EP3841229A1 - Abradable coating for rotating blades of a turbomachine - Google Patents

Abradable coating for rotating blades of a turbomachine

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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
Application number
EP19782658.9A
Other languages
German (de)
French (fr)
Other versions
EP3841229B1 (en
Inventor
Philippe Charles Alain Le Biez
Nicolas DROZ
Lisa PIN
Serge Georges Vladimir Selezneff
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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Publication date
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3841229A1 publication Critical patent/EP3841229A1/en
Application granted granted Critical
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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

Abstract

The invention relates to an abradable coating (2) comprising a matrix (21) and particles (22) dispersed in said matrix (21), the particles (22) being made of a material which changes to a fluid phase under the effect of the increase in temperature in the event of contact between a blade tip and the abradable coating (2).

Description

Revêtement abradable pour aubes tournantes d'une turbomachine  Abradable coating for rotating blades of a turbomachine
Arrière-plan de l'invention Invention background
La présente invention se rapporte au domaine général des revêtements en matériau abradable pour les turbomachines, et en particulier pour les moteurs d'aéronefs.  The present invention relates to the general field of coatings made of abradable material for turbomachinery, and in particular for aircraft engines.
Afin d'assurer une étanchéité aérodynamique entre le sommet d'aubes tournantes et le carter entourant lesdites aubes tournantes, il est connu de déposer un revêtement abradable en appliquant sur le contour intérieur du carter une couche en un matériau abradable formant une piste pour le parcours du sommet des aubes le long du carter.  In order to ensure an aerodynamic seal between the top of rotating vanes and the casing surrounding said rotating vanes, it is known to deposit an abradable coating by applying a layer of abradable material forming a track for the route on the inside contour of the casing. from the top of the blades along the casing.
Par abradable on désigne ici le fait que le matériau est prévu pour s'user par abrasion lors de contact avec les aubes. Le revêtement abradable est érodé par le passage des aubes, permettant ainsi au carter d'épouser la forme réelle des sommets des aubes.  By 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.
Pour les turbines hautes pression, c'est-à-dire les turbines situées directement en sorties de la chambre de combustion, les matériaux utilisés pour former le revêtement abradable sont des matériaux à hautes températures d'utilisation et résistant à l'oxydation qui peuvent être en céramique, comme par exemple de la zircone yttriée, de l'alumine, ou du disilicate d'yttrium, ou en alliages métalliques, comme par exemple le CoNiCrAlY qui est un alliage base cobalt comportant de forte proportion de nickel et de chrome, pour la tenue en oxydation ainsi que de l'aluminium pour la résilience et de l'yttrium pour la tenue thermique.  For high pressure turbines, i.e. turbines located directly at the outlet of the combustion chamber, 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.
Cependant, le caractère abradable de ces matériaux qui sont capables de résister aux conditions d'utilisation des turbines hautes pression est très faible.  However, the abradable nature of these materials which are able to withstand the conditions of use of high pressure turbines is very low.
Ainsi, afin d'augmenter le caractère abradable de ces matériaux, les revêtements abradables sont fabriqués en matériaux poreux, le taux de porosité permettant ainsi de contrôler le caractère abradable du matériau.  Thus, in order to increase the abradable character of these materials, the abradable coatings are made of porous materials, the rate of porosity thus making it possible to control the abradable character of the material.
Cependant, d'une part les procédés actuels d'obtention du revêtement en matériau abradable, et d'autre part la résistance à l'érosion dudit revêtement en matériau abradable provoquée par la circulation de particules abrasives, impose un taux de porosité du matériau abradable inférieur à 30%, limitant ainsi le caractère abradable des matériaux abradables existants. However, on the one hand the current methods of obtaining the coating of abradable material, and on the other hand the resistance to erosion of said coating of abradable material caused by the circulation of abrasive particles, imposes a rate of porosity of the abradable material. less than 30%, thus limiting the abradable nature of existing abradable materials.
Or, les progrès dans la gestion du rendement et de la consommation en carburant amènent une augmentation des températures de fonctionnement, en particulier pour les étages de la turbine haute pression situés directement en aval de la chambre de combustion, ainsi qu'à une diminution du jeu entre les aubes tournantes et le carter.  However, progress in the management of fuel efficiency and consumption leads to an increase in operating temperatures, in particular for the stages of the high pressure turbine located directly downstream of the combustion chamber, as well as to a decrease in clearance between the rotating vanes and the housing.
Il est donc nécessaire de développer des matériaux abradables ayant des comportements abradables suffisant dans les conditions de fonctionnement des nouvelles turbomachines, et notamment pour les turbines haute pression.  It is therefore necessary to develop abradable materials having abradable behaviors sufficient under the operating conditions of new turbomachines, and in particular for high pressure turbines.
Objet et résumé de l'invention Subject and summary of the invention
La présente invention a donc pour but principal de pallier de tels inconvénients en proposant un nouveau revêtement abradable.  The main object of the present invention is therefore to overcome such drawbacks by proposing a new abradable coating.
Le revêtement abradable selon l'invention offre l'avantage de résister à des températures d'utilisation très élevées, supérieure à 900°C et par exemple de l'ordre de 1300°C.  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.
De plus, un tel matériau abradable permet d'obtenir une abradabilité au moins égale à l'abradabilité des matériaux abradables existants.  In addition, such an abradable material makes it possible to obtain an abradability at least equal to the abradability of existing abradable materials.
En outre, le revêtement abradable selon l'invention possède de bonnes performances aérodynamiques.  In addition, the abradable coating according to the invention has good aerodynamic performance.
Le revêtement abradable selon l'invention possède également une longue durée de vie.  The abradable coating according to the invention also has a long service life.
Selon un premier mode de réalisation, l'invention propose un revêtement abradable pour pièce de turbomachine qui comprend une matrice en un premier matériau céramique et des particules en un deuxième matériau céramique dispersées dans ladite matrice, le premier matériau céramique possédant une viscosité dynamique supérieure ou égale à 1012 Pa.s à 1300°C, le deuxième matériau céramique possédant une viscosité dynamique inférieure ou égale à 102 Pa.s à 1300°C. According to a first embodiment, 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.
Selon une caractéristique possible du premier mode de réalisation, le deuxième matériau céramique est une céramique feldspathique, une vitrocéramique, un verre hydrothermal, de la silice, ou un verre réfractaire à base silico-alumineux avec un taux de silice d'au moins 60%. According to a possible characteristic of the first embodiment, 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%.
Selon une autre caractéristique du premier mode de réalisation, le premier matériau un est disilicate d'yttrium ou une zircone yttriée.  According to another characteristic of the first embodiment, the first material one is yttrium disilicate or a yttria zirconia.
Selon un deuxième mode de réalisation, l'invention propose un revêtement abradable pour pièce de turbomachine, caractérisé en ce qu'il comprend une matrice en un premier matériau métallique et des particules en un deuxième matériau métallique dispersées dans ladite matrice, le premier matériau métallique possédant une température de fusion supérieure à 900°C, le deuxième matériau métallique possédant une température de fusion inférieure d'au moins 50°C à la température de fusion du premier matériau métallique.  According to a second embodiment, 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.
Selon une caractéristique additionnelle du deuxième mode de réalisation, le premier matériau métallique est un MCrAlY, avec M désignant Ni et/ou Co.  According to an additional characteristic of the second embodiment, the first metallic material is an MCrAlY, with M denoting Ni and / or Co.
Selon une caractéristique supplémentaire du deuxième mode de réalisation, le deuxième matériau métallique est de l'aluminium ou un alliage d'aluminium, ou bien du cuivre ou un alliage de cuivre, ou bien de l'argent ou un alliage d'argent.  According to an additional characteristic of the second embodiment, the second metallic material is aluminum or an aluminum alloy, or else copper or a copper alloy, or else silver or a silver alloy.
Selon une caractéristique possible pour l'un quelconque des modes de réalisation, les particules ont une taille moyenne comprise entre 45 pm et 90 pm. According to a possible characteristic for any one of the embodiments, the particles have an average size of between 45 μm and 90 μm.
Selon une autre caractéristique pour l'un quelconque des modes de réalisation, le revêtement abradable comprend un taux de charge volumique de particules compris entre 30% et 70%.  According to another characteristic for any of the embodiments, the abradable coating comprises a rate of volumetric charge of particles of between 30% and 70%.
Selon une caractéristique supplémentaire pour l'un quelconque des modes de réalisation, le revêtement abradable comprend un taux de porosité compris entre 5% et 30%.  According to an additional characteristic for any of the embodiments, the abradable coating comprises a porosity rate of between 5% and 30%.
Selon un autre aspect, l'invention propose une turbomachine comprenant une turbine haute pression, la turbine haute pression comprenant un revêtement abradable selon l'une quelconque des caractéristiques précédentes. Brève description des dessins According to another aspect, 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. Brief description of the drawings
D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :  Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment thereof devoid of any limiting character. In the figures:
- la figure 1 est une représentation schématique d'une turbomachine ;  - Figure 1 is a schematic representation of a turbomachine;
- la figure 2 est une représentation schématique du revêtement abradabie selon l'invention ;  - Figure 2 is a schematic representation of the abradabie coating according to the invention;
- la figure 3 est une représentation schématique d'un aubage tournant située à l'intérieur d'un carter, un revêtement d'abradable étant déposé sur le contour interne du carter afin de coopérer avec le sommet de l'aubage. Description détaillée de l'invention  - Figure 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. Detailed description of the invention
Comme cela est illustré sur la figure 1, une turbomachine 1, notamment une turbomachine d'aéronef, comprend :  As illustrated in FIG. 1, a turbomachine 1, in particular an aircraft turbomachine, comprises:
- une soufflante 11 située en entrée de la turbomachine 1 ;  - a fan 11 located at the inlet of the turbomachine 1;
- un compresseur basse pression 12 en aval de la soufflante 11 ;  - a low pressure compressor 12 downstream of the fan 11;
- un compresseur haute pression 13 en aval du compresseur basse pression 12 ; - a high pressure compressor 13 downstream of the low pressure compressor 12;
- une chambre de combustion 14 en aval du compresseur haute pression 13 ;  - a combustion chamber 14 downstream of the high pressure compressor 13;
- une turbine haute pression 15 en aval de la chambre de combustion ; et  - a high pressure turbine 15 downstream of the combustion chamber; and
- une turbine basse pression 16 en aval de la turbine haute pression 15.  - a low pressure turbine 16 downstream of the high pressure turbine 15.
La turbine haute pression 15 comprend des aubages 17 tournants situés à l'intérieur d'un carter 18 annulaire, le sommet 171 des aubages 17 tournants étant situés en regard du carter 18, et plus précisément en regard de la paroi interne du carter 18.  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.
Afin d'améliorer les performances de la turbine haute pression 15, un revêtement abradabie 2 tel qu'illustré sur la figure 2 est disposé sur le contour intérieur du carter 18.  In order to improve the performance of the high pressure turbine 15, an abradable coating 2 as illustrated in FIG. 2 is placed on the inside contour of the casing 18.
Le revêtement abradabie 2 est destiné à s'user par abrasion lors de contact entre le sommet 171 des aubages 17 tournants et le revêtement abradabie 2. Le contact entre le sommet 171 des aubages 17 tournants et le revêtement abradable 2 peut par exemple être dû à la dilatation thermique desdits aubages 17 tournants lors du fonctionnement de la turbomachine 1. 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.
Une telle dilatation thermique des aubages 17 tournants de la turbine haute pression 15 est d'autant plus importante avec l'augmentation de la température de fonctionnement de la turbomachine 1 réalisée afin d'augmenter le rendement de ladite turbomachine 1 et diminuer sa consommation en carburant.  Such thermal expansion of the rotating blades 17 of the high pressure turbine 15 is all the more important with the increase in the operating temperature of the turbomachine 1 produced in order to increase the efficiency of said turbomachine 1 and reduce its fuel consumption. .
La température de fonctionnement de la turbine haute pression 15 est comprise entre 900°C et 1300°C.  The operating temperature of the high pressure turbine 15 is between 900 ° C and 1300 ° C.
Le revêtement abradable comprend une matrice 21 dans laquelle sont dispersées des particules 22.  The abradable coating comprises a matrix 21 in which particles 22 are dispersed.
Le rôle de la matrice 21 est d'assurer la tenue mécanique du revêtement abradable 2, ainsi que la résistance aux hautes températures, c'est-à-dire supérieure à 900°C et de préférence supérieure à 1300°C, ainsi que la résistance à l'oxydation.  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.
La matrice 21 est donc constituée d'un matériau capable de garder ses propriétés mécaniques à une température supérieure à 900°C, et de préférence supérieure à 1300°C, et de résister à l'oxydation à de telles températures.  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.
Les particules 22 sont quant à elles utilisées afin de fragiliser la matrice et apporter son caractère abradable au revêtement abradable 2.  The particles 22 are used to weaken the matrix and bring its abradable nature to the abradable coating 2.
Afin de fragiliser la matrice 21, les particules 22 sont réalisées dans un matériau dont les propriétés mécaniques se dégradent fortement par passage à un état fluide lors d'un contact entre le revêtement abradable 2 et le sommet d'un aubage tournant de turbine haute pression 15, afin de former des zones de faiblesses dans la matrice 21.  In order to weaken the matrix 21, 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.
Lors d'un contact entre le sommet d'un aubage et le revêtement abradable, la température augmente très rapidement d'une centaine de degrés.  Upon contact between the top of a vane and the abradable coating, the temperature increases very quickly by a hundred degrees.
Cette augmentation de température fait passer les particules 22 d'un état solide à un état fluide, fragilisant ainsi le revêtement abradable 2 qui s'use par abrasion au contact du sommet de l'aubage.  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.
De plus, outre le fait d'apporter son caractère abradable au revêtement abradable 2, le fait que les particules 22 forment une phase fluide permet de lisser la surface dudit revêtement abradable 2 après le contact avec le sommet de l'aubage. In addition, in addition to bringing its abradable nature to the abradable coating 2, 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.
Le lissage du revêtement abradable 2 permet d'améliorer les performances aérodynamiques de l'anneau de carter recouvert par ledit revêtement abradable 2.  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.
En outre, le fait que les particules 22 forment une phase fluide permet une auto-cicatrisation du revêtement abradable 2 lors du refroidissement dudit revêtement abradable 2, le fluide provenant des particules venant combler les fissures dudit revêtement abradable 2 par exemple provoquées par un différentiel de dilatation thermique, ce qui améliore la durée de vie dudit revêtement abradable 2.  In addition, 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.
Pour réaliser un tel revêtement abradable, deux variantes sont possibles.  To produce such an abradable coating, two variants are possible.
Selon une premier mode de réalisation, la matrice 21 est en un premier matériau céramique, et les particules 22 sont dans un premier matériau céramique.  According to a first embodiment, the matrix 21 is made of a first ceramic material, and the particles 22 are made of a first ceramic material.
Le premier matériau céramique possède une viscosité dynamique supérieure ou égale à 1012 Pa.s à 1300°C, tandis que le deuxième matériau céramique possède une viscosité dynamique inférieure ou égale à 102 Pa.s à 1300°C. 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.
La viscosité dynamique est ici mesurée par avec un viscosimètre Brookfield RVT équipé d'un mobile tournant à 20 tr/minute ou par une mesure d'écoulement.  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.
Le fait que le premier matériau céramique par exemple possède une viscosité dynamique supérieure à 1012 Pa.s à 1300°C permet à la matrice 21 de garder ses propriétés mécaniques, et ainsi permet au revêtement abradable 2 de résister à la température très élevée. The fact that 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.
Le fait que le second matériau céramique possède une viscosité dynamique inférieure ou égale à 102 Pa.s à 1300°C permet de fragiliser suffisamment la matrice 21. The fact that 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.
De plus, une viscosité aussi faible du second matériau permet que le frottement du sommet de l'aubage vienne lisser la surface du revêtement abradable 2, améliorant ainsi les performances aérodynamiques du revêtement abradable 2.  In addition, 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.
Une telle viscosité aussi permet également au second matériau constituant les particules 22 d'être suffisamment fluide pour qu'il puisse s'écouler et ainsi combler les éventuelles fissures qui peuvent apparaître dans le revêtement abradable 2, donnant ainsi un effet auto-cicatrisant audit revêtement abradable 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.
La matrice 21 est de préférence en disilicate d'yttrium (Y2Si207), permettant ainsi au revêtement abradable 2 de résister de manière durable à un fonctionnement à 1300°C. 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.
Les particules 22 peuvent être en céramique feldspathique, de préférence en céramique feldspathique qui présente un teneur en cristaux de leucite supérieure ou égale à 10% car elle présente une résistance mécanique améliorée et un coefficient de dilatation thermique augmenté.  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.
Les particules 22 peuvent également être en une vitrocéramique, qui est un matériau mis en forme à l'état de verre puis traité thermiquement pour obtenir une cristallisation partielle contrôlée.  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.
Les particules 22 peuvent en aussi être en verre hydrothermal, qui est un matériau monophasé, sans phase cristalline, dans la structure duquel des ions OH ont été incorporés.  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.
Les particules 22 peuvent également être en silice Si02 ou en verre réfractaire à base silico-alumineux où la silice est présente à au moins 60%. 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%.
Selon un deuxième mode de réalisation, la matrice 21 est en un premier matériau métallique, et les particules 22 sont dans un deuxième matériau métallique.  According to a second embodiment, the matrix 21 is made of a first metallic material, and the particles 22 are made of a second metallic material.
Le premier matériau métallique composant la matrice 21 possède une température de fusion supérieure à 900°C, et de préférence supérieure à 1000°C, et de manière encore plus préférentielle supérieure à 1100°C, de manière à garder de bonnes propriétés mécaniques et assurer la tenue du revêtement abradable 2 à de telles températures.  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.
Le deuxième matériau métallique composant les particules 22 possède quant à lui une température de fusion inférieure au moins inférieure à 50°C à la température de fusion du premier matériau métallique.  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.
Une telle différence de température de fusion permet que les particules 22 passent à l'état liquide lors d'un contact entre le sommet d'un aubage et le revêtement abradable 2 sous l'effet de l'augmentation de la température, fragilisant ainsi la matrice 21 qui est restée solide. Préférentiellement, le deuxième matériau métallique possède une température de fusion inférieure de 50°C à 200°C à la température de fusion du premier matériau métallique. En effet, il est avantageux que d'une part la différence de température de fusion ne soit pas trop importante pour éviter que le deuxième matériau passe à l'état liquide à une température trop basse, ce qui favoriserait l'érosion du revêtement abradable 2 ainsi que la perte en surface de cette phase liquide. Such a difference in melting temperature allows the particles 22 to pass into the liquid state upon contact between the top of a blade and the abradable coating 2 under the effect of the increase in temperature, thus weakening the matrix 21 which remained solid. Preferably, the second metallic material has a melting temperature 50 ° C to 200 ° C lower than the melting temperature of the first metallic material. Indeed, it is advantageous that on the one hand 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.
Le premier matériau composant la matrice 21 est de préférence est un MCrAlY, avec M désignant le nickel (Ni), ou le cobalt (Co), ou un alliage de nickel et de cobalt.  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.
Le deuxième matériau composant les particules 22 peut être par exemple de l'aluminium ou un alliage d'aluminium pour une base de matériau de classe 900°C, ou bien par exemple des particules d'argent ou d'alliage d'argent, ou des particules de cuivre ou d'alliage de cuivre pour une base matériau de classe 1000-1050°C.  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.
Par alliage d'aluminium, d'argent et de cuivre on comprend ici un alliage dont le composant principal est respectivement l'aluminium, l'argent et le cuivre.  By aluminum, silver and copper alloy is understood here an alloy of which the main component is respectively aluminum, silver and copper.
Le premier mode de réalisation offre l'avantage d'une tenue à des températures très élevées, de l'ordre de 1300°C, et possède également une résistance à l'oxydation à de telles températures.  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.
Le deuxième mode de réalisation offre quant à lui plus de simplicité de fabrication de par sa nature métallique, mais possède une tenue à la température moins importante, supérieure à 900°C et inférieure à 1300°C.  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.
Par ailleurs, pour le premier et le deuxième mode de réalisation, les particules 22 peuvent avoir une taille moyenne comprise entre 45 pm et 90 pm, permettant ainsi aux particules 22 de pouvoir passer rapidement dans l'état fluide.  Furthermore, for the first and second embodiments, the particles 22 can have an average size of between 45 μm and 90 μm, thus allowing the particles 22 to be able to pass rapidly into the fluid state.
Par « taille moyenne » on désigne la dimension donnée par la distribution granulométrique statistique à la moitié de la population, dite D50.  By "average size" is meant the dimension given by the statistical particle size distribution to half the population, called D50.
Les particules 22, pour l'un quelconque des modes de réalisation, sont préférentiellement en forme de billes comme illustré à la figure 2, mais peuvent également avoir une forme aciculaire. De plus, pour le premier et le deuxième mode de réalisation, le revêtement abradable 2 comprend un taux de charge volumique de particules 22 compris entre 30% et 70%, la matrice 21 occupant le reste. 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. In addition, for the first and second embodiments, the abradable coating 2 comprises a volume loading rate of particles 22 of between 30% and 70%, the matrix 21 occupying the rest.
Une telle proportion de particules permet d'assurer une bonne abradabilité du revêtement abradable 2, d'assurer également un bon effet lissant et un bon effet auto-cicatrisant, tout en assurant une résistance suffisante dudit revêtement abradable 2.  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.
Le revêtement abradable 2, selon l'un quelconque des modes de réalisation, peut être fabriqué par projection thermique durant laquelle le premier matériau formant la matrice 21 et le deuxième matériau formant les particules 22 sont projetés ensemble sur un support à recouvrir en étant mélangés dans les proportions désirées.  The abradable coating 2, according to any one of the embodiments, 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.
Le revêtement abradable 2 peut également être obtenu par frittage ou par procédé MIM (moulage par injection, ou « Meta! Injection Mo!ding » selon la terminologie anglo-saxonne bien connue).  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).
Par ailleurs, un agent porogène, comme par exemple un polyester ou un polyamide, peut être utilisé durant la fabrication du revêtement abradable 2 afin de le rendre poreux et améliorer son abradabilité, notamment à plus basse température.  Furthermore, 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.
Ainsi, le revêtement abradable 2 peut comprendre un taux de porosité compris entre 5% et 30%.  Thus, the abradable coating 2 can comprise a porosity rate of between 5% and 30%.
L'expression « compris(e) entre ... et ... » doit se comprendre comme incluant les bornes.  The expression "included between ... and ..." must be understood as including the limits.

Claims

REVENDICATIONS
1. Revêtement abradable (2) pour pièce de turbomachine, caractérisé en ce qu'il comprend une matrice (21) en un premier matériau céramique et des particules (22) en un deuxième matériau céramique dispersées dans ladite matrice (21), le premier matériau céramique possédant une viscosité dynamique supérieure ou égale à 1012 Pa.s à 1300°C, le deuxième matériau céramique possédant une viscosité dynamique inférieure ou égale à 102 Pa.s à 1300°C. 1. Abradable coating (2) for a turbomachine part, characterized in that it comprises a matrix (21) made of a first ceramic material and particles (22) made of a second ceramic material dispersed in said matrix (21), the first ceramic material having a dynamic viscosity greater than 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.
2. Revêtement abradable (2) selon la revendication 1 dans lequel le deuxième matériau céramique est une céramique feldspathique, une vitrocéramique, un verre hydrothermal, de la silice, ou un verre réfractaire à base silico-alumineux avec un taux de silice d'au moins 60%. 2. Abradable coating (2) according to claim 1 wherein the second ceramic material is a feldspar ceramic, a glass ceramic, a hydrothermal glass, silica, or a refractory glass based on silico-aluminous with a silica content of at least minus 60%.
3. Revêtement abradable (2) selon l'une quelconque des revendications 1 à 2, dans lequel le premier matériau est un disilicate d'yttrium ou une zircone yttriée. 3. Abradable coating (2) according to any one of claims 1 to 2, wherein the first material is a yttrium disilicate or a yttria zirconia.
4. Revêtement abradable (2) pour pièce de turbomachine, caractérisé en ce qu'il comprend une matrice (21) en un premier matériau métallique et des particules (22) en un deuxième matériau métallique dispersées dans ladite matrice (21), le premier matériau métallique possédant une température de fusion supérieure à 900°C, le deuxième matériau métallique possédant une température de fusion inférieure d'au moins 50°C à la température de fusion du premier matériau métallique. 4. Abradable coating (2) for a turbomachine part, characterized in that it comprises a matrix (21) made of a first metallic material and particles (22) made of a second metallic material dispersed in said matrix (21), 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.
5. Revêtement abradable (2) selon la revendication 4, dans lequel le premier matériau métallique est un MCrAlY, avec M désignant Ni et/ou Co. 5. Abradable coating (2) according to claim 4, in which the first metallic material is an MCrAlY, with M denoting Ni and / or Co.
6. Revêtement abradable (2) selon l'une quelconque des revendications 4 à 5, dans lequel le deuxième matériau métallique est de l'aluminium ou un alliage d'aluminium, ou bien du cuivre ou alliage de cuivre, ou bien de l'argent ou un alliage d'argent. 6. Abradable coating (2) according to any one of claims 4 to 5, in which the second metallic material is aluminum or an aluminum alloy, or else copper or copper alloy, or else silver or a silver alloy.
7. Revêtement abradable (2) selon l'une quelconque des revendications 1 à 6, dans lequel les particules (22) ont une taille moyenne comprise entre 45 pm et 90 pm. 7. Abradable coating (2) according to any one of claims 1 to 6, in which the particles (22) have an average size of between 45 μm and 90 μm.
8. Revêtement abradable (2) selon l'une quelconque des revendications8. Abradable coating (2) according to any one of claims
1 à 7, dans lequel ledit revêtement abradable (2) comprend un taux de charge volumique de particules (22) compris entre 30% et 70%. 1 to 7, in which said abradable coating (2) comprises a volume charge rate of particles (22) of between 30% and 70%.
9. Revêtement abradable (2) selon l'une quelconque des revendications 1 à 8, dans lequel le revêtement abradable (2) comprend un taux de porosité compris entre 5% et 30%. 9. Abradable coating (2) according to any one of claims 1 to 8, wherein the abradable coating (2) comprises a porosity rate between 5% and 30%.
10. Turbomachine comprenant une turbine haute pression, la turbine haute pression (15) comprenant un revêtement abradable (2) selon l'une quelconque des revendications 1 à 9. 10. Turbomachine comprising a high pressure turbine, the high pressure turbine (15) comprising an abradable coating (2) according to any one of claims 1 to 9.
EP19782658.9A 2018-08-22 2019-08-20 Abradable coating for rotating blades of a turbomachine Active EP3841229B1 (en)

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FR1857581A FR3085172B1 (en) 2018-08-22 2018-08-22 ABRADABLE COATING FOR TURBOMACHINE ROTATING BLADES
PCT/FR2019/051943 WO2020039146A1 (en) 2018-08-22 2019-08-20 Abradable coating for rotating blades of a turbomachine

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US11933181B2 (en) 2024-03-19
CN112601841B (en) 2022-03-22
CN112601841A (en) 2021-04-02
FR3085172A1 (en) 2020-02-28
US20220282634A1 (en) 2022-09-08
WO2020039146A1 (en) 2020-02-27
US11359508B2 (en) 2022-06-14
FR3085172B1 (en) 2021-03-05

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