EP3118345B1 - Revêtement protecteur à haute température - Google Patents

Revêtement protecteur à haute température Download PDF

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Publication number
EP3118345B1
EP3118345B1 EP15177229.0A EP15177229A EP3118345B1 EP 3118345 B1 EP3118345 B1 EP 3118345B1 EP 15177229 A EP15177229 A EP 15177229A EP 3118345 B1 EP3118345 B1 EP 3118345B1
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Prior art keywords
coating
content
high temperature
formation
coating according
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EP15177229.0A
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German (de)
English (en)
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EP3118345A1 (fr
Inventor
Johannes Clemens Schab
Julien Rene Andre Zimmermann
Alexander Stankowski
Piero-Daniele Grasso
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Priority to EP15177229.0A priority Critical patent/EP3118345B1/fr
Priority to CN201610557032.0A priority patent/CN106435277B/zh
Priority to JP2016140472A priority patent/JP2017053022A/ja
Priority to US15/211,588 priority patent/US20170016123A1/en
Priority to KR1020160089987A priority patent/KR20170009784A/ko
Publication of EP3118345A1 publication Critical patent/EP3118345A1/fr
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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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F11/00—Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent
    • C23F11/02—Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent in air or gases by adding vapour phase inhibitors
    • 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
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • 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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/005—Ferrous alloys, e.g. steel alloys containing rare earths, i.e. Sc, Y, Lanthanides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/26—Ferrous alloys, e.g. steel alloys containing chromium with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/32—Ferrous alloys, e.g. steel alloys containing chromium with boron
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C23C30/005—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process on hard metal substrates
    • 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
    • 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
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/132—Chromium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys

Definitions

  • MCrAlY coatings are commonly applied on hot gas paths components of modern gas turbines. In general, MCrAlY coatings are either applied as an overlay or as a bond coat for thermal barrier coating systems (TBC).
  • TBC thermal barrier coating systems
  • the main target of an overlay is to protect the Ni-/Co-base superalloy substrate from oxidation and hot corrosion. Furthermore, the mechanical integrity of the coating system and of the corresponding base material shall be ensured.
  • the boundary conditions like e.g. temperature, mechanical stresses, etc.
  • Some components or some specific component areas are prone to fatigue (cyclic loading), while others face increased creep, oxidation and/or hot corrosion impact (base-load).
  • the lack of ductility at low temperature is caused by the large amount of fine ⁇ ', ⁇ -(NiAl), and ⁇ -Cr precipitates (coming from the high content of Al and Cr) limiting the dislocation propagation.
  • the lack of strength at high temperature is caused by the partial dissolution of the ⁇ ', ⁇ -(NiAl), and ⁇ -Cr precipitates into the ⁇ matrix, leading to a softening effect and loss of strength.
  • Fig. 1 shows an overview about prior art MCrAlY alloy classes and their oxidation resistance and hot corrosion resistance. This well-known figure is disclosed in: Eskner, M.: Mechanical behaviour of gas turbine coatings. Swiss: Kungl. Tekniska högskolan., 2004, p. 3 , and shows very clearly that NiCrAlY coatings have a high oxidation resistance, but as a disadvantage only a low hot corrosion resistance.
  • NiCrAlY alloys are for example described in the following documents: WO 03/060194 A1 , US-A-3,620,693 , US-A-4,477,538 , US-A-4,537,744 , US-A-3,754,903 , US-A-4,013,424 , US-A-4,022,587 and US-A-4,743,514 .
  • the coating contains between 23 and 27 wt.% Cr, between 4 and 7 wt.% Al, between 0.1 and 3 wt.% Si, between 0.1 and 3 wt.% Ta, between 0.2 and 2 wt.% Y, between 0.001 and 0.01 wt.% B, between 0.001 and 0.01 wt.% Mg and between 0.001 and 0.01 Ca, with Ni and inevitable impurities making up the remainder. But although the formation of ⁇ -(NiAl) could be prevented, the coating still suffers from the ductile to brittle transition (DBTT) if operated at elevated temperatures.
  • DBTT ductile to brittle transition
  • Document US 2010/0330295 A1 describes an improvement of the coating ductility by obtaining a predominantly ⁇ ' structure that is modified with a platinum group metal in order to avoid the formation of the ⁇ -(NiAl) phase which is brittle at low temperature.
  • the plastic energy is increased for the entire working temperature range and crack initiation is avoided, or at least significantly reduced, leading to increased service lifetime in (high-) cyclic operation modus.
  • the inventive advanced high temperature protective MCrAlY coating wherein M is at least one element out of the group of Ni, Co and Fe, for a component of a turbo machine, especially a gas turbine, contains at least 1.75 vol.-% chromium borides and consists of the following chemical composition (in wt.-%):
  • the coating consists of the following chemical composition (in wt.-%):
  • the coating consists of the following chemical composition (in wt.-%):
  • the invention describes an advanced MCrAlYB coating class containing the element boron in higher amount.
  • the respective material composition is disclosed as well as the application of MCrAlYB and/or Cr 2 B containing coatings.
  • Key advantages are the higher coating ductility at lower operation temperatures ( ⁇ 500°C) and significantly increased tensile strengths (at comparable strain) at elevated operation temperatures ( ⁇ 500°C).
  • the plastic energy, toughness respectively is increased for the entire working temperature range. Crack initiation is avoided, or at least significantly reduced, leading to increased service lifetime in (high-) cyclic operation modus.
  • An increased ductility level is promoted at different temperatures, whereas the detrimental influence of ⁇ -(NiAl) formation and dissolution is avoided.
  • Increased high temperature strength ensures creep resistance in base-load operation.
  • the strengthening effect resulting from the presence of CrB and/or Cr 2 B precipitates, is independent of any phase transition of e.g. ⁇ , ⁇ ', ⁇ -(NiAl), ⁇ -Cr or ⁇ and can easily be adjusted by the added quantity of boron.
  • the high temperature stability of CrB and/or Cr 2 B ensures a stable strengthening effect until melting of the coating matrix (e.g. ⁇ -phase).
  • the presence of CrB and/or Cr 2 B reduces the chromium depletion rate, which is not the case for regular coatings containing only ⁇ -Cr or ⁇ -Cr phase.
  • the CrB and/or Cr 2 B precipitates will progressively dissolve and release the chromium needed to form a protective chromium-oxide-scale increasing the coating service lifetime in base-load operation with respect to hot corrosion.
  • the advanced coating promotes formation of highly protective alumina scales which increases the coating service lifetime in base-load operation with respect to oxidation.
  • the invention describes an advanced high temperature resistant MCrAlYB coating class containing - as the main factor - the element boron, leading to the formation of chromium-borides, in higher amount (at least 1.75 vol.-% chromium-borides) compared to similar state of the art coatings.
  • M is at least one element out of the group of Ni, Co and Fe.
  • Si and Ta are alloying elements in said MCrAlYB coating according to the invention.
  • Some examples of preferred embodiments are coatings consisting of the following elements (given in wt.-%), wherein the balance is always Ni and inevitable impurities: Table 1: Chemical composition of several exemplary embodiments of the coating according to the invention Element Ni Cr Al Si Ta Co B Y Coating AC-I Balance 24.02 5.3 2.34 1.24 1.02 0.23 0.45 AC-II Balance 23.04 5.1 2.08 1.48 2.04 0.46 0.40 AC-III Balance 22.07 4.9 1.82 1.72 3.06 0.69 0.35 AC-IV Balance 21.08 4.7 1.56 1.96 4.08 0.92 0.30
  • the coating is applied onto the surface of a metallic component, for example a gas turbine blade made of a Ni-base superalloy.
  • the application is done under air, vacuum or inert gas by one of the following thermal spray processes:
  • the coating microstructure (phase distribution), at thermodynamic equilibrium, was calculated using Thermo-Calc method.
  • the results for coating composition AC-III are shown in Fig. 2 .
  • the Cr 2 B volume fraction is constant over the complete test temperature range, while the ⁇ -Cr fraction is decreasing with increasing the temperature and does not more exist at temperatures above about 760 °C.
  • the volume fraction of ⁇ ' is significantly decreasing with increasing temperature.
  • Fig. 3 shows the dependence between the boron content and the Cr 2 B volume fraction of the standard MCrAlY (0 wt.-% B - see Table 2) and the four different advanced metallic coating systems according to the invention with their chemical composition (given in wt.-%) described in Table 1.
  • Table 2 Chemical composition of the tested reference standard coating Element Ni Cr Al Si Ta Co B Y Coating MCrAlY Balance 25.0 5.5 2.6 1.0 0.5 - 0.5
  • the nominal content of Ni, Ta, Co, and B in the four samples of the embodiments according to the invention was increased, whereas the Cr, Al, Si and Y content was decreased.
  • the adjustment of the coating microstructure is simple, as the volume fraction of borides is linearly increasing with the boron content.
  • the advanced NiCrAlSiTaCoBY coating microstructure is comprised of a ⁇ -matrix which contains ⁇ ', ⁇ -Cr and Cr 2 B precipitates. Formation of undesirable phases like ⁇ -Cr or ⁇ -(NiAl), which have a significant influence on the ductile to brittle temperature (DBTT) and on the coefficient of thermal expansion, is avoided. The risk of stress accumulation in the coating (overlay) leading to surface cracking and stress build-up when used as bond coat eventually causing TBC spallation is significantly reduced.
  • NiCrAlY alloys Main hardening effect for NiCrAlY alloys is precipitation hardening. With increasing temperature, the volume-fraction of ⁇ ' and ⁇ -Cr precipitates is significantly decreasing (see Fig. 2 ). In consequence, mechanical properties change and e.g. ultimate tensile strengths is significantly decreased. If compared to common NiCrAlY alloys, the NiCrAlSiTaCoBY coating has increased high temperature strength due to precipitation hardening by thermodynamically stable CrB and/or Cr 2 B precipitates.
  • NiCrAlSiTaCoBY coatings offer higher tensile ductility at lower temperatures and higher tensile strengths at comparable strain ( ⁇ 6 %) for higher temperatures.
  • the disclosed advanced coating class according to the invention does perform much better in cyclic loading.
  • Enhanced tensile strength, respectively creep resistance, at elevated temperature and less crack probability and severity due to increased ductility at low temperature do lead to a significantly extended lifetime of the high temperature protective layer.
  • the hot corrosion resistance will be increased, due to a diffusion-controlled dissolution of the CrB and/orCr 2 B phase which is acting as a chromium reservoir during long term service.
  • Coatings with a chemical composition at the lower specified range show a significant ductility, toughness respectively, increase. These coatings are especially optimized for application in high-cyclic operation with less oxidation and corrosion attack.
  • coatings with a chemical composition at the upper specification range deliver best protection from oxidation and hot corrosion at increased ductility (compared to standard MCrAlY). These coatings are especially optimized for cyclic and base-load mode with extended service lifetime intervals (compared to the current state-of-the-art MCrAlY's).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Claims (10)

  1. Revêtement protecteur à haute température à base de revêtement MCrAlY, avec M étant au moins un élément n'appartenant pas au groupe constitué du Ni, du Co et du Fe, pour un composant d'une turbomachine, en particulier d'une turbine à gaz, le revêtement contenant au moins 1,75 % en vol de borures de chrome et étant constitué de la composition chimique suivante (en % en poids) :
    de 10 à 27 % de Cr;
    de 3 à 12 % d'Al ;
    de 1 à 4 % de Si ;
    de 0,1 à 3 % de Ta ;
    de 0,01 à 3 % d'Y ;
    de 0,1 à 3 % de B ;
    de 0 à 7 % de M, avec M étant un élément différent n'appartenant pas audit groupe comparé au reste ;
    le reste étant M et les impuretés inévitables.
  2. Revêtement selon la revendication 1, caractérisé en ce que le revêtement est constitué de la composition chimique suivante (en % en poids) :
    de 10 à 27 % de Cr;
    de 3 à 12 % d'Al ;
    de 1 à 4 % de Si ;
    de 0,1 à 3 % de Ta ;
    de 0,01 à 3 % d'Y ;
    de 0,1 à 3 % de B ;
    de 0 à 7 % de Co ;
    le reste étant du Ni et des impuretés inévitables.
  3. Revêtement selon la revendication 1, caractérisé en ce que le revêtement est constitué de la composition chimique suivante (en % en poids) :
    de 10 à 27 % de Cr;
    de 3 à 12 % d'Al ;
    de 1 à 4 % de Si ;
    de 0,1 à 3 % de Ta ;
    de 0,01 à 3 % d'Y ;
    de 0,1 à 3 % de B ;
    de 0 à 7 % de Ni ;
    le reste étant du Co et des impuretés inévitables.
  4. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en Cr est de 21 à 25 % en poids, de préférence de 22 à 25 % en poids.
  5. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en Al est de 4 à 6 % en poids.
  6. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en Si est de 1,5 à 2,6 % en poids.
  7. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en Ta est de 1,5 à 3 % en poids.
  8. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en Y est de 0,01 à 1 % en poids.
  9. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en B est de 0,1 à 1 % en poids.
  10. Revêtement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la teneur en M, avec M étant un élément différent n'appartenant pas audit groupe comparé au reste, est de 0 à 1 % en poids.
EP15177229.0A 2015-07-17 2015-07-17 Revêtement protecteur à haute température Active EP3118345B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP15177229.0A EP3118345B1 (fr) 2015-07-17 2015-07-17 Revêtement protecteur à haute température
CN201610557032.0A CN106435277B (zh) 2015-07-17 2016-07-15 高温保护涂层
JP2016140472A JP2017053022A (ja) 2015-07-17 2016-07-15 高温保護コーティング
US15/211,588 US20170016123A1 (en) 2015-07-17 2016-07-15 High temperature protective coating
KR1020160089987A KR20170009784A (ko) 2015-07-17 2016-07-15 고온 보호 코팅

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15177229.0A EP3118345B1 (fr) 2015-07-17 2015-07-17 Revêtement protecteur à haute température

Publications (2)

Publication Number Publication Date
EP3118345A1 EP3118345A1 (fr) 2017-01-18
EP3118345B1 true EP3118345B1 (fr) 2018-04-11

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US (1) US20170016123A1 (fr)
EP (1) EP3118345B1 (fr)
JP (1) JP2017053022A (fr)
KR (1) KR20170009784A (fr)
CN (1) CN106435277B (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
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CN108644016B (zh) * 2018-03-26 2019-08-16 杭州意能电力技术有限公司 燃气-蒸汽联合循环机组热力系统停备用腐蚀防护工艺
RU2693283C1 (ru) * 2018-06-13 2019-07-02 Акционерное общество "Государственный космический научно-производственный центр имени М.В. Хруничева" (АО "ГКНПЦ им. М.В. Хруничева") Способ получения эрозионно-стойких теплозащитных покрытий
CA3129143A1 (fr) * 2019-03-07 2020-09-10 Oerlikon Metco (Us) Inc. Materiaux de couche d'accrochage avances pour des tbc presentant une resistance amelioree a la fatigue sous des variations cycliques de temperature et a la sulfuration
US11426822B2 (en) * 2020-12-03 2022-08-30 General Electric Company Braze composition and process of using
US20230287542A1 (en) * 2022-03-10 2023-09-14 General Electric Company Boride-reinforced aluminum-containing high entropy alloy composition

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3620693A (en) 1969-04-22 1971-11-16 Gte Electric Inc Ductile, high-temperature oxidation-resistant composites and processes for producing same
US3754903A (en) 1970-09-15 1973-08-28 United Aircraft Corp High temperature oxidation resistant coating alloy
US4013424A (en) 1971-06-19 1977-03-22 Rolls-Royce (1971) Limited Composite articles
US4022587A (en) 1974-04-24 1977-05-10 Cabot Corporation Protective nickel base alloy coatings
DE2816520C2 (de) * 1978-04-17 1984-04-12 Brown, Boveri & Cie Ag, 6800 Mannheim Verwendung eines Hartmetalls
US4477538A (en) 1981-02-17 1984-10-16 The United States Of America As Represented By The Secretary Of The Navy Platinum underlayers and overlayers for coatings
DE3246507A1 (de) 1982-12-16 1984-06-20 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Hochtemperatur-schutzschicht
US4743514A (en) 1983-06-29 1988-05-10 Allied-Signal Inc. Oxidation resistant protective coating system for gas turbine components, and process for preparation of coated components
EP0194391B1 (fr) * 1985-03-13 1989-06-21 General Electric Company Superalliages à base de nickel et comportant de l'yttrium ou le l'yttrium-silicium, spécialement utilisables comme revêtement compatible avec des superalliages modernes
JP3491872B2 (ja) * 1997-03-24 2004-01-26 松下電器産業株式会社 水素吸蔵合金電極
CN1198964C (zh) * 1997-10-30 2005-04-27 阿尔斯通公司 高温保护涂料
JP4217626B2 (ja) 2002-01-18 2009-02-04 アルストム テクノロジー リミテッド 高温保護層
JP4332449B2 (ja) * 2004-02-27 2009-09-16 新日本製鐵株式会社 鋼板の連続焼鈍炉用ハースロールに被覆した溶射被膜
JP2008030159A (ja) * 2006-07-28 2008-02-14 Mitsubishi Materials Corp 耐熱合金の高速重切削加工で硬質被覆層がすぐれた耐チッピング性と耐摩耗性を発揮する表面被覆切削工具
US8075662B2 (en) * 2008-04-25 2011-12-13 United Technologies Corporation Nickel braze alloy composition
US8273148B2 (en) * 2009-01-30 2012-09-25 Untied Technologies Corporation Nickel braze alloy composition
EP2248923A1 (fr) * 2009-04-27 2010-11-10 Siemens Aktiengesellschaft Superalliage de y/ý à base de nickel avec plusieurs éléments réactifs et utilisation de cet alliage dans des systèmes de matériau complexes
US8354176B2 (en) * 2009-05-22 2013-01-15 United Technologies Corporation Oxidation-corrosion resistant coating
US20100330295A1 (en) 2009-06-30 2010-12-30 General Electric Company Method for providing ductile environmental coating having fatigue and corrosion resistance
EP2374909B1 (fr) * 2010-03-30 2015-09-16 United Technologies Corporation Composition améliorée d'alliage de brasage au nickel
US20120128525A1 (en) 2010-11-24 2012-05-24 Kulkarni Anand A Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component
EP2781616A1 (fr) 2013-03-19 2014-09-24 ALSTOM Technology Ltd Procédé de revêtement d'un composant d'une turbomachine et composant revêtu pour une turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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JP2017053022A (ja) 2017-03-16
US20170016123A1 (en) 2017-01-19
CN106435277A (zh) 2017-02-22
CN106435277B (zh) 2021-02-02
KR20170009784A (ko) 2017-01-25
EP3118345A1 (fr) 2017-01-18

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