US20070264126A1 - Method of Protecting a Component Against Hot Corrosion - Google Patents

Method of Protecting a Component Against Hot Corrosion Download PDF

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Publication number
US20070264126A1
US20070264126A1 US11/792,629 US79262905A US2007264126A1 US 20070264126 A1 US20070264126 A1 US 20070264126A1 US 79262905 A US79262905 A US 79262905A US 2007264126 A1 US2007264126 A1 US 2007264126A1
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US
United States
Prior art keywords
turbine blade
coating
layer
aerofoil
weight
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.)
Abandoned
Application number
US11/792,629
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English (en)
Inventor
Paul Box
Mick Whitehurst
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOX, PAUL, WHITEHURST, MICK
Publication of US20070264126A1 publication Critical patent/US20070264126A1/en
Abandoned legal-status Critical Current

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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
    • 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.
  • MCrAlY overlay coatings (where M is Ni or Co or a combination of the two) have been used as an alternative to diffusion coatings at higher temperatures to protect against oxidation.
  • diffused chromium alone (chromising) is known to provide excellent protection against relatively low temperature Type II hot corrosion, and further to be strain tolerant (to have no effect on the fatigue properties of the substrate).
  • 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 % Yttrium.
  • 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 .
  • 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 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. If such stray depositing does occur, this is acceptable between dotted lines M and S, but not below dotted line S, i.e. not on the so called fir tree root of root part 7 .
  • 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.
  • 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 .
  • the blade is heat treated to ensure that it maintains its optimum mechanical properties.
  • 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 .
  • 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.
  • 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.
  • the blade is heat treated to ensure that it maintains its optimum mechanical properties.
  • 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)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Resistance Heating (AREA)
US11/792,629 2004-12-11 2005-12-09 Method of Protecting a Component Against Hot Corrosion Abandoned US20070264126A1 (en)

Applications Claiming Priority (3)

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
PCT/EP2005/056643 WO2006061431A2 (de) 2004-12-11 2005-12-09 A method of protecting a component against hot corrosion

Publications (1)

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US20070264126A1 true US20070264126A1 (en) 2007-11-15

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US11/792,629 Abandoned US20070264126A1 (en) 2004-12-11 2005-12-09 Method of Protecting a Component Against Hot Corrosion

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US (1) US20070264126A1 (de)
EP (1) EP1819906A2 (de)
GB (1) GB2421032A (de)
WO (1) WO2006061431A2 (de)

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US20090162209A1 (en) * 2007-12-19 2009-06-25 David John Wortman Turbine engine components with environmental protection for interior passages
US20130115096A1 (en) * 2011-11-03 2013-05-09 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
US9109279B2 (en) 2005-12-14 2015-08-18 Man Diesel & Turbo Se Method for coating a blade and blade of a gas turbine
US20150300200A1 (en) * 2012-12-11 2015-10-22 Siemens Aktiengesellschaft Coating system, method of coating a substrate, and gas turbine component
US20160010472A1 (en) * 2012-02-21 2016-01-14 Howment Corporation Coating and coating method for gas turbine engine component
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
WO2024023428A1 (fr) * 2022-07-28 2024-02-01 Safran Procede d'application de revetement et aube de turbine avec revetement applique suivant ce procede
US11987877B2 (en) * 2014-07-18 2024-05-21 Rtx Corporation Chromium-enriched diffused aluminide coating

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US20070116875A1 (en) * 2005-11-22 2007-05-24 United Technologies Corporation Strip process for superalloys
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
US8708658B2 (en) * 2007-04-12 2014-04-29 United Technologies Corporation Local application of a protective coating on a shrouded gas turbine engine component
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
EP2098606A1 (de) * 2008-03-04 2009-09-09 Siemens Aktiengesellschaft MCrAIY-Legierung, Verfahren zur Herstellung einer MCrAIY-Schicht und Wabendichtung
DE102008039969A1 (de) * 2008-08-27 2010-03-04 Mtu Aero Engines Gmbh Turbinenschaufel einer Gasturbine und Verfahren zum Beschichten einer Turbinenschaufel einer Gasturbine
EP2166126A1 (de) * 2008-09-18 2010-03-24 Siemens Aktiengesellschaft Verfahren zur Beschichtung und Gasturbinenkomponente
US9139903B2 (en) 2010-05-17 2015-09-22 Aeromet Technologies, Inc. Chemical vapor deposition of metal layers for improved brazing
US8662849B2 (en) * 2011-02-14 2014-03-04 General Electric Company Component of a turbine bucket platform
EP2695964B1 (de) * 2012-08-10 2020-05-06 MTU Aero Engines AG Bauteilangepasste Schutzschicht
JP6480662B2 (ja) 2013-03-13 2019-03-13 ハウメット コーポレイションＨｏｗｍｅｔ Ｃｏｒｐｏｒａｔｉｏｎ タービン部品のアルミナイジングに用いられるマスカント
EP2918783A1 (de) * 2014-03-12 2015-09-16 Siemens Aktiengesellschaft Turbinenschaufel mit einer beschichteten Plattform
US10023749B2 (en) * 2015-01-15 2018-07-17 United Technologies Corporation Method for nitride free vapor deposition of chromium coating
US9932665B2 (en) * 2015-01-22 2018-04-03 United Technologies Corporation Corrosion resistant coating application method
GB2559806A (en) * 2017-02-21 2018-08-22 Siemens Ag Coating and method of applying a coating for an aerofoil of a gas turbine engine
DE102017212075A1 (de) * 2017-07-14 2019-01-17 MTU Aero Engines AG Verfahren zum Beschichten eines Bauteils für den Heißgaskanal einer Strömungsmaschine
EP3502314A1 (de) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Verbesserungen im zusammenhang mit beschichtungen für metalllegierungskomponenten
WO2019121247A1 (en) * 2017-12-19 2019-06-27 Siemens Aktiengesellschaft Improvements relating to coatings for metal alloy components

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Cited By (15)

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WO2006061431A3 (de) 2006-08-24
EP1819906A2 (de) 2007-08-22
GB0427155D0 (en) 2005-01-12
GB2421032A (en) 2006-06-14
WO2006061431A2 (de) 2006-06-15

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