EP2331723B1 - Process for coating a turbine blade or vane of a gas turbine - Google Patents

Process for coating a turbine blade or vane of a gas turbine Download PDF

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Publication number
EP2331723B1
EP2331723B1 EP09776056A EP09776056A EP2331723B1 EP 2331723 B1 EP2331723 B1 EP 2331723B1 EP 09776056 A EP09776056 A EP 09776056A EP 09776056 A EP09776056 A EP 09776056A EP 2331723 B1 EP2331723 B1 EP 2331723B1
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EP
European Patent Office
Prior art keywords
particles
lacquer
vane
coating
turbine
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EP09776056A
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German (de)
French (fr)
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EP2331723A1 (en
Inventor
Heinrich Walter
Horst Pillhöfer
Michael Strasser
Karl-Heinz Manier
Max Morant
Richard Lange
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2331723A1 publication Critical patent/EP2331723A1/en
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Classifications

    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • C23C10/32—Chromising
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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

Definitions

  • the invention relates to a method for coating a turbine blade of a gas turbine according to the preamble of patent claim 1.
  • a turbine blade of a gas turbine engine and a method of coating a turbine blade of a gas turbine engine wherein the turbine blade has an airfoil, a blade root, and a platform positioned between the airfoil and the blade root.
  • a wear protection coating namely a corrosion resistant protective coating
  • the wear protection coating being an MCrAlY coating.
  • This coating coating has a chromium content of between 10% and 40% by weight.
  • a turbine blade whose outer surface is coated with aluminum.
  • An inner surface, in particular cooling holes, has a chromium coating with a chromium concentration of between 30 and 60% by weight.
  • GB2424 032 A is a turbine blade is known, the blade root is erhieten with Chromium. Then one is applied directly to the chromium coating aluminum or MCrAlY coating.
  • the present invention based on the problem to provide a novel method for coating a turbine blade.
  • the method according to the invention for coating a turbine blade is defined in claim 1.
  • the method according to the invention comprises at least the following steps: a) provision of a turbine blade; b) projecting at least one lacquer layer on at least a portion of the Matbinenschaufel, wherein the paint chromium particles and / or chromium alloy particles, halides and binders; c) drying the applied paint at a temperature between 50 ° C and 600 ° C with decomposition of the binder; d) subsequent reaction bonding at a temperature of between 900 ° C and 1160 ° C.
  • the life of turbine blades can be increased and effective protection against hot gas corrosion or sulfidation can be realized, this protection being increased by a factor of 6 compared with the base material of the turbine blade. Even with a complex contouring of the underside of the platform and the transition region between the underside of the platform and the blade root, a good coating can be ensured.
  • Fig. 1 1 shows a schematic representation of a turbine blade 10 of a gas turbine designed as a rotor blade, the turbine blade 10 comprising an airfoil 11, a blade root 12 and a platform 13 positioned between the airfoil 11 and the blade root 12.
  • the turbine blade 10 is coated on an underside 14 of the platform and / or on a transition region 15 between the underside 14 of the platform 13 and the blade root 12 with a corrosion protection coating.
  • the anticorrosive coating is a diffusion coating having a chromium content in the surface region of more than 30 wt .-%.
  • the anticorrosive coating is formed as a graded, ductile Inchromiertik whose chromium content in the surface region is preferably between 40 wt .-% and 95 wt .-%.
  • An ⁇ -chromium phase fraction having a chromium content of more than 30% by weight of the anticorrosive coating is between 5% by weight and 50% by weight.
  • the remainder of the chromium content of the corrosion protection coating is formed by other chromium phases and by chromium dissolved in the mixed crystal of the base material.
  • the ⁇ -chromium phase content of the chromium content of the anticorrosive coating has a Vickers hardness of less than 800.
  • the total layer thickness of the anticorrosive coating is between 5 ⁇ m and 120 ⁇ m, preferably between 15 ⁇ m and 50 ⁇ m.
  • At least one coating layer is applied to the underside 14 of the platform 13 and / or the transition region 15 between the underside 14 of the platform 13 and the blade root 12, wherein the paint chromium particles and / or chromium alloy particles, halides and binder.
  • the particle size of the chromium particles and / or chromium alloy particles is in particular up to 20 microns.
  • the halides of the paint are preferably metal chloride particles, in particular CrCl 2 particles and / or CrCl 3 particles.
  • the binder of the paint is preferably acrylic or glycol based or polyvinyl based.
  • an acrylic acid ester or methacrylic acid ester, a methyl cellulose compound, a polysaccharide, a polyvinyl alcohol, a polyvinyl ether, a polyvinyl acetate, a polyvinylpyrrolidone or a colloidal silica mixture may be used to provide an aqueous dispersion. It is also possible to provide a nonaqueous dispersion as a lacquer.
  • At least one lacquer layer of this lacquer is applied to the underside 14 of the platform 13 and / or the transition region 15 between platform 13 and blade root 12, preferably several lacquer layers are applied to these regions of the turbine blade, each lacquer layer having a layer thickness between 2 microns and 50 microns is applied. It is preferably applied between one and ten layers of paint, in particular between three and six layers of paint.
  • the chromium particles and / or chromium alloy particles are reacted with molten chromium chloride particles at a temperature between 900 ° C. and 1160 ° C., the reaction being carried out for a period of time between 15 min and 15 h.
  • Subsequent to the reaction bonding is preferably a diffusion annealing of the formed pure chromium layer at a temperature between 950 ° C and 1200 ° C for the diffusion of chromium into the surface of the previously coated with the paint areas of the turbine blade, in which case preferably Cl compounds be withdrawn.
  • the diffusion annealing takes place for a time between 30 minutes and 12 hours.
  • the diffusion annealing is preferably carried out in a hydrogen atmosphere or in an inert gas partial pressure atmosphere with a pressure between ambient pressure, ie in about 1000 mbar, and 0.01 mbar.
  • the diffusion annealing preferably takes place in a halide atmosphere, the hydrogen atmosphere or the inert gas partial pressure atmosphere then having a gaseous addition of metal chloride particles, in particular a gaseous addition of CrCl 2 particles and / or CrCl 3 particles.
  • Argon is preferably used as the inert gas.

Description

Die Erfindung betrifft eine ein Verfahren zum Beschichten einer Turbinenschaufel einer Gasturbine nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a method for coating a turbine blade of a gas turbine according to the preamble of patent claim 1.

Aus der EP 1 111 192 B1 ist eine Turbinenschaufel einer Gasturbine und ein Verfahren zum Beschichten einer Turbinenschaufel einer Gasturbine bekannt, wobei die Turbinenschaufel ein Schaufelblatt, einen Schaufelfuß und eine zwischen dem Schaufelblatt und dem Schaufelfuß positionierte Plattform aufweist. In diesem Stand der Technik wird vorgeschlagen, die Turbinenschaufel an einer Unterseite der Plattform und an einem Übergangsbereich zwischen der Unterseite der Plattform und dem Schaufelfuß mit einer Verschleißschutzbeschichtung, nämlich einer korrosionsbeständigen Schutzbeschichtung, zu beschichten, wobei die Verschleißschutzbeschichtung eine MCrAlY-Überzugsbeschichtung ist. Diese Überzugsbeschichtung weist einen Chromgehalt zwischen 10 Gew.-% und 40 Gew.-% auf.From the EP 1 111 192 B1 For example, a turbine blade of a gas turbine engine and a method of coating a turbine blade of a gas turbine engine are known, wherein the turbine blade has an airfoil, a blade root, and a platform positioned between the airfoil and the blade root. In this prior art, it is proposed to coat the turbine blade at an underside of the platform and at a transition region between the underside of the platform and the blade root with a wear protection coating, namely a corrosion resistant protective coating, the wear protection coating being an MCrAlY coating. This coating coating has a chromium content of between 10% and 40% by weight.

Aus der WO 2005/106064 A1 ist eine Turbinenschaufel bekannt, deren Außenfläche mit Aluminium beschichtet ist. Eine Innenfläche, insbesondere Kühlbohrungen, weist eine Chrombeschichtung mit einer Chromkonzentration zwischen 30 und 60 Gew.-% auf.From the WO 2005/106064 A1 is known a turbine blade whose outer surface is coated with aluminum. An inner surface, in particular cooling holes, has a chromium coating with a chromium concentration of between 30 and 60% by weight.

Aus GB2424 032 A ist eine Turbinenschaufel bekannt, deren Schaufelfuß mit Chromium beschietet ist. Anschließend wird einer direkt auf die Chromienbeschictung Aluminium oder MCrAlY Beschichtung aufgetragen.Out GB2424 032 A is a turbine blade is known, the blade root is erhieten with Chromium. Then one is applied directly to the chromium coating aluminum or MCrAlY coating.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zum Beschichten einer Turbinenschaufel zu schaffen.On this basis, the present invention based on the problem to provide a novel method for coating a turbine blade.

Das erfindungsgemäße Verfahren zum Beschichten einer Turbinenschaufel ist in Patentanspruch1 definiert. Das erfindungsgemäße Verfahren umfasst zumindest die folgenden Schritte: a) Bereitstellen einer Turbinenschaufel; b) Aufragen mindestens einer Lackschicht auf zumindest einen Bereich der Türbinenschaufel, wobei der Lack Chrom-Partikel und/oder Chromlegierungs-Partikel, Halogenide und Bindemittel umfasst; c) Trocken des aufgetragenen Lacks bei einer Temperatur zwischen 50°C und 600°C unter Zersetzen des Bindemittels; d) anschließendes Reaktionsverbinden bei einer Temperatur zwischen 900°C und 1160°C.The method according to the invention for coating a turbine blade is defined in claim 1. The method according to the invention comprises at least the following steps: a) provision of a turbine blade; b) projecting at least one lacquer layer on at least a portion of the Türbinenschaufel, wherein the paint chromium particles and / or chromium alloy particles, halides and binders; c) drying the applied paint at a temperature between 50 ° C and 600 ° C with decomposition of the binder; d) subsequent reaction bonding at a temperature of between 900 ° C and 1160 ° C.

Mit der hier vorliegenden Erfindung kann die Lebensdauer von Turbinenschaufeln erhöht und ein effektiver Schutz gegen Heißgaskorrosion bzw. Sulfidation realisiert werden, wobei dieser Schutz gegenüber dem Grundwerkstoff der Turbinenschaufel um den Faktor 6 vergrößert ist. Auch bei einer komplexen Konturierung der Unterseite der Plattform sowie des Übergangsbereichs zwischen der Unterseite der Plattform und den Schaufelfuß kann eine gute Beschichtung gewährleistet werden.With the present invention, the life of turbine blades can be increased and effective protection against hot gas corrosion or sulfidation can be realized, this protection being increased by a factor of 6 compared with the base material of the turbine blade. Even with a complex contouring of the underside of the platform and the transition region between the underside of the platform and the blade root, a good coating can be ensured.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
eine schematisierte Ansicht einer Turbinenschaufel einer Gasturbine.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a schematic view of a turbine blade of a gas turbine.

Fig. 1 zeigt eine schematisierte Darstellung einer als Laufschaufel ausgebildeten Turbinenschaufel 10 einer Gasturbine, wobei die Turbinenschaufel 10 ein Schaufelblatt 11, einen Schaufelfuß 12 und eine zwischen dem Schaufelblatt 11 und dem Schaufelfuß 12 positionierte Plattform 13 umfasst. Die Turbinenschaufel 10 ist an einer Unterseite 14 der Plattform und/oder an einem Übergangsbereich 15 zwischen der Unterseite 14 der Plattform 13 und dem Schaufelfuß 12 mit einer Korrosionsschutzbeschichtung beschichtet. Fig. 1 1 shows a schematic representation of a turbine blade 10 of a gas turbine designed as a rotor blade, the turbine blade 10 comprising an airfoil 11, a blade root 12 and a platform 13 positioned between the airfoil 11 and the blade root 12. The turbine blade 10 is coated on an underside 14 of the platform and / or on a transition region 15 between the underside 14 of the platform 13 and the blade root 12 with a corrosion protection coating.

Im Sinne der hier vorliegenden Erfindung ist die Korrosionsschutzbeschichtung eine Diffusionsbeschichtung mit einen Chromgehalt im Oberflächenbereich von mehr als 30 Gew.-%. Die Korrosionsschutzbeschichtung ist dabei als gradierte, duktile Inchromierschicht ausgebildet, deren Chromgehalt im Oberflächenbereich vorzugsweise zwischen 40 Gew.-% und 95 Gew.-% beträgt.For the purposes of the present invention, the anticorrosive coating is a diffusion coating having a chromium content in the surface region of more than 30 wt .-%. The anticorrosive coating is formed as a graded, ductile Inchromierschicht whose chromium content in the surface region is preferably between 40 wt .-% and 95 wt .-%.

Ein α-Chrom-Phasenanteil mit einem Chromgehalt von mehr als 30 Gew.-% der Korrosionsschutzbeschichtung beträgt dabei zwischen 5 Gew.-% und 50 Gew.-%. Der Rest des Chromgehalts der Korrosionsschutzbeschichtung ist durch andere Chrom-Phasen und durch im Mischkristall des Grundwerkstoff gelöstes Chrom gebildet.An α-chromium phase fraction having a chromium content of more than 30% by weight of the anticorrosive coating is between 5% by weight and 50% by weight. The remainder of the chromium content of the corrosion protection coating is formed by other chromium phases and by chromium dissolved in the mixed crystal of the base material.

Der α-Chrom-Phasenanteil des Chromgehalts der Korrosionsschutzbeschichtung weist eine Vickershärte von weniger als 800 auf.The α-chromium phase content of the chromium content of the anticorrosive coating has a Vickers hardness of less than 800.

Die Gesamtschichtdicke der Korrosionsschutzbeschichtung beträgt zwischen 5 µm und 120 µm, vorzugsweise zwischen 15 µm und 50 µm.The total layer thickness of the anticorrosive coating is between 5 μm and 120 μm, preferably between 15 μm and 50 μm.

Beim Beschichten einer Turbinenschaufel einer Gasturbine im Bereich der Unterseite 14 der Plattform 13 und/oder im Übergangsbereich 15 zwischen der Unterseite 14 der Plattform 13 und dem Schäufelfuß 12 wird so vorgegangen, dass zuerst eine Turbinenschaufel bereitgestellt wird.When coating a turbine blade of a gas turbine in the region of the underside 14 of the platform 13 and / or in the transition region 15 between the underside 14 of the platform 13 and the blade foot 12, the procedure is such that a turbine blade is first provided.

Anschließend an das Bereitstellen der Turbinenschaufel wird mindestens eine Lackschicht auf die Unterseite 14 der Plattform 13 und/oder den Übergangsbereich 15 zwischen der Unterseite 14 der Plattform 13 und dem Schaufelfuß 12 aufgetragen, wobei der Lack Chrom-Partikel und/oder Chromlegierungs-Partikel, Halogenide und Bindemittel umfasst.Subsequent to the provision of the turbine blade, at least one coating layer is applied to the underside 14 of the platform 13 and / or the transition region 15 between the underside 14 of the platform 13 and the blade root 12, wherein the paint chromium particles and / or chromium alloy particles, halides and binder.

Die Partikelgröße der Chrom-Partikel und/oder Chromlegierungs-Partikel beträgt dabei insbesondere bis zu 20 µm. Bei den Halogeniden des Lacks handelt es sich vorzugsweise um Metallchlorid-Partikel, insbesondere um CrCl2-Partikel und/oder um CrCl3-Partikel. Das Bindemittel des Lacks ist vorzugsweise auf Acrylbasis oder Glycolbasis oder Polyvinylbasis ausgebildet.The particle size of the chromium particles and / or chromium alloy particles is in particular up to 20 microns. The halides of the paint are preferably metal chloride particles, in particular CrCl 2 particles and / or CrCl 3 particles. The binder of the paint is preferably acrylic or glycol based or polyvinyl based.

Der Lack weist vorzugsweise folgende Zusammensetzung auf:

  • 25 bis 95 Gew.-% Bindemittel;
  • 0,1 bis 10 Gew.-% CrC12-Partikel und/oder um CrC13-Partikel;
  • im Rest Chrom-Partikel und/oder Chromlegierungs-Partikel.
The paint preferably has the following composition:
  • From 25 to 95% by weight of binder;
  • 0.1% to 10% by weight of CrC12 particles and / or CrC13 particles;
  • in the rest, chromium particles and / or chromium alloy particles.

Als Bindemittel für den Lack kann zur Bereitstellung einer wässrigen Dispersion ein Acrylsäureester oder Methacrylsäureester, eine Methyl-Cellulose-Verbindung, ein Polysacharid, ein Polyvinylalkohol, ein Polyvinylether, ein Polyvinylacetat, ein Polyvinylpyrrolidon oder eine kolloidale Kieselsäure-Mischung verwendet werden. Es kann auch eine nichtwässrige Dispersion als Lack bereitgestellt werden.As the binder for the paint, an acrylic acid ester or methacrylic acid ester, a methyl cellulose compound, a polysaccharide, a polyvinyl alcohol, a polyvinyl ether, a polyvinyl acetate, a polyvinylpyrrolidone or a colloidal silica mixture may be used to provide an aqueous dispersion. It is also possible to provide a nonaqueous dispersion as a lacquer.

Wie bereits erwähnt, wird mindestens eine Lackschicht aus diesem Lack auf die Unterseite 14 der Plattform 13 und/oder den Übergangsbereich 15 zwischen Plattform 13 und Schaufelfuß 12 aufgetragen, vorzugsweise werden mehrere Lackschichten auf diese Bereiche der Turbinenschaufel aufgetragen, wobei jede Lackschicht mit einer Schichtdicke zwischen 2 µm und 50 µm aufgetragen wird. Es werden vorzugsweise zwischen ein und zehn Lackschichten, insbesondere zwischen drei und sechs Lackschichten, aufgetragen.As already mentioned, at least one lacquer layer of this lacquer is applied to the underside 14 of the platform 13 and / or the transition region 15 between platform 13 and blade root 12, preferably several lacquer layers are applied to these regions of the turbine blade, each lacquer layer having a layer thickness between 2 microns and 50 microns is applied. It is preferably applied between one and ten layers of paint, in particular between three and six layers of paint.

Anschließend an das Auftragen der oder jeder Lackschicht auf die entsprechenden Bereiche der Turbinenschaufel erfolgt ein Trocknen des aufgetragenen Lacks bei einer Temperatur zwischen 50°C und 600°C unter Zersetzen des Bindemittels. Dieses Trocknen erfolgt dabei für eine Zeitspanne zwischen 5 min und 240 min.Subsequent to the application of the or each lacquer layer to the corresponding areas of the turbine blade drying of the applied paint is carried out at a temperature between 50 ° C and 600 ° C with decomposition of the binder. This drying takes place for a period of time between 5 min and 240 min.

Anschließend an das Trocknen des Lacks erfolgt ein Reaktionsverbinden der Chrom-Partikel und/oder Chromlegierungs-Partikel mit schmelzflüssigen Chromchlorid-Partikeln bei einer Temperatur zwischen 900°C und 1160°C, wobei das Reaktionsverbinden für eine Zeitspanne zwischen 15 min und 15 h erfolgt.Subsequent to the drying of the varnish, the chromium particles and / or chromium alloy particles are reacted with molten chromium chloride particles at a temperature between 900 ° C. and 1160 ° C., the reaction being carried out for a period of time between 15 min and 15 h.

Anschließend an das Reaktionsverbinden erfolgt vorzugsweise ein Diffusionsglühen der sich ausgebildeten Rein-Chrom-Schicht bei einer Temperatur zwischen 950°C und 1200°C zur Eindiffusion des Chroms in die Oberfläche der zuvor mit dem Lack beschichteten Bereiche der Turbinenschaufel, wobei hierbei vorzugsweise Cl-Verbindungen entzogen werden.Subsequent to the reaction bonding is preferably a diffusion annealing of the formed pure chromium layer at a temperature between 950 ° C and 1200 ° C for the diffusion of chromium into the surface of the previously coated with the paint areas of the turbine blade, in which case preferably Cl compounds be withdrawn.

Das Diffusionsglühen erfolgt für eine Zeitspanne zwischen 30 min und 12 h. Das Diffusionsglühen wird vorzugsweise in einer Wasserstoffatmosphäre oder in einer Inertgas-Partialdruckatmosphäre mit einem Druck zwischen Umgebungsdruck, also in etwa 1000 mbar, und 0,01 mbar durchgeführt.The diffusion annealing takes place for a time between 30 minutes and 12 hours. The diffusion annealing is preferably carried out in a hydrogen atmosphere or in an inert gas partial pressure atmosphere with a pressure between ambient pressure, ie in about 1000 mbar, and 0.01 mbar.

Das Diffusionsglühen erfolgt vorzugsweise in einer Halogenidatmosphäre, wobei dann die Wasserstoffatmosphäre oder die Inertgas-Partialdruckatmosphäre einen gasförmigen Zusatz von Metallchlorid-Partikeln, insbesondere einen gasförmigen Zusatz von CrCl2-Partikeln und/oder CrCl3-Partikeln aufweist. Als Inertgas findet vorzugsweise Argon Verwendung. The diffusion annealing preferably takes place in a halide atmosphere, the hydrogen atmosphere or the inert gas partial pressure atmosphere then having a gaseous addition of metal chloride particles, in particular a gaseous addition of CrCl 2 particles and / or CrCl 3 particles. Argon is preferably used as the inert gas.

Claims (14)

  1. Method for coating a turbine vane (10) of a gas turbine, wherein the turbine vane has a vane blade (11), a vane foot (12), and a platform (13) located between the vane blade and the vane foot, namely to apply a corrosion protection coating on at least one region of the turbine vane, in particular on a lower side (14) of the platform and/or a transition region (15) between the lower side of the platform and the vane foot, with at least the following steps:
    a) providing a turbine vane (10);
    b) applying at least a lacquer coating on at least one region of the turbine vane, wherein the lacquer comprises chrome particles and/or chrome-alloy particles, halogenides, and binding material;
    c) drying of the applied lacquer at a temperature between 50°C and 600°C while decomposing the binding material;
    d) subsequently reaction binding at a temperature between 900°C and 1160°C.
  2. Method according to claim 1,
    characterized in that
    the lacquer applied in step b) comprises metal chloride particles as halogenides.
  3. Method according to claim 1 or 2,
    characterized in that
    the lacquer applied in step b) comprises CrCl2-particles and/or CrCl3-particles as metal chloride particles.
  4. Method according to one of the preceding claims,
    characterized in that
    the lacquer applied in the step b) comprises a binding material on acrylic basis or glycol basis or polyvinyl basis.
  5. Method according to one of the preceding claims,
    characterized in that,
    the drying in step c) is carried out for a time period between 5 min and 240 min.
  6. Method according to one of the preceding claims,
    characterized in that
    the reaction binding in step d) is carried out for a time period between 15 min and 15 hours.
  7. Method according to one of the preceding claims,
    characterized in that
    after the reaction binding a diffusion glowing is carried out.
  8. Method according to claim 7,
    characterized in that
    the diffusion glowing occurs for a time period between 30 min and 12 hours at a temperature between 950°C and 1200°C.
  9. Method according to claim 7 or 8,
    characterized in that
    the diffusion glowing is carried out in a halogenide atmosphere.
  10. Method according to claim 7, 8 or 9
    characterized in that,
    the diffusion glowing is carried out in a hydrogen atmosphere or in an inert gas partial pressure atmosphere with a gaseous add-on of metal chloride particles with a pressure between ambient pressure, thus circa 1000 mbar, and 0.01 mbar.
  11. Method according to claim 10,
    characterized in that
    the hydrogen atmosphere or the inert gas partial pressure atmosphere has a gaseous add-on of CrCl2-particles and/or CrCl3-particles.
  12. Method according to one of the preceding claims,
    characterized in that
    1 to 10 lacquer layers are applied with a thickness of 2 µm to 50 µm of each lacquer layer.
  13. Method according to claim 12
    characterized in that
    3 to 6 lacquer layers are applied.
  14. Method according to one of the preceding claims,
    characterized in that
    the content of chrome in the surface region is adjusted to a value between 40% by mass and 95% by mass.
EP09776056A 2008-08-27 2009-08-01 Process for coating a turbine blade or vane of a gas turbine Active EP2331723B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200810039969 DE102008039969A1 (en) 2008-08-27 2008-08-27 Turbine blade of a gas turbine and method for coating a turbine blade of a gas turbine
PCT/DE2009/001095 WO2010022698A1 (en) 2008-08-27 2009-08-01 Turbine blade or vane of a gas turbine and process for coating a turbine blade or vane of a gas turbine

Publications (2)

Publication Number Publication Date
EP2331723A1 EP2331723A1 (en) 2011-06-15
EP2331723B1 true EP2331723B1 (en) 2013-02-27

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EP (1) EP2331723B1 (en)
DE (1) DE102008039969A1 (en)
WO (1) WO2010022698A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL2741983T3 (en) 2011-08-11 2016-05-31 Mol Belting Systems Inc Conveyor roller
DE102011089131A1 (en) * 2011-12-20 2013-06-20 Mtu Aero Engines Gmbh Diffusion coating process and chromium layer made therewith
US20140004372A1 (en) * 2012-06-28 2014-01-02 Kevin L. Collins Chromium diffusion coating
DE102012015586A1 (en) 2012-08-08 2014-05-15 MTU Aero Engines AG Duplex phase CrAl coating for improved corrosion / oxidation protection
DE102014222024A1 (en) 2014-10-29 2016-06-16 MTU Aero Engines AG Slip and method of making an oxidation and corrosion resistant diffusion layer
DE102017212075A1 (en) * 2017-07-14 2019-01-17 MTU Aero Engines AG Process for coating a component for the hot gas duct of a turbomachine
DE102017213553A1 (en) 2017-08-04 2019-02-07 MTU Aero Engines AG VESSEL FOR FLOW MACHINE WITH VARIOUS DIFFUSION PROTECTION LAYERS AND METHOD OF MANUFACTURING THEREOF

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE303503T1 (en) 1999-12-20 2005-09-15 United Technologies Corp ITEMS WITH CORROSION-RESISTANT COATINGS
GB0409486D0 (en) * 2004-04-28 2004-06-02 Diffusion Alloys Ltd Coatings for turbine blades
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
GB2439313B (en) * 2006-06-24 2011-11-23 Siemens Ag Method of protecting a component against hot corrosion and a component protected by said method

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Publication number Publication date
EP2331723A1 (en) 2011-06-15
WO2010022698A1 (en) 2010-03-04
DE102008039969A1 (en) 2010-03-04

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