EP1637622A1 - Procédé pour le dépôt d'un revêtement protecteur - Google Patents

Procédé pour le dépôt d'un revêtement protecteur Download PDF

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Publication number
EP1637622A1
EP1637622A1 EP05018871A EP05018871A EP1637622A1 EP 1637622 A1 EP1637622 A1 EP 1637622A1 EP 05018871 A EP05018871 A EP 05018871A EP 05018871 A EP05018871 A EP 05018871A EP 1637622 A1 EP1637622 A1 EP 1637622A1
Authority
EP
European Patent Office
Prior art keywords
layer
diffusion layer
diffusion
content
base metal
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.)
Ceased
Application number
EP05018871A
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German (de)
English (en)
Inventor
Sharad Dr. Chandra
Norbert Dr. Czech
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.)
Everllence SE
Original Assignee
MAN Turbo AG
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 MAN Turbo AG filed Critical MAN Turbo AG
Publication of EP1637622A1 publication Critical patent/EP1637622A1/fr
Ceased legal-status Critical Current

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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
    • C23C10/60—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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02—Pretreatment 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties

Definitions

  • the invention relates to a method for applying a protective layer to a base metal having the features of the preamble of claim 1.
  • thermal barrier coatings serve to lower the material temperature of cooled components. This can extend their service life, reduce cooling air or operate the machine with higher inlet temperatures.
  • Thermal barrier coating systems always consist of a metal with the base material (base metal) by diffusion bonded metallic adhesive layer and an overlying ceramic layer with poor thermal conductivity, which is the actual barrier to heat flow and protects the base metal against high temperature corrosion and high temperature erosion.
  • thermal barrier coating zirconia As a ceramic material for the thermal barrier coating zirconia has prevailed, which is partially stabilized with about 7 wt .-% yttria (International abbreviation: "YPSZ" Yttria Partially Stabilized Zirconia).
  • the thermal barrier coatings are divided into two main classes according to the respective application method. In the layers sprayed thermally (usually with atmospheric plasma, APS), a porosity of between about 10 and 25% by volume is set depending on the desired layer thickness and stress distribution. The bond to the rough sprayed adhesive layer is made by mechanical clamping.
  • Thermal barrier coatings deposited by physical vapor deposition processes by electron beam have a columnar (columnar), strain-tolerant structure, while maintaining certain deposition conditions.
  • the layer is chemically bonded by the formation of an Al / Zr mixed oxide on a pure aluminum oxide layer (T G hermally rown O xide, TGO) which is subsequently formed from the adhesive layer during the application and operation.
  • T G hermally rown O xide
  • Adhesive layers are subject to the following complex requirements, namely low static and cyclic oxidation rates, the formation of a pure aluminum oxide layer as TGO (for layers produced by the EB-PVD process), sufficient resistance to high-temperature corrosion, low brittleness, Ductile transition temperature, high creep resistance, good adhesion, minimal long-term interdiffusion with the base material and economical application of the adhesive layer in reproducible quality.
  • the properties of the coating layers can be further improved by adding special refractory elements such as rhenium and tantalum or by alitating.
  • MCrAlY layers contain the intermetallic ⁇ -phase NiCoAl as an aluminum source. However, this phase also has a brittle effect, so that the practically realizable Al content in the MCrAlY layer is less than 12% by weight.
  • the invention has for its object to provide a method by which the oxidation resistance of simple MCrAlY layers as adhesive layers by increasing the Al content of the MCrAlY layer to improve without embrittlement occurs.
  • the structure of the aluminized MCrAlY layer consists of the inner, largely unchanged y / ⁇ mixed phase, a diffusion zone in which the A1 content increases to about 20% and an outer layer with a ⁇ -NiAl phase, which forms a fraction of has about 30% Al.
  • This outer layer represents the weak point of the layer system with regard to brittleness and crack sensitivity. It is removed according to the invention by the abrasive treatment down to the diffusion zone, whereby an Al content of 18 to less than 30% is set in the surface of the remaining layer. Removal of the outer layer may be accomplished by blasting with conventional media such as corundum, silicon carbide, reduced metal wires, and similar materials.
  • the oxidation resistance of this adhesive layer is improved.
  • the embrittlement on the surface of the aluminized layer caused by the alitization is avoided by the abrasive aftertreatment, or at least minimized.
  • the method according to the invention is applicable to all blades and, if appropriate, other turbine components subjected to hot gas, which are coated with thermal barrier coatings, in particular with thermal barrier coatings produced by the EB-PVD method.
  • the gas turbine blade 10 according to FIG. 2 is hollow and has cooling channels 11 in the interior.
  • the thermal barrier coating 2 consists of zirconium oxide, which is teilstablinstrument with about 7 wt .-%.
  • the adhesive layer 3 consists of a special alloy based on MCrAlY.
  • M stands for Ni or Co.
  • the adhesive layer is applied after the physical vapor deposition process using electron beam (EB-PVD method) or preferably by the low pressure plasma spray method (LPPS method).
  • Coating is accomplished by alitination, that is, a treatment in which a reactive Al-containing gas, which is typically an Al halide (AlX 2 ), causes inward diffusion of Al at higher temperature, associated with outward diffusion of Ni ,
  • a reactive Al-containing gas which is typically an Al halide (AlX 2 )
  • the outer make coat 4,2 is removed by blasting with hard particles, such as corundum, silicon carbide, metal wires or other known grinding or polishing down to the inner diffusion zone 4,1 of the diffusion layer 4.
  • hard particles such as corundum, silicon carbide, metal wires or other known grinding or polishing down to the inner diffusion zone 4,1 of the diffusion layer 4.
  • the abrasive treatment is driven so far that the surface of the remaining diffusion layer 4 has an Al content of more than 18% and less than 30%.
  • the blasted diffusion layer 4 is preferably subjected to fine flattening after the abrasive treatment.
  • the thermal barrier coating 2 is applied by a physical vapor deposition process by means of electron beams.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05018871A 2004-09-15 2005-08-31 Procédé pour le dépôt d'un revêtement protecteur Ceased EP1637622A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004045049A DE102004045049A1 (de) 2004-09-15 2004-09-15 Verfahren zum Aufbringen einer Schutzschicht

Publications (1)

Publication Number Publication Date
EP1637622A1 true EP1637622A1 (fr) 2006-03-22

Family

ID=35431301

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05018871A Ceased EP1637622A1 (fr) 2004-09-15 2005-08-31 Procédé pour le dépôt d'un revêtement protecteur

Country Status (5)

Country Link
US (1) US7736704B2 (fr)
EP (1) EP1637622A1 (fr)
JP (1) JP2006083469A (fr)
CA (1) CA2517298C (fr)
DE (1) DE102004045049A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
EP1840238A2 (fr) 2006-03-27 2007-10-03 Mitsubishi Heavy Industries, Ltd. Revêtement résistant à l'oxydation et son procédé de formation, revêtement de barrière thermique, élément résistant à la chaleur et turbine à gaz
WO2007054265A3 (fr) * 2005-11-08 2007-11-01 Man Turbo Ag Couche de protection calorifuge destinee a un composant situe dans la zone des gaz chauds d'une turbine a gaz
CN102352680A (zh) * 2011-11-04 2012-02-15 北京恒源景升生态科技有限责任公司 一种围护、保温一体墙板
DE102011103731A1 (de) 2011-05-31 2012-12-06 Man Diesel & Turbo Se Verfahren zum Aufbringen einer Schutzschicht, mit einer Schutzschicht beschichtetes Bauteil und Gasturbine mit einem solchen Bauteil

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FR2921937B1 (fr) * 2007-10-03 2009-12-04 Snecma Procede d'aluminisation en phase vapeur d'une piece metallique de turbomachine
JP5435395B2 (ja) * 2008-02-06 2014-03-05 日本電気硝子株式会社 ガラス物品の製造方法
DE102009022059A1 (de) * 2009-05-20 2010-11-25 Schott Solar Ag Strahlungsselektive Absorberbeschichtung und Absorberrohr mit strahlungsselektiver Absorberbeschichtung
US9175568B2 (en) 2010-06-22 2015-11-03 Honeywell International Inc. Methods for manufacturing turbine components
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US8807955B2 (en) * 2011-06-30 2014-08-19 United Technologies Corporation Abrasive airfoil tip
US8506836B2 (en) 2011-09-16 2013-08-13 Honeywell International Inc. Methods for manufacturing components from articles formed by additive-manufacturing processes
US8956700B2 (en) 2011-10-19 2015-02-17 General Electric Company Method for adhering a coating to a substrate structure
US9266170B2 (en) 2012-01-27 2016-02-23 Honeywell International Inc. Multi-material turbine components
US9120151B2 (en) 2012-08-01 2015-09-01 Honeywell International Inc. Methods for manufacturing titanium aluminide components from articles formed by consolidation processes
US9527262B2 (en) * 2012-09-28 2016-12-27 General Electric Company Layered arrangement, hot-gas path component, and process of producing a layered arrangement
RU2528695C1 (ru) * 2013-06-11 2014-09-20 Общество с ограниченной ответственностью "Новые углеволоконные материалы" Бестраншейный способ нанесения изоляции на внутреннюю поверхность трубопровода
US9587302B2 (en) * 2014-01-14 2017-03-07 Praxair S.T. Technology, Inc. Methods of applying chromium diffusion coatings onto selective regions of a component
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
WO2016133987A2 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Formation de passages de refroidissement dans des pièces coulées en superalliage d'une turbine à combustion
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
US8939706B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
WO2015130526A2 (fr) 2014-02-25 2015-09-03 Siemens Aktiengesellschaft Revêtement formant une barrière thermique pour pièce de turbine présentant des éléments de rainure usinés pour isoler les fissures
WO2016133581A1 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Carénage de turbine à couche abradable ayant des arêtes et rainures composites non fléchies à trois angles

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007054265A3 (fr) * 2005-11-08 2007-11-01 Man Turbo Ag Couche de protection calorifuge destinee a un composant situe dans la zone des gaz chauds d'une turbine a gaz
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
US9109279B2 (en) 2005-12-14 2015-08-18 Man Diesel & Turbo Se Method for coating a blade and blade of a gas turbine
EP1840238A2 (fr) 2006-03-27 2007-10-03 Mitsubishi Heavy Industries, Ltd. Revêtement résistant à l'oxydation et son procédé de formation, revêtement de barrière thermique, élément résistant à la chaleur et turbine à gaz
EP1840238A3 (fr) * 2006-03-27 2008-06-25 Mitsubishi Heavy Industries, Ltd. Revêtement résistant à l'oxydation et son procédé de formation, revêtement de barrière thermique, élément résistant à la chaleur et turbine à gaz
DE102011103731A1 (de) 2011-05-31 2012-12-06 Man Diesel & Turbo Se Verfahren zum Aufbringen einer Schutzschicht, mit einer Schutzschicht beschichtetes Bauteil und Gasturbine mit einem solchen Bauteil
WO2012163991A1 (fr) 2011-05-31 2012-12-06 Man Diesel & Turbo Se Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément
CN102352680A (zh) * 2011-11-04 2012-02-15 北京恒源景升生态科技有限责任公司 一种围护、保温一体墙板

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US20060177582A1 (en) 2006-08-10
DE102004045049A1 (de) 2006-03-16
CA2517298C (fr) 2010-06-29
CA2517298A1 (fr) 2006-03-15
US7736704B2 (en) 2010-06-15

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