EP0318803B1 - High-temperature protective coating - Google Patents

High-temperature protective coating Download PDF

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Publication number
EP0318803B1
EP0318803B1 EP88119394A EP88119394A EP0318803B1 EP 0318803 B1 EP0318803 B1 EP 0318803B1 EP 88119394 A EP88119394 A EP 88119394A EP 88119394 A EP88119394 A EP 88119394A EP 0318803 B1 EP0318803 B1 EP 0318803B1
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EP
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Prior art keywords
weight
protective layer
yttrium
temperature protective
nickel
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Expired - Lifetime
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EP88119394A
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German (de)
French (fr)
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EP0318803A1 (en
Inventor
Lorenz Dr. Singheiser
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General Electric Technology GmbH
ABB AG Germany
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Asea Brown Boveri AG Germany
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12937—Co- or Ni-base component next to Fe-base component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component

Definitions

  • the invention relates to a high-temperature protective layer.
  • Such high-temperature protective layers are used above all where the base material of components made of heat-resistant steels and / or alloys that are used at temperatures above 600 ° C is to be protected.
  • high-temperature protective layers are intended to slow down or completely prevent the effects of high-temperature corrosion, especially of sulfur, oil ash, oxygen, alkaline earths and vanadium.
  • Such high-temperature protective layers are designed so that they can be applied directly to the base material of the component to be protected.
  • High-temperature protective layers are of particular importance for components of gas turbines. They are mainly applied to rotor blades and guide vanes as well as to heat accumulation segments in gas turbines.
  • An austenitic material based on nickel, cobalt or iron is preferably used to manufacture these components.
  • nickel superalloys in particular are used as the base material.
  • Such high-temperature protective layers have a matrix in which an aluminum-containing phase is embedded.
  • this top layer does not have particularly good adhesion, and is therefore worn away over time by the action of corrosion, so that the protection for the high-temperature protective layer that is automatically created as a result is lost. Over time, the corrosion progresses so far that the matrix of the high-temperature protective layer itself is attacked.
  • An improved high-temperature layer has become known from EP-A-0 134 821.
  • the well-known protective layer is an oxide dispersion hardened nickel-based alloy with a high chromium and aluminum content. Silicon and zirconium or silicon and tantalum are optionally provided as adhesion-increasing additives, which should contribute to the Improve oxidation resistance and adhesion to components. As practice shows, however, not with the desired success.
  • the high-temperature protective layer according to the invention which is also an oxide dispersion-hardened alloy, has not only the known elements such as nickel, chromium and aluminum, as well as silicon and zirconium or tantalum, but also contents of up to 2% of yttrium and / or hafnium.
  • the oxidation resistance is considerably increased in comparison with known high-temperature protective layers, since it also has aluminum-containing phases which enable the formation of an aluminum oxide-containing cover layer.
  • an additional aluminum-nickel-chromium-oxide layer is formed on the aluminum oxide-containing top layer, which significantly increases the protection of the high-temperature protective layer and the component underneath.
  • silicon and tantalum With the addition of silicon and tantalum, the formation of an aluminum oxide cover layer can also be achieved.
  • the high-temperature protective layer according to the invention produced with one or the other additive experiences a considerably better adhesive strength on the components than known layers of this type. This also applies to its cover layers.
  • the firm and permanent adhesion of the protective layer and its cover layer is achieved by the percentage of yttrium and / or hafnium that is specifically determined for the alloy.
  • the high-temperature protective layer according to the invention is formed by an alloy which contains chromium, aluminum, nickel, yttrium, silicon and zirconium. Instead of ytrium, yttrium and hafnium or hafnium alone can also be used.
  • Such an alloy has 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, and 1 to 2% by weight of zirconium, the remaining part of the alloy is formed by nickel.
  • the 0.2 to 2% by weight ytrrium can also be replaced by 0.2 to 2% by weight yttrium and hafnium or by 0.2 to 2% by weight hafnium.
  • a high temperature protective layer with the same properties is achieved by using an alloy containing chromium, aluminum, yttrium, nickel, silicon and tantalum.
  • the proportion of yttrium can be replaced by yttrium and hafnium or hafnium alone.
  • an alloy which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 contains up to 3% by weight of tantalum, the remainder of the alloy consisting of nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium. All weights refer to the total weight of the respective alloy.
  • All the alloys described here are in the same way for the formation of a high-temperature protective layer suitable. Regardless of which of the alloys described above they are formed, aluminum oxide cover layers are formed in each case under operating conditions on these protective layers, which form equally quickly and equally strongly with each of the alloy compositions according to the invention, and also at temperatures which are greater than 950 ° C are not removed.
  • the invention is explained in more detail using an exemplary embodiment which describes the production of a coated gas turbine component.
  • the gas turbine component to be coated is made of an austenitic material, in particular a nickel superalloy. Before coating, the component is first chemically cleaned and then roughened with a sandblast. The component is coated under vacuum using plasma spraying.
  • An alloy is used for the coating, which contains 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, 1 to 2% by weight of zirconium having. The rest of the alloy consists of nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium.
  • this alloy it is also possible to use an alloy which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 up to 3% by weight of tantalum, the remainder of the alloy being nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by the same amount of hafnium alone.
  • All weight figures refer to the total weight the alloy used.
  • the material forming the alloy is in powder form and preferably has a grain size of 45 ⁇ m.
  • the component is heated to 800 ° C. using the plasma.
  • the alloy is applied directly to the base material of the component.
  • Argon and hydrogen are used as the plasma gas.
  • the component is subjected to a heat treatment. This takes place in a high vacuum annealing furnace. A pressure is maintained in it that is less than 0.66 Pa (5x10 ⁇ 3 Torr). After reaching the vacuum, the furnace is heated to a temperature of 1100 ° C.
  • the above temperature is held for about 1 hour with a tolerance of about +/- 4 ° C.
  • the heating of the furnace is then switched off.
  • the coated and heat-treated component is slowly cooled in the oven. Its production is finished after cooling. All alloy variants are applied in the same way.

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

Description

Die Erfindung bezieht sich auf eine Hochtemperatur-Schutzschicht.The invention relates to a high-temperature protective layer.

Solche Hochtemperatur-Schutzschichten kommen vor allem dort zur Anwendung, wo das Grundmaterial von Bauelementen aus warmfesten Stählen und/oder Legierungen zu schützen ist, die bei Temperaturen über 600 °C verwendet werden.Such high-temperature protective layers are used above all where the base material of components made of heat-resistant steels and / or alloys that are used at temperatures above 600 ° C is to be protected.

Durch diese Hochtemperatur-Schutzschichten soll die Wirkung von Hochtemperaturkorrosionen vor allem von Schwefel, Ölaschen, Sauerstoff, Erdalkalien und Vanadium verlangsamt bzw. vollständig unterbunden werden. Solche Hochtemperatur-Schutzschichten sind so ausgebildet, daß sie direkt auf das Grundmaterial des zu schützenden Bauelementes aufgetragen werden können.These high-temperature protective layers are intended to slow down or completely prevent the effects of high-temperature corrosion, especially of sulfur, oil ash, oxygen, alkaline earths and vanadium. Such high-temperature protective layers are designed so that they can be applied directly to the base material of the component to be protected.

Bei Bauelementen von Gasturbinen sind Hochtemperatur-Schutzschichten von besonderer Bedeutung. Sie werden vor allem auf Lauf- und Leitschaufeln sowie auf Wärmestausegmente von Gasturbinen aufgetragen.High-temperature protective layers are of particular importance for components of gas turbines. They are mainly applied to rotor blades and guide vanes as well as to heat accumulation segments in gas turbines.

Für die Fertigung dieser Bauelemente wird vorzugsweise ein austenititsches Material auf der Basis von Nickel, Kobalt oder Eisen verwendet. Bei der Herstellung von Gasturbinenbauteilen kommen vor allem Nickel-Superlegierungen als Grundmaterial zur Anwendung.An austenitic material based on nickel, cobalt or iron is preferably used to manufacture these components. In the manufacture of gas turbine components, nickel superalloys in particular are used as the base material.

Bis jetzt ist es üblich, Bauelemente, die für Gasturbinen bestimmt sind, mit Schutzschichten zu versehen, die durch Legierungen gebildet werden, deren wesentliche Bestandteile Nickel, Chrom, Aluminium und Yttrium sind (FR-A-2 511 042).Up to now it has been customary to provide components intended for gas turbines with protective layers formed by alloys, the essential components of which are nickel, chromium, aluminum and yttrium (FR-A-2 511 042).

Solche Hochtemperaturschutzschichten weisen eine Matrix auf, in die eine aluminiumhaltige Phase eingelagert ist.Such high-temperature protective layers have a matrix in which an aluminum-containing phase is embedded.

Wird ein Bauelement, das mit einer solchen Hochtemperaturschutzschicht versehen ist, einer Betriebstemperatur von mehr als 950°C ausgesetzt, so beginnt das in der Phase enthaltene Aluminium an die Oberfläche zu diffundieren, wo es zur Ausbildung einer Alumniniumoxiddeckschicht kommt.If a component that is provided with such a high-temperature protective layer is exposed to an operating temperature of more than 950 ° C., the aluminum contained in the phase begins to diffuse to the surface, where an aluminum oxide cover layer is formed.

Von Nachteil ist hierbei, daß diese Deckschicht keine besonders gute Haftung aufweist, und deshalb durch die Einwirkung von Korrosionen mit der Zeit abgetragen wird, so daß der hierdurch selbsttätig entstandene Schutz für die Hochtemperaturschutzschicht verloren geht. Im Laufe der Zeit schreitet die Korrosion so weit fort, daß die Matrix der Hochtemperaturschutzschicht selbst angegriffen wird.The disadvantage here is that this top layer does not have particularly good adhesion, and is therefore worn away over time by the action of corrosion, so that the protection for the high-temperature protective layer that is automatically created as a result is lost. Over time, the corrosion progresses so far that the matrix of the high-temperature protective layer itself is attacked.

Es hat sich jedoch gezeigt, daß durch solche Hochtemperaturschutzschichten Bauelemente aus austenitischen Werkstoffen am besten geschützt werden, so daß auf diese Schutzschichten nicht verzichtet werden kann.However, it has been shown that components made of austenitic materials are best protected by such high-temperature protective layers, so that these protective layers cannot be dispensed with.

Eine verbesserte Hochtemperaturschicht ist aus der EP-A-0 134 821 bekanntgeworden. Die bekannte Schutzschicht ist eine oxiddispersionsgehärtete Nickelbasislegierung mit hohem Chrom- und Aluminiumgehalt. Als haftungssteigernde Zusätze sind wahlweise Silizium und Zirkonium oder Silizium und Tantal vorgesehen, welche dazu beitragen sollen, die Oxidationsbeständigkeit und die Haftung an den Bauteilen zu verbessern. Wie die Praxis jedoch zeigt, nicht mit dem gewünschten Erfolg.An improved high-temperature layer has become known from EP-A-0 134 821. The well-known protective layer is an oxide dispersion hardened nickel-based alloy with a high chromium and aluminum content. Silicon and zirconium or silicon and tantalum are optionally provided as adhesion-increasing additives, which should contribute to the Improve oxidation resistance and adhesion to components. As practice shows, however, not with the desired success.

Ausgehend von diesem Stand der Technik ist es daher Aufgabe der Erfindung, eine Hochtemperaturschutzschicht der eingangs genannten Art so zu verbessern, daß ihre Haftfestigkeit und ihr Korrosionswiderstand erhöht sind.Starting from this prior art, it is therefore an object of the invention to improve a high-temperature protective layer of the type mentioned at the outset in such a way that its adhesive strength and its corrosion resistance are increased.

Die Lösung der Aufgabe ist in den Ansprüchen 1 - 4 angegeben. Demgemäß weist die erfindungsgemäße Hochtemperaturschutzschicht, die ebenfalls eine oxiddispersionsgehärtete Legierung ist, neben den bekannten Elementen wie Nickel, Chrom und Aluminium sowie Silizium und Zirkonium oder Tantal auch Gehalte bis 2 % an Yttrium und/oder Hafnium auf.The solution to the problem is given in claims 1-4. Accordingly, the high-temperature protective layer according to the invention, which is also an oxide dispersion-hardened alloy, has not only the known elements such as nickel, chromium and aluminum, as well as silicon and zirconium or tantalum, but also contents of up to 2% of yttrium and / or hafnium.

Durch die Zugabe von Yttrium und/oder Hafnium wird die Oxidationsbeständigkeit im Vergleich mit bekannten Hochtemperaturschutzschichten beträchtlich erhöht, da sie ebenfalls aluminiumhaltige Phasen aufweist, welche die Ausbildung einer aluminiumoxidhaltigen Deckschicht ermöglichen.By adding yttrium and / or hafnium, the oxidation resistance is considerably increased in comparison with known high-temperature protective layers, since it also has aluminum-containing phases which enable the formation of an aluminum oxide-containing cover layer.

Wird dem Basiswerkstoff, der die Hochtemperaturschutzschicht bildet, Zirkonium und Silizium zulegiert, so kommt es auf der aluminiumoxidhaltigen Deckschicht zur Ausbildung einer zusätzlichen Aluminium-Nickel-Chrom-Oxidschicht, welche den Schutz der Hochtemperaturschutzschicht und des darunter befindlichen Bauelementes wesentlich erhöht. Mit einem Zusatz von Silizium und Tantal kann ebenfalls die Ausbildung einer Aluminiumoxiddeckschicht erreicht werden. Die mit dem einen oder anderen Zusatz hergestellte erfindungsgemäße Hochtemperaturschutzschicht erfährt eine wesentlich bessere Haftfestigkeit auf den Bauelementen als bekannte Schichten dieser Art. Dies gilt auch für ihre Deckschichten. Die feste und beständige Haftung der Schutzschicht und ihrer Deckschicht wird duch den speziell für die Legierung festgelegten Anteil an Yttrium und/oder Hafnium erreicht.If zirconium and silicon are alloyed into the base material that forms the high-temperature protective layer, an additional aluminum-nickel-chromium-oxide layer is formed on the aluminum oxide-containing top layer, which significantly increases the protection of the high-temperature protective layer and the component underneath. With the addition of silicon and tantalum, the formation of an aluminum oxide cover layer can also be achieved. The high-temperature protective layer according to the invention produced with one or the other additive experiences a considerably better adhesive strength on the components than known layers of this type. This also applies to its cover layers. The firm and permanent adhesion of the protective layer and its cover layer is achieved by the percentage of yttrium and / or hafnium that is specifically determined for the alloy.

Durch den Zusatz des Yttrium in Mengen von 0,2 bis 2 Gew.% wird die Oxidationsgeschwindigkeit auf der Oberfläche der Hochtemteraturschutzschicht in einem bisher nicht dagewesenen Maß reduziert. Dieser Effekt wird durch den Zusatz von Hafnium sogar noch etwas verstärkt. Die erfindungsgemäße Hochtemperatur-Schutzschicht wird bei einer ersten Ausführungsform durch eine Legierung gebildet, die Chrom, Aluminium, Nickel, Yttrium, Silizium und Zirkonium enthält. An Stelle von Ytrium können auch Yttrium und Hafnium oder Hafnium alleine verwendet werden. Eine solche Legierung weist 25 bis 27 Gew.% Chrom, 4 bis 7 Gew.% Aluminium, 0,2 bis 2 Gew.% Yttrium, 1 bis 3 Gew.% Silizium, und 1 bis 2 Gew.% Zirkomium auf, wobei der übrige Anteil der Legierung durch Nickel gebildet wird. Die 0,2 bis 2 Gew % Ytrrium können auch durch 0,2 bis 2 Gew % Yttrium und Hafnium bzw. durch 0,2 bis 2 Gew % Hafnium ersetzt werden.By adding the yttrium in amounts from 0.2 to 2 % By weight, the rate of oxidation on the surface of the high-temperature protection layer is reduced to an unprecedented degree. This effect is even somewhat enhanced by the addition of hafnium. In a first embodiment, the high-temperature protective layer according to the invention is formed by an alloy which contains chromium, aluminum, nickel, yttrium, silicon and zirconium. Instead of ytrium, yttrium and hafnium or hafnium alone can also be used. Such an alloy has 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, and 1 to 2% by weight of zirconium, the remaining part of the alloy is formed by nickel. The 0.2 to 2% by weight ytrrium can also be replaced by 0.2 to 2% by weight yttrium and hafnium or by 0.2 to 2% by weight hafnium.

Eine Hochtemperatur-Schutzschicht mit den gleichen Eigenschaften wird durch die Verwendung einer Legierung erzielt, die Chrom, Aluminium, Yttrium, Nickel, Silizium und Tantal enthält. Auch hierbei kann der Anteil des Yttriums durch Yttrium und Hafnium bzw. Hafnium alleine ersetzt werden. Nach einer entsprechenden zweiten Ausführungsform wird eine Legierung verwendet, die 23 bis 27 Gew.% Chrom, 3 bis 5 Gew.% Aluminium, 0,2 bis 2 Gew. % Yttrium, 1 bis 2,5 Gew.% Silizium, 0,1 bis 3 Gew.% Tantal enthält, wobei der übrige Anteil der Legierung aus Nickel besteht. Die 0,2 bis 2 Gew.% Yttrium können auch durch 0,2 bis 2 Gew.% Yttrium und Hafnium bzw. durch 0,2 bis 2 Gew.% Hafnium ersetzt werden. Alle Gewichtsangaben beziehen sich auf das Gesamtgewicht der jeweiligen Legierung.A high temperature protective layer with the same properties is achieved by using an alloy containing chromium, aluminum, yttrium, nickel, silicon and tantalum. Here, too, the proportion of yttrium can be replaced by yttrium and hafnium or hafnium alone. According to a corresponding second embodiment, an alloy is used which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 contains up to 3% by weight of tantalum, the remainder of the alloy consisting of nickel. The 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium. All weights refer to the total weight of the respective alloy.

Alle hier beschriebenen Legierungen sind in gleicher Weise für die Ausbildung einer Hochtemperatur-Schutzschicht geeignet. Gleichgültig durch welche der oben beschriebenen Legierungen sie gebildet werden, es entstehen in jedem Fall unter Betriebsbedingungen auf diesen Schutzschichten Aluminiumoxid-Deckschichten, die sich bei jeder der erfindungsgemäßen Legierungszusammensetzungen gleich schnell und gleich stark ausbilden, und die auch bei Temperaturen, die größer als 950°C sind, nicht abgetragen werden.All the alloys described here are in the same way for the formation of a high-temperature protective layer suitable. Regardless of which of the alloys described above they are formed, aluminum oxide cover layers are formed in each case under operating conditions on these protective layers, which form equally quickly and equally strongly with each of the alloy compositions according to the invention, and also at temperatures which are greater than 950 ° C are not removed.

Anhand eines Ausführungsbeispiels, das die Herstellung eines beschichteten Gasturbinenenbauteils beschreibt, wird die Erfindung näher erläutert. Das zu beschichtende Gasturbinenbauteil ist aus einem austenitischen Material, insbesondere einer Nickel-Superlegierung gefertigt. Vor der Beschichtung wird das Bauteil zunächst chemisch gereinigt und dann mit einem Sandstrahl aufgerauht. Die Beschichtung des Bauelementes erfolgt unter Vakuum mittels Plasmaspritzen.
Für die Beschichtung wird eine Legierung verwendet, die 25 bis 27 Gew.% Chrom, 4 bis 7 Gew.% Aluminium, 0,2 bis 2 Gew.% Yttrium, 1 bis 3 Gew.% Silizium, 1 bis 2 Gew.% Zirkonium aufweist. Der übrige Anteil der Legierung besteht aus Nickel.
Die 0,2 bis 2 Gew.% Yttrium können auch durch 0,2 bis 2 Gew.% Yttrium und Hafnium oder durch 0,2 bis 2 Gew.% Hafnium ersetzt werden.
Anstelle dieser Legierung kann auch eine Legierung verwendet werden, die 23 bis 27 Gew.% Chrom, 3 bis 5 Gew.% Aluminium, 0,2 bis 2 Gew.% Yttrium, 1 bis 2,5 Gew.% Silizium, 0,1 bis 3 Gew.% Tantal aufweist, wobei der restliche Anteil der Legierung Nickel ist. Die 0,2 bis 2 Gew.% Yttrium können auch durch 0,2 bis 2 Gew.% Yttrium und Hafnium bzw. durch die gleiche Menge Hafnium alleine ersetzt werden.
Alle Gewichtsanganben beziehen sich auf das Gesamtgewicht der verwendeten Legierung.
Das die Legierung bildende Material liegt in Pulverform vor, und weist vorzugsweise eine Korngröße von 45 µm auf. Vor dem Aufbringen der Hochtemperatur-Schutzschicht, insbeondere vor dem Aufbringen der die Schutzschicht bildenden Legierung, wird das Bauelement mit Hilfe des Plasmas auf 800 °C erhitzt. Die Legierung, wird direkt auf das Grundmaterial des Bauelementes aufgetragen. Als Plasmagas wird Argon und Wasserstoff verwendet. Nach dem Aufbringen der Legierung wird das Bauelement einer Wärmebehandlung unterzogen. Diese erfolgt in einem Hochvakuumglühofen. In ihm wird ein Druck aufrecht erhalten, der kleiner als 0,66 Pa (5x10⁻³ Torr) ist. Nach dem Erreichen des Vakuums wird der Ofen auf eine Temperatur von 1100 °C aufgeheizt. Die oben angegebene Temperatur wird während etwa 1 Stunde mit einer Toleranz von etwa +/- 4 °C gehalten. Anschließend wird die Heizung des Ofens abgeschaltet. Das beschichtete und wärmebehandelte Bauelement wird im Ofen langsam abgekühlt. Seine Herstellung ist nach dem Abkühlen beendet. Alle Legierungsvarianten werden in der gleichen Weise aufgetragen.The invention is explained in more detail using an exemplary embodiment which describes the production of a coated gas turbine component. The gas turbine component to be coated is made of an austenitic material, in particular a nickel superalloy. Before coating, the component is first chemically cleaned and then roughened with a sandblast. The component is coated under vacuum using plasma spraying.
An alloy is used for the coating, which contains 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, 1 to 2% by weight of zirconium having. The rest of the alloy consists of nickel.
The 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium.
Instead of this alloy, it is also possible to use an alloy which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 up to 3% by weight of tantalum, the remainder of the alloy being nickel. The 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by the same amount of hafnium alone.
All weight figures refer to the total weight the alloy used.
The material forming the alloy is in powder form and preferably has a grain size of 45 μm. Before the high-temperature protective layer is applied, in particular before the alloy forming the protective layer is applied, the component is heated to 800 ° C. using the plasma. The alloy is applied directly to the base material of the component. Argon and hydrogen are used as the plasma gas. After the alloy has been applied, the component is subjected to a heat treatment. This takes place in a high vacuum annealing furnace. A pressure is maintained in it that is less than 0.66 Pa (5x10⁻³ Torr). After reaching the vacuum, the furnace is heated to a temperature of 1100 ° C. The above temperature is held for about 1 hour with a tolerance of about +/- 4 ° C. The heating of the furnace is then switched off. The coated and heat-treated component is slowly cooled in the oven. Its production is finished after cooling. All alloy variants are applied in the same way.

Claims (6)

  1. High-temperature protective layer, characterised in that it contains 25 to 27% by weight of chromium, 4 to 7% by weight of aluminium, 0.2 to 2% by weight of yttrium and/or hafnium, 1 to 3% by weight of silicon and 1 to 2% by weight of zirconium, the remaining part consisting of nickel.
  2. High-temperature protective layer, characterised in that it contains 25 to 27% by weight of chromium, 4 to 7% by weight of aluminium, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon and 1 to 2% by weight of zirconium, the consisting part consisting of nickel.
  3. High-temperature protective layer, characterised in that it contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminium, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon and 0.1 to 3% by weight of tantalum, the remaining part consisting of nickel.
  4. High-temperature protective layer, characterised in that it contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminium, 0.2 to 2% by weight of yttrium and/or hafnium, 1 to 2.5% by weight of silicon and 0.1 to 3% by weight of tantalum, the remaining part consisting of nickel.
  5. Base material for producing a high-temperature protective layer according to one of Claims 1 to 4, characterised in that the material forming the alloy is in the form of a powder having a grain size of preferably 45 µm.
  6. Process for producing a high-temperature protective layer according to one of Claims 1 to 4, characterised in that the component to be coated is, before the application of the protective layer, first chemically cleaned, then roughened by means of sandblasting and finally heated to 800°C by means of plasma.
EP88119394A 1987-11-28 1988-11-22 High-temperature protective coating Expired - Lifetime EP0318803B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3740478A DE3740478C1 (en) 1987-11-28 1987-11-28 High temperature protective layer
DE3740478 1987-11-28

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EP0318803A1 EP0318803A1 (en) 1989-06-07
EP0318803B1 true EP0318803B1 (en) 1993-06-23

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EP (1) EP0318803B1 (en)
DE (2) DE3740478C1 (en)

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EP1260608A1 (en) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Method of depositing a MCrAIY bond coating
EP1260612A1 (en) 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd A bond or overlay MCrAIY-coating
EP1295969A1 (en) * 2001-09-22 2003-03-26 ALSTOM (Switzerland) Ltd Method of growing a MCrAIY-coating and an article coated with the MCrAIY-coating
EP1295970A1 (en) * 2001-09-22 2003-03-26 ALSTOM (Switzerland) Ltd MCrAlY type alloy coating
US7371467B2 (en) * 2002-01-08 2008-05-13 Applied Materials, Inc. Process chamber component having electroplated yttrium containing coating
US6942929B2 (en) 2002-01-08 2005-09-13 Nianci Han Process chamber having component with yttrium-aluminum coating
EP1327702A1 (en) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Mcraiy bond coating and method of depositing said mcraiy bond coating
RU2301284C2 (en) * 2002-01-18 2007-06-20 Альстом Текнолоджи Лтд High-temperature protective layer
EP1411210A1 (en) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Method of depositing an oxidation and fatigue resistant MCrAIY-coating
EP1426759B1 (en) 2002-12-06 2011-11-16 Alstom Technology Ltd A non-destructive testing method of determining the depletion of a coating
EP1426760A1 (en) 2002-12-06 2004-06-09 ALSTOM Technology Ltd A non-destructive testing method of determining the service metal temperature of a component
EP1426458B1 (en) * 2002-12-06 2008-03-12 ALSTOM Technology Ltd Method of locally depositing a MCrAlY coating
EP1428982B1 (en) * 2002-12-06 2009-02-04 ALSTOM Technology Ltd A method of depositing a local MCrAIY-coating
ATE329067T1 (en) * 2003-06-26 2006-06-15 Alstom Technology Ltd PROCEDURE FOR APPLYING A MULTI-LAYER SYSTEM
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Also Published As

Publication number Publication date
EP0318803A1 (en) 1989-06-07
DE3882024D1 (en) 1993-07-29
US4973445A (en) 1990-11-27
DE3740478C1 (en) 1989-01-19

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