US20090169372A1 - Method of producing a protective coating, protective coating, and component with a protective coating - Google Patents

Method of producing a protective coating, protective coating, and component with a protective coating Download PDF

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Publication number
US20090169372A1
US20090169372A1 US12/067,274 US6727406A US2009169372A1 US 20090169372 A1 US20090169372 A1 US 20090169372A1 US 6727406 A US6727406 A US 6727406A US 2009169372 A1 US2009169372 A1 US 2009169372A1
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US
United States
Prior art keywords
protective coating
resistant
component
recited
carbide particles
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.)
Abandoned
Application number
US12/067,274
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English (en)
Inventor
Christian Friedrich
Klaus Breitschwerdt
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
Individual
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Filing date
Publication date
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Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BREITSCHWERDT, KLAUS, FRIEDRICH, CHRISTIAN
Publication of US20090169372A1 publication Critical patent/US20090169372A1/en
Abandoned legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • 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
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]

Definitions

  • the present invention relates to a method for producing a wear-resistant, temperature-resistant, and corrosion-resistant protective coating or layer for a component, in particular for components of a gas turbine, using thermal spraying.
  • the present invention relates to a protective coating, namely a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, having an abrasive surface.
  • the present invention relates to a component, in particular a component of a gas turbine, having a protective coating.
  • Such coatings for protecting against corrosion and against oxidation are known, and are used in particular in parts of turbines or aircraft engines, and also combustion chambers.
  • What are known as MCrAlY coatings are used as heat corrosion protective coatings, as described for example in U.S. Pat. No. 4,080,486, EP-B1-0486489, and U.S. Pat. No. 4,585,481.
  • these MCrAlY coatings may be used as bonding agents or as an adhesive layer between the metallic substrate onto which the protective coating is applied and a ceramic covering layer.
  • the application of the protective coating takes place in particular using thermal spraying methods, such as e.g.
  • a disadvantage of these known methods, and of the protective coatings that result from them, is that in order to produce known protective coatings having abrasive surfaces or properties, it is always necessary to use a plurality of method steps to apply the actual protective coating.
  • the protective coatings resulting therefrom always have a multilayer construction (see also EP-A1-0443877). Because of the high time expense involved in a corresponding coating of a workpiece and the material outlay connected therewith, this results in relatively high manufacturing costs. In addition, required repairs of damaged protective coatings are also very time-intensive and expensive to perform.
  • the object of the present invention is to provide a method of the type named above that on the one hand can be carried out economically and on the other hand permits a simple and rapid coating of corresponding components.
  • the object of the present invention is to provide a protective coating of the type named above that can be manufactured simply and with a low material outlay and that has abrasive properties.
  • the object of the present invention is also to provide a component of the type named above that is at least partly coated with a protective coating that is simple and that can be applied economically.
  • a wear-resistant, temperature-resistant, and corrosion-resistant protective coating is applied to a component, in particular a component of a gas turbine, by thermal spraying, the protective coating, which consists of ceramic and/or of a hard material-metal combination, being applied onto the component in order to produce an abrasive surface of a structuring of the surface of the protective coating facing away from the component.
  • the wear-resistant layer it is advantageously possible for the wear-resistant layer to be applied in a single working step, i.e. in one layer, using thermal spraying.
  • the structuring of the surface of the protective coating facing away from the component takes place simultaneously. Because no additional work steps are required to produce the protective coating, the method can be carried out economically, simply, and rapidly.
  • the structuring is produced by a covering masking during the application of the protective coating.
  • the structuring it is also possible for the structuring to be produced by a segmented application of the protective coating, or of individual protective coating elements.
  • the structuring it is possible for the structuring to be produced by an application of the protective coating onto the component having different thicknesses.
  • the type of structuring can be predetermined and adapted to the corresponding requirements of the component or of the protective coating.
  • a protective coating according to the present invention namely a wear-resistant, temperature-resistant, corrosion-resistant protective coating for a component, in particular for components of a gas turbine, has an abrasive surface, the protective coating having a one-layer construction and being applied onto the corresponding component by thermal spraying, a structuring of the surface of the protective coating facing away from the component taking place during the application of the protective coating, which is made of ceramic and/or a hard material-metal combination, in order to produce the abrasive surface.
  • a protective coating can be produced simply and economically. In particular, repairs to damaged protective coatings can be carried out very quickly.
  • this layer has a thickness of 10 ⁇ m-6 mm, in particular 10 ⁇ m-300 ⁇ m.
  • the hard material or materials are made up of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, or zirconium oxide particles, or a mixture thereof.
  • the hard materials can have a particle size of 0.1 ⁇ m-200 ⁇ m.
  • the hard materials are arranged in a matrix made of metal or a metal alloy.
  • this layer can be fashioned as a continuous or as a segmented layer.
  • the protective coating it is possible for the protective coating to have different thicknesses, to be formed with a blade-like shape, or to have a multiplicity of projections on the surface of the layer that faces away from the component. These projections can be for example tooth-like, blade-like, or pointed.
  • the named structuring possibilities of the protective coating according to the present invention are used to form the named abrasive surface.
  • a component according to the present invention in particular a component of a gas turbine, in particular a blade, has in at least one partial area, in particular the blade tip, a protective coating having the features described above.
  • the wear-resistant, high-temperature-resistant, oxidation-resistant, and corrosion-resistant protective coating according to the present invention is used in particular for the coating and/or repair of turbine parts and engine parts, in particular of gas turbines in aircraft engines.
  • FIG. 1 shows a schematic representation of a first exemplary embodiment of a component according to the present invention having a protective coating according to the present invention
  • FIG. 2 shows a schematic representation of a second exemplary embodiment of a component according to the present invention having a protective coating according to the present invention
  • FIGS. 3 a to 3 c show schematically represented side views of further exemplary embodiments of components according to the present invention, each having a protective coating according to the present invention.
  • FIG. 1 shows a schematic representation of a first exemplary embodiment of a component 10 having a protective coating 12 .
  • the depicted component 10 is a turbine blade 20 having a blade foot 22 and a blade tip 18 situated opposite blade foot 22 .
  • protective coating 12 is fashioned on blade tip 18 .
  • protective coating 12 is intended to be wear-resistant, temperature-resistant, and corrosion-resistant, and is standardly called a blade tip armor.
  • protective coating 12 is fashioned so as to be structured on the surface of the layer that faces away from component 10 . The structuring takes place during the application of protective coating 12 onto component 10 .
  • protective coating 12 has a multiplicity of projections 16 on surface 14 that faces away from component 10 .
  • FIG. 2 shows a schematic representation of a second exemplary embodiment of a component 10 having a protective coating 12 .
  • component 10 is also a turbine blade 20 .
  • protective coating 12 is fashioned as a continuous layer. Abrasive properties of protective coating 12 are achieved in this exemplary embodiment through different thicknesses of protective coating 12 , or also through a blade-like design of protective coating 12 (cf. FIG. 3 c ).
  • FIGS. 3 a to 3 c show schematic side views of additional exemplary embodiments of components 10 , each having a protective coating 12 .
  • These components 10 are, again, turbine blades 20 . It can be seen that each of the blade tips 18 is covered at least partly with protective coating 12 .
  • Protective coating 12 shown in FIG. 3 a has a segmented construction (cf. also FIG. 1 ).
  • the protective coatings 12 shown in FIGS. 3 b and 3 c have cross-sections that taper outwardly. This results in cutting edges 24 that create the abrasive property of protective coating 12 on surface 14 situated opposite component 10 .

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/067,274 2005-09-21 2006-09-16 Method of producing a protective coating, protective coating, and component with a protective coating Abandoned US20090169372A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102005044991A DE102005044991A1 (de) 2005-09-21 2005-09-21 Verfahren zur Herstellung einer Schutzschicht, Schutzschicht und Bauteil mit einer Schutzschicht
DE102005044991.3 2005-09-21
PCT/DE2006/001636 WO2007033650A1 (de) 2005-09-21 2006-09-16 Verfahren zur herstellung einer schutzschicht, schutzschicht und bauteil mit einer schutzschicht

Publications (1)

Publication Number Publication Date
US20090169372A1 true US20090169372A1 (en) 2009-07-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US12/067,274 Abandoned US20090169372A1 (en) 2005-09-21 2006-09-16 Method of producing a protective coating, protective coating, and component with a protective coating

Country Status (4)

Country Link
US (1) US20090169372A1 (de)
EP (1) EP1929060A1 (de)
DE (1) DE102005044991A1 (de)
WO (1) WO2007033650A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100173092A1 (en) * 2007-06-05 2010-07-08 Mtu Aero Engines, Gmbh Adhesive masking tapes and method for coating and/or repairing components
CN102418065A (zh) * 2011-12-12 2012-04-18 中国矿业大学 复合金属碳化物耐磨涂层及其制备工艺
US20130199193A1 (en) * 2009-12-15 2013-08-08 Massimo Giannozzi Tungsten carbide inserts and method
WO2013133997A1 (en) * 2012-03-09 2013-09-12 United Technologies Corporation Erosion resistant and hydrophobic article

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2177643A1 (de) * 2008-10-07 2010-04-21 Siemens Aktiengesellschaft Verfahren zum Reparieren einer Superlegierung mit dem gleichen Superlegierungspulver und Keramik
DE102008056652A1 (de) 2008-11-10 2010-05-12 Mtu Aero Engines Gmbh Maske für das kinetische Kaltgaskompaktieren
EP3216980A1 (de) 2016-03-08 2017-09-13 Siemens Aktiengesellschaft Verfahren zur herstellung oder zur reparatur einer laufschaufel und/oder eines gehäuses einer strömungsmaschine
EP3222812A1 (de) 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Verfahren zur herstellung oder reparatur einer lauf-schaufel, laufschaufel, verfahren zur herstellung oder reparatur eines gehäuses einer strömungsmaschine sowie derartiges gehäuse
CN117328013B (zh) * 2023-11-30 2024-01-26 西安致远航空科技有限公司 一种航空拉刀表面涂层及其制备工艺

Citations (17)

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Publication number Priority date Publication date Assignee Title
US3199836A (en) * 1964-05-04 1965-08-10 Gen Electric Axial flow turbo-machine blade with abrasive tip
US4232995A (en) * 1978-11-27 1980-11-11 General Electric Company Gas seal for turbine blade tip
US4610698A (en) * 1984-06-25 1986-09-09 United Technologies Corporation Abrasive surface coating process for superalloys
US5141821A (en) * 1989-06-06 1992-08-25 Hermann C. Starck Berlin Gmbh & Co Kg High temperature mcral(y) composite material containing carbide particle inclusions
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
US5756217A (en) * 1994-09-16 1998-05-26 Mtu Motoren-Und Turbinen Union Munchen Gmbh Strip coatings for metal components of drive units and their process of manufacture
US5952110A (en) * 1996-12-24 1999-09-14 General Electric Company Abrasive ceramic matrix turbine blade tip and method for forming
US5997248A (en) * 1998-12-03 1999-12-07 Sulzer Metco (Us) Inc. Silicon carbide composition for turbine blade tips
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
US6548161B1 (en) * 1998-05-28 2003-04-15 Mitsubishi Heavy Industries, Ltd. High temperature equipment
US20030185965A1 (en) * 2002-03-27 2003-10-02 Applied Materials, Inc. Evaluation of chamber components having textured coatings
US6666646B1 (en) * 1999-07-30 2003-12-23 Chromalloy Holland B.V. Drag reduction for gas turbine engine components
US20040086689A1 (en) * 2002-10-31 2004-05-06 Tosoh Corporation Island projection-modified part, method for producing the same, and apparatus comprising the same
US20040115351A1 (en) * 2002-12-17 2004-06-17 Yuk-Chiu Lau High temperature abradable coatings
US20040258842A1 (en) * 2003-06-19 2004-12-23 Noriaki Hamaya Coated member and method of manufacture
US20050014010A1 (en) * 2003-04-22 2005-01-20 Dumm Timothy Francis Method to provide wear-resistant coating and related coated articles
US7166372B2 (en) * 2002-08-05 2007-01-23 United Technologies Corporation Thermal barrier coating utilizing a dispersion strengthened metallic bond coat

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GB2117269B (en) * 1982-03-11 1985-08-29 Rolls Royce Thermal barrier coating
DE19840966A1 (de) * 1998-09-08 2000-03-09 Impreglon International L L C Oberflächenbeschichtung für ein Substrat und Verfahren zur Ausbildung einer Oberflächenbeschichtung
DE19934418A1 (de) * 1999-07-22 2001-01-25 Abb Alstom Power Ch Ag Verfahren zum Beschichten einer lokal unterschiedlich beanspruchten Komponente

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3199836A (en) * 1964-05-04 1965-08-10 Gen Electric Axial flow turbo-machine blade with abrasive tip
US4232995A (en) * 1978-11-27 1980-11-11 General Electric Company Gas seal for turbine blade tip
US4610698A (en) * 1984-06-25 1986-09-09 United Technologies Corporation Abrasive surface coating process for superalloys
US5141821A (en) * 1989-06-06 1992-08-25 Hermann C. Starck Berlin Gmbh & Co Kg High temperature mcral(y) composite material containing carbide particle inclusions
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
US5756217A (en) * 1994-09-16 1998-05-26 Mtu Motoren-Und Turbinen Union Munchen Gmbh Strip coatings for metal components of drive units and their process of manufacture
US5952110A (en) * 1996-12-24 1999-09-14 General Electric Company Abrasive ceramic matrix turbine blade tip and method for forming
US6548161B1 (en) * 1998-05-28 2003-04-15 Mitsubishi Heavy Industries, Ltd. High temperature equipment
US5997248A (en) * 1998-12-03 1999-12-07 Sulzer Metco (Us) Inc. Silicon carbide composition for turbine blade tips
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
US6666646B1 (en) * 1999-07-30 2003-12-23 Chromalloy Holland B.V. Drag reduction for gas turbine engine components
US20030185965A1 (en) * 2002-03-27 2003-10-02 Applied Materials, Inc. Evaluation of chamber components having textured coatings
US7166372B2 (en) * 2002-08-05 2007-01-23 United Technologies Corporation Thermal barrier coating utilizing a dispersion strengthened metallic bond coat
US20040086689A1 (en) * 2002-10-31 2004-05-06 Tosoh Corporation Island projection-modified part, method for producing the same, and apparatus comprising the same
US20040115351A1 (en) * 2002-12-17 2004-06-17 Yuk-Chiu Lau High temperature abradable coatings
US20050014010A1 (en) * 2003-04-22 2005-01-20 Dumm Timothy Francis Method to provide wear-resistant coating and related coated articles
US20040258842A1 (en) * 2003-06-19 2004-12-23 Noriaki Hamaya Coated member and method of manufacture

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100173092A1 (en) * 2007-06-05 2010-07-08 Mtu Aero Engines, Gmbh Adhesive masking tapes and method for coating and/or repairing components
US20130199193A1 (en) * 2009-12-15 2013-08-08 Massimo Giannozzi Tungsten carbide inserts and method
CN102418065A (zh) * 2011-12-12 2012-04-18 中国矿业大学 复合金属碳化物耐磨涂层及其制备工艺
WO2013133997A1 (en) * 2012-03-09 2013-09-12 United Technologies Corporation Erosion resistant and hydrophobic article
US9827735B2 (en) 2012-03-09 2017-11-28 United Technologies Corporation Erosion resistant and hydrophobic article
US10814580B2 (en) 2012-03-09 2020-10-27 Raytheon Technologies Corporation Erosion resistant and hydrophobic article

Also Published As

Publication number Publication date
WO2007033650A1 (de) 2007-03-29
EP1929060A1 (de) 2008-06-11
DE102005044991A1 (de) 2007-03-22

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Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FRIEDRICH, CHRISTIAN;BREITSCHWERDT, KLAUS;REEL/FRAME:021896/0279;SIGNING DATES FROM 20081105 TO 20081121

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION