FR3128150A1 - Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process - Google Patents
Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process Download PDFInfo
- Publication number
- FR3128150A1 FR3128150A1 FR2111016A FR2111016A FR3128150A1 FR 3128150 A1 FR3128150 A1 FR 3128150A1 FR 2111016 A FR2111016 A FR 2111016A FR 2111016 A FR2111016 A FR 2111016A FR 3128150 A1 FR3128150 A1 FR 3128150A1
- Authority
- FR
- France
- Prior art keywords
- riblets
- counterform
- protective coating
- printed
- aeronautical
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 37
- 239000011253 protective coating Substances 0.000 claims abstract description 18
- 238000000576 coating method Methods 0.000 claims abstract description 17
- 239000011248 coating agent Substances 0.000 claims abstract description 16
- 238000005260 corrosion Methods 0.000 claims abstract description 13
- 238000009434 installation Methods 0.000 claims abstract description 9
- 239000003973 paint Substances 0.000 claims description 8
- 229920006264 polyurethane film Polymers 0.000 claims description 3
- 238000006116 polymerization reaction Methods 0.000 claims description 2
- 239000004814 polyurethane Substances 0.000 description 12
- 238000011282 treatment Methods 0.000 description 3
- 230000003628 erosive effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002519 antifouling agent Substances 0.000 description 1
- 230000000739 chaotic effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000010147 laser engraving Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C59/00—Surface shaping of articles, e.g. embossing; Apparatus therefor
- B29C59/02—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing
- B29C59/026—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing of layered or coated substantially flat surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C59/00—Surface shaping of articles, e.g. embossing; Apparatus therefor
- B29C59/02—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing
- B29C59/022—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing characterised by the disposition or the configuration, e.g. dimensions, of the embossments or the shaping tools therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
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- 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
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/002—Influencing flow of fluids by influencing the boundary layer
- F15D1/0085—Methods of making characteristic surfaces for influencing the boundary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C59/00—Surface shaping of articles, e.g. embossing; Apparatus therefor
- B29C59/02—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing
- B29C59/022—Surface shaping of articles, e.g. embossing; Apparatus therefor by mechanical means, e.g. pressing characterised by the disposition or the configuration, e.g. dimensions, of the embossments or the shaping tools therefor
- B29C2059/023—Microembossing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
- B29C35/0227—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould using pressure vessels, e.g. autoclaves, vulcanising pans
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/26—Boundary layer controls by using rib lets or hydrophobic surfaces
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/002—Influencing flow of fluids by influencing the boundary layer
- F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
- F15D1/003—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions
- F15D1/0035—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions in the form of riblets
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
Procédé d ’ impression d e riblet s sur la surface d’une pièce et pièce aéronautique comportant des riblets imprimés par un tel procédé Un aspect de l’invention concerne un procédé d’impression de riblets (50) sur la surface d’une pièce aéronautique (10), comportant les opérations suivantes : application (110) d’un revêtement anti-corrosion (12) sur la surface de la pièce,application (120) d’un revêtement de protection (20), lisse, sur la surface de la pièce,installation (130), sur la surface de la pièce recouverte du revêtement de protection, d’une contreforme (30) comportant des empreintes (45) de riblets,installation (140), sur la contreforme (30), d’une plaque de pression (40)application (150) d’une pression prédéfinie sur la plaque de pression (40) pendant une durée prédéterminée, etretrait de la plaque de pression (40) et de la contreforme (30) de sorte à obtenir des riblets (50) imprimés sur le revêtement de protection (20) recouvrant la surface de la pièce. Un autre aspect de l’invention concerne une pièce aéronautique (10) comportant une surface au moins partiellement recouverte de riblets imprimés selon ce procédé. Figure à publier avec l’abrégé : Figure 3 Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process One aspect of the invention relates to a method of printing riblets (50) on the surface of an aeronautical part (10), comprising the following operations: application (110) of an anti-corrosion coating (12) to the surface of the part,application (120) of a protective coating (20), smooth, to the surface of the part,installation (130), on the surface of the part covered with the protective coating, a counterform (30) comprising imprints (45) of riblets, installation (140), on the counterform (30), of a pressure plate (40) application ( 150) of a predefined pressure on the pressure plate (40) for a predetermined duration, and removal of the pressure plate (40) and the counterform (30) so as to obtain riblets (50) printed on the coating of protection (20) covering the surface of the part. Another aspect of the invention relates to an aeronautical part (10) comprising a surface at least partially covered with riblets printed according to this process. Figure to be published with the abstract: Figure 3
Description
DOMAINE TECHNIQUE DE L’INVENTIONTECHNICAL FIELD OF THE INVENTION
La présente invention concerne un procédé pour imprimer des riblets à la surface d’une pièce aéronautique, comme une aube mobile ou fixe d’une turbomachine. Elle concerne également une pièce aéronautique revêtue de riblets imprimés au moyen d’un tel procédé.The present invention relates to a method for printing riblets on the surface of an aeronautical part, such as a moving or fixed blade of a turbomachine. It also relates to an aeronautical part coated with riblets printed by means of such a process.
L’invention trouve des applications dans le domaine de l’aéronautique et, en particulier, dans le domaine de la mécanique des fluides appliquée à des pièces aéronautiques telles que des pièces de turbomachines.The invention finds applications in the field of aeronautics and, in particular, in the field of fluid mechanics applied to aeronautical parts such as parts of turbomachines.
ARRIERE-PLAN TECHNOLOGIQUE DE L’INVENTIONTECHNOLOGICAL BACKGROUND OF THE INVENTION
Il est connu que les constructeurs aéronautiques cherchent en permanence à améliorer les performances aérodynamiques des aéronefs. En particulier, les motoristes cherchent à améliorer le rendement des moteurs d’avion, en analysant systématiquement et individuellement chaque source à l’origine de pertes de rendement afin de la réduire, voire de la supprimer. Parmi ces sources, les frottements de l’écoulement de l’air sur une surface rugueuse représentent une part non-négligeable des pertes totales. La proportion des frottements dans la génération des pertes dépend du nombre de Mach et de la complexité de la structure exposée à l’écoulement d’air.It is known that aircraft manufacturers are constantly seeking to improve the aerodynamic performance of aircraft. In particular, engine manufacturers seek to improve the efficiency of aircraft engines, by systematically and individually analyzing each source causing efficiency losses in order to reduce or even eliminate them. Among these sources, the friction of the air flow on a rough surface represents a non-negligible part of the total losses. The proportion of friction in the generation of losses depends on the Mach number and the complexity of the structure exposed to the airflow.
Pour des surfaces exposées à l’écoulement de l’air mais qui ne sont pas directement dans l’écoulement d’air (typiquement les parois de la veine d’air dans le cas d’une turbomachine), les frottements prennent une part encore plus prépondérante dans la génération des pertes. Afin de réduire ces pertes, il est possible de faire en sorte que les surfaces ne soient exposées qu’à des écoulements laminaires et non turbulents. Il est possible, alternativement, d’appliquer un traitement à la surface exposée à un écoulement turbulent de telle sorte que les pertes générées soient de moindre envergure.For surfaces exposed to the air flow but which are not directly in the air flow (typically the walls of the air stream in the case of a turbomachine), friction still plays a part more predominant in the generation of losses. In order to reduce these losses, it is possible to ensure that the surfaces are only exposed to laminar and non-turbulent flows. It is possible, alternatively, to apply a treatment to the surface exposed to a turbulent flow so that the losses generated are less extensive.
Un des traitements de surface connu pour réduire les frottements de l’écoulement d’air est le revêtement à base de riblets. Ce traitement consiste à revêtir la surface externe des éléments du moteur d’aéronef, appelés aussi pièces aérodynamiques, de riblets destinés à améliorer l’écoulement de l’air sur ces surfaces. Les riblets sont de fines nervures, ou rainures, imprimées sur la surface d’un élément soumis à un flux d’air et orientées parallèlement au sens d’écoulement du flux d’air afin de réduire le frottement dudit flux d’air sur la surface. Il est connu que lorsque la forme et les dimensions des riblets sont adaptées aux conditions (nombre de Mach, nombre de Reynolds, etc.), la réduction des frottements peut atteindre de l’ordre de 5 à 10%.One of the surface treatments known to reduce airflow friction is the coating based on riblets. This treatment consists of coating the external surface of aircraft engine elements, also called aerodynamic parts, with riblets intended to improve the flow of air over these surfaces. Riblets are thin ribs, or grooves, impressed on the surface of an element subjected to an airflow and oriented parallel to the direction of flow of the airflow in order to reduce the friction of said airflow on the surface. It is known that when the shape and dimensions of the riblets are adapted to the conditions (Mach number, Reynolds number, etc.), the reduction in friction can reach around 5 to 10%.
Un tel traitement, lorsqu’il est correctement appliqué, permet de réduire la trainée de frottement générée par les couches limites turbulentes. En revanche, il peut amener à augmenter les frottements s’il agit sur une couche limite laminaire ou à générer des pertes accrues s’il agit sur des couches limites décollées ou, plus généralement, sur des écoulements chaotiques non-orientés. Il est donc important que le revêtement contenant les riblets soit correctement appliqué et qu’il soit appliqué sur les zones de l’élément soumises à des couches limites turbulentes.Such treatment, when properly applied, reduces the frictional drag generated by turbulent boundary layers. On the other hand, it can lead to increased friction if it acts on a laminar boundary layer or to generate increased losses if it acts on separated boundary layers or, more generally, on chaotic non-oriented flows. It is therefore important that the coating containing the riblets is properly applied and that it is applied to areas of the element subject to turbulent boundary layers.
Un exemple d’un élément de moteur d’aéronef tel qu’une aube fixe est représenté sur la
Une des techniques d’impression de riblets connues consiste à appliquer, sur la surface de la pièce, un film polyuréthane, ou film PU, contenant des riblets. Ce film PU a pour but, d’une part, de protéger la pièce notamment contre l’érosion et, d’autre part, d’améliorer l’état de surface de la pièce par apport de riblets. Cependant, la fixation d’un film PU à riblets est une opération totalement manuelle, qui requière une grande précision. En effet, il est nécessaire que le film soit posé de façon à ce que les riblets soient correctement orientés par rapport au sens d'écoulement de l’air et sans qu’ils ne soient déformés.One of the known techniques for printing riblets consists of applying a polyurethane film, or PU film, containing riblets to the surface of the part. The purpose of this PU film is, on the one hand, to protect the part in particular against erosion and, on the other hand, to improve the surface condition of the part by adding riblets. However, attaching a PU film to riblets is a totally manual operation, which requires great precision. Indeed, it is necessary that the film be applied so that the riblets are correctly oriented in relation to the direction of air flow and without them being deformed.
De plus, les riblets devant généralement ne recouvrir qu’une portion de la pièce (partie 11 sur la
Par ailleurs, il est connu que les films PU avec riblets présentent un coût relativement élevé, par rapport à des films PU simples, ce qui augmente le coût de production de la pièce. En outre, compte tenu de la difficulté de pose d’un tel revêtement avec riblets, il existe un risque élevé de non-conformité des pièces, ce qui augmente encore le coût moyen de la pièce sur l’ensemble de la production, à cause notamment du plus grand nombre de rebuts.Furthermore, it is known that PU films with riblets have a relatively high cost, compared to simple PU films, which increases the production cost of the part. In addition, given the difficulty of laying such a coating with riblets, there is a high risk of non-conformity of the parts, which further increases the average cost of the part over the entire production, because in particular the greater number of rejects.
Une autre technique d’impression de riblets consiste à graver les riblets au laser sur le matériau brut de la pièce aéronautique ou sur un revêtement de protection, de type peinture, déposé sur la surface de ladite pièce. Cependant, un tel procédé est non seulement long et coûteux, mais en plus il est difficilement applicable sur le plan industriel.Another technique for printing riblets consists of laser engraving the riblets on the raw material of the aeronautical part or on a protective coating, such as paint, deposited on the surface of said part. However, such a method is not only long and costly, but in addition it is difficult to apply industrially.
Il existe donc un réel besoin d’un procédé industrialisable, facile à mettre en œuvre sur toutes sortes de pièces aéronautiques, présentant un coût plus faible que les procédés connus et permettant de limiter le risque de non-conformité.There is therefore a real need for an industrializable process, easy to implement on all kinds of aeronautical parts, with a lower cost than known processes and making it possible to limit the risk of non-compliance.
Pour répondre aux problèmes évoqués ci-dessus de coût et de mise en œuvre des procédés d’impression des riblets sur la surface d’une pièce aéronautique, le demandeur propose un procédé d’impression de riblets dans lequel la totalité de la surface de la pièce est recouverte des mêmes revêtements, les riblets étant imprimés par pression d’une contreforme munie d’une empreinte.To respond to the problems mentioned above of cost and implementation of processes for printing riblets on the surface of an aeronautical part, the applicant proposes a process for printing riblets in which the entire surface of the part is covered with the same coatings, the riblets being printed by pressure of a counterform provided with an imprint.
Selon un premier aspect, l’invention concerne un procédé d’impression de riblets sur la surface d’une pièce aéronautique, comportant les opérations suivantes :
- application d’un revêtement anti-corrosion sur la surface de la pièce,
- application d’un revêtement de protection, lisse, sur la surface de la pièce,
- installation, sur la surface de la pièce recouverte du revêtement de protection, d’une contreforme comportant une empreinte de riblets,
- installation, sur la contreforme, d’une plaque de pression,
- application d’une pression prédéfinie sur la plaque de pression pendant une durée prédéterminée, et
- retrait de la plaque de pression et de la contreforme de sorte à obtenir des riblets imprimés sur le revêtement de protection recouvrant la surface de la pièce.
- application of an anti-corrosion coating on the surface of the part,
- application of a protective coating, smooth, on the surface of the part,
- installation, on the surface of the part covered with the protective coating, of a counterform comprising an imprint of riblets,
- installation, on the counterform, of a pressure plate,
- applying a predefined pressure to the pressure plate for a predefined time, and
- removal of the pressure plate and the counterform so as to obtain riblets printed on the protective coating covering the surface of the part.
Ce procédé présente notamment les avantages d’être moins couteux que les procédés de l’art antérieur et d’être facilement industrialisable. Il offre, en outre, une surface externe sans écart ni discontinuité entre la zone avec riblets et la zone sans riblets, ce qui assure une continuité de l’écoulement d’air le long de la pièce.This process has in particular the advantages of being less expensive than the processes of the prior art and of being easily industrializable. It also offers an external surface with no gaps or discontinuities between the area with riblets and the area without riblets, which ensures continuity of the air flow along the part.
Outre les caractéristiques qui viennent d’être évoquées dans le paragraphe précédent, le procédé d’impression de riblets selon un aspect de l’invention peut présenter une ou plusieurs caractéristiques complémentaires parmi les suivantes, considérées individuellement ou selon toutes les combinaisons techniquement possibles :
- le revêtement anti-corrosion et le revêtement de protection sont appliqués sur la totalité de la surface de la pièce.
- les empreintes de riblets sont appliquées sur une portion uniquement de ladite surface de la pièce de sorte qu’une portion seulement du revêtement de protection recouvrant la pièce est imprimée de riblets.
- La contreforme comporte une première zone sur laquelle sont gravées des empreintes de riblets et une seconde zone lisse.
- le revêtement anti-corrosion est une couche de peinture.
- le revêtement de protection est appliqué sur la pièce après séchage partiel du revêtement anti-corrosion.
- la pression sur la contreforme est réalisée sous-vide, au cours d’un cycle en autoclave.
- la pression sur la contreforme est réalisée mécaniquement, au moyen d’un dispositif de pression, au cours d’un cycle de polymérisation.
- le revêtement de protection est une peinture ou un film en polyuréthane.
- la contreforme comporte des empreintes de riblets de formes différentes.
- la contreforme comporte, sur une face avant, des empreintes de riblets en forme de nervures parallèles les unes aux autres et de section en forme de U ou de V.
- the anti-corrosion coating and the protective coating are applied to the entire surface of the part.
- the imprints of riblets are applied to a portion only of said surface of the part so that only a portion of the protective coating covering the part is printed with riblets.
- The counterform comprises a first zone on which are engraved imprints of riblets and a second smooth zone.
- the anti-corrosion coating is a layer of paint.
- the protective coating is applied to the part after the anti-corrosion coating has partially dried.
- the pressure on the counterform is carried out under vacuum, during an autoclave cycle.
- the pressure on the counterform is carried out mechanically, by means of a pressure device, during a polymerization cycle.
- the protective coating is paint or polyurethane film.
- the counterform has imprints of riblets of different shapes.
- the counterform comprises, on a front face, imprints of riblets in the form of ribs parallel to each other and of U-shaped or V-shaped section.
Un deuxième aspect de l’invention concerne une pièce aéronautique, caractérisée en ce qu’elle comporte une surface au moins partiellement recouverte de riblets imprimés selon le procédé défini ci-dessus.A second aspect of the invention relates to an aeronautical part, characterized in that it comprises a surface at least partially covered with riblets printed according to the method defined above.
Une telle pièce a l’avantage de ne présenter aucun écart ni discontinuité entre la zone revêtue de riblets et la zone sans riblet.Such a part has the advantage of not presenting any gap or discontinuity between the zone coated with riblets and the zone without riblets.
Avantageusement, la pièce aéronautique est une aube d’un aubage mobile ou fixe de turbomachine.Advantageously, the aeronautical part is a vane of a moving or fixed blade of a turbomachine.
Un troisième aspect de l’invention concerne une turbomachine, caractérisée en ce qu’elle comporte au moins une pièce aéronautique telle que définie ci-dessus.A third aspect of the invention relates to a turbomachine, characterized in that it comprises at least one aeronautical part as defined above.
BREVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF FIGURES
D’autres avantages et caractéristiques de l’invention apparaîtront à la lecture de la description qui suit, illustrée par les figures dans lesquelles :Other advantages and characteristics of the invention will appear on reading the following description, illustrated by the figures in which:
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Claims (14)
- application (110) d’un revêtement anti-corrosion (12) sur la surface de la pièce,
- application (120) d’un revêtement de protection (20), lisse, sur la surface de la pièce,
- installation (130), sur la surface de la pièce recouverte du revêtement de protection, d’une contreforme (30) comportant des empreintes (45) de riblets,
- installation (140), sur la contreforme (30), d’une plaque de pression (40)
- application (150) d’une pression prédéfinie sur la plaque de pression (40) pendant une durée prédéterminée, et
- retrait de la plaque de pression (40) et de la contreforme (30) de sorte à obtenir des riblets (50) imprimés sur le revêtement de protection (20) recouvrant la surface de la pièce.
- application (110) of an anti-corrosion coating (12) on the surface of the part,
- application (120) of a protective coating (20), smooth, on the surface of the part,
- installation (130), on the surface of the part covered with the protective coating, of a counterform (30) comprising imprints (45) of riblets,
- installation (140), on the counterform (30), of a pressure plate (40)
- applying (150) a predefined pressure to the pressure plate (40) for a predefined time, and
- removing the pressure plate (40) and the counterform (30) so as to obtain riblets (50) printed on the protective coating (20) covering the surface of the part.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2111016A FR3128150A1 (en) | 2021-10-18 | 2021-10-18 | Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR2111016 | 2021-10-18 | ||
FR2111016A FR3128150A1 (en) | 2021-10-18 | 2021-10-18 | Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process |
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FR3128150A1 true FR3128150A1 (en) | 2023-04-21 |
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FR2111016A Pending FR3128150A1 (en) | 2021-10-18 | 2021-10-18 | Process for printing riblets on the surface of a part and aeronautical part comprising riblets printed by such a process |
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Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
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EP2982599A1 (en) * | 2014-08-01 | 2016-02-10 | The Boeing Company | Drag reduction riblets integrated in a paint layer |
FR3052097A1 (en) * | 2016-06-03 | 2017-12-08 | Safran | PROCESS FOR FORMING A RIBLET ON A PIECE AND A RIBLET MOLD |
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2021
- 2021-10-18 FR FR2111016A patent/FR3128150A1/en active Pending
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2982599A1 (en) * | 2014-08-01 | 2016-02-10 | The Boeing Company | Drag reduction riblets integrated in a paint layer |
FR3052097A1 (en) * | 2016-06-03 | 2017-12-08 | Safran | PROCESS FOR FORMING A RIBLET ON A PIECE AND A RIBLET MOLD |
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