EP3987155B1 - Method for coating a turbomachine guide vane and associated guide vane - Google Patents

Method for coating a turbomachine guide vane and associated guide vane Download PDF

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Publication number
EP3987155B1
EP3987155B1 EP20785773.1A EP20785773A EP3987155B1 EP 3987155 B1 EP3987155 B1 EP 3987155B1 EP 20785773 A EP20785773 A EP 20785773A EP 3987155 B1 EP3987155 B1 EP 3987155B1
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EP
European Patent Office
Prior art keywords
thickness
coating
grooved zone
zone
vane
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.)
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Application number
EP20785773.1A
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German (de)
French (fr)
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EP3987155A1 (en
Inventor
Célia Iglesias Cano
Vincent Marie Jacques Rémi De Carné-Carnavalet
Antoine Hubert Marie Jean Masson
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3987155A1 publication Critical patent/EP3987155A1/en
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular

Definitions

  • the invention relates to the general field of turbomachines.
  • the invention relates more particularly to a process for coating a turbine engine stator vane making it possible to optimize the aerodynamic performance of said vane.
  • the invention also relates to a stator vane provided with a coating.
  • a dual-flow turbomachine comprises, at its upstream end, an air inlet supplying a fan which delivers an annular air flow splitting into two flows.
  • Part of the flow is injected into a compressor which powers a turbine driving the fan.
  • the other part of the flow is injected into the atmosphere to provide part of the thrust of the turbomachine, after having passed through a ring of fixed blades arranged downstream of the fan.
  • the crown of fixed vanes called a rectifier (also known by the acronym OGV for “Outlet Guide Valve”), makes it possible to straighten the flow of air at the outlet of the fan in the secondary flow.
  • the stator vanes made of composite material, are manufactured using a known process called "RTM” (Resin Transfer Moulding).
  • the RTM process consists of injecting a liquid resin into layers of dry reinforcing fibers previously preformed to the shape of the blade and placed in a closed mold placed under vacuum. After the molding step, it is known to deposit a metallic reinforcement, in the form of a foil, on the leading edge of the blade in order to protect it from erosion and/or shocks. possible (birds, gravel, ice, sand, etc.). Alternatively, the metal reinforcement is placed on the layers of preformed reinforcing fibers during the step of injecting the resin.
  • a polymer coating with grooves is applied to surfaces exposed to airflow. These grooves are oriented in the flow direction of the air flow and make it possible to reduce the friction generated by the turbulent boundary layers on the surface of the blades exposed to the secondary flow.
  • the document EN 3041375 discloses an example of such a coating.
  • the presence of the grooves makes it possible to reduce between 5 and 10% of the drag of friction generated by the turbulent boundary layers, they can also lead to an increase in friction when it comes to laminar boundary layers.
  • the grooves can generate significant aerodynamic losses if they act on separated boundary layers or more generally on chaotic non-oriented flows.
  • the invention offers a solution to the problems mentioned above, making it possible to limit the friction of the air flow on the surface of a stator vane.
  • a first aspect of the invention relates to a process for coating a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.
  • the aerodynamic performance of the blade is improved.
  • the coating process according to the invention makes it possible to obtain a stator vane having a grooved zone on the surfaces exposed to a turbulent flow and a substantially flat zone, i.e. the paint layer, on the surfaces exposed to a flow. laminar.
  • the presence of said zones on one of the surfaces of the blade makes it possible to reduce the frictional drag generated by the secondary flow during its passage over the exposed surfaces of the blade.
  • the fact that the paint layer is in the continuity of the grooved zone makes it possible to limit the steps in the surface transitions and therefore to limit the aerodynamic losses associated with the presence of such steps.
  • the steps consisting in completely covering the face of the blade with a polymer coating provided with grooves and then proceeding with the removal of the grooves on a determined zone of the polymer coating make it possible to simplify the integration of the polymer coating on the blade.
  • the fact of keeping part of the polymer coating, i.e. the non-grooved zone, on a zone where the grooves are not desired makes it possible to limit the quantity of paint necessary to fill the thickness of polymer coating previously removed. Thus, this makes it possible to reduce manufacturing costs as well as the risks of non-compliance due to the presence of the paint layer.
  • the coating process according to the first aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.
  • the step of removing the grooves is carried out by a sandblasting operation on a part of the polymer coating intended to form the non-grooved zone.
  • the sandblasting operation is carried out at a pressure greater than 2.5 bars.
  • the coating process comprises a step of depositing a protective film on a part of the polymer coating intended to form the grooved zone.
  • a second aspect of the invention relates to a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.
  • stator vane according to the second aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.
  • the polymer coating is made of polyurethane.
  • the paint layer is made of polyurethane.
  • the paint layer extends over the extrados face, along the root of the blade.
  • the paint layer extends over the extrados face, along the leading edge.
  • the invention according to a third aspect relates to a turbomachine stator comprising at least one blade according to the second aspect of the invention.
  • FIG. 1 shows a schematic representation in longitudinal section of a bypass turbomachine 1.
  • a dual-flow turbomachine 1 has a longitudinal axis A and comprises an outer casing 10 inside which are arranged, from upstream to downstream, a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, a chamber combustion chamber 18, a high pressure turbine 20, a low pressure turbine 22 and an exhaust cone 24.
  • An inner casing 28 is arranged in the outer casing 10, around the compressors 14 and 16, of the combustion chamber 18 and turbines 20 and 22.
  • a rectifier 30 extends downstream of the fan 12, between the inner 28 and outer 10 casings, in the region of the compressors 14 and 16.
  • the inner casing 28 divides the flow of air accelerated by the fan 12 between a primary flow Fp which supplies the compressors 14 and 16, and a secondary flow Fs which flows between the inner 28 and outer 10 casings and is thus ejected from the turbomachine 1 after passing through the rectifier 30 to provide part of the thrust.
  • the rectifier 30, also designated by the acronym OGV for "Outlet Guide Vane" makes it possible to straighten the secondary flow Fs at the outlet of the fan 12 and comprises a plurality of fixed vanes 100 arranged in a crown around a ring 32 carried through the inner casing 28.
  • FIG. 2 illustrates a vane 100 of a stator 30 according to a first embodiment of the invention.
  • the blade 100 of the rectifier 30 has a leading edge 101, and a trailing edge 102, extending between a radially inner end 103, called the root of the blade 100, and a radially outer end 104, called the tip of the blade 100.
  • the leading edge 101 and the trailing edge 102 delimit an extrados face 105 and an intrados face 106.
  • the blade 100 is for example manufactured using a molding process called RTM for "Resin Transfer Moulding" during which a resin liquid, preferably of the epoxy type, is injected into layers of dry reinforcing fibers, in particular made of carbon, previously preformed substantially to the shape of the blade 100 and placed in a closed mold placed under vacuum.
  • RTM Resin Transfer Moulding
  • the leading edge 101 is covered with a metal reinforcement 112, for example made of Nickel-Cobalt alloy.
  • the metallic reinforcement 112 is preferably injected onto the preform in layers of reinforcing fibers during the injection of the liquid resin.
  • a film of adhesive is positioned between the metal reinforcement 112 and the preform in order to ensure the maintenance of the metal reinforcement 112 on the leading edge 101.
  • the extrados face 105 is completely covered with a polymer coating 107, for example polyurethane.
  • the polymer coating 107 is fixed to the extrados face by means of an adhesive applied to the leading edge 101.
  • a part 109 of the polymer coating 107 which will be called the grooved zone, comprises a plurality of grooves 108 provided at the level of the part of the blade 100 intended to be exposed to turbulent flows.
  • the grooved zone 109 of generally rectangular shape, is delimited by the head 104 of the blade 100 and the trailing edge 102 so as to cover approximately 75% of the extrados face 105.
  • the grooves 108 also called riblets, have a shape, for example a U-shaped or V-shaped section, and dimensions adapted to the flow conditions of said secondary flow Fs.
  • the grooved zone 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 ⁇ m.
  • the other part 110 of the polymer coating 107 which will be called the non-grooved zone, is substantially flat and covers approximately 25% of the extrados face 105.
  • the non-grooved zone 110 extends along the foot 103 of blade 100 and along the metal reinforcement 112 so as to form an L.
  • the non-grooved zone 110 extends along the flow direction of the secondary flow Fs, ie for the portion which extends along the root 103 of the blade 100, and along a direction perpendicular to the direction of flow of the secondary flow Fs, ie for the portion which extends along the metal reinforcement 112.
  • the non-grooved zone 110 has a thickness e2 of between 100 and 200 ⁇ m.
  • the non-grooved area 110 is covered with a layer of paint 111, for example polyurethane, intended to be exposed to laminar flows.
  • the paint layer 111 has a thickness e3 such that when the paint layer 111 is applied to the non-grooved zone 110, the thickness of the paint layer 111 superimposed on the non-grooved zone 110 of the polymer coating 107 is substantially equal to the thickness e1 of the grooved zone 109 of the polymer coating 107.
  • the layer of paint 111 has a thickness e3 of between 80 and 120 ⁇ m.
  • the intrados face 106 is also covered with a polymer coating 107 and with a layer of paint 111 arranged on the surface of the blade 100 according to the flow conditions of the secondary flow Fs on the intrados face 106.
  • FIG. 3a is a block diagram illustrating the steps of the coating process 200 of the blade 100 of the stator 30 according to one embodiment of the invention. It should be noted that the coating process 200 according to the invention takes place after the manufacture of the blade 100 and the deposition of the metal reinforcement 112.
  • FIG. 3b illustrates part of the stages of the coating process schematized in picture 3a .
  • a polymer coating 107, of thickness e1, having grooves 108 is applied over the entire extrados face 105.
  • a film of glue is used to maintain the polymer coating 107 on the extrados face 105 of the dawn 100.
  • a part 109 of the polymer coating 107 is covered with a protective film, for example made of polymer material.
  • a third step 203 the grooves 108 present on the other part of the polymer coating 107, ie which is not covered by the protective film, are removed so as to obtain a non-grooved zone 110, of thickness e2, and a grooved zone 109.
  • the grooves 108 are removed by a sandblasting operation, preferably at a pressure greater than 2.5 bars.
  • a fourth step 204 the protective film is removed from part 109 of polymer coating 107.
  • the non-grooved zone 110 is coated with a layer of paint 111 of thickness e3 so that the thickness of the layer of paint 111 superimposed on the non-grooved zone 110 is substantially equal to the thickness e1 of the grooved zone 109.
  • the layer of paint 111 of thickness e3 can be obtained by applying one or more layers of paint to the non-grooved zone 110.
  • FIG. 4 illustrates a vane 100 of a stator 30 according to a second embodiment of the invention.
  • the blade 100 according to the second embodiment is identical to the blade 100 according to the first embodiment, except that the grooved 109 and non-grooved 110 zones are arranged in another way on the extrados face 105 of the dawn 100.
  • the grooved zone 109 has a generally rectangular shape and is delimited by the head 104 of the blade 100, the trailing edge 102 and the metal reinforcement 112 so as to cover approximately 75% of the extrados face 105.
  • the zone grooved 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 ⁇ m.
  • the non-grooved zone 110 of generally rectangular shape extends only along the root 103 of the blade 100 so as to cover approximately 20% of the extrados face 105. In this configuration, the non-grooved zone 110 extends along only along the direction of flow of the secondary flow Fs.
  • the non-grooved zone 110 has a thickness e2 of between 100 and 200 ⁇ m.
  • the non-grooved zone 110 is also covered with a layer of paint 111 of thickness e3 so that the layer of paint 111 superimposed on the non-grooved zone 110 has a thickness substantially equal to the thickness e1 of the grooved zone 109.
  • the paint layer 111 has a thickness e3 of between 80 and 120 ⁇ m.
  • the vane 100 of the stator 30 according to the second embodiment is made using the coating process 200 described above.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

DOMAINE TECHNIQUE DE L'INVENTIONTECHNICAL FIELD OF THE INVENTION

L'invention se rapporte au domaine général des turbomachines.The invention relates to the general field of turbomachines.

L'invention concerne plus particulièrement à un procédé de revêtement d'une aube de redresseur de turbomachine permettant d'optimiser les performances aérodynamiques de ladite aube. L'invention se rapporte également à une aube de redresseur munie d'un revêtement.The invention relates more particularly to a process for coating a turbine engine stator vane making it possible to optimize the aerodynamic performance of said vane. The invention also relates to a stator vane provided with a coating.

ARRIERE-PLAN TECHNOLOGIQUE DE L'INVENTIONTECHNOLOGICAL BACKGROUND OF THE INVENTION

Une turbomachine à double flux comprend, à son extrémité amont, une entrée d'air alimentant une soufflante qui délivre un flux d'air annulaire se scindant en deux flux.A dual-flow turbomachine comprises, at its upstream end, an air inlet supplying a fan which delivers an annular air flow splitting into two flows.

Une partie du flux, appelé flux primaire, est injectée dans un compresseur qui alimente une turbine entraînant la soufflante. L'autre partie du flux, appelée flux secondaire, est injectée vers l'atmosphère pour fournir une partie de la poussée de la turbomachine, après avoir franchi une couronne d'aubes fixes disposée en aval de la soufflante.Part of the flow, called the primary flow, is injected into a compressor which powers a turbine driving the fan. The other part of the flow, called the secondary flow, is injected into the atmosphere to provide part of the thrust of the turbomachine, after having passed through a ring of fixed blades arranged downstream of the fan.

La couronne d'aubes fixes, appelée redresseur (également connue sous l'acronyme anglais OGV pour « Outlet Guide Vanne »), permet de redresser le flux d'air à la sortie de la soufflante dans le flux secondaire. Les aubes de redresseurs, réalisées en matériau composite, sont fabriquées en utilisant un procédé connu dit "RTM" (Resin Transfer Moulding).The crown of fixed vanes, called a rectifier (also known by the acronym OGV for “Outlet Guide Valve”), makes it possible to straighten the flow of air at the outlet of the fan in the secondary flow. The stator vanes, made of composite material, are manufactured using a known process called "RTM" (Resin Transfer Moulding).

Le procédé RTM consiste à injecter une résine liquide dans des couches de fibres de renfort sèches préalablement préformées à la forme de l'aube et disposées dans un moule fermé mis sous vide. Après l'étape de moulage, il est connu de déposer un renfort métallique, sous la forme d'un clinquant, sur le bord d'attaque de l'aube afin de le protéger de l'érosion et/ou de chocs éventuels (oiseaux, gravier, glace, sable, etc.). De manière alternative, le renfort métallique est disposé sur les couches de fibres de renfort préformées lors de l'étape d'injection de la résine.The RTM process consists of injecting a liquid resin into layers of dry reinforcing fibers previously preformed to the shape of the blade and placed in a closed mold placed under vacuum. After the molding step, it is known to deposit a metallic reinforcement, in the form of a foil, on the leading edge of the blade in order to protect it from erosion and/or shocks. possible (birds, gravel, ice, sand, etc.). Alternatively, the metal reinforcement is placed on the layers of preformed reinforcing fibers during the step of injecting the resin.

En outre, un revêtement polymère muni de rainures est appliqué sur les surfaces exposées aux flux d'air. Ces rainures sont orientées dans la direction d'écoulement du flux d'air et permettent de réduire les frottements générés par les couches limites turbulentes sur la surface des aubes exposées au flux secondaire. Le document FR 3041375 divulgue un exemple d'un tel revêtement.In addition, a polymer coating with grooves is applied to surfaces exposed to airflow. These grooves are oriented in the flow direction of the air flow and make it possible to reduce the friction generated by the turbulent boundary layers on the surface of the blades exposed to the secondary flow. The document EN 3041375 discloses an example of such a coating.

Si la présence des rainures permet de réduire entre 5 et 10% de la trainée de frottement générée par les couches limites turbulentes, ils peuvent également entrainer une augmentation des frottements lorsqu'il s'agit de couches limites laminaires. De plus, les rainures peuvent générer des pertes aérodynamiques importantes s'ils agissent sur des couches limites décollées ou plus généralement sur des écoulements chaotiques non orientés.If the presence of the grooves makes it possible to reduce between 5 and 10% of the drag of friction generated by the turbulent boundary layers, they can also lead to an increase in friction when it comes to laminar boundary layers. In addition, the grooves can generate significant aerodynamic losses if they act on separated boundary layers or more generally on chaotic non-oriented flows.

RESUME DE L'INVENTIONSUMMARY OF THE INVENTION

L'invention offre une solution aux problèmes évoqués précédemment, permettant de limiter les frottements du flux d'air à la surface d'une aube de redresseur.The invention offers a solution to the problems mentioned above, making it possible to limit the friction of the air flow on the surface of a stator vane.

Un premier aspect de l'invention concerne un procédé de revêtement d'une aube de redresseur de turbomachine comportant un pied et une tête, une face extrados et une face intrados reliées entre elles par un bord d'attaque et un bord de fuite.A first aspect of the invention relates to a process for coating a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.

Le procédé de revêtement selon le premier aspect comporte les étapes suivantes :

  • recouvrir intégralement une des faces de l'aube d'un revêtement polymère muni de rainures,
  • retirer les rainures d'une partie du revêtement polymère de manière à ce que le revêtement polymère comporte une zone rainurée d'épaisseur e1 et une zone non rainurée d'épaisseur e2,
  • enduire la zone non rainurée d'une couche de peinture d'épaisseur e3 de sorte que l'épaisseur de la couche de peinture superposée à la zone non rainurée soit sensiblement égale à l'épaisseur e1 de la zone rainurée.
The coating process according to the first aspect comprises the following steps:
  • completely cover one of the faces of the blade with a polymer coating fitted with grooves,
  • removing the grooves from part of the polymer coating so that the polymer coating comprises a grooved zone with a thickness of e1 and an ungrooved zone with a thickness of e2,
  • coating the non-grooved zone with a layer of paint of thickness e3 so that the thickness of the layer of paint superimposed on the non-grooved zone is substantially equal to the thickness e1 of the grooved zone.

Grâce au procédé de revêtement selon l'invention, les performances aérodynamiques de l'aube sont améliorées.Thanks to the coating process according to the invention, the aerodynamic performance of the blade is improved.

En effet, le procédé de revêtement selon l'invention permet d'obtenir une aube de redresseur présentant une zone rainurée sur les surfaces exposées à un écoulement turbulent et une zone sensiblement plane, i.e. la couche de peinture, sur les surfaces exposées à un écoulement laminaire. La présence desdites zones sur une des surfaces de l'aube permet de réduire la trainée de frottement générée par le flux secondaire lors de son passage sur les surfaces exposées de l'aube. De plus, le fait que la couche de peinture soit dans la continuité de la zone rainurée permet de limiter les marches dans les transitions de surface et donc de limiter les pertes aérodynamiques associées à la présence de telles marches.Indeed, the coating process according to the invention makes it possible to obtain a stator vane having a grooved zone on the surfaces exposed to a turbulent flow and a substantially flat zone, i.e. the paint layer, on the surfaces exposed to a flow. laminar. The presence of said zones on one of the surfaces of the blade makes it possible to reduce the frictional drag generated by the secondary flow during its passage over the exposed surfaces of the blade. In addition, the fact that the paint layer is in the continuity of the grooved zone makes it possible to limit the steps in the surface transitions and therefore to limit the aerodynamic losses associated with the presence of such steps.

En outre, les étapes consistant à recouvrir intégralement la face de l'aube d'un revêtement polymère muni de rainures puis à procéder au retrait des rainures sur une zone déterminée du revêtement polymère permettent de simplifier l'intégration du revêtement polymère sur l'aube. De plus, le fait de garder une partie du revêtement polymère, i.e. la zone non rainurée, sur une zone où les rainures ne sont pas souhaitées permet de limiter la quantité de peinture nécessaire pour combler l'épaisseur de revêtement polymère préalablement retiré. Ainsi, cela permet de réduire les coûts de fabrication ainsi que les risques de non-conformité dus à la présence de la couche de peinture.In addition, the steps consisting in completely covering the face of the blade with a polymer coating provided with grooves and then proceeding with the removal of the grooves on a determined zone of the polymer coating make it possible to simplify the integration of the polymer coating on the blade. . In addition, the fact of keeping part of the polymer coating, i.e. the non-grooved zone, on a zone where the grooves are not desired makes it possible to limit the quantity of paint necessary to fill the thickness of polymer coating previously removed. Thus, this makes it possible to reduce manufacturing costs as well as the risks of non-compliance due to the presence of the paint layer.

Outre les caractéristiques qui viennent d'être évoquées dans le paragraphe précédent, le procédé de revêtement selon le premier aspect de l'invention peut présenter une ou plusieurs caractéristiques complémentaires parmi les suivantes, considérées individuellement ou selon toutes les combinaisons techniquement possibles.In addition to the characteristics which have just been mentioned in the preceding paragraph, the coating process according to the first aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.

Selon un mode de réalisation non limitatif, l'étape de retrait des rainures est réalisée par une opération de sablage sur une partie du revêtement polymère destiné à former la zone non rainurée.According to a non-limiting embodiment, the step of removing the grooves is carried out by a sandblasting operation on a part of the polymer coating intended to form the non-grooved zone.

Selon un mode de réalisation non limitatif, l'opération de sablage est réalisée à une pression supérieure à 2,5 Bars.According to a non-limiting embodiment, the sandblasting operation is carried out at a pressure greater than 2.5 bars.

Selon un mode de réalisation non limitatif, préalablement à l'étape de retrait, le procédé de revêtement comporte une étape de dépôt d'un film protecteur sur une partie du revêtement polymère destinée à former la zone rainurée.According to a non-limiting embodiment, prior to the removal step, the coating process comprises a step of depositing a protective film on a part of the polymer coating intended to form the grooved zone.

Un deuxième aspect de l'invention concerne une aube de redresseur de turbomachine comportant un pied et une tête, une face extrados et une face intrados reliées entre elles par un bord d'attaque et un bord de fuite.A second aspect of the invention relates to a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.

L'aube selon le deuxième aspect étant caractérisée en ce que :

  • au moins une de ses faces est intégralement recouverte d'un revêtement polymère comportant :
    • o une zone rainurée d'épaisseur e1,
    • o une zone non rainurée d'épaisseur e2 inférieure à l'épaisseur e1 de la zone rainurée,
  • une couche de peinture, d'épaisseur e3, recouvre la zone non rainurée de sorte que l'épaisseur de la couche de peinture superposée à la zone non rainurée soit sensiblement égale à l'épaisseur e1 de la zone rainurée.
The dawn according to the second aspect being characterized in that:
  • at least one of its faces is entirely covered with a polymer coating comprising:
    • o a grooved zone of thickness e1,
    • o a non-grooved zone of thickness e2 less than the thickness e1 of the grooved zone,
  • a layer of paint, of thickness e3, covers the non-grooved zone so that the thickness of the layer of paint superimposed on the non-grooved zone is substantially equal to the thickness e1 of the grooved zone.

Outre les caractéristiques qui viennent d'être évoquées dans le paragraphe précédent, l'aube de redresseur selon le deuxième aspect de l'invention peut présenter une ou plusieurs caractéristiques complémentaires parmi les suivantes, considérées individuellement ou selon toutes les combinaisons techniquement possibles.In addition to the characteristics which have just been mentioned in the preceding paragraph, the stator vane according to the second aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.

Selon un mode de réalisation non limitatif, le revêtement polymère est en polyuréthane.According to a non-limiting embodiment, the polymer coating is made of polyurethane.

Selon un mode de réalisation non limitatif, la couche de peinture est en polyuréthane.According to a non-limiting embodiment, the paint layer is made of polyurethane.

Selon un mode de réalisation non limitatif, la couche de peinture s'étend sur la face extrados, le long du pied de l'aube.According to a non-limiting embodiment, the paint layer extends over the extrados face, along the root of the blade.

Selon un mode de réalisation non limitatif, la couche de peinture s'étend sur la face extrados, le long du bord d'attaque.According to a non-limiting embodiment, the paint layer extends over the extrados face, along the leading edge.

L'invention selon un troisième aspect concerne un redresseur de turbomachine comportant au moins une aube selon le deuxième aspect de l'invention.The invention according to a third aspect relates to a turbomachine stator comprising at least one blade according to the second aspect of the invention.

L'invention et ses différentes applications seront mieux comprises à la lecture de la description qui suit et à l'examen des figures qui l'accompagnent.The invention and its various applications will be better understood on reading the following description and on examining the accompanying figures.

BREVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF FIGURES

Les figures sont présentées à titre indicatif et nullement limitatif de l'invention.

  • La figure 1 illustre une vue en coupe longitudinale d'une turbomachine à double flux,
  • La figure 2 illustre une aube de redresseur de turbomachine selon un premier mode de réalisation de l'invention,
  • La figure 3a est un schéma en bloc illustrant les étapes du procédé de revêtement selon un mode de réalisation de l'invention,
  • La figure 3b, illustre une partie des étapes du procédé de revêtement schématisé à la figure 3a,
  • La figure 4 illustre une aube de redresseur de turbomachine selon un deuxième mode de réalisation de l'invention.
The figures are presented by way of indication and in no way limit the invention.
  • There figure 1 illustrates a longitudinal sectional view of a turbofan engine,
  • There figure 2 illustrates a turbomachine stator vane according to a first embodiment of the invention,
  • There picture 3a is a block diagram illustrating the steps of the coating process according to one embodiment of the invention,
  • There figure 3b , illustrates part of the stages of the coating process schematized in picture 3a ,
  • There figure 4 illustrates a turbomachine stator vane according to a second embodiment of the invention.

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

Les figures sont présentées à titre indicatif et nullement limitatif de l'invention.The figures are presented by way of indication and in no way limit the invention.

Sauf précision contraire, un même élément apparaissant sur des figures différentes présente une référence unique.Unless specified otherwise, the same element appearing in different figures has a single reference.

[Fig. 1] montre une représentation schématique en coupe longitudinale d'une turbomachine 1 à double flux.[ Fig. 1 ] shows a schematic representation in longitudinal section of a bypass turbomachine 1.

Dans la suite de la description, les termes « interne » et « externe », « axial » et « radial », et leurs dérivés, sont définis par rapport à l'axe longitudinal A de la turbomachine 1.In the rest of the description, the terms “internal” and “external”, “axial” and “radial”, and their derivatives, are defined with respect to the longitudinal axis A of the turbomachine 1.

En référence à la figure 1, une turbomachine 1 à double flux présente un axe longitudinal A et comprend un carter extérieur 10 à l'intérieur duquel sont disposés, d'amont en aval, une soufflante 12, un compresseur basse pression 14, un compresseur haute pression 16, une chambre de combustion 18, une turbine haute pression 20, une turbine basse pression 22 ainsi qu'un cône d'échappement 24. Un carter intérieur 28 est disposé dans le carter extérieur 10, autour des compresseurs 14 et 16, de la chambre de combustion 18 et des turbines 20 et 22. En outre, un redresseur 30 s'étend en aval de la soufflante 12, entre les carters intérieur 28 et extérieur 10, dans la région des compresseurs 14 et 16.With reference to the figure 1 , a dual-flow turbomachine 1 has a longitudinal axis A and comprises an outer casing 10 inside which are arranged, from upstream to downstream, a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, a chamber combustion chamber 18, a high pressure turbine 20, a low pressure turbine 22 and an exhaust cone 24. An inner casing 28 is arranged in the outer casing 10, around the compressors 14 and 16, of the combustion chamber 18 and turbines 20 and 22. In addition, a rectifier 30 extends downstream of the fan 12, between the inner 28 and outer 10 casings, in the region of the compressors 14 and 16.

En fonctionnement, le carter intérieur 28 divise le flux d'air accéléré par la soufflante 12 entre un flux primaire Fp qui alimente les compresseurs 14 et 16, et un flux secondaire Fs qui s'écoule entre les carters intérieur 28 et extérieur 10 et est ainsi éjecté de la turbomachine 1 après avoir franchi le redresseur 30 pour fournir une partie de la poussée.In operation, the inner casing 28 divides the flow of air accelerated by the fan 12 between a primary flow Fp which supplies the compressors 14 and 16, and a secondary flow Fs which flows between the inner 28 and outer 10 casings and is thus ejected from the turbomachine 1 after passing through the rectifier 30 to provide part of the thrust.

Le redresseur 30, également désigné par l'acronyme OGV pour « Outlet Guide Vane », permet de redresser le flux secondaire Fs en sortie de la soufflante 12 et comprend une pluralité d'aubes 100 fixes disposées en couronne autour d'un anneau 32 porté par le carter intérieur 28.The rectifier 30, also designated by the acronym OGV for "Outlet Guide Vane", makes it possible to straighten the secondary flow Fs at the outlet of the fan 12 and comprises a plurality of fixed vanes 100 arranged in a crown around a ring 32 carried through the inner casing 28.

[Fig. 2] illustre une aube 100 de redresseur 30 selon un premier mode de réalisation de l'invention.[ Fig. 2 ] illustrates a vane 100 of a stator 30 according to a first embodiment of the invention.

En référence à la figure 2, l'aube 100 du redresseur 30 présente un bord d'attaque 101, et un bord de fuite 102, s'étendant entre une extrémité radialement interne 103, appelée pied de l'aube 100, et une extrémité radialement externe 104, appelée tête de l'aube 100. Le bord d'attaque 101 et le bord de fuite 102 délimitent une face extrados 105 et une face intrados 106.With reference to the picture 2 , the blade 100 of the rectifier 30 has a leading edge 101, and a trailing edge 102, extending between a radially inner end 103, called the root of the blade 100, and a radially outer end 104, called the tip of the blade 100. The leading edge 101 and the trailing edge 102 delimit an extrados face 105 and an intrados face 106.

L'aube 100 est par exemple fabriquée en utilisant un procédé de moulage appelé RTM pour « Resin Transfer Moulding » au cours duquel une résine liquide, préférentiellement de type époxy, est injectée dans des couches de fibres de renfort sèches, notamment en carbone, préalablement préformées sensiblement à la forme de l'aube 100 et disposées dans un moule fermé mis sous vide.The blade 100 is for example manufactured using a molding process called RTM for "Resin Transfer Moulding" during which a resin liquid, preferably of the epoxy type, is injected into layers of dry reinforcing fibers, in particular made of carbon, previously preformed substantially to the shape of the blade 100 and placed in a closed mold placed under vacuum.

Par ailleurs, afin de protéger le bord d'attaque 101 de l'érosion et/ou des chocs éventuels, celui-ci est recouvert d'un renfort métallique 112, par exemple en alliage Nickel-Cobalt. Le renfort métallique 112 est de préférence injecté sur la préforme en couches de fibres de renfort pendant l'injection de la résine liquide. Avantageusement, un film de colle est positionné entre le renfort métallique 112 et la préforme afin d'assurer le maintien du renfort métallique 112 sur le bord d'attaque 101.Furthermore, in order to protect the leading edge 101 from erosion and/or possible shocks, the latter is covered with a metal reinforcement 112, for example made of Nickel-Cobalt alloy. The metallic reinforcement 112 is preferably injected onto the preform in layers of reinforcing fibers during the injection of the liquid resin. Advantageously, a film of adhesive is positioned between the metal reinforcement 112 and the preform in order to ensure the maintenance of the metal reinforcement 112 on the leading edge 101.

En outre, la face extrados 105 est intégralement recouverte d'un revêtement polymère 107, par exemple en polyuréthane. Avantageusement, le revêtement polymère 107 est fixé à la face extrados au moyen d'une colle appliquée sur le bord d'attaque 101.In addition, the extrados face 105 is completely covered with a polymer coating 107, for example polyurethane. Advantageously, the polymer coating 107 is fixed to the extrados face by means of an adhesive applied to the leading edge 101.

Une partie 109 du revêtement polymère 107, que l'on appellera zone rainurée, comprend une pluralité de rainures 108 ménagées au niveau de la partie de l'aube 100 destinée à être exposée aux écoulements turbulents. La zone rainurée 109, de forme globalement rectangulaire, est délimitée par la tête 104 de l'aube 100 et le bord de fuite 102 de manière à recouvrir environ 75% de la face extrados 105. Les rainures 108, appelées également riblets, présentent une forme, par exemple une section en forme de U ou de V, et des dimensions adaptées aux conditions d'écoulement dudit flux secondaire Fs. Avantageusement, la zone rainurée 109 du revêtement polymère 107 présente une épaisseur e1 comprise entre 200 et 300 µm.A part 109 of the polymer coating 107, which will be called the grooved zone, comprises a plurality of grooves 108 provided at the level of the part of the blade 100 intended to be exposed to turbulent flows. The grooved zone 109, of generally rectangular shape, is delimited by the head 104 of the blade 100 and the trailing edge 102 so as to cover approximately 75% of the extrados face 105. The grooves 108, also called riblets, have a shape, for example a U-shaped or V-shaped section, and dimensions adapted to the flow conditions of said secondary flow Fs. Advantageously, the grooved zone 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 μm.

L'autre partie 110 du revêtement polymère 107, que l'on appellera zone non rainurée, est sensiblement plane et recouvre environ 25 % de la face extrados 105. En particulier, la zone non rainurée 110 s'étend le long du pied 103 de l'aube 100 et le long du renfort métallique 112 de manière à former un L. Dans cette configuration, la zone non rainurée 110 s'étend suivant la direction d'écoulement du flux secondaire Fs, i.e. pour la portion qui s'étend le long du pied 103 de l'aube 100, et selon suivant une direction perpendiculaire à la direction d'écoulement du flux secondaire Fs, i.e. pour la portion qui s'étend le long du renfort métallique 112. Avantageusement, la zone non rainurée 110 présente une épaisseur e2 comprise entre 100 et 200 µm.The other part 110 of the polymer coating 107, which will be called the non-grooved zone, is substantially flat and covers approximately 25% of the extrados face 105. In particular, the non-grooved zone 110 extends along the foot 103 of blade 100 and along the metal reinforcement 112 so as to form an L. In this configuration, the non-grooved zone 110 extends along the flow direction of the secondary flow Fs, ie for the portion which extends along the root 103 of the blade 100, and along a direction perpendicular to the direction of flow of the secondary flow Fs, ie for the portion which extends along the metal reinforcement 112. Advantageously, the non-grooved zone 110 has a thickness e2 of between 100 and 200 μm.

De plus, la zone non rainurée 110 est recouverte d'une couche de peinture 111, par exemple en polyuréthane, destinée à être exposée aux écoulements laminaires. La couche de peinture 111 présente une épaisseur e3 telle que lorsque la couche de peinture 111 est appliquée sur la zone non rainurée 110, l'épaisseur de la couche de peinture 111 superposée à la zone non rainurée 110 du revêtement polymère 107 est sensiblement égale à l'épaisseur e1 de la zone rainurée 109 du revêtement polymère 107. Avantageusement, la couche de peinture 111 présente une épaisseur e3 comprise entre 80 et 120 µm.In addition, the non-grooved area 110 is covered with a layer of paint 111, for example polyurethane, intended to be exposed to laminar flows. The paint layer 111 has a thickness e3 such that when the paint layer 111 is applied to the non-grooved zone 110, the thickness of the paint layer 111 superimposed on the non-grooved zone 110 of the polymer coating 107 is substantially equal to the thickness e1 of the grooved zone 109 of the polymer coating 107. Advantageously, the layer of paint 111 has a thickness e3 of between 80 and 120 μm.

Avantageusement, la face intrados 106 est également recouverte d'un revêtement polymère 107 et d'une couche de peinture 111 agencées à la surface de l'aube 100 selon les conditions d'écoulement du flux secondaire Fs sur la face intrados 106.Advantageously, the intrados face 106 is also covered with a polymer coating 107 and with a layer of paint 111 arranged on the surface of the blade 100 according to the flow conditions of the secondary flow Fs on the intrados face 106.

[Fig. 3a] est un schéma en bloc illustrant les étapes du procédé de revêtement 200 de l'aube 100 de redresseur 30 selon un mode de réalisation de l'invention. À noter que le procédé de revêtement 200 selon l'invention intervient après la fabrication de l'aube 100 et le dépôt du renfort métallique 112.[ Fig. 3a ] is a block diagram illustrating the steps of the coating process 200 of the blade 100 of the stator 30 according to one embodiment of the invention. It should be noted that the coating process 200 according to the invention takes place after the manufacture of the blade 100 and the deposition of the metal reinforcement 112.

[Fig. 3b] illustre une partie des étapes du procédé de revêtement schématisé à la figure 3a.[ Fig. 3b ] illustrates part of the stages of the coating process schematized in picture 3a .

Dans une première étape 201, un revêtement polymère 107, d'épaisseur e1, présentant des rainures 108 est appliqué sur toute la face extrados 105. Avantageusement, un film de colle est utilisé pour maintenir le revêtement polymère 107 sur la face extrados 105 de l'aube 100.In a first step 201, a polymer coating 107, of thickness e1, having grooves 108 is applied over the entire extrados face 105. Advantageously, a film of glue is used to maintain the polymer coating 107 on the extrados face 105 of the dawn 100.

Dans une deuxième étape 202, une partie 109 du revêtement polymère 107 est recouverte d'un film protecteur, par exemple en matériau polymère.In a second step 202, a part 109 of the polymer coating 107 is covered with a protective film, for example made of polymer material.

Dans une troisième étape 203, les rainures 108 présentes sur l'autre partie du revêtement polymère 107, i.e. qui n'est pas recouverte par le film protecteur, sont retirées de manière à obtenir une zone non rainurée 110, d'épaisseur e2, et une zone rainurée 109. Avantageusement, le retrait des rainures 108 est réalisé par une opération de sablage, de préférence à une pression supérieure à 2,5 Bars.In a third step 203, the grooves 108 present on the other part of the polymer coating 107, ie which is not covered by the protective film, are removed so as to obtain a non-grooved zone 110, of thickness e2, and a grooved zone 109. Advantageously, the grooves 108 are removed by a sandblasting operation, preferably at a pressure greater than 2.5 bars.

Dans une quatrième étape 204, le film protecteur est retiré de la partie 109 du revêtement polymère 107.In a fourth step 204, the protective film is removed from part 109 of polymer coating 107.

Dans une cinquième étape 205, la zone non rainurée 110 est enduite d'une couche de peinture 111 d'épaisseur e3 de sorte que l'épaisseur de la couche de peinture 111 superposée à la zone non rainurée 110 soit sensiblement égale à l'épaisseur e1 de la zone rainurée 109. À noter que la couche de peinture 111 d'épaisseur e3 peut être obtenue par l'application d'une ou plusieurs couches de peinture sur la zone non rainurée 110.In a fifth step 205, the non-grooved zone 110 is coated with a layer of paint 111 of thickness e3 so that the thickness of the layer of paint 111 superimposed on the non-grooved zone 110 is substantially equal to the thickness e1 of the grooved zone 109. It should be noted that the layer of paint 111 of thickness e3 can be obtained by applying one or more layers of paint to the non-grooved zone 110.

[Fig. 4] illustre une aube 100 de redresseur 30 selon un deuxième mode de réalisation de l'invention.[ Fig. 4 ] illustrates a vane 100 of a stator 30 according to a second embodiment of the invention.

L'aube 100 selon le deuxième mode de réalisation est identique à l'aube 100 selon le premier mode de réalisation, à la différence que les zones rainurée 109 et non rainurée 110 sont agencées d'une autre manière sur la face extrados 105 de l'aube 100.The blade 100 according to the second embodiment is identical to the blade 100 according to the first embodiment, except that the grooved 109 and non-grooved 110 zones are arranged in another way on the extrados face 105 of the dawn 100.

Comme on peut le voir sur la figure 4, la zone rainurée 109 présente une forme globalement rectangulaire et est délimitée par la tête 104 de l'aube 100, le bord de fuite 102 et le renfort métallique 112 de manière à recouvrir environ 75% de la face extrados 105. Avantageusement, la zone rainurée 109 du revêtement polymère 107 présente une épaisseur e1 comprise entre 200 et 300 µm.As can be seen on the figure 4 , the grooved zone 109 has a generally rectangular shape and is delimited by the head 104 of the blade 100, the trailing edge 102 and the metal reinforcement 112 so as to cover approximately 75% of the extrados face 105. Advantageously, the zone grooved 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 μm.

La zone non rainurée 110 de forme globalement rectangulaire s'étend uniquement le long du pied 103 de l'aube 100 de manière à recouvrir environ 20 % de la face extrados 105. Dans cette configuration, la zone non rainurée 110 s'étend suivant uniquement suivant la direction d'écoulement du flux secondaire Fs. Avantageusement, la zone non rainurée 110 présente une épaisseur e2 comprise entre 100 et 200 µm.The non-grooved zone 110 of generally rectangular shape extends only along the root 103 of the blade 100 so as to cover approximately 20% of the extrados face 105. In this configuration, the non-grooved zone 110 extends along only along the direction of flow of the secondary flow Fs. Advantageously, the non-grooved zone 110 has a thickness e2 of between 100 and 200 μm.

La zone non rainurée 110 est également recouverte d'une couche de peinture 111 d'épaisseur e3 de sorte que la couche de peinture 111 superposée à la zone non rainurée 110 présente une épaisseur sensiblement égale à l'épaisseur e1 de la zone rainurée 109. Avantageusement, la couche de peinture 111 présente une épaisseur e3 comprise entre 80 et 120 µm.The non-grooved zone 110 is also covered with a layer of paint 111 of thickness e3 so that the layer of paint 111 superimposed on the non-grooved zone 110 has a thickness substantially equal to the thickness e1 of the grooved zone 109. Advantageously, the paint layer 111 has a thickness e3 of between 80 and 120 μm.

L'aube 100 de redresseur 30 selon le deuxième mode de réalisation est réalisée en utilisant le procède de revêtement 200 décrit précédemment.The vane 100 of the stator 30 according to the second embodiment is made using the coating process 200 described above.

Claims (10)

  1. Method for coating (200) a turbomachine (1) guide (30) vane (100) comprising a root (103) and a tip (104), an extrados face (105) and an intrados face (106) connected to one another by a leading edge (101) and a trailing edge (102), the method for coating (200) being characterised in that it comprises the following steps:
    - completely covering (201) one of the faces (105, 106) of the vane (100) with a polymer coating (107) of thickness (e1) provided with grooves (108),
    - removing (203) the grooves (108) from a part of the polymer coating (107) in such a way that the polymer coating (107) comprises a grooved zone (109) and a non-grooved zone (110),
    - coating (205) the non-grooved zone (110) with a coat of paint (111) of thickness (e3) such that the thickness of the coat of paint (111) superimposed on the non-grooved zone (110) is substantially equal to the thickness (e1) of the grooved zone (109).
  2. Method for coating (200) according to the preceding claim, characterised in that the step of removal (205) of the grooves (108) is carried out by a sanding operation on a part of the polymer coating (107) intended to form the non-grooved zone (110).
  3. Method for coating (200) according to the preceding claim, characterised in that the sanding operation is carried out at a pressure greater than 2.5 bars.
  4. Method for coating (200) according to one of the preceding claims, characterised in that, prior to the step of removal (205), the method for coating (200) comprises a step of deposition (20) of a protective film on a part of the polymer coating (107) intended to form the grooved zone (109).
  5. Turbomachine (1) guide (30) vane (100) comprising a root (103) and a tip (104), an extrados face (105) and an intrados face (106) connected to one another by a leading edge (101) and a trailing edge (102), the vane (100) being characterised in that:
    - at least one of its faces (105, 106) is completely covered with a polymer coating (107) comprising:
    ∘ a grooved zone (109) of thickness (e1),
    ∘ a non-grooved zone (110) of thickness (e2) less than the thickness (e1) of the grooved zone (109),
    - a coat of paint (111), of thickness (e3), covers the non-grooved zone (110) such that the thickness of the coat of paint (111) superimposed on the non-grooved zone (109) is substantially equal to the thickness (e1) of the grooved zone (109).
  6. Guide (30) vane (100) according to the preceding claim, characterised in that the polymer coating (107) is made of polyurethane.
  7. Guide (30) vane (100) according to one of claims 5 to 6, characterised in that the coat of paint (111) is made of polyurethane.
  8. Guide (30) vane (100) according to one of claims 5 to 7, characterised in that the coat of paint (111) extends onto the extrados face (105), along the root (103) of the vane (100).
  9. Guide (30) vane (100) according to the preceding claim, characterised in that the coat of paint (111) extends onto the extrados face (105), along the leading edge (101).
  10. Turbomachine (1) guide (30), characterised in that it comprises at least one vane (100) according to any of claims 5 to 9.
EP20785773.1A 2019-06-20 2020-06-18 Method for coating a turbomachine guide vane and associated guide vane Active EP3987155B1 (en)

Applications Claiming Priority (2)

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FR1906647A FR3097452B1 (en) 2019-06-20 2019-06-20 PROCESS FOR COATING A TURBOMACHINE RECTIFIER VANE, ASSOCIATED RECTIFIER VANE
PCT/FR2020/051055 WO2020254764A1 (en) 2019-06-20 2020-06-18 Method for coating a turbomachine guide vane and associated guide vane

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CN108843402A (en) * 2018-06-08 2018-11-20 南京赛达机械制造有限公司 A kind of high temperature resistant titanium alloy turbine blade

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EP3987155A1 (en) 2022-04-27
FR3097452A1 (en) 2020-12-25
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FR3097452B1 (en) 2021-05-21
WO2020254764A1 (en) 2020-12-24
CN114008298A (en) 2022-02-01
US11898466B2 (en) 2024-02-13

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