EP4341037A1 - Equipment for treating an aircraft turbomachine component - Google Patents

Equipment for treating an aircraft turbomachine component

Info

Publication number
EP4341037A1
EP4341037A1 EP22724830.9A EP22724830A EP4341037A1 EP 4341037 A1 EP4341037 A1 EP 4341037A1 EP 22724830 A EP22724830 A EP 22724830A EP 4341037 A1 EP4341037 A1 EP 4341037A1
Authority
EP
European Patent Office
Prior art keywords
axis
seal
cover
support
tool
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
Application number
EP22724830.9A
Other languages
German (de)
French (fr)
Inventor
Christelle Muth-Seng
William Duarte
Guillaume GAVA
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4341037A1 publication Critical patent/EP4341037A1/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • 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
    • B24C1/04—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
    • 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
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • 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
    • 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
    • C23C4/134—Plasma spraying
    • 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
    • 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

Definitions

  • TITLE PROCESSING TOOLS FOR AN AIRCRAFT TURBOMACHINE PART
  • the present invention relates to a tool for processing an aircraft turbomachine part as well as the method implemented for such processing.
  • the various parts and elements that make up said turbomachine can be subject to wear related to the operation of the turbomachine. This wear can, among other things, be due to friction of one part on another and result in a loss of material.
  • Repair means the treatment of a worn area or surface so that it regains its original dimensions.
  • the treatment can for example be the deposition of a coating by thermal spraying.
  • Such a treatment implies that the part to be treated must be partially masked with precision to leave the areas and surfaces to be treated visible.
  • the object of the present invention is in particular to solve all or part of the aforementioned problems.
  • the present invention proposes a tool for processing an annular part of an aircraft turbomachine, the tool being characterized in that it comprises:
  • a support having a generally elongated shape along an axis, the support comprising at one of its longitudinal ends a base configured to receive the part to be treated which is intended to extend around the axis;
  • a cover configured to be mounted on the part and to cover at least one upstream end of this part, the cover comprising an orifice oriented along the axis;
  • annular seal masking said part, said seal extending around the axis and being configured to be inserted between the base and a downstream end of the part, said seal comprising an annular groove configured to be a counter-form of this downstream end of said part.
  • the joint used being of a pre-established shape and adapted to the part to be repaired, the zones to be treated are distinctly delimited and are easily reproduced from one part to another thanks to the joint.
  • the treatment envisaged is the deposition of a coating, the quality of the latter is improved, as is its reproducibility from one part to be treated to another.
  • the seal is reusable and can easily be placed on another part of the same series to mask areas that do not require treatment. In this way, the repair of the part is made compatible with industrialization.
  • the tool may comprise one or more of the characteristics below, taken separately with each other or in combination with each other:
  • the seal comprises a chamfer at its outer periphery and at a free end, in particular upstream;
  • the chamfer extends continuously over 360° around the axis
  • the seal has notches which extend radially with respect to the axis, at the free end of the seal, and from the inner periphery to the outer periphery of the seal, the chamfer being interrupted by the notches;
  • each of the notches is delimited by a frustoconical surface portion which extends from the internal periphery to the external periphery of the seal;
  • the groove comprises an internal cylindrical surface extending around the axis and configured to cover an external cylindrical surface of the downstream end of the part;
  • the groove comprises a frustoconical surface facing the aforementioned internal cylindrical surface and configured to cover an internal frustoconical surface of the downstream end of the part;
  • the seal is made of a silicone-based material, and preferably has a hardness of between 60 and 65 Shore A;
  • the support comprises feet which extend along the axis, from the base to a base configured to rest on a work surface;
  • the support comprises a clamping column aligned on the axis and extending from the base or the work surface to the base, this column comprising a free end configured to cooperate by screwing with the clamping member which is also aligned on axis;
  • the clamping device is configured to cooperate by screwing with the clamping column.
  • the present invention also relates to an assembly comprising a tool as described above and an annular part of an aircraft turbomachine, this part comprising:
  • the assembly may comprise one or more of the characteristics below, taken separately with each other or in combination with each other:
  • the part is a support ring for a rolling bearing
  • the groove covers 90 or 99% of a height or longitudinal dimension of an external cylindrical surface of the downstream end of the part, measured from a lower edge of said part.
  • the invention also proposes a method for treating an annular part of an aircraft turbomachine, by means of a tool as described above, said method comprising the following steps: a) positioning the part so that its longitudinal axis is aligned with the axis of the tool and engage the downstream end of the part in the groove of the masking seal; b) mounting the cover on the part so that the cover covers the upstream end of the part; c) engage the clamping member through the orifice of the cover and fix the cover to the support; and d) treating at least one surface not covered by the lid and the seal, by a treatment chosen from sandblasting and thermal spraying.
  • Figure 1 is a schematic view of a turbomachine part, in particular a rolling bearing support as it exists in the state of the art;
  • FIG.2A-2B Figures 2A and 2B are schematic sectional half views of the turbomachine part of Figure 1 along different cutting axes, Figure 2A is a view along the cutting axis l-l and Figure 2B is a view along section line II-II;
  • FIG.3 is a schematic perspective view of a processing tool for a turbomachine part according to the invention.
  • Figure 4 is a schematic sectional view of the tool of Figure 3;
  • FIG.5 Figure 5 is a detailed schematic view of part of Figure 4.
  • Figure 6 is a schematic view of a masking seal according to one form of the invention.
  • Figure 7 is a schematic view of an assembly comprising the turbomachine part of Figure 1 inserted into the seal of Figure 6;
  • Figure 8 is a schematic view of the masking seal according to another form of the invention having a chamfer with radial notches;
  • Figure 9 is a schematic view of an assembly comprising the turbomachine part of Figure 1 inserted into the seal of Figure 8;
  • Figures 10A and 10B are schematic views of the tool of Figure 3 and illustrate the treatment method using such a tool;
  • Figure 10C is another schematic view of the tooling of Figure 3 and illustrates the treatment method using this tooling
  • FIG.10D Figures 10D is another schematic view of the tooling of Figure 3 and illustrates the processing method using this tooling; and [Fig.11] Figure 11 is a partial sectional view of a turbomachine. Detailed description of the invention
  • FIG. 11 represents a portion of turbomachine 1, known in the art, extending along an axis of revolution A.
  • the turbomachine 1 comprises an annular part 10 located upstream or in front of a rolling bearing 2
  • An outer periphery of the part 10 is fixed to an outer annular part 3 which forms a stator and carries an outer race 4 of the bearing 2.
  • An inner periphery of the part 10 forms a labyrinth seal 5 with annular wipers carried by a rotor in which is integrated the inner ring 6 of the bearing 2.
  • the bearings of the bearing here are roller bearings.
  • annular part 10 of the turbomachine 1 which is either, for example, a rolling bearing support or forms part of such a support.
  • Part 10 is shown in detail in Figures 1 and 2.
  • Such a part 10, known in the art extends around an axis Y and has an upstream end 11 and a downstream end 13.
  • the upstream end 11 comprises a cylindrical support surface for a rolling bearing ring.
  • the downstream end 13 comprises an outer periphery from which at least a first outer cylindrical surface portion 13a and at least a second outer cylindrical surface portion 13b can be distinguished.
  • the outer periphery of the downstream end 13 may comprise four first cylindrical surface portions 13a. Each of these portions 13a has a first dimension, corresponding to a length of the arc of a circle, which may have an angular extent a, referred to a plane perpendicular to the Y axis, of between 5 and 45° (degrees).
  • the outer periphery of the downstream end 13 may also include four second cylindrical surface portions 13b. Each of these portions 13b has a second dimension, corresponding to a length of the arc of a circle, which can have an angular extent b, relative to a plane perpendicular to the axis Y, comprised between 5 and 45° (degrees).
  • a first surface portion 13a is between two second surface portions 13b, and a second surface portion 13b is between two first surface portions 13a.
  • the first outer cylindrical surface portion 13a is located on a first circumference having a diameter substantially greater than the diameter of a second circumference on which the second outer cylindrical surface portion 13b is located.
  • Figures 2A and 2B respectively show the part 10 of Figure 1 along a cutting axis l-l and a cutting axis ll-ll. It is understood there that the first portion of outer cylindrical surface 13a has a first axial dimension H1 substantially greater than a second axial dimension H2 of the second portion of outer cylindrical surface 13b.
  • the end 13 can also comprise at its internal periphery an internal frustoconical surface 13c.
  • the part 10 also comprises one or two annular surfaces 12, 14 located between the two ends 11, 13.
  • the annular surface 14 extends perpendicular to the external cylindrical surface portions 13a, 13b and forms an annular lower edge.
  • the annular surface 12 connects the annular flange to the upstream end 11 of the part 10, this surface 12 may have a generally frustoconical shape.
  • the second external cylindrical surface 13b and/or the surfaces 12 and 14 are zones likely to undergo friction during the operation of the turbomachine, which can lead to wear of the aforementioned zones. Also, the second outer cylindrical surface portion 13b and/or the surfaces 12 and 14 are areas which it is sought to treat, for example by depositing a coating.
  • Figures 3 to 9 illustrate a tool 100 for processing an annular part 10 of an aircraft turbomachine.
  • Figures 3 to 5 show the tool 100 which comprises a support 110, a cover 120, a clamping member 130 and an annular gasket 20 for masking part 10.
  • the support 110 has a generally elongated shape along an axis X. In the example shown, this axis X is substantially vertical.
  • the support 110 comprises at one of its longitudinal ends a base 111 configured to receive the part 10 to be treated.
  • the part 10 is intended to extend around the X axis so that the Y axis of the part 10 coincides with the X axis.
  • the support 110 can comprise feet 112 which extend along the along the X axis, from the base 111 to a base 113 configured to rest on a work surface.
  • the base 113 allows, among other things, the centering of the support 110 on the work surface.
  • the support 110 can also comprise a clamping column 114 aligned on the X axis which extends from the base 113 or the work surface to the base 111.
  • This column 114 comprises an upper end 114a configured to cooperate by screwing with the member 130 clamping.
  • the cover 120 is configured to be mounted on the part 10 and to cover at least partly the upper end 11 of the part 10.
  • the cover 120 comprises an orifice 122, this orifice 122 being able to be drilled in a wall 121 perpendicular to the axis X.
  • the cover 120 may include an annular shoulder 124 at its end intended to be in contact with the part 10. During the treatment of the part 10, and in particular for a deposit of coating, this shoulder 124 makes it possible to make a decreasing deposit by shading effect limiting the risk of flaking.
  • the lid 120 may further include one or more side openings 126 or even be devoid of them. These openings 126, when present, can be used for positioning of devices allowing the realization of test or control of the coating once carried out.
  • the clamping member 130 passes through the orifice 122 and extends parallel to the axis X.
  • the member 130 is configured to cooperate with the support 110 and is configured to fix the cover 120 to the support 110.
  • the member 130 clamping can also be configured to cooperate by screwing, when present, with the clamping column 114 of the support 110 and in particular with the free end 114a. It is understood that in such a case, the member 130 is aligned on the X axis, as well as the orifice 122.
  • the annular masking seal 20 is intended to at least partially mask the annular part 10.
  • the seal 20 extends around the axis X and is configured to be inserted between the base 111 of the support and the downstream end 13 of the part 10.
  • the seal 20 comprises a groove 24 annular configured to be a counter-form of this downstream end 13 of the part 10.
  • the groove 24 comprises an internal cylindrical surface 24a extending around the axis X and configured to cover the first external cylindrical surface portion 13a of the downstream end 13 of the part 10.
  • the groove 24 also comprises a frustoconical surface 24c facing the internal cylindrical surface 24a. This frustoconical surface 24c is configured to cover an internal frustoconical surface 13c of the downstream end 13 of the part 10.
  • the seal 20 comprises a chamfer 22 at its outer periphery and at a free end, in particular upstream.
  • the chamfer 22 can extend continuously over 360° around the axis X.
  • the groove 24 also comprises an internal cylindrical surface 24b configured to cover the second external cylindrical surface portion 13b of the part 10.
  • Figure 7 shows the assembly formed by the part 10 and the seal 20.
  • the first external cylindrical surface 13a as well as the second surface external cylindrical surface 13b are at least partly masked by the internal cylindrical surface 24a of the groove 24.
  • the gasket 20 is mounted in a fitted manner with the part 10, and in particular with the first and second portions of external cylindrical surface 13a , 13b.
  • the groove 24 can thus cover 90 or 99% of the height or longitudinal dimension of a portion of external cylindrical surface 13a, 13b of the downstream end 13 of the part 10, measured from a lower edge of the part 10. that a step of dimension S is left free on the outer cylindrical surface 13a, 13b.
  • the value of the step of dimension S can be between 0.1 and 1 mm (millimeter).
  • the dimension S is preferably equal to 0.6 mm.
  • the first and second outer cylindrical surface portions 13a, 13b having different longitudinal dimensions, it is understood that the counter-shape of the groove 24 has different depths adapted to the portion 13a, 13b that it covers.
  • the upstream end 11 of the part 10 is also masked, in other words covered, by the cover 120.
  • the surface 12, the surface 14 of the lower edge and the height S of the outer cylindrical surface 13a, 13b are at least left visible. It is understood that these surfaces left free are intended to undergo treatment from the outside.
  • the gasket 20 described above has at least the advantage of improving the quality of the deposit on the areas to be treated.
  • the chamfer 22 allows, thanks to its inclination, the rebound of the particles of material sent on the part 10 towards the outside of the tool 100 and not towards the zones to be treated. In this way, the deposit on the areas to be treated is uniform.
  • Another advantage is the S-dimension step, which allows optimum sanding of the surfaces to be treated. It also makes it possible to avoid flaking of the coating deposited when part 10 is extracted from seal 20.
  • seal 20 has notches 25 which extend radially with respect to the axis X, at the free end of the seal 20, and from the inner periphery to the outer periphery of the seal 20.
  • the chamfer 22 which extends to the outer periphery of the gasket 20 is interrupted by the notches 25.
  • each of the notches 25 is delimited by a frustoconical surface portion which extends from the inner periphery to the outer periphery of the gasket 20, thus forming an angle w, greater than angle b.
  • the chamfer 22 and the notches 25 have the same aforementioned advantages.
  • the downstream end 13 of the part 10 When the downstream end 13 of the part 10 is inserted into the groove 24 of the gasket 20, only the first outer cylindrical surface portion 13a is at least partly masked by the inner cylindrical surface 24a of the groove 24.
  • the groove 24 can thus covering 90 or 99% of the height or longitudinal dimension of the outer cylindrical surface 13a. It is understood that a step of dimension S, similar to that described above, is left free on the first external cylindrical surface 13a.
  • the internal cylindrical surface 24b is absent, in other words the second external cylindrical surface portion 13b of the part 10 is left free.
  • the cover 120 covers the upstream end 11 of the part 10.
  • the surface 12, the surface 14 of the lower edge, the step of dimension S of the external cylindrical surface 13a, 13b and the second external cylindrical surface 13b are at least left visible. It is understood that these surfaces left free are intended to undergo treatment from the outside.
  • Each notch 25 is configured to be aligned with a free surface 13b, as visible in the example of FIG. 9, so that the second dimension of the second portion of external cylindrical surface 13b, in other words the length of the arc of circle formed by this portion 13b, is substantially equal to or substantially less than the dimension of the notch 25 at the internal periphery of the seal 20. It is understood that there are as many notches 25 as there are seconds surface portions 13b.
  • a connecting portion 13d of dimension L between the first portion of outer cylindrical surface 13a and the second portion of outer cylindrical surface 13b can also be left partly free at the level of the notch 25.
  • the dimension L can for example be between 0.1 and 1.5 mm (millimeter).
  • the dimension L is preferably equal to 1 mm.
  • the portion 13d of dimension L creates an offset with the seal 20, which allows easier extraction of the part 10 without flaking the deposit.
  • the seal 20 can be made of a silicone-based material and preferably has a hardness of between 60 and 65 Shore A, which allows the seal 20 to have sufficient temperature resistance. treatment.
  • the seal 20 is capable of deforming, in particular under the pressure exerted by the cover 120 on the part 10.
  • the Applicant has also developed a process for treating an annular part 10 of an aircraft turbomachine, using a tool 100 as described above.
  • This method comprises the following steps, illustrated in FIGS. 10A to 10D: a) positioning the part 10 so that its longitudinal axis Y is aligned with the axis X of the tool 100 and engaging the downstream end 13 of the part 10 in the groove 24 of the seal 20 masking, as shown in Figures 10A and 10B; b) mounting the cover 120 on the part so that the cover covers the upstream end 11 of the part, as shown in Figure 10C; c) engage the clamping member 130 through the orifice 122 of the cover 120 and fix the cover 120 to the support 110, as shown in FIG. 10D; and d) treating at least one surface 12, 13b, 14 not covered by the lid and the seal 20, by a treatment chosen from sandblasting and thermal spraying of material by plasma.
  • the surfaces left free by the masking seal 20 and the cover 120 can be treated.
  • the treatment is generally a metallization, assisted by plasma, which consists of a projection of molten metal particles on the desired areas.
  • the configuration of the joint 20 makes it possible to precisely delimit the zones to be treated while ensuring a uniform and homogeneous coating. Indeed, the chamfer 22 and the notches 25, when they are present, allow the rebound of the metal particles towards the outside of the tool. In this way, excess thicknesses, for example, which subsequently require retouching, are avoided.
  • the invention as described above has the advantage of being a single tool, which saves time during the masking phase of the part while ensuring repeatability and reproducibility of the results, and this regardless of the embodiment of the seal used.
  • another advantage lies in the shape and material of the joint, which makes it possible to avoid non-conformities during processing, and thus avoid an additional retouching step.

Abstract

The invention relates to equipment (100) for treating an annular component (10) of an aircraft turbomachine, having: a support (110) of elongate shape along an axis (X), the support comprising, at one of its ends, a mount (111) configured to receive the component, which is intended to extend about the axis; a cover (120) configured to be mounted on the component and to cover an upstream end of this component, the cover comprising an orifice (122) oriented along the axis (X); a clamping member (130) passing through the orifice, the member being configured to cooperate with the support and to fix the cover to the support; and an annular masking gasket (20) extending about the axis and being configured to be interposed between the mount and a downstream end of the component, the gasket having an annular groove configured to be a counter-form of this downstream end.

Description

DESCRIPTION DESCRIPTION
TITRE : OUTILLAGE DE TRAITEMENT D’UNE PIECE DE TURBOMACHINE D’AERONEF TITLE: PROCESSING TOOLS FOR AN AIRCRAFT TURBOMACHINE PART
Domaine technique de l'invention Technical field of the invention
La présente invention concerne un outillage de traitement d’une pièce de turbomachine d’aéronef ainsi que le procédé mis en œuvre pour un tel traitement. The present invention relates to a tool for processing an aircraft turbomachine part as well as the method implemented for such processing.
Arrière-plan technique Technical background
Dans une turbomachine d’aéronef, les différentes pièces et éléments qui composent ladite turbomachine peuvent subir des usures liées au fonctionnement de la turbomachine. Ces usures peuvent, entre autres, être dues à des frottements d’une pièce sur une autre et ont pour conséquences une perte de matière. In an aircraft turbomachine, the various parts and elements that make up said turbomachine can be subject to wear related to the operation of the turbomachine. This wear can, among other things, be due to friction of one part on another and result in a loss of material.
Il est possible qu’une pièce usée puisse subir une réparation. On entend par réparation le traitement d’une zone ou surface usée de sorte que celle-ci retrouve ses dimensions d’origine. Le traitement peut par exemple être le dépôt d’un revêtement par projection thermique. Un tel traitement implique que la pièce à traiter doit être partiellement masquée avec précision pour laisser apparentes les zones et surfaces à traiter. It is possible that a worn part can be repaired. Repair means the treatment of a worn area or surface so that it regains its original dimensions. The treatment can for example be the deposition of a coating by thermal spraying. Such a treatment implies that the part to be treated must be partially masked with precision to leave the areas and surfaces to be treated visible.
Actuellement, une pièce usée est remplacée par une neuve à défaut d’être réparée. Ceci peut s’expliquer par l’absence de méthodes de réparation fiables et adaptées, notamment dans le cas de pièces à géométries complexes comme par exemple un support de palier à roulement où le revêtement doit être déposé avec précision sur des zones spécifiques en fonction des besoins. En effet, la réparation par dépôt d’un revêtement se fait manuellement au moyen d’un masquage au ruban adhésif de la pièce. Cette procédure a plusieurs inconvénients : elle peut entraîner le dépôt du revêtement sur des zones non souhaitées du fait d’un décollement du ruban adhésif durant l’opération, ce qui contribue à un manque de répétabilité et de fiabilité. En outre, la technique étant manuelle, le temps passé pour masquer la pièce est important. Elle est donc peu propice à une utilisation routinière. Dans l’état de la technique, des moyens existent pour traiter des pièces et sont notamment décrits dans US-A1 -2007/0361422, DE-A1 -102016211397, FR-A1 -3050671 ou EP-A1 -2778256. Currently, a worn part is replaced by a new one if it is not repaired. This can be explained by the lack of reliable and suitable repair methods, particularly in the case of parts with complex geometries such as a rolling bearing support, where the coating must be deposited with precision on specific areas depending on the needs. Indeed, the repair by deposition of a coating is done manually by masking the part with adhesive tape. This procedure has several disadvantages: it can lead to the deposition of the coating on undesired areas due to the detachment of the adhesive tape during the operation, which contributes to a lack of repeatability and reliability. In addition, the technique being manual, the time spent masking the part is significant. It is therefore not conducive to routine use. In the state of the art, means exist for treating parts and are described in particular in US-A1 -2007/0361422, DE-A1 -102016211397, FR-A1 -3050671 or EP-A1 -2778256.
La présente invention a notamment pour but de résoudre tout ou partie des problèmes précités. The object of the present invention is in particular to solve all or part of the aforementioned problems.
Résumé de l'invention Summary of the invention
La présente invention propose un outillage de traitement d’une pièce annulaire de turbomachine d’aéronef, l’outillage étant caractérisé en ce qu’il comporte : The present invention proposes a tool for processing an annular part of an aircraft turbomachine, the tool being characterized in that it comprises:
- un support présentant une forme générale allongée le long d‘un axe, le support comprenant à une de ses extrémités longitudinales un socle configuré pour recevoir la pièce à traiter qui est destinée à s’étendre autour de l’axe ; - a support having a generally elongated shape along an axis, the support comprising at one of its longitudinal ends a base configured to receive the part to be treated which is intended to extend around the axis;
- un couvercle configuré pour être monté sur la pièce et pour recouvrir au moins une extrémité amont de cette pièce, le couvercle comprenant un orifice orienté suivant l’axe ; - a cover configured to be mounted on the part and to cover at least one upstream end of this part, the cover comprising an orifice oriented along the axis;
- un organe de bridage traversant ledit orifice et s’étendant parallèlement audit axe, ledit organe étant configuré pour coopérer avec le support et pour fixer le couvercle audit support ; et - a clamping member passing through said orifice and extending parallel to said axis, said member being configured to cooperate with the support and to fix the cover to said support; and
- un joint annulaire de masquage de ladite pièce, ledit joint s’étendant autour de l’axe et étant configuré pour être intercalé entre le socle et une extrémité aval de la pièce, ledit joint comportant une gorge annulaire configurée pour être une contre-forme de cette extrémité aval de ladite pièce. - an annular seal masking said part, said seal extending around the axis and being configured to be inserted between the base and a downstream end of the part, said seal comprising an annular groove configured to be a counter-form of this downstream end of said part.
Ainsi, grâce à l’invention on assure une amélioration de la répétabilité et de la reproductibilité du traitement sur les zones concernées, autrement dit non masquées par le joint. En effet, le joint utilisé étant d’une forme préétablie et adaptée à la pièce à réparer, les zones à traiter sont distinctement délimitées et sont facilement reproduites d’une pièce à l’autre grâce au joint. De la sorte, on s’assure d’avoir un traitement de qualité répondant aux critères définis qui est à la fois répétable et nécessitant peu ou pas de retouches a posteriori. Ainsi, lorsque le traitement envisagé est le dépôt d’un revêtement, la qualité de ce dernier est améliorée, de même que sa reproductibilité d’une pièce à traiter à l’autre. Thus, thanks to the invention, an improvement in the repeatability and the reproducibility of the treatment is ensured on the zones concerned, in other words not masked by the joint. Indeed, the joint used being of a pre-established shape and adapted to the part to be repaired, the zones to be treated are distinctly delimited and are easily reproduced from one part to another thanks to the joint. In this way, we are sure to have a quality treatment meeting the defined criteria which is both repeatable and requiring little or no post-processing. Thus, when the treatment envisaged is the deposition of a coating, the quality of the latter is improved, as is its reproducibility from one part to be treated to another.
Encore grâce à l’invention, on s’assure d’une amélioration de la productivité lors des réparations sur la pièce. En effet, le joint est réutilisable et peut facilement être placé sur une autre pièce de la même série pour masquer les zones ne nécessitant pas de traitement. De la sorte, la réparation de la pièce est rendue compatible avec une industrialisation. Again thanks to the invention, we ensure an improvement in productivity during repairs on the part. Indeed, the seal is reusable and can easily be placed on another part of the same series to mask areas that do not require treatment. In this way, the repair of the part is made compatible with industrialization.
L’outillage, selon l’invention, peut comprendre une ou plusieurs des caractéristiques ci-dessous, prises isolément les unes avec les autres ou en combinaison les unes avec les autres : The tool, according to the invention, may comprise one or more of the characteristics below, taken separately with each other or in combination with each other:
- le joint comprend un chanfrein à sa périphérie externe et à une extrémité libre, en particulier amont ; - the seal comprises a chamfer at its outer periphery and at a free end, in particular upstream;
- le chanfrein s’étend en continu sur 360° autour de l’axe ; - the chamfer extends continuously over 360° around the axis;
- le joint comporte des encoches qui s’étendent radialement par rapport à l’axe, à l’extrémité libre du joint, et depuis la périphérie interne jusqu’à la périphérie externe du joint, le chanfrein étant interrompu par les encoches ;- the seal has notches which extend radially with respect to the axis, at the free end of the seal, and from the inner periphery to the outer periphery of the seal, the chamfer being interrupted by the notches;
- chacune des encoches est délimitée par une portion de surface tronconique qui s’étend depuis la périphérie interne jusqu’à la périphérie externe du joint ;- each of the notches is delimited by a frustoconical surface portion which extends from the internal periphery to the external periphery of the seal;
- la gorge comprend une surface cylindrique interne s’étendant autour de l’axe et configurée pour recouvrir une surface cylindrique externe de l’extrémité aval de la pièce ; - the groove comprises an internal cylindrical surface extending around the axis and configured to cover an external cylindrical surface of the downstream end of the part;
- la gorge comprend une surface tronconique en regard de la surface cylindrique interne précitée et configurée pour recouvrir une surface tronconique interne de l’extrémité aval de la pièce ; - the groove comprises a frustoconical surface facing the aforementioned internal cylindrical surface and configured to cover an internal frustoconical surface of the downstream end of the part;
- le joint est en un matériau à base de silicone, et a de préférence une dureté comprise entre 60 et 65 Shore A ; - the seal is made of a silicone-based material, and preferably has a hardness of between 60 and 65 Shore A;
- le support comprend des pieds qui s’étendent le long de l’axe, depuis le socle jusqu’à une embase configurée pour être en appui sur une surface de travail ; - le support comprend une colonne de serrage alignée sur l’axe et s’étendant depuis l’embase ou la surface de travail jusqu’au socle, cette colonne comportant une extrémité libre configurée pour coopérer par vissage avec l’organe de bridage qui est également aligné sur l’axe ; - the support comprises feet which extend along the axis, from the base to a base configured to rest on a work surface; - the support comprises a clamping column aligned on the axis and extending from the base or the work surface to the base, this column comprising a free end configured to cooperate by screwing with the clamping member which is also aligned on axis;
- l’organe de bridage est configuré pour coopérer par vissage avec la colonne de serrage. - the clamping device is configured to cooperate by screwing with the clamping column.
La présente invention concerne également un ensemble comportant un outillage tel que décrit ci-avant et une pièce annulaire de turbomachine d’aéronef, cette pièce comportant : The present invention also relates to an assembly comprising a tool as described above and an annular part of an aircraft turbomachine, this part comprising:
- une extrémité aval engagée dans la gorge du joint de masquage, - a downstream end engaged in the groove of the masking seal,
- une extrémité amont recouverte par le couvercle, et - an upstream end covered by the lid, and
- au moins une surface située entre les extrémités aval et amont, qui est laissée libre et destinée à subir un traitement depuis l’extérieur. - at least one surface located between the downstream and upstream ends, which is left free and intended to undergo treatment from the outside.
L’ensemble, selon l’invention, peut comprendre une ou plusieurs des caractéristiques ci-dessous, prises isolément les unes avec les autres ou en combinaison les unes avec les autres : The assembly, according to the invention, may comprise one or more of the characteristics below, taken separately with each other or in combination with each other:
- la pièce est une bague de support d’un palier à roulement ; - the part is a support ring for a rolling bearing;
- la gorge recouvre 90 ou 99% d’une hauteur ou dimension longitudinale d’une surface cylindrique externe de l’extrémité aval de la pièce, mesurée depuis un bord inférieur de ladite pièce. - the groove covers 90 or 99% of a height or longitudinal dimension of an external cylindrical surface of the downstream end of the part, measured from a lower edge of said part.
L’invention propose également un procédé de traitement d’une pièce annulaire de turbomachine d’aéronef, au moyen d’un outillage tel que décrit précédemment, ledit procédé comprenant les étapes suivantes : a) positionner la pièce de sorte que son axe longitudinal soit aligné sur l’axe de l’outillage et engager l’extrémité aval de la pièce dans la gorge du joint de masquage ; b) monter le couvercle sur la pièce de sorte que le couvercle recouvre l’extrémité amont de la pièce ; c) engager l’organe de bridage à travers l’orifice du couvercle et fixer le couvercle au support ; et d) traiter au moins une surface non recouverte par le couvercle et le joint, par un traitement choisi parmi le sablage et la projection thermique. The invention also proposes a method for treating an annular part of an aircraft turbomachine, by means of a tool as described above, said method comprising the following steps: a) positioning the part so that its longitudinal axis is aligned with the axis of the tool and engage the downstream end of the part in the groove of the masking seal; b) mounting the cover on the part so that the cover covers the upstream end of the part; c) engage the clamping member through the orifice of the cover and fix the cover to the support; and d) treating at least one surface not covered by the lid and the seal, by a treatment chosen from sandblasting and thermal spraying.
Brève description des figures Brief description of figures
L’invention sera mieux comprise et d’autres détails, caractéristiques et avantages de l’invention apparaîtront plus clairement à la lecture de la description suivante faite à titre d’exemple non limitatif et en référence aux dessins annexés dans lesquels : The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:
[Fig .1 ] la figure 1 est une vue schématique d’une pièce de turbomachine, en particulier un support de palier à roulement tel qu’existant dans l’état de la technique ; [Fig.1] Figure 1 is a schematic view of a turbomachine part, in particular a rolling bearing support as it exists in the state of the art;
[Fig.2A-2B] les figures 2A et 2B sont des demie vues schématiques en coupe de la pièce de turbomachine de la figure 1 selon différents axes de coupe, la figure 2A est une vue selon l’axe de coupe l-l et la figure 2B est une vue selon l’axe de coupe ll-ll ; [Fig.2A-2B] Figures 2A and 2B are schematic sectional half views of the turbomachine part of Figure 1 along different cutting axes, Figure 2A is a view along the cutting axis l-l and Figure 2B is a view along section line II-II;
[Fig.3] la figure 3 est une vue schématique en perspective d’un outillage de traitement d’une pièce de turbomachine selon l’invention ; [Fig.3] Figure 3 is a schematic perspective view of a processing tool for a turbomachine part according to the invention;
[Fig.4] la figure 4 est une vue schématique en coupe de l’outillage de la figure 3 ; [Fig.4] Figure 4 is a schematic sectional view of the tool of Figure 3;
[Fig.5] la figure 5 est une vue schématique détaillée d’une partie de la figure 4 ; [Fig.5] Figure 5 is a detailed schematic view of part of Figure 4;
[Fig.6] la figure 6 est une vue schématique d’un joint de masquage selon une forme de l’invention ; [Fig.6] Figure 6 is a schematic view of a masking seal according to one form of the invention;
[Fig.7] la figure 7 est une vue schématique d’un ensemble comportant la pièce de turbomachine de la figure 1 insérée dans le joint de la figure 6 ; [Fig.8] la figure 8 est une vue schématique du joint de masquage selon une autre forme de l’invention présentant un chanfrein avec des encoches radiales ; [Fig.7] Figure 7 is a schematic view of an assembly comprising the turbomachine part of Figure 1 inserted into the seal of Figure 6; [Fig.8] Figure 8 is a schematic view of the masking seal according to another form of the invention having a chamfer with radial notches;
[Fig.9] la figure 9 est une vue schématique d’un ensemble comportant la pièce de turbomachine de la figure 1 insérée dans le joint de la figure 8 ; [Fig.10A-10B] les figures 10A et 10B sont des vues schématiques de l’outillage de la figure 3 et illustrent le procédé de traitement utilisant un tel outillage ; [Fig.9] Figure 9 is a schematic view of an assembly comprising the turbomachine part of Figure 1 inserted into the seal of Figure 8; [Fig.10A-10B] Figures 10A and 10B are schematic views of the tool of Figure 3 and illustrate the treatment method using such a tool;
[Fig.10C] la figure 10C est une autre vue schématique de l’outillage de la figure 3 et illustre le procédé de traitement utilisant cet outillage ; [Fig.10C] Figure 10C is another schematic view of the tooling of Figure 3 and illustrates the treatment method using this tooling;
[Fig.lOD] les figures 10D est une autre vue schématique de l’outillage de la figure 3 et illustre le procédé de traitement utilisant cet outillage; et [Fig.11 ] la figure 11 est une vue partielle en coupe d’une turbomachine. Description détaillée de l'invention [Fig.10D] Figures 10D is another schematic view of the tooling of Figure 3 and illustrates the processing method using this tooling; and [Fig.11] Figure 11 is a partial sectional view of a turbomachine. Detailed description of the invention
La figure 11 représente une portion de turbomachine 1 , connue de la technique, s’étendant selon un axe de révolution A. Dans cet exemple, la turbomachine 1 comprend une pièce annulaire 10 située en amont ou en avant d’un palier à roulement 2. Une périphérie externe de la pièce 10 est fixée à une pièce annulaire externe 3 qui forme un stator et porte une bague externe 4 du palier 2. Une périphérie interne de la pièce 10 forme un joint d’étanchéité 5 à labyrinthe avec des léchettes annulaires portées par un rotor dans lequel est intégrée la bague interne 6 du palier 2. Les roulements du palier sont ici à rouleaux. FIG. 11 represents a portion of turbomachine 1, known in the art, extending along an axis of revolution A. In this example, the turbomachine 1 comprises an annular part 10 located upstream or in front of a rolling bearing 2 An outer periphery of the part 10 is fixed to an outer annular part 3 which forms a stator and carries an outer race 4 of the bearing 2. An inner periphery of the part 10 forms a labyrinth seal 5 with annular wipers carried by a rotor in which is integrated the inner ring 6 of the bearing 2. The bearings of the bearing here are roller bearings.
Dans ce qui suit, on fait référence à la pièce 10 annulaire de la turbomachine 1 qui est ou par exemple un support de palier à roulement ou fait partie d’un tel support. La pièce 10 est représentée de manière détaillée sur les figures 1 et 2. Une telle pièce 10, connue de la technique, s’étend autour d’un axe Y et comporte une extrémité amont 11 et une extrémité aval 13. L’extrémité amont 11 comprend une surface cylindrique de support d’une bague de palier à roulement. L’extrémité aval 13 comprend une périphérie externe de laquelle on distingue au moins une première portion de surface cylindrique externe 13a et au moins une seconde portion de surface cylindrique externe 13b. In what follows, reference is made to the annular part 10 of the turbomachine 1 which is either, for example, a rolling bearing support or forms part of such a support. Part 10 is shown in detail in Figures 1 and 2. Such a part 10, known in the art, extends around an axis Y and has an upstream end 11 and a downstream end 13. The upstream end 11 comprises a cylindrical support surface for a rolling bearing ring. The downstream end 13 comprises an outer periphery from which at least a first outer cylindrical surface portion 13a and at least a second outer cylindrical surface portion 13b can be distinguished.
La périphérie externe de l’extrémité aval 13 peut comprendre quatre premières portions de surface cylindrique 13a. Chacune de ces portions 13a a une première dimension, correspondant à une longueur de d’arc de cercle, qui peut avoir une étendue angulaire a, rapportée sur un plan perpendiculaire à l’axe Y, comprise entre 5 et 45° (degrés). La périphérie externe de l’extrémité aval 13 peut également comprendre quatre secondes portions de surface cylindrique 13b. Chacune de ces portions 13b a une seconde dimension, correspondant à une longueur de d’arc de cercle, qui peut avoir une étendue angulaire b, rapportée sur un plan perpendiculaire à l’axe Y, comprise entre 5 et 45° (degrés). Une première portion de surface 13a est comprise entre deux secondes portions de surface 13b, et une seconde portion de surface 13b est comprise entre deux premières portions de surface 13a. The outer periphery of the downstream end 13 may comprise four first cylindrical surface portions 13a. Each of these portions 13a has a first dimension, corresponding to a length of the arc of a circle, which may have an angular extent a, referred to a plane perpendicular to the Y axis, of between 5 and 45° (degrees). The outer periphery of the downstream end 13 may also include four second cylindrical surface portions 13b. Each of these portions 13b has a second dimension, corresponding to a length of the arc of a circle, which can have an angular extent b, relative to a plane perpendicular to the axis Y, comprised between 5 and 45° (degrees). A first surface portion 13a is between two second surface portions 13b, and a second surface portion 13b is between two first surface portions 13a.
La première portion de surface cylindrique externe 13a est située sur une première circonférence ayant un diamètre sensiblement supérieur au diamètre d’une seconde circonférence sur laquelle est située la seconde portion de surface cylindrique externe 13b. The first outer cylindrical surface portion 13a is located on a first circumference having a diameter substantially greater than the diameter of a second circumference on which the second outer cylindrical surface portion 13b is located.
Les figures 2A et 2B montrent respectivement la pièce 10 de la figure 1 selon un axe de coupe l-l et un axe de coupe ll-ll. On y comprend que la première portion de surface cylindrique externe 13a a une première dimension axiale H1 sensiblement supérieure à une seconde dimension axiale H2 de la seconde portion de surface cylindrique externe 13b. L’extrémité 13 peut aussi comprendre à sa périphérie interne une surface tronconique interne 13c. Figures 2A and 2B respectively show the part 10 of Figure 1 along a cutting axis l-l and a cutting axis ll-ll. It is understood there that the first portion of outer cylindrical surface 13a has a first axial dimension H1 substantially greater than a second axial dimension H2 of the second portion of outer cylindrical surface 13b. The end 13 can also comprise at its internal periphery an internal frustoconical surface 13c.
La pièce 10 comporte également une ou deux surfaces annulaires 12, 14 situées entre les deux extrémités 11 , 13. La surface annulaire 14 s’étend perpendiculairement aux portions de surface cylindrique externe 13a, 13b et forme un bord inférieur annulaire. La surface annulaire 12 relie le rebord annulaire à l’extrémité amont 11 de la pièce 10, cette surface 12 peut avoir une forme générale tronconique. The part 10 also comprises one or two annular surfaces 12, 14 located between the two ends 11, 13. The annular surface 14 extends perpendicular to the external cylindrical surface portions 13a, 13b and forms an annular lower edge. The annular surface 12 connects the annular flange to the upstream end 11 of the part 10, this surface 12 may have a generally frustoconical shape.
La seconde surface cylindrique externe 13b et/ou les surfaces 12 et 14 sont des zones susceptibles de subir des frottements pendant le fonctionnement de la turbomachine, ce qui peut entraîner une usure des zones précitées. Aussi, la seconde portion de surface cylindrique externe 13b et/ou les surfaces 12 et 14 sont des zones que l’on cherche à traiter par exemple par le dépôt d’un revêtement. The second external cylindrical surface 13b and/or the surfaces 12 and 14 are zones likely to undergo friction during the operation of the turbomachine, which can lead to wear of the aforementioned zones. Also, the second outer cylindrical surface portion 13b and/or the surfaces 12 and 14 are areas which it is sought to treat, for example by depositing a coating.
On s’intéresse à présent aux figures 3 à 9 qui illustrent un outillage 100 de traitement d’une pièce annulaire 10 de turbomachine d’aéronef. En particulier, les figures 3 à 5 montrent l’outillage 100 qui comprend un support 110, un couvercle 120, un organe 130 de bridage et un joint annulaire 20 de masquage de la pièce 10. We are now interested in Figures 3 to 9 which illustrate a tool 100 for processing an annular part 10 of an aircraft turbomachine. In particular, Figures 3 to 5 show the tool 100 which comprises a support 110, a cover 120, a clamping member 130 and an annular gasket 20 for masking part 10.
Le support 110 présente une forme générale allongée le long d’un axe X. Dans l’exemple représenté, cet axe X est sensiblement vertical. Le support 110 comprend à une de ses extrémités longitudinales un socle 111 configuré pour recevoir la pièce 10 à traiter. Autrement dit, la pièce 10 est destinée à s’étendre autour de l’axe X de sorte que l’axe Y de la pièce 10 soit confondu avec l’axe X. Le support 110 peut comprendre des pieds 112 qui s’étendent le long de l’axe X, depuis le socle 111 jusqu’à une embase 113 configurée pour être en appui sur une surface de travail. L’embase 113 permet entre autres le centrage du support 110 sur la surface de travail. Le support 110 peut comprendre également une colonne 114 de serrage alignée sur l’axe X qui s’étend depuis l’embase 113 ou la surface de travail jusqu’au socle 111. Cette colonne 114 comporte une extrémité supérieure 114a configurée pour coopérer par vissage avec l’organe 130 de bridage. The support 110 has a generally elongated shape along an axis X. In the example shown, this axis X is substantially vertical. The support 110 comprises at one of its longitudinal ends a base 111 configured to receive the part 10 to be treated. In other words, the part 10 is intended to extend around the X axis so that the Y axis of the part 10 coincides with the X axis. The support 110 can comprise feet 112 which extend along the along the X axis, from the base 111 to a base 113 configured to rest on a work surface. The base 113 allows, among other things, the centering of the support 110 on the work surface. The support 110 can also comprise a clamping column 114 aligned on the X axis which extends from the base 113 or the work surface to the base 111. This column 114 comprises an upper end 114a configured to cooperate by screwing with the member 130 clamping.
Le couvercle 120 est configuré pour être monté sur la pièce 10 et pour recouvrir au moins en partie l’extrémité 11 supérieure de la pièce 10. Le couvercle 120 comprend un orifice 122, cet orifice 122 pouvant être percé dans une paroi 121 perpendiculaire à l’axe X. Le couvercle 120 peut comporter un épaulement 124 annulaire à son extrémité destinée à être au contact de la pièce 10. Lors du traitement de la pièce 10, et en particulier pour un dépôt de revêtement, cet épaulement 124 permet de faire un dépôt dégressif par effet d’ombrage limitant le risque d’écaillage. Le couvercle 120 peut en outre comporter une ou plusieurs ouvertures latérales 126 ou bien en être dépourvu. Ces ouvertures 126, lorsque présentes, peuvent servir au positionnement de dispositifs permettant la réalisation d’essai ou de contrôle du revêtement une fois réalisé. The cover 120 is configured to be mounted on the part 10 and to cover at least partly the upper end 11 of the part 10. The cover 120 comprises an orifice 122, this orifice 122 being able to be drilled in a wall 121 perpendicular to the axis X. The cover 120 may include an annular shoulder 124 at its end intended to be in contact with the part 10. During the treatment of the part 10, and in particular for a deposit of coating, this shoulder 124 makes it possible to make a decreasing deposit by shading effect limiting the risk of flaking. The lid 120 may further include one or more side openings 126 or even be devoid of them. These openings 126, when present, can be used for positioning of devices allowing the realization of test or control of the coating once carried out.
L’organe 130 de bridage traverse l’orifice 122 et s’étend parallèlement à l’axe X. L’organe 130 est configuré pour coopérer avec le support 110 et est configuré pour fixer le couvercle 120 au support 110. L’organe 130 de bridage peut également être configuré pour coopérer par vissage, lorsqu’elle est présente, avec la colonne 114 de serrage du support 110 et en particulier avec l’extrémité libre 114a. On comprend que dans un tel cas, l’organe 130 est aligné sur l’axe X, ainsi que l’orifice 122. The clamping member 130 passes through the orifice 122 and extends parallel to the axis X. The member 130 is configured to cooperate with the support 110 and is configured to fix the cover 120 to the support 110. The member 130 clamping can also be configured to cooperate by screwing, when present, with the clamping column 114 of the support 110 and in particular with the free end 114a. It is understood that in such a case, the member 130 is aligned on the X axis, as well as the orifice 122.
Le joint 20 annulaire de masquage est destiné à masquer au moins en partie la pièce 10 annulaire. Le joint 20 s’étend autour de l’axe X et est configuré pour être intercalé entre le socle 111 du support et l’extrémité aval 13 de la pièce 10. Comme visible sur les figures 6 et 8, le joint 20 comporte une gorge 24 annulaire configurée pour être une contre-forme de cette extrémité aval 13 de la pièce 10. La gorge 24 comprend une surface cylindrique interne 24a s’étendant autour de l’axe X et configurée pour recouvrir la première portion de surface cylindrique externe 13a de l’extrémité aval 13 de la pièce 10. La gorge 24 comprend également une surface tronconique 24c en regard de la surface cylindrique interne 24a. Cette surface tronconique 24c est configurée pour recouvrir une surface tronconique interne 13c de l’extrémité aval 13 de la pièce 10. The annular masking seal 20 is intended to at least partially mask the annular part 10. The seal 20 extends around the axis X and is configured to be inserted between the base 111 of the support and the downstream end 13 of the part 10. As can be seen in FIGS. 6 and 8, the seal 20 comprises a groove 24 annular configured to be a counter-form of this downstream end 13 of the part 10. The groove 24 comprises an internal cylindrical surface 24a extending around the axis X and configured to cover the first external cylindrical surface portion 13a of the downstream end 13 of the part 10. The groove 24 also comprises a frustoconical surface 24c facing the internal cylindrical surface 24a. This frustoconical surface 24c is configured to cover an internal frustoconical surface 13c of the downstream end 13 of the part 10.
On s’intéresse à présent aux figures 6 et 7, illustrant un joint 20 selon une première forme de réalisation. Dans cet exemple, le joint 20 comprend un chanfrein 22 à sa périphérie externe et à une extrémité libre, en particulier amont. Le chanfrein 22 peut s’étendre de façon continue sur 360° autour de l’axe X. On comprend que la gorge 24 comprend également une surface cylindrique interne 24b configurée pour recouvrir la seconde portion de surface cylindrique externe 13b de la pièce 10. We are now interested in Figures 6 and 7, illustrating a seal 20 according to a first embodiment. In this example, the seal 20 comprises a chamfer 22 at its outer periphery and at a free end, in particular upstream. The chamfer 22 can extend continuously over 360° around the axis X. It is understood that the groove 24 also comprises an internal cylindrical surface 24b configured to cover the second external cylindrical surface portion 13b of the part 10.
La figure 7 montre l’ensemble formé par la pièce 10 et le joint 20. Lorsque l’extrémité aval 13 de la pièce 10 est insérée dans la gorge 24 du joint 20, la première surface cylindrique externe 13a ainsi que la seconde surface cylindrique externe 13b sont au moins en partie masquées par la surface cylindrique interne 24a de la gorge 24. On comprend que le joint 20 est monté de manière ajusté avec la pièce 10, et en particulier avec les première et seconde portions de surface cylindrique externe 13a, 13b. La gorge 24 peut ainsi recouvrir 90 ou 99% de la hauteur ou dimension longitudinale d’une portion de surface cylindrique externe 13a, 13b de l’extrémité aval 13 de la pièce 10, mesurée depuis un bord inférieur de la pièce 10. On comprend qu’une marche de dimension S est laissée libre sur la surface cylindrique externe 13a, 13b. La valeur de la marche de dimension S peut être comprise entre 0,1 et 1 mm (millimètre). La dimension S est de préférence égale à 0,6 mm. Les première et seconde portions de surface cylindrique externe 13a, 13b ayant des dimensions longitudinales différentes, on comprend que la contre-forme de la gorge 24 a des profondeurs différentes adaptées à la portion 13a, 13b qu’elle recouvre.Figure 7 shows the assembly formed by the part 10 and the seal 20. When the downstream end 13 of the part 10 is inserted into the groove 24 of the seal 20, the first external cylindrical surface 13a as well as the second surface external cylindrical surface 13b are at least partly masked by the internal cylindrical surface 24a of the groove 24. It is understood that the gasket 20 is mounted in a fitted manner with the part 10, and in particular with the first and second portions of external cylindrical surface 13a , 13b. The groove 24 can thus cover 90 or 99% of the height or longitudinal dimension of a portion of external cylindrical surface 13a, 13b of the downstream end 13 of the part 10, measured from a lower edge of the part 10. that a step of dimension S is left free on the outer cylindrical surface 13a, 13b. The value of the step of dimension S can be between 0.1 and 1 mm (millimeter). The dimension S is preferably equal to 0.6 mm. The first and second outer cylindrical surface portions 13a, 13b having different longitudinal dimensions, it is understood that the counter-shape of the groove 24 has different depths adapted to the portion 13a, 13b that it covers.
En outre, l’extrémité amont 11 de la pièce 10 est également masquée, autrement dit recouverte, par le couvercle 120. In addition, the upstream end 11 of the part 10 is also masked, in other words covered, by the cover 120.
De la sorte, la surface 12, la surface 14 du bord inférieur et la hauteur S de la surface cylindrique externe 13a, 13b sont au moins laissées apparentes. On comprend que ces surfaces laissées libres sont destinées à subir un traitement depuis l’extérieur. In this way, the surface 12, the surface 14 of the lower edge and the height S of the outer cylindrical surface 13a, 13b are at least left visible. It is understood that these surfaces left free are intended to undergo treatment from the outside.
Le joint 20 décrit dans ce qui précède présente au moins l’avantage d’améliorer la qualité du dépôt sur les zones à traiter. En effet, le chanfrein 22 permet, grâce à son inclinaison, le rebond des particules de matière envoyées sur la pièce 10 vers l’extérieur de l’outillage 100 et non vers les zones à traiter. De la sorte, le dépôt sur les zones à traiter est uniforme.The gasket 20 described above has at least the advantage of improving the quality of the deposit on the areas to be treated. Indeed, the chamfer 22 allows, thanks to its inclination, the rebound of the particles of material sent on the part 10 towards the outside of the tool 100 and not towards the zones to be treated. In this way, the deposit on the areas to be treated is uniform.
Un autre avantage réside dans la marche de dimension S qui permet de réaliser un sablage optimal des surfaces à traiter. Elle permet également d’éviter un écaillage du revêtement déposé lorsque la pièce 10 est extraite du joint 20. Another advantage is the S-dimension step, which allows optimum sanding of the surfaces to be treated. It also makes it possible to avoid flaking of the coating deposited when part 10 is extracted from seal 20.
On se réfère maintenant aux figures 8 et 9, illustrant une autre forme de réalisation du joint 20. Dans cet exemple, le joint 20 comporte des encoches 25 qui s’étendent radialement par rapport à l’axe X, à l’extrémité libre du joint 20, et depuis la périphérie interne jusqu’à la périphérie externe du joint 20. De la sorte, le chanfrein 22 qui s’étend à la périphérie externe du joint 20 est interrompu par les encoches 25. En outre, chacune des encoches 25 est délimitée par une portion de surface tronconique qui s’étend depuis la périphérie interne jusqu’à la périphérie externe du joint 20, formant ainsi un angle w, supérieur à l’angle b. Le chanfrein 22 et les encoches 25 présentent les mêmes avantages précités. Reference is now made to FIGS. 8 and 9, illustrating another embodiment of seal 20. In this example, seal 20 has notches 25 which extend radially with respect to the axis X, at the free end of the seal 20, and from the inner periphery to the outer periphery of the seal 20. In this way, the chamfer 22 which extends to the outer periphery of the gasket 20 is interrupted by the notches 25. In addition, each of the notches 25 is delimited by a frustoconical surface portion which extends from the inner periphery to the outer periphery of the gasket 20, thus forming an angle w, greater than angle b. The chamfer 22 and the notches 25 have the same aforementioned advantages.
Lorsque l’extrémité aval 13 de la pièce 10 est insérée dans la gorge 24 du joint 20, seule la première portion de surface cylindrique externe 13a est au moins en partie masquée par la surface cylindrique interne 24a de la gorge 24. La gorge 24 peut ainsi recouvrir 90 ou 99% de la hauteur ou dimension longitudinale de la surface cylindrique externe 13a. On comprend qu’une marche de dimension S, similaire à celle décrite précédemment, est laissée libre sur la première surface cylindrique externe 13a. La surface cylindrique interne 24b est absente, autrement dit la seconde portion de surface cylindrique externe 13b de la pièce 10 est laissée libre. When the downstream end 13 of the part 10 is inserted into the groove 24 of the gasket 20, only the first outer cylindrical surface portion 13a is at least partly masked by the inner cylindrical surface 24a of the groove 24. The groove 24 can thus covering 90 or 99% of the height or longitudinal dimension of the outer cylindrical surface 13a. It is understood that a step of dimension S, similar to that described above, is left free on the first external cylindrical surface 13a. The internal cylindrical surface 24b is absent, in other words the second external cylindrical surface portion 13b of the part 10 is left free.
Comme dans l’exemple de la figure 7, le couvercle 120 recouvre l’extrémité amont 11 de la pièce 10. La surface 12, la surface 14 du bord inférieur, la marche de dimension S de la surface cylindrique externe 13a, 13b et la seconde surface cylindrique externe 13b sont au moins laissées apparentes. On comprend que ces surfaces laissées libres sont destinées à subir un traitement depuis l’extérieur. As in the example of FIG. 7, the cover 120 covers the upstream end 11 of the part 10. The surface 12, the surface 14 of the lower edge, the step of dimension S of the external cylindrical surface 13a, 13b and the second external cylindrical surface 13b are at least left visible. It is understood that these surfaces left free are intended to undergo treatment from the outside.
Chaque encoche 25 est configurée pour être alignée avec une surface 13b libre, comme visible sur l’exemple de la figure 9, de sorte que la seconde dimension de la seconde portion de surface cylindrique externe 13b, autrement dit la longueur de l’arc de cercle formé par cette portion 13b, est sensiblement égale ou sensiblement inférieure à la dimension de l’encoche 25 au niveau de la périphérie interne du joint 20. On comprend qu’il y a autant d’encoches 25 qu’il y a de secondes portions de surface 13b. Une portion de liaison 13d de dimension L entre la première portion de surface cylindrique externe 13a et la seconde portion de surface cylindrique externe 13b peut également être laissée en partie libre au niveau de l’encoche 25. La dimension L peut par exemple être comprise entre 0,1 et 1 ,5 mm (millimètre). La dimension L est de préférence égale à 1 mm. La portion 13d de dimension L crée un décalage avec le joint 20, ce qui permet une extraction plus facile de la pièce 10 sans écailler le dépôt. Each notch 25 is configured to be aligned with a free surface 13b, as visible in the example of FIG. 9, so that the second dimension of the second portion of external cylindrical surface 13b, in other words the length of the arc of circle formed by this portion 13b, is substantially equal to or substantially less than the dimension of the notch 25 at the internal periphery of the seal 20. It is understood that there are as many notches 25 as there are seconds surface portions 13b. A connecting portion 13d of dimension L between the first portion of outer cylindrical surface 13a and the second portion of outer cylindrical surface 13b can also be left partly free at the level of the notch 25. The dimension L can for example be between 0.1 and 1.5 mm (millimeter). The dimension L is preferably equal to 1 mm. The portion 13d of dimension L creates an offset with the seal 20, which allows easier extraction of the part 10 without flaking the deposit.
Dans les formes de réalisation présentées, le joint 20 peut être en un matériau à base de silicone et a, de préférence, une dureté comprise entre 60 et 65 Shore A, ce qui permet au joint 20 d’avoir une résistance suffisante à la température de traitement. Le joint 20 est apte à se déformer, notamment sous la pression exercée par le couvercle 120 sur la pièce 10. In the embodiments presented, the seal 20 can be made of a silicone-based material and preferably has a hardness of between 60 and 65 Shore A, which allows the seal 20 to have sufficient temperature resistance. treatment. The seal 20 is capable of deforming, in particular under the pressure exerted by the cover 120 on the part 10.
La Demanderesse a aussi mis au point un procédé de traitement d’une pièce annulaire 10 de turbomachine d’aéronef, au moyen d’un outillage 100 tel que décrit dans ce qui précède. Ce procédé comprend les étapes suivantes, illustrées sur les figures 10A à 10D : a) positionner la pièce 10 de sorte que son axe longitudinal Y soit aligné sur l’axe X de l’outillage 100 et engager l’extrémité aval 13 de la pièce 10 dans la gorge 24 du joint 20 de masquage, tel que montré sur les figures 10A et 10B ; b) monter le couvercle 120 sur la pièce de sorte que le couvercle recouvre l’extrémité amont 11 de la pièce, tel que montré sur la figure 10C ; c) engager l’organe 130 de bridage à travers l’orifice 122 du couvercle 120 et fixer le couvercle 120 au support 110, tel que montré sur la figure 10D ; et d) traiter au moins une surface 12, 13b, 14 non recouverte par le couvercle et le joint 20, par un traitement choisi parmi le sablage et la projection thermique de matière par plasma. The Applicant has also developed a process for treating an annular part 10 of an aircraft turbomachine, using a tool 100 as described above. This method comprises the following steps, illustrated in FIGS. 10A to 10D: a) positioning the part 10 so that its longitudinal axis Y is aligned with the axis X of the tool 100 and engaging the downstream end 13 of the part 10 in the groove 24 of the seal 20 masking, as shown in Figures 10A and 10B; b) mounting the cover 120 on the part so that the cover covers the upstream end 11 of the part, as shown in Figure 10C; c) engage the clamping member 130 through the orifice 122 of the cover 120 and fix the cover 120 to the support 110, as shown in FIG. 10D; and d) treating at least one surface 12, 13b, 14 not covered by the lid and the seal 20, by a treatment chosen from sandblasting and thermal spraying of material by plasma.
Lors de l’étape d) de traitement, les surfaces laissées libres par le joint 20 de masquage et le couvercle 120 peuvent être traitées. Le traitement est généralement une métallisation, assistée par plasma, qui consiste en une projection de particules métalliques fondues sur les zones souhaitées. La configuration du joint 20 permet de délimiter précisément les zones à traiter tout en assurant un revêtement uniforme et homogène. En effet, le chanfrein 22 et les encoches 25, quand elles sont présentes, permettent le rebond des particules métalliques vers l’extérieur de l’outillage. De la sorte, on évite des surépaisseurs par exemple qui nécessitent par la suite des retouches. During step d) of treatment, the surfaces left free by the masking seal 20 and the cover 120 can be treated. The treatment is generally a metallization, assisted by plasma, which consists of a projection of molten metal particles on the desired areas. The configuration of the joint 20 makes it possible to precisely delimit the zones to be treated while ensuring a uniform and homogeneous coating. Indeed, the chamfer 22 and the notches 25, when they are present, allow the rebound of the metal particles towards the outside of the tool. In this way, excess thicknesses, for example, which subsequently require retouching, are avoided.
L’invention telle que décrite dans ce qui précède présente l’avantage d’être un outillage unique, ce qui permet de gagner du temps lors de la phase de masquage de la pièce tout en assurant une répétabilité et une reproductibilité des résultats, et ce indépendamment de la forme de réalisation du joint utilisé. En outre, un autre avantage réside dans la forme et le matériau du joint qui permettent d’éviter des non conformités lors du traitement, et ainsi éviter une étape supplémentaire de retouche. The invention as described above has the advantage of being a single tool, which saves time during the masking phase of the part while ensuring repeatability and reproducibility of the results, and this regardless of the embodiment of the seal used. In addition, another advantage lies in the shape and material of the joint, which makes it possible to avoid non-conformities during processing, and thus avoid an additional retouching step.

Claims

REVENDICATIONS
1. Outillage (100) de traitement d’une pièce annulaire (10) de turbomachine d’aéronef, ledit outillage étant caractérisé en ce qu’il comporte : 1. Tooling (100) for processing an annular part (10) of an aircraft turbomachine, said tooling being characterized in that it comprises:
- un support (110) présentant une forme générale allongée le long d‘un axe (X), ledit support comprenant à une de ses extrémités longitudinales un socle (111) configuré pour recevoir la pièce (10) à traiter qui est destinée à s’étendre autour dudit axe ; - a support (110) having a generally elongated shape along an axis (X), said support comprising at one of its longitudinal ends a base (111) configured to receive the part (10) to be treated which is intended to be extend around said axis;
- un couvercle (120) configuré pour être monté sur ladite pièce et pour recouvrir au moins une extrémité (11) amont de cette pièce, ledit couvercle comprenant un orifice (122) orienté suivant l’axe (X) ; - a cover (120) configured to be mounted on said part and to cover at least one upstream end (11) of this part, said cover comprising an orifice (122) oriented along the axis (X);
- un organe (130) de bridage traversant ledit orifice et s’étendant parallèlement audit axe (X), ledit organe étant configuré pour coopérer avec le support et pour fixer le couvercle audit support ; et - a clamping member (130) passing through said orifice and extending parallel to said axis (X), said member being configured to cooperate with the support and to fix the cover to said support; and
- un joint annulaire (20) de masquage de ladite pièce, ledit joint s’étendant autour de l’axe (X) et étant configuré pour être intercalé entre le socle et une extrémité aval (13) de la pièce, ledit joint comportant une gorge (24) annulaire configurée pour être une contre-forme de cette extrémité aval de ladite pièce. - an annular seal (20) masking said part, said seal extending around the axis (X) and being configured to be inserted between the base and a downstream end (13) of the part, said seal comprising a annular groove (24) configured to be a counter-shape of this downstream end of said part.
2. Outillage (100) selon la revendication précédente, dans lequel le joint (20) comprend un chanfrein (22) à sa périphérie externe et à une extrémité libre. 2. Tool (100) according to the preceding claim, wherein the seal (20) comprises a chamfer (22) at its outer periphery and at a free end.
3. Outillage (100) selon la revendication précédente, dans lequel le chanfrein (22) s’étend en continu sur 360° autour de l’axe (X). 3. Tooling (100) according to the preceding claim, in which the chamfer (22) extends continuously over 360° around the axis (X).
4. Outillage (100) selon la revendication 2, dans lequel le joint (20) comporte des encoches (25) qui s’étendent radialement par rapport audit axe (X), à l’extrémité libre dudit joint, et depuis la périphérie interne jusqu’à la périphérie externe dudit joint, le chanfrein (22) étant interrompu par lesdites encoches. 4. Tool (100) according to claim 2, wherein the seal (20) has notches (25) which extend radially relative to said axis (X), at the free end of said seal, and from the internal periphery to the outer periphery of said joint, the chamfer (22) being interrupted by said notches.
5. Outillage (100) selon la revendication précédente, dans lequel chacune des encoches (25) est délimitée par une portion de surface tronconique qui s’étend depuis la périphérie interne jusqu’à la périphérie externe du joint (20). 5. Tooling (100) according to the preceding claim, in which each of the notches (25) is delimited by a frustoconical surface portion which extends from the inner periphery to the outer periphery of the seal (20).
6. Outillage (100) selon l’une des revendications précédentes, dans lequel le joint (20) est en un matériau à base de silicone, et a de préférence une dureté comprise entre 60 et 65 Shore A. 6. Tooling (100) according to one of the preceding claims, in which the seal (20) is made of a silicone-based material, and preferably has a hardness of between 60 and 65 Shore A.
7. Outillage (100) selon l’une des revendications précédentes, dans lequel le support (110) comprend des pieds (112) qui s’étendent le long de l’axe (X), depuis le socle (111) jusqu’à une embase (113) configurée pour être en appui sur une surface de travail. 7. Tool (100) according to one of the preceding claims, wherein the support (110) comprises feet (112) which extend along the axis (X), from the base (111) to a base (113) configured to rest on a work surface.
8. Outillage (100) selon la revendication précédente, dans lequel le support (110) comprend une colonne (114) de serrage alignée sur l’axe (X) et s’étendant depuis l’embase (113) ou la surface de travail jusqu’au socle (111), cette colonne comportant une extrémité libre (114a) configurée pour coopérer par vissage avec ledit organe de bridage qui est également aligné sur l’axe (X). 8. Tool (100) according to the preceding claim, wherein the support (110) comprises a clamping column (114) aligned on the axis (X) and extending from the base (113) or the work surface as far as the base (111), this column comprising a free end (114a) configured to cooperate by screwing with the said clamping member which is also aligned on the axis (X).
9. Outillage (100) selon la revendication précédente, dans lequel l’organe (130) de bridage est configuré pour coopérer par vissage avec la colonne (114) de serrage. 9. Tooling (100) according to the preceding claim, in which the member (130) for clamping is configured to cooperate by screwing with the column (114) for clamping.
10. Outillage (100) selon l’une des revendications précédentes, dans lequel la gorge (24) comprend une surface cylindrique interne (24a, 24b) s’étendant autour de l’axe (X) et configurée pour recouvrir une surface cylindrique externe (13a, 13b) de l’extrémité aval (13) de la pièce (10). 10. Tool (100) according to one of the preceding claims, wherein the groove (24) comprises an internal cylindrical surface (24a, 24b) extending around the axis (X) and configured to cover an external cylindrical surface (13a, 13b) of the downstream end (13) of the part (10).
11. Outillage (100) selon la revendication précédente, dans lequel la gorge (24) comprend une surface tronconique (24c) en regard de la surface cylindrique interne (24a, 24b) et configurée pour recouvrir une surface tronconique interne (13c) de l’extrémité aval (13) de la pièce (10). 11. Tooling (100) according to the preceding claim, in which the groove (24) comprises a frustoconical surface (24c) facing the internal cylindrical surface (24a, 24b) and configured to cover an internal frustoconical surface (13c) of the downstream end (13) of the part (10).
12. Ensemble comportant un outillage (100) selon l’une des revendications précédentes et une pièce annulaire (10) de turbomachine d’aéronef, cette pièce comportant : - une extrémité aval (13) engagée dans la gorge (24) du joint (20) de masquage, 12. Assembly comprising a tool (100) according to one of the preceding claims and an annular part (10) of an aircraft turbomachine, this part comprising: - a downstream end (13) engaged in the groove (24) of the masking seal (20),
- une extrémité amont (11) recouverte par le couvercle (120), et - an upstream end (11) covered by the cover (120), and
- au moins une surface (12, 13b, 14) située entre les extrémités aval et amont, qui est laissée libre et destinée à subir un traitement depuis l’extérieur. - at least one surface (12, 13b, 14) located between the downstream and upstream ends, which is left free and intended to undergo treatment from the outside.
13. Ensemble selon la revendication précédente, dans lequel la pièce (10) est une bague de support d’un palier à roulement. 13. Assembly according to the preceding claim, in which the part (10) is a support ring for a rolling bearing.
14. Ensemble selon l’une des revendications 12 ou 13, dans lequel la gorge (24) recouvre 90 ou 99% d’une hauteur ou dimension longitudinale d’une surface cylindrique externe (13a, 13b) de l’extrémité aval (13) de la pièce (10), mesurée depuis un bord inférieur de ladite pièce. 14. Assembly according to one of claims 12 or 13, wherein the groove (24) covers 90 or 99% of a height or longitudinal dimension of an outer cylindrical surface (13a, 13b) of the downstream end (13 ) of the part (10), measured from a lower edge of said part.
15. Procédé de traitement d’une pièce annulaire (10) de turbomachine d’aéronef, au moyen d’un outillage (100) selon l’une des revendications 1 à 11 , ledit procédé comprenant les étapes suivantes : a) positionner la pièce (10) de sorte que son axe longitudinal soit aligné sur l’axe (X) de l’outillage et engager l’extrémité aval (13) de la pièce dans la gorge (24) du joint (20) de masquage ; b) monter le couvercle (120) sur la pièce de sorte que le couvercle recouvre l’extrémité amont (11) de la pièce ; c) engager l’organe (130) de bridage à travers l’orifice (122) du couvercle et fixer le couvercle au support (110) ; et d) traiter au moins une surface (12, 13b, 14) non recouverte par le couvercle et le joint, par un traitement choisi parmi le sablage et la projection thermique. 15. Method for treating an annular part (10) of an aircraft turbine engine, by means of a tool (100) according to one of claims 1 to 11, said method comprising the following steps: a) positioning the part (10) so that its longitudinal axis is aligned with the axis (X) of the tool and engage the downstream end (13) of the part in the groove (24) of the masking seal (20); b) mounting the cover (120) on the part so that the cover covers the upstream end (11) of the part; c) engage the clamping member (130) through the orifice (122) of the cover and fix the cover to the support (110); and d) treating at least one surface (12, 13b, 14) not covered by the lid and the seal, by a treatment chosen from sandblasting and thermal spraying.
EP22724830.9A 2021-05-19 2022-05-09 Equipment for treating an aircraft turbomachine component Pending EP4341037A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2105224A FR3123011B1 (en) 2021-05-19 2021-05-19 PROCESSING TOOLS FOR AN AIRCRAFT TURBOMACHINE PART
PCT/FR2022/050876 WO2022243619A1 (en) 2021-05-19 2022-05-09 Equipment for treating an aircraft turbomachine component

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EP4341037A1 true EP4341037A1 (en) 2024-03-27

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EP (1) EP4341037A1 (en)
CN (1) CN117320836A (en)
FR (1) FR3123011B1 (en)
WO (1) WO2022243619A1 (en)

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US8737290B2 (en) 2005-08-12 2014-05-27 Edgeaccess, Inc. Performance enhancement protocol, systems, methods and devices
US9394063B2 (en) * 2013-03-15 2016-07-19 Bell Helicopter Textron Inc. Methods utilizing cold spray techniques for repairing and protecting rotary components of aviation propulsion systems
US9956580B2 (en) * 2014-02-14 2018-05-01 United Technologies Corporation Spray masking for rotors
FR3050671B1 (en) * 2016-04-28 2018-04-27 Safran Aircraft Engines METHOD FOR PRODUCING A TURBOMACHINE PART COMPRISING AT LEAST ONE PROTUBERANCE COATED WITH ABRASIVE MATERIAL
US20170361422A1 (en) * 2016-06-16 2017-12-21 General Electric Company Polishing method for turbine components
DE102016211397A1 (en) * 2016-06-24 2017-12-28 MTU Aero Engines AG Masking device and method for producing a masking device for partially covering a component

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WO2022243619A1 (en) 2022-11-24
FR3123011A1 (en) 2022-11-25
CN117320836A (en) 2023-12-29

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