EP3409902A1 - Sealing system for a turbine engine compressor - Google Patents

Sealing system for a turbine engine compressor Download PDF

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Publication number
EP3409902A1
EP3409902A1 EP18173133.2A EP18173133A EP3409902A1 EP 3409902 A1 EP3409902 A1 EP 3409902A1 EP 18173133 A EP18173133 A EP 18173133A EP 3409902 A1 EP3409902 A1 EP 3409902A1
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EP
European Patent Office
Prior art keywords
annular
compressor
rotor
tooth
rib
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
EP18173133.2A
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German (de)
French (fr)
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EP3409902B1 (en
Inventor
Stéphane Hiernaux
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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Publication of EP3409902A1 publication Critical patent/EP3409902A1/en
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Classifications

    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness

Definitions

  • the invention relates to sealing in an axial turbomachine compressor, in particular at an inner ferrule.
  • the invention also relates to an axial turbomachine, such as an aircraft turbojet engine or an aircraft turboprop engine.
  • the invention also proposes a method of manufacturing a compressor.
  • the compression ratio at the outlet of a turbojet compressor depends on the seal between the ferrules and the rotor. This seal must adapt to vibrations as well as ingestions when it comes to a low pressure compressor. The centrifugal force and the expansion remain constraints that add to the previous ones.
  • Each inner ferrule or each inner ferrule segment comprises: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall. Each opening has opposite edges intended to be arranged laterally on either side of a stator blade positioned in said opening for attachment.
  • the wall comprises a radial flange which passes through the openings in the circumferential direction of the ferrule or ferrule segment, so as to form a mechanical link within each opening to bond opposite edges.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to reduce leakage in a compressor. The invention also aims to offer a simple, durable, lightweight, economical, reliable, easy to produce, convenient maintenance, easy inspection, and improved performance.
  • the invention relates to a turbomachine compressor, in particular a low-pressure turbine engine compressor, the compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an inner ferrule connected to the stator vanes and comprising at least one layer of abradable material adapted to cooperate with the at least one annular rib of the rotor to ensure a seal; remarkable in that the inner ferrule comprises at least one annular tooth made of abradable material and extending radially towards the rotor.
  • the invention also relates to a turbomachine compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an inner ferrule connected to the stator vanes which comprises: at least one layer of abradable material capable of cooperating with the at least one annular rib of the rotor, an annular tooth made of abradable material and extending radially towards the rotor, the measured radial clearances axially of the annular rib and the annular tooth being equal.
  • the invention also relates to a turbomachine, in particular an aircraft turbojet, comprising a compressor, which is remarkable in that the compressor is in accordance with the invention, preferably the annular tooth comprises an organic material such as a polymer.
  • the invention also relates to a method for manufacturing a turbomachine compressor, the method comprising the following steps: (a) supplying or producing an annular row of stator vanes; (b) attaching an inner ferrule to the annular row of stator vanes, said inner ferrule comprising abradable material; (d) positioning the abradable material of the inner ferrule around an annular rib of a rotor of the compressor; remarkable in that prior to step (d) positioning it comprises a step (c) addition of at least one annular tooth of abradable material inside the inner shell, at the end of step (d) ) positioning, the compressor is optionally in accordance with the invention.
  • step (c) addition comprises a phase of molding, or gluing, or plasma spraying of abradable material inside the inner shell; at the end of step (d) positioning, the compressor is optionally in accordance with the invention.
  • step (c) addition comprises a machining phase of the abradable in order to cut the annular tooth.
  • the abradable form the annular tooth.
  • the thicknesses and / or the heights can be average values.
  • each object of the invention is also applicable to the other objects of the invention.
  • Each object of the invention is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise be explicitly specified.
  • the invention allows to create other wipers embedded by the inner ferrule. Their presence brings an effect that is added to that of the rotor, by amplifying the vortices under the ferrule to slow down the secondary flows.
  • the seal is improved without penalizing the inertia of the rotor.
  • teeth of abradable material respects the integrity of the rotor.
  • Radially two levels of tightness are created and act in series, while allowing implantation that respects the axial and radial compactness.
  • the terms “internal” and “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 radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • abradable material is meant a material capable of crumbling in contact with the rotor to limit the wear of the latter.
  • 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 4, 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 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • a commonly designated fan or fan input fan 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into 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 blower may be of the non-ducted type.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the primary 18 and secondary 20 streams are coaxial annular flows and fitted into one another. They are channeled by the casing of the turbomachine and / or ferrules.
  • 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 4. It can observe the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It can be a monobloc drum. It forms a solid connecting all its rows of blades.
  • one or more or each row of rotor blades 24 is rigidly connected to the rotor, and thus to the drum if necessary.
  • the rotor blades are dovetail attachment.
  • the low pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan or a row of rotor vanes to straighten the air flow, so converting the speed of the flow into pressure, in particular into static pressure.
  • the stator vanes 26 extend substantially radially from an outer casing 28, and can be fixed and immobilized by means of axes.
  • the housing 28 may be formed of two half-shells.
  • the rows of stator vanes 26 support inner shells 30 whose outer surfaces guide the primary flow 18.
  • the inner shells 30 may have a profile of revolution about the axis of rotation 14. They provide dynamic sealing with the rotor 12 , especially in combination with its annular ribs, commonly known as wipers. They minimize leakage in that they allow a rimpedement with the rotor, said approximation closing the mechanical clearances in operation.
  • a ferrule and a rotor portion 12 may form a sealing system.
  • the figure 3 sketch a sealing system such as those of the figure 2 .
  • a stator blade 26 representative of its row
  • an axial rotor portion 12 and an inner ring 30.
  • the shell 30 may be segmented. It can be made of organic matrix composite material reinforced with fibers.
  • the system is here represented at rest, the speed of rotation of the ribs 42 relative to the teeth 32 being zero.
  • the rotor 12 comprises at least one, in this case two annular ribs 32 which extend radially outwardly from the casing 34 of the rotor 12.
  • the casing 34 may correspond to that of the drum.
  • These ribs 32 form circular blades with circular points facing the inner ferrule 30, in particular radially opposite layers of abradable material 36 dedicated. These layers 36 may be housed in the radial thickness of the annular wall 38 of the inner shell 30.
  • the latter has at least one annular tooth 42, for example two or three annular teeth 42. These teeth 42 extend radially from the inner surface 44 of the ferrule 30. The teeth 42 project from this inner surface 44.
  • the teeth 42 may be distributed axially along the length of the shell 30, possibly homogeneously. That upstream may be axially, or upstream, the leading edge 46 of the blade 26. The downstream may be at the axial level, or downstream, the trailing edge 48 of the blade 26.
  • the teeth 42 and the ribs 32 form an alternation, so that they enclose annular chambers between the rotor 12 and the ferrule 30; said chambers see their circular edges close in operation, hence improving the sealing, increasing the compression ratio, and optimizing the engine efficiency.
  • the teeth 42 and the ribs 32 extend radially in opposite directions. They can cross radially. They may overlap radially, possibly on the majority of their respective radial heights. Their axial faces, possibly flat or substantially conical, are facing axially.
  • the teeth 42 and the ribs 32 may be of equal heights or the like, ie with a difference of at most: 10%, or 5%.
  • the one or more or each set J1 radially remaining between one of the teeth 42 and the rotor 12, more precisely between one of the teeth 42 and the envelope 34, may be equal to at least one, or several, or each set J2 between the ferrule 38 and one of the ribs 32.
  • all the games J1 are equal; and / or all J2 games are equal.
  • This arrangement favors sealing, and allows the teeth to play a role substantially equivalent to the ribs.
  • the ribs reduce their margins with the ferrule simultaneously. In case of contact, on both sides, the mechanical impact is controlled since the teeth can crumble against the rotor without damaging it.
  • the abradable material of the teeth 42 may differ from that of the layers 36 radially in front of the ribs 32. Thus, different properties may be chosen.
  • the first abradable material used in the teeth 42 may be softer than the second which is present in the layers 36. This preserves the rotor 12.
  • These materials may be elastomers, possibly with concentrations of spheres different digs, or different charge contents.
  • the teeth can be softer than the ribs.
  • the ribs may be made of titanium, and / or with a Vickers hardness greater than or equal to: 200 MPa, or 900 MPa. The Vickers hardness of the teeth is less than or equal to: 100 MPa, or 10 MPa.
  • the ribs 32 may be thinner axially than the teeth 42. This optimizes the occupancy under the shell, optimizes the rotating mass and the mechanical strength.
  • the inner ferrule 30 may comprise at least one circular groove 50, possibly one for each rib 32.
  • Each circular groove 50 is open radially inward, and can receive the circular tip of a rib 32.
  • Each groove 50 s extends radially in a different direction of the teeth 42, especially from the inner surface 44. This allows a better closure of the games in operation.
  • Each set J2 can be measured against the bottom of the corresponding groove 50.
  • the grooves 50 are formed in the layers 36.
  • the figure 4 represents a sealing system according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of this embodiment.
  • This sealing system is substantially identical to that of the figure 3 , however, it differs in that the annular teeth 142 are formed in a same abradable layer 136 which cooperates further with the ribs 132.
  • the latter is carried by the wall 138 of the inner shell 130, and forms the inner surface 144.
  • the numbers of teeth 142 and rib 132 also change.
  • the ribs 132 and the teeth 142 are placed alternately.
  • the ribs 142 are opposite two teeth 132.
  • the radial heights of teeth are equal to the heights of the ribs.
  • a mixed compressor that is to say one which comprises one or more sealing systems according to the figure 3 , and one or more sealing systems according to the figure 4 .
  • Circular grooves may be added, especially in layer 136.
  • the figure 5 sketch a diagram of the manufacturing process of a turbomachine compressor. This process can be a method of assembly and / or shaping.
  • the compressor may correspond to that described in relation to the figures 1 and 2 , the compressor sealing systems being for example according to the teachings of the figures 3 and / or 4.
  • Step (c) addition 204 may be a step of making or mounting a tooth inside the ferrule.
  • Step (c) addition 204 may comprise an application phase 208 of abradable material in the ferrule.
  • the application phase 208 can be performed by molding, or gluing, or plasma projection.
  • step (c) addition 204 comprises a machining step 210 of the abradable to cut the annular tooth.
  • the machining can be by turning, in particular by placing the ferrule on a mandrel.
  • the phase application 208 tends to implement an annular layer of abradable extra thickness relative to the teeth.
  • the superfluous material is cut to keep only the material proper to the teeth.
  • the application phase 208 of abradable can directly form one or each tooth.
  • a tooth has its final shape, another shows a surplus of material that is removed, by cutting and / or machining.

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

Abstract

L'invention propose un compresseur basse pression de turbomachine, tel un turboréacteur d'aéronef. Le compresseur comprend un rotor (12) avec deux rangées d'aubes rotoriques entre lesquelles sont placées deux nervures annulaires (32) ; une rangée annulaire d'aubes statoriques (26) entre les aubes rotoriques. Une virole interne (30) est reliée aux aubes statorique. La virole interne comprend du matériau abradable coopérant avec les nervures annulaires, et des dents annulaires (42) réalisées en matériau abradable qui s'étendent radialement vers le rotor (12) afin d'assurer une étanchéité. L'invention a également pour objet un procédé de fabrication d'un compresseur de turboréacteur double flux.

Figure imgaf001
The invention proposes a low-pressure turbomachine compressor, such as an aircraft turbojet engine. The compressor comprises a rotor (12) with two rows of rotor blades between which are placed two annular ribs (32); an annular row of stator vanes (26) between the rotor vanes. An inner ferrule (30) is connected to the stator vanes. The inner ferrule comprises abradable material cooperating with the annular ribs, and annular teeth (42) made of abradable material which extend radially towards the rotor (12) to provide a seal. The invention also relates to a method for manufacturing a turbofan compressor.
Figure imgaf001

Description

Domaine techniqueTechnical area

L'invention se rapporte à l'étanchéité dans un compresseur de turbomachine axiale, notamment au niveau d'une virole interne. L'invention a également trait à une turbomachine axiale, tel un turboréacteur d'avion ou un turbopropulseur d'aéronef. L'invention propose également un procédé de fabrication d'un compresseur.The invention relates to sealing in an axial turbomachine compressor, in particular at an inner ferrule. The invention also relates to an axial turbomachine, such as an aircraft turbojet engine or an aircraft turboprop engine. The invention also proposes a method of manufacturing a compressor.

Technique antérieurePrior art

Le taux de compression en sortie d'un compresseur de turboréacteur dépend de l'étanchéité entre les viroles et le rotor. Cette étanchéité doit s'adapter aux vibrations comme aux ingestions lorsqu'il s'agit d'un compresseur basse pression. La force centrifuge et la dilatation restent des contraintes qui s'ajoutent aux précédentes.The compression ratio at the outlet of a turbojet compressor depends on the seal between the ferrules and the rotor. This seal must adapt to vibrations as well as ingestions when it comes to a low pressure compressor. The centrifugal force and the expansion remain constraints that add to the previous ones.

Le document EP 3 023 595 A1 divulgue un turboréacteur équipé d'un compresseur basse pression où des viroles internes limitent les fuites autour du rotor. Chaque virole interne ou chaque segment de virole interne comprend: 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 présente 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. En outre, la paroi comprend 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 document EP 3,023,595 A1 discloses a turbojet engine equipped with a low pressure compressor where internal shrouds limit leakage around the rotor. Each inner ferrule or each inner ferrule segment comprises: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall. Each opening has opposite edges intended to be arranged laterally on either side of a stator blade positioned in said opening for attachment. In addition, the wall comprises a radial flange which passes through the openings in the circumferential direction of the ferrule or ferrule segment, so as to form a mechanical link within each opening to bond opposite edges.

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 pouvoir réduire les fuites dans un compresseur. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, commode d'entretien, d'inspection aisée, et améliorant le rendement.The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to reduce leakage in a compressor. The invention also aims to offer a simple, durable, lightweight, economical, reliable, easy to produce, convenient maintenance, easy inspection, and improved performance.

Solution techniqueTechnical solution

L'invention a pour objet un compresseur de turbomachine, notamment un compresseur basse pression de turbomachine, le compresseur comprenant : un rotor avec au moins une nervure annulaire ; une rangée annulaire d'aubes statoriques ; une virole interne reliée aux aubes statoriques et comprenant au moins une couche de matériau abradable apte à coopérer avec la au moins une nervure annulaire du rotor afin d'assurer une étanchéité ; remarquable en ce que la virole interne comprend au moins une dent annulaire réalisée en matériau abradable et s'étendant radialement vers le rotor.The invention relates to a turbomachine compressor, in particular a low-pressure turbine engine compressor, the compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an inner ferrule connected to the stator vanes and comprising at least one layer of abradable material adapted to cooperate with the at least one annular rib of the rotor to ensure a seal; remarkable in that the inner ferrule comprises at least one annular tooth made of abradable material and extending radially towards the rotor.

Selon des modes avantageux de l'invention, le réservoir peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément ou selon toutes les combinaisons techniques possibles :

  • La dent annulaire et le rotor comprennent entre eux un premier jeu radial J1, la nervure annulaire et la virole interne comprennent entre elles un deuxième jeu radial J2 qui représente entre 50% et 150% du premier jeu radial J1.
  • Le premier jeu radial J1 est égal au deuxième jeu radial J2.
  • La dent annulaire comprend un profil de révolution trapézoïdal ou triangulaire. Le profil de révolution est considéré autour de l'axe de rotation du rotor.
  • La dent annulaire est plus épaisse axialement que la nervure annulaire.
  • La dent annulaire présente une hauteur radiale égale à la hauteur radiale de la nervure annulaire.
  • La dent annulaire et la nervure annulaire se chevauchent radialement sur la majorité de leurs hauteurs radiales.
  • Le matériau de la dent annulaire est différent de celui coopérant avec la nervure annulaire, et est éventuellement plus friable.
  • Le matériau abradable de la dent annulaire est le même que celui coopérant avec la nervure annulaire ; lesdits matériaux étant éventuellement venus de matière et/ou formant un ensemble monobloc.
  • Le rotor comprend au moins deux rangées annulaires d'aubes rotoriques entre lesquelles est disposée axialement la dent annulaire, les au moins deux rangées annulaires d'aube rotoriques étant un ensemble monobloc.
  • La virole interne comprend une surface annulaire interne d'où s'étend radialement la dent annulaire, ladite surface comprenant une gorge circulaire disposée axialement au niveau de la nervure annulaire.
  • La virole interne comprend une paroi annulaire, éventuellement réalisée en un matériau composite.
  • La paroi annulaire sépare radialement les aubes statoriques de la dent annulaire.
  • La dent annulaire est une première dent annulaire, la virole interne comprenant d'autres, éventuellement au moins deux autres, dents annulaires réalisées en matériau abradable et s'étendant radialement vers le rotor, les dents annulaires étant éventuellement réparties axialement le long de la virole interne.
  • La nervure annulaire est une première nervure, le rotor comprenant en outre au moins une deuxième nervure annulaire, les nervures annulaires et la ou chaque dent annulaire formant une alternance.
  • Le jeu radial J2 représente entre 80% et 120%, ou entre 90% et 110% du jeu radial J1.
  • Le jeu J1 et/ou le jeu J2 représente au plus : 20%, ou 10%, ou 5% ; ou 3% de la hauteur radiale de la dent ou de la nervure respectivement.
  • Le compresseur est à écoulement axial.
  • La dent comprend une pointe circulaire orientée radialement vers l'intérieur.
  • La nervure comprend une pointe circulaire orientée radialement vers l'extérieur.
  • La dent présente un profil de révolution dont la hauteur radiale est supérieure à l'épaisseur axiale, éventuellement au moins : deux, ou trois, ou quatre, ou cinq fois supérieure à l'épaisseur axiale. Ces proportions peuvent s'appliquer au profil de révolution de la nervure annulaire.
  • En fonctionnement, la dent tourne et/ou rentre dans la gorge.
  • Le matériau abradable de la dent est un premier matériau, celui coopérant avec la nervure est un deuxième matériau qui est éventuellement de densité supérieure au, et/ou plus dur que le, premier matériau.
  • Le rotor est un tambour monobloc avec une surface externe supportant chaque nervure annulaire.
  • La paroi et la dent sont réalisées en des matériaux différents.
  • Le rotor comprend une surépaisseur radiale en regard radialement de la dent, et/ou s'étendant radialement vers la dent.
  • La dent et la nervure s'étendent sur la majorité de l'espace radial entre l'enveloppe du rotor et la surface interne de la virole. Ledit espace s'étend sur toute la longueur de la virole.
  • La nervure présente une dureté supérieure à la dureté de la dent, éventuellement au moins : deux fois, ou cinq fois, ou dix fois supérieure. Les duretés peuvent être des duretés Vickers.
According to advantageous embodiments of the invention, the reservoir may comprise one or more of the following characteristics, taken separately or according to all the possible technical combinations:
  • The annular tooth and the rotor comprise between them a first radial clearance J1, the annular rib and the inner ring comprise between them a second radial clearance J2 which represents between 50% and 150% of the first radial clearance J1.
  • The first radial clearance J1 is equal to the second radial clearance J2.
  • The annular tooth comprises a trapezoidal or triangular revolution profile. The revolution profile is considered around the axis of rotation of the rotor.
  • The annular tooth is thicker axially than the annular rib.
  • The annular tooth has a radial height equal to the radial height of the annular rib.
  • The annular tooth and the annular rib overlap radially over most of their radial heights.
  • The material of the annular tooth is different from that cooperating with the annular rib, and is optionally more friable.
  • The abradable material of the annular tooth is the same as that cooperating with the annular rib; said materials possibly being made of material and / or forming a one-piece assembly.
  • The rotor comprises at least two annular rows of rotor blades between which is disposed axially the annular tooth, the at least two annular rows of rotor blades being a one-piece assembly.
  • The inner ferrule comprises an inner annular surface from which the annular tooth extends radially, said surface comprising a circular groove disposed axially at the level of the annular rib.
  • The inner ferrule comprises an annular wall, possibly made of a composite material.
  • The annular wall radially separates the stator vanes from the annular tooth.
  • The annular tooth is a first annular tooth, the inner ferrule comprising others, possibly at least two other, annular teeth made of abradable material and extending radially towards the rotor, the annular teeth possibly being distributed axially along the ferrule internal.
  • The annular rib is a first rib, the rotor further comprising at least one second annular rib, the annular ribs and the or each annular tooth forming an alternation.
  • The radial clearance J2 represents between 80% and 120%, or between 90% and 110% of the radial clearance J1.
  • The game J1 and / or the game J2 represents at most: 20%, or 10%, or 5%; or 3% of the radial height of the tooth or rib, respectively.
  • The compressor is axial flow.
  • The tooth comprises a circular tip oriented radially inwards.
  • The rib comprises a circular tip oriented radially outwardly.
  • The tooth has a revolution profile whose radial height is greater than the axial thickness, possibly at least two, or three, or four, or five times greater than the axial thickness. These proportions can be applied to the revolution profile of the annular rib.
  • In operation, the tooth rotates and / or enters the groove.
  • The abradable material of the tooth is a first material, the one cooperating with the rib is a second material which is optionally of density greater than, and / or harder than, the first material.
  • The rotor is a one-piece drum with an outer surface supporting each annular rib.
  • The wall and the tooth are made of different materials.
  • The rotor comprises a radial extra thickness radially facing the tooth, and / or extending radially towards the tooth.
  • The tooth and rib extend over most of the radial space between the rotor casing and the inner surface of the ferrule. Said space extends over the entire length of the ferrule.
  • The rib has a hardness greater than the hardness of the tooth, possibly at least twice, or five times, or ten times higher. The hardnesses can be Vickers hardnesses.

L'invention a également pour objet un compresseur de turbomachine comprenant : un rotor avec au moins une nervure annulaire ; une rangée annulaire d'aubes statoriques ; une virole interne reliée aux aubes statoriques qui comprend : au moins une couche de matériau abradable apte à coopérer avec la au moins une nervure annulaire du rotor, une dent annulaire réalisée en matériau abradable et s'étendant radialement vers le rotor, les jeux radiaux mesurés au niveau axialement de la nervure annulaire et de la dent annulaire étant égaux.The invention also relates to a turbomachine compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an inner ferrule connected to the stator vanes which comprises: at least one layer of abradable material capable of cooperating with the at least one annular rib of the rotor, an annular tooth made of abradable material and extending radially towards the rotor, the measured radial clearances axially of the annular rib and the annular tooth being equal.

L'invention a également pour objet une turbomachine, notamment un turboréacteur d'aéronef, comprenant un compresseur, remarquable en ce que le compresseur est conforme à l'invention, préférentiellement la dent annulaire comprend un matériau organique tel un polymère.The invention also relates to a turbomachine, in particular an aircraft turbojet, comprising a compressor, which is remarkable in that the compressor is in accordance with the invention, preferably the annular tooth comprises an organic material such as a polymer.

L'invention a également pour objet un procédé de fabrication d'un compresseur de turbomachine, le procédé comprenant les étapes suivantes : (a) fourniture ou réalisation d'une rangée annulaire d'aubes statoriques ; (b) fixation d'une virole interne à la rangée annulaire d'aubes statoriques, ladite virole interne comprenant du matériau abradable ; (d) positionnement du matériau abradable de la virole interne autour d'une nervure annulaire d'un rotor du compresseur ; remarquable en ce que préalablement à l'étape (d) positionnement il comprend une étape (c) ajout d'au moins une dent annulaire en matériau abradable à l'intérieur de la virole interne, à l'issue de l'étape (d) positionnement, le compresseur est éventuellement conforme à l'invention.The invention also relates to a method for manufacturing a turbomachine compressor, the method comprising the following steps: (a) supplying or producing an annular row of stator vanes; (b) attaching an inner ferrule to the annular row of stator vanes, said inner ferrule comprising abradable material; (d) positioning the abradable material of the inner ferrule around an annular rib of a rotor of the compressor; remarkable in that prior to step (d) positioning it comprises a step (c) addition of at least one annular tooth of abradable material inside the inner shell, at the end of step (d) ) positioning, the compressor is optionally in accordance with the invention.

Selon un mode avantageux de l'invention, l'étape (c) ajout comprend une phase de moulage, ou de collage, ou de projection plasma de matériau abradable à l'intérieur de la virole interne ; à l'issue de l'étape (d) positionnement, le compresseur est éventuellement conforme à l'invention.According to an advantageous embodiment of the invention, step (c) addition comprises a phase of molding, or gluing, or plasma spraying of abradable material inside the inner shell; at the end of step (d) positioning, the compressor is optionally in accordance with the invention.

Selon un mode avantageux de l'invention, l'étape (c) ajout comprend une phase d'usinage de l'abradable afin d'y tailler la dent annulaire.According to an advantageous embodiment of the invention, step (c) addition comprises a machining phase of the abradable in order to cut the annular tooth.

Selon un mode avantageux de l'invention, à l'issue de la phase de moulage, ou de collage, l'abradable forme la dent annulaire.According to an advantageous embodiment of the invention, at the end of the molding phase, or bonding, the abradable form the annular tooth.

Les épaisseurs et/ou les hauteurs peuvent être des valeurs moyennes.The thicknesses and / or the heights can be average values.

Les caractéristiques présentées en relation avec une dent annulaire peuvent s'appliquer à chaque dent annulaire. Le même s'applique aux nervures.The features presented in connection with an annular tooth can be applied to each annular tooth. The same applies to the ribs.

De manière générale, les modes avantageux de chaque objet de l'invention sont également applicables aux autres objets de l'invention. Chaque objet de l'invention est combinable aux autres objets, et les objets de l'invention sont également combinables aux modes de réalisation de la description, qui en plus sont combinables entre eux, selon toutes les combinaisons techniques possibles, à moins que le contraire soit explicitement précisé.In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. Each object of the invention is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise be explicitly specified.

Avantages apportésBenefits brought

L'invention permet de créer d'autres léchettes embarquées par la virole interne. Leur présence apporte un effet qui s'ajoute à celui du rotor, en amplifiant les tourbillons sous la virole pour freiner les écoulements secondaires. L'étanchéité est améliorée sans pénaliser l'inertie du rotor.The invention allows to create other wipers embedded by the inner ferrule. Their presence brings an effect that is added to that of the rotor, by amplifying the vortices under the ferrule to slow down the secondary flows. The seal is improved without penalizing the inertia of the rotor.

Par ailleurs, la réalisation des dents en matériau abradable respecte l'intégrité du rotor. Radialement deux niveaux d'étanchéité sont créés et agissent en série, tout en permettant une implantation qui respecte la compacité axiale et radiale.Furthermore, the realization of teeth of abradable material respects the integrity of the rotor. Radially two levels of tightness are created and act in series, while allowing implantation that respects the axial and radial compactness.

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 un système d'étanchéité selon un premier mode de réalisation de l'invention.The figure 3 illustrates a sealing system according to a first embodiment of the invention.
  • La figure 4 illustre un système d'étanchéité selon un deuxième mode de réalisation de l'invention.The figure 4 illustrates a sealing system according to a second embodiment of the invention.
  • La figure 5 est un diagramme du procédé de fabrication d'un compresseur de turbomachine selon l'invention.The figure 5 is a diagram of the method of manufacturing a turbomachine compressor according to the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes « interne » et « 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 radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine. Par matériau abradable, on entend un matériau apte à s'effriter au contact du rotor afin de limiter l'usure de ce dernier.In the following description, the terms "internal" and "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 radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine. By abradable material is meant a material capable of crumbling in contact with the rotor to limit the wear of the latter.

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 4, 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 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. 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.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 4, 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 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.

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 susmentionnés de la turbomachine, et en 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. La soufflante peut être du type non carénée.A commonly designated fan or fan input fan 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into 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 blower may be of the non-ducted type.

Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée nécessaire au vol d'un avion. Les flux primaire 18 et secondaire 20 sont des flux annulaires coaxiaux et emmanchés l'un dans l'autre. Ils sont canalisés par le carter de la turbomachine et/ou des viroles.The secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft. The primary 18 and secondary 20 streams are coaxial annular flows and fitted into one another. They are channeled by the casing of the turbomachine and / or ferrules.

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 4. On peut y observer le bec de séparation 22 du flux primaire 18 et du flux secondaire 20. Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois. Il peut être un tambour monobloc. Il forme un solide reliant toutes ses rangées d'aubes. Eventuellement un, ou plusieurs, ou chacune des rangées d'aubes rotoriques 24 est rigidement liée au rotor, et donc au tambour le cas échéant. Alternativement, les aubes rotoriques sont à fixation par queue d'aronde.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 4. It can observe the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, in this case three. It can be a monobloc drum. It forms a solid connecting all its rows of blades. Optionally one or more or each row of rotor blades 24 is rigidly connected to the rotor, and thus to the drum if necessary. Alternatively, the rotor blades are dovetail attachment.

Le compresseur basse pression 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression, notamment en pression statique.The low pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26. The rectifiers are associated with the fan or a row of rotor vanes to straighten the air flow, so converting the speed of the flow into pressure, in particular into static pressure.

Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter extérieur 28, et peuvent y être fixées et immobilisées à l'aide d'axes. Le carter 28 peut être formé de deux demi-coquilles. Les rangées d'aubes statoriques 26 supportent des viroles internes 30 dont les surfaces externes guident le flux primaire 18. Les viroles internes 30 peuvent présenter un profil de révolution autour de l'axe de rotation 14. Elles assurent des étanchéités dynamiques avec le rotor 12, notamment en combinaison avec ses nervures annulaires, communément appelées léchettes. Elles minimisent les fuites en ce sens qu'elles autorisent un rapprochement avec le rotor, ledit rapprochement refermant les jeux mécaniques en fonctionnement. Ainsi, une virole et une portion de rotor 12 peuvent former un système d'étanchéité.The stator vanes 26 extend substantially radially from an outer casing 28, and can be fixed and immobilized by means of axes. The housing 28 may be formed of two half-shells. The rows of stator vanes 26 support inner shells 30 whose outer surfaces guide the primary flow 18. The inner shells 30 may have a profile of revolution about the axis of rotation 14. They provide dynamic sealing with the rotor 12 , especially in combination with its annular ribs, commonly known as wipers. They minimize leakage in that they allow a rapprochement with the rotor, said approximation closing the mechanical clearances in operation. Thus, a ferrule and a rotor portion 12 may form a sealing system.

La figure 3 esquisse un système d'étanchéité tels que ceux de la figure 2. Sont visibles: une aube statorique 26 représentative de sa rangée, un tronçon axial de rotor 12, et une virole interne 30. La virole 30 peut être segmentée. Elle peut être réalisée en matériau composite à matrice organique renforcée par des fibres. Le système est ici représenté au repos, la vitesse de rotation des nervures 42 par rapport aux dents 32 étant nulle.The figure 3 sketch a sealing system such as those of the figure 2 . Are visible: a stator blade 26 representative of its row, an axial rotor portion 12, and an inner ring 30. The shell 30 may be segmented. It can be made of organic matrix composite material reinforced with fibers. The system is here represented at rest, the speed of rotation of the ribs 42 relative to the teeth 32 being zero.

Le rotor 12 comprend au moins une, en l'occurrence deux nervures annulaires 32 qui s'étendent radialement vers l'extérieur depuis l'enveloppe 34 du rotor 12. L'enveloppe 34 peut correspondre à celle du tambour. Ces nervures 32 forment des lames circulaires avec des pointes circulaires en regard de la virole interne 30, notamment en regard radialement de couches de matériau abradable 36 dédiées. Ces couches 36 peuvent être logées dans l'épaisseur radiale de la paroi annulaire 38 de la virole interne 30.The rotor 12 comprises at least one, in this case two annular ribs 32 which extend radially outwardly from the casing 34 of the rotor 12. The casing 34 may correspond to that of the drum. These ribs 32 form circular blades with circular points facing the inner ferrule 30, in particular radially opposite layers of abradable material 36 dedicated. These layers 36 may be housed in the radial thickness of the annular wall 38 of the inner shell 30.

Radialement à l'opposé de la surface externe 40 de la virole 30, cette dernière présente au moins une dent annulaire 42, par exemple deux ou trois dents annulaires 42. Ces dents 42 s'étendent radialement depuis la surface interne 44 de la virole 30. Les dents 42 font saillie depuis cette surface interne 44.Radially opposite the outer surface 40 of the shell 30, the latter has at least one annular tooth 42, for example two or three annular teeth 42. These teeth 42 extend radially from the inner surface 44 of the ferrule 30. The teeth 42 project from this inner surface 44.

Les dents 42 peuvent être réparties axialement sur la longueur de la virole 30, éventuellement de manière homogène. Celle en amont peut être au niveau axialement, ou en amont, du bord d'attaque 46 de l'aube 26. Celle en aval peut être au niveau axialement, ou en aval, du bord de fuite 48 de l'aube 26. Les dents 42 et les nervures 32 forment une alternance, si bien qu'elles renferment des chambres annulaires entre le rotor 12 et la virole 30 ; lesdites chambres voient leurs arrêtes circulaires se refermer en fonctionnement, d'où l'amélioration de l'étanchéité, l'augmentation du taux de compression, et l'optimisation du rendement moteur.The teeth 42 may be distributed axially along the length of the shell 30, possibly homogeneously. That upstream may be axially, or upstream, the leading edge 46 of the blade 26. The downstream may be at the axial level, or downstream, the trailing edge 48 of the blade 26. The teeth 42 and the ribs 32 form an alternation, so that they enclose annular chambers between the rotor 12 and the ferrule 30; said chambers see their circular edges close in operation, hence improving the sealing, increasing the compression ratio, and optimizing the engine efficiency.

Les dents 42 et les nervures 32 s'étendent radialement dans des sens opposés. Elles peuvent se croiser radialement. Elles peuvent se chevaucher radialement, éventuellement sur la majorité de leurs hauteurs radiales respectives. Leurs faces axiales, éventuellement planes ou sensiblement coniques, sont en regard axialement. Les dents 42 et les nervures 32 peuvent être de hauteurs égales ou similaires, s'est à dire avec une différence d'au plus: 10%, ou 5%.The teeth 42 and the ribs 32 extend radially in opposite directions. They can cross radially. They may overlap radially, possibly on the majority of their respective radial heights. Their axial faces, possibly flat or substantially conical, are facing axially. The teeth 42 and the ribs 32 may be of equal heights or the like, ie with a difference of at most: 10%, or 5%.

Eventuellement, le ou plusieurs ou chaque jeu J1 subsistant radialement entre une des dents 42 et le rotor 12, plus précisément entre une des dents 42 et l'enveloppe 34, peut être égal à au moins un, ou plusieurs, ou chaque jeu J2 entre la virole 38 et l'une des nervures 32. Eventuellement, tous les jeux J1 sont égaux ; et/ou tous les jeux J2 sont égaux. Cet arrangement favorise l'étanchéité, et permet aux dents de jouer un rôle sensiblement équivalent aux nervures. Lorsque les dents se rapprochent radialement du rotor, les nervures réduisent leurs marges avec la virole simultanément. En cas de contact, d'un côté comme de l'autre, l'impact mécanique est maîtrisé puisque les dents peuvent s'effriter contre le rotor sans l'endommager.Optionally, the one or more or each set J1 radially remaining between one of the teeth 42 and the rotor 12, more precisely between one of the teeth 42 and the envelope 34, may be equal to at least one, or several, or each set J2 between the ferrule 38 and one of the ribs 32. Optionally, all the games J1 are equal; and / or all J2 games are equal. This arrangement favors sealing, and allows the teeth to play a role substantially equivalent to the ribs. When the teeth move radially closer to the rotor, the ribs reduce their margins with the ferrule simultaneously. In case of contact, on both sides, the mechanical impact is controlled since the teeth can crumble against the rotor without damaging it.

Le matériau abradable des dents 42 peut différer de celui des couches 36 radialement en face des nervures 32. Ainsi, des propriétés différentes peuvent être choisies. A titre d'exemple le premier matériau abradable, employé dans les dents 42, peut être plus tendre que le deuxième qui est présent dans les couches 36. Cela préserve le rotor 12. Ces matériaux peuvent être des élastomères, éventuellement avec des concentrations de sphères creuses différentes, ou des teneurs en charges distinctes. Aussi, les dents peuvent être plus tendre que les nervures. Les nervures peuvent être en titane, et/ou avec une dureté Vickers supérieure ou égale à : 200 MPa, ou 900 MPa. La dureté Vickers des dents est inférieure ou égale à: 100 MPa, ou 10 MPa.The abradable material of the teeth 42 may differ from that of the layers 36 radially in front of the ribs 32. Thus, different properties may be chosen. By way of example, the first abradable material used in the teeth 42 may be softer than the second which is present in the layers 36. This preserves the rotor 12. These materials may be elastomers, possibly with concentrations of spheres different digs, or different charge contents. Also, the teeth can be softer than the ribs. The ribs may be made of titanium, and / or with a Vickers hardness greater than or equal to: 200 MPa, or 900 MPa. The Vickers hardness of the teeth is less than or equal to: 100 MPa, or 10 MPa.

Les nervures 32 peuvent être plus fines axialement que les dents 42. Cela optimise l'occupation sous virole, optimise la masse tournante et la résistance mécanique.The ribs 32 may be thinner axially than the teeth 42. This optimizes the occupancy under the shell, optimizes the rotating mass and the mechanical strength.

Optionnellement, la virole interne 30 peut comprendre au moins une gorge circulaire 50, éventuellement une pour chaque nervure 32. Chaque gorge circulaire 50 est ouverte radialement vers l'intérieur, et peut recevoir la pointe circulaire d'une nervure 32. Chaque gorge 50 s'étend radialement dans un sens différent des dents 42, notamment depuis la surface interne 44. Ceci permet une meilleure fermeture des jeux en fonctionnement. Chaque jeu J2 peut être mesuré contre le fond de la gorge 50 correspondante. Optionnellement, les gorges 50 sont formées dans les couches 36.Optionally, the inner ferrule 30 may comprise at least one circular groove 50, possibly one for each rib 32. Each circular groove 50 is open radially inward, and can receive the circular tip of a rib 32. Each groove 50 s extends radially in a different direction of the teeth 42, especially from the inner surface 44. This allows a better closure of the games in operation. Each set J2 can be measured against the bottom of the corresponding groove 50. Optionally, the grooves 50 are formed in the layers 36.

La figure 4 représente un système d'étanchéité selon un deuxième mode de réalisation de l'invention. Cette figure 4 reprend la numérotation des figures précédentes pour les éléments identiques ou similaires, la numération étant toutefois incrémentée de 100. Des numéros spécifiques sont utilisés pour les éléments spécifiques à ce mode de réalisation.The figure 4 represents a sealing system according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of this embodiment.

Ce système d'étanchéité est sensiblement identique à celui de la figure 3, il en diffère toutefois en ce que les dents annulaires 142 sont formées dans une même couche d'abradable 136 qui coopère en outre avec les nervures 132.This sealing system is substantially identical to that of the figure 3 , however, it differs in that the annular teeth 142 are formed in a same abradable layer 136 which cooperates further with the ribs 132.

Cette dernière est portée par la paroi 138 de la virole interne 130, et forme la surface interne 144. Les nombres de dents 142 et de nervure 132 changent également.The latter is carried by the wall 138 of the inner shell 130, and forms the inner surface 144. The numbers of teeth 142 and rib 132 also change.

A nouveau les nervures 132 et les dents 142 sont placés par alternance. Les nervures 142 sont en regard de deux dents 132. Les hauteurs radiales de dents sont égales aux hauteurs des nervures.Again the ribs 132 and the teeth 142 are placed alternately. The ribs 142 are opposite two teeth 132. The radial heights of teeth are equal to the heights of the ribs.

Selon l'invention, il est envisageable de réaliser un compresseur mixte, c'est-à-dire qui comprend un ou plusieurs systèmes d'étanchéité selon la figure 3, et un ou plusieurs systèmes d'étanchéité selon la figure 4. Des gorges circulaires (non représentées) peuvent être ajoutées, notamment dans la couche 136.According to the invention, it is conceivable to produce a mixed compressor, that is to say one which comprises one or more sealing systems according to the figure 3 , and one or more sealing systems according to the figure 4 . Circular grooves (not shown) may be added, especially in layer 136.

La figure 5 esquisse un diagramme du procédé de fabrication d'un compresseur de turbomachine. Ce procédé peut être un procédé d'assemblage et/ou de mise en forme. Le compresseur peut correspondre à celui décrit en relation avec les figures 1 et 2, les systèmes d'étanchéité du compresseur étant par exemple suivant les enseignements des figures 3 et/ou 4.The figure 5 sketch a diagram of the manufacturing process of a turbomachine compressor. This process can be a method of assembly and / or shaping. The compressor may correspond to that described in relation to the figures 1 and 2 , the compressor sealing systems being for example according to the teachings of the figures 3 and / or 4.

Le procédé de fabrication du compresseur peut comprendre les étapes suivantes, éventuellement réalisées dans l'ordre qui suit:

  1. (a) fourniture ou réalisation 200 d'une rangée annulaire d'aubes, et montage de ces aubes au carter externe du compresseur ;
  2. (b) fixation 202 d'une virole interne à la rangée annulaire d'aube, ladite virole interne comprenant du matériau abradable ;
  3. (c) ajout 204 d'au moins une ou de plusieurs dents annulaires en matériau abradable à l'intérieur de la virole interne ;
  4. (d) positionnement 206 du matériau abradable de la virole interne autour des nervures annulaires du rotor du compresseur.
The method of manufacturing the compressor may comprise the following steps, possibly carried out in the following order:
  1. (a) supplying or producing 200 an annular array of vanes, and mounting these vanes to the outer casing of the compressor;
  2. (b) attachment 202 of an inner ring to the annular row of blade, said inner ring comprising abradable material;
  3. (c) adding 204 of at least one annular tooth or teeth of abradable material inside the inner ferrule;
  4. (d) positioning 206 of the abradable material of the inner shell around the annular ribs of the compressor rotor.

L'étape (c) ajout 204 peut être une étape de réalisation ou de montage d'une dent à l'intérieur de la virole. L'étape (c) ajout 204 peut comprendre une phase d'application 208 de matériau abradable dans la virole. La phase application 208 peut s'effectuer par moulage, ou collage, ou projection plasma.Step (c) addition 204 may be a step of making or mounting a tooth inside the ferrule. Step (c) addition 204 may comprise an application phase 208 of abradable material in the ferrule. The application phase 208 can be performed by molding, or gluing, or plasma projection.

Par la suite, l'étape (c) ajout 204 comprend une phase d'usinage 210 de l'abradable afin d'y tailler la dent annulaire. L'usinage peut être par tournage, notamment en plaçant la virole sur un mandrin. Dans ce cas, la phase d'application 208 tend à mettre en oeuvre une strate annulaire d'abradable en surépaisseur par rapport aux dents. La matière superflue est taillée pour ne garder que la matière propre aux dents.Subsequently, step (c) addition 204 comprises a machining step 210 of the abradable to cut the annular tooth. The machining can be by turning, in particular by placing the ferrule on a mandrel. In this case, the phase application 208 tends to implement an annular layer of abradable extra thickness relative to the teeth. The superfluous material is cut to keep only the material proper to the teeth.

En alternative ou en complément, la phase d'application 208 d'abradable permet de former directement une ou chaque dent. Eventuellement, une dent présente sa forme définitive, une autre montre un surplus de matière qui est enlevé, par découpe et/ou usinage.Alternatively or in addition, the application phase 208 of abradable can directly form one or each tooth. Possibly, a tooth has its final shape, another shows a surplus of material that is removed, by cutting and / or machining.

Claims (15)

Compresseur (4 ; 6) de turbomachine (2), notamment un compresseur basse pression de turbomachine, le compresseur (4 ; 6) comprenant : - un rotor (12) avec au moins une nervure annulaire (32 ; 132) ; - une rangée annulaire d'aubes statoriques (26) ; - une virole interne (30 ; 130) reliée aux aubes statoriques (26) et comprenant au moins une couche de matériau abradable (36 ; 136) apte à coopérer avec la au moins une nervure annulaire (32 ; 132) du rotor (12); caractérisé en ce que
la virole interne (30 ; 130) comprend au moins une dent annulaire (42 ; 142) réalisée en matériau abradable et s'étendant radialement vers le rotor (12).A turbomachine compressor (4; 6), in particular a turbomachine low pressure compressor, the compressor (4; 6) comprising: - a rotor (12) with at least one annular rib (32; 132); an annular row of stator vanes (26); an inner ferrule (30; 130) connected to the stator vanes (26) and comprising at least one layer of abradable material (36; 136) capable of cooperating with the at least one annular rib (32; 132) of the rotor (12); ; characterized in that
the inner ferrule (30; 130) comprises at least one annular tooth (42; 142) made of abradable material and extending radially towards the rotor (12). Compresseur (4 ; 6) selon la revendication 1, caractérisé en ce que la dent annulaire (42 ; 142) et le rotor (12) comprennent entre eux un premier jeu radial J1, la nervure annulaire (32 ; 132) et la virole interne (30; 130) comprennent entre elles un deuxième jeu radial J2 qui représente entre 50% et 150% du premier jeu radial J1.Compressor (4; 6) according to claim 1, characterized in that the annular tooth (42; 142) and the rotor (12) comprise between them a first radial clearance J1, the annular rib (32; 132) and the inner ferrule (30; 130) comprise between them a second radial clearance J2 which represents between 50% and 150% of the first radial clearance J1. Compresseur (4 ; 6) selon l'une des revendications 1 ou 2, caractérisé en ce que la dureté Vickers de la nervure annulaire (32 ; 132) est supérieure à la dureté Vickers de la dent annulaire (42 ; 142).Compressor (4; 6) according to one of claims 1 or 2, characterized in that the Vickers hardness of the annular rib (32; 132) is greater than the Vickers hardness of the annular tooth (42; 142). Compresseur (4 ; 6) selon l'une des revendications 1 à 3, caractérisé en ce que la dent annulaire (42 ; 142) présente une hauteur radiale égale à la hauteur radiale de la nervure annulaire (32 ; 132).Compressor (4; 6) according to one of claims 1 to 3, characterized in that the annular tooth (42; 142) has a radial height equal to the radial height of the annular rib (32; 132). Compresseur (4 ; 6) selon l'une des revendications 1 à 4, caractérisé en ce que le matériau de la dent annulaire (42) est différent de celui coopérant avec la nervure annulaire (32), et est éventuellement plus friable.Compressor (4; 6) according to one of claims 1 to 4, characterized in that the material of the annular tooth (42) is different from that cooperating with the annular rib (32), and is optionally more friable. Compresseur (4 ; 6) selon l'une des revendications 1 à 5, caractérisé en ce que le matériau abradable de la dent annulaire (142) est le même que celui coopérant avec la nervure annulaire (132) ; lesdits matériaux étant éventuellement venus de matière et/ou formant un ensemble monobloc.Compressor (4; 6) according to one of claims 1 to 5, characterized in that the abradable material of the annular tooth (142) is the same as that cooperating with the annular rib (132); said materials possibly being made of material and / or forming a one-piece assembly. Compresseur (4 ; 6) selon l'une des revendications 1 à 6, caractérisé en ce que le rotor (12) comprend au moins deux rangées annulaires d'aubes rotoriques (24) entre lesquelles est disposée axialement la dent annulaire (42 ; 142), les au moins deux rangées annulaires d'aube rotoriques (24) formant un ensemble monobloc.Compressor (4; 6) according to one of claims 1 to 6, characterized in that the rotor (12) comprises at least two annular rows of rotor blades (24) between which is arranged axially the annular tooth (42; ), the at least two annular rows of rotor blades (24) forming a one-piece assembly. Compresseur (4 ; 6) selon l'une des revendications 1 à 7, caractérisé en ce que la virole interne (30) comprend une surface annulaire interne (44) d'où s'étend radialement la dent annulaire (42), ladite surface interne (44) comprenant une gorge circulaire (50) disposée axialement au niveau de la nervure annulaire (32).Compressor (4; 6) according to one of claims 1 to 7, characterized in that the inner ring (30) comprises an inner annular surface (44) from which radially extends the annular tooth (42), said surface internal member (44) comprising a circular groove (50) arranged axially at the annular rib (32). Compresseur (4 ; 6) selon l'une des revendications 1 à 8, caractérisé en ce que la dent annulaire (42 ; 142) est une première dent annulaire, la virole interne (30 ; 130) comprenant d'autres, éventuellement au moins deux autres, dents annulaires réalisées en matériau abradable et s'étendant radialement vers le rotor (12), les dents annulaires étant éventuellement réparties axialement le long de la virole interne.Compressor (4; 6) according to one of claims 1 to 8, characterized in that the annular tooth (42; 142) is a first annular tooth, the inner ferrule (30; 130) comprising others, possibly at least two others, annular teeth made of abradable material and extending radially towards the rotor (12), the annular teeth possibly being distributed axially along the inner ferrule. Compresseur (4 ; 6) selon l'une des revendications 1 à 9, caractérisé en ce que la nervure annulaire (32 ; 132) est une première nervure, le rotor (12) comprenant en outre au moins une deuxième nervure annulaire, les nervures annulaires et la ou chaque dent annulaire (42 ; 142) formant une alternance.Compressor (4; 6) according to one of claims 1 to 9, characterized in that the annular rib (32; 132) is a first rib, the rotor (12) further comprising at least a second annular rib, the ribs annular and the or each annular tooth (42; 142) forming an alternation. Turbomachine (2), notamment un turboréacteur d'aéronef, comprenant un compresseur (4 ; 6) axial, caractérisée en ce que le compresseur (4 ; 6) est conforme à l'une des revendications 1 à 10, préférentiellement la dent annulaire (42 ; 142) comprend un matériau organique tel un polymère.Turbine engine (2), in particular an aircraft turbojet, comprising an axial compressor (4; 6), characterized in that the compressor (4; 6) is according to one of claims 1 to 10, preferably the annular tooth ( 42; 142) comprises an organic material such as a polymer. Procédé de fabrication d'un compresseur (4 ; 6) de turbomachine, le procédé comprenant les étapes suivantes : (a) fourniture ou réalisation (200) d'une rangée annulaire d'aubes statoriques (26) ; (b) fixation (202) d'une virole interne (30; 130) à la rangée annulaire d'aubes statoriques (26), ladite virole interne (30; 130) comprenant du matériau abradable ; (d) positionnement (206) du matériau abradable de la virole interne (30 ; 130) autour d'une nervure annulaire (32 ; 132) d'un rotor (12) du compresseur (4 ; 6); caractérisé en ce que préalablement à l'étape (d) positionnement (206), il comprend une étape : (c) ajout (204) d'au moins une dent annulaire (42 ; 142) en matériau abradable à l'intérieur de la virole interne (30 ; 130) ; à l'issue de l'étape (d) positionnement (206), le compresseur (4 ; 6) est éventuellement conforme à l'une des revendications 1 à 10. A method of manufacturing a turbomachine compressor (4; 6), the method comprising the steps of: (a) providing or producing (200) an annular row of stator vanes (26); (b) attaching (202) an inner shroud (30; 130) to the annular row of stator vanes (26), said inner shroud (30; 130) comprising abradable material; (d) positioning (206) the abradable material of the inner ferrule (30; 130) around an annular rib (32; 132) of a rotor (12) of the compressor (4; 6); characterized in that prior to step (d) positioning (206), it comprises a step: (c) adding (204) at least one annular tooth (42; 142) of abradable material within the inner ferrule (30; 130); at the end of step (d) positioning (206), the compressor (4; 6) is optionally in accordance with one of claims 1 to 10. Procédé selon la revendication 12, caractérisé en ce que l'étape (c) ajout (204) comprend une phase (208) de moulage, ou de collage, ou de projection plasma de matériau abradable à l'intérieur de la virole interne (30 ; 130).Method according to claim 12, characterized in that the step (c) adding (204) comprises a phase (208) for molding, or gluing, or plasma spraying abradable material inside the inner shell (30). 130). Procédé selon l'une des revendications 12 à 13, caractérisé en ce que l'étape (c) ajout (204) comprend une phase d'usinage (201) de l'abradable afin d'y tailler la dent annulaire (42 ; 142).Method according to one of claims 12 to 13, characterized in that the step (c) addition (204) comprises a machining step (201) of the abradable in order to cut the annular tooth (42; ). Procédé selon l'une des revendications 12 à 14, caractérisé en ce qu'à l'issue de la phase de moulage, ou de collage, l'abradable forme la dent annulaire (42 ; 142).Process according to one of Claims 12 to 14, characterized in that the abradable tooth forms the annular tooth (42; 142) at the end of the molding or bonding phase.
EP18173133.2A 2017-06-02 2018-05-18 Sealing system for a turbine engine compressor Active EP3409902B1 (en)

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CN108979738B (en) 2022-05-31
US10746036B2 (en) 2020-08-18
US20180347579A1 (en) 2018-12-06
EP3409902B1 (en) 2020-02-19
CN108979738A (en) 2018-12-11
BE1025283A1 (en) 2019-01-04
BE1025283B1 (en) 2019-01-11

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