DE102016204627A1 - Process for machining a component provided with a thermal barrier coating - Google Patents
Process for machining a component provided with a thermal barrier coating Download PDFInfo
- Publication number
- DE102016204627A1 DE102016204627A1 DE102016204627.6A DE102016204627A DE102016204627A1 DE 102016204627 A1 DE102016204627 A1 DE 102016204627A1 DE 102016204627 A DE102016204627 A DE 102016204627A DE 102016204627 A1 DE102016204627 A1 DE 102016204627A1
- Authority
- DE
- Germany
- Prior art keywords
- protective layer
- barrier coating
- thermal barrier
- component
- thickness
- 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.)
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Classifications
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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
- C23C24/00—Coating starting from inorganic powder
-
- 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
-
- 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
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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
- C23C28/34—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
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- 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
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- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
-
- 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
Abstract
Die Erfindung betrifft ein Verfahren zur Bearbeitung eines Bauteils (1), das mit einer Wärmedämmschicht (4) versehen ist, wobei zumindest auf Bereichen der Wärmedämmschicht (4) eine nichtmetallische, wenigstens einen oxidationsfähigen Bestandteil aufweisende Schutzschicht (5) aufgetragen wird.The invention relates to a method for processing a component (1) which is provided with a thermal barrier coating (4), wherein a non-metallic, at least one oxidation-resistant constituent protective layer (5) is applied at least on areas of the thermal barrier coating (4).
Description
Die vorliegende Erfindung betrifft ein Verfahren zur Bearbeitung eines Bauteils, das mit einer Wärmedämmschicht versehen ist. The present invention relates to a method for processing a component which is provided with a thermal barrier coating.
Bauteile, deren Substrat durch eine auf diesem aufgetragene Wärmedämmschicht vor den negativen Einflüssen hoher Temperaturen geschützt ist, sind im Stand der Technik in unterschiedlichsten Ausgestaltungen bekannt, beispielsweise in Form von Heißgaskomponenten einer Gasturbine oder dergleichen. Das Substrat solcher Bauteile wird meist durch eine Superlegierung gebildet, insbesondere durch eine solche auf Nickel-, Cobalt- oder Eisenbasis. Die Wärmedämmschicht besteht meist aus keramischen Materialien, wie beispielsweise aus teilstabilisiertem Zirkon oder Gadoliniumzirkonat. Zur Verbesserung der Haftung zwischen dem Substrat und der Wärmedämmschicht kann zwischen diesen eine Haftschicht vorgesehen werden, beispielsweise aus MCrAlX, wobei M für Eisen, Cobalt und/oder Nickel und X für Yttrium oder andere Seltenerdmetalle steht. Components whose substrate is protected from the negative influences of high temperatures by a thermal barrier coating applied thereto are known in the prior art in a wide variety of configurations, for example in the form of hot gas components of a gas turbine or the like. The substrate of such components is usually formed by a superalloy, in particular by one based on nickel, cobalt or iron. The thermal barrier coating is usually made of ceramic materials, such as partially stabilized zirconium or gadolinium zirconate. To improve the adhesion between the substrate and the thermal barrier coating, an adhesive layer may be provided between them, for example MCrAlX, where M is iron, cobalt and / or nickel and X is yttrium or other rare earth metals.
Während des Betriebs von Heißgaskomponenten lagern sich auf der Wärmedämmschicht aufgrund von in der Umgebungsluft enthaltenen Substanzen Verunreinigungen ab, die bei hohen Temperaturen auch als CMAS bezeichnete eutektische Legierungen mit geringem Schmelzpunkt bilden können, die Calciumoxid, Magnesiumoxid, Aluminiumoxid und Siliziumoxid enthalten. Oberhalb der eutektischen Temperatur können die CMAS-Ablagerungen schmelzen und die Wärmedämmschicht infiltrieren, was häufig zu Rissbildungen oder gar zum Abplatzen der Wärmedämmschicht führt. During operation of hot gas components, contaminants are deposited on the thermal barrier coating due to substances in the ambient air which, at high temperatures, may also form low melting point eutectic alloys called CMAS containing calcium oxide, magnesium oxide, aluminum oxide and silicon oxide. Above the eutectic temperature, the CMAS deposits can melt and infiltrate the thermal barrier coating, often causing cracking or even spalling of the thermal barrier coating.
Ausgehend von diesem Stand der Technik ist es eine Aufgabe der vorliegenden Erfindung, ein Verfahren der eingangs genannten Art bereitzustellen, mit dem die negative Beeinflussung der Wärmedämmschicht durch CMAS-Ablagerungen verringert werden kann. Based on this prior art, it is an object of the present invention to provide a method of the type mentioned, with which the negative influence of the thermal barrier coating by CMAS deposits can be reduced.
Zur Lösung dieser Aufgabe schafft die vorliegende Erfindung ein Verfahren der eingangs genannten Art, das dadurch gekennzeichnet ist, dass zumindest auf Bereichen der Wärmedämmschicht eine nichtmetallische, wenigstens einen oxidationsfähigen Bestandteil aufweisende Schutzschicht aufgetragen wird. Spätestens während der bestimmungsgemäßen Verwendung des Bauteils in Umgebungsluftatmosphäre bei hohen Temperaturen oxidiert der wenigstens eine oxidationsfähige Bestandteil der Schutzschicht. Die gebildeten Oxide reagieren wiederum mit sich ausbildenden CMAS-Ablagerungen derart, dass der Schmelzpunkt der CMAS-Ablagerungen heraufgesetzt wird, wodurch die Infiltration und die Reaktion der CMAS-Ablagerungen in bzw. mit der Wärmedämmschicht verringert werden. Auf diese Weise werden Rissbildungen und Abplatzungen der Wärmedämmschicht zumindest reduziert, was mit einer Verlängerung der Lebensdauer des Bauteils einhergeht. To achieve this object, the present invention provides a method of the type mentioned, which is characterized in that at least on areas of the thermal barrier coating, a non-metallic, at least one oxidation-capable component having protective layer is applied. At the latest during the intended use of the component in an ambient air atmosphere at high temperatures, the oxidized at least one oxidizable component of the protective layer. The formed oxides, in turn, react with CMAS deposits that form to increase the melting point of the CMAS deposits, thereby reducing infiltration and the reaction of the CMAS deposits in the thermal barrier coating. In this way, cracking and flaking of the thermal barrier coating are at least reduced, which is associated with an extension of the life of the component.
Gemäß einer Ausgestaltung der vorliegenden Erfindung weist die Schutzschicht Aluminiumphosphat auf. Die Verwendung von Aluminiumphosphat hat sich als besonders effektiv und unproblematisch erwiesen. According to one embodiment of the present invention, the protective layer comprises aluminum phosphate. The use of aluminum phosphate has proven to be particularly effective and unproblematic.
Bevorzugt weist die Schutzschicht zumindest ein Element ausgewählt aus der Gruppe Magnesium (Mg), Zirkon (Zr), Titan (Ti), Tantal (Ta), Niob (Nb), Hafnium (Hf), Silizium (Si), Bor (B), Germanium (Ge) und /oder Gallium (Ga) in nichtmetallischer Bindung auf. The protective layer preferably comprises at least one element selected from the group magnesium (Mg), zirconium (Zr), titanium (Ti), tantalum (Ta), niobium (Nb), hafnium (Hf), silicon (Si), boron (B) , Germanium (Ge) and / or gallium (Ga) in non-metallic bond.
Gemäß einer Ausgestaltung des erfindungsgemäßen Verfahrens wird die Schutzschicht in einer Dicke aufgetragen, die maximal der 0,2-fachen Dicke der Wärmedämmschicht entspricht. According to one embodiment of the method according to the invention, the protective layer is applied in a thickness which corresponds at most to 0.2 times the thickness of the thermal barrier coating.
Vorteilhaft wird die Schutzschicht in einer Dicke von maximal 20µm aufgetragen, wodurch ein hinreichender Schutz vor den negativen Einflüssen von CMAS-Ablagerungen gewährleistet wird. Dicken über diese Obergrenze hinaus scheinen keine zusätzliche positive Wirkung zu entfalten. Advantageously, the protective layer is applied in a thickness of a maximum of 20 microns, whereby a sufficient protection against the negative effects of CMAS deposits is ensured. Thicknesses beyond this upper limit do not appear to have an additional positive effect.
Gemäß einer Ausgestaltung der vorliegenden Erfindung wird die Schutzschicht durch einen Schlicker, Aufdampfen, Aufsprühen oder unter Verwendung eines Pinsels aufgetragen. According to one embodiment of the present invention, the protective layer is applied by a slurry, vapor deposition, spraying or using a brush.
Gemäß einer Variante des erfindungsgemäßen Verfahrens wird die Schutzschicht nach ihrem Auftrag in einem weiteren Schritt oxidiert. Dies hat den Vorteil, dass die schützende Oxidschicht bereits zu Beginn der bestimmungsgemäßen Verwendung des Bauteils vorhanden ist und nicht erst ausgebildet werden muss. Die Oxidation kann beispielsweise durch Erwärmen des Bauteils in einer oxidationsfördernden Umgebung wie Luft oder dergleichen erfolgen. Ebenso kann die Oxidation auch elektrochemisch hervorgerufen werden. According to a variant of the method according to the invention, the protective layer is oxidized after its application in a further step. This has the advantage that the protective oxide layer is already present at the beginning of the intended use of the component and does not have to be formed first. The oxidation can be carried out, for example, by heating the component in an oxidation-promoting environment such as air or the like. Likewise, the oxidation can also be caused electrochemically.
Vorteilhaft ist das Bauteil eine Heißgaskomponente einer Gasturbine, wie beispielsweise eine Leit- oder Laufschaufel. Advantageously, the component is a hot gas component of a gas turbine, such as a guide or blade.
Gemäß der vorliegenden Erfindung kann das erfindungsgemäße Verfahren im Rahmen einer Neuherstellung eines Bauteils oder an einem bereits existierenden Bauteil durchgeführt werden, wie beispielsweise im Rahmen von Reparaturarbeiten. According to the present invention, the method according to the invention may be carried out as part of a new production of a component or on an already existing component, such as in the context of repair work.
Weitere Merkmale und Vorteile der vorliegenden Erfindung werden anhand der nachfolgenden Beschreibung einer Ausführungsform des erfindungsgemäßen Verfahrens unter Bezugnahme auf die beiliegende Zeichnung deutlich, die eine Querschnittansicht eines Bauteils zeigt. Further features and advantages of the present invention will become apparent from the following description of an embodiment of the method according to the invention with reference to the accompanying drawing, which shows a cross-sectional view of a component.
Das Bauteil
Gemäß dem erfindungsgemäßen Verfahren wird an der Außenseite der Wärmedämmschicht
Gemäß eine ersten Variante des erfindungsgemäßen Verfahrens erfolgt eine Oxidation der Schutzschicht
Die gebildeten Oxide reagieren während des bestimmungsgemäßen Einsatzes des Bauteils
Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen. Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.
Claims (9)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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DE102016204627.6A DE102016204627A1 (en) | 2016-03-21 | 2016-03-21 | Process for machining a component provided with a thermal barrier coating |
PCT/EP2017/054693 WO2017162411A1 (en) | 2016-03-21 | 2017-03-01 | Method for treating a component which is provided with a thermal barrier coating |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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DE102016204627.6A DE102016204627A1 (en) | 2016-03-21 | 2016-03-21 | Process for machining a component provided with a thermal barrier coating |
Publications (1)
Publication Number | Publication Date |
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DE102016204627A1 true DE102016204627A1 (en) | 2017-09-21 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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DE102016204627.6A Ceased DE102016204627A1 (en) | 2016-03-21 | 2016-03-21 | Process for machining a component provided with a thermal barrier coating |
Country Status (2)
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DE (1) | DE102016204627A1 (en) |
WO (1) | WO2017162411A1 (en) |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1666633B1 (en) * | 2004-12-01 | 2008-07-16 | General Electric Company | Protection of a thermal barrier coating by a sacrificial coating |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6720038B2 (en) * | 2002-02-11 | 2004-04-13 | General Electric Company | Method of forming a coating resistant to deposits and coating formed thereby |
US20070160859A1 (en) * | 2006-01-06 | 2007-07-12 | General Electric Company | Layered thermal barrier coatings containing lanthanide series oxides for improved resistance to CMAS degradation |
US9869188B2 (en) * | 2014-12-12 | 2018-01-16 | General Electric Company | Articles for high temperature service and method for making |
DE102015206332A1 (en) * | 2015-04-09 | 2016-10-13 | Siemens Aktiengesellschaft | Process for the preparation of a corrosion protection layer for thermal insulation layers of hollow aluminum oxide spheres and outermost glass layer and component |
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2016
- 2016-03-21 DE DE102016204627.6A patent/DE102016204627A1/en not_active Ceased
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2017
- 2017-03-01 WO PCT/EP2017/054693 patent/WO2017162411A1/en active Application Filing
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1666633B1 (en) * | 2004-12-01 | 2008-07-16 | General Electric Company | Protection of a thermal barrier coating by a sacrificial coating |
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WO2017162411A1 (en) | 2017-09-28 |
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