EP0713957A1 - Méthode pour la réparation des couches protectives des aubes de turbine à gaz - Google Patents

Méthode pour la réparation des couches protectives des aubes de turbine à gaz Download PDF

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Publication number
EP0713957A1
EP0713957A1 EP94830550A EP94830550A EP0713957A1 EP 0713957 A1 EP0713957 A1 EP 0713957A1 EP 94830550 A EP94830550 A EP 94830550A EP 94830550 A EP94830550 A EP 94830550A EP 0713957 A1 EP0713957 A1 EP 0713957A1
Authority
EP
European Patent Office
Prior art keywords
blade
coating
temperature
region
carried out
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Withdrawn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
EP94830550A
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German (de)
English (en)
Inventor
Umberto Guerreschi
Ettore Gandini
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.)
ATLA Srl
Leonardo SpA
Original Assignee
ATLA Srl
Finmeccanica SpA
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 ATLA Srl, Finmeccanica SpA filed Critical ATLA Srl
Priority to EP94830550A priority Critical patent/EP0713957A1/fr
Publication of EP0713957A1 publication Critical patent/EP0713957A1/fr
Withdrawn legal-status Critical Current

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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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F1/00—Etching metallic material by chemical means
    • C23F1/44—Compositions for etching metallic material from a metallic material substrate of different composition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the invention relates to a method of repairing the coating of turbine blade produced by the deposition of drops of a protective material of the so-called MCrAlY type on a structure of base material of the Inconel type.
  • the blades referred to are subjected to particularly hard working conditions on account of the high-temperature and highly oxidizing and corrosive environments in which they are used; these blades, and it should be pointed out that this name also means, in general, both the rotor and stator blades of the turbine in question, are consequently produced by special techniques and with special materials.
  • MCrAlY materials the class of powders known in the field as MCrAlY materials, should be mentioned; these are powders based on metals mixed with chromium, aluminium and yttrium, the chemical symbols of which (Cr, Al, Y) in fact form the word which defines them.
  • the thermal energy for melting the material to be sprayed can be produced by the combustion of a gas, as in the case of so-called “flame spraying”, or by the striking of an electric arc and, in this case, one speaks of "electric-arc spraying", or, finally, by an electric discharge which takes place in an ionized gas, as in the case of "plasma spraying".
  • the technical problem underlying the invention is that of devising a method of repairing the coatings of turbine blades produced by the deposition of drops of a protective material of the so-called MCrAlY type.
  • a rotor blade for a gas turbine has a structure 1a made of Inconel IN738 base material (for the exact composition of the material identified by this name see, for example, the German standard TLV9560.03), with a damaged region 2 thereon shown by hatching where a repair is to be carried out with the method of the invention.
  • the blade 1 has a protective coating 3 of the type which is applied by deposition of drops carried out under vacuum and with the use of plasma; this technique is also known by the name VPS which represents the abbreviation of the English words "vacuum plasma spray".
  • the coating material is of the type already mentioned above, known as MCrAlY, which is constituted by a powder with the following composition: Co 31.8,; Ni 31.4; Cr 27.8; Al 7.6; Y 0.7; Si 0.7; and the thickness applied is between 170 and 300 ⁇ m.
  • the hatched region 2 therefore relates to a damaged region of the coating 3.
  • First step removal of the original coating from the damaged region .
  • This step was carried out by two possible alternative operative techniques, the selection thereof depending essentially on the position and shape of the defect found; both will be described briefly below.
  • the first technique consists of a chemical etching cycle preceded at first by a sand-blasting treatment of the damaged region 2 to increase roughness and thus favour the etching effect; moreover, the surface of the blade not concerned by the repair was protected with the usual varnishes suitable for this purpose.
  • the blade thus prepared was then immersed in a solution, at 70°C, of one litre of hydrochloric acid (HCl) diluted to 35% and containing 5 gr (equal to 0.5% by weight) of a fluorinated compound to activate the chemical etching constituted, in this example, by a product known commercially as ACTANE 70.
  • HCl hydrochloric acid
  • the bath in which the blade is placed was kept under agitation and the permanency time of the blade in the acid solution was about 3 hours. It should be pointed out, however, that this time spent depends upon the thickness of the coating to be removed, upon its composition and, possibly, upon the position of the damaged region and may therefore vary from case to case.
  • the time spent will naturally be shorter than previously and can be calculated in dependence on the thickness still to be removed which can be detected by micrographic observations.
  • the second operative technique used to carry out the first step of the method of this invention provides for a treatment for the diffusion of aluminium on the region to be repaired.
  • the surface of the blade was protected with masking 4 (see Figure 3) around the damaged region, by the application of an adhesive tape 5; the masking was constituted essentially by a piece of sheet metal disposed at a distance of about 2-3 mm from the coating 3 and a layer of aluminium 6 was then applied to the blade thus prepared, by the deposition of drops with plasma technique of the type already referred to above, for a thickness of 0.12-0.16 mm.
  • the blade was then brought to the solubilization temperature of the base material which, in the case in question, for the material IN738, is 1120°C, in a muffle furnace and in an inert-gas atmosphere; more precisely, the time spent by the blade at the solubilization temperature and, in general, the heating cycle to which it was subjected is illustrated in Figure 4; it can be inferred from this that, in general, after the blade had been brought to the solubilization temperature, the heating cycle provided for the blade to remain at that temperature for at least one hour, plus a further hour for each tenth of a millimetre of coating to be removed.
  • This treatment allows the aluminium to diffuse into the coating 3 causing it to become fragile locally, facilitating its subsequent removal as a result of a sand-blasting step to be carried out after the heating in the furnace.
  • Second step deposition of a new protective coating in the damaged region .
  • the region 2 subjected to the first step of the method is then ready for the local application of a new layer of coating; in the embodiment carried out, this application was preceded by cleaning and preparation of a substantially frustoconical seat 10 in the region 2 where the coating had been removed and in the neighbouring regions, so that the new coating could be superimposed gradually on the previous coating (see Figure 5).
  • This cleaning and preparation were carried out by further sand-blasting but it could have also been achieved by another equivalent working technique.
  • the plasma technique was selected for the local application of the new layer of coating by the deposition of drops and was carried out in an atmosphere protected by inert gas with a torch 20 shown in Figure 2; this torch comprises a substantially frustoconical body 21 in which there is a space 22 for the circulation of cooling water which is supplied from an inlet 22a and expelled from an outlet 22b.
  • a cathode 23 disposed on the axis of the body 21 extends in a duct 24a for the discharge of the plasma from a nozzle 24 of the torch; furthermore, the torch has a conveying structure 25 comprising an essentially cylindrical wall 25a fitted coaxially on the body 21 and fixed thereto.
  • This structure includes an annular chamber 26 into which inert gas is supplied through an inlet 26a which communicates with the interior of the structure by means of holes 27; these holes are disposed near the wall for the reasons which will become clearer from the following. Furthermore, an injector 29 extends adjacent the nozzle 24 for supplying material to be deposited on the surface to be coated which, in this case, is powder of the MCrAlY type with the composition already given.
  • the operating parameters of the torch described above are the flow-rate of argon and of hydrogen, as well as the current necessary for ionizing the gas and the distance at which the torch is kept from the surface of the blade; these depend, in general, on the operating region.
  • the flow-rate of argon was 625 slpm (standard litres per minute)
  • the flow-rate of hydrogen was 14 slpm
  • the electric current was 600 A
  • the distance of the torch from the blade was about 110 mm.
  • the inert gas is introduced into the annular chamber 26 through the inlet opening 26a and reaches the interior of the conveying structure through the holes 27; by virtue of the distribution of the holes 27 near the walls, the inert gas is distributed coaxially around the plasma jet discharged from the nozzle, isolating it from the exterior and protecting the deposit of drops of molten material on the surface, preventing possible oxidation of the region 2.
  • the blade was subjected to a heat treatment to diffuse the material deposited by the torch; this treatment was carried out in a furnace with a chamber under vacuum to avoid the dangers of oxidation of the blade, with a heating cycle in which, first of all, the solubilization temperature of the base material (1120°C in the case of IN738) was reached with increments of 10°C per minute and then, after remaining at this temperature for 4 hours, the whole blade was brought back to 540°C with a progressive decrease of 20-40°C per minute and then to ambient temperature, with the admission of inert gas to the chamber of the furnace.
  • the blade repaired as just described was then subjected to surface finishing to bring its geometrical characteristics and roughness back within the limits required by the characteristics for gas-turbine applications.
  • the blades which were subjected to this method in fact showed a degree of adhesion of the new material applied in the repaired region which was completely satisfactory and such as to confer on the blade an optimal degree of reliability in operation.
  • the operating region was cleared without alteration of the structure of the base material of the blade; this enabled the new coating subsequently deposited for the repair to adhere locally to the base material mentioned in substantially the same way as the original coating adhered to the blade during production.
  • the application of the material by the plasma technique with protection by inert gas carried out with a torch permits quick and relatively inexpensive processing which is very suitable for the localized application necessary for the carrying out of this method.
  • the diffusion of the protective material deposited also helps to achieve a better result particularly as regards the final adhesion of the new material deposited to the base material of the blade.
  • the repair of a blade by the method described can be carried out off line and therefore without using resources intended for production, for example, by mounting the torch on a mechanical arm, preferably of the type with programmable electronic control means, but without the use of vacuum chambers or other complex equipment.
  • the inert gas of the torch itself can protect the deposit of material, avoiding the danger of oxidation and, since the blade on which the repair is carried out is already coated with the original protective material in the regions surrounding the operating region, there is no risk of oxidation of these, in spite of the high temperatures involved, to which they are also subjected.
  • the solubilization temperature of this material is 1160°C and it has been found that, in general, the time spent at the solubilization temperature in the aluminium diffusion attack cycle, calculated on the basis of the graph of Figure 4, may vary in the region of about 10 minutes.
  • the values of the other parameters of the method may vary within a range which will depend, from case to case, upon the base material used, upon the position of the damaged region on the blade, upon the composition of the coating, etc. etc.
EP94830550A 1994-11-25 1994-11-25 Méthode pour la réparation des couches protectives des aubes de turbine à gaz Withdrawn EP0713957A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP94830550A EP0713957A1 (fr) 1994-11-25 1994-11-25 Méthode pour la réparation des couches protectives des aubes de turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP94830550A EP0713957A1 (fr) 1994-11-25 1994-11-25 Méthode pour la réparation des couches protectives des aubes de turbine à gaz

Publications (1)

Publication Number Publication Date
EP0713957A1 true EP0713957A1 (fr) 1996-05-29

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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0808913A1 (fr) * 1996-05-24 1997-11-26 General Electric Company Procédé pour la réparation d'un revêtement de barrière thermique
EP0861919A2 (fr) * 1997-01-31 1998-09-02 Sermatech International Inc. Procédé pour enlever des couches superficielles de revêtements métalliques
WO1999001587A1 (fr) * 1997-07-02 1999-01-14 United Technologies Corporation Procede de preparation d'un article dote de trous qui doit etre recouvert d'une couche protectrice
US6004620A (en) * 1997-11-12 1999-12-21 Rolls-Royce Plc Method of unblocking an obstructed cooling passage
WO2000000667A1 (fr) * 1998-06-29 2000-01-06 General Electric Company Procede permettant de decaper un revetement d'un joint rotatif d'un moteur d'avion
EP1013787A1 (fr) 1998-12-22 2000-06-28 General Electric Company Revêtement d'une surface sélective et discrète d'un article
EP1013796A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Rénovation d' un revêtement d'isolation thermique
US6328810B1 (en) * 1999-04-07 2001-12-11 General Electric Company Method for locally removing oxidation and corrosion product from the surface of turbine engine components
EP1162284A1 (fr) * 2000-06-05 2001-12-12 Alstom (Switzerland) Ltd Procédé de réparation d'un composant revêtu
WO2002103088A1 (fr) * 2001-06-14 2002-12-27 Mtu Aero Engines Gmbh Procede et dispositif d'enlevement de couche local sur des pieces
EP1298230A1 (fr) * 2001-10-01 2003-04-02 Siemens Aktiengesellschaft Procédé pour enlever des produits de corrosion d'un composant métallique
EP1316389A2 (fr) * 2001-11-29 2003-06-04 General Electric Company Procédé d'enlèvement d'une région endommagée sous un revêtement protecteur sur une aube
EP1522604A1 (fr) * 2003-10-02 2005-04-13 Siemens Aktiengesellschaft Système de couches et procédé pour sa fabrication
GB2408514A (en) * 2003-11-06 2005-06-01 Gen Electric Method for HVOF or LPPS restoration coating repair of a nickel based superalloy article
US7182581B2 (en) 2004-10-07 2007-02-27 Siemens Aktiengesellschaft Layer system
WO2007060062A1 (fr) * 2005-11-24 2007-05-31 Siemens Aktiengesellschaft Systeme en couche comportant une phase pyrochlore constituee de cristal mixte de gadolinium
WO2008017559A1 (fr) * 2006-08-08 2008-02-14 Siemens Aktiengesellschaft Procédé de fabrication d'une couche d'usure
US20090208662A1 (en) * 2004-11-04 2009-08-20 United Technologies Corporation Methods for Repairing a Workpiece
EP2108713A1 (fr) * 2008-04-03 2009-10-14 Samsung Electronics Co., Ltd Structure de substrat et procédé de fabrication de celle-ci
EP2166125A1 (fr) 2008-09-19 2010-03-24 ALSTOM Technology Ltd Procédé pour la configuration des services d'un réseau personnel
US8221825B2 (en) 2009-03-30 2012-07-17 Alstom Technology Ltd. Comprehensive method for local application and local repair of thermal barrier coatings
US8460760B2 (en) 2010-11-30 2013-06-11 United Technologies Corporation Coating a perforated surface
CN103882441A (zh) * 2014-03-25 2014-06-25 东方电气集团东方汽轮机有限公司 一种2Cr12NiMo1W1V叶片表面Al涂层的修复方法
US20140174091A1 (en) * 2012-12-21 2014-06-26 United Technologies Corporation Repair procedure for a gas turbine engine via variable polarity welding
US8859479B2 (en) 2011-08-26 2014-10-14 United Technologies Corporation Chemical stripping composition and method
US9879337B2 (en) 2013-12-20 2018-01-30 Pratt & Whitney Canada Corp. Method of spray coating a surface having a magnesium base
US10590800B2 (en) 2014-09-25 2020-03-17 General Electric Company Method for selective aluminide diffusion coating removal
CN113957378A (zh) * 2021-10-22 2022-01-21 中国航发贵州黎阳航空动力有限公司 一种涡轮叶片的涂层修复方法
CN113969405A (zh) * 2021-10-27 2022-01-25 中国航发贵州黎阳航空动力有限公司 一种用于去除航空发动机叶片NiCrAlY涂层的方法
CN113981457A (zh) * 2021-10-27 2022-01-28 中国航发贵州黎阳航空动力有限公司 一种用于单晶高压涡轮叶片失效涂层的去除方法
CN114107993A (zh) * 2021-11-23 2022-03-01 华瑞（江苏）燃机服务有限公司 一种燃气轮机透平动叶叶片的金属粘结层的酸洗剥离工艺

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2021543A1 (fr) * 1968-10-25 1970-07-24 United Aircraft Corp
FR2300142A1 (fr) * 1975-02-10 1976-09-03 United Technologies Corp Procede pour enlever des reveteme
FR2359965A1 (fr) * 1976-07-30 1978-02-24 Gulf & Western Industries Produit de masquage et procede pour empecher le depot d'un revetement sur un substrat
US4123595A (en) * 1977-09-22 1978-10-31 General Electric Company Metallic coated article
GB2006274A (en) * 1977-10-17 1979-05-02 United Technologies Corp Oxidation and Wear Resistant Coated Article
DE3325251A1 (de) * 1983-07-13 1985-01-24 Brown, Boveri & Cie Ag, 6800 Mannheim Verfahren zum pruefen und nachbessern von auf bauelementen aufgetragenen schutzschichten
EP0558053A1 (fr) * 1992-02-27 1993-09-01 Turbine Blading Limited Méthode de réparation des aubes de turbine
DE4303137A1 (de) * 1993-02-04 1994-08-11 Mtu Muenchen Gmbh Verfahren zum Entfernen von Keramikschichten auf Metallbauteilen

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2021543A1 (fr) * 1968-10-25 1970-07-24 United Aircraft Corp
FR2300142A1 (fr) * 1975-02-10 1976-09-03 United Technologies Corp Procede pour enlever des reveteme
FR2359965A1 (fr) * 1976-07-30 1978-02-24 Gulf & Western Industries Produit de masquage et procede pour empecher le depot d'un revetement sur un substrat
US4123595A (en) * 1977-09-22 1978-10-31 General Electric Company Metallic coated article
GB2006274A (en) * 1977-10-17 1979-05-02 United Technologies Corp Oxidation and Wear Resistant Coated Article
DE3325251A1 (de) * 1983-07-13 1985-01-24 Brown, Boveri & Cie Ag, 6800 Mannheim Verfahren zum pruefen und nachbessern von auf bauelementen aufgetragenen schutzschichten
EP0558053A1 (fr) * 1992-02-27 1993-09-01 Turbine Blading Limited Méthode de réparation des aubes de turbine
DE4303137A1 (de) * 1993-02-04 1994-08-11 Mtu Muenchen Gmbh Verfahren zum Entfernen von Keramikschichten auf Metallbauteilen

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
JOURNAL OF VACUUM SCIENCE AND TECHNOLOGY: PART A, vol. 3, no. 6, NEW YORK US, pages 2525 - 2531 *
R. BÜRGEL, J. ELLNER, K. SCHNEIDER, B. JAHNKE: "experience gained refurbishing gas turbine blades", BROWN BOVERI REVIEW, vol. 74, no. 10, BADEN CH, pages 593 - 599, XP001207564 *

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EP0808913A1 (fr) * 1996-05-24 1997-11-26 General Electric Company Procédé pour la réparation d'un revêtement de barrière thermique
US6036995A (en) * 1997-01-31 2000-03-14 Sermatech International, Inc. Method for removal of surface layers of metallic coatings
EP0861919A2 (fr) * 1997-01-31 1998-09-02 Sermatech International Inc. Procédé pour enlever des couches superficielles de revêtements métalliques
EP0861919A3 (fr) * 1997-01-31 1998-09-09 Sermatech International Inc. Procédé pour enlever des couches superficielles de revêtements métalliques
WO1999001587A1 (fr) * 1997-07-02 1999-01-14 United Technologies Corporation Procede de preparation d'un article dote de trous qui doit etre recouvert d'une couche protectrice
US6042879A (en) * 1997-07-02 2000-03-28 United Technologies Corporation Method for preparing an apertured article to be recoated
US6004620A (en) * 1997-11-12 1999-12-21 Rolls-Royce Plc Method of unblocking an obstructed cooling passage
WO2000000667A1 (fr) * 1998-06-29 2000-01-06 General Electric Company Procede permettant de decaper un revetement d'un joint rotatif d'un moteur d'avion
EP1013787A1 (fr) 1998-12-22 2000-06-28 General Electric Company Revêtement d'une surface sélective et discrète d'un article
EP1013796A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Rénovation d' un revêtement d'isolation thermique
US6328810B1 (en) * 1999-04-07 2001-12-11 General Electric Company Method for locally removing oxidation and corrosion product from the surface of turbine engine components
EP1162284A1 (fr) * 2000-06-05 2001-12-12 Alstom (Switzerland) Ltd Procédé de réparation d'un composant revêtu
US6569492B2 (en) 2000-06-05 2003-05-27 Alstom Ltd Process for repairing a coated component
WO2002103088A1 (fr) * 2001-06-14 2002-12-27 Mtu Aero Engines Gmbh Procede et dispositif d'enlevement de couche local sur des pieces
US7513986B2 (en) 2001-06-14 2009-04-07 Mtu Aero Engines Gmbh Method and device for locally removing coating from parts
WO2003029521A1 (fr) * 2001-10-01 2003-04-10 Siemens Aktiengesellschaft Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique
EP1298230A1 (fr) * 2001-10-01 2003-04-02 Siemens Aktiengesellschaft Procédé pour enlever des produits de corrosion d'un composant métallique
US7138065B2 (en) 2001-10-01 2006-11-21 Siemens Aktiengesellschaft Method for removing at least one area of a layer of a component consisting of metal or a metal compound
US7429337B2 (en) 2001-10-01 2008-09-30 Siemens Aktiengesellschaft Method for removing at least one area of a layer of a component consisting of metal or a metal compound
EP1316389A2 (fr) * 2001-11-29 2003-06-04 General Electric Company Procédé d'enlèvement d'une région endommagée sous un revêtement protecteur sur une aube
EP1316389A3 (fr) * 2001-11-29 2004-11-24 General Electric Company Procédé d'enlèvement d'une région endommagée sous un revêtement protecteur sur une aube
EP1522604A1 (fr) * 2003-10-02 2005-04-13 Siemens Aktiengesellschaft Système de couches et procédé pour sa fabrication
US7182580B2 (en) 2003-10-02 2007-02-27 Siemens Aktiengesellschaft Layer system, and process for producing a layer system
GB2408514A (en) * 2003-11-06 2005-06-01 Gen Electric Method for HVOF or LPPS restoration coating repair of a nickel based superalloy article
US7811396B2 (en) 2003-11-06 2010-10-12 General Electric Company Method for HVOF or LPPS restoration coating repair of a nickel-base superalloy article
GB2408514B (en) * 2003-11-06 2007-09-05 Gen Electric Method for HVOF or LPPS restoration coating repair of a nickel-base superalloy article
US7182581B2 (en) 2004-10-07 2007-02-27 Siemens Aktiengesellschaft Layer system
US20090208662A1 (en) * 2004-11-04 2009-08-20 United Technologies Corporation Methods for Repairing a Workpiece
US9611551B2 (en) 2005-11-24 2017-04-04 Siemens Aktiengesellschaft Layer system comprising gadolinium solid solution pyrochlore phase
WO2007060062A1 (fr) * 2005-11-24 2007-05-31 Siemens Aktiengesellschaft Systeme en couche comportant une phase pyrochlore constituee de cristal mixte de gadolinium
WO2008017559A1 (fr) * 2006-08-08 2008-02-14 Siemens Aktiengesellschaft Procédé de fabrication d'une couche d'usure
US8673405B2 (en) 2006-08-08 2014-03-18 Siemens Aktiengesellschaft Method for producing a wear layer
CN101552184B (zh) * 2008-04-03 2013-11-06 三星电子株式会社 基板结构及其形成方法与太赫装置及其制造方法
EP2108713A1 (fr) * 2008-04-03 2009-10-14 Samsung Electronics Co., Ltd Structure de substrat et procédé de fabrication de celle-ci
US8563076B2 (en) 2008-04-03 2013-10-22 Samsung Electronics Co., Ltd. Substrate structure and method of forming the same
EP2166125A1 (fr) 2008-09-19 2010-03-24 ALSTOM Technology Ltd Procédé pour la configuration des services d'un réseau personnel
US8221825B2 (en) 2009-03-30 2012-07-17 Alstom Technology Ltd. Comprehensive method for local application and local repair of thermal barrier coatings
US8460760B2 (en) 2010-11-30 2013-06-11 United Technologies Corporation Coating a perforated surface
US8859479B2 (en) 2011-08-26 2014-10-14 United Technologies Corporation Chemical stripping composition and method
US20140174091A1 (en) * 2012-12-21 2014-06-26 United Technologies Corporation Repair procedure for a gas turbine engine via variable polarity welding
US9879337B2 (en) 2013-12-20 2018-01-30 Pratt & Whitney Canada Corp. Method of spray coating a surface having a magnesium base
CN103882441A (zh) * 2014-03-25 2014-06-25 东方电气集团东方汽轮机有限公司 一种2Cr12NiMo1W1V叶片表面Al涂层的修复方法
US10590800B2 (en) 2014-09-25 2020-03-17 General Electric Company Method for selective aluminide diffusion coating removal
CN113957378A (zh) * 2021-10-22 2022-01-21 中国航发贵州黎阳航空动力有限公司 一种涡轮叶片的涂层修复方法
CN113969405A (zh) * 2021-10-27 2022-01-25 中国航发贵州黎阳航空动力有限公司 一种用于去除航空发动机叶片NiCrAlY涂层的方法
CN113981457A (zh) * 2021-10-27 2022-01-28 中国航发贵州黎阳航空动力有限公司 一种用于单晶高压涡轮叶片失效涂层的去除方法
CN114107993A (zh) * 2021-11-23 2022-03-01 华瑞（江苏）燃机服务有限公司 一种燃气轮机透平动叶叶片的金属粘结层的酸洗剥离工艺

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