Classifications

• • 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
  • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
  • C23C4/11—Oxides
• • 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
• • 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
  • C23C4/04—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
• • 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
• • 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
  • C23C4/123—Spraying molten metal
• • 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
  • C23C4/129—Flame 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
  • F05D2230/30—Manufacture with deposition of material
  • F05D2230/31—Layer deposition
  • F05D2230/311—Layer deposition by torch or flame 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/611—Coating

Definitions

• This presentation relates to an abradable coating for a turbomachine as well as a turbomachine module and a turbomachine comprising such an abradable coating.
• Such an abradable coating can be used in any type of turbomachine, and in particular civil or military turbojets. In particular, it is particularly useful in environments subject to very high temperatures.
• Such abradable tracks can also be provided at the interface between the rotor and the stator fixed vanes in order to reduce air leakage also at this level.
• a conventional way of making such an abradable material is to include in a matrix, metallic for example, porosities which will reduce the tenacity of the coating.
• porosities can for example be created by incorporation and then pyrolysis of polyester fillers.
• these porosities result in significant surface roughness, which increases the coefficient of aerodynamic friction in the boundary layer and therefore leads to performance losses.
• abradable coating takes the form of a metallic honeycomb structure.
• this type of coating is more resistant to high temperatures, it suffers from an abradability which leads to strong heating on contact as well as unwanted wear of the rotor.
• turbomachine as well as a turbomachine module and a turbomachine comprising such an abradable coating, devoid, at least in part, of the drawbacks inherent in the aforementioned known configurations.
• the present disclosure relates to an abradable coating for a turbomachine, comprising, with a content greater than 50% by volume, an inorganic compound whose Mohs hardness is less than 6 and whose melting temperature is greater than 900 ° C ° C. , preferably above 1000 ° C.
• the term “mineral compound” is understood to mean a solid compound having an ordered atomic structure and a defined chemical composition.
• such an inorganic compound can have a crystalline structure characterized by the arrangement of its atoms according to a given periodicity and symmetry (crystal system and space group of the mineral compound).
• such an inorganic compound has an intrinsic abradable nature such that it is unnecessary to artificially incorporate porosities within the coating. Therefore, the surface roughness of the coating remains substantially the same, including after it has been scraped during operation of the
• the abrasion debris is inert, which reduces its impact on the downstream side of the turbomachine.
• Such a coating reduces the risk of clogging of the cooling channels of the module.
• the content of said mineral compound is greater than 55% by volume, preferably greater than 60% by volume.
• the abradable coating has a porosity of less than 15%.
• porosity is understood to mean the ratio between the volume of the voids present in the material and the total volume of the material. Thanks to such reduced porosity, the roughness of the coating is reduced, even in the absence of surface treatment, which limits aerodynamic losses.
• the surface roughness Ra is less than 3 ⁇ m.
• the inorganic compound is stable at least up to 900 ° C and preferably up to 1000 ° C.
• stable is meant that the compound does not undergo a change in physical state (fusion or phase transformation for example) or chemical transformation (oxidation for example) when it is brought to the temperature in question from room temperature. .
• the mineral compound comprises a
• alkaline earth element preferably Calcium.
• the mineral compound is chosen from:
• the inorganic compound constitutes at least 95% by volume, preferably at least 99% by volume, of the material of the abradable coating.
• the abradable coating is not limited to:
• This metallic compound forms a matrix for the mineral compound. This improves the resistance to erosion of the coating.
• this metallic compound is chosen according to the application temperature.
• the metal compound is based on Nickel, Cobalt or Iron.
• the metal compound is chosen from:
• the inorganic compound and the metal compound together constitute at least 95% by volume, preferably at least 99% by volume, of the material of the abradable coating.
• This presentation also relates to a turbomachine module
• At least one abradable coating according to any one of the preceding embodiments provided at the interface between a portion of the rotor and a portion of the stator.
• At least one abradable coating of this type forms an abradable track provided on a stator ferrule, facing the moving blades of the rotor.
• the stator is provided with a plurality of fixed vanes.
• At least one abradable coating of this type forms an abradable track provided at the inner end of the fixed blades of the stator, opposite the wipers carried by the rotor.
• the module is a high-pressure compressor or a low-pressure turbine for a turbomachine.
• This disclosure also relates to a turbomachine, comprising a module according to any one of the preceding embodiments.
• Figure 1 is an axial sectional view of a turbomachine according to the disclosure.
• Figure 2 is a sectional view of a module according to the disclosure.
• Figure 3 is a photograph illustrating the microstructure of a
• Figure 4 is a graph illustrating the aerodynamic losses within a module as a function of the roughness of the abradable coating.
• Figure 5 schematically illustrates an abradability test.
• Figure 1 shows, in section along a vertical plane passing through its main axis A, a bypass turbojet 1, constituting an example of a turbomachine according to the disclosure. It comprises, from upstream to downstream according to the circulation of the air flow, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.
• Figure 2 shows, schematically, a stage of the high pressure compressor 4, the high pressure compressor 4 comprising a succession of stages of this type.
• the rotor 10 of each stage comprises a plurality of movable vanes 1 1, mounted on a disc 12 coupled to the high pressure shaft of the
• a ferrule 13 connects the disc 12 to the disc 12 'of the preceding stage.
• the stator 20 of each stage comprises for its part a ferrule 21, provided vis-à-vis the movable vanes 11, and a plurality of fixed vanes 22 provided vis-à-vis the ferrule 13 of the rotor 10.
• the ferrule 21 of the stator carries abradable tracks 31 against which rubs the outer ends of the movable blades 1 1.
• another abradable track 32 is provided on the inner end of each fixed blade 22; wipers 15 provided on the ferrule 13 of the rotor then rub against this abradable track 32.
• abradable coatings making it possible to form these abradable tracks 31 and 32, will now be described.
• the abradable coating is made of
• this abradable coating does not include any other component.
• This inorganic compound has a hexagonal crystal system and a space group of 6 / m. It is stable up to at least 900 ° C and has a hardness of 5 on the Mohs scale. Plus, it is insoluble in water, acetone, and alcohol.
• the substrate to be coated in this case the ferrule 21 and the ring 32, from a powder having a particle size of between 45 and 90 ⁇ m. In the present example, a thickness of 1.5 mm is desired for the coating.
• Figure 5 shows the aerodynamic losses suffered by the air stream circulating in a high pressure compressor equipped with abradable tracks, depending on the roughness of the coating forming these abradable tracks.
• This curve 50 was drawn by comparing several materials on a test bench. Points 51 and 52 correspond to the cases of two abradable coatings currently preferred for a high pressure compressor: it is a raw Metco 2043 coating for point 51 and a Metco 2043 coating with Alumina slip for point 52.
• Point 53 corresponds for its part to the case of this coating produced in
• a / S ratio (abradability on overpenetration) which is measured using a measuring device 90 illustrated in FIG. 6: three Simulacral vanes 91 are disposed projecting on the perimeter of a rotating wheel 92. An abradable sample 93 to be tested is placed below the rotating wheel 92. The rotating wheel 92 advances at constant speed towards the abradable sample 93 and penetrates it. up to a set depth. We then measure the depth actually dug in the abradable and we calculate the set depth / dug depth ratio. This ratio is called the A / S ratio and is expressed as a percentage.
• the test parameters are as follows. The speed of rotation at the end of the sham vanes 91 is 210 m / s, the speed of advance of the rotating wheel 92 towards the sample 93 is 150 pm / s and the set depth is 0.5mm.
• this hydroxyapatite coating has shown during these tests an A / S ratio of between 110% and 120%, without the blades being subjected to wear.

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

Applications Claiming Priority (2)

Publications (1)

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Family Cites Families (21)

• 2019
  • 2019-07-26 FR FR1908492A patent/FR3099187B1/fr active Active
• 2020
  • 2020-07-22 WO PCT/FR2020/051333 patent/WO2021019154A1/fr unknown
  • 2020-07-22 CN CN202080053816.4A patent/CN114174548A/zh active Pending
  • 2020-07-22 US US17/630,031 patent/US20220282633A1/en active Pending
  • 2020-07-22 EP EP20757631.5A patent/EP4004250A1/de active Pending

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