EP1934387B1 - Procede pour retirer un revetement present sur un composant de turbine a gaz - Google Patents

Procede pour retirer un revetement present sur un composant de turbine a gaz Download PDF

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Publication number
EP1934387B1
EP1934387B1 EP06805384.2A EP06805384A EP1934387B1 EP 1934387 B1 EP1934387 B1 EP 1934387B1 EP 06805384 A EP06805384 A EP 06805384A EP 1934387 B1 EP1934387 B1 EP 1934387B1
Authority
EP
European Patent Office
Prior art keywords
bath
layer
turbine component
remove
gas turbine
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.)
Expired - Fee Related
Application number
EP06805384.2A
Other languages
German (de)
English (en)
Other versions
EP1934387A1 (fr
Inventor
Karl-Heinz Manier
Thomas Uihlein
Carl-Stefan Thöne
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.)
Solut Chemie AB GmbH
MTU Aero Engines AG
Original Assignee
Solut Chemie AB GmbH
MTU Aero Engines 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 Solut Chemie AB GmbH, MTU Aero Engines AG filed Critical Solut Chemie AB GmbH
Priority to PL06805384T priority Critical patent/PL1934387T3/pl
Publication of EP1934387A1 publication Critical patent/EP1934387A1/fr
Application granted granted Critical
Publication of EP1934387B1 publication Critical patent/EP1934387B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • 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
    • 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
    • C23G1/02—Cleaning or pickling metallic material with solutions or molten salts with acid solutions
    • C23G1/10—Other heavy metals
    • C23G1/106—Other heavy metals refractory metals
    • 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 for stripping a gas turbine component according to.
  • Components of a gas turbine such as the rotor blades, are provided with special anti-wear coatings to provide oxidation resistance, corrosion resistance, or erosion resistance on the surfaces.
  • the components of gas turbines are subject to wear during operation of the same or can be damaged in any other way. In order to repair damage, it is generally necessary to remove or remove the wear protection coating from the component to be repaired in regions, partially or even in total.
  • the removal or removal of coatings is also referred to as stripping. In the stripping process, a distinction is made between those in which stripping takes place by mechanical means, by chemical means or by electrochemical means.
  • wear protection coatings are designed as so-called multilayer coatings consisting of several alternately applied to the gas turbine component layers. So it is e.g. it is possible that a wear protection coating designed as a multilayer coating comprises a relatively soft, metallic layer and a relatively hard, ceramic layer, which are applied to the gas turbine component repeatedly alternately in succession. Furthermore, wear-resistant coatings are known in practice, in which more than two different layers are alternately applied successively to the gas turbine component, e.g.
  • Multilayer coatings of four alternatingly applied successively to the gas turbine component layers namely a first, adapted to the material composition of the gas turbine component metallic and thus relatively soft layer, a relatively soft, metallic layer of a metal alloy material, a third, relatively hard graded metal Ceramic layer and a fourth relatively hard, ceramic layer.
  • the publication US 5,972,424 A discloses a method for stripping turbine components.
  • the method comprises a treatment in an alkaline solution for removing the thermal protective layer and an acid treatment for removing the metallic adhesive layer. This coating also provides protection against wear.
  • the publication US 2005/152805 A1 discloses a method for refurbishment Turbine components with a wear protection coating.
  • the upper wear protection layer is removed mechanically, a metallic diffusion layer is chemically removed.
  • the present invention is based on the problem to provide a novel method for stripping a gas turbine component.
  • the gas turbine component is alternately positioned in two different chemical baths, a first bath excluding removal of the or each relatively hard ceramic layer and a second bath excluding removal of the or each relatively soft metallic layer the wear protection coating is used.
  • the component with a multilayer wear protection coating alternately in different baths, wherein the different baths selectively ablate either a relatively hard, ceramic layer or a relatively soft, metallic layer of the wear protection coating to be removed.
  • a method is proposed for the first time, with the aid of which gas turbine components can be effectively freed from a so-called multilayer wear protection coating without the risk of damage to the gas turbine component.
  • the first bath which serves solely to remove the or each relatively hard ceramic layer is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein.
  • the first bath may comprise a nitrogen-containing organic compound.
  • the first bath has a pH between 3 and 5.
  • the second bath which serves exclusively for removing the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or alkaline earth hydroxide with silicon and / or phosphorus contained therein, the second bath having a pH of has at least 12.
  • the first bath is a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids.
  • the first bath may have 1 g / L to 10 g / L of a nitrogen-containing organic compound.
  • the second bath is preferably a 2% to 50% alkali hydroxide solution containing 1 g / l to 200 g / l of silicon and / or 10 g / l to 100 g / l of phosphorus.
  • the gas turbine component is positioned to remove a relatively hard, ceramic layer in the first bath at a temperature between 10 ° C and 70 ° C for a period of 1-60 minutes per 1 nm thickness of the layer to be removed .
  • the gas turbine component is positioned in the second bath at a temperature between 20 ° C and 150 ° C for a period of 10-120 minutes per 1 nm thickness of the layer to be removed.
  • the inventive method is used for stripping of coated with multilayer wear protection coatings gas turbine components, the multilayer wear protection coatings from at least two different, alternately successively arranged layers, namely alternately arranged one behind the other ceramic, relatively hard layers and metallic, relatively soft layers are formed.
  • the method is used for stripping gas turbine components, on which a wear protection coating of four different, alternately successive layers are applied.
  • the first layer is preferably formed of titanium or palladium or platinum.
  • a second layer is applied, which is preferably formed by a TiCrAl material.
  • the third layer is followed by a grading layer, which is formed from a TiAlN1-x material.
  • the third layer is followed by a fourth layer of titanium aluminum nitride (TiAlN).
  • TiAlN titanium aluminum nitride
  • a first bath exclusively removes the or each relatively hard, ceramic layer and a second bath solely for removing the or any relatively soft, metallic layer of the wear-resistant coating.
  • the first bath which serves exclusively to remove the or each relatively hard ceramic layer, is an acid of a hydrogen peroxide solution and at least one sodium salt and / or potassium salt of an organic acid contained therein.
  • the first bath may comprise a nitrogen-containing organic compound.
  • the first bath is formed from a 5% to 50% hydrogen peroxide solution with 10 g / l to 100 g / l sodium salts of organic acids.
  • the pH of this first bath is between 3 and 5.
  • the second bath which serves exclusively to remove the or each relatively soft, metallic layer, is a base of an aqueous solution of at least one alkali hydroxide or an alkaline earth hydroxide with silicon and / or phosphorus contained therein.
  • the second bath is a base of a 2% to 50% alkali hydroxide solution with 1 g / l to 200 g / l of silicon compounds and 10 g / l to 100 g / l of phosphorus compounds.
  • the pH of this second bath is at least 12.
  • the first bath is an acid of a 10% hydrogen peroxide solution with 70 g / l of ethylenediaminetetraacetate sodium salt and 20 g / l of phenol-4-sulfonic acid sodium salt and a 20% in the second bath Alkali hydroxide solution with 100 g / l silicon compounds and 50 g / l phosphorus compounds.
  • the gas turbine component is alternately positioned in the first bath and the second bath, with the first bath selectively removing only the hard, ceramic layers and the second bath only serves to remove the soft, metallic layers.
  • a gas turbine component is accordingly positioned in the first bath, for which purpose the first bath has a temperature between 10 ° C and 70 ° C.
  • the temperature of this bath is in the order of the room temperature, ie at about 20 ° C.
  • the gas turbine component is placed in this bath for a period of 1 to 60 minutes per 1 nm thickness of the ceramic, relatively hard layer to be removed.
  • the gas turbine component is positioned in the second bath, the temperature of the second bath being between 20 ° C and 150 ° C, preferably the temperature of the second bath is 80 ° C.
  • the component is positioned in the second bath for a period between 10 minutes and 120 minutes per 1 nm thickness of the metallic, relatively soft layer to be removed. Between the repositioning of a gas turbine component to be stripped between the two baths, the gas turbine component can be purged.
  • wear protection coatings of gas turbine components can be effectively removed without the risk of damage to the gas turbine component.
  • wear protection coatings can be completely or even partially removed from a gas turbine component, with partial removal of the wear protection coatings either submerged in the baths by a gas turbine component, or areas of the gas turbine component not to be stripped prior to immersion in the corresponding bath with a protective layer of z. B. wax are provided.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • General Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • ing And Chemical Polishing (AREA)
  • Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Detergent Compositions (AREA)

Claims (8)

  1. Procédé pour retirer un revêtement sur un composant de turbine à gaz, notamment pour enlever totalement ou partiellement un revêtement de protection contre l'usure multicouches sur la surface du composant de turbine à gaz, dans lequel le revêtement de protection contre l'usure comprend des couches céramiques relativement dures et des couches métalliques relativement molles, avec respectivement au moins une première couche de titane, de palladium ou de platine, une deuxième couche d'un matériau de TiCrAl, une troisième couche d'un matériau de TiAlN(1-x) et une quatrième couche de TiAlN, dans lequel le composant de turbine à gaz est placé tour à tour dans deux bains chimiques différents pour retirer le revêtement de protection contre l'usure multicouches, un premier bain servant exclusivement à retirer toute couche céramique relativement dure et un deuxième bain servant exclusivement à retirer toute couche métallique relativement molle du revêtement de protection contre l'usure, caractérisé en ce que
    le premier bain, qui sert exclusivement à retirer toute couche céramique relativement dure est un acide constitué d'une solution de peroxyde d'hydrogène et d'au moins un sel sodique et/ou sel potassique d'un acide organique présent dans celle-ci, et le deuxième bain, qui sert exclusivement à retirer toute couche métallique relativement molle est une base constituée d'une solution aqueuse d'au moins un hydroxyde alcalin ou un hydroxyde d'alcalino-terreux renfermant du silicium et/ou du phosphore.
  2. Procédé selon la revendication 1, caractérisé en ce que le premier bain est une solution de 5 % à 50 % de peroxyde d'hydrogène avec 10 g/litre à 100 g/litre de sels sodiques d'acides organiques.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que le premier bain présente un pH situé entre 3 et 5.
  4. Procédé selon l'une des revendications 1 à 3, caractérisé en ce que, pour retirer une couche céramique relativement dure, le composant de turbine à gaz est placé dans un premier bain à une température située entre 10°C et 70 °C pendant une durée de 1 à 60 minutes par 1 nm d'épaisseur de la couche à retirer.
  5. Procédé selon l'une des revendications 1 à 4, caractérisé en ce que le deuxième bain est une solution de 2 % à 50 % d'hydroxyde alcalin avec 1 g/litre à 200 g/litre de silicium et/ou 10 g/litre à 100 g/litre de phosphore.
  6. Procédé selon l'une des revendications 1 à 5, caractérisé en ce que le deuxième bain présente un pH supérieur à 12.
  7. Procédé selon l'une des revendications 1 à 6, caractérisé en ce que, pour retirer une couche métallique relativement molle, le composant de turbine à gaz est placé dans un deuxième bain à une température située entre 20°C et 150°C pendant une durée de 10 à 120 minutes par 1 nm d'épaisseur de la couche à retirer.
  8. Procédé selon l'une des revendications 1 à 7, caractérisé en ce que le premier bain est un acide constitué d'une solution à 10 % de peroxyde d'hydrogène avec 70 g/litre d'éthylènediamine tétraacétate sel sodique et 20 g/litre d'acide phénol-4-sulfonique sel sodique.
EP06805384.2A 2005-10-14 2006-10-10 Procede pour retirer un revetement present sur un composant de turbine a gaz Expired - Fee Related EP1934387B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL06805384T PL1934387T3 (pl) 2005-10-14 2006-10-10 Sposób odwarstwiania elementu turbiny gazowej

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005049249.5A DE102005049249B4 (de) 2005-10-14 2005-10-14 Verfahren zur Entschichtung eines Gasturbinenbauteils
PCT/DE2006/001766 WO2007041998A1 (fr) 2005-10-14 2006-10-10 Procede pour retirer un revetement present sur un composant de turbine a gaz

Publications (2)

Publication Number Publication Date
EP1934387A1 EP1934387A1 (fr) 2008-06-25
EP1934387B1 true EP1934387B1 (fr) 2015-06-17

Family

ID=37605754

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06805384.2A Expired - Fee Related EP1934387B1 (fr) 2005-10-14 2006-10-10 Procede pour retirer un revetement present sur un composant de turbine a gaz

Country Status (6)

Country Link
US (1) US9212555B2 (fr)
EP (1) EP1934387B1 (fr)
JP (1) JP2009511804A (fr)
DE (1) DE102005049249B4 (fr)
PL (1) PL1934387T3 (fr)
WO (1) WO2007041998A1 (fr)

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DE102010034336B4 (de) 2010-08-14 2013-05-29 Mtu Aero Engines Gmbh Verfahren und Vorrichtung zum Entfernen einer Schicht von einer Oberfläche eines Körpers
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US11661646B2 (en) 2021-04-21 2023-05-30 General Electric Comapny Dual phase magnetic material component and method of its formation
US11926880B2 (en) 2021-04-21 2024-03-12 General Electric Company Fabrication method for a component having magnetic and non-magnetic dual phases

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Also Published As

Publication number Publication date
US20090302004A1 (en) 2009-12-10
JP2009511804A (ja) 2009-03-19
US9212555B2 (en) 2015-12-15
EP1934387A1 (fr) 2008-06-25
PL1934387T3 (pl) 2016-03-31
WO2007041998A1 (fr) 2007-04-19
DE102005049249B4 (de) 2018-03-29
DE102005049249A1 (de) 2007-04-19

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