EP1913176A1 - Systeme de couche calorifuge - Google Patents

Systeme de couche calorifuge

Info

Publication number
EP1913176A1
EP1913176A1 EP06775798A EP06775798A EP1913176A1 EP 1913176 A1 EP1913176 A1 EP 1913176A1 EP 06775798 A EP06775798 A EP 06775798A EP 06775798 A EP06775798 A EP 06775798A EP 1913176 A1 EP1913176 A1 EP 1913176A1
Authority
EP
European Patent Office
Prior art keywords
barrier coating
thermal barrier
coating system
base material
thermal insulation
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Withdrawn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
EP06775798A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1913176A1 publication Critical patent/EP1913176A1/fr
Withdrawn legal-status Critical Current

Links

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
    • 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
    • C23C28/04—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 only coatings of inorganic non-metallic material
    • C23C28/042—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 only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • 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
    • C23C28/04—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 only coatings of inorganic non-metallic material
    • C23C28/044—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 only coatings of inorganic non-metallic material coatings specially adapted for cutting tools or wear applications
    • 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
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
    • C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a thermal barrier coating system for components, in particular for metallic components of a gas turbine such as an aircraft engine, according to the preamble of claim 1. Furthermore, the invention relates to a component with a thermal barrier coating system according to the preamble of claim 11.
  • DE 100 08 861 A1 shows a thermal barrier coating system for a metallic component, the thermal barrier coating system consisting of two layers, namely an inner contact layer and an outer cover layer.
  • the inner contact layer is located between an adhesion-promoting layer and the outer cover layer, with the adhesion-promoting layer being applied to the component.
  • the inner contact layer of the thermal barrier coating system consists entirely of predominantly yttria (Y 2 O 3 ) partially stabilized zirconia or of a glass-metal composite, the outer cover consists of fully stabilized, cubic zirconia.
  • DE 197 43 579 C2 discloses a thermal barrier coating system of a ceramic thermal insulation base material, wherein the thermal insulation base material is applied by thermal spraying on a component surface of a metallic component.
  • DE 198 07 163 C1 discloses a special thermal insulation base material for a thermal barrier coating system.
  • the known from the prior art thermal barrier coating systems which are made of the known thermal insulation materials, have a thermal conductivity in the order of 1 to 2 W / Km. As a result, the maximum thermal insulation of the known from the prior art thermal barrier coating systems is defined.
  • the present invention is based on the problem of creating a novel thermal barrier coating system for components, in particular for metallic components of a gas turbine such as an aircraft engine, and a corresponding component.
  • This problem is solved by a réelledäiran Anlagensystem according to claim 1.
  • at least one airgel is embedded or embedded in the thermal insulation base material.
  • a thermal barrier coating system made of a thermal insulation base material wherein at least one airgel is embedded or embedded in the thermal insulation base material.
  • Aerogels are extremely porous and very light materials that can be made from virtually any metal oxide, metal oxide or other material.
  • the incorporation or embedding of at least one airgel in the thermal insulation base material of a thermal barrier coating system the thermal conductivity can be greatly reduced, preferably to a magnitude between 0.01 and 0.02 W / Km.
  • the thermal barrier coating system according to the invention therefore, a significantly higher thermal insulation can be realized compared with thermal barrier coating systems known from the prior art.
  • the thermal barrier coating system according to the invention Due to the fact that the aerogels are embedded or incorporated in a thermal insulation base material, the thermal barrier coating system according to the invention has an abrasion resistance that is comparable to the thermal barrier coating systems known from the prior art.
  • the or each airgel embedded or embedded in the thermal insulation base material is preferably designed as an oxidic airgel and formed from a material corresponding to the thermal insulation base material.
  • the thermal barrier coating system is designed as a deposit system, wherein the single layer thereof is formed from the thermal insulation base material and the or each embedded in the thermal insulation material airgel.
  • the thermal barrier coating system is designed as a multi-layer system, wherein between two layers, which are formed exclusively of the thermal insulation base material, respectively a position is positioned, which is formed from the thermal insulation base material and the or each embedded in the same airgel.
  • FIG. 1 shows a highly schematic cross section through a thermal barrier coating system according to a first embodiment of the invention.
  • FIG. 2 shows a highly schematic cross section through a thermal barrier coating system according to a second embodiment of the invention.
  • Fig. 3 is a highly schematic cross section through a thermal barrier coating system according to a third embodiment of the invention
  • Fig. 1 shows a first embodiment of the present invention in a highly schematic representation, wherein on a component 10, an inventive thermal barrier coating system 11 is applied.
  • the component 10 is preferably a metallic component of a gas turbine, in particular a metallic component of an aircraft engine.
  • the thermal barrier coating system 11 On a surface 12 of the component 10, the thermal barrier coating system 11 according to the invention is applied, wherein the thermal barrier coating system 11 of the embodiment of FIG. 1 is designed as a deposit system. Accordingly, the thermal barrier coating system 11 of FIG. 1 has a single layer, wherein the layer is formed of a thermal insulation base material and of at least one aeroderge embedded or embedded in the thermal insulation base material.
  • the thermal insulation base material of the thermal barrier coating system 11 can be all thermal insulation base materials known from gas turbine construction or aircraft engine construction, such as e.g. aluminum oxide, yttrium-stabilized zirconium oxide or else lanthanum hexaaluminate.
  • At least one airgel, preferably an oxidic airgel, is embedded in such a thermal insulation base material.
  • the or each airgel is formed of a material which is adapted to the thermal insulation base material.
  • the thermal barrier base material is yttrium stabilized zirconia
  • the aerogels may be formed of zirconia.
  • the thermal barrier base material is lanthanum hexaaluminate
  • the airgel is preferably formed from lanthanum hexaaluminate.
  • aerogels are extremely porous and very light materials. Aerogels can almost be made of any metal oxide or of metal oxide mixtures or of other materials. Aerogels have a pore volume between 85% and 99%.
  • Such aerogels are preferably prepared by dissolving a starting material, for example a metal oxide, in a solvent, followed by hydrolysis by the addition of water. Then, aggregation of hydrolyzed monomers into colloidal particles takes place, followed by gelation in which the colloidal particles form a three-dimensional network. After gelation, drying is carried out by removing the liquid phases, the result being an airgel.
  • the thermal insulation layer system 13 of the embodiment of FIG. 2 is designed as a multi-layer system and thus has several layers.
  • First layers 14 are formed exclusively from the thermal insulation base material
  • second layers 15 consist of the thermal insulation base material and at least one airgel embedded in the thermal insulation base material.
  • a layer 15 is arranged from the Warmedammgroundtechnikstoff with the same embedded airgel.
  • FIG. 3 A further exemplary embodiment of an inventive thermal insulation layer system 16 is shown in FIG. 3, wherein the thermal insulation layer system 16 of FIG. 3 differs from the thermal insulation layer system 13 of FIG. 2 only in that the outer layer 15, which consists of the thermal insulation base material and the m a layer 17 of the thermal dam base material is applied.
  • the thermal insulation layer system 16 is accordingly closed to the outside from a layer 17 of the thermal insulation base material.
  • the outer layer 17 the abrasion resistance of the thermal insulation layer system 16 can be increased.
  • thermal insulation layer systems For the production of erfmdungsge18 thermal insulation layer systems is proceeded so that a powder of thermal insulation base material with particles be mixed from airgel, in which case this mixture is used to the thermal barrier coating system of Fig. 1 or the layers 15 of the thermal barrier coating systems 13 and 16 of the embodiments of FIGS. 2 and 3 via a slip process or sol-gel process or thermal spraying on to apply the component 10.
  • an adhesion-promoting layer can be arranged in each case.
  • Such adhesion-promoting layers are preferably formed from a MCrAlY material.
  • thermal insulation material of the thermal barrier coating systems according to the invention also several different aerogels can be embedded or embedded.
  • the thermal barrier coating system according to the invention is preferably used in metallic components of a gas turbine, in particular an aircraft engine.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L'invention concerne un système de couche calorifuge (11) pour des éléments (10), notamment des éléments métalliques de turbine à gaz, comme un groupe motopropulseur, le système de couche calorifuge (11) étant composé d'un matériau de base calorifuge. Selon l'invention, au moins un aérogel est intercalé ou incorporé dans le matériau de base calorifuge.
EP06775798A 2005-08-09 2006-08-04 Systeme de couche calorifuge Withdrawn EP1913176A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005037448A DE102005037448A1 (de) 2005-08-09 2005-08-09 Wärmedämmschichtsystem
PCT/DE2006/001359 WO2007016906A1 (fr) 2005-08-09 2006-08-04 Systeme de couche calorifuge

Publications (1)

Publication Number Publication Date
EP1913176A1 true EP1913176A1 (fr) 2008-04-23

Family

ID=37114531

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06775798A Withdrawn EP1913176A1 (fr) 2005-08-09 2006-08-04 Systeme de couche calorifuge

Country Status (4)

Country Link
US (1) US20090233111A1 (fr)
EP (1) EP1913176A1 (fr)
DE (1) DE102005037448A1 (fr)
WO (1) WO2007016906A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006027728A1 (de) 2006-06-16 2007-12-20 Mtu Aero Engines Gmbh Wärmedämmschicht
US20080241490A1 (en) * 2007-04-02 2008-10-02 Physical Sciences, Inc. Sprayable Aerogel Insulation
DE102008002514A1 (de) 2008-06-18 2009-12-24 Federal-Mogul Nürnberg GmbH Kolben, Zylinderlaufbuchse oder sonstiges, den Brennraum eines Verbrennungsmotors begrenzendes Motorbauteil und Verfahren zur Herstellung derselben
DE102012101032A1 (de) * 2012-02-08 2013-08-08 Eads Deutschland Gmbh Kreiskolbenmotor und Verfahren zum Herstellen eines Kreiskolbenmotors
DE102013217627A1 (de) * 2013-09-04 2015-03-05 MTU Aero Engines AG Wärmedämmschichtsystem mit Korrosions- und Erosionsschutz
DE102014213911A1 (de) * 2014-07-17 2016-01-21 MTU Aero Engines AG Aerogel-Auskleidungselement für Strömungsmaschinen
KR101724487B1 (ko) * 2015-12-15 2017-04-07 현대자동차 주식회사 다공성 단열 코팅층 및 그 제조방법

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DE3108816A1 (de) * 1981-03-09 1982-09-30 Grünzweig + Hartmann und Glasfaser AG, 6700 Ludwigshafen Waermedaemmender pressstoff auf der basis von aus der flammenhydrolyse gewonnenem mikroporoesem oxidaerogel, sowie verfahren zu seiner herstellung, eine daraus hergestellte folie und ein damit hergestelltes kaschiertes waermedaemmelement
AU7720596A (en) * 1995-11-09 1997-05-29 Aspen Systems, Inc. Flexible aerogel superinsulation and its manufacture
DE19743579C2 (de) * 1997-10-02 2001-08-16 Mtu Aero Engines Gmbh Wärmedämmschicht und Verfahren zu ihrer Herstellung
DE19807163C1 (de) * 1998-02-20 1999-10-28 Rainer Gadow Wärmedämmaterial und Verfahren zum Herstellen eines solchen
DE10008861A1 (de) * 2000-02-25 2001-09-06 Forschungszentrum Juelich Gmbh Kombinierte Wärmedämmschichtsysteme
DE10122545A1 (de) * 2001-05-09 2002-11-28 Deutsch Zentr Luft & Raumfahrt Wärmedämmmaterial mit im wesentlichen magnetoplumbitischer Kristallstruktur
WO2003064025A1 (fr) * 2002-01-29 2003-08-07 Cabot Corporation Aerogel composite isolant thermoresistant et procede de preparation, composition de liant d'aerogel et procede de preparation
WO2007011750A2 (fr) * 2005-07-15 2007-01-25 Aspen Aerogels, Inc. Composites aerogel renforces et procedes de fabrication

Non-Patent Citations (1)

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See references of WO2007016906A1 *

Also Published As

Publication number Publication date
US20090233111A1 (en) 2009-09-17
DE102005037448A1 (de) 2007-02-15
WO2007016906A1 (fr) 2007-02-15

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