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WO1996034129A1 - Composant de superalliage presentant un systeme de revetement protecteur - Google Patents

Composant de superalliage presentant un systeme de revetement protecteur Download PDF

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Publication number
WO1996034129A1
WO1996034129A1 PCT/EP1996/001565 EP9601565W WO9634129A1 WO 1996034129 A1 WO1996034129 A1 WO 1996034129A1 EP 9601565 W EP9601565 W EP 9601565W WO 9634129 A1 WO9634129 A1 WO 9634129A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
article according
anchoring layer
anchoring
substrate
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.)
Ceased
Application number
PCT/EP1996/001565
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English (en)
Inventor
Wolfram Beele
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to UA97105207A priority Critical patent/UA46760C2/uk
Priority to DK96910964T priority patent/DK0832313T3/da
Priority to JP8532129A priority patent/JPH11504075A/ja
Priority to DE69606708T priority patent/DE69606708T2/de
Priority to EP96910964A priority patent/EP0832313B1/fr
Publication of WO1996034129A1 publication Critical patent/WO1996034129A1/fr
Anticipated expiration legal-status Critical
Priority to US08/958,260 priority patent/US5985467A/en
Priority to US09/419,692 priority patent/US6071556A/en
Ceased legal-status Critical Current

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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
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/024—Deposition of sublayers, e.g. to promote adhesion of the coating
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/0676—Oxynitrides
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C23C14/081—Oxides of aluminium, magnesium or beryllium
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • 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
    • 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

Definitions

  • the invention relates to a superalloy component which has applied thereon a protective coating system with various layers.
  • U.S. Patent Nos. 4,055,705 to Stecura et al. ; 4,321,310 to Ulion et al. , and 4,321,311 to Strangman disclose coating systems for gas turbine components made from nickel or cobalt-based superalloys.
  • a coating system described comprises a thermal barrier layer made from ceramic, which in particular has a columnar grained structure, placed on a bonding layer or bond coating which in its turn is placed on the substrate and bonds the thermal barrier layer to the substrate.
  • the bonding layer is made from an alloy of the MCrAlY type, namely an alloy containing chromium, aluminum and a rare earth metal such as yttrium in a base comprising at least one of iron, cobalt and nickel.
  • an important feature of the bonding layer is a thin layer developed on the MCrAlY alloy and used for anchoring the thermal barrier layer.
  • This layer may be alumina or alumina mixed with chromium oxide, depending on the composition of the MCrAlY alloy and the temperature of the oxidizing environment where the layer is developed.
  • an alumina layer may be placed purposefully by a separate coating process like PVD.
  • U.S. Patent No. 5,238,752 to Duderstadt et al. discloses a coating system for a gas turbine component which also incorporates a ceramic thermal barrier layer and a bonding layer or bond coating bonding the thermal barrier layer to the substrate.
  • the bonding layer is made from an intermetallic alu inide compound, in particular a nickel aluminide or a platinum aluminide.
  • the bonding layer also has a thin alumina layer which serves to anchor the thermal barrier layer.
  • U.S. Patent No. 5,262,245 to Ulion et al. describes a result of an effort to simplify coating systems incorporating thermal barrier layers for gas turbine components by avoiding a bonding layer to be placed below the thermal barrier layer.
  • a composition for a superalloy which may be used to form a substrate of a gas turbine component and which develops an alumina layer on its outer surfaces under a suitable treatment. That alumina layer is used to anchor a ceramic thermal barrier layer directly on the substrate, eliminating the need for a special bonding layer to be interposed between the substrate and the thermal barrier layer.
  • the superalloy consists essentially of, as specified in weight percent: 3 to 12 Cr, 3 to 10 W, 6 to 12 Ta, 4 to 7 Al, 0 to 15 Co, 0 to 3 Mo, 0 to 15 Re, 0 to 0.0020 B, 0 to 0.045 C, 0 to 0.8 Hf, 0 to 2 Nb, 0 to 1 V, 0 to 0.01 Zr, 0 to 0.07 Ti, 0 to 10 of the noble metals, 0 to 0.1 of the rare earth metals including Sc and Y, balance Ni.
  • U.S. Patent No. 5,087,477 to Giggins, Jr., et al shows a method for placing a ceramic thermal barrier layer on a gas turbine component by a physical vapor deposition process comprising evaporating compounds forming the thermal barrier layer with an electron beam and establishing an atmosphere having a controlled content of oxygen at the component to receive the thermal barrier layer.
  • modified alumina compounds may be derived from an essay by L. Peichl and D. Bettridge entitled “Overlay and Diffusion Coatings for Aero Gas Turbines” and contained in a book entitled “Materials for Advanced Power Engineering, Part One", edited by D. Coutsouradis et al. , Kluwer Academic Publishers, Dordrecht, Netherlands, 1994, pages 717-740, and from an essay by 0. Knotek, E. Lugscheider, F. L ⁇ ffler and W. Beele, published in: Surface and Coating Techniques, Vol. 68/69 (1994), pages 22 to 26.
  • a standard practice in placing a thermal barrier coating on a substrate of an article of manufacture includes developing an oxide layer on the article, either by placing a suitable bonding layer on the article which develops the oxide layer on its surface under oxidizing conditions or by selecting a material for the article which is itself capable of developing an oxide layer on its surface.That oxide layer is then used to anchor the thermal barrier layer placed on it subsequently. Under thermal load, diffusion processes will occur within the article. In particular, diffusion active chemical elements like hafnium, titanium, tungsten and silicon which form constituents of most superalloys used for the articles considered may migrate through the oxide layer and into the thermal barrier layer. The diffusion active chemical elements may cause damage to the thermal barrier layer by modifying and eventually worsening its essential properties.
  • a thermal barrier layer made from a zirconia compound like partly stabilized zirconia, since almost all zirconia compounds must rely on certain ingredients to define and stabilize their particular properties. The action of such ingredients is likely to be imparted by chemical elements migrating into a compound, be it by diffusion or otherwise.
  • thermal barrier layer placed on a substrate containing diffusion active chemical elements keeps its essential properties over a time period as long as may be desired, it is therefore material to prevent migration of diffusion active chemical elements into the thermal barrier layer.
  • an article of manufacture comprising: a substrate formed of a nickel or cobalt-based superalloy; an anchoring layer disposed on the substrate, the anchoring layer comprising an oxide compound doped with nitrogen; and a ceramic coating disposed on the anchoring layer.
  • the oxide compound comprises alumina and/or chromium oxide.
  • the oxide compound consists essentially of alumina.
  • the article includes a diffusion active chemical element covered by the anchoring layer.
  • the diffusion active chemical element is preferably an element selected from the group consisting of hafnium, titanium, tungsten and silicon.
  • the diffusion active element is contained in the substrate or a bonding layer disposed thereon.
  • the ceramic coating includes Zr0 2 .
  • the ceramic coating consists essentially of Zr0 2 and a stabilizer selected from the group consisting of Y 2 0 3 , Ce0 2 , LaO and MgO.
  • the anchoring layer has a thickness of less than 3 urn.
  • the anchoring layer contains from 1 to 10 atom percent of nitrogen, and preferably from 2 to 5 atom percent.
  • the anchoring layer is also doped with a further chemical element, the further chemical element being also covered by the anchoring layer.
  • the further chemical element is chromium.
  • the further chemical element is contained in the substrate or a bonding layer disposed thereon.
  • the anchoring layer is doped with a further chemical element, and the further chemical element is also present in the ceramic coating.
  • the article is provided with a bonding layer interposed between the substrate and the anchoring layer.
  • the bonding layer is formed of a metal aluminide, or it is formed of an MCrAlY alloy.
  • the anchoring layer is doped with a further chemical element, and the further element is also present in the bonding layer.
  • the substrate, the bonding layer (if present) , the anchoring layer and the ceramic coating form a gas turbine component.
  • the gas turbine component is a gas turbine airfoil component comprising a mounting portion and an airfoil portion, the mounting portion being adapted to fixedly hold the component in operation and the airfoil portion being adapted to be exposed to a gas stream streaming along the component in operation, the anchoring layer and the ceramic layer being disposed on the airfoil portion.
  • the substrate may have a bonding layer placed thereon, as described hereinabove.
  • the method comprises the following steps: placing an anchoring layer comprising an oxide compound doped with nitrogen on a substrate formed of a nickel or cobalt-based superalloy; and placing a ceramic coating on the anchoring layer.
  • the step of placing the anchoring layer is performed by a physical vapor deposition process.
  • a physical vapor deposition process including sputtering or electron beam evaporation is used.
  • the step of placing the anchoring layer comprises: placing a layer comprising an other oxide compound essentially free of nitrogen on the substrate; establishing an atmosphere containing nitrogen around the layer; and - creating the anchoring layer by subjecting the layer and the atmosphere to an elevated temperature and diffusing the nitrogen into the layer.
  • the ceramic coating may also be placed onto the system by physical vapor deposition (PVD) process.
  • Fig. 1 is a fragmentary cross-sectional view of a substrate having a protective coating system incorporating a ceramic coating placed thereon;
  • Fig. 2 is a perspective view of a gas turbine airfoil component comprising the substrate and protective coating system shown in Fig. 1.
  • a substrate 1 of an article of manufacture in particular a gas turbine component, which in operation is subject to heavy thermal load and concurrently to corrosive and erosive attack.
  • the substrate 1 is formed of a material which is suitable to provide strength and structural stability when subjected to a heavy thermal load and eventually an additional mechanical load by severe forces like centrifugal forces.
  • a material which is widely recognized and employed for such a purpose in a gas turbine engine is a nickel or cobalt-based superalloy.
  • a thermal barrier layer 2 is placed thereon.
  • the thermal barrier layer 2 is made from a columnar grained ceramic, in particular consisting essentially of a stabilized or partly stabilized zirconia, as explained above.
  • the thermal barrier layer 2 is anchored to the substrate 1 by means of an intermediate layer 3.
  • the intermediate layer 3 is made by placing a bonding layer 4 on the substrate 1, which bonding layer 4 consists of an MCrAlY alloy and preferably of an MCrAlY alloy as disclosed in one of U.S. Patents 5,154,885; 5,268,238; 5,273,712; and 5,401,307, and developing an anchoring layer 5 on the bonding layer 4, as explained subsequently.
  • the bonding layer 4 has certain functions in common with a bonding layer as known from the state of the art and in particular has a tight bond to the substrate 1.
  • the anchoring layer 5 serves as an anchor for the thermal barrier layer 2. Both the bonding layer 4 and the anchoring layer 5 form the intermediate layer 3.
  • the drawing is not intended to show the thicknesses of the layers 4 and 5 to scale; the thickness of the anchoring layer 5 might in reality be very much less than the thickness of the bonding layer 4 and amount only to a few atomic layers, as specified hereinabove.
  • the anchoring layer 5 essentially consists of an oxide compound, namely alumina, doped with nitrogen.
  • the nitrogen content need not be very high, and a nitrogen content of a few atom percent is considered to be effective.
  • the effect of the nitrogen doping in the anchoring layer 5 relies on the fact that the nitrogen atoms distributed in the oxide crystals, which are ion crystals made from positively charged metal ions and 0 2" ions, introduce imbalances into the distribution of electric charges in the ion crystal and thus hinder diffusion of atoms through the ion crystal. It can be said that an addition of a minor quantity of atoms effectively different from the atoms or related ions making up the crystal introduces irregularities into the crystal and renders it opaque or impenetrable for diffusing atoms, which no longer experience a regular pattern of constituents essential for easy penetration through a crystal. An addition of nitrogen in a considerably large amount and far beyond any addition which might be considered to be a doping could of course give rise to a complete restructuring of an oxide crystal into a crystal consisting of a regular pattern of metal, oxygen and nitrogen constituents.
  • the anchoring layer 5 can be made by several methods, in particular by a physical vapor deposition process like electron beam PVD, sputter ion plating and cathodic arc-PVD, or by thermal treatment of an oxide compound layer in a nitrogen-containing atmosphere. Such thermal treatment is in particular carried out at a temperature within a range between 700°C and 1100°C.
  • a nitrogen-containing atmosphere may also serve to provide the nitrogen for a PVD-process, which comprises evaporating the required metal and oxygen compound from a suitable source and adding the nitrogen from the atmosphere.
  • the nitrogen-containing atmosphere essentially consists of argon, oxygen and nitrogen, at a total pressure between 10 "2 Pa and 1 Pa. Fig.
  • the component 2 shows the complete gas turbine component, namely a gas turbine airfoil component 6, in particular a turbine blade.
  • the component 6 has an airfoil portion 7, which in operation forms an "active part" of the gas turbine engine, a mounting portion 8, at which the component 6 is fixedly held in its place, and a sealing portion 9, which forms a seal together with adjacent sealing portions of neighboring components to prevent an escape of a gas stream 10 flowing along the airfoil portion 7 during operation.
  • Fig. 1 The section of Fig. 1 is taken along the line I-I in Fig. 2.
  • the anchoring layer 5 has a high content of compounds made up of metal and oxygen, whereof an exact chemical formula can hardly been given due to the distorting action of the nitrogen also present, it is indeed very suitable for anchoring a thermal barrier layer 2.
  • That thermal barrier layer 2 may expediently be deposited on the substrate 1 immediately after deposition of the anchoring layer 5 and in particular within the same apparatus and by using as much as possible installations which have been already in use for depositing the anchoring layer 5.
  • the combination of the anchoring layer 5 and the thermal barrier layer 2 thus made has all the advantages of such combinations known from the prior art and additionally features a substantially prolonged lifetime due to the suppression of migration of diffusion active elements into the thermal barrier layer 2.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Physical Vapour Deposition (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

On a couvert un substrat (1) de superalliage à base de nickel ou de cobalt, avec un système protecteur résistant à la chaleur, à la corrosion ainsi qu'à l'érosion. On a disposé sur ce substrat une couche (5) d'ancrage, laquelle se présente sous forme d'un composé d'oxyde dopé à l'azote, ledit composé étant notamment de l'oxyde d'aluminium. On a déposé sur la couche d'ancrage un revêtement (2) céramique. La modification de la couche d'ancrage empêche la transmission, à travers elle et en direction de la couche d'isolation thermique, d'éléments diffuseurs.
PCT/EP1996/001565 1995-04-25 1996-04-12 Composant de superalliage presentant un systeme de revetement protecteur Ceased WO1996034129A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
UA97105207A UA46760C2 (uk) 1995-04-25 1996-04-12 Деталь із суперсплаву з системою захисного покриття і спосіб його нанесення
DK96910964T DK0832313T3 (da) 1995-04-25 1996-04-12 Superlergeringskomponent med et beskyttende belægningssystem
JP8532129A JPH11504075A (ja) 1995-04-25 1996-04-12 保護被覆システムを有する超合金構成要素
DE69606708T DE69606708T2 (de) 1995-04-25 1996-04-12 Bauteil aus superlegierung mit einem schutzschichtsystem
EP96910964A EP0832313B1 (fr) 1995-04-25 1996-04-12 Composant de superalliage presentant un systeme de revetement protecteur
US08/958,260 US5985467A (en) 1995-04-25 1997-10-27 Superalloy component with a protective coating system
US09/419,692 US6071556A (en) 1995-04-25 1999-10-14 Method of coating an article of manufacturing having a substrate formed of a nickel or cobalt-based superalloy

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US42844995A 1995-04-25 1995-04-25
US08/428,449 1995-04-25
US08/428,452 1995-04-25

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
US42845295A Continuation 1995-04-25 1995-04-25
US42844995A Continuation 1995-04-25 1995-04-25

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US08/958,260 Continuation US5985467A (en) 1995-04-25 1997-10-27 Superalloy component with a protective coating system

Publications (1)

Publication Number Publication Date
WO1996034129A1 true WO1996034129A1 (fr) 1996-10-31

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Application Number Title Priority Date Filing Date
PCT/EP1996/001565 Ceased WO1996034129A1 (fr) 1995-04-25 1996-04-12 Composant de superalliage presentant un systeme de revetement protecteur

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RU (1) RU2165478C2 (fr)
WO (1) WO1996034129A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19807359A1 (de) * 1998-02-21 1999-08-26 Deutsch Zentr Luft & Raumfahrt Wärmedämmschichtsystem mit integrierter Aluminiumoxidschicht
EP0949410A2 (fr) 1998-04-07 1999-10-13 GHH BORSIG Turbomaschinen GmbH Conduit de transition revêtu pour une turbine à gaz
EP1637622A1 (fr) 2004-09-15 2006-03-22 Man Turbo Ag Procédé pour le dépôt d'un revêtement protecteur
CN102416459A (zh) * 2011-11-28 2012-04-18 机械科学研究总院先进制造技术研究中心 一种超高温成型模具及其制备方法
US11655544B2 (en) 2018-10-17 2023-05-23 Oerlikon Surface Solutions Ag, Pfäffikon PVD barrier coating for superalloy substrates

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RU2613005C1 (ru) * 2015-12-03 2017-03-14 Общество С Ограниченной Ответственностью "Твинн" Материал керамического слоя теплозащитного покрытия
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DE19807359A1 (de) * 1998-02-21 1999-08-26 Deutsch Zentr Luft & Raumfahrt Wärmedämmschichtsystem mit integrierter Aluminiumoxidschicht
EP0937786A3 (fr) * 1998-02-21 2001-05-16 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de revêtement de barrière thermique avec une couche d'alumine intégrée
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US6226978B1 (en) 1998-04-07 2001-05-08 Ghh Borsig Turbomaschinen Gmbh Hot gas-carrying gas collection pipe of gas turbine
EP1637622A1 (fr) 2004-09-15 2006-03-22 Man Turbo Ag Procédé pour le dépôt d'un revêtement protecteur
US7736704B2 (en) 2004-09-15 2010-06-15 Man Turbo Ag Process for applying a protective layer
CN102416459A (zh) * 2011-11-28 2012-04-18 机械科学研究总院先进制造技术研究中心 一种超高温成型模具及其制备方法
US11655544B2 (en) 2018-10-17 2023-05-23 Oerlikon Surface Solutions Ag, Pfäffikon PVD barrier coating for superalloy substrates

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