EP3023595A1 - 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
EP3023595A1
EP3023595A1 EP15190957.9A EP15190957A EP3023595A1 EP 3023595 A1 EP3023595 A1 EP 3023595A1 EP 15190957 A EP15190957 A EP 15190957A EP 3023595 A1 EP3023595 A1 EP 3023595A1
Authority
EP
European Patent Office
Prior art keywords
ferrule
segment
radial
radial flange
openings
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15190957.9A
Other languages
German (de)
French (fr)
Other versions
EP3023595B1 (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
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP18159641.2A priority Critical patent/EP3351736B1/en
Publication of EP3023595A1 publication Critical patent/EP3023595A1/en
Application granted granted Critical
Publication of EP3023595B1 publication Critical patent/EP3023595B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 inner ferrules connected to a row of stator vanes.
  • An inner ferrule is known for delimiting the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid vein. Thanks to its external surface, it helps to guide the flow during its expansion in a turbine, or its compression in a compressor.
  • an inner ring may be mounted on inner ends of blades arranged in an annular row, themselves linked to an outer casing.
  • the ferrule has recesses for the introduction of ferrule attachment ends.
  • the inner ferrule is also intended to provide a seal with the rotor around which it is placed.
  • 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 cuts, so that a dynamic seal is ensured.
  • the document EP 2 075 414 A1 discloses an axial turbomachine compressor comprising rectifiers provided with segmented internal ferrules.
  • Each inner ferrule comprises a tubular wall in which rows of openings are provided. These allow the introduction of the blade roots used for fixing between the ferrule and the blades.
  • Each opening has a lip which radially extends the contour, ribs join the lips of the adjacent openings, the assembly for stiffening the ferrule.
  • the flexural stiffness of the ferrule; especially of its segments remains limited. In case of solicitation, most of the effort is taken up by the branches of the U-shape of the ferrule. In case of vibrations, the openings can open more around the joints 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 whose ends are connected to an inner shell.
  • the latter has two openings connected to the blades, the opposite edges of the openings being joined by a flange.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the object of the invention is to stiffen an inner ferrule or an inner ferrule segment bonded to stator vanes.
  • the invention also aims to improve the rigidity of an assembly comprising a ferrule and blades connected in openings formed in the ferrule.
  • the invention also aims to improve the sealing of a ferrule or a ferrule segment.
  • the subject of the invention is a ferrule or an axial turbomachine shell segment, in particular a compressor, the ferrule or the ferrule segment comprises a circular or semi-circular wall whose profile extends mainly axially, and a circular radial flange. or semi-circular extend radially from the wall towards the inside, the flange having a circular or semicircular surface whose profile extends mainly radially, said surface having asperities.
  • the subject of the invention is also an internal ferrule or inner ring segment of an axial turbomachine, in particular a compressor, the ferrule or the ferrule segment comprising: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall, each opening having opposing edges to be laterally arranged on the side and another of a stator blade positioned in said opening for attachment; remarkable in that the wall comprises at least one radial flange which passes through the apertures in the circumferential direction of the shell or ferrule segment, so as to form a mechanical link within each opening to bond the opposite edges.
  • each opening extends mainly axially and each radial flange extends radially inwards from the wall, and travels all around the ferrule or the entire width of the ferrule segment according to the direction of alignment of the row of openings.
  • the ferrule or the ferrule segment comprises at least one band of abradable material, each radial flange extending more radially inwards than each abradable layer.
  • the ferrule or the ferrule segment comprises a plurality of radial flanges which each pass through the openings, possibly each abradable strip is disposed axially between two radial flanges.
  • the axial wall and each radial flange are integral, optionally the axial wall and each radial flange are made of polymer, such as an organic matrix composite material.
  • the radial flange is a through radial flange which passes through the openings, the ferrule or ferrule segment comprising an upstream radial flange disposed upstream of the openings, and a downstream radial flange disposed downstream of the openings.
  • the upstream flange and the downstream flange axially delimit the axial wall.
  • 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 ferrule segment.
  • the asperities form a repeated pattern on substantially an entire face of the corresponding radial flange.
  • the asperities have tooth shapes, possibly triangular, each tooth extends over the majority or over the entire radial height of the associated radial flange.
  • the radial flange comprises portions which each bar an opening, possibly in the direction of alignment of the row of openings.
  • the radial height of at least one or each radial flange is greater than the radial height of each annular rib.
  • At least one or each opening extends over the majority of the axial length of the axial wall.
  • the wall comprises a radial flange disposed at the axial center of the openings, or the wall comprises a plurality of radial flanges distributed axially on the openings.
  • the invention also relates to a method of assembling a stator blade to an inner ferrule or to an inner ring segment of an axial turbomachine, the method comprising the following steps: (a) supplying one or more blades statoric, each stator blade having an inner radial end; (b) providing an inner ferrule or inner ferrule segment with a row of openings; (c) positioning each stator blade end in an opening; (d) attaching each blade tip to the associated opening; remarkable in that the ferrule or the ferrule segment comprises at least one circular or semicircular radial flange passing through the openings, and in that during step (c) positioning each end of blade is in abutment against the flange radial, optionally the inner ferrule or the inner ring segment is in accordance with the invention.
  • each blade end passes through the associated opening.
  • each blade end comes into axial abutment and / or radial abutment against the radial flange, optionally each blade end comprises fastening means .
  • the step (b) supply comprises the realization by additive manufacture of the ferrule or the ferrule segment.
  • the method further comprises a step (e) implementation or realization of seals in the openings around the stator vanes.
  • the invention also relates to a turbomachine comprising a rotor and an inner ring around the rotor or an inner ferrule segment conforming to the rotor, remarkable in that the ferrule or the ferrule segment is in accordance with the invention; and / or the turbomachine comprises a stator blade and an inner ferrule or an inner ferrule segment assembled according to an assembly method, remarkable in that the method is in accordance with the invention.
  • the rotor comprises annular ribs sealingly cooperating with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced apart from each radial flange of the ferrule or ferrule segment.
  • At least one radial flange covers radially and circularly one of the annular ribs.
  • At least one or each radial flange comprises asperities which are formed over the majority of the radial height of the revolution profile of one of the annular ribs of the rotor disposed opposite the associated radial flange.
  • the radial clearance between each radial flange and the rotor is greater than the radial clearance between the annular ribs and the ferrule or the ferrule segment.
  • the rotor comprises N annular ribs, the ferrule or the ferrule segment comprising at least N + 1 radial flanges, preferably at least 2 * N radial flanges forming N pairs of radial flanges adjoining the upstream and downstream surfaces of each annular rib.
  • each opening comprises a seal intended to surround a stator vane disposed in said opening, the seal being in contact with the radial flange which passes through said opening, preferably the seal is made in an elastomeric material such as silicone.
  • At least one or each stator blade comprises a radial step form in axial abutment and / or in radial abutment against one or one of the radial flanges.
  • At least one or each stator blade comprises a notch in which is engaged one or one of the radial flanges of the ferrule, and / or one or one of the radial flanges comprises notches in which are engaged the stator blades.
  • At least one or each stator blade comprises fixing means such as radial retention means.
  • the annular ribs of the rotor and the radial flanges of the inner ring form an alternation.
  • each radial flange has a profile of revolution which extends essentially radially, and the annular ribs each comprise a profile of revolution which extends essentially radially, each flange profile extends over the most of the radial height of each neighboring annular rib profile.
  • the radial flange forms a bridge that spans each opening.
  • the flange thus makes it possible to bind the opposite edges of the openings so as to connect the edges.
  • This mechanical seal makes it possible to bind the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the void of material openings.
  • the invention makes it possible to improve the seal between a ferrule or a ferrule segment with openings in which stator vanes are fixed.
  • the invention thus provides a ferrule or a ferrule segment that is light, rigid and economical to produce.
  • inner or inner and outer or outer 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 simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 5, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power 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 vanes. Rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow rate and to compress it gradually to the inlet of the combustion chamber 8. Reducing means can increase the rotational speed transmitted to the compressors.
  • An inlet fan commonly referred to as a fan or fan 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned 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 turbine outlet.
  • the secondary flow can be accelerated to generate a thrust reaction.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules 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 may be a low-pressure compressor 5.
  • the rotor 12 comprises a drum with an outer 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, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan or with a row of rotor vanes for straightening the flow of air, so as to convert the speed of the flow into static pressure.
  • the stator vanes 26 extend substantially radially from an outer casing 22, and can be attached thereto by means of an axis.
  • the housing 22 then forms an external support for the different rows.
  • the compressor 5 also comprises internal ferrules 28 which are fixed to the radially inner ends of the stator vanes 26.
  • the inner ferrules 28 serve to guide and delimit the primary flux 18. They also seal with the rotor 12 to avoid recirculation of the air decreasing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine.
  • Each ferrule 28 may form a ring of one turn, or be segmented angularly.
  • the figure 3 represents a portion of the compressor such as that of the figure 2 .
  • Y is visible a rotor portion 12, an inner radial end of stator vane 26, and an inner ferrule 28 attached thereto.
  • the inner ferrule 28 could be segmented.
  • the shell 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 ferrule 28.
  • the ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are traversed by the ends 30 of the blades 26 to suspend the ferrule 28. 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 dawn 26 associated. One is facing the intrados surface of the dawn, the other facing the extrados face. Edges 36 may be generally conjugates; one is concave, the other convex.
  • the ferrule 28 further comprises at least one radial flange 38 which extends radially inwardly from the axial wall 32.
  • the ferrule 28 may comprise a plurality of 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 radial flange 38 is axially disposed 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 ferrule 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in case of contact.
  • abradable material is meant a friable material in case of contact.
  • the abradable layers 46 may be applied to the blade tips 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 associated in pairs to frame each annular rib 44 of rotor 12, possibly individually.
  • Each radial flange (38; 40; 42) comprises a profile of revolution that extends substantially radially, each flange profile extends over most of the radial height of each profile of the neighboring radial flange.
  • Each rib profile (38; 40; 42) extends over most of the radial height of the profiles of neighboring annular ribs 44.
  • the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with asperities 48 which amplify the turbulences 50 or vortices 50 opposing the recirculations 52.
  • the figure 4 represents a section of ferrule 28 and stator vanes 26 along the axis 4-4 plotted on the figure 3 .
  • the cutting plane passes through the radial flange 38 which passes through the openings 34.
  • the ferrule could be formed by ferrule segments which would be placed end to end so as to form a circle.
  • the blades 26 extend radially from the shell 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 an abutment surface. corresponding slot. Seals 54 extend radially into openings 34 and pass through them, they come into contact with radial flange 38. Notch bottoms, or abutment surfaces of notches, are spaced apart from joints 54 and / or the axial wall.
  • the radial flange 38 not only joins all the openings 34, but it also connects all the opposite edges 36 to each other through the openings 34. It forms a reinforcement bar which, in each opening 34, blocks the opposite edges 36
  • the radial flange 38 has an arcuate shape and a crenellated profile. It has a step series forming notches 56 in which are placed the ends of the blades 26. These notches 56 may be a place for fixing the blades 26, for example by gluing or with the aid of fixing plates (not shown). For this purpose, the ends 30 may comprise fixing holes (not shown). Within each opening 34 the radial flange 38 binds the opposite edges 36. This configuration stiffens the ferrule 28, and prevents its bending at the openings, 38 so that the risk of separation at the joints 54 decreases.
  • the figure 5 represents a section along the axis 5-5 drawn on the figure 3 .
  • the section shows a compressor slice between the rotor 12 and an inner shell, seen from the outside. The location of the blade tips 30 is shown.
  • the asperities 48 comprise grooves and ridges forming an alternation with the grooves, which extend radially and are optionally perpendicular to the axis of rotation of the turbomachine.
  • the assembly can form a ridged annular surface.
  • Asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.
  • Asperities 48 are formed in front of wipers 44, preferably on each side.
  • the pattern may be formed circumferentially along radial flanges (38; 40; 42); or all the way round. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air driven by the rotor 12
  • the figure 6 is a diagram of a method of assembling a stator vane on a ferrule, the ferrule being segmentable.
  • Step (b) supply 102 may include the additive manufacture of the ferrule or ferrule segment.
  • the ferrule or each segment can be rimmed and made of polymer, for example a composite hammer with fibers, possibly less than 10 mm in length.
  • Step (c) positioning 104 can be performed by fixing the vanes to an outer compressor casing. Then the shell is moved radially so that the inner ends of the blades are found in the openings. At first, the blade tips enter the openings and then pass through them. Finally, these ends abut against a radial flange. The abutment is then axial and / or radial, which makes it possible to improve the relative position between the blade and the ferrule.
  • the seal made or implemented during step (e) implementation or embodiment 108 is better positioned and / or better achieved.

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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)

Abstract

L'invention a trait à une virole interne (28) segmentée de compresseur basse pression de turbomachine axiale. La virole comprend : une paroi tubulaire axiale (32), et une rangée d'ouvertures (34) formées dans la paroi axiale (32). Chaque ouverture (34) présente des bords opposés (36) placés de part et d'autre d'une aube statorique (26) positionnée dans l'ouverture (34) en vue de sa fixation. La paroi axiale (32) comprend une bride radiale (38) qui traverse les ouvertures (34) selon la direction circonférentielle de la virole (28), de sorte à former un lien mécanique entre les bords opposés (36) des ouvertures. Ce joint mécanique permet de lier les bords opposés (36) au travers de chaque ouverture (34), ce qui améliore la rigidité et l'étanchéité. La virole (28) présente un profil en E formant une alternance avec les nervures annulaires (44) d'étanchéité du rotor (12), ou léchettes. L'invention traite également d'un procédé d'assemblage d'aubes statoriques (26) venant en butée radiale contre la bride radiale traversante (38).The invention relates to a segmented internal shell (28) of axial-turbomachine low-pressure compressor. The ferrule comprises: an axial tubular wall (32), and a row of openings (34) formed in the axial wall (32). Each opening (34) has opposite edges (36) placed on either side of a stator vane (26) positioned in the opening (34) for attachment. The axial wall (32) includes a radial flange (38) which extends through the openings (34) in the circumferential direction of the ferrule (28) so as to form a mechanical link between the opposite edges (36) of the openings. This mechanical seal makes it possible to bond the opposite edges (36) through each opening (34), which improves rigidity and tightness. The shell (28) has an E-shaped profile alternating with the annular ribs (44) sealing the rotor (12) or wipers. The invention also relates to a method of assembling stator vanes (26) abutting radially against the radial flange (38).

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 inner 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 inner ferrule is known for delimiting the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid vein. Thanks to its external surface, it helps to 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 inner ring may be mounted on inner ends of blades arranged in an annular row, themselves linked to an outer casing. The ferrule has recesses for the introduction of ferrule attachment 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 inner ferrule is also intended to provide a seal with the rotor around which it is placed. For this purpose, 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 cuts, 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 inner ferrule comprises a tubular wall in which rows of openings are provided. These allow the introduction of the blade roots used for fixing between the ferrule and the blades. Each opening has a lip which radially extends the contour, ribs join the lips of the adjacent openings, the assembly for stiffening the ferrule. However, the flexural stiffness of the ferrule; especially of its segments remains limited. In case of solicitation, most of the effort is taken up by the branches of the U-shape of the ferrule. In case of vibrations, the openings can open more around the joints 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 whose ends are connected to an inner shell. The latter has two openings connected 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 de rigidifier une virole interne ou un segment de virole interne lié(e) à des aubes statoriques. 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 d'améliorer l'étanchéité d'une virole ou d'un segment de virole.The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the object of the invention is to stiffen an inner ferrule or an inner ferrule segment bonded to stator vanes. The invention also aims to improve the rigidity of an assembly comprising a ferrule and blades connected in openings formed in the ferrule. The invention also aims to improve the sealing of a ferrule or a ferrule segment.

Solution techniqueTechnical solution

L'invention a pour objet une virole ou un segment de virole de turbomachine axiale, notamment de compresseur, la virole ou le segment de virole comprend 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.The subject of the invention is a ferrule or an axial turbomachine shell segment, in particular a compressor, the ferrule or the ferrule segment comprises a circular or semi-circular wall whose profile extends mainly axially, and a circular radial flange. or semi-circular extend radially from the wall towards the inside, the flange having a circular or semicircular surface whose profile extends mainly radially, said surface having asperities.

L'invention a également pour objet une virole interne ou segment de virole interne de turbomachine axiale, notamment de compresseur, la virole ou le segment de virole comprenant : une paroi circulaire ou semi-circulaire dont le profil s'étend principalement axialement ; et une rangée d'ouvertures formées dans la paroi axiale, chaque ouverture présentant des bords opposés destinés à être disposés latéralement de part et d'autre d'une aube statorique positionnée dans ladite ouverture en vue de sa fixation ; remarquable en ce que la paroi comprend au moins une bride radiale qui traverse les ouvertures selon la direction circonférentielle de la virole ou du segment de virole, de sorte à former un lien mécanique au sein de chaque ouverture pour en lier les bords opposés.The subject of the invention is also an internal ferrule or inner ring segment of an axial turbomachine, in particular a compressor, the ferrule or the ferrule segment comprising: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall, each opening having opposing edges to be laterally arranged on the side and another of a stator blade positioned in said opening for attachment; remarkable in that the wall comprises at least one radial flange which passes through the apertures in the circumferential direction of the shell or ferrule segment, so as to form a mechanical link within each opening to bond the opposite edges.

Selon un mode avantageux de l'invention, chaque ouverture s'étend principalement axialement et chaque bride radiale s'étend radialement vers l'intérieur depuis la paroi, et parcourt tout le tour de la virole ou toute la largeur du segment de virole selon la direction de l'alignement de la rangée d'ouvertures.According to an advantageous embodiment of the invention, each opening extends mainly axially and each radial flange extends radially inwards from the wall, and travels all around the ferrule or the entire width of the ferrule segment according to the direction of alignment of the row of openings.

Selon un mode avantageux de l'invention, la virole ou le segment de virole comprend au moins une bande de matériau abradable, chaque bride radiale s'étendant davantage radialement vers l'intérieur que chaque couche d'abradable.According to an advantageous embodiment of the invention, the ferrule or the ferrule segment comprises at least one band of abradable material, each radial flange extending more radially inwards than each abradable layer.

Selon un mode avantageux de l'invention, la virole ou le segment de virole comprend plusieurs brides radiales qui traversent chacune les ouvertures, éventuellement chaque bande d'abradable est disposée axialement entre deux brides radiales.According to an advantageous embodiment of the invention, the ferrule or the ferrule segment comprises a plurality of radial flanges which each pass through the openings, possibly each abradable strip is disposed axially between two radial flanges.

Selon un mode avantageux de l'invention, la paroi axiale et chaque bride radiale sont venues de matière, éventuellement la paroi axiale et chaque bride radiale sont réalisées en polymère, tel un matériau composite à matrice organique.According to an advantageous embodiment of the invention, the axial wall and each radial flange are integral, optionally the axial wall and each radial flange are made of polymer, such as an organic matrix composite material.

Selon un mode avantageux de l'invention, la bride radiale est une bride radiale traversante qui traverse les ouvertures, la virole ou le segment de virole comprenant une bride radiale amont disposée en amont des ouvertures, et une bride radiale aval disposée en aval des ouvertures, préférentiellement la bride amont et la bride aval délimitent axialement la paroi axiale.According to an advantageous embodiment of the invention, the radial flange is a through radial flange which passes through the openings, the ferrule or ferrule segment comprising an upstream radial flange disposed upstream of the openings, and a downstream radial flange disposed downstream of the openings. preferably, the upstream flange and the downstream flange axially delimit the axial wall.

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 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 repeated pattern on substantially an entire face of the corresponding radial flange.

Selon un mode avantageux de l'invention, les aspérités présentent des formes de dents, éventuellement triangulaires, chaque dent s'étend sur la majorité ou sur toute la hauteur radiale de la bride radiale associée.According to an advantageous embodiment of the invention, the asperities have tooth shapes, possibly triangular, each tooth extends over the majority or over the entire radial height of the associated radial flange.

Selon un mode avantageux de l'invention, la bride radiale comprend des portions qui barrent chacune une ouverture, éventuellement selon la direction de l'alignement de la rangée d'ouvertures.According to an advantageous embodiment of the invention, the radial flange comprises portions which each bar an opening, possibly in the direction of alignment of the row of openings.

Selon un mode avantageux de l'invention, la hauteur radiale d'au moins une ou de chaque bride radiale est supérieure à la hauteur radiale de chaque nervure annulaire.According to an advantageous embodiment of the invention, the radial height of at least one or each radial flange is greater than the radial height of each annular rib.

Selon un mode avantageux de l'invention, au moins une ou chaque ouverture s'étend sur la majorité de la longueur axiale de la paroi axiale.According to an advantageous embodiment of the invention, at least one or each opening extends over the majority of the axial length of the axial wall.

Selon un mode avantageux de l'invention, la paroi comprend une bride radiale disposée au centre axialement des ouvertures, ou la paroi comprend plusieurs brides radiales réparties axialement sur les ouvertures.According to an advantageous embodiment of the invention, the wall comprises a radial flange disposed at the axial center of the openings, or the wall comprises a plurality of radial flanges distributed axially on the openings.

L'invention a également pour objet un procédé d'assemblage d'une aube statorique à une virole interne ou à un segment de virole interne de turbomachine axiale, le procédé comprenant les étapes suivantes : (a) fourniture d'une ou de plusieurs aubes statoriques, chaque aube statorique comportant une extrémité radiale interne ; (b) fourniture d'une virole interne ou d'un segment de virole interne avec une rangée d'ouvertures ; (c) positionnement de chaque extrémité d'aube statorique dans une ouverture ; (d) fixation de chaque extrémité d'aube dans l'ouverture associée ; remarquable en ce que la virole ou le segment de virole comprend au moins une bride radiale circulaire ou semi-circulaire traversant les ouvertures, et en ce que lors de l'étape (c) positionnement chaque extrémité d'aube est en butée contre la bride radiale, éventuellement la virole interne ou le segment de virole interne est conforme à l'invention.The invention also relates to a method of assembling a stator blade to an inner ferrule or to an inner ring segment of an axial turbomachine, the method comprising the following steps: (a) supplying one or more blades statoric, each stator blade having an inner radial end; (b) providing an inner ferrule or inner ferrule segment with a row of openings; (c) positioning each stator blade end in an opening; (d) attaching each blade tip to the associated opening; remarkable in that the ferrule or the ferrule segment comprises at least one circular or semicircular radial flange passing through the openings, and in that during step (c) positioning each end of blade is in abutment against the flange radial, optionally the inner ferrule or the inner ring segment is in accordance with the invention.

Selon un mode avantageux de l'invention, lors de l'étape (c) positionnement, chaque extrémité d'aube traverse l'ouverture associée.According to an advantageous embodiment of the invention, during step (c) positioning, each blade end passes through the associated opening.

Selon un mode avantageux de l'invention, lors de l'étape (c) positionnement, chaque extrémité d'aube vient en butée axiale et/ou en butée radiale contre la bride radiale, éventuellement chaque extrémité d' aube comprend des moyens de fixation.According to an advantageous embodiment of the invention, during step (c) positioning, each blade end comes into axial abutment and / or radial abutment against the radial flange, optionally each blade end comprises fastening means .

Selon un mode avantageux de l'invention, l'étape (b) fourniture, comprend la réalisation par fabrication additive de la virole ou du segment de virole.According to an advantageous mode of the invention, the step (b) supply, comprises the realization by additive manufacture of the ferrule or the ferrule segment.

Selon un mode avantageux de l'invention, le procédé comprend en outre une étape (e) mise en oeuvre ou réalisation de joints d'étanchéité dans les ouvertures autour des aubes statoriques.According to an advantageous embodiment of the invention, the method further comprises a step (e) implementation or realization of seals in the openings around the stator vanes.

L'invention a également pour objet une turbomachine comprenant un rotor et une virole interne autour du rotor ou un segment de virole interne épousant le rotor, remarquable en ce que la virole ou le segment de virole est conforme à l'invention ; et/ou la turbomachine comprend une aube statorique et une virole interne ou un segment de virole interne assemblés selon un procédé d'assemblage, remarquable en ce que le procédé est conforme à l'invention.The invention also relates to a turbomachine comprising a rotor and an inner ring around the rotor or an inner ferrule segment conforming to the rotor, remarkable in that the ferrule or the ferrule segment is in accordance with the invention; and / or the turbomachine comprises a stator blade and an inner ferrule or an inner ferrule segment assembled according to an assembly method, remarkable in that the method is in accordance with the invention.

Selon un mode avantageux de l'invention, 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.According to an advantageous embodiment of the invention, the rotor comprises annular ribs sealingly cooperating with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced apart from each radial flange of the ferrule or ferrule segment. .

Selon un mode avantageux de l'invention, au moins une bride radiale recouvre radialement et circulairement l'une des nervures annulaires.According to an advantageous embodiment of the invention, at least one radial flange covers radially and circularly one of the annular ribs.

Selon un mode avantageux de l'invention, 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.According to an advantageous embodiment of the invention, at least one or each radial flange comprises asperities which are formed over the majority of the radial height of the revolution profile of one of the annular ribs of the rotor disposed opposite the associated radial flange.

Selon un mode avantageux de l'invention, le jeu radial entre chaque bride radiale et le rotor est supérieur au jeu radial entre les nervures annulaires et la virole ou le segment de virole.According to an advantageous embodiment of the invention, the radial clearance between each radial flange and the rotor is greater than the radial clearance between the annular ribs and the ferrule or the ferrule segment.

Selon un mode avantageux de l'invention, le rotor comprend N nervures annulaires, la virole ou le segment de virole comprenant au moins N+1 brides radiales, préférentiellement au moins 2*N brides radiales formant N paires de brides radiales qui jouxtent les surfaces amont et aval de chaque nervure annulaire.According to an advantageous embodiment of the invention, the rotor comprises N annular ribs, the ferrule or the ferrule segment comprising at least N + 1 radial flanges, preferably at least 2 * N radial flanges forming N pairs of radial flanges adjoining the upstream and downstream surfaces of each annular rib.

Selon un mode avantageux de l'invention, chaque ouverture comprend un joint d'étanchéité destiné à entourer une aube statorique disposée dans ladite ouverture, le joint d'étanchéité étant en contact de la bride radiale qui traverse ladite ouverture, préférentiellement le joint est réalisé en un matériau élastomère tel du silicone.According to an advantageous embodiment of the invention, each opening comprises a seal intended to surround a stator vane disposed in said opening, the seal being in contact with the radial flange which passes through said opening, preferably the seal is made in an elastomeric material such as silicone.

Selon un mode avantageux de l'invention, au moins une ou chaque aube statorique comprend une forme de marche radiale en butée axiale et/ou en butée radiale contre la ou une des brides radiales.According to an advantageous embodiment of the invention, at least one or each stator blade comprises a radial step form in axial abutment and / or in radial abutment against one or one of the radial flanges.

Selon un mode avantageux de l'invention, au moins une ou chaque aube statorique comprend une encoche dans laquelle est engagée la ou une des brides radiales de la virole, et/ou la ou une des brides radiales comprend des encoches dans lesquelles sont engagées les aubes statoriques.According to an advantageous embodiment of the invention, at least one or each stator blade comprises a notch in which is engaged one or one of the radial flanges of the ferrule, and / or one or one of the radial flanges comprises notches in which are engaged the stator blades.

Selon un mode avantageux de l'invention, au moins une ou chaque aube statorique comprend des moyens de fixation tels des moyens de rétention radiale.According to an advantageous embodiment of the invention, at least one or each stator blade comprises fixing means such as radial retention means.

Selon un mode avantageux de l'invention, les nervures annulaires du rotor et les brides radiales de la virole interne forment une alternance.According to an advantageous embodiment of the invention, the annular ribs of the rotor and the radial flanges of the inner ring form an alternation.

Selon un mode avantageux de l'invention, chaque bride radiale présente un profil de révolution qui s'étend essentiellement radialement, et les nervures annulaires comprennent chacune 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 nervure annulaire voisine.According to an advantageous embodiment of the invention, each radial flange has a profile of revolution which extends essentially radially, and the annular ribs each comprise a profile of revolution which extends essentially radially, each flange profile extends over the most of the radial height of each neighboring annular rib profile.

Avantages apportésBenefits brought

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 forms a bridge that spans each opening. The flange thus makes it possible to bind the opposite edges of the openings so as to connect the edges. This mechanical seal makes it possible to bind the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the void of material 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 ferrule segment with openings in which stator vanes are fixed. The invention thus provides a ferrule or a ferrule segment that is 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 compressor portion 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 roughing a section of the compressor portion along the axis 4-4 plotted 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 the 5-5 axis drawn 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 blade to an inner ferrule or to an inner 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 inner or inner and outer or outer 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 simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 5, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power 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 vanes. Rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow rate and to compress it gradually to the inlet of the combustion chamber 8. Reducing means can increase the rotational speed 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 referred to as a fan or fan 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned 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 turbine outlet. The secondary flow can be accelerated to generate a thrust reaction. The primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical walls or ferrules 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 may be a low-pressure compressor 5. The rotor 12 comprises a drum with an outer 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, each containing a row of stator vanes 26. The rectifiers are associated with the fan or with a row of rotor vanes for straightening the flow of air, so as to convert the speed 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 substantially radially from an outer casing 22, and can be attached thereto by means of an axis. The housing 22 then forms an external support for the different rows. The compressor 5 also comprises internal ferrules 28 which are fixed to the radially inner ends of the stator vanes 26. The inner ferrules 28 serve to guide and delimit the primary flux 18. They also seal with the rotor 12 to avoid recirculation of the air decreasing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine. Each ferrule 28 may form a ring of one 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 . Y is visible a rotor portion 12, an inner radial end of stator vane 26, and an inner ferrule 28 attached thereto. The inner 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 shell 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 ferrule 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 traversed by the ends 30 of the blades 26 to suspend the ferrule 28. 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 dawn 26 associated. One is facing the intrados surface of the dawn, the other facing the extrados face. Edges 36 may be generally 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 inwardly from the axial wall 32. The ferrule 28 may comprise a plurality of 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 radial flange 38 is axially disposed 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 ferrule 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in case of contact. By abradable material is meant a friable material in case of contact. The abradable layers 46 may be applied to the blade tips 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 associated in pairs to frame each annular rib 44 of rotor 12, possibly individually. Each radial flange (38; 40; 42) comprises a profile of revolution that extends substantially radially, each flange profile extends over most of the radial height of each profile of the neighboring radial flange. Each rib profile (38; 40; 42) extends over most of the radial height of the profiles of neighboring 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 asperities 48 which amplify the turbulences 50 or vortices 50 opposing the 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 ferrule 28 and stator vanes 26 along the axis 4-4 plotted on the figure 3 . The cutting plane passes through the radial flange 38 which passes through the openings 34. The ferrule could be formed by ferrule segments 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 shell 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 an abutment surface. corresponding slot. Seals 54 extend radially into openings 34 and pass through them, they come into contact with radial flange 38. Notch bottoms, or abutment surfaces of notches, are spaced apart from joints 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'amenuisent.The radial flange 38 not only joins all the openings 34, but it also connects all the opposite edges 36 to each other through the openings 34. It forms a reinforcement bar which, in each opening 34, blocks the opposite edges 36 The radial flange 38 has an arcuate shape and a crenellated profile. It has a step series forming notches 56 in which are placed the ends of the blades 26. These notches 56 may be a place for fixing the blades 26, for example by gluing or with the aid of fixing plates (not shown). For this purpose, the ends 30 may comprise fixing holes (not shown). Within each opening 34 the radial flange 38 binds the opposite edges 36. This configuration stiffens the ferrule 28, and prevents its bending at the openings, 38 so that the risk of separation at the joints 54 decreases.

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 the axis 5-5 drawn on the figure 3 . The section shows a compressor slice between the rotor 12 and an inner shell, seen from the outside. The location of the blade tips 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 forming an alternation with the grooves, which extend radially and are optionally perpendicular to the axis of rotation of the turbomachine. The assembly can form a ridged annular surface. 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 12Asperities 48 are formed in front of wipers 44, preferably on each side. The pattern may be formed circumferentially along radial flanges (38; 40; 42); or all the way round. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air driven 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 is a diagram of a method of assembling a stator vane on a ferrule, the ferrule being segmentable.

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 oeuvre 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 method may comprise the following steps, possibly carried out in the order presented below:
  1. (a) providing one or more stator vanes 100, each stator vane having an inner radial end, optionally with fixing means;
  2. (b) providing an inner ferrule or inner ferrule segment 102 comprising a row of openings and a circular radial flange or semi-circular through the openings crossing them from edge to edge;
  3. (c) positioning each stator vane end 104 in an opening by abutting each vane end 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 may include the additive manufacture of the ferrule or ferrule segment. The ferrule or each segment can be rimmed and made of polymer, for example a composite hammer with fibers, possibly less than 10 mm in length.

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 oeuvre lors de l'étape (e) mise en oeuvre ou réalisation 108 est mieux positionné et/ou mieux réalisé.Step (c) positioning 104 can be performed by fixing the vanes to an outer compressor casing. Then the shell is moved radially so that the inner ends of the blades are found in the openings. At first, the blade tips enter the openings and then pass through them. Finally, these ends abut against a radial flange. The abutment is then axial and / or radial, which makes it possible to improve the relative position between the blade and the ferrule. Thus, the seal made or implemented during step (e) implementation or embodiment 108 is better positioned and / or better achieved.

Claims (15)

Virole interne (28) ou segment de virole interne de turbomachine axiale (2), notamment de compresseur (5 ; 6), la virole (28) ou le segment de virole comprenant : - une paroi (32) circulaire ou semi-circulaire dont le profil s'étend principalement axialement, et - une rangée d'ouvertures (34) formées dans la paroi axiale (32), chaque ouverture (34) présentant des bords opposés (36) destinés à être disposés latéralement de part et d'autre d'une aube statorique (26) positionnée dans ladite ouverture (34) en vue de sa fixation, - la paroi (32) comprend au moins une bride radiale (38) qui traverse les ouvertures (34) selon la direction circonférentielle de la virole (28) ou du segment de virole, de sorte à former un lien mécanique au sein de chaque ouverture (34) pour en lier les bords opposés (36) ; caractérisée en ce que
la virole (28) ou le segment de virole comprend au moins une bande de matériau abradable (46), chaque bride radiale (38 ; 40 ; 42) s'étendant davantage radialement vers l'intérieur que chaque couche d'abradable (46).Internal ferrule (28) or inner ring segment of an axial turbomachine (2), in particular a compressor (5; 6), the ferrule (28) or the ferrule segment comprising: a wall (32) which is circular or semicircular and whose profile extends mainly axially, and - a row of openings (34) formed in the axial wall (32), each opening (34) having opposite edges (36) intended to be arranged laterally on either side of a stator blade (26) positioned in said opening (34) for attachment, the wall (32) comprises at least one radial flange (38) which passes through the openings (34) in the circumferential direction of the ferrule (28) or the ferrule segment, so as to form a mechanical link within each opening (34) to bond the opposite edges (36); characterized in that
the ferrule (28) or ferrule segment comprises at least one strip of abradable material (46), each radial flange (38; 40; 42) extending further radially inwardly than each abradable layer (46). . Virole (28) ou segment de virole selon la revendication 1, caractérisé(e) en ce que chaque ouverture (34) s'étend principalement axialement et chaque bride radiale (38) s'étend radialement vers l'intérieur depuis la paroi (32), et parcourt tout le tour de la virole (28) ou toute la largeur du segment de virole selon la direction de l'alignement de la rangée d'ouvertures (34).Ferrule (28) or ferrule segment according to claim 1, characterized in that each opening (34) extends mainly axially and each radial flange (38) extends radially inwardly from the wall (32). ), and runs all around the ferrule (28) or the entire width of the ferrule segment in the direction of alignment of the row of openings (34). Virole (28) ou segment de virole selon l'une des revendications 1 à 2, caractérisé(e) en ce que la virole (28) ou le segment de virole comprend plusieurs brides radiales (38) qui traversent chacune les ouvertures, éventuellement chaque bande d'abradable (46) est disposée axialement entre deux brides radiales (38 ; 40 ; 42).Ferrule (28) or ferrule segment according to one of claims 1 to 2, characterized in that the ferrule (28) or the ferrule segment comprises a plurality of radial flanges (38) which each pass through the openings, possibly each abradable strip (46) is disposed axially between two radial flanges (38; 40; 42). Virole (28) ou segment de virole selon l'une des revendications 1 à 3, caractérisé(e) en ce que la bride radiale (38) est une bride radiale traversante (38) qui traverse les ouvertures (34), la virole (28) ou le segment de virole comprenant une bride radiale amont (40) disposée en amont des ouvertures (34), et une bride radiale aval (42) disposée en aval des ouvertures (34), préférentiellement la bride amont (40) et la bride aval (42) délimitent axialement la paroi axiale (32).Ferrule (28) or ferrule segment according to one of claims 1 to 3, characterized in that the radial flange (38) is a through radial flange (38) which passes through the openings (34), the ferrule ( 28) or the ferrule segment comprising an upstream radial flange (40) disposed upstream of the openings (34), and a downstream radial flange (42) disposed downstream of the openings (34), preferably the upstream flange (40) and the downstream flange (42) axially define the axial wall (32). Virole (28) ou segment de virole selon l'une des revendications 1 à 4, caractérisé(e) en ce qu'au moins une ou chaque bride radiale (38 ; 40 ; 42) comprend au moins une surface avec des aspérités (48), ladite surface étant généralement perpendiculaire à l'axe de révolution (14) de la virole (28) ou du segment de virole.Ferrule (28) or ferrule segment according to one of claims 1 to 4, characterized in that at least one or each radial flange (38; 40; 42) comprises at least one surface with asperities (48). ), said surface being generally perpendicular to the axis of revolution (14) of the ferrule (28) or the ferrule segment. Virole (28) ou segment de virole selon la revendication 5, caractérisé(e) en ce que les aspérités (48) forment un motif répété sur sensiblement toute une face de la bride radiale (38 ; 40 ; 42) correspondante, et/ou les aspérités (48) présentent des formes de dents, éventuellement triangulaires, chaque dent s'étend sur la majorité ou sur toute la hauteur radiale de la bride radiale (38 ; 40 ; 42) associée.Ferrule (28) or ferrule segment according to claim 5, characterized in that the asperities (48) form a repeating pattern over substantially an entire face of the corresponding radial flange (38; 40; 42), and / or the asperities (48) have tooth shapes, possibly triangular, each tooth extends over most or all of the radial height of the associated radial flange (38; 40; 42). Procédé d'assemblage d'une aube statorique (26) à une virole interne (28) ou à un segment de virole interne de turbomachine axiale (2), le procédé comprenant les étapes suivantes : (a) fourniture (100) d'une ou de plusieurs aubes statoriques (26), chaque aube statorique (26) comportant une extrémité radiale interne (30) ; (b) fourniture (102) d'une virole interne (28) ou d'un segment de virole interne avec une rangée d'ouvertures (34), la virole (28) ou le segment de virole comprend au moins une bride radiale (38) circulaire ou semi-circulaire traversant les ouvertures (34); (c) positionnement (104) de chaque extrémité (30) d'aube statorique dans une ouverture (34), de sorte que chaque extrémité (30) d'aube soit en butée contre la bride radiale (38) ; (d) fixation (106) de chaque extrémité (30) d'aube dans l'ouverture associée (34); caractérisé en ce que
la virole (28) ou le segment de virole comprend au moins une bande de matériau abradable (46), chaque bride radiale (38 ; 40 ; 42) s'étendant davantage radialement vers l'intérieur que chaque couche d'abradable (46), éventuellement la virole interne (28) ou le segment de virole interne est selon l'une des revendications 1 à 6.A method of assembling a stator vane (26) to an inner ferrule (28) or to an axial turbomachine inner ferrule segment (2), the method comprising the steps of: (a) providing (100) one or more stator vanes (26), each stator vane (26) having an inner radial end (30); (b) providing (102) an inner ferrule (28) or an inner ferrule segment with a row of openings (34), the ferrule (28) or the ferrule segment includes at least one radial flange ( 38) circular or semicircular through the openings (34); (c) positioning (104) each stator vane end (30) in an opening (34) so that each blade end (30) abuts the radial flange (38); (d) attaching (106) each blade tip (30) to the associated aperture (34); characterized in that
the ferrule (28) or ferrule segment comprises at least one strip of abradable material (46), each radial flange (38; 40; 42) extending further radially inwardly than each abradable layer (46). , optionally the inner ferrule (28) or the inner ferrule segment is according to one of claims 1 to 6. Procédé selon la revendication 7, caractérisé en ce que lors de l'étape (c) positionnement (104), chaque extrémité (30) d'aube vient en butée axiale et/ou en butée radiale contre la bride radiale (38), éventuellement chaque extrémité (30) d'aube comprend des moyens de fixation.Method according to claim 7, characterized in that during step (c) positioning (104), each blade end (30) comes into axial abutment and / or abuts against the radial flange (38), optionally each end (30) of blade comprises fixing means. Procédé selon l'une des revendications 7 à 8, caractérisé en ce que l'étape (b) fourniture, comprend la réalisation par fabrication additive de la virole (28) ou du segment de virole ; et/ou. la paroi axiale (32) et chaque bride radiale (38 ; 40 ; 42) sont venues de matière, éventuellement la paroi axiale (32) et chaque bride radiale (38 ; 40 ; 42) sont réalisées en polymère, tel un matériau composite à matrice organiqueMethod according to one of claims 7 to 8, characterized in that the step (b) supply, comprises the embodiment by additive manufacture of the ferrule (28) or the ferrule segment; and or. the axial wall (32) and each radial flange (38; 40; 42) are of material, optionally the axial wall (32) and each radial flange (38; 40; 42) are made of polymer, such as a composite material to organic matrix Turbomachine (2) comprenant un rotor (12) et une virole interne (28) autour du rotor (12) ou un segment de virole interne épousant le rotor (12), caractérisée en ce que la virole (28) ou le segment de virole est conforme à l'une des revendications 1 à 6 ; et/ou la turbomachine (2) comprend une aube statorique (26) et une virole interne (28) ou un segment de virole interne assemblés selon un procédé d'assemblage, caractérisée en ce que le procédé est conforme à l'une des revendications 7 à 9.Turbomachine (2) comprising a rotor (12) and an inner ferrule (28) around the rotor (12) or an inner ferrule segment conforming to the rotor (12), characterized in that the ferrule (28) or ferrule segment is according to one of claims 1 to 6; and / or the turbomachine (2) comprises a stator vane (26) and an inner ferrule (28) or an inner ferrule segment assembled according to an assembly method, characterized in that the method is in accordance with one of the claims 7 to 9. Turbomachine (2) selon la revendication 10, caractérisée en ce que le rotor (12) comporte des nervures annulaires (44) coopérant de manière étanche avec la virole (28) ou le segment de virole, les nervures annulaires (44) du rotor (12) sont chacune à distance axialement de chaque bride radiale (38 ; 40 ; 42) de la virole (28) ou du segment de virole.Turbine engine (2) according to claim 10, characterized in that the rotor (12) comprises annular ribs (44) sealingly engaging the ferrule (28) or the ferrule segment, the annular ribs (44) of the rotor ( 12) are each axially spaced from each radial flange (38; 40; 42) of the ferrule (28) or ferrule segment. Turbomachine (2) selon l'une des revendications 10 à 11, caractérisée en ce qu'au moins une ou chaque bride radiale (38 ; 40 ; 42) comprend des aspérités (48) qui sont formées sur la majorité de la hauteur radiale du profil de révolution d'une des nervures annulaires (44) du rotor (12) disposée en regard de la bride radiale (38 ; 40 ; 42) associée.Turbomachine (2) according to one of claims 10 to 11, characterized in that at least one or each radial flange (38; 40; 42) comprises asperities (48) which are formed over the majority of the radial height of the profile of revolution of one of the annular ribs (44) of the rotor (12) arranged facing the radial flange (38; 40; 42) associated. Turbomachine (2) selon l'une des revendications 10 à 12, caractérisée en ce que chaque ouverture (34) comprend un joint d'étanchéité (54) destiné à entourer une aube statorique (26) disposée dans ladite ouverture (34), le joint d'étanchéité (54) étant en contact de la bride radiale (38) qui traverse ladite ouverture (34), préférentiellement le joint est réalisé en un matériau élastomère tel du silicone.Turbomachine (2) according to one of claims 10 to 12, characterized in that each opening (34) comprises a seal (54) for surrounding a stator vane (26) disposed in said opening (34), the seal (54) being in contact with the radial flange (38) passing through said opening (34), preferably the seal is made of an elastomeric material such as silicone. Turbomachine (2) selon l'une des revendications 10 à 13, caractérisée en ce qu'au moins une ou chaque aube statorique (26) comprend une forme de marche radiale en butée axiale et/ou en butée radiale contre la ou une des brides radiales (38).Turbomachine (2) according to one of claims 10 to 13, characterized in that at least one or each stator blade (26) comprises a radial step form in axial abutment and / or in radial abutment against the or one of the flanges radial (38). Turbomachine (2) selon l'une des revendications 10 à 14, caractérisée en ce qu'au moins une ou chaque aube statorique (26) comprend une encoche dans laquelle est engagée la ou une des brides radiales (38) de la virole, et/ou la ou une des brides radiales (38) comprend des encoches (56) dans lesquelles sont engagées les aubes statoriques (26).Turbomachine (2) according to one of claims 10 to 14, characterized in that at least one or each stator vane (26) comprises a notch in which is engaged one or one of the radial flanges (38) of the ferrule, and / or one or one of the radial flanges (38) comprises notches (56) in which are engaged the stator vanes (26).
EP15190957.9A 2014-11-18 2015-10-22 Internal ferrule of an axial turbine-engine compressor Active EP3023595B1 (en)

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US11028855B2 (en) * 2015-02-27 2021-06-08 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Method of manufacturing supercharger
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FR3085993B1 (en) * 2018-09-17 2020-12-25 Safran Aircraft Engines MOBILE DAWN FOR ONE WHEEL OF A TURBOMACHINE
FR3087825B1 (en) * 2018-10-29 2020-10-30 Safran Aircraft Engines TURBINE RING SECTOR WITH COOLED SEALING TABS
US10822987B1 (en) 2019-04-16 2020-11-03 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins
JP7370226B2 (en) * 2019-11-19 2023-10-27 三菱重工業株式会社 steam turbine
FR3103851B1 (en) * 2019-12-03 2021-11-05 Safran Aircraft Engines RIGID BAR FOR THE ELECTRICAL CONNECTION OF A MACHINE IN AN AIRCRAFT TURBOMACHINE

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FR3088671A1 (en) * 2018-11-16 2020-05-22 Safran Aircraft Engines SEALING BETWEEN A MOBILE WHEEL AND A DISTRIBUTOR OF A TURBOMACHINE
US11525367B2 (en) 2018-11-16 2022-12-13 Safran Aircraft Engines Sealing between a rotor disc and a stator of a turbomachine
FR3091725A1 (en) 2019-01-14 2020-07-17 Safran Aircraft Engines SET FOR A TURBOMACHINE
WO2020148489A1 (en) 2019-01-14 2020-07-23 Safran Aircraft Engines Assembly for a turbomachine
FR3091720A1 (en) 2019-01-14 2020-07-17 Safran Aircraft Engines SET FOR A TURBOMACHINE
US11585230B2 (en) 2019-01-14 2023-02-21 Safran Aircraft Engines Assembly for a turbomachine

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EP3023595B1 (en) 2018-04-18
EP3351736A1 (en) 2018-07-25
RU2015146074A3 (en) 2019-05-20
EP3351736B1 (en) 2020-01-29
RU2015146074A (en) 2017-05-16
CN105604612B (en) 2018-08-28
BE1022513B1 (en) 2016-05-19
US10113439B2 (en) 2018-10-30
US20160138413A1 (en) 2016-05-19
CN105604612A (en) 2016-05-25
RU2719521C2 (en) 2020-04-21
CA2909256A1 (en) 2016-05-18

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