EP2236651A1 - Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique - Google Patents

Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique Download PDF

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Publication number
EP2236651A1
EP2236651A1 EP09004849A EP09004849A EP2236651A1 EP 2236651 A1 EP2236651 A1 EP 2236651A1 EP 09004849 A EP09004849 A EP 09004849A EP 09004849 A EP09004849 A EP 09004849A EP 2236651 A1 EP2236651 A1 EP 2236651A1
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EP
European Patent Office
Prior art keywords
layer
bondcoat
thermal barrier
substrate
bondcoat layer
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Withdrawn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
EP09004849A
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German (de)
English (en)
Inventor
Xin-hai LI
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09004849A priority Critical patent/EP2236651A1/fr
Publication of EP2236651A1 publication Critical patent/EP2236651A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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

Definitions

  • the invention relates to a thermal barrier coating system for a high Titanium content superalloy substrate and a method for applying the substrate with the thermal barrier system.
  • An internal combustion engine in particular a gas turbine, is desirably operated at a combustion temperature which is close to the maximum allowable temperature of hot gas bearing internal pars of the gas turbine in order to obtain a high thermal efficiency.
  • parts down stream of a combustion are subject to high temperatures.
  • the hot gas bearing parts are provided with measures protecting the parts from excessive heat.
  • the ceramic thermal barrier coating with a metallic bondcoat layer which is located between the ceramic thermal barrier coating and the surface of the hot gas bearing part.
  • the hot gas bearing part is highly stressed and therefore manufactured with a high Titanium content superalloy, since the higher Titanium content results in a higher volume fraction of strengthening Gamma prime particles in the superalloy.
  • Titanium diffuses from the substrate through the metallic bondcoat layer and forms Titanium rich inclusions at the interface between the metallic bondcoat layer and the ceramic thermal barrier coating. These inclusions affect the bonding capability of the metallic bondcoat layer. Therefore, the lifespan of the ceramic thermal barrier coating is reduced and consequently the life cycle of the highly stressed parts is limited.
  • a remedy to overcome this problem is to reduce the Titanium content in the highly stressed parts.
  • this remedy can reduce the stability of these highly stressed parts.
  • the thermal barrier coating system for a high Titanium content superalloy substrate comprises a first bondcoat layer being applied to the substrate surface and adhering thereon, a second bondcoat layer being applied to the first bondcoat layer and adhering thereon, and a thermal barrier topcoat layer made of a ceramic material and being applied to the second bondcoat layer and adhering thereon in such a way that the surface of said substrate is protected from corrosion, oxidation and high temperature thermal exposure, wherein the first bondcoat layer and the second bondcoat layer are made of metal material alloys having similar compositions but different phase structures so that the combination of both bondcoat layers is to inhibit diffusion of Titanium from the substrate material into the second bondcoat layer surface beneath the topcoat layer and to keep bondcoat functions.
  • the first bondcoat layer and the second bondcoat layer provide a two-bondcoat layer to be arranged between the substrate and the thermal barrier topcoat layer.
  • Titanium diffusion from the substrate to the thermal barrier topcoat layer is reduced without deteriorating the bondcoat functions such as oxidation and corrosion protection as well as bonding the thermal barrier topcoat layer.
  • the combination of both layers is to reduce the Titanium diffusion and to keep bondcoat functions, so that an early failure of the ceramic thermal barrier layer is prevented.
  • first bondcoat layer and the second bondcoat layer comprise the same chemical elements.
  • first bondcoat layer has a Gamma prime phase structure and the second bondcoat layer preferably has a Beta phase structure.
  • the second bondcoat layer has a Gamma prime phase structure and the first bondcoat layer has a Beta phase structure.
  • thermal barrier topcoat layer is manufactured by an electronic beam physical vapour deposition method.
  • the method for applying the substrate with the thermal barrier system comprises the steps:
  • the first bondcoat layer and the second bondcoat layer comprise the same chemical elements.
  • the first bondcoat layer has preferably a Gamma prime phase structure and the second bondcoat layer has preferably a Beta phase structure.
  • the second bondcoat layer has preferably a Gamma prime phase structure and the first bondcoat layer has preferably a Beta phase structure.
  • FIG. 1 shows a cut out of a cross section of the inventive thermal barrier coating system.
  • a thermal barrier coating system 1 comprises a first bondcoat layer 3, a second bondcoat layer 4 and a thermal barrier topcoat layer 5.
  • the thermal barrier coating system 1 is applied to the surface of a substrate 2.
  • the substrate 2 is for example a hot gas bearing part of a gas turbine and is manufactured from a high Titanium content superalloy.
  • the first bondcoat layer 3 is applied to the substrate 2 surface and adheres thereon.
  • the second bondcoat layer 4 is applied and adheres thereon.
  • the thermal barrier topcoat layer 5 is made of a ceramic material and is applied to the second bondcoat 4 layer and adheres thereon. By means of the thermal barrier topcoat layer 5 the surface of the substrate 2 is protected from corrosion and oxidation caused by hot gas contacting the free surface of the thermal barrier topcoat layer 5.
  • the first bondcoat layer 3 and the second bondcoat layer 4 are made of metal material alloys having similar compositions but different phase structures, wherein the first bondcoat layer 3 and the second bondcoat layer 4 comprise the same chemical elements. Further, the first bondcoat layer 3 has a Gamma prime phase structure and the second bondcoat layer 4 has a Beta phase structure, or, alternatively, the second bondcoat layer 4 has a Gamma prime phase structure and the first bondcoat layer 3 has a Beta phase structure.
  • the thermal barrier topcoat layer 5 is applied to the second bondcoat layer 4 by an electronic beam physical vapour deposition method.
  • the first bondcoat layer 3 and the second bondcoat layer 4 provide a two-bondcoat layer which is arranged between the substrate 2 and the thermal barrier topcoat layer 5.
  • the Titanium diffusion from the substrate to the thermal barrier topcoat layer is reduced by means of the two-layer bondcoat layer, wherein the bondcoat functions, in particular the oxidation and the corrosion protection, as well as bonding the thermal barrier topcoat layer 5 are not deteriorated.
  • the bondcoat layer containing Gamma prime phase is to inhibit diffusion of Titanium from the substrate 2 material into the second bondcoat surface beneath the topcoat 5.
  • the bondcoat layer containing Beta phase is more active on corrosion and oxidation protection than the gamma prime one.
  • the second bondcoat layer 4 is to keep bonding functions in order to attach the thermal barrier coating system 1 to the substrate 1. Thus, an early failure of the ceramic thermal barrier layer 5 is prevented.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP09004849A 2009-04-01 2009-04-01 Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique Withdrawn EP2236651A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09004849A EP2236651A1 (fr) 2009-04-01 2009-04-01 Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09004849A EP2236651A1 (fr) 2009-04-01 2009-04-01 Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique

Publications (1)

Publication Number Publication Date
EP2236651A1 true EP2236651A1 (fr) 2010-10-06

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP09004849A Withdrawn EP2236651A1 (fr) 2009-04-01 2009-04-01 Système de revêtement de barrière thermique pour un substrat de superalliage à contenu élevé en titane et procédé pour appliquer le substrat avec le système de barrière thermique

Country Status (1)

Country Link
EP (1) EP2236651A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021146231A1 (fr) * 2020-01-17 2021-07-22 Lockheed Martin Corporation Système de protection thermique pour ailette légère de missile hypersonique

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260608A1 (fr) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Procédé pour la déposition d'un couche de liaison à base de MCrAlY
EP1327702A1 (fr) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Revêtement de liaison de type MCrAlY et procédé de depôt de ce revêtement de liason de type MCrAlY
EP1491650A1 (fr) * 2003-06-26 2004-12-29 ALSTOM Technology Ltd Méthode d'application d'un système de couches
EP1767667A2 (fr) * 2005-09-26 2007-03-28 General Electric Company Revêtement à base de gamma-prime Nickel aluminiure
US20070190354A1 (en) * 2006-02-13 2007-08-16 Taylor Thomas A Low thermal expansion bondcoats for thermal barrier coatings

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260608A1 (fr) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Procédé pour la déposition d'un couche de liaison à base de MCrAlY
EP1327702A1 (fr) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Revêtement de liaison de type MCrAlY et procédé de depôt de ce revêtement de liason de type MCrAlY
EP1491650A1 (fr) * 2003-06-26 2004-12-29 ALSTOM Technology Ltd Méthode d'application d'un système de couches
EP1767667A2 (fr) * 2005-09-26 2007-03-28 General Electric Company Revêtement à base de gamma-prime Nickel aluminiure
US20070190354A1 (en) * 2006-02-13 2007-08-16 Taylor Thomas A Low thermal expansion bondcoats for thermal barrier coatings

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021146231A1 (fr) * 2020-01-17 2021-07-22 Lockheed Martin Corporation Système de protection thermique pour ailette légère de missile hypersonique
US11306387B2 (en) 2020-01-17 2022-04-19 Lockheed Martin Corporation Thermal protection system for lightweight hypersonic missile fin
GB2606327A (en) * 2020-01-17 2022-11-02 Lockheed Corp Thermal protection system for lightweight hypersonic missile fin
GB2606327B (en) * 2020-01-17 2023-05-10 Lockheed Corp Thermal protection system for lightweight hypersonic missile fin

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