EP1805344A1 - Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure - Google Patents

Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure

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)
English (en)
Other versions
EP1805344B1 (fr
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/fr
Application granted granted Critical
Publication of EP1805344B1 publication Critical patent/EP1805344B1/fr
Anticipated expiration legal-status Critical
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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening

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.

Landscapes

  • 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

Procédé de fabrication d'une pièce pourvue d'un revêtement de protection contre l'usure, en particulier d'un revêtement de protection contre la corrosion ou d'un revêtement de protection contre l'érosion, en particulier d'une pièce pour turbine à gaz. Ledit procédé consiste (a) à préparer une pièce (10) dont la surface (13) doit être couverte d'un revêtement, (b) à appliquer au moins partiellement un revêtement contre l'usure (14) constitué d'au moins deux couches sur la surface de la pièce (11), ledit revêtement contre l'usure (14) comportant au moins une couche relativement molle (15) et au moins une couche relativement dure (16) et (c) à consolider la surface de la pièce au moins partiellement couverte d'un revêtement dans ses parties couvertes d'un revêtement.
EP05799632A 2004-10-16 2005-10-07 Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure Ceased EP1805344B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004050474A DE102004050474A1 (de) 2004-10-16 2004-10-16 Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils
PCT/DE2005/001795 WO2006042506A1 (fr) 2004-10-16 2005-10-07 Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure

Publications (2)

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

Family

ID=35502594

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05799632A Ceased EP1805344B1 (fr) 2004-10-16 2005-10-07 Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure

Country Status (5)

Country Link
US (1) US8920881B2 (fr)
EP (1) EP1805344B1 (fr)
CA (1) CA2584350A1 (fr)
DE (2) DE102004050474A1 (fr)
WO (1) WO2006042506A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005030266A1 (de) * 2005-06-29 2007-01-18 Mtu Aero Engines Gmbh Schaufel einer Turbomaschine mit einer Schaufelspitzenpanzerung
DE102007050141A1 (de) * 2007-10-19 2009-04-23 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung
DE102010048147B4 (de) 2010-10-11 2016-04-21 MTU Aero Engines AG Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems
EP2570674A1 (fr) * 2011-09-15 2013-03-20 Sandvik Intellectual Property AB Aube de rotor résistant à l'érosion consistant en un stratifié métallique
EP2767616A1 (fr) * 2013-02-15 2014-08-20 Alstom Technology Ltd Composant de turbomachine avec revêtement résistant à la corrosion et l'érosion, système et procédé de fabrication d'un tel composant
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 (fr) 2019-10-30 2022-06-03 Safran Aircraft Engines Procede de compactage d’un revetement anti-corrosion

Family Cites Families (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB826057A (en) 1957-03-15 1959-12-23 Glacier Co Ltd Bearings
US4414249A (en) * 1980-01-07 1983-11-08 United Technologies Corporation Method for producing metallic articles having durable ceramic thermal barrier coatings
US4428213A (en) * 1981-09-10 1984-01-31 United Technologies Corporation Duplex peening and smoothing process
US4481237A (en) * 1981-12-14 1984-11-06 United Technologies Corporation Method of applying ceramic coatings on a metallic substrate
US4528079A (en) * 1983-05-25 1985-07-09 Miracle Metals, Inc. Method of mitigating boundary friction and wear in metal surfaces in sliding contacts
US4562090A (en) * 1983-11-30 1985-12-31 Gray Tool Company Method for improving the density, strength and bonding of coatings
EP0186266A1 (fr) 1984-11-19 1986-07-02 Avco Corporation Système de revêtement résistant à l'érosion
EP0188057A1 (fr) 1984-11-19 1986-07-23 Avco Corporation Revêtements résistant à l'érosion
US4761346A (en) * 1984-11-19 1988-08-02 Avco Corporation Erosion-resistant coating system
USRE34173E (en) * 1988-10-11 1993-02-02 Midwest Research Technologies, Inc. Multi-layer wear resistant coatings
EP0366298B1 (fr) 1988-10-12 1996-03-13 Detector Electronics Corporation Reconnaissance et traitement de formes d'ondes
DE3907625C1 (fr) 1989-03-09 1990-02-15 Mtu Muenchen Gmbh
US5232789A (en) * 1989-03-09 1993-08-03 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Structural component with a protective coating having a nickel or cobalt basis and method for making such a coating
US5059095A (en) * 1989-10-30 1991-10-22 The Perkin-Elmer Corporation Turbine rotor blade tip coated with alumina-zirconia ceramic
DE69122461T2 (de) * 1990-08-11 1997-02-27 Johnson Matthey Plc, London Beschichteter Gegenstand
US5169674A (en) * 1990-10-23 1992-12-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method of applying a thermal barrier coating system to a substrate
DE4041103A1 (de) 1990-12-21 1992-07-02 Mtu Muenchen Gmbh Verfahren zur oberflaechenbehandlung von bauteilen
GB9112499D0 (en) * 1991-06-11 1991-07-31 Sprayforming Dev Ltd Improved corrosion protection of marine structures
US5547767A (en) * 1991-10-14 1996-08-20 Commissariat A L'energie Atomique Multilayer material, anti-erosion and anti-abrasion coating incorporating said multilayer material and process for producing said multilayer material
WO1993008315A1 (fr) 1991-10-18 1993-04-29 Harold Leroy Harford Fabrication d'un revetement anti-usure
GB9203394D0 (en) * 1992-02-18 1992-04-01 Johnson Matthey Plc Coated article
DE4229600C1 (de) 1992-07-07 1993-11-25 Mtu Muenchen Gmbh Schutzschicht für Titanbauteile und Verfahren zu ihrer Herstellung
DE69514994T3 (de) * 1994-03-16 2008-07-03 Taiho Kogyo Co., Ltd., Toyota Taumelscheibe für taumelscheibenverdichter
GB9405934D0 (en) * 1994-03-25 1994-05-11 Johnson Matthey Plc Coated article
DE59406283D1 (de) 1994-08-17 1998-07-23 Asea Brown Boveri Verfahren zur Herstellung einer Turbinenschaufel aus einer (alpha-Beta)-Titan-Basislegierung
WO1996012049A1 (fr) 1994-10-14 1996-04-25 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
DE19652872C2 (de) * 1996-12-18 2000-07-06 Fraunhofer Ges Forschung Verfahren zur Steigerung der Randschichtfestigkeit an Oberflächen von aus sprödharten Werkstoffen gefertigten Werkstücken
DE19743579C2 (de) * 1997-10-02 2001-08-16 Mtu Aero Engines Gmbh Wärmedämmschicht und Verfahren zu ihrer Herstellung
US6190124B1 (en) 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
US20020079602A1 (en) * 1997-12-18 2002-06-27 Hans-Wulf Pfeiffer Method of increasing the boundary layer strength on surfaces of workpieces made of brittle hard materials
JPH11343565A (ja) 1998-05-29 1999-12-14 Daido Steel Co Ltd 表面に硬化層を有するＴｉ基合金材料およびその製造方法
WO2001032799A1 (fr) 1999-11-04 2001-05-10 Nanogram Corporation Dispersions de particules
CA2327031C (fr) * 1999-11-29 2007-07-03 Vladimir Gorokhovsky Revetements composites deposes par evaporation sous vide et procede afferent
FR2816636B1 (fr) 2000-11-16 2003-07-18 Snecma Moteurs Grenaillage des sommets des aubes refroidies
US20020076573A1 (en) * 2000-12-19 2002-06-20 Neal James Wesley Vapor deposition repair of superalloy articles
US6465040B2 (en) * 2001-02-06 2002-10-15 General Electric Company Method for refurbishing a coating including a thermally grown oxide
US6780458B2 (en) * 2001-08-01 2004-08-24 Siemens Westinghouse Power Corporation Wear and erosion resistant alloys applied by cold spray technique
JP3876168B2 (ja) 2002-02-14 2007-01-31 三菱重工業株式会社 アブレイダブルコーティング及びその作製方法
JP3996809B2 (ja) 2002-07-11 2007-10-24 住友電工ハードメタル株式会社 被覆切削工具
US6858333B2 (en) * 2002-10-09 2005-02-22 Kennametal Inc. Tool with wear resistant low friction coating and method of making the same
US7226668B2 (en) * 2002-12-12 2007-06-05 General Electric Company Thermal barrier coating containing reactive protective materials and method for preparing same
GB2397307A (en) * 2003-01-20 2004-07-21 Rolls Royce Plc Abradable Coatings
DE102004001392A1 (de) * 2004-01-09 2005-08-04 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same
US20060040129A1 (en) * 2004-08-20 2006-02-23 General Electric Company Article protected by a strong local coating
US7160635B2 (en) * 2004-11-09 2007-01-09 Sheffield Hallam University Protective Ti-Al-Cr-based nitrided coatings

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006042506A1 *

Also Published As

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

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