EP3444443B1 - Zusammensetzung einer anstreifdichtung für den kompressor einer turbomaschine - Google Patents

Zusammensetzung einer anstreifdichtung für den kompressor einer turbomaschine Download PDF

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Publication number
EP3444443B1
EP3444443B1 EP18186069.3A EP18186069A EP3444443B1 EP 3444443 B1 EP3444443 B1 EP 3444443B1 EP 18186069 A EP18186069 A EP 18186069A EP 3444443 B1 EP3444443 B1 EP 3444443B1
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EP
European Patent Office
Prior art keywords
composition
phase
abradable
turbomachine
compressor
Prior art date
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Active
Application number
EP18186069.3A
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English (en)
French (fr)
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EP3444443A1 (de
Inventor
Laurent Schuster
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D11/125—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 with a reinforcing structure
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular 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
    • 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
    • F05D2230/30—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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/132—Chromium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2282—Nitrides of boron
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]

Definitions

  • the invention relates to the field of turbomachine sealing by abradable two-phase seal.
  • the invention also provides a method of producing an abradable seal.
  • the invention also relates to a compressor and an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
  • the document EP3023511A1 discloses a composition for abradable gasket of a turbomachine, the composition comprising an aluminum base, nickel powder, polyester powder. It also teaches an external low-pressure compressor housing for an axial turbomachine with an abradable seal surrounding an annular row of rotor blades.
  • the joint comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly of aluminum, and with nickel in a lesser proportion.
  • the abradable material further comprises 25% and 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride.
  • the support is segmented, and forms an external casing organic matrix composite of the compressor. However, the characteristics of such a seal can be improved. Furthermore, the application of the seal remains complex.
  • EP 1,428,600 describes an abradable with an organic / mineral phase and a metallic aluminum phase. The particular mechanical characteristics of such a seal can be improved.
  • the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the friable nature of the joint. The invention also aims to provide a simple, resistant, light, economical, reliable, easy to produce, convenient maintenance, easy inspection, and performance improving solution.
  • the subject of the invention is a composition according to claim 1.
  • the subject of the invention is a composition for an abradable gasket for a turbomachine, in particular in powder form, said gasket being able to crumble in the event of contact with a rotor of said turbomachine, the composition comprising : a metallic phase with a majority by weight of aluminum, a second phase comprising an inorganic material and / or an organic material; remarkable in that the metallic phase represents between 80% and 90% of the mass of the composition, and / or represents at least: 81%, or 82% or 83% of the mass of the composition.
  • the subject of the invention is a composition for an abradable gasket for a turbomachine, in particular in powder form, said gasket being able to crumble in the event of contact with a rotor of said turbomachine, the composition comprising : a metallic phase with a majority by weight of aluminum, a second phase comprising an inorganic material and / or an organic material; remarkable in that the mineral material represents: from 10% to 45%, or from 10% to 25% of the mass of the composition.
  • the invention also relates to a composition for an abradable gasket for a turbomachine, in particular in powder form, said gasket being able to crumble in the event of contact with a rotor of said turbomachine, the composition comprising: a metallic phase with a majority by weight of aluminum, a second phase comprising an inorganic material and / or an organic material; remarkable in that the organic material represents: from 10% to 45%, or from 10% to 25% of the mass of the composition.
  • the invention also relates to a composition for an abradable gasket for a turbomachine, in particular in powder form, said gasket being able to crumble in the event of contact with a rotor of said turbomachine, the composition comprising: a metallic phase with a majority of aluminum by mass, a second phase; remarkable in that the second phase comprises at least one of the following materials: polyimide, polyamide-imide, polyether-imide, bismaleimide, fluoroplastic, a ketone-based resin, polymer liquid crystals, disulfide of molybdenum, graphite, talc, bentonite, mica; or any workable combination.
  • the invention also relates to a turbomachine compressor, in particular a low-pressure turbomachine compressor, comprising a rotor with rotor blades and an abradable seal cooperating in leaktight manner with said rotor blades, remarkable in that the abradable seal comprises a composition in accordance with the invention.
  • the invention also relates to a turbomachine, in particular a turbojet engine, comprising an abradable seal, remarkable in that the composition of the abradable seal is in accordance with the invention, the turbomachine optionally comprises a compressor in accordance with the invention.
  • the invention also relates to a method for producing an abradable gasket for a turbomachine, in particular a turbojet, the gasket having an arcuate wall and an abradable composition applied against the arcuate wall, the method comprising the following steps: (a) providing or making an arcuate wall; (f) application by thermal spraying of an abradable seal composition against the arcuate wall, said composition comprising a majority of aluminum in a metallic phase, and a second phase; remarkable in that in step (f) application, the metallic phase also comprises nickel, optionally at the start and / or at the end of step (f) application the composition is in accordance with the invention.
  • the composition is applied by plasma spraying.
  • 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 is not explicitly mentioned.
  • the presence of chromium in the abradable composition provides better anchoring on a support.
  • cohesion with the metal strip is improved, in particular bonded to a composite casing with an organic matrix.
  • the brittle behavior of the abradable which results from it after plasma spraying increases. This is notably due to a better mixing of the metal portion and the second portion.
  • Each of them forms grains of reduced size compared to the state of the art. The geometry and the surfaces of the grains eventually show better interpenetration.
  • 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 a rotor element of a turbomachine. This material may be suitable for concentrating wear and deformation therein while preserving the integrity of the rotor.
  • 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 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 and fitted one inside the other. They are channeled through the casing of the turbomachine and / or of the ferrules.
  • the casing has cylindrical walls 21 which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low pressure compressor 4.
  • a portion of the fan 16 and the separation nozzle 22 for the primary flow 18 and the secondary flow 20 can be observed there.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three.
  • the low-pressure compressor 4 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26. Some stator vanes can have an adjustable orientation, also called variable pitch vanes.
  • the rectifiers are associated with the fan 16 or with a row of rotor blades to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.
  • the compressor 4 may comprise an external casing 28. This may include an arcuate wall 30. This wall 30 may describe a closed monobloc loop around the axis of rotation 14, or be formed of half-shells, or even of half - circles.
  • the casing 28, and in particular its wall 30 can be made of a composite material with an organic matrix.
  • the matrix can be reinforced with fibers, possibly in the form of a preform.
  • the reinforcement may include fibrous plies, for example with carbon fibers or glass fibers.
  • the stator vanes 26 extend essentially radially from the wall 30, and can be fixed and immobilized therein using pins 32.
  • the stator vanes 26 comprise fixing platforms 34, which optionally receive the axes of fixing 32. Both the blades and the platforms can be made of titanium.
  • the stator via its housing 28, receives at least one annular seal 36, optionally an annular seal 36 around each annular row of rotor blades 24.
  • At least one or more or each annular seal 36 can be an abradable seal with an annular layer of abradable material 38.
  • the seals are abradable seal 36, they participate in the reduction of leaks by allowing a bringing together between the blades 24 and the casing 28. .
  • internal ferrules 40 are connected to the internal ends of the stator vanes 26. These ferrules 40 can also receive an abradable seal as described in the present invention, and cooperating with the rotor 12 in a sealed manner.
  • the figure 3 shows an abradable compressor seal 36 such as that of the figure 2 .
  • an abradable compressor seal 36 such as that of the figure 2 .
  • a wall 34 of housing 28, or support 28 an abradable layer 38 of seal 36 which is applied thereto, and an end of rotor blade 24 between two stator blades 26.
  • the abradable layer 38 extends from a platform 34 of blade 26 to the other, which belongs to a neighboring row arranged upstream or downstream. At least one or each abradable seal may be in contact with the material of the blade platforms, possibly in electrical contact.
  • the abradable layer 38 can be applied to the same wall 30 of the casing 28.
  • the seal 36 can comprise an intermediate layer between the support and the abradable layer 38.
  • the intermediate layer can be a strip 42, such as a sheet of metal. steel, or a sheet of nickel.
  • the strip 42 can be perforated and / or cut. It can be of constant thickness.
  • the abradable layer 38 can be thicker than the strip 42.
  • the strip 42 can be glued to the wall 30, and / or be maintained thanks to the platforms 34 of the blades 26.
  • the upstream and / or downstream edges of the strip 42 are pinched between the platforms 34 and the wall 30.
  • the abradable layer 38 has an internal surface 44 in contact with the primary flow 18. Its surface 44 guides and delimits the primary flow 18 during its compression. It can be flush with the internal surfaces of the platforms 34.
  • the composition of the material forming the abradable layer 38 and therefore the seal 36 can comprise at least two mixed phases, namely a metallic phase and a second phase.
  • the second phase can be mineral and / or organic.
  • the abradable can be composite; and / or granular; and / or with spaces filled with some of its constituents.
  • the second phase can form a lubricant.
  • the metallic phase mainly comprises aluminum.
  • the metallic phase of the composition is aluminum based. That is to say that among the metals of the abradable, the one whose mass is the most important is aluminum.
  • the preponderance of aluminum optimizes the mass of the seal 36.
  • the metallic phase may also include chromium, in a mass proportion lower than that of aluminum.
  • the metallic phase can comprise between 20% and 45% of chromium; and between 55% and 80% aluminum.
  • Aluminum and chromium can be the only two metals, each of whose masses represents at least 0.10%, or at least 1% of the mass of the composition.
  • the metallic phase can consist of aluminum and chromium.
  • the metallic phase can also comprise nickel, in particular in a mass proportion lower than that of chromium, for example twice lower.
  • the metallic phase can comprise, by mass, 10% of chromium and / or 5% of nickel; or, by mass, 30% chromium and 10% nickel.
  • the metallic phase may optionally include iron, copper, zinc, manganese, magnesium, impurities; these components representing each or in all between 1% and 0.1% of the mass of the metallic phase.
  • the organic material of the second phase of the composition can comprise polymer, such as polyester, polyimide, polyamide-imide, polyether-imide, bismaleimide, fluoroplastic, a ketone-based resin, liquid crystals of polymers; or all of their possible combinations.
  • polymer such as polyester, polyimide, polyamide-imide, polyether-imide, bismaleimide, fluoroplastic, a ketone-based resin, liquid crystals of polymers; or all of their possible combinations.
  • the second phase can also include hexagonal boron nitride, calcium fluoride, molybdenum disulfide, graphite, talc, bentonite, mica; or all of their possible combinations. These materials can be considered as mineral materials.
  • the second phase can comprise a mixture of at least one mineral material with at least one organic material.
  • the mass of the second phase can represent: from 5% to 50%, or from 15% to 25%, possibly 20% of the mass of the composition.
  • the metallic phase can represent the majority of the volume of the abradable layer, thus, the metallic phase can form there a matrix receiving the second phase.
  • the abradable layer can be formed of grains of metal powders whose inter-grain spaces are filled by the second phase.
  • the void space in the abradable layer is less than 1%, preferably less than 0.1%.
  • the figure 4 represents a diagram of a process for producing an abradable seal for an axial turbomachine as presented in figures 2 and / or 3.
  • the seal can be used on a compressor, in particular low-pressure, as detailed in relation to the figures 1 and / or 2.
  • the composition has a metallic phase with mainly aluminum, for example in the form of a powder.
  • Aluminum can be pure, or in the form of an alloy. The same applies to chromium.
  • the composition can also comprise chromium and optionally a second metal; both in powders.
  • the mass of chromium represents at least: 20%, or 21%, or 22%, or 23% of the metallic phase.
  • the composition of the powder can correspond to the chemical composition of the abradable layer presented above.
  • step (f) application 110 At the end of step (f) application 110, at least one or each compound of the composition remains in powder form, or at least one of the compounds has melted, or each compound has melted.
  • each type of grain of powder is essentially full.
  • Each grain can form a homogeneous material.
  • one type of grain is hollow, for example aluminum or chromium grains.
  • the composition can be applied to the casing, therefore against the arcuate wall, by plasma spraying.
  • plasma spraying Such a thermal technique is well known to those skilled in the art, it can be carried out in a similar manner to that disclosed in the document EP 1 010 861 A2 .
  • the powder of the second phase can be introduced into the plasma jet downstream of the metal powders.
  • Other techniques are possible.
  • the composition can be applied to the support by sintering, optionally with prolonged heating. In this alternative, some grains can keep their original shapes.
  • the stages: (b) supply 102 of stator vanes; (c) supply or manufacture 104 of a strip; (d) placing the strip 106 against the casing, in particular against the internal surface of the arcuate wall; (e) fixing 108 of the blades; are entirely optional according to the invention.
  • the abradable composition can be applied on a support free of blades and / or free of strip.
  • step (f) application 110 can be carried out in a groove formed in the thickness of the arcuate wall; and / or directly on the internal surface of the arcuate wall.
  • composition can apply to the joint, and vice versa.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (15)

  1. Zusammensetzung für eine abreibbare Dichtung (36) einer Turbomaschine (2), insbesondere in Pulverform, wobei die Dichtung (36) im Falle eines Kontakts mit einem Rotor (12) der Turbomaschine (2) zerbröckeln kann, wobei die Zusammensetzung Folgendes umfasst:
    - eine metallische Phase mit einer Massenmehrheit von Aluminium,
    - eine zweite Phase, die ein mineralisches Material und/oder ein organisches Material enthält;
    dadurch gekennzeichnet ist, dass
    die Metallphase außerdem Chrom und Nickel enthält, wobei die Metallphase mehr Masse Chrom als Nickel enthält.
  2. Zusammensetzung nach Anspruch 1, dadurch gekennzeichnet, dass die metallische Phase von 20 % bis 45 % Masse Chrom enthält.
  3. Zusammensetzung nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass das organische Material Polyester und das anorganische Material hexagonales Bornitrid enthält.
  4. Zusammensetzung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Metallphase 82 % bis 90 % der Masse der Zusammensetzung ausmacht.
  5. Zusammensetzung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die zweite Phase 10 % bis 25 % der Masse der Zusammensetzung ausmacht.
  6. Zusammensetzung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die zweite Phase mindestens eines der folgenden Materialien enthält: Polyimid, Polyamidimid, Polyetherimid, Bismaleimid, Fluorkunststoff, Harz auf Ketonbasis, polymere Flüssigkristalle; oder eine beliebige Kombination daraus.
  7. Zusammensetzung nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die zweite Phase mindestens eines der folgenden Materialien enthält: Molybdändisulfid, Graphit, Talkum, Bentonit, Glimmer; oder eine beliebige Kombination daraus.
  8. Kompressor (4; 6) einer Turbomaschine (2), insbesondere ein Niederdruckkompressor einer Turbomaschine (2), mit einem Rotor (12) mit Rotorschaufeln (24) und einer abreibbaren Dichtung (36), die mit den genannten Rotorschaufeln (24) abdichtend zusammenwirkt, dadurch gekennzeichnet, dass die abreibbare Dichtung (36) eine Zusammensetzung nach einem der Ansprüche 1 bis 7 aufweist.
  9. Kompressor (4; 6) nach Anspruch 8, dadurch gekennzeichnet, dass der Kompressor eine Wand (30) mit organischer Matrix umfasst, auf der die abreibbare Dichtung (36) angeordnet ist sowie eine Grenzfläche zwischen der Wand (30) und der abreibbaren Dichtung (36), die durch einen Metallstreifen (42) gebildet wird.
  10. Kompressor (4; 6) nach einem der Ansprüche 8 bis 9, dadurch gekennzeichnet, dass die Rotorschaufeln (24), die abdichtend mit der abreibbaren Dichtung (36) zusammenwirken, aus Titan hergestellt sind.
  11. Kompressor (4; 6) nach einem der Ansprüche 8 bis 10, dadurch gekennzeichnet, dass die Rotorschaufeln (24) so ausgelegt sind, dass sie mit Überschallgeschwindigkeit arbeiten.
  12. Kompressor (4; 6) nach einem der Ansprüche 8 bis 11, dadurch gekennzeichnet, dass die radiale Dicke der abreibbaren Dichtung (36) größer oder gleich der mittleren Dicke der Rotorblätter (24) und/oder größer oder gleich 3,00 mm ist.
  13. Turbomaschine (2), insbesondere ein Turbostrahltriebwerk, mit einer abreibbaren Dichtung (36), dadurch gekennzeichnet, dass die Zusammensetzung der abreibbaren Dichtung (36) einem der Ansprüche 1 bis 7 entspricht, wobei die Turbomaschine (2) gegebenenfalls einen Kompressor (4; 6) aufweist, der einem der Ansprüche 8 bis 12 entspricht.
  14. Verfahren zur Herstellung einer abreibbaren Dichtung (36) für eine Turbomaschine (2), insbesondere für ein Turboluftstrahltriebwerk, wobei die Dichtung (36) eine bogenförmige Wand (30) und eine an die bogenförmige Wand (30) aufgebrachte abreibbare Zusammensetzung aufweist, wobei das Verfahren die folgenden Schritte umfasst:
    (a) Lieferung oder Bau (100) einer gewölbten Wand (30);
    (f) Auftragen (110) einer abreibbaren Dichtungs-Zusammensetzung (36) an die bogenförmige Wand (30) durch thermisches Spritzen, wobei die Zusammensetzung eine Mehrheit von Aluminium in einer metallischen Phase und eine zweite Phase umfasst;
    dadurch gekennzeichnet, dass in Schritt (f) Auftragen (110) die metallische Phase unter anderem Nickel enthält,
    die Zusammensetzung wahlweise zu Beginn und/oder am Ende von Schritt (f) Auftragen (110) einem der Ansprüche 1 bis 7 entspricht.
  15. Verfahren nach Anspruch 14, dadurch gekennzeichnet, dass in Schritt (f) Auftragen (110) die Zusammensetzung durch Plasmaspritzen aufgetragen wird.
EP18186069.3A 2017-08-14 2018-07-27 Zusammensetzung einer anstreifdichtung für den kompressor einer turbomaschine Active EP3444443B1 (de)

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BE1027280B1 (fr) * 2019-05-16 2020-12-15 Safran Aero Boosters Sa Carter de compresseur pour turbomachine
CN111155120A (zh) * 2019-12-31 2020-05-15 中山市皓祥模具五金有限公司 一种耐腐蚀合金件的表面处理方法
US11674210B2 (en) 2020-08-31 2023-06-13 Metal Improvement Company, Llc Method for making high lubricity abradable material and abradable coating
CN112210743A (zh) * 2020-09-30 2021-01-12 美图（福建）铝业有限公司 一种铝合金型材及其制造方法
WO2024099721A1 (fr) 2022-11-09 2024-05-16 Safran Aero Boosters Composition pour joint abradable de turbomachine

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BE1025469A1 (fr) 2019-03-11
US20190048454A1 (en) 2019-02-14
JP2019052637A (ja) 2019-04-04
CN109386315B (zh) 2022-08-09
EP3444443A1 (de) 2019-02-20
CN109386315A (zh) 2019-02-26
JP7349778B2 (ja) 2023-09-25

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