EP1674662A1 - Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique - Google Patents

Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique Download PDF

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Publication number
EP1674662A1
EP1674662A1 EP04030732A EP04030732A EP1674662A1 EP 1674662 A1 EP1674662 A1 EP 1674662A1 EP 04030732 A EP04030732 A EP 04030732A EP 04030732 A EP04030732 A EP 04030732A EP 1674662 A1 EP1674662 A1 EP 1674662A1
Authority
EP
European Patent Office
Prior art keywords
electrolyte
nickel
cobalt
alloy
electrolyte according
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Withdrawn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
EP04030732A
Other languages
German (de)
English (en)
Inventor
Ursus Dr. Krüger
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 EP04030732A priority Critical patent/EP1674662A1/fr
Priority to EP05801373A priority patent/EP1807554A2/fr
Priority to AT07008970T priority patent/ATE426733T1/de
Priority to EP07008970A priority patent/EP1840335B1/fr
Priority to EP07008969A priority patent/EP1840334A3/fr
Priority to PCT/EP2005/054917 priority patent/WO2006069816A2/fr
Priority to ES07008970T priority patent/ES2321236T3/es
Priority to DE502005006969T priority patent/DE502005006969D1/de
Publication of EP1674662A1 publication Critical patent/EP1674662A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/045—Alloys based on refractory metals
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • C22C27/06—Alloys based on chromium

Definitions

  • the invention relates to an electrolyte for depositing an alloy according to claim 1 and an electrodeposition process according to claim 23.
  • Electrolytic coating processes use an electrolyte in which the elements to be deposited are either dissolved in a solution or dispersed as powder particles in a solution. However, alloys can be deposited poorly in this way.
  • an electrolyte according to claim 1 by at least the matrix material, i. H. the component of the alloy with the largest relative proportion of the layer to be deposited is dissolved in the electrolyte and further constituents are dispersed as a powder in the electrolyte and deposited according to claim 23.
  • the electrolyte for the electrolytic deposition of an alloy is a solution of at least the element of the matrix material and furthermore contains dispersed powder.
  • Solved means that the component is present as an ion in a solution (water, alcohol, acid, lye, ).
  • the matrix material may be either cobalt or nickel.
  • at least one further element of the alloy may be dissolved in the electrolyte.
  • nickel and cobalt may be dissolved in the electrolyte.
  • the powder containing the further constituents of the alloy may have either chromium or aluminum or chromium and aluminum.
  • the powder may comprise the elements chromium, aluminum and yttrium.
  • the elements chromium, aluminum and yttrium, silicon and / or rhenium may also be present as dispersed powder in the electrolyte.
  • the matrix material consists of nickel or cobalt.
  • the alloy consists, for example, of at least three elements, in particular of at least five elements (for example NiCoCrAlX).
  • the electrolyte contains, for example, at least one of the elements chromium, aluminum as a dispersed powder.
  • melting point depressants such as B, Si, Hf, Zr may be dissolved in the electrolyte or may be present as a powder.
  • coatings based on superalloys can be deposited with the electrolyte according to the invention.
  • the powder contains nor the elements titanium, tantalum, tungsten, molybdenum, niobium, boron, zirconium or carbon.
  • layers can be deposited on a substrate by means of the electrolytes according to the invention.
  • a heat treatment can be carried out in order, for example, to achieve a better bonding of the electrolytically produced layer to the substrate.
  • further metallic and / or ceramic layers can be applied to the electrolytically produced layer.
  • the electrolyte of the invention solves the problem in that the largest proportion (matrix material) of the alloy to be deposited is dissolved and the other elements are present as a powder.
  • the electrolyte according to the invention opens up the possibility of varying the stoichiometry of the alloy during the electrolytic deposition by varying the proportions of powder by constantly increasing, for example by adding powder, the proportion of an alloying element and thus achieving a gradation in the concentration of this alloying element in the layer to be produced.
  • FIG. 1 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine, which extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjoining thereto and an airfoil 406. As a guide blade 130, the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • blades 120, 130 for example, solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; these references are part of the disclosure regarding the superalloy chemical compositions.
  • the blade 120, 130 can in this case by a casting process, also by means of directional solidification, by a forging process, be made by a milling method or combinations thereof.
  • the blades 120, 130 may be coatings against corrosion or oxidation (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, whose chemical compositions are intended to be part of this disclosure. These layers can be applied electrolytically using the method according to the invention.
  • a thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , ie it is not, partially or completely stabilized by yttria 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.
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 2 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged around the rotation axis 102 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 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. These may be solid ceramic stones or alloys with MCrAlX and / or ceramic coatings. The materials of the combustion chamber wall and its coatings may be similar to the turbine blades.
  • Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system.
  • 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. 3 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 Along the rotor 103 follow one another 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, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, 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 relaxes on the rotor blades 120 in a pulse-transmitting manner, so that the 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. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure only longitudinal grains
  • 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 an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium.
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which are intended to be part of this disclosure.
  • MCrAIX On the MCrAIX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , that is, it is not, partially or completely stabilized by yttria 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 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.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Conductive Materials (AREA)
  • Electrolytic Production Of Metals (AREA)
  • Non-Silver Salt Photosensitive Materials And Non-Silver Salt Photography (AREA)
  • Medicinal Preparation (AREA)
  • Preventing Corrosion Or Incrustation Of Metals (AREA)
  • Chemical Treatment Of Metals (AREA)
EP04030732A 2004-12-23 2004-12-23 Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique Withdrawn EP1674662A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP04030732A EP1674662A1 (fr) 2004-12-23 2004-12-23 Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique
EP05801373A EP1807554A2 (fr) 2004-12-23 2005-09-29 Electrolyte destine au depot d'un alliage et procede de depot electrolytique
AT07008970T ATE426733T1 (de) 2004-12-23 2005-09-29 Schicht
EP07008970A EP1840335B1 (fr) 2004-12-23 2005-09-29 Dépôt
EP07008969A EP1840334A3 (fr) 2004-12-23 2005-09-29 Dépôt
PCT/EP2005/054917 WO2006069816A2 (fr) 2004-12-23 2005-09-29 Electrolyte destine au depot d'un alliage et procede de depot electrolytique
ES07008970T ES2321236T3 (es) 2004-12-23 2005-09-29 Capa.
DE502005006969T DE502005006969D1 (de) 2004-12-23 2005-09-29 Schicht

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04030732A EP1674662A1 (fr) 2004-12-23 2004-12-23 Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique

Publications (1)

Publication Number Publication Date
EP1674662A1 true EP1674662A1 (fr) 2006-06-28

Family

ID=34927990

Family Applications (4)

Application Number Title Priority Date Filing Date
EP04030732A Withdrawn EP1674662A1 (fr) 2004-12-23 2004-12-23 Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique
EP07008970A Not-in-force EP1840335B1 (fr) 2004-12-23 2005-09-29 Dépôt
EP05801373A Withdrawn EP1807554A2 (fr) 2004-12-23 2005-09-29 Electrolyte destine au depot d'un alliage et procede de depot electrolytique
EP07008969A Withdrawn EP1840334A3 (fr) 2004-12-23 2005-09-29 Dépôt

Family Applications After (3)

Application Number Title Priority Date Filing Date
EP07008970A Not-in-force EP1840335B1 (fr) 2004-12-23 2005-09-29 Dépôt
EP05801373A Withdrawn EP1807554A2 (fr) 2004-12-23 2005-09-29 Electrolyte destine au depot d'un alliage et procede de depot electrolytique
EP07008969A Withdrawn EP1840334A3 (fr) 2004-12-23 2005-09-29 Dépôt

Country Status (5)

Country Link
EP (4) EP1674662A1 (fr)
AT (1) ATE426733T1 (fr)
DE (1) DE502005006969D1 (fr)
ES (1) ES2321236T3 (fr)
WO (1) WO2006069816A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1793008A1 (fr) * 2005-12-02 2007-06-06 Siemens Aktiengesellschaft Alliage, couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel
CN101352357B (zh) * 2007-07-25 2011-09-28 伊西康内外科公司 带有手动旋转样本桶的活检装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2367833A1 (fr) * 1976-10-15 1978-05-12 Bbc Brown Boveri & Cie Couche anticorrosive pour alliages resistant a la chaleur
EP0484115A1 (fr) * 1990-11-01 1992-05-06 General Electric Company Extrémité abrasive pour aube de turbine
EP0532150A1 (fr) * 1991-09-09 1993-03-17 General Electric Company Revêtements protecteurs consolidés pour super-alliages
US5833829A (en) * 1994-07-22 1998-11-10 Praxair S.T. Technology, Inc. Protective coating
WO2000036180A1 (fr) * 1998-12-16 2000-06-22 Onera (Office National D'etudes Et De Recherches Aerospatiales) PROCEDE POUR FORMER UN REVETEMENT D'ALLIAGE METALLIQUE DE TYPE MCrAlY

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5273712A (en) * 1989-08-10 1993-12-28 Siemens Aktiengesellschaft Highly corrosion and/or oxidation-resistant protective coating containing rhenium
US5582635A (en) * 1990-08-10 1996-12-10 Siemens Aktiengesellschaft High temperature-resistant corrosion protection coating for a component in particular a gas turbine component
US5939204A (en) * 1995-08-16 1999-08-17 Siemens Aktiengesellschaft Article for transporting a hot, oxidizing gas
EP1295969A1 (fr) * 2001-09-22 2003-03-26 ALSTOM (Switzerland) Ltd Procédé pour la croissance d'un revêtement de MCrAlY ainsi qu'un objet revêtu de cet alliage
EP1380672A1 (fr) * 2002-07-09 2004-01-14 Siemens Aktiengesellschaft Composant à haute résistance contre l'oxydation

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2367833A1 (fr) * 1976-10-15 1978-05-12 Bbc Brown Boveri & Cie Couche anticorrosive pour alliages resistant a la chaleur
EP0484115A1 (fr) * 1990-11-01 1992-05-06 General Electric Company Extrémité abrasive pour aube de turbine
EP0532150A1 (fr) * 1991-09-09 1993-03-17 General Electric Company Revêtements protecteurs consolidés pour super-alliages
US5833829A (en) * 1994-07-22 1998-11-10 Praxair S.T. Technology, Inc. Protective coating
WO2000036180A1 (fr) * 1998-12-16 2000-06-22 Onera (Office National D'etudes Et De Recherches Aerospatiales) PROCEDE POUR FORMER UN REVETEMENT D'ALLIAGE METALLIQUE DE TYPE MCrAlY

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
JUN L ET AL: "MICROSTRUCTURE CHARACTERISTICS OF THE NICKEL MATRIX IN ELECTRODEPOSITED NI-PSZ GRADIENT COATING", TRANSACTIONS OF THE INSTITUTE OF METAL FINISHING, INSTITUTE OF METAL FINISHING, LONDON, GB, vol. 76, no. PART 4, July 1998 (1998-07-01), pages 131 - 134, XP000765554, ISSN: 0020-2967 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1793008A1 (fr) * 2005-12-02 2007-06-06 Siemens Aktiengesellschaft Alliage, couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel
WO2007063091A1 (fr) * 2005-12-02 2007-06-07 Siemens Aktiengesellschaft Alliage, couche de protection destinee a proteger un composant contre la corrosion et l'oxydation a haute temperature, et composant
CN101352357B (zh) * 2007-07-25 2011-09-28 伊西康内外科公司 带有手动旋转样本桶的活检装置

Also Published As

Publication number Publication date
EP1840334A3 (fr) 2007-11-14
EP1840335A3 (fr) 2007-11-14
WO2006069816A2 (fr) 2006-07-06
EP1840334A2 (fr) 2007-10-03
EP1840335B1 (fr) 2009-03-25
EP1807554A2 (fr) 2007-07-18
ES2321236T3 (es) 2009-06-03
WO2006069816A3 (fr) 2007-08-23
ATE426733T1 (de) 2009-04-15
EP1840335A2 (fr) 2007-10-03
DE502005006969D1 (de) 2009-05-07

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