EP1061152A1 - Protective coating for turbine blades - Google Patents

Protective coating for turbine blades Download PDF

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Publication number
EP1061152A1
EP1061152A1 EP00112185A EP00112185A EP1061152A1 EP 1061152 A1 EP1061152 A1 EP 1061152A1 EP 00112185 A EP00112185 A EP 00112185A EP 00112185 A EP00112185 A EP 00112185A EP 1061152 A1 EP1061152 A1 EP 1061152A1
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EP
European Patent Office
Prior art keywords
protective layer
powder
phase
powders
coating
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP00112185A
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German (de)
French (fr)
Inventor
Hans-Peter Dr. Bossmann
Hans-Joachim Dr. Schmutzler
Marianne Dr. Sommer
Bettina Dipl.-Ing. Waschbüsch
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Alstom SA
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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Filing date
Publication date
Application filed by ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP1061152A1 publication Critical patent/EP1061152A1/en
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a protective layer for turbine blades according to the Preamble of claim 1.
  • Turbine blades of this type are in many cases made from a Ni-based alloy and directly charged with hot combustion gases to drive gas turbines. They are both thermal and mechanical stresses exposed during the operation of the gas turbine and stress cycles.
  • Around the turbine blades in front of corrosive chemical elements and compounds Protect the form of sulfur, oil ash, oxygen, alkaline earths and vanadium, which are carried by the hot gases are the turbine blades with one Provide protective layer.
  • MCrAlY layers are used for this, M represents Ni, Co, Fe or a combination of the elements mentioned.
  • the coating is made from a powder that contains the above metals contains. Such a powder is produced, for example, by atomization from the molten state, the powder particles then very be cooled down quickly.
  • MCrAIY protective layers have ⁇ -, ⁇ '-and after their heat treatment ⁇ phases in a ⁇ matrix. It cannot be avoided with these layers that the volume fractions of the individual phases change or change subsequently certain phases coarsen through Ostwald ripening, which through slow processes of balance settings is caused.
  • the invention has for its object a MCrAlY protective layer for turbine blades with improved properties.
  • the disadvantages mentioned at the outset become in the protective layer according to the invention avoided by using special powder mixtures.
  • the MCrAIY protective layer according to the invention is composed of at least two powders that are applied with the help of a thermal spraying process that a contiguous on the boundary surfaces of a turbine blade Coating is formed.
  • the two powders have different ones chemical compositions.
  • Protective layer are preferably a first powder with a first phase and used a second powder with a second phase, the protective layer this also has two phases at the application temperature.
  • the powders are also selected so that at least one chemical element in both Powders are included.
  • a first powder with a composition used which enables the formation of a Ni-base ⁇ matrix
  • the second powder has a composition of intermetallic aluminide phases of Ni, Fe, Pt or Ru.
  • the protective layer is a microstructure with a Ni-based ⁇ matrix and such ⁇ phase.
  • the protective layer can also be formed so that it is under the operating temperature that occurs in a gas turbine, a microstructure with ⁇ -, ⁇ -, ⁇ 'phases.
  • Two powders are also used to make this layer used, both of which have two phases.
  • the first powder is like this chosen that its composition is suitable for the formation of a ⁇ and a ⁇ phase is when it is exposed to the application temperature.
  • the second powder is chosen so that its composition the formation of a ⁇ and a ⁇ 'phase under the same conditions of use. After the heat treatment the desired three-phase microstructure is established in the layer.
  • This microstructure of the MCrAIY protective layer according to the invention has the known layers of this type have improved properties. Therefore changed The protective layer only changes slightly when it reaches the operating temperatures of a gas turbine is exposed. Adverse phase transformations, for example, the elimination of ⁇ phases are avoided in any case.
  • the only figure belonging to the description shows a turbine blade 1, which with a Cover 2 is provided in the form of a MCrAlY protective layer.
  • M stands here representative of Ni, Co, Fe or a combination of these chemical elements.
  • a first powder is used, which forms a ⁇ matrix forms.
  • a second powder is used, from which a ⁇ phase forms.
  • the two powders are mixed together or separately on the Turbine blade 1 applied.
  • the powders (not shown here) are selected so that contain at least one chemical element in both powders is.
  • a first powder is preferably used which forms a Ni-based ⁇ matrix contains the chemical elements Ni, Fe, Cr, Co, and Al, while the second Powder for the formation of intermetallic aluminide phases of Ni, Fe, Pt or Ru has chemical elements Ni, Fe, Pt, Ru and Al.
  • the powders used have preferably a particle size between 1 micron to 150 microns. After a heat treatment the coating 2 has a microstructure with these phases.
  • the protective layer can also be formed so that it is under the operating temperature that occurs in a gas turbine, a microstructure with ⁇ -, ⁇ -, ⁇ 'phases.
  • Two powders are also used to make this layer used, both of which form two phases.
  • the first powder is chosen so that its composition is suitable for the formation of a ⁇ and a ⁇ phase is when it is exposed to the application temperature.
  • the second powder is chosen so that its composition the formation of a ⁇ and a ⁇ 'phase under the same conditions of use. After the heat treatment the desired three-phase microstructure is established in the layer.

Abstract

MCrAlY protective layer has a coating (2) made of at least two metallic powders of different compositions on the boundary surfaces (1B) of the turbine blades. At least the same chemical element is present in both powders.

Description

Die Erfindung bezieht sich auf eine Schutzschicht für Turbinenschaufeln gemäß dem Oberbegriff des Patentanspruchs 1.The invention relates to a protective layer for turbine blades according to the Preamble of claim 1.

Turbinenschaufeln dieser Art werden in vielen Fällen aus einer Ni-Basislegierung hergestellt und zum Antrieb von Gasturbinen direkt mit heißen Verbrennungsgasen beaufschlagt. Sie sind dabei sowohl thermischen als auch mechanischen Beanspruchungen während des Betrieb der Gastrubine sowie Belastungszyklen ausgesetzt. Um die Turbinenschaufeln vor korrosiven chemischen Elementen und Verbindungen in Form von Schwefel, Ölaschen, Sauerstoff, Erdalkalien und Vanadium zu schützen, welche von den heißen Gasen mitgeführt werden, sind die Turbinenschaufeln mit einer Schutzschicht versehen. Hierfür werden MCrAlY-Schichten verwendet, wobei M stellvertretend für Ni, Co, Fe oder eine Kombination der genannten Elemente steht. Die Beschichtung wird aus einen Pulver hergestellt, das die oben genannten Metalle enthält. Die Herstellung eines solchen Pulvers erfolgt beispielsweise durch Verdüsung aus dem schmelzflüssigen Zustand, wobei die Pulverpartikel anschließend sehr schnell abgekühlt werden. Das Ausbilden der Beschichtung auf einer Turbinenschaufel erfolgt mit Luft-Plasmaspritzen, Vakuum-Plasmaspritzen, Niederdruck-Plasmaspritzen oder Hochgeschwindigkeitsflammspritzen. Die Mikrostruktur der aufgebrachten Schicht resultiert auf dem Herstellungsprozeß des Pulvers, dem Spritzprozeß, der chemischen Zusammensetzung und der Wärmebehandlung, wobei Art, Größe und Menge der Phasen nur geringfügig variiert werden können. Von Nachteil ist bei diesen bekannten Schichten, daß ihre mechanischen, thermomechanischen und physikalischen Eigenschaften durch bestimmte ungünstige Mikrostrukturen negativ beeinflußt werden. So weisen MCrAIY-Schutzschichten nach ihrer Wärmebehandlung β-, γ'-und σ-Phasen in einer γ-Matrix auf. Es läßt sich bei diesen Schichten nicht vermeiden, daß sich die Volumenanteile der einzelnen Phasen nachträglich verändern bzw. sich bestimmte Phasen durch Ostwald Reifung vergröbern, was durch langsame Prozesse der Gleichgewichtseinstellungen verursacht wird.Turbine blades of this type are in many cases made from a Ni-based alloy and directly charged with hot combustion gases to drive gas turbines. They are both thermal and mechanical stresses exposed during the operation of the gas turbine and stress cycles. Around the turbine blades in front of corrosive chemical elements and compounds Protect the form of sulfur, oil ash, oxygen, alkaline earths and vanadium, which are carried by the hot gases are the turbine blades with one Provide protective layer. MCrAlY layers are used for this, M represents Ni, Co, Fe or a combination of the elements mentioned. The coating is made from a powder that contains the above metals contains. Such a powder is produced, for example, by atomization from the molten state, the powder particles then very be cooled down quickly. Forming the coating on a turbine blade done with air plasma spraying, vacuum plasma spraying, low pressure plasma spraying or high speed flame spraying. The microstructure of the applied Layer results on the manufacturing process of the powder, the spraying process, the chemical composition and the heat treatment, whereby type, size and the amount of phases can only be varied slightly. A disadvantage is these known layers that their mechanical, thermomechanical and physical Properties adversely affected by certain unfavorable microstructures become. MCrAIY protective layers have β-, γ'-and after their heat treatment σ phases in a γ matrix. It cannot be avoided with these layers that the volume fractions of the individual phases change or change subsequently certain phases coarsen through Ostwald ripening, which through slow processes of balance settings is caused.

Der Erfindung liegt die Aufgabe zugrunde, eine MCrAlY-Schutzschicht für Turbinenschaufeln mit verbesserten Eigenschaften aufzuzeigen.The invention has for its object a MCrAlY protective layer for turbine blades with improved properties.

Diese Aufgabe wird durch die Merkmale des Patentanspruchs 1 gelöst.This object is achieved by the features of patent claim 1.

Bei der erfindungsgemäßen Schutzschicht werden die eingangs genannten Nachteile durch den Einsatz von speziellen Pulvermischungen vermieden. Für die Ausbildung der erfindungsgemäßen MCrAIY-Schutzschicht wird von wenigstens zwei Pulvern ausgegangen, die mit Hilfe eines thermischen Spritzprozesses so aufgetragen werden, daß auf den Begrenzungsflächen einer Turbinenschaufel ein zusammenhängender Überzug ausgebildet wird. Die beiden Pulver haben erfindungsgemäß unterschiedliche chemische Zusammensetzungen. Für die Ausbildung der erfindungsgemäßen Schutzschicht werden bevorzugt ein erstes Pulver mit einer ersten Phase und ein zweites Pulver mit einer zweiten Phase verwendet, wobei die Schutzschicht diese beiden Phasen bei der Anwendungstemperatur ebenfalls aufweist. Die Pulver werden zudem so ausgewählt, daß mindestens ein gleiches chemisches Element in beiden Pulvern enthalten ist. Beispielsweise wird ein erstes Pulver mit einer Zusammensetzung verwendet, welches die Bildung einer Ni-Basis γ-Matrix ermöglicht, während das zweite Pulver eine Zusammensetzung aufweist, aus der intermetallische Aluminid-Phasen von Ni, Fe, Pt oder Ru gebildet werden. Nach einer Wärmebehandlung weist die Schutzschicht eine Mikrostruktur mit einer Ni-Basis γ-Matrix und einer solchen β-Phase auf.The disadvantages mentioned at the outset become in the protective layer according to the invention avoided by using special powder mixtures. For training the MCrAIY protective layer according to the invention is composed of at least two powders that are applied with the help of a thermal spraying process that a contiguous on the boundary surfaces of a turbine blade Coating is formed. According to the invention, the two powders have different ones chemical compositions. For the formation of the invention Protective layer are preferably a first powder with a first phase and used a second powder with a second phase, the protective layer this also has two phases at the application temperature. The powders are also selected so that at least one chemical element in both Powders are included. For example, a first powder with a composition used, which enables the formation of a Ni-base γ matrix, while the second powder has a composition of intermetallic aluminide phases of Ni, Fe, Pt or Ru. After heat treatment points the protective layer is a microstructure with a Ni-based γ matrix and such β phase.

Erfindungsgemäß kann die Schutzschicht auch so ausgebildet werden, daß sie unter der Betriebstemperatur, die in einer Gasturbine auftritt, eine Mikrostruktur mit β-, γ-, γ'-Phasen aufweist. Für die Herstellung diese Schicht werden ebenfalls zwei Pulver verwendet, die beide jeweils zwei Phasen aufweisen. Dabei wird das erste Pulver so gewählt, daß seine Zusammensetzung für die Bildung einer β- und einer γ-Phase geeignet ist, wenn es der Anwendungstemperatur ausgesetzt ist. Das zweite Pulver wird so gewählt, daß seine Zusammensetzung die Bildung einer γ- und einer γ'- Phase unter den gleichen Anwendungsbedingungen ermöglicht. Nach der Wärmebehandlung der Schicht stellt sich die gewünschte dreiphasige Mikrostruktur ein.According to the invention, the protective layer can also be formed so that it is under the operating temperature that occurs in a gas turbine, a microstructure with β-, γ-, γ 'phases. Two powders are also used to make this layer used, both of which have two phases. The first powder is like this chosen that its composition is suitable for the formation of a β and a γ phase is when it is exposed to the application temperature. The second powder is chosen so that its composition the formation of a γ and a γ 'phase under the same conditions of use. After the heat treatment the desired three-phase microstructure is established in the layer.

Diese Mikrostruktur der erfindungsgemäßen MCrAIY-Schutzschicht besitzt gegenüber den bekannten Schichten dieser Art verbesserte Eigenschaften. Deshalb verändert sich die Schutzschicht nur geringfügig, wenn sie den Betriebstemperaturen einer Gasturbine ausgesetzt wird. Nachteilige Phasentransformationen beispielsweise die Ausscheidung von σ-Phasen werden in jeden Fall vermieden.This microstructure of the MCrAIY protective layer according to the invention has the known layers of this type have improved properties. Therefore changed The protective layer only changes slightly when it reaches the operating temperatures of a gas turbine is exposed. Adverse phase transformations, for example, the elimination of σ phases are avoided in any case.

Weitere erfinderische Merkmale sind in den abhängigen Ansprüchen gekennzeichnet.Further inventive features are characterized in the dependent claims.

Die Erfindung wird nachfolgend an Hand von einer Zeichnung näher erläutert.The invention is explained below with reference to a drawing.

Die einzige zur Beschreibung gehörige Figur zeigt eine Turbinenschaufel 1, die mit einem Überzug 2 in Form einer MCrAlY-Schutzschicht versehen ist. M steht hierbei stellvertretend für Ni, Co, Fe oder einer Kombination dieser chemischen Elemente. Für die Ausbildung des Überzugs 2 wird ein erstes Pulver verwendet, aus dem sich eine γ-Matrix bildet. Desweiteren wird eine zweites Pulver benutzt, aus dem sich eine β-Phase bildet. Die beiden Pulver werden zusammen oder getrennt voneinander auf die Turbinenschaufel 1 aufgetragen. Die Pulver (hier nicht dargestellt) werden so ausgewählt, daß mindestens ein gleiches chemisches Element in beiden Pulvern enthalten ist. Vorzugsweise wird ein erstes Pulver verwendet, das zur Bildung einer Ni-Basis γ-Matrix die chemischen Elemente Ni, Fe, Cr, Co, und Al enthält, während das zweite Pulver zur Bildung von intermetallischen Aluminid-Phasen von Ni, Fe, Pt oder Ru die chemischen Elemente Ni, Fe, Pt, Ru und Al aufweist. Die verwendeten Pulver weisen vorzugsweise eine Teilchengröße zwischen 1 µm bis 150 µm auf. Nach einer Wärmebehandlung des Überzugs 2 weist dieser eine Mikrostruktur mit diesen Phasen auf. The only figure belonging to the description shows a turbine blade 1, which with a Cover 2 is provided in the form of a MCrAlY protective layer. M stands here representative of Ni, Co, Fe or a combination of these chemical elements. For the formation of the coating 2, a first powder is used, which forms a γ matrix forms. Furthermore, a second powder is used, from which a β phase forms. The two powders are mixed together or separately on the Turbine blade 1 applied. The powders (not shown here) are selected so that contain at least one chemical element in both powders is. A first powder is preferably used which forms a Ni-based γ matrix contains the chemical elements Ni, Fe, Cr, Co, and Al, while the second Powder for the formation of intermetallic aluminide phases of Ni, Fe, Pt or Ru has chemical elements Ni, Fe, Pt, Ru and Al. The powders used have preferably a particle size between 1 micron to 150 microns. After a heat treatment the coating 2 has a microstructure with these phases.

Erfindungsgemäß kann die Schutzschicht auch so ausgebildet werden, daß sie unter der Betriebstemperatur, die in einer Gasturbine auftritt, eine Mikrostruktur mit β-, γ-, γ'-Phasen aufweist. Für die Herstellung diese Schicht werden ebenfalls zwei Pulver verwendet, die beide jeweils zwei Phasen bilden. Dabei wird das erste Pulver so gewählt, daß seine Zusammensetzung für die Bildung einer β- und einer γ-Phase geeignet ist, wenn es der Anwendungstemperatur ausgesetzt ist. Das zweite Pulver wird so gewählt, daß seine Zusammensetzung die Bildung einer γ- und einer γ'- Phase unter den gleichen Anwendungsbedingungen ermöglicht. Nach der Wärmebehandlung der Schicht stellt sich die gewünschte dreiphasige Mikrostruktur ein.According to the invention, the protective layer can also be formed so that it is under the operating temperature that occurs in a gas turbine, a microstructure with β-, γ-, γ 'phases. Two powders are also used to make this layer used, both of which form two phases. The first powder is chosen so that its composition is suitable for the formation of a β and a γ phase is when it is exposed to the application temperature. The second powder is chosen so that its composition the formation of a γ and a γ 'phase under the same conditions of use. After the heat treatment the desired three-phase microstructure is established in the layer.

Claims (7)

MCrAlY-Schutzschicht für Turbinenschaufeln (1), dadurch gekennzeichnet, daß auf die Begrenzungsflächen (1B) der Turbinenschaufel (1) ein Überzug (2) aus mindestens zwei metallischen Pulvern verschiedener Zusammensetzungen aufgetragen ist, und daß mindestens ein gleiches chemisches Element in beiden Pulvern enthalten ist.MCrAlY protective layer for turbine blades (1), characterized in that a coating (2) of at least two metallic powders of different compositions is applied to the boundary surfaces (1B) of the turbine blade (1) and that at least one chemical element is contained in both powders is. Schutzschicht nach Anspruch 1, dadurch gekennzeichnet, daß das erste Pulver eine Zusammensetzung für die Bildung einer ersten Phase und das zweite Pulver eine Zusammensetzung für die Bildung einer zweiten Phase aufweist, welche der Überzug (2) bei der Betriebstemperatur einer Gasturbine besitzt.Protective layer according to claim 1, characterized in that the first Powder a composition for the formation of a first phase and the second powder has a composition for the formation of a second phase which the Has coating (2) at the operating temperature of a gas turbine. Schutzschicht nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß das erste Pulver die chemischen Elemente Ni, Fe, Cr, Co, Al und das zweite Pulver die chemischen Elemente Ni, Fe, Pt, Ru und Al enthält.Protective layer according to one of claims 1 or 2, characterized in that that the first powder contains the chemical elements Ni, Fe, Cr, Co, Al and the second Powder containing the chemical elements Ni, Fe, Pt, Ru and Al. Schutzschicht nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der Überzug (2) eine Ni-Basis γ-Matrix und intermetallische Aluminid-Phasen von Ni, Fe, Pt oder Ru aufweist.Protective layer according to one of claims 1 to 3, characterized in that that the coating (2) has a Ni-based γ matrix and intermetallic aluminide phases Ni, Fe, Pt or Ru has. Schutzschicht nach Anspruch 1, dadurch gekennzeichnet, daß das erste Pulver eine Zusammensetzung für die Bildung einer β- und einer γ-Phase und das zweite Pulver eine Zusammensetzung für die Bildung einer γ- und einer γ'- Phase aufweist, und daß der Überzug (2) unter Anwendungsbedingungen eine dreiphasige Mikrostruktur mit β-, γ-, γ'-Phasen hat.Protective layer according to claim 1, characterized in that the first Powder a composition for the formation of a β and a γ phase and that second powder a composition for the formation of a γ and a γ 'phase has, and that the coating (2) a three-phase under conditions of use Has microstructure with β, γ, γ 'phases. Schutzschicht nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die beiden Pulver zur Ausbildung des Überzugs (2) gemeinsam oder voneinander getrennt aufgebracht sind. Protective layer according to one of claims 1 to 5, characterized in that the two powders to form the coating (2) together or from each other are applied separately. Schutzschicht nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Teilchengröße der beiden Pulver 1 µm bis 150 µm beträgt.Protective layer according to one of claims 1 to 6, characterized in that the particle size of the two powders is 1 µm to 150 µm.
EP00112185A 1999-06-12 2000-06-07 Protective coating for turbine blades Withdrawn EP1061152A1 (en)

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Application Number Priority Date Filing Date Title
DE19926818A DE19926818B4 (en) 1999-06-12 1999-06-12 Protective layer for turbine blades
DE19926818 1999-06-12

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