EP1559485A1 - Procédé pour l'enlèvement d'une couche - Google Patents

Procédé pour l'enlèvement d'une couche Download PDF

Info

Publication number
EP1559485A1
EP1559485A1 EP04002158A EP04002158A EP1559485A1 EP 1559485 A1 EP1559485 A1 EP 1559485A1 EP 04002158 A EP04002158 A EP 04002158A EP 04002158 A EP04002158 A EP 04002158A EP 1559485 A1 EP1559485 A1 EP 1559485A1
Authority
EP
European Patent Office
Prior art keywords
removal area
removal
damage
component
generated
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Withdrawn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
EP04002158A
Other languages
German (de)
English (en)
Inventor
Georg Dr. Bostanjoglo
Stefan Krause
Michael Dr. Ott
Ralph Reiche
Jan Dr. Steinbach
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 EP04002158A priority Critical patent/EP1559485A1/fr
Priority to EP07010914A priority patent/EP1818112A3/fr
Priority to PCT/EP2005/000405 priority patent/WO2005072884A1/fr
Priority to DE502005006806T priority patent/DE502005006806D1/de
Priority to EP05700980A priority patent/EP1708829B1/fr
Priority to US10/587,702 priority patent/US20070170150A1/en
Priority to CNA2005800079667A priority patent/CN1929931A/zh
Publication of EP1559485A1 publication Critical patent/EP1559485A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B7/00—Cleaning by methods not provided for in a single other subclass or a single group in this subclass
    • 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
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G1/00—Cleaning or pickling metallic material with solutions or molten salts
    • 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
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents

Definitions

  • FIG. 1 shows a component 1 which can be treated by the method according to the invention.
  • the component 1 consists of a ceramic or metallic substrate 4 (main body), which is, for example, especially for turbines, a cobalt-, iron- or nickel-based superalloy.
  • the component 1 is, for example, a guide 130 or rotor blade 120 (FIGS. 6, 8) of a gas 100 (FIG. 6), a steam turbine 300, 303 (FIG. 9), or an aircraft turbine, a combustion chamber lining 155 (FIG. 7) or another hot gas charged component of a turbine.
  • the component 1 can have at least one ceramic or metallic layer on the surface 13 for use, such as, for example, an MCrAlX layer and / or a thermal insulation layer lying thereon, which can be roughly removed in a first method step.
  • the MCrAlX layer can also represent the removal region 10, which is treated by the method according to the invention.
  • the removal region 10 is considered as a corrosion product 10 (corrosion layer 10).
  • the removal region 10 can also be a functional layer without corrosion products.
  • the removal region 10 may be a metallic and / or ceramic layer, wherein the layer may be metallic and has corrosion products.
  • the corrosion product 10, for example an oxide, a sulfide, a nitride, a phosphide or a carbide, etc., may be present on a surface 13 of the component 1 or in a crack 7 of the component 1.
  • the corrosion products 10 must from the crack 7 or from the Surface 13 are removed so that the crack 7 with a solder or weld metal can be filled and the surface 13 can be re-coated. Corrosion products would be 10 otherwise a good adhesion of the solder or a renewed Prevent coating or at least reduce it.
  • FIG. 2 shows schematically the implementation of the invention Process.
  • a material 16 for example a salt 16 which can react chemically with the corrosion product 10 in order to damage the removal region 10 is applied to the corrosion product 10.
  • the salt used is preferably Na 2 SO 4 (sodium sulfate) and / or CoSO 4 (cobalt sulfate).
  • Other salts or combinations are conceivable.
  • the corrosion products aluminum oxide and / or cobalt oxide and / or titanium oxide of the metals titanium, aluminum and / or cobalt, which are contained in the alloy (for example superalloy) of the substrate 4, can be removed very well.
  • the salt 16 may, for example, by means of a laser 19 and his laser beams 22 are heated in particular locally, so that a chemical reaction of the salt 16 with the corrosion product 10 or a thermal shock occurs.
  • the heating can also be effected by electromagnetic induction, in particular when the substrate 4 is metallic.
  • the heating of the component 1 can take place locally by means of induction or by means of a light source, for example by means of a laser, in that the laser 19 irradiates the laser beam 22 only into the crack 7.
  • Tunable means that among others the wavelength and intensity can be changed.
  • FIG. 3 shows a component 1 with a corrosion product 10 after the damage of the corrosion product 10 by a Pre-treatment according to the invention.
  • pretreatment cracks 25 are generated starting from the surface 14 of the layer 10 towards the substrate 4 run, leaving a larger attack surface of the Corrosion product 10 to the acid and / or the Fluorine ions, etc. is given.
  • the component 1 a final cleaning by means of an acid or fluorine ion treatment subjected to complete removal of the Corrosion product 10 leads, as by the damage of the corrosion product 10 the removal rate at the FIC or a other method is significantly increased and no significant Reduction of the removal rate with time.
  • FIG. 4 shows another possibility for achieving damage to the corrosion product 10.
  • the corrosion product 10, which rests on a surface 13 of the substrate 4 is subjected to a thermal shock.
  • FIG. 5 shows further damage in the corrosion product 10 according to the method according to the invention. If the material of the corrosion product 10 has been melted, for example, the material contracts again on cooling, so that mechanical stresses occur which may lead to cracking.
  • delaminations 34 can occur between the corrosion product 10 and a surface 13 on which the corrosion product 10 rests form.
  • the special feature of the process is that caused by corrosion products 10 damaged and to be repaired component 1 with the corrosion products 10 again in the range of corrosion products 10 is damaged.
  • FIG. 6 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a suction housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed of two blade rings.
  • a series 125 formed of rotor blades 120 follows.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the substrates may have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the material used is iron-, nickel- or cobalt-based superalloys.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is yttrium (Y) and / or at least one element of the rare Erden) and have heat through a thermal barrier coating.
  • the thermal barrier coating consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
  • EB-PVD electron beam evaporation
  • the vane 130 has an inner housing 138 of the Turbine 108 facing Leitschaufelfuß (not shown here) and a vane foot opposite Guide vane head on.
  • the vane head is the rotor 103 facing and on a mounting ring 140 of the stator 143rd established.
  • the working medium M of about 1000 ° C to 1600 ° C designed.
  • the combustion chamber wall 153 on its the working medium M facing side with one of heat shield elements 155 formed inner lining provided.
  • Each heat shield element 155 is working medium side with a particularly heat-resistant Protective layer equipped or made of high temperature resistant Material made. Due to the high temperatures inside the combustion chamber 110 is also for the Heat shield elements 155 or for their holding elements Cooling system provided.
  • FIG. 8 shows a perspective view of a blade 120, 130 which extends along a longitudinal axis 121.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjoining thereto and an airfoil region 406.
  • a blade root 183 is formed, which serves for fastening the rotor blades 120, 130 to the shaft.
  • the blade root 183 is designed as a hammer head.
  • Other configurations, for example as a Christmas tree or Schwalbenschwanzfuß are possible.
  • solid metallic materials are used in all regions 400, 403, 406 of the blades 120, 130.
  • the blade 120, 130 may be manufactured by a casting process, by a forging process, by a milling process or combinations thereof.
  • FIG. 9 shows a steam turbine 300, 303 by way of example one extending along a rotation axis 306 Turbine shaft 309 shown.
  • the steam turbine has a high pressure turbine part 300 and a medium-pressure turbine section 303, each with an inner housing 312 and a surrounding this outer housing 315th on.
  • the high pressure turbine part 300 is, for example, in Pot type executed.
  • the medium-pressure turbine section 303 is double-flowed. It is also possible that the Medium-pressure turbine section 303 is designed to be single-entry.
  • Along the axis of rotation 306 is between the high pressure turbine part 300 and the medium-pressure turbine section 303 a bearing 318 arranged, wherein the turbine shaft 309 in the bearing 318 a Storage area 321 has.
  • the turbine shaft 309 is on another bearing 324 adjacent to the high pressure turbine 300 superimposed.
  • the high-pressure turbine part 300 In the area of this bearing 324, the high-pressure turbine part 300, a shaft seal 345 on.
  • the turbine shaft 309 is opposite the outer casing 315 of the medium-pressure turbine section 303 by two further shaft seals 345th sealed.
  • Between a high pressure steam inlet 348 and a steam exit region 351 has the turbine shaft 309 in the high pressure turbine section 300, the high pressure runner blading 354, 357 on.
  • This high pressure blading 354, 357 with the associated, not shown Blades a first blading area 360 dar.
  • the medium-pressure turbine section 303 has a central Steam inlet 333 on.
  • the components of the steam turbine 300, 303 have protective layers and / or corrosion products 10 associated with the process according to the invention are removed before a reprocessing the components can be made.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
  • Preventing Corrosion Or Incrustation Of Metals (AREA)
EP04002158A 2004-01-30 2004-01-30 Procédé pour l'enlèvement d'une couche Withdrawn EP1559485A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP04002158A EP1559485A1 (fr) 2004-01-30 2004-01-30 Procédé pour l'enlèvement d'une couche
EP07010914A EP1818112A3 (fr) 2004-01-30 2005-01-17 Procédé pour éliminer une couche
PCT/EP2005/000405 WO2005072884A1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche
DE502005006806T DE502005006806D1 (de) 2004-01-30 2005-01-17 Verfahren zur entfernung einer schicht
EP05700980A EP1708829B1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche
US10/587,702 US20070170150A1 (en) 2004-01-30 2005-01-17 Process for removing a layer
CNA2005800079667A CN1929931A (zh) 2004-01-30 2005-01-17 去除面层的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04002158A EP1559485A1 (fr) 2004-01-30 2004-01-30 Procédé pour l'enlèvement d'une couche

Publications (1)

Publication Number Publication Date
EP1559485A1 true EP1559485A1 (fr) 2005-08-03

Family

ID=34639430

Family Applications (3)

Application Number Title Priority Date Filing Date
EP04002158A Withdrawn EP1559485A1 (fr) 2004-01-30 2004-01-30 Procédé pour l'enlèvement d'une couche
EP07010914A Withdrawn EP1818112A3 (fr) 2004-01-30 2005-01-17 Procédé pour éliminer une couche
EP05700980A Not-in-force EP1708829B1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche

Family Applications After (2)

Application Number Title Priority Date Filing Date
EP07010914A Withdrawn EP1818112A3 (fr) 2004-01-30 2005-01-17 Procédé pour éliminer une couche
EP05700980A Not-in-force EP1708829B1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche

Country Status (5)

Country Link
US (1) US20070170150A1 (fr)
EP (3) EP1559485A1 (fr)
CN (1) CN1929931A (fr)
DE (1) DE502005006806D1 (fr)
WO (1) WO2005072884A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006061338A1 (fr) * 2004-12-10 2006-06-15 Siemens Aktiengesellschaft Procede pour nettoyer un outil comprenant des ions halogenures
EP1818112A2 (fr) * 2004-01-30 2007-08-15 Siemens Aktiengesellschaft Procédé pour éliminer une couche
WO2008000663A1 (fr) * 2006-06-27 2008-01-03 Siemens Aktiengesellschaft Procédé pour éliminer un revêtement de protection d'un élément constitutif
EP2090677A1 (fr) * 2008-01-19 2009-08-19 MTU Aero Engines GmbH Procédé de suppression au moins sélective d'une première couche d'un composant de turbine
WO2011057829A1 (fr) * 2009-11-11 2011-05-19 Siemens Aktiengesellschaft Nettoyage par ions fluor renforcé de fissures non nettoyées
EP2716788A1 (fr) * 2012-10-08 2014-04-09 Siemens Aktiengesellschaft Procédé destiné à supprimer une couche métallique sur un substrat
US9657414B2 (en) 2007-05-24 2017-05-23 Oerlikon Textile Gmbh & Co. Kg Method and device for operating a drawing line or drawing unit

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100840902B1 (ko) 2007-03-20 2008-06-24 주식회사 에이팩 마이크로웨이브를 이용한 광디스크의 반사층 박리장치
ES2367855T3 (es) * 2008-12-17 2011-11-10 Saab Ab Restauración de la fuerza y de la resistencia al desgaste de un compuesto de matriz metálica (mmc).
SG165202A1 (en) * 2009-03-25 2010-10-28 United Technologies Corp Method and apparatus for cleaning a component using microwave radiation
US9061375B2 (en) * 2009-12-23 2015-06-23 General Electric Company Methods for treating superalloy articles, and related repair processes
US9205509B2 (en) * 2011-08-31 2015-12-08 General Electric Company Localized cleaning process and apparatus therefor
CN102392249B (zh) * 2011-11-28 2013-06-05 江西省科学院应用物理研究所 一种去除硬质合金件表面涂层的方法
JP6508823B2 (ja) * 2015-05-08 2019-05-08 三菱重工航空エンジン株式会社 酸化膜除去方法
CN105297056A (zh) * 2015-10-15 2016-02-03 谭华 一种银合金焊料的清洗方法
US11247249B2 (en) * 2017-04-18 2022-02-15 General Electric Company Method for removing oxide materials from a crack
CN110497049B (zh) * 2019-07-19 2020-08-25 江苏江航智飞机发动机部件研究院有限公司 一种镍基超合金材料叶片的加工方法
EP4175772A1 (fr) * 2020-07-03 2023-05-10 Applied Materials, Inc. Procédés de remise à neuf de composants aérospatiaux

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4439241A (en) * 1982-03-01 1984-03-27 United Technologies Corporation Cleaning process for internal passages of superalloy airfoils
US5464479A (en) * 1994-08-31 1995-11-07 Kenton; Donald J. Method for removing undesired material from internal spaces of parts
US5575858A (en) * 1994-05-02 1996-11-19 United Technologies Corporation Effective cleaning method for turbine airfoils
EP1013797A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Procédé d'enlèvement de produits de corrosion à haute température d'un revêtement d'une aluminure par diffusion
EP1411149A1 (fr) * 2002-10-18 2004-04-21 Siemens Aktiengesellschaft Procédé pour l'enlèvement d'un revêtement d'un composant

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2120494A (en) * 1935-09-25 1938-06-14 Keystone Steel & Wire Co Method of cleaning metal articles
US2710271A (en) * 1951-08-09 1955-06-07 Int Nickel Co Process for annealing and cleaning oxidized metal in a salt bath
US3266477A (en) * 1964-04-15 1966-08-16 Du Pont Self-cleaning cooking apparatus
US4098450A (en) * 1977-03-17 1978-07-04 General Electric Company Superalloy article cleaning and repair method
KR940008936B1 (ko) * 1990-02-15 1994-09-28 가부시끼가이샤 도시바 고순도 금속재와 그 성질을 이용한 반도체 장치 및 그 제조방법
EP1312437A1 (fr) * 2001-11-19 2003-05-21 ALSTOM (Switzerland) Ltd Procédé pour réparer une fissure
EP1559485A1 (fr) * 2004-01-30 2005-08-03 Siemens Aktiengesellschaft Procédé pour l'enlèvement d'une couche

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4439241A (en) * 1982-03-01 1984-03-27 United Technologies Corporation Cleaning process for internal passages of superalloy airfoils
US5575858A (en) * 1994-05-02 1996-11-19 United Technologies Corporation Effective cleaning method for turbine airfoils
US5464479A (en) * 1994-08-31 1995-11-07 Kenton; Donald J. Method for removing undesired material from internal spaces of parts
EP1013797A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Procédé d'enlèvement de produits de corrosion à haute température d'un revêtement d'une aluminure par diffusion
EP1411149A1 (fr) * 2002-10-18 2004-04-21 Siemens Aktiengesellschaft Procédé pour l'enlèvement d'un revêtement d'un composant

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1818112A2 (fr) * 2004-01-30 2007-08-15 Siemens Aktiengesellschaft Procédé pour éliminer une couche
EP1818112A3 (fr) * 2004-01-30 2007-09-12 Siemens Aktiengesellschaft Procédé pour éliminer une couche
WO2006061338A1 (fr) * 2004-12-10 2006-06-15 Siemens Aktiengesellschaft Procede pour nettoyer un outil comprenant des ions halogenures
WO2008000663A1 (fr) * 2006-06-27 2008-01-03 Siemens Aktiengesellschaft Procédé pour éliminer un revêtement de protection d'un élément constitutif
US9657414B2 (en) 2007-05-24 2017-05-23 Oerlikon Textile Gmbh & Co. Kg Method and device for operating a drawing line or drawing unit
EP2090677A1 (fr) * 2008-01-19 2009-08-19 MTU Aero Engines GmbH Procédé de suppression au moins sélective d'une première couche d'un composant de turbine
WO2011057829A1 (fr) * 2009-11-11 2011-05-19 Siemens Aktiengesellschaft Nettoyage par ions fluor renforcé de fissures non nettoyées
EP2327813A1 (fr) * 2009-11-11 2011-06-01 Siemens Aktiengesellschaft Nettoyage par fluor-ions renforcé de fissures contaminées
EP2716788A1 (fr) * 2012-10-08 2014-04-09 Siemens Aktiengesellschaft Procédé destiné à supprimer une couche métallique sur un substrat

Also Published As

Publication number Publication date
US20070170150A1 (en) 2007-07-26
EP1708829B1 (fr) 2009-03-11
EP1818112A2 (fr) 2007-08-15
EP1818112A3 (fr) 2007-09-12
WO2005072884A1 (fr) 2005-08-11
CN1929931A (zh) 2007-03-14
DE502005006806D1 (de) 2009-04-23
EP1708829A1 (fr) 2006-10-11

Similar Documents

Publication Publication Date Title
EP1708829B1 (fr) Procede pour eliminer une couche
DE102011055612A1 (de) Turbinenkomponenten mit Kühleinrichtungen und Verfahren zur Herstellung derselben
WO2005044508A1 (fr) Procede pour produire un trou et dispositif
EP1722901B1 (fr) Procede de nettoyage au plasma d'un composant
EP1864742A1 (fr) Procédé pour usiner par électro-érosion des materiaux électriquement non-conducteur
WO2007110277A1 (fr) Procédé d'usinage par électroérosion d'une matière non électroconductrice
WO2007048696A1 (fr) Procede de nettoyage aux ions fluor de composants oxydes ou attaques par la corrosion
EP1816316A1 (fr) Procédé de réparation de composants
EP2230041B1 (fr) Procédé de fabrication d'un trou
EP2150636A1 (fr) Revêtements céramiques polymères pour la protection de surfaces contre des ions fluorure lors d'un processus de nettoyage
EP1666625A1 (fr) Procédé de revêtement d'un composant a l'interieur d'un aparat
EP1707651A1 (fr) Système de revêtement et procédé de fabrication d'une système de revêtement
EP1797985A1 (fr) Procédé et dispositif de soudage
WO2009053154A1 (fr) Procédé pour éliminer une couche métallique au moyen du procédé fic au cours d'une étape intermédiaire
EP1772529A1 (fr) Composition chimique sèche, utilisation de celle-ci composition pour fabriquer un revêtement multicouche et méthode pour fabriquer ce revêtement
EP1645652A1 (fr) Procédé de fabrication d'un système de couches
EP1508628A1 (fr) Pièce comprenant un masque et méthode de revêtement d'une pièce
EP1808236A1 (fr) Procédé pour masquer des trous de refroidissement, en particulier d'aubes de turbine
EP1808251B1 (fr) Procédé de dressage d'un électrode d'érosion et d'usinage par électro-érosion
EP1674193A1 (fr) Procédé de fabrication d'un trou
EP1867749A1 (fr) Procédé de revêtement d'un matériau à une pièce
WO2007085512A1 (fr) Procede de fabrication d'un composant dote de trous
EP1561839A1 (fr) Procédé de fabrication d'une structure en couches comprenant une couche céramique et colonnaire
EP1676938A1 (fr) Methode de fabrication d'un component d'une turbine et le component d'une turbine
WO2007082787A1 (fr) Procede de soudage suivi par un traitement de diffusion

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

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

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid
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: 20060204

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566