EP3899081B1 - Verfahren zur herstellung eines kerns - Google Patents

Verfahren zur herstellung eines kerns Download PDF

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Publication number
EP3899081B1
EP3899081B1 EP19848898.3A EP19848898A EP3899081B1 EP 3899081 B1 EP3899081 B1 EP 3899081B1 EP 19848898 A EP19848898 A EP 19848898A EP 3899081 B1 EP3899081 B1 EP 3899081B1
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EP
European Patent Office
Prior art keywords
core
layer
nickel
based alloy
leading edge
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EP19848898.3A
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English (en)
French (fr)
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EP3899081A1 (de
Inventor
Denis FLECHE
Jean-Michel Patrick Maurice Franchet
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Safran SA
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Safran SA
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    • 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
    • C23C4/04—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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—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
    • 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

Definitions

  • the invention relates to the field of manufacturing the leading edge for Organic Matrix Composite (OMC) fan blades.
  • OMC Organic Matrix Composite
  • a blade conventionally has a leading edge and a trailing edge.
  • the leading edge corresponds to the anterior part of the airfoil which faces the airflow and which divides the airflow into a lower surface flow and an upper surface flow, and a trailing edge which corresponds to the rear part of the airfoil.
  • solid debris In the environment of a turbomachine, of an aircraft, it is possible for solid debris to be caught in a flow of air circulating in the turbomachine. This debris will then strike the leading edge of a blade and risk damaging it. Consequently, it is customary to reinforce the leading edge of the blades. This technical arrangement is all the more important in the case of a CMO blade. Indeed, the composite material may poorly resist perforation.
  • the document FR1051992 describes a known method of manufacturing such a blade. This method takes place as follows: two sheets, intrados and extrados, formed, are shaped, via a hot isostatic compaction operation, around a refractory alloy core whose geometry corresponds to the internal geometry of the desired leading edge . After shaping, the core, which is a reusable tool, is removed and the leading edge is machined only on its outer surfaces to obtain the final geometry of the part.
  • This method makes it possible to control the internal shape of the cavity of the leading edge, which is a replica of the blade on which the leading edge will be placed, thus making it possible to do no re-machining of the internal cavity of the leading edge.
  • this technique makes it possible to control and facilitate final machining operations thanks to the presence of the internal core which makes it possible both to stiffen the assembly and to have integrated dimensional references which makes it possible to avoid having recourse , as for the other techniques, to complex machining tools.
  • these different arrangements induce a significant reduction in the cost of the manufacturing range due to the reuse of the cores, then considered as tools.
  • the first characteristic linked to the choice of core material, makes it possible not to have to machine the internal cavity of the leading edge.
  • the second avoids or minimizes the chemical decontamination of the surfaces of the internal cavity of the leading edge.
  • the metal alloys selected for the core are nickel-based or cobalt-based alloys in order to be sufficiently rigid not to deform during high-temperature shaping cycles.
  • this type of alloy brought into contact at high temperature with the titanium alloys of the part are reactive with each other and form solid solutions or intermetallic compounds, which leads at best to contamination of the titanium alloy, to worse a prohibitive bonding between nickel / cobalt and titanium.
  • a technical solution consists of inserting an anti-diffusion barrier between the two metal alloys in contact, namely the nickel or cobalt base alloy of the core and the titanium alloy of the leading edge, which will undergo thermomechanical treatment at high temperature for many hours.
  • a method described by the document EN 1653221 is the realization of a nitriding or nitro-carburizing of the core in nickel or cobalt base. This treatment generates a superficial layer rich in nitrogen and carbon of a few tens of microns on the surface of the core ensuring the role of anti-diffusion barrier.
  • the document FR2463191 discloses a nickel base alloy substrate coated with a layer of a cobalt base alloy.
  • the thermal spraying of this type of alloy provides a chemical inertia which makes it possible to produce an anti-diffusion barrier between the nickel base alloy core and sheets titanium used for the manufacture of the fan blade.
  • this process makes it possible to cover the core with a layer guaranteeing thermomechanical stability, protecting against chemical contamination and avoiding any adhesion of the blade parts to the core.
  • the cobalt base alloy may include carbon.
  • the cobalt base alloy comprises, as a mass percentage, between 26% and 32% molybdenum, between 7% and 20% chromium, between 1% and 5% silicon and less than 1% carbon.
  • the layer can have a hardness between 40 and 65 HRC.
  • the deposited layer may have a thickness of between 100 microns and 2 millimeters, preferably 500 microns.
  • Step (b) can be performed using a method selected from: supersonic flame spraying, blown arc plasma spraying or plasma torch deposition.
  • the method may also comprise, following step (b) of thermal spraying, a step (c) of heat treatment of the layer, carried out between 800 and 1000°C.
  • the method may further comprise, following step (b) of thermal spraying, a step (d) of machining by rectification.
  • the method may further comprise, following step (b) of thermal spraying, a step (e) of heat treatment in air, comprising a first stage of thirty minutes at a temperature between 300° C. and 400° C. C, a second stage of thirty minutes at a temperature between 500°C and 700°C, a third stage of thirty minutes at a temperature between 800°C and 1000°C, and cooling in ambient air, for oxidize the layer.
  • a step (e) of heat treatment in air comprising a first stage of thirty minutes at a temperature between 300° C. and 400° C. C, a second stage of thirty minutes at a temperature between 500°C and 700°C, a third stage of thirty minutes at a temperature between 800°C and 1000°C, and cooling in ambient air, for oxidize the layer.
  • a nickel base alloy core according to claim 8.
  • Step (a) of supplying the initial core can be carried out by machining a nickel-based alloy block to obtain the initial core 11.
  • the initial core 11 can be sandblasted (step (a1)) to increase the roughness of its outer surface.
  • This arrangement advantageously facilitates the attachment of the layer 12 projected in step (b).
  • step (a2) the initial core 11 can be cleaned and degreased. This step makes it possible to guarantee a surface state, of the initial core 11, that is optimal for the next step (b) of projection.
  • the - next - step (b) consists of the thermal spraying on the initial core 11 of a layer 12 of a cobalt-based alloy, comprising chromium and at least one element among tungsten and/or molybdenum.
  • tungsten, molybdenum and chromium may be present in the form of carbide.
  • molybdenum can be used in an intermetallic mixture.
  • an intermetallic mixture is a mixture comprising at least one metalloid.
  • Metalloids being chemical elements whose properties are intermediate between those of metals and non-metals, or are a combination of these properties.
  • the metalloids are the following elements: Boron, Silicon, Germanium, Arsenic, Antimony, Tellurium and Astate.
  • the metalloid preferentially used in combination with molybdenum is silicon.
  • the cobalt-based alloy comprises, as a mass percentage, between 26% and 32% molybdenum, between 7% and 20% chromium, between 1% and 5% silicon and less than 1% carbon.
  • the cobalt base alloy may comprise 29% molybdenum, 8.5% chromium, 2.6% silicon and less than 0.08% carbon.
  • the cobalt base alloy may comprise 28% molybdenum, 18% chromium, 3.4% silicon and less than 0.08% carbon.
  • the thermal spraying of these types of alloys provides a chemical inertia which makes it possible to produce an anti-diffusion barrier between the initial core 11 made of nickel base alloy and metal sheets.
  • titanium used for the manufacture of the fan blade.
  • the thermal spraying can be carried out by supersonic flame, according to a so-called “High Velocity Oxy-Fuel” (HVOF) method or according to a so-called “High Velocity Air-Fuel” (HVAF) method.
  • HVOF High Velocity Oxy-Fuel
  • HVAC High Velocity Air-Fuel
  • the HVOF method is particularly preferred because it consists of spraying the cobalt base alloy at very high speed with a moderate temperature, which generates very little porosity in the layer 12 deposited.
  • the layer can be sprayed by blown arc plasma.
  • This method leads to a porous layer but having a good mechanical grip on the surface of the core.
  • This method can optionally consider vacuum pumping during projection.
  • the layer can be deposited by a plasma torch according to the so-called “Plasma Transferred Arc” (PTA) method.
  • PTA Plasma Transferred Arc
  • the method may comprise a step (c) of heat treatment of layer 12, carried out between 800°C and 1000°C.
  • step (c) is carried out between 850°C and 900°C. This heat treatment makes it possible to relax the internal stresses induced by the deposition of the layer 12, in the previous step.
  • the method can comprise a step (d) of rectification to reduce a thickness of the layer 12.
  • the layer 12 can have a thickness comprised between 100 and 500 microns. This step can also be used as a practical check of deposit adhesion.
  • the method may comprise a step (e) of heat treatment in air, comprising a first stage of thirty minutes at a temperature between 300° C. and 400° C., a second stage of thirty minutes at a temperature of between 500° C. and 700° C., a third stage of thirty minutes at a temperature of between 800° C. and 1000° C., and cooling in ambient air.
  • step (e) may comprise a first plateau of thirty minutes at 350° C., then a second plateau of thirty minutes at 650° C., then a third plateau of thirty minutes at 900° C., followed by cooling to Ambiant air.
  • Step (e), called passivation makes it possible to oxidize the layer 12 on the surface, which makes it possible to reduce the risks of chemical interaction between the layer 12 and the material used to manufacture the blade (most often titanium ).
  • the layer 12 can have a hardness of between 35 and 65 HRC, preferably between 45 and 55 HRC. It is specified that the hardness is expressed and measured according to the so-called Rockwell test, using an indenter on which is applied an initial load and then an additional load. The hardness being measured by comparing the depth of penetration of the indenter during the application of the initial load and during the application of the additional load.
  • the HRC scale In this case, the test is carried out with an indenter consisting of a diamond cone of circular section with a rounded spherical tip of 0.2 millimeters.
  • the initial load applied is 98N and the total load (corresponding to the initial load plus the additional load) is 1471.5N.
  • One HRC hardness unit corresponds to a penetration of 0.002 millimeters.
  • the HR15N scale is preferred because the initial load applied is only 29N and the total load (corresponding to the initial load plus the additional load) is only 147.1N.
  • HV Vickers
  • the test is then carried out with an indenter consisting of a square-based diamond pyramid.
  • the hardness being determined by measuring the two diagonals of the indentation.
  • the load is adapted to the thickness of the layer: 5 to 10 kilograms for thicknesses ⁇ 400 microns and 20 to 30 kilograms maximum for thicknesses greater than 400 microns.
  • this process makes it possible to cover the initial core 11 with a layer 12 guaranteeing thermomechanical stability, protecting against chemical contamination and avoiding any adhesion of the blade parts to the core.
  • the invention relates to a core 1 of nickel-based alloy obtained by a method according to the invention.
  • the core 1 has a layer 12 composed of a cobalt base alloy according to claim 8.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (8)

  1. Verfahren zur Herstellung eines Kerns (1) für die Herstellung einer Vorderkante einer Ventilatorschaufel, dadurch gekennzeichnet, dass es die folgenden Schritte umfasst:
    (a) Bereitstellen eines Ausgangskerns (11) aus einer Legierung auf Nickelbasis,
    (b) thermisches Aufspritzen einer Schicht aus einer Legierung auf Kobaltbasis, die zwischen 26 % und 32 % Molybdän, zwischen 7 % und 20 % Chrom, zwischen 1 % und 5 % Silizium und weniger als 1 % Kohlenstoff in Gewichtsprozent enthält, auf den Ausgangskern (12).
  2. Verfahren nach einem der Ansprüche 1, wobei die Schicht (12) eine Härte zwischen 40 und 65 HRC aufweist.
  3. Verfahren nach Anspruch 1 oder Anspruch 2, wobei die abgeschiedene Schicht (12) eine Dicke zwischen 100 Mikrometer und 2 Millimeter, vorzugsweise 500 Mikrometer, aufweist.
  4. Verfahren nach einem der Ansprüche 1 bis 3, wobei Schritt (b) unter Verwendung eines Verfahrens durchgeführt wird, das ausgewählt ist aus: Überschallflammspritzen, Blaslichtbogenplasmaspritzen oder Plasmabrennerabscheidung.
  5. Verfahren nach einem der Ansprüche 1 bis 4, das nach dem Schritt (b) des thermischen Spritzens einen Schritt (c) der Wärmebehandlung der Schicht (12) umfasst, der zwischen 800 und 1000 °C durchgeführt wird.
  6. Verfahren nach einem der Ansprüche 1 bis 5, das ferner nach dem thermischen Aufspritzen (b) einen Schleifbearbeitungsschritt (d) umfasst.
  7. Verfahren nach einem der Ansprüche 1 bis 6, das ferner nach dem thermischen Aufspritzschritt (b) einen Wärmebehandlungsschritt (e) an Luft umfasst, der eine erste Stufe von dreißig Minuten bei einer Temperatur zwischen 300°C und 400°C, eine zweite Stufe von dreißig Minuten bei einer Temperatur zwischen 500°C und 700°C, eine dritte Stufe von dreißig Minuten bei einer Temperatur zwischen 800°C und 1000°C und ein Abkühlen an Umgebungsluft umfasst, um die Schicht (12) zu oxidieren.
  8. Kern aus einer Legierung auf Nickelbasis, der aus einem ursprünglichen Kern (12) aus einer Legierung auf Nickelbasis erhalten wird, wobei der Kern eine Schicht (12) aufweist, die aus einer Legierung auf Kobaltbasis besteht, die in Gewichtsprozent zwischen 26 % und 32 % Molybdän, zwischen 7 % und 20 % Chrom, zwischen 1 % und 5 % Silizium und weniger als 1 % Kohlenstoff enthält.
EP19848898.3A 2018-12-21 2019-12-20 Verfahren zur herstellung eines kerns Active EP3899081B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1873958A FR3090427B1 (fr) 2018-12-21 2018-12-21 Procede de fabrication d’un noyau
PCT/FR2019/053241 WO2020128391A1 (fr) 2018-12-21 2019-12-20 Procede de fabrication d'un noyau

Publications (2)

Publication Number Publication Date
EP3899081A1 EP3899081A1 (de) 2021-10-27
EP3899081B1 true EP3899081B1 (de) 2022-06-15

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Country Link
US (1) US20220064776A1 (de)
EP (1) EP3899081B1 (de)
CN (1) CN113260731B (de)
FR (1) FR3090427B1 (de)
WO (1) WO2020128391A1 (de)

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GB933406A (en) * 1960-11-17 1963-08-08 Deloro Stellite Ltd A cobalt-chromium base alloy
US3642519A (en) * 1969-03-21 1972-02-15 Us Air Force Method for the development of hard coat seal surfaces
US4339509A (en) * 1979-05-29 1982-07-13 Howmet Turbine Components Corporation Superalloy coating composition with oxidation and/or sulfidation resistance
US4837389A (en) * 1984-06-04 1989-06-06 Turbine Components Corporation Composite alloy structures
DE10041974B4 (de) * 2000-08-25 2008-02-14 Daimler Ag Beschichtungsverfahren für Zylinderköpfe und Verwendung
DE10334703A1 (de) * 2003-07-30 2005-02-24 Daimlerchrysler Ag Ventilsitzringe aus Co oder Co/Mo-Basislegierungen und deren Herstellung
US6933052B2 (en) * 2003-10-08 2005-08-23 General Electric Company Diffusion barrier and protective coating for turbine engine component and method for forming
JP2008522039A (ja) * 2004-11-30 2008-06-26 デロロ・ステライト・ホールディングズ・コーポレイション 耐クラック性を有する溶着可能なコバルト系合金
EP1715140A1 (de) * 2005-04-21 2006-10-25 Siemens Aktiengesellschaft Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht
JP5529366B2 (ja) * 2007-03-29 2014-06-25 三菱重工業株式会社 コーティング材料及びその製造方法並びにコーティング方法並びにシュラウド付き動翼
FR2920440B1 (fr) * 2007-08-31 2010-11-05 Commissariat Energie Atomique Procede de traitement anti-corrosion d'une piece par depot d'une couche de zirconium et/ou d'alliage de zirconium
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FR2957545B1 (fr) * 2010-03-19 2012-07-27 Snecma Procede de realisation d'un insert metallique pour la protection d'un bord d'attaque en materiau composite
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JP5842772B2 (ja) * 2012-09-11 2016-01-13 Ｊｆｅスチール株式会社 継目無鋼管圧延用プラグおよびその製造方法
ITUB20152136A1 (it) * 2015-07-13 2017-01-13 Nuovo Pignone Srl Pala di turbomacchina con struttura protettiva, turbomacchina, e metodo per formare una struttura protettiva
CN107083502B (zh) * 2016-02-12 2023-10-13 肯纳金属公司 耐磨且耐蚀的钴基合金粉末及其施加方法

Also Published As

Publication number Publication date
FR3090427A1 (fr) 2020-06-26
FR3090427B1 (fr) 2023-11-10
CN113260731B (zh) 2023-07-28
WO2020128391A1 (fr) 2020-06-25
US20220064776A1 (en) 2022-03-03
EP3899081A1 (de) 2021-10-27
CN113260731A (zh) 2021-08-13

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