EP3409902B1 - Abdichtungssystem für kompressor einer strömungsmaschine - Google Patents

Abdichtungssystem für kompressor einer strömungsmaschine Download PDF

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Publication number
EP3409902B1
EP3409902B1 EP18173133.2A EP18173133A EP3409902B1 EP 3409902 B1 EP3409902 B1 EP 3409902B1 EP 18173133 A EP18173133 A EP 18173133A EP 3409902 B1 EP3409902 B1 EP 3409902B1
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EP
European Patent Office
Prior art keywords
annular
compressor
rotor
tooth
rib
Prior art date
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Active
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EP18173133.2A
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English (en)
French (fr)
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EP3409902A1 (de
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/de
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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
    • 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
    • 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
    • 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 the level of an internal shroud.
  • the invention also relates to an axial turbomachine, such as an aircraft turbojet or an aircraft turboprop.
  • the invention also provides a method of manufacturing a compressor.
  • the compression ratio at the outlet of a turbojet compressor depends on the tightness between the ferrules and the rotor. This tightness must adapt to vibrations as well as ingestion when it is a low pressure compressor. The centrifugal force and the expansion remain constraints which are added to the previous ones.
  • each internal ferrule or each internal 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 vane positioned in said opening for its attachment.
  • the wall comprises a radial flange which crosses the openings in the circumferential direction of the ferrule or of the ferrule segment, so as to form a mechanical link within each opening to link the opposite edges.
  • the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to be able to reduce leaks in a compressor. The invention also aims to propose a simple, resistant, light, economical, reliable solution, easy to produce, convenient to maintain, easy to inspect, and improving performance.
  • the subject of the invention is a turbomachine compressor, in particular a low pressure turbomachine compressor, the compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an internal ferrule connected to the stator vanes and comprising at least one layer of abradable material capable of cooperating with the at least one annular rib of the rotor in order to ensure sealing; remarkable in that the internal 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 internal 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 radial clearances measured axially at the level 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, 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 of manufacturing a turbomachine compressor, the method comprising the following steps: (a) supplying or producing an annular row of stator vanes; (b) fixing an internal ferrule to the annular row of stator vanes, said internal ferrule comprising abradable material; (d) positioning the abradable material of the internal ferrule around an annular rib of a rotor of the compressor; remarkable in that, prior to step (d) positioning, it comprises a step (c) adding at least one annular tooth made of abradable material inside the internal ferrule, at the end of step (d ) positioning, the compressor may be in accordance with the invention.
  • step (c) addition comprises a molding phase, or bonding, 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 includes a machining phase of the abradable in order to cut the annular tooth there.
  • the abradable material forms 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 can be combined with the other objects, and the objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another, according to all possible technical combinations, unless the opposite be explicitly stated.
  • the invention makes it possible to create other wipers on board by the internal ferrule. Their presence brings an effect which is added to that of the rotor, by amplifying the vortices under the ferrule to slow secondary flows. The seal is improved without penalizing the inertia of the rotor.
  • 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 in order to limit wear of the latter.
  • the figure 1 represents in a simplified manner an axial turbomachine.
  • the turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 4, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first level of compression called a low-pressure compressor 4
  • a second level of compression called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.
  • An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various 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-vetted 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 flows are annular coaxial flows which are fitted one inside the other. They are channeled through the casing of the turbomachine and / or of the ferrules.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 4.
  • One can observe there 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 one-piece drum. It forms a solid connecting all its rows of blades.
  • one, or more, or each of the rows of rotor blades 24 is rigidly linked to the rotor, and therefore to the drum if necessary.
  • the rotor blades are fixed by dovetail.
  • 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 essentially radially from an external casing 28, and can be fixed and immobilized therein using pins.
  • the casing 28 can be formed from two half-shells.
  • the rows of stator vanes 26 support internal ferrules 30 whose external surfaces guide the primary flow 18.
  • the internal ferrules 30 may have a profile of revolution around the axis of rotation 14. They provide dynamic seals with the rotor 12 , especially in combination with its annular ribs, commonly called wipers. They minimize leaks in the sense that they allow approximation with the rotor, said approximation closing the mechanical clearances in operation.
  • a ferrule and a rotor portion 12 can form a sealing system.
  • the figure 3 outlines a sealing system such as those of the figure 2 .
  • the following are visible: a stator blade 26 representative of its row, an axial section of rotor 12, and an internal ferrule 30.
  • the ferrule 30 can be segmented. It can be made of composite material with an organic matrix reinforced by fibers. The system is shown here 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 outwards 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 internal ferrule 30, in particular facing radially layers of dedicated abradable material 36. These layers 36 can be housed in the radial thickness of the annular wall 38 of the internal 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 internal surface 44 of the shell 30 The teeth 42 protrude from this internal surface 44.
  • the teeth 42 can be distributed axially along the length of the ferrule 30, possibly homogeneously. That upstream can be axially, or upstream, from the leading edge 46 of the blade 26. That downstream can be axially, or downstream, from the trailing edge 48 of the blade 26.
  • the teeth 42 and the ribs 32 form an alternation, so that they contain annular chambers between the rotor 12 and the ferrule 30; said chambers see their circular edges close in operation, hence improving the seal, 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 can overlap radially, possibly over the majority of their respective radial heights. Their axial faces, possibly flat or substantially conical, are opposite axially.
  • the teeth 42 and the ribs 32 can be of equal or similar heights, that is to say with a difference of at most: 10%, or 5%.
  • the one or more or each set J1 remaining radially between one of the teeth 42 and the rotor 12, more precisely between one of the teeth 42 and the casing 34, can be equal to at least one, or more, or each set J2 between the ferrule 38 and one of the ribs 32.
  • all the sets 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 either side, 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 opposite the ribs 32. Thus, different properties can be chosen.
  • the first abradable material, used in the teeth 42 can be softer than the second which is present in the layers 36. This preserves the rotor 12.
  • These materials can be elastomers, possibly with concentrations of spheres different hollows, or different fill contents.
  • the teeth can be softer than the ribs.
  • the ribs can 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 can be axially thinner than the teeth 42. This optimizes the occupation under the shell, optimizes the rotating mass and the mechanical strength.
  • the internal 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 from the teeth 42, in particular from the internal surface 44. This allows better closing of the games in operation.
  • Each clearance J2 can be measured against the bottom of the corresponding groove 50.
  • the grooves 50 are formed in the layers 36.
  • the figure 4 shows a sealing system according to a second embodiment of the invention.
  • This figure 4 uses the numbering of the previous figures for identical or similar elements, the number being however incremented by 100. Specific numbers are used for the elements specific to 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 layer of abradable 136 which also cooperates with the ribs 132. The latter is carried by the wall 138 of the internal ferrule 130, and forms the internal 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 depending on the figure 4 .
  • Circular grooves can be added, in particular in layer 136.
  • the figure 5 sketch a diagram of the manufacturing process of a turbomachine compressor.
  • This process can be an assembly and / or shaping process.
  • the compressor can correspond to that described in relation to the figures 1 and 2 , the compressor sealing systems being for example according to the teachings of figures 3 and / or 4.
  • Step (c) addition 204 can be a step of making or mounting a tooth inside the ferrule.
  • Step (c) addition 204 may include a phase 208 of application of abradable material in the shell.
  • the application phase 208 can be carried out by molding, or gluing, or plasma spraying.
  • step (c) addition 204 comprises a machining phase 210 of the abradable in order to cut the annular tooth there.
  • the machining can be by turning, in particular by placing the ferrule on a mandrel.
  • the phase 208 application tends to implement an annular layer of abradable in excess thickness relative to the teeth. The superfluous material is cut to keep only the material clean for the teeth.
  • the abradable application phase 208 makes it possible to directly form one or each tooth.
  • one tooth has its final shape, another shows a surplus of material which 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)

Claims (15)

  1. Kompressor (4; 6) einer Turbomaschine (2), vorzugsweise ein Turbomaschinen-Niederdruckkompressors, wobei der Kompressor (4; 6) Folgendes umfasst:
    - einen Rotor (12) mit mindestens einer ringförmigen Rippe (32; 132);
    - eine ringförmige Reihe von Statorschaufeln (26);
    - eine innere Verkleidung (30; 130), die mit den Statorschaufeln (26) verbunden ist und mindestens eine Schicht abriebfähiges Material (36; 136) enthält, die in der Lage ist, mit mindestens einer ringförmigen Rippe (32; 132) des Rotors (12) zusammenzuwirken;
    dadurch gekennzeichnet, dass
    die innere Verkleidung (30; 130) aus mindestens einem ringförmigen Zahn (42; 142) aus abriebfähigem Material besteht und sich radial zum Rotor (12) erstreckt.
  2. Kompressor (4; 6) nach Anspruch 1, dadurch gekennzeichnet, dass der ringförmige Zahn (42; 142) und der Rotor (12) zwischen sich ein erstes radiales Spiel J1 aufweisen und die ringförmige Rippe (32; 132) und die innere Verkleidung (30; 130) zwischen sich ein zweites radiales Spiel J2 aufweisen, das zwischen 50% und 150% des ersten radialen Spiels J1 darstellt.
  3. Kompressor (4; 6) nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Vickershärte der ringförmigen Rippe (32; 132) größer ist als die Vickershärte des ringförmigen Zahns (42; 142).
  4. Kompressor (4; 6) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der ringförmige Zahn (42; 142) eine radiale Höhe aufweist, die gleich der radialen Höhe der ringförmigen Rippe (32; 132) ist.
  5. Kompressor (4; 6) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass sich das Material des ringförmigen Zahns (42) von dem mit der ringförmigen Rippe (32) zusammenwirkenden Material unterscheidet und möglicherweise brüchiger ist.
  6. Kompressor (4; 6) nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das abriebfähige Material des ringförmigen Zahns (142) dasselbe ist wie das Material, das mit der ringförmigen Rippe (132) zusammenwirkt; wobei die Materialien potentiell einteilig sind und/oder eine einteilige Einheit bilden.
  7. Kompressor (4; 6) nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Rotor (12) mindestens zwei ringförmige Reihen von Rotorblättern (24) aufweist, zwischen denen der ringförmige Zahn (42; 142) axial angeordnet ist, wobei mindestens zwei ringförmige Reihen von Rotorblättern (24) eine einteilige Anordnung bilden.
  8. Kompressor (4; 6) nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die innere Verkleidung(30) eine innere ringförmige Fläche (44) aufweist, von der sich der ringförmige Zahn (42) radial erstreckt, wobei diese innere Fläche (44) eine kreisförmige Nut (50) umfasst, die axial an der Position der ringförmigen Rippe (32) angeordnet ist.
  9. Kompressor (4; 6) nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der ringförmige Zahn (42; 142) ein erster ringförmiger Zahn ist, die innere Verkleidung (30; 130) anderen, möglicherweise mindestens zwei anderen ringförmigen Zähnen umfasst, die aus abriebfähigen Material bestehen und sich radial zum Rotor (12) erstrecken, wobei die ringförmigen Zähne möglicherweise axial entlang der inneren Verkleidung verteilt sind.
  10. Kompressor (4; 6) nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die ringförmige Rippe (32; 132) eine erste Rippe ist, wobei der Rotor (12) ferner mindestens eine zweite ringförmige Rippe umfasst, wobei die ringförmigen Rippen und der oder jeder ringförmige Zahn (42; 142) sich abwechseln.
  11. Turbomaschine (2), vorzugsweise ein Flugzeugturbojet-Triebwerk, umfassend einen Axialkompressor (4; 6), dadurch gekennzeichnet, dass der Kompressor (4; 6) einem der Ansprüche 1 bis 10 entspricht, und vorzugsweise der ringförmige Zahn (42; 142) ein organisches Material wie ein Polymer enthält.
  12. Verfahren zur Herstellung eines Turbomaschinen-Kompressors (4; 6) mit folgenden Schritten:
    (a) Bereitstellen oder Erzeugen (200) einer ringförmigen Reihe von Statorschaufeln (26);
    (b) Anbringen (202) einer inneren Verkleidung (30; 130) an der ringförmigen Reihe von Statorschaufeln (26), wobei die innere Verkleidung (30; 130) ein abriebfähiges Material aufweist;
    (d) Positionieren (206) des abriebfähigen Materials der inneren Verkleidung (30; 130) um eine ringförmige Rippe (32; 132) eines Rotors (12) des Kompressors (4; 6);
    dadurch gekennzeichnet, dass es vor dem Schritt (d) des Positionierens (206) einen Schritt umfasst:
    (c) Hinzufügen (204) mindestens eines ringförmigen Zahns (42; 142) aus abriebfestem Material innerhalb der inneren Verkleidung (30; 130); am Ende von Schritt (d) des Positionierens (206) erfüllt der Kompressor (4; 6) möglicherweise einen der Ansprüche 1 bis 10.
  13. Verfahren nach Anspruch 12, dadurch gekennzeichnet, dass der Schritt (c) des Hinzufügens (204) eine Phase (208) des Formens, Klebens oder Plasmaspritzens von abriebfähigem Material in die innere Verkleidung (30; 130) umfasst.
  14. Verfahren nach einem der Ansprüche 12 und 13, dadurch gekennzeichnet, dass der Schritt (c) des Hinzufügens (204) eine Phase (201) des Bearbeitens des abriebfähigen Materials umfasst, um den ringförmigen Zahn (42; 142) hineinzuschneiden.
  15. Verfahren nach einem der Ansprüche 12 bis 14, dadurch gekennzeichnet, dass das abriebfähige Material am Ende der Formungs- oder Klebephase den ringförmigen Zahn (42; 142) bildet.
EP18173133.2A 2017-06-02 2018-05-18 Abdichtungssystem für kompressor einer strömungsmaschine Active EP3409902B1 (de)

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FR3088671B1 (fr) * 2018-11-16 2021-01-29 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091725B1 (fr) * 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine

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BE1025283A1 (fr) 2019-01-04
US20180347579A1 (en) 2018-12-06
EP3409902A1 (de) 2018-12-05
US10746036B2 (en) 2020-08-18
CN108979738A (zh) 2018-12-11
CN108979738B (zh) 2022-05-31
BE1025283B1 (fr) 2019-01-11

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