EP1934387B1 - Method for removing the coating from a gas turbine component - Google Patents

Method for removing the coating from a gas turbine component Download PDF

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Publication number
EP1934387B1
EP1934387B1 EP06805384.2A EP06805384A EP1934387B1 EP 1934387 B1 EP1934387 B1 EP 1934387B1 EP 06805384 A EP06805384 A EP 06805384A EP 1934387 B1 EP1934387 B1 EP 1934387B1
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EP
European Patent Office
Prior art keywords
bath
layer
turbine component
remove
gas turbine
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.)
Not-in-force
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EP06805384.2A
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German (de)
French (fr)
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EP1934387A1 (en
Inventor
Karl-Heinz Manier
Thomas Uihlein
Carl-Stefan Thöne
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.)
Solut Chemie AB GmbH
MTU Aero Engines AG
Original Assignee
Solut Chemie AB GmbH
MTU Aero Engines AG
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Publication date
Application filed by Solut Chemie AB GmbH, MTU Aero Engines AG filed Critical Solut Chemie AB GmbH
Priority to PL06805384T priority Critical patent/PL1934387T3/en
Publication of EP1934387A1 publication Critical patent/EP1934387A1/en
Application granted granted Critical
Publication of EP1934387B1 publication Critical patent/EP1934387B1/en
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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
    • F01D5/005—Repairing methods or devices
    • 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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F1/00—Etching metallic material by chemical means
    • C23F1/44—Compositions for etching metallic material from a metallic material substrate of different composition
    • 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
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G1/00—Cleaning or pickling metallic material with solutions or molten salts
    • C23G1/02—Cleaning or pickling metallic material with solutions or molten salts with acid solutions
    • C23G1/10—Other heavy metals
    • C23G1/106—Other heavy metals refractory metals
    • 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

Definitions

  • the invention relates to a method for stripping a gas turbine component according to.
  • Components of a gas turbine such as the rotor blades, are provided with special anti-wear coatings to provide oxidation resistance, corrosion resistance, or erosion resistance on the surfaces.
  • the components of gas turbines are subject to wear during operation of the same or can be damaged in any other way. In order to repair damage, it is generally necessary to remove or remove the wear protection coating from the component to be repaired in regions, partially or even in total.
  • the removal or removal of coatings is also referred to as stripping. In the stripping process, a distinction is made between those in which stripping takes place by mechanical means, by chemical means or by electrochemical means.
  • wear protection coatings are designed as so-called multilayer coatings consisting of several alternately applied to the gas turbine component layers. So it is e.g. it is possible that a wear protection coating designed as a multilayer coating comprises a relatively soft, metallic layer and a relatively hard, ceramic layer, which are applied to the gas turbine component repeatedly alternately in succession. Furthermore, wear-resistant coatings are known in practice, in which more than two different layers are alternately applied successively to the gas turbine component, e.g.
  • Multilayer coatings of four alternatingly applied successively to the gas turbine component layers namely a first, adapted to the material composition of the gas turbine component metallic and thus relatively soft layer, a relatively soft, metallic layer of a metal alloy material, a third, relatively hard graded metal Ceramic layer and a fourth relatively hard, ceramic layer.
  • the publication US 5,972,424 A discloses a method for stripping turbine components.
  • the method comprises a treatment in an alkaline solution for removing the thermal protective layer and an acid treatment for removing the metallic adhesive layer. This coating also provides protection against wear.
  • the publication US 2005/152805 A1 discloses a method for refurbishment Turbine components with a wear protection coating.
  • the upper wear protection layer is removed mechanically, a metallic diffusion layer is chemically removed.
  • the present invention is based on the problem to provide a novel method for stripping a gas turbine component.
  • the gas turbine component is alternately positioned in two different chemical baths, a first bath excluding removal of the or each relatively hard ceramic layer and a second bath excluding removal of the or each relatively soft metallic layer the wear protection coating is used.
  • the component with a multilayer wear protection coating alternately in different baths, wherein the different baths selectively ablate either a relatively hard, ceramic layer or a relatively soft, metallic layer of the wear protection coating to be removed.
  • a method is proposed for the first time, with the aid of which gas turbine components can be effectively freed from a so-called multilayer wear protection coating without the risk of damage to the gas turbine component.
  • the first bath which serves solely to remove the or each relatively hard ceramic layer is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein.
  • the first bath may comprise a nitrogen-containing organic compound.
  • the first bath has a pH between 3 and 5.
  • the second bath which serves exclusively for removing the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or alkaline earth hydroxide with silicon and / or phosphorus contained therein, the second bath having a pH of has at least 12.
  • the first bath is a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids.
  • the first bath may have 1 g / L to 10 g / L of a nitrogen-containing organic compound.
  • the second bath is preferably a 2% to 50% alkali hydroxide solution containing 1 g / l to 200 g / l of silicon and / or 10 g / l to 100 g / l of phosphorus.
  • the gas turbine component is positioned to remove a relatively hard, ceramic layer in the first bath at a temperature between 10 ° C and 70 ° C for a period of 1-60 minutes per 1 nm thickness of the layer to be removed .
  • the gas turbine component is positioned in the second bath at a temperature between 20 ° C and 150 ° C for a period of 10-120 minutes per 1 nm thickness of the layer to be removed.
  • the inventive method is used for stripping of coated with multilayer wear protection coatings gas turbine components, the multilayer wear protection coatings from at least two different, alternately successively arranged layers, namely alternately arranged one behind the other ceramic, relatively hard layers and metallic, relatively soft layers are formed.
  • the method is used for stripping gas turbine components, on which a wear protection coating of four different, alternately successive layers are applied.
  • the first layer is preferably formed of titanium or palladium or platinum.
  • a second layer is applied, which is preferably formed by a TiCrAl material.
  • the third layer is followed by a grading layer, which is formed from a TiAlN1-x material.
  • the third layer is followed by a fourth layer of titanium aluminum nitride (TiAlN).
  • TiAlN titanium aluminum nitride
  • a first bath exclusively removes the or each relatively hard, ceramic layer and a second bath solely for removing the or any relatively soft, metallic layer of the wear-resistant coating.
  • the first bath which serves exclusively to remove the or each relatively hard ceramic layer, is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein.
  • the first bath may comprise a nitrogen-containing organic compound.
  • the first bath is formed from a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids.
  • the pH of this first bath is between 3 and 5.
  • the second bath which serves exclusively to remove the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or an alkaline earth hydroxide with silicon and / or phosphorus contained therein.
  • the second bath is a base of a 2% to 50% alkali hydroxide solution with 1 g / l to 200 g / l of silicon compounds and 10 g / l to 100 g / l of phosphorus compounds.
  • the pH of this second bath is at least 12.
  • the first bath is an acid of a 10% hydrogen peroxide solution with 70 g / l of ethylenediaminetetraacetate sodium salt and 20 g / l of phenol-4-sulfonic acid sodium salt and a 20% in the second bath Alkali hydroxide solution with 100 g / l silicon compounds and 50 g / l phosphorus compounds.
  • the gas turbine component is alternately positioned in the first bath and the second bath, with the first bath selectively removing only the hard, ceramic layers and the second bath only serves to remove the soft, metallic layers.
  • a gas turbine component is accordingly positioned in the first bath, for which purpose the first bath has a temperature between 10 ° C and 70 ° C.
  • the temperature of this bath is in the order of the room temperature, ie at about 20 ° C.
  • the gas turbine component is placed in this bath for a period of 1 to 60 minutes per 1 nm thickness of the ceramic, relatively hard layer to be removed.
  • the gas turbine component is positioned in the second bath, the temperature of the second bath being between 20 ° C and 150 ° C, preferably the temperature of the second bath is 80 ° C.
  • the component is positioned in the second bath for a period between 10 minutes and 120 minutes per 1 nm thickness of the metallic, relatively soft layer to be removed. Between the repositioning of a gas turbine component to be stripped between the two baths, the gas turbine component can be purged.
  • wear protection coatings of gas turbine components can be effectively removed without the risk of damage to the gas turbine component.
  • wear protection coatings can be completely or even partially removed from a gas turbine component, with partial removal of the wear protection coatings either submerged in the baths by a gas turbine component, or areas of the gas turbine component not to be stripped prior to immersion in the corresponding bath with a protective layer of z. B. wax are provided.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • General Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • ing And Chemical Polishing (AREA)
  • Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Detergent Compositions (AREA)

Description

Die Erfindung betrifft ein Verfahren zur Entschichtung eines Gasturbinenbauteils nach.The invention relates to a method for stripping a gas turbine component according to.

Bauteile einer Gasturbine, wie zum Beispiel die Laufschaufeln, sind zur Bereitstellung einer Oxidationsbeständigkeit, einer Korrosionsbeständigkeit oder auch einer Erosionsbeständigkeit an den Oberflächen mit speziellen Verschleißschutzbeschichtungen versehen. Die Bauteile von Gasturbinen unterliegen während des Betriebs derselben einem Verschleiß oder können auf sonstige Art und Weise beschädigt werden. Zur Reparatur von Beschädigungen ist es in der Regel erforderlich, vom zu reparierenden Bauteil die verschleißschutzbeschichtung bereichsweise, teilweise oder auch insgesamt zu entfernen bzw. abzutragen. Das Entfernen bzw. Abtragen von Beschichtungen bezeichnet man auch als Entschichten. Bei den Entschichtungsverfahren unterscheidet man solche, bei denen die Entschichtung auf mechanischem Wege, chemischem Wege oder elektrochemischem Wege erfolgt.Components of a gas turbine, such as the rotor blades, are provided with special anti-wear coatings to provide oxidation resistance, corrosion resistance, or erosion resistance on the surfaces. The components of gas turbines are subject to wear during operation of the same or can be damaged in any other way. In order to repair damage, it is generally necessary to remove or remove the wear protection coating from the component to be repaired in regions, partially or even in total. The removal or removal of coatings is also referred to as stripping. In the stripping process, a distinction is made between those in which stripping takes place by mechanical means, by chemical means or by electrochemical means.

Üblicherweise sind Verschleißschutzbeschichtungen als sogenannte Multilayer-Beschichtungen ausgeführt, die aus mehreren wechselweise auf das Gasturbinenbauteil aufgebrachten Lagen bestehen. So ist es z.B. möglich, dass eine als Multilayer-Beschichtung ausgeführte Verschleißschutzbeschichtung eine relativ weiche, metallische Lage und eine relativ harte, keramische Lage umfasst, die mehrfach wechselweise hintereinander auf das Gasturbinenbauteil aufgebracht sind. Weiterhin sind aus der Praxis verschleißscrutzbeschichtungen bekannt, bei welchen mehr als zwei unterschiedliche Lagen wechselweise hintereinander auf das Gasturbinenbauteil aufgebracht sind, so z.B. Multilayer-Beschichtungen aus jeweils vier wechselweise hintereinander auf das Gasturbinenbauteil aufgebrachten Lagen, nämlich einer ersten, an die Werkstoffzusammensetzung des Gasturbinenbauteils angepassten metallischen und damit relativ weichen Lage, einer ebenfalls relativ weichen, metallische Lage aus einem Metalllegierungswerkstoff, einer dritten, relativ harten gradierten Metall-Keramik-Lage sowie einer vierten relativ harten, keramischen Lage.Usually wear protection coatings are designed as so-called multilayer coatings consisting of several alternately applied to the gas turbine component layers. So it is e.g. it is possible that a wear protection coating designed as a multilayer coating comprises a relatively soft, metallic layer and a relatively hard, ceramic layer, which are applied to the gas turbine component repeatedly alternately in succession. Furthermore, wear-resistant coatings are known in practice, in which more than two different layers are alternately applied successively to the gas turbine component, e.g. Multilayer coatings of four alternatingly applied successively to the gas turbine component layers, namely a first, adapted to the material composition of the gas turbine component metallic and thus relatively soft layer, a relatively soft, metallic layer of a metal alloy material, a third, relatively hard graded metal Ceramic layer and a fourth relatively hard, ceramic layer.

Die Druckschrift US 5,972,424 A offenbart ein Verfahren zur Entschichtung vcn Turbinenbauteilen. Das Verfahren umfasst eine Behandlung in einer alkalische Lösung zur Entfernung der thermischen Schutzschicht sowie eine Säurebehandlung zur Entfernung der metallischen Haftschicht. Diese Beschichtung bietet auch einen Schutz gegen verschleiß.The publication US 5,972,424 A discloses a method for stripping turbine components. The method comprises a treatment in an alkaline solution for removing the thermal protective layer and an acid treatment for removing the metallic adhesive layer. This coating also provides protection against wear.

Die Druckschrift US 2005/152805 A1 offenbart ein Verfahren zur Wideraufbereitung von Turbinenbauteilen mit einer Verschleißschutzbeschichtung. Die oberste Verschleißschutzschicht wird mechanisch entfernt, eine metallische Diffusionsschicht wird chemisch entfernt.The publication US 2005/152805 A1 discloses a method for refurbishment Turbine components with a wear protection coating. The upper wear protection layer is removed mechanically, a metallic diffusion layer is chemically removed.

Aus dem Stand der Technik ist bislang kein Verfahren bekannt, mit Hilfe dessen als Multilayer-Beschichtungen ausgebildete verschleißschutzbeschichtungen effektiv entfernt werden können, ohne dass die Gefahr von Beschädigungen des Gasturbinenbauteils besteht.From the state of the art, no method is yet known with the aid of which multilayer coatings designed wear protection coatings can be effectively removed without the risk of damage to the gas turbine component.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Entschichtung eines Gasturbinenbauteils zu schaffen.On this basis, the present invention is based on the problem to provide a novel method for stripping a gas turbine component.

Dieses Problem wird durch ein Verfahren zur Entschichtung eines Gasturbinenbauteils im Sinne von Anspruch 1 gelöst. Erfindungsgemäß wird zum Entfernen der mehrlagigen bzw. mehrschichtigen Verschleißschutzbeschichtung das Gasturbinenbauteil wechselweise in zwei unterschiedlichen chemischen Bädern positioniert, wobei ein erstes Bad ausschließlich dem Entfernen der oder jeder relativ harten, keramischen Lage und ein zweites Bad ausschließlich dem Entfernen der oder jeder relativ weichen, metallischen Lage der Verschleißschutzbeschichtung dient.This problem is solved by a method for stripping a gas turbine component in the sense of claim 1. According to the present invention, to remove the multi-layer or anti-wear coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath excluding removal of the or each relatively hard ceramic layer and a second bath excluding removal of the or each relatively soft metallic layer the wear protection coating is used.

Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, das Bauteil mit einer Multilayer-Verschleißschutzbeschichtung wechselweise in unterschiedlichen Bädern anzuordnen, wobei die unterschiedlichen Bäder selektiv entweder eine relativ harte, keramische Lage oder eine relativ weiche, metallische Lage der zu entfernenden Verschleißschutzbeschichtung abtragen. Hierdurch wird erstmals ein Verfahren vorgeschlagen, mit Hilfe dessen Gasturbinenbauteile effektiv von einer sogenannten Multilayer-Verschleißschutzbeschichtung befreit werden können, ohne dass die Gefahr von Beschädigungen des Gasturbinenbauteils besteht.For the purposes of the present invention, it is proposed to arrange the component with a multilayer wear protection coating alternately in different baths, wherein the different baths selectively ablate either a relatively hard, ceramic layer or a relatively soft, metallic layer of the wear protection coating to be removed. As a result, a method is proposed for the first time, with the aid of which gas turbine components can be effectively freed from a so-called multilayer wear protection coating without the risk of damage to the gas turbine component.

Das erste Bad, welches ausschließlich dem Entfernen der oder jeder relativ harten, keramischen Lage dient, ist eine Säure aus einer Wasserstoffperoxydlösung und mindestens einem darin enthaltenen Natriumsalz und/oder Kaliumsalz einer organischen Säure. Zusätzlich zum Natriumsalz und/oder Kaliumsalz kann das erste Bad eine stickstoffhaltige organische Verbindung aufweisen. Das erste Bad weist einen pH-Wert zwischen 3 und 5 auf.The first bath which serves solely to remove the or each relatively hard ceramic layer is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein. In addition to the sodium salt and / or potassium salt, the first bath may comprise a nitrogen-containing organic compound. The first bath has a pH between 3 and 5.

Das zweite Bad, welches ausschließlich dem Entfernen der oder jeder relativ weichen, metallischen Lage dient, ist eine Base aus einer wässrigen Lösung mindestens eines Alkalihydroxids oder Erdalkalihydroxids mit darin enthaltenem Silizium und/oder Phosphor bzw., wobei das zweite Bad einen pH-wert von mindestens 12 aufweist.The second bath, which serves exclusively for removing the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or alkaline earth hydroxide with silicon and / or phosphorus contained therein, the second bath having a pH of has at least 12.

Vorzugsweise ist das erste Bad eine 5%ige bis 50%ige wasserstoffperoxydlösung mit 10 g/l bis 100 g/l Natriumsalzen organischer Säuren. Zusätzlich zu den Natriumsalzen kann das erste Bad 1 g/l bis 10 g/l einer stickstoffhaltigen organischen Verbindung aufweisen. Das zweite Bad ist vorzugsweise eine 2%ige bis 50%ige Alkalihydroxidlösung mit 1 g/l bis 200 g/l Silizium und/oder 10 g/l bis 100 g/l Phosphor.Preferably, the first bath is a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids. In addition to the sodium salts, the first bath may have 1 g / L to 10 g / L of a nitrogen-containing organic compound. The second bath is preferably a 2% to 50% alkali hydroxide solution containing 1 g / l to 200 g / l of silicon and / or 10 g / l to 100 g / l of phosphorus.

Nach einer weiteren vorteilhaften Weiterbildung der Erfindung wird das Gasturbinenbauteil zum Entfernen einer relativ harten, keramischen Lage in dem ersten Bad bei einer Temperatur zwischen 10°C und 70°C für eine Zeitdauer von 1-60 Minuten pro 1 nm Dicke der zu entfernenden Lage positioniert. Zum Entfernen einer relativ weichen, metallischen Lage wird das Gasturbinenbauteil in dem zweiten Bad bei einer Temperatur zwischen 20°C und 150°C für eine Zeitdauer von 10-120 Minuten pro 1 nm Dicke der zu entfernenden Lage positioniert.According to a further advantageous development of the invention, the gas turbine component is positioned to remove a relatively hard, ceramic layer in the first bath at a temperature between 10 ° C and 70 ° C for a period of 1-60 minutes per 1 nm thickness of the layer to be removed , To remove a relatively soft metallic layer, the gas turbine component is positioned in the second bath at a temperature between 20 ° C and 150 ° C for a period of 10-120 minutes per 1 nm thickness of the layer to be removed.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ein Ausführungsbeispiel der Erfindung wird nachfolgend in größerem Detail beschrieben.Preferred embodiments of the invention will become apparent from the dependent claims and the description below. An embodiment of the invention will be described below in more detail.

Das erfindungsgemäße Verfahren dient dem Entschichten von mit Multilayer-Verschleißschutzbeschichtungen beschichteten Gasturbinenbauteilen, wobei die Multilayer-Verschleißschutzbeschichtungen aus mindestens zwei unterschiedlichen, wechselweise hintereinander angeordneten Lagen, nämlich aus wechselweise hintereinander angeordneten keramischen, relativ harten Lagen sowie metallischen, relativ weichen Lagen gebildet sind. Das Verfahren dient dem Entschichten von Gasturbinenbauteilen, auf welche eine Verschleißschutzbeschichtung aus vier unterschiedlichen, wechselweise aufeinander folgenden Lagen aufgebracht sind.The inventive method is used for stripping of coated with multilayer wear protection coatings gas turbine components, the multilayer wear protection coatings from at least two different, alternately successively arranged layers, namely alternately arranged one behind the other ceramic, relatively hard layers and metallic, relatively soft layers are formed. The method is used for stripping gas turbine components, on which a wear protection coating of four different, alternately successive layers are applied.

Bei einem Gasturbinenbauteil, welches aus einem Titanbasiswerkstoff gebildet ist, ist die erste Lage vorzugsweise aus Titan oder Palladium oder Platin gebildet. Auf die erste Lage ist eine zweite Lage aufgebracht, die vorzugsweise von einem TiCrAl-Werkstoff gebildet wird. Als dritte Lage schließt sich eine Gradierungsschicht an, die aus einem TiAlN1-x Werkstoff gebildet ist. An die dritte Lage schließt sich eine vierte Lage aus Titanaluminiumnitrid (TiAlN) an. Diese vier Lagen sind wiederum zur Bildung einer mehrlagigen bzw. mehrschichtigen Verschleißschutzbeschichtung wechselweise hintereinander auf das Gasturbinenbauteil aufgebracht, wobei die erste und zweite Lage jeweils metallisch und relativ weich und die dritte und vierte Lage jeweils keramisch und relativ hart sind.In a gas turbine component formed of a titanium base material, the first layer is preferably formed of titanium or palladium or platinum. On the first layer, a second layer is applied, which is preferably formed by a TiCrAl material. The third layer is followed by a grading layer, which is formed from a TiAlN1-x material. The third layer is followed by a fourth layer of titanium aluminum nitride (TiAlN). These four layers are in turn applied to the formation of a multilayer or multi-layer wear protection coating alternately one behind the other on the gas turbine component, wherein the first and second layer respectively metallic and relatively soft and the third and fourth layers are each ceramic and relatively hard.

Zum Entfernen solcher mehrlagiger bzw. mehrschichtiger Verschleißschutzbeschichtungen von einem Gasturbinenbauteil wird im Sinne der hier vorliegenden Erfindung vorgeschlagen, das Gasturbinenbauteil wechselweise in zwei unterschiedlichen chemischen Bädern zu positionieren, wobei ein erstes Bad ausschließlich dem Entfernen der oder jeder relativ harten, keramischen Lage und ein zweites Bad ausschließlich dem Entfernen der oder jeder relativ weichen, metallischen Lage der Verschleißschutzbeschichtung dient.For the purpose of the present invention, in order to remove such multilayer or wear-resistant coatings from a gas turbine component, it is proposed to alternately position the gas turbine component in two different chemical baths, wherein a first bath exclusively removes the or each relatively hard, ceramic layer and a second bath solely for removing the or any relatively soft, metallic layer of the wear-resistant coating.

Bei dem ersten Bad, welches ausschließlich dem Entfernen der oder jeder relativ harten, keramischen Lage dient, handelt es sich um eine Säure aus einer Wasserstoffperoxydlösung und mindestens einem darin enthaltenen Natriumsalz und/oder Kaliumsalz einer organischen Säure. Zusätzlich zum Natriumsalz und/oder Kaliumsalz kann das erste Bad eine stickstoffhaltige organische Verbindung aufweisen.The first bath, which serves exclusively to remove the or each relatively hard ceramic layer, is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein. In addition to the sodium salt and / or potassium salt, the first bath may comprise a nitrogen-containing organic compound.

Vorzugsweise wird das erste Bad von einer 5%igen bis 50%igen Wasserstoffperoxydlösung mit 10 g/l bis 100 g/l Natriumsalzen organischer Säuren gebildet. Der pH-Wert dieses ersten Bads liegt zwischen 3 und 5.Preferably, the first bath is formed from a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids. The pH of this first bath is between 3 and 5.

Bei dem zweiten Bad, welches ausschließlich dem Entfernen der oder jeder relativ weichen, metallischen Lage dient, handelt es sich um eine Base aus einer wässrigen Lösung mindestens eines Alkalihydroxids oder eines Erdalkalihydroxids mit darin enthaltenem Silizium und/oder Phosphor.The second bath, which serves exclusively to remove the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or an alkaline earth hydroxide with silicon and / or phosphorus contained therein.

Vorzugsweise ist das zweite Bad eine Base aus einer 2%igen bis 50%igen Alkalihydroxidlösung mit 1 g/l bis 200 g/l Siliziumverbindungen und 10 g/l bis 100 g/l Phosphorverbindungen. Der pH-Wert dieses zweiten Bads beträgt mindestens 12.Preferably, the second bath is a base of a 2% to 50% alkali hydroxide solution with 1 g / l to 200 g / l of silicon compounds and 10 g / l to 100 g / l of phosphorus compounds. The pH of this second bath is at least 12.

In einem konkreten Ausführungsbeispiel handelt es sich bei dem ersten Bad um eine Säure aus einer 10%igen Wasserstoffperoxydlösung mit 70 g/l Ethylendiamintetraacetat-Natriumsalz und 20 g/l Phenol-4-Sulfonsäure-Natriumsalz und bei dem zweiten Bad um eine 20%ige Alkalihydroxidlösung mit 100 g/l Siliziumverbindungen und 50 g/l Phosphorverbindungen.In a specific embodiment, the first bath is an acid of a 10% hydrogen peroxide solution with 70 g / l of ethylenediaminetetraacetate sodium salt and 20 g / l of phenol-4-sulfonic acid sodium salt and a 20% in the second bath Alkali hydroxide solution with 100 g / l silicon compounds and 50 g / l phosphorus compounds.

Wie bereits erwähnt, wird das Gasturbinenbauteil zum Entfernen der Verschleißschutzbeschichtung wechselweise in dem ersten Bad sowie dem zweiten Bad positioniert, wobei das erste Bad selektiv lediglich dem Entfernen der harten, keramischen Lagen und das zweite Bad ausschließlich dem Entfernen der weichen, metallischen Lagen dient. Zum Entfernen einer keramischen Lage wird ein Gasturbinenbauteil demnach in dem ersten Bad positioniert, wobei hierzu das erste Bad eine Temperatur zwischen 10°C und 70°C aufweist. Vorzugsweise liegt die Temperatur dieses Bads in der Größenordnung der Raumtemperatur, also bei in etwa 20°C. Das Gasturbinenbauteil wird in diesem Bad für eine Zeitdauer von 1 bis 60 Minuten pro 1 nm Dicke der zu entfernenden keramischen, relativ harten Lage angeordnet. Zum Entschichten einer metallischen, relativ weichen Lage der Verschleißschutzbeschichtung wird das Gasturbinenbauteil im zweiten Bad positioniert, wobei die Temperatur des zweiten Bads zwischen 20°C und 150°C beträgt, vorzugsweise liegt die Temperatur des zweiten Bads bei 80°C. Das Bauteil wird im zweiten Bad für eine Zeitdauer zwischen 10 Minuten und 120 Minuten pro 1 nm Dicke der zu entfernenden metallischen, relativ weichen Lage positioniert. Zwischen dem Umpositionieren eines zu entschichtenden Gasturbinenbauteils zwischen den beiden Bädern kann das Gasturbinenbauteil gespült werden.As previously mentioned, to remove the anti-wear coating, the gas turbine component is alternately positioned in the first bath and the second bath, with the first bath selectively removing only the hard, ceramic layers and the second bath only serves to remove the soft, metallic layers. For removing a ceramic layer, a gas turbine component is accordingly positioned in the first bath, for which purpose the first bath has a temperature between 10 ° C and 70 ° C. Preferably, the temperature of this bath is in the order of the room temperature, ie at about 20 ° C. The gas turbine component is placed in this bath for a period of 1 to 60 minutes per 1 nm thickness of the ceramic, relatively hard layer to be removed. For stripping a metallic, relatively soft layer of wear protection coating, the gas turbine component is positioned in the second bath, the temperature of the second bath being between 20 ° C and 150 ° C, preferably the temperature of the second bath is 80 ° C. The component is positioned in the second bath for a period between 10 minutes and 120 minutes per 1 nm thickness of the metallic, relatively soft layer to be removed. Between the repositioning of a gas turbine component to be stripped between the two baths, the gas turbine component can be purged.

Mit dem erfindungsgemäßen Verfahren lassen sich sogenannte Multilayer-Verschleißschutzbeschichtungen von Gasturbinenbauteilen effektiv entfernen, ohne dass die Gefahr von Beschädigungen des Gasturbinenbauteils besteht. Mit Hilfe des erfindungsgemäßen Verfahrens können Verschleißschutzbeschichtungen von einem Gasturbinenbauteil vollständig oder auch lediglich teilweise entfernt werden, wobei zum teilweisen Entfernen der Verschleißschutzbeschichtungen ein Gasturbinenbauteil entweder nur teilweise in die Bäder eingetaucht wird, oder wobei nicht zu entschichtende Bereiche des Gasturbinenbauteils vor dem Eintauchen in das entsprechende Bad mit einer Schutzschicht aus z. B. Wachs versehen werden.With the method according to the invention, so-called multilayer wear protection coatings of gas turbine components can be effectively removed without the risk of damage to the gas turbine component. With the aid of the method according to the invention, wear protection coatings can be completely or even partially removed from a gas turbine component, with partial removal of the wear protection coatings either submerged in the baths by a gas turbine component, or areas of the gas turbine component not to be stripped prior to immersion in the corresponding bath with a protective layer of z. B. wax are provided.

Claims (8)

  1. A method for removing the coating from a gas-turbine component, namely for completely or partially removing a multi-layer or multi-coat wear-protection coating from the surface of the gas-turbine component, wherein the wear-protection coating comprises relatively hard ceramic layers and relatively soft metallic layers, having in each case at least one first layer of titanium, palladium or platinum, a second layer of a TiCrAl material, a third layer of a TiAlN(1-x) material and a fourth layer of TiAlN, wherein in order to remove the multi-layer or multi-coat wear-protection coating the gas-turbine component is alternately positioned in two different chemical baths, wherein a first bath is used exclusively to remove each relatively hard ceramic layer, and a second bath is used exclusively to remove each relatively soft metallic layer of the wear-protection coating, characterised in that the first bath, which is used exclusively to remove each relatively hard ceramic layer, is an acid consisting of a hydrogen peroxide solution and at least one sodium salt and/or potassium salt of an organic acid contained therein, and the second bath, which is used exclusively to remove each relatively soft metallic layer, is a base consisting of an aqueous solution of at least one alkali hydroxide or an alkaline earth hydroxide with silicon and/or phosphorus contained therein.
  2. A method according to claim 1,
    characterised in that
    the first bath is a 5% to 50% hydrogen peroxide solution with 10 g/l to 100 g/l sodium salts of organic acids.
  3. A method according to claim 1 or 2,
    characterised in that
    the first bath has a pH value between 3 and 5.
  4. A method according to one of claims 1 to 3,
    characterised in that
    in order to remove a relatively hard ceramic layer the gas-turbine component is positioned in the first bath at a temperature between 10°C and 70°C for a period of time of 1-60 minutes per 1 nm thickness of the layer that is to be removed.
  5. A method according to one of claims 1 to 4,
    characterised in that
    the second bath is a 2% to 50% alkali hydroxide solution with 1 g/l to 200 g/l silicon and/or 10 g/l to 100 g/l phosphorus.
  6. A method according to one of claims 1 to 5,
    characterised in that
    the second bath has a pH value that is greater than 12.
  7. A method according to one of claims 1 to 6,
    characterised in that in order to remove a relatively soft metallic layer the gas-turbine component is positioned in the second bath at a temperature between 20°C and 150°C for a period of time of 10-120 minutes per 1 nm thickness of the layer that is to be removed.
  8. A method according to one of claims 1 to 7,
    characterised in that
    the first bath is an acid consisting of a 10% hydrogen peroxide solution with 70g/l ethylenediamine tetraacetate sodium salt and 20 g/l phenol-4-sulphonic acid sodium salt.
EP06805384.2A 2005-10-14 2006-10-10 Method for removing the coating from a gas turbine component Not-in-force EP1934387B1 (en)

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DE102005049249.5A DE102005049249B4 (en) 2005-10-14 2005-10-14 Process for stripping a gas turbine component
PCT/DE2006/001766 WO2007041998A1 (en) 2005-10-14 2006-10-10 Method for removing the coating from a gas turbine component

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US9212555B2 (en) 2015-12-15
WO2007041998A1 (en) 2007-04-19
JP2009511804A (en) 2009-03-19
DE102005049249B4 (en) 2018-03-29
PL1934387T3 (en) 2016-03-31
DE102005049249A1 (en) 2007-04-19
EP1934387A1 (en) 2008-06-25
US20090302004A1 (en) 2009-12-10

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