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WO2006061431A2 - Procede permettant de proteger une composante contre la corrosion a chaud - Google Patents

Procede permettant de proteger une composante contre la corrosion a chaud Download PDF

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Publication number
WO2006061431A2
WO2006061431A2 PCT/EP2005/056643 EP2005056643W WO2006061431A2 WO 2006061431 A2 WO2006061431 A2 WO 2006061431A2 EP 2005056643 W EP2005056643 W EP 2005056643W WO 2006061431 A2 WO2006061431 A2 WO 2006061431A2
Authority
WO
WIPO (PCT)
Prior art keywords
coating
component
weight
chromium
aluminium
Prior art date
Application number
PCT/EP2005/056643
Other languages
German (de)
English (en)
Other versions
WO2006061431A3 (fr
Inventor
Paul Box
Mick Whitehurst
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP05818992A priority Critical patent/EP1819906A2/fr
Priority to US11/792,629 priority patent/US20070264126A1/en
Publication of WO2006061431A2 publication Critical patent/WO2006061431A2/fr
Publication of WO2006061431A3 publication Critical patent/WO2006061431A3/fr

Links

Classifications

    • 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
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks
    • 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
    • C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
    • C23C10/16—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases 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
    • 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
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C23C10/54—Diffusion of at least chromium
    • C23C10/56—Diffusion of at least chromium and at least aluminium
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/60—After-treatment
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • This invention relates to a method of protecting a component against hot corrosion.
  • the invention finds particular application in the protection against hot corrosion of a gas turbine engine rotor blade.
  • chromium provides excellent protection against so called Type I and Type II hot corrosion.
  • diffusion coatings produced by the diffusion of chromium and aluminium into the alloy substrate have long been used to provide this protection.
  • a method of protecting a component against hot corrosion comprising the steps: (a) applying a chromium diffusion coating to the component; and (b) applying a further coating to selected regions of the chromium diffusion coating, the selected regions being chosen dependent on subsequent use of the component.
  • the selected regions are regions not subject to higher physical stress in the subsequent use of the component .
  • the further coating comprises an aluminium diffusion coating.
  • the further coating comprises an MCrAlY overlay coating, where M is Ni or Co or a combination of the two.
  • the further coating comprises an MCrAlY overlay coating, where M is Ni or Co or a combination of the two, and the method further comprises the step (c) applying an aluminium diffusion coating to the selected regions coated with the MCrAlY overlay coating.
  • the MCrAlY overlay coating applied in step (b) suitably comprises: 30 to 70 weight % Nickel; 30 to 50 weight % Cobalt; 15 to 25 weight % Chromium; 5 to 15 weight % Aluminium; and up to 1 weight %
  • the MCrAlY overlay coating applied in step (b) may additionally include one or more elements selected from the group consisting of rhenium, silicon and hafnium.
  • the chromium diffusion coating applied in step (a) suitably comprises 15 to 30 weight % chromium and is 5 to 25 microns thick.
  • Methods according to the present invention find particular application in the protection against hot corrosion of nickel based superalloy components.
  • Methods according to the present invention find particular application in the protection against hot corrosion of gas turbine engine rotor blades.
  • the present invention also extends to components protected against hot corrosion by means of a method according to the present invention.
  • Fig 1 shows a gas turbine engine rotor blade and the coating of this blade using a first method in accordance with the present invention
  • Fig 2 is a view of a side of the rotor blade of Fig 1 hidden in Fig 1 but to be seen when looking from the right in Fig 1;
  • Fig 3 shows a gas turbine engine rotor blade and the coating of this blade using a second method in accordance with the present invention
  • Fig 4 is a view of a side of the rotor blade of Fig 3 hidden in Fig 3 but to be seen when looking from the right in Fig 3;
  • Fig 5 shows a gas turbine engine rotor blade and the coating of this blade using a third method in accordance with the present invention.
  • Fig 6 is a view of a side of the rotor blade of Fig 5 hidden in Fig 5 but to be seen when looking from the right in Fig 5.
  • the rotor blade coated is a nickel based superalloy rotor blade.
  • the rotor blade may be produced by conventional or directionally solidified (including single crystal) casting techniques. Typical alloys are MarM247, IN6203 and CMSX-4.
  • the blade coated comprises an outer shroud part 1 (above dotted line A) , an aerofoil part 3 (between dotted lines A and B) , a platform part 5 (between dotted lines B and C) , and a root part 7 (below dotted line C) .
  • the blade includes an internal cooling passage 9 which commences as shown in Fig 1, loops within the blade, and exits (exit not shown) via the top side of shroud part 1.
  • chromised i.e. chromium is diffused into the surfaces.
  • This diffusion is achieved by any suitable method, e.g. pack cementation or chemical vapour deposition (CVD) .
  • CVD chemical vapour deposition
  • the layer should typically contain 15 to 30 weight % chromium and be 5 to 25 microns thick.
  • an aluminium diffusion coating is applied to all external surfaces of the blade above dotted line M. This diffusion is again achieved by any suitable method, e.g. pack cementation or CVD. Masking is employed below dotted line M to prevent stray aluminium depositing below this line.
  • a chromium modified aluminide coating results on all external surfaces of the blade above dotted line M.
  • the so called outer beta layer of the chromium modified aluminide coating should typically contain 15 to 30 weight % aluminium and 5 to 15 weight % chromium.
  • the total thickness of the chromium modified aluminide coating, including inter-diffusion zone, should typically be 25 to 100 microns.
  • the blade is heat treated to ensure that it maintains its optimum mechanical properties.
  • the blade coated comprises an outer shroud part 1 (above dotted line A) , an aerofoil part 3 (between dotted lines A and B) , a platform part 5 (between dotted lines B and C) , and a root part 7 (below dotted line C) .
  • the blade includes an internal cooling passage 9 which commences as shown in Fig 3, loops within the blade, and exits (exit not shown) via the top side of shroud part 1.
  • all surfaces of all parts of the blade, including internal cooling passage 9 are chromised, i.e. chromium is diffused into the surfaces. This diffusion is achieved by any suitable method, e.g. pack cementation or CVD. This results in a surface layer rich in chromium.
  • the layer should typically contain 15 to 30 weight % chromium and be 5 to 25 microns thick.
  • an MCrAlY overlay coating (where M is Ni or Co or a combination of the two) is applied to the following parts of the blade: outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5.
  • the coating suitably comprises 30 to 70 weight % Nickel, 30 to 50 weight % Cobalt, 15 to 25 weight % Chromium, 5 to 15 weight % Aluminium, and up to 1 weight % Yttrium.
  • the coating may additionally include one or more elements selected from the group consisting of rhenium, silicon and hafnium.
  • the coating is applied by any suitable method, e.g.
  • thermal spray techniques such as vacuum plasma spraying (VPS) , low pressure plasma spraying (LPPS) , and high velocity ox-fuel spraying (HVOF) , or by electroplating.
  • VPS vacuum plasma spraying
  • LPPS low pressure plasma spraying
  • HVOF high velocity ox-fuel spraying
  • Masking is employed to ensure that MCrAlY is not deposited on the remainder of platform part 5 below top face 11, and on root part 7.
  • outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5 are chromised plus have an overlay coating of MCrAlY, whereas the remainder of platform part 5 below top face 11, root part 7, and internal cooling passage 9 are chromised only.
  • the blade coated comprises an outer shroud part 1 (above dotted line A) , an aerofoil part 3 (between dotted lines A and B) , a platform part 5 (between dotted lines B and C) , and a root part 7 (below dotted line C) .
  • the blade includes an internal cooling passage 9 which commences as shown in Fig 5, loops within the blade, and exits (exit not shown) via the top side of shroud part 1.
  • chromised i.e. chromium is diffused into the surfaces. This diffusion is achieved by any suitable method, e.g. pack cementation or CVD. This results in a surface layer rich in chromium. The layer should typically contain 15 to 30 weight % chromium and be 5 to 25 microns thick.
  • an MCrAlY overlay coating (where M is Ni or Co or a combination of the two) is applied to the following parts of the blade: outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5.
  • the coating suitably comprises 30 to 70 weight % Nickel, 30 to 50 weight % Cobalt, 15 to 25 weight % Chromium, 5 to 15 weight % Aluminium, and up to 1 weight % Yttrium.
  • the coating may additionally include one or more elements selected from the group consisting of rhenium, silicon and hafnium.
  • the coating is applied by any suitable method, e.g. by thermal spray techniques such as VPS, LPPS, and HVOF, or by electroplating. Masking is employed to ensure that MCrAlY is not deposited on the remainder of platform part 5 below top face 11, and on root part 7.
  • those parts of the blade to which the MCrAlY overlay coating was applied are over-aluminised, i.e. an aluminium diffusion coating is applied to these parts.
  • the diffusion is achieved by any suitable method, e.g. pack cementation or CVD.
  • Masking is employed to ensure that stray aluminium is not deposited on the remainder of platform part 5 below top face 11, and on root part 7.
  • the result of the over- aluminisation should be that the outer surface of the MCrAlY overlay coating has an aluminium content of typically 15 to 30 weight %.
  • the total thickness of the over-aluminised MCrAlY coating, including inter-diffusion zone, should typically be 100 to 200 microns.
  • outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5 are chromised plus have an overlay coating of MCrAlY, which MCrAlY overlay coating has been over-aluminised, whereas the remainder of platform part 5 below top face 11, root part 7, and internal cooling passage 9 are chromised only.
  • the application of further coating (s) in addition to the initial chromium diffusion coating is restricted to regions of the rotor blade not subject to higher physical stress in use of the blade.
  • the diffused aluminium coating is restricted to all external surfaces above dotted line M.
  • the MCrAlY overlay coating is restricted to outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5.
  • the MCrAlY overlay coating plus over- aluminisation is restricted to outer shroud part 1, aerofoil part 3, and the top face 11 of platform part 5.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Resistance Heating (AREA)

Abstract

L'invention concerne un procédé permettant de protéger une composante contre la corrosion à chaud, lequel procédé comprend les étapes consistant: (a) à appliquer un revêtement de diffusion de chrome sur la composante et (b) à appliquer un revêtement supplémentaire sur des zones sélectionnées du revêtement de diffusion de chrome, ces zones sélectionnées étant choisies en fonction de l'utilisation subséquente de la composante.
PCT/EP2005/056643 2004-12-11 2005-12-09 Procede permettant de proteger une composante contre la corrosion a chaud WO2006061431A2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP05818992A EP1819906A2 (fr) 2004-12-11 2005-12-09 Procede permettant de proteger une composante contre la corrosion a chaud
US11/792,629 US20070264126A1 (en) 2004-12-11 2005-12-09 Method of Protecting a Component Against Hot Corrosion

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0427155A GB2421032A (en) 2004-12-11 2004-12-11 A method of protecting a component against hot corrosion
GB0427155.7 2004-12-11

Publications (2)

Publication Number Publication Date
WO2006061431A2 true WO2006061431A2 (fr) 2006-06-15
WO2006061431A3 WO2006061431A3 (fr) 2006-08-24

Family

ID=34073550

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/056643 WO2006061431A2 (fr) 2004-12-11 2005-12-09 Procede permettant de proteger une composante contre la corrosion a chaud

Country Status (4)

Country Link
US (1) US20070264126A1 (fr)
EP (1) EP1819906A2 (fr)
GB (1) GB2421032A (fr)
WO (1) WO2006061431A2 (fr)

Cited By (11)

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Publication number Priority date Publication date Assignee Title
EP1788125A2 (fr) * 2005-11-22 2007-05-23 United Technologies Corporation Procédé d'enlèvement d'une revêtment sur un pièce en superalliage
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
EP2166126A1 (fr) * 2008-09-18 2010-03-24 Siemens Aktiengesellschaft Procédé de revêtement et composants de turbines à gaz
EP1980713A3 (fr) * 2007-04-12 2012-01-04 United Technologies Corporation Aube rotorique carénée de turbine et procédé de revêtement pour une telle aube
EP2695964A1 (fr) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Couche de protection adaptée au composant
EP2918783A1 (fr) * 2014-03-12 2015-09-16 Siemens Aktiengesellschaft Aube de turbine avec une plateforme ayant un revêtement
EP3048183A1 (fr) * 2015-01-22 2016-07-27 United Technologies Corporation Procédé d'application de revêtement résistant à la corrosion
WO2018153558A1 (fr) * 2017-02-21 2018-08-30 Siemens Aktiengesellschaft Revêtement et procédé d'application d'un revêtement pour un élément aérodynamique profilé d'un moteur à turbine à gaz
US10113225B2 (en) 2013-03-13 2018-10-30 Howmet Corporation Maskant for use in aluminizing a turbine component
EP3428308A1 (fr) * 2017-07-14 2019-01-16 MTU Aero Engines GmbH Procédé de revêtement d'un composant pour le canal de gaz chaud d'une turbomachine
DE102017213553A1 (de) * 2017-08-04 2019-02-07 MTU Aero Engines AG Schaufel für strömungsmaschine mit verschiedenen diffusionsschutzschichten und verfahren zur herstellung

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GB2439313B (en) * 2006-06-24 2011-11-23 Siemens Ag Method of protecting a component against hot corrosion and a component protected by said method
CN101126146B (zh) * 2007-09-21 2010-06-23 南京利民机械有限责任公司 一种使用井式炉渗铬的方法
US8545185B2 (en) * 2007-12-19 2013-10-01 General Electric Company Turbine engine components with environmental protection for interior passages
EP2098606A1 (fr) * 2008-03-04 2009-09-09 Siemens Aktiengesellschaft Micro-alliage, procédés de production d'une couche de micro-alliage et joint en nids d'abeille
DE102008039969A1 (de) * 2008-08-27 2010-03-04 Mtu Aero Engines Gmbh Turbinenschaufel einer Gasturbine und Verfahren zum Beschichten einer Turbinenschaufel einer Gasturbine
EP2572015A4 (fr) * 2010-05-17 2014-04-02 Aeromet Technologies Inc Dépôt chimique en phase vapeur de couches métalliques pour brasage amélioré
US8662849B2 (en) * 2011-02-14 2014-03-04 General Electric Company Component of a turbine bucket platform
US8967957B2 (en) * 2011-11-03 2015-03-03 General Electric Company Rotating airfoil component of a turbomachine
US20130115072A1 (en) * 2011-11-09 2013-05-09 General Electric Company Alloys for bond coatings and articles incorporating the same
JP6126852B2 (ja) * 2012-02-21 2017-05-10 ハウメット コーポレイションＨｏｗｍｅｔ Ｃｏｒｐｏｒａｔｉｏｎ ガスタービン部品のコーティング及びコーティング方法
EP2743369A1 (fr) * 2012-12-11 2014-06-18 Siemens Aktiengesellschaft Système de revêtement, procédé de revêtement d'un substrat et composant de turbine à gaz
US10584411B2 (en) * 2014-07-18 2020-03-10 United Technologies Corporation Chromium-enriched diffused aluminide
US10023749B2 (en) 2015-01-15 2018-07-17 United Technologies Corporation Method for nitride free vapor deposition of chromium coating
EP3502314A1 (fr) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Améliorations apportées à des revêtements pour des composants d'alliage métallique
WO2019121247A1 (fr) * 2017-12-19 2019-06-27 Siemens Aktiengesellschaft Améliorations concernant des revêtements pour composants en alliage métallique
FR3138451A1 (fr) * 2022-07-28 2024-02-02 Safran Procédé d’application de revêtement et aube de turbine avec revêtement appliqué suivant ce procédé

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US20040161628A1 (en) * 2003-02-19 2004-08-19 Gupta Bhupendra Kumar Article including a substrate with a metallic coating and a chromium-aluminide protective coating thereon, and its preparation and use in component restoration

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US8475598B2 (en) 2005-11-22 2013-07-02 United Technologies Corporation Strip process for superalloys
EP1788125A3 (fr) * 2005-11-22 2007-06-13 United Technologies Corporation Procédé d'enlèvement d'une revêtment sur un pièce en superalliage
EP1788125A2 (fr) * 2005-11-22 2007-05-23 United Technologies Corporation Procédé d'enlèvement d'une revêtment sur un pièce en superalliage
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
US9109279B2 (en) 2005-12-14 2015-08-18 Man Diesel & Turbo Se Method for coating a blade and blade of a gas turbine
EP1980713A3 (fr) * 2007-04-12 2012-01-04 United Technologies Corporation Aube rotorique carénée de turbine et procédé de revêtement pour une telle aube
US8708658B2 (en) * 2007-04-12 2014-04-29 United Technologies Corporation Local application of a protective coating on a shrouded gas turbine engine component
EP2166126A1 (fr) * 2008-09-18 2010-03-24 Siemens Aktiengesellschaft Procédé de revêtement et composants de turbines à gaz
EP2695964A1 (fr) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Couche de protection adaptée au composant
US10113225B2 (en) 2013-03-13 2018-10-30 Howmet Corporation Maskant for use in aluminizing a turbine component
EP2918783A1 (fr) * 2014-03-12 2015-09-16 Siemens Aktiengesellschaft Aube de turbine avec une plateforme ayant un revêtement
EP3048183A1 (fr) * 2015-01-22 2016-07-27 United Technologies Corporation Procédé d'application de revêtement résistant à la corrosion
WO2018153558A1 (fr) * 2017-02-21 2018-08-30 Siemens Aktiengesellschaft Revêtement et procédé d'application d'un revêtement pour un élément aérodynamique profilé d'un moteur à turbine à gaz
EP3428308A1 (fr) * 2017-07-14 2019-01-16 MTU Aero Engines GmbH Procédé de revêtement d'un composant pour le canal de gaz chaud d'une turbomachine
US11359289B2 (en) 2017-07-14 2022-06-14 MTU Aero Engines AG Method for coating a component for the hot gas duct of a turbomachine
DE102017213553A1 (de) * 2017-08-04 2019-02-07 MTU Aero Engines AG Schaufel für strömungsmaschine mit verschiedenen diffusionsschutzschichten und verfahren zur herstellung
US10914181B2 (en) 2017-08-04 2021-02-09 MTU Aero Engines AG Blade or vane for turbomachine with different diffusion protective coatings and method for manufacture thereof

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US20070264126A1 (en) 2007-11-15
EP1819906A2 (fr) 2007-08-22
WO2006061431A3 (fr) 2006-08-24
GB0427155D0 (en) 2005-01-12
GB2421032A (en) 2006-06-14

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