EP1382707A1 - Layer system - Google Patents

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Publication number
EP1382707A1
EP1382707A1 EP02015955A EP02015955A EP1382707A1 EP 1382707 A1 EP1382707 A1 EP 1382707A1 EP 02015955 A EP02015955 A EP 02015955A EP 02015955 A EP02015955 A EP 02015955A EP 1382707 A1 EP1382707 A1 EP 1382707A1
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EP
European Patent Office
Prior art keywords
layer
thermal barrier
barrier coating
layer system
intermediate layer
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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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EP02015955A
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German (de)
French (fr)
Inventor
Jens Birkner
Werner Dr. Stamm
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Siemens AG
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Siemens AG
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Priority to EP02015955A priority Critical patent/EP1382707A1/en
Priority to PCT/EP2003/005978 priority patent/WO2004007787A1/en
Publication of EP1382707A1 publication Critical patent/EP1382707A1/en
Withdrawn legal-status Critical Current

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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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • 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
    • C23C28/3455—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 with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying

Definitions

  • the invention relates to a layer system according to the preamble of claim 1.
  • thermal barrier coatings have been developed on thermally stressed components, for example made of superalloys, which are applied alone the high inlet temperatures in the long term no longer withstand can.
  • the ceramic thermal barrier coating offers the advantage of a high Temperature / corrosion resistance due to their ceramic Properties, and the metallic substrate offers the advantage the good mechanical properties in this composite or shift system.
  • an adhesion or corrosion protection layer of composition MCrAlY as the main constituent is applied between the substrate and the ceramic thermal barrier coating, where M means that one of the metals nickel, chromium or iron is used.
  • M means that one of the metals nickel, chromium or iron is used.
  • the composition of these MCrAlY layers can vary.
  • thermal barrier coating on the anti-corrosion layer or MCrAlY layer during application or does not stick well and / or flakes off during operation and sprayed by non-melting coating method must become.
  • the object is achieved by a layer system according to claim 1 solved.
  • FIG. 1 shows a layer system 1 according to the invention.
  • the layer system 1 has a substrate 4.
  • the substrate 4 is, for example, a nickel- or cobalt-based superalloy.
  • at least one intermediate layer 7 is present, which serves as a corrosion, oxidation or adhesion-promoting layer and consists of an intermediate layer material.
  • a single intermediate layer 7 is used. This is, for example, a so-called MCrAlY layer, where M is an element of the group iron, cobalt or nickel.
  • MCrAlY layer where M is an element of the group iron, cobalt or nickel.
  • the thermal barrier coating 10 is, for example, ceramic and consists, for example, of partially or fully stabilized zirconium oxide with up to 8% yttrium oxide or other rare earth oxides.
  • the thermal insulation layer 10 contains a total of 5-60 vol% of the material of the intermediate layer 7, whereby a good adhesion of the thermal barrier coating 10 is ensured to the intermediate layer 7.
  • the thermal barrier coating 10 begins at the interface at which the material of the thermal barrier coating 10 forms the matrix.
  • the layers 7, 10 can be applied by various types of plasma spraying, in particular by atmospheric plasma spraying (APS), or by cold gas spraying.
  • APS atmospheric plasma spraying
  • cold gas spraying the particles of the material to be applied to the layers 7, 10 as well as the substrate 4 during manufacture have a low temperature, ie they do not form a plasma.
  • the coated particles are applied at high speeds up to 1000m / s on the substrate 4, whereby they connect with each other.
  • a metallic constituent is necessary. This green body layer thus produced may still be sintered or heat treated to allow improved resistance to external mechanical stress.
  • zirconia instead of zirconia, other ceramic materials may be used be used.
  • FIG. 2 shows a further layer system 1 according to the invention, in which the concentration of the intermediate layer material 7 in the thermal barrier coating 10, for example, continuously decreases, starting from an interface 8 between the intermediate layer 7 and the thermal barrier coating 10 to an outer surface 11 of the thermal barrier coating 10.
  • the proportion of the intermediate layer material 7 may also be constant at 0vol%.
  • the thermal barrier coating 10 begins at the interface at which the material of the thermal barrier coating 10 forms the matrix.
  • the gradient of the material composition in the thermal barrier coating can be produced in various ways.
  • plasma spraying more and more material of the thermal barrier coating 10 is continuously added to the plasma jet which directs the particles onto the substrate 4 from an initial mixture of the various materials of the layers 7, 10 and / or less or less continuously or discontinuously added to the intermediate layer 7 material.
  • two burners ie two separate plasma jets or a plasma jet and a cold gas jet for the two different materials.
  • FIG. 3 shows a further exemplary embodiment of a layer system 1 according to the invention.
  • the layer system 1 according to the invention is constructed, for example, according to FIG. 1 or 2, wherein a first partial layer 13 of the thermal barrier coating 10 has been applied by cold gas spraying.
  • this cold gas-sprayed sub-layer 13 of the thermal barrier coating 10 is still a second sub-layer 16 of the thermal barrier coating 10 of the same material or with a modified composition by means of atmospheric plasma spraying or by other plasma spray applied (in vacuo, ..).
  • the concentration of the metallic Materials towards the outside in the thermal barrier coating 10 should decrease during the application with the increasing Coating time, the temperature of the particle beam continuously to increase until, for example, a plasma is generated.
  • interlayer material 7 By arranging interlayer material 7 in the thermal barrier coating 10, the expansion coefficients of the layers 7, 10 are matched to each other, so that there is no or little thermal stress between the layers 7, 10 when heated, whereby spalling is prevented. This applies in particular when there is a graded or continuous transition of the layers 7, 10. In particular, even porous layers 7, 10 are produced in order to achieve an expansion tolerance, because a porosity from 5% by volume can influence the coefficient of expansion and the modulus of elasticity.
  • FIG. 4 shows a perspective view of a moving blade as an example of a layer system 1 which extends along a longitudinal axis 19.
  • the rotor blade 1 has, along the longitudinal axis 19, successively a fastening region 22, a blade platform 25 adjacent thereto and an airfoil region 28.
  • a blade root 31 is formed, which serves for fastening the blade 1 to a shaft of a turbomachine, also not shown.
  • the turbine blade 1 is exposed with its airfoil region 28 within a gas turbine to high temperatures and is therefore protected against oxidation and heat by a layer system 1 according to the invention.

Abstract

Layer system (1) comprises a substrate (4) with an intermediate layer (7) and an outer heat insulating layer (10). The material of the intermediate layer is partially formed in the heat insulating layer. One of the layers is applied by cold gas spraying.

Description

Gebiet der ErfindungField of the invention

Die Erfindung betrifft ein Schichtsystem gemäss dem Oberbegriff des Anspruchs 1.The invention relates to a layer system according to the preamble of claim 1.

In heutigen modernen Energieerzeugungsanlagen, wie z.B. Gasturbinenanlagen, spielt der Wirkungsgrad eine wichtige Rolle, weil dadurch die Kosten für den Betrieb der Gasturbinenanlage reduziert wird. Eine Möglichkeit, den Wirkungsgrad zu erhöhen und damit die Betriebskosten zu reduzieren, besteht darin, die Einlasstemperaturen eines Verbrennungsgases innerhalb einer Gasturbine zu erhöhen.In today's modern power generation plants, such as Gas turbine systems, the efficiency plays an important role, because thereby the costs for the operation of the gas turbine plant is reduced. A way to increase the efficiency and thus reduce operating costs, is to the inlet temperatures of a combustion gas within to increase a gas turbine.

Aus diesem Grund wurden keramische Wärmedämmschichten entwickelt, die auf thermisch belasteten Bauteilen, beispielsweise aus Superlegierungen, aufgebracht werden, die alleine den hohen Einlasstemperaturen auf Dauer nicht mehr Stand halten können.For this reason, ceramic thermal barrier coatings have been developed on thermally stressed components, for example made of superalloys, which are applied alone the high inlet temperatures in the long term no longer withstand can.

Die keramische Wärmedämmschicht bietet den Vorteil einer hohen Temperatur/Korrosionsresistenz aufgrund ihrer keramischen Eigenschaften, und das metallische Substrat bietet den Vorteil der guten mechanischen Eigenschaften in diesem Verbund oder Schichtsystem.The ceramic thermal barrier coating offers the advantage of a high Temperature / corrosion resistance due to their ceramic Properties, and the metallic substrate offers the advantage the good mechanical properties in this composite or shift system.

Typischerweise ist zwischen dem Substrat und der keramischen Wärmedämmschicht eine Haftvermittlungs- oder Korrosionsschutzschicht der Zusammensetzung MCrAlY als Hauptbestandteil aufgebracht, wobei M bedeutet, dass ein Metall aus der Gruppe Nickel, Chrom oder Eisen verwendet wird.
Die Zusammensetzung dieser MCrAlY-Schichten kann variieren.Typically, an adhesion or corrosion protection layer of composition MCrAlY as the main constituent is applied between the substrate and the ceramic thermal barrier coating, where M means that one of the metals nickel, chromium or iron is used.
The composition of these MCrAlY layers can vary.

Häufig kommt es dazu, dass die Wärmedämmschicht auf der Korrosionsschutzschicht oder MCrAlY-Schicht beim Aufbringen oder während des Betriebs nicht gut haftet und/oder abplatzt und durch nichtaufschmelzende Beschichtungsverfahren nachgespritzt werden muss.It often happens that the thermal barrier coating on the anti-corrosion layer or MCrAlY layer during application or does not stick well and / or flakes off during operation and sprayed by non-melting coating method must become.

Es ist daher Aufgabe der Erfindung, dieses Problem zu überwinden.It is therefore an object of the invention to overcome this problem.

Die Aufgabe wird durch ein Schichtsystem gemäss Anspruch 1 gelöst.The object is achieved by a layer system according to claim 1 solved.

Weitere vorteilhafte Ausgestaltungen des Schichtsystems sind in den Unteransprüchen aufgeführt.Further advantageous embodiments of the layer system are listed in the subclaims.

In den Figuren sind Ausführungsbeispiele des erfindungsgemässen Schichtsystems dargestellt.In the figures, embodiments of the inventive Layer system shown.

Es zeigen:

  • Figur 1 ein erstes erfindungsgemässes Schichtsystem,
  • Figur 2 ein zweites erfindungsgemässes Schichtsystem mit einem Konzentrationsgradienten,
  • Figur 3 ein weiteres erfindungsgemässes Schichtsystem und
  • Figur 4 ein Anwendungsbeispiel für ein erfindungsgemässes Schichtsystem.
    • Show it:
  • FIG. 1 shows a first layer system according to the invention,
  • FIG. 2 shows a second layer system according to the invention with a concentration gradient,
  • FIG. 3 shows another layer system according to the invention and FIG
  • FIG. 4 shows an application example of a layer system according to the invention.

    • Figur 1 zeigt ein erfindungsgemässes Schichtsystem 1.
    Das Schichtsystem 1 weist ein Substrat 4 auf. Das Substrat 4 ist beispielsweise eine Nickel- oder Kobalt-basierte Superlegierung.
    Auf dem Substrat 4 ist zumindest eine Zwischenschicht 7 vorhanden, die als Korrosions-, Oxidations- oder Haftvermittlungsschicht dient und aus einem Zwischenschichtmaterial besteht. Hier wird eine einzige Zwischenschicht 7 verwendet.
    Dies ist beispielsweise eine sogenannte MCrAlY-Schicht, wobei M ein Element der Gruppe Eisen, Kobalt oder Nickel ist.
    Auf die äusserste Grenzfläche der Zwischenschicht 7 ist eine Wärmedämmschicht 10 aufgebracht.     FIG. 1 shows a layer system 1 according to the invention.
    The layer system 1 has a substrate 4. The substrate 4 is, for example, a nickel- or cobalt-based superalloy.
    On the substrate 4, at least one intermediate layer 7 is present, which serves as a corrosion, oxidation or adhesion-promoting layer and consists of an intermediate layer material. Here, a single intermediate layer 7 is used.
    This is, for example, a so-called MCrAlY layer, where M is an element of the group iron, cobalt or nickel.
    On the outermost interface of the intermediate layer 7, a thermal barrier coating 10 is applied.

    Die Wärmedämmschicht 10 ist beispielsweise keramisch und besteht bspw. aus teil- oder vollstabilisiertem Zirkonoxid mit bis zu 8% Yttriumoxid oder anderen Seltenerdoxiden.
    Die Wärmdämmschicht 10 enthält insgesamt 5 - 60 vol% des Materials der Zwischenschicht 7, wodurch eine gute Anhaftung der Wärmedämmschicht 10 an die Zwischenschicht 7 gewährleistet ist. Die Wärmedämmschicht 10 beginnt an der Grenzfläche, an der das Material der Wärmedämmschicht 10 die Matrix bildet.    The thermal barrier coating 10 is, for example, ceramic and consists, for example, of partially or fully stabilized zirconium oxide with up to 8% yttrium oxide or other rare earth oxides.
    The thermal insulation layer 10 contains a total of 5-60 vol% of the material of the intermediate layer 7, whereby a good adhesion of the thermal barrier coating 10 is ensured to the intermediate layer 7. The thermal barrier coating 10 begins at the interface at which the material of the thermal barrier coating 10 forms the matrix.

    Die Schichten 7, 10 können durch verschiedene Arten des Plasmaspritzens, insbesondere durch atmosphärisches Plasmaspritzen (APS), oder durch Kaltgasspritzen aufgebracht werden.
    Beim Kaltgasspritzen weisen die Partikel des aufzubringenden Materials der Schichten 7, 10 ebenso wie das Substrat 4 während der Herstellung eine geringe Temperatur auf, d.h. sie bilden kein Plasma.
    Um eine Verschweissung bzw. eine Verankerung der Teilchen miteinander zu erreichen, werden die aufgetragenen Partikel mit hohen Geschwindigkeiten bis zu 1000m/s auf das Substrat 4 aufgebracht, wodurch sie sich miteinander verbinden.
    Um eine Verschweissung zu erreichen ist die Zugabe eines metallischen Bestandteils notwendig.
    Diese so hergestellte Grünkörperschicht kann noch gesintert oder wärmebehandelt werden, um eine verbesserte Beständigkeit gegenüber einer äusseren mechanischen Belastung zu ermöglichen.    The layers 7, 10 can be applied by various types of plasma spraying, in particular by atmospheric plasma spraying (APS), or by cold gas spraying.
    During cold gas spraying, the particles of the material to be applied to the layers 7, 10 as well as the substrate 4 during manufacture have a low temperature, ie they do not form a plasma.
    In order to achieve a fusion or anchoring of the particles with each other, the coated particles are applied at high speeds up to 1000m / s on the substrate 4, whereby they connect with each other.
    In order to achieve a weld, the addition of a metallic constituent is necessary.
    This green body layer thus produced may still be sintered or heat treated to allow improved resistance to external mechanical stress.

    Anstatt des Zirkonoxids können auch andere keramische Materialien verwendet werden.Instead of zirconia, other ceramic materials may be used be used.

    Figur 2 zeigt ein weiteres erfindungsgemässes Schichtsystem 1, bei dem die Konzentration des Zwischenschichtmaterials 7 in der Wärmedämmschicht 10 beginnend von einer Grenzfläche 8 zwischen der Zwischenschicht 7 und der Wärmedämmschicht 10 bis hin zu einer äusseren Oberfläche 11 der Wärmedämmschicht 10 bspw. kontinuierlich abnimmt. In einem Bereich 12 unterhalb der äusseren Oberfläche 11 innerhalb einer gewissen Schichtdicke kann der Anteil des Zwischenschichtmaterials 7 auch konstant bei 0vol% liegen.
    Die Wärmedämmschicht 10 beginnt an der Grenzfläche, an der das Material der Wärmedämmschicht 10 die Matrix bildet.    FIG. 2 shows a further layer system 1 according to the invention, in which the concentration of the intermediate layer material 7 in the thermal barrier coating 10, for example, continuously decreases, starting from an interface 8 between the intermediate layer 7 and the thermal barrier coating 10 to an outer surface 11 of the thermal barrier coating 10. In a region 12 below the outer surface 11 within a certain layer thickness, the proportion of the intermediate layer material 7 may also be constant at 0vol%.
    The thermal barrier coating 10 begins at the interface at which the material of the thermal barrier coating 10 forms the matrix.

    Der Gradient der Materialzusammensetzung in der Wärmedämmschicht kann auf verschiedene Art und Weise erzeugt werden.
    Beim Plasmaspritzen wird in den Plasmastrahl, der die Partikel auf das Substrat 4 lenkt, von einer Anfangsmischung der verschiedenen Materialien der Schichten 7, 10 kontinuierlich mehr und mehr Material der Wärmedämmschicht 10 hinzugefügt und/oder kontinuierlich oder diskontinuierlich weniger Material der Zwischenschicht 7 hinzugefügt.
    Ebenso ist es möglich zwei Brenner, also zwei separate Plasmastrahlen oder ein Plasmastrahl und einen Kaltgasstrahl für die beiden unterschiedlichen Materialien zu verwenden.    The gradient of the material composition in the thermal barrier coating can be produced in various ways.
    In plasma spraying, more and more material of the thermal barrier coating 10 is continuously added to the plasma jet which directs the particles onto the substrate 4 from an initial mixture of the various materials of the layers 7, 10 and / or less or less continuously or discontinuously added to the intermediate layer 7 material.
    It is also possible to use two burners, ie two separate plasma jets or a plasma jet and a cold gas jet for the two different materials.

    Figur 3 zeigt ein weiteres Ausführungsbeispiel eines erfindungsgemässen Schichtsystems 1.
    Das erfindungsgemässe Schichtsystem 1 ist beispielsweise gemäss Figur 1 oder 2 aufgebaut, wobei eine erste Teilschicht 13 der Wärmedämmschicht 10 durch Kaltgasspritzen aufgebracht worden ist.
    Auf diese kaltgasgespritzte Teilschicht 13 der Wärmedämmschicht 10 wird noch eine zweite Teilschicht 16 der Wärmedämmschicht 10 des gleichen Materials oder mit veränderter Zusammensetzung mittels atmosphärischem Plasmaspritzen oder mittels anderer Plasmaspritzarten (im Vakuum,..) aufgebracht.    FIG. 3 shows a further exemplary embodiment of a layer system 1 according to the invention.
    The layer system 1 according to the invention is constructed, for example, according to FIG. 1 or 2, wherein a first partial layer 13 of the thermal barrier coating 10 has been applied by cold gas spraying.
    In this cold gas-sprayed sub-layer 13 of the thermal barrier coating 10 is still a second sub-layer 16 of the thermal barrier coating 10 of the same material or with a modified composition by means of atmospheric plasma spraying or by other plasma spray applied (in vacuo, ..).

    Es ist bspw. auch möglich, wenn die Konzentration des metallischen Materials nach aussen hin in der Wärmedämmschicht 10 abnehmen soll, während der Aufbringung mit der zunehmenden Beschichtungszeit, die Temperatur des Teilchenstrahls kontinuierlich zu erhöhen bis bspw. ein Plasma erzeugt wird. It is also possible, for example, if the concentration of the metallic Materials towards the outside in the thermal barrier coating 10 should decrease during the application with the increasing Coating time, the temperature of the particle beam continuously to increase until, for example, a plasma is generated.

    Durch die Anordnung von Zwischenschichtmaterial 7 in der Wärmedämmschicht 10 werden die Ausdehnungkoeffizienten der Schichten 7, 10 aneinander angeglichen, so dass es bei Erwärmung gar nicht oder kaum zu thermischen Spannungen zwischen den Schichten 7, 10 kommt, wodurch ein Abplatzen verhindert wird.
    Dies gilt insbesondere dann, wenn ein gradierter oder kontinuierlicher Übergang der Schichten 7, 10 vorliegt.
    Insbesondere werden auch noch poröse Schichten 7, 10 hergestellt, um eine Dehnungstoleranz zu erreichen, weil eine Porosität ab 5vol% den Ausdehungskoeffizienten und den E-Modul beeinflussen kann.    By arranging interlayer material 7 in the thermal barrier coating 10, the expansion coefficients of the layers 7, 10 are matched to each other, so that there is no or little thermal stress between the layers 7, 10 when heated, whereby spalling is prevented.
    This applies in particular when there is a graded or continuous transition of the layers 7, 10.
    In particular, even porous layers 7, 10 are produced in order to achieve an expansion tolerance, because a porosity from 5% by volume can influence the coefficient of expansion and the modulus of elasticity.

    Figur 4 zeigt in perspektivischer Ansicht eine Laufschaufel als Beispiel für ein Schichtsystem 1, die sich entlang einer Längsachse 19 erstreckt.
    Die Laufschaufel 1 weist entlang der Längsachse 19 aufeinanderfolgend einen Befestigungsbereich 22, eine daran angrenzende Schaufelplattform 25 sowie einen Schaufelblattbereich 28 auf.    FIG. 4 shows a perspective view of a moving blade as an example of a layer system 1 which extends along a longitudinal axis 19.
    The rotor blade 1 has, along the longitudinal axis 19, successively a fastening region 22, a blade platform 25 adjacent thereto and an airfoil region 28.

    Im Befestigungsbereich 9 ist ein Schaufelfuss 31 gebildet, der zur Befestigung der Laufschaufel 1 an einer Welle einer ebenfalls nicht dargestellten Strömungsmaschine dient.
    Die Turbinenschaufel 1 ist mit ihrem Schaufelblattbereich 28 innerhalb einer Gasturbine hohen Temperaturen ausgesetzt und ist daher gegen Oxidation und Wärme durch ein erfindungsgemässes Schichtsystem 1 geschützt.    In the mounting region 9, a blade root 31 is formed, which serves for fastening the blade 1 to a shaft of a turbomachine, also not shown.
    The turbine blade 1 is exposed with its airfoil region 28 within a gas turbine to high temperatures and is therefore protected against oxidation and heat by a layer system 1 according to the invention.

    Claims (11)

    Schichtsystem,
    insbesondere Turbinenschaufel,
    das ein Substrat,
    zumindest eine darauf aufliegende Zwischenschicht aus einem Zwischenschichtmaterial und
    eine äußere Wärmedämmschicht aufweist,
    dadurch gekennzeichnet, dass
    das Zwischenschichtmaterial (7) teilweise in der Wärmdämmschicht (10) vorhanden ist.    Layer system,
    in particular turbine blade,
    that a substrate,
    at least one intermediate layer of an intermediate layer material resting thereon and
    having an outer thermal barrier coating,
    characterized in that
    the interlayer material (7) is partially present in the thermal barrier coating (10).         Schichtsystem nach Anspruch 1,
    dadurch gekennzeichnet, dass
    die Zwischenschicht (7) eine Korrosionsschutzschicht ist.    Layer system according to claim 1,
    characterized in that
    the intermediate layer (7) is a corrosion protection layer.         Schichtsystem nach Anspruch 1,
    dadurch gekennzeichnet, dass
    die Wärmedämmschicht (10) aus Keramik ist.    Layer system according to claim 1,
    characterized in that
    the thermal barrier coating (10) is made of ceramic.         Schichtsystem nach Anspruch 1 oder 2,
    dadurch gekennzeichnet, dass
    die Korrosionsschutzschicht (7) eine Schicht der Zusammensetzung MCrAlY aufweist,
    wobei M für ein Element der Gruppe Eisen, Kobalt oder Nickel steht.    Layer system according to claim 1 or 2,
    characterized in that
    the corrosion protection layer (7) has a layer of the composition MCrAlY,
    where M is an element of the group iron, cobalt or nickel.         Schichtsystem nach Anspruch 1 oder 3,
    dadurch gekennzeichnet, dass
    die Wärmedämmschicht (10) als Matrixmaterial Zirkonoxid aufweist.     Layer system according to claim 1 or 3,
    characterized in that
    the thermal barrier coating (10) comprises zirconium oxide as the matrix material.         Schichtsystem nach einem oder mehreren der vorherigen Ansprüche,
    dadurch gekennzeichnet, dass zumindest eine Schicht (7, 10) durch Kaltgasspritzen aufgebracht worden ist.    Layer system according to one or more of the preceding claims,
    characterized in that at least one layer (7, 10) has been applied by cold gas spraying.         Schichtsystem nach Anspruch 1, 3 oder 5,
    dadurch gekennzeichnet, dass
    die Wärmedämmschicht (10) zumindest teilweise durch atmosphärisches Plasmaspritzen aufgebracht worden ist.    Layer system according to claim 1, 3 or 5,
    characterized in that
    the thermal barrier coating (10) has been at least partially applied by atmospheric plasma spraying.         Schichtsystem nach Anspruch 1,
    dadurch gekennzeichnet, dass
    die Konzentration des Materials der Zwischenschicht (7) in der Wärmdämmschicht (10) kontinuierlich abnimmt.    Layer system according to claim 1,
    characterized in that
    the concentration of the material of the intermediate layer (7) in the thermal insulation layer (10) decreases continuously.         Schichtsystem nach Anspruch 1,
    dadurch gekennzeichnet, dass
    das Zwischenschichtmaterial (7) zumindest teilweise metallisch ist.    Layer system according to claim 1,
    characterized in that
    the interlayer material (7) is at least partially metallic.         Schichtsystem nach einem der Ansprüche 1 - 9,
    dadurch gekennzeichnet, dass
    der Anteil des in der Wärmedämmschicht (10) vorhandenen Zwischenschichtmaterials (7) im Bereich von 5 - 60 vol % liegt.    Layer system according to one of claims 1 - 9,
    characterized in that
    the proportion of interlayer material (7) present in the thermal barrier coating (10) is in the range of 5 to 60% by volume.         Schichtsystem nach einem der Ansprüche 1 - 9,
    dadurch gekennzeichnet, dass
    die Wärmedämmschicht (10) oder die zumindest eine Zwischenschicht (7) eine Porosität von mehr als 5 vol% aufweisen.    Layer system according to one of claims 1 - 9,
    characterized in that
    the thermal barrier coating (10) or the at least one intermediate layer (7) have a porosity of more than 5 vol%.
    EP02015955A 2002-07-17 2002-07-17 Layer system Withdrawn EP1382707A1 (en)

    Priority Applications (2)

    Application Number Priority Date Filing Date Title
    EP02015955A EP1382707A1 (en) 2002-07-17 2002-07-17 Layer system
    PCT/EP2003/005978 WO2004007787A1 (en) 2002-07-17 2003-06-06 Layered system

    Applications Claiming Priority (1)

    Application Number Priority Date Filing Date Title
    EP02015955A EP1382707A1 (en) 2002-07-17 2002-07-17 Layer system

    Publications (1)

    Publication Number Publication Date
    EP1382707A1 true EP1382707A1 (en) 2004-01-21

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    WO (1) WO2004007787A1 (en)

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    EP1672175A1 (en) * 2004-12-14 2006-06-21 Honeywell International Inc. A method for applying environmental-resistant mcraly coatings on gas turbine components
    WO2006075994A2 (en) * 2004-04-06 2006-07-20 Honeywell International Inc. Cold gas-dynamic spraying of wear resistant alloys on turbine blades
    EP1712657A2 (en) * 2005-04-14 2006-10-18 United Technologies Corporation Method and system for creating functionally graded materials using cold spray
    WO2009056235A2 (en) * 2007-11-02 2009-05-07 Interpane Entwicklungs- Und Beratungsgesellschaft Mbh & Co. Kg Multilayer system comprising contact elements, and method for the production of a contact element for a multilayer system
    DE102008058141A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing a blade for a rotor of a turbomachine
    DE102008058142A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing and / or repairing a rotor of a turbomachine and rotor for this purpose
    EP2072634A3 (en) * 2007-12-19 2011-03-16 United Technologies Corporation Porous protective clothing for turbine engine components
    DE102009049707A1 (en) * 2009-10-17 2011-07-28 MTU Aero Engines GmbH, 80995 Method for producing a rotor or stator blade and such a blade
    EP2381005A1 (en) * 2010-04-22 2011-10-26 Siemens Aktiengesellschaft Coating system for turbine components
    EP2617869A2 (en) * 2012-01-20 2013-07-24 General Electric Company Process of fabricating a thermal barrier coating and an article having a cold sprayed thermal barrier coating
    EP2781622A1 (en) * 2013-03-21 2014-09-24 Siemens Aktiengesellschaft Generative method particularly for producing a coating, device for carrying out the method, coating and a component manufacturing method and a component
    WO2016055324A1 (en) * 2014-10-08 2016-04-14 Siemens Aktiengesellschaft Double-layered zirconium oxide layer having a high-purity content
    EP3404127A1 (en) * 2017-05-08 2018-11-21 United Technologies Corporation Functionally graded environmental barrier coating
    WO2019129457A1 (en) * 2017-12-29 2019-07-04 Siemens Aktiengesellschaft Ceramic material, method of production, layer and layer system

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    EP2778257B1 (en) * 2013-03-13 2017-05-10 General Electric Company Process of fabricating thermal barrier coatings

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    Publication number Priority date Publication date Assignee Title
    WO2006075994A2 (en) * 2004-04-06 2006-07-20 Honeywell International Inc. Cold gas-dynamic spraying of wear resistant alloys on turbine blades
    WO2006075994A3 (en) * 2004-04-06 2006-09-28 Honeywell Int Inc Cold gas-dynamic spraying of wear resistant alloys on turbine blades
    EP1672175A1 (en) * 2004-12-14 2006-06-21 Honeywell International Inc. A method for applying environmental-resistant mcraly coatings on gas turbine components
    EP1712657A2 (en) * 2005-04-14 2006-10-18 United Technologies Corporation Method and system for creating functionally graded materials using cold spray
    EP1712657A3 (en) * 2005-04-14 2007-07-11 United Technologies Corporation Method and system for creating functionally graded materials using cold spray
    WO2009056235A2 (en) * 2007-11-02 2009-05-07 Interpane Entwicklungs- Und Beratungsgesellschaft Mbh & Co. Kg Multilayer system comprising contact elements, and method for the production of a contact element for a multilayer system
    WO2009056235A3 (en) * 2007-11-02 2009-08-27 Interpane Entwicklungs- Und Beratungsgesellschaft Mbh & Co. Kg Multilayer system comprising contact elements, and method for the production of a contact element for a multilayer system
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    EP2072634A3 (en) * 2007-12-19 2011-03-16 United Technologies Corporation Porous protective clothing for turbine engine components
    DE102008058141A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing a blade for a rotor of a turbomachine
    DE102008058142A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing and / or repairing a rotor of a turbomachine and rotor for this purpose
    DE102009049707A1 (en) * 2009-10-17 2011-07-28 MTU Aero Engines GmbH, 80995 Method for producing a rotor or stator blade and such a blade
    US9132508B2 (en) 2009-10-17 2015-09-15 Mtu Aero Engines Gmbh Method for producing a rotor or stator blade and such a blade
    EP2381005A1 (en) * 2010-04-22 2011-10-26 Siemens Aktiengesellschaft Coating system for turbine components
    EP2617869A2 (en) * 2012-01-20 2013-07-24 General Electric Company Process of fabricating a thermal barrier coating and an article having a cold sprayed thermal barrier coating
    EP2617869A3 (en) * 2012-01-20 2014-09-24 General Electric Company Process of fabricating a thermal barrier coating and an article having a cold sprayed thermal barrier coating
    EP2781622A1 (en) * 2013-03-21 2014-09-24 Siemens Aktiengesellschaft Generative method particularly for producing a coating, device for carrying out the method, coating and a component manufacturing method and a component
    WO2014146997A1 (en) * 2013-03-21 2014-09-25 Siemens Aktiengesellschaft Additive method, in particular for producing a coating, device for performing the method, coating, component production method, and component
    WO2016055324A1 (en) * 2014-10-08 2016-04-14 Siemens Aktiengesellschaft Double-layered zirconium oxide layer having a high-purity content
    EP3404127A1 (en) * 2017-05-08 2018-11-21 United Technologies Corporation Functionally graded environmental barrier coating
    WO2019129457A1 (en) * 2017-12-29 2019-07-04 Siemens Aktiengesellschaft Ceramic material, method of production, layer and layer system

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