US20130115085A1 - Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns - Google Patents

Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns Download PDF

Info

Publication number
US20130115085A1
US20130115085A1 US13/808,216 US201113808216A US2013115085A1 US 20130115085 A1 US20130115085 A1 US 20130115085A1 US 201113808216 A US201113808216 A US 201113808216A US 2013115085 A1 US2013115085 A1 US 2013115085A1
Authority
US
United States
Prior art keywords
thermal barrier
ceramic
columns
substrate
depositing
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.)
Abandoned
Application number
US13/808,216
Other languages
English (en)
Inventor
Justine Menuey
Sarah Hamadi
Juliette Hugot
André Hubert Louis Malie
Fabrice Crabos
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CRABOS, FABRICE, HAMADI, SARAH, HUGOT, JULIETTE, MALIE, ANDRE HUBERT LOUIS, MENUEY, JUSTINE
Publication of US20130115085A1 publication Critical patent/US20130115085A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • 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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/04—Coating on selected surface areas, e.g. using masks
    • C23C14/042—Coating on selected surface areas, e.g. using masks using masks
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/24—Vacuum evaporation
    • C23C14/28—Vacuum evaporation by wave energy or particle radiation
    • C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/58—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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/06—Coating on selected surface areas, e.g. using masks
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/1204—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material inorganic material, e.g. non-oxide and non-metallic such as sulfides, nitrides based compounds
    • C23C18/1208—Oxides, e.g. ceramics
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/1225—Deposition of multilayers of inorganic 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/1229—Composition of the substrate
    • C23C18/1245—Inorganic substrates other than metallic
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/125—Process of deposition of the inorganic material
    • C23C18/1254—Sol or sol-gel processing
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet

Definitions

  • the field of the present invention is that of turbomachines and, more particularly that of components for these turbomachines which are subjected to high temperatures.
  • a turbomachine as used for propulsion in the aeronautical field, comprises an atmospheric air intake that communicates with one or more compressors, generally including a fan, which are rotated about one and the same axis.
  • the main stream of this air after having been compressed, supplies a combustion chamber positioned annularly around this axis and is mixed with a fuel in order to provide hot gases, downstream, to one or more turbines through which these hot gases are expanded, the turbine rotors driving the rotors of the compressors.
  • the engines operate at a temperature of the engine gases at the turbine inlet which is sought to be as high as possible because this temperature conditions the performances of the turbomachine.
  • the materials of the hot sections are selected to withstand these operating conditions and the walls of the components swept by the hot gases, such as the turbine nozzles or the rotating turbine blades, are provided with cooling means. Furthermore, due to the metallic structure of these blades, made of a superalloy based on nickel or on cobalt, it is also necessary to protect them against the erosion and corrosion which are generated by the constituents of the engine gases at these temperatures.
  • a thermal barrier is generally composed of a ceramic layer of around a hundred microns, which is deposited at the surface of the metallic layer.
  • This aluminum sublayer which is generally deposited by a vapor phase aluminization process (referred to as APVS for the version of the process used by the applicant), is fastened to the substrate by metallic interdiffusion and forms a protective oxide layer at the surface.
  • APVS vapor phase aluminization
  • thermal barrier made of ceramic, it may be produced in several ways, depending on the use which will be made thereof. Two types of structures are roughly distinguished for thermal barriers: columnar barriers, the structure of which is that of columns juxtaposed next to one another and which extend perpendicular to the surface of the substrate, and laminar or isotropic barriers that extend in uniform layers over the surface of the substrate.
  • the first ones are generally produced by a process referred to as EBPVD (electron beam physical vapor deposition) in which a target anode is bombarded, under high vacuum, by an electron beam emitted by a charged tungsten filament.
  • EBPVD electron beam physical vapor deposition
  • the electron beam makes the molecules from the target pass into the gaseous phase.
  • These molecules then precipitate in a solid form, covering the part to be protected with a thin layer of the anode material.
  • These thermal barriers are characterized by a good resistance to thermal cycling but also by a relatively high thermal conductivity.
  • the isotropic barriers are generally deposited by plasma, using a thermal spraying process of the APS (atmospheric plasma spraying) type or by a sol-gel process.
  • the sol-gel process makes it possible, via a simple polymerization of molecular precursors in solution, to obtain, at a temperature close to ambient temperature, glassy materials without passing through a melting step. These precursors exist for a large number of metals and are, for the most part, soluble in standard solvents.
  • the chemical reactions contribute to the formation of a three-dimensional inorganic network, known under the name of gel, in which the solvent remains.
  • the process of obtaining the material, from the gel passes through a drying step which consists in evacuating the solvent out of the polymer network.
  • the advantage of such a barrier is the porosity that it exhibits.
  • the isotropic barriers are therefore characterized by a low thermal conductivity, which is the desired objective, but they have an inadequate resistance to thermal cycling.
  • the barriers obtained by the sol-gel process have, themselves, a mediocre erosion resistance.
  • the objective of the present invention is to overcome these drawbacks by proposing a process for producing a thermal barrier which does not comprise some of the drawbacks of the prior art and, in particular, which has a low conductivity combined with a good service life.
  • one subject of the invention is a process for depositing a ceramic layer onto a metallic substrate for producing a thermal barrier, comprising a step of depositing said ceramic in a columnar structure, characterized in that said deposition is carried out through a grid pierced with holes, positioned parallel to the surface of the substrate so as to produce at least two columns of ceramic which are separated from one another by a spacing.
  • the columns thus produced are sufficient to ensure the mechanical strength of the barrier and its erosion resistance and leave, furthermore, space between them in order to fill the latter with the most appropriate material.
  • the invention thus creates a great flexibility for the composition of the thermal barrier.
  • the width of the holes is between 10 and 300 microns.
  • the spacing between the holes is between 10 and 100 microns.
  • the process also comprises a subsequent step of depositing an isotropic layer of ceramic in said spacings.
  • the isotropic structure of the deposit in the spacings guarantees a good impermeability of the barrier against the invasion of oxidizing gases from the stream in the direction of the substrate.
  • the second deposition is carried out by an operation for dip-coating the substrate equipped with its columns into a solution of sol-gel type.
  • a ceramic with an isotropic structure is thus obtained, which has a high porosity and therefore a low thermal conductivity.
  • the isotropic deposition is carried out by a sequence of dip-coating and withdrawal operations in said sol-gel solution and drying operations carried out between two dip-coating and withdrawal operations, until a thickness substantially equal to the height of the columns is obtained.
  • the columns ensure both a good mechanical strength and a protection of the isotropic layer.
  • the process also comprises a final step of heat treatment.
  • the invention also relates to a thermal barrier deposited on a metallic substrate, characterized in that it comprises ceramic columns that extend perpendicular to the surface of said substrate and that are separated from one another by spacings, said spacings being filled with an isotropic ceramic layer.
  • the columns have a maximum width of between 10 and 300 microns.
  • the spacings have a width of between 10 and 100 microns.
  • the isotropic layer is made of porous ceramic.
  • the invention finally relates to a turbine blade for a turbomachine comprising a thermal barrier as described above and to a turbomachine comprising at least one such blade.
  • FIG. 1 is a schematic view of the physical composition of a thermal barrier for a turbine blade
  • FIG. 2 is a schematic cross-sectional view of a thermal barrier after carrying out a first step of a process according to one embodiment of the invention
  • FIG. 3 represents the four phases for carrying out the second step of the process according to one embodiment of the invention.
  • FIG. 4 is a schematic cross-sectional view of a thermal barrier at the end of the process according to the invention.
  • FIG. 1 seen in cross section is the composition of a thermal barrier deposited on the surface of a turbine blade, the latter being based by a stream of hot gas represented by an arrow pointed toward the left of the figure.
  • the metal constituting the blade typically a superalloy based on nickel or cobalt, forms a substrate 1 , deposited on which is a sublayer made of aluminum 2 , sandwiched between the substrate 1 and a ceramic layer 3 .
  • the role of the aluminum sublayer is to retain the ceramic layer and to offer a certain elasticity to the assembly in order to enable it to absorb the difference in expansion, represented by two arrows in opposite directions, that exists between the high-expansion substrate 1 and the low-expansion ceramic 3 .
  • the ceramic 3 represented here is of columnar structure, which allows lateral displacements, owing to the appearance of cracks between the columns, and which gives it a good service life.
  • the aluminum is then brought into contact with the oxygen conveyed by the gases that circulate in the stream of the turbomachine, which results in an average thermal conductivity of the barrier and a gradual damaging thereof.
  • FIG. 2 the progress of the production of a thermal barrier after the implementation of the first step of the process according to the invention is seen.
  • a grid 10 placed on top of the substrate 1 to be covered is a grid 10 formed of evenly-spaced holes 11 so as to let through the vapor-phase deposition carried out by the EBPVD process or by any other process enabling the production of a columnar deposition (such as for example the APS process under very low pressure, carried out by the company Sulzer and known under the name LPPS-TF).
  • the grid forms a mask which enables the deposition of the ceramic in the form of columns or of a group of columns 5 spaced apart from one another.
  • the spacing thereof is, on the one hand, large enough so that a subsequent inter-columnar deposition can be carried out and, on the other hand, close enough to guarantee the mechanical strength of the whole of the thermal barrier.
  • the columns or the groups of columns 5 have a thickness between 10 and 300 microns and the spacing 6 between them varies between one and a few tens of microns.
  • the thermal barrier is in the situation represented, with a substrate 1 and a sublayer 2 which are surmounted by an assembly of columns 5 made of ceramic. These columns conventionally have a shape which gets wider towards the top and which results from the gradual aggregation of the particles deposited. Between these columns are empty spaces which will be filled during the second step of the process according to the invention.
  • FIG. 3 shows, in four diagrams referenced 3 a to 3 d , the carrying out of this second step. Each diagram corresponds to a phase during which:
  • the substrate equipped with its ceramic columns 5 is dip-coated in a solution 20 of sol-gel type based in particular on precursors of yttriated zirconia, which is used in the processes for producing an isotropic thermal barrier.
  • the viscosity of the solution is such that it is sufficiently fluid in order to be able to be inserted into the spacing 6 between the columns 5 and fill them completely, and it is sufficiently viscous so that it remains stuck to the component during the withdrawal thereof;
  • 3-phase 3 c the component is then withdrawn from the solution 20 at a controlled speed so that a film of a desired thickness can be formed at the surface of the thermal barrier, homogeneously and with good adhesion;
  • 4-phase 3 d it is dried so that the solution 20 which has remained trapped between the columns 5 solidifies. After drying and removal of the solvent, a thin layer of ceramic is obtained which remains lodged between the columns. Since the thickness of ceramic deposited during the fourth phase is very small, it is necessary to carry out the operation, known as dip-coating, several times, that is to say to repeat the four operations after the drying of each of the layers formed in 3 d.
  • FIG. 4 gives the result obtained after repetition of the four operations from FIG. 3 .
  • the substrate 1 and its sublayer 2 are covered with a thermal barrier 3 composed of evenly-spaced columns 5 , between which ceramic is deposited in isotropic form 7 .
  • This isotropic layer has many air bubbles that are trapped, which gives it a high porosity, and also gives the thermal barrier a good resistance to heat conduction.
  • the substrate constituting the material of the blade to be protected is first covered with a sublayer made of aluminum or of any other metal capable of constituting a thermal barrier sublayer. It is placed in equipment for the deposition of a ceramic layer, for example by electron beam physical vapor deposition, by positioning a grid 10 , pierced with holes 11 , on top of the component to be protected, at a distance that enables the formation of ceramic columns or a group of ceramic columns. The deposition takes place through holes 11 and the ceramic is deposited on the substrate 1 by growing perpendicularly to said substrate.
  • the deposition takes place along columns 5 distributed discretely over the surface of the substrate 1 ; between these columns 5 empty spacings 6 remain, which will be filled during the next step of the process.
  • the component to be protected is then withdrawn from the columnar deposition equipment and transferred to a second piece of equipment for the deposition of the porous portion.
  • the second step of the process consists of a succession of dip-coating operations in a sol-gel type solution, comprising the four phases described previously. During each of these operations, the spacings 6 are filled with a thin layer of porous ceramic which accumulates, dip coating after dip coating, until a layer 7 is formed that completely fills the spacings 6 .
  • the production of the thermal barrier is completed by a conventional heat treatment, during which the ceramic is stabilized and acquires the desired crystalline structure.
  • a mixed thermal barrier that comprises, on the one hand, a series of columns 5 which ensure a good mechanical strength and a good resistance to erosion by the gases which sweep over the component, and, on the other hand, a highly porous isotropic layer which ensures a good resistance to thermal conduction in the direction of the substrate.
  • This protects the substrate 1 and the sublayer 2 against oxidation by the gases from the stream that circulates in the engine.
  • the presence of columns enables the thermal barrier to spread out longitudinally over the surface of the substrate, during the expansion thereof, without risking the appearance of cracks which would enable oxygen from the gases to reach the metal of the substrate and damage it.
  • thermo mechanical stresses The objective of having a thermal barrier which combines a low thermal conductivity, a good erosion resistance and a good adaptation to thermo mechanical stresses, is thus achieved.
  • the first step of the production of the thermal barrier was described using the EBPVD process, but it can just as well be carried out with the other known deposition processes, such as thermal spraying, the presence of the mask formed by the grid being sufficient to generate the desired columnar structure during this step.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Physics & Mathematics (AREA)
  • General Chemical & Material Sciences (AREA)
  • Thermal Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Dispersion Chemistry (AREA)
  • Toxicology (AREA)
  • Health & Medical Sciences (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
US13/808,216 2010-07-06 2011-07-05 Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns Abandoned US20130115085A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1055462A FR2962447B1 (fr) 2010-07-06 2010-07-06 Barriere thermique pour aube de turbine, a structure colonnaire avec des colonnes espacees
FR1055462 2010-07-06
PCT/FR2011/051596 WO2012004525A1 (fr) 2010-07-06 2011-07-05 Barriere thermique pour aube de turbine, a structure colonnaire avec des colonnes espacees

Publications (1)

Publication Number Publication Date
US20130115085A1 true US20130115085A1 (en) 2013-05-09

Family

ID=43567933

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/808,216 Abandoned US20130115085A1 (en) 2010-07-06 2011-07-05 Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns

Country Status (9)

Country Link
US (1) US20130115085A1 (ru)
EP (1) EP2591138B1 (ru)
JP (1) JP2013543073A (ru)
CN (1) CN102971446B (ru)
BR (1) BR112013000072A2 (ru)
CA (1) CA2803160A1 (ru)
FR (1) FR2962447B1 (ru)
RU (1) RU2578625C2 (ru)
WO (1) WO2012004525A1 (ru)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3055351B1 (fr) * 2016-08-25 2019-11-08 Safran Procede de realisation d'un systeme barriere thermique sur un substrat metallique d'une piece de turbomachine
CN109147984B (zh) * 2018-07-24 2020-03-27 北京工业大学 一种提高表面耐强束脉冲热疲劳的方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6060177A (en) * 1998-02-19 2000-05-09 United Technologies Corporation Method of applying an overcoat to a thermal barrier coating and coated article
US20070071996A1 (en) * 2005-09-26 2007-03-29 General Electric Company Gamma prime phase-containing nickel aluminide coating
US20070116883A1 (en) * 2005-11-22 2007-05-24 General Electric Company Process for forming thermal barrier coating resistant to infiltration

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2218451C2 (ru) * 1996-12-10 2003-12-10 Сименс Акциенгезелльшафт Изделие с теплоизолирующим слоем, подвергаемое воздействию горячего газа, а также способ его изготовления
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
GB9800511D0 (en) * 1998-01-13 1998-03-11 Rolls Royce Plc A metallic article having a thermal barrier coating and a method of application thereof
US6203927B1 (en) * 1999-02-05 2001-03-20 Siemens Westinghouse Power Corporation Thermal barrier coating resistant to sintering
US6482537B1 (en) * 2000-03-24 2002-11-19 Honeywell International, Inc. Lower conductivity barrier coating
JP4533718B2 (ja) * 2000-06-16 2010-09-01 三菱重工業株式会社 遮熱コーティング材、遮熱コーティング材を適用したガスタービン部材およびガスタービン
US6670046B1 (en) * 2000-08-31 2003-12-30 Siemens Westinghouse Power Corporation Thermal barrier coating system for turbine components
US6528118B2 (en) * 2001-02-06 2003-03-04 General Electric Company Process for creating structured porosity in thermal barrier coating
US8357454B2 (en) * 2001-08-02 2013-01-22 Siemens Energy, Inc. Segmented thermal barrier coating
WO2004043691A1 (en) * 2002-11-12 2004-05-27 University Of Virginia Patent Foundation Extremely strain tolerant thermal protection coating and related method and apparatus thereof
FR2854166B1 (fr) 2003-04-25 2007-02-09 Snecma Moteurs Procede d'obtention d'une barriere thermique flexo-adaptative
US7150926B2 (en) * 2003-07-16 2006-12-19 Honeywell International, Inc. Thermal barrier coating with stabilized compliant microstructure
US7285312B2 (en) * 2004-01-16 2007-10-23 Honeywell International, Inc. Atomic layer deposition for turbine components
EP1645654A1 (fr) 2004-05-18 2006-04-12 Snecma Procédé d'obtention d'une barrière thermique flexo-adaptive
JP3803104B2 (ja) * 2004-06-07 2006-08-02 トーカロ株式会社 耐食性および耐熱性に優れる熱遮蔽皮膜被覆部材とその製造方法
EP1645655A1 (de) * 2004-10-05 2006-04-12 Siemens Aktiengesellschaft Bauteil mit Beschichtung und Verfahren zum Herstellen einer Beschichtung
JP4568094B2 (ja) * 2004-11-18 2010-10-27 株式会社東芝 遮熱コーティング部材およびその形成方法
CN1621556A (zh) * 2004-12-15 2005-06-01 北京航空航天大学 一种具有高热稳定性、抗高温烧结、低热导率的热障涂层
EP1808508A1 (de) * 2006-01-17 2007-07-18 Siemens Aktiengesellschaft Im Strömungskanal einer Strömungsmaschine anzuordnendes Bauteil und Spritzverfahren zum Erzeugen einer Beschichtung
JP4775715B2 (ja) * 2006-02-01 2011-09-21 独立行政法人物質・材料研究機構 有機−無機ハイブリッド高分子組成物とその膜の製造方法
DE102006010860A1 (de) * 2006-03-09 2007-09-13 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer Wärmedämmschicht und Wärmedämmschicht für ein Bauteil
FR2914319B1 (fr) * 2007-03-30 2009-06-26 Snecma Sa Barriere thermique deposee directement sur superalliages monocristallins.
FR2928664B1 (fr) 2008-03-14 2010-04-16 Snecma Procede pour former un revetement protecteur contenant de l'aluminium et du zirconium sur une piece metallique.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6060177A (en) * 1998-02-19 2000-05-09 United Technologies Corporation Method of applying an overcoat to a thermal barrier coating and coated article
US20070071996A1 (en) * 2005-09-26 2007-03-29 General Electric Company Gamma prime phase-containing nickel aluminide coating
US20070116883A1 (en) * 2005-11-22 2007-05-24 General Electric Company Process for forming thermal barrier coating resistant to infiltration

Also Published As

Publication number Publication date
BR112013000072A2 (pt) 2016-05-10
RU2578625C2 (ru) 2016-03-27
CN102971446A (zh) 2013-03-13
RU2012157971A (ru) 2014-08-20
EP2591138B1 (fr) 2014-11-19
CN102971446B (zh) 2015-11-25
JP2013543073A (ja) 2013-11-28
FR2962447B1 (fr) 2013-09-20
WO2012004525A1 (fr) 2012-01-12
EP2591138A1 (fr) 2013-05-15
CA2803160A1 (fr) 2012-01-12
FR2962447A1 (fr) 2012-01-13

Similar Documents

Publication Publication Date Title
CN109874330B (zh) 含陶瓷化合物的层涂覆固体基材表面的方法及所获得的涂覆的基材
US8741420B2 (en) Component and methods of fabricating and coating a component
US7700167B2 (en) Erosion-protective coatings on polymer-matrix composites and components incorporating such coated composites
RU2007107675A (ru) Способ нанесения термобарьерного покрытия на изделие с покрытием
US20120148769A1 (en) Method of fabricating a component using a two-layer structural coating
US9347126B2 (en) Process of fabricating thermal barrier coatings
JP4401576B2 (ja) 耐焼結性断熱被覆を有する装置及び製造方法
EP1710398A1 (en) Turbine component other than airfoil having ceramic corrosion resistant coating and methods for making same
EP2258889B1 (en) Method and apparatus for applying a thermal barrier coating
JP2008151128A (ja) ガスタービンエンジン構成要素、そのコーティング方法およびコーティング設計方法
JP2011508093A (ja) Ｃｍａｓ浸透耐性を向上させる方法
US20220025523A1 (en) Cmas-resistant themal barrier coating for part of gas turbine engine
US11946147B2 (en) Thermal barrier coating, turbine member, gas turbine, and method for producing thermal barrier coating
EP2431495A1 (en) A method for forming thermal barrier coating and device with the thermal barrier coating
CA2964118C (en) System and methods of forming a multilayer thermal barrier coating system
US20130115085A1 (en) Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns
EP3943636A1 (en) Cmas-resistant themal coating for part of gas turbine engine
US12006269B2 (en) Multilayer protective coating systems for gas turbine engine applications and methods for fabricating the same
EP2423347A1 (en) Method for forming a thermal barrier coating and a turbine component with the thermal barrier coating
EP1538239A2 (en) Sprayable noble metal coating for high temperature use on ceramic and smoothcoat coated aircraft engine parts
US11970950B2 (en) Ceramic coating, turbine component, and gas turbine
EP2778257B1 (en) Process of fabricating thermal barrier coatings
CN116605904A (zh) 烧绿石/缺陷萤石锆酸盐

Legal Events

Date Code Title Description
AS Assignment

Owner name: SNECMA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MENUEY, JUSTINE;HAMADI, SARAH;HUGOT, JULIETTE;AND OTHERS;REEL/FRAME:029587/0028

Effective date: 20120915

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION