(19)
(11)EP 3 080 338 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
03.10.2018 Bulletin 2018/40

(21)Application number: 14870576.7

(22)Date of filing:  04.12.2014
(51)Int. Cl.: 
C25D 3/02  (2006.01)
C25D 3/66  (2006.01)
C25D 3/56  (2006.01)
C22F 1/10  (2006.01)
F01D 5/28  (2006.01)
C25D 5/18  (2006.01)
C25D 3/04  (2006.01)
C25D 7/00  (2006.01)
C25D 17/10  (2006.01)
C22C 19/05  (2006.01)
C25D 5/12  (2006.01)
C25D 5/50  (2006.01)
(86)International application number:
PCT/US2014/068580
(87)International publication number:
WO 2015/088876 (18.06.2015 Gazette  2015/24)

(54)

NICKEL-CHROMIUM-ALUMINUM COMPOSITE BY ELECTRODEPOSITION

NICKEL-CHROM-ALUMINIUM-VERBUNDSTOFF DURCH ELEKTROLYTISCHE ABSCHEIDUNG

COMPOSITE DE NICKEL-CHROME-ALUMINIUM PAR ÉLECTRODÉPOSITION


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 10.12.2013 US 201361914307 P

(43)Date of publication of application:
19.10.2016 Bulletin 2016/42

(73)Proprietors:
  • Chen, Lei
    Hartford, Connecticut 06103 (US)
  • Brindley, William J.
    Hartford, Connecticut 06103 (US)
  • Kinstler, Monika D.
    Hartford, Connecticut 06103 (US)

(72)Inventors:
  • Chen, Lei
    Hartford, Connecticut 06103 (US)
  • Brindley, William J.
    Hartford, Connecticut 06103 (US)
  • Kinstler, Monika D.
    Hartford, Connecticut 06103 (US)

(74)Representative: Dehns 
St. Brides House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A1- 2 623 644
CN-C- 100 342 059
US-A- 3 917 517
US-A- 4 461 680
US-A1- 2004 054 231
EP-A1- 2 623 644
US-A- 3 338 733
US-A- 3 998 603
US-A1- 2002 130 047
US-A1- 2008 017 280
  
  • Gengan Saravanan ET AL: "Electrodeposition of Fe-Ni-Cr alloy from Deep Eutectic System containing Choline chloride and Ethylene Glycol", Int. J. Electrochem. Sci. International Journal, January 2011 (2011-01), pages 1468-1478, XP055384643, Retrieved from the Internet: URL:http://www.electrochemsci.org/papers/v ol6/6051468.pdf [retrieved on 2017-06-22]
  • ANDREW P. ABBOTT ET AL: "Ionic Liquid Analogues Formed from Hydrated Metal Salts", CHEMISTRY - A EUROPEAN JOURNAL, vol. 10, no. 15, 6 August 2004 (2004-08-06), pages 3769-3774, XP055027767, ISSN: 0947-6539, DOI: 10.1002/chem.200400127
  
Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


Description

FIELD OF USE



[0001] The present disclosure relates to a composite including nickel-chromium alloy and aluminum, and alloys or compounds formed by nickel, chromium and aluminum, and more particularly to a nickel-chromium-aluminum (Ni-Cr-Al) alloy applied to gas turbine parts for wall restoration and bond coat, a method for electrodepositing the Ni-Cr-Al alloy and associated heat treatment, and coated articles.

BACKGROUND



[0002] High and low pressure turbine parts including turbine vanes or airfoils are made of nickel based superalloys. These components are protected against the high temperature environment by a thermal barrier coating (TBC). In the TBC, a bond coat disposed in between the top oxide layer and the substrate superalloy provides an aluminum reservoir, which supply aluminum diffusing outwards to form protective α-A12O3, an adherent thermally grown oxide (TGO). Thus, the bond coat is critical for protecting gas turbine components from high temperature oxidation. Like aluminum, chromium tends to form dense oxide chromia in a high temperature environment, providing hot corrosion protection. These elements allow the parts made from nickel alloys to perform well in gas turbine engines.

[0003] Turbine vanes are occasionally removed from service due to the loss of wall thickness during such repair processes as coating stripping, recoating, grit blast cleaning, and chemical processing which typically remove some base metal and often reduce component wall thicknesses below the required minimum thickness.

[0004] Thinned turbine vanes or airfoils are either replaced with new parts or scrapped unless the lost wall thickness is restored by adding metal materials that include key elements (e.g., Cr and Al) lost during the repair processes.

[0005] Accordingly, it is desirable to restore the lost wall thickness of turbine vanes or airfoils by providing a metal coating layer that includes key elements (e.g., Cr and Al) lost during the repair processes to increase the number of repair cycles for the vanes or airfoils.

[0006] US3998603 describes a protective coating for nickel-based and chromium-based superalloys.

[0007] US2008/017280 describes a process for repairing a metal component.

[0008] EP2623644 describes a method for producing a NiCrAlHf coating on a superalloy substrate comprising the steps of electroplating Ni from an aqueous nickel chloride bath, electroplating Cr from a chromic acid bath, electroplating Al alloyed with Hf from an AlCl3 and HfCl4-containing ionic liquid bath and heat treating the plated substrate.

SUMMARY



[0009] The present disclosure relates to a composite including nickel-chromium alloy and aluminum, and alloys or compounds formed by nickel, chromium-and aluminum applied to gas turbine components for wall restoration or enhanced bond coat. Specifically, Ni-Cr alloy and Al are sequentially electro-deposited from environmentally benign ionic liquid chemicals. The Ni-Cr-Al composite is subsequently heat-treated to form a diffused Ni-Cr-Al alloy having a composition that mimics the main chemistry of the base alloy, e.g., Ni-based superalloy. The diffused Ni-Cr-Al alloy allows to restore materials lost during the repair processes, and contributes to prolong the lifetime of the turbine parts that are subject to high temperature environment and repeated repair processes.

[0010] Described herein, a coated article includes a turbine component and a Ni-Cr alloy and an Al deposit coated on the turbine component, wherein the Ni-Cr-Al composite alloy includes from 2 to 50 wt% chromium, from 0.1 to 6 wt% aluminum, and remaining nickel, and wherein the Ni-Cr-Al composite is heat-treated to form a diffused Ni-Cr-Al alloy that includes an aluminum compound (aluminides) formed by nickel and aluminum and to restore materials lost during repair processes of the turbine component.

[0011] According to an aspect of the present invention, a method for forming a nickel-chromium-aluminum (Ni-Cr-Al) composite on a turbine component is disclosed. The method includes providing a first plating bath for Ni-Cr alloy deposition, which is made from a solution including a solvent, a surfactant, and an ionic liquid (deep eutectic solvent), including choline chloride, nickel chloride, and chromium chloride, wherein a molar ratio of the choline chloride to chromium chloride ranges from 0.5 to 3.5 and the solvent comprises from 5 to 80 vol.% relative to a mixture of the choline chloride and metal chlorides including the nickel and chromium chlorides.

[0012] The method further includes electrodepositing a Ni-Cr alloy on the turbine component coupled to a cathode by providing an external supply of current to the cathode and an anode in the first plating bath. In addition, the method includes providing a second plating bath made from an ionic liquid including Lewis acidic 1-ethyl-3-methylimidazolium chloride or 1-butyl-3-methylimidazolium chloride and an aluminum compound such aluminum chloride (AlCl3), and electrodepositing an aluminum (Al) onto the Ni-Cr alloy in the second plating bath. The method further includes heat-treating the electrodeposited composite Ni-Cr alloy and Al layer at a high temperature to form a diffused Ni-Cr-Al alloy that includes an aluminum compound primarily formed between nickel and aluminum, and to restore materials lost during repair processes of the turbine component.

[0013] The details of one or more embodiments of the present disclosure and other benefits are set forth in the accompanying drawings and the description below. Other features, objects, and advantages of the present invention will be apparent from the description and drawings, and from the claims.

BRIEF DESCRIPTION OF THE FIGURES



[0014] 

Fig. 1 illustrates an example of a plating bath filled with an electrolytic solution for electrodepositing either a Ni-Cr alloy or aluminum on a turbine component according to an aspect of the present disclosure.

Fig. 2 is a cross-sectional view of a Ni-Cr alloy electrodeposited on a metal substrate in a choline chloride-mixed metal chlorides solution.

Fig. 3 is a flow chart of a Ni-Cr-Al composite layer deposition process of the present disclosure.

Fig. 4A is a schematic cross-sectional view of a diffused Ni-Cr-Al composite alloy coated on a turbine component.

Fig. 4B is a micrograph of a diffused Al coated Ni superalloy.



[0015] The drawings depict various preferred embodiments of the present invention for purposes of illustration only. One skilled in the art will readily recognize from the following discussion that alternative embodiments of the structures and methods illustrated herein may be employed without departing from the principles of the invention described herein.

DETAILED DESCRIPTION



[0016] Fig. 1 illustrates an example of a plating bath filled with an electrolytic solution for electrodepositing a Ni-Cr alloy or aluminum on a turbine component according to an aspect of the present disclosure. A turbine component 104 which is to be plated with a Ni-Cr alloy and aluminum respectively is pre-treated prior to electrodeposition. A pre-treatment is typically performed to remove grease, oil, oxides and debris from the turbine component by mechanical abrasion, acid or alkaline etching, and/or electro-etching followed by surface activation, but is not specifically limited to the above processing steps and specified sequence.

[0017] Referring now to Fig. 1, there is provided a plating bath 102 containing an electrolytic solution that includes a room temperature ionic liquid including choline chloride, nickel chloride, chromium chloride, solvents, and surfactants like anionic, cationic, or Zwitterionic (amphoteric) surfactants. One of the surfactants includes one of more species of a sodium dodecyl sulfate, fluorosurfactants, cetyl trimethylammonium bromide (CTAB), or cetyl trimethyammonium chloride (CTAC). It is noted that the choline chloride based processing is low-cost and environmentally friendly. In one embodiment, a molar ratio of the choline chloride and chromium chloride ranges from 0.5 to 3.5 , and polar aprotic and polar protic solvents are used to adjust the viscosity and conductivity of the plating bath 102 to attain a high quality Ni-Cr alloy coating.

[0018] Specifically, protic solvents are preferred due to their ability to donate hydrogen bonds. The solvents further include formic acid, citric acid, Isopropanol (IPA), water, acetic acid, and ethylene glycol. In the embodiment, preferred solvent content is from 10 to 80 vol% relative to the mixture of choline chloride and metal chlorides including nickel and chromium chlorides.

[0019] Referring to Fig. 1, an external supply of current is provided to an anode 106 and a cathode which is a turbine component 104 to be plated with Ni and Cr. The current can be a direct current or an alternating current including a pulse or pulse reverse current (not shown). The amount of current supplied can be controlled during the electrodeposition to achieve a desired coating composition, density, and morphology.

[0020] When the current is supplied, the metal (Ni and/or Cr) at the anode is oxidized from the zero valence state to form cations with a positive charge. These cations, generally forming complexes with the anions in the solution, are reduced at the cathode to produce metallic deposit. The result is the reduction of Ni and Cr species from the electrolytic solution onto the turbine component to be restored. The turbine component 104 is a cathode during electrodeposition. The electrodeposition inevitably decomposes water in the bath 102, and thus the solution in the bath can be replenished to maintain consistent deposition quality.

[0021] The anode 106 includes a Ni-Cr alloy anode, a Ni and/or Cr anode, or any combination of these materials that can be chosen to satisfy different requirements. An insoluble catalytic anode (catalyzing oxygen evolution electrode) is preferred, but the type of anode used is not specifically limited to the above anode. A second layer of aluminum is deposited from a different plating bath, where the anode is pure aluminum. Aluminum electrodeposition is conducted in a water free environment and has been known to approach 100% efficiency because both hydrogen evolution and oxygen evolution are avoided.

[0022] In one embodiment, the Ni-Cr alloy includes from 2 to 50 wt% chromium and a remaining weight percentage of nickel. In a preferred embodiment, the Ni-Cr alloy comprises from 8 to 20 wt% chromium, and a remaining weight percentage of nickel. The electrodeposited Ni-Cr alloy is thicker than at least 10 µm. In a preferred embodiment, the electrodeposited Ni-Cr alloy is thicker than 125µm. The top aluminum layer can vary in thickness, ranging from 2 µm to more than 125µm.

[0023] Fig. 2 is a cross-sectional view of the Ni-Cr alloy 202 formed on a metal substrate 200 in a choline chloride-mixed metal chlorides solution. Referring to Fig. 2, a Ni-Cr coating thicker than about 70 µm is formed on the substrate 200. The Ni-Cr coating 202 and aluminum deposit may be applied directly to a surface of a turbine component which is formed from a wide range of metallic materials including, but not limited to, a single crystal nickel-based superalloy, and the copper substrate 200 represents a turbine component. The Ni-Cr aluminum composite 202 coated on a turbine component is subject to a post heat-treatment to homogenize the composition and add wall thickness back to the turbine component and replenish chromium and aluminum lost during the repair of the component.

[0024] Fig. 3 is a process flow chart of applying a Ni-Cr aluminum composite layer described in the present disclosure. Typically, a turbine component to be coated with a Ni-Cr-Al composite layer is pre-treated prior to the electrodeposition to remove foreign materials like debris, oxides and grease/oil from its surface. A method for electrodepositing a nickel-chromium-aluminum (Ni-Cr-Al) alloy on a turbine component begins at step 300 where a first plating bath filled with a solution is provided. The solution includes a solvent, a surfactant, and an ionic liquid including choline chloride, nickel chloride, and chromium chloride, wherein a molar ratio of the choline chloride to chromium chloride ranges from 0.5 to 3.5, and the solvent comprises from 5 to 80 vol.% relative to a mixture of the choline chloride and metal chlorides including the nickel and chromium chlorides, as disclosed above with reference to Fig. 1.

[0025] At step 302, electrodepositing a Ni-Cr alloy on the turbine component is performed. An external supply of current is provided to a cathode and an anode in the first plating bath. The turbine component is the cathode, and a metal source is the anode. The component coated with Ni-Cr alloy is then rinsed and dried and prior to aluminum deposition. Additional surface preparation required for aluminum deposition is also performed. At step 304, a second plating bath filled with an ionic liquid including Lewis acidic 1-ethyl-3-methylimidazolium chloride or l-butyl-3-methylimidazolium chloride and an aluminum salt is provided for aluminum deposition on the Ni-Cr alloy coated component. At step 306, electrodepositing aluminum (Al) onto the Ni-Cr alloy is performed in the second plating bath to form a Ni-Cr-Al composite on the turbine component. Once the Ni-Cr-Al composite is formed on the turbine component, at step 308, a post heat-treatment of the Ni-Cr-Al alloy at 1100 °C or at a higher temperature is applied to the coated article to homogenize the composition, to form alloys and intermetallic compounds, and to restore key materials lost during previous repair processes or service of the turbine component, as shown in Figs. 4A and 4B.

[0026] Fig. 4A is a cross-sectional view of a diffused Ni-Cr-Al alloy coated on a turbine component. The coated article 400 comprises a turbine component 402 which is typically made of Ni-based superalloy, a Ni-Cr alloy 404, a Ni-Cr-Al zone 406, an Al coating 408, and a bond coat 410 which is typically re-applied after the dimensional restoration of the turbine component.

[0027] The coated article 400 is subject to a post heat-treatment at a high temperature as described above to form a diffused Ni-Cr-Al alloy 404/406/408. Referring to Fig. 4, aluminum (Al) diffuses from Al coating 408 to Ni-Cr alloy 404 to form a Ni-Cr-Al zone 406, chromium (Cr) diffuses from the Ni-Cr alloy 404 to the Al coating 408, and Ni and/or Cr from the Ni-Cr alloy 404 diffuses into bond coat 410 and turbine component 402, respectively, to homogenize the composition, to form an aluminum compound between nickel and aluminum, and to restore materials lost during previous repair processes of the turbine component. Fig. 4B is a micrograph of an Al deposit 420 on a Ni superalloy 422 before heat-treatment, and a diffused Al coated Ni superalloy 424 after heat-treatment at a high temperature.

[0028] In one embodiment, the Ni-Cr-Al composite includes from 2 to 50 wt% chromium, from 0.1 to 6 wt% aluminum, and a remaining weight percentage of nickel. In the embodiment, the electrodeposited Ni-Cr-Al alloy is thicker than 10 µm. In a preferred embodiment, the Ni-Cr-Al alloy includes from 8 to 20 wt% chromium, from 0.1 to 6 wt% aluminum, and a remaining balance of nickel. In the preferred embodiment, the electrodeposited Ni-Cr-Al composite is thicker than 125 µm. The coated article includes turbine vanes, rotor blades, or stators.

[0029] It is to be understood that the disclosure of the present invention is not limited to the illustrations described and shown herein, which are deemed to be merely illustrative of the best modes of carrying out the invention, and which are susceptible to modification of form, size, arrangement of parts, and details of operation. The disclosure of the present invention rather is intended to encompass all such modifications which are within the scope of the invention as defined by the following claims.


Claims

1. A method for forming a nickel-chromium-aluminum (Ni-Cr-Al) composite on a turbine component, the method comprising:

providing a turbine component which has lost materials during repair processes;

providing a first plating bath filled with a solution including a solvent, a surfactant, and an ionic liquid including choline chloride, nickel chloride, and chromium chloride, wherein a molar ratio of the choline chloride to chromium chloride ranges from 0.5 to 3.5, and the solvent comprises from 5 to 80 vol.% relative to a mixture of the choline chloride and metal chlorides including the nickel and chromium chlorides;

electrodepositing a Ni-Cr alloy on the turbine component coupled to a cathode by providing an external supply of current to the cathode and an anode in the first plating bath;

providing a second plating bath filled with an ionic liquid including Lewis acidic 1-ethyl-3-methylimidazolium chloride or 1-butyl-3-methylimidazolium chloride and an aluminum salt;

electrodepositing an aluminum (Al) onto the Ni-Cr alloy in the second plating bath; and

heat-treating the electrodeposited Ni-Cr-Al composite layer at a high temperature to form a diffused Ni-Cr-Al alloy such that an aluminum compound is formed between aluminum and nickel and to restore materials lost during the repair processes of the turbine component.


 
2. The method of claim 1 further comprising pre-treating the turbine component to remove foreign materials and oxides from the turbine component.
 
3. The method according to claim 1, wherein the temperature is 1100°C or higher.
 
4. The method according to claim 1, wherein the anode is a non-consumable anode to deposit the Ni-Cr alloy, and/or wherein the anode is a Ni-Cr alloy anode, a Ni anode, or a Cr anode to deposit the Ni-Cr alloy.
 
5. The method according to claim 1, wherein the current is a direct current to deposit the Ni-Cr alloy, or wherein the current is an alternating current to deposit the Ni-Cr alloy.
 
6. The method according to claim 1 further comprising providing a bond coat on the Ni-Cr-AI composite after the heat-treating is done.
 
7. The method according to claim 1, wherein the solvent comprises a formic acid, a citric acid, an isopropanol (IPA), a water, an acetic acid, and ethylene glycol.
 
8. The method according to claim 1, wherein the surfactant is anionic, cationic, or amphoteric surfactant, preferably wherein the surfactant is chosen from a sodium dodecyl sulfate, fluorosurfactants, cetyl trimethylammonium bromide (CTAB), or cetyl trimethyammonium chloride (CTAC).
 
9. The method according to claim 1, wherein the Ni-Cr alloy comprises from 2 to 50 wt% chromium and a remaining balance of nickel, preferably wherein the Ni- Cr alloy comprises from 8 to 20 wt% chromium and a remaining balance of nickel.
 
10. The method according to claim 1, wherein the Ni-Cr alloy is thicker than 125 µm.
 


Ansprüche

1. Verfahren zum Ausbilden eines Nickel-Chrom-Aluminium-(Ni-Cr-Al)-Verbundstoffs auf einem Turbinenbauteil, wobei das Verfahren Folgendes umfasst:

Bereitstellen eines Turbinenbauteils, bei dem während Reparaturvorgängen Materialien verloren gegangen sind;

Bereitstellen eines ersten Galvanisierbads, das mit einer Lösung gefüllt ist, die ein Lösungsmittel, eine oberflächenaktive Substanz und eine ionische Flüssigkeit umfasst, die Cholinchlorid, Nickelchlorid und Chromchlorid umfasst, wobei ein Molverhältnis von Chloinchlorid zu Chromchlorid von 0,5 bis 3,5 reicht und wobei das Lösungsmittel von 5 bis 80 Vol.-% in Bezug auf eine Mischung von Cholinchlorid und Metallchloriden, die die Nickel- und Chromchloride umfassen, umfasst;

elektrolytische Abscheidung einer Ni-Cr-Legierung auf das Turbinenbauteil, das an eine Kathode gekoppelt ist, durch Bereitstellen einer externen Stromversorgung zur Kathode und einer Anode im ersten Galvanisierbad;

Bereitstellen eines zweiten Galvanisierbads, das mit einer ionischen Flüssigkeit gefüllt ist, die Lewis-saures 1-Ethyl-3-methylimidazoliumchlorid oder 1-Butyl-3-methylimidazoliumchlorid und ein Aluminiumsalz umfasst;

elektrolytische Abscheidung eines Aluminiums (Al) auf die Ni-Cr-Legierung im zweiten Galvanisierbad; und

Wärmebehandeln der elektrolytisch abgeschiedenen Ni-Cr-Al-Verbundstoffschicht bei einer hohen Temperatur, um eine Ni-Cr-Al-Diffusionslegierung zu bilden, so dass eine Aluminiumverbindung zwischen Aluminium und Nickel ausgebildet wird, und um Materialien, die während der Reparaturvorgänge des Turbinenbauteils verloren gegangen sind, wiederherzustellen.


 
2. Verfahren nach Anspruch 1, weiter umfassend das Vorbehandeln des Turbinenbauteils, um Fremdstoffe und Oxide vom Turbinenbauteil zu entfernen.
 
3. Verfahren nach Anspruch 1, wobei die Temperatur 1100 °C oder höher ist.
 
4. Verfahren nach Anspruch 1, wobei die Anode eine nichtabschmelzende Anode zum Abscheiden der Ni-Cr-Legierung ist und/oder wobei die Anode eine Ni-Cr-Legierungsanode, eine Ni-Anode oder eine Cr-Anode zum Abscheiden der Ni-Cr-Legierung ist.
 
5. Verfahren nach Anspruch 1, wobei der Strom ein Gleichstrom zum Abscheiden der Ni-Cr-Legierung ist oder wobei der Strom ein Wechselstrom zum Abscheiden der Ni-Cr-Legierung ist.
 
6. Verfahren nach Anspruch 1, weiter umfassend das Bereitstellen eines Haftvermittlers auf dem Ni-Cr-AI-Verbundstoff, nachdem die Wärmebehandlung durchgeführt wurde.
 
7. Verfahren nach Anspruch 1, wobei das Lösungsmittel Ameisensäure, Zitronensäure, Isopropanol (IPA), Wasser, Essigsäure und Ethylenglycol umfasst.
 
8. Verfahren nach Anspruch 1, wobei die oberflächenaktive Substanz eine anionische, kationische oder eine amphotere oberflächenaktive Substanz ist, vorzugsweise wobei die oberflächenaktive Substanz aus Natriumdodecylsulfat, Fluortensiden, Cetyltrimethylammoniumbromid (CTAB) oder Cetyltrimethyammoniumchlorid (CTAC) ausgewählt ist.
 
9. Verfahren nach Anspruch 1, wobei die Ni-Cr-Legierung von 2 bis 50 Gew.-% Chrom und einen Rest Nickel umfasst, wobei vorzugsweise die Ni-Cr-Legierung von 8 bis 20 Gew.-% Chrom und einen Rest Nickel umfasst.
 
10. Verfahren nach Anspruch 1, wobei die Ni-Cr-Legierung dicker als 125 µm ist.
 


Revendications

1. Procédé de formation d'un composite de nickel-chrome-aluminium (Ni-Cr-Al) sur un composant de turbine, le procédé comprenant :

la fourniture d'un composant de turbine qui a perdu des matériaux au cours de processus de réparation ;

la fourniture d'un premier bain de placage rempli d'une solution comprenant un solvant, un tensioactif, et un liquide ionique comprenant du chlorure de choline, du chlorure de nickel et du chlorure de chrome, dans lequel un rapport molaire du chlorure de choline au chlorure de chrome va de 0,5 à 3,5, et le solvant comprend de 5 à 80 % en volume par rapport à un mélange du chlorure de choline et de chlorures métalliques comprenant les chlorures de nickel et de chrome ;

le dépôt électrolytique d'un alliage de Ni-Cr sur le composant de turbine couplé à une cathode par fourniture d'une alimentation externe de courant à la cathode et à une anode dans le premier bain de placage ;

la fourniture d'un second bain de placage rempli d'un liquide ionique comprenant du chlorure de 1-éthyl-3-méthylimidazolium ou du chlorure 1-butyl-3-méthylimidazolium acides de Lewis, et un sel l'aluminium ;

le dépôt électrolytique d'un aluminium (Al) sur l'alliage Ni-Cr dans le second bain de placage ; et

le traitement thermique de la couche composite de Ni-Cr-Al déposée par électrolyse à une température élevée pour former un alliage de Ni-Cr-Al diffusé de telle sorte qu'un composé d'aluminium est formé entre l'aluminium et le nickel et pour reconstituer les matériaux perdus au cours des processus de réparation du composant de turbine.


 
2. Procédé selon la revendication 1, comprenant en outre le prétraitement du composant de turbine pour éliminer les matières étrangères et les oxydes du composant de turbine.
 
3. Procédé selon la revendication 1, dans lequel la température est supérieure ou égale à 1 100 °C.
 
4. Procédé selon la revendication 1, dans lequel l'anode est une anode non consommable pour déposer l'alliage de Ni-Cr, et/ou dans lequel l'anode est une anode en alliage de Ni-Cr, une anode en Ni, ou une anode en Cr pour déposer l'alliage de Ni-Cr.
 
5. Procédé selon la revendication 1, dans lequel le courant est un courant continu pour déposer l'alliage de Ni-Cr, ou dans lequel le courant est un courant alternatif pour déposer l'alliage de Ni-Cr.
 
6. Procédé selon la revendication 1, comprenant en outre la fourniture d'une couche d'accrochage sur le composite de Ni-Cr-AI après l'exécution du traitement thermique.
 
7. Procédé selon la revendication 1, dans lequel le solvant comprend un acide formique, un acide citrique, un isopropanol (IPA), une eau, un acide acétique et de l'éthylène glycol.
 
8. Procédé selon la revendication 1, dans lequel le tensioactif est un tensioactif anionique, cationique ou amphotérique, de préférence dans lequel le tensioactif est choisi parmi un sulfate dodécylique de sodium, des tensioactifs fluorés, du bromure de cétyltriméthylammonium (CTAB), ou du chlorure cétyltriméthylammonium (CTAC).
 
9. Procédé selon la revendication 1, dans lequel l'alliage de Ni-Cr comprend de 2 à 50 % en poids de chrome et un reste de nickel, de préférence dans lequel l'alliage de Ni-Cr comprend de 8 à 20 % en poids de chrome et un reste de nickel.
 
10. Procédé selon la revendication 1, dans lequel l'alliage de Ni-Cr a une épaisseur supérieure à 125 µm.
 




Drawing


















REFERENCES CITED IN THE DESCRIPTION



This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

Patent documents cited in the description