EP4055201A1 - Superlegierungsflugzeugteil mit kühlkanal - Google Patents

Superlegierungsflugzeugteil mit kühlkanal

Info

Publication number
EP4055201A1
EP4055201A1 EP20816268.5A EP20816268A EP4055201A1 EP 4055201 A1 EP4055201 A1 EP 4055201A1 EP 20816268 A EP20816268 A EP 20816268A EP 4055201 A1 EP4055201 A1 EP 4055201A1
Authority
EP
European Patent Office
Prior art keywords
substrate
mass fraction
cavity
layer
superalloy
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.)
Pending
Application number
EP20816268.5A
Other languages
English (en)
French (fr)
Inventor
Amar Saboundji
Jérémy RAME
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.)
Safran SA
Original Assignee
Safran SA
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 Safran SA filed Critical Safran SA
Publication of EP4055201A1 publication Critical patent/EP4055201A1/de
Pending 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
    • C23C10/08—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases only one element being diffused
    • C23C10/10—Chromising
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • C23C10/32—Chromising
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/38—Chromising
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/38—Chromising
    • C23C10/40—Chromising of ferrous surfaces
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/44—Siliconising
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/44—Siliconising
    • C23C10/46—Siliconising of ferrous surfaces
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/58—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than one step
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/60—After-treatment
    • 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
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/06—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of metallic material
    • 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
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/22—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of inorganic material, other than metallic material
    • C23C16/24—Deposition of silicon only
    • 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/021—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 only coatings only including layers of metallic material including 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/023—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 only coatings only including layers of metallic material only coatings of metal elements only
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an aircraft part, such as a turbine blade or a distributor blade.
  • the exhaust gases generated by the combustion chamber can reach high temperatures, for example greater than 1200 ° C, or even 1600 ° C.
  • the parts of the turbojet, in contact with these gases. exhaust, such as turbine blades for example, must thus be able to retain their mechanical properties at these high temperatures.
  • Superalloys are a family of high strength metal alloys that can work at temperatures relatively close to their melting points (typically 0.7 to 0.8 times their melting point).
  • a superalloy part always has an operating temperature limit above which the part creep is too great for the part to be usable.
  • a fluid such as a gas leaving the low pressure compressor, can be introduced into the cooling channel or channels. Its circulation then allows the room to be cooled.
  • the walls of the cooling channel (s) are sensitive to the environment. In particular, these walls can be oxidized and / or corroded during the use of the part, which reduces its time of use.
  • An aim of the invention is to provide a solution for manufacturing a turbine part comprising a cooling channel which is less sensitive to oxidation and or to corrosion than the cooling channels of the prior art.
  • a part comprising a substrate made of a nickel-based superalloy, the substrate having a first average mass fraction of one or more first elements chosen from hafnium, silicon and chromium, substrate comprising at least one cavity open in the room and preferably a cooling channel, the substrate comprising a surface layer at least partially forming the cavity, the surface layer having a second average mass fraction of the first element (s) strictly greater than the first average mass fraction.
  • the part further comprises a coating covering the surface layer, the coating having a mass fraction of the first element (s) greater than 50%, and preferably greater than 90 3 ⁇ 4,
  • the thickness I2 of the protective coating being at least greater than 50 nm
  • the first element is hafnium and the second mass fraction is between 0.4% and 4.5%
  • the first element is silicon
  • the second mass fraction is between 4% and 10%
  • the first element is chromium and the second mass fraction is between 0.2% and 5%
  • the substrate comprises rhenium and / or ruthenium and the average mass fraction of rhenium and / or ruthenium of the substrate is greater than or equal to 3%, and preferably greater than or equal to 4%,
  • the part is a turbine part.
  • Another aspect of the invention is an aircraft turbine comprising a part according to the invention.
  • Another aspect of the invention is an aircraft comprising a part according to the invention.
  • Another aspect of the invention is a method of manufacturing an aircraft part according to the invention, comprising at least the following steps:
  • the heat treatment is carried out in a vacuum chamber or in an enclosure comprising one or more inert gases, preferably at least one gas chosen from argon and helium,
  • the heat treatment step is carried out for one to eight hours, in an enclosure in which the temperature is controlled between 700 ° C and 1300 ° C and preferably between 900 ° C and 1250 ° C.
  • Another aspect of the invention is a method for cooling an aircraft part, in which the part is in accordance with the invention, the method comprising a step of injecting a cooling fluid into the cavity.
  • FIG. 1 schematically illustrates a section of an aircraft part, for example a turbine blade, or a distributor fin, comprising a cooling channel,
  • FIG. 2 schematically illustrates a method of manufacturing a part according to one embodiment of the invention
  • FIG. 3 schematically illustrates the wall of a cooling channel during the manufacture of a part according to an embodiment of the invention
  • FIG. 4 schematically illustrates the wall of a cooling channel during the manufacture of a part according to an embodiment of the invention
  • FIG. 5 schematically illustrates the wall of a cooling channel of a room according to one embodiment of the invention
  • FIG. 6 is a photomicrograph of a wall of a cooling channel during the manufacture of a part according to an embodiment of the invention
  • FIG. 7 is a photomicrograph of a wall of a cooling channel of a room according to one embodiment of the invention.
  • superalloy denotes an alloy exhibiting, at high temperature and at high pressure, very good resistance to oxidation, corrosion, creep and cyclic stresses (in particular mechanical or thermal).
  • superalloys find a particular application in the manufacture of parts used in aeronautics, for example turbine blades, because they constitute a family of high resistance alloys which can work at temperatures relatively close to their melting points (typically 0 , 7 to 0.8 times their melting temperatures).
  • a superalloy can have a two-phase microstructure comprising a first phase (called “y phase”) forming a matrix, and a second phase (called “y phase”) forming precipitates hardening in the matrix.
  • y phase a first phase
  • y phase a second phase
  • the coexistence of these two phases is referred to as "y-y phase”.
  • the "base” of the superalloy refers to the main metal component of the matrix. In the majority of cases, the superalloys include an iron, cobalt or nickel base, but also sometimes a titanium or aluminum base.
  • the base of the superalloy is preferably a nickel base.
  • Nickel-based superalloys have the advantage of offering a good compromise between resistance to oxidation, resistance to breakage at high temperature and weight, which justifies their use in the hottest parts of turbojets.
  • the phase y ' has an ordered L12 structure, derived from the face-centered cubic structure, consistent with the matrix, that is to say having an atomic mesh very close to the latter.
  • phase g ' has the remarkable property of having a mechanical resistance which increases with temperature up to approximately 800 ° C.
  • the very strong coherence between phases g and g ′ confers a very high mechanical resistance to hot nickel-based superalloys, which itself depends on the ratio g / g ′ and on the size of the hardening precipitates.
  • a superalloy is preferably rich in rhenium and / or ruthenium, that is to say that the average mass fraction of rhenium and ruthenium of the superalloy is greater than or equal to 3%, and preferably to 4%, making it possible to increase the creep resistance of superalloy parts compared to rhenium-free superalloy parts.
  • a superalloy is preferably poor in chromium on average, that is to say that the average mass fraction in the whole of the chromium superalloy is less than 5%, preferably less than 3%.
  • the chromium depletion during rhenium and / or ruthenium enrichment of the superalloy makes it possible to keep a stable allotropic structure of the superalloy, in particular a g-Y phase ’ ⁇
  • mass fraction refers to the ratio of the mass of an element or a group of elements to the total mass.
  • the term “protective coating” is understood to mean a layer covering the substrate and making it possible to protect it chemically and / or mechanically.
  • the protective coating preferably makes it possible to prevent corrosion and / or oxidation of the substrate.
  • the protective coating can preferably be a bonding layer between the substrate and a thermal protection layer.
  • open cavity of a room is meant a cavity connected to the outside of the room.
  • second vacuum is understood to mean a vacuum in which the atmosphere is controlled at a pressure of between 10 7 millibars and 10 3 millibars excluded.
  • primary vacuum is understood to mean a vacuum in which the atmosphere is controlled at a pressure of between 10 3 and 1 millibars.
  • an aircraft part 1 comprises a substrate 2 in monocrystalline superalloy.
  • the aircraft part is preferably a turbine part.
  • the monocrystalline superalloy is preferably a nickel-based superalloy, but can also be a cobalt-based superalloy, for example obtained by an equiaxial casting process or by directed solidification.
  • Substrate 2 preferably mainly has a g-g ’phase.
  • the substrate 2 can also comprise rhenium and / or ruthenium, the average mass fraction of rhenium and / or ruthenium being greater than or equal to 3%, and preferably greater than or equal to 4%, making it possible to increase the creep resistance of the superalloy part compared to superalloy parts without rhenium and / or ruthenium.
  • the substrate 2 preferably has a first average mass fraction of chromium in the whole of the weak substrate, that is to say less than 5 3 ⁇ 4.
  • the substrate exhibits mechanical properties of resistance to creep at high temperature which are greater than a substrate exhibiting a first mass fraction of chromium greater than 5%.
  • Table 1 describes examples of the composition of substrate 2, in average mass fraction of each element in the whole of substrate 2.
  • the substrate 2 forms at least one cavity 12 in the part 1.
  • the cavity 12 is a cooling channel 13 of the part 1.
  • the cooling channel 13 can have a fluid inlet. coolant and a coolant outlet. It is thus possible to introduce a cooling fluid, such as a gas from the low-pressure compressor, into the room's cooling channel, so as to reduce the temperature of the room during its use.
  • one aspect of the invention is a method for manufacturing an aircraft part.
  • Such a method comprises a step 201 of supplying a part comprising a substrate 2 as described above. Such a substrate 2 has then already undergone the steps of dissolving the eutectics and quenching.
  • the method comprises a step 202 of depositing, on at least part of the cavity 12, at least one layer 14 for treating a first element chosen from hafnium, silicon and chromium.
  • several layers 14, each layer 14 comprising a different element chosen from hafnium, silicon and chromium can be deposited on at least part of the cavity 12.
  • the thickness h of the layer 14 deposited during step 102 can be between 10 nm and 10 ⁇ m.
  • the thickness h of the deposited layer 14 is preferably between 50 nm and 500 nm.
  • the thickness h of the deposited layer 14 is preferably between 100 nm and 500 nm.
  • the thickness h of the layer 14 deposits and is preferably between 0.5 micrometers and 3 micrometers.
  • the deposition of the layer or layers 14 on the cavity 12 can be carried out by chemical vapor deposition (CVD) methods, such as PECVD, LPCVD, UHVCVD, APCVD, ALCVD, UHVCVD.
  • CVD chemical vapor deposition
  • the method comprises a step 203 of heat treatment of the substrate 2 and of the layer 14 so as to diffuse the first element (s) of the layer 14 in the substrate 2.
  • the first element (s) of the layer 14 diffuse in the substrate 2, so as to form a surface layer C1 in the substrate 2.
  • a second average mass fraction in the first element (s) ( s) in the surface layer C1 is strictly greater than the first average mass fraction in the first element in the substrate 2.
  • the substrate 2 comprises the surface layer C1, and is covered by a coating C2, resulting from the layer 14 deposited before the heat treatment step 203.
  • the coating C2 may only include the first element (s). However, it is possible that, during the heat treatment step 203, certain elements of the substrate 2 are introduced into the layer 14. Thus, the coating C2 has a mass fraction of the first element (s) greater than 50%, and preferably greater than at 90%.
  • the thickness I2 of the surface layer C1 is greater than 50 nm, ie the characteristic diffusion length of the first element (s).
  • the thickness I2 can in particular be greater than 100 nm, and preferably between 100 nm and 100 ⁇ m.
  • the coating C2 has a thickness I3 of between 50 nm and 100 ⁇ m.
  • the surface layer C1 has a second mass fraction of the first element suitable for forming a protective coating by oxidation of the first element.
  • the second mass fraction may preferably be between 0.4% and 4.5%.
  • the first element is silicon
  • the second mass fraction may preferably be between 4% and 10%.
  • the first element is chromium
  • the second mass fraction may preferably be between 0.2% and 5%.
  • the substrate 2 and the layer or layers 14 obtained during step 202 can for example be placed in an enclosure for the implementation of the thermal treatment step 203.
  • the enclosure can be placed under vacuum, or filled with one or more inert gases, such as argon and / or helium.
  • a secondary vacuum can be maintained inside the enclosure.
  • a primary vacuum can be controlled inside the enclosure, the primary vacuum being formed by at least one element chosen from among argon, helium and dihydrogen.
  • the heat treatment step 203 comprises a thermal rise sub-step in which the temperature in the enclosure is controlled so as to increase at a rate within a range of 5 to 100 ° C. per minute.
  • the heat treatment step is carried out for one to eight hours, in an enclosure in which the temperature is controlled between 700 ° C and 1300 ° C, and preferably between 900 ° C and 1250 ° C. Above 700 ° C, and preferably above 900 ° C, the first element or elements diffuse into the substrate 2.
  • the temperature is controlled below 1300 ° C, and preferably below 1250 ° C, from so as not to degrade the superalloy.

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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 Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physical Vapour Deposition (AREA)
EP20816268.5A 2019-11-05 2020-11-05 Superlegierungsflugzeugteil mit kühlkanal Pending EP4055201A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1912379A FR3102775B1 (fr) 2019-11-05 2019-11-05 Piece d'aeronef en superalliage comprenant un canal de refroidissement
PCT/FR2020/052002 WO2021089945A1 (fr) 2019-11-05 2020-11-05 Piece d'aeronef en superalliage comprenant un canal de refroidissement

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EP4055201A1 true EP4055201A1 (de) 2022-09-14

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US (1) US20220356555A1 (de)
EP (1) EP4055201A1 (de)
CN (1) CN114667365A (de)
FR (1) FR3102775B1 (de)
WO (1) WO2021089945A1 (de)

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WO2021089945A1 (fr) 2021-05-14
FR3102775B1 (fr) 2022-04-22
US20220356555A1 (en) 2022-11-10
FR3102775A1 (fr) 2021-05-07
CN114667365A (zh) 2022-06-24

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