WO2010102609A1 - Method for producing an abrasive coating and component for a turbomachine - Google Patents

Method for producing an abrasive coating and component for a turbomachine Download PDF

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Publication number
WO2010102609A1
WO2010102609A1 PCT/DE2010/000255 DE2010000255W WO2010102609A1 WO 2010102609 A1 WO2010102609 A1 WO 2010102609A1 DE 2010000255 W DE2010000255 W DE 2010000255W WO 2010102609 A1 WO2010102609 A1 WO 2010102609A1
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WIPO (PCT)
Prior art keywords
component
turbomachine
coating
producing
abrasive
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PCT/DE2010/000255
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German (de)
French (fr)
Inventor
André Werner
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Mtu Aero Engines Gmbh
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Publication of WO2010102609A1 publication Critical patent/WO2010102609A1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/026—Anodisation with spark discharge
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/26—Anodisation of refractory metals or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/30—Anodisation of magnesium or alloys based thereon
    • 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

Definitions

  • the invention relates to a method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade.
  • the invention further relates to a component for a turbomachine, in particular a compressor or turbine blade.
  • shear tip blade seals are a particular form of solution to such sealing problems.
  • the blade tips are oversized with abrasive cladding. When entering the turbine, the blade tips dig into soft inlet linings of the housing, so that it no longer comes to a direct contact of the turbine blades with the housing.
  • the blade tips are provided with hard tarnish.
  • the blade tips are provided with a shroud, which serves the relative fixation and the bias in the engine. Due to the frequent contact of adjacent blades on the shroud this wears particularly strong. To avoid this, the respective contact surfaces of the shroud are armored with a hard layer.
  • an impeller of a gas turbine wherein between the impeller and a housing, a sealing gap is provided which has labyrinth-like structural elements.
  • the surface areas of the impeller are composite educated.
  • the composite comprises a metallic matrix with a structured ceramic embedded therein. Parts of the ceramic phase emerge on the surface as elevations from the composite and thereby form the labyrinth-like structural elements.
  • EP 0 702 130 A2 shows a metallic engine component with a tarpaulin covering of a thermally sprayed ceramic layer, which is incorporated into an inlet lining.
  • the ceramic layer is profiled in such a way that it has edges capable of being cut, free spaces being arranged between the edges which absorb and clear out the wear of the inlet lining.
  • the object of the invention is to provide a cost-effective alternative for producing an abrasive coating of a turbomachinery component with improved adhesive properties.
  • the inventive method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade is characterized in that the coating is formed by a conversion of the surface into an oxide ceramic. Since, in contrast to the methods commonly used in engine technology, the coating according to the invention is not produced by deposition or deposition of particles but by transformation of the component surface, a coating produced according to the invention has a significantly better adhesion. Depending on the component and production concept, cost savings compared to conventional methods are possible. Application potential exists mainly for components that are complete or whose surfaces are made of titanium alloys (including titanium aluminides).
  • the surface is converted by so-called plasma-electrolytic oxidation.
  • This method of converting a light metal surface which is also referred to in the literature as PEO (plasma electrolytic oxidation), plasma chemical oxidation, anodic oxidation with spark discharge (ANOF), dielectric breakdown process, micro arc oxidation (MAO) or anodic spark deposition (ASO) , is generally z.
  • PEO plasma electrolytic oxidation
  • ANOF anodic oxidation with spark discharge
  • MAO micro arc oxidation
  • ASO anodic spark deposition
  • the Protective layer in both directions, ie the layer forms partly above and partly below the original surface.
  • the pronounced hardness of the oxide-ceramic layer promotes damage-free shrinkage when rubbed against turbomachinery.
  • a further advantage of the coating produced in this way is that no interactions with the base material of the component surface are to be feared, especially at relatively high temperatures, since the coating is indeed a species-specific oxide.
  • the process of plasma electrolytic oxidation is suitable for a number of light metal alloys, eg. For alloys based on aluminum, magnesium or titanium, including titanium aluminides.
  • the invention also relates to a component for a turbomachine, in particular a compressor or turbine blade, which is characterized in that a light metal surface of the component has an abrasive oxide ceramic coating.
  • the oxide ceramic coating is an armor or tarnish.
  • FIG. 1 shows a rotor blade and a housing part of a turbomachine
  • Figure 2 shows a vane and a rotor of a turbomachine
  • Figures 3a, 3b in each case a compressor blade with fin seal.
  • a rotor blade 10 has at its tip an armor 12 produced according to the invention, which runs into an inlet lining 14 of a housing 16.
  • FIG. 2 a region of a rotor 18, which lies opposite a housing-fixed guide blade 20, is protected by a starting lining 22 produced according to the invention.
  • FIGS. 3 a and 3 b the extensions 24 of a cover strip 26 formed in the manner of a knife edge, which run into a housing-mounted inlet lining 28, are provided with an abrasive coating 30 produced according to the invention.
  • the component which is either complete or whose surface to be coated consists of a light metal alloy, is immersed in an acidic or basic electrolyte bath with a specific aqueous electrolyte.
  • the component forms the anode, the bath container usually the cathode.
  • the voltage applied to the device is significantly higher than that of anodization (anodization), typically greater than 200 V. This locally exceeds the dielectric strength of the growing oxide layer, causing electrostatic discharges.
  • the discharges form locally limited plasma reactors with high temperatures and high pressures that modify the growing oxide.
  • the modification may include melting, flowing, re-solidification, sintering, and densification of the growing oxide.
  • One of the main effects is the formation of an oxide ceramic, which z. For example, in the case of an aluminum surface, the conversion of amorphous alumina into harder crystalline forms such as corundum (Q-Al 2 O 3 ) is based.

Abstract

A method for producing an abrasive coating (12; 22; 30) on a light metal surface of a component (10; 18; 26) of a turbomachine, particularly a compressor or turbine blade, is characterized in that the coating (12; 22; 30) is formed by converting the surface into an oxide ceramic. A component (10; 18; 26) for a turbomachine, particularly a compressor or turbine blade, is characterized in that a light metal surface of the component (10; 18; 26) has an abrasive oxide ceramic coating (12; 22; 30).

Description

Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine Method for producing an abrasive coating and component for a turbomachine
Die Erfindung betrifft ein Verfahren zur Herstellung einer abrasiven Beschichtung an einer Leichtmetall-Oberfläche eines Bauteils einer Turbomaschine, insbesondere einer Verdichteroder Turbinenschaufel. Die Erfindung betrifft ferner ein Bauteil für eine Turbomaschine, insbesondere eine Verdichter- oder Turbinenschaufel.The invention relates to a method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade. The invention further relates to a component for a turbomachine, in particular a compressor or turbine blade.
Um die Druckverluste zwischen den einzelnen Triebwerksstufen einer Gasturbine gering zu halten, ist eine optimale Abdichtung zwischen Rotor und Turbinengehäuse notwendig. Schaufelspitzen-Dichtungen (blade tip seals) mit Anstreifbelägen stellen eine besondere Form zur Lösung solcher Dichtungsprobleme dar. Zur Erzielung eines möglichst kleinen radialen Abstands zwischen den Spitzen der rotierenden Turbinenschaufeln und dem Gehäuse werden die Schaufelspitzen mit einer abrasiv wirkenden Panzerung mit Übermaß versehen. Beim Einlaufen der Turbine graben sich die Schaufelspitzen in weiche Einlaufbeläge des Gehäuses ein, sodass es nicht mehr zu einer direkten Berührung der Turbinenschaufeln mit dem Gehäuse kommt. Zum Schutz der Bereiche des Rotors, die den feststehenden Leitschaufeln der Turbine gegenüberliegen, werden diese mit harten Anlaufbelägen versehen. Bei sogenannten Fin-Dichtungen (knife-edge seals) sind die Schaufelspitzen mit einem Deckband versehen, das der relativen Fixierung sowie der Vorspannung im Triebwerk dient. Durch die oftmalige Berührung benachbarter Schaufeln am Deckband verschleißt dieses besonders stark. Um dies zu vermeiden, werden die jeweiligen Berührungsflächen des Deckbandes mit einer harten Schicht gepanzert.In order to keep the pressure losses between the individual engine stages of a gas turbine low, an optimal seal between the rotor and the turbine housing is necessary. Shear tip blade seals are a particular form of solution to such sealing problems. To achieve the least possible radial clearance between the tips of the rotating turbine blades and the housing, the blade tips are oversized with abrasive cladding. When entering the turbine, the blade tips dig into soft inlet linings of the housing, so that it no longer comes to a direct contact of the turbine blades with the housing. To protect the areas of the rotor, which face the fixed vanes of the turbine, they are provided with hard tarnish. In so-called fin-seals (knife-edge seals), the blade tips are provided with a shroud, which serves the relative fixation and the bias in the engine. Due to the frequent contact of adjacent blades on the shroud this wears particularly strong. To avoid this, the respective contact surfaces of the shroud are armored with a hard layer.
Es ist bekannt, solche Panzerungen bzw. Anlaufbeläge thermisch zu spritzen (z. B. Panzerungen mit Aluminiumoxid oder Zirkonoxid auf Labyrinthspitzen oder Blattspitzen), galvanisch aufzubringen oder aufzulöten (z. B. Panzerungen mit Hartstoffpartikeln aus kubischem Bornitrid). Diese Verfahren sind aber einerseits kostenintensiv, andererseits weisen die mit diesen Verfahren hergestellten Beschichtungen nur eine begrenzte Haftung auf den Oberflächen auf.It is known to thermally spray such armorings or start-up coverings (eg armor with aluminum oxide or zirconium oxide on labyrinth tips or blade tips), to be applied by electroplating or to be soldered on (eg armor with cubic boron nitride hard material particles). On the one hand, these processes are cost-intensive, on the other hand, the coatings produced by these processes have only limited adhesion to the surfaces.
Aus der EP 0 661 415 A1 ist ein Laufrad einer Gasturbine bekannt, wobei zwischen dem Laufrad und einem Gehäuse ein Dichtspalt vorgesehen ist, der labyrinthartige Strukturelemente aufweist. Die Oberflächenbereiche des Laufrads sind verbundartig ausgebildet. Der Verbund umfasst eine metallische Matrix mit einer darin eingebetteten strukturierten Keramik. Teile der keramischen Phase treten an der Oberfläche als Erhebungen aus dem Verbund heraus und bilden dadurch die labyrinthartigen Strukturelemente.From EP 0 661 415 A1 an impeller of a gas turbine is known, wherein between the impeller and a housing, a sealing gap is provided which has labyrinth-like structural elements. The surface areas of the impeller are composite educated. The composite comprises a metallic matrix with a structured ceramic embedded therein. Parts of the ceramic phase emerge on the surface as elevations from the composite and thereby form the labyrinth-like structural elements.
Die EP 0 702 130 A2 zeigt eine metallische Triebwerkskomponente mit einem Anlaufbelag aus einer thermisch gespritzten Keramikschicht, die sich in einen Einlaufbelag einarbeitet. Die Keramikschicht ist derart profiliert, dass sie schneidfähige Kanten aufweist, wobei zwischen den Kanten Freiräume angeordnet sind, die den Abrieb des Einlaufbelages aufnehmen und ausräumen.EP 0 702 130 A2 shows a metallic engine component with a tarpaulin covering of a thermally sprayed ceramic layer, which is incorporated into an inlet lining. The ceramic layer is profiled in such a way that it has edges capable of being cut, free spaces being arranged between the edges which absorb and clear out the wear of the inlet lining.
Aufgabe der Erfindung ist es, eine kostengünstige Alternative zur Herstellung einer abrasiven Beschichtung eines Turbomaschinenbauteils mit verbesserten Hafteigenschaften anzugeben.The object of the invention is to provide a cost-effective alternative for producing an abrasive coating of a turbomachinery component with improved adhesive properties.
Gelöst wird diese Aufgabe durch ein Verfahren mit den Merkmalen des Anspruchs 1.This object is achieved by a method having the features of claim 1.
Das erfindungsgemäße Verfahren zur Herstellung einer abrasiven Beschichtung an einer Leichtmetall-Oberfläche eines Bauteils einer Turbomaschine, insbesondere einer Verdichteroder Turbinenschaufel, ist dadurch gekennzeichnet, dass die Beschichtung durch eine Umwandlung der Oberfläche in eine Oxidkeramik gebildet wird. Da im Gegensatz zu den in der Triebwerkstechnik gängigen Verfahren die Beschichtung gemäß der Erfindung nicht durch Abscheidung oder Ablagerung von Partikeln, sondern durch Umwandlung der Bauteiloberfläche erzeugt wird, weist eine erfindungsgemäß hergestellte Beschichtung eine deutlich bessere Haftung auf. Je nach Bauteil- und Fertigungskonzept sind gegenüber den konventionellen Verfahren Kosteneinsparungen möglich. Anwendungspotenzial besteht vor allem für Bauteile, die vollständig oder deren Oberflächen aus Titanlegierungen (einschließlich Titanaluminiden) bestehen.The inventive method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade, is characterized in that the coating is formed by a conversion of the surface into an oxide ceramic. Since, in contrast to the methods commonly used in engine technology, the coating according to the invention is not produced by deposition or deposition of particles but by transformation of the component surface, a coating produced according to the invention has a significantly better adhesion. Depending on the component and production concept, cost savings compared to conventional methods are possible. Application potential exists mainly for components that are complete or whose surfaces are made of titanium alloys (including titanium aluminides).
Gemäß der bevorzugten Ausführungsform der Erfindung wird die Oberfläche durch sogenannte plasmaelektrolytische Oxidation umgewandelt. Dieses Verfahren zur Umwandlung einer Leichtmetalloberfläche, das in der Literatur auch als PEO (plasma electrolytic oxidation), plasmachemische Oxidation, anodische Oxidation mit Funkenentladung (ANOF), dielectric breakdown process, micro arc oxidation (MAO) oder anodic spark deposition (ASO) bezeichnet wird, ist allgemein z. B. in der WO 00/05493 A1 und in der US 6 197 178 beschrieben. Bei diesem Verfahren bildet sich eine - bezogen auf das Material der Bauteiloberfläche - arteigene und deshalb bestens haftende oxidkeramische Schicht. Ausgehend von der ursprünglichen Oberfläche des Bauteils wächst die Schutzschicht in beide Richtungen, d. h. die Schicht bildet sich teils über und teils unter der ursprünglichen Oberfläche. Die ausgeprägte Härte der oxidkeramischen Schicht fördert bei Anstreifvorgängen in Turbomaschinen ein schädigungsfreies Einlaufen. Ein weiterer Vorteil der so hergestellten Beschichtung besteht darin, dass insbesondere bei höheren Temperaturen keine Wechselwirkungen mit dem Grundwerkstoff der Bauteiloberfläche zu befürchten sind, da die Beschichtung ja ein arteigenes Oxid ist. Das Verfahren der plasmaelektrolytischen Oxidation eignet sich für eine Reihe von Leichtmetalllegierungen, z. B. für Legierungen auf Basis von Aluminium, Magnesium oder Titan, einschließlich Titanaluminiden.According to the preferred embodiment of the invention, the surface is converted by so-called plasma-electrolytic oxidation. This method of converting a light metal surface, which is also referred to in the literature as PEO (plasma electrolytic oxidation), plasma chemical oxidation, anodic oxidation with spark discharge (ANOF), dielectric breakdown process, micro arc oxidation (MAO) or anodic spark deposition (ASO) , is generally z. As described in WO 00/05493 A1 and in US 6,197,178. In this process, a - based on the material of the component surface - species-specific and therefore highly adherent oxide ceramic layer forms. Starting from the original surface of the component grows the Protective layer in both directions, ie the layer forms partly above and partly below the original surface. The pronounced hardness of the oxide-ceramic layer promotes damage-free shrinkage when rubbed against turbomachinery. A further advantage of the coating produced in this way is that no interactions with the base material of the component surface are to be feared, especially at relatively high temperatures, since the coating is indeed a species-specific oxide. The process of plasma electrolytic oxidation is suitable for a number of light metal alloys, eg. For alloys based on aluminum, magnesium or titanium, including titanium aluminides.
Gegenstand der Erfindung ist auch ein Bauteil für eine Turbomaschine, insbesondere eine Verdichter- oder Turbinenschaufel, das dadurch gekennzeichnet ist, dass eine Leichtmetalloberfläche des Bauteils eine abrasive Oxidkeramikbeschichtung aufweist.The invention also relates to a component for a turbomachine, in particular a compressor or turbine blade, which is characterized in that a light metal surface of the component has an abrasive oxide ceramic coating.
Vorzugsweise stellt die Oxidkeramikbeschichtung eine Panzerung oder einen Anlaufbelag dar.Preferably, the oxide ceramic coating is an armor or tarnish.
Weitere Merkmale und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung und aus den beigefügten Zeichnungen, auf die Bezug genommen wird. In den Zeichnungen zeigen:Further features and advantages of the invention will become apparent from the following description and from the accompanying drawings, to which reference is made. In the drawings show:
Figur 1 eine Rotorschaufel und ein Gehäuseteil einer Turbomaschine;1 shows a rotor blade and a housing part of a turbomachine;
Figur 2 eine Leitschaufel und einen Rotor einer Turbomaschine; undFigure 2 shows a vane and a rotor of a turbomachine; and
Figuren 3a, 3b jeweils eine Verdichterschaufel mit Fin-Dichtung.Figures 3a, 3b in each case a compressor blade with fin seal.
In den Figuren sind Anwendungspositionen für abrasive Panzerungen bzw. Anlaufbeläge bei einer Turbomaschine dargestellt.In the figures application positions for abrasive armor or tarnish are shown in a turbomachine.
Gemäß Figur 1 weist eine Rotorschaufel 10 an ihrer Spitze eine erfindungsgemäß hergestellte Panzerung 12 auf, die in einen Einlaufbelag 14 eines Gehäuses 16 einläuft.According to FIG. 1, a rotor blade 10 has at its tip an armor 12 produced according to the invention, which runs into an inlet lining 14 of a housing 16.
Gemäß Figur 2 ist ein Bereich eines Rotors 18, der einer gehäusefesten Leitschaufel 20 gegenüberliegt, durch einen erfindungsgemäß hergestellten Anlaufbelag 22 geschützt. Gemäß den Figuren 3a und 3b sind die nach Art einer Messerschneide gebildeten Fortsätze 24 eines Deckbands 26, die in einen gehäusefesten Einlaufbelag 28 einlaufen, mit einer erfindungsgemäß hergestellten abrasiven Beschichtung 30 versehen.According to FIG. 2, a region of a rotor 18, which lies opposite a housing-fixed guide blade 20, is protected by a starting lining 22 produced according to the invention. According to FIGS. 3 a and 3 b, the extensions 24 of a cover strip 26 formed in the manner of a knife edge, which run into a housing-mounted inlet lining 28, are provided with an abrasive coating 30 produced according to the invention.
Zur Herstellung einer erfindungsgemäßen Beschichtung wird das Bauteil, das entweder vollständig oder dessen zu beschichtende Oberfläche aus einer Leichtmetalllegierung besteht, in ein saures oder basisches Elektrolytbad mit einem spezifischen wässrigen Elektrolyt eingetaucht. Das Bauteil bildet die Anode, der Badbehälter üblicherweise die Kathode. An das Bauteil wird eine Spannung angelegt, die deutlich höher als bei der anodischen Oxidation (Eloxieren) ist, in der Regel größer als 200 V. Dadurch wird lokal die elektrische Durchschlagfestigkeit der wachsenden Oxidschicht überschritten, sodass elektrostatische Entladungen stattfinden. Die Entladungen bilden lokal begrenzte Plasmareaktoren mit hohen Temperaturen und hohen Drücken, die das wachsende Oxid modifizieren. Die Modifikation kann Schmelzen, Fließen, Wiedererstarren, Sintern und Verdichtung des wachsenden Oxids einschließen. Einer der wesentlichen Effekte dabei ist die Bildung einer Oxidkeramik, was z. B. im Falle einer Aluminiumoberfläche auf der Umwandlung von amorphem Aluminiumoxid in härtere kristalline Formen wie etwa Korund (Q-AI2O3) basiert. To produce a coating according to the invention, the component, which is either complete or whose surface to be coated consists of a light metal alloy, is immersed in an acidic or basic electrolyte bath with a specific aqueous electrolyte. The component forms the anode, the bath container usually the cathode. The voltage applied to the device is significantly higher than that of anodization (anodization), typically greater than 200 V. This locally exceeds the dielectric strength of the growing oxide layer, causing electrostatic discharges. The discharges form locally limited plasma reactors with high temperatures and high pressures that modify the growing oxide. The modification may include melting, flowing, re-solidification, sintering, and densification of the growing oxide. One of the main effects is the formation of an oxide ceramic, which z. For example, in the case of an aluminum surface, the conversion of amorphous alumina into harder crystalline forms such as corundum (Q-Al 2 O 3 ) is based.

Claims

Ansprüche claims
1. Verfahren zur Herstellung einer abrasiven Beschichtung (12; 22; 30) an einer Leichtmetall-Oberfläche eines Bauteils (10; 18; 26) einer Turbomaschine, insbesondere einer Verdichter- oder Turbinenschaufel, dadurch gekennzeichnet, dass die Beschichtung (12; 22; 30) durch eine Umwandlung der Oberfläche in eine Oxidkeramik gebildet wird.A method for producing an abrasive coating (12; 22; 30) on a light metal surface of a component (10; 18; 26) of a turbomachine, in particular a compressor or turbine blade, characterized in that the coating (12; 22; 30) is formed by a conversion of the surface into an oxide ceramic.
2. Verfahren nach Anspruch 1 , dadurch gekennzeichnet, dass die Oberfläche durch plasmaelektrolytische Oxidation umgewandelt wird.2. The method according to claim 1, characterized in that the surface is converted by plasma electrolytic oxidation.
3. Bauteil (10; 18; 26) für eine Turbomaschine, insbesondere eine Verdichter- oder Turbinenschaufel, dadurch gekennzeichnet, dass eine Leichtmetalloberfläche des Bauteils (10; 18; 26) eine abrasive Oxidkeramikbeschichtung (12; 22; 30) aufweist.3. component (10; 18; 26) for a turbomachine, in particular a compressor or turbine blade, characterized in that a light metal surface of the component (10; 18; 26) has an abrasive oxide ceramic coating (12; 22; 30).
4. Bauteil (10; 18; 26) nach Anspruch 3, dadurch gekennzeichnet, dass die Oxidkeramikbeschichtung (12; 22; 30) eine Panzerung oder einen Anlaufbelag darstellt.4. The component (10; 18; 26) according to claim 3, characterized in that the oxide ceramic coating (12; 22; 30) constitutes an armor or a tarpaulin covering.
5. Bauteil (10; 18; 26) nach Anspruch 3 oder 4, dadurch gekennzeichnet, dass die Oxidkeramikbeschichtung (12; 22; 30) nach einem Verfahren gemäß Anspruch 1 oder 2 hergestellt ist. A component (10; 18; 26) according to claim 3 or 4, characterized in that the oxide ceramic coating (12; 22; 30) is produced by a method according to claim 1 or 2.
PCT/DE2010/000255 2009-03-12 2010-03-10 Method for producing an abrasive coating and component for a turbomachine WO2010102609A1 (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996858A1 (en) * 2012-10-17 2014-04-18 Figeac Aero Manufacturing an aircraft structural part, which is a part of a seat rail, comprises surface treating the produced aircraft structural part by an oxidation electrolytic type micro arc to obtain a ceramic coating
WO2015158964A1 (en) * 2014-04-15 2015-10-22 Figeac Aero Method for producing aircraft structural parts and device for implementing same
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2492443A1 (en) * 2011-02-22 2012-08-29 Siemens Aktiengesellschaft Method of creating a protective coating for a rotor blade
EP2784268A1 (en) 2013-03-28 2014-10-01 MTU Aero Engines GmbH A turbine blade outer air seal comprising an abradable ceramic coating on the stator and the rotor respectively.
RS59879B1 (en) * 2014-12-04 2020-03-31 Meotec Gmbh & Co Kg Component of a turbocharger, combustion engine comprising said turbocharger and manufacturing method for a component of a turbocharger
DE102015212330A1 (en) * 2015-07-01 2017-01-19 Bosch Mahle Turbo Systems Gmbh & Co. Kg Process for coating an impeller, in particular a turbine wheel and / or compressor wheel, of an exhaust gas turbocharger

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH314013A (en) * 1952-10-15 1956-05-31 Hard Aluminium Surfaces Limite Process for the production of hard layers on aluminum and aluminum alloys by anodic oxidation
US5487825A (en) * 1991-11-27 1996-01-30 Electro Chemical Engineering Gmbh Method of producing articles of aluminum, magnesium or titanium with an oxide ceramic layer filled with fluorine polymers
DE19721730A1 (en) * 1997-05-24 1998-11-26 Anatoli J Prof Dr Vassiliev Process for producing hard oxide layers on the surface of a substrate based on light metals
US6264817B1 (en) * 1997-12-30 2001-07-24 R-Amtech International, Inc. Method for microplasma oxidation of valve metals and their alloys
EP1541717A2 (en) * 2003-11-22 2005-06-15 DaimlerChrysler AG Process for the manufacture of coated light-metal components that are exposed to a turbulent flow
US6919012B1 (en) * 2003-03-25 2005-07-19 Olimex Group, Inc. Method of making a composite article comprising a ceramic coating
DE202008010896U1 (en) * 2008-08-05 2008-10-23 AHC Oberflächentechnik GmbH Material, in particular components, with improved wear protection layers

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0661415A1 (en) 1993-12-17 1995-07-05 Sulzer Innotec Ag Sealing means between a housing and a rotating body
DE4432998C1 (en) 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Brush coating for metallic engine components and manufacturing process
DE19516815A1 (en) * 1995-05-08 1996-11-14 Electro Chem Eng Gmbh Ceramicized light alloy pistons for internal combustion engines
WO2000005493A1 (en) 1998-07-23 2000-02-03 Fedor Dmitrievich Muravlev Internal combustion engine, part thereof comprising a surface coating, and method and devices for producing said part
US6197178B1 (en) 1999-04-02 2001-03-06 Microplasmic Corporation Method for forming ceramic coatings by micro-arc oxidation of reactive metals
CN100503899C (en) * 2002-03-27 2009-06-24 岛屿涂层有限公司 Process for forming ceramic coatings on metals and alloys, and coatings produced by this process
DE102005040648A1 (en) * 2005-08-27 2007-03-01 Leybold Vacuum Gmbh Process for coating valve metal or alloy for e.g. aluminum or alloy rotor for turbomolecular pump involves vapor coating with optionally halogenated xylylene dimer and polymerization in capillary system of surface film of oxide ceramic
EP1967615A1 (en) * 2007-03-07 2008-09-10 Siemens Aktiengesellschaft Method for applying a heat insulation coating and turbine components with a heat insulation coating
EA200901050A1 (en) * 2007-04-02 2009-12-30 Владимир Никандрович Кокарев METHOD OF FORMATION ON THE SURFACE OF METAL PRODUCTS OF PROTECTIVE CERAMIC COATINGS

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH314013A (en) * 1952-10-15 1956-05-31 Hard Aluminium Surfaces Limite Process for the production of hard layers on aluminum and aluminum alloys by anodic oxidation
US5487825A (en) * 1991-11-27 1996-01-30 Electro Chemical Engineering Gmbh Method of producing articles of aluminum, magnesium or titanium with an oxide ceramic layer filled with fluorine polymers
DE19721730A1 (en) * 1997-05-24 1998-11-26 Anatoli J Prof Dr Vassiliev Process for producing hard oxide layers on the surface of a substrate based on light metals
US6264817B1 (en) * 1997-12-30 2001-07-24 R-Amtech International, Inc. Method for microplasma oxidation of valve metals and their alloys
US6919012B1 (en) * 2003-03-25 2005-07-19 Olimex Group, Inc. Method of making a composite article comprising a ceramic coating
EP1541717A2 (en) * 2003-11-22 2005-06-15 DaimlerChrysler AG Process for the manufacture of coated light-metal components that are exposed to a turbulent flow
DE202008010896U1 (en) * 2008-08-05 2008-10-23 AHC Oberflächentechnik GmbH Material, in particular components, with improved wear protection layers

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996858A1 (en) * 2012-10-17 2014-04-18 Figeac Aero Manufacturing an aircraft structural part, which is a part of a seat rail, comprises surface treating the produced aircraft structural part by an oxidation electrolytic type micro arc to obtain a ceramic coating
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
WO2015158964A1 (en) * 2014-04-15 2015-10-22 Figeac Aero Method for producing aircraft structural parts and device for implementing same

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