WO2004007787A1 - Systeme stratifie - Google Patents

Systeme stratifie Download PDF

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Publication number
WO2004007787A1
WO2004007787A1 PCT/EP2003/005978 EP0305978W WO2004007787A1 WO 2004007787 A1 WO2004007787 A1 WO 2004007787A1 EP 0305978 W EP0305978 W EP 0305978W WO 2004007787 A1 WO2004007787 A1 WO 2004007787A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
thermal insulation
insulation layer
intermediate layer
layer system
Prior art date
Application number
PCT/EP2003/005978
Other languages
German (de)
English (en)
Inventor
Jens Birkner
Werner Stamm
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2004007787A1 publication Critical patent/WO2004007787A1/fr

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Classifications

    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • C23C28/34—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
    • 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 a layer system according to the preamble of claim 1.
  • thermal barrier coatings have been developed that are applied to thermally stressed components, for example made of superalloys, that cannot withstand the high inlet temperatures in the long run.
  • the ceramic thermal barrier coating offers the advantage of a high temperature / corrosion resistance due to its ceramic properties
  • the metallic substrate offers the advantage of the good mechanical properties in this composite or layer system.
  • an adhesion promoting or corrosion protective layer of the composition MCrAlY as the main component is applied between the substrate and the ceramic thermal barrier layer, where M means that a metal from the group
  • Nickel, chrome or iron is used.
  • composition of these MCrAlY layers can vary.
  • thermal barrier coating on the corrosion protection layer or MCrAlY layer does not adhere well and / or flake off during application or during operation need to be re-injected by operating personnel not melting.
  • the object is achieved by a layer system according to claim 1.
  • FIG. 1 shows a first layer system according to the invention
  • FIG. 2 shows a second layer system according to the invention with a concentration gradient
  • FIG. 3 shows a further layer system according to the invention
  • Figure 4 shows an application example for a layer system according to the invention.
  • FIG. 1 shows a layer system 1 according to the invention.
  • the layer system 1 has a substrate 4.
  • the substrate 4 is, for example, a nickel or cobalt-based superalloy.
  • At least one intermediate layer 7 is present on the substrate 4, which serves as a corrosion, oxidation or adhesion-promoting layer and consists of an intermediate layer material.
  • a single intermediate layer 7 is used here. This is, for example, a so-called MCrAlY layer, where M is an element from the group iron, cobalt or nickel.
  • a thermal insulation layer 10 is applied to the outermost interface of the intermediate layer 7.
  • the thermal barrier coating 10 is, for example, ceramic and consists, for example, of partially or fully stabilized zirconium oxide with up to 8% yttrium oxide or other rare earth oxides.
  • the thermal insulation layer 10 contains a total of 5-60 vol% of the material of the intermediate layer 7, which ensures good adhesion of the thermal insulation layer 10 to the intermediate layer 7.
  • the heat insulation layer 10 begins at the interface at which the material of the heat insulation layer 10 forms the matrix.
  • the layers 7, 10 can be applied by various types of plasma spraying, in particular by atmospheric plasma spraying (APS), or by cold gas spraying.
  • APS atmospheric plasma spraying
  • cold gas spraying the particles of the material of the layers 7, 10 to be applied, like the substrate 4, have a low temperature during manufacture, i.e. they do not form plasma.
  • the applied particles are applied to the substrate 4 at high speeds of up to 1000 m / s, as a result of which they bond to one another.
  • the addition of a metallic component is necessary.
  • This green body layer produced in this way can also be sintered or heat-treated in order to enable improved resistance to external mechanical stress.
  • FIG. 2 shows a further layer system 1 according to the invention, in which the concentration of the intermediate layer material 7 in the thermal insulation layer 10 decreases continuously, for example, starting from an interface 8 between the intermediate layer 7 and the thermal insulation layer 10 up to an outer surface 11 of the thermal insulation layer 10.
  • the proportion of the intermediate layer material 7 can also be constant at 0 vol%.
  • the heat insulation layer 10 begins at the interface at which the material of the heat insulation layer 10 forms the matrix.
  • the gradient of the material composition in the thermal insulation layer can be created in various ways.
  • an initial mixture of the different materials of the layers 7, 10 continuously and more or more material of the thermal insulation layer 10 and / or continuously or discontinuously less material of the intermediate layer 7 is added to the plasma jet, which directs the particles onto the substrate 4 added.
  • FIG. 3 shows a further exemplary embodiment of a layer system 1 according to the invention.
  • the layer system 1 according to the invention is constructed, for example, according to FIG. 1 or 2, a first partial layer 13 of the thermal insulation layer 10 being applied by cold gas spraying.
  • a second partial layer 16 of the thermal insulation layer 10 of the same material or with a different composition is applied to this cold gas-sprayed partial layer 13 of the thermal insulation layer 10 by means of atmospheric plasma spraying or by means of other types of plasma spraying (in a vacuum, ..).
  • the concentration of the metallic material in the thermal insulation layer 10 is to decrease towards the outside, during the application with the increasing coating time, to continuously increase the temperature of the particle beam until, for example, a plasma is generated.
  • the arrangement of intermediate layer material 7 in the thermal insulation layer 10 aligns the expansion coefficients of the layers 7, 10 with one another, so that there is little or no thermal stress between the layers 7, 10 when heated, which prevents chipping.
  • porous layers 7, 10 are also produced in order to achieve an elongation tolerance because one
  • Porosity from 5 vol% can influence the expansion coefficient and the E-module.
  • FIG. 4 shows a rotor blade in a perspective view as an example of a layer system 1, which extends along a longitudinal axis 19.
  • the rotor blade 1 has, in succession along the longitudinal axis 19, a fastening area 22, an adjoining blade platform 25 and an airfoil area 28.
  • a blade root 31 is formed, which serves to fasten the rotor blade 1 to a shaft of a turbomachine, also not shown.
  • the turbine blade 1 with its blade area 28 is exposed to high temperatures within a gas turbine and is therefore protected against oxidation and heat by a layer system 1 according to the invention.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

Les systèmes stratifiés connus présentent fréquemment une mauvaise adhérence entre les différentes couches, ce qui entraîne une désolidarisation des couches et une dégradation du substrat sous-jacent. Le système stratifié (1) selon l'invention comporte une couche thermoisolante (10) formée au moins en partie par le matériau de la couche intermédiaire (7) sous-jacente.
PCT/EP2003/005978 2002-07-17 2003-06-06 Systeme stratifie WO2004007787A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP02015955A EP1382707A1 (fr) 2002-07-17 2002-07-17 Systeme stratifie
EP02015955.4 2002-07-17

Publications (1)

Publication Number Publication Date
WO2004007787A1 true WO2004007787A1 (fr) 2004-01-22

Family

ID=29762646

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2003/005978 WO2004007787A1 (fr) 2002-07-17 2003-06-06 Systeme stratifie

Country Status (2)

Country Link
EP (1) EP1382707A1 (fr)
WO (1) WO2004007787A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2778257A3 (fr) * 2013-03-13 2014-12-24 General Electric Company Procédé de fabrication de revêtements de barrière thermique
US9347126B2 (en) 2012-01-20 2016-05-24 General Electric Company Process of fabricating thermal barrier coatings

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050220995A1 (en) * 2004-04-06 2005-10-06 Yiping Hu Cold gas-dynamic spraying of wear resistant alloys on turbine blades
US7378132B2 (en) * 2004-12-14 2008-05-27 Honeywell International, Inc. Method for applying environmental-resistant MCrAlY coatings on gas turbine components
US8349396B2 (en) * 2005-04-14 2013-01-08 United Technologies Corporation Method and system for creating functionally graded materials using cold spray
DE102008051921B4 (de) * 2007-11-02 2023-02-16 Gfe Fremat Gmbh Schichtsystem und Verfahren zum Erstellen eines Kontaktelements für ein Schichtsystem
US8147982B2 (en) * 2007-12-19 2012-04-03 United Technologies Corporation Porous protective coating for turbine engine components
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
DE102009049707A1 (de) * 2009-10-17 2011-07-28 MTU Aero Engines GmbH, 80995 Verfahren zur Herstellung einer Lauf- oder Statorschaufel und eine derartige Schaufel
EP2381005A1 (fr) * 2010-04-22 2011-10-26 Siemens Aktiengesellschaft Système de couche pour composants de turbine
US20130186304A1 (en) * 2012-01-20 2013-07-25 General Electric Company Process of fabricating a thermal barrier coating and an article having a cold sprayed thermal barrier coating
EP2781622A1 (fr) * 2013-03-21 2014-09-24 Siemens Aktiengesellschaft Procédé génératif, notamment de fabrication d'un revêtement, dispositif d'exécution du procédé, revêtement et procédé de fabrication de composant et composant
DE102014220359A1 (de) * 2014-10-08 2016-04-14 Siemens Aktiengesellschaft Doppellagige Zirkonoxidschicht mit hochreinem Anteil
US20180320270A1 (en) * 2017-05-08 2018-11-08 United Technologies Corporation Functionally graded environmental barrier coating
DE102017223879A1 (de) * 2017-12-29 2019-07-04 Siemens Aktiengesellschaft Keramisches Material, Verfahren zur Herstellung, Schicht und Schichtsystem

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248940A (en) * 1977-06-30 1981-02-03 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
EP0185603A1 (fr) * 1984-11-28 1986-06-25 United Technologies Corporation Amélioration de la résistance à l'usure d'un joint d'étanchéité d'une turbine constitué d'un matériau métal céramique
EP0217991A1 (fr) * 1985-10-04 1987-04-15 Repco Limited Revêtement céramique
US4751099A (en) * 1985-12-28 1988-06-14 National Aerospace Laboratories of Science and Technology Agency Method of producing a functionally gradient material
DE10045783A1 (de) * 2000-05-08 2001-11-22 Ami Doduco Gmbh Verfahren zum Herstellen von Werkstücken, welche der Leitung von elektrischem Strom dienen und mit einem überwiegend metallischen Material beschichtet sind

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248940A (en) * 1977-06-30 1981-02-03 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
EP0185603A1 (fr) * 1984-11-28 1986-06-25 United Technologies Corporation Amélioration de la résistance à l'usure d'un joint d'étanchéité d'une turbine constitué d'un matériau métal céramique
EP0217991A1 (fr) * 1985-10-04 1987-04-15 Repco Limited Revêtement céramique
US4751099A (en) * 1985-12-28 1988-06-14 National Aerospace Laboratories of Science and Technology Agency Method of producing a functionally gradient material
DE10045783A1 (de) * 2000-05-08 2001-11-22 Ami Doduco Gmbh Verfahren zum Herstellen von Werkstücken, welche der Leitung von elektrischem Strom dienen und mit einem überwiegend metallischen Material beschichtet sind

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9347126B2 (en) 2012-01-20 2016-05-24 General Electric Company Process of fabricating thermal barrier coatings
EP2778257A3 (fr) * 2013-03-13 2014-12-24 General Electric Company Procédé de fabrication de revêtements de barrière thermique

Also Published As

Publication number Publication date
EP1382707A1 (fr) 2004-01-21

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