EP3841229B1 - Abreibbare beschichtung für rotierende schaufeln einer turbomaschine - Google Patents

Abreibbare beschichtung für rotierende schaufeln einer turbomaschine Download PDF

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Publication number
EP3841229B1
EP3841229B1 EP19782658.9A EP19782658A EP3841229B1 EP 3841229 B1 EP3841229 B1 EP 3841229B1 EP 19782658 A EP19782658 A EP 19782658A EP 3841229 B1 EP3841229 B1 EP 3841229B1
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EP
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Prior art keywords
abradable coating
abradable
particles
matrix
ceramic
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EP19782658.9A
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English (en)
French (fr)
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EP3841229A1 (de
Inventor
Philippe Charles Alain Le Biez
Nicolas DROZ
Lisa PIN
Serge Georges Vladimir Selezneff
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F01D11/08—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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • 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]
    • 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
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • 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

  • the present invention relates to the general field of coatings made of abradable material for turbomachines, and in particular for aircraft engines.
  • abradable is meant here the fact that the material is intended to wear by abrasion during contact with the blades.
  • the abradable coating is eroded by the passage of the blades, thus allowing the casing to match the actual shape of the tips of the blades.
  • the materials used to form the abradable coating are materials with high operating temperatures and resistant to oxidation which can be ceramic, such as yttria zirconia, alumina, or yttrium disilicate, or metal alloys, such as CoNiCrAIY, which is a cobalt-based alloy comprising a high proportion of nickel and chromium, for oxidation resistance as well as aluminum for resilience and yttrium for thermal resistance.
  • the abradable coatings are made of porous materials, the porosity rate thus making it possible to control the abradable character of the material.
  • the main object of the present invention is therefore to overcome such drawbacks by proposing a new abradable coating.
  • the abradable coating according to the invention offers the advantage of resisting very high operating temperatures, greater than 900° C. and for example of the order of 1300° C.
  • such an abradable material makes it possible to obtain an abradability at least equal to the abradability of existing abradable materials.
  • the abradable coating according to the invention has good aerodynamic performance.
  • the abradable coating according to the invention also has a long service life.
  • the invention proposes an abradable coating for a turbomachine part which comprises a matrix made of a first ceramic material and particles made of a second ceramic material dispersed in said matrix, the first ceramic material having a higher dynamic viscosity or equal to 10 12 Pa.s at 1300°C, the second ceramic material having a dynamic viscosity less than or equal to 10 2 Pa.s at 1300°C.
  • the second ceramic material is a feldspathic ceramic, a glass-ceramic, a hydrothermal glass, silica, or a silico-aluminous based refractory glass with a silica content of at least 60%.
  • the first material is yttrium disilicate or a yttria zirconia.
  • the invention proposes an abradable coating for a turbomachine part, characterized in that it comprises a matrix made of a first metallic material and particles made of a second metallic material dispersed in said matrix, the first metallic material having a melting temperature greater than 900°C, the second metallic material having a melting temperature at least 50°C lower than the melting temperature of the first metallic material.
  • the first metallic material is an MCrAIY, with M denoting Ni and/or Co.
  • the second metallic material is aluminum or an aluminum alloy, or else copper or a copper alloy, or else silver or a silver alloy.
  • the particles have an average size of between 45 ⁇ m and 90 ⁇ m.
  • the abradable coating comprises a volume loading rate of particles of between 30% and 70%.
  • the abradable coating comprises a porosity rate of between 5% and 30%.
  • the invention proposes a turbomachine comprising a high pressure turbine, the high pressure turbine comprising an abradable coating according to any one of the preceding characteristics.
  • the high-pressure turbine 15 comprises rotating vanes 17 located inside an annular casing 18, the top 171 of the rotating vanes 17 being located facing the casing 18, and more precisely facing the internal wall of the casing 18.
  • an abradable coating 2 as illustrated in the picture 2 is arranged on the inner contour of the housing 18.
  • the abradable coating 2 is intended to wear by abrasion during contact between the top 171 of the rotating blades 17 and the abradable coating 2.
  • the contact between the top 171 of the rotating vanes 17 and the abradable coating 2 may for example be due to the thermal expansion of said rotating vanes 17 during operation of the turbomachine 1.
  • Such thermal expansion of the rotating blades 17 of the high pressure turbine 15 is all the greater with the increase in the operating temperature of the turbomachine 1 carried out in order to increase the efficiency of said turbomachine 1 and reduce its fuel consumption. .
  • the operating temperature of the high pressure turbine 15 is between 900°C and 1300°C.
  • the abradable coating comprises a matrix 21 in which particles 22 are dispersed.
  • the role of the matrix 21 is to ensure the mechanical strength of the abradable coating 2, as well as the resistance to high temperatures, that is to say above 900° C. and preferably above 1300° C., as well as the oxidation resistance.
  • the matrix 21 is therefore made of a material capable of keeping its mechanical properties at a temperature above 900° C., and preferably above 1300° C., and of resisting oxidation at such temperatures.
  • the particles 22 are for their part used in order to weaken the matrix and provide its abradable character to the abradable coating 2.
  • the particles 22 are made of a material whose mechanical properties are greatly degraded by passing to a fluid state during contact between the abradable coating 2 and the top of a rotating blade of a high pressure turbine. 15, in order to form areas of weakness in the matrix 21.
  • the temperature increases very rapidly by around one hundred degrees.
  • This increase in temperature causes the particles 22 to pass from a solid state to a fluid state, thus weakening the abradable coating 2 which wears by abrasion in contact with the tip of the blade.
  • the fact that the particles 22 form a phase fluid makes it possible to smooth the surface of said abradable coating 2 after contact with the top of the blading.
  • the smoothing of the abradable coating 2 makes it possible to improve the aerodynamic performance of the casing ring covered by said abradable coating 2.
  • the fact that the particles 22 form a fluid phase allows self-healing of the abradable coating 2 during the cooling of said abradable coating 2, the fluid coming from the particles filling the cracks of said abradable coating 2 for example caused by a differential of thermal expansion, which improves the life of said abradable coating 2.
  • the matrix 21 is made of a first ceramic material
  • the particles 22 are made of a first ceramic material.
  • the first ceramic material has a dynamic viscosity greater than or equal to 10 12 Pa.s at 1300°C, while the second ceramic material has a dynamic viscosity less than or equal to 10 2 Pa.s at 1300°C.
  • the dynamic viscosity is measured here using a Brookfield RVT viscometer equipped with a spindle rotating at 20 rev/minute or by measuring the flow.
  • the first ceramic material for example, has a dynamic viscosity greater than 10 12 Pa.s at 1300° C. enables the matrix 21 to retain its mechanical properties, and thus enables the abradable coating 2 to withstand the very high temperature.
  • the second ceramic material has a dynamic viscosity less than or equal to 10 2 Pa.s at 1300° C. makes it possible to weaken the matrix 21 sufficiently.
  • such a low viscosity of the second material allows the friction of the tip of the blade to smooth the surface of the abradable coating 2, thus improving the aerodynamic performance of the abradable coating 2.
  • Such a viscosity also also allows the second material constituting the particles 22 to be sufficiently fluid so that it can flow and thus fill any cracks that may appear in the abradable coating 2, thus giving a self-healing effect to said abradable coating 2.
  • the matrix 21 is preferably made of yttrium disilicate (Y 2 Si 2 O 7 ), thus enabling the abradable coating 2 to withstand operation at 1300° C. in a durable manner.
  • Y 2 Si 2 O 7 yttrium disilicate
  • the particles 22 can be made of feldspathic ceramic, preferably of feldspathic ceramic which has a content of leucite crystals greater than or equal to 10% because it has improved mechanical strength and an increased coefficient of thermal expansion.
  • Particles 22 can also be made of glass-ceramic, which is a material shaped in the glass state and then heat-treated to obtain controlled partial crystallization.
  • the particles 22 can also be made of hydrothermal glass, which is a single-phase material, without a crystalline phase, in the structure of which OH ions have been incorporated.
  • the particles 22 can also be made of silica SiO 2 or of refractory glass based on silico-aluminous material where the silica is present at at least 60%.
  • the matrix 21 is made of a first metallic material, and the particles 22 are made of a second metallic material.
  • the first metallic material composing the matrix 21 has a melting temperature greater than 900° C., and preferably greater than 1000° C., and even more preferably greater than 1100° C., so as to keep good mechanical properties and ensure the behavior of the abradable coating 2 at such temperatures.
  • the second metallic material making up the particles 22 has for its part a lower melting temperature at least lower than 50° C. than the melting temperature of the first metallic material.
  • Such a difference in melting temperature allows the particles 22 to pass into the liquid state during contact between the tip of a blade and the abradable coating 2 under the effect of the increase in temperature, thus weakening the matrix 21 which remained solid.
  • the second metallic material has a melting temperature lower by 50° C. to 200° C. than the melting temperature of the first metallic material.
  • the difference in melting temperature is not too great to prevent the second material from changing to the liquid state at too low a temperature, which would promote erosion of the abradable coating 2 as well as the surface loss of this liquid phase.
  • the first material making up the matrix 21 is preferably an MCrAlY, with M denoting nickel (Ni), or cobalt (Co), or an alloy of nickel and cobalt.
  • the second material making up the particles 22 can be, for example, aluminum or an aluminum alloy for a 900° C. class material base, or else, for example, silver or silver alloy particles, or copper or copper alloy particles for a base material class 1000-1050°C.
  • silver and copper is understood here an alloy whose main component is respectively aluminum, silver and copper.
  • the first embodiment offers the advantage of resistance to very high temperatures, of the order of 1300° C., and also has resistance to oxidation at such temperatures.
  • the second embodiment offers greater simplicity of manufacture due to its metallic nature, but has a lower temperature resistance, greater than 900° C. and less than 1300° C.
  • the particles 22 can have an average size of between 45 ⁇ m and 90 ⁇ m, thus allowing the particles 22 to be able to pass quickly into the fluid state.
  • average size is meant the dimension given by the statistical particle size distribution to half of the population, called D50.
  • the particles 22, for any one of the embodiments, are preferably in the form of balls as illustrated in figure 2 , but can also have an acicular shape.
  • the abradable coating 2 comprises a volumetric loading rate of particles 22 of between 30% and 70%, the matrix 21 occupying the rest.
  • Such a proportion of particles makes it possible to ensure good abradability of the abradable coating 2, also to ensure a good smoothing effect and a good self-healing effect, while ensuring sufficient resistance of said abradable coating 2.
  • the abradable coating 2 can be manufactured by thermal spraying during which the first material forming the matrix 21 and the second material forming the particles 22 are sprayed together onto a support to be coated by being mixed in the desired proportions.
  • the abradable coating 2 can also be obtained by sintering or by MIM process (injection molding, or “ Metal Injection Molding ” according to the well-known Anglo-Saxon terminology).
  • a pore-forming agent such as for example a polyester or a polyamide, can be used during the manufacture of the abradable coating 2 in order to make it porous and improve its abradability, in particular at lower temperature.
  • the abradable coating 2 may comprise a porosity rate of between 5% and 30%.

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

Claims (10)

  1. Abreibbare Beschichtung (2) für Turbomaschinen-Bauteil, dadurch gekennzeichnet, dass sie eine Matrix (21) aus einem ersten Keramikmaterial und Partikel (22) aus einem zweiten Keramikmaterial umfasst, die in der Matrix (21) dispergiert sind, wobei das erste Keramikmaterial bei 1300 °C eine dynamische Viskosität von höher oder gleich 1012 Pa.s besitzt, wobei das zweite Keramikmaterial bei 1300 °C eine dynamische Viskosität von niedriger oder gleich 102 Pa.s besitzt.
  2. Abreibbare Beschichtung (2) nach Anspruch 1, wobei das zweite Keramikmaterial eine feldspathaltige Keramik, eine Glaskeramik, ein hydrothermales Glas, Siliziumoxid oder ein feuerfestes Glas auf Schamottebasis mit einem Siliziumoxidgehalt von mindestens 60 % ist.
  3. Abreibbare Beschichtung (2) nach einem der Ansprüche 1 bis 2, wobei das erste Material ein Yttriumdisilicat oder ein Yttriumzirkon ist.
  4. Abreibbare Beschichtung (2) für Turbomaschinen-Bauteil, dadurch gekennzeichnet, dass sie eine Matrix (21) aus einem ersten Metallmaterial und Partikel (22) aus einem zweiten Metallmaterial umfasst, die in der Matrix (21) dispergiert sind, wobei das erste Metallmaterial eine Schmelztemperatur von höher als 900 °C besitzt, wobei das zweite Metallmaterial eine Schmelztemperatur besitzt, die mindestens 50 °C niedriger als die Schmelztemperatur des ersten Metallmaterials ist.
  5. Abreibbare Beschichtung (2) nach Anspruch 4, wobei das erste Metallmaterial ein MCrAIY ist, wobei M Ni und/oder Co bezeichnet.
  6. Abreibbare Beschichtung (2) nach einem der Ansprüche 4 bis 5, wobei das zweite Metallmaterial Aluminium oder eine Aluminiumlegierung oder Kupfer oder Kupferlegierung oder Silber oder eine Silberlegierung ist.
  7. Abreibbare Beschichtung (2) nach einem der Ansprüche 1 bis 6, wobei die Partikel (22) eine mittlere Größe von zwischen 45 µm und 90 µm aufweisen.
  8. Abreibbare Beschichtung (2) nach einem der Ansprüche 1 bis 7, wobei der Anteil des mit Partikeln (22) gefüllten Volumens der abreibbaren Beschichtung (2) zwischen 30 % und 70 % beträgt.
  9. Abreibbare Beschichtung (2) nach einem der Ansprüche 1 bis 8, wobei die abreibbare Beschichtung (2) einen Porositätsgrad von zwischen 5 % und 30 % umfasst.
  10. Turbomaschine, die eine Hochdruckturbine umfasst, wobei die Hochdruckturbine (15) eine abreibbare Beschichtung (2) nach einem der Ansprüche 1 bis 9 umfasst.
EP19782658.9A 2018-08-22 2019-08-20 Abreibbare beschichtung für rotierende schaufeln einer turbomaschine Active EP3841229B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1857581A FR3085172B1 (fr) 2018-08-22 2018-08-22 Revetement abradable pour aubes tournantes d'une turbomachine
PCT/FR2019/051943 WO2020039146A1 (fr) 2018-08-22 2019-08-20 Revetement abradable pour aubes tournantes d'une turbomachine

Publications (2)

Publication Number Publication Date
EP3841229A1 EP3841229A1 (de) 2021-06-30
EP3841229B1 true EP3841229B1 (de) 2022-02-09

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EP19782658.9A Active EP3841229B1 (de) 2018-08-22 2019-08-20 Abreibbare beschichtung für rotierende schaufeln einer turbomaschine

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US (2) US11359508B2 (de)
EP (1) EP3841229B1 (de)
CN (1) CN112601841B (de)
FR (1) FR3085172B1 (de)
WO (1) WO2020039146A1 (de)

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CN113623022A (zh) * 2021-07-30 2021-11-09 中国航发沈阳发动机研究所 一种具有易磨涂层的涡轮外环

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US20220282634A1 (en) 2022-09-08
FR3085172A1 (fr) 2020-02-28
FR3085172B1 (fr) 2021-03-05
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CN112601841B (zh) 2022-03-22
US20210172331A1 (en) 2021-06-10

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