EP1929060A1 - Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection - Google Patents

Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection

Info

Publication number
EP1929060A1
EP1929060A1 EP06805298A EP06805298A EP1929060A1 EP 1929060 A1 EP1929060 A1 EP 1929060A1 EP 06805298 A EP06805298 A EP 06805298A EP 06805298 A EP06805298 A EP 06805298A EP 1929060 A1 EP1929060 A1 EP 1929060A1
Authority
EP
European Patent Office
Prior art keywords
protective layer
component
protective coating
structuring
resistant
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP06805298A
Other languages
German (de)
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
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 EP1929060A1 publication Critical patent/EP1929060A1/fr
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
    • 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 and corrosion-resistant protective layer for a component, in particular for components of a gas turbine, by means of thermal spraying.
  • the invention further relates to a protective layer, namely a wear-resistant, temperature and corrosion-resistant protective layer for a component, in particular for components of a gas turbine, with an abrasive surface.
  • the invention relates to a component, in particular a component of a gas turbine, with a protective layer.
  • Such corrosion and oxidation protection layers are known and are used in particular in parts of turbines or aircraft engines as well as combustion chambers.
  • hot corrosion protective layers so-called MCrAlY support layers are used, as described for example in US-A-4080486, EP-Bl-0486489 and US-A-4585481.
  • these MCrAlY support layers can be used as a primer or as an adhesive layer between the metallic substrate to which the protective layer is applied and a ceramic cover layer.
  • the application of the protective layer is carried out in particular by thermal spraying method, such. As flame spraying, high-speed flame spraying, detonation spraying, plasma spraying, arc spraying, laser spraying or Schmelzbadspritzen.
  • DE-A1-10260462 and DE-A1-10351168 disclose further processes for producing a wear-resistant layer by means of thermal spraying.
  • OS-A-5935407 also describes the application of an MCrAlY base layer to a workpiece by means of a plasma spraying method.
  • a wear-resistant, temperature- and corrosion-resistant protective layer is applied by thermal spraying on a component, in particular on a component of a gas turbine, wherein during the application of the consisting of ceramic and / or a hard-metal combination protective layer on the Component for generating an abrasive surface of a structuring of the remote from the component surface of the protective layer is carried out.
  • the wear-resistant layer in one operation d. H. single-layer
  • the structuring of the component-remote surface of the protective layer takes place. Since no further operations are necessary for the production of the protective layer, the process can be carried out inexpensively, simply and quickly.
  • the structuring is produced by a Abdeckmasktechnik during the application of the protective layer. But it is also possible that the structuring is produced by a segmented application of the protective layer or individual protective layer elements. Furthermore, it is possible that the structuring is produced by a different thickness order of the protective layer on the component.
  • the Type of structuring can be predetermined and adapted to the corresponding requirements for the component or the requirements of the protective layer.
  • a protective layer according to the invention namely a wear-resistant, ter ⁇ pe- ratur- corrosion resistant protective layer for a component, in particular for components of a gas turbine has an abrasive surface, wherein the protective layer is formed ein Anlagenig and applied by thermal spraying on the corresponding component, wherein during the application the protective layer consisting of ceramic and / or a hard metal / metal combination is structured on the component for producing the abrasive surface, structuring the surface of the protective layer facing away from the component.
  • a protective layer is simple and inexpensive to produce. In particular, repairs to damaged protective layers can also be carried out very quickly.
  • this has a thickness of 10 .mu.m-6 mm, in particular 30 .mu.m-300 .mu.m.
  • the hard material or substances consist of boron nitride, titanium carbide, tungsten carbide, chromium carbide or zirconium oxide particles or a mixture thereof.
  • the hard materials may have a particle size of 0.1 microns - 200 microns.
  • the hard materials are arranged in a matrix of metal or a metal alloy.
  • this may be formed as a continuous or segmented layer. It is also possible that the protective layer has different thicknesses, is cut-shaped or has a plurality of projections on the surface facing away from the component. These projections may be formed, for example, tooth, cutting or tip-shaped.
  • the mentioned structuring possibilities of the protective layer according to the invention serve to form the abovementioned abrasive surface.
  • An inventive component in particular a component of a gas turbine, in particular a rotor blade, has at least in a partial area, in particular the blade tip, a protective layer according to the features described above.
  • the wear-resistant, high-temperature, oxidation-resistant and corrosion-resistant protective layer according to the invention is used in particular in the coating and / or repair of turbine and engine parts, in particular of gas turbines in aircraft engines.
  • Figure 1 is a schematic representation of a first embodiment of a component according to the invention with a protective layer according to the invention
  • Figure 2 is a schematic representation of a second embodiment of a component according to the invention with a protective layer according to the invention.
  • FIGS. 3a to 3c schematically show side views of further exemplary embodiments of components according to the invention, each with a protective layer according to the invention.
  • FIG. 1 shows a schematic representation of a first exemplary embodiment of a component 10 with a protective layer 12.
  • the illustrated component 10 is a turbine blade 20 with a blade root 22 and a blade tip 18 opposite the blade root 22. It can be seen that at the blade tip 18, the protective layer 12 is formed.
  • the protective layer 12 is intended to be wear-resistant, temperature-resistant and corrosion-resistant and is usually referred to as blade tip armor.
  • the protective layer 12 is structured on the surface facing away from the component 10. The structuring takes place during the application of the protective layer 12 to the component 10.
  • the protective layer 12 has a plurality of protrusions 16 on the surface 14 facing away from the component 10.
  • FIG. 2 shows a schematic representation of a second embodiment of a component 10 with a protective layer 12.
  • the component 10 is likewise a turbine. Shovel 20.
  • the protective layer 12 is formed as a continuous layer. Abrasive properties of the protective layer 12 are achieved in this embodiment by different thicknesses of the protective layer 12 or by a blade-shaped design of the protective layer 12 (see Figure 3c).
  • FIGS. 3 a to 3 c show schematically illustrated side views of further exemplary embodiments of components 10, each with a protective layer 12.
  • the components 10 are again turbine blades 20. It can be seen that the blade tips 18 are each covered at least partially with the protective layer 12.
  • the protective layer 12 shown in FIG. 3a is segmented (see also FIG. 1).
  • the protective layers 12 shown in FIGS. 3b and 3c have cross-sections tapering outwards. This results in cutting edges 24, which leads to the formation of the abrasive property of the protective layer 12 on the component 10 opposite surface 14.

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)

Abstract

L'invention concerne un procédé pour produire par thermo-injection une couche de protection résistant à l'usure, à la chaleur et à la corrosion, cette couche de protection étant destinée à un composant, en particulier à des composants d'une turbine à gaz. Ce procédé se caractérise en ce que, lorsque la couche de protection constituée de céramique et/ou d'une combinaison matériau dur/métal est appliquée sur le composant pour produire une surface abrasive, la surface de la couche de protection opposée au composant fait l'objet d'une texturation. L'invention concerne en outre une couche de protection, notamment une couche de protection résistant à l'usure, à la chaleur et à la corrosion, cette couche de protection étant destinée à un composant, en particulier à des composants d'une turbine à gaz, et présentant une surface abrasive. Cette couche de protection est conçue en une seule couche et elle est produite par le procédé selon l'invention. L'invention concerne par ailleurs un composant, en particulier un composant d'une turbine à gaz, pourvu d'une couche de protection.
EP06805298A 2005-09-21 2006-09-16 Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection Ceased EP1929060A1 (fr)

Applications Claiming Priority (2)

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
PCT/DE2006/001636 WO2007033650A1 (fr) 2005-09-21 2006-09-16 Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection

Publications (1)

Publication Number Publication Date
EP1929060A1 true EP1929060A1 (fr) 2008-06-11

Family

ID=37450740

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06805298A Ceased EP1929060A1 (fr) 2005-09-21 2006-09-16 Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection

Country Status (4)

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

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007026271A1 (de) * 2007-06-05 2008-12-11 Mtu Aero Engines Gmbh Abdeckklebebänder und Verfahren zum Beschichten und/oder Ausbessern von Bauteilen
EP2177643A1 (fr) * 2008-10-07 2010-04-21 Siemens Aktiengesellschaft Procédé de réparation d'un superalliage à l'aide de la même poudre de superalliage et de céramique
DE102008056652A1 (de) * 2008-11-10 2010-05-12 Mtu Aero Engines Gmbh Maske für das kinetische Kaltgaskompaktieren
IT1396884B1 (it) * 2009-12-15 2012-12-20 Nuovo Pignone Spa Inserti in carburo di tungsteno e metodo
CN102418065B (zh) * 2011-12-12 2013-07-03 中国矿业大学 复合金属碳化物耐磨涂层及其制备工艺
US9827735B2 (en) 2012-03-09 2017-11-28 United Technologies Corporation Erosion resistant and hydrophobic article
EP3216980A1 (fr) 2016-03-08 2017-09-13 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube et/ou d'un carter d'une turbomachine
EP3222812A1 (fr) 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube directrice, aube directrice, procede de fabrication ou de reparation d'un boitier d'une turbomachine et boitier
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

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GB2117269B (en) * 1982-03-11 1985-08-29 Rolls Royce Thermal barrier coating
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DE4432998C1 (de) * 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
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Also Published As

Publication number Publication date
US20090169372A1 (en) 2009-07-02
WO2007033650A1 (fr) 2007-03-29
DE102005044991A1 (de) 2007-03-22

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