EP3202946B1 - Formung einer aluminidbeschichtung mithilfe von metalllegierungskies - Google Patents

Formung einer aluminidbeschichtung mithilfe von metalllegierungskies Download PDF

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Publication number
EP3202946B1
EP3202946B1 EP17153434.0A EP17153434A EP3202946B1 EP 3202946 B1 EP3202946 B1 EP 3202946B1 EP 17153434 A EP17153434 A EP 17153434A EP 3202946 B1 EP3202946 B1 EP 3202946B1
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EP
European Patent Office
Prior art keywords
component
coating
metal alloy
gravel
aluminide 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.)
Active
Application number
EP17153434.0A
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English (en)
French (fr)
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EP3202946A1 (de
Inventor
Kevin L. Collins
Michael J. Minor
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RTX Corp
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United Technologies Corp
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Publication date
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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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/48—Aluminising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • 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
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C23C10/54—Diffusion of at least chromium
    • C23C10/56—Diffusion of at least chromium and at least aluminium
    • 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
    • C23C10/60—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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat

Definitions

  • This disclosure relates to forming an aluminide coating on a component.
  • aluminide coatings on a component Various methods are known for forming aluminide coatings on a component.
  • a pack cementation method for example, aluminum from an aluminum powder surrounding the component can be heated and diffused into a base material of that component.
  • Such a method may be susceptible to cracking and/or trenching.
  • the aluminum source may be chrome aluminum and/or cobalt aluminum.
  • Activator material may be disposed with the metal alloy gravel.
  • the activator material may be configured as or otherwise include halide material.
  • the method may include a further step of heat treating the aluminide coating to provide a heat treated diffusion coating.
  • the aluminide coating may be a green state coating.
  • the heat treated diffusion coating may be a three-zone aluminide coating.
  • the component may be laid on top of the metal alloy gravel.
  • the component may be partially submersed in the metal alloy gravel.
  • the component may be completely submersed in the metal alloy gravel.
  • the method may include a step of masking a portion of the component such that the masked portion of the component is not coated with the aluminide coating.
  • the component may be configured from or otherwise include a nickel alloy.
  • the component may be configured as a part of a gas turbine engine.
  • the component may be configured as an airfoil.
  • FIG. 1 is a block diagram illustration of a system 20 for coating a component 22.
  • FIG. 2 is a flow diagram of a method 200 for coating a component (e.g., 22) using a system such as, for example, the system 20 of FIG. 1 .
  • the component 22 may be configured for an item of rotational equipment such as a gas turbine engine.
  • This gas turbine engine may be configured in an aircraft propulsion system.
  • the gas turbine engine may be configured in an auxiliary power unit for the aircraft.
  • the methods and apparatuses of the present disclosure are not limited to such aircraft applications.
  • the gas turbine engine may be configured as an industrial gas turbine engine in a power generation system.
  • the item of rotational equipment may alternatively be configured as a wind turbine, a water turbine or any other item of rotational equipment which includes a component with a coating as described below.
  • the component 22 is described below as a component of a gas turbine engine.
  • the component 22, for example, may be configured as or include an airfoil as described below.
  • Examples of such a component include, but are not limited to, a fan blade, a compressor blade, a turbine blade, a guide vane, a compressor vane, a turbine vane and a propeller.
  • the component 22 of the present disclosure is not limited to the foregoing exemplary component configurations, or to rotational equipment applications.
  • the component 22 has a metal component body 24; e.g., base material.
  • This component body 24 provides the component 22 with its structure and general geometry; e.g., shape and dimensions.
  • the component body 24 is constructed from metal, which is the base material.
  • suitable metals include, but are not limited to, nickel (Ni), titanium (Ti) or an alloy of one or more of the foregoing materials.
  • suitable metal alloy include, but are not limited to, airfoil and various hot section turbine components.
  • the component body 24 of the present disclosure is not limited to the foregoing exemplary component body materials.
  • source material 26 is provided for coating the component 22 and, more particularly, its body 24.
  • the source material 26, for example, may be disposed in an open container 27 to provide a bed of the source material 26 as shown in FIG. 1 .
  • This source material 26 includes metal alloy gravel.
  • the source material 26 may also include activator material, which may be homogeneously or heterogeneously mixed with some or all of the metal alloy gravel.
  • the metal alloy gravel includes a loose aggregation of small particles of metal alloy material. This metal alloy gravel is different from a quantity of metal alloy dust or powder.
  • the metal alloy gravel of the present invention has an average particle size of at least about 0.125 inches (3.18 mm).
  • the particle size may be a measure of a particle's diameter where that particle is generally spherical.
  • the particle size may alternatively be a measure of a particle's length, width or height where that particle is non-spherical; e.g., globular cluster, cubic, ellipsoidal, etc.
  • the average particle size of that particle may be the average of the particle's length, width and height.
  • the average particle size of the metal alloy gravel may be calculated as an average of the particle sizes of the particles in the metal alloy gravel.
  • the metal alloy material is a metal alloy which includes aluminum.
  • the metal alloy material may be an alloy of cobalt (Co) and aluminum such as, for example, CoAl.
  • the metal alloy material may be an alloy of chrome (Cr) and aluminum such as, for example, CrAl.
  • the present disclosure is not limited to the foregoing exemplary alloys.
  • the activator material is selected to promote diffusion of the aluminum from the metal alloy gravel into the component 22 and its body 24 to form an aluminide coating 28 (see FIG. 6 ).
  • An example of such an activation material is a halide material; e.g., chloride halide.
  • the present disclosure is not limited to the foregoing exemplary halide or activator material.
  • the component 22 is disposed with the source material 26.
  • the component 22, for example, may be partially submersed (e.g., covered) within the bed of the source material 26 as shown in FIGS. 1 and 3 . In this manner, the component 22 projects into the bed of the source material 26 such as that the source material 26 contacts multiple exterior surfaces 30-32 of the component body 24.
  • the component 22 may be laid on top of the bed of the source material 26 as shown in FIG. 4 . In this manner, only the bottom surface 30 of the component body 24 contacts the source material 26.
  • the component 22 may be completely submersed within (e.g., covered and surrounded by) the source material 26 as shown in FIG. 5 . In this manner, the source material 26 contacts all exterior surfaces (e.g., 30-33) of the component body 24 of FIG. 5 .
  • the aluminide coating 28 is formed on the component 22 (see FIG. 6 ).
  • a heating vessel 34 e.g., oven
  • at least an outer peripheral portion of the component 22 as well as the source material 26 is heated to an elevated temperature using a heater 36 (see FIG. 1 ).
  • the aluminum from the metal alloy gravel diffuses into material in an outer peripheral region of the component body 24 and thereby forms the aluminide coating 28 (see FIG. 6 ).
  • the elevated temperature may be selected such that the aluminide coating 28 is generally (or more of) an inward diffusion coating rather than an outward diffusion coating.
  • inward diffusion coating may describe a coating formed by diffusing material into a base material; i.e., the material being coated. Generally speaking, such an inward diffusion coating does not substantially change the exterior dimensions of the original base material.
  • outward diffusion coating may describe a coating formed by the diffusion of a base material outward into surrounding material; i.e., coating material. Generally speaking, such an outward diffusion coating increases the exterior dimensions of the original base material.
  • the elevated temperature is selected to be between fourteen-hundred degrees Fahrenheit (1400°F or 760°C) and sixteen-hundred degrees Fahrenheit (1600°F or 871°C).
  • an exterior of the component body 24 of FIG. 6 is completely (partially in FIG. 10 ) coated with the aluminide coating 28; e.g., an inward diffusion aluminide coating.
  • This aluminide coating 28 may be referred to as a green state coating.
  • the term "green state coating” may describe a coating with a relatively high weight percentage and a relatively high atomic percentage of aluminum.
  • the aluminide coating 28, for example may have a weight percentage of aluminum of about forty percent (40%) to about sixty percent (60%).
  • the aluminide coating 28 may have an atomic percentage of aluminum of about sixty percent (60%) to about seventy percent (70%).
  • Such a green state coating may be relatively brittle.
  • the aluminide coating 28 formed in the coating step 206 is not limited to the foregoing exemplary weight and atomic percentages of aluminum.
  • the coated component 22 and, more particularly, the aluminide coating 28 is heat treated to provide a heat treated aluminide coating 28' (see FIG. 7 ).
  • the environment within the heating vessel 34 of FIG. 1 (or another heating vessel or system) and, as a result, the aluminide coating 28 is heated to another elevated temperature.
  • the relatively brittle green state coating may be transformed into a less brittle diffused state coating.
  • the term "diffused state coating” may describe a coating with a relatively low weight percentage and a relatively low atomic percentage of aluminum.
  • the heat treated aluminide coating 28' may have a weight percentage of aluminum of about twenty-five percent (25%) to about thirty-two percent (32%).
  • the heat treated aluminide coating 28' may have an atomic percentage of aluminum of about forty percent (40%) to about fifty percent (50%).
  • the heat treated aluminide coating 28' formed in the heat treating step 208 is not limited to the foregoing exemplary weight and atomic percentages of aluminum.
  • the heat treated aluminide coating 28' may be a three-zone aluminide coating as shown in FIG. 7 .
  • Such a three-zone aluminide coating may include a diffusion zone 38, an intermediate zone 40 and an additive zone 42.
  • the diffusion zone 38 is between the base material of the component body 24 and the intermediate zone 40.
  • This zone 38 includes a relatively low atomic percentage of aluminum which has diffused into the base material of the component body 24.
  • the intermediate zone 40 is between the diffusion zone 38 and the additive zone 42.
  • This zone 40 includes a higher atomic percentage of aluminum than the diffusion zone 38, in which aluminum is also diffused to a lesser degree into the base material of the component body 24.
  • the additive zone 42 is the outermost zone and includes the highest atomic percentage of aluminum, where the base material of the component body 24 may have diffused outward to form an additive portion.
  • one or more portions of the component body 24 may be masked to prevent coating those portions with the aluminide coating 28, 28' described above.
  • a mask 44 e.g., masking putty
  • the masked off component 22 may then undergo the coating step 206 as shown in FIG. 9 .
  • the mask 44 may be removed from the now coated component body 24 to reveal an uncoated (e.g., bare) surface 46 of the component body 24 as shown in FIG. 10 where the mask was removed.
  • FIG. 11 illustrates one such type and configuration of the rotational equipment - a geared turbofan gas turbine engine 70.
  • This turbine engine 70 includes various types and configurations of rotor blade airfoils as described below as well as stator vane airfoils, where the component 22 can be configured as anyone of the foregoing airfoils, or other structures not mentioned herein.
  • the turbine engine 70 extends along an axial centerline 76 between an upstream airflow inlet 78 and a downstream airflow exhaust 80.
  • the turbine engine 70 includes a fan section 82, a compressor section 83, a combustor section 84 and a turbine section 85.
  • the compressor section 83 includes a low pressure compressor (LPC) section 83A and a high pressure compressor (HPC) section 83B.
  • the turbine section 85 includes a high pressure turbine (HPT) section 85A and a low pressure turbine (LPT) section 85B.
  • the engine sections 82-85 are arranged sequentially along the centerline 76 within an engine housing 86.
  • This housing 86 includes an inner case 88 (e.g., a core case) and an outer case 90 (e.g., a fan case).
  • the inner case 88 may house one or more of the engine sections 83-85; e.g., an engine core.
  • the outer case 90 may house at least the fan section 82.
  • Each of the engine sections 82, 83A, 83B, 85A and 85B includes a respective rotor 92-96.
  • Each of these rotors 92-96 includes a plurality of rotor blades with airfoils arranged circumferentially around and connected to one or more respective rotor disks.
  • the rotor blades may be formed integral with or mechanically fastened, welded, brazed, adhered and/or otherwise attached to the respective rotor disk(s).
  • the fan rotor 92 is connected to a gear train 98, for example, through a fan shaft 100.
  • the gear train 98 and the LPC rotor 93 are connected to and driven by the LPT rotor 96 through a low speed shaft 101.
  • the HPC rotor 94 is connected to and driven by the HPT rotor 95 through a high speed shaft 102.
  • the shafts 100-102 are rotatably supported by a plurality of bearings 104. Each of these bearings 104 is connected to the engine housing 86 by at least one stationary structure such as, for example, an annular support strut.
  • This air is directed through the fan section 82 and into a core gas path 106 and a bypass gas path 108.
  • the core gas path 106 flows sequentially through the engine sections 83-85.
  • the bypass gas path 108 flows away from the fan section 82 through a bypass duct, which circumscribes and bypasses the engine core.
  • the air within the core gas path 106 may be referred to as "core air”.
  • the air within the bypass gas path 108 may be referred to as "bypass air”.
  • the core air is compressed by the compressor rotors 93 and 94 and directed into a combustion chamber 110 of a combustor in the combustor section 84.
  • Fuel is injected into the combustion chamber 110 and mixed with the compressed core air to provide a fuel-air mixture.
  • This fuel air mixture is ignited and combustion products thereof flow through and sequentially cause the turbine rotors 95 and 96 to rotate.
  • the rotation of the turbine rotors 95 and 96 respectively drive rotation of the compressor rotors 94 and 93 and, thus, compression of the air received from a core airflow inlet.
  • the rotation of the turbine rotor 96 also drives rotation of the fan rotor 92, which propels bypass air through and out of the bypass gas path 108.
  • the propulsion of the bypass air may account for a majority of thrust generated by the turbine engine 70, e.g., more than seventy-five percent (75%) of engine thrust.
  • the turbine engine 70 of the present disclosure is not limited to the foregoing exemplary thrust ratio.
  • the component 22 may be included in various aircraft and industrial turbine engines other than the one described above as well as in other types of rotational equipment and non-rotating equipment.
  • the component 22 may be included in a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section.
  • the component 22 may be included in a turbine engine configured without a gear train.
  • the component 22 may be included in a geared or non-geared turbine engine configured with a single spool, with two spools (e.g., see FIG. 11 ), or with more than two spools.
  • the turbine engine may be configured as a turbofan engine, a turbojet engine, a propfan engine, a pusher fan engine or any other type of turbine engine.
  • the present invention is not limited to any particular types or configurations of turbine engines or rotational equipment.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Verfahren zum Beschichten einer Komponente (22), umfassend:
    Anordnen der Komponente (22) mit Metalllegierungskies, der Aluminium umfasst;
    Erhitzen des Metalllegierungskies, der an die Komponente (22) angrenzt, auf eine Temperatur zwischen 1400 Grad Fahrenheit und 1600 Grad Fahrenheit (760 Grad Celsius und 871 Grad Celsius); und
    Formen einer Aluminidbeschichtung (28) an der Komponente (22), wobei das Aluminium aus dem Metalllegierungskies in die Komponente (22) eindringt, um die Aluminidbeschichtung (28) zu formen,
    dadurch gekennzeichnet, dass der Metalllegierungskies eine durchschnittliche Partikelgröße von mindestens 0,125 Zoll (3,18 mm) aufweist.
  2. Verfahren nach Anspruch 1, wobei der Metalllegierungskies ferner Chrom-Aluminium und/oder Cobalt-Aluminium umfasst.
  3. Verfahren nach einem der vorgehenden Ansprüche, wobei Aktivatormaterial mit dem Metalllegierungskies angeordnet ist.
  4. Verfahren nach Anspruch 3, wobei das Aktivatormaterial Halogenidmaterial umfasst.
  5. Verfahren nach einem der vorgehenden Ansprüche, ferner umfassend Wärmebehandeln der Aluminidbeschichtung (28), um eine wärmebehandelte Diffusionsbeschichtung bereitzustellen.
  6. Verfahren nach Anspruch 5, wobei die Aluminidbeschichtung (28) eine Beschichtung im Grünzustand ist und die wärmebehandelte Diffusionsbeschichtung eine Dreizonen-Aluminidbeschichtung ist.
  7. Verfahren nach einem der vorgehenden Ansprüche, wobei die Komponente (22) oben auf den Metalllegierungskies gelegt wird.
  8. Verfahren nach einem der Ansprüche 1 bis 6, wobei die Komponente (22) teilweise oder vollständig in den Metalllegierungskies eingetaucht ist.
  9. Verfahren nach einem der vorgehenden Ansprüche, ferner umfassend Maskieren eines Abschnitts der Komponente (22), sodass der maskierte Abschnitt der Komponente (22) nicht mit der Aluminidbeschichtung (28) beschichtet wird.
  10. Verfahren nach einem der vorgehenden Ansprüche, wobei die Komponente (22) eine Nickellegierung umfasst.
  11. Verfahren nach einem der vorgehenden Ansprüche, wobei die Komponente (22) als ein Teil eines Gasturbinentriebwerks (70) konfiguriert ist.
  12. Verfahren nach Anspruch 11, wobei die Komponente (22) ein Schaufelprofil ist.
EP17153434.0A 2016-02-05 2017-01-27 Formung einer aluminidbeschichtung mithilfe von metalllegierungskies Active EP3202946B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/016,344 US20170226623A1 (en) 2016-02-05 2016-02-05 Forming aluminide coating using metal alloy gravel

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EP3202946A1 EP3202946A1 (de) 2017-08-09
EP3202946B1 true EP3202946B1 (de) 2020-10-21

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Citations (1)

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US20110074113A1 (en) * 2009-09-30 2011-03-31 General Electric Company Method and composition for coating of honeycomb seals

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
US3837901A (en) * 1970-08-21 1974-09-24 Gen Electric Diffusion-coating of nickel-base superalloy articles
EP0731187A1 (de) * 1995-03-07 1996-09-11 Turbine Components Corporation Verfahren zur Erzeugung einer Schutzdiffusionsschicht auf Legierungen auf Nickel-, Kobalt- und Eisenbasis
US6224941B1 (en) * 1998-12-22 2001-05-01 General Electric Company Pulsed-vapor phase aluminide process for high temperature oxidation-resistant coating applications
US7371428B2 (en) * 2005-11-28 2008-05-13 Howmet Corporation Duplex gas phase coating
US20090035485A1 (en) * 2007-08-02 2009-02-05 United Technologies Corporation Method for forming active-element aluminide diffusion coatings
JP5654003B2 (ja) * 2009-05-18 2015-01-14 シフコ インダストリーズ, インコーポレイテッドSifco Industries, Inc. 気相拡散技術を用いた、反応成分量の低い、反応成分で修飾されたアルミニウム化合物コーティング

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110074113A1 (en) * 2009-09-30 2011-03-31 General Electric Company Method and composition for coating of honeycomb seals

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EP3202946A1 (de) 2017-08-09

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