EP1508628A1 - Pièce comprenant un masque et méthode de revêtement d'une pièce - Google Patents

Pièce comprenant un masque et méthode de revêtement d'une pièce Download PDF

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Publication number
EP1508628A1
EP1508628A1 EP03018574A EP03018574A EP1508628A1 EP 1508628 A1 EP1508628 A1 EP 1508628A1 EP 03018574 A EP03018574 A EP 03018574A EP 03018574 A EP03018574 A EP 03018574A EP 1508628 A1 EP1508628 A1 EP 1508628A1
Authority
EP
European Patent Office
Prior art keywords
component
masking layer
ceramic
base material
coating
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.)
Withdrawn
Application number
EP03018574A
Other languages
German (de)
English (en)
Inventor
Nigel-Philip Cox
Oliver Dr. Dernovsek
Ralph Reiche
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP03018574A priority Critical patent/EP1508628A1/fr
Publication of EP1508628A1 publication Critical patent/EP1508628A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks
    • 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
    • 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
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/04—Treatment of selected surface areas, e.g. using masks
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the invention relates to a component with a Masking layer according to the preamble of claim 1 and a method according to the preamble of claim 12.
  • Components such as turbine blades, in particular for gas turbines, are coated in particular in the blade area, because they are exposed to high thermal loads.
  • Components such as turbine blades, in particular for gas turbines, are coated in particular in the blade area, because they are exposed to high thermal loads.
  • In the base or in the mounting region of the turbine blade lower temperatures prevail, so that there is no coating in the form of a thermal barrier coating is necessary. Ceramic coatings are even undesirable in this area, because the base must be fitted exactly in a metallic disc.
  • Prior art masks that have a coating to prevent unwanted places have the The disadvantage that they are often difficult to remove, as a good adhesion of the material of the masking with the Basic material of the turbine blade is given, or as a unwanted diffusion of elements from the masking layer into the base material of the turbine blade.
  • the object of the invention is therefore to provide a component with a Masking layer to show, which after a desired Coating of the component in the unwanted areas easy to remove again without it becoming one Influencing the basic material or the geometry of the Component in the masked area comes.
  • the object is achieved by a component according to claim 1.
  • the component has a plasma-sprayed layer directly on the base material of the component.
  • Another object of the invention is to provide a method for Show coating of a component in which the Masking layer after a desired coating of Component in unwanted areas again easily can be removed without affecting the Base material or the geometry of the component in the masked area is coming.
  • a masking layer is applied by means of plasma spraying directly on the base material of the component (eg turbine blade).
  • Thermal barrier coatings that are applied to a turbine blade in the airfoil region generally have intermediate layers between a substrate, ie, the base material of the turbine blade and the thermal barrier coating, such as so-called adhesive layers, for example metallic MCrAlX, or diffusion barriers.
  • these intermediate layers are dispensed with in order to prevent a good binding of the masking layer.
  • the masking layer is in particular of ceramic, because the brittle ceramic can be removed by simple methods, such as sandblasting, dry ice blasting.
  • the material for the ceramic is chosen so that there is little or no diffusion out of the ceramic into the substrate, resulting in no chemical bonding between masking layer and base material. Therefore, ceramics are preferred.
  • the invention is based on Embodiments explained in more detail.
  • FIG. 1 shows a perspective view of a turbine blade 1, in particular a rotor blade for a gas turbine, which extends along a longitudinal axis 4.
  • the turbine blade 1 has, along the longitudinal axis 4, a fastening area 7, an adjacent blade platform 10 and an airfoil area 13 in succession.
  • the fastening region 7 is designed as a blade root 16, which serves for fastening the turbine blade 1 to a shaft (not shown here) of a turbomachine (FIG. 7).
  • the blade root 16 is designed, for example, as a hammer head. Other configurations, for example as a Christmas tree or Schwalbenschwanzfuß are possible.
  • turbine blades 1 are in all areas the turbine blade solid metallic materials, especially nickel- or cobalt-based superalloys, used.
  • the turbine blade can in this case by a casting process, by a forging process, by a milling process or combinations thereof.
  • the attachment portion 7 is made of metal, because the exact fit in a corresponding shape of a disc of the Turbine rotor is trapped. Brittle ceramic Coatings for thermal insulation would thereby flake off and change the geometry in the attachment area. A coating is therefore not desirable there.
  • the airfoil region 13 is, for example, with a Thermal barrier coated, being between the base material the turbine blade 1, for example, even more Layers, such as e.g. Adhesion promoter layers (MCrAlX layers) can be arranged.
  • a Thermal barrier coated being between the base material the turbine blade 1, for example, even more Layers, such as e.g. Adhesion promoter layers (MCrAlX layers) can be arranged.
  • FIG. 2 shows what happens when the surface of the component 1, for example the blade 1, has no masking layer 25 (FIG. 3).
  • the coating takes place wherever the material 22 impinges.
  • the material 22 of an intermediate layer 19 (MCrAlX) which has been applied to a surface of the turbine blade 1 by plasma spraying, PVD or CVD or immersion in a liquid metal or powder in any form, for example, may also be made into a Reaction of the material 22 with the base material 40 of the turbine blade 1 and lead to a good adhesion of the intermediate layer 19 with the base material 40 of the turbine blade 1. If the intermediate layer 19 is to be removed again because it is undesirable, for example, in the attachment region 7, this presents great problems because the geometry of the attachment region 7 changes due to partial removal of the base material 40.
  • the material 22 is, for example, aluminum, which is applied to the turbine blade 1 to form an aluminide layer.
  • Such an aluminide layer or MCrAlX layer can be applied by plasma spraying or by methods such as those disclosed in EP patent 0 525 545 B1 and EP patent 0 861 919 B1.
  • the parameters are set to give good physical adhesion to the base material 40, for example, by a correspondingly high plasma temperature so that the powder particles also melt sufficiently and / or not too finely (evaporate too fine powder particles) and become too coarse not soft enough and do not deform when hitting) powder particles.
  • heat treatments are performed with the component and the layer, which leads to the optimal adhesion of the layer on the base material 40.
  • Figure 3 shows an inventive component in the form of a Turbine blade 1 with a masking layer 25.
  • a masking layer 25 made of metal, but in particular a ceramic masking layer 37 by means of plasma spraying is applied directly to the metallic turbine blade 1, so that there is no chemical bond between the masking layer 25 and base material 40 results.
  • the plasma-sprayed layer physically adheres to the base material 40 by clamping, the surface of which is roughened, for example.
  • the parameters in plasma spraying can also be set so that the adhesion of the masking layer 25 to the base material 40 is poor, namely by choosing low plasma temperatures, so that the powder particles are not so strongly melted and the use of coarser powder particles, which melt poorly.
  • the plasma-sprayed layer can be as dense or porous as possible.
  • no heat treatment is performed to achieve optimum adhesion between masking layer 25 and base material 40.
  • the dense or partially porous ceramic layer 37 also forms a diffusion barrier during a coating process of the turbine blade 1 with various layers, such as adhesion promoter layers or thermal barrier coatings.
  • the good adhesion of a ceramic layer to the base material 40 for operational use is generally made possible only by a primer layer (MCrAlX).
  • the ceramic layer 37 would flake off after a short period of use, since the thermal expansion coefficients of base material 40 and ceramic layer differ too much.
  • the ceramic layer as the ceramic masking layer 37 has to hold only one, two or three coating operations, this is not a problem, on the contrary, since it is easy to remove and undergoes little or no chemical reaction with the substrate 40.
  • the masking layer 25 can therefore be made of ceramic and / or metal.
  • an expansion coefficient of the masking layer 25 can be adjusted so that a clear difference between the expansion coefficients of the base material 40 of the component 1 and the masking layer 25 results. Due to this difference, good adhesion between the masking layer 25 and the base material 40 is not achieved.
  • the ceramic may for example be an oxide ceramic, which is adapted to the thermal expansion coefficient of the base material or be alumina and / or zirconia.
  • the zirconia may be non-stabilized, partially stabilized or fully stabilized zirconia using stabilizers of yttria, magnesia and / or calcia.
  • Non-stabilized zirconium oxide in particular, is advantageous, since in the phase transition orthogonal-tetragonal a volume change results, which only takes place at higher temperatures above the coating temperature.
  • a thermal process for example. By simple heating of the component 1 with the masking layer 37, a detachment of the masking layer 37 take place. A thermal shock can also be used.
  • the component 1 is for example a component of a gas 100 (FIG. 7) or steam turbine, that is to say a turbine blade 120, 130, a combustor liner 155 or another Housing part, which is a hot medium, such as water vapor or Hot gas is exposed.
  • a gas 100 FIG. 7
  • steam turbine that is to say a turbine blade 120, 130, a combustor liner 155 or another Housing part, which is a hot medium, such as water vapor or Hot gas is exposed.
  • the base material 40 of the component 1 is for example a nickel- or cobalt-based superalloy.
  • FIGS. 4, 5 and 6 show the sequence of a coating of the component 1 with a masking layer 25, 37.
  • the masking layer 25 is applied to the base material 40 of the component 1 at points 55 as described above, which are not to be provided later with the actual desired coating (eg thermal barrier coating).
  • the component 1 is coated with a material 22.
  • FIG. 5 shows the component 1 after being coated with the material 22.
  • the material 22 is present in the desired manner.
  • the masking layer 25, 37 has also been coated with the material 22 and now forms a layer 43, which is easy to remove.
  • the layer 43 can easily be obtained by etching (acid treatment) and / or thermal shock and / or sandblasting and / or water jets and / or dry ice blasting and / or heating, whereby the layer 43 and the base material 40 become so strongly different, for example because of the different coefficients of expansion Thermal mismatch that the masking layer 43 peels off.
  • FIG. 6 shows the component 1 after the masking layer 25, 43 has been removed. Only at the desired locations 55 is a coating available.
  • a further layer can be applied to the component 1 according to FIG. 5 so that, for example, a ceramic thermal barrier coating is still applied to the material 22 at the desired locations 55.
  • the masking layer 25 with the material 22, ie the layer 43 is not yet removed, but is in turn used so that no coating takes place at undesirable locations.
  • the method can be carried out with newly manufactured components 1 or components 1 to be reprocessed.
  • Remanufacturing means that a part 1 that was in use or had errors after the rebuild is reworked.
  • corrosion and oxidation products and / or existing layers are removed.
  • existing cracks are repaired, for example, by filling with solder.
  • a new coating can be applied to such a component 1, again using a masking layer 25, 37.
  • the reprocessing of components 1 is also called refurbishment.
  • FIG. 7 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a suction housing 104 Along the rotor 103 follow one another a suction housing 104, a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed of two blade rings. As seen in the flow direction of a working medium 113 follows in the hot gas duct 111 of a guide vane 115 a from Blades 120 series 125 formed.
  • the guide vanes 130 are in this case on an inner housing 138 a stator 143 attached, whereas the blades 120 a series 125, for example by means of a turbine disk 133 are mounted on the rotor 103.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the substrates may have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the material used is iron-, nickel- or cobalt-based superalloys.
  • superalloys are used, as are known from EP 1204776, EP 1306454, EP 1319729, WO 99/67435 or WO 00/44949; these writings are part of the revelation.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is yttrium (Y) and / or at least one element of the rare Erden) and have heat through a thermal barrier coating.
  • the thermal barrier coating consists for example of ZrO 2 , Y 2 O 4 -ZrO 2, ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
  • the vane 130 has an inner housing 138 of the Turbine 108 facing Leitschaufelfuß (not here shown) and a Leitschaufelfuß opposite Guide vane head on.
  • the vane head is the rotor 103 facing and on a mounting ring 140 of the stator 143rd established.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP03018574A 2003-08-18 2003-08-18 Pièce comprenant un masque et méthode de revêtement d'une pièce Withdrawn EP1508628A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03018574A EP1508628A1 (fr) 2003-08-18 2003-08-18 Pièce comprenant un masque et méthode de revêtement d'une pièce

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03018574A EP1508628A1 (fr) 2003-08-18 2003-08-18 Pièce comprenant un masque et méthode de revêtement d'une pièce

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EP1508628A1 true EP1508628A1 (fr) 2005-02-23

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EP03018574A Withdrawn EP1508628A1 (fr) 2003-08-18 2003-08-18 Pièce comprenant un masque et méthode de revêtement d'une pièce

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006033047A1 (de) * 2006-07-14 2008-01-24 Viktor Georgiev Abdeckbauteil zum Maskieren von Oberflächen zu behandelnden Werkstücken
EP1760168A3 (fr) * 2005-09-01 2008-08-27 United Technologies Corporation Méthode de déposition d'un revêtement de barrière thermique hybride et composant revetu
EP2196555A1 (fr) * 2008-12-03 2010-06-16 Siemens Aktiengesellschaft Mélange de poudre de céramique et de verre, composant doté d'un masque et procédé d'application
EP2876185A1 (fr) 2013-11-21 2015-05-27 Siemens Aktiengesellschaft Article revêtu et procédé d'application d'un revêtement sur un article
US20160333705A1 (en) * 2015-05-12 2016-11-17 MTU Aero Engines AG Combination of blade tip cladding and erosion-resistant layer and method for the production thereof
US11466407B2 (en) * 2016-03-31 2022-10-11 Btg Eclepens S.A. Masked coating blade

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5893866A (ja) * 1981-12-01 1983-06-03 Agency Of Ind Science & Technol 表面処理防止方法
US4845139A (en) * 1979-09-07 1989-07-04 Alloy Surfaces Company, Inc. Masked metal diffusion
US5262245A (en) * 1988-08-12 1993-11-16 United Technologies Corporation Advanced thermal barrier coated superalloy components
EP0844368A2 (fr) * 1996-11-26 1998-05-27 United Technologies Corporation Revêtissement partiel des aubes de turbine à gaz pour améliorer la résistance à la fatigue

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4845139A (en) * 1979-09-07 1989-07-04 Alloy Surfaces Company, Inc. Masked metal diffusion
JPS5893866A (ja) * 1981-12-01 1983-06-03 Agency Of Ind Science & Technol 表面処理防止方法
US5262245A (en) * 1988-08-12 1993-11-16 United Technologies Corporation Advanced thermal barrier coated superalloy components
EP0844368A2 (fr) * 1996-11-26 1998-05-27 United Technologies Corporation Revêtissement partiel des aubes de turbine à gaz pour améliorer la résistance à la fatigue

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 007, no. 191 (C - 182) 20 August 1983 (1983-08-20) *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1760168A3 (fr) * 2005-09-01 2008-08-27 United Technologies Corporation Méthode de déposition d'un revêtement de barrière thermique hybride et composant revetu
US7422771B2 (en) 2005-09-01 2008-09-09 United Technologies Corporation Methods for applying a hybrid thermal barrier coating
DE102006033047A1 (de) * 2006-07-14 2008-01-24 Viktor Georgiev Abdeckbauteil zum Maskieren von Oberflächen zu behandelnden Werkstücken
EP2196555A1 (fr) * 2008-12-03 2010-06-16 Siemens Aktiengesellschaft Mélange de poudre de céramique et de verre, composant doté d'un masque et procédé d'application
EP2876185A1 (fr) 2013-11-21 2015-05-27 Siemens Aktiengesellschaft Article revêtu et procédé d'application d'un revêtement sur un article
US20160333705A1 (en) * 2015-05-12 2016-11-17 MTU Aero Engines AG Combination of blade tip cladding and erosion-resistant layer and method for the production thereof
DE102015208781A1 (de) * 2015-05-12 2016-11-17 MTU Aero Engines AG Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht sowie Verfahren zur Herstellung derselben
US11466407B2 (en) * 2016-03-31 2022-10-11 Btg Eclepens S.A. Masked coating blade

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