EP2754733A1 - Anti-corrosion and anti-erosion protective coating - Google Patents
Anti-corrosion and anti-erosion protective coating Download PDFInfo
- Publication number
- EP2754733A1 EP2754733A1 EP13151157.8A EP13151157A EP2754733A1 EP 2754733 A1 EP2754733 A1 EP 2754733A1 EP 13151157 A EP13151157 A EP 13151157A EP 2754733 A1 EP2754733 A1 EP 2754733A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- chromium
- protective layer
- substrate
- nitride
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
- C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
-
- 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
Definitions
- the invention relates to a protective layer against corrosion and erosion of components, which are flowed around by a fluid.
- compressor blades of gas turbines are known which are to be protected against erosion and corrosion.
- FIG. 1 an inventive layer system 1 is shown schematically.
- the layer system 1 in particular for a compressor blade, in particular for a gas turbine 100 (FIG. Fig. 2 ), has a substrate 4.
- an at least two-layer 13 is present, which is in particular only two layers.
- the substrate 4 preferably has a 6% to 18% chromium-containing steel, in particular 12% to 16% chromium steel.
- the underlying layer 7, preferably directly on the substrate 4, serves for corrosion protection, with the outermost layer 10, preferably directly on the underlying layer 7, serving for erosion protection.
- the cathodic corrosion protection is carried out by elemental aluminum (Al), zinc (Zn), magnesium (Mg) and / or alloys (Al-Zn, Al-Mg, Zn-Mg, Al-Zn-Mg) thereof.
- the outermost layer 10 is a hard layer, in particular a metal nitride layer, very particularly CrN, CrAlN (chromium nitride or chromium aluminum nitride layer), TiN and / or TiAlN.
- a metal nitride layer very particularly CrN, CrAlN (chromium nitride or chromium aluminum nitride layer), TiN and / or TiAlN.
- both the lower layer 7 and the outer erosion layer 13 are applied in a coating process, preferably by PVD or sputtering, very particularly by PVD.
- PVD coating is that the roughness of these layers is known to be very good, which provides further advantages from an aerodynamic point of view.
- the layer 13 has a layer thickness of 10 .mu.m to 50 .mu.m.
- the underlying layer 7 preferably has a thickness of 1 ⁇ m-25 ⁇ m, the outer layer 10 has a thickness of 1 ⁇ m-25 ⁇ m.
- the soft bottom layer 7 absorbs the impact energy of the particles, whereby the erosion resistance of the cover layer becomes even higher, and the hard cover layer 10 has increased erosion resistance.
- FIG. 2 shows by way of example a gas turbine 100 in a longitudinal partial section.
- the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
- an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
- annular annular hot gas channel 111 for example.
- turbine stages 112 connected in series form the turbine 108.
- Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
- the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
- air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
- the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
- the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
- the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
- the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
- the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
- the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
- substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
- iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
- Such superalloys are for example from EP 1 204 776 B1 .
- EP 1 306 454 .
- the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earths or hafnium).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
- X is an active element and represents yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earths or hafnium.
- Such alloys are known from the EP 0 486 489 B1 . EP 0 786 017 B1 . EP 0 412 397 B1 or EP 1 306 454 A1 ,
- MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
- Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
- the vane 130 has a guide vane foot (not shown here) facing the inner casing 138 of the turbine 108 and a vane head opposite the vane root.
- the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
Landscapes
- Chemical & Material Sciences (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft eine Schutzschicht gegen Korrosion und Erosion von Bauteilen, die von einem Fluid umströmt werden.The invention relates to a protective layer against corrosion and erosion of components, which are flowed around by a fluid.
Als ein Anwendungsbeispiel von Schutzschichten gegen Korrosion und Erosion sind Verdichterschaufeln von Gasturbinen bekannt, die gegen Erosionen und Korrosion geschützt werden sollen.As an example of use of protective layers against corrosion and erosion, compressor blades of gas turbines are known which are to be protected against erosion and corrosion.
Bekannt sind Systeme, bei denen Lacke mit aluminiumhaltigen Partikeln aufgetragen werden, wobei der Lack zum Erosionsschutz beiträgt und die Aluminiumpartikel im Lack zum Korrosionsschutz beitragen, indem sie als Opferanode wirken.Systems are known in which paints are applied with aluminum-containing particles, wherein the paint contributes to erosion protection and contribute to the aluminum particles in the paint for corrosion protection by acting as a sacrificial anode.
Es ist Aufgabe der Erfindung ein Schutzschichtsystem vorzuschlagen, das verbesserte Eigenschaften gegenüber Korrosion und Erosion aufweist.It is an object of the invention to propose a protective layer system which has improved properties against corrosion and erosion.
Die Aufgabe wird gelöst durch eine Schutzschicht gemäß Anspruch 1.The object is achieved by a protective layer according to claim 1.
In den Unteransprüchen sind weitere vorteilhafte Maßnahmen aufgelistet, die beliebig miteinander kombiniert werden können, um weitere Vorteile zu erzielen.In the dependent claims further advantageous measures are listed, which can be combined with each other in order to achieve further advantages.
Es zeigen:
- Figur 1
- ein erfindungsgemäßes Schichtsystem,
- Figur 2
- eine Gasturbine.
- FIG. 1
- a layer system according to the invention,
- FIG. 2
- a gas turbine.
Die Beschreibung und die Figuren stellen nur Ausführungsbeispiele der Erfindung dar. In
Das Schichtsystem 1, insbesondere für eine Verdichterschaufel, insbesondere für eine Gasturbine 100 (
Auf dem Substrat 4 ist eine zumindest zweilagige Schicht 13 vorhanden, die insbesondere nur zweilagig ist.On the substrate 4, an at least two-
Das Substrat 4 weist vorzugsweise einen 6% bis 18% chromhaltigen Stahl, insbesondere 12% bis 16% Chromstahl auf.The substrate 4 preferably has a 6% to 18% chromium-containing steel, in particular 12% to 16% chromium steel.
Die untenliegende Schicht 7, vorzugsweise direkt auf dem Substrat 4, dient zum Korrosionsschutz, wobei die äußerste Schicht 10, vorzugsweise direkt auf der untenliegenden Schicht 7, zum Erosionsschutz dient.The
Der kathodische Korrosionsschutz erfolgt durch elementares Aluminium (Al), Zink (Zn), Magnesium (Mg) und/oder Legierungen (Al-Zn, Al-Mg, Zn-Mg, Al-Zn-Mg) daraus.The cathodic corrosion protection is carried out by elemental aluminum (Al), zinc (Zn), magnesium (Mg) and / or alloys (Al-Zn, Al-Mg, Zn-Mg, Al-Zn-Mg) thereof.
Die äußerste Schicht 10 ist eine Hartschicht, insbesondere eine Metallnitridschicht, ganz insbesondere CrN, CrAlN (Chromnitrid- oder Chromaluminiumnitridschicht), TiN und/oder TiAlN.The
Vorteilhafterweise werden sowohl die untere Schicht 7 als auch die äußere Erosionsschicht 13 in einem Beschichtungsprozess aufgebracht, vorzugsweise durch PVD oder Sputtering, ganz insbesondere durch PVD.Advantageously, both the
Einen weiteren Vorteil stellt die PVD-Beschichtung dadurch dar, dass die Rauheit dieser Schichten bekannterweise sehr gut ist, was aus aerodynamischer Sicht weitere Vorteile erbringt.A further advantage of the PVD coating is that the roughness of these layers is known to be very good, which provides further advantages from an aerodynamic point of view.
Die Schicht 13 weist eine Schichtdicke von 10µm bis 50µm auf. Die untenliegende Schicht 7 weist vorzugsweise eine Dicke von 1µm - 25 µm auf, die äußere Schicht 10 eine Dicke von 1µm -25 µm.The
Bei einer Gasturbinenverdichterschaufel erfolgt keine Wärmebehandlung der Schicht 13 und sie ist direkt nach dem Aufbringen einsetzbar.In a gas turbine compressor blade, there is no heat treatment of the
Die weiche untere Schicht 7 absorbiert die Aufprallenergie der Partikel, wodurch die Erosionsbeständigkeit der Deckschicht noch höher wird und die harte Deckschicht 10 besitzt eine erhöhte Erosionsbeständigkeit.The
Die
Die Gasturbine 100 weist im Inneren einen um eine Rotationsachse 102 drehgelagerten Rotor 103 mit einer Welle 101 auf, der auch als Turbinenläufer bezeichnet wird.The
Entlang des Rotors 103 folgen aufeinander ein Ansauggehäuse 104, ein Verdichter 105, eine beispielsweise torusartige Brennkammer 110, insbesondere Ringbrennkammer, mit mehreren koaxial angeordneten Brennern 107, eine Turbine 108 und das Abgasgehäuse 109.Along the
Die Ringbrennkammer 110 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108.The
Jede Turbinenstufe 112 ist beispielsweise aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 113 gesehen folgt im Heißgaskanal 111 einer Leitschaufelreihe 115 eine aus Laufschaufeln 120 gebildete Reihe 125.Each
Die Leitschaufeln 130 sind dabei an einem Innengehäuse 138 eines Stators 143 befestigt, wohingegen die Laufschaufeln 120 einer Reihe 125 beispielsweise mittels einer Turbinenscheibe 133 am Rotor 103 angebracht sind.The
An dem Rotor 103 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).Coupled to the
Während des Betriebes der Gasturbine 100 wird vom Verdichter 105 durch das Ansauggehäuse 104 Luft 135 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 105 bereitgestellte verdichtete Luft wird zu den Brennern 107 geführt und dort mit einem Brennmittel vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 113 in der Brennkammer 110 verbrannt. Von dort aus strömt das Arbeitsmedium 113 entlang des Heißgaskanals 111 vorbei an den Leitschaufeln 130 und den Laufschaufeln 120. An den Laufschaufeln 120 entspannt sich das Arbeitsmedium 113 impulsübertragend, so dass die Laufschaufeln 120 den Rotor 103 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the
Die dem heißen Arbeitsmedium 113 ausgesetzten Bauteile unterliegen während des Betriebes der Gasturbine 100 thermischen Belastungen. Die Leitschaufeln 130 und Laufschaufeln 120 der in Strömungsrichtung des Arbeitsmediums 113 gesehen ersten Turbinenstufe 112 werden neben den die Ringbrennkammer 110 auskleidenden Hitzeschildelementen am meisten thermisch belastet.The components exposed to the hot working
Um den dort herrschenden Temperaturen standzuhalten, können diese mittels eines Kühlmittels gekühlt werden.To withstand the prevailing temperatures, they can be cooled by means of a coolant.
Ebenso können Substrate der Bauteile eine gerichtete Struktur aufweisen, d.h. sie sind einkristallin (SX-Struktur) oder weisen nur längsgerichtete Körner auf (DS-Struktur).Likewise, substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
Als Material für die Bauteile, insbesondere für die Turbinenschaufel 120, 130 und Bauteile der Brennkammer 110 werden beispielsweise eisen-, nickel- oder kobaltbasierte Superlegierungen verwendet.As the material for the components, in particular for the
Solche Superlegierungen sind beispielsweise aus der
Ebenso können die Schaufeln 120, 130 Beschichtungen gegen Korrosion (MCrAlX; M ist zumindest ein Element der Gruppe Eisen (Fe), Kobalt (Co), Nickel (Ni), X ist ein Aktivelement und steht für Yttrium (Y) und/oder Silizium, Scandium (Sc) und/oder zumindest ein Element der Seltenen Erden bzw. Hafnium). Solche Legierungen sind bekannt aus der
Auf der MCrAlX kann noch eine Wärmedämmschicht vorhanden sein, und besteht beispielsweise aus ZrO2, Y2O3-ZrO2, d.h. sie ist nicht, teilweise oder vollständig stabilisiert durch Yttriumoxid und/oder Kalziumoxid und/oder Magnesiumoxid.On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
Durch geeignete Beschichtungsverfahren wie z.B. Elektronenstrahlverdampfen (EB-PVD) werden stängelförmige Körner in der Wärmedämmschicht erzeugt.By suitable coating methods, e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
Die Leitschaufel 130 weist einen dem Innengehäuse 138 der Turbine 108 zugewandten Leitschaufelfuß (hier nicht dargestellt) und einen dem Leitschaufelfuß gegenüberliegenden Leitschaufelkopf auf. Der Leitschaufelkopf ist dem Rotor 103 zugewandt und an einem Befestigungsring 140 des Stators 143 festgelegt.The
Claims (6)
zumindest aufweisend:
at least having:
bei dem die kathodisch-wirksame Korrosionsschutzschicht (7) ein elementares Metall oder
eine Legierung aus
Aluminium (Al) und/oder Zink (Zn) und/oder Magnesium (Mg) aufweist,
insbesondere daraus besteht.Protective layer according to claim 1,
wherein the cathodic-effective corrosion protection layer (7) is an elemental metal or
an alloy out
Aluminum (Al) and / or zinc (Zn) and / or magnesium (Mg),
in particular.
bei dem die Erosionsschutzschicht (10) eine Hartstoffschicht,
insbesondere eine Metallnitridverbindung,
ganz insbesondere Chromnitrid (CrN), Chromaluminiumnitrid (CrAlN), Titannitrid (TiN) und/oder Titanaluminiumnitrid (TiAlN) aufweist,
insbesondere daraus besteht.Protective layer according to one or both of Claims 1 or 2,
in which the erosion protection layer (10) has a hard material layer,
in particular a metal nitride compound,
especially chromium nitride (CrN), chromium aluminum nitride (CrAlN), titanium nitride (TiN) and / or titanium aluminum nitride (TiAlN),
in particular.
bei dem die untere Schicht (7) und die äußere Schicht (10) durch dieselben Beschichtungsverfahren,
insbesondere PVD oder Sputtering,
aufgebracht wurden.Protective layer according to one or more of the preceding claims 1 to 3,
in which the lower layer (7) and the outer layer (10) are formed by the same coating methods,
in particular PVD or sputtering,
were applied.
die mehrlagig (7, 10) ausgebildet ist,
insbesondere zur zweilagig.Protective layer according to one or more of the preceding claims,
which is multi-layered (7, 10),
especially for two-ply.
wobei die untenliegende Schicht (7) eine Dicke von 1µm - 25µm und
die äußere Schicht (10) vorzugsweise eine Dicke von 1µm - 25µm aufweist.Protective layer according to one or more of the preceding claims,
wherein the underlying layer (7) has a thickness of 1μm - 25μm and
the outer layer (10) preferably has a thickness of 1μm - 25μm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP13151157.8A EP2754733A1 (en) | 2013-01-14 | 2013-01-14 | Anti-corrosion and anti-erosion protective coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP13151157.8A EP2754733A1 (en) | 2013-01-14 | 2013-01-14 | Anti-corrosion and anti-erosion protective coating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP2754733A1 true EP2754733A1 (en) | 2014-07-16 |
Family
ID=47559291
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP13151157.8A Withdrawn EP2754733A1 (en) | 2013-01-14 | 2013-01-14 | Anti-corrosion and anti-erosion protective coating |
Country Status (1)
| Country | Link |
|---|---|
| EP (1) | EP2754733A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017005460A1 (en) * | 2015-07-06 | 2017-01-12 | Siemens Aktiengesellschaft | Contour-following protective coating for compressor components of gas turbines |
| EP3592953A1 (en) * | 2017-04-28 | 2020-01-15 | Siemens Aktiengesellschaft | Sealing system for a rotor blade and housing |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0366289A1 (en) * | 1988-10-11 | 1990-05-02 | Midwest Research Technologies, Inc. | Multi-layer wear resistant coatings |
| EP0486489B1 (en) | 1989-08-10 | 1994-11-02 | Siemens Aktiengesellschaft | High-temperature-resistant, corrosion-resistant coating, in particular for components of gas turbines |
| EP0412397B1 (en) | 1989-08-10 | 1998-03-25 | Siemens Aktiengesellschaft | Rhenium-containing protective coating with high corrosion and oxidation resistance |
| EP0786017B1 (en) | 1994-10-14 | 1999-03-24 | Siemens Aktiengesellschaft | Protective layer for protecting parts against corrosion, oxidation and excessive thermal stresses, as well as process for producing the same |
| WO1999067435A1 (en) | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
| WO2000044949A1 (en) | 1999-01-28 | 2000-08-03 | Siemens Aktiengesellschaft | Nickel base superalloy with good machinability |
| EP1306454A1 (en) | 2001-10-24 | 2003-05-02 | Siemens Aktiengesellschaft | Rhenium containing protective coating protecting a product against corrosion and oxidation at high temperatures |
| EP1319729A1 (en) | 2001-12-13 | 2003-06-18 | Siemens Aktiengesellschaft | High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy |
| EP1204776B1 (en) | 1999-07-29 | 2004-06-02 | Siemens Aktiengesellschaft | High-temperature part and method for producing the same |
| EP2226409A2 (en) * | 2009-03-06 | 2010-09-08 | General Electric Company | Erosion and corrosion resistant turbine compressor airfoil and method of making the same |
| US20100247321A1 (en) * | 2008-01-08 | 2010-09-30 | General Electric Company | Anti-fouling coatings and articles coated therewith |
| US20120171511A1 (en) * | 2010-12-30 | 2012-07-05 | Hon Hai Precision Industry Co., Ltd. | Process for surface treating aluminum or aluminum alloy and article made with same |
-
2013
- 2013-01-14 EP EP13151157.8A patent/EP2754733A1/en not_active Withdrawn
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0366289A1 (en) * | 1988-10-11 | 1990-05-02 | Midwest Research Technologies, Inc. | Multi-layer wear resistant coatings |
| EP0486489B1 (en) | 1989-08-10 | 1994-11-02 | Siemens Aktiengesellschaft | High-temperature-resistant, corrosion-resistant coating, in particular for components of gas turbines |
| EP0412397B1 (en) | 1989-08-10 | 1998-03-25 | Siemens Aktiengesellschaft | Rhenium-containing protective coating with high corrosion and oxidation resistance |
| EP0786017B1 (en) | 1994-10-14 | 1999-03-24 | Siemens Aktiengesellschaft | Protective layer for protecting parts against corrosion, oxidation and excessive thermal stresses, as well as process for producing the same |
| WO1999067435A1 (en) | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
| WO2000044949A1 (en) | 1999-01-28 | 2000-08-03 | Siemens Aktiengesellschaft | Nickel base superalloy with good machinability |
| EP1204776B1 (en) | 1999-07-29 | 2004-06-02 | Siemens Aktiengesellschaft | High-temperature part and method for producing the same |
| EP1306454A1 (en) | 2001-10-24 | 2003-05-02 | Siemens Aktiengesellschaft | Rhenium containing protective coating protecting a product against corrosion and oxidation at high temperatures |
| EP1319729A1 (en) | 2001-12-13 | 2003-06-18 | Siemens Aktiengesellschaft | High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy |
| US20100247321A1 (en) * | 2008-01-08 | 2010-09-30 | General Electric Company | Anti-fouling coatings and articles coated therewith |
| EP2226409A2 (en) * | 2009-03-06 | 2010-09-08 | General Electric Company | Erosion and corrosion resistant turbine compressor airfoil and method of making the same |
| US20120171511A1 (en) * | 2010-12-30 | 2012-07-05 | Hon Hai Precision Industry Co., Ltd. | Process for surface treating aluminum or aluminum alloy and article made with same |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017005460A1 (en) * | 2015-07-06 | 2017-01-12 | Siemens Aktiengesellschaft | Contour-following protective coating for compressor components of gas turbines |
| RU2691822C1 (en) * | 2015-07-06 | 2019-06-18 | Сименс Акциенгезелльшафт | Repeating contour protective coating for parts of gas turbine compressor |
| US10697068B2 (en) | 2015-07-06 | 2020-06-30 | Siemens Aktiengesellschaft | Contour-following protective layer for compressor components of gas turbines |
| EP3592953A1 (en) * | 2017-04-28 | 2020-01-15 | Siemens Aktiengesellschaft | Sealing system for a rotor blade and housing |
| US11274560B2 (en) | 2017-04-28 | 2022-03-15 | Siemens Energy Global GmbH & Co. KG | Sealing system for a rotor blade and housing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1707653B1 (en) | Coating system | |
| EP1954854B1 (en) | Two-layer thermal barrier coating system containing a pyrochlore phase | |
| EP1951928B1 (en) | Coating system including a mixed gadolinium pyrochlor phase. | |
| EP1990327B1 (en) | Ceramic powder, ceramic layer and layer system with a gadolinium pyrochlorphase solid solution and oxides | |
| EP2382333B1 (en) | Alloy, protective layer and component | |
| EP2576853B1 (en) | Alloy, protective layer and component | |
| EP2230329A1 (en) | Dual layer porous coating system with pyrochlorine phase | |
| EP1793008A1 (en) | Alloy, protective coating for protecting a structural member against corrosion and oxidation at high temperatures and structural member | |
| EP1798299B1 (en) | Alloy, protective coating and component | |
| DE202006009603U1 (en) | Layer system comprises a substrate, a metallic binding layer, and an inner ceramic layer | |
| EP1790743A1 (en) | Alloy, protective layer and component | |
| EP1854899A1 (en) | Alloy, protective layer and component | |
| EP1783236A1 (en) | Alloy, protecting coating for a component protection against corrosion and oxidation at high temperature and component | |
| EP2557201A1 (en) | Alloy, protective coating and component | |
| EP2474413A1 (en) | Alloy, protective coating and component | |
| EP2754733A1 (en) | Anti-corrosion and anti-erosion protective coating | |
| EP2128285A1 (en) | Two-layer MCrAIX coating with different cobalt and nickel contents | |
| EP2661370B1 (en) | Alloy, protective layer and component | |
| EP2611949B1 (en) | Nickel base alloy, protective coating, and component | |
| WO2015071015A1 (en) | Porous ceramic coating system | |
| EP1790746B1 (en) | Alloy, protective layer and component | |
| EP1818419A1 (en) | Alloy, protective layer and component | |
| EP2524064A2 (en) | Alloy, protective layer, and component | |
| EP2354260A1 (en) | Alloy, protective layer and component | |
| EP2206806A1 (en) | Two-layer MCrAIX coating with different cobalt and nickel contents |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| 17P | Request for examination filed |
Effective date: 20130114 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
| AX | Request for extension of the european patent |
Extension state: BA ME |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
| 18D | Application deemed to be withdrawn |
Effective date: 20150117 |