EP2662470A1 - Verwendung von Oxiddispersion-verstärkten Legierungen für Schaufelungsteile - Google Patents

Verwendung von Oxiddispersion-verstärkten Legierungen für Schaufelungsteile Download PDF

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Publication number
EP2662470A1
EP2662470A1 EP12167245.5A EP12167245A EP2662470A1 EP 2662470 A1 EP2662470 A1 EP 2662470A1 EP 12167245 A EP12167245 A EP 12167245A EP 2662470 A1 EP2662470 A1 EP 2662470A1
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EP
European Patent Office
Prior art keywords
airfoil
coating
arrangement
coated
oxide dispersion
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.)
Withdrawn
Application number
EP12167245.5A
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English (en)
French (fr)
Inventor
Anthony Davis
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
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP12167245.5A priority Critical patent/EP2662470A1/de
Publication of EP2662470A1 publication Critical patent/EP2662470A1/de
Withdrawn legal-status Critical Current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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D15/00—Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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

Definitions

  • the present invention relates to an airfoil and to an airfoil arrangement for a gas turbine with a bond coating comprising an oxide dispersion strengthened alloy. Furthermore, the present invention relates to a method for manufacturing an airfoil arrangement for a gas turbine.
  • stator vanes and the rotor blades in a gas turbine are exposed to the high temperature of the working fluid passing the vanes and the blades. Due to the high temperature oxidation of a base alloy e. g. at a leading edge of an airfoil of the stator vane or the rotor blade, or at platforms of an inner shroud or an outer shroud of the stator vane or the rotor blade occur. Such an oxidation may be the life limiting mechanism on this component.
  • Material used for such hot turbine components will exhibit increasing oxidation rates as temperatures increase above 800deg C.
  • the increasing oxidation rate becomes more significant as turbine operating temperatures increase in order to improve the overall efficiency of the turbine.
  • US 5,449,536 A discloses a method for the application of coatings of oxide dispersion strengthened metals by laser powder injection.
  • a laser in a spray apparatus forms a hot zone at a distance above a substrate sufficient to prevent the substrate from melting.
  • An oxide dispersion strengthened metal powder coating material is injected into the hot zone to heat the coating material such that it will be in a plastic state when it impinges against the substrate.
  • the coating material has an initial microstructure before it is injected into the hot zone.
  • the coating material is caused to impinge against the substrate to form a uniform coating on the substrate, wherein the micro structure of the coating on the substrate is substantially identical to the coating material's initial microstructure.
  • the subject may be solved by an airfoil for a gas turbine, an airfoil arrangement and by a method for manufacturing an airfoil for a gas turbine.
  • an airfoil arrangement comprising an airfoil device for a gas turbine.
  • the airfoil device comprises a coated surface section (e.g. a coated "patch") which represents at least a part of the total surface of the airfoil device.
  • the coated surface section is coated with a bond coating which comprises an oxide dispersion strengthened alloy.
  • the bond coating maybe coated with a thermal barrier coating.
  • the airfoil device may comprise an airfoil and an inner shroud.
  • the airfoil device may in addition comprise an outer shroud.
  • the airfoil is arranged between the inner shroud and the outer shroud.
  • a method for manufacturing an airfoil arrangement for a gas turbine comprising an airfoil device.
  • a surface section of the airfoil device is coated with a bond coating which comprises an oxide dispersion strengthened alloy.
  • the coated surface section represents at least a part of the total surface of the airfoil.
  • the bond coating maybe coated with a thermal barrier coating.
  • An airfoil arrangement may describe a rotor blade arrangement or a stator vane arrangement.
  • the airfoil as described above is e.g. a vane, wherein the stator vane arrangement is fixed to a casing of the gas turbine.
  • a rotor blade arrangement is fixed to a rotary shaft of the gas turbine and rotates with respect to the stator vane device.
  • the airfoil of a rotor blade arrangement is a blade which is driven by the working fluid of the gas turbine.
  • the airfoil comprises a leading edge and a trailing edge. At the leading edge, the airfoil has a maximum curvature, for example.
  • the fluid which flows against the airfoil contacts firstly the leading edge and the fluid is separated in a first part which flows along a suction side of the airfoil and in a second part which flows along a pressure side of the airfoil.
  • the suction side is generally associated with higher velocity and thus lower static pressure.
  • the pressure side has a comparatively higher static pressure than the suction side.
  • the trailing edge defines the edge of the airfoil where the fluid flowing along the suction surface and the fluid flowing along the pressure surface is emerged again.
  • the airfoil device may comprise one airfoil or a plurality of further airfoils which are spaced apart from each other along a circumferential direction with respect to a rotary axis of the gas turbine.
  • the airfoil device further comprises an inner shroud.
  • the airfoil extends from the inner shroud.
  • the inner shroud is located closer to the rotary axis of the gas turbine than the airfoil.
  • the inner shroud comprises a first inner platform.
  • the airfoil device further comprises an outer shroud.
  • the airfoil is arranged between the inner shroud and the outer shroud.
  • the leading edge and the trailing edge extend between the inner shroud and the outer shroud.
  • the inner shroud is located closer to the rotary axis of the gas turbine than the outer shroud.
  • the outer shroud comprises a second inner platform, wherein respective inner surfaces of the inner and outer shroud face the inner volume of the gas turbine through which inner volume the hot working gas streams. Hence, the respective inner surfaces of the inner and outer shroud are gas-washed by the hot working gas of the gas turbine.
  • a thinning out section may be formed onto a surface of the airfoil.
  • the thickness of the thermal barrier coating i.e. the ceramic-based coating
  • the thickness of the thermal barrier coating is thinning out (in particular till zero thickness) from the edge of the coated surface section to the inner and the outer shroud, respectively, so that i.e. the first inner platform and/or the second inner platform which is/are washed by working fluid of the turbine is/are free of a thermal barrier coating.
  • TBC thermal barrier coating
  • the bond coating enforces the bonding of the ceramic coating (i.e. the thermal barrier coating (TBC)) to the surface of the airfoil in comparison to a direct coating of the thermal barrier coating (TBC) to the surface of the airfoil device.
  • the bond coating is located beneath the thermal barrier coating, i.e. between the airfoil and the thermal barrier coating.
  • the bond coating comprising the oxide dispersion strengthened alloy provides the airfoil with a corrosion resistance and high temperature oxidation protection.
  • the bond coating may be used without a thermal barrier coating on features or sections of the airfoil arrangement, which operate e.g. at a lower temperature than the airfoils.
  • the thermal barrier coating may reduce the temperature of the airfoil.
  • the (ceramic) thermal barrier coating may require a bond coat to enable it to adhere to the surface of the airfoil.
  • the bond coating is used as described above.
  • the bond coat acts as an interface between the TBC coating and the base material of the airfoil.
  • the coated surface section covers the airfoil of the airfoil device from the leading edge to the trailing edge along the suction side and/or the pressure side of the airfoil.
  • the coating life at the leading edge of the airfoil is increased.
  • additional efficient protection against oxidation is achieved.
  • the bond coating comprising the oxide dispersion strengthened alloy coating may be coated onto the coated surface section by application methods such as electro-plating, thermal spray techniques and/or Electron Beam Vapour Deposition (EPPVD).
  • the airfoil may be exposed to a heat treatment, so that a partial diffusion between the coated layers occurs. Additionally, a final ageing heat treatment may be applied for the airfoil substrate material.
  • a post coating surface finish may be applied to the coated surface section in order to achieve a desired roughness of the coating.
  • Oxide dispersion strengthened (O.D.S.) alloys may comprise in particular iron (with the chemical symbol Fe) and/or nickel (Ni) constituents (e.g. primary constituents). Additionally or alternatively oxide dispersion strengthened alloys may also comprise chrome (Cr), aluminium (Al), titanium (Ti), molybdenum (Mo), tungsten (W), carbon (C) and/or yttrium (Y), in particular Yttrium(III) oxide (Y203) constituents (first and/or second constituents).
  • oxide dispersion strengthened alloys based on iron (Fe) may have an oxidation resistance superior to that of the aluminide based coatings of approximately five times better than the base material of the airfoil.
  • oxide dispersion strengthened alloys as a bond coating will result in a significant increase in the service life of the airfoil for the common operating temperatures or in an increase in operating temperatures thus improving engine efficiency.
  • oxide dispersion strengthened alloy may also be used as a bond coat for the thermal barrier coating which increases the coating life for the same operational temperature of the gas turbines.
  • Fig. 1 shows an airfoil arrangement 100, in particular a stator vane arrangement, for a gas turbine.
  • the airfoil arrangement 100 comprises an airfoil device 101, 110, 120, comprising e.g. an airfoil 101 (e.g. a vane) with a leading edge 102 and a trailing edge 103.
  • the leading edge 102 is covered by a coated surface section 104 which comprises a bond coating 302 (see Fig. 3 ).
  • the airfoil device 101, 110, 120 may further comprise an inner shroud 110 and an outer shroud 120.
  • the airfoil 101 is arranged between the inner shroud 110 and the outer shroud 120.
  • the inner shroud 110 and the outer shroud 120 may comprise also a coated surface section 106, 106' which is coated with a bond coating 302 (see Fig. 3 ) comprising an oxide dispersion strengthened alloy.
  • the bond coating 302 is coated with a thermal barrier coating 302 (see Fig. 3 ).
  • the leading edge 102 and the trailing edge 103 extend between the inner shroud 110 and the outer shroud 120.
  • Fig. 1 further shows a flow direction F of a working fluid of the gas turbine.
  • the working fluid flows against the leading edge 102.
  • the working fluid streams along the surfaces of the airfoil 101, i.e. the pressure side and the suction side, and leave the airfoil 101 at the trailing edge 103.
  • the coated surface section 104 is shown which represents at least a part of the total surface of the airfoil 101.
  • the coated surface section 104 is coated with a bond coating 302 (see Fig. 3 ) which comprises an oxide dispersion strengthened alloy.
  • the bond coating 302 is coated with a thermal barrier coating 303(see Fig.3 ).
  • the coated surface section 104 may be spaced apart from the respective inner shroud 110 or the outer shroud 120. Between the coated surface section 104 and the respective inner shroud 110 or the outer shroud 120 a transition section, i.e. a thinning out section 105, may be formed.
  • the coated surface section 104 is spaced from the inner shroud 110 and/or the outer shroud 120 with a distance x.
  • the distance x is measured e.g. by a length along a normal of a plane in which the inner surface of the inner shroud 110 or the inner surface of the outer shroud 120, respectively, is located.
  • guiding rails are located at the inner shroud 110 and/or at the outer shroud 120.
  • the guiding rails are needed for a fixation of the airfoil arrangement 100 to a respective housing of the turbine or for guiding cooling fluid.
  • surface sections 106", 106"', 106"" are coated for example with a further anti-oxidation coating, e. g. a MCrAlY or a PtAl coating, a vapor phase aluminide coating and/or an oxide dispersion strengthened alloy coating.
  • Fig. 2 shows an exemplary embodiment of an airfoil arrangement 100 which comprises an airfoil device with the airfoil 101 and with further airfoils 201, 201', 201".
  • the airfoils 101, 201, 201', 201" are arranged between the inner shroud 110 and the outer shroud 120.
  • an inner surface 106 of the inner shroud 110 is shown.
  • the inner surface 106 of the inner shroud faces the inner volume of the gas turbine through which the hot working fluid flows. Hence, the inner surface 106 is washed by the hot working fluid.
  • the inner surface 106 of the inner shrouds 110 and/or the inner surface of the outer shrouds 120 may be coated with an oxidation and corrosion preventative coating in order to reduce oxidation and corrosion.
  • Seal slots such as scallop seal slots, and machined surfaces of the airfoil arrangement 100 may be kept free from any coating in order to maintain the original dimensions.
  • Fig. 3 shows a layer composition of the coated section 104 of the airfoil 101 with respective coatings according to an exemplary embodiment of the present invention.
  • the bond coating 302 is used in connection with a thermal barrier coating (TBC) 303.
  • the bond coating 302 comprises an oxide dispersion strengthened alloy and functions as a bond coat for e.g. ceramic coatings (i.e. the thermal barrier coating 303).
  • the bond coating 302 is located beneath the thermal barrier coating 303, i.e. between the airfoil surface 301 and the thermal barrier coating 303.
  • the thermal barrier coating 303 forms metaphorically a "feathered section" onto the bond coating 302.
EP12167245.5A 2012-05-09 2012-05-09 Verwendung von Oxiddispersion-verstärkten Legierungen für Schaufelungsteile Withdrawn EP2662470A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12167245.5A EP2662470A1 (de) 2012-05-09 2012-05-09 Verwendung von Oxiddispersion-verstärkten Legierungen für Schaufelungsteile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12167245.5A EP2662470A1 (de) 2012-05-09 2012-05-09 Verwendung von Oxiddispersion-verstärkten Legierungen für Schaufelungsteile

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056590A1 (de) * 2015-02-16 2016-08-17 United Technologies Corporation Klingenwiederherstellung unter verwendung von ummantelungsplattierung und hergestelltes produkt
US20230138749A1 (en) * 2021-10-29 2023-05-04 Pratt & Whitney Canada Corp. Selectively coated gas path surfaces within a hot section of a gas turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5449536A (en) 1992-12-18 1995-09-12 United Technologies Corporation Method for the application of coatings of oxide dispersion strengthened metals by laser powder injection
EP0933448A1 (de) * 1998-02-02 1999-08-04 General Electric Company Verbesserte Aluminid-Diffusionsverbundschicht für thermische Sperrschichtsysteme und Verfahren dazu
US6485845B1 (en) * 2000-01-24 2002-11-26 General Electric Company Thermal barrier coating system with improved bond coat
EP1391531A2 (de) * 2002-08-05 2004-02-25 United Technologies Corporation Wärmedämmschicht mit Nitridpartikeln
EP1469100A1 (de) * 2003-04-18 2004-10-20 General Electric Company Nickel-Aluminid-Beschichtung und diese aufweisendes Schichtsystem
EP1806433A2 (de) * 2005-12-09 2007-07-11 General Electric Company Diffusionsschicht und Verfahren zum Herstellen

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5449536A (en) 1992-12-18 1995-09-12 United Technologies Corporation Method for the application of coatings of oxide dispersion strengthened metals by laser powder injection
EP0933448A1 (de) * 1998-02-02 1999-08-04 General Electric Company Verbesserte Aluminid-Diffusionsverbundschicht für thermische Sperrschichtsysteme und Verfahren dazu
US6485845B1 (en) * 2000-01-24 2002-11-26 General Electric Company Thermal barrier coating system with improved bond coat
EP1391531A2 (de) * 2002-08-05 2004-02-25 United Technologies Corporation Wärmedämmschicht mit Nitridpartikeln
EP1469100A1 (de) * 2003-04-18 2004-10-20 General Electric Company Nickel-Aluminid-Beschichtung und diese aufweisendes Schichtsystem
EP1806433A2 (de) * 2005-12-09 2007-07-11 General Electric Company Diffusionsschicht und Verfahren zum Herstellen

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056590A1 (de) * 2015-02-16 2016-08-17 United Technologies Corporation Klingenwiederherstellung unter verwendung von ummantelungsplattierung und hergestelltes produkt
US20230138749A1 (en) * 2021-10-29 2023-05-04 Pratt & Whitney Canada Corp. Selectively coated gas path surfaces within a hot section of a gas turbine engine

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