WO2008104188A1 - Component with a substrate and a protective layer - Google Patents

Component with a substrate and a protective layer Download PDF

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Publication number
WO2008104188A1
WO2008104188A1 PCT/EP2007/001289 EP2007001289W WO2008104188A1 WO 2008104188 A1 WO2008104188 A1 WO 2008104188A1 EP 2007001289 W EP2007001289 W EP 2007001289W WO 2008104188 A1 WO2008104188 A1 WO 2008104188A1
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WO
WIPO (PCT)
Prior art keywords
layer zone
component
outer layer
balance
zone
Prior art date
Application number
PCT/EP2007/001289
Other languages
French (fr)
Inventor
Werner Stamm
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 EP07703474A priority Critical patent/EP2115186A1/en
Priority to PCT/EP2007/001289 priority patent/WO2008104188A1/en
Publication of WO2008104188A1 publication Critical patent/WO2008104188A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • 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
    • C23C28/32—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
    • C23C28/325—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with layers graded in composition or in physical properties
    • 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
    • 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

Definitions

  • the invention relates to a component with a substrate and a protective layer, which consists of an intermediate NiCoCrAlY layer zone on the substrate and an outer layer zone arranged on the intermediate NiCoCrAlY layer zone .
  • the bonding of the three different layers is crucial for a high durability of the protection layer as a whole. Problems may arise, if there are big differences in the thermal expansion factors of the different layers. In this case failure of the thermal barrier coating might occur, which can lead to the destruction of the whole compound.
  • the US-PS-5, 792, 521 shows a multi layer thermal barrier coating.
  • US-PS-5, 514,482 discloses a thermal barrier coating system for super alloy components, in which the MCrAlY layer is substituted by an aluminium coating layer such as NiAl.
  • the NiAl layer has to be quite thick because of its brittleness.
  • EP 1 380 672 Al discloses a highly oxidation resistant component with a protective layer, which consists of an intermediate MCrAlY layer zone and an outer layer zone, having the structure of the phase ⁇ -NiAl.
  • EP 1 411 148 Al a coated article is described which comprises an intermediate MCrAlY layer and deposited thereon an outer layer of ⁇ -NiAl .
  • the outer layer comprises (in wt%) : 18-24% Al.
  • the layer systems mentioned above are either expensive or lack a strong bonding between the different layer zones.
  • components having an outer layer zone which comprises (in wt%) : 17% - 23% Al, 6% - 11% Co, and Ni balance .
  • an outer layer zone of this composition is able to form an extraordinary strong bonding to the intermediate layer zone.
  • the protective layer shows a high oxidation resistance and a good durability.
  • the outer layer zone comprises (in wt%) : 19% - 21% Al, 7% - 9% Co, and Ni balance. In one preferred embodiment the outer layer zone comprises (in wt%) : 20% Al, 8% Co and Ni balance.
  • the outer layer zone can also comprise up to 5 wt% of Cr.
  • the outer layer zone further comprises at least one additional element selected from the group: HF, Zr, La, Ce, Y or other elements of the Lanthanide group.
  • the maximum amount of the at least one additional element can be 1 wt%.
  • the outer layer zone comprises 0.4 - 1.0 wt% of Y.
  • the outer layer zone may also comprise at least one of the elements selected from the group Si, Re and Ta.
  • the outer layer zone comprises (in wt%) less than 0.04% C, and/or less than 0.01% H, and/or 0.02% N, and/or less than 0.06% O. Most preferably the outer layer zone comprises less than 0.025% C, especially less than 0.01% C, and/or less than 0.008% H, especially less than 0.006% H, and/or less than 0.01% N, especially less than 0.005% N, and/or less than 0.04% O, especially less than 0.025% O.
  • the outer layer zone can have a thickness between 3 ⁇ m - lOO ⁇ m, preferably 3 ⁇ m - 50 ⁇ m.
  • the intermediate NiCoCrAlY layer zone can comprises 24% - 26% Co, 16% - 18% Cr, 9,5% - 11% Al, 0,3% - 0,5% Y, 1% - 1,8% Re und Ni balance .
  • the outer layer zone further comprises (in wt%) : 0.1% - 2% Si and/or 0.2% - 8% Ta.
  • the intermediate NiCoCrAlY layer zone may- comprise one of the following compositions (in wt%) :
  • the intermediate NiCoCrAlY layer zone may consist of one of the following compositions (in wt%) :
  • Y is at least partly replaced in the intermediate NiCoCrAlY layer zone by at least one element selected from the group: Si, Hf, Zr, La, Ce or other elements of the Lanthanide group.
  • a thickness between 50 ⁇ m to 600 ⁇ m and preferably between lOO ⁇ m to 300 ⁇ m is an optimal for the intermediate layer zone .
  • the outer layer zone is thinner than the intermediate layer zone .
  • the component according to the invention can be a part of a gas turbine like a turbine blade, a turbine vane or a heat shield. In this case an excellent protection of the turbine part against corrosion is achieved.
  • Figure 1 shows a heat resistant component known from the state of the art
  • Figure 2 shows an oxidation resistant component according to the invention
  • Figure 3 shows a blade or a vane
  • Figure 4 shows a combustion chamber
  • Figure 5 shows a gas turbine.
  • FIG. 1 shows a heat resistant component 1 known in the art. It comprises a substrate 2 which is coated with a MCrAlY layer 3. A thermally grow oxide layer (TGO) 4 is provided on the MCrAlY layer 3. The oxide layer 4 is covered by an outer thermal barrier coating (TBC) 5.
  • TGO thermally grow oxide layer
  • TBC outer thermal barrier coating
  • Figure 2 shows an oxidation resistant component 6 according to the invention which can be a part of a gas turbine, like a turbine blade or vane or a heat shield.
  • Component 6 comprises a substrate 2 which can consist of a metal or an alloy, e.g. a superalloy.
  • An intermediate NiCoCrAlY layer zone 7 is provided on the substrate 2.
  • the NiCoCrAlY layer zone 7 is Ni-based. It has a composition (in wt%) of 24% - 26% Co, 16% - 18% Cr,
  • the NiCoCrAlY layer 7 may contain 0.1% - 2% Si and/or 0.2% -
  • NiCoCrAlY layer zone 7 contains additional elements like Hf, Zr, La, Ce or other elements of the Lanthanide group. These elements can also replace part of the Y in the layer 7.
  • the intermediate NiCoCrAlY layer zone 7 is approximately 200 ⁇ m thick but its thickness can be especially at least lOO ⁇ m or especially in the range from 50 ⁇ m to 600 ⁇ m and very especially from lOO ⁇ m to 600 ⁇ m.
  • An outermost metallic layer zone 8 of a protective layer 9 is provided on the intermediate NiCoCrAlY layer zone 7. This outer layer zone 8 possesses the structure of the phase ⁇ - NiAl and comprises (in wt%) : 17% - 23% Al, 6% - 11% Co and Ni balance .
  • outer layer zone 8 consists of the ⁇ -NiAl phase.
  • the outer layer zone consists of Ni, Al and Co.
  • the outer layer zone 8 consists of Ni, Al, Co and Y.
  • this outer layer zone 8 can possess the structure of the phase ⁇ -NiAl and comprises (in wt%) : 17% - 23% Al, 0,1% to 5%
  • outer layer zone 8 consists of the ⁇ -NiAl phase .
  • outer layer zone 8 consists of Ni, Al, and Cr.
  • the outer layer zone 8 consists of Ni, Al, Cr and Y.
  • outer layer zone 8 consists of the elements Ni, Al, Co, Cr and very especially consists of the elements Ni, Al, Co, Cr and Y.
  • the outer layer zone 8 comprises (in wt%) less than 0.04% C, and/or less than 0.01% H, and/or less than 0.02% N, and/or less than 0.06% O.
  • outer layer zone 8 is 15 ⁇ m thick and thus thinner than the intermediate NiCoCrAlY layer zone 7.
  • the outer layer zone 8 is at least 10% thinner than the layer zone 7. Especially the outer layer zone 8 is at least 20% thinner than the layer zone 7 and very especially the outer layer zone 8 is at least 30% thinner than the layer zone 7.
  • the thickness of the intermediate NiCoCrAlY layer zone 7 can be in the range of lOO ⁇ m to 300 ⁇ m.
  • Both layers I 1 8 can be applied by plasma spraying (VPS, APS,..) or other conventional coating methods.
  • plasma spraying or the other conventional coating methods especially one powder or an ingot (in case of PVD) is used wherein the powder or the ingot contains all elements which are listed above for the outer layer zone 8.
  • Example given for plasma spraying a ⁇ -NiAl outer layer zone which comprises also cobalt one single powder with the elements Ni, Al and Co is used and fed to the plasma gun.
  • the outer layer zone 8 is covered by a thermally grown oxide layer (TGO) 4, which can consist of a metastable aluminium oxide, preferably having the ⁇ -phase or a mixture of the ⁇ - and the ⁇ -phase.
  • TGO thermally grown oxide layer
  • the oxidation of the outer layer zone 8 should take place at a temperature between 850 0 C and 1000 0 C, especially between 875°C and 925°C for 2h-100h, especially between Stand 15h. Further improvements are possible, if water vapour (0.2-50 vol%, especially 20-50 vol.%) is added to the oxidation atmosphere or if an atmosphere is used which has a low oxygen partial pressure between 800 0 C and HOO 0 C, especially between 850 0 C and 1050 0 C. In addition to water vapour the atmosphere can also contain non-oxidizing gases such as a nitrogen, argon or helium.
  • the TGO 4 consists of metastable aluminium oxide it can have a needle like structure which ensures a strong bonding between the TGO 4 and a thermal barrier coating 5 being provided on the TGO 4.
  • the component 6 can be part of a gas turbine for example a turbine blade, a turbine vane or a heat shield.
  • Figure 3 shows a perspective view of a blade or vane 120, 130 which extends along a longitudinal axis 121.
  • the blade or vane 120, 130 has, in succession, a securing region 400, an adjoining blade or vane platform 403 and a main blade region 406.
  • a blade root 183 which is used to secure the rotor blades 120, 130 to the shaft is formed in the securing region 400.
  • the blade or vane root 183 is designed as a hammer head. Other configurations, for example as a fir-tree root or a dovetail root, are possible.
  • solid metallic materials are used in all regions 400, 403, 406 of the rotor blade 120, 130.
  • the rotor blade 120, 130 may in this case be produced using a casting process, a forging process, a milling process or a combination thereof.
  • FIG 4 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as what is known as an annular combustion chamber, in which a multiplicity of burners 107 arranged around the turbine shaft in the circumferential direction open out into a common burner chamber space.
  • the overall combustion chamber 110 is configured as an annular structure which is positioned around the turbine shaft.
  • the combustion chamber 110 is designed for a relatively high temperature of the working medium M of approximately 1000 0 C to 1600 0 C.
  • the combustion chamber wall 153 is provided, on its side facing the working medium M, with an inner lining formed from heat shield elements 155.
  • each heat shield element 155 is equipped with a particularly heat resistant protective layer or is made from material which is able to withstand high temperatures . Moreover, on account of the high temperatures in the interior of the combustion chamber 110, a cooling system is provided for the heat shield elements 155 and/or their holding elements .
  • the materials used for the combustion chamber wall and its coatings may be similar to the turbine blades or vanes 120, 130.
  • the combustion chamber 110 is designed in particular to detect losses of the heat shield elements 155.
  • a number of temperature sensors 158 are positioned between the combustion chamber wall 153 and the heat shield elements 155.
  • Figure 5 shows, by way of example, a gas turbine 100 in partial longitudinal section.
  • the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102.
  • the annular combustion chamber 106 is in communication with an, for example annular, hot gas passage 111, where, for example, four turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed from two rings of blades or vanes. As seen in the direction of flow of a working medium 113, a row 125 formed from rotor blades 120 follows a row 115 of guide vanes in the hot gas passage 111.
  • the guide vanes 120 are in this case secured to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are arranged on the rotor 103 by way of example by means of a turbine disk 133.
  • a generator or machine (not shown) is coupled to the rotor 103.
  • the compressor 105 While the gas turbine 100 is operating, the compressor 105 sucks in air 135 through the intake housing 104 and compresses it. The compressed air provided at the turbine side end of the compressor 105 is passed to the burners 107, where it is mixed with a fuel. The mixture is then burnt in the combustion chamber 110, forming the working medium 113.
  • the working medium 113 expands at the rotor blades 120, transmitting its momentum, so that the rotor blades 120 drive the rotor 130 and the latter drives the machine coupled to it.
  • the guide vanes 130 and rotor blades 120 belonging to the first turbine stage 112, as seen in the direction of flow of the working medium 113, are subject to the highest thermal loads apart from the heat shield blocks which line the annular combustion chamber 106. To enable them to withstand the prevailing temperatures, they are cooled by means of a coolant .
  • the substrates may also have a directional structure, i.e. they are in single crystal form (SX structure) or comprise only longitudinally directed grains (DS structure) .
  • SX structure single crystal form
  • DS structure longitudinally directed grains
  • Ironbase, nickelbase or cobaltbase superalloys are used as the material .
  • the blades or vanes 120, 130 may also have coatings protecting them from corrosion (MCrAlY; M is at least one element selected from the group consisting of iron (Fe) , cobalt (Co) , Nickel (Ni) , Y represents Yttrium (Y) and/or silicon (Si) and/or at least one rare earth) and to protect against heat by means of a thermal barrier coating.
  • M is at least one element selected from the group consisting of iron (Fe) , cobalt (Co) , Nickel (Ni) , Y represents Yttrium (Y) and/or silicon (Si) and/or at least one rare earth) and to protect against heat by means of a thermal barrier coating.
  • the thermal barrier coating consists, for example, of ZrO 2 , Y 2 O 3 - ZrO 2 , i.e. it is not stabilized, is partially stabilized or is completely stabilized by Yttrium oxide and/or calcium oxide and/or magnesium oxide.
  • the guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head on the opposite side from the guide vane root.
  • the guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a component (6) with a substrate (2) and a protective layer (9), which consists of an intermediate NiCoCrAlY layer zone (7) on or near the substrate (2) and an outer layer zone (8) arranged on the intermediate NiCoCrAlY layer zone (7), wherein the outer layer zone (8) posses the structure of the phase β-NiAl and comprises (in wt%): 17% - 23% Al, 6% - 11% Co, and Ni balance.

Description

Component with a substrate and a protective layer
The invention relates to a component with a substrate and a protective layer, which consists of an intermediate NiCoCrAlY layer zone on the substrate and an outer layer zone arranged on the intermediate NiCoCrAlY layer zone .
Metallic compounds, which are exposed to high temperatures, must be protected against heat and corrosion. This is especially true for parts of gas turbines like combustion chambers, turbine blades or vanes. These parts are commonly coated with an intermediate MCrAlY layer (M = Fe, Co, Ni) and a thermal barrier coating (TBC) which is applied on top of the intermediate layer. Between the two layers an aluminium oxide layer is formed due to oxidation.
The bonding of the three different layers is crucial for a high durability of the protection layer as a whole. Problems may arise, if there are big differences in the thermal expansion factors of the different layers. In this case failure of the thermal barrier coating might occur, which can lead to the destruction of the whole compound.
From US-PS-6, 287, 644 a continuously graded MCrAlY bond coat is known which has a continuously increasing amount of Cr, Si or Zr with increasing distance from the underlying substrate in order to reduce the thermal mismatch between the bond coat and the thermal barrier coating by adjusting the thermal expansion factors.
The US-PS-5, 792, 521 shows a multi layer thermal barrier coating.
US-PS-5, 514,482 discloses a thermal barrier coating system for super alloy components, in which the MCrAlY layer is substituted by an aluminium coating layer such as NiAl. In order to obtain the desired properties the NiAl layer has to be quite thick because of its brittleness.
From EP 1 082 216 Bl a MCrAlY layer is known, which has the γ-phase at its outer layer. This γ-phase can only be obtained by remelting or deposition from a liquid phase in an expensive way.
EP 1 380 672 Al discloses a highly oxidation resistant component with a protective layer, which consists of an intermediate MCrAlY layer zone and an outer layer zone, having the structure of the phase β-NiAl.
In EP 1 411 148 Al a coated article is described which comprises an intermediate MCrAlY layer and deposited thereon an outer layer of β-NiAl . The outer layer comprises (in wt%) : 18-24% Al.
The layer systems mentioned above are either expensive or lack a strong bonding between the different layer zones.
It is thus an object of the present invention to describe a component having a substrate and a protective layer, which possesses a high oxidation resistance and a strong bonding between the different layer zones.
This object is met by components having an outer layer zone, which comprises (in wt%) : 17% - 23% Al, 6% - 11% Co, and Ni balance .
Surprisingly it was found that an outer layer zone of this composition is able to form an extraordinary strong bonding to the intermediate layer zone. As a result the protective layer shows a high oxidation resistance and a good durability.
According to one embodiment the outer layer zone comprises (in wt%) : 19% - 21% Al, 7% - 9% Co, and Ni balance. In one preferred embodiment the outer layer zone comprises (in wt%) : 20% Al, 8% Co and Ni balance.
The outer layer zone can also comprise up to 5 wt% of Cr.
It is also possible that the outer layer zone further comprises at least one additional element selected from the group: HF, Zr, La, Ce, Y or other elements of the Lanthanide group. The maximum amount of the at least one additional element can be 1 wt%.
According to another embodiment the outer layer zone comprises 0.4 - 1.0 wt% of Y.
The outer layer zone may also comprise at least one of the elements selected from the group Si, Re and Ta.
In one preferred embodiment the outer layer zone comprises (in wt%) less than 0.04% C, and/or less than 0.01% H, and/or 0.02% N, and/or less than 0.06% O. Most preferably the outer layer zone comprises less than 0.025% C, especially less than 0.01% C, and/or less than 0.008% H, especially less than 0.006% H, and/or less than 0.01% N, especially less than 0.005% N, and/or less than 0.04% O, especially less than 0.025% O.
The outer layer zone can have a thickness between 3μm - lOOμm, preferably 3μm - 50μm.
The intermediate NiCoCrAlY layer zone can comprises 24% - 26% Co, 16% - 18% Cr, 9,5% - 11% Al, 0,3% - 0,5% Y, 1% - 1,8% Re und Ni balance .
It is also possible that the outer layer zone further comprises (in wt%) : 0.1% - 2% Si and/or 0.2% - 8% Ta. Alternatively the intermediate NiCoCrAlY layer zone may- comprise one of the following compositions (in wt%) :
11% - 13% Co, 20% - 22% Cr, 10.5% - 11.5% Al, 0.3% - 0.5% Y, 1.5% - 2.5% Re and Ni balance, especially Ni-12Co-21Cr-llAl- 0.4Y-2Re, or
11% - 13.5% Co, 19.5% - 23% Cr, 9% - 12% Al, 0.1% - 0.8% Y, 1% - 3.2% Re and Ni balance, especially Ni-12Co-21-Cr-llAl- 0.4Y-2Re, or
29% - 31% Ni, 26.5% - 29.5% Cr, 6.5% - 9.5% Al, 0.3% - 0.9% Y and 0.5% - 0.9% Si and Co balance, especially Co-30Ni-28Cr- 8Al-0.6Y-0.7Si, or
27% - 29% Ni, 22.5% - 25.5% Cr, 9% - 11% Al; 0.1% - 1.1% Y and Co balance, especially Co-28Ni-24Cr-10Al-0.6Y.
Alternatively the intermediate NiCoCrAlY layer zone may consist of one of the following compositions (in wt%) :
24% - 26% Co, 16% - 18% Cr, 9,5% - 11% Al, 0,3% - 0,5% Y, 1% - 1,8% Re and Ni balance, or
11% - 13% Co, 20% - 22% Cr, 10.5% - 11.5% Al, 0.3% - 0.5% Y, 1.5% - 2.5% Re and Ni balance, especially Ni-12Co-21Cr-llAl-0.4Y-2Re, or
11% - 13.5% Co, 19.5% - 23% Cr, 9% - 12% Al, 0.1% - 0.8% Y, 1% - 3.2% Re and Ni balance, especially Ni-12Co-21-Cr-llAl-0.4Y-2Re, or
29% - 31% Ni, 26.5% - 29.5% Cr, 6.5% - 9.5% Al, 0.3% - 0.9% Y and 0.5% - 0.9% Si and Co balance, especially Co-30Ni-28Cr-8Al-0.6Y-0.7Si, or 27% - 29% Ni, 22.5% - 25.5% Cr, 9% - 11% Al; 0.1% - 1.1% Y and Co balance, especially Co-28Ni-24Cr-10Al-0.6Y.
According to one preferred embodiment of the invention Y is at least partly replaced in the intermediate NiCoCrAlY layer zone by at least one element selected from the group: Si, Hf, Zr, La, Ce or other elements of the Lanthanide group.
It was found that a thickness between 50μm to 600μm and preferably between lOOμm to 300μm is an optimal for the intermediate layer zone .
Preferably the outer layer zone is thinner than the intermediate layer zone .
The component according to the invention can be a part of a gas turbine like a turbine blade, a turbine vane or a heat shield. In this case an excellent protection of the turbine part against corrosion is achieved.
In the following the invention will be explained in more detail with reference to the attached drawings. In the drawings :
Figure 1 shows a heat resistant component known from the state of the art,
Figure 2 shows an oxidation resistant component according to the invention,
Figure 3 shows a blade or a vane, Figure 4 shows a combustion chamber and Figure 5 shows a gas turbine.
The invention may be embodied in many different forms and should not be construed as limited to the illustrated embodiments set forth herein. Rather, the illustrated embodiments are provided so that this disclosure will be through and complete, and will fully convey the scope of the invention to those skilled in the art.
Figure 1 shows a heat resistant component 1 known in the art. It comprises a substrate 2 which is coated with a MCrAlY layer 3. A thermally grow oxide layer (TGO) 4 is provided on the MCrAlY layer 3. The oxide layer 4 is covered by an outer thermal barrier coating (TBC) 5.
Figure 2 shows an oxidation resistant component 6 according to the invention which can be a part of a gas turbine, like a turbine blade or vane or a heat shield. Component 6 comprises a substrate 2 which can consist of a metal or an alloy, e.g. a superalloy.
An intermediate NiCoCrAlY layer zone 7 is provided on the substrate 2.
The NiCoCrAlY layer zone 7 is Ni-based. It has a composition (in wt%) of 24% - 26% Co, 16% - 18% Cr,
9.5% - 11% Al, 0.3% - 0.5% Y, 1.0% - 1.8% Re and Ni balance.
The NiCoCrAlY layer 7 may contain 0.1% - 2% Si and/or 0.2% -
8% Ta.
It is possible that the NiCoCrAlY layer zone 7 contains additional elements like Hf, Zr, La, Ce or other elements of the Lanthanide group. These elements can also replace part of the Y in the layer 7. The intermediate NiCoCrAlY layer zone 7 is approximately 200μm thick but its thickness can be especially at least lOOμm or especially in the range from 50μm to 600μm and very especially from lOOμm to 600μm. An outermost metallic layer zone 8 of a protective layer 9 is provided on the intermediate NiCoCrAlY layer zone 7. This outer layer zone 8 possesses the structure of the phase β- NiAl and comprises (in wt%) : 17% - 23% Al, 6% - 11% Co and Ni balance .
Especially the outer layer zone 8 consists of the β-NiAl phase.
Preferably the outer layer zone consists of Ni, Al and Co. Very especially the outer layer zone 8 consists of Ni, Al, Co and Y.
Also this outer layer zone 8 can possess the structure of the phase β-NiAl and comprises (in wt%) : 17% - 23% Al, 0,1% to 5%
Cr and Ni balance . Especially the outer layer zone 8 consists of the β-NiAl phase .
Especially the outer layer zone 8 consists of Ni, Al, and Cr.
Very especially the outer layer zone 8 consists of Ni, Al, Cr and Y.
Especially the outer layer zone 8 consists of the elements Ni, Al, Co, Cr and very especially consists of the elements Ni, Al, Co, Cr and Y.
Further elements like Zr, Si, Re, Ta, Hf, Zr, La, Ce, Y and other elements of the Lanthanide group can also be included in the outer layer zone 8.
Preferably the outer layer zone 8 comprises (in wt%) less than 0.04% C, and/or less than 0.01% H, and/or less than 0.02% N, and/or less than 0.06% O.
Preferably outer layer zone 8 is 15μm thick and thus thinner than the intermediate NiCoCrAlY layer zone 7.
The outer layer zone 8 is at least 10% thinner than the layer zone 7. Especially the outer layer zone 8 is at least 20% thinner than the layer zone 7 and very especially the outer layer zone 8 is at least 30% thinner than the layer zone 7.
While the thickness of the intermediate NiCoCrAlY layer zone 7 can be in the range of lOOμm to 300μm.
Both layers I1 8 can be applied by plasma spraying (VPS, APS,..) or other conventional coating methods. For plasma spraying or the other conventional coating methods especially one powder or an ingot (in case of PVD) is used wherein the powder or the ingot contains all elements which are listed above for the outer layer zone 8. Example given for plasma spraying a β-NiAl outer layer zone which comprises also cobalt one single powder with the elements Ni, Al and Co is used and fed to the plasma gun.
This means that all the elements listed above in the advantageous examples are distributed throughout the whole outer layer zone 8 (for all kind of coatings methods) . Very especially besides Ni and Al the other elements, especially the elements Co and/or Cr and/or Y are homogenousIy distributed throughout the outer layer zone 8 NiAl. Together they form a metallic protective layer 9. "Outermost" means that on the layer 8 there is no other metallic layer.
The outer layer zone 8 is covered by a thermally grown oxide layer (TGO) 4, which can consist of a metastable aluminium oxide, preferably having the θ-phase or a mixture of the θ- and the γ-phase.
To improve the formation of desired metastable aluminium oxide the oxidation of the outer layer zone 8 should take place at a temperature between 8500C and 10000C, especially between 875°C and 925°C for 2h-100h, especially between Stand 15h. Further improvements are possible, if water vapour (0.2-50 vol%, especially 20-50 vol.%) is added to the oxidation atmosphere or if an atmosphere is used which has a low oxygen partial pressure between 8000C and HOO0C, especially between 8500C and 10500C. In addition to water vapour the atmosphere can also contain non-oxidizing gases such as a nitrogen, argon or helium.
If the TGO 4 consists of metastable aluminium oxide it can have a needle like structure which ensures a strong bonding between the TGO 4 and a thermal barrier coating 5 being provided on the TGO 4.
The component 6 can be part of a gas turbine for example a turbine blade, a turbine vane or a heat shield.
Figure 3 shows a perspective view of a blade or vane 120, 130 which extends along a longitudinal axis 121. Along the longitudinal axis 121, the blade or vane 120, 130 has, in succession, a securing region 400, an adjoining blade or vane platform 403 and a main blade region 406. A blade root 183 which is used to secure the rotor blades 120, 130 to the shaft is formed in the securing region 400. The blade or vane root 183 is designed as a hammer head. Other configurations, for example as a fir-tree root or a dovetail root, are possible. In the case of conventional blades or vanes 120, 130, solid metallic materials are used in all regions 400, 403, 406 of the rotor blade 120, 130. The rotor blade 120, 130 may in this case be produced using a casting process, a forging process, a milling process or a combination thereof.
Figure 4 shows a combustion chamber 110 of a gas turbine. The combustion chamber 110 is designed, for example, as what is known as an annular combustion chamber, in which a multiplicity of burners 107 arranged around the turbine shaft in the circumferential direction open out into a common burner chamber space. For this purpose, the overall combustion chamber 110 is configured as an annular structure which is positioned around the turbine shaft. To achieve a relatively high efficiency, the combustion chamber 110 is designed for a relatively high temperature of the working medium M of approximately 10000C to 16000C. To allow a relatively long service life to be achieved with these operating parameters, which are unfavourable for the materials, the combustion chamber wall 153 is provided, on its side facing the working medium M, with an inner lining formed from heat shield elements 155. On the working medium side, each heat shield element 155 is equipped with a particularly heat resistant protective layer or is made from material which is able to withstand high temperatures . Moreover, on account of the high temperatures in the interior of the combustion chamber 110, a cooling system is provided for the heat shield elements 155 and/or their holding elements .
The materials used for the combustion chamber wall and its coatings may be similar to the turbine blades or vanes 120, 130.
The combustion chamber 110 is designed in particular to detect losses of the heat shield elements 155. For this purpose, a number of temperature sensors 158 are positioned between the combustion chamber wall 153 and the heat shield elements 155.
Figure 5 shows, by way of example, a gas turbine 100 in partial longitudinal section.
In the interior, the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102.
An intake housing 104, a compressor 105, a, for example torus like combustion chamber 110, in particular an annular combustion chamber 106, having a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust gas housing 109 follow one another along the rotor 103. The annular combustion chamber 106 is in communication with an, for example annular, hot gas passage 111, where, for example, four turbine stages 112 connected in series form the turbine 108.
Each turbine stage 112 is formed from two rings of blades or vanes. As seen in the direction of flow of a working medium 113, a row 125 formed from rotor blades 120 follows a row 115 of guide vanes in the hot gas passage 111.
The guide vanes 120 are in this case secured to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are arranged on the rotor 103 by way of example by means of a turbine disk 133. A generator or machine (not shown) is coupled to the rotor 103.
While the gas turbine 100 is operating, the compressor 105 sucks in air 135 through the intake housing 104 and compresses it. The compressed air provided at the turbine side end of the compressor 105 is passed to the burners 107, where it is mixed with a fuel. The mixture is then burnt in the combustion chamber 110, forming the working medium 113.
From there, the working medium 113 flows along the hot gas passage 111 past the guide vanes 130 and the rotor blades
120. The working medium 113 expands at the rotor blades 120, transmitting its momentum, so that the rotor blades 120 drive the rotor 130 and the latter drives the machine coupled to it.
While the gas turbine 100 is operating, the components exposed to the hot working medium 113 are subject to thermal loads. The guide vanes 130 and rotor blades 120 belonging to the first turbine stage 112, as seen in the direction of flow of the working medium 113, are subject to the highest thermal loads apart from the heat shield blocks which line the annular combustion chamber 106. To enable them to withstand the prevailing temperatures, they are cooled by means of a coolant .
The substrates may also have a directional structure, i.e. they are in single crystal form (SX structure) or comprise only longitudinally directed grains (DS structure) .
Ironbase, nickelbase or cobaltbase superalloys are used as the material .
By way of example, superalloys as known from EP 1 204 776, EP 1 306 454, EP 1 319 729, WO 99/67435 or WO 00/44949 are used; these documents form part of the present disclosure.
The blades or vanes 120, 130 may also have coatings protecting them from corrosion (MCrAlY; M is at least one element selected from the group consisting of iron (Fe) , cobalt (Co) , Nickel (Ni) , Y represents Yttrium (Y) and/or silicon (Si) and/or at least one rare earth) and to protect against heat by means of a thermal barrier coating. The thermal barrier coating consists, for example, of ZrO2, Y2O3- ZrO2, i.e. it is not stabilized, is partially stabilized or is completely stabilized by Yttrium oxide and/or calcium oxide and/or magnesium oxide.
Columnar grains are produced in the thermal barrier coating by suitable coating processes, such as electron beam physical vapour deposition (EBPVD) .
The guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head on the opposite side from the guide vane root. The guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143.

Claims

Claims
1. Component (6) with a substrate (2) and a metallic protective layer (9) , which consists of an intermediate
NiCoCrAlY layer zone (7) on the substrate (2) and an outermost layer zone (8) arranged on the intermediate NiCoCrAlY layer zone (7) , wherein the outer layer zone (8) possesses the structure of the phase β-NiAl and comprises (in wt%) :
17% - 23% Al
6% - 11% Co, and Ni balance .
2. Component (6) with a substrate (2) and a metallic protective layer (9) , which consists of an intermediate
NiCoCrAlY layer zone (7) on the substrate (2) and an outermost layer zone (8) arranged on the intermediate NiCoCrAlY layer zone (7) , wherein the outer layer zone (8) possesses the structure of the phase β-NiAl and comprises (in wt%) :
17% - 23% Al 0,1% to 5% Cr, and Ni balance .
3. Component (6) according to claim 1 or 2, wherein the outermost layer zone (8) comprises (in wt%)
19% - 21% Al.
4. Component (6) according to claim 3, wherein the outermost layer zone (8) comprises (in wt%) :
20% Al.
5. Component (6) according to claim 1, wherein the outermost layer zone (8) comprises (in wt%) : 7% - 9% Co and especially 8% Co.
6. Component (6) according to claim 2, wherein the outermost layer zone (8) comprises (in wt%) :
6% - 11% Co, especially 7% - 9% Co and very especially 8% Co.
7. Component (6) according to claim 1, 3, 4 or 5, wherein the outer layer zone (8) further comprises (in wt%) 0,1% to 5% Cr.
8. Component (6) according to any of the preceding claims, wherein the outer layer zone (8) further comprises at least one additional element selected from the group consisting of Hf, Zr, La, Ce, Y and other elements of the Lanthanide group, especially Y.
9. Component (6) according to claim 8, wherein the maximum amount of the at least one additional element is 1 wt%, especially at least 0.1 wt%.
10. Component (6) according to claim 8 or 9, wherein the outer layer zone (8) comprises (in wt%) 0.4% - 1.0% Y.
11. Component (6) according to claim 1, 3, 4 or 5, wherein the outer layer zone (8) consists of Ni, Al, Co.
12. Component (6) according to claim 2, 3 or 4 , wherein the outer layer zone (8) consists of Ni, Al, Cr.
13. Component (6) according to claim 1, 2, 3, 4, 5, 6 or 7, wherein the outer layer zone (8) consists of Ni, Al, Co, Cr.
14. Component (6) according to claim 1, 3, 4, 5, 8, 9 or 10, wherein the outer layer zone (8) consists of Ni, Al, Co and Y.
15. Component (6) according to claim 2, 3, 4, 8, 9 or 10, wherein the outer layer zone (8) consists of Ni, Al, Cr and Y.
16. Component (6) according to any of the preceding claims 1 to 10, wherein the outer layer zone (8) consists of Ni, Al, Co, Cr and Y.
17. Component (6) according to any of the preceding claims 1 to 10, wherein the outer layer zone (8) further comprises at least one of the elements selected from the group Si, Re and Ta.
18. Component (6) according to any of the preceding claims 1 to 10 or 17, wherein the outer layer zone (8) comprises (in wt%) :
less than 0.04% C7 and/or less than 0.01% H, and/or less than 0.02% N, and/or less than 0.06% O.
19. Component (6) according to any of the preceding claims 1 to 10 or 17, wherein the outer layer zone (8) comprises (in wt%) :
less than 0.025% C, especially less than 0.01% C, and/or less than 0.008% H, especially less than 0.006% H, and/or less than 0.01% N, especially less than 0.005% N, and/or less than 0.04% O, especially less than 0.025% 0.
20. Component (6) according to any of the preceding claims, wherein the outer layer zone (8) has a thickness between 3μm to lOOμm, preferably between 3μm to 50μm.
21. Component (6) according to any of the preceding claims, wherein the intermediate NiCoCrAlY layer zone (7) comprises (in wt%) :
24% - 26% Co,
16% - 18% Cr,
9.5% - 11% Al,
1.0% - 1.8% Re
0.3% - 0.5 Y, and Ni balance, especially 25% Co, 17% Cr, 10% Al, 1.5% Re, 0.4% Y and Ni balance .
22. Component (6) according to any of the claims 1 to 20, wherein the intermediate NiCoCrAlY layer zone (7) comprises (in wt%) :
11% - 13% Co, 20% - 22% Cr,
10.5% - 11.5% Al,
1.5% - 2.5% Re
0.3% - 0.5 Y, and Ni balance, especially 12% Co, 21% Cr, 11% Al, 1.5% - 2% Re, 0.4% Y and Ni balance .
23. Component (6) according to any of the claims 1 to 20, wherein the intermediate NiCoCrAlY layer zone (7) comprises (in wt%) :
9% - 11% Co,
22% - 24% Cr,
11 % - 13% Al,
0.3% - 0.9 Y,
1.5% - 2.5% Re and Ni balance especially 10% Co, 23% Cr, 12% Al, 0.6% Y and Ni balance.
24. Component (6) according to any of the claims 1 to 20, wherein the intermediate NiCoCrAlY layer zone (7) comprises
(in wt%) :
29% - 31% Ni, 26.5% - 29.5% Cr, 6.5% - 9.5% Al,
0.3% - 0.9 Y, 0.5% - 0.9 Si and Co balance,
especially 30% Ni, 28% Cr, 8% Al, 0.6% Y, 0.7% Si and Co balance .
25. Component (6) according to any of the claims 1 to 20, wherein the intermediate NiCoCrAlY layer zone (7) comprises (in wt%) :
27% - 29% Ni, 22.5% - 25.5% Cr, 9% - 11% Al, 0.1% - 1.1 Y, and Co balance,
especially 28% Ni, 24% Cr, 10% Al, 0.6 Y and Co balance.
26. Component (6) according any of the claims 21 to 25, wherein in the intermediate NiCoCrAlY layer zone (7) Y is at least partly replaced by at least one element selected from the group consisting of Si, Hf, Zr, La, Ce and other elements of the Lanthanide group .
27. Component (6) according to any of the preceding claims, wherein the intermediate NiCoCrAlY layer zone (7) has a thickness of 50μm to 600μm, preferably lOOμm to 600μm, very preferably lOOμm to 300μm.
28. Component (6) according to any of the preceding claims, wherein the outer layer zone (8) consists of the phase β- NiAl.
29. Component (6) according to any of the preceding claims, wherein the outer layer zone (8) is thinner than the intermediate NiCoCrAlY layer zone (7) .
30. Component (6) according to any of the preceding claims, wherein the protective layer (9) consists of two separate layers (7, 8) .
31. Component (6) according to any of the preceding claims, wherein it is a part of a gas turbine (100) , especially a turbine blade (120, 130), a turbine vane (120, 130) or a heat shield (155) .
PCT/EP2007/001289 2007-02-26 2007-02-26 Component with a substrate and a protective layer WO2008104188A1 (en)

Priority Applications (2)

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EP07703474A EP2115186A1 (en) 2007-02-26 2007-02-26 Component with a substrate and a protective layer
PCT/EP2007/001289 WO2008104188A1 (en) 2007-02-26 2007-02-26 Component with a substrate and a protective layer

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Application Number Priority Date Filing Date Title
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1365044A1 (en) * 2002-05-24 2003-11-26 Siemens Aktiengesellschaft MCrAl-coating
EP1380672A1 (en) * 2002-07-09 2004-01-14 Siemens Aktiengesellschaft Highly oxidation resistant component
EP1411148A1 (en) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Method of depositing a MCrALY-coating on an article and the coated article

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1365044A1 (en) * 2002-05-24 2003-11-26 Siemens Aktiengesellschaft MCrAl-coating
EP1380672A1 (en) * 2002-07-09 2004-01-14 Siemens Aktiengesellschaft Highly oxidation resistant component
EP1411148A1 (en) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Method of depositing a MCrALY-coating on an article and the coated article

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