EP2085498A1 - Ceramic heat insulation layers with increased resistance to corrosion due to impure fuels - Google Patents
Ceramic heat insulation layers with increased resistance to corrosion due to impure fuels Download PDFInfo
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- EP2085498A1 EP2085498A1 EP08002050A EP08002050A EP2085498A1 EP 2085498 A1 EP2085498 A1 EP 2085498A1 EP 08002050 A EP08002050 A EP 08002050A EP 08002050 A EP08002050 A EP 08002050A EP 2085498 A1 EP2085498 A1 EP 2085498A1
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- Prior art keywords
- coating
- layer system
- turbine blade
- coatings
- ceramic
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- 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.)
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Classifications
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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
- C23C28/04—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 only coatings of inorganic non-metallic material
- C23C28/042—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 only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
Definitions
- the present invention relates to a ceramic coating for a component which is exposed to high temperatures, in particular ceramic coatings for a turbine blade.
- Ceramic coatings for turbine blades are, for example, from DE 198 01 424 known.
- the ceramic coatings described in this application relate to compositions consisting essentially of barium zirconate and / or lanthanum zirconate and / or strontium zirconate.
- coatings for turbine blades consist of zirconia or by the addition of yttria partially stabilized zirconia.
- a disadvantage of yttria-stabilized zirconia ceramics is that when used as a coating for turbine blades operated under heavy oil conditions, they may be subject to degradation phenomena.
- the object of the present invention is to provide a ceramic coating for components of the type mentioned, which have good thermal insulation properties at the same time high stability even in aggressive environments.
- the object is achieved according to the invention by a ceramic coating which contains one or more compounds selected from Al 2 TiO 5 , alkaline earth silicates, magnesium titanates, ZrV 2 O 7 and Mg 3 (VO 4 ) 2 .
- the invention is based on the finding that the conventionally used for turbine blades Ceramic coatings based on yttrium-stabilized zirconia are decomposed by the attack of sodium, potassium, vanadium or magnesium. These elements occur primarily in the operation of a gas turbine under heavy oil conditions or in contact with low-purity synthesis gases.
- the contact of the yttria-stabilized zirconia with the above-mentioned elements in detail leads to a destabilization of the yttria, whereby the destruction of the ceramic is caused.
- the ceramic coatings according to the invention can generally be used for components which are exposed to high temperatures.
- a possible method for producing such a coating is that a coating of the type according to the invention is applied to a substrate which predetermines the basic shape of the component.
- the coating can be effected by physical vapor deposition, which is also referred to as PVD (physical vapor deposition), in particular also by physical electron beam vapor deposition (EB-PVD method, electron beam physical vapor deposition).
- PVD physical vapor deposition
- EB-PVD method electron beam physical vapor deposition
- the coating can also be applied by plasma spraying, in particular by atmospheric plasma spraying.
- the coating according to the invention contains at least 90 wt.%, In particular at least 95 wt.%, Particularly preferably greater than 99 wt.% Of Al 2 TiO 5 , alkaline earth silicates, magnesium titanates, ZrV 2 O 7 and Mg 3 (VO 4 ) 2 .
- This is particularly advantageous because ceramics of these compounds already without further additives have good thermal insulation properties and high resistance to aggressive environments.
- the coating according to the invention consists exclusively of the abovementioned compounds, in particular of a single one of the abovementioned compounds.
- the presence of small amounts of impurities in particular in the order of less than 1 wt.%, In particular less than 0.1 wt.% Possible.
- the alkaline earth silicates are selected from steatite, cordierite, barium silicate and calcium silicate. It is also preferable that the magnesium titanates are selected from MgTiO 3 and Mg 2 TiO 4 . This is particularly advantageous because coatings of ceramic materials of this type have a particularly high resistance to attack by sodium, potassium, vanadium or magnesium.
- the coating according to the invention has no addition of stabilizers. This is particularly advantageous since the coatings according to the invention can thus be applied as a single-phase system. Possible errors in the weighing of stabilizing additives can be ruled out from the outset. The possibility to dispense with the addition of stabilizers is due to the high resistance of the coatings according to the invention even in aggressive environments.
- the coatings according to the invention are largely free of yttrium oxide.
- the coatings according to the invention do not contain yttrium oxide. This is special advantageous, since this stabilizer commonly used in coating ceramics for turbine blades is responsible for the destruction of the ceramic materials under the aggressive conditions described above.
- the coatings according to the invention do not require the addition of yttrium or yttrium oxide.
- the coating has a thickness of 200 to 1000 .mu.m, in particular from 200 to 500 .mu.m.
- Coatings, which are applied with these thicknesses to the components to be coated have the particular advantage that even with coatings of this thickness sufficient thermal insulation of the underlying material is ensured at the same time good stability against aggressive environments.
- Another object of the present invention relates to a layer system which contains at least one coating of the type according to the invention.
- a particularly preferred layer system is formed by applying a coating according to the invention to a layer of partially stabilized zirconium oxide already present on the component. If appropriate, further layers, in particular adhesion promoter layers, may be introduced between the layer of partially stabilized zirconium oxide and the component surface.
- a multilayer coating system of this type is particularly advantageous since possible differences in the coefficients of thermal expansion of the coatings of the invention and the base material can be compensated by the intermediate layer of partially stabilized zirconium oxide, whereby the thermal stability of the coating can be increased. Turbines coated with the layer systems according to the invention can therefore be operated at higher temperatures. This is special This is relevant because the operating efficiency of turbines increases with their operating temperature.
- Another object of the present invention is the use of a coating according to the invention or a layer system which contains a coating according to the invention, as a thermal barrier coating for a component which is exposed to high temperatures.
- a coating according to the invention or a layer system which contains a coating according to the invention as a thermal barrier coating for a component which is exposed to high temperatures.
- the coatings and layer systems according to the invention have good heat-insulating properties combined with high resistance even in aggressive environments. These properties are particularly advantageous when using such a coating or such a layer system as a coating for a turbine blade, in particular a turbine blade for a steam turbine.
- Another object of the present invention is a turbine blade having a coating according to the invention or a layer system of the type mentioned above. This is particularly advantageous, since turbine blades with such ceramic coatings, especially when used in a steam turbine, have a very high temperature resistance and are operated under severe oil conditions or under contact with low-purity synthesis gases due to the good stability of the coating or the layer systems against aggressive environments at high temperatures can.
Abstract
Description
Die vorliegende Erfindung betrifft eine keramische Beschichtung für ein Bauteil, das hohen Temperaturen ausgesetzt ist, insbesondere keramische Beschichtungen für eine Turbinenschaufel.The present invention relates to a ceramic coating for a component which is exposed to high temperatures, in particular ceramic coatings for a turbine blade.
Keramische Beschichtungen für Turbinenschaufeln sind beispielsweise aus der
Weiterhin sind Beschichtungen für Turbinenschaufeln bekannt, die auf Zirkondioxid oder durch Zusatz von Yttriumoxid teilstabilisiertem Zirkondioxid bestehen.Furthermore, coatings for turbine blades are known, which consist of zirconia or by the addition of yttria partially stabilized zirconia.
Nachteilig bei Yttrium-stabilisierten Zirkon-Keramiken ist, dass diese, wenn sie als Beschichtung für Turbinenschaufeln verwendet werden, die unter Schwerölbedingungen betrieben werden, Zersetzungserscheinungen unterliegen können.A disadvantage of yttria-stabilized zirconia ceramics is that when used as a coating for turbine blades operated under heavy oil conditions, they may be subject to degradation phenomena.
Die Aufgabe der vorliegenden Erfindung besteht darin, eine keramische Beschichtung für Bauteile der eingangs genannten Art zu schaffen, welche gute Wärmedämmeigenschaften bei gleichzeitig hoher Stabilität auch in aggressiven Umgebungen aufweisen.The object of the present invention is to provide a ceramic coating for components of the type mentioned, which have good thermal insulation properties at the same time high stability even in aggressive environments.
Die Aufgabe ist erfindungsgemäß gelöst durch eine keramische Beschichtung, welche eine oder mehrere Verbindungen enthält, die ausgewählt sind aus Al2TiO5, Erdalkalisilikaten, Magnesiumtitanaten, ZrV2O7 und Mg3(VO4)2.The object is achieved according to the invention by a ceramic coating which contains one or more compounds selected from Al 2 TiO 5 , alkaline earth silicates, magnesium titanates, ZrV 2 O 7 and Mg 3 (VO 4 ) 2 .
Der Erfindung liegt die Erkenntnis zugrunde, dass die üblicherweise für Turbinenschaufeln eingesetzten Keramikbeschichtungen auf Basis von Yttrium-stabilisiertem Zirkonoxid durch den Angriff von Natrium, Kalium, Vanadium oder Magnesium zersetzt werden. Diese Elemente treten vornehmlich beim Betrieb einer Gasturbine unter Schwerölbedingungen oder bei Kontakt mit gering gereinigten Synthesegasen auf. Dabei führt der Kontakt der Yttriumoxidstabilisierten Zirkonkeramik mit den oben genannten Elementen im Detail zu einer Destabilisierung des Yttriumoxids, wodurch die Zerstörung der Keramik hervorgerufen wird.The invention is based on the finding that the conventionally used for turbine blades Ceramic coatings based on yttrium-stabilized zirconia are decomposed by the attack of sodium, potassium, vanadium or magnesium. These elements occur primarily in the operation of a gas turbine under heavy oil conditions or in contact with low-purity synthesis gases. The contact of the yttria-stabilized zirconia with the above-mentioned elements in detail leads to a destabilization of the yttria, whereby the destruction of the ceramic is caused.
Mit Hilfe der in der vorliegenden Erfindung beschriebenen keramischen Beschichtungen ist es nunmehr möglich, Gasturbinenschaufeln mit Wärmedämmschichten auszurüsten, die auch unter den oben genannten aggressiven Bedingungen betrieben werden können, ohne dass die keramischen Beschichtungen angegriffen werden.With the aid of the ceramic coatings described in the present invention, it is now possible to equip gas turbine blades with heat-insulating layers which can also be operated under the abovementioned aggressive conditions without the ceramic coatings being attacked.
Die erfindungsgemäßen keramischen Beschichtungen können allgemein für Bauteile verwendet werden, die hohen Temperaturen ausgesetzt werden.The ceramic coatings according to the invention can generally be used for components which are exposed to high temperatures.
Ein mögliches Verfahren zur Herstellung einer derartigen Beschichtung besteht darin, dass auf ein die Grundform des Bauteils vorgebendes Substrat eine Beschichtung der erfindungsgemäßen Art aufgebracht wird.A possible method for producing such a coating is that a coating of the type according to the invention is applied to a substrate which predetermines the basic shape of the component.
Die Beschichtung kann dabei durch physikalisches Aufdampfen, das auch als PVD-Verfahren (physical vapour deposition) bezeichnet wird, insbesondere auch durch physikalisches Elektronenstrahl-Aufdampfen (EB-PVD-Verfahren; electron beam physical vapour deposition) erfolgen. Die Beschichtung kann darüber hinaus auch durch Plasmaspritzen, insbesondere durch atmosphärisches Plasmaspritzen aufgebracht werden.The coating can be effected by physical vapor deposition, which is also referred to as PVD (physical vapor deposition), in particular also by physical electron beam vapor deposition (EB-PVD method, electron beam physical vapor deposition). In addition, the coating can also be applied by plasma spraying, in particular by atmospheric plasma spraying.
Nach einer bevorzugten Ausführungsform der erfindungsgemäßen Beschichtung enthält diese wenigstens 90 Gew.%, insbesondere wenigstens 95 Gew.%, besonders bevorzugt größer 99 Gew.% an Al2TiO5, Erdalkalisilikaten, Magnesiumtitanaten, ZrV2O7 und Mg3(VO4)2. Dies ist besonders vorteilhaft, da Keramiken aus diesen Verbindungen bereits ohne weitere Zusätze gute Wärmedämmeigenschaften bei gleichzeitig hoher Beständigkeit gegenüber aggressiven Umgebungen aufweisen. Es ist insbesondere vorteilhaft, wenn die erfindungsgemäße Beschichtung ausschließlich aus den oben genannten Verbindungen besteht, insbesondere aus einer einzigen der oben genannten Verbindungen. Hierbei ist das Vorhandensein geringer Mengen Verunreinigungen insbesondere in der Größenordnung kleiner als 1 Gew.%, insbesondere kleiner als 0,1 Gew.% möglich.According to a preferred embodiment of the coating according to the invention this contains at least 90 wt.%, In particular at least 95 wt.%, Particularly preferably greater than 99 wt.% Of Al 2 TiO 5 , alkaline earth silicates, magnesium titanates, ZrV 2 O 7 and Mg 3 (VO 4 ) 2 . This is particularly advantageous because ceramics of these compounds already without further additives have good thermal insulation properties and high resistance to aggressive environments. It is particularly advantageous if the coating according to the invention consists exclusively of the abovementioned compounds, in particular of a single one of the abovementioned compounds. Here, the presence of small amounts of impurities, in particular in the order of less than 1 wt.%, In particular less than 0.1 wt.% Possible.
Gemäß einer bevorzugten Ausführungsform der erfindungsgemäßen Beschichtung werden die Erdalkalisilikate aus Steatit, Cordierit, Bariumsilikat und Calciumsilikat ausgewählt. Es ist ebenso bevorzugt, dass die Magnesiumtitanate ausgewählt sind aus MgTiO3 und Mg2TiO4 ausgewählt werden. Dies ist besonders vorteilhaft, da Beschichtungen aus keramischen Materialien dieser Art eine besonders hohe Resistenz gegenüber einem Angriff von Natrium, Kalium, Vanadium oder Magnesium aufweisen.According to a preferred embodiment of the coating according to the invention, the alkaline earth silicates are selected from steatite, cordierite, barium silicate and calcium silicate. It is also preferable that the magnesium titanates are selected from MgTiO 3 and Mg 2 TiO 4 . This is particularly advantageous because coatings of ceramic materials of this type have a particularly high resistance to attack by sodium, potassium, vanadium or magnesium.
Gemäß einer weiteren bevorzugten Ausführungsform weist die erfindungsgemäße Beschichtung keinen Zusatz von Stabilisatoren auf. Dies ist besonders vorteilhaft, da die erfindungsgemäßen Beschichtungen somit als einphasiges System aufgebracht werden können. Mögliche Fehler beim Einwiegen von stabilisierenden Zusatzstoffen lassen sich dadurch von vornherein ausschließen. Die Möglichkeit auf den Zusatz von Stabilisatoren zu verzichten ist in der hohen Beständigkeit der erfindungsgemäßen Beschichtungen selbst in aggressiven Umgebungen begründet.According to a further preferred embodiment, the coating according to the invention has no addition of stabilizers. This is particularly advantageous since the coatings according to the invention can thus be applied as a single-phase system. Possible errors in the weighing of stabilizing additives can be ruled out from the outset. The possibility to dispense with the addition of stabilizers is due to the high resistance of the coatings according to the invention even in aggressive environments.
Gemäß einer besonders bevorzugten Ausführungsform der vorliegenden Erfindung sind die erfindungsgemäßen Beschichtungen weitestgehend frei von Yttriumoxid. Ganz besonders bevorzugt enthalten die erfindungsgemäßen Beschichtungen kein Yttriumoxid. Dies ist besonders vorteilhaft, da dieser üblicherweise in Beschichtungskeramiken für Turbinenschaufeln eingesetzte Stabilisator für die Zerstörung der keramischen Werkstoffe unter den oben beschriebenen aggressiven Bedingungen verantwortlich ist. Die erfindungsgemäßen Beschichtungen kommen hingegen ohne den Zusatz von Yttrium oder Yttriumoxid aus.According to a particularly preferred embodiment of the present invention, the coatings according to the invention are largely free of yttrium oxide. Most preferably, the coatings according to the invention do not contain yttrium oxide. This is special advantageous, since this stabilizer commonly used in coating ceramics for turbine blades is responsible for the destruction of the ceramic materials under the aggressive conditions described above. By contrast, the coatings according to the invention do not require the addition of yttrium or yttrium oxide.
Nach einer besonders bevorzugten Ausführungsform der vorliegenden Erfindung weist die Beschichtung eine Dicke von 200 bis 1000 µm, insbesondere von 200 bis 500 µm auf. Beschichtungen, welche mit diesen Dicken auf die zu beschichtenden Bauteile aufgebracht werden, weisen den besonderen Vorteil auf, dass bereits bei Beschichtungen dieser Stärke eine ausreichende Wärmedämmung des darunterliegenden Materials bei gleichzeitig guter Stabilität gegenüber aggressiven Umgebungen gewährleistet ist.According to a particularly preferred embodiment of the present invention, the coating has a thickness of 200 to 1000 .mu.m, in particular from 200 to 500 .mu.m. Coatings, which are applied with these thicknesses to the components to be coated, have the particular advantage that even with coatings of this thickness sufficient thermal insulation of the underlying material is ensured at the same time good stability against aggressive environments.
Ein weiterer Gegenstand der vorliegenden Erfindung betrifft ein Schichtsystem, welches wenigstens eine Beschichtung der erfindungsgemäßen Art enthält.Another object of the present invention relates to a layer system which contains at least one coating of the type according to the invention.
Ein besonders bevorzugtes Schichtsystem wird dadurch gebildet, dass eine erfindungsgemäße Beschichtung auf eine bereits auf dem Bauteil befindliche Schicht aus teilstabilisiertem Zirkonoxid aufgebracht wird. Zwischen die Schicht aus teilstabilisiertem Zirkonoxid und der Bauteiloberfläche können gegebenenfalls weitere Schichten, insbesondere Haftvermittlerschichten eingebracht sein. Ein mehrlagiges Schichtsystem dieser Art ist besonders vorteilhaft, da durch die Zwischenschicht aus teilstabilisiertem Zirkonoxid mögliche Unterschiede in den thermischen Ausdehnungskoeffizienten der erfindungsgemäßen Beschichtungen und dem Grundwerkstoff kompensiert werden können, wodurch sich die thermische Stabilität der Beschichtung steigern lässt. Mit den erfindungsgemäßen Schichtsystemen beschichtete Turbinen können deshalb bei höheren Temperaturen betrieben werden. Dies ist insbesondere deshalb relevant, da die Betriebseffizienz von Turbinen mit deren Betriebstemperatur steigt.A particularly preferred layer system is formed by applying a coating according to the invention to a layer of partially stabilized zirconium oxide already present on the component. If appropriate, further layers, in particular adhesion promoter layers, may be introduced between the layer of partially stabilized zirconium oxide and the component surface. A multilayer coating system of this type is particularly advantageous since possible differences in the coefficients of thermal expansion of the coatings of the invention and the base material can be compensated by the intermediate layer of partially stabilized zirconium oxide, whereby the thermal stability of the coating can be increased. Turbines coated with the layer systems according to the invention can therefore be operated at higher temperatures. This is special This is relevant because the operating efficiency of turbines increases with their operating temperature.
Ein weiterer Gegenstand der vorliegenden Erfindung ist die Verwendung einer erfindungsgemäßen Beschichtung oder eines Schichtsystems, welches eine erfindungsgemäße Beschichtung enthält, als Wärmedämmschicht für ein Bauteil, das hohen Temperaturen ausgesetzt ist. Dies ist besonders vorteilhaft, da die erfindungsgemäßen Beschichtungen und Schichtsysteme gute Wärmedämmeigenschaften bei gleichzeitig hoher Beständigkeit auch in aggressiven Umgebungen besitzen. Diese Eigenschaften sind insbesondere vorteilhaft bei einer Verwendung einer solchen Beschichtung oder eines solchen Schichtsystems als Beschichtung für eine Turbinenschaufel, insbesondere einer Turbinenschaufel für eine Dampfturbine.Another object of the present invention is the use of a coating according to the invention or a layer system which contains a coating according to the invention, as a thermal barrier coating for a component which is exposed to high temperatures. This is particularly advantageous, since the coatings and layer systems according to the invention have good heat-insulating properties combined with high resistance even in aggressive environments. These properties are particularly advantageous when using such a coating or such a layer system as a coating for a turbine blade, in particular a turbine blade for a steam turbine.
Ein weiterer Gegenstand der vorliegenden Erfindung ist eine Turbinenschaufel, die eine erfindungsgemäße Beschichtung oder ein Schichtsystem der oben genannten Art aufweist. Dies ist besonders vorteilhaft, da Turbinenschaufeln mit solchen keramischen Beschichtungen insbesondere beim Einsatz in einer Dampfturbine eine sehr hohe Temperaturbeständigkeit aufweisen und aufgrund der guten Stabilität der Beschichtung oder der Schichtsysteme gegenüber aggressiven Umgebungen bei hohen Temperaturen auch unter Schwerölbedingungen oder unter Kontakt mit gering gereinigten Synthesegasen betrieben werden können.Another object of the present invention is a turbine blade having a coating according to the invention or a layer system of the type mentioned above. This is particularly advantageous, since turbine blades with such ceramic coatings, especially when used in a steam turbine, have a very high temperature resistance and are operated under severe oil conditions or under contact with low-purity synthesis gases due to the good stability of the coating or the layer systems against aggressive environments at high temperatures can.
Claims (12)
dadurch gekennzeichnet, dass
der Gehalt an Al2TiO5, Erdalkalisilikaten, Magnesiumtitanaten, ZrV2O7 und Mg3(VO4)2 in der Beschichtung wenigstens 90 Gew.-%, insbesondere wenigstens 95 Gew.-% beträgt.Coating according to claim 1,
characterized in that
the content of Al 2 TiO 5 , alkaline earth silicates, magnesium titanates, ZrV 2 O 7 and Mg 3 (VO 4 ) 2 in the coating is at least 90% by weight, in particular at least 95% by weight.
dadurch gekennzeichnet, dass
die Erdalkalisilikate ausgewählt sind aus Steatit, Cordierit, Bariumsilikat und Calciumsilikat.Coating according to claim 1 or 2,
characterized in that
the alkaline earth silicates are selected from steatite, cordierite, barium silicate and calcium silicate.
dadurch gekennzeichnet, dass
die Magnesiumtitanate ausgewählt sind aus MgTiO3 und Mg2TiO4.Coating according to claim 1 or 2,
characterized in that
the magnesium titanates are selected from MgTiO 3 and Mg 2 TiO 4 .
dadurch gekennzeichnet, dass
die Beschichtung keine Stabilisatoren aufweist.Coating according to one of the preceding claims,
characterized in that
the coating has no stabilizers.
dadurch gekennzeichnet, dass
die Beschichtung weitestgehend frei von Yttrium ist.Coating according to one of the preceding claims,
characterized in that
the coating is largely free of yttrium.
dadurch gekennzeichnet, dass
die Beschichtung eine Dicke von 200 bis 1000 µm und insbesondere 200 bis 500 µm aufweist.Coating according to one of the preceding claims,
characterized in that
the coating has a thickness of 200 to 1000 microns and more preferably 200 to 500 microns.
dadurch gekennzeichnet, dass
das Bauteil eine Turbinenschaufel, insbesondere einer Dampfturbine ist.Use according to claim 10,
characterized in that
the component is a turbine blade, in particular a steam turbine.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP08002050A EP2085498A1 (en) | 2008-02-04 | 2008-02-04 | Ceramic heat insulation layers with increased resistance to corrosion due to impure fuels |
| PCT/EP2008/066809 WO2009097931A1 (en) | 2008-02-04 | 2008-12-04 | Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels |
| EP08872105A EP2238278B1 (en) | 2008-02-04 | 2008-12-04 | Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels |
| US12/865,910 US8592044B2 (en) | 2008-02-04 | 2008-12-04 | Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP08002050A EP2085498A1 (en) | 2008-02-04 | 2008-02-04 | Ceramic heat insulation layers with increased resistance to corrosion due to impure fuels |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP2085498A1 true EP2085498A1 (en) | 2009-08-05 |
Family
ID=39535650
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP08002050A Withdrawn EP2085498A1 (en) | 2008-02-04 | 2008-02-04 | Ceramic heat insulation layers with increased resistance to corrosion due to impure fuels |
| EP08872105A Not-in-force EP2238278B1 (en) | 2008-02-04 | 2008-12-04 | Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP08872105A Not-in-force EP2238278B1 (en) | 2008-02-04 | 2008-12-04 | Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8592044B2 (en) |
| EP (2) | EP2085498A1 (en) |
| WO (1) | WO2009097931A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2366813A3 (en) * | 2010-03-05 | 2011-12-21 | General Electric Company | Layered Article |
| EP2428765A1 (en) | 2010-09-14 | 2012-03-14 | Siemens Aktiengesellschaft | Method and device for processing turbine blades |
| CN117265452A (en) * | 2023-11-22 | 2023-12-22 | 北京理工大学 | Water-cooled copper crucible heat shielding composite coating and preparation method thereof |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11479846B2 (en) | 2014-01-07 | 2022-10-25 | Honeywell International Inc. | Thermal barrier coatings for turbine engine components |
| FR3110003A1 (en) | 2020-05-11 | 2021-11-12 | Institut Mines Telecom | Screen for displaying a projected image with a structured coating. |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3644664A1 (en) * | 1986-12-30 | 1988-07-14 | Didier Werke Ag | Aluminium titanate ceramic and use thereof |
| EP0494389A1 (en) * | 1991-01-07 | 1992-07-15 | Westinghouse Electric Corporation | Corrosion resistant magnesium titanate coatings for gas turbines |
| US5236787A (en) * | 1991-07-29 | 1993-08-17 | Caterpillar Inc. | Thermal barrier coating for metallic components |
| US5667898A (en) * | 1989-01-30 | 1997-09-16 | Lanxide Technology Company, Lp | Self-supporting aluminum titanate composites and products relating thereto |
| DE19801424A1 (en) | 1998-01-16 | 1999-07-29 | Forschungszentrum Juelich Gmbh | High melting point heat insulating material especially for coating nickel base superalloy gas turbine blades or combustion chambers |
| US20070248764A1 (en) * | 2004-05-26 | 2007-10-25 | Mtu Aero Engines Gmbh | Heat-Insulating Layer System |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3832245A (en) * | 1971-06-14 | 1974-08-27 | Asea Ab | Method of manufacturing an object of silicon steel having low sulphur content |
| US4255495A (en) * | 1979-10-31 | 1981-03-10 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Corrosion resistant thermal barrier coating |
| US4761346A (en) * | 1984-11-19 | 1988-08-02 | Avco Corporation | Erosion-resistant coating system |
| BR9408073A (en) * | 1993-11-16 | 1997-08-12 | Ici Australia Operations | Anti-corrosion treatment of metal-coated steel with aluminum zinc or alloy coatings thereof |
| NZ531492A (en) * | 2001-08-28 | 2007-11-30 | Eden Research Plc | Treatment and prevention of fungal, bacterial, mycoplasma and phytoplasma infections in plants comprising terpene compounds in true solution |
| US7226668B2 (en) * | 2002-12-12 | 2007-06-05 | General Electric Company | Thermal barrier coating containing reactive protective materials and method for preparing same |
-
2008
- 2008-02-04 EP EP08002050A patent/EP2085498A1/en not_active Withdrawn
- 2008-12-04 US US12/865,910 patent/US8592044B2/en not_active Expired - Fee Related
- 2008-12-04 WO PCT/EP2008/066809 patent/WO2009097931A1/en active Application Filing
- 2008-12-04 EP EP08872105A patent/EP2238278B1/en not_active Not-in-force
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3644664A1 (en) * | 1986-12-30 | 1988-07-14 | Didier Werke Ag | Aluminium titanate ceramic and use thereof |
| US5667898A (en) * | 1989-01-30 | 1997-09-16 | Lanxide Technology Company, Lp | Self-supporting aluminum titanate composites and products relating thereto |
| EP0494389A1 (en) * | 1991-01-07 | 1992-07-15 | Westinghouse Electric Corporation | Corrosion resistant magnesium titanate coatings for gas turbines |
| US5236787A (en) * | 1991-07-29 | 1993-08-17 | Caterpillar Inc. | Thermal barrier coating for metallic components |
| DE19801424A1 (en) | 1998-01-16 | 1999-07-29 | Forschungszentrum Juelich Gmbh | High melting point heat insulating material especially for coating nickel base superalloy gas turbine blades or combustion chambers |
| US20070248764A1 (en) * | 2004-05-26 | 2007-10-25 | Mtu Aero Engines Gmbh | Heat-Insulating Layer System |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2366813A3 (en) * | 2010-03-05 | 2011-12-21 | General Electric Company | Layered Article |
| EP2428765A1 (en) | 2010-09-14 | 2012-03-14 | Siemens Aktiengesellschaft | Method and device for processing turbine blades |
| WO2012035060A1 (en) | 2010-09-14 | 2012-03-22 | Siemens Aktiengesellschaft | Method for treating turbine blades and device therefor |
| US9403245B2 (en) | 2010-09-14 | 2016-08-02 | Siemens Aktiengesellschaft | Method for treating turbine blades and device therefor |
| CN117265452A (en) * | 2023-11-22 | 2023-12-22 | 北京理工大学 | Water-cooled copper crucible heat shielding composite coating and preparation method thereof |
| CN117265452B (en) * | 2023-11-22 | 2024-02-06 | 北京理工大学 | Water-cooled copper crucible heat shielding composite coating and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2238278B1 (en) | 2012-10-17 |
| WO2009097931A1 (en) | 2009-08-13 |
| US8592044B2 (en) | 2013-11-26 |
| EP2238278A1 (en) | 2010-10-13 |
| US20100329882A1 (en) | 2010-12-30 |
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