EP3789518B1 - Procede de reparation localisee d'une barriere thermique endommagee - Google Patents

Procede de reparation localisee d'une barriere thermique endommagee Download PDF

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Publication number
EP3789518B1
EP3789518B1 EP20203886.5A EP20203886A EP3789518B1 EP 3789518 B1 EP3789518 B1 EP 3789518B1 EP 20203886 A EP20203886 A EP 20203886A EP 3789518 B1 EP3789518 B1 EP 3789518B1
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EP
European Patent Office
Prior art keywords
damaged
thermal barrier
particles
equal
ceramic coating
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.)
Active
Application number
EP20203886.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3789518A1 (fr
Inventor
André Hubert Louis MALIE
Sarah Hamadi
Florence Ansart
Jean-Pierre Bonino
Hélène CERDA
Guillaume PUJOL
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.)
Safran Aircraft Engines SAS
Centre National de la Recherche Scientifique CNRS
Institut National Polytechnique de Toulouse INPT
Universite de Toulouse
Original Assignee
Safran Aircraft Engines SAS
Centre National de la Recherche Scientifique CNRS
Universite Toulouse III Paul Sabatier
Institut National Polytechnique de Toulouse INPT
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 Safran Aircraft Engines SAS, Centre National de la Recherche Scientifique CNRS, Universite Toulouse III Paul Sabatier, Institut National Polytechnique de Toulouse INPT filed Critical Safran Aircraft Engines SAS
Publication of EP3789518A1 publication Critical patent/EP3789518A1/fr
Application granted granted Critical
Publication of EP3789518B1 publication Critical patent/EP3789518B1/fr
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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
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/02—Electrophoretic coating characterised by the process with inorganic material
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/12—Electrophoretic coating characterised by the process characterised by the article coated
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/18—Electrophoretic coating characterised by the process using modulated, pulsed, or reversing current
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/20—Pretreatment
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/22—Servicing or operating apparatus or multistep processes
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5023—Thermal capacity

Definitions

  • the blades of high-pressure turbines in aeronautical engines are exposed to a very aggressive environment.
  • These parts are, in general, coated with a protective oxidation coating as well as a thermal barrier coating.
  • the thermal barrier coating makes it possible to thermally insulate the underlying part in order to maintain it at temperatures where its mechanical performance and lifespan are acceptable.
  • the part is formed of an electrically conductive material and the damaged thermal barrier allows the conduction of electricity in the damaged area to be repaired and therefore the deposition of the ceramic coating by electrophoresis in this area during step a).
  • the ceramic coating obtained during step a) is formed by the deposition of the particles on the part.
  • the ceramic coating can be mainly deposited in the damaged area.
  • a mass of ceramic coating greater than or equal to 50% of the total mass of the ceramic coating deposited during step a) can be deposited in the damaged zone.
  • This mass of ceramic coating deposited in the damaged zone can for example be greater than or equal to 75%, or even 90%, of the total mass of the ceramic coating deposited during step a).
  • the ceramic coating can be deposited only in the damaged area.
  • the invention advantageously makes it possible to repair the damaged thermal barrier quickly, inexpensively and locally and thus to avoid the scrapping of partially damaged parts or the complete stripping of the damaged thermal barrier.
  • the invention therefore makes it possible to extend the lifespan of the parts and to limit the cost of restarting parts whose thermal barrier has been damaged.
  • electrophoresis deposition unlike the vapor phase deposition process with evaporation under an electron beam (“electron beam physical vapor deposition”; EB-PVD) or plasma projection (“plasma spraying”; PS) which does not or makes it difficult to carry out a localized repair.
  • electron beam physical vapor deposition EB-PVD
  • plasma projection plasma projection
  • the electrophoresis deposition process has the advantage of being usable for parts with complex geometries.
  • the repaired thermal barrier may be intended for use in an environment where the temperature on the surface of the thermal barrier is greater than or equal to 1000°C.
  • the part can advantageously be made of metallic material and, for example, contain nickel.
  • the damaged thermal barrier may have a lack of material in the damaged zone.
  • the particles may have an average size less than or equal to 10 ⁇ m.
  • average size we designate the dimension given by the statistical particle size distribution to half of the population, called D50.
  • the particles, in the non-agglomerated state can have an average size of between 20 nm and 1 ⁇ m.
  • Such particle sizes advantageously make it possible to obtain a stable suspension.
  • the particles may or may not have been obtained by sol-gel route.
  • the process may comprise, before step a), a step of forming particles by implementing a sol-gel process. These particles can then be dispersed in the liquid medium to form the electrolyte.
  • the particles of the electrolyte can, for example, be particles of yttriated zirconia (YSZ; “Yttria-Stabilized Zirconia”) which may or may not have been obtained by sol-gel method.
  • Zirconium oxide particles can also be used.
  • any particles likely to present an electric charge within the electrolyte can be used for electrophoresis deposition.
  • the particles are made of a material different from the ceramic material present in the damaged thermal barrier.
  • the material constituting the particles and the ceramic material of the damaged thermal barrier are advantageously compatible thermomechanically and chemically.
  • the difference between the thermal expansion coefficients of the ceramic material present in the damaged thermal barrier and of the material constituting the particles can in absolute value advantageously be less than or equal to 2.10 -6 K -1 .
  • the use of a different material can advantageously make it possible to provide an additional property, for example anti-CMAS property or heat-sensitive material, and thus to functionalize the thermal barrier while repairing it.
  • the liquid medium can, for example, be chosen from: alcohols, for example ethanol or isopropanol, ketones, for example acetylacetone, water and their mixtures.
  • the particles may be present in the liquid medium, before the start of step a), in a concentration greater than or equal to 0.1 g/L, preferably greater than or equal to 1 g/L .
  • the thickness of the ceramic coating deposited may be greater than or equal to 50 nm, for example greater than or equal to 30 ⁇ m. In an exemplary embodiment, the thickness of the ceramic coating deposited may be less than or equal to 200 ⁇ m.
  • the part can be coated with an adhesion layer allowing the thermal barrier to be attached to the part and the ceramic coating can be deposited on the adhesion layer.
  • the bonding layer advantageously makes it possible to improve the bonding of the thermal barrier to the part.
  • the bonding layer can, moreover, advantageously help protect the part against oxidation and corrosion.
  • the bonding layer may, for example, be metallic.
  • the thermal barrier can be directly present on the part.
  • the thermal barrier can be directly present on the part.
  • the duration of step a) may be greater than or equal to 1 minute, preferably 5 minutes.
  • a voltage greater than or equal to 1 V can be imposed during all or part of step a) between the part and a counter electrode.
  • the voltage imposed during all or part of step a) may, preferably, be greater than or equal to 50 V.
  • the damaged zone may, before step a), have been subjected to a stripping step.
  • Carrying out stripping advantageously makes it possible to eliminate the thermal barrier residues and the layers of oxides possibly present and thus to improve the electrically conductive nature of the damaged area to be repaired in order to promote the formation of the deposit of the ceramic coating by electrophoresis.
  • Stripping can be carried out mechanically, for example by sanding, sanding, grinding, high pressure water jet or by laser stripping.
  • the pickling may be chemical pickling, for example electrolytic pickling or pickling in an acidic or basic medium.
  • the damaged thermal barrier may, at the start of step a), present a lack of material in the damaged zone.
  • the method may include, after step a), a step b) of consolidation by heat treatment of the deposited ceramic coating.
  • Step b) may, for example, include subjecting the part obtained after implementation of step a) to a temperature greater than or equal to 1000°C, for example greater than or equal to 1100°C.
  • the part can constitute a turbomachine blade.
  • a part 1 for example made of a nickel-based superalloy coated with a bonding layer 2 on which there is a damaged thermal barrier 3.
  • An oxide layer 2a is present between the bonding layer 2 and the thermal barrier 3 damaged.
  • Layer 2a can consist of ⁇ -Al 2 O 3 alumina.
  • the damaged thermal barrier 3 comprises a ceramic material and has a damaged area 4 to be repaired.
  • the damaged zone 4 may have at least one adjacent undamaged zone. In the example illustrated, the damaged zone 4 is present between two adjacent undamaged zones 5a and 5b.
  • the part 1 carrying the damaged thermal barrier 3 is present in an electrolyte 10 comprising a suspension of particles 11 in a liquid medium.
  • the particles 11 can, for example, be particles of yttriated zirconia (zirconia stabilized by yttrium oxide).
  • the oxide powder (yttriated zirconia) thus obtained is then suspended in a liquid medium consisting for example of isopropanol in order to form the electrolyte 10.
  • the part 1 coated with the damaged thermal barrier 3 constitutes an electrode of the electrophoresis system facing which a counter-electrode 20 is present.
  • the counter-electrode 20 is, for example, made of platinum. Due to the conductive nature of the part 1 and the damaged zone 4, a deposition by electrophoresis is carried out in the damaged zone 4.
  • the damaged zone 4 is constituted, in the example illustrated, by a region devoid of material.
  • the damaged zone comprises a first region devoid of material as well as a second region in which a ceramic layer is present, the thickness of the ceramic layer present in the second region being sufficiently low for this second region to be electrically conductive.
  • the damaged zone is constituted by a region in which a ceramic layer is present, the thickness of the ceramic layer being sufficiently low for this region to conduct electricity.
  • the deposition is preferably carried out in the most conductive zones (thickness of the ceramic layer sufficiently low or total absence of ceramic layer) because the electric field will be relatively high in these zones.
  • the damaged thermal barrier 3 has a single damaged zone 4 to be repaired, but we do not depart from the scope of the present invention if the damaged thermal barrier has a plurality of damaged zones to be repaired. In this case, each of the damaged areas to be repaired conducts electricity.
  • a generator G imposes a potential difference between part 1 and counter electrode 20.
  • Generator G is pulsed current.
  • the part 1 is polarized at a charge opposite to that of the particles 11. Due to the application of an electric field between the part 1 and the counter electrode 20, the particles 11 move and are deposited on the part 1 to form a ceramic coating 6.
  • the deposition of the ceramic coating 6 in the damaged zone 4 makes it possible to obtain a repaired thermal barrier 7.
  • the deposition of the ceramic coating 6 in the damaged zone 4 induces a progressive reduction in the electrical conductivity of this zone at course of time. Indeed, as the ceramic coating 6 is deposited, this zone becomes more and more insulating, which slows down or even stops the formation of the ceramic coating 6 on the part 1.
  • the ceramic coating 6 is deposited in the damaged zone 4 and covers the entire surface of the damaged zone 4.
  • the damaged thermal barrier 3 is not covered with a mask having an opening overlapping with the damaged zone 4 to fix. Furthermore, it is not necessary before step a) to strip part of the damaged thermal barrier 3 located outside the damaged zone 4 to be repaired.
  • the ceramic coating 6 may have a thickness e greater than or equal to 50 nm, for example greater than or equal to 30 ⁇ m.
  • the thickness e of the ceramic coating 6 corresponds to its largest dimension measured perpendicular to the surface S of the coated part 1.
  • step a drying then a heat treatment to consolidate the ceramic coating 6 can be carried out.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Electrochemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP20203886.5A 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee Active EP3789518B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1400224 2014-01-29
PCT/FR2014/053268 WO2015114227A1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee
EP14828044.9A EP3099848B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP14828044.9A Division EP3099848B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee
EP14828044.9A Division-Into EP3099848B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee

Publications (2)

Publication Number Publication Date
EP3789518A1 EP3789518A1 (fr) 2021-03-10
EP3789518B1 true EP3789518B1 (fr) 2023-11-29

Family

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Application Number Title Priority Date Filing Date
EP20203886.5A Active EP3789518B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee
EP14828044.9A Active EP3099848B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee

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Application Number Title Priority Date Filing Date
EP14828044.9A Active EP3099848B1 (fr) 2014-01-29 2014-12-11 Procede de reparation localisee d'une barriere thermique endommagee

Country Status (7)

Country Link
US (1) US9840914B2 (enExample)
EP (2) EP3789518B1 (enExample)
CN (1) CN106414813B (enExample)
BR (1) BR112016017562B1 (enExample)
CA (1) CA2938031C (enExample)
RU (1) RU2678347C2 (enExample)
WO (1) WO2015114227A1 (enExample)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3073866B1 (fr) 2017-11-21 2019-11-29 Safran Helicopter Engines Procede de fabrication d'une barriere thermique sur une piece d'une turbomachine
CN110129859B (zh) * 2018-02-08 2021-09-21 通用电气公司 掩蔽元件中的孔并对元件进行处理的方法
FR3099935B1 (fr) * 2019-08-12 2021-09-10 Safran Aircraft Engines Procédé de revêtement d’une pièce de turbomachine
US12139808B2 (en) * 2022-01-12 2024-11-12 General Electric Company Formation of a barrier coating using electrophoretic deposition of a slurry

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3416165A1 (de) * 1983-06-03 1984-12-06 VEB Thuringia Sonneberg, DDR 6412 Sonneberg Verfahren zur elektrophoretischen herstellung einer masseschicht
SU1730209A1 (ru) * 1988-09-23 1992-04-30 Предприятие П/Я А-7555 Установка дл электрофоретических покрытий
US5723078A (en) * 1996-05-24 1998-03-03 General Electric Company Method for repairing a thermal barrier coating
FR2827311B1 (fr) * 2001-07-12 2003-09-19 Snecma Moteurs Procede de reparation locale de pieces revetues d'une barriere thermique
DE10335406A1 (de) * 2003-08-01 2005-02-17 Mtu Aero Engines Gmbh Verfahren zum Reparieren von Wärmedämmschichten mit lokalen Beschädigungen
US20070087129A1 (en) * 2005-10-19 2007-04-19 Blankenship Donn R Methods for repairing a workpiece
US7780832B2 (en) * 2005-11-30 2010-08-24 General Electric Company Methods for applying mitigation coatings, and related articles
KR100753909B1 (ko) * 2006-09-09 2007-08-31 한국원자력연구원 전기영동 보수기술을 이용한 금속 또는 합금의 결함 또는 균열 보수 방법
EP2000557B1 (en) 2007-06-04 2015-04-29 United Technologies Corporation Erosion barrier for thermal barrier coatings

Also Published As

Publication number Publication date
EP3099848A1 (fr) 2016-12-07
BR112016017562B1 (pt) 2022-04-12
BR112016017562A2 (enExample) 2017-08-08
RU2016135017A3 (enExample) 2018-08-22
WO2015114227A1 (fr) 2015-08-06
CN106414813A (zh) 2017-02-15
CN106414813B (zh) 2019-04-30
US9840914B2 (en) 2017-12-12
EP3789518A1 (fr) 2021-03-10
CA2938031C (fr) 2022-05-10
EP3099848B1 (fr) 2021-08-25
RU2016135017A (ru) 2018-03-05
US20160348509A1 (en) 2016-12-01
CA2938031A1 (fr) 2015-08-06
RU2678347C2 (ru) 2019-01-28

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