EP1805344B1 - Method for producing a component covered with a wear-resistant coating - Google Patents

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

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Publication number
EP1805344B1
EP1805344B1 EP05799632A EP05799632A EP1805344B1 EP 1805344 B1 EP1805344 B1 EP 1805344B1 EP 05799632 A EP05799632 A EP 05799632A EP 05799632 A EP05799632 A EP 05799632A EP 1805344 B1 EP1805344 B1 EP 1805344B1
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EP
European Patent Office
Prior art keywords
component
coated
resistant coating
wear
coating
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EP05799632A
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German (de)
French (fr)
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EP1805344A1 (en
Inventor
Wolfgang Eichmann
Karl-Heinz Manier
Markus Uecker
Thomas Uihlein
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MTU Aero Engines AG
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MTU Aero Engines GmbH
MTU Aero Engines AG
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • 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 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.
  • 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 applying a wear protection coating, however, the so-called HCF service life of the base material of the coated gas turbine component is reduced. In order to compensate for this reduction in 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 blasting in particular before the coating. By the subsequent coating of the gas turbine component, which usually takes place at elevated coating temperatures, however, a part of the solidification achieved by the shot peening is degraded again. The surface hardening of the component to be coated before coating it with the wear protection coating is therefore only partially effective.
  • EP 1 338 670 A2 discloses a method of making an abradable coating on a gas turbine component by first depositing an MCrAlY layer on the surface of the device, then secondarily treating a second MCrO index 2-Y index 2 O index 3 layer and subsequent coating by shot peening ,
  • JP-11343565-A It is already known to apply to a component made of a titanium-based alloy, a coating of an intermetallic material. According to this prior art, the coating of the intermetallic material is subjected to a 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 wear-resistant coating component.
  • This problem is solved by a method according to claim 1.
  • the method comprises at least the following steps: a) provision of a component to be coated on a component surface, wherein the component to be coated is subjected to surface hardening before the coating; b) at least partially coating the component on its component surface with an at least two-layer or at least two-layer wear protection coating, wherein the wear protection coating comprises at least one relatively soft, metallic and porous layer and at least one relatively hard, ceramic layer; c) surface solidification of the at least partially coated component on its coated component surface by shot peening, such that the compressive stress profile of the base material of the coated component is maintained and a smoothing on the surface of the coated component is achieved.
  • the energy applied to the wear protection coating during surface hardening can be elastically broken down, without the risk of damage to the wear protection coating.
  • FIGS Fig. 1 to 4 described in greater detail.
  • Fig. 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 provided gas turbine blade 10 is now to be coated in the region of the surface 13 of the blade 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.
  • 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 blade 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 wear protection 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 anti-wear coating 14 or 17 during shot peening can be elastically broken down in the relatively soft, metallic layers 15 as a result of the above-described multilayer structure of the wear protection coating. There is then no risk of damage to the relatively hard, ceramic layers 16.
  • Fig. 4 a diagram in which on the horizontally extending axis 18, starting from the surface of the coated component, the depth thereof and on the vertical axis 19 which is applied by means of the method according to the invention in the component induced compressive stress.
  • the line 20 the surface of the uncoated component is shown; the area to the left of the line 20 thus relates to the anti-wear coating, the area to the right of the line 20 relates to 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 smoothing effect on the surface of the coated component is furthermore achieved.
  • the method according to the invention is preferably used for coating gas turbine blades which are formed from a titanium-based alloy or nickel-based alloy.
  • blades of a turbine or a compressor of an aircraft engine can be coated with the method according to the invention.
  • the relatively soft, metallic layers are 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.

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

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

Die Erfindung betrifft ein Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung, insbesondere einer Korrosionsschutzbeschichtung oder Erosionsschutzbeschichtung, beschichteten Bauteils, insbesondere Gasturbinenbauteils.The invention relates to 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.

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 entsprechenden Verschleißschutzbeschichtungen zu versehen. Durch das Aufbringen einer Verschleißschutzbeschichtung wird jedoch die sogenannte HCF-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 bekannt, das zu beschichtende Gasturbinenbauteil vor der Beschichtung einer Oberflächenverfestigung durch insbesondere Kugelstrahlen zu unterziehen. Durch die nachfolgende Beschichtung des Gasturbinenbauteils, die üblicherweise bei erhöhten Beschichtungstemperaturen abläuft, wird jedoch ein Teil der durch das Kugelstrahlen erzielten Verfestigung wieder abgebaut. Das Oberflächenverfestigen des zu beschichtenden Bauteils vor dem Beschichten 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 applying a wear protection coating, however, the so-called HCF service life of the base material of the coated gas turbine component is reduced. In order to compensate for this reduction in 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 blasting in particular before the coating. By the subsequent coating of the gas turbine component, which usually takes place at elevated coating temperatures, however, a part of the solidification achieved by the shot peening is degraded again. The surface hardening of the component to be coated before coating it with the wear protection coating is therefore only partially effective.

Die Druckschrift EP 1 338 670 A2 offenbart ein Verfahren zur Herstellung einer abreibbaren Beschichtung auf ein Gasturbinenbauteil, wobei zunächst eine MCrAlY-Schicht auf der Oberfläche des Bauteils aufgebracht wird, anschließend eine zweite MCrO-Index 2- Y-Index 2 O-Index 3-Schicht und nachfolgende Beschichtung mittels Kugelstrahlenbehandelt wird.The publication EP 1 338 670 A2 discloses a method of making an abradable coating on a gas turbine component by first depositing an MCrAlY layer on the surface of the device, then secondarily treating a second MCrO index 2-Y index 2 O index 3 layer and subsequent coating by shot peening ,

Aus der JP-11343565-A ist es bereits bekannt, auf ein Bauteil aus einer Titanbasislegierung eine Beschichtung aus einem intermetallischen Werkstoff aufzubringen. Die Beschichtung aus dem intermetallischen Werkstoff wird gemäß diesem Stand der Technik einer Diffusionswärmebehandlung und gegebenenfalls einem Oberflächenverfestigen durch Kugelstrahlen unterzogen. Dabei tritt jedoch das Problem auf, dass die spröde, intermetallische Diffusionsbeschichtung beim Oberflächenverfestigen beschädigt wird.From the , JP-11343565-A It is already known to apply to a component made of a titanium-based alloy, a coating of an intermetallic material. According to this prior art, the coating of the intermetallic material is subjected to a 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.

Aus dem Stand der Technik gemäß EP-A-1 338 670 , gemäß US-A-5 169 674 , gemäß US-A-5 516 586 und gemäß DE-C-42 29 600 sind jeweils Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils bekannt, bei welchen ein Bauteil an seiner Bauteiloberfläche zumindest teilweises mit einer mindestens zweischichtigen bzw. mindestens zweilagigen Verschleißschutzbeschichtung beschichtet wird, wobei die Verschleißschutzbeschichtung mindestens eine relativ weiche Schicht und mindestens eine relativ harte Schicht umfasst; und wobei anschließend des zumindest teilweise beschichtete Bauteils an seiner beschichteten Bauteiloberfläche einem Oberflächenverfestigen unterzogen wird.According to the prior art EP-A-1 338 670 , according to US-A-5,169,674 , according to US-A-5 516 586 and according to DE-C-42 29 600 In each case, methods for producing a component coated with a wear protection coating are known in which a component is coated on its component surface at least partially with an at least two-layer or at least two-layer wear protection coating, the wear protection coating at least one relatively soft layer and at least one relatively hard layer; and wherein subsequently the at least partially coated component is subjected to a surface hardening on its coated component surface.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils zu schaffen. Dieses Problem wird durch ein Verfahren gemäß Patentanspruch 1 gelöst. Erfindungsgemäß umfasst das Verfahren zumindest die folgenden Schritte: a) Bereitstellen eines an einer Bauteiloberfläche zu beschichtenden Bauteils, wobei das zu beschichtende Bauteil vor der Beschichtung einer Oberflächenverfestigung zu unterziehen ist; b) zumindest teilweises Beschichten des Bauteils an seiner Bauteiloberfläche mit einer mindestens zweischichtigen bzw. mindestens zweilagigen Verschleißschutzbeschichtung, wobei die Verschleißschutzbeschichtung mindestens eine relativ weiche, metallische sowie poröse Schicht und mindestens eine relativ harte, keramische Schicht umfasst; c) Oberflächenverfestigen des zumindest teilweise beschichteten Bauteils an seiner beschichteten Bauteiloberfläche durch Kugelstrahlen, derart, dass der Druckspannungsverlauf des Grundwerkstoffs des beschichteten Bauteils erhalten bleibt und eine Glättung an der Oberfläche des beschichteten Bauteils erzielt wird.On this basis, the present invention is based on the problem to provide a novel method for producing a coated with a wear-resistant coating component. This problem is solved by a method according to claim 1. According to the invention, the method comprises at least the following steps: a) provision of a component to be coated on a component surface, wherein the component to be coated is subjected to surface hardening before the coating; b) at least partially coating the component on its component surface with an at least two-layer or at least two-layer wear protection coating, wherein the wear protection coating comprises at least one relatively soft, metallic and porous layer and at least one relatively hard, ceramic layer; c) surface solidification of the at least partially coated component on its coated component surface by shot peening, such that the compressive stress profile of the base material of the coated component is maintained and a smoothing on the surface of the coated component is achieved.

Durch die erfindungsgemäße Kombination des Beschichtens des Bauteils mit einer Multilayer-Verschleißschutzbeschichtung mit nachfolgendem Oberflächenverfestigen, kann die beim Oberflächenverfestigen auf die Verschleißschutzbeschichtung aufgebrachte Energie elastisch abgebaut werden, ohne dass die Gefahr von Beschädigungen der Verschleißschutzbeschichtung besteht.The inventive combination of coating the component with a multilayer wear protection coating with subsequent surface hardening, the energy applied to the wear protection coating during surface hardening can be elastically broken down, without the risk of damage to the wear protection coating.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
eine zu beschichtende Gasturbinenschaufel in schematisierter Seitenansicht;
Fig. 2
einen schematisierten Querschnitt durch eine Verschleißschutzbeschichtung;
Fig. 3
einen schematisierten Querschnitt durch eine alternative Verschleißschutzbeschichtung; und
Fig. 4
ein Diagramm zur Verdeutlichung des sich bei Durchführung des erfindungsgemäßen Verfahrens im beschichteten Bauteil einstellenden Druckspannungsverlaufs.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a gas turbine blade to be coated in a schematic side view;
Fig. 2
a schematic cross section through a wear protection coating;
Fig. 3
a schematic cross section through an alternative wear protection coating; and
Fig. 4
a diagram illustrating the setting in carrying out the method according to the invention in the coated component compressive stress profile.

Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf die Fig. 1 bis 4 im größeren Detail beschrieben.Hereinafter, the present invention will be described with reference to FIGS Fig. 1 to 4 described in greater detail.

Fig. 1 zeigt exemplarisch als mit dem erfindungsgemäßen Verfahren zu beschichtendes Bauteil eine Gasturbinenschaufel 10, die ein Schaufelblatt 11 sowie einen Schaufelfuß 12 aufweist. Mit dem erfindungsgemäßen Verfahren soll die bereitgestellte Gasturbinenschaufel 10 nun im Bereich der Oberfläche 13 des Schaufelblatts 11 mit einer Verschleißschutzbeschichtung, vorzugsweise mit einer Korrosionsschutzbeschichtung oder Erosionsschutzbeschichtung, beschichtet werden. Fig. 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 provided gas turbine blade 10 is now to be coated in the region of the surface 13 of the blade 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, keramischen 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 Verschleißschutzbeschichtung 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. So shows, for example Fig. 2 in 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 blade 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 wear protection 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 Verschleißschutzbeschichtung 14, 17 beschichtete Bauteil nachfolgend einem Oberflächenverfestigen durch insbesondere Kugelstrahlen unterzogen. Die beim Kugelstrahlen auf die Verschleißschutzbeschichtung 14 bzw. 17 aufgebrachte Energie kann infolge des oben beschriebenen Multilayer-Aufbaus der Verschleißschutzbeschichtung in den relativ weichen, metallischen Schichten 15 elastisch abgebaut werden. Es besteht dann keine Gefahr von Beschädigungen der relativ harten, keramischen Schichten 16.For the purposes 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 anti-wear coating 14 or 17 during shot peening can be elastically broken down in the relatively soft, metallic layers 15 as a result of the above-described multilayer structure of the wear protection coating. 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 Verschleißschutzbeschichtung durch nachfolgendes Oberflächenverfestigen einen optimalen Spannungsverlauf über die Verschleißschutzbeschichtung sowie das Bauteil einzustellen, ohne dass die Gefahr von Beschädigungen der Verschleißschutzbeschichtung besteht.With the method according to the invention, it is possible, after the coating of a component with a wear protection coating designed as a multilayer coating system, to set an optimum stress curve over the wear protection coating and the component by subsequent surface hardening, without the risk of damaging the wear protection coating.

So zeigt Fig. 4 ein Diagramm, in welchem auf der horizontal verlaufenden Achse 18 ausgehend von der Oberfläche des beschichteten Bauteils die Tiefe desselben und auf der vertikal verlaufenden Achse 19 die mit Hilfe des erfindungsgemäßen Verfahrens im Bauteil induzierte Druckspannung aufgetragen ist. Mit der Linie 20 ist die Oberfläche des unbeschichteten Bauteils dargestellt; der Bereich links von der Linie 20 betrifft demnach die Verschleißschutzbeschichtung, der Bereich rechts von der Linie 20 betrifft das Bauteil als solches. Mit dem erfindungsgemäßen Verfahren lässt sich der mit der Bezugsziffer 21 gekennzeichnete Druckspannungsverlauf über der Tiefe des beschichteten Bauteils realisieren.So shows Fig. 4 a diagram in which on the horizontally extending axis 18, starting from the surface of the coated component, the depth thereof and on the vertical axis 19 which is applied by means of the method according to the invention in the component induced compressive stress. With the line 20, the surface of the uncoated component is shown; the area to the left of the line 20 thus relates to the anti-wear coating, the area to the right of the line 20 relates to 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 erhalten. Bei entsprechender Wahl der Parameter für das Kugelstrahlen bzw. Oberflächenverfestigen wird weiterhin ein Glättungseffekt an der Oberfläche des beschichteten Bauteils erzielt.When using the method according to the invention for producing a component coated with a wear-resistant coating, the fatigue strength of the base material of the coated component remains fully intact. With a suitable choice of the parameters for shot peening or surface hardening, a smoothing effect on the surface of the coated component is furthermore achieved.

Wie bereits erwähnt, wird das erfindungsgemäße Verfahren vorzugsweise zur Beschichtung von Gasturbinenschaufeln eingesetzt, die aus einer Titanbasislegierung oder Nickelbasislegierung gebildet sind. So können mit dem erfindungsgemäßen Verfahren zum Beispiel Schaufeln einer Turbine oder eines 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-based alloy or nickel-based alloy. Thus, for example, blades of a turbine or a compressor of an aircraft engine can be coated with the method according to the invention.

Abschließend sei darauf hingewiesen, dass die relativ weichen, metallischen Schichten als poröse Schichten ausgeführt sind weiterhin ist es möglich, zwischen einer relativ weichen, metallischen Schicht und einer relativ harten, keramischen Schicht eine gradierte Werkstoffschicht anzuordnen. Die Schichten werden vorzugsweise durch einen PVD (Physical Vapor Deposition)-Prozess auf die Oberfläche des zu beschichtenden Bauteils aufgetragen.Finally, it should be noted that the relatively soft, metallic layers are 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 (4)

  1. Method for producing a component that is coated with a wear-resistant coating, in particular a corrosion-resistant coating or an erosion-resistant coating, in particular a gas-turbine component, having the following steps:
    a) provision of a component (10) that is to be coated on a component surface (13), wherein the component that is to be coated is to be subjected to surface-consolidation prior to the coating;
    b) at least partial coating of the component (11) on its component surface with an at least double-layer or an at least double-ply wear-resistant coating (14; 17), wherein the wear-resistant coating (14; 17) comprises at least one relatively soft, metallic and also porous layer (15) and at least one relatively hard, ceramic layer (16);
    c) surface-consolidation of the at least partially coated component on its coated component surface by shot-peening in such a way that the compressive-stress distribution of the base material and of the wear-resistant coating (14, 17) is optimal over the depth of the coated component and smoothing is attained on the surface of the coated component.
  2. Method according to claim 1,
    characterised 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).
  3. Method according to claim 1 or 2,
    characterised in that
    a gas-turbine component is provided and at least partially coated as the component (10).
  4. Method according to claim 3,
    characterised in that
    a gas-turbine vane is provided that is coated on its vane-blade surface.
EP05799632A 2004-10-16 2005-10-07 Method for producing a component covered with a wear-resistant coating Ceased EP1805344B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
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

Publications (2)

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

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EP05799632A Ceased EP1805344B1 (en) 2004-10-16 2005-10-07 Method for producing a component covered with a wear-resistant coating

Country Status (5)

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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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EP2570674A1 (en) * 2011-09-15 2013-03-20 Sandvik Intellectual Property AB Erosion resistant impeller vane made of metallic laminate
EP2767616A1 (en) * 2013-02-15 2014-08-20 Alstom Technology Ltd Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component
US10578014B2 (en) * 2015-11-20 2020-03-03 Tenneco Inc. Combustion engine components with dynamic thermal insulation coating and method of making and using such a coating
US11002701B2 (en) * 2018-11-07 2021-05-11 Cameron International Corporation Electrically smart multi-layered coating for condition-base monitoring
FR3102694B1 (en) * 2019-10-30 2022-06-03 Safran Aircraft Engines PROCESS FOR COMPACTING AN ANTI-CORROSION COATING

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Also Published As

Publication number Publication date
WO2006042506A1 (en) 2006-04-27
DE102004050474A1 (en) 2006-04-20
US20080124469A1 (en) 2008-05-29
US8920881B2 (en) 2014-12-30
CA2584350A1 (en) 2006-04-27
DE502005011139D1 (en) 2011-04-28
EP1805344A1 (en) 2007-07-11

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