EP1805344A1 - Method for producing a component covered with a wear-resistant coating - Google Patents

Method for producing a component covered with a wear-resistant coating

Info

Publication number
EP1805344A1
EP1805344A1 EP05799632A EP05799632A EP1805344A1 EP 1805344 A1 EP1805344 A1 EP 1805344A1 EP 05799632 A EP05799632 A EP 05799632A EP 05799632 A EP05799632 A EP 05799632A EP 1805344 A1 EP1805344 A1 EP 1805344A1
Authority
EP
European Patent Office
Prior art keywords
component
coated
protection coating
coating
wear
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.)
Granted
Application number
EP05799632A
Other languages
German (de)
French (fr)
Other versions
EP1805344B1 (en
Inventor
Wolfgang Eichmann
Karl-Heinz Manier
Markus Uecker
Thomas Uihlein
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
Original Assignee
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1805344A1 publication Critical patent/EP1805344A1/en
Application granted granted Critical
Publication of EP1805344B1 publication Critical patent/EP1805344B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • 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
    • C23C4/18—After-treatment

Definitions

  • the invention relates to a process for producing a component coated with a wear protection coating, in particular a corrosion protection coating or anti-corrosion coating, in particular a gas turbine component.
  • Gas turbine components are exposed during their operation to high wear, in particular by oxidation, corrosion or erosion. It is therefore known from the prior art to provide gas turbine components with corresponding wear protection coatings. By putting on a wear protection coating, however, the so-called HCP service life of the base material of the coated gas turbine component is reduced. In order to compensate for this reduction of the HCF service life caused by the coating, it is already known from the prior art to subject the gas turbine component to be coated to a surface hardening by means of shot peening in particular before the coating. Due to the subsequent coating of the gas turbine component, which usually takes place at elevated coating temperatures, however, part of the solidification achieved by the shot peening is degraded again. Surface hardening of the component to be coated prior to coating thereof with the wear protection coating is therefore only partially effective.
  • JP-11343565-A it is already known to apply a coating of an intermetallic material to a component made of a titanium-based alloy. According to this prior art, the coating of the intermetallic material undergoes diffusion heat treatment and, if appropriate, surface hardening by shot peening. However, the problem arises that the brittle, intermetallic diffusion coating is damaged during surface hardening.
  • the present invention is based on the problem to provide a novel method for producing a coated with a Verschl divide ⁇ protective coating component.
  • the method comprises at least the following steps: a) provision of a component to be coated on a component surface; b) at least partially coating the component on its component surface with a wear protection coating having at least two layers or at least two layers, wherein the wear protection coating comprises at least one relatively soft layer and at least one relatively hard layer; c) surface hardening of the at least partially coated component on its coated component surface.
  • the present invention it is proposed to apply a minimum of two-layer or at least two-layer wear protection coating to the surface of the component to be coated, and subsequently to subject the component thus coated to surface hardening by preferably shot peening.
  • the at least two-layer wear protection coating has at least one relatively soft layer and at least one relatively hard layer. Due to the combination according to the invention of coating the component with a multilayer wear protection coating with subsequent surface treatment, the energy applied to the wear protection coating during surface hardening can be reduced without the risk of damage to the wear protection coating.
  • FIG. 2 shows a schematic cross section through a wear protection coating
  • FIG. 4 shows a diagram for clarifying the pressure-voltage profile which is set in the coated component when the method according to the invention is carried out.
  • 1 shows by way of example as a component to be coated with the method according to the invention a gas turbine blade 10 which has an airfoil 11 and a blade root 12.
  • the gas turbine blade 10 provided is now to be coated in the area of the surface 13 of the airfoil 11 with a wear protection coating, preferably with a corrosion protection coating or erosion protection coating.
  • the procedure is such that an at least two-layer or at least two-layer wear protection coating is applied to the surface 13.
  • FIG. 2 shows that a two-layer or two-layer wear protection coating 14 made of a relatively soft, metallic layer 15 and a relatively hard, ceramic layer 16 is applied to the surface 13 of the airfoil 11.
  • the relatively hard, metallic layer 15 is applied directly to the surface 13 and has a material composition which is adapted to the material composition of the blade 11.
  • FIG. 3 shows a Verschleisstik ⁇ coating 17, which is composed of a plurality of relatively soft, metallic layers 15 and a plurality of relatively hard, ceramic layers 16.
  • the specific number of relatively hard, ceramic layers and the specific number of relatively soft, metallic layers is for the present invention of minor importance and is responsible for the selection of the person skilled in the art.
  • the component coated with the wear protection coating 14, 17 is subsequently subjected to surface hardening by, in particular, shot peening.
  • the energy applied to the wear-resistant coating 14 or 17 during cooling can be elastically broken down in the relatively soft, metallic layers 15 as a result of the multilayer structure of the wear protection coating described above. There is then no risk of damage to the relatively hard, ceramic layers 16.
  • FIG. 4 shows a diagram in which, on the horizontally extending axis 18, starting from the surface of the coated component, the bottom thereof and on the vertically extending axis 19 are applied with the compressive stress induced in the component by means of the method according to the invention.
  • the line 20 the surface of the uncoated Bau ⁇ part is shown; the region to the left of the line 20 accordingly relates to the wear protection coating, the region to the right of the line 20 meets the component as such.
  • the compressive stress profile indicated by the reference numeral 21 can be realized over the depth of the coated component.
  • the fatigue strength of the base material of the coated component remains fully intact.
  • a suitable choice of the parameters for the shot peening or surface hardening furthermore, a smoothing effect on the surface of the coated component can be achieved.
  • the method according to the invention is preferably used for coating gas turbine blades, which are formed from a titanium base alloy or nickel-base alloy.
  • blades of a turbine or of a compressor of an aircraft engine can be coated with the method according to the invention.
  • the relatively soft, metallic layers can also be designed as porous layers. Furthermore, it is possible to arrange a graded material layer between a relatively soft, metallic layer and a relatively hard, ceramic layer.
  • the layers are preferably applied to the surface of the component to be coated by a PVD (Physical Vapor Deposition) process.

Abstract

The invention relates to a method for producing a component which is coated with a wear-resistant coating, in particular a corrosion-resistant coating or erosion- resistant coating, in particular a gas turbine component. Said method comprises the following steps; a) a component (10), whereby the surface (13) thereof is to be coated, is prepared; b) the component (11) is at least partially coated on the surface thereof with an at least hard double-layered and/or at least soft double-layered wear-resistant coating (14). The wear-resistant coating (14) comprises at least one relatively soft layer (15) and at least one relatively hard layer (16); c) the at least partially coated component on the covered component surface thereof is surface hardened.

Description

Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils Process for producing a component coated with a wear protection coating
Die Erfindung betrifft ein Verfahren zur Herstellung eines mit einer Ver¬ schleißschutzbeschichtung, insbesondere einer Korrosionsschutzbeschich- tung oder Ξrosionsschutzbeschichtung, beschichteten Bauteils, insbesonde¬ re Gasturbinenbauteils.The invention relates to a process for producing a component coated with a wear protection coating, in particular a corrosion protection coating or anti-corrosion coating, in particular a gas turbine component.
Gasturbinenbauteile sind während ihres Betriebs einem hohen Verschleiß, insbesondere durch Oxidation, Korrosion oder auch Erosion, ausgesetzt. Es ist daher aus dem Stand der Technik bekannt, Gasturbinenbauteile mit ent¬ sprechenden Verschleißschutzbeschichtungen zu versehen. Durch das Auf¬ bringen einer Verschleißschutzbeschichtung wird jedoch die sogenannte HCP-Lebensdauer des Grundwerkstoffs des beschichteten Gasturbinenbauteils reduziert. Um diese durch die Beschichtung bedingte Reduktion der HCF- Lebensdauer auszugleichen, ist es aus dem Stand der Technik bereits be¬ kannt, das zu beschichtende Gasturbinenbauteil vor der Beschichtung einer Oberflächenverfestigung durch insbesondere Kugelstrahlen zu unterziehen. Durch die nachfolgende Beschichtung des Gasturbinenbauteils, die übli¬ cherweise bei erhöhten Beschichtungstemperaturen abläuft, wird jedoch ein Teil der durch das Kugelstrahlen erzielten Verfestigung wieder abgebaut. Das Oberflächenverfestigen des zu beschichtenden Bauteils vor dem Be¬ schichten desselben mit der Verschleißschutzbeschichtung ist demnach nur bedingt wirksam.Gas turbine components are exposed during their operation to high wear, in particular by oxidation, corrosion or erosion. It is therefore known from the prior art to provide gas turbine components with corresponding wear protection coatings. By putting on a wear protection coating, however, the so-called HCP service life of the base material of the coated gas turbine component is reduced. In order to compensate for this reduction of the HCF service life caused by the coating, it is already known from the prior art to subject the gas turbine component to be coated to a surface hardening by means of shot peening in particular before the coating. Due to the subsequent coating of the gas turbine component, which usually takes place at elevated coating temperatures, however, part of the solidification achieved by the shot peening is degraded again. Surface hardening of the component to be coated prior to coating thereof with the wear protection coating is therefore only partially effective.
Aus der JP-11343565-A ist es bereits bekannt, auf ein Bauteil aus einer Titanbasislegierung eine Beschichtung aus einem intermetallischen Werk¬ stoff aufzubringen. Die Beschichtung aus dem intermetallischen Werkstoff wird gemäß diesem Stand der Technik einer Diffusions-wärmebehandlung und gegebenenfalls einem Oberflächenverfestigen durch Kugelstrahlen unterzo¬ gen. Dabei tritt jedoch das Problem auf, dass die spröde, intermetalli¬ sche Diffusionsbeschichtung beim Oberflächenverfestigen beschädigt wird.From JP-11343565-A it is already known to apply a coating of an intermetallic material to a component made of a titanium-based alloy. According to this prior art, the coating of the intermetallic material undergoes diffusion heat treatment and, if appropriate, surface hardening by shot peening. However, the problem arises that the brittle, intermetallic diffusion coating is damaged during surface hardening.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Herstellung eines mit einer Verschlei߬ schutzbeschichtung beschichteten Bauteils zu schaffen.On this basis, the present invention is based on the problem to provide a novel method for producing a coated with a Verschlei߬ protective coating component.
Dieses Problem wird durch ein Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils gemäß Patentanspruch 1 gelöst. Erfindungsgemäß umfasst das Verfahren zumindest die folgenden Schritte: a) Bereitstellen eines an einer Bauteiloberfläche zu beschich¬ tenden Bauteils; b) zumindest teilweises Beschichten des Bauteils an sei¬ ner Bauteiloberfläche mit einer mindestens zweischichtigen bzw. mindes¬ tens zweilagigen Verschleißschutzbeschichtung, wobei die Verschleiß- schutzbeschichtung mindestens eine relativ weiche Schicht und mindestens eine relativ harte Schicht umfasst; c) Oberflächenverfestigen des zumin¬ dest teilweise beschichteten Bauteils an seiner beschichteten Bauteil¬ oberfläche.This problem is solved by a method for producing a wear-resistant coated component according to claim 1 solved. According to the invention, the method comprises at least the following steps: a) provision of a component to be coated on a component surface; b) at least partially coating the component on its component surface with a wear protection coating having at least two layers or at least two layers, wherein the wear protection coating comprises at least one relatively soft layer and at least one relatively hard layer; c) surface hardening of the at least partially coated component on its coated component surface.
Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, eine mindes¬ tens zweischichtige bzw. mindestens zweilagige Verschleißschutzbeschich¬ tung auf die Oberfläche des zu beschichtenden Bauteils aufzutragen, und das so beschichtete Bauteil nachfolgend einem Oberflächenverfestigen durch vorzugsweise Kugelstrahlen zu unterziehen. Die mindestens zwei¬ schichtige Verschleißschutzbeschichtung verfügt über mindestens eine re¬ lativ weiche Schicht und mindestens eine relativ harte Schicht. Durch die erfindungsgemäße Kombination des Beschichtens des Bauteils mit einer MuI- tilayer-Verschleißschutzbeschichtung mit nachfolgendem Oberflächenverfes¬ tigen, kann die beim Oberflächenverfestigen auf die Verschleißschutzbe¬ schichtung aufgebrachte Energie abgebaut werden, ohne dass die Gefahr von Beschädigungen der Verschleißschutzbeschichtung besteht.For the purposes of the present invention, it is proposed to apply a minimum of two-layer or at least two-layer wear protection coating to the surface of the component to be coated, and subsequently to subject the component thus coated to surface hardening by preferably shot peening. The at least two-layer wear protection coating has at least one relatively soft layer and at least one relatively hard layer. Due to the combination according to the invention of coating the component with a multilayer wear protection coating with subsequent surface treatment, the energy applied to the wear protection coating during surface hardening can be reduced without the risk of damage to the wear protection coating.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteran¬ sprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Er¬ findung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:Preferred developments of the invention will become apparent from the subclaims and the following description. Exemplary embodiments of the invention will be explained in more detail with reference to the drawing, without being limited thereto. Showing:
Fig. 1 eine zu beschichtende Gasturbinenschaufel in schematisierter Seitenansicht;Fig. 1 to be coated gas turbine blade in a schematic side view;
Fig. 2 einen schematisierten Querschnitt durch eine Verschleißschutz¬ beschichtung;FIG. 2 shows a schematic cross section through a wear protection coating; FIG.
Fig. 3 einen schematisierten Querschnitt durch eine alternative Ver¬ schleißschutzbeschichtung; und3 shows a schematic cross section through an alternative wear protection coating; and
Fig. 4 ein Diagramm zur Verdeutlichung des sich bei Durchführung des erfindungsgemäßen Verfahrens im beschichteten Bauteil einstel¬ lenden Druckspannungsverlaufs.4 shows a diagram for clarifying the pressure-voltage profile which is set in the coated component when the method according to the invention is carried out.
Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf die Fig. 1 bis 4 im größeren Detail beschrieben. Fig. 1 zeigt exemplarisch als mit dem erfindungsgemäßen Verfahren zu be¬ schichtendes Bauteil eine Gasturbinenschaufel 10, die ein Schaufelblatt 11 sowie einen Schaufelfuß 12 aufweist. Mit dem erfindungsgemäßen Verfah¬ ren soll die bereitgestellte Gasturbinenschaufel 10 nun im Bereich der Oberfläche 13 des Schaufelblatts 11 mit einer Verschleißschutzbeschich- tung, vorzugsweise mit einer Korrosionsschutzbeschichtung oder Erosions- schutzbeschichtung, beschichtet werden.Hereinafter, the present invention will be described in more detail with reference to FIGS. 1 to 4. 1 shows by way of example as a component to be coated with the method according to the invention a gas turbine blade 10 which has an airfoil 11 and a blade root 12. With the method according to the invention, the gas turbine blade 10 provided is now to be coated in the area of the surface 13 of the airfoil 11 with a wear protection coating, preferably with a corrosion protection coating or erosion protection coating.
Hierzu wird im Sinne des erfindungsgemäßen Verfahrens so vorgegangen, dass auf die Oberfläche 13 eine mindestens zweischichtige bzw. mindestens zweilagige Verschleißschutzbeschichtung aufgebracht wird. So zeigt zum Beispiel Fig. 2, dass auf die Oberfläche 13 des Schaufelblatts 11 eine zweilagige bzw. zweischichtige Verschleißschutzbeschichtung 14 aus einer relativ weichen, metallischen Schicht 15 und einer relativ harten, kera¬ mischen Schicht 16 aufgebracht ist. Die relativ harte, metallische Schicht 15 ist unmittelbar auf die Oberfläche 13 aufgebracht und verfügt über eine WerkstoffZusammensetzung, die an die Werkstoffzusammensetzung des Schaufelblatts 11 angepasst ist. Fig. 3 zeigt eine Verschleißschutz¬ beschichtung 17, die aus mehreren relativ weichen, metallischen Schichten 15 sowie mehreren relativ harten, keramischen Schichten 16 aufgebaut ist. Die konkrete Anzahl der relativ harten, keramischen Schichten sowie die konkrete Anzahl der relativ weichen, metallischen Schichten ist für die hier vorliegende Erfindung von untergeordneter Bedeutung und obliegt der Auswahl des hier angesprochenen Fachmanns.For this purpose, in the sense of the method according to the invention, the procedure is such that an at least two-layer or at least two-layer wear protection coating is applied to the surface 13. Thus, for example, FIG. 2 shows that a two-layer or two-layer wear protection coating 14 made of a relatively soft, metallic layer 15 and a relatively hard, ceramic layer 16 is applied to the surface 13 of the airfoil 11. The relatively hard, metallic layer 15 is applied directly to the surface 13 and has a material composition which is adapted to the material composition of the blade 11. FIG. 3 shows a Verschleissschutz¬ coating 17, which is composed of a plurality of relatively soft, metallic layers 15 and a plurality of relatively hard, ceramic layers 16. The specific number of relatively hard, ceramic layers and the specific number of relatively soft, metallic layers is for the present invention of minor importance and is responsible for the selection of the person skilled in the art.
Im Sinne der hier vorliegenden Erfindung wird das mit der Verschlei߬ schutzbeschichtung 14, 17 beschichtete Bauteil nachfolgend einem Oberflä- chenverfestigen durch insbesondere Kugelstrahlen unterzogen. Die beim Ku¬ gelstrahlen auf die Verschleißschutzbeschichtung 14 bzw. 17 aufgebrachte Energie kann infolge des oben beschriebenen Multilayer-Aufbaus der Ver¬ schleißschutzbeschichtung in den relativ weichen, metallischen Schichten 15 elastisch abgebaut werden. Es besteht dann keine Gefahr von Beschädi¬ gungen der relativ harten, keramischen Schichten 16.In the context of the present invention, the component coated with the wear protection coating 14, 17 is subsequently subjected to surface hardening by, in particular, shot peening. The energy applied to the wear-resistant coating 14 or 17 during cooling can be elastically broken down in the relatively soft, metallic layers 15 as a result of the multilayer structure of the wear protection coating described above. There is then no risk of damage to the relatively hard, ceramic layers 16.
Mit dem erfindungsgemäßen Verfahren ist es möglich, nach dem Beschichten eines Bauteils mit einer als Multilayer-Schichtsystem ausgebildeten Ver¬ schleißschutzbeschichtung durch nachfolgendes Oberflächenverfestigen ei¬ nen optimalen Spannungsverlauf über die Verschleißschutzbeschichtung so¬ wie das Bauteil einzustellen, ohne dass die Gefahr von Beschädigungen der Verschleißschutzbeschichtung besteht. So zeigt Fig. 4 ein Diagramm, in welchem auf der horizontal verlaufenden Achse 18 ausgehend von der Oberfläche des beschichteten Bauteils die Tie¬ fe desselben und auf der vertikal verlaufenden Achse 19 die mit Hilfe des erfindungsgemäßen Verfahrens im Bauteil induzierte Druckspannung aufge¬ tragen ist. Mit der Linie 20 ist die Oberfläche des unbeschichteten Bau¬ teils dargestellt; der Bereich links von der Linie 20 betrifft demnach die Verschleißschutzbeschichtung, der Bereich rechts von der Linie 20 be¬ trifft das Bauteil als solches. Mit dem erfindungsgemäßen Verfahren lässt sich der mit der Bezugsziffer 21 gekennzeichnete Druckspannungsverlauf über der Tiefe des beschichteten Bauteils realisieren.With the method according to the invention, it is possible, after coating a component with a wear protection coating designed as a multilayer layer system, to set an optimum stress curve over the wear protection coating by subsequent surface hardening, without the risk of damaging the wear protection coating , Thus, FIG. 4 shows a diagram in which, on the horizontally extending axis 18, starting from the surface of the coated component, the bottom thereof and on the vertically extending axis 19 are applied with the compressive stress induced in the component by means of the method according to the invention. With the line 20, the surface of the uncoated Bau¬ part is shown; the region to the left of the line 20 accordingly relates to the wear protection coating, the region to the right of the line 20 meets the component as such. With the method according to the invention, the compressive stress profile indicated by the reference numeral 21 can be realized over the depth of the coated component.
Bei Verwendung des erfindungsgemäßen Verfahrens zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils bleibt die Schwingfestigkeit des Grundwerkstoffs des beschichteten Bauteils voll er¬ halten. Bei entsprechender Wahl der Parameter für das Kugelstrahlen bzw. Oberflächenverfestigen kann weiterhin ein Glättungseffekt an der Oberflä¬ che des beschichteten Bauteils erzielt werden.When using the method according to the invention for producing a component coated with a wear protection coating, the fatigue strength of the base material of the coated component remains fully intact. With a suitable choice of the parameters for the shot peening or surface hardening, furthermore, a smoothing effect on the surface of the coated component can be achieved.
Wie bereits erwähnt, wird das erfindungsgemäße Verfahren vorzugsweise zur Beschichtung von Gasturbinenschaufeln eingesetzt, die aus einer Titanba¬ sislegierung oder Nickelbasislegierung gebildet sind. So können mit dem erfindungsgemäßen Verfahren zum Beispiel Schaufeln einer Turbine oder ei¬ nes Verdichters eines Flugtriebwerks beschichtet werden.As already mentioned, the method according to the invention is preferably used for coating gas turbine blades, which are formed from a titanium base alloy or nickel-base alloy. Thus, for example, blades of a turbine or of a compressor of an aircraft engine can be coated with the method according to the invention.
Abschließend sei darauf hingewiesen, dass die relativ weichen, metalli¬ schen Schichten auch als poröse Schichten ausgeführt sein können. Weiter¬ hin ist es möglich, zwischen einer relativ weichen, metallischen Schicht und einer relativ harten, keramischen Schicht eine gradierte Werkstoff¬ schicht anzuordnen. Die Schichten werden vorzugsweise durch einen PVD (Physical Vapor Deposition) -Prozess auf die Oberfläche des zu beschich¬ tenden Bauteils aufgetragen. Finally, it should be pointed out that the relatively soft, metallic layers can also be designed as porous layers. Furthermore, it is possible to arrange a graded material layer between a relatively soft, metallic layer and a relatively hard, ceramic layer. The layers are preferably applied to the surface of the component to be coated by a PVD (Physical Vapor Deposition) process.

Claims

Patentansprüche claims
1. Verfahren zur Herstellung eines mit einer Verschleißschutzbeschich- tung, insbesondere einer Korrosionsschutzbeschichtung oder Erosions- schutzbeschichtung, beschichteten Bauteils, insbesondere Gasturbi¬ nenbauteils, mit folgenden Schritten: a) Bereitstellen eines an einer Bauteiloberfläche (13) zu be¬ schichtenden Bauteils (10) ; b) zumindest teilweises Beschichten des Bauteils (11) an seiner Bauteiloberfläche mit einer mindestens zweischichtigen bzw. mindes¬ tens zweilagigen Verschleißschutzbeschichtung (14; 17) , wobei die Verschleißschutzbeschichtung (14; 17) mindestens eine relativ weiche Schicht (15) und mindestens eine relativ harte Schicht (16) umfasst; c) Oberflächenverfestigen des zumindest teilweise beschichteten Bauteils an seiner beschichteten Bauteiloberfläche.1. A method for producing a component coated with a wear protection coating, in particular a corrosion protection coating or erosion protection coating, in particular a gas turbine component, comprising the following steps: a) providing a component (10) to be coated on a component surface (13) ; b) at least partially coating the component (11) on its component surface with a wear protection coating (14; 17) having at least two layers or at least two layers, wherein the wear protection coating (14; 17) comprises at least one relatively soft layer (15) and at least one relative hard layer (16); c) surface hardening of the at least partially coated component on its coated component surface.
2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die Verschleißschutzbeschichtung (14; 17) mindestens eine rela¬ tiv weiche, metallische Schicht (15) und mindestens eine relativ harte, keramische Schicht (16) umfasst.2. The method according to claim 1, characterized in that the wear protection coating (14; 17) comprises at least one rela¬ tively soft metallic layer (15) and at least one relatively hard, ceramic layer (16).
3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Verschleißschutzbeschichtung (17) mehrere relativ weiche, metallische Schichten (15) und mehrere relativ harte, keramische Schichten (16) umfasst.3. The method of claim 1 or 2, characterized in that the wear-resistant coating (17) comprises a plurality of relatively soft, metallic layers (15) and a plurality of relatively hard, ceramic layers (16).
4. Verfahren nach einem oder mehreren der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass als Bauteil (10) ein Gasturbinenbauteil bereitgestellt und zu¬ mindest teilweise beschichtet wird.4. The method according to one or more of claims 1 to 3, characterized in that a gas turbine component is provided as a component (10) and at least partially coated.
5. Verfahren nach Anspruch 4, dadurch gekennzeichnet, dass eine Gasturbinenschaufel bereitgestellt wird, die an ihrer Schaufelblattoberfläche beschichtet wird. 5. The method according to claim 4, characterized in that a gas turbine blade is provided, which is coated on its blade surface.
6. Verfahren nach einem oder mehreren der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Oberflächenverfestigen des Bauteils an seiner beschichteten Bauteiloberfläche mittels Strahlen durchgeführt wird.6. The method according to one or more of claims 1 to 5, characterized in that the surface solidification of the component is carried out on its coated component surface by means of beams.
7. Verfahren nach Ansprüche 6, dadurch gekennzeichnet, dass das Oberflächenverfestigen mittels Kugelstrahlen durchgeführt wird. 7. The method according to claims 6, characterized in that the surface strengthening is carried out by means of shot peening.
EP05799632A 2004-10-16 2005-10-07 Method for producing a component covered with a wear-resistant coating Expired - Fee Related EP1805344B1 (en)

Applications Claiming Priority (2)

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DE102004050474A DE102004050474A1 (en) 2004-10-16 2004-10-16 Process for producing a component coated with a wear protection coating
PCT/DE2005/001795 WO2006042506A1 (en) 2004-10-16 2005-10-07 Method for producing a component covered with a wear-resistant coating

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EP1805344A1 true EP1805344A1 (en) 2007-07-11
EP1805344B1 EP1805344B1 (en) 2011-03-16

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US (1) US8920881B2 (en)
EP (1) EP1805344B1 (en)
CA (1) CA2584350A1 (en)
DE (2) DE102004050474A1 (en)
WO (1) WO2006042506A1 (en)

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DE102004050474A1 (en) 2006-04-20
US20080124469A1 (en) 2008-05-29
CA2584350A1 (en) 2006-04-27
EP1805344B1 (en) 2011-03-16
WO2006042506A1 (en) 2006-04-27
DE502005011139D1 (en) 2011-04-28
US8920881B2 (en) 2014-12-30

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