FR3122595A1 - Method of manufacturing a turbine blade for a turbomachine - Google Patents

Method of manufacturing a turbine blade for a turbomachine Download PDF

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Publication number
FR3122595A1
FR3122595A1 FR2104725A FR2104725A FR3122595A1 FR 3122595 A1 FR3122595 A1 FR 3122595A1 FR 2104725 A FR2104725 A FR 2104725A FR 2104725 A FR2104725 A FR 2104725A FR 3122595 A1 FR3122595 A1 FR 3122595A1
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France
Prior art keywords
blade
radially outer
outer end
sandblasting
metallization
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Granted
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FR2104725A
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French (fr)
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FR3122595B1 (en
Inventor
Yoan GAZAL
Stéphane CASNABET
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Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
    • 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
    • C23C4/08—Metallic material containing only 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/131—Wire arc spraying
    • 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
    • C23C4/18—After-treatment
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C3/00—Abrasive blasting machines or devices; Plants
    • B24C3/32—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
    • 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
    • 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
    • F05D2230/10—Manufacture by removing 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/14—Micromachining
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/236—Diffusion bonding
    • 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
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/40—Heat 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
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/18—Intermetallic compounds
    • F05D2300/182—Metal-aluminide intermetallic compounds
    • 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
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/701—Heat treatment

Abstract

L’invention concerne un procédé de fabrication d’une aube de turbine pour une turbomachine, ladite aube comportant un pied et une pale, la pale comportant une extrémité radialement interne rattachée au pied et une extrémité radialement externe, ledit procédé comportant les étapes consistant à : Métalliser (E3) l’extrémité radialement externe de la pale,Ragréer (E4) la surface externe de la zone de la pale métallisée par sablage. Figure à publier avec l’abrégé : [Fig. 4]The invention relates to a method of manufacturing a turbine blade for a turbomachine, said blade comprising a root and a blade, the blade having a radially inner end attached to the root and a radially outer end, said method comprising the steps consisting in : Metallize (E3) the radially outer end of the blade,Smooth (E4) the outer surface of the metallized zone of the blade by sandblasting. Figure to be published with abstract: [Fig. 4]

Description

Procédé de fabrication d’une aube de turbine pour une turbomachineMethod of manufacturing a turbine blade for a turbomachine

Domaine technique de l’inventionTechnical field of the invention

L’invention concerne un procédé de fabrication d’une aube de turbine pour une turbomachine, en particulier une aube de turbine d’un turboréacteur ou d’un turbopropulseur d’aéronef.The invention relates to a method for manufacturing a turbine blade for a turbomachine, in particular a turbine blade of a turbojet engine or an aircraft turboprop engine.

Etat de la technique antérieureState of the prior art

Une turbomachine comporte classiquement, d’amont en aval dans le sens de circulation des gaz, un compresseur basse pression, un compresseur haute pression, une chambre de combustion, une turbine haute pression et une turbine basse pression. La turbine basse pression est reliée au compresseur basse pression par l’intermédiaire d’un arbre dit basse pression. La turbine haute pression est reliée au compresseur haute pression par l’intermédiaire d’un arbre dit haute pression.A turbomachine conventionally comprises, from upstream to downstream in the direction of gas circulation, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The low pressure turbine is connected to the low pressure compressor via a so-called low pressure shaft. The high pressure turbine is connected to the high pressure compressor via a so-called high pressure shaft.

La turbine haute pression comporte une roue aubagée comprenant en particulier un disque comportant des alvéoles et des aubes montées sur le disque. Chaque aube comporte un pied et une pale. La pale comporte une extrémité radialement interne reliée au pied, par l’intermédiaire d’une plate-forme, et une extrémité radialement externe. Les pieds des aubes sont engagés dans les alvéoles du disque de manière à maintenir les aubes sur le disque en fonctionnement.The high pressure turbine comprises a bladed wheel comprising in particular a disc comprising cells and blades mounted on the disc. Each blade has a foot and a blade. The blade has a radially inner end connected to the root, via a platform, and a radially outer end. The roots of the blades are engaged in the cells of the disc so as to maintain the blades on the disc in operation.

Les termes radial, axial et circonférentiel sont définis par rapport à l’axe de la turbomachine, qui est confondu avec l’axe de rotation de la roue aubagée.The terms radial, axial and circumferential are defined with respect to the axis of the turbomachine, which coincides with the axis of rotation of the bladed wheel.

Afin d’assurer que la majorité du flux de gaz chauds issus de la chambre de combustion traverse la turbine haute pression en entrainant la roue aubagée correspondante, il convient de limiter le flux d’air pouvant passer radialement à l’extérieur des pales. Les pales sont entourées extérieurement par un anneau pouvant comporter un matériau abradable ou non, le jeu entre les extrémités radialement externes des pales et l’anneau étant ajusté de manière à limiter l’écoulement de gaz au niveau de ce jeu.In order to ensure that the majority of the flow of hot gases from the combustion chamber passes through the high pressure turbine by driving the corresponding bladed wheel, it is necessary to limit the flow of air that can pass radially outside the blades. The blades are surrounded on the outside by a ring which may or may not comprise an abradable material, the play between the radially outer ends of the blades and the ring being adjusted so as to limit the flow of gas at the level of this play.

Il convient également de s’assurer que lesdites extrémités des pales ne s’érodent pas par abrasion en fonctionnement, le caractère abradable devant être assuré par l’anneau et le caractère abrasif par les pales.It should also be ensured that said ends of the blades do not erode by abrasion in operation, the abradable character having to be ensured by the ring and the abrasive character by the blades.

Pour cela, il est connu de déposer un revêtement ou dépôt métallique au niveau des extrémités radialement externes des pales, l’aube étant préalablement réalisée par fonderie.For this, it is known to deposit a metal coating or deposit at the radially outer ends of the blades, the blade being previously made by foundry.

Une telle opération de dépôt peut générer des débords, qui sont des bourrelets ou des zones de plus grande épaisseur de matière (typiquement entre 0,03 et 0,2 mm), au niveau de l’interface entre la zone revêtue et la pale. Ces débords génèrent notamment des perturbations aérodynamiques non souhaitées en fonctionnement et peuvent être le siège d’un décollement de revêtement.Such a deposition operation can generate overhangs, which are beads or areas of greater material thickness (typically between 0.03 and 0.2 mm), at the interface between the coated area and the blade. These overhangs generate in particular unwanted aerodynamic disturbances in operation and can be the site of a detachment of the coating.

Les figures 1 à 3 illustrent une aube 1 de turbine haute pression pour une turbomachine, conformément à l’art antérieur. Celle-ci comporte un pied 2, une plate-forme 3 et une pale 4 réalisés par fonderie. Un revêtement ou dépôt métallique 5 est effectué au niveau de l’extrémité radialement externe de la pale 4, l’ensemble de la pale 1 étant ensuite revêtue d’une couche externe 6 ( ).Figures 1 to 3 illustrate a high pressure turbine blade 1 for a turbomachine, in accordance with the prior art. This comprises a foot 2, a platform 3 and a blade 4 made by foundry. A metal coating or deposit 5 is made at the radially outer end of the blade 4, the whole of the blade 1 then being coated with an outer layer 6 ( ).

Les débords 7 pouvant apparaître sont visibles aux figures 2 et 3. Ces débords sont classiquement retirés par action mécanique à l’aide d’une brosse. Le brossage est une opération difficile à maîtriser, de sorte que, une fois la pale brossée, certains débords subsistent dans certaines zones ou, à l’inverse, trop de matière peut être retirée dans certaines zones de sorte que l’aube finie présente des anomalies dimensionnelles ou de structure et n’est pas conforme aux spécifications requises.The overhangs 7 that may appear are visible in Figures 2 and 3. These overhangs are conventionally removed by mechanical action using a brush. Brushing is a difficult operation to master, so that once the blade has been brushed, some protrusions remain in certain areas or, conversely, too much material can be removed in certain areas so that the finished blade presents dimensional or structural anomalies and does not conform to the required specifications.

La présence de débords peut également être la source d’un écaillage du revêtement de surface, comme illustré à la .The presence of overhangs can also be the source of flaking of the surface coating, as illustrated in .

Par ailleurs, un tel brossage est relativement fastidieux à mettre en œuvre et nécessite l’utilisation de plusieurs brosses différentes.Furthermore, such brushing is relatively tedious to implement and requires the use of several different brushes.

Il a également été relevé que l’utilisation de brosses métalliques peut générer des contaminations ferriques, pouvant altérer la santé métallurgique de la pièce. Un tel brossage génère enfin des poussières pouvant engendrer des contraintes sanitaires.It has also been noted that the use of metal brushes can generate ferric contamination, which can alter the metallurgical health of the part. Finally, such brushing generates dust that can cause health constraints.

Présentation de l’inventionPresentation of the invention

L’invention vise à remédier à ces inconvénients, de façon simple, efficace et peu onéreuse.The invention aims to remedy these drawbacks in a simple, effective and inexpensive manner.

A cet effet, l’invention concerne un procédé de fabrication d’une aube de turbine pour une turbomachine, ladite aube comportant un pied et une pale, la pale comportant une extrémité radialement interne rattachée au pied et une extrémité radialement externe, ledit procédé comportant les étapes consistant à :To this end, the invention relates to a method for manufacturing a turbine blade for a turbomachine, said blade comprising a root and a blade, the blade having a radially inner end attached to the root and a radially outer end, said method comprising the steps consisting of:

- métalliser l’extrémité radialement externe de la pale,- metallize the radially outer end of the blade,

- ragréer la surface externe de la zone de la pale métallisée par sablage.- smooth the outer surface of the metallized blade area by sandblasting.

L’utilisation du procédé de sablage pour effectuer le ragréage permet d’éviter les problèmes précités liés au brossage, en contrôlant finement le retrait des débords apparaissant lors de l’opération de métallisation. Le sablage permet en particulier d’obtenir un état de surface uniforme et correspondant aux spécifications requises.The use of the sanding process to carry out the leveling makes it possible to avoid the aforementioned problems related to brushing, by finely controlling the shrinkage of the overhangs appearing during the metallization operation. In particular, sandblasting makes it possible to obtain a uniform surface finish corresponding to the required specifications.

Lors de l’étape de sablage, une partie de l’aube peut être masquée. Le pied de l’aube peut ainsi être masqué de façon à ne pas être impacté par le sablage.During the sanding step, part of the blade can be masked. The foot of the blade can thus be masked so as not to be impacted by sandblasting.

La turbomachine peut être un turboréacteur ou un turbopropulseur d’aéronef.The turbomachine may be a turbojet or an aircraft turboprop.

L’aube peut être une aube de turbine haute pression.The blade may be a high pressure turbine blade.

Le dépôt ou revêtement métallique, obtenu par métallisation de l’extrémité radialement externe de la pale, peut être un revêtement d'alliage métallique réfractaire, de type MCrAlY, où M est le métal Ni et/ou Co.The metal deposit or coating, obtained by metallization of the radially outer end of the blade, may be a refractory metal alloy coating, of the MCrAlY type, where M is the metal Ni and/or Co.

Le dépôt ou revêtement métallique peut conférer les propriétés de résistance mécanique et d’abrasion souhaitées, ainsi que des propriétés de protection contre l'oxydation / corrosion.The metallic deposit or coating can provide the desired mechanical resistance and abrasion properties, as well as protection properties against oxidation/corrosion.

L’aube peut être réalisée par fonderie et peut être en superalliage, par exemple à base de nickel.The blade can be made by foundry and can be made of a superalloy, for example nickel-based.

Le sablage peut être réalisé à l’aide d’un média de type corindon et présentant une granulométrie moyenne comprise entre 30 et 80 microns.Sandblasting can be carried out using corundum-type media with an average particle size between 30 and 80 microns.

La granulométrie du média peut être de l’ordre de 50 microns ou 220 mesh.The particle size of the media can be of the order of 50 microns or 220 mesh.

Le sablage peut être réalisé à une pression comprise entre 2,5 et 5,5 bars, par exemple entre 3,5 et 5,5 bars, le média étant projeté à l’aide d’une buse située à une distance comprise entre 40 et 100 mm, par exemple entre 60 et 80 mm, de la zone concernée de l’aube, la vitesse de déplacement de la buse par rapport à la surface de l’aube à sabler étant comprise entre 0,5 et 5 mm/s, par exemple entre 0,7 et 1,5 mm/s.The sandblasting can be carried out at a pressure of between 2.5 and 5.5 bars, for example between 3.5 and 5.5 bars, the media being projected using a nozzle located at a distance of between 40 and 100 mm, for example between 60 and 80 mm, from the zone concerned of the blade, the speed of movement of the nozzle relative to the surface of the blade to be sandblasted being between 0.5 and 5 mm/s , for example between 0.7 and 1.5 mm/s.

La pression de sablage est par exemple de l’ordre de 4 bars. La vitesse de déplacement de la buse par rapport à la surface de l’aube à sabler est par exemple de l’ordre de 1 mm/s.The sandblasting pressure is for example of the order of 4 bars. The speed of movement of the nozzle relative to the surface of the blade to be sandblasted is for example of the order of 1 mm/s.

De tels paramètres offrent de bons résultats lors de l’étape de sablage en permettant de respecter la définition de la pièce lors du retrait des débords de métallisation, tout en minimisant le temps de sablage dans la gamme de fabrication. Le temps de sablage peut être inférieur à 1 minute.Such parameters offer good results during the sandblasting step by making it possible to respect the definition of the part when removing the metallization edges, while minimizing the sandblasting time in the manufacturing process. Blasting time can be less than 1 minute.

A l’issue du sablage, l’aube ou la zone traitée par sablage peut être soufflée à l’air sec.At the end of the sandblasting, the vane or the area treated by sandblasting can be blown with dry air.

Avant l’étape de métallisation, l’extrémité radialement externe de la pale peut être dégraissée et/ou sablée.Before the metallization step, the radially outer end of the blade can be degreased and/or sandblasted.

Une telle étape permet de préparer la surface de ladite extrémité radialement externe de façon à favoriser l’accroche du dépôt réalisé par métallisation.Such a step makes it possible to prepare the surface of said radially outer end so as to promote the attachment of the deposit produced by metallization.

L'épaisseur du dépôt métallique sur l'extrémité radialement externe de la pale est typiquement comprise entre 0,15 et 0,75 mm.The thickness of the metal deposit on the radially outer end of the blade is typically between 0.15 and 0.75 mm.

Un traitement thermique de diffusion peut être appliqué au dépôt ou revêtement métallique réalisé par métallisation de l’extrémité radialement externe de la pale.A diffusion heat treatment can be applied to the metal deposit or coating produced by metallization of the radially outer end of the blade.

Un tel traitement permet notamment d’améliorer les propriétés d'adhérence du dépôt métallique sur la zone traitée.Such a treatment makes it possible in particular to improve the adhesion properties of the metal deposit on the treated area.

Le procédé peut comporter une étape de dépôt d’un revêtement d'aluminisation simple (aluminiure de nickel, NiAl) ou modifiée (e.g. aluminiure de nickel modifiée platine, NiPtAl) sur au moins une partie de la pale de l’aube pouvant recouvrir ladite extrémité radialement externe, après l’étape de ragréage par sablage.The method may include a step of depositing a simple (nickel aluminide, NiAl) or modified (e.g. platinum-modified nickel aluminide, NiPtAl) aluminization coating on at least part of the blade of the blade which can cover said radially outer end, after the leveling step by sandblasting.

L'épaisseur caractéristique d'un tel revêtement d’aluminiure de nickel modifié platine peut être comprise entre 30 et 80 microns, par exemple de l’ordre de 50 microns.The characteristic thickness of such a coating of platinum-modified nickel aluminide can be between 30 and 80 microns, for example of the order of 50 microns.

L'aluminure de nickel modifié platine est principalement réalisée en deux étapes successives, (i) le dépôt d'une couche de platine de 3 à 10 µm d'épaisseur par dépôt électrolytique ; (ii) l'aluminisation par procédé en phase vapeur ou par cémentation en caisse (pack cementation, en anglais).The platinum-modified nickel aluminide is mainly produced in two successive steps, (i) the deposition of a layer of platinum 3 to 10 μm thick by electrolytic deposition; (ii) aluminization by vapor phase process or by case cementation (pack cementation, in English).

Un tel procédé est notamment connu du document FR 2 924 129.Such a method is known in particular from document FR 2 924 129.

L’extrémité radialement externe de l’aube peut être rectifiée, au moins en partie, après dépôt dudit revêtement d’aluminure de platine ou après sablage. Une telle opération de rectification permet d’ajuster le jeu radial entre l’extrémité de l’aube et l’anneau entourant les aubes de l’étage concernée de la turbine. L’épaisseur du revêtement métallique après rectification peut être compris entre 150 et 350 microns, dans la zone rectifiée.The radially outer end of the blade may be ground, at least in part, after deposition of said platinum aluminide coating or after sandblasting. Such a grinding operation makes it possible to adjust the radial clearance between the end of the blade and the ring surrounding the blades of the relevant stage of the turbine. The thickness of the metal coating after rectification can be between 150 and 350 microns, in the rectified zone.

La métallisation de l’extrémité radialement externe de la pale peut être réalisée par projection thermique.The metallization of the radially outer end of the blade can be carried out by thermal spraying.

Alternativement, une telle métallisation peut être réalisée par dépôt par voie électrolytique (codépôt électrolytique).Alternatively, such metallization can be carried out by electrolytic deposition (electrolytic codeposition).

Le procédé de projection thermique utilisé lors de l’étape de métallisation de l’extrémité radialement externe de la pale peut être un procédé de type projection supersonique par combustion HVOF ou HVAF.The thermal spraying process used during the metallization step of the radially outer end of the blade can be a process of the supersonic spraying type by HVOF or HVAF combustion.

Les termes HVOF et HVAF désignent respectivement les procédés connus sous les appellations anglaises « high velocity air fuel » et « high velocity oxy fuel »The terms HVOF and HVAF designate respectively the processes known under the English names "high velocity air fuel" and "high velocity oxy fuel".

Alternativement, ledit procédé de projection thermique peut être de type projection à froid.Alternatively, said thermal spraying process can be of the cold spraying type.

Alternativement, ledit procédé de projection thermique peut être une projection plasma à pression atmosphérique ou sous atmosphère contrôlée.Alternatively, said thermal spraying process can be plasma spraying at atmospheric pressure or under controlled atmosphere.

La projection plasma peut comporter une étape consistant à projeter, à l’aide d’une torche plasma, un revêtement d'alliage à grande vitesse et à température élevée (plus de 2 500°K) sur la surface à traiter pour y obtenir son accrochage. La torche peut être placée préférentiellement perpendiculairement à la surface à traiter. Un tel procédé est notamment connu du document EP 1 911 549.Plasma spraying may include a step consisting in spraying, using a plasma torch, an alloy coating at high speed and at high temperature (more than 2,500°K) onto the surface to be treated in order to obtain its hooking. The torch can preferably be placed perpendicular to the surface to be treated. Such a method is known in particular from document EP 1 911 549.

De tels procédés sont connus en soi, pour d’autres applications.Such methods are known per se, for other applications.

Brève description des figuresBrief description of figures

est une vue en perspective d’une aube de turbine de l’art antérieur, is a perspective view of a prior art turbine blade,

est une vue en perspective de l’aube de la , is a perspective view of the dawn of the ,

est une vue en coupe d’une partie d’une pale de l’aube des figures 1 et 2, is a sectional view of part of a blade of the blade of Figures 1 and 2,

est un diagramme illustrant les différentes étapes du procédé selon l’invention. is a diagram illustrating the different steps of the method according to the invention.

Claims (8)

Procédé de fabrication d’une aube (1) (1) de turbine pour une turbomachine, ladite aube (1) comportant un pied (2) et une pale (4), la pale (4) comportant une extrémité radialement interne rattachée au pied (2) et une extrémité radialement externe, ledit procédé comportant les étapes consistant à :
  • métalliser (E3) l’extrémité radialement externe de la pale (4),
  • ragréer (E4) la surface externe de la zone de la pale (4) métallisée par sablage.
Method of manufacturing a turbine blade (1) (1) for a turbomachine, said blade (1) comprising a root (2) and a blade (4), the blade (4) comprising a radially inner end attached to the root (2) and a radially outer end, said method comprising the steps of:
  • metallize (E3) the radially outer end of the blade (4),
  • smoothing (E4) the external surface of the zone of the blade (4) metallized by sandblasting.
Procédé de fabrication selon la revendication précédente, caractérisé en ce que le sablage est réalisé à l’aide d’un média de type corindon et présentant une granulométrie moyenne comprise entre 30 et 80 microns.Manufacturing process according to the preceding claim, characterized in that the sandblasting is carried out using a medium of the corundum type and having an average particle size of between 30 and 80 microns. Procédé de fabrication selon l’une des revendications précédentes, caractérisé en ce que le sablage est réalisé à une pression comprise entre 2,5 et 5,5 bars, par exemple entre 3,5 et 5,5 bars, le média étant projeté à l’aide d’une buse située à une distance comprise entre 400 et 100 mm, par exemple entre 60 et 80 mm, de la zone concernée de l’aube (1), la vitesse de déplacement de la buse par rapport à la surface de l’aube (1) à sabler étant comprise entre 0,5 et 5 mm/s, par exemple entre 0,7 et 1,5 mm/s.Manufacturing process according to one of the preceding claims, characterized in that the sandblasting is carried out at a pressure of between 2.5 and 5.5 bars, for example between 3.5 and 5.5 bars, the medium being projected at using a nozzle located at a distance of between 400 and 100 mm, for example between 60 and 80 mm, from the zone concerned of the blade (1), the speed of movement of the nozzle with respect to the surface of the blade (1) to be sandblasted being between 0.5 and 5 mm/s, for example between 0.7 and 1.5 mm/s. Procédé de fabrication selon l’une des revendications précédentes, caractérisé en ce que, avant l’étape de métallisation (E3), l’extrémité radialement externe de la pale (4) est dégraissée et/ou sablée (E2).Manufacturing process according to one of the preceding claims, characterized in that, before the metallization step (E3), the radially outer end of the blade (4) is degreased and/or sandblasted (E2). Procédé selon l’une des revendications précédentes, caractérisé en ce qu’un traitement thermique de diffusion (E6) est appliqué au dépôt ou revêtement métallique réalisé par métallisation de l’extrémité radialement externe de la pale (4).Method according to one of the preceding claims, characterized in that a diffusion heat treatment (E6) is applied to the metal deposit or coating produced by metallization of the radially outer end of the blade (4). Procédé selon l’une des revendications précédentes, caractérisé en ce qu’il comporte une étape de dépôt d’un revêtement d'aluminisation pouvant être de type aluminiure de nickel modifié platine ou NiPtAl sur au moins une partie de la pale (4) de l’aube (1) pouvant recouvrir ladite extrémité radialement externe, après l’étape de ragréage (E4) par sablage.Method according to one of the preceding claims, characterized in that it comprises a step of depositing an aluminization coating which may be of the platinum-modified nickel aluminide or NiPtAl type on at least part of the blade (4) of the blade (1) being able to cover said radially outer end, after the leveling step (E4) by sandblasting. Procédé selon l’une des revendications précédentes, caractérisé en ce que la métallisation (E3) de l’extrémité radialement externe de la pale (4) est réalisée par projection thermique.Method according to one of the preceding claims, characterized in that the metallization (E3) of the radially outer end of the blade (4) is produced by thermal spraying. Procédé selon l’une des revendications précédentes, caractérisé en ce que le procédé de projection thermique utilisé lors de l’étape de métallisation (E3) de l’extrémité radialement externe de la pale (4) est un procédé de type HVOF ou HVAF.Method according to one of the preceding claims, characterized in that the thermal spraying method used during the step of metallization (E3) of the radially outer end of the blade (4) is an HVOF or HVAF type method.
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US20040213919A1 (en) * 2001-08-03 2004-10-28 Reinhard Fried Coating process and coated base material
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