5 also includes internal ferrules 28 which are fixed to the radially internal ends of the stator vanes 26.
  • the internal ferrules 28 make it possible to guide and delimit the primary flow 18. They also provide a seal with the rotor 12 to avoid recirculation d air reducing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine.
  • Each ferrule 28 can form a ring of a turn, or be segmented angularly.
  • the figure 3 represents a portion of the compressor such as that of the figure 2 .
  • the internal ferrule 28 could be segmented.
  • the ferrule 28 has a profile of revolution with a portion extending mainly axially and which generates an axial wall 32.
  • the axial wall 32 may be generally tubular, and be substantially inclined relative to the axis of rotation 14 of the turbomachine; the latter may coincide with the general axis of symmetry 14 of the shell 28.
  • the ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are crossed by the ends 30 of the vanes 26 to suspend the ferrule 28 there. Each opening 34 has opposite edges 36 in the direction of the row of openings 34, these edges 36 being placed opposite the faces of the associated dawn 26. One is facing the lower surface of the dawn, the other facing the upper surface.
  • the edges 36 can generally be conjugates; one is concave, the other convex.
  • the ferrule 28 further comprises at least one radial flange 38 which extends radially inwards from the axial wall 32.
  • the ferrule 28 may comprise several radial flanges 38 which each cut the openings 34. These radial flanges may be parallel, and distributed axially through the openings.
  • the ferrule 28 may comprise at least three radial flanges, including an upstream radial flange 40, a downstream radial flange 42, and a through radial flange 38 which passes through the openings 34, or central radial flange 38.
  • the through radial flange 38 is disposed axially between the upstream 40 and downstream 42 flanges.
  • the ferrule may have an “E” or comb profile.
  • the rotor 12 in particular its wall has annular ribs 44, also called “wipers". They extend radially and cooperate with the shell 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in the event of contact.
  • abradable material is meant a friable material in the event of contact.
  • the abradable layers 46 can be applied to the ends of the blades 30, and / or to the axial wall 32.
  • the abradable layers 46 and the radial flanges (38; 40; 42) form an alternation.
  • the radial flanges (38; 40; 42) can be combined in pairs to frame each annular rib 44 of rotor 12, possibly individually.
  • Each radial flange (38; 40; 42) comprises a profile of revolution which extends essentially radially, each flange profile extends over the majority of the radial height of each profile of the flange neighboring radial.
  • Each rib profile (38; 40; 42) extends over the majority of the radial height of the profiles of the adjacent annular ribs 44.
  • the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with roughness 48 which amplifies turbulence 50, or vortices 50 opposing recirculations 52.
  • the figure 4 represents a section of the ferrule 28 and the stator vanes 26 along the axis 4-4 traced on the figure 3 .
  • the cutting plane passes through the radial flange 38 which crosses the openings 34.
  • the ferrule could be formed by segments of ferrule which would be placed end to end so as to form a circle.
  • the blades 26 extend radially from the ferrule 28 and pass through the openings 34. Their radial ends 30 are in radial abutment against the radial flange 38. Each blade end 30 has a radial abutment surface which cooperates with a abutment surface niche correspondent. Seals 54 extend radially into the openings 34 and pass through them, they come into contact with the radial flange 38. The bottoms of notches, or abutment surfaces of the notches, are spaced from the seals 54 and / or the axial wall.
  • the radial flange 38 not only joins all the openings 34, but also connects all the opposite edges 36 to each other by crossing the openings 34. It forms a reinforcing bar which, in each opening 34, blocks the opposite edges 36
  • the radial flange 38 has an arcuate shape and a notched profile. It comprises a series of steps forming notches 56 in which the ends 30 of the blades 30 are placed. These notches 56 can be a place for fixing the blades 26, for example by gluing or using fixing plates (not shown). To this end, the ends 30 may include fixing orifices (not shown). Within each opening 34, the radial flange 38 links the opposite edges 36. This configuration stiffens the ferrule 28, and prevents it from bending at the openings, 38 so that the risk of detachment at the joints 54 is reduced.
  • the figure 5 represents a section along axis 5-5 drawn on the figure 3 .
  • the section shows a compressor section between the rotor 12 and an internal shroud, seen from the outside. The location of the blade ends 30 is shown.
  • the asperities 48 comprise grooves and ridges alternating with the grooves, They extend radially and are optionally perpendicular to the axis of rotation of the turbomachine.
  • the assembly can form a striated annular surface.
  • the asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.
  • the asperities 48 are formed opposite the wipers 44, preferably on each side.
  • the pattern can be formed along, along the circumference, radial flanges (38; 40; 42); or all around. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air entrained by the rotor 12
  • the figure 6 shows a diagram of a method of assembling a stator vane on a ferrule, the ferrule being able to be segmented.
  • Step (b) supply 102 can comprise additive manufacturing of the shell or of the shell segment.
  • the ferrule or each segment may have come from a mantle and be made of polymer, for example a composite martial material with fibers, possibly of length less than 10 mm.
  • Positioning step (c) 104 can be carried out by fixing the blades to an external compressor casing. Then the ferrule is brought together radially so that the internal ends of the blades are found in the openings. Initially, the blade tips enter the openings, then pass through them. Finally, these ends abut against a radial flange. The stop is then axial and / or radial, which makes it possible to improve the relative position between the blade and the shell. Thus, the joint produced or implemented during step (e) implementation or production 108 is better positioned and / or better produced.

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

Description

Domaine techniqueTechnical area

Le domaine de la présente invention est celui des turbomachines axiales. Plus particulièrement, l'invention aborde les viroles internes reliées à une rangée d'aubes de stator.The field of the present invention is that of axial turbomachines. More particularly, the invention addresses the internal ferrules connected to a row of stator vanes.

Technique antérieurePrior art

Une virole interne est connue pour permettre de délimiter le flux primaire d'une turbomachine axiale, elle forme une paroi annulaire qui délimite l'intérieur de la veine fluide. Grâce à sa surface externe, elle contribue à guider le flux au cours de sa détente dans une turbine, ou de sa compression dans un compresseur.An internal ferrule is known for making it possible to delimit the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid stream. Thanks to its external surface, it helps guide the flow during its expansion in a turbine, or its compression in a compressor.

De manière classique, une virole interne peut être montée sur des extrémités internes d'aubes disposées en une rangée annulaire, elles-mêmes liées à un carter externe. La virole présente des évidements pour l'introduction des extrémités de fixation des viroles.Conventionally, an internal ferrule can be mounted on the internal ends of vanes arranged in an annular row, themselves linked to an external casing. The ferrule has recesses for the introduction of the ferrule fixing ends.

La virole interne a également pour vocation d'assurer une étanchéité avec le rotor autour duquel elle est placée. A cet effet, elle présente une couche de matériau abradable coopérant par abrasion avec des léchettes formées à l'extérieur du rotor. En fonctionnement, les léchettes viennent à proximité de l'abradable, y créent éventuellement des entailles circulaires, si bien qu'une étanchéité dynamique est assurée.The internal ferrule is also intended to ensure a seal with the rotor around which it is placed. To this end, it has a layer of abradable material cooperating by abrasion with wipers formed outside the rotor. In operation, the wipers come close to the abradable, possibly creating circular notches there, so that a dynamic seal is ensured.

Le document EP 2 075 414 A1 divulgue un compresseur de turbomachine axiale comprenant des redresseurs munis de viroles internes segmentées. Chaque virole interne comprend une paroi tubulaire dans laquelle sont prévues des rangées d'ouvertures. Ces dernières permettent l'introduction des pieds d'aubes servant à la fixation entre la virole et les aubes. Chaque ouverture présente une lèvre qui en prolonge radialement le contour, des nervures joignent les lèvres des ouvertures voisines, l'ensemble permettant de rigidifier la virole. Cependant, la rigidité en flexion de la virole ; en particulier de ses segments reste limitée. En cas de sollicitation, l'essentiel des efforts est repris par les branches de la forme de U de la virole. En cas de vibrations, les ajours peuvent s'ouvrir d'avantage autour des joints entourant les aubes, ce qui dégrade l'étanchéité.The document EP 2,075,414 A1 discloses an axial turbomachine compressor comprising rectifiers provided with segmented internal ferrules. Each internal ferrule comprises a tubular wall in which are provided rows of openings. These allow the introduction of the blade roots used for fixing between the ferrule and the blades. Each opening has a lip which extends radially around it, ribs join the lips of the neighboring openings, the assembly making it possible to stiffen the ferrule. However, the bending stiffness of the shell; in particular of its segments remains limited. In the event of stress, the main efforts are taken up by the branches of the U shape of the ferrule. In the event of vibrations, the openings can open further around the seals surrounding the blades, which degrades the seal.

Le document EP1419849A1 divulgue un procédé de réparation d'un segment de turbine. Le segment comprend une paire d'aubes dont les extrémités sont liées à une virole interne. Cette dernière présente deux ouvertures liées aux aubes, les bords opposés des ouvertures étant joints par une bride.The document EP1419849A1 discloses a method of repairing a turbine segment. The segment comprises a pair of blades, the ends of which are linked to an internal ferrule. The latter has two openings linked to the blades, the opposite edges of the openings being joined by a flange.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'améliorer l'étanchéité d'une virole ou d'un segment de virole. L'invention a également pour objectif d'améliorer la rigidité d'un assemblage comportant une virole et des aubes liées dans des ouvertures formées dans la virole. L'invention a également pour objectif de rigidifier une virole interne ou un segment de virole interne lié(e) à des aubes statoriques.The invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the sealing of a ferrule or a segment of a ferrule. The invention also aims to improve the rigidity of an assembly comprising a ferrule and vanes linked in openings formed in the ferrule. Another object of the invention is to stiffen an internal ferrule or an internal ferrule segment linked to stator vanes.

Solution techniqueTechnical solution

L'invention a pour objet une turbomachine comprenant un rotor et une virole interne autour du rotor ou un segment de virole interne épousant le rotor, la virole ou le segment de virole comprenant une paroi circulaire ou semi-circulaire dont le profil s'étend principalement axialement, et une bride radiale circulaire ou semi circulaire s'étendent radialement depuis la paroi vers l'intérieur, la bride présentant une surface circulaire ou semi-circulaire dont le profil s'étend principalement radialement, ladite surface présentant des aspérités. Le rotor comporte des nervures annulaires coopérant de manière étanche avec la virole ou le segment de virole, les nervures annulaires du rotor sont chacune à distance axialement de chaque bride radiale de la virole ou du segment de virole. Par ailleurs au moins une ou chaque bride radiale comprend des aspérités qui sont formées sur la majorité de la hauteur radiale du profil de révolution d'une des nervures annulaires du rotor disposée en regard de la bride radiale associée.The subject of the invention is a turbomachine comprising a rotor and an internal ferrule around the rotor or an internal ferrule segment matching the rotor, the ferrule or the ferrule segment comprising a circular or semi-circular wall whose profile mainly extends axially, and a circular or semi-circular radial flange extend radially from the wall towards the inside, the flange having a circular or semi-circular surface whose profile extends mainly radially, said surface having asperities. The rotor has annular ribs cooperating sealingly with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced from each radial flange of the ferrule or the ferrule segment. Furthermore, at least one or each radial flange comprises asperities which are formed over the majority of the radial height of the profile of revolution of one of the annular ribs of the rotor disposed opposite the associated radial flange.

Selon un mode avantageux de l'invention, au moins une ou chaque bride radiale comprend au moins une surface avec des aspérités, ladite surface étant généralement perpendiculaire à l'axe de révolution de la virole ou du segment de virole.According to an advantageous embodiment of the invention, at least one or each radial flange comprises at least one surface with asperities, said surface being generally perpendicular to the axis of revolution of the ferrule or of the ferrule segment.

Selon un mode avantageux de l'invention, les aspérités forment un motif répété sur sensiblement toute une face de la bride radiale correspondante.According to an advantageous embodiment of the invention, the asperities form a pattern repeated on substantially an entire face of the corresponding radial flange.

D'autres aspects de l'invention sont indiqués dans les revendications 4 à 9.Other aspects of the invention are indicated in claims 4 to 9.

Avantages apportésBenefits

La bride radiale permet de former un pont qui enjambe chaque ouverture. La bride permet ainsi de lier les bords opposés des ouvertures de manière à en relier les bords. Ce joint mécanique permet de lier les bords opposés au travers de chaque ouverture, de sorte à éviter qu'ils ne s'écartent ou se rapprochent malgré le vide de matière des ouvertures.The radial flange makes it possible to form a bridge which spans each opening. The flange thus makes it possible to link the opposite edges of the openings so as to connect the edges. This mechanical seal makes it possible to link the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the material vacuum of the openings.

En parallèle, l'invention permet d'améliorer l'étanchéité entre une virole ou un segment de virole avec des ouvertures dans lesquelles sont fixées des aubes statoriques. L'invention offre ainsi une virole ou un segment de virole à la fois léger, rigide, et économe à réaliser.In parallel, the invention makes it possible to improve the seal between a ferrule or a segment of a ferrule with openings in which stator vanes are fixed. The invention thus provides a ferrule or a segment of ferrule which is both light, rigid, and economical to produce.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.
  • La figure 3 illustre une portion de compresseur selon l'invention.The figure 3 illustrates a portion of compressor according to the invention.
  • La figure 4 ébauche une coupe de la portion de compresseur selon l'axe 4-4 tracé sur la figure 3 selon l'invention.The figure 4 sketch a section of the compressor portion along axis 4-4 traced on the figure 3 according to the invention.
  • La figure 5 esquisse une coupe de la portion de compresseur selon l'axe 5-5 tracé sur la figure 3 selon l'invention.The figure 5 sketch a section of the compressor portion along axis 5-5 plotted on the figure 3 according to the invention.
  • La figure 6 est un diagramme du procédé d'assemblage d'une aube statorique à une virole interne ou à un segment de virole interne selon l'invention.The figure 6 is a diagram of the method of assembling a stator vane to an internal ferrule or to an internal ferrule segment according to the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes intérieur ou interne et extérieur ou externe renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction latérale est selon la circonférence.In the following description, the terms internal or internal and external or external refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The lateral direction is according to the circumference.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 5, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 5 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stators. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8. Des moyens de démultiplication peuvent augmenter la vitesse de rotation transmise aux compresseurs.The figure 1 represents in a simplified manner an axial turbomachine. In this specific case, it is a double-flow turbojet engine. The turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 5, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8. Reduction means can increase the speed of rotation transmitted to the compressors.

Un ventilateur d'entrée communément désigné fan ou soufflante 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine. Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes et externes.An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the outlet of the turbine. The secondary flow can be accelerated so as to generate a thrust reaction. The primary 18 and secondary 20 flows are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical or ferrule walls which can be internal and external.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 5. Le rotor 12 comprend un tambour avec une paroi annulaire externe qui supporte plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois rangées.The figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 . The compressor can be a low-pressure compressor 5. The rotor 12 comprises a drum with an external annular wall which supports several rows of rotor blades 24, in this case three rows.

Le compresseur basse-pression 5 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés à la soufflante ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression statique.The low-pressure compressor 5 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26. The rectifiers are associated with the fan or with a row of rotor vanes to straighten the air flow, so as to convert the velocity of the flow into static pressure.

Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter extérieur 22, et peuvent y être fixées à l'aide d'un axe. Le carter 22 forme alors un support externe pour les différentes rangées. Le compresseur 5 comprend également des viroles internes 28 qui sont fixées aux extrémités radialement internes des aubes statoriques 26. Les viroles internes 28 permettent de guider et de délimiter le flux primaire 18. Elles assurent également une étanchéité avec le rotor 12 pour éviter une recirculation d'air diminuant le taux de compression du compresseur 5, et limitant le rendement de la turbomachine. Chaque virole 28 peut former une bague d'un tour, ou être segmentée angulairement.The stator vanes 26 extend essentially radially from an external casing 22, and can be fixed to it using a pin. The casing 22 then forms an external support for the different rows. The compressor 5 also includes internal ferrules 28 which are fixed to the radially internal ends of the stator vanes 26. The internal ferrules 28 make it possible to guide and delimit the primary flow 18. They also provide a seal with the rotor 12 to avoid recirculation d air reducing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine. Each ferrule 28 can form a ring of a turn, or be segmented angularly.

La figure 3 représente une portion du compresseur tel que celui de la figure 2. Y est visible une portion de rotor12, une extrémité radiale 30 interne d'aube statorique 26, et une virole interne 28 qui y est fixée. La virole interne 28 pourrait être segmentée.The figure 3 represents a portion of the compressor such as that of the figure 2 . There is visible a portion of the rotor 12, an internal radial end 30 of the stator vane 26, and an internal ferrule 28 which is fixed to it. The internal ferrule 28 could be segmented.

La virole 28 présente un profil de révolution avec une portion s'étendant principalement axialement et qui génère une paroi axiale 32. La paroi axiale 32 peut être généralement tubulaire, et être sensiblement inclinée par rapport à l'axe de rotation 14 de la turbomachine ; ce dernier peut coïncider avec l'axe de symétrie 14 générale de la virole 28.The ferrule 28 has a profile of revolution with a portion extending mainly axially and which generates an axial wall 32. The axial wall 32 may be generally tubular, and be substantially inclined relative to the axis of rotation 14 of the turbomachine; the latter may coincide with the general axis of symmetry 14 of the shell 28.

La virole 28 présente une série d'ouvertures 34 disposées en une rangée annulaire. Ces ouvertures 34 sont traversées par les extrémités 30 des aubes 26 pour y suspendre la virole 28. Chaque ouverture 34 présente des bords opposés 36 selon la direction de la rangée d'ouvertures 34, ces bords 36 étant placés en regard des faces de l'aube 26 associée. L'un est en regard de la surface intrados de l'aube, l'autre en regard de la face extrados. Les bords 36 peuvent être généralement des conjugués ; l'un est concave, l'autre convexe.The ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are crossed by the ends 30 of the vanes 26 to suspend the ferrule 28 there. Each opening 34 has opposite edges 36 in the direction of the row of openings 34, these edges 36 being placed opposite the faces of the associated dawn 26. One is facing the lower surface of the dawn, the other facing the upper surface. The edges 36 can generally be conjugates; one is concave, the other convex.

La virole 28 comprend en outre au moins une bride radiale 38 qui s'étend radialement vers l'intérieur depuis la paroi axiale 32. La virole 28 peut comprendre plusieurs brides radiales 38 qui coupent chacune les ouvertures 34. Ces brides radiales peuvent être parallèles, et réparties axialement au travers des ouvertures.The ferrule 28 further comprises at least one radial flange 38 which extends radially inwards from the axial wall 32. The ferrule 28 may comprise several radial flanges 38 which each cut the openings 34. These radial flanges may be parallel, and distributed axially through the openings.

La virole 28 peut comprendre au moins trois brides radiales dont une bride radiale amont 40, une bride radiale aval 42, et une bride radiale traversante 38 qui traverse les ouvertures 34, ou bride radiale centrale 38. La bride radiale traversante 38 est disposée axialement entre les brides amont 40 et aval 42. La virole peut présenter un profil en « E » ou en peigne.The ferrule 28 may comprise at least three radial flanges, including an upstream radial flange 40, a downstream radial flange 42, and a through radial flange 38 which passes through the openings 34, or central radial flange 38. The through radial flange 38 is disposed axially between the upstream 40 and downstream 42 flanges. The ferrule may have an “E” or comb profile.

Le rotor 12, en particulier sa paroi présente des nervures annulaires 44, encore appelées « léchettes ». Elles s'étendent radialement et coopèrent avec la virole 28 de manière étanche. Elles peuvent coopérer par abrasion avec des couches de matériau abradable 46 où elles creusent des sillons en cas de contact. Par matériau abradable on entend un matériau friable en cas de contact. Les couches d'abradable 46 peuvent être appliquées sur les extrémités d'aubes 30, et/ou sur la paroi axiale 32. Les couches d'abradable 46 et les brides radiales (38 ; 40 ; 42) forment une alternance.The rotor 12, in particular its wall has annular ribs 44, also called "wipers". They extend radially and cooperate with the shell 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in the event of contact. By abradable material is meant a friable material in the event of contact. The abradable layers 46 can be applied to the ends of the blades 30, and / or to the axial wall 32. The abradable layers 46 and the radial flanges (38; 40; 42) form an alternation.

Les brides radiales (38 ; 40 ; 42) peuvent être associées par paires pour encadrer chaque nervure annulaire 44 de rotor 12, éventuellement individuellement. Chaque bride radiale (38 ; 40 ; 42) comprend un profil de révolution qui s'étend essentiellement radialement, chaque profil de bride s'étend sur la majorité de la hauteur radiale de chaque profil de la bride radiale voisine. Chaque profil de nervure (38 ; 40 ; 42) s'étend sur la majorité de la hauteur radiale des profils des nervures annulaires 44 voisines.The radial flanges (38; 40; 42) can be combined in pairs to frame each annular rib 44 of rotor 12, possibly individually. Each radial flange (38; 40; 42) comprises a profile of revolution which extends essentially radially, each flange profile extends over the majority of the radial height of each profile of the flange neighboring radial. Each rib profile (38; 40; 42) extends over the majority of the radial height of the profiles of the adjacent annular ribs 44.

Pour améliorer l'étanchéité dynamique de la turbomachine, les faces de brides radiales (38 ; 40 ; 42) en regard de nervures annulaires 44 sont recouvertes d'aspérités 48 qui amplifient les turbulences 50, ou tourbillons 50 s'opposant aux recirculations 52.To improve the dynamic sealing of the turbomachine, the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with roughness 48 which amplifies turbulence 50, or vortices 50 opposing recirculations 52.

La figure 4 représente une coupe de la virole 28 et des aubes statoriques 26 selon l'axe 4-4 tracé sur la figure 3. Le plan de coupe passe par la bride radiale 38 qui traverse les ouvertures 34. La virole pourrait être formée par des segments de virole qui seraient mis bout à bout de sorte à former un cercle.The figure 4 represents a section of the ferrule 28 and the stator vanes 26 along the axis 4-4 traced on the figure 3 . The cutting plane passes through the radial flange 38 which crosses the openings 34. The ferrule could be formed by segments of ferrule which would be placed end to end so as to form a circle.

Les aubes 26 s'étendent radialement depuis la virole 28 et traversent les ouvertures 34. Leurs extrémités radiales 30 sont en butée radiale contre la bride radiale 38. Chaque extrémité 30 d'aube présente une surface de butée radiale qui coopère avec une surface de butée correspondante de créneau. Des joints d'étanchéité 54 s'étendent radialement dans les ouvertures 34 et les traversent, ils viennent en contact de la bride radiale 38. Les fonds d'encoches, ou surfaces de butée des encoches sont à distance des joints 54 et/ou de la paroi axiale.The blades 26 extend radially from the ferrule 28 and pass through the openings 34. Their radial ends 30 are in radial abutment against the radial flange 38. Each blade end 30 has a radial abutment surface which cooperates with a abutment surface niche correspondent. Seals 54 extend radially into the openings 34 and pass through them, they come into contact with the radial flange 38. The bottoms of notches, or abutment surfaces of the notches, are spaced from the seals 54 and / or the axial wall.

La bride radiale 38 joint non seulement toutes les ouvertures 34, mais elle en relie également tous les bords opposés 36 les uns aux autres en franchissant les ouvertures 34. Elle forme une barre de renfort qui, dans chaque ouverture 34, bloque les bords opposés 36. La bride radiale 38 présente une forme arquée, et un profil en créneaux. Elle comporte une série de marche formant des encoches 56 dans lesquelles sont placées les extrémités 30 d'aubes 26. Ces encoches 56 peuvent être un lieu de fixation des aubes 26, par exemple par collage ou à l'aide de plaquettes de fixation (non représentées). A cet effet, les extrémités 30 peuvent comprendre des orifices de fixation (non représentés). Au sein de chaque ouverture 34 la bride radiale 38 lie les bords opposés 36. Cette configuration rigidifie la virole 28, et évite sa flexion au niveau des ouvertures, 38 si bien que le risque de décollement au niveau des joints 54 s'amenuise.The radial flange 38 not only joins all the openings 34, but also connects all the opposite edges 36 to each other by crossing the openings 34. It forms a reinforcing bar which, in each opening 34, blocks the opposite edges 36 The radial flange 38 has an arcuate shape and a notched profile. It comprises a series of steps forming notches 56 in which the ends 30 of the blades 30 are placed. These notches 56 can be a place for fixing the blades 26, for example by gluing or using fixing plates (not shown). To this end, the ends 30 may include fixing orifices (not shown). Within each opening 34, the radial flange 38 links the opposite edges 36. This configuration stiffens the ferrule 28, and prevents it from bending at the openings, 38 so that the risk of detachment at the joints 54 is reduced.

La figure 5 représente une coupe selon l'axe 5-5 tracé sur la figure 3. La coupe montre une tranche de compresseur entre le rotor 12 et une virole interne, vus depuis l'extérieur. L'emplacement des extrémités 30 d'aubes est représenté.The figure 5 represents a section along axis 5-5 drawn on the figure 3 . The section shows a compressor section between the rotor 12 and an internal shroud, seen from the outside. The location of the blade ends 30 is shown.

Les aspérités 48 comprennent des sillons et des crêtes formant une alternance avec les sillons, Ils s'étendant radialement et sont éventuellement perpendiculaires à l'axe de rotation de la turbomachine. L'ensemble peut former une surface annulaire striée. Les aspérités 48 peuvent avoir des formes de dents triangulaires, et présenter un profil général en dents de scie.The asperities 48 comprise grooves and ridges alternating with the grooves, They extend radially and are optionally perpendicular to the axis of rotation of the turbomachine. The assembly can form a striated annular surface. The asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.

Les aspéritées 48 sont formées en face des léchettes 44, préférentiellement de chaque côté. Le motif peut être formé tout le long, suivant la circonférence, des brides radiales (38 ; 40 ; 42) ; ou sur tout le tour. Grâce aux aspérités 48, les brides radiales (38 ; 40 ; 42) provoquent des tourbillons 50 dans l'air entraîné par le rotor 12The asperities 48 are formed opposite the wipers 44, preferably on each side. The pattern can be formed along, along the circumference, radial flanges (38; 40; 42); or all around. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air entrained by the rotor 12

La figure 6 représente un diagramme d'un procédé d'assemblage d'une aube de stator sur une virole, la virole pouvant être segmentée.The figure 6 shows a diagram of a method of assembling a stator vane on a ferrule, the ferrule being able to be segmented.

Le procédé peut comprendre les étapes suivantes, éventuellement effectuées dans l'ordre présenté ci-dessous :

  1. (a) fourniture d'une ou plusieurs aubes statoriques 100, chaque aube statorique comportant une extrémité radiale interne, optionnellement avec des moyens de fixation ;
  2. (b) fourniture d'une virole interne ou d'un segment de virole interne 102 comprenant une rangée d'ouvertures et une bride radiale circulaire ou semi-circulaire traversant les ouvertures en les franchissant de bord à bord ;
  3. (c) positionnement 104 de chaque extrémité d'aube statorique dans une ouverture en mettant en butée chaque extrémité d'aube contre la bride radiale ;
  4. (d) fixation 106 de chaque extrémité d'aube dans l'ouverture associée ;
  5. (e) mise en œuvre ou réalisation 108 de joints d'étanchéité dans les ouvertures autour des aubes statoriques, de sorte à permettre une étanchéité entre la virole et les aubes statoriques.
The process can include the following stages, possibly carried out in the order presented below:
  1. (a) supply of one or more stator vanes 100, each stator vane having an internal radial end, optionally with fixing means;
  2. (b) providing an internal ferrule or an internal ferrule segment 102 comprising a row of openings and a circular or semicircular radial flange passing through the openings crossing them from edge to edge;
  3. (c) positioning 104 of each end of the stator vane in an opening by abutting each end of the vane against the radial flange;
  4. (d) fixing 106 of each blade tip in the associated opening;
  5. (E) implementation or realization 108 of seals in the openings around the stator vanes, so as to allow a seal between the ferrule and the stator vanes.

L'étape (b) fourniture 102, peut comprendre la fabrication additive de la virole ou du segment de virole. La virole ou chaque segment peut être venu(e) de mantière et être réalisée en polymère, par exemple en un martériau composite avec des fibres, éventuellement de longueur inférieure à 10 mm.Step (b) supply 102, can comprise additive manufacturing of the shell or of the shell segment. The ferrule or each segment may have come from a mantle and be made of polymer, for example a composite martial material with fibers, possibly of length less than 10 mm.

L'étape (c) positionnement 104 peut s'effectuer en fixant les aubes à un carter externe de compresseur. Puis la virole est rapprochée radialement de sorte à ce que les extrémités internes des aubes se retrouvent dans les ouvertures. Dans un premier temps, les extrémités d'aubes rentrent dans les ouvertures, puis les traversent. Enfin, ces extrémités viennent en butée contre une bride radiale. La butée est alors axiale et/ou radiale, ce qui permet d'améliorer la positon relative entre l'aube et la virole. Ainsi, le joint réalisé ou mis en œuvre lors de l'étape (e) mise en œuvre ou réalisation 108 est mieux positionné et/ou mieux réalisé.Positioning step (c) 104 can be carried out by fixing the blades to an external compressor casing. Then the ferrule is brought together radially so that the internal ends of the blades are found in the openings. Initially, the blade tips enter the openings, then pass through them. Finally, these ends abut against a radial flange. The stop is then axial and / or radial, which makes it possible to improve the relative position between the blade and the shell. Thus, the joint produced or implemented during step (e) implementation or production 108 is better positioned and / or better produced.

Claims (9)

  1. Turbomachine (2) comprising a rotor (12) and an internal shroud (28) around the rotor (12) or a segment of an internal shroud adopting the form of the rotor (12), the shroud (28) or the segment of a shroud comprising:
    - a circular or semi-circular wall (32), of which the profile extends essentially axially, and
    - at least one circular or semi-circular radial flange (38, 40, 42) extending radially from the interior of the wall (32)
    characterized in that
    the or each flange (38, 40, 42) has at least one circular or semi-circular surface, the profile of which extends substantially radially, said surface having areas of roughness (48),
    in that the rotor (12) comprises annular ribs (44) interacting in a sealed manner with the shroud (28) or the segment of a shroud, the annular ribs (44) of the rotor (12) each being located at a distance axially from each radial flange (38; 40; 42) of the shroud (28) or of the segment of a shroud,
    and in that the areas of roughness (48) are formed on more than half of the radial height of the profile of one of the annular ribs (44) of the rotor (12) facing the associated radial flange (38; 40; 42).
  2. Turbomachine (2) according to claim 1, characterized in that said surface of the flange (38; 40; 42) with areas of roughness (48) is generally perpendicular to the axis of revolution of the shroud (28) or of the segment of a shroud.
  3. Turbomachine (2) according to claim 1 or 2, characterized in that said areas of roughness (48) form a pattern that is repeated on substantially the entire face of the corresponding radial flange (38; 40; 42).
  4. Turbomachine (2) according to any of claims 1 to 3, characterized in that the areas of roughness (48) comprises furrows and ridges, said ridges alternating with furrows and extending radially.
  5. Turbomachine (2) according to claim 4, characterized in that the furrows and the ridges are perpendicular to the axis of revolution (14) of the turbomachine (2).
  6. Turbomachine (2) according to any of claims 4 or 5, characterized in that the entirety of the furrows and ridges forms a annular and serrated surface.
  7. Turbomachine (2) according to any of claims 1 to 3, characterized in that the areas of roughness (48) exhibit the form of teeth, possibly triangular, each tooth extending over more than half of, or all of, the radial height of the associated radial flange (38; 40; 42).
  8. Turbomachine (2) according to any of claims 1 to 7, characterized in that the areas of roughness (48) are formed opposite the annular ribs (44), preferably on each side.
  9. Turbomachine (2) according to any of claims 1 to 8, characterized in that the pattern of the areas of roughness (48) is formed circumferentially over the entirety of the radial flanges (38; 40; 42); or on the entire circle of flanges (38; 40; 42).
EP18159641.2A 2014-11-18 2015-10-22 Internal ferrule of an axial turbine-engine compressor Active EP3351736B1 (en)

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BE2014/0820A BE1022513B1 (en) 2014-11-18 2014-11-18 INTERNAL COMPRESSOR OF AXIAL TURBOMACHINE COMPRESSOR
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Also Published As

Publication number Publication date
EP3023595A1 (en) 2016-05-25
CA2909256A1 (en) 2016-05-18
EP3023595B1 (en) 2018-04-18
CN105604612A (en) 2016-05-25
RU2015146074A (en) 2017-05-16
CN105604612B (en) 2018-08-28
EP3351736A1 (en) 2018-07-25
BE1022513B1 (en) 2016-05-19
RU2719521C2 (en) 2020-04-21
US20160138413A1 (en) 2016-05-19
RU2015146074A3 (en) 2019-05-20
US10113439B2 (en) 2018-10-30

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