EP2228461A1 - Component coating - Google Patents

Component coating Download PDF

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Publication number
EP2228461A1
EP2228461A1 EP09002778A EP09002778A EP2228461A1 EP 2228461 A1 EP2228461 A1 EP 2228461A1 EP 09002778 A EP09002778 A EP 09002778A EP 09002778 A EP09002778 A EP 09002778A EP 2228461 A1 EP2228461 A1 EP 2228461A1
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EP
European Patent Office
Prior art keywords
component
component coating
rhenium
layer
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Withdrawn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
EP09002778A
Other languages
German (de)
French (fr)
Inventor
Alessandro Casu
Dr. Werner Stamm
Ulrich Wörz
Dr. Jaap Van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP09002778A priority Critical patent/EP2228461A1/en
Priority to PCT/EP2010/050937 priority patent/WO2010097262A1/en
Publication of EP2228461A1 publication Critical patent/EP2228461A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the invention relates to a component coating, a component with the component coating, methods for producing the component coating and the use of the component coating as an abrasion and wear protection layer.
  • Components that are exposed to high loads are often provided with protective layers to protect them in particular from wear.
  • Such components are used for example in turbines, where they are exposed in a chemically aggressive atmosphere at high temperatures strong mechanical stresses.
  • wear protection layers or systems based on titanium nitride or titanium carbide are applied to the components.
  • Such wear protection systems are for example in the WO 2005/031038 A1 described.
  • fretting wear with superimposed vibrations or by a high temperature load to damage.
  • Other known wear protection layers based on tungsten carbide chromium or chromium carbide nickel chromium also do not have the necessary temperature resistance.
  • wear layers which serve as run-in layers. They are applied to the surface of a stationary component to serve as a seal between the stationary and a relative to this moving component, after the moving component during operation of the turbine has been ground in abrasion layer.
  • abrasion layers are for example in the EP 1 253 294 A2 described.
  • the known abrasion layers do not have the necessary capacity.
  • the cubic boron nitride wear layers used in many cases oxidize very rapidly under the influence of hot gas, which adversely affects their functionality and service life.
  • the object of the invention was therefore to provide a component coating, the thermal, chemical and mechanical stresses, such as occur in turbines, resists.
  • component coatings containing rhenium diboride meet these requirements.
  • component coatings that consist of either rhenium diboride or rhenium diboride particles have a high temperature resistance and, moreover, are chemically and mechanically highly resistant. This is partly due to the very high hardness of rhenium diboride.
  • the component coating contains rhenium diboride particles, these may be embedded in a ductile matrix, wherein the ductile matrix may in particular consist of MCrAlY.
  • the ductile matrix may in particular consist of MCrAlY.
  • the proportion of rhenium diboride particles in the component coating can be from 1 to 70, preferably from 2 to 40, more preferably from 4 to 25, and especially preferably from 6 to 10,% by weight.
  • the component coating may be 10 to 500, preferably 50 to 400 and particularly preferably 100 to 300 ⁇ m thick.
  • the component coating when it is rhenium diboride, it may be 0.1 to 600 ⁇ m thick.
  • the component may preferably be a turbine component, for example a spring clip.
  • the invention also provides a process for producing a component coating in which rhenium diboride particles are embedded in a ductile matrix of MCrAlY.
  • a mixture of MCrAlY and rhenium diboride is sprayed onto a component.
  • the mixture can be sprayed onto the component by means of HVOF or cold spray.
  • the invention also encompasses a process for producing a component coating consisting of rhenium diboride.
  • a layer of rhenium and a layer of boron which preferably each have a thickness in the range from 0.1 to 400 .mu.m, are first applied to a component in any order one above the other. Subsequently, the layers of rhenium and boron are heated in vacuo at a temperature> 1000 ° C until a layer of rhenium diboride has formed from the layers.
  • rhenium diboride from rhenium and boron, for example, is generally in Hsiu-Ying Chung et al., Science, April 20, 2007, Vol. 316, no. 5823, pp. 436-439 described.
  • the layer of rhenium and / or the layer of boron can be vapor-deposited or sprayed onto the component. In particular, this can be done with the aid of HVOF and / or cold spray.
  • the component coating as an abrasion or wear protection layer on a component.
  • the component may in particular be a turbine component.
  • the spring clip 1 is provided with a component coating 2 according to the invention as a wear protection layer.
  • the component coating 2 consists of rhenium diboride.
  • the Spring Clip 1 serves to realize the transition of the basket and transition of the turbine blade with as little leakage as possible. It also provides the necessary axial degree of freedom to allow the burner of the turbine thermal expansion. Therefore, it constantly moves relative to the transition and needs at the provided with the component coating contact surface high wear resistance. Function and structure of a Spring Clip are for example in the US 2007/0012043 A1 described.
  • a layer of rhenium is first deposited on the Spring Clip 1 by means of HVOF. Then a layer of boron is applied to the layer of rhenium. This can again be done by HVOF. Alternatively, the order of the layers on the spring clip 1 can also be reversed, i. First, the boron layer and then on this rhenium layer can be applied.
  • the Spring Clip 1 with the rhenium and the boron layer is then heated in vacuo at a temperature> 1000 ° C until a layer of rhenium diboride has formed from the two layers.
  • Temperature and duration of the heat treatment depend, inter alia, on the thicknesses of the rhenium and the boron layer and, in this specific case, can easily be determined experimentally by a person skilled in the art with the aid of a few experiments.
  • the component coating 2 of rhenium diboride thus obtained has a high temperature resistance and is above it also chemically resistant. Above all, it is due to their high hardness mechanically extremely strong.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The component coating (2) useful as abrasion- and wear protection layer for spring clip of turbine (1), consists of rhenium diboride particles (6-10 wt.%), which are imbedded in a ductile matrix. The ductile matrix is made of alloy of chromium, aluminum and yttrium (MCrAlY). The thickness of the component coating is 0.1-600 mu m. An independent claim is included for a method for the production of component coating.

Description

Die Erfindung betrifft eine Bauteilbeschichtung, ein Bauteil mit der Bauteilbeschichtung, Verfahren zur Herstellung der Bauteilbeschichtung und die Verwendung der Bauteilbeschichtung als Abrieb- und Verschleißschutzschicht.The invention relates to a component coating, a component with the component coating, methods for producing the component coating and the use of the component coating as an abrasion and wear protection layer.

Bauteile, die hohen Belastungen ausgesetzt sind, werden häufig mit Schutzschichten versehen, um sie insbesondere vor Verschleiß schützen sollen. Derartige Bauteile kommen beispielsweise in Turbinen zum Einsatz, wo sie in einer chemisch aggressiven Atmosphäre bei hohen Temperaturen starken mechanischen Beanspruchungen ausgesetzt sind.Components that are exposed to high loads are often provided with protective layers to protect them in particular from wear. Such components are used for example in turbines, where they are exposed in a chemically aggressive atmosphere at high temperatures strong mechanical stresses.

Insbesondere dann, wenn zwei solche Bauteile eine Relativbewegung zueinander ausführen, kann reibender und hämmernder Verschleiß auftreten. Darüber hinaus kann es zu dem so genannten "Fretting" kommen, worunter man die gleichzeitige Abnutzung und Korrosion von Bauteilen versteht.In particular, when two such components perform a relative movement to each other, rubbing and hammering wear can occur. In addition, it can come to the so-called "fretting", which means the simultaneous wear and corrosion of components.

Um solche Beschädigungen zu vermeiden, werden bisher spezielle Verschleißschutzschichten bzw. -systeme auf Basis von Titannitrid oder Titancarbid auf die Bauteile aufgebracht. Derartige Verschleißschutzsysteme sind beispielsweise in der WO 2005/031038 A1 beschrieben. Allerdings kommt es auch bei diesen Systemen durch Reibverschleiß mit überlagerten Schwingungen oder durch eine hohe Temperaturbelastung zu Beschädigungen. Andere bekannte Verschleißschutzschichten auf Basis von Wolframcarbid-Chrom oder Chromcarbid-Nickel-Chrom weisen ebenfalls nicht die notwendige Temperaturbeständigkeit auf.In order to avoid such damage, so far special wear protection layers or systems based on titanium nitride or titanium carbide are applied to the components. Such wear protection systems are for example in the WO 2005/031038 A1 described. However, it also comes with these systems by fretting wear with superimposed vibrations or by a high temperature load to damage. Other known wear protection layers based on tungsten carbide chromium or chromium carbide nickel chromium also do not have the necessary temperature resistance.

Eine weitere Gruppe von Bauteilbeschichtungen, die insbesondere beim Turbinenbau von Bedeutung haben, sind Abriebschichten, die als Einlaufschichten dienen. Sie werden auf die Oberfläche eines ruhenden Bauteils aufgebracht, um als Dichtung zwischen dem ruhenden und einem sich relativ zu diesem bewegenden Bauteil zu dienen, nachdem sich das bewegende Bauteil während des Betriebes der Turbine in Abriebschicht eingeschliffen hat. Derartige Abriebschichten sind beispielsweise in der EP 1 253 294 A2 beschrieben.Another group of component coatings, which are of particular importance in turbine construction, are wear layers which serve as run-in layers. They are applied to the surface of a stationary component to serve as a seal between the stationary and a relative to this moving component, after the moving component during operation of the turbine has been ground in abrasion layer. Such abrasion layers are for example in the EP 1 253 294 A2 described.

Die bekannten Abriebschichten weisen jedoch nicht die notwendige Belastbarkeit auf. So oxidieren die in vielen Fällen zum Einsatz kommenden Abriebschichten aus kubischem Bornitrid sehr schnell unter Heißgaseinfluss, was ihre Funktionalität und Lebensdauer negative beeinflusst.However, the known abrasion layers do not have the necessary capacity. For example, the cubic boron nitride wear layers used in many cases oxidize very rapidly under the influence of hot gas, which adversely affects their functionality and service life.

Aufgabe der Erfindung war es daher, eine Bauteilbeschichtung bereit zu stellen, die thermischen, chemischen und mechanischen Belastungen, wie sie etwa in Turbinen auftreten, widersteht.The object of the invention was therefore to provide a component coating, the thermal, chemical and mechanical stresses, such as occur in turbines, resists.

Überraschender Weise wurde gefunden, das Bauteilbeschichtungen, die Rheniumdiborid enthalten, diesen Anforderungen genügen. So weisen Bauteilbeschichtungen, die entweder aus Rheniumdiborid bestehen oder Rheniumdiboridpartikel enthalten eine hohe Temperaturbeständigkeit auf und sind darüber hinaus chemisch wie mechanisch hoch widerstandsfähig. Dies ist unter anderem durch die sehr große Härte des Rheniumdiborids bedingt.Surprisingly, it has been found that component coatings containing rhenium diboride meet these requirements. For example, component coatings that consist of either rhenium diboride or rhenium diboride particles have a high temperature resistance and, moreover, are chemically and mechanically highly resistant. This is partly due to the very high hardness of rhenium diboride.

Wenn die Bauteilbeschichtung Rheniumdiboridpartikel enthält, können diese in einer duktilen Matrix eingebettet sein, wobei die duktile Matrix insbesondere aus MCrAlY bestehen kann. Beispielsweise kann als MCrAlY SC 2464 verwendet werden. Vorteilhafterweise kann der Anteil der Rheniumdiboridpartikel in der Bauteilbeschichtung kann 1 bis 70, bevorzugt 2 bis 40, besonders bevorzugt 4 bis 25 und insbesondere bevorzugt 6 bis 10 Gew.-% betragen. Die Bauteilbeschichtung kann 10 bis 500, bevorzugt 50 bis 400 und besonders bevorzugt 100 bis 300 µm dick sein.If the component coating contains rhenium diboride particles, these may be embedded in a ductile matrix, wherein the ductile matrix may in particular consist of MCrAlY. For example, as MCrAlY SC 2464 can be used. Advantageously, the proportion of rhenium diboride particles in the component coating can be from 1 to 70, preferably from 2 to 40, more preferably from 4 to 25, and especially preferably from 6 to 10,% by weight. The component coating may be 10 to 500, preferably 50 to 400 and particularly preferably 100 to 300 μm thick.

Wenn die Bauteilbeschichtung aus Rheniumdiborid besteht, kann sie insbesondere 0,1 bis 600 µm dick sein.In particular, when the component coating is rhenium diboride, it may be 0.1 to 600 μm thick.

Ein weiterer Aspekt der Erfindung betrifft ein Bauteil, das die Bauteilbeschichtung aufweist. Bei dem Bauteil kann es sich bevorzugt um ein Turbinenbauteil, beispielsweise um eine Spring Clip handeln.Another aspect of the invention relates to a component having the component coating. The component may preferably be a turbine component, for example a spring clip.

Gegenstand der Erfindung ist auch ein Verfahren zur Herstellung einer Bauteilbeschichtung, bei der Rheniumdiboridpartikel in einer duktilen Matrix aus MCrAlY eingebettet sind. Zur Herstellung einer solchen Bauteilbeschichtung wird eine Mischung aus MCrAlY und Rheniumdiborid auf ein Bauteil aufgesprüht. Vorzugsweise kann die Mischung mittels HVOF oder Coldspray auf das Bauteil aufgesprüht werden.The invention also provides a process for producing a component coating in which rhenium diboride particles are embedded in a ductile matrix of MCrAlY. To produce such a component coating, a mixture of MCrAlY and rhenium diboride is sprayed onto a component. Preferably, the mixture can be sprayed onto the component by means of HVOF or cold spray.

Von der Erfindung ist auch ein Verfahren zur Herstellung einer Bauteilbeschichtung, die aus Rheniumdiborid besteht, umfasst. Bei diesem Verfahren werden zunächst auf ein Bauteil in beliebiger Reihenfolge übereinander eine Schicht aus Rhenium und eine Schicht aus Bor aufgebracht, die vorzugsweise jeweils eine Dicke im Bereich von 0,1 bis 400µm aufweisen. Anschließend werden die Schichten aus Rhenium und Bor im Vakuum bei einer Temperatur > 1000°C solange erhitzt, bis sich aus den Schichten eine Schicht aus Rheniumdiborid gebildet hat.The invention also encompasses a process for producing a component coating consisting of rhenium diboride. In this method, a layer of rhenium and a layer of boron, which preferably each have a thickness in the range from 0.1 to 400 .mu.m, are first applied to a component in any order one above the other. Subsequently, the layers of rhenium and boron are heated in vacuo at a temperature> 1000 ° C until a layer of rhenium diboride has formed from the layers.

Die Herstellung von Rheniumdiborid aus Rhenium und Bor ist beispielsweise allgemein in Hsiu-Ying Chung et al., Science 20. April 2007, Vol. 316, no. 5823, pp. 436-439 beschrieben.The preparation of rhenium diboride from rhenium and boron, for example, is generally in Hsiu-Ying Chung et al., Science, April 20, 2007, Vol. 316, no. 5823, pp. 436-439 described.

Vorzugsweise kann die Schicht aus Rhenium und/oder die Schicht aus Bor auf das Bauteil aufgedampft oder aufgespritzt werden. Insbesondere kann dies mit Hilfe von HVOF und/oder Coldspray erfolgen.Preferably, the layer of rhenium and / or the layer of boron can be vapor-deposited or sprayed onto the component. In particular, this can be done with the aid of HVOF and / or cold spray.

Weitere Gegenstände der Erfindung sind schließlich die Verwendung der Bauteilbeschichtung als Abrieb- oder als Verschleißschutzschicht auf einem Bauteil. Bei dem Bauteil kann es sich insbesondere um ein Turbinenbauteil handeln.Further objects of the invention are finally the use of the component coating as an abrasion or wear protection layer on a component. The component may in particular be a turbine component.

Die Erfindung wird im Folgenden anhand eines Ausführungsbeispiels unter Bezugnahme auf die Zeichnung näher erläutert. Die einzige Figur der Zeichnung zeigt schematisch im Schnitt eine Spring Clip einer Turbinenschaufel.The invention will be explained in more detail below with reference to an embodiment with reference to the drawing. The sole figure of the drawing shows schematically in section a spring clip of a turbine blade.

Die Spring Clip 1 ist mit einer erfindungsgemäßen Bauteilbeschichtung 2 als Verschleißschutzschicht versehen. Die Bauteilbeschichtung 2 besteht aus Rheniumdiborid.The spring clip 1 is provided with a component coating 2 according to the invention as a wear protection layer. The component coating 2 consists of rhenium diboride.

Die Spring Clip 1 dient dazu den Übergang von Basket und Transition der Turbinenschaufel mit möglichst wenig Leckage zu realisieren. Sie gewährleistet auch den nötigen axialen Freiheitsgrad, um dem Brenner der Turbine eine thermische Dehnung zu erlauben. Daher bewegt sie sich ständig relativ zum Transition und benötigt an der mit der Bauteilbeschichtung versehenen Kontaktfläche eine hohe Verschleißfestigkeit. Funktion und Aufbau einer Spring Clip sind beispielsweise in der US 2007/0012043 A1 beschrieben.The Spring Clip 1 serves to realize the transition of the basket and transition of the turbine blade with as little leakage as possible. It also provides the necessary axial degree of freedom to allow the burner of the turbine thermal expansion. Therefore, it constantly moves relative to the transition and needs at the provided with the component coating contact surface high wear resistance. Function and structure of a Spring Clip are for example in the US 2007/0012043 A1 described.

Um die Bauteilbeschichtung 2 auf der Spring Clip 1 aufzubringen, wird zunächst eine Schicht aus Rhenium auf der Spring Clip 1 mittels HVOF abgeschieden. Dann wird auf der Schicht aus Rhenium eine Schicht aus Bor aufgebracht. Dies kann wiederum durch HVOF erfolgen. Alternativ kann die Reihenfolge der Schichten auf der Spring Clip 1 auch vertauscht werden, d.h. zunächst kann die Borschicht und dann auf dieser die Rheniumschicht aufgebracht werden.In order to apply the component coating 2 on the Spring Clip 1, a layer of rhenium is first deposited on the Spring Clip 1 by means of HVOF. Then a layer of boron is applied to the layer of rhenium. This can again be done by HVOF. Alternatively, the order of the layers on the spring clip 1 can also be reversed, i. First, the boron layer and then on this rhenium layer can be applied.

Die Spring Clip 1 mit der Rhenium- und der Borschicht wird dann im Vakuum bei einer Temperatur > 1000°C solange erhitzt, bis sich aus den beiden Schichten eine Schicht aus Rheniumdiborid gebildet hat. Temperatur und Dauer der Wärmebehandlung hängen unter anderem von den Dicken der Rhenium- und der Borschicht ab und können im konkreten Fall leicht vom Fachmann experimentell mit Hilfe weniger Versuche ermittelt werden.The Spring Clip 1 with the rhenium and the boron layer is then heated in vacuo at a temperature> 1000 ° C until a layer of rhenium diboride has formed from the two layers. Temperature and duration of the heat treatment depend, inter alia, on the thicknesses of the rhenium and the boron layer and, in this specific case, can easily be determined experimentally by a person skilled in the art with the aid of a few experiments.

Die so erhaltene Bauteilbeschichtung 2 aus Rheniumdiborid weist eine hohe Temperaturbeständigkeit auf und ist darüber hinaus chemisch widerstandsfähig. Vor allem ist sie auf Grund ihrer hohen Härte mechanisch extrem belastbar.The component coating 2 of rhenium diboride thus obtained has a high temperature resistance and is above it also chemically resistant. Above all, it is due to their high hardness mechanically extremely strong.

Claims (17)

Bauteilbeschichtung (2),
dadurch gekennzeichnet, dass
sie Rheniumdiborid enthält.Component coating (2),
characterized in that
it contains rhenium diboride. Bauteilbeschichtung (2) nach Anspruch 1,
dadurch gekennzeichnet, dass
sie Rheniumdiboridpartikel enthält.Component coating (2) according to claim 1,
characterized in that
it contains rhenium diboride particles. Bauteilbeschichtung (2) nach Anspruch 2,
dadurch gekennzeichnet, dass
die Rheniumdiboridpartikel in einer duktilen Matrix eingebettet sind.Component coating (2) according to claim 2,
characterized in that
the rhenium diboride particles are embedded in a ductile matrix. Bauteilbeschichtung (2) nach Anspruch 3,
dadurch gekennzeichnet, dass
die duktile Matrix aus MCrAlY besteht.Component coating (2) according to claim 3,
characterized in that
the ductile matrix consists of MCrAlY. Bauteilbeschichtung (2) nach Anspruch 4,
dadurch gekennzeichnet, dass
sie 1 bis 70, bevorzugt 2 bis 40, besonders bevorzugt 4 bis 25 und insbesondere bevorzugt 6 bis 10 Gew.-% Rheniumdiboridpartikel enthält.Component coating (2) according to claim 4,
characterized in that
it contains from 1 to 70, preferably from 2 to 40, more preferably from 4 to 25, and especially preferably from 6 to 10,% by weight of rhenium diboride particles. Bauteilbeschichtung (2) nach einem der Ansprüche 2 bis 5,
dadurch gekennzeichnet, dass
sie 10 bis 500, bevorzugt 50 bis 400 und besonders bevorzugt 100 bis 300 µm dick ist.Component coating (2) according to one of claims 2 to 5,
characterized in that
it is 10 to 500, preferably 50 to 400 and particularly preferably 100 to 300 microns thick. Bauteilbeschichtung (2) nach Anspruch 1,
dadurch gekennzeichnet, dass
sie aus Rheniumdiborid besteht.Component coating (2) according to claim 1,
characterized in that
it consists of rhenium diboride. Bauteilbeschichtung (2) nach Anspruch 7,
dadurch gekennzeichnet, dass
sie 0,1 bis 600 µm dick ist.Component coating (2) according to claim 7,
characterized in that
it is 0.1 to 600 microns thick. Bauteil (1),
insbesondere Turbinenbauteil,
dadurch gekennzeichnet, dass
es eine Bauteilbeschichtung (2) gemäß einem der vorhergehenden Ansprüche aufweist.Component (1),
in particular turbine component,
characterized in that
it has a component coating (2) according to one of the preceding claims. Bauteil (1) nach Anspruch 9,
dadurch gekennzeichnet, dass
es eine Spring Clip einer Turbine ist.Component (1) according to claim 9,
characterized in that
it is a spring clip of a turbine. Verfahren zur Herstellung einer Bauteilbeschichtung (2) nach Anspruch 4,
dadurch gekennzeichnet, dass
eine Mischung aus MCrAlY und Rheniumdiborid auf ein Bauteil (1) aufgesprüht wird.Method for producing a component coating (2) according to Claim 4,
characterized in that
a mixture of MCrAlY and rhenium diboride is sprayed onto a component (1). Verfahren nach Anspruch 11,
dadurch gekennzeichnet, dass
die Mischung mittels HVOF oder Coldspray auf das Bauteil (1) aufgesprüht wird.Method according to claim 11,
characterized in that
the mixture is sprayed onto the component (1) by means of HVOF or cold spray. Verfahren zur Herstellung einer Bauteilbeschichtung (2) nach Anspruch 7,
dadurch gekennzeichnet, dass
auf ein Bauteil (1) in beliebiger Reihenfolge übereinander eine Schicht aus Rhenium und eine Schicht aus Bor aufgebracht und im Vakuum bei einer Temperatur > 1000°C erhitzt werden, bis sich aus den Schichten aus Rhenium und Bor eine Schicht aus Rheniumdiborid gebildet hat.Method for producing a component coating (2) according to Claim 7,
characterized in that
a layer of rhenium and a layer of boron are applied to a component (1) one above the other in any desired order and heated in vacuo at a temperature> 1000 ° C. until a layer of rhenium diboride has formed from the layers of rhenium and boron. Verfahren nach Anspruch 13,
bei dem die Schicht aus Rhenium und/oder die Schicht aus Bor aufgedampft oder aufgespritzt werden.Method according to claim 13,
in which the layer of rhenium and / or the layer of boron are vapor-deposited or sprayed on. Verfahren nach Anspruch 14,
dadurch gekennzeichnet, dass
die Schicht aus Rhenium und/oder die Schicht aus Bor mittels HVOF und/oder Coldspray aufgespritzt werden.Method according to claim 14,
characterized in that
the layer of rhenium and / or the layer of boron can be sprayed by means of HVOF and / or cold spray. Verwendung einer Bauteilbeschichtung (2) nach einem der Ansprüche 1 bis 8 als Abriebschicht auf einem Bauteil (1) insbesondere auf einem Turbinenbauteil.Use of a component coating (2) according to one of Claims 1 to 8 as an abrasion layer on a component (1), in particular on a turbine component. Verwendung einer Bauteilbeschichtung (2) nach einem der Ansprüche 1 bis 8 als Verschleißschutzschicht auf einem Bauteil (1) insbesondere auf einem Turbinenbauteil.Use of a component coating (2) according to one of claims 1 to 8 as a wear protection layer on a component (1), in particular on a turbine component.
EP09002778A 2009-02-26 2009-02-26 Component coating Withdrawn EP2228461A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09002778A EP2228461A1 (en) 2009-02-26 2009-02-26 Component coating
PCT/EP2010/050937 WO2010097262A1 (en) 2009-02-26 2010-01-27 Component coating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09002778A EP2228461A1 (en) 2009-02-26 2009-02-26 Component coating

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DE102010019958B4 (en) * 2010-05-08 2016-05-04 MTU Aero Engines AG Method for producing an inlet lining

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1253294A2 (en) 2001-04-28 2002-10-30 ALSTOM (Switzerland) Ltd Gas turbine shroud seal
WO2005031038A1 (en) 2003-09-22 2005-04-07 Mtu Aero Engines Gmbh Wear-resistant layer, component comprising such a wear-resistant layer, and production method
US20070012043A1 (en) 2005-07-18 2007-01-18 Siemens Westinghouse Power Corporation Turbine spring clip seal
US20090003123A1 (en) * 2007-06-28 2009-01-01 Morrison Jr Lowen Robert Apparatus and method for mixing by producing shear and/or cavitation, and components for apparatus

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1253294A2 (en) 2001-04-28 2002-10-30 ALSTOM (Switzerland) Ltd Gas turbine shroud seal
WO2005031038A1 (en) 2003-09-22 2005-04-07 Mtu Aero Engines Gmbh Wear-resistant layer, component comprising such a wear-resistant layer, and production method
US20070012043A1 (en) 2005-07-18 2007-01-18 Siemens Westinghouse Power Corporation Turbine spring clip seal
US20090003123A1 (en) * 2007-06-28 2009-01-01 Morrison Jr Lowen Robert Apparatus and method for mixing by producing shear and/or cavitation, and components for apparatus

Non-Patent Citations (3)

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Title
HSIU-YING CHUNG ET AL., SCIENCE, vol. 316, no. 5823, 20 April 2007 (2007-04-20), pages 436 - 439
HSIU-YING ET AL: "Synthesis of Ultra-Incompressible Superhard Rhenium Diboride at Ambient Pressure", SCIENCE, vol. 316, 20 April 2008 (2008-04-20), pages 436 - 439, XP002529265 *
LATININ, RAU ET AL: "Superhard Rhenium Diboride Films:Preparation and Characterization", CHEM. MATER, no. 20, 2008, usa, pages 4507 - 4511, XP002529264 *

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