EP1097249B1 - Method for producing a plating for a metal component - Google Patents

Method for producing a plating for a metal component Download PDF

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Publication number
EP1097249B1
EP1097249B1 EP99939334A EP99939334A EP1097249B1 EP 1097249 B1 EP1097249 B1 EP 1097249B1 EP 99939334 A EP99939334 A EP 99939334A EP 99939334 A EP99939334 A EP 99939334A EP 1097249 B1 EP1097249 B1 EP 1097249B1
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EP
European Patent Office
Prior art keywords
slip
accordance
particles
layer
alitization
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EP99939334A
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German (de)
French (fr)
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EP1097249A1 (en
Inventor
Gerhard Wydra
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/18—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
    • C23C10/26—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions more than one element being diffused

Definitions

  • the invention relates to a method for producing armor for a metal Component that is provided on its surface.
  • Armorings or brushed coverings are e.g. on engine components, e.g. seal tips of labyrinth seals or blade tips, provided to their To counteract processing during brushing operations during operation. Since the Efficiency of a compressor or turbine largely depends on the gap size depends between the rotating and the standing component, it will be with increasing processing, e.g. the blade tips, reduced.
  • the armor usually works its way into an intake lining when the engine is operating an opposite, second component.
  • Such run-in coverings are abradable and mostly consist of a corrosion and erosion-resistant layer. Armoring of the engine component is particularly necessary if the Strength and hardness of the run-in coatings to increase erosion and temperature resistance is increased and the processing of the engine components additionally strengthened.
  • the armor ensures that the brushing process is minimal Gap is formed between the armor and the intake coating.
  • an MCrAIY powder is used applied by galvanic application to the component to be armored, where the necessary hard particles in the bath, e.g. BN, are included.
  • This Particles are etched free after application.
  • Such a process is expensive and consuming.
  • the subsequent etching is due to the lack Environmental compatibility and the necessary covering of the material disadvantageous.
  • a contour adapted to the component contour is used
  • the solder foil is attached to the component by gluing or the like.
  • BN particles are in the solder foil inserted.
  • the solder foil is then melted by heat treatment and the BN particles embedded in it. This procedure is also proportionate expensive and complex. In addition, the connection between the particles and the component is insufficient.
  • JP 55-82765 A it is known that consisting of a Ni or Co base alloy Substrate first with a mixture of ceramic, aluminum and metal powder to coat to ensure the heat resistance of the long-term high temperature exposure Improve layer. This is followed by a layer of one with one Binder-provided Ni powder, a heat treatment and the alitation by a Pack process.
  • the first layer should consist of the mixture containing ceramics prevent Al from penetrating into the substrate from the layer and hence the layer due to the depletion of Al their heat resistance is reduced.
  • JP 55-082759 A discloses a method for improving the thermal resistance a coating that is based on a substrate made of a Ni or Co-based alloy is applied, during coating a metal powder or an alloy powder mixed with ceramic elements and then applied to the substrate becomes. A binder and a subsequent heat treatment can be used be performed. The method is used for components of e.g. Gas turbines used, which are exposed to hot gas corrosion.
  • the object of the present invention is a method for manufacturing to create an armor of the type described at the outset, which can be manufactured can be carried out as easily as possible and high-quality armor results.
  • the solution to this problem is characterized according to the invention by the steps: Producing a slip by mixing at least one of the elements Ni or powder containing Cr or Ce with a binder; Apply the slip on the surface to be armored; Add ceramic hard particles to the slip before or after application of the slip, the size of which is chosen so that they protrude over the layer after alitation; Drying the slip at one Temperature from room temperature to 300 ° C; and alitizing the slip layer.
  • the advantage of this method is that the armor with a manufacturing technology simple processes can be applied to the component. Also are the hard, ceramic particles in the void fraction from 0 to 40% Slip layer embedded and firmly connected to the component.
  • the particles become the slip mixed before application to the surface to be armored. In this way the particles are evenly distributed in the slurry in suspension.
  • the particles are applied to the Slip used, e.g. a special arrangement of the particles on the to achieve armored surface.
  • Particles of BN, SiC or Al 2 O 3 are preferably used, since these are harder than the slip layer and can cut into run-in coatings or the like during operation.
  • the slip is made from a powder of MCrAIY is, the powder preferably in a grain size distribution of 5 to 120 microns is present.
  • the M stands for at least one of the elements Ni, Co, Pt or Pd. Instead of Y, Hf or Ce can also be used.
  • the slip is applied to the surface of the component to be armored preferably by spraying, brushing or dipping, which means that the process is manufacturing-related can be carried out easily and inexpensively.
  • spraying brushing or dipping
  • dipping a means that the process is manufacturing-related can be carried out easily and inexpensively.
  • Localized layers can also be applied in a simple manner, even geometrically apply complicated components. In addition, they are not expensive and complex Spraying or evaporation systems required
  • the slip layer is at a temperature of 750 to 1200 ° C is heat treated in argon or vacuum, the heat treating the Layer is preferably carried out over 1-4 hours using the slip layer to connect the component via diffusion.
  • the final step Alit the layer at a temperature between 800 and 1200 ° C and one Duration of 1 - 12 hours.
  • the metallic component preferably consists of an alloy based on nickel or cobalt, the component being an engine component, e.g. a turbine blade can, the armor is applied to the tip of the blade.
  • z is not growing using a MCrAlY powder to make a slurry into a suspension mixed with a conventional inorganic binder. That is in the suspension MCrAlY powder with 80 - 90 wt .-%, the binder with 5 - 10 wt .-% and additional Water with 5-7% by weight.
  • the grain sizes of the particles of the MCrAIY powder are between 5 and 120 ⁇ m. BN particles become into this flowable and sprayable mass introduced, the size of which is greater than that of the MCrAlY powder particles.
  • the blade tip of a turbine blade is made into a mass Nickel-based alloy immersed in such a way that on the to be armored Blade tip forms a slip layer.
  • it could contain the particles Slip e.g. also with a brush, forming a layer on the Blade tip to be applied.
  • the next step is the suspension in a suspension existing, still moist slip or the slip layer at room temperature dried over about 1.5 hours.
  • the dried slip layer is then heat-treated in a vacuum at 1000 ° C. for 1 hour, to connect the slip layer with the material of the turkey blade to achieve by diffusion.
  • the layer is then attached to Alitized at about 1100 ° C for 4 hours using a conventional method to make the compound the engine blade is further reinforced by diffusion and the slip layer to compact.
  • Al penetrates the layer and the base material the turbine blade and ensures both a firm connection of the layer with the component as well as for a firm connection of the spherical MCrAIY particles with each other.
  • the spherical MCrAlY particles at least sinter partly together.
  • Ni can also be made from the base material emerge and diffuse into the slip layer. Stand after the alitation step the hard, ceramic particles of BN or the like. Outward via the slip layer from and can protect them and the blade tip during operation.
  • the BN particles are firmly connected to the blade tip via the slip layer and can touch one another while brushing against the gas turbine Cut in the run-in covering to prevent damage to prevent the blade tip and the gap size between the rotating and to keep the standing component as low as possible.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft ein Verfahren zum Herstellen einer Panzerung für ein metall isches Bauteil, die auf dessen Oberfläche vorgesehen wird.The invention relates to a method for producing armor for a metal Component that is provided on its surface.

Panzerungen bzw. Anstreifbeläge werden z.B. an Triebwerksbauteilen, wie z.B. Dichtungsspitzen von Labyrinthdichtungen oder Schaufelspitzen, vorgesehen, um deren Abarbeitung bei Anstreifvorgängen während des Betriebs entgegenzuwirken. Da der Wirkungsgrad eines Verdichters oder einer Turbine in hohem Maße von der Spal tgröße zwischen dem rotierenden und dem stehenden Bauteil abhängt, wird er mit zunehmender Abarbeitung, z.B. der Schaufelspitzen, vermindert.Armorings or brushed coverings are e.g. on engine components, e.g. seal tips of labyrinth seals or blade tips, provided to their To counteract processing during brushing operations during operation. Since the Efficiency of a compressor or turbine largely depends on the gap size depends between the rotating and the standing component, it will be with increasing processing, e.g. the blade tips, reduced.

Die Panzerung arbeitet sich beim Betrieb des Triebwerks üblicherweise in einen Einlaufbelag eines gegenüberliegenden, zweiten Bauteils ein. Derartige Einlaufbeläge sind abreibbar und bestehen meist aus einer korrosions- und erosionsfesten Schicht. Eine Panzerung des Triebwerksbauteils ist insbesondere dann erforderlich, wenn die Festigkeit und Härte der Einlaufbeläge zur Steigerung der Erosions- und Temperaturbeständigkeit erhöht wird und sich die Abarbeitung der Triebwerksbauteile zusätzlich verstärkt. Durch die Panzerung wird erreicht, daß beim Anstreifvorgang ein minimaler Spalt zwischen der Panzerung und dem Einlaufbelag gebildet wird.The armor usually works its way into an intake lining when the engine is operating an opposite, second component. Such run-in coverings are abradable and mostly consist of a corrosion and erosion-resistant layer. Armoring of the engine component is particularly necessary if the Strength and hardness of the run-in coatings to increase erosion and temperature resistance is increased and the processing of the engine components additionally strengthened. The armor ensures that the brushing process is minimal Gap is formed between the armor and the intake coating.

Bei einem bekannten Verfahren zum Herstellen einer Panzerung wird ein MCrAIY-Pulver durch galvanisches Auftragen auf das zu panzernde Bauteil aufgebracht, w obei in dem Bad die erforderlichen harten Partikel, wie z.B. BN, enthalten sind. Diese Partikel werden nach dem Auftragen freigeätzt. Ein solches Verfahren ist teuer und aufwendig. Insbesondere das anschließende Ätzen ist aufgrund der mangelnden Umweltverträglichkeit und dem erforderlichen Abdecken des Werkstoffs nachteilig.In a known method for producing armor, an MCrAIY powder is used applied by galvanic application to the component to be armored, where the necessary hard particles in the bath, e.g. BN, are included. This Particles are etched free after application. Such a process is expensive and consuming. In particular, the subsequent etching is due to the lack Environmental compatibility and the necessary covering of the material disadvantageous.

Bei einem anderen bekannten Verfahren wird eine an die Bauteilkontur angepaßte Lotfolie durch Kleben od dgl. an dem Bauteil befestigt. Danach werden BN-Partikel in die Lotfolie eingesetzt. Anschließend wird die Lotfolie durch Wärmebehandlung geschmolzen und die BN-Partikel darin eingebettet. Auch dieses Verfahren ist verhäl t-nismäßig teuer und aufwendig. Zudem ist die Verbindung zwischen den Partikeln und dem Bauteil unzureichend.In another known method, a contour adapted to the component contour is used The solder foil is attached to the component by gluing or the like. Then BN particles are in the solder foil inserted. The solder foil is then melted by heat treatment and the BN particles embedded in it. This procedure is also proportionate expensive and complex. In addition, the connection between the particles and the component is insufficient.

Aus der JP 55-82765 A ist es bekannt, das aus einer Ni- oder Co-Basislegierung bestehende Substrat zunächst mit einer Mischung aus Keramik-, AI- und Metallpulver zu beschichten, um die Wärmebeständigkeit der langandauernd hochtemperaturbelasteten Schicht zu verbessern. Anschließend folgt eine Schicht aus einem mit einem Binder versehenen Ni-Pulver, eine Wärmebehandlung und das Alitieren durch ein Packverfahren. Dabei soll die erste Schicht aus der Keramik enthaltenden Mischung verhindern, daß Al von der Schicht in das Substrat eindringt und die Schicht mithin durch die Verarmung von Al ihre Wärmebeständigkeit ei nbüßt.From JP 55-82765 A it is known that consisting of a Ni or Co base alloy Substrate first with a mixture of ceramic, aluminum and metal powder to coat to ensure the heat resistance of the long-term high temperature exposure Improve layer. This is followed by a layer of one with one Binder-provided Ni powder, a heat treatment and the alitation by a Pack process. The first layer should consist of the mixture containing ceramics prevent Al from penetrating into the substrate from the layer and hence the layer due to the depletion of Al their heat resistance is reduced.

Die JP 55-082759 A offenbart ein Verfahren zur Verbesserung der thermischen B eständigkeit einer Beschichtung, die auf ein Substrat aus einer Ni- oder Co-Basislegierung aufgebracht wird, wobei beim Beschichten ein Metall- oder ein Legi erungspulver mit Keramikelementen gemischt und dann auf das Substrat aufgebracht wird. Es kann ein Bindemittel eingesetzt und eine anschließende Wärmebehandlung durchgeführt werden. Das Verfahren wird bei Bauteilen von z.B. Gasturbinen eing esetzt, die der Heißgaskorrosion ausgesetzt sind.JP 55-082759 A discloses a method for improving the thermal resistance a coating that is based on a substrate made of a Ni or Co-based alloy is applied, during coating a metal powder or an alloy powder mixed with ceramic elements and then applied to the substrate becomes. A binder and a subsequent heat treatment can be used be performed. The method is used for components of e.g. Gas turbines used, which are exposed to hot gas corrosion.

Die Aufgabe der vorliegenden Erfindung besteht darin, ein Verfahren zum Herstellen einer Panzerung der eingangs beschriebenen Gattung zu schaffen, das sich fertigungstechnisch möglichst einfach durchführen läßt und eine hochwertige Panzerung ergibt.The object of the present invention is a method for manufacturing to create an armor of the type described at the outset, which can be manufactured can be carried out as easily as possible and high-quality armor results.

Die Lösung dieser Aufgabe ist erfindungsgemäß durch die Schritte gekennzeichnet: Herstellen eines Schlickers durch Mischen eines wenigstens eines der Elemente Ni oder Cr oder Ce enthaltenden Pulvers mit einem Bindemittel; Auftragen des Schlikkers auf die zu panzernde Oberfläche; Zugabe keramischer Hartpartikel zum Schli kker vor oder nach dem Auftragen des Schlickers, deren Größe so gewählt wird, daß sie nach dem Alitieren über die Schicht vorstehen; Trocknen des Schlickers bei einer Temperatur von Raumtemperatur bis 300 °C; und Alitieren der Schlickerschicht. The solution to this problem is characterized according to the invention by the steps: Producing a slip by mixing at least one of the elements Ni or powder containing Cr or Ce with a binder; Apply the slip on the surface to be armored; Add ceramic hard particles to the slip before or after application of the slip, the size of which is chosen so that they protrude over the layer after alitation; Drying the slip at one Temperature from room temperature to 300 ° C; and alitizing the slip layer.

Der Vorteil dieses Verfahrens liegt darin, daß die Panzerung mit einem fertigungstechnisch einfachen Verfahren auf das Bauteil aufgebracht werden kann. Zudem sind die harten, keramischen Partikel in der einen Hohlraumanteil von 0 bis 40 % aufweisende Schlickerschicht eingebettet und mit dem Bauteil fest verbunden.The advantage of this method is that the armor with a manufacturing technology simple processes can be applied to the component. Also are the hard, ceramic particles in the void fraction from 0 to 40% Slip layer embedded and firmly connected to the component.

In einer bevorzugten Ausgestaltung des Verfahrens werden die Partikel dem Schli kker vor dem Auftragen auf die zu panzernde Oberfläche zugemischt. Auf diese Weise sind die Partikel in dem in einer Suspension vorliegenden Schlicker gleichmäßig ve rteilt.In a preferred embodiment of the method, the particles become the slip mixed before application to the surface to be armored. In this way the particles are evenly distributed in the slurry in suspension.

In einer alternativen Ausgestaltung werden die Partikel nach dem Auftragen in den Schlicker eingesetzt, wodurch sich z.B. eine spezielle Anordnung der Partikel auf der zu panzernden Oberfläche erzielen läßt.In an alternative embodiment, the particles are applied to the Slip used, e.g. a special arrangement of the particles on the to achieve armored surface.

Bevorzugt werden Partikel aus BN, SiC oder Al2O3 verwendet, da diese härter als die Schlickerschicht sind und sich beim Betrieb in Einlaufbeläge od. dgl. einschneiden können.Particles of BN, SiC or Al 2 O 3 are preferably used, since these are harder than the slip layer and can cut into run-in coatings or the like during operation.

Ferner ist bevorzugt, daß der Schlicker aus einem Pulver aus MCrAIY hergestellt wird, wobei das Pulver bevorzugt in einer Korngrößenverteilung von 5 bis 120 µm vorliegt. Das M steht dabei für wenigstens eines der Elemente Ni, Co, Pt oder Pd. Anstelle von Y kann auch Hf oder Ce verwendet werden.It is further preferred that the slip is made from a powder of MCrAIY is, the powder preferably in a grain size distribution of 5 to 120 microns is present. The M stands for at least one of the elements Ni, Co, Pt or Pd. Instead of Y, Hf or Ce can also be used.

Das Auftragen des Schlickers auf die zu panzernde Oberfläche des Bauteils erfolgt bevorzugt durch Spritzen, Pinseln oder Tauchen, wodurch sich das Verfahren fertigungstechnisch einfach und kostengünstig durchführen läßt. Durch diese Art des Auftragens lassen sich auf einfache Weise lokal begrenzte Schichten auch auf ge ometrisch komplizierten Bauteilen aufbringen. Zudem sind keine teuren und aufwe ndigen Spritz- oder Verdampfungsanlagen erforderlichThe slip is applied to the surface of the component to be armored preferably by spraying, brushing or dipping, which means that the process is manufacturing-related can be carried out easily and inexpensively. Through this kind of Localized layers can also be applied in a simple manner, even geometrically apply complicated components. In addition, they are not expensive and complex Spraying or evaporation systems required

Bevorzugt wird das Trocknen des Schlickers, der zusammen mit dem organischen oder anorganischen Bindemittel in einer Suspension vorliegt, über 0,5 - 4 Stunden durchgeführt, wobei sich eine Dauer von 1 - 2 Stunden als besonders vorteilhaft e rwiesen hat.It is preferred to dry the slip together with the organic or inorganic binder in a suspension, over 0.5 - 4 hours carried out, a duration of 1 - 2 hours proved to be particularly advantageous Has.

Bevorzugt ist ferner, daß die Schlickerschicht bei einer Temperatur von 750 bis 1200 °C in Argon oder Vakuum wärmebehandelt wird, wobei das Wärmebehandeln der Schicht bevorzugt über 1 - 4 Stunden durchgeführt wird, um die Schlickerschicht mit dem Bauteil über Diffusion zu verbinden.It is further preferred that the slip layer is at a temperature of 750 to 1200 ° C is heat treated in argon or vacuum, the heat treating the Layer is preferably carried out over 1-4 hours using the slip layer to connect the component via diffusion.

In einer bevorzugten Ausgestaltung des Verfahrens wird der abschließende Schritt Alitieren der Schicht bei einer Temperatur zwischen 800 und 1200 °C und einer Dauer von 1 - 12 Stunden durchgeführt.In a preferred embodiment of the method, the final step Alit the layer at a temperature between 800 and 1200 ° C and one Duration of 1 - 12 hours.

Bevorzugt besteht das metallische Bauteil aus einer Legierung auf Nickel- oder Kobaltbasis, wobei das Bauteil ein Triebwerksbauteil, z.B. eine Turbinenschaufel, sein kann, auf deren Schaufelspitze die Panzerung aufgebracht wird.The metallic component preferably consists of an alloy based on nickel or cobalt, the component being an engine component, e.g. a turbine blade can, the armor is applied to the tip of the blade.

Weitere bevorzugte Ausgestaltungen der Erfindung sind in den Unteransprüchen beschrieben.Further preferred embodiments of the invention are in the subclaims described.

Im folgenden wird die Erfindung anhand eines Beispiels näher erläutert.The invention is explained in more detail below using an example.

Bei einer Ausgestaltung des Verfahrens zum Herstellen einer Panzerung wird z unächst zur Herstellung eines Schlickers ein MCrAlY-Pulver zu einer Suspension mit einem üblichen anorganischen Bindemittel gemischt. In der Suspension liegt das MCrAlY-Pulver mit 80 - 90 Gew.-%, das Bindemittel mit 5 - 10 Gew.-% und zusätzlich Wasser mit 5 - 7 Gew.-% vor. Die Korngrößen der Partikel des MCrAIY-Pulvers liegen zwischen 5 und 120 µm. In diese fließfähige und spritzbare Masse werden BN-Partikel eingebracht, deren Größe über jener der MCrAlY-Pulverpartikel liegt.In one embodiment of the method for producing armor, z is not growing using a MCrAlY powder to make a slurry into a suspension mixed with a conventional inorganic binder. That is in the suspension MCrAlY powder with 80 - 90 wt .-%, the binder with 5 - 10 wt .-% and additional Water with 5-7% by weight. The grain sizes of the particles of the MCrAIY powder are between 5 and 120 µm. BN particles become into this flowable and sprayable mass introduced, the size of which is greater than that of the MCrAlY powder particles.

In die Masse wird anschließend die Schaufelspitze einer Turbinenschaufel aus einer Nickelbasislegierung in der Weise eingetaucht, daß sich auf der zu panzernden Schaufelspitze eine Schlickerschicht bildet. Alternativ könnte der die Partikel entha Itende Schlicker z.B. auch mit einem Pinsel unter Bildung einer Schicht auf die Schaufelspitze aufgetragen werden. Im nächsten Schritt wird der in einer Suspens ion vorliegende, noch feuchte Schlicker bzw. die Schlickerschicht bei Raumtemperatur über etwa 1,5 Stunden getrocknet.Then the blade tip of a turbine blade is made into a mass Nickel-based alloy immersed in such a way that on the to be armored Blade tip forms a slip layer. Alternatively, it could contain the particles Slip e.g. also with a brush, forming a layer on the Blade tip to be applied. The next step is the suspension in a suspension existing, still moist slip or the slip layer at room temperature dried over about 1.5 hours.

Die getrocknete Schlickerschicht wird dann bei 1000 °C 1 Stunde im Vakuum wärmebehandelt, um eine Verbindung der Schlickerschicht mit dem Werkstoff der Tu rbinenschaufel durch Diffusion zu erzielen. Daran anschließend wird die Schicht bei etwa 1100 °C 4 Stunden lang mit einem üblichen Verfahren alitiert, um die Verbindung der Triebwerksschaufel durch Diffusion weiter zu verstärken und die Schlickerschicht zu kompaktieren. Dabei dringt Al in die Schicht und in den Grundwerkstoff der Turbinenschaufel ein und sorgt sowohl für eine feste Verbindung der Schicht mit dem Bauteil als auch für eine feste Verbindung der kugligen MCrAIY-Partikel untereinander. Zudem sintern die in kugliger Form vorliegenden MCrAlY-Partikel wenigstens teilweise zusammen. Darüber hinaus kann auch Ni aus dem Grundwerkstoff austreten und in die Schlickerschicht diffundieren. Nach dem Alitierschritt stehen die harten, keramischen Partikel aus BN od. dgl. nach außen über die Schlickerschicht vor und können diese sowie die Schaufelspitze beim Betrieb schützen.The dried slip layer is then heat-treated in a vacuum at 1000 ° C. for 1 hour, to connect the slip layer with the material of the turkey blade to achieve by diffusion. The layer is then attached to Alitized at about 1100 ° C for 4 hours using a conventional method to make the compound the engine blade is further reinforced by diffusion and the slip layer to compact. Al penetrates the layer and the base material the turbine blade and ensures both a firm connection of the layer with the component as well as for a firm connection of the spherical MCrAIY particles with each other. In addition, the spherical MCrAlY particles at least sinter partly together. In addition, Ni can also be made from the base material emerge and diffuse into the slip layer. Stand after the alitation step the hard, ceramic particles of BN or the like. Outward via the slip layer from and can protect them and the blade tip during operation.

Die BN-Partikel sind über die Schlickerschicht fest mit der Schaufelspitze verbunden und können sich während des Betriebs der Gasturbine beim Anstreifen in einen g egenüberliegenden Einlaufbelag einschneiden, um auf diese Weise eine Beschädigung der Schaufelspitze zu verhindern und die Spaltgröße zwischen dem rotierenden und dem stehenden Bauteil möglichst gering zu halten.The BN particles are firmly connected to the blade tip via the slip layer and can touch one another while brushing against the gas turbine Cut in the run-in covering to prevent damage to prevent the blade tip and the gap size between the rotating and to keep the standing component as low as possible.

Claims (12)

  1. A process for the production of armour-plating for a turbine blade which is provided on the tip of the blade, characterised by the following steps:
    production of a slip by mixing a powder containing at least one of the elements Ni, Cr or Ce with a binding agent; application of the slip to the surface to be armour-plated; addition to the slip prior to or following application of hard ceramic particles of a size selected to ensure that they protrude above the layer after alitization; drying of the slip at a temperature of between room temperature and 300°C; alitization of the slip layer.
  2. A process in accordance with claim 1,
    characterised in that
    the particles are mixed together with the slip prior to application.
  3. A process in accordance with claim 1,
    characterised in that
    the particles are introduced into the slip following application.
  4. A process in accordance with one or more of the preceding claims,
    characterised in that
    particles of BN, SiC or Al2O3 are used.
  5. A process in accordance with one or more of the preceding claims,
    characterised in that
    the slip is produced from an MCrAlY powder.
  6. A process in accordance with one or more of the preceding claims,
    characterised in that
    the powder has a grain size distribution of 5 to 120 µm.
  7. A process in accordance with one or more of the preceding claims,
    characterised in that
    application is by means of spraying, painting or dipping.
  8. A process in accordance with one or more of the preceding claims,
    characterised in that
    drying takes place over 0.5 to 4 hours.
  9. A process in accordance with one or more of the preceding claims,
    characterised in that
    prior to alitization the slip layer is heat-treated at a temperature of 750 to 1200°C in argon or a vacuum.
  10. A process in accordance with claim 9,
    characterised in that
    the heat treatment is carried out over 1 to 4 hours.
  11. A process in accordance with one or more of the preceding claims,
    characterised in that
    the component consists of a nickel- or cobalt-based allay.
  12. A precess in accordance with one or more of the preceding claims,
    characterised in that
    alitization is carried out at a temperature of between 800 and 1200 °C and for a period of 1 to 12 hours.
EP99939334A 1998-06-20 1999-06-16 Method for producing a plating for a metal component Expired - Lifetime EP1097249B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19827620 1998-06-20
DE19827620A DE19827620C2 (en) 1998-06-20 1998-06-20 Process for the production of armor for a metallic component and its use
PCT/DE1999/001753 WO1999067438A1 (en) 1998-06-20 1999-06-16 Method for producing a plating for a metal component

Publications (2)

Publication Number Publication Date
EP1097249A1 EP1097249A1 (en) 2001-05-09
EP1097249B1 true EP1097249B1 (en) 2002-04-03

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EP99939334A Expired - Lifetime EP1097249B1 (en) 1998-06-20 1999-06-16 Method for producing a plating for a metal component

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EP (1) EP1097249B1 (en)
JP (1) JP2002518600A (en)
DE (2) DE19827620C2 (en)
ES (1) ES2176013T3 (en)
WO (1) WO1999067438A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19946650C2 (en) * 1999-09-29 2003-11-27 Mtu Aero Engines Gmbh Process for the production of armor for a metallic component
US7314674B2 (en) * 2004-12-15 2008-01-01 General Electric Company Corrosion resistant coating composition, coated turbine component and method for coating same
US7601400B2 (en) * 2005-03-10 2009-10-13 General Electric Company Liquid electrostatic coating composition comprising corrosion resistant metal particulates and method for using same
DE102005055200A1 (en) * 2005-11-19 2007-05-24 Mtu Aero Engines Gmbh Method for producing an inlet lining
DE102006028297A1 (en) 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Method of repairing inlet coverings
DE102007003735B4 (en) * 2007-01-25 2010-07-01 Mtu Aero Engines Gmbh Process for producing a protective coating and protective coating
DE102009008510A1 (en) * 2009-02-11 2010-08-12 Mtu Aero Engines Gmbh Coating and method for coating a workpiece
DE102014222024A1 (en) * 2014-10-29 2016-06-16 MTU Aero Engines AG Slip and method of making an oxidation and corrosion resistant diffusion layer
DE102015213555A1 (en) * 2015-07-20 2017-03-09 MTU Aero Engines AG Sealing ridge armor and method of making the same
DE102015221482A1 (en) * 2015-11-03 2017-05-04 MTU Aero Engines AG diffusion layers

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Publication number Priority date Publication date Assignee Title
GB1427054A (en) * 1973-09-19 1976-03-03 Rolls Royce Method of and mixture for aluminishing a metal surface
IT1083665B (en) * 1977-07-14 1985-05-25 Fiat Spa PROCEDURE FOR THE CREATION OF HIGH TEMPERATURE COATINGS ON METALS AND METAL ALLOYS
DE2910962C2 (en) * 1979-03-21 1981-07-02 Josef 4250 Bottrop Adam Method for applying a matrix-forming metallic layer with wear-resistant material embedded therein on a carrier
JPS58197203A (en) * 1982-05-12 1983-11-16 Toshiba Corp Formation of wear resistant coating layer
JPS6089503A (en) * 1983-10-21 1985-05-20 Toshiba Mach Co Ltd Coating method of wear resistant material

Also Published As

Publication number Publication date
ES2176013T3 (en) 2002-11-16
DE19827620A1 (en) 1999-12-23
WO1999067438A1 (en) 1999-12-29
JP2002518600A (en) 2002-06-25
DE19827620C2 (en) 2003-12-18
EP1097249A1 (en) 2001-05-09
DE59901139D1 (en) 2002-05-08

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