EP1708829B1 - Procede pour eliminer une couche - Google Patents

Procede pour eliminer une couche Download PDF

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Publication number
EP1708829B1
EP1708829B1 EP05700980A EP05700980A EP1708829B1 EP 1708829 B1 EP1708829 B1 EP 1708829B1 EP 05700980 A EP05700980 A EP 05700980A EP 05700980 A EP05700980 A EP 05700980A EP 1708829 B1 EP1708829 B1 EP 1708829B1
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EP
European Patent Office
Prior art keywords
removal region
process according
component
salt
removal
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.)
Not-in-force
Application number
EP05700980A
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German (de)
English (en)
Other versions
EP1708829A1 (fr
Inventor
Georg Bostanjoglo
Stefan Krause
Michael Ott
Ralph Reiche
Jan 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
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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 EP07010914A priority Critical patent/EP1818112A3/fr
Priority to EP05700980A priority patent/EP1708829B1/fr
Publication of EP1708829A1 publication Critical patent/EP1708829A1/fr
Application granted granted Critical
Publication of EP1708829B1 publication Critical patent/EP1708829B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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

  • the invention relates to a method for removing a layer according to claim 1.
  • Components such as turbine blades, for example, after use corrosion products such as oxides, sulfides, nitrides, carbides, phosphates, etc., which form a layer. Such components can be used again after their use, if, inter alia, the corrosion products have been removed. The complete removal of the corrosion products, for example, by sandblasting, but this can lead to damage to the substrate.
  • corrosion products such as oxides, sulfides, nitrides, carbides, phosphates, etc.
  • the U.S. Patent 5,575,858 describes a method for removing a removal area, in particular a corrosion product of a component, in which the removal area is pre-negotiated before a final cleaning, so that a damage of the removal area takes place, so that then a removal rate in the final cleaning of the removal area is greater than without the damage to the removal area ,
  • the object is achieved by a method according to claim 1.
  • 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 blade 120 (FIG. FIG. 6 . 8th ) of a gas 100 ( FIG. 6 ), a steam turbine 300, 303 ( FIG. 9 ), or an aircraft turbine, a combustion liner 155 (FIG. Fig. 7 ) or another hot gas charged component of a turbine.
  • the component 1 can either be newly manufactured or remanufactured. Refurbishment means that after use, components 1 may be separated from layers (thermal barrier coating) and corrosion and oxidation products removed. If necessary, cracks still have to be repaired. Thereafter, such a component 1 can be coated again; This is particularly advantageous because the body is very expensive.
  • the component 1 can have at least one ceramic or metallic layer on the surface 13 for use, such as 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 be removed from the crack 7 or from the surface 13, so that the crack 7 can be filled with a solder or weld metal and the surface 13 can be coated again. Corrosion products 10 would otherwise good adhesion of the solder or a renewed Prevent coating or at least reduce it.
  • the prior art corrosion product 10 has a certain removal rate (mass per time) when it is cleaned, for example, by the FIC process. However, this erosion rate is too low and may even be zero after a certain time.
  • FIG. 2 shows schematically the implementation of the method according to the invention.
  • a salt 16 is applied to the corrosion product 10 in order to damage it, which salt can chemically react with the corrosion product 10 in order to damage the removal region 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.
  • a molten salt can be applied directly in the crack 7 or on the corrosion product 10 or the component 1 is immersed in a molten salt.
  • the salt in the form of a slurry in the crack 7 and on the surface 13.
  • laying a film containing the material 16 or salt 16 is suitable.
  • the salt 16 may, for example, be locally heated by means of a laser 19 and its laser beams 22, so that a chemical reaction of the salt 16 with the corrosion product 10 or a thermal shock takes place.
  • 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.
  • the local heating can also be done by means of tunable microwaves. Tunable means that among other things, 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 pretreatment according to the invention.
  • the pretreatment produces cracks 25 which extend from the surface 14 of the layer 10 towards the substrate 4, so that a larger surface of attack of the corrosion product 10 with respect to the acid and / or the fluorine ions, etc. is given.
  • the component 1 is subjected to a final cleaning by means of an acid or fluorine ion treatment, which leads to the complete removal of the corrosion product 10, since the damage rate of the corrosion product 10, the removal rate in FIC or another method is significantly increased and no significant reduction of Removal rate occurs over time.
  • FIG. 4 shows another way to achieve 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.
  • the thermal shock can be done by immersion in a hot salt bath.
  • the corrosion product 10 can also be partially melted.
  • FIG. 5 shows further damage in the corrosion product 10 according to the method of 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.
  • cracks 31 within the corrosion product 10 may also be generated.
  • delaminations 34 may form between the corrosion product 10 and a surface 13 on which the corrosion product 10 rests.
  • the special feature of the method is that the damaged by corrosion products 10 and to be repaired component 1 with the corrosion products 10 is damaged again in the field of corrosion products 10.
  • 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.
  • annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine 108th Each turbine stage 112 is formed of two blade rings.
  • a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example. Coupled to the rotor 103 is a generator or work machine (not shown).
  • 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.
  • corrosion products 10 can form on the component.
  • the corrosion products must be removed by the method according to the invention if the component is to be recoated. Possibly. Then cracks are still repaired in the substrate of the component.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the FIG. 7 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a plurality of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 in its entirety as an annular Structured structure, which is positioned around the turbine shaft 103 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of high-temperature-resistant material. Due to the high temperatures in the interior of the combustion chamber 110, a cooling system is additionally provided for the heat shield elements 155 or for their holding elements.
  • the materials of the combustor wall and their coatings may be similar to the turbine blades 120, 130.
  • the combustion chamber 110 is designed in particular for detecting losses of the heat shield elements 155.
  • a number of temperature sensors 158 are positioned between the combustion chamber wall 153 and the heat shield elements 155.
  • 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.
  • With conventional blades 120, 130, in all areas 400, 403, 406 of the blade 120, 130 used massive metallic materials.
  • the blade 120, 130 may be manufactured by a casting process, by a forging process, by a milling process or combinations thereof.
  • FIG. 9 For example, a steam turbine 300, 303 with a turbine shaft 309 extending along a rotation axis 306 is shown.
  • the steam turbine has a high-pressure turbine section 300 and a medium-pressure turbine section 303, each having an inner housing 312 and an outer housing 315 surrounding it.
  • the high-pressure turbine part 300 is designed, for example, in Topfbauart.
  • the medium-pressure turbine section 303 is double-flow. It is also possible for the medium-pressure turbine section 303 to be single-flow.
  • a bearing 318 is arranged between the high-pressure turbine section 300 and the medium-pressure turbine section 303, the turbine shaft 309 having a bearing region 321 in the bearing 318.
  • the turbine shaft 309 is supported on another bearing 324 adjacent to the high pressure turbine sub 300. In the area of this bearing 324, the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed from the outer housing 315 of the medium-pressure turbine section 303 by two further shaft seals 345. Between a high-pressure steam inflow region 348 and a steam outlet region 351, the turbine shaft 309 in the high-pressure turbine section 300 has the high-pressure impeller blade 354, 357. This high-pressure blading 354, 357 with the associated, not closer provided rotor blades a first Beschaufelungs Suite 360.
  • the medium-pressure turbine section 303 has a central Dampfeinström Suite 333 on.
  • the turbine shaft 309 Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetrical shaft shield 363, a cover plate, on the one hand for dividing the steam flow into the two flows of the medium-pressure turbine section 303 and for preventing direct contact of the hot steam with the turbine shaft 309.
  • the turbine shaft 309 has in the medium-pressure turbine section 303 a second blading area 366 with the medium-pressure blades 354, 342.
  • the hot steam flowing through the second blading area 366 flows out of the medium-pressure turbine section 303 from a discharge connection 369 to a downstream low-pressure turbine, not shown.
  • the components of the steam turbine 300, 303 have protective layers and / or corrosion products 10, which are removed by the method according to the invention, before a reprocessing of the components can take place.

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  • 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)

Abstract

Des composants à produits de corrosion sont souvent réutilisés, et le produit de corrosion (10) doit être éliminé. Dans l'état de la technique, ce processus nécessite un temps important en raison du fait que les temps réactionnels avec la produit de corrosion sont souvent importants. Selon l'invention, le produit de corrosion subit un traitement préalable par attaque au sel, afin de produire des surfaces d'attaque importantes de sorte que l'élimination du produit de corrosion (10) peut s'effectuer plus rapidement. Le sulfate de sodium (Na2SO4) et/ou le sulfate de cobalt (CoSO4) est/sont utilisé(s) pour l'attaque au sel.

Claims (23)

  1. Procédé d'élimination d'une partie ( 10 ) à enlever,
    notamment d'un produit ( 10 ) de corrosion,
    d'un élément ( 1 ),
    dans lequel on traite au préalable la partie ( 10 ) à enlever avant un nettoyage final,
    de façon à ce qu'une vitesse d'enlèvement dans le nettoyage final de la partie ( 10 ) à enlever soit plus grande que sans l'endommagement de la partie ( 10 ) à enlever,
    caractérisé en ce que
    l'on produit une surface d'attaque plus grande par une attaque par du sel notamment par un sel fondu de manière à endommager la partie ( 10 ) à enlever,
    en utilisant pour l'attaque par un sel, le sel sulfate de sodium ( Na2SO4 et/ou sulfate de cobalt ( CoSO4 ).
  2. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'on endommage la partie ( 10 ) à enlever de façon à produire une surface d'attaque plus grande.
  3. Procédé suivant la revendication 1 ou 2,
    caractérisé en ce que
    l'on produit des fissures ( 25, 31 ) dans la partie ( 10 ) à enlever,
    qui endommage la partie ( 10 ) à enlever.
  4. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'on produit des délaminations ( 34 ) entre la partie ( 10 ) à enlever sous forme de couche et d'une surface ( 13 ) sur laquelle est disposée la partie ( 10 ) à enlever.
  5. Procédé suivant l'une des revendications 1, 2, 3 ou 4,
    caractérisé en ce que
    l'on dépose une matière ( 16 ) pour l'attaque par un sel sur la partie ( 10 ) à enlever pour endommager la partie ( 10 ) à enlever, et
    en ce que l'on dépose la matière ( 16 ) sous la forme d'une suspension.
  6. Procédé suivant l'une des revendications 1, 2, 3 ou 4,
    caractérisé en ce que
    l'on dépose une matière ( 16 ) pour l'attaque par un sel sur la partie ( 10 ) à enlever pour endommager la partie ( 10 ) à enlever, et
    en ce que l'on met la matière ( 16 ) sous la forme d'une feuille sur la partie ( 10 ) à enlever.
  7. Procédé suivant l'une des revendications 5 ou 6,
    caractérisé en ce que
    l'on échauffe la matière ( 16 ) pour l'attaque par un sel,
    qui est présente sur la partie ( 10 ) à enlever.
  8. Procédé suivant la revendication 7,
    caractérisé en ce que
    l'on échauffe l'élément ( 1 ),
    notamment seulement localement dans la partie ( 10 ) à enlever.
  9. Procédé suivant la revendication 7 ou 8,
    caractérisé en ce que
    l'on effectue l'échauffement de la matière ( 16 ),
    notamment l'échauffement local,
    par une source de lumière, notamment par un laser ( 19 ).
  10. Procédé suivant la revendication 7 ou 8,
    caractérisé en ce que
    l'on produit l'échauffement,
    notamment l'échauffement local,
    par induction électromagnétique.
  11. Procédé suivant la revendication 7 ou 8,
    caractérisé en ce que
    l'on produit l'échauffement,
    notamment l'échauffement local,
    au moyen de micro-ondes.
  12. Procédé suivant la revendication 1,
    caractérisé en ce que
    la partie ( 10 ) à enlever est un produit de corrosion et on ce que l'on élimine par le procédé des produits ( 10 ) de corrosion oxyde d'aluminium ( Al2O3 ) et/ou oxyde de cobalt ( CoO2 ) et/ou oxyde de titane ( TiO2 ).
  13. Procédé suivant l'une des revendications 1, 2, 3, 4 ou 5,
    caractérisé en ce que
    l'on endommage la partie ( 10 ) à enlever par le choc thermique d'un sel fondu.
  14. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'on effectue comme nettoyage final un nettoyage par des ions fluor ( FIC ) de l'élément ( 1 ),
    pour éliminer complètement la partie ( 10 ) à enlever.
  15. Procédé suivant la revendication 1,
    caractérisé en ce que
    dans l'un des derniers stades du procédé on élimine complètement par un traitement à l'acide la partie ( 10 ) à enlever qui est endommagée.
  16. Procédé suivant la revendication 1,
    caractérisé en ce que
    la partie ( 10 ) à enlever est présente sur un substrat ( 4 ) métallique.
  17. Procédé suivant la revendication 16,
    caractérisé en ce que
    le substrat ( 4 ) est un super alliage à base de nickel, de cobalt ou de fer.
  18. Procédé suivant la revendication 1,
    caractérisé en ce que
    la partie ( 10 ) à enlever est présente sous la forme d'une couche sur une couche MCrAlX,
    M représentant au moins un élément du groupe fer, cobalt, nickel,
    tandis que X représente l'yttrium et/ou au moins un élément de terre rare.
  19. Procédé suivant l'une des revendications 1 ou 18,
    caractérisé en ce que
    la partie ( 10 ) à enlever est métallique.
  20. Procédé suivant l'une des revendications 1 ou 18,
    caractérisé en ce que
    la partie ( 10 ) à enlever est céramique.
  21. Procédé suivant l'une des revendications 1, 19 ou 20,
    caractérisé en ce que
    la partie ( 10 ) métallique à enlever, notamment sous forme de couche, a des produits de corrosion.
  22. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'élément ( 1 ) est un élément ( 1 ) d'une turbine à gaz
    ( 100 ) ou à vapeur ( 300, 300 ) notamment une aube ( 120, 130 ) mobile ou directrice ou un revêtement ( 155 ) de chambre de combustion.
  23. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'on effectue le procédé avec un élément ( 1 ) qui doit être retraité.
EP05700980A 2004-01-30 2005-01-17 Procede pour eliminer une couche Not-in-force EP1708829B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07010914A EP1818112A3 (fr) 2004-01-30 2005-01-17 Procédé pour éliminer une couche
EP05700980A EP1708829B1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04002158A EP1559485A1 (fr) 2004-01-30 2004-01-30 Procédé pour l'enlèvement d'une couche
PCT/EP2005/000405 WO2005072884A1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche
EP05700980A EP1708829B1 (fr) 2004-01-30 2005-01-17 Procede pour eliminer une couche

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP07010914A Division EP1818112A3 (fr) 2004-01-30 2005-01-17 Procédé pour éliminer une couche

Publications (2)

Publication Number Publication Date
EP1708829A1 EP1708829A1 (fr) 2006-10-11
EP1708829B1 true EP1708829B1 (fr) 2009-03-11

Family

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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 Before (2)

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

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)

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EP1559485A1 (fr) * 2004-01-30 2005-08-03 Siemens Aktiengesellschaft Procédé pour l'enlèvement d'une couche
DE102004061269A1 (de) * 2004-12-10 2006-06-14 Siemens Ag Verfahren zum Reinigen eines Werkstückes mit Halogenionen
DE102006030364A1 (de) * 2006-06-27 2008-01-03 Siemens Ag Verfahren zum Entfernen einer Schutzbeschichtung von einem Bauteil
KR100840902B1 (ko) 2007-03-20 2008-06-24 주식회사 에이팩 마이크로웨이브를 이용한 광디스크의 반사층 박리장치
PL2147138T3 (pl) 2007-05-24 2015-11-30 Oerlikon Textile Gmbh & Co Kg Zespół mechanizmu rozciągowego, bądź mechanizm rozciągowy, i sposób jego eksploatacji
DE102008005168A1 (de) * 2008-01-19 2009-07-23 Mtu Aero Engines Gmbh Verfahren zum zumindest selektiven Entfernen einer ersten Schicht von einem Triebwerksbauteil
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SG165202A1 (en) * 2009-03-25 2010-10-28 United Technologies Corp Method and apparatus for cleaning a component using microwave radiation
EP2327813A1 (fr) * 2009-11-11 2011-06-01 Siemens Aktiengesellschaft Nettoyage par fluor-ions renforcé de fissures contaminées
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EP2716788A1 (fr) * 2012-10-08 2014-04-09 Siemens Aktiengesellschaft Procédé destiné à supprimer une couche métallique sur un substrat
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
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CN1929931A (zh) 2007-03-14
US20070170150A1 (en) 2007-07-26
EP1818112A2 (fr) 2007-08-15
EP1559485A1 (fr) 2005-08-03
EP1818112A3 (fr) 2007-09-12
EP1708829A1 (fr) 2006-10-11
DE502005006806D1 (de) 2009-04-23
WO2005072884A1 (fr) 2005-08-11

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