EP0587341A1 - Revêtements composites résistant à la corrosion à haute température - Google Patents

Revêtements composites résistant à la corrosion à haute température Download PDF

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Publication number
EP0587341A1
EP0587341A1 EP93306699A EP93306699A EP0587341A1 EP 0587341 A1 EP0587341 A1 EP 0587341A1 EP 93306699 A EP93306699 A EP 93306699A EP 93306699 A EP93306699 A EP 93306699A EP 0587341 A1 EP0587341 A1 EP 0587341A1
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EP
European Patent Office
Prior art keywords
coating
platinum
mcraly
surface layer
aluminides
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Granted
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EP93306699A
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German (de)
English (en)
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EP0587341B1 (fr
Inventor
Mehar Chand Meelu
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Rolls Royce PLC
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Rolls Royce PLC
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    • 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
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C23C28/022—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer with at least one MCrAlX layer
    • 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
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/58—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than one step
    • 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
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/028—Including graded layers in composition or in physical properties, e.g. density, porosity, grain size

Definitions

  • the present invention relates to so-called "MCrAlY” overlay coating systems modified to enhance resistance of superalloy gas turbine components to high temperature oxidation and corrosion attack.
  • MrAlY is a shorthand way of referring to well known temperature and oxidation/corrosion resistant alloy systems comprising in general one or more of nickel, cobalt and iron as the major "M” constituent, together with chromium and aluminium in quite large amounts, plus (usually) a minor amount of yttrium or other rare earth element.
  • M nickel, cobalt and iron
  • chromium and aluminium in quite large amounts, plus (usually) a minor amount of yttrium or other rare earth element.
  • weight percentage terms such alloys may be broadly defined as having the following compositions:
  • one well known alloy used as the basis of the present work, has a nominal composition in weight percent of:
  • This superalloy is available from the International Nickel company, and has the nominal composition in weight percent of: Cr-16%, Al-3.4%, Ti-3.4%, Co-8.5%, W-2.6%, Mo-1.75%, Ta-1.75%, Cb-0.9%, Fe-0.5%, Si-0.3%, Mn-0.2%, C-0.17%, Zr-0.1%, B-0.01%, Ni-Balance.
  • MCrAlY coatings do act as a barrier between the base material and any outer aluminide coating to limit migration of base material elements, particularly aluminium and chromium, during service.
  • MCrAlY coatings by the argon shrouded plasma spray process as mentioned above, proprietary to Union Carbide Coatings Service Corporation, of Indianapolis, U.S.A.
  • the coatings can be aluminised, but must, of course, be heat treated to inter-diffuse them with the base material.
  • the required extra Al to maintain the concentration of aluminides in the surface layers of the coating could be supplied from the MCrAlY inner portion of the coating.
  • the Al content is insufficient for the migration mechanism to be able to continue to supply the deficient surface layers with Al for a lengthy period.
  • MCrAlY coatings with such relatively low aluminium contents are preferred because higher Al contents tend to make the coating brittle in service after the necessary diffusion heat treatment has been carried out.
  • low temperature in the present context meaning about 550 - 750 °C. This, of course, should be accomplished without any detrimental effect on the high temperature protection afforded by the coatings.
  • Chromising improves low temperature oxidation/ corrosion resistance of coating systems because Cr oxidises to form chromia, Cr2O3, which forms a protective oxide film at the coating surface.
  • Cr oxidises to form chromia, Cr2O3, which forms a protective oxide film at the coating surface.
  • chromising is ineffective to improve high temperature oxidation/corrosion resistance of coating systems. This is because Cr2O3 dissociates into Cr and gaseous CrO3 at temperatures above about 750°C.
  • the present invention includes a process for providing an M-based superalloy base material, where M is at least one of iron, cobalt and nickel, with a graded multiplex protective coating system containing aluminides in and near its surface, the process comprising the steps of: applying an alloy coating material of the MCrAlY type to the surface of the base material, the Al content of the coating material being in the range 4 to 20 wt.%; optionally, chromising the MCrAlY-type coating to produce a coating with a chromised top layer having extra chromium in solid solution in the M constituent of the coating, the total chromium content in the surface layer of the MCrAlY-type coating after chromising preferably being not more than about 40%, most preferably 35 to 40%; aluminising the coating resulting from the preceding utilised process step to produce a coating having a surface layer containing aluminides of the M constituent of the coating; depositing a platinum layer onto the surface of
  • the platinum layer has a thickness of 5 to 15 ⁇ m when applied, and the subsequent diffusing heat treatment is conveniently that normally utilised to restore the properties of the base material after the aluminising step.
  • the subsequent diffusing heat treatment is conveniently that normally utilised to restore the properties of the base material after the aluminising step.
  • this is one hour diffusion treatment at 1120°C, gas fan quench, and age 24 hours at 845°C.
  • the thickness of the platinum layer as deposited is very important to the final structure of the above coating.
  • a deposited platinum layer having a thickness of 10 to 15 ⁇ m gives a structure comprising an MCrAlY coating having a single surface layer containing platinum modified aluminide. This is achieved because during heat treatment the platinum and the underlying aluminides inter-diffuse completely.
  • the deposited platinum layer should have a thickness of 5 to 10 ⁇ m. This can be achieved because during heat treatment the platinum and the underlying aluminides do not inter-diffuse completely.
  • the present invention also includes an alternative process for providing an M-based superalloy base material, where M is at least one of iron, cobalt and nickel, with a graded multiplex protective coating system containing aluminides with enhanced aluminium content in and near its surface, the process comprising the steps of: applying an alloy coating material of the MCrAlY type to the surface of the base material, the Al content of the coating material being in the range 4 to 20 wt.%; optionally, chromising the MCrAlY-type coating to produce a coating with a chromised top layer having extra chromium in solid solution in the M constituent of the coating, the total chromium content in the surface layer of the MCrAlY-type coating after chromising preferably being not more than about 40%, most preferably 35 to 40%; depositing a platinum layer onto the surface of the coating resulting from the preceding utilised process step, heat treating the resulting coating to diffuse the platinum layer into the underlying MCrAlY coating, and
  • the platinum layer has a thickness of 5 to 10 ⁇ m when applied.
  • the time of aluminising is very important to the final structure of the above coating.
  • the platinised coating should be aluminised only for a relatively short time of about 4 to 6 hours at the aluminising temperature. This will allow the aluminium to diffuse into the platinised coating only about as far as the platinum has already diffused.
  • the platinised coating should be aluminised for a relatively long time of about 6 to 12 hours at the aluminising temperature. This will allow the aluminium to diffuse into the platinised coating further than the platinum has already diffused.
  • the chromising step in the above processes is performed essentially to obtain a large gradient of concentration of Cr in and near the surface of the MCrAlY coating. This increases its low temperature sulphidation resistance.
  • the overlay coating was first applied to IN738 alloy bars by the previously mentioned argon shrouded plasma spray technique. Extra elements were then introduced into the outer layer of the coating using various methods as described below:
  • the vapour aluminising process took place in an argon-filled retort vessel, with the parts to be aluminised being suspended in close proximity over packs of aluminising powder which liberate aluminium halide gas when heated. Aluminium from the gas is deposited onto the parts and diffuses into it due to the elevated temperature.
  • RT69 trade name
  • Chromalloy U.K. Limited of Bramble Way, Clover Nook Industrial Estate, Somercoates, Derby DE55 4RH, England, or its parent company, Chromalloy Research and Technology, Blaisdell, Orangeburg, NY 10962, U.S.A.
  • Platinum plating was accomplished by an electroplating process, again available from Chromalloy at the sites mentioned above under the trade name RT22.
  • Vapour chromising is performed in a similar way to vapour aluminising and is also available from Chromalloy under the trade name CN70.
  • Coating (4) had been processed in the same way as coating (5), except for the application of the thicker 16 micron platinum plate.
  • Coating (6) had been chromised and aluminised, but not platinised.
  • Coatings (3) and (2) had been aluminised and platinised, but not chromised.
  • Figure 5 shows a typical microstructure of coating (5) at x200 magnification before sulphidation testing, with the various layers indicated.
  • Figure 6 shows the result of an electron probe microanalysis of this coating, in which the concentration in weight percentage terms of various elements in the coating is graphically plotted against the depth of the coating in microns.
  • the Cr content of the coating is up to about 40wt.% in the chromised layer, up to about 20 wt.% in the platinum aluminide layer and about 25wt.% retained in the body of the MCrAlY coating.
  • the highest aluminium content is only about 20 wt.% and is less than this near the surface of the coating in the platinum modified layer.
  • the results of the electron probe microanalysis as plotted are subject to variation due to experimental error and to local variations in element concentrations in the small scale microstructure.
  • the method of platinising an MCrAlY coating before aluminising it, in order to gain higher Al concentrations in the platinum modified aluminide surface layer of the finished coating will also plainly be advantageous when utilised without the prior chromising step.
EP93306699A 1992-09-05 1993-08-24 Revêtements composites résistant à la corrosion à haute température Expired - Lifetime EP0587341B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB929218858A GB9218858D0 (en) 1992-09-05 1992-09-05 High temperature corrosion resistant composite coatings
GB9218858 1992-09-05

Publications (2)

Publication Number Publication Date
EP0587341A1 true EP0587341A1 (fr) 1994-03-16
EP0587341B1 EP0587341B1 (fr) 1996-03-20

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EP (1) EP0587341B1 (fr)
JP (1) JPH06220607A (fr)
DE (1) DE69301883T2 (fr)
GB (1) GB9218858D0 (fr)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718419A3 (fr) * 1994-12-24 1997-01-08 Rolls Royce Plc Revêtement de barrière thermique pour superalliage et méthode d'application
EP0683826B1 (fr) * 1993-02-15 1997-05-21 THE SECRETARY OF STATE FOR DEFENCE in Her Britannic Majesty's Gvmnt. of the United Kingdom of Great Britain & Northern Ireland Couches de barrage a diffusion
EP0784104A1 (fr) * 1995-12-22 1997-07-16 General Electric Company Superalliage à base de nickel ayant un revêtement de platine-aluminure optimisé
EP0792948A1 (fr) * 1996-02-29 1997-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Revêtement de barrière thermique à sous-couche ameliorée et pièces revêtues par une telle barrière thermique
EP0821076A1 (fr) * 1996-07-23 1998-01-28 ROLLS-ROYCE plc Procédé d'aluminisation d'un superalliage
WO1998024943A1 (fr) * 1996-12-06 1998-06-11 Siemens Aktiengesellschaft Article comportant un substrat de superalliage et une couche d'enrichissement placee sur ce dernier, et procedes de fabrication de cet article
EP0848079A1 (fr) * 1996-12-12 1998-06-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé de réalisation d'un revêtement protecteur à haute efficacité contre la corrosion à haute température pour superalliages, revêtement protecteur obtenu par ce procédé et pièces protégées par ce revêtement
GB2322382A (en) * 1997-02-22 1998-08-26 Rolls Royce Plc A coated superalloy article
US5967755A (en) * 1995-07-25 1999-10-19 Siemens Aktiengesellschaft Product with a metallic basic body and method for manufacturing a product
DE19807636C1 (de) * 1998-02-23 1999-11-18 Mtu Muenchen Gmbh Verfahren zum Herstellen einer korrosions- und oxidationsbeständigen Schlickerschicht
EP1111091A1 (fr) * 1999-12-21 2001-06-27 United Technologies Corporation Procédé de formation d'une couche d'aluminure renfermant un élément actif comme revêtement et couche de liaison et article revêtu
EP1127959A1 (fr) * 2000-02-23 2001-08-29 Howmet Research Corporation Revêtement de barrière thermique et article
EP1236812A2 (fr) * 2001-02-06 2002-09-04 General Electric Company Procédé de rénovation d'une couche comportant un oxyde formé par croissance thermique
US6565931B1 (en) 1999-10-23 2003-05-20 Rolls-Royce Plc Corrosion protective coating for a metallic article and a method of applying a corrosion protective coating to a metallic article
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
US7229701B2 (en) 2004-08-26 2007-06-12 Honeywell International, Inc. Chromium and active elements modified platinum aluminide coatings
EP1801263A1 (fr) * 2005-12-21 2007-06-27 United Technologies Corporation Couche de liaison de NiCoCrAly modifié par le platine pour revêtement de barrière thermique
EP2537959A1 (fr) 2011-06-22 2012-12-26 MTU Aero Engines GmbH Revêtement multicouches anti-usure et procédé de fabrication
US8475598B2 (en) 2005-11-22 2013-07-02 United Technologies Corporation Strip process for superalloys
EP2796588A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Procédé de fabrication d'un revêtement de protection haute température et composant ainsi fabriqué
US8968528B2 (en) 2008-04-14 2015-03-03 United Technologies Corporation Platinum-modified cathodic arc coating
WO2015088721A1 (fr) * 2013-12-10 2015-06-18 United Technologies Corporation Revêtement de chromisation sur arc cathodique
WO2018048486A1 (fr) * 2016-06-02 2018-03-15 General Electric Company Profil aérodynamique à système de revêtement amélioré et ses procédés de formation
EP3388545A1 (fr) * 2017-04-13 2018-10-17 General Electric Company Surface portante réparée munie d'un système de revêtement amélioré et ses procédés de formation

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JP2003073841A (ja) * 2001-08-28 2003-03-12 Kyocera Corp 配線基板およびその製造方法
DE102005060243A1 (de) * 2005-12-14 2007-06-21 Man Turbo Ag Verfahren zum Beschichten einer Schaufel und Schaufel einer Gasturbine
GB2452515B (en) 2007-09-06 2009-08-05 Siemens Ag Seal coating between rotor blade and rotor disk slot in gas turbine engine
JP5653421B2 (ja) * 2009-05-26 2015-01-14 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ ＭＣｒＡｌＸ層およびクロムリッチ層を含む層状コーティングシステムならびにその製造方法
DE102012015586A1 (de) * 2012-08-08 2014-05-15 MTU Aero Engines AG Duplex Phasen CrAl-Beschichtung für verbesserten Korrosions-/Oxidations-Schutz
US10266926B2 (en) 2013-04-23 2019-04-23 General Electric Company Cast nickel-base alloys including iron
DE102021127344A1 (de) * 2021-10-21 2023-04-27 MTU Aero Engines AG Verfahren zum Beschichten eines Bauteils eines Flugtriebwerks mit einer Verschleißschutzschicht und Bauteil für ein Flugtriebwerk mit wenigstens einer Verschleißschutzschicht

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US4477538A (en) * 1981-02-17 1984-10-16 The United States Of America As Represented By The Secretary Of The Navy Platinum underlayers and overlayers for coatings
US5141821A (en) * 1989-06-06 1992-08-25 Hermann C. Starck Berlin Gmbh & Co Kg High temperature mcral(y) composite material containing carbide particle inclusions

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US4123594A (en) * 1977-09-22 1978-10-31 General Electric Company Metallic coated article of improved environmental resistance

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US4477538A (en) * 1981-02-17 1984-10-16 The United States Of America As Represented By The Secretary Of The Navy Platinum underlayers and overlayers for coatings
GB2095700A (en) * 1981-03-31 1982-10-06 Howmet Turbine Components Superalloy coating compositions
US5141821A (en) * 1989-06-06 1992-08-25 Hermann C. Starck Berlin Gmbh & Co Kg High temperature mcral(y) composite material containing carbide particle inclusions

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0683826B1 (fr) * 1993-02-15 1997-05-21 THE SECRETARY OF STATE FOR DEFENCE in Her Britannic Majesty's Gvmnt. of the United Kingdom of Great Britain & Northern Ireland Couches de barrage a diffusion
EP0718419A3 (fr) * 1994-12-24 1997-01-08 Rolls Royce Plc Revêtement de barrière thermique pour superalliage et méthode d'application
US5967755A (en) * 1995-07-25 1999-10-19 Siemens Aktiengesellschaft Product with a metallic basic body and method for manufacturing a product
US6156133A (en) * 1995-07-25 2000-12-05 Siemens Aktiengesellschaft Method for manufacturing a product with a metallic basic body
EP0784104A1 (fr) * 1995-12-22 1997-07-16 General Electric Company Superalliage à base de nickel ayant un revêtement de platine-aluminure optimisé
US6066405A (en) * 1995-12-22 2000-05-23 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
US7083827B2 (en) 1995-12-22 2006-08-01 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
FR2745590A1 (fr) * 1996-02-29 1997-09-05 Snecma Revetement de barriere thermique a sous-couche amelioree et pieces revetues par une telle barriere thermique
US5843585A (en) * 1996-02-29 1998-12-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Thermal barrier coating with improved sub-layer and parts coated with said thermal barrier
EP0792948A1 (fr) * 1996-02-29 1997-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Revêtement de barrière thermique à sous-couche ameliorée et pièces revêtues par une telle barrière thermique
EP0821076A1 (fr) * 1996-07-23 1998-01-28 ROLLS-ROYCE plc Procédé d'aluminisation d'un superalliage
US6080246A (en) * 1996-07-23 2000-06-27 Rolls-Royce, Plc Method of aluminising a superalloy
WO1998024943A1 (fr) * 1996-12-06 1998-06-11 Siemens Aktiengesellschaft Article comportant un substrat de superalliage et une couche d'enrichissement placee sur ce dernier, et procedes de fabrication de cet article
US6139976A (en) * 1996-12-06 2000-10-31 Siemens Aktiengesellschaft Article having a superalloy substrate and an enrichment layer placed thereon, and methods of its manufacturing
FR2757181A1 (fr) * 1996-12-12 1998-06-19 Snecma Procede de realisation d'un revetement protecteur a haute efficacite contre la corrosion a haute temperature pour superalliages, revetement protecteur obtenu par ce procede et pieces protegees par ce revetement
EP0848079A1 (fr) * 1996-12-12 1998-06-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé de réalisation d'un revêtement protecteur à haute efficacité contre la corrosion à haute température pour superalliages, revêtement protecteur obtenu par ce procédé et pièces protégées par ce revêtement
US6183888B1 (en) * 1996-12-12 2001-02-06 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Process for producing a coating for providing superalloys with highly efficient protection against high-temperature corrosion, a protective coating formed by the process, and articles protected by the coating
GB2322382A (en) * 1997-02-22 1998-08-26 Rolls Royce Plc A coated superalloy article
US6440499B1 (en) 1998-02-23 2002-08-27 Mtu Aero Engines Gmbh Method for producing a slip layer which is resistant to corrosion and oxidation
DE19807636C1 (de) * 1998-02-23 1999-11-18 Mtu Muenchen Gmbh Verfahren zum Herstellen einer korrosions- und oxidationsbeständigen Schlickerschicht
US6565931B1 (en) 1999-10-23 2003-05-20 Rolls-Royce Plc Corrosion protective coating for a metallic article and a method of applying a corrosion protective coating to a metallic article
EP1111091A1 (fr) * 1999-12-21 2001-06-27 United Technologies Corporation Procédé de formation d'une couche d'aluminure renfermant un élément actif comme revêtement et couche de liaison et article revêtu
EP1127959A1 (fr) * 2000-02-23 2001-08-29 Howmet Research Corporation Revêtement de barrière thermique et article
US7501187B2 (en) 2000-02-23 2009-03-10 Howmet Research Corporation Thermal barrier coating method and article
EP1236812A2 (fr) * 2001-02-06 2002-09-04 General Electric Company Procédé de rénovation d'une couche comportant un oxyde formé par croissance thermique
EP1236812A3 (fr) * 2001-02-06 2004-03-24 General Electric Company Procédé de rénovation d'une couche comportant un oxyde formé par croissance thermique
US7229701B2 (en) 2004-08-26 2007-06-12 Honeywell International, Inc. Chromium and active elements modified platinum aluminide coatings
WO2006061431A3 (fr) * 2004-12-11 2006-08-24 Siemens Ag Procede permettant de proteger une composante contre la corrosion a chaud
WO2006061431A2 (fr) * 2004-12-11 2006-06-15 Siemens Aktiengesellschaft Procede permettant de proteger une composante contre la corrosion a chaud
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
US8475598B2 (en) 2005-11-22 2013-07-02 United Technologies Corporation Strip process for superalloys
EP1801263A1 (fr) * 2005-12-21 2007-06-27 United Technologies Corporation Couche de liaison de NiCoCrAly modifié par le platine pour revêtement de barrière thermique
US8968528B2 (en) 2008-04-14 2015-03-03 United Technologies Corporation Platinum-modified cathodic arc coating
EP2537959A1 (fr) 2011-06-22 2012-12-26 MTU Aero Engines GmbH Revêtement multicouches anti-usure et procédé de fabrication
EP2796588A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Procédé de fabrication d'un revêtement de protection haute température et composant ainsi fabriqué
US9932661B2 (en) 2013-04-24 2018-04-03 MTU Aero Engines AG Process for producing a high-temperature protective coating
WO2015088721A1 (fr) * 2013-12-10 2015-06-18 United Technologies Corporation Revêtement de chromisation sur arc cathodique
US10364490B2 (en) 2013-12-10 2019-07-30 United Technologies Corporation Chromizing over cathodic arc coating
US10844478B2 (en) 2013-12-10 2020-11-24 Raytheon Technologies Corporation Chromizing over cathodic arc coating
WO2018048486A1 (fr) * 2016-06-02 2018-03-15 General Electric Company Profil aérodynamique à système de revêtement amélioré et ses procédés de formation
US10202855B2 (en) 2016-06-02 2019-02-12 General Electric Company Airfoil with improved coating system
US11181000B2 (en) 2016-06-02 2021-11-23 General Electric Company Airfoil with improved coating system and methods of forming the same
EP3388545A1 (fr) * 2017-04-13 2018-10-17 General Electric Company Surface portante réparée munie d'un système de revêtement amélioré et ses procédés de formation

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EP0587341B1 (fr) 1996-03-20
GB9218858D0 (en) 1992-10-21
DE69301883D1 (de) 1996-04-25
DE69301883T2 (de) 1996-08-08
JPH06220607A (ja) 1994-08-09

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