EP3841229A1 - Revetement abradable pour aubes tournantes d'une turbomachine - Google Patents
Revetement abradable pour aubes tournantes d'une turbomachineInfo
- Publication number
- EP3841229A1 EP3841229A1 EP19782658.9A EP19782658A EP3841229A1 EP 3841229 A1 EP3841229 A1 EP 3841229A1 EP 19782658 A EP19782658 A EP 19782658A EP 3841229 A1 EP3841229 A1 EP 3841229A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- abradable coating
- particles
- abradable
- matrix
- metallic material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 69
- 239000011248 coating agent Substances 0.000 title claims abstract description 67
- 239000002245 particle Substances 0.000 claims abstract description 35
- 239000000463 material Substances 0.000 claims abstract description 31
- 239000011159 matrix material Substances 0.000 claims abstract description 26
- 239000007769 metal material Substances 0.000 claims description 21
- 229910010293 ceramic material Inorganic materials 0.000 claims description 16
- 238000002844 melting Methods 0.000 claims description 13
- 230000008018 melting Effects 0.000 claims description 13
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 12
- 239000011521 glass Substances 0.000 claims description 7
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 239000000377 silicon dioxide Substances 0.000 claims description 6
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 5
- 239000000919 ceramic Substances 0.000 claims description 5
- 239000004332 silver Substances 0.000 claims description 5
- 229910001316 Ag alloy Inorganic materials 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- 239000010433 feldspar Substances 0.000 claims description 4
- 229910052709 silver Inorganic materials 0.000 claims description 4
- AKTQKAXQEMMCIF-UHFFFAOYSA-N trioxido(trioxidosilyloxy)silane;yttrium(3+) Chemical compound [Y+3].[Y+3].[O-][Si]([O-])([O-])O[Si]([O-])([O-])[O-] AKTQKAXQEMMCIF-UHFFFAOYSA-N 0.000 claims description 4
- 239000002241 glass-ceramic Substances 0.000 claims description 3
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 claims description 3
- 239000013528 metallic particle Substances 0.000 claims description 2
- 239000012530 fluid Substances 0.000 abstract description 8
- 230000000694 effects Effects 0.000 abstract description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 230000003647 oxidation Effects 0.000 description 5
- 238000007254 oxidation reaction Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000012071 phase Substances 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 229910000531 Co alloy Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009499 grossing Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000003313 weakening effect Effects 0.000 description 2
- 239000004604 Blowing Agent Substances 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 229910052907 leucite Inorganic materials 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
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
- 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
- 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
- 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 turbomachinery, and in particular for aircraft engines.
- abradable is meant here the fact that the material is intended to wear out by abrasion upon contact with the blades.
- the abradable coating is eroded by the passage of the blades, thus allowing the casing to match the real shape of the tips of the blades.
- the materials used to form the abradable coating are materials with high temperatures of use and resistant to oxidation which can be made of ceramic, such as, for example, yttria zirconia, alumina, or yttrium disilicate, or made of metal alloys, such as, for example, CoNiCrAlY 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.
- ceramic such as, for example, yttria zirconia, alumina, or yttrium disilicate
- metal alloys such as, for example, CoNiCrAlY 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 rate of porosity 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 withstanding very high operating temperatures, greater than 900 ° C. and for example of the order of 1300 ° C.
- 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 provides an abradable coating for a turbomachine part which comprises a matrix of a first ceramic material and particles 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 feldspar ceramic, a glass ceramic, a hydrothermal glass, silica, or a silico-aluminous refractory glass with a silica content of at least 60%.
- the first material one is yttrium disilicate or a yttria zirconia.
- the invention provides an abradable coating for a turbomachine part, characterized in that it comprises a matrix made of a first metallic material and particles of a second metallic material dispersed in said matrix, the first metallic material having a melting temperature above 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 MCrAlY, 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 rate of volumetric charge of particles of between 30% and 70%.
- the abradable coating comprises a porosity rate of between 5% and 30%.
- the invention provides a turbomachine comprising a high pressure turbine, the high pressure turbine comprising an abradable coating according to any one of the preceding characteristics.
- FIG. 1 is a schematic representation of a turbomachine
- FIG. 2 is a schematic representation of the abradabie coating according to the invention.
- FIG. 3 is a schematic representation of a rotating vane located inside a housing, an abradable coating being deposited on the internal contour of the housing in order to cooperate with the top of the vane.
- a turbomachine in particular an aircraft turbomachine, comprises:
- the high pressure turbine 15 comprises rotating blades 17 located inside an annular casing 18, the top 171 of the rotating blades 17 being located opposite the casing 18, and more precisely facing the internal wall of the casing 18.
- an abradable coating 2 as illustrated in FIG. 2 is placed on the inside contour of the casing 18.
- the abradabie coating 2 is intended to wear by abrasion during contact between the top 171 of the rotating blades 17 and the abradabie coating 2.
- the contact between the top 171 of the rotating blades 17 and the abradable coating 2 may for example be due to the thermal expansion of said rotating blades 17 during the operation of the turbomachine 1.
- 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 greater than 900 ° C. and preferably greater than 1300 ° C., as well as the resistance to oxidation.
- the matrix 21 is therefore made of a material capable of retaining its mechanical properties at a temperature above 900 ° C, and preferably above 1300 ° C, and to resist oxidation at such temperatures.
- the particles 22 are used to weaken the matrix and bring its abradable nature 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 upon contact between the abradable coating 2 and the top of a rotating vane of a high pressure turbine. 15, in order to form zones of weaknesses in the matrix 21.
- the temperature increases very quickly by a 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 top of the blading.
- 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 vane.
- 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 coming to fill 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 here measured by using a Brookfield RVT viscometer equipped with a mobile rotating at 20 rpm or by a flow measurement.
- the first ceramic material for example has a dynamic viscosity greater than 10 12 Pa.s at 1300 ° C allows the matrix 21 to keep its mechanical properties, and thus allows 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 top of the blading 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 0 7 ), thus allowing the abradable coating 2 to withstand lasting operation at 1300 ° C.
- the particles 22 can be made of feldspar ceramic, preferably feldspar 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.
- the particles 22 can also be made of a glass ceramic, which is a material formed in the form of glass and then heat treated to obtain a controlled partial crystallization.
- the particles 22 can also be made of hydrothermal glass, which is a single-phase material, without crystalline phase, in the structure of which OH ions have been incorporated.
- the particles 22 can also be made of silica Si0 2 or of refractory glass based on a silico-aluminous base where the silica is present 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 making up the matrix 21 has a melting temperature above 900 ° C, and preferably above 1000 ° C, and even more preferably above 1100 ° C, so as to keep good mechanical properties and ensure the resistance of the abradable coating 2 at such temperatures.
- the second metallic material composing the particles 22 has a melting temperature below at least less than 50 ° C than the melting temperature of the first metallic material.
- the second metallic material has a melting temperature 50 ° C to 200 ° C lower than the melting temperature of the first metallic material.
- the difference in melting temperature is not too great to prevent the second material from going into the liquid state at too low a temperature, which would promote the erosion of the abradable coating 2 as well as the loss on the surface 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 composing the particles 22 can be for example aluminum or an aluminum alloy for a base of material of class 900 ° C., or else for example particles of silver or silver alloy, or particles of copper or copper alloy for a base material of class 1000-1050 ° C.
- silver and copper alloy is understood here an alloy of which the 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 more 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 rapidly into the fluid state.
- average size is meant the dimension given by the statistical particle size distribution to half the population, called D50.
- the particles 22, for any one of the embodiments, are preferably in the form of beads as illustrated in FIG. 2, but can also have an acicular shape.
- the abradable coating 2 comprises a volume 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 produced by thermal spraying during which the first material forming the matrix 21 and the second material forming the particles 22 are sprayed together on a support to be covered by being mixed in the desired proportions.
- the abradable coating 2 can also be obtained by sintering or by MIM process (injection molding, or "Meta! Injection Mo! Ding" according to the well-known Anglo-Saxon terminology).
- a blowing 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 can comprise a porosity rate of between 5% and 30%.
Landscapes
- 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)
Abstract
Description
Claims
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 true EP3841229A1 (fr) | 2021-06-30 |
EP3841229B1 EP3841229B1 (fr) | 2022-02-09 |
Family
ID=66286369
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19782658.9A Active EP3841229B1 (fr) | 2018-08-22 | 2019-08-20 | Revetement abradable pour aubes tournantes d'une turbomachine |
Country Status (5)
Country | Link |
---|---|
US (2) | US11359508B2 (fr) |
EP (1) | EP3841229B1 (fr) |
CN (1) | CN112601841B (fr) |
FR (1) | FR3085172B1 (fr) |
WO (1) | WO2020039146A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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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GB9513252D0 (en) * | 1995-06-29 | 1995-09-06 | Rolls Royce Plc | An abradable composition |
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JP4130894B2 (ja) * | 2003-01-23 | 2008-08-06 | 本田技研工業株式会社 | ガスタービンエンジンおよびその製造方法 |
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ATE405686T1 (de) | 2005-06-16 | 2008-09-15 | Sulzer Metco Us Inc | Aluminiumoxid dotierter verschleissbarer keramischer werkstoff |
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-
2018
- 2018-08-22 FR FR1857581A patent/FR3085172B1/fr active Active
-
2019
- 2019-08-20 WO PCT/FR2019/051943 patent/WO2020039146A1/fr unknown
- 2019-08-20 US US17/269,854 patent/US11359508B2/en active Active
- 2019-08-20 EP EP19782658.9A patent/EP3841229B1/fr active Active
- 2019-08-20 CN CN201980054182.1A patent/CN112601841B/zh active Active
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2022
- 2022-05-17 US US17/746,417 patent/US11933181B2/en active Active
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Publication number | Publication date |
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US20220282634A1 (en) | 2022-09-08 |
US20210172331A1 (en) | 2021-06-10 |
EP3841229B1 (fr) | 2022-02-09 |
US11359508B2 (en) | 2022-06-14 |
CN112601841A (zh) | 2021-04-02 |
FR3085172A1 (fr) | 2020-02-28 |
WO2020039146A1 (fr) | 2020-02-27 |
FR3085172B1 (fr) | 2021-03-05 |
CN112601841B (zh) | 2022-03-22 |
US11933181B2 (en) | 2024-03-19 |
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