EP2684982A1 - Protective coating for a component of a fluid flow engine - Google Patents
Protective coating for a component of a fluid flow engine Download PDFInfo
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- EP2684982A1 EP2684982A1 EP12175910.4A EP12175910A EP2684982A1 EP 2684982 A1 EP2684982 A1 EP 2684982A1 EP 12175910 A EP12175910 A EP 12175910A EP 2684982 A1 EP2684982 A1 EP 2684982A1
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- component
- hard material
- material layer
- ceramic hard
- layer
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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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
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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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
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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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
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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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
Definitions
- the invention relates to a component for a turbomachine, in particular steam turbine, with a component surface.
- Vibration increases as the blade natural frequencies resonate at operating speeds or other transient frequencies.
- the materials used in thermally stressed zones of a steam turbine must fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above by significantly cheaper materials, such as ferritic 10% chromium steels or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
- the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys.
- the established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C, since the oxidation resistance of such chromium steels in this range is no longer sufficient.
- a component for a turbomachine in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
- a duplex protective layer consisting of two layers is applied to the component.
- the component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer.
- a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer.
- the invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy.
- the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range from 5 ⁇ m to 25 ⁇ m.
- FIG. 1 shows a component 1.
- This component is designed for use in a turbomachine.
- turbomachine is understood, for example, a steam turbine, a compressor or a gas turbine or other thermal machines.
- the component has a component surface 2.
- a ceramic hard material layer 3 is arranged directly.
- the ceramic hard material layer 3 is arranged directly on the component surface, ie, no further layer is arranged between the ceramic hard material layer 3 and the component surface 2.
- On the ceramic hard coating is directly a metallic layer 4 is arranged.
- the metallic layer 4 is arranged directly on the ceramic hard material layer 3, ie no further intermediate layer is arranged between the metallic layer 4 and the ceramic hard material layer 3.
- the embodiment according to FIG. 1 may be referred to as a duplex layer because the erosion and oxidation protection layer on the component surface 2 comprises two layers.
- the ceramic hard material layer 3 is formed such that the thickness of the ceramic hard material layer 3 is in the range of 5 .mu.m to 25 .mu.m.
- the metallic layer 4 is formed in such a way that the metallic layer 4 has a thickness which lies in the range between 5 ⁇ m and 25 ⁇ m.
- the second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 ⁇ m to 25 ⁇ m.
- the component is designed, for example, as a turbine blade for a steam turbine.
- the turbine blade may be a blade or a vane.
- the combination of the two layers comprising the ceramic hard material layer 3 and the metallic layer 4 form a very good protection of the component 1 against oxidation and at the same time also offer good erosion resistance.
- the ceramic hard material layer 3 acts primarily as a diffusion barrier, which ensures that there is no interdiffusion between the base material of the component 1 and the metallic protective layer 4. In addition, this layer already offers good oxidation protection.
- the metallic layer 4 offers a very good protection against oxidation and erosion, in particular against particles which strike the surface perpendicular to the surface.
- the triplex layer is carried out at sites particularly subject to erosion.
- the second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection.
- duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.
Abstract
Description
Die Erfindung betrifft eine Komponente für eine Strömungsmaschine, insbesondere Dampfturbine, mit einer Komponentenoberfläche.The invention relates to a component for a turbomachine, in particular steam turbine, with a component surface.
Schutzschichten für hohe Betriebstemperaturen werden heute im Strömungsmaschinenbau allgemein häufig verwendet. Das Hauptanwendungsgebiet derartiger Hochtemperatur-Schutzschichten findet sich im Bereich thermischer Strömungsmaschinen, insbesondere bei hochbeanspruchten Dampfturbinen-Komponenten. Solche Schutzschichten dienen zur Verlängerung der Lebensdauer der zu schützenden Hochtemperatur-Werkstoffe.Protective coatings for high operating temperatures are commonly used today in turbomachinery. The main field of application of such high-temperature protective layers is found in the field of thermal turbomachines, especially in highly stressed steam turbine components. Such protective layers serve to extend the life of the high-temperature materials to be protected.
Dampfturbinen-Laufschaufeln werden in Umgebungen eingesetzt, in der sie hohen zentrifugalen Belastungen und Schwingungsbeanspruchungen ausgesetzt sind.Steam turbine blades are used in environments exposed to high centrifugal loads and vibratory loads.
Schwingungsbeanspruchungen nehmen zu, wenn die Laufschaufel-Eigenfrequenzen mit Betriebsdrehzahlen oder anderen vorübergehenden Frequenzen in Resonanz kommen.Vibration increases as the blade natural frequencies resonate at operating speeds or other transient frequencies.
Für Komponenten einer Hochdruck- und/oder Mitteldruck-Dampfturbine, wie insbesondere Turbinenschaufeln, die mehr als ca. 600°C heißem Dampf ausgesetzt sind, ergeben sich besondere Anforderungen an die zu verwendenden Werkstoffe. Im Wesentlichen müssen die Werkstoffe, die in thermisch beanspruchten Zonen einer Dampfturbine verwendet werden, zwei Eigenschaften erfüllen. Dies sind zum einen die Oxidationsbeständigkeit und zum anderen die Zeitstandsfestigkeit. Im Grunde genommen sind Werkstoffe bekannt, die solche Anforderungen erfüllen können, wie z.B. Nickel-Basis-Legierungen, die vermehrt zum Einsatz kommen. Allerdings sind solche Werkstoffe vergleichsweise teuer. Daher werden die vorgenannten Werkstoffe durch wesentlich preiswertere Werkstoffe, wie z.B. ferritische 10%-Chromstähle oder ähnliche ersetzt. Der Nachteil solcher ferritischen 10%-igen Chromstähle oder anderer ähnlicher Werkstoffe liegt darin, dass diese keine hinreichende Oxidationsbeständigkeit besitzen und daher ungeeignet sind für manche Anwendungen in der Dampfturbine.For components of a high-pressure and / or medium-pressure steam turbine, in particular turbine blades, which are exposed to more than about 600 ° C hot steam, there are special requirements for the materials to be used. In essence, the materials used in thermally stressed zones of a steam turbine must fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above by significantly cheaper materials, such as ferritic 10% chromium steels or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
Bisher wurden die thermisch beanspruchten Komponenten in Bereichen, die ca. 600°C heißem Dampf ausgesetzt sind, wie z.B. Hochdruck- bzw. Mitteldruck-Turbinenschaufeln, teilweise aus Nickel-Basis-Legierungen hergestellt. Die etablierten Chromstähle werden in der Regel bei Dampftemperaturen im Bereich von deutlich über 600°C nicht mehr verwendet, da die Oxidationsbeständigkeit solcher Chromstähle in diesem Bereich nicht mehr ausreichend ist.Heretofore, the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys. The established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C, since the oxidation resistance of such chromium steels in this range is no longer sufficient.
Es ist Aufgabe der Erfindung, eine geeignete Schutzschicht für eine Komponente einer Strömungsmaschine anzugeben.It is an object of the invention to provide a suitable protective layer for a component of a turbomachine.
Gelöst wird diese Aufgabe durch eine Komponente für eine Strömungsmaschine, insbesondere Dampfturbine, mit einer Komponentenoberfläche, wobei direkt auf die Komponentenoberfläche eine keramische Hartstoffschicht appliziert ist, wobei direkt auf die keramische Hartstoffschicht eine metallische Schicht aufgebracht ist.This object is achieved by a component for a turbomachine, in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
Ein wesentliches Merkmal ist, dass auf die Komponente eine Duplexschutzschicht aufgebracht wird, die aus zwei Schichten besteht. Die Komponente weist eine Komponentenoberfläche auf, wobei direkt auf diese Komponentenoberfläche eine keramische Hartstoffschicht angeordnet ist. Wesentlich hierbei ist, dass die keramische Hartstoffschicht direkt auf die Komponentenoberfläche aufgebracht wird, d.h., dass zwischen der Komponentenoberfläche und der keramischen Hartstoffschicht keine Zwischenschicht angeordnet ist. Erfindungsgemäß wird auf diese keramische Hartstoffschicht direkt eine metallische Schicht aufgebracht. Wesentlich ist hierbei auch wiederum, dass zwischen der keramischen Hartstoffschicht und der metallischen Schicht keine weitere Zwischenschicht angeordnet ist. Die Erfindung geht von dem Gedanken aus, dass die erfindungsgemäße Duplexschicht einen verbesserten Oxidationsschutz und eine verbesserte Erosionsbeständigkeit bietet. Das bedeutet, dass der Grundwerkstoff der Komponente nicht zwingend eine Nickel-Basis-Legierung sein muss. Es können vielmehr preiswertere Werkstoffe statt der Nickel-Basis-Legierung verwendet werden.An essential feature is that a duplex protective layer consisting of two layers is applied to the component. The component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer. According to the invention, a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer. The invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy.
Vorteilhafte Weiterbildungen sind in den Unteransprüchen angegeben.Advantageous developments are specified in the subclaims.
In einer ersten vorteilhaften Weiterbildung weist die Komponente folgende Materialien auf:
- Hochtemperaturgeeignete Cr-legierte Stähle für die Anwendung in Strömungsmaschinen, wie z.B. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1-1 (1.4906), 10CrMo9-10 (1.7380).
- High temperature suitable Cr-alloyed steels for use in turbomachinery, such as X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1-1 (1.4906), 10CrMo9-10 (1.7380).
Die keramische Hartstoffschicht weist vorteilhafterweise folgende Materialien auf:
- CrN
- CrAlN
- TiAlN
- Al2O3
- CrN
- CrAlN
- TiAlN
- Al 2 O 3
In einer weiteren vorteilhaften Weiterbildung weist die metallische Schicht folgende Materialien auf:
- metallische Schicht des Typs MCrAl(Y) oder Ni-basierte Schichten mit mindestens 15% Cr.
- metallic layer of the type MCrAl (Y) or Ni-based layers with at least 15% Cr.
In einer wesentlichen vorteilhaften Weiterbildung wird die Duplexschicht zu einer Triplexschicht weitergebildet, indem direkt auf der metallischen Schicht eine zweite keramische Hartstoffschicht aufgebracht ist. Das bedeutet, dass die Komponente nunmehr drei Schichten übereinander aufweist. Wesentliches Merkmal hierbei ist, dass die keramische Hartstoffschicht direkt auf der metallischen Schicht angeordnet ist, d.h. dass zwischen der keramischen Hartstoffschicht und der metallischen Schicht keine weitere Zwischenschicht aufgebracht ist. In einer vorteilhaften Weiterbildung umfasst die zweite keramische Hartstoffschicht folgende Materialien:
- CrN
- CrAlN
- TiAlN
- Al2O3
- CrN
- CrAlN
- TiAlN
- Al 2 O 3
In vorteilhaften Weiterbildungen weisen die Dicken der keramischen Hartstoffschicht, der metallischen Schutzschicht und der zweiten keramischen Hartstoffschicht Dicken im Bereich von 5µm bis 25µm auf.In advantageous developments, the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range from 5 μm to 25 μm.
Die Erfindung wird anhand eines Ausführungsbeispiels nun näher erläutert.The invention will now be explained in more detail with reference to an embodiment.
Es zeigen:
- Figur 1
- eine erfindungsgemäße Duplex-Schutzschicht;
Figur 2- eine erfindungsgemäße Triplex-Schutzschicht.
- FIG. 1
- a duplex protective layer according to the invention;
- FIG. 2
- a triplex protective layer according to the invention.
Die Komponente weist folgende Materialien auf:
- Hochtemperaturgeeignete Cr-legierte Stähle für die Anwendung in Strömungsmaschinen, wie z.B. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1-1 (1.4906), 10CrMo9-10 (1.7380).
- High temperature suitable Cr-alloyed steels for use in turbomachinery, such as X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1-1 (1.4906), 10CrMo9-10 (1.7380).
Die keramische Hartstoffschicht weist folgende Materialien auf:
- CrN
- CrAlN
- TiAlN
- Al2O3
- CrN
- CrAlN
- TiAlN
- Al 2 O 3
Die metallische Schicht weist folgende Materialien auf:
- metallische Schicht des Typs MCrAl(Y) oder Ni-basierte Schichten mit mindestens 15% Cr.
- metallic layer of the type MCrAl (Y) or Ni-based layers with at least 15% Cr.
Die Ausführungsform gemäß
Die
- CrN
- CrAlN
- TiAlN
- Al2O3
- CrN
- CrAlN
- TiAlN
- Al 2 O 3
Die keramische Hartstoffschicht 3 wird derart ausgebildet, dass die Dicke der keramischen Hartstoffschicht 3 im Bereich von 5µm bis 25µm liegt.The ceramic
Die metallische Schicht 4 wird derart ausgebildet, dass die metallische Schicht 4 eine Dicke aufweist, die im Bereich zwischen 5µm und 25µm liegt.The metallic layer 4 is formed in such a way that the metallic layer 4 has a thickness which lies in the range between 5 μm and 25 μm.
Die zweite keramische Hartstoffschicht 5 wird derart ausgebildet, dass die zweite keramische Hartstoffschicht 5 eine Dicke aufweist, die im Bereich zwischen 5µm bis 25µm liegt.The second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 μm to 25 μm.
Die Komponente wird beispielsweise als Turbinenschaufel für eine Dampfturbine ausgebildet. Die Turbinenschaufel kann eine Laufschaufel oder eine Leitschaufel sein. Die Kombination der beiden Schichten umfassend die keramische Hartstoffschicht 3 und die metallische Schicht 4 bilden einen sehr guten Schutz der Komponente 1 gegen Oxidation und bieten auch gleichzeitig eine gute Erosionsbeständigkeit.The component is designed, for example, as a turbine blade for a steam turbine. The turbine blade may be a blade or a vane. The combination of the two layers comprising the ceramic
Die keramische Hartstoffschicht 3 fungiert dabei in erster Linie als Diffusionsbarriere, die sicherstellt, dass es nicht zur Interdiffusion zwischen Grundwerkstoff der Komponente 1 und der metallischen Schutzschicht 4 kommt. Zusätzlich bietet diese Schicht bereits einen guten Oxidationsschutz. Die metallische Schicht 4 bietet einen sehr guten Oxidations- und Erosionsschutz, insbesondere gegenüber senkrecht auf die Oberfläche treffende Partikel.The ceramic
Die Triplexschicht wird an besonders durch Erosion belasteten Stellen ausgeführt. Die zweite keramische Hartstoffschicht 5 in der Triplexschicht bietet einen besonders guten Schutz als Erosionsschutz und zusätzlich als Oxidationsschutz.The triplex layer is carried out at sites particularly subject to erosion. The second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection.
Die Duplex- und/oder Triplexschichten werden bevorzugt mittels eines PVD-Verfahrens, wobei hier insbesondere SputterVerfahren verwendet werden sollen, aufgebracht.The duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.
Claims (10)
wobei direkt auf die Komponentenoberfläche (2) eine keramische Hartstoffschicht (3) appliziert ist,
wobei direkt auf die keramische Hartstoffschicht (3) eine metallische Schicht (4) aufgebracht ist.Component (1) for a turbomachine, in particular a steam turbine, with a component surface (2),
wherein a ceramic hard material layer (3) is applied directly to the component surface (2),
wherein a metallic layer (4) is applied directly to the ceramic hard material layer (3).
wobei die Komponente folgende Materialien aufweist:
wherein the component comprises the following materials:
wobei die keramische Hartstoffschicht (3) folgende Materialien aufweist:
wherein the ceramic hard material layer (3) comprises the following materials:
wobei die metallische Schicht (4) folgende Materialien aufweist:
wherein the metallic layer (4) comprises the following materials:
wobei direkt auf der metallischen Schicht (4) eine zweite keramische Hartstoffschicht (5) aufgebracht ist.Component (1) according to one of claims 1 to 4,
wherein directly on the metallic layer (4) a second ceramic hard material layer (5) is applied.
wobei die zweite keramische Hartstoffschicht (5) folgende Materialien aufweist:
wherein the second ceramic hard material layer (5) comprises the following materials:
wobei die keramische Hartstoffschicht (3) eine Dicke im Bereich von 5µm bis 25µm aufweist.Component (1) according to one of claims 1 to 6,
wherein the ceramic hard material layer (3) has a thickness in the range of 5μm to 25μm.
wobei die metallische Schicht (4) eine Dicke im Bereich von 5µm bis 25µm aufweist.Component (1) according to one of claims 1 to 7,
wherein the metallic layer (4) has a thickness in the range of 5μm to 25μm.
wobei die zweite keramische Hartstoffschicht (5) eine Dicke im Bereich von 5µm bis 25µm aufweist.Component (1) according to one of claims 1 to 8,
wherein the second ceramic hard material layer (5) has a thickness in the range of 5μm to 25μm.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12175910.4A EP2684982A1 (en) | 2012-07-11 | 2012-07-11 | Protective coating for a component of a fluid flow engine |
PCT/EP2013/062155 WO2014009089A1 (en) | 2012-07-11 | 2013-06-12 | Protective layer for a component of a turbomachine |
CN201390000611.5U CN204803410U (en) | 2012-07-11 | 2013-06-12 | A part for fluid machinery |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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EP12175910.4A EP2684982A1 (en) | 2012-07-11 | 2012-07-11 | Protective coating for a component of a fluid flow engine |
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EP2684982A1 true EP2684982A1 (en) | 2014-01-15 |
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EP12175910.4A Withdrawn EP2684982A1 (en) | 2012-07-11 | 2012-07-11 | Protective coating for a component of a fluid flow engine |
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EP (1) | EP2684982A1 (en) |
CN (1) | CN204803410U (en) |
WO (1) | WO2014009089A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2907888A1 (en) * | 2014-02-14 | 2015-08-19 | Siemens Aktiengesellschaft | Compressor blade with erosion resistant hard material coating |
DE102016222296A1 (en) * | 2016-11-14 | 2018-05-17 | Siemens Aktiengesellschaft | Multi-layer aluminum-containing protective coating and component |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
AT7941U1 (en) * | 2004-12-02 | 2005-11-15 | Ceratizit Austria Gmbh | TOOL FOR DISCONTINUING MACHINING |
US20070078521A1 (en) * | 2005-09-30 | 2007-04-05 | Depuy Products, Inc. | Aluminum oxide coated implants and components |
DE102007050918A1 (en) * | 2006-10-26 | 2008-04-30 | General Electric Co. | Turbine components have erosion-resistant coating applied using electron beam physical vapor deposition or ion plasma arc coating |
DE102007027335A1 (en) * | 2007-06-14 | 2008-12-18 | Mtu Aero Engines Gmbh | Wear protection coating and component with a wear protection coating |
EP2072636A2 (en) * | 2007-12-21 | 2009-06-24 | Sandvik Intellectual Property AB | Method of making a coated cutting tool, and cutting tools thereof |
-
2012
- 2012-07-11 EP EP12175910.4A patent/EP2684982A1/en not_active Withdrawn
-
2013
- 2013-06-12 CN CN201390000611.5U patent/CN204803410U/en not_active Expired - Fee Related
- 2013-06-12 WO PCT/EP2013/062155 patent/WO2014009089A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
AT7941U1 (en) * | 2004-12-02 | 2005-11-15 | Ceratizit Austria Gmbh | TOOL FOR DISCONTINUING MACHINING |
US20070078521A1 (en) * | 2005-09-30 | 2007-04-05 | Depuy Products, Inc. | Aluminum oxide coated implants and components |
DE102007050918A1 (en) * | 2006-10-26 | 2008-04-30 | General Electric Co. | Turbine components have erosion-resistant coating applied using electron beam physical vapor deposition or ion plasma arc coating |
DE102007027335A1 (en) * | 2007-06-14 | 2008-12-18 | Mtu Aero Engines Gmbh | Wear protection coating and component with a wear protection coating |
EP2072636A2 (en) * | 2007-12-21 | 2009-06-24 | Sandvik Intellectual Property AB | Method of making a coated cutting tool, and cutting tools thereof |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2907888A1 (en) * | 2014-02-14 | 2015-08-19 | Siemens Aktiengesellschaft | Compressor blade with erosion resistant hard material coating |
WO2015121000A1 (en) * | 2014-02-14 | 2015-08-20 | Siemens Aktiengesellschaft | Compressor blade having an erosion-resistant hard material coating |
US10465535B2 (en) | 2014-02-14 | 2019-11-05 | Siemens Aktiengesellschaft | Compressor blade or vane having an erosion-resistant hard material coating |
DE102016222296A1 (en) * | 2016-11-14 | 2018-05-17 | Siemens Aktiengesellschaft | Multi-layer aluminum-containing protective coating and component |
US11078574B2 (en) | 2016-11-14 | 2021-08-03 | Siemens Energy Global GmbH & Co. KG | Multilayered aluminiferous protective coating and component |
Also Published As
Publication number | Publication date |
---|---|
WO2014009089A1 (en) | 2014-01-16 |
CN204803410U (en) | 2015-11-25 |
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