[go: up one dir, main page]

EP1664383A1 - Wear-resistant layer, component comprising such a wear-resistant layer, and production method - Google Patents

Wear-resistant layer, component comprising such a wear-resistant layer, and production method

Info

Publication number
EP1664383A1
EP1664383A1 EP04762715A EP04762715A EP1664383A1 EP 1664383 A1 EP1664383 A1 EP 1664383A1 EP 04762715 A EP04762715 A EP 04762715A EP 04762715 A EP04762715 A EP 04762715A EP 1664383 A1 EP1664383 A1 EP 1664383A1
Authority
EP
European Patent Office
Prior art keywords
layer
component
wear protection
protection layer
protected
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.)
Ceased
Application number
EP04762715A
Other languages
German (de)
French (fr)
Inventor
Erwin Bayer
Wilfried Smarsly
Jürgen STEINWANDEL
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Mercedes Benz Group AG
Original Assignee
DaimlerChrysler AG
MTU Aero Engines GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by DaimlerChrysler AG, MTU Aero Engines GmbH filed Critical DaimlerChrysler AG
Publication of EP1664383A1 publication Critical patent/EP1664383A1/en
Ceased legal-status Critical Current

Links

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
    • 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
    • C23C28/323—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 amorphous metallic material 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
    • 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
    • C23C28/347—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 layers adapted for cutting tools or wear applications
    • 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
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/02—Pretreatment of the material to be coated
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2281—Nitrides of aluminium
    • 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
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2284—Nitrides of titanium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12576—Boride, carbide or nitride component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component

Definitions

  • Wear protection layer component with such a wear protection layer and manufacturing process
  • the invention relates to a wear protection layer, in particular an erosion protection layer for gas turbine components, according to the preamble of patent claim 1. Furthermore, the invention relates to a component with such a wear protection layer according to the preamble of patent claim 1 1 and a method for producing a wear protection layer according to the preamble of patent claim 13.
  • Fluid mechanically loaded components such as gas turbine components
  • Erosion is a wear process that is caused by solid substances moving in the gas flow.
  • wear protection layers are required which protect the components against wear, in particular against erosion, corrosion and oxidation.
  • the wear protection layer disclosed there essentially consists of amorphous or amorphous-nanocrystalline metals, in particular of an alloy based on nickel-tungsten.
  • the present invention is based on the problem of creating a novel wear protection layer, in particular for gas turbine components, and a component with such a wear protection layer and a corresponding production method.
  • the wear protection layer according to the invention has an at least two-layer structure, a first layer being applied to the surface of the component to be protected and having a material composition adapted to the material composition of the component, and a second layer forming an outer cover layer.
  • the first layer is preferably designed as a porous, relatively soft layer with damping properties, whereas the second layer is designed as a relatively hard layer.
  • the outer, second layer provides the actual erosion protection.
  • the underlying, damping first layer can absorb energy when particles are impacted, thus preventing cracking in the component to be protected.
  • the component according to the invention is defined in independent claim 1 1 and the method according to the invention is defined in independent claim 13.
  • FIG. 1 shows a highly schematic representation of a blade of a gas turbine which has a wear protection layer according to the invention
  • FIGS. 1 and 2 show a blade of a gas turbine in perspective view, which carries a wear protection layer according to the invention.
  • Fig. 2 shows a schematic cross section through the blade and the wear protection view.
  • 1 shows a blade 10 of a gas turbine with an airfoil 11 and a blade root 12.
  • the entire blade 10, namely a surface to be protected is coated with a wear protection layer 13.
  • the complete blade 10 is coated with the wear protection layer 13 in the exemplary embodiment shown, it is also possible for the blade 10 to have the wear protection layer 13 only in sections, that is to say only in the area of the airfoil 11 or in the area of the blade root 12.
  • Other gas turbine components such as integrally bladed rotors, can also be coated with the wear protection layer 13.
  • FIG. 2 shows a cross section through the blade 10 in the region of the airfoil 11, the wear protection layer 13 being applied to a surface 14 of the airfoil 11.
  • the wear protection layer 13 which forms an erosion protection layer in the exemplary embodiment shown, is constructed at least in two layers or two layers.
  • the wear protection layer 13 comprises two layers.
  • a first layer 15 is applied directly to the surface 1 of the airfoil 11.
  • a second layer 16 forms an outer cover layer of the wear protection layer 13 and is applied directly to the first layer 15.
  • the first layer 15 is produced from a material or a material that is adapted to the material composition of the component to be coated, in the exemplary embodiment shown to the material composition of the blade 10 or of the airfoil 11 . If the component to be coated, namely the airfoil 11, consists of a titanium alloy, then the first layer 15 of the wear protection layer 13 is also formed from a titanium alloy. In the exemplary embodiment shown, the airfoil is formed from a titanium-aluminum material or a titanium-aluminum material and the first layer 15 of the wear protection layer 13 likewise consists of a titanium-aluminum material.
  • the first layer 15 of the wear protection layer 13 is porous and relatively soft compared to the component to be coated, namely the airfoil 11 to be coated.
  • pores 17 are within the The first layer 15 of the wear protection layer 13 is shown in a highly schematic manner.
  • the porous and relatively soft first layer 15 has damping properties.
  • the second layer 16 applied to the first layer 15 is relatively hard in comparison to the first layer 15 and in comparison to the component to be coated, namely the airfoil 11 to be coated.
  • the second layer 16 of the wear protection layer 13 is preferably made of a titanium nitride material, an aluminum nitride material or a titanium aluminum -Nitride material manufactured.
  • the second layer 16, which forms the cover layer of the wear protection layer 13, is relatively thin compared to the first layer 15.
  • the outer, second layer 16 preferably has a thickness of less than 0.1 mm.
  • the inner first layer 15 has a thickness of up to 1 mm.
  • the relatively hard, outer second layer 16 provides the actual erosion protection of the wear protection layer 13.
  • the second layer 16 protects the airfoil 11 against erosion by fine particles.
  • the underlying first layer 15, which is porous and relatively soft, has damping properties so that the same energy can be absorbed when larger particles impact the wear protection layer 13.
  • the fine, round and microscopic pores 17 within the first layer 15 of the wear protection layer 13 prevent a crack from the relatively hard, outer layer 16 into the component to be protected, namely the airfoil 1 1 to be protected, when larger particles impact ,
  • the wear protection layer 13 according to the invention represents effective protection against erosion wear.
  • the first layer 15 of the wear protection layer 13 consists of a similar or the same material as the component to be protected, thermally induced internal stresses or diffusion problems on the part to be protected become Avoided component.
  • the wear protection layer 13 can thus be safely and permanently applied to the component to be protected.
  • the wear protection layer 13 is applied in layers to the component to be protected.
  • the first layer 15 and subsequently and the second layer 16 of the wear protection layer 13 are applied to the component to be protected, which has a component material composition.
  • the first layer 15 of the wear protection layer 13 has a material composition adapted to the component material composition and is designed as a porous layer.
  • the first layer 15 of the wear protection layer 13 is applied to the surface of the component to be protected by means of a directed, atomic or nanoscale particle beam or matter vapor jet.
  • a PVD process Physical Vapor Deposition
  • additives are incorporated into the matter vapor jet, which evaporate during the subsequent hardening of the first layer 15 and thereby leave the pores 17.
  • the additives are preferably designed as fulerenes. Instead of the fulerenes, however, other additives can also be used which evaporate when the first layer 15 hardens or burns in and leave the pores 17.
  • the first layer 15 can also be applied to the surface of the component to be protected using a slip process.
  • a slip material the composition of which is adapted to the material composition of the component to be protected, is applied to the component to be protected by brushing, dipping or spraying.
  • additives are embedded in this slip material, which evaporate when the first layer hardens and leave behind the pores.
  • the second layer 16 is then applied to the first layer 15.
  • the second layer 16 is applied directly to the first layer 15. This is preferably done by vapor deposition, nitriding, aluminizing or oxidizing.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention relates to a wear-resistant layer, particularly an erosion-resistant layer for components of a gas turbine. Said wear-resistant layer (13) is applied to a surface (14) of a fluidically stressed component (10), which is to be protected. The inventive wear-resistant layer (13) comprises an at least double-layered structure. A first layer (15) is applied to the surface (14) of the component (10), which is to be protected, and is provided with a material composition that is adapted to the material composition of the component (10) while a second layer (16) forms an outer coating.

Description

Verschleißschutzschicht, Bauteil mit einer derartigen Verschleißschutzschicht sowie HerstellverfahrenWear protection layer, component with such a wear protection layer and manufacturing process
Die Erfindung betrifft eine Verschleißschutzschicht, insbesondere eine Erosionsschutzschicht für Gasturbinenbauteile, gemäß dem Oberbegriff des Patentanspruchs 1. Weiterhin betrifft die Erfindung ein Bauteil mit einer derartigen Verschleißschutzschicht gemäß dem Oberbegriff des Patentanspruchs 1 1 und ein Verfahren zur Herstellung einer Verschleißschutzschicht gemäß dem Oberbegriff des Patentanspruchs 13.The invention relates to a wear protection layer, in particular an erosion protection layer for gas turbine components, according to the preamble of patent claim 1. Furthermore, the invention relates to a component with such a wear protection layer according to the preamble of patent claim 1 1 and a method for producing a wear protection layer according to the preamble of patent claim 13.
Strömungsmechanisch belastete Bauteile, wie Gasturbinenbauteile, unterliegen einem Verschleiß infolge von Oxidation, Korrosion und Erosion. Bei der Erosion handelt es sich um einen Verschleißvorgang, der durch in der Gasströmung mitbewegte feste Stoffe hervorgerufen wird. Um die Lebensdauer von strömungsmechanisch belasteten Bauteilen zu verlängern, sind Verschleißschutzschichten erforderlich, welche die Bauteile vor Verschleiß schützen, insbesondere gegen Erosion, Korrosion und Oxidation.Fluid mechanically loaded components, such as gas turbine components, are subject to wear due to oxidation, corrosion and erosion. Erosion is a wear process that is caused by solid substances moving in the gas flow. In order to extend the service life of components subject to fluid mechanical stress, wear protection layers are required which protect the components against wear, in particular against erosion, corrosion and oxidation.
Aus der DE 198 59 477 AI ist eine Verschleißschutzschicht für strömungsmechanisch beanspruchte Bauteile bekannt. Die dort offenbarte Verschleißschutzschicht besteht im Wesentlichen aus amorphen oder amorph-nanokristallinen Metallen, insbesondere aus einer Legierung auf Nickel-Wolfram-Basis.From DE 198 59 477 AI a wear protection layer for fluid mechanically stressed components is known. The wear protection layer disclosed there essentially consists of amorphous or amorphous-nanocrystalline metals, in particular of an alloy based on nickel-tungsten.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Verschleißschutzschicht insbesondere für Gasturbinenbauteile sowie eine Bauteil mit einer derartigen Verschleißschutzschicht und ein entsprechendes Herstellungsverfahren zu schaffen.Proceeding from this, the present invention is based on the problem of creating a novel wear protection layer, in particular for gas turbine components, and a component with such a wear protection layer and a corresponding production method.
Dieses Problem wird dadurch gelöst, dass die Eingangs genannte Verschleißschutzschicht durch die Merkmale des kennzeichnenden Teils des Patentanspruchs 1 weitergebildet ist. Die erfindungsgemäße Verschleißschutzschicht verfügt über einen zumindest zweischichtigen Aufbau, wobei eine erste Schicht auf der zu schützenden Oberfläche des Bauteils aufgebracht ist und über eine an die Materialzusammensetzung des Bauteils angepasste Materialzusammensetzung verfügt, und wobei eine zweite Schicht eine äußere Deckschicht bildet.This problem is solved in that the wear protection layer mentioned at the outset is developed by the features of the characterizing part of patent claim 1. The wear protection layer according to the invention has an at least two-layer structure, a first layer being applied to the surface of the component to be protected and having a material composition adapted to the material composition of the component, and a second layer forming an outer cover layer.
Die erste Schicht ist vorzugsweise als poröse, relativ weiche Schicht mit Dämpfungseigenschaften ausgebildet, wohingegen die zweite Schicht als relativ harte Schicht ausgebildet ist. Die äußere, zweite Schicht bewirkt den eigentlichen Erosionsschutz. Die darunter liegende, dämpfende erste Schicht kann beim Einschlag von Partikeln Energie absorbieren und so eine Rissbildung im zu schützenden Bauteil verhindern.The first layer is preferably designed as a porous, relatively soft layer with damping properties, whereas the second layer is designed as a relatively hard layer. The outer, second layer provides the actual erosion protection. The underlying, damping first layer can absorb energy when particles are impacted, thus preventing cracking in the component to be protected.
Das erfindungsgemäße Bauteil ist im unabhängigen Patentanspruch 1 1 und das erfindungsgemäße Verfahren ist im unabhängigen Patentanspruch 13 definiert.The component according to the invention is defined in independent claim 1 1 and the method according to the invention is defined in independent claim 13.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den abhängigen Unteransprüchen und der nachfolgenden Beschreibung.Preferred developments of the invention result from the dependent subclaims and the following description.
Nachfolgend werden Ausführungsbeispiele der Erfindung, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. In der Zeichnung zeigt:In the following, exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted thereto. The drawing shows:
Fig. 1 : eine stark schematisierte Darstellung einer Schaufel einer Gasturbine, die eine erfindungsgemäße Verschleißschutzschicht aufweist, und1 shows a highly schematic representation of a blade of a gas turbine which has a wear protection layer according to the invention, and
Fig. 2: einen stark schematisierten Querschnitt durch die erfindungsgemäße Verschleißschutzschicht.2: a highly schematic cross section through the wear protection layer according to the invention.
Nachfolgend wird die hier vorliegende Erfindung unter Bezugsnahme auf Figuren 1 und 2 in größerem Detail erläutert. Fig. 1 zeigt eine Schaufel einer Gasturbine in perspektivischer Ansicht, die eine erfindungsgemäße Verschleißschutzschicht trägt. Fig. 2 zeigt einen schematisierten Querschnitt durch die Schaufel und die Verschleißschutzsicht. Fig. 1 zeigt eine Schaufel 10 einer Gasturbine mit einem Schaufelblatt 1 1 und einem Schaufelfuß 12. Im Ausführungsbeispiel der Fig. 1 ist die gesamte Schaufel 10, nämlich eine zu schützende Oberfläche derselben, mit einer Verschleißschutzschicht 13 beschichtet. Obwohl im gezeigten Ausführungsbeispiel die komplette Schaufel 10 mit der Verschleißschutzschicht 13 beschichtet ist, ist es auch möglich, dass die Schaufel 10 nur abschnittsweise, also nur im Bereich des Schaufelblatts 1 1 oder im Bereich des Schaufelfußes 12, die Verschleißschutzschicht 13 aufweist. Auch können andere Gasturbinenbauteile wie zum Beispiel integral beschaufelte Rotoren mit der Verschleißschutzschicht 13 beschichtet sein.The present invention is explained in greater detail below with reference to FIGS. 1 and 2. 1 shows a blade of a gas turbine in perspective view, which carries a wear protection layer according to the invention. Fig. 2 shows a schematic cross section through the blade and the wear protection view. 1 shows a blade 10 of a gas turbine with an airfoil 11 and a blade root 12. In the exemplary embodiment in FIG. 1, the entire blade 10, namely a surface to be protected, is coated with a wear protection layer 13. Although the complete blade 10 is coated with the wear protection layer 13 in the exemplary embodiment shown, it is also possible for the blade 10 to have the wear protection layer 13 only in sections, that is to say only in the area of the airfoil 11 or in the area of the blade root 12. Other gas turbine components, such as integrally bladed rotors, can also be coated with the wear protection layer 13.
Fig. 2 zeigt einen Querschnitt durch die Schaufel 10 im Bereich des Schaufelblatts 1 1, wobei auf eine Oberfläche 14 des Schaufelblatts 1 1 die Verschleißschutzschicht 13 aufgebracht ist. Im Sinne der Erfindung ist die Verschleißschutzschicht 13, die im gezeigten Ausführungsbeispiel eine Erosionsschutzschicht bildet, zumindest zweischichtig bzw. zweilagig aufgebaut. Im konkreten Ausführungsbeispiel der Fig. 2 um- fasst die Verschleißschutzschicht 13 zwei Schichten. Eine erste Schicht 15 ist unmittelbar auf die Oberfläche 1 des Schaufelblatts 1 1 aufgebracht. Eine zweite Schicht 16 bildet eine äußere Deckschicht der Verschleißschutzschicht 13 und ist unmittelbar auf die erste Schicht 15 aufgebracht.FIG. 2 shows a cross section through the blade 10 in the region of the airfoil 11, the wear protection layer 13 being applied to a surface 14 of the airfoil 11. In the sense of the invention, the wear protection layer 13, which forms an erosion protection layer in the exemplary embodiment shown, is constructed at least in two layers or two layers. In the specific exemplary embodiment in FIG. 2, the wear protection layer 13 comprises two layers. A first layer 15 is applied directly to the surface 1 of the airfoil 11. A second layer 16 forms an outer cover layer of the wear protection layer 13 and is applied directly to the first layer 15.
Es liegt nun im Sinne der hier vorliegenden Erfindung, die erste Schicht 15 aus einem Material bzw. einem Werkstoff herzustellen, der an die Materialzusammensetzung des zu beschichtenden Bauteils, im gezeigten Ausführungsbeispiel an die Materialzusammensetzung der Schaufel 10 bzw. des Schaufelblatts 1 1, angepasst ist. Besteht das zu beschichtende Bauteil, nämlich das Schaufelblatt 1 1, aus einer Titanlegierung, so ist die erste Schicht 15 der Verschleißschutzschicht 13 ebenfalls aus einer Titanlegierung bebildet. Im gezeigten Ausführungsbeispiel ist das Schaufelblatt aus einem Titan-Aluminium-Material bzw. einem Titan-Aluminium-Werkstoff gebildet und die erste Schicht 15 der Verschleißschutzschicht 13 besteht ebenfalls aus einem Titan- Aluminium-Werkstoff. Die erste Schicht 15 der Verschleißschutzschicht 13 ist jedoch gegenüber dem zu beschichtenden Bauteil, nämlich dem zu beschichtenden Schaufelblatt 1 1, porös und relativ weich ausgebildet. In Fig. 2 sind Poren 17 innerhalb der ersten Schicht 15 der Verschleißschutzschicht 13 stark schematisiert dargestellt. Die poröse sowie relativ weiche erste Schicht 15 verfügt über dämpfende Eigenschaften.It is within the meaning of the present invention to produce the first layer 15 from a material or a material that is adapted to the material composition of the component to be coated, in the exemplary embodiment shown to the material composition of the blade 10 or of the airfoil 11 , If the component to be coated, namely the airfoil 11, consists of a titanium alloy, then the first layer 15 of the wear protection layer 13 is also formed from a titanium alloy. In the exemplary embodiment shown, the airfoil is formed from a titanium-aluminum material or a titanium-aluminum material and the first layer 15 of the wear protection layer 13 likewise consists of a titanium-aluminum material. However, the first layer 15 of the wear protection layer 13 is porous and relatively soft compared to the component to be coated, namely the airfoil 11 to be coated. In Fig. 2, pores 17 are within the The first layer 15 of the wear protection layer 13 is shown in a highly schematic manner. The porous and relatively soft first layer 15 has damping properties.
Die auf die erste Schicht 15 aufgebrachte zweite Schicht 16 ist im Vergleich zur ersten Schicht 15 sowie im Vergleich zum zu beschichtenden Bauteil, nämlich zum zu beschichtenden Schaufelblatt 1 1, relativ hart ausgebildet. Bei einem Bauteil aus einem Titan-Aluminium-Werkstoff und einer ersten Schicht aus einem porösen Titan- Aluminium-Werkstoff ist die zweite Schicht 16 der Verschleißschutzschicht 13 vorzugsweise aus einem Titan-Nitrid-Werkstoff, einem Aluminium-Nitrid-Werkstoff oder einem Titan-Aluminium-Nitrid-Werkstoff hergestellt.The second layer 16 applied to the first layer 15 is relatively hard in comparison to the first layer 15 and in comparison to the component to be coated, namely the airfoil 11 to be coated. In the case of a component made of a titanium-aluminum material and a first layer made of a porous titanium-aluminum material, the second layer 16 of the wear protection layer 13 is preferably made of a titanium nitride material, an aluminum nitride material or a titanium aluminum -Nitride material manufactured.
Die zweite Schicht 16, welche die Deckschicht der Verschleißschutzschicht 13 bildet, ist gegenüber der ersten Schicht 15 relativ dünn ausgebildet. Die äußere, zweite Schicht 16 verfügt vorzugsweise über eine Dicke von weniger als 0, 1 mm. Die innenliegende erste Schicht 15 verfügt über eine Dicke von bis zu 1 mm.The second layer 16, which forms the cover layer of the wear protection layer 13, is relatively thin compared to the first layer 15. The outer, second layer 16 preferably has a thickness of less than 0.1 mm. The inner first layer 15 has a thickness of up to 1 mm.
Die relativ harte, äußere zweite Schicht 16 stellt den eigentlichen Erosionsschutz der Verschleißschutzschicht 13 bereit. Die zweite Schicht 16 schützt das Schaufelblatt 1 1 vor Erosion durch feine Partikel. Die darunter liegende, erste Schicht 15, die porös und relativ weich ausgebildet ist, verfügt über Dämpfungseigenschaften, so dass bei einem Einschlag von größeren Partikeln auf die Verschleißschutzschicht 13 von derselben Energie absorbiert werden kann. Die feinen, runden und mikroskopisch kleinen Poren 17 innerhalb der ersten Schicht 15 der Verschleißschutzschicht 13 verhindern, dass sich beim Einschlag größerer Partikel ein Riss von der relativ harten, äußeren Schicht 16 in das zu schützende Bauteil, nämlich das zu schützende Schaufelblatt 1 1 fortsetzen kann. Insofern stellt die erfindungsgemäße Verschleißschutzschicht 13 einen effektiven Schutz vor Erosionsverschleiß dar.The relatively hard, outer second layer 16 provides the actual erosion protection of the wear protection layer 13. The second layer 16 protects the airfoil 11 against erosion by fine particles. The underlying first layer 15, which is porous and relatively soft, has damping properties so that the same energy can be absorbed when larger particles impact the wear protection layer 13. The fine, round and microscopic pores 17 within the first layer 15 of the wear protection layer 13 prevent a crack from the relatively hard, outer layer 16 into the component to be protected, namely the airfoil 1 1 to be protected, when larger particles impact , In this respect, the wear protection layer 13 according to the invention represents effective protection against erosion wear.
Dadurch, dass die erste Schicht 15 der Verschleißschutzschicht 13 aus einem ähnlichen oder dem gleichen Material besteht wie das zu schützende Bauteil, werden thermisch bedingte Eigenspannungen oder Diffusionsprobleme am zu schützenden Bauteil vermieden. Die Verschleißschutzschicht 13 kann damit sicher und dauerhaft auf das zu schützende Bauteil aufgebracht werden.Because the first layer 15 of the wear protection layer 13 consists of a similar or the same material as the component to be protected, thermally induced internal stresses or diffusion problems on the part to be protected become Avoided component. The wear protection layer 13 can thus be safely and permanently applied to the component to be protected.
Die erfindungsgemäße Verschleißschutzschicht 13 wird schichtweise auf das zu schützende Bauteil aufgetragen. Auf das zu schützende Bauteil, welches eine Bauteil- Materialzusammensetzung aufweist, wird zuerst die erste Schicht 15 und darauffolgend und die zweite Schicht 16 der Verschleißschutzschicht 13 aufgetragen. Wie bereits erwähnt, fügt die erste Schicht 15 der Verschleißschutzschicht 13 über eine an die Bauteil-Materialzusammensetzung angepasste Materialzusammensetzung und ist als poröse Schicht ausgebildet.The wear protection layer 13 according to the invention is applied in layers to the component to be protected. First, the first layer 15 and subsequently and the second layer 16 of the wear protection layer 13 are applied to the component to be protected, which has a component material composition. As already mentioned, the first layer 15 of the wear protection layer 13 has a material composition adapted to the component material composition and is designed as a porous layer.
Nach einer bevorzugten Ausgestaltung des erfindungsgemäßen Verfahrens, wird die erste Schicht 15 der Verschleißschutzschicht 13 über einen gerichteten, atomaren oder nanoskaligen Teilchenstrahl bzw. Materiedampfstrahl auf die zu schützende Oberfläche des Bauteils aufgetragen. Hierzu dient insbesondere ein PVD-Verfahren (Physical Vapor Deposition). Kurz vor dem Auftreffen des gerichteten Materiedampfstrahls werden in den Materiedampfstrahl Zusatzstoffe eingelagert, die beim nachfolgenden Aushärten der ersten Schicht 15 verdampfen und dabei die Poren 17 hinterlassen. Die Zusatzstoffe sind vorzugsweise als Fulerene ausgebildet. Anstelle der Fulerene können jedoch auch andere Zusatzstoffe verwendet werden, die beim Aushärten bzw. Einbrennen der ersten Schicht 15 verdampfen und die Poren 17 hinterlassen.According to a preferred embodiment of the method according to the invention, the first layer 15 of the wear protection layer 13 is applied to the surface of the component to be protected by means of a directed, atomic or nanoscale particle beam or matter vapor jet. A PVD process (Physical Vapor Deposition) is used in particular for this. Shortly before the directional matter vapor jet strikes, additives are incorporated into the matter vapor jet, which evaporate during the subsequent hardening of the first layer 15 and thereby leave the pores 17. The additives are preferably designed as fulerenes. Instead of the fulerenes, however, other additives can also be used which evaporate when the first layer 15 hardens or burns in and leave the pores 17.
An dieser Stelle sei darauf hingewiesen, dass die erste Schicht 15 auch mithilfe eines Schlickerverfahrens auf die zu schützende Oberfläche des Bauteils aufgebracht werden kann. In diesem Fall wird ein Schlickerwerkstoff, dessen Zusammensetzung an die Materialzusammensetzung des zu schützenden Bauteils angepasst ist, durch Pinseln, Tauchen oder Spritzen auf das zu schützende Bauteil aufgetragen. In diesen Schlickerwerkstoff sind wiederum Zusatzstoffe eingelagert, die beim Aushärten der ersten Schicht verdampfen und die Poren hinterlassen.At this point it should be pointed out that the first layer 15 can also be applied to the surface of the component to be protected using a slip process. In this case, a slip material, the composition of which is adapted to the material composition of the component to be protected, is applied to the component to be protected by brushing, dipping or spraying. In turn, additives are embedded in this slip material, which evaporate when the first layer hardens and leave behind the pores.
Anschließend wird auf die erste Schicht 15 die zweite Schicht 16 aufgetragen. Im gezeigten Ausführungsbeispiel, in welchem die Verschleißschutzschicht 13 zweilagig ausgebildet ist, wird die zweite Schicht 16 unmittelbar auf die erste Schicht 15 aufgetragen. Dies erfolgt vorzugsweise durch Aufdampfen, Nitrieren, Aluminisieren oder Oxidieren. The second layer 16 is then applied to the first layer 15. In the exemplary embodiment shown, in which the wear protection layer 13 has two layers is formed, the second layer 16 is applied directly to the first layer 15. This is preferably done by vapor deposition, nitriding, aluminizing or oxidizing.

Claims

Patentansprüche claims
1. Verschleißschutzschicht, insbesondere Erosionsschutzschicht für Gasturbinenbauteile, die auf eine zu schützende Oberfläche (14) eines strömungsmechanisch beanspruchten Bauteils (10) aufgebracht ist, gekennzeichnet durch einen zumindest zweischichtigen Aufbau, wobei eine erste Schicht (15) auf der zu schützenden Oberfläche (14) des Bauteils (10) aufgebracht ist und über eine an die Materialzusammensetzung des Bauteils (10) angepasste Materialzusammensetzung verfügt, und wobei eine zweite Schicht (16) eine äußere Deckschicht bildet.1. Wear protection layer, in particular erosion protection layer for gas turbine components, which is applied to a surface (14) to be protected of a fluid-mechanically stressed component (10), characterized by an at least two-layer structure, a first layer (15) on the surface to be protected (14) of the component (10) is applied and has a material composition adapted to the material composition of the component (10), and wherein a second layer (16) forms an outer cover layer.
2. Verschleißschutzschicht nach Anspruch 1, dadurch gekennzeichnet, dass die erste Schicht (15) der Verschleißschutzschicht (13) aus dem gleichen o- der einem ähnlichen Material besteht wie das Bauteil (10).2. Wear protection layer according to claim 1, characterized in that the first layer (15) of the wear protection layer (13) consists of the same or a similar material as the component (10).
3. Verschleißschutzschicht nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die erste Schicht (15) porös und relativ weich ausgebildet ist.3. Wear protection layer according to claim 1 or 2, characterized in that the first layer (15) is porous and relatively soft.
4. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die erste Schicht (15) dämpfende Eigenschaften aufweist.4. Wear protection layer according to one or more of claims 1 to 3, characterized in that the first layer (15) has damping properties.
5. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die erste Schicht (15) unmittelbar auf die zu schützenden Oberfläche (14) des Bauteils (10) aufgebracht ist.5. Wear protection layer according to one or more of claims 1 to 4, characterized in that the first layer (15) is applied directly to the surface to be protected (14) of the component (10).
6. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Bauteil (10) aus einer Titanlegierung und die erste Schicht (15) aus einer porösen Titanlegierung besteht, wobei das Bauteil (10) insbesondere als Schaufel einer Gasturbine ausgebildet ist.6. Wear protection layer according to one or more of claims 1 to 5, characterized in that the component (10) consists of a titanium alloy and the first layer (15) consists of a porous titanium alloy, the component (10) being designed in particular as a blade of a gas turbine is.
7. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass das Bauteil (10) aus einem Titan-Aluminium- Werkstoff und die erste Schicht (15) aus einem porösen Titan-Aluminium- Werkstoff besteht.7. Wear protection layer according to one or more of claims 1 to 6, characterized in that the component (10) made of a titanium-aluminum Material and the first layer (15) consists of a porous titanium-aluminum material.
8. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die zweite Schicht (16) der Verschleißschutzschicht relativ hart ausgebildet ist.8. Wear protection layer according to one or more of claims 1 to 7, characterized in that the second layer (16) of the wear protection layer is relatively hard.
9. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass dieselbe zweischichtig ausgebildet ist, wobei die zweite Schicht (16) unmittelbar auf die erste Schicht (15) aufgebracht ist.9. Wear protection layer according to one or more of claims 1 to 8, characterized in that the same is formed in two layers, the second layer (16) being applied directly to the first layer (15).
10. Verschleißschutzschicht nach einem oder mehreren der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die zweite Schicht (16) aus einem Titan- Nitrid-Werkstoff, einem Aluminium-Nitrid-Werkstoff oder einem Titan- Aluminium-Nitrid-Werkstoff besteht.10. Wear protection layer according to one or more of claims 1 to 9, characterized in that the second layer (16) consists of a titanium nitride material, an aluminum nitride material or a titanium aluminum nitride material.
1 1. Bauteil, insbesondere Gasturbinenbauteil, mit einer Verschleißschutzschicht (13), insbesondere mit einer Erosionsschutzschicht, die auf eine zu schützende Oberfläche (14) des strömungsmechanisch beanspruchten Bauteils (10) aufgebracht ist, dadurch gekennzeichnet, dass die Verschleißschutzschicht (13) einen zumindest zweischichtigen Aufbau aufweist, wobei eine erste Schicht (15) auf der zu schützenden Oberfläche (14) des Bauteils (10) aufgebracht ist und über eine an die Materialzusammensetzung des Bauteils (10) angepasste Materialzusammensetzung verfügt, und wobei eine zweite Schicht (16) eine äußere Deckschicht bildet.1 1. Component, in particular gas turbine component, with a wear protection layer (13), in particular with an erosion protection layer, which is applied to a surface (14) to be protected of the fluid mechanically stressed component (10), characterized in that the wear protection layer (13) at least one has a two-layer structure, a first layer (15) being applied to the surface (14) of the component (10) to be protected and having a material composition adapted to the material composition of the component (10), and a second layer (16) being one forms outer cover layer.
12. Bauteil nach Anspruch 1 1, dadurch gekennzeichnet, dass die Verschleißschutzschicht nach einem oder mehreren der Ansprüche 2 bis 10 ausgebildet ist.12. The component according to claim 1 1, characterized in that the wear protection layer is formed according to one or more of claims 2 to 10.
13. Verfahren zur Herstellung einer Verschleißschutzschicht ( 13), insbesondere einer Erosionsschutzschicht für Gasturbinenbauteile, die auf eine zu schüt- zende Oberfläche (14) eines strömungsmechanisch beanspruchten Bauteils (10) aufgebracht wird, gekennzeichnet durch folgende Schritte: a) Bereitstellen des Bauteils (10) bestehend aus einer Bauteil- Materialzusammensetzuπg, b) Aufbringen der Verschleißschutzschicht ( 13) auf die zu schützende Oberfläche (14) des Bauteils (10), wobei die Verschleißschutzschicht (13) einen zumindest zweischichtigen Aufbau aufweist, wobei eine erste Schicht (15) auf der zu schützenden Oberfläche (14) des Bauteils (10) aufgebracht wird und über eine an die Bauteil- Materialzusammensetzung angepasste Materialzusammensetzung verfügt, und wobei eine zweite Schicht (16) eine äußere Deckschicht bildet.13. Method for producing a wear protection layer (13), in particular an erosion protection layer for gas turbine components, which is to be protected against a zende surface (14) of a fluid mechanically stressed component (10) is applied, characterized by the following steps: a) providing the component (10) consisting of a component material composition, b) applying the wear protection layer (13) to the surface to be protected (14 ) of the component (10), the wear protection layer (13) having an at least two-layer structure, a first layer (15) being applied to the surface (14) of the component (10) to be protected and via a component material composition that is adapted Material composition, and wherein a second layer (16) forms an outer cover layer.
14. Verfahren nach Anspruch 13, dadurch gekennzeichnet, dass die erste Schicht (15) unmittelbar auf die zu schützende Oberfläche (14) des Bauteils (10) als poröse Schicht aufgebracht wird.14. The method according to claim 13, characterized in that the first layer (15) is applied directly to the surface to be protected (14) of the component (10) as a porous layer.
15. Verfahren nach Anspruch 13 oder 14, dadurch gekennzeichnet, dass in das Material der ersten Schicht (15) Zusatzstoffe eingelagert werden, wobei diese Zusatzstoffe verdampft werden und dabei Poren (17) innerhalb der ersten Schicht (15) hinterlassen.15. The method according to claim 13 or 14, characterized in that additives are incorporated into the material of the first layer (15), these additives being evaporated and thereby leaving pores (17) within the first layer (15).
16. Verfahren nach einem oder mehreren der Ansprüche 13 bis 15, dadurch gekennzeichnet, dass die erste Schicht ( 15) der Verschleißschutzschicht als Schlickerwerkstoff durch Pinseln, Tauchen oder Spritzen aufgetragen und anschließend vorzugsweise durch Einbrennen oder durch Alitieren ausgehärtet wird.16. The method according to one or more of claims 13 to 15, characterized in that the first layer (15) of the wear protection layer is applied as a slip material by brushing, dipping or spraying and is then preferably cured by baking or by alitizing.
17. Verfahren nach einem oder mehreren der Ansprüche 13 bis 15, dadurch gekennzeichnet, dass die erste Schicht (15) der Verschleißschutzschicht mit Hilfe eines gerichteten Materiedampfstrahls, insbesondere eines PVD- Materiestrahls, aufgetragen wird. 17. The method according to one or more of claims 13 to 15, characterized in that the first layer (15) of the wear protection layer is applied with the aid of a directed material vapor jet, in particular a PVD material jet.
18. Verfahren nach einem oder mehreren der Ansprüche 13 bis 17, dadurch gekennzeichnet, dass die zweite Schicht (16) durch Aufdampfen oder durch Nitrieren oder durch Oxidieren oder durch Alitieren hergestellt wird.18. The method according to one or more of claims 13 to 17, characterized in that the second layer (16) is produced by vapor deposition or by nitriding or by oxidation or by alitation.
19. Verfahren nach Anspruch 18, dadurch gekennzeichnet, dass die zweite Schicht (16) unmittelbar auf die erste Schicht (15) aufgetragen wird. 19. The method according to claim 18, characterized in that the second layer (16) is applied directly to the first layer (15).
EP04762715A 2003-09-22 2004-08-26 Wear-resistant layer, component comprising such a wear-resistant layer, and production method Ceased EP1664383A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10343761A DE10343761A1 (en) 2003-09-22 2003-09-22 Wear protection layer, component with such a wear protection layer and manufacturing process
PCT/DE2004/001882 WO2005031038A1 (en) 2003-09-22 2004-08-26 Wear-resistant layer, component comprising such a wear-resistant layer, and production method

Publications (1)

Publication Number Publication Date
EP1664383A1 true EP1664383A1 (en) 2006-06-07

Family

ID=34306005

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04762715A Ceased EP1664383A1 (en) 2003-09-22 2004-08-26 Wear-resistant layer, component comprising such a wear-resistant layer, and production method

Country Status (4)

Country Link
US (1) US20070190352A1 (en)
EP (1) EP1664383A1 (en)
DE (1) DE10343761A1 (en)
WO (1) WO2005031038A1 (en)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102135018B (en) * 2006-06-08 2012-12-05 西门子公司 Coated turbine part and method for coating turbine part
RU2414603C2 (en) 2006-06-08 2011-03-20 Сименс Акциенгезелльшафт Component of turbine (versions), turbine and procedure for turbine component coating
DE102006050789A1 (en) * 2006-10-27 2008-04-30 Mtu Aero Engines Gmbh Vaporized coating for a gas turbine of an aircraft engine comprises pore formers formed as an adhesion promoting layer and/or a heat insulating layer
DE102007005755A1 (en) * 2007-02-06 2008-08-07 Mtu Aero Engines Gmbh Device for the protection of components with combustible titanium alloy from titanium fire and process for their production
DE102008019891A1 (en) 2008-04-21 2009-10-22 Mtu Aero Engines Gmbh Erosion protection coating
DE102008045381A1 (en) * 2008-09-02 2010-03-04 Schaeffler Kg Wear and corrosion-inhibiting layer composite
EP2228461A1 (en) 2009-02-26 2010-09-15 Siemens Aktiengesellschaft Component coating
DE102009018685A1 (en) * 2009-04-23 2010-10-28 Mtu Aero Engines Gmbh Method for producing an armor of a blade tip as well as correspondingly produced blades and gas turbines
US20100304107A1 (en) * 2009-05-27 2010-12-02 United Technologies Corporation Layered coating for erosion protection
US8721294B2 (en) 2010-05-20 2014-05-13 United Technologies Corporation Airfoil with galvanically isolated metal coating
US9291062B2 (en) 2012-09-07 2016-03-22 General Electric Company Methods of forming blades and method for rendering a blade resistant to erosion
WO2015006438A1 (en) 2013-07-09 2015-01-15 United Technologies Corporation Plated polymer compressor
WO2015006421A1 (en) 2013-07-09 2015-01-15 United Technologies Corporation Metal-encapsulated polymeric article
EP3019710A4 (en) 2013-07-09 2017-05-10 United Technologies Corporation Plated polymer fan
WO2015017095A2 (en) 2013-07-09 2015-02-05 United Technologies Corporation Plated polymer nosecone
US10227704B2 (en) * 2013-07-09 2019-03-12 United Technologies Corporation High-modulus coating for local stiffening of airfoil trailing edges
WO2015069335A2 (en) * 2013-09-09 2015-05-14 United Technologies Corporation Fan blades and manufacture methods
US9834835B2 (en) * 2015-02-18 2017-12-05 United Technologies Corporation Fire containment coating system for titanium
US10450876B2 (en) * 2015-04-15 2019-10-22 United Technologies Corporation Abrasive tip blade manufacture methods
CN114150254B (en) * 2021-11-10 2022-09-06 中国科学院上海硅酸盐研究所 Thermal barrier coating for TiAl alloy and preparation method thereof

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3758233A (en) * 1972-01-17 1973-09-11 Gen Motors Corp Vibration damping coatings
US3951612A (en) * 1974-11-12 1976-04-20 Aerospace Materials Inc. Erosion resistant coatings
US4917960A (en) * 1983-12-29 1990-04-17 Sermatech International, Inc. Porous coated product
US4839245A (en) * 1985-09-30 1989-06-13 Union Carbide Corporation Zirconium nitride coated article and method for making same
GB8710296D0 (en) * 1987-04-30 1987-06-03 British Petroleum Co Plc Wear resistant multi-layered composite
DE3742944C1 (en) * 1987-12-18 1988-10-27 Mtu Muenchen Gmbh Oxidation protection layer
US4904528A (en) * 1987-12-24 1990-02-27 United Technologies Corporation Coated gas turbine engine compressor components
US4904542A (en) * 1988-10-11 1990-02-27 Midwest Research Technologies, Inc. Multi-layer wear resistant coatings
JPH03221441A (en) * 1990-01-26 1991-09-30 Ishikawajima Harima Heavy Ind Co Ltd Anticorrosive and oxidation-resistant material and manufacture thereof
US5672436A (en) * 1990-05-31 1997-09-30 Grumman Aerospace Corporation Oxidation protection method for titanium
US5413871A (en) * 1993-02-25 1995-05-09 General Electric Company Thermal barrier coating system for titanium aluminides
US5952085A (en) * 1994-03-23 1999-09-14 Rolls-Royce Plc Multiple layer erosion resistant coating and a method for its production
US5975912A (en) * 1994-06-03 1999-11-02 Materials Research Corporation Low temperature plasma-enhanced formation of integrated circuits
US5783315A (en) * 1997-03-10 1998-07-21 General Electric Company Ti-Cr-Al protective coatings for alloys
FR2767841B1 (en) * 1997-08-29 1999-10-01 Commissariat Energie Atomique PROCESS FOR THE PREPARATION BY CHEMICAL VAPOR DEPOSITION (CVD) OF A MULTI-LAYER COATING BASED ON Ti-Al-N
GB9911006D0 (en) * 1999-05-13 1999-07-14 Rolls Royce Plc A titanium article having a protective coating and a method of applying a protective coating to a titanium article
US6544665B2 (en) * 2001-01-18 2003-04-08 General Electric Company Thermally-stabilized thermal barrier coating
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005031038A1 *

Also Published As

Publication number Publication date
US20070190352A1 (en) 2007-08-16
DE10343761A1 (en) 2005-04-14
WO2005031038A1 (en) 2005-04-07

Similar Documents

Publication Publication Date Title
EP1664383A1 (en) Wear-resistant layer, component comprising such a wear-resistant layer, and production method
EP2398936B1 (en) Erosion resistant coating system for gas turbine components
EP2245274B1 (en) Device and method for the partial coating of components
EP3155284A1 (en) Brake disc for a motor vehicle
EP2352907B1 (en) Anti-erosion layer for aerodynamic components and structures and method for the production thereof
DE102009049707A1 (en) Method for producing a rotor or stator blade and such a blade
DE102011056307A1 (en) Brake disc, used for motor car, includes brake disc pot, and brake disc ring provided with friction surfaces, where brake disc ring consists of cast iron material, which is coated with protective coating in region of the friction surfaces
DE102005060243A1 (en) Process for coating hollow internally cooled gas turbine blades with adhesive-, zirconium oxide ceramic- and Cr diffusion layers useful in gas turbine engine technology has adhesive layer applied by plasma or high rate spraying method
DE102009011913A1 (en) Thermal insulation layer system for use in gas turbine, comprises metallic adhesion-promoting layer, and ceramic thermal insulation layer applied on adhesion-promoting layer
EP2576863B1 (en) Method for producing a layer by means of cold spraying and use of such a layer
WO2011151195A1 (en) Bogie shaft for a railway vehicle having a stone guard and method for producing same
EP3320127A1 (en) Contour-following protective coating for compressor components of gas turbines
DE102010005389A1 (en) Structured surface coating by means of kinetic cold gas spraying
EP1654441B1 (en) Run-in coating of a gas turbine and method for fabricating such a coating
EP2537959B1 (en) Multiple wear-resistant coating and method for its production
EP1805344B1 (en) Method for producing a component covered with a wear-resistant coating
WO2007144374A1 (en) Method of coating a component in whose surface holes are provided
DE102005044991A1 (en) Process for producing a protective layer, protective layer and component with a protective layer
DE10329049A1 (en) Method for producing a protective layer, protective layer, use thereof and component with a protective layer
DE102012105521A1 (en) Use of a carbon coating for coating a masking agent for section-wise masking of surface portions of a component, which is provided for thermal spraying
WO2021175879A1 (en) Cleaning method for ceramic fiber composite materials
WO2012038217A1 (en) Turbine blade comprising a ceramic anti-erosion layer for a low-pressure stage of a steam turbine
DE102018220338A1 (en) Turbine component for a turbomachine, method for producing, maintaining and / or overhauling a turbine component, turbine of a turbomachine and turbomachine
DE10254823A1 (en) Procedure for manufacture of test blades for gas turbines comprises first stage where blade with initial profile is manufactured, and second stage where by flame spraying process a material is applied to blade surface to change profile
DE102016221023A1 (en) PROCESS FOR COATING THROUGH THERMAL SPRAYING AND PREPARATION OF A SURFACE THEREFOR BY ELECTROCHEMICAL OR CHEMICAL ETCHING OR LASER MATERIAL PROCESSING

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: 20060211

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES GMBH

Owner name: DAIMLERCHRYSLER AG

17Q First examination report despatched

Effective date: 20070720

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES GMBH

Owner name: DAIMLER AG

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20090509