EP1492900A1 - Composant pourvu d'une couche de masquage - Google Patents

Composant pourvu d'une couche de masquage

Info

Publication number
EP1492900A1
EP1492900A1 EP03717250A EP03717250A EP1492900A1 EP 1492900 A1 EP1492900 A1 EP 1492900A1 EP 03717250 A EP03717250 A EP 03717250A EP 03717250 A EP03717250 A EP 03717250A EP 1492900 A1 EP1492900 A1 EP 1492900A1
Authority
EP
European Patent Office
Prior art keywords
layer
component
masking layer
component according
ceramic
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.)
Withdrawn
Application number
EP03717250A
Other languages
German (de)
English (en)
Inventor
Oliver Dernovsek
Ralph Reiche
Nigel-Philip Cox
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP03717250A priority Critical patent/EP1492900A1/fr
Publication of EP1492900A1 publication Critical patent/EP1492900A1/fr
Withdrawn legal-status Critical Current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
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/04—Coating on selected surface areas, e.g. using masks
    • C23C16/042—Coating on selected surface areas, e.g. using masks using masks
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks
    • 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
    • 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
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/04—Treatment of selected surface areas, e.g. using masks
    • 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
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31536—Including interfacial reaction product of adjacent layers
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31652—Of asbestos
    • Y10T428/31663—As siloxane, silicone or silane

Definitions

  • the object of the invention is further achieved by a turbine blade according to claim 3.
  • the masking layer reacts with the material of the material to be applied, making it easy to remove.
  • Figure 3 shows a masking layer of an inventive
  • FIG. 4 shows a further masking layer of a turbine blade according to the invention
  • FIGS. 7 and 8 show how the masking layer can be easily removed again after a reaction.
  • FIG. 1 shows a perspective view of a turbine blade 1, in particular a rotor blade for a gas turbine, which extends along a longitudinal axis 4.
  • the turbine blade 1 has, in succession along the longitudinal axis 4, a fastening region 7, an adjacent blade platform 10 and an airfoil region 13.
  • the fastening area 7 is designed as a blade root 16, which serves to fasten the turbine blade 1 to a shaft, not shown in more detail, of a turbomachine, also not shown.
  • the blade root 16 is designed, for example, as a hammer head. Other configurations, for example as a fir tree or dovetail foot, are possible.
  • solid metallic materials in particular nickel- or cobalt-based superalloys, are used in all areas of the turbine blade.
  • the turbine blade can be manufactured by a casting process, a forging process, a milling process or combinations thereof.
  • the fastening area 7 is made of metal, because it is clamped into a corresponding shape of a pane with a precise fit. Brittle ceramic coatings would flake off and change the geometry in the fastening area.
  • the airfoil area 13 is coated, for example, with a heat insulation layer, it being possible for further layers, such as, for example, adhesion promoter layers (MCrAlY layers), to be arranged between the base material of the turbine blade 1.
  • MrAlY layers adhesion promoter layers
  • a component according to the invention in the form of a turbine blade 1 can be a guide or rotor blade of any turbine, in particular a steam or gas turbine.
  • FIG. 2 shows what happens when the surface of the blade 1 has no masking layer 25 (FIG. 3).
  • the material 22 of an intermediate layer 19 (MCrAlY), which has been applied to a surface of the turbine blade 1 and forms the intermediate layer 19, for example by plasma spraying, by PVD or CVD or immersion in a liquid metal or application of powder in any form, and leads to a reaction of the material 22 with the turbine blade 1 and for good adhesion of the intermediate layer 19 with the base material of the turbine blade 1.
  • FIG. 3 shows a component according to the invention in the form of a turbine blade 1 with a masking layer 25.
  • a first functional layer 28 is first applied to the turbine blade 1.
  • This is, for example, a nanometer-thin polycarbosilane layer that crosslinks in air at 200 ° C. and enables good adhesion to the base material 40 of the turbine blade 1.
  • a gradient layer 31 is applied to the first functional layer 28, the material for the gradient layer 31 being a mixture of polysiloxane and a metal ceramic and / or metal.
  • the gradient layer 31 can, for example, in the form of a
  • slips with layer thicknesses of 10 - 30 ⁇ m thickness are applied and also crosslinked in air at about 200 ° C.
  • a further powder in particular the composition MCrAlY, where M stands for Fe, Co, Ni, is added to this material of the gradient layer 31 because, due to its expansion coefficient, it is used as an intermediate layer (adhesion promoter layer) between the base material 40 and the ceramic thermal insulation layer.
  • a reactive layer 34 is applied to the gradient layer, which consists, for example, of a pure carbon precursor.
  • the crosslinking within the reactive layer 34 takes place at 180 ° C. in air.
  • the crosslinked layers 28, 31, 34 are converted into a ceramic by a thermal treatment at 1000 ° C. in an argon atmosphere, using the so-called pyrolysis process. Due to the change in density of the organometallic precursor such as, for example, the polysiloxane with a density of 1 g / cm 3 in a silicon oxycabid phase (SiOC) with a density of approx.
  • the organometallic precursor such as, for example, the polysiloxane with a density of 1 g / cm 3 in a silicon oxycabid phase (SiOC) with a density of approx.
  • a material 22 is applied to the airfoil area 13 of the turbine blade 1 and to the masking layer 25.
  • the material 22 reacts with the reactive layer 34 to form a reaction layer 43, i.e. to a material that is resistant to high temperatures, but is, for example, soluble in water, i.e. easily removable.
  • the material 22 is, for example, aluminum, which is applied to the turbine blade 1 to form an aluminide layer.
  • an aluminide layer can be applied by plasma spraying or by methods as specified in EP patent 0 525 545 B1 and EP patent 0 861 919 B1.
  • the carbon of the reactive layer 34 reacts with aluminum to form Al 4 C 3 . If the airfoil region 13 is completely coated, the entire airfoil, in particular the fastening region 7, can be introduced into water, as a result of which the water-soluble reaction layer 43 converted with the material 22 dissolves.
  • the underlying layers 28, 31 can easily be removed by dry ice blasting, so that the geometry of the fastening area 7 is not changed by the removal method.
  • Aluminum is used for example in refurbishment, i.e. et al when removing used MCrAlY layers, applied to a turbine blade 1.
  • the masking layer 25 can also be a gradient layer which has a gradual structure, that is, the composition on the substrate 40 is selected so that good adhesion is possible, and on the outer surface the composition is such that it reacts with the material 22 of layers still to be applied.
  • FIG. 4 shows a component according to the invention in the form of a turbine blade 1 with a masking layer 25.
  • a ceramic layer 37, which forms the masking layer 25, is applied directly to the metallic turbine blade 1, for example.
  • This can, for example, be an oxide ceramic that is adapted to the thermal expansion coefficient of the substrate.
  • the dense ceramic layer 37 also forms during a coating process of the turbine blade 1 with different layers, e.g. Adhesion promoter layers or thermal insulation layers, a diff barrier.
  • the masking layer 25 can also only react with the material 22 of layers still to be applied, for example to form a brittle layer 43, for example a ceramic layer 37.
  • the ceramic layer 37 can, for example, also only form after a further heat treatment (pyrolysis).
  • Such brittle layers 43 can be removed by simple processes such as thermal shock processes or sandblasting or dry ice blasting, ie by energy-introducing, but not abrasive, blasting processes. It is particularly advantageous if the masking layer 25 reacts with the material 22 of layers to be applied to form a water-soluble layer 43.
  • Masking layer further layers may be present, i.e. the masking layer 25 can be constructed in multiple layers.
  • the masking layer 25 can be constructed in multiple layers.
  • FIG. 5 shows a turbine blade 1 with a substrate 40, on which a masking layer 25 is applied.
  • the material of the masking layer does not react and diffuse at the higher temperatures of the
  • material 22 hits and reacts with the masking layer 25.
  • the reaction can also take place in a downstream heat treatment if the reaction temperature is higher than the substrate temperature during the coating.
  • the reaction layer 43 (FIG. 6) formed in this way can easily be removed again after the coating process of the turbine blade, because it is, for example, brittle or water-soluble.
  • the material 22 thus also strikes the unmasked areas of the substrate 40 of the turbine blade 1 and forms a desired coating 55 (FIG. 6).
  • FIG. 7 shows a water bath 46 in which a turbine blade with a water-soluble layer 43 is introduced.
  • the water solubility can be easily removed from the layer 43, so that after the turbine blade 1 has been removed from the water bath, an uncoated part and a desired coated part 55 of the turbine blade 1 are present.
  • the reaction layer 43 can also by
  • the brittle reaction layer 43 can be removed by an energy input from an irradiation cannon 49 (ultrasound, dry ice blaster, sand blaster). (Fig. 8)

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)
  • General Chemical & Material Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L'invention concerne un procédé de recouvrement de composant. Les couches de masquage pour composant de l'art antérieur réagissent avec le matériau de base du composant ou bien sont difficiles à enlever. L'invention concerne donc un composant qui est pourvu d'une couche de masquage (25) qui, après avoir été appliquée sur le composant (1), peut être facilement enlevée car il n'y a pas une grande adhérence entre cette couche de masquage (25) et le matériau de base (40) du composant (1), ou bien la pénétration d'un liquide peut facilement enlever cette couche de masquage (25).
EP03717250A 2002-04-10 2003-03-28 Composant pourvu d'une couche de masquage Withdrawn EP1492900A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03717250A EP1492900A1 (fr) 2002-04-10 2003-03-28 Composant pourvu d'une couche de masquage

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP20020008045 EP1352989A1 (fr) 2002-04-10 2002-04-10 Objet avec une couche de masquage
EP02008045 2002-04-10
PCT/EP2003/003283 WO2003085163A1 (fr) 2002-04-10 2003-03-28 Composant pourvu d'une couche de masquage
EP03717250A EP1492900A1 (fr) 2002-04-10 2003-03-28 Composant pourvu d'une couche de masquage

Publications (1)

Publication Number Publication Date
EP1492900A1 true EP1492900A1 (fr) 2005-01-05

Family

ID=28051773

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20020008045 Withdrawn EP1352989A1 (fr) 2002-04-10 2002-04-10 Objet avec une couche de masquage
EP03717250A Withdrawn EP1492900A1 (fr) 2002-04-10 2003-03-28 Composant pourvu d'une couche de masquage

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP20020008045 Withdrawn EP1352989A1 (fr) 2002-04-10 2002-04-10 Objet avec une couche de masquage

Country Status (4)

Country Link
US (2) US7163747B2 (fr)
EP (2) EP1352989A1 (fr)
JP (1) JP2005526907A (fr)
WO (1) WO2003085163A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1510592B1 (fr) * 2003-08-28 2012-12-26 Siemens Aktiengesellschaft Procédé pour revêtir un objet et objet
EP1783243A1 (fr) * 2005-11-04 2007-05-09 Siemens Aktiengesellschaft Composition sèche, son utilisation, système de couches et procédé de revêtement
TW200718805A (en) * 2005-11-07 2007-05-16 United Technologies Corp Coating methods and apparatus
US20100068556A1 (en) * 2005-12-09 2010-03-18 General Electric Company Diffusion barrier layer and methods of forming
DE102010009616A1 (de) * 2010-02-27 2011-09-01 Mtu Aero Engines Gmbh Verfahren zur Herstellung oder Reparatur eines Bauteils und Abdeckbeschichtung
US8347636B2 (en) 2010-09-24 2013-01-08 General Electric Company Turbomachine including a ceramic matrix composite (CMC) bridge
DE102015208781A1 (de) * 2015-05-12 2016-11-17 MTU Aero Engines AG Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht sowie Verfahren zur Herstellung derselben
JP7224096B2 (ja) * 2017-07-13 2023-02-17 東京エレクトロン株式会社 プラズマ処理装置用部品の溶射方法及びプラズマ処理装置用部品
JP7369499B2 (ja) * 2021-04-02 2023-10-26 株式会社ディ・ビー・シー・システム研究所 耐熱合金部材およびその製造方法ならびに高温装置およびその製造方法
US11753713B2 (en) 2021-07-20 2023-09-12 General Electric Company Methods for coating a component

Family Cites Families (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3647497A (en) * 1968-11-29 1972-03-07 Gen Electric Masking method in metallic diffusion coating
US3904789A (en) * 1974-04-24 1975-09-09 Chromalloy American Corp Masking method for use in aluminizing selected portions of metal substrates
US4181758A (en) * 1976-07-30 1980-01-01 Gulf & Western Industries, Inc. Method for preventing the deposition of a coating on a substrate
US4128522A (en) * 1976-07-30 1978-12-05 Gulf & Western Industries, Inc. Method and maskant composition for preventing the deposition of a coating on a substrate
US4845139A (en) * 1979-09-07 1989-07-04 Alloy Surfaces Company, Inc. Masked metal diffusion
JPS6045704B2 (ja) * 1981-12-01 1985-10-11 工業技術院長 表面処理防止方法
US4726104A (en) * 1986-11-20 1988-02-23 United Technologies Corporation Methods for weld repairing hollow, air cooled turbine blades and vanes
GB2210387B (en) * 1987-09-30 1992-03-11 Rolls Royce Plc Chemical vapour deposition
US5262466A (en) * 1988-04-18 1993-11-16 Alloy Surfaces Co. Inc. Aqueous masking solution for metal treatment
GB9116332D0 (en) 1991-07-29 1991-09-11 Diffusion Alloys Ltd Refurbishing of corroded superalloy or heat resistant steel parts and parts so refurbished
US5867762A (en) * 1994-05-26 1999-02-02 Rafferty; Kevin Masking tape
DE4423619A1 (de) * 1994-07-06 1996-01-11 Bosch Gmbh Robert Laterale Halbleiterstruktur zur Bildung einer temperaturkompensierten Spannungsbegrenzung
US5902647A (en) * 1996-12-03 1999-05-11 General Electric Company Method for protecting passage holes in a metal-based substrate from becoming obstructed, and related compositions
US6036995A (en) * 1997-01-31 2000-03-14 Sermatech International, Inc. Method for removal of surface layers of metallic coatings
JPH11181561A (ja) * 1997-12-22 1999-07-06 Toshiba Mach Co Ltd 溶融メッキのマスキング方法
US6110262A (en) * 1998-08-31 2000-08-29 Sermatech International, Inc. Slurry compositions for diffusion coatings
GB2348439A (en) * 1999-03-29 2000-10-04 Chromalloy Uk Limited Mask for diffusion coating
US6253441B1 (en) * 1999-04-16 2001-07-03 General Electric Company Fabrication of articles having a coating deposited through a mask
JP2000311870A (ja) * 1999-04-28 2000-11-07 Mitsubishi Electric Corp 半導体装置の製造方法
US6521294B2 (en) * 1999-08-11 2003-02-18 General Electric Co. Aluminiding of a metallic surface using an aluminum-modified maskant, and aluminum-modified maskant
KR100677965B1 (ko) * 1999-11-01 2007-02-01 동경 엘렉트론 주식회사 기판처리방법 및 기판처리장치
US6605160B2 (en) * 2000-08-21 2003-08-12 Robert Frank Hoskin Repair of coatings and surfaces using reactive metals coating processes
US6617003B1 (en) * 2000-11-06 2003-09-09 General Electric Company Directly cooled thermal barrier coating system
EP1350860A1 (fr) * 2002-04-04 2003-10-08 ALSTOM (Switzerland) Ltd Procédé pour couvrir les orifices de refroidissement d'un composant d'une turbine à gaz
EP1365039A1 (fr) * 2002-05-24 2003-11-26 ALSTOM (Switzerland) Ltd Porcédé pour couvrir les orifices de refroidissement d'un composant d'une turbine à gaz
DE60310168T2 (de) * 2002-08-02 2007-09-13 Alstom Technology Ltd. Verfahren zum Schutz von Teilflächen eines Werkstücks
US6884470B2 (en) * 2002-10-03 2005-04-26 General Electric Company Application method for abradable material
US6884476B2 (en) * 2002-10-28 2005-04-26 General Electric Company Ceramic masking material and application method for protecting turbine airfoil component surfaces during vapor phase aluminiding

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO03085163A1 *

Also Published As

Publication number Publication date
US20050181222A1 (en) 2005-08-18
US20070292719A1 (en) 2007-12-20
JP2005526907A (ja) 2005-09-08
EP1352989A1 (fr) 2003-10-15
WO2003085163A1 (fr) 2003-10-16
US7163747B2 (en) 2007-01-16

Similar Documents

Publication Publication Date Title
EP2398936B1 (fr) Une système de revêtement résistante à l'érosion pour eléments de turbine
DE69707365T2 (de) Isolierendes, wärmedämmendes Beschichtungssystem
EP1708829B1 (fr) Procede pour eliminer une couche
WO2006103127A1 (fr) Matrice et systeme de couches
DE19807636C1 (de) Verfahren zum Herstellen einer korrosions- und oxidationsbeständigen Schlickerschicht
CH704833A1 (de) Komponente für eine Turbomaschine und ein Verfahren zum Herstellen einer derartigen Komponente.
EP1707301B1 (fr) Procédé pour appliquer des mats de fibres sur la surface ou dans une cavité d'un composant
WO2009100706A1 (fr) Procédé et dispositif de revêtement partiel d'éléments
EP1772594A1 (fr) Procédé pour couvrir les orifices d'un composant dans un procédé et composition de céramique contenant de polysiloxane
EP1492900A1 (fr) Composant pourvu d'une couche de masquage
EP3458431B1 (fr) Procédé de fabrication d'un écran thermique céramique à revêtement de réaction
WO2008128848A1 (fr) Revêtements céramiques polymères pour la protection de surfaces contre des ions fluorure lors d'un processus de nettoyage
EP1097249B1 (fr) Procede de realisation d'un blindage pour un composant metallique
EP1582694A1 (fr) Procédé de protection des ouvertures dans un component pendant le traitement
EP3078649B1 (fr) Céramique composite dotée d'une couche de protection contre la corrosion et son procédé de production
WO2008000247A1 (fr) Procédé de protection anticorrosion de surfaces céramiques, corps présentant des surfaces céramiques correspondantes et leur utilisation
EP1522603B1 (fr) Procédé pour revêtir un objet et objet
EP1670613A1 (fr) Procede pour produire un systeme stratifie
EP1639152A1 (fr) Procede de fabrication d'une couche de protection, couche de protection, utilisation de celle-ci et composant comportant une couche de protection
EP1772529A1 (fr) Composition chimique sèche, utilisation de celle-ci composition pour fabriquer un revêtement multicouche et méthode pour fabriquer ce revêtement
EP1510592B1 (fr) Procédé pour revêtir un objet et objet
DE102005038374A1 (de) Verfahren zur Herstellung einer Schutzschicht für ein Bauteil
EP1088907B1 (fr) Procédé de réalisation d'un blindage pour un composant métallique
EP1508628A1 (fr) Pièce comprenant un masque et méthode de revêtement d'une pièce
WO2011057829A1 (fr) Nettoyage par ions fluor renforcé de fissures non nettoyées

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20040920

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

RIN1 Information on inventor provided before grant (corrected)

Inventor name: REICHE, RALPH

Inventor name: COX, NIGEL-PHILIP

Inventor name: DERNOVSEK, OLIVER

17Q First examination report despatched

Effective date: 20061127

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20070410