EP1007753B1 - Method for producing an adhesive layer for a heat insulating layer - Google Patents

Method for producing an adhesive layer for a heat insulating layer Download PDF

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Publication number
EP1007753B1
EP1007753B1 EP99936366A EP99936366A EP1007753B1 EP 1007753 B1 EP1007753 B1 EP 1007753B1 EP 99936366 A EP99936366 A EP 99936366A EP 99936366 A EP99936366 A EP 99936366A EP 1007753 B1 EP1007753 B1 EP 1007753B1
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Prior art keywords
layer
component
slurry
powder
hours
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EP99936366A
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German (de)
French (fr)
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EP1007753A1 (en
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Gerhard Wydra
Martin Thoma
Horst Pillhöfer
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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
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/58—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than one step

Definitions

  • the invention relates to a method for producing an adhesive layer for a thermal insulation layer, which is applied to a component.
  • Thermally or mechanically stressed components are covered with protective layers, e.g. Wear protection layers or thermal insulation layers. Between one Such an outer layer and the component are generally provided with an adhesive layer. Such adhesive layers must have a certain roughness and surface topography for clinging to the outer layer.
  • the adhesive layers are e.g. with high thermal loads, metallic components, such as turbine blades, between the component and one Thermal insulation layer provided.
  • thermal insulation layers can be made from a Made of zirconium oxide with additions of calcium or magnesium oxide.
  • Diffusion layers which contain Al, Cr or Si are known as adhesive layers, which are manufactured using the so-called powder pack process or out of pack process become.
  • the disadvantages of the diffusion layers produced using these methods exist in their brittleness and the limited layer thicknesses of up to approx. 100 ⁇ m.
  • MCrAIY-based coating is by means of plasma spraying sprayed onto the component or by evaporation of the layer components evaporated onto the component in the electron beam.
  • Layer will be thick achieved up to approx. 300 ⁇ m.
  • Such processes are very technical in terms of production complex and expensive.
  • Other disadvantages are that the layers are geometric complicated components cannot be applied evenly, scattering in the layer composition occur and the layer elements when sprayed or vapor deposition.
  • JP 55-82761 A it is known to expose components of e.g. to protect a gas turbine by first using a binder-provided Ni powder is applied to the component and heat treated, then Cr by chemical Vapor deposition or Al can be introduced by a packing process and finally Pt, Pd or Rh are deposited and heat treated.
  • the object of the present invention is a method for manufacturing to create a layer of the type described in the introduction, which with the manufacturing technology is as simple and inexpensive to manufacture.
  • the advantage of the method is that it is mixed with a binder Powder is easily applied to the component to form a layer can be done without expensive processes such as plasma spraying or that electron beam evaporation is required. Those with this procedure
  • the layers produced have a comparatively fine-grained structure a grain size that is less than 75 microns.
  • the layer has a void portion from 0 to 40%.
  • the layer has improved thermal fatigue resistance as well as an advantageous expansion behavior that is fault tolerant against cracks.
  • additions of elements such as Y, evenly distributed and not oxidized.
  • the slip is made with a powder made of MCrAIY or an MCrAIY alloy, where M for at least one of the elements Ni, Co, Pt or Pd stands and also uses Hf or Ce instead of Y. can be.
  • the powder is preferably present with a grain size distribution of 5 to 120 ⁇ m.
  • the slip is preferably applied to the component by spraying, pinning or diving, which makes the process technically simple and can be carried out inexpensively.
  • This type of application makes it easy to Wise locally limited layers even on geometrically complex components muster.
  • the slip layer prior to the alitation at temperatures from 750 to 1200 ° C is heat treated in argon or vacuum, the heat treatment can be done over 1 - 6 hours to the slip layer to connect to the component by means of diffusion.
  • the final step Alit the slip layer at temperatures between 800 and 1200 ° C and one Duration of 1 - 12 hours.
  • the alitation serves for diffusion bonding and compacting the layer and is made in a conventional method such as e.g. in the Powder pack process, carried out with the introduction of Al.
  • the Al diffuses in the layer and in the base material of the component.
  • the layer is preferably an adhesive layer on which a thermal barrier coating is applied as an outer layer or protective layer, which is done in the usual way Plasma spraying or electron beam evaporation can be done.
  • a slip is first used for the production MCrAlY powder in a suspension with a common inorganic binder mixed.
  • the grain sizes of the powder particles are between 5 and 120 ⁇ m. there a flowable, sprayable mass forms.
  • the viscosity of this mass can be e.g. by the grain size of the powder particles used.
  • the M stands for nickel or cobalt or an alloy of the two elements.
  • the proportion of aluminum and chrome is chosen as high as possible in order to protect it against Exploit oxidation, which relies on the chrome and aluminum at high Form temperatures as protective films oxides.
  • the slip is applied with a brush to form a layer metallic component, such as a turbine guide vane made of a nickel-based alloy, applied.
  • a layer metallic component such as a turbine guide vane made of a nickel-based alloy
  • the thickness and local spread of the layer can be determined in this way influence the application in a simple way.
  • the application could e.g. also done with a spray gun.
  • the slurry in suspension is at room temperature dried over about 1.5 hours.
  • the dried layer is then heat-treated in argon at 1000 ° C. for one hour, to connect the layer with the material of the turbine guide vane to achieve by diffusion. Then the layer is at about 1100 ° C Alitated for 4 hours using a standard procedure to connect to the reinforce metallic component by means of diffusion and compact the layer. Al enters the layer and the base material of the metallic component and thus ensures both a firm connection of the layer with the component also for a connection of the spherical MCrAlY particles to each other. Also sinter the MCrAIY particles at least partially together.
  • the layer 1 shows a layer 2, which has been applied to a metallic component 1 and is heat-treated but has not yet been alitated.
  • the layer 2 is the spherical structure the MCrAlY particles as well as the cavities in between detect.
  • FIG. 2 shows the component 1 and the layer 2 after the alitation step.
  • the MCrAlY particles are sintered together.
  • the layer produced in this way has a significantly improved thermal fatigue resistance compared to (adhesive) layers produced in a conventional manner on.
  • the active elements like Y evenly distributed and not oxidized.
  • the layer produced in this way can be used as an adhesive layer, finally a thermal barrier coating by plasma spraying or another common method is applied.
  • the layer can also be easily as high quality Use hot gas corrosion layer without an additional outer protective layer is to be brought up.
  • the properties of corrosion and oxidation resistant Layer can be varied by extending the alitation process or improve.

Description

Die Erfindung betrifft ein Verfahren zum Herstellen einer Haftschicht für eine Wär-medämmschicht, die auf ein Bauteil aufgebracht wird.The invention relates to a method for producing an adhesive layer for a thermal insulation layer, which is applied to a component.

Thermisch oder mechanisch belastete Bauteile werden mit Schutzschichten, z.B. Verschleißschutzschichten oder Wärmedämmschichten versehen. Zwischen einer solchen äußeren Schicht und dem Bauteil wird im allgemeinen eine Haftschicht vorgesehen. Derartige Haftschichten müssen eine bestimmte Rauhigkeit und Oberflächentopographie zur Verklammerung mit der äußeren Schicht aufweisen.Thermally or mechanically stressed components are covered with protective layers, e.g. Wear protection layers or thermal insulation layers. Between one Such an outer layer and the component are generally provided with an adhesive layer. Such adhesive layers must have a certain roughness and surface topography for clinging to the outer layer.

Im Gasturbinenbau werden die Haftschichten z.B. bei thermisch hochbelasteten, metallischen Bauteilen, wie Turbinenschaufeln, zwischen dem Bauteil und einer Wärmedämmschicht vorgesehen. Derartige Wärmedämmschichten können aus einer Basis aus Zirkonoxid mit Zusätzen von Calcium- oder Magnesiumoxid bestehen. Die Haftschichten müssen neben der Rauhigkeit zur Verklammerung mit der äußeren Schutzschicht bzw. der Wärmedämmschicht oxidfrei und heißgaskorrosionsbeständig sein. Da in der Wärmedämmschicht und dem Werkstoff des metallischen Bauteils im allgemeinen unterschiedliche Wärmedehnungen auftreten, müssen diese darüberhinaus von der Haftschicht wenigstens teilweise ausgeglichen werden.In gas turbine construction, the adhesive layers are e.g. with high thermal loads, metallic components, such as turbine blades, between the component and one Thermal insulation layer provided. Such thermal insulation layers can be made from a Made of zirconium oxide with additions of calcium or magnesium oxide. The In addition to the roughness, adhesive layers need to cling to the outer Protective layer or the thermal insulation layer oxide-free and resistant to hot gas corrosion his. Because in the thermal insulation layer and the material of the metallic component in general, different thermal expansions occur, they also have to be at least partially compensated for by the adhesive layer.

Als Haftschichten sind Diffusionsschichten, die Al, Cr oder Si enthalten, bekannt, welche mittels sog. Pulverpackverfahren oder Out of Pack-Verfahren hergestellt werden. Die Nachteile der mit diesen Verfahren hergestellten Diffusionsschichten bestehen in ihrer Sprödigkeit und den begrenzten Schichtdicken von bis ca. 100 µm.Diffusion layers which contain Al, Cr or Si are known as adhesive layers, which are manufactured using the so-called powder pack process or out of pack process become. The disadvantages of the diffusion layers produced using these methods exist in their brittleness and the limited layer thicknesses of up to approx. 100 µm.

Eine andere bekannte sog. Auflageschicht auf MCrAIY-Basis wird mittels Plasmaspritzen auf das Bauteil aufgespritzt oder mittels Verdampfen der Schichtbestandteile im Elektronenstrahl auf das Bauteil aufgedampft. Dabei werden Schich tdicken bis zu ca. 300 µm erzielt. Derartige Verfahren sind fertigungstechnisch sehr aufwendig und teuer. Weitere Nachteile bestehen darin, daß die Schichten auf geometrisch komplizierten Bauteilen nicht gleichmäßig aufzubringen sind, Streuungen in der Schichtzusammensetzung auftreten und die Schichtelemente beim Aufspritzen bzw. Aufdampfen oxidieren.Another known so-called MCrAIY-based coating is by means of plasma spraying sprayed onto the component or by evaporation of the layer components evaporated onto the component in the electron beam. Layer will be thick achieved up to approx. 300 µm. Such processes are very technical in terms of production complex and expensive. Other disadvantages are that the layers are geometric complicated components cannot be applied evenly, scattering in the layer composition occur and the layer elements when sprayed or vapor deposition.

Aus der JP 55-82761 A ist es bekannt, heißen Gasen ausgesetzte Bauteile von, z.B. einer Gasturbine, zu schützen, indem zunächst mit einem Binder versehenes Ni-Pulver auf das Bauteil aufgebracht und wärmebehandelt wird, dann Cr durch chemische Gasphasenabscheidung oder Al durch ein Packverfahren eingebracht werden und schließlich Pt, Pd oder Rh abgeschieden und wärmebehandelt werden.From JP 55-82761 A it is known to expose components of e.g. to protect a gas turbine by first using a binder-provided Ni powder is applied to the component and heat treated, then Cr by chemical Vapor deposition or Al can be introduced by a packing process and finally Pt, Pd or Rh are deposited and heat treated.

Die Aufgabe der vorliegenden Erfindung besteht darin, ein Verfahren zum Herstellen einer Schicht der eingangs beschriebenen Gattung zu schaffen, die mit dem fertigungstechnisch möglichst einfach und kostengünstig herzustellen ist.The object of the present invention is a method for manufacturing to create a layer of the type described in the introduction, which with the manufacturing technology is as simple and inexpensive to manufacture.

Die Lösung der Aufgabe ist erfindungsgemäß durch die Schritte gekennzeichnet,

  • a) Herstellen eines Schlickers durch Mischen wenigstens eines der Elemente Cr, Ni oder Ce enthaltenden Pulvers mit einem Bindemittel,
  • b) Auftragen des Schlickers auf das Bauteil,
  • c) Trocknen des Schlickers bei Temperaturen von Raumtempeartur bis 300° C, und
  • d) Alitieren der Schlickerschicht, wobei das Verfahren so gesteuert wird, daß die Haftschicht eine Struktur mit einer Korngröße kleiner als 75 um und einem Hohlraumanteil von 0 bis 40% aufweist.
    • According to the invention, the solution to the problem is characterized by the steps
  • a) producing a slip by mixing at least one powder containing Cr, Ni or Ce with a binder,
  • b) applying the slip to the component,
  • c) drying the slip at temperatures from room temperature to 300 ° C, and
  • d) Alitizing the slip layer, the process being controlled so that the adhesive layer has a structure with a grain size smaller than 75 µm and a void fraction of 0 to 40%.

    • Der Vorteil des Verfahrens besteht darin, daß das mit einem Bindemittel gemischte Pulver auf einfache Weise auf das Bauteil unter Bildung einer Schicht aufgetragen werden kann, ohne daß vom Anlagenaufwand teure Verfahren wie das Plasmaspritzen oder das Elektronenstrahlaufdampfen erforderlich sind. Die mit diesem Verfahren hergestellten Schichten haben eine vergleichsweise feinkörnige Struktur mit einer Korngröße, die kleiner als 75 µm ist. Die Schicht weist einen Hohlraumanteil von 0 bis 40 % auf. Als Folge besitzt die Schicht eine verbesserte thermische Ermüdungsbeständigkeit sowie ein vorteilhaftes Ausdehnungsverhalten, das fehlertolerant gegenüber Rissen ist. Zudem sind Zusätze von Elementen, wie z.B. Y, gleich verteilt und nicht oxidiert. The advantage of the method is that it is mixed with a binder Powder is easily applied to the component to form a layer can be done without expensive processes such as plasma spraying or that electron beam evaporation is required. Those with this procedure The layers produced have a comparatively fine-grained structure a grain size that is less than 75 microns. The layer has a void portion from 0 to 40%. As a result, the layer has improved thermal fatigue resistance as well as an advantageous expansion behavior that is fault tolerant against cracks. In addition, additions of elements such as Y, evenly distributed and not oxidized.

    In einer bevorzugten Ausgestaltung des Verfahrens wir der Schlicker mit einem Pulver aus MCrAIY bzw. einer MCrAIY-Legierung hergestellt, wobei M für wenigstens eines der Elemente Ni, Co, Pt oder Pd steht und anstelle von Y auch Hf oder Ce verwendet werden kann.In a preferred embodiment of the method, the slip is made with a powder made of MCrAIY or an MCrAIY alloy, where M for at least one of the elements Ni, Co, Pt or Pd stands and also uses Hf or Ce instead of Y. can be.

    Bevorzugt liegt das Pulver mit einer Komgrößenverteilung von 5 bis 120 µm vor.The powder is preferably present with a grain size distribution of 5 to 120 μm.

    Das Auftragen des Schlickers auf das Bauteil erfolgt bevorzugt durch Spritzen, Pi n-seln 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 geometrisch komplizierten Bauteilen aufbringen. Zudem sind keine teuren und aufwendigen Spritz- und Verdampferanlagen erforderlich. Außerdem tritt anders als beim thermischen Spritzen oder dem Elektronenstrahlaufdampfen das Problem der Oxidation von Pulverpartikeln nicht auf.The slip is preferably applied to the component by spraying, pinning or diving, which makes the process technically simple and can be carried out inexpensively. This type of application makes it easy to Wise locally limited layers even on geometrically complex components muster. In addition, there are no expensive and complex spraying and evaporating systems required. It also occurs differently than with thermal spraying or that Electron beam evaporation does not solve the problem of oxidation of powder particles on.

    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 vorteilhaft erwiesen 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, with a duration of 1-2 hours has proven to be advantageous.

    Bevorzugt ist ferner, daß die Schlickerschicht vor dem Alitieren bei Temperaturen von 750 bis 1200 °C in Argon oder Vakuum wärmebehandelt wird, wobei das Wärmebehandeln über 1 - 6 Stunden durchgeführt werden kann, um die Schlickerschicht mit dem Bauteil mittels Diffusion zu verbinden.It is furthermore preferred that the slip layer prior to the alitation at temperatures from 750 to 1200 ° C is heat treated in argon or vacuum, the heat treatment can be done over 1 - 6 hours to the slip layer to connect to the component by means of diffusion.

    In einer bevorzugten Ausgestaltung des Verfahrens wird der abschließende Schritt Alitieren der Schlickerschicht bei Temperaturen zwischen 800 bis 1200 °C und einer Dauer von 1 - 12 Stunden durchgeführt. Das Alitieren dient zum Diffusionsverbinden und Kompaktieren der Schicht und wird in einem üblichen Verfahren, wie z.B. im Pulverpack-Verfahren, unter Einbringung von Al durchgeführt. Das Al diffundiert in die Schicht und in den Grundwerkstoff des Bauteils. In a preferred embodiment of the method, the final step Alit the slip layer at temperatures between 800 and 1200 ° C and one Duration of 1 - 12 hours. The alitation serves for diffusion bonding and compacting the layer and is made in a conventional method such as e.g. in the Powder pack process, carried out with the introduction of Al. The Al diffuses in the layer and in the base material of the component.

    Ferner ist die Schicht bevorzugt eine Haftschicht, auf die eine Wärmedämmschicht als äußere Schicht bzw. Schutzschicht aufgebracht wird, was in üblicher Weise mittels Plasmaspritzen oder Elektronenstrahlaufdampfen erfolgen kann.Furthermore, the layer is preferably an adhesive layer on which a thermal barrier coating is applied as an outer layer or protective layer, which is done in the usual way Plasma spraying or electron beam evaporation can be done.

    Im folgenden wird die Erfindung anhand einer Zeichnung unter Bezugnahme auf ein Beispiel näher erläutert. Es zeigt:

    Fig. 1
    ein Schliffbild der Schicht vor dem Alitieren und
    Fig. 2
    ein Schliffbild der Schicht nach dem Alitieren.
    The invention is explained in more detail below with reference to a drawing and with reference to an example. It shows:
    Fig. 1
    a micrograph of the layer before the alitation and
    Fig. 2
    a micrograph of the layer after alitation.

    Bei der Herstellung einer Schicht wird zunächst zur Herstellung eines Schlickers ein MCrAlY-Pulver in einer Suspension mit einem üblichen anorganischen Bindemittel gemischt. Die Korngrößen der Pulverpartikel liegen zwischen 5 und 120 µm. Dabei bildet sich eine fließfähige, spritzbare Masse. Die Viskosität dieser Masse läßt sich z.B. durch die Korngröße der verwendeten Pulverpartikel beeinflussen. Das M steht für Nickel oder Kobalt oder eine Legierung der beiden Elemente. Der Anteil von Aluminium und Chrom wird so hoch wie möglich gewählt, um deren Schutzeffekt gegen Oxidation auszunutzen, der darauf beruht, das Chrom und Aluminium bei hohen Temperaturen als Schutzfilme dienende Oxide bilden.In the production of a layer, a slip is first used for the production MCrAlY powder in a suspension with a common inorganic binder mixed. The grain sizes of the powder particles are between 5 and 120 µm. there a flowable, sprayable mass forms. The viscosity of this mass can be e.g. by the grain size of the powder particles used. The M stands for nickel or cobalt or an alloy of the two elements. The proportion of aluminum and chrome is chosen as high as possible in order to protect it against Exploit oxidation, which relies on the chrome and aluminum at high Form temperatures as protective films oxides.

    Anschießend wird der Schlicker unter Bildung einer Schicht mit einem Pinsel auf ein metallisches Bauteil, wie eine Turbinenleitschaufel aus einer Nickelbasis-Legierung, aufgetragen. Die Dicke und lokale Ausbreitung der Schicht läßt sich bei dieser Art des Auftragens auf einfache Weise beeinflussen. Alternativ könnte das Auftragen z.B. auch mit einer Spritzpistole erfolgen.Then the slip is applied with a brush to form a layer metallic component, such as a turbine guide vane made of a nickel-based alloy, applied. The thickness and local spread of the layer can be determined in this way influence the application in a simple way. Alternatively, the application could e.g. also done with a spray gun.

    Im nächsten Schritt wird der in einer Suspension vorliegende Schlicker bei Raumtemperatur über etwa 1,5 Stunden getrocknet.In the next step, the slurry in suspension is at room temperature dried over about 1.5 hours.

    Die getrocknete Schicht wird dann bei 1000 °C eine Stunde in Argon wärmebehandelt, um eine Verbindung der Schicht mit dem Werkstoff der Turbinenleitschaufel mittels Diffusion zu erzielen. Daran anschließend wird die Schicht bei etwa 1100 °C 4 Stunden lang mit einem üblichen Verfahren alitiert, um die Verbindung mit dem metallischen Bauteil mittels Diffusion zu verstärken und die Schicht zu kompaktieren. Dabei tritt Al in die Schicht und den Grundwerkstoff des metallischen Bauteils ein und sorgt so sowohl für eine feste Verbindung der Schicht mit dem Bauteil als auch für eine Verbindung der kugligen MCrAlY-Partikel untereinander. Zudem sintern die MCrAIY-Partikel untereinander wenigstens teilweise zusammen.The dried layer is then heat-treated in argon at 1000 ° C. for one hour, to connect the layer with the material of the turbine guide vane to achieve by diffusion. Then the layer is at about 1100 ° C Alitated for 4 hours using a standard procedure to connect to the reinforce metallic component by means of diffusion and compact the layer. Al enters the layer and the base material of the metallic component and thus ensures both a firm connection of the layer with the component also for a connection of the spherical MCrAlY particles to each other. Also sinter the MCrAIY particles at least partially together.

    Fig. 1 zeigt eine auf ein metallisches Bauteil 1 aufgebrachte Schicht 2, die wärmebehandelt aber noch nicht alitiert worden ist. In der Schicht 2 ist die kuglige Struktur der MCrAlY-Partikel ebenso wie die dazwischen befindlichen Hohlräume deutlich zu erkennen.1 shows a layer 2, which has been applied to a metallic component 1 and is heat-treated but has not yet been alitated. In the layer 2 is the spherical structure the MCrAlY particles as well as the cavities in between detect.

    In Fig. 2 ist das Bauteil 1 und die Schicht 2 nach dem Alitierungsschritt dargestellt. In der Schicht 2 liegen deutlich weniger Hohlräume vor. Zudem sind die kugligen MCrAlY-Partikel durch das Eindringen von Al in die Schicht und in den Grundwerkstoff des Bauteils 1 miteinander verbunden. Außerdem ist bei dem Alitierungsschritt ein Zusammensintern der MCrAlY-Partikel erfolgt.2 shows the component 1 and the layer 2 after the alitation step. There are significantly fewer voids in layer 2. In addition, they are spherical MCrAlY particles due to the penetration of Al into the layer and into the base material of component 1 connected to each other. Also in the alitation step the MCrAlY particles are sintered together.

    Die so hergestellte Schicht weist eine deutlich verbesserte thermische Ermüdungsbeständigkeit im Vergleich zu auf herkömmliche Weise hergestellten (Haft-) Schichten auf. Zudem erfolgt keine Oxidbildung der Schicht. Darüberhinaus sind die Aktivelemente, wie Y, gleichmäßig verteilt und nicht oxidiert.The layer produced in this way has a significantly improved thermal fatigue resistance compared to (adhesive) layers produced in a conventional manner on. In addition, there is no oxide formation in the layer. Furthermore, the active elements like Y, evenly distributed and not oxidized.

    Die so hergestellte Schicht kann als Haftschicht eingesetzt werden, auf die abschließend eine Wärmedämmschicht durch Plasmaspritzen oder ein anderes übliches Verfahren aufgebracht wird. Die Schicht läßt sich zudem ohne weiteres als hochwertige Heißgaskorrosionsschicht einsetzen, ohne daß eine zusätzliche, äußere Schutzschicht aufzubringen ist. Die eigenschaften der korrosions- und oxidationsbeständigen Schicht lassen sich durch Verlängern des Alitierungsvorgangs variieren bzw. verbessern.The layer produced in this way can be used as an adhesive layer, finally a thermal barrier coating by plasma spraying or another common method is applied. The layer can also be easily as high quality Use hot gas corrosion layer without an additional outer protective layer is to be brought up. The properties of corrosion and oxidation resistant Layer can be varied by extending the alitation process or improve.

    Claims (9)

    1. Method of producing a bonding layer for a heat-insulating coating applied to a component, characterised by steps in which
      a) a slurry is produced by mixing a powder containing at least one of the elements Cr, Ni or Ce with a binding agent,
      b) the slurry is applied to the component,
      c) the slurry is dried at temperatures ranging from room temperature to 300°C and
      d) the slurry coating is aluminized, the process being controlled so that the bonding layer has a structure with a grain size of less than 75 µm and a proportion of cavities of 0 to 40%.
    2. Method as claimed in claim 1, characterised in that the slurry is made from a powder comprising MCrAlY.
    3. Method as claimed in claim 1 or 2, characterised in that the powder has a grain size distribution of from 5 to 120 µm.
    4. Method as claimed in one or more of the preceding claims, characterised in that application is by spraying, brushing or dipping.
    5. Method as claimed in one of the preceding claims, characterised in that the component is made from an alloy with a nickel or cobalt base.
    6. Method as claimed in one or more of the preceding claims, characterised in that drying takes place for 0.5 - 5 hours.
    7. Method as claimed in one or more of the preceding claims, characterised in that the slurry coating is heat-treated at temperatures of from 750 to 1200°C prior to aluminising.
    8. Method as claimed in claim 7, characterised in that the heat-treatment is conducted for 1 - 6 hours.
    9. Method as claimed in one or more of the preceding claims, characterised in that aluminising takes place at temperatures of between 800 and 1200°C and lasts for a period of 1 to 12 hours.
    EP99936366A 1998-06-03 1999-05-31 Method for producing an adhesive layer for a heat insulating layer Expired - Lifetime EP1007753B1 (en)

    Applications Claiming Priority (3)

    Application Number Priority Date Filing Date Title
    DE19824792 1998-06-03
    DE19824792A DE19824792B4 (en) 1998-06-03 1998-06-03 Method for producing an adhesive layer for a thermal barrier coating
    PCT/DE1999/001598 WO1999063126A1 (en) 1998-06-03 1999-05-31 Method for producing an adhesive layer for a heat insulating layer

    Publications (2)

    Publication Number Publication Date
    EP1007753A1 EP1007753A1 (en) 2000-06-14
    EP1007753B1 true EP1007753B1 (en) 2002-04-03

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    EP99936366A Expired - Lifetime EP1007753B1 (en) 1998-06-03 1999-05-31 Method for producing an adhesive layer for a heat insulating layer

    Country Status (6)

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    US (1) US6709711B1 (en)
    EP (1) EP1007753B1 (en)
    JP (1) JP4469083B2 (en)
    DE (2) DE19824792B4 (en)
    ES (1) ES2176003T3 (en)
    WO (1) WO1999063126A1 (en)

    Families Citing this family (15)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US6228510B1 (en) * 1998-12-22 2001-05-08 General Electric Company Coating and method for minimizing consumption of base material during high temperature service
    US6485780B1 (en) 1999-08-23 2002-11-26 General Electric Company Method for applying coatings on substrates
    DE19946650C2 (en) * 1999-09-29 2003-11-27 Mtu Aero Engines Gmbh Process for the production of armor for a metallic component
    EP1123987A1 (en) * 2000-02-11 2001-08-16 General Electric Company Repairable diffusion aluminide coatings
    FR2813318B1 (en) * 2000-08-28 2003-04-25 Snecma Moteurs FORMATION OF AN ALUMINIURE COATING INCORPORATING A REACTIVE ELEMENT, ON A METAL SUBSTRATE
    DE102004034410A1 (en) * 2004-07-16 2006-02-02 Mtu Aero Engines Gmbh Protective layer for application to a substrate and method for producing a protective layer
    US7316057B2 (en) * 2004-10-08 2008-01-08 Siemens Power Generation, Inc. Method of manufacturing a rotating apparatus disk
    JP2007262447A (en) * 2006-03-27 2007-10-11 Mitsubishi Heavy Ind Ltd Oxidation-resistant film and its deposition method, thermal barrier coating, heat-resistant member, and gas turbine
    DE102009008510A1 (en) * 2009-02-11 2010-08-12 Mtu Aero Engines Gmbh Coating and method for coating a workpiece
    DE102013207457B4 (en) 2013-04-24 2017-05-18 MTU Aero Engines AG Process for the preparation of a high temperature protective coating
    US9587302B2 (en) * 2014-01-14 2017-03-07 Praxair S.T. Technology, Inc. Methods of applying chromium diffusion coatings onto selective regions of a component
    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
    DE102016009854A1 (en) * 2016-08-12 2018-02-15 Dechema Forschungsinstitut Stiftung Bürgerlichen Rechts Long-term stable, storable slip for environmentally friendly diffusion coatings
    DE102021127344A1 (en) * 2021-10-21 2023-04-27 MTU Aero Engines AG Method for coating a component of an aircraft engine with a wear protection layer and component for an aircraft engine with at least one wear protection layer

    Family Cites Families (11)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US3720537A (en) * 1970-11-25 1973-03-13 United Aircraft Corp Process of coating an alloy substrate with an alloy
    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
    JPS5582761A (en) * 1978-12-15 1980-06-21 Hitachi Ltd Coating method for platinum group metal onto cobalt alloy
    JPS5754282A (en) 1980-09-17 1982-03-31 Mitsubishi Heavy Ind Ltd Surface treatment of heat resistant alloy
    JPS58177401A (en) 1982-04-12 1983-10-18 Sumitomo Metal Ind Ltd Coating method of nickel and chromium alloy
    JPS6067652A (en) 1983-09-20 1985-04-18 Asia Kogyo Kk Formation of alloy layer
    US4910092A (en) * 1986-09-03 1990-03-20 United Technologies Corporation Yttrium enriched aluminide coating for superalloys
    DE4226272C1 (en) 1992-08-08 1994-02-10 Mtu Muenchen Gmbh Process for treating MCrAlZ layers and components produced using the process
    GB9426257D0 (en) * 1994-12-24 1995-03-01 Rolls Royce Plc Thermal barrier coating for a superalloy article and method of application
    US5759142A (en) * 1995-01-20 1998-06-02 Bender Machine, Inc. Coated roll for aluminizing processes

    Also Published As

    Publication number Publication date
    EP1007753A1 (en) 2000-06-14
    DE19824792B4 (en) 2005-06-30
    DE59901109D1 (en) 2002-05-08
    DE19824792A1 (en) 1999-12-16
    ES2176003T3 (en) 2002-11-16
    JP4469083B2 (en) 2010-05-26
    US6709711B1 (en) 2004-03-23
    WO1999063126A1 (en) 1999-12-09
    JP2002517608A (en) 2002-06-18

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