CN115449786A - Thermal barrier coating and preparation method and application thereof - Google Patents

Thermal barrier coating and preparation method and application thereof Download PDF

Info

Publication number
CN115449786A
CN115449786A CN202211112923.7A CN202211112923A CN115449786A CN 115449786 A CN115449786 A CN 115449786A CN 202211112923 A CN202211112923 A CN 202211112923A CN 115449786 A CN115449786 A CN 115449786A
Authority
CN
China
Prior art keywords
barrier coating
ysz
thermal barrier
layer
content
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.)
Granted
Application number
CN202211112923.7A
Other languages
Chinese (zh)
Other versions
CN115449786B (en
Inventor
南晴
肖俊峰
高斯峰
唐文书
李永君
张炯
刘全明
马伟
徐小卜
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.)
Xian Thermal Power Research Institute Co Ltd
Original Assignee
Xian Thermal Power Research Institute Co Ltd
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 Xian Thermal Power Research Institute Co Ltd filed Critical Xian Thermal Power Research Institute Co Ltd
Priority to CN202211112923.7A priority Critical patent/CN115449786B/en
Publication of CN115449786A publication Critical patent/CN115449786A/en
Application granted granted Critical
Publication of CN115449786B publication Critical patent/CN115449786B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/082—Coating starting from inorganic powder by application of heat or pressure and heat without intermediate formation of a liquid in the layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • 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

Landscapes

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

Abstract

The present invention belongs to the field of heat barrier coating material technologyThe technical field, in particular to a thermal barrier coating and a preparation method and application thereof. The thermal barrier coating comprises a YSZ base layer and a YSZ surface layer, wherein Y in the YSZ base layer 2 O 3 The content is 6-8 wt.%, al 2 O 3 The content is 5-10 wt.%; y in the YSZ surface layer 2 O 3 Content of 10-12wt.%, al 2 O 3 The content is 5-10 wt.%. The invention is realized by the opposite dispersion phase Al in the YSZ substrate layer and the YSZ surface layer 2 O 3 And a stabilizer Y 2 O 3 The content of the composite is limited, so that the Young modulus, the bending strength and the fracture toughness of the YSZ substrate layer and the YSZ surface layer can be improved; meanwhile, the structure is properly improved on the YSZ surface layer, and the ZrO is improved 2 Phase stability of (2). The thermal barrier coating has the advantages of simple production process, high efficiency, excellent and stable performance, and is suitable for large-scale application to high-temperature components such as combustion chamber flame tubes and transition sections of aeroengines, marine gas turbines and gas turbines for power generation, turbines or turbine blades, retaining rings and the like.

Description

Thermal barrier coating and preparation method and application thereof
Technical Field
The invention belongs to the technical field of thermal barrier coating materials, and particularly relates to a thermal barrier coating and a preparation method and application thereof.
Background
Thermal Barrier Coatings (TBCs) are coating systems consisting of a metallic bond coat (typically composed of a nickel-based alloy such as NiAl, niCrAlY, niCoCrAlY, etc.) and a thermally insulating ceramic layer (typically composed of a low Thermal conductivity, high Thermal expansion coefficient ceramic such as zirconia, yttria Stabilized Zirconia (YSZ), zirconate, etc.).
The thermal barrier coating can greatly reduce the surface temperature of the alloy substrate due to the excellent heat insulation effect, and is widely applied toThe surface of hot end components of aircraft engines, gas turbines, and the like. At present, the most widely used thermal barrier coating material is 8YSZ (6% -8%Y) 2 O 3 Partially stabilized ZrO 2 ) As a ceramic layer and MCrAlY (M = Ni or Co or Ni + Co) as a bond coat. However, the thermal barrier coating can bear the actions of mechanical load, thermal stress, sintering, thermal shock, erosion and the like in the service process, so that cracking failure inevitably occurs, and therefore, the solution of the failure problem of the thermal barrier coating becomes the research focus in the field of the current thermal barrier coating.
In order to solve the technical problems, in the prior art, a transition layer is arranged to enable the composition between ceramic layers to be changed continuously so as to avoid failure and falling, and the expansion coefficient of the ceramic layers is adjusted so as to avoid failure and falling.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects that the elastic modulus, the fracture toughness and the like of the thermal barrier coating cannot be effectively improved in the prior art, so that the thermal barrier coating, the preparation method and the application thereof are provided.
Therefore, the invention provides the following technical scheme:
the invention provides a thermal barrier coating, which comprises a YSZ substrate layer and a YSZ surface layer,
wherein Y in the YSZ base layer 2 O 3 6-8 wt.% of Al 2 O 3 The content is 5-10 wt.%; y in the YSZ surface layer 2 O 3 Content of 10-12wt.%, al 2 O 3 The content is 5-10 wt.%;
the YSZ substrate layer and the YSZ surface layer are prepared by a discharge plasma sintering method.
Optionally, the total thickness of the YSZ base layer and the YSZ surface layer is 200-700 μm.
Optionally, the thickness of the YSZ surface layer is 100-150 μm.
Optionally, the thermal barrier coating is disposed on the surface of the base alloy through a bonding layer.
Optionally, the thickness of the bonding layer is 150-350 μm.
The composition of the bond coat is the same as conventional bond coats in the art, typically but not limited to MCrAlY, where M is Ni or Co or Ni + Co.
The invention also provides a preparation method of the thermal barrier coating, which comprises the following steps of preparing a YSZ substrate layer and a YSZ surface layer on the surface of the substrate alloy by a discharge plasma sintering method.
Optionally, the sintering temperature of the spark plasma sintering is 1200-1600 ℃, the pressure is 30-60MPa, and the sintering time is 0.5-1h.
Optionally, the method further comprises the step of preparing a bonding layer on the surface of the base alloy in advance;
the preparation method of the bonding layer is a conventional method in the field, and is typically, but not limited to, the bonding layer is prepared by a flame spraying method, a plasma spraying method or an electron beam-physical vapor deposition method and other thermal spraying processes.
Specifically, the preparation method of the thermal barrier coating can comprise the following steps:
(1) Preparing a thermal barrier coating bonding layer: the coating is prepared by adopting thermal spraying processes such as flame spraying, plasma spraying or electron beam-physical vapor deposition;
(2) Uniformly mixing a thermal barrier coating ceramic layer: weighing Al according to a certain proportion by mass fraction 2 O 3 Respectively carrying out high-energy ball milling and mixing on powder materials corresponding to a YSZ substrate layer and a YSZ surface layer by using a ball mill;
(3) Spark plasma sintering: uniformly coating the sample sprayed with the bonding layer with the YSZ substrate layer mixed powder obtained in the step (2) in a graphite mold, and uniformly coating the YSZ substrate layer mixed powder with the YSZ surface layer mixed powder obtained in the step (2); and then placing the die into a discharge plasma sintering furnace for sintering treatment, applying pressure of 30-60MPa, heating at the heating rate of 100-150 ℃/min, sintering at the temperature of 1200-1600 ℃ for 0.5-1h, and obtaining two ceramic layers of a YSZ substrate layer and a YSZ surface layer on the surface of the bonding layer after sintering.
The invention also provides an application of the thermal barrier coating or the thermal barrier coating prepared by the preparation method on the surface of a hot end component;
typically, the hot end component is a high temperature component such as a combustor liner, a transition section, a turbine or turbine blade, a shroud ring, and the like of an aircraft engine, a marine gas turbine, and a gas turbine for power generation.
The technical scheme of the invention has the following advantages:
the thermal barrier coating provided by the invention comprises a YSZ base layer and a YSZ surface layer, wherein Y in the YSZ base layer 2 O 3 The content is 6-8 wt.%, al 2 O 3 The content is 5-10 wt.%; y in the YSZ surface layer 2 O 3 Content of 10-12wt.%, al 2 O 3 The content is 5-10 wt.%. The invention is realized by aligning dispersed phase Al in a YSZ substrate layer and a YSZ surface layer 2 O 3 And a stabilizer Y 2 O 3 The content of (A) is limited, so that the Young modulus, the bending strength and the fracture toughness of the YSZ substrate layer and the YSZ surface layer can be improved; meanwhile, the structure is properly improved on the YSZ surface layer, and the ZrO is improved 2 Phase stability of (2). The thermal barrier coating has the advantages of simple production process, high efficiency, excellent and stable performance, and is suitable for large-scale application to high-temperature components such as combustion chamber flame tubes and transition sections of aeroengines, marine gas turbines and gas turbines for power generation, turbines or turbine blades, retaining rings and the like.
According to the preparation method of the thermal barrier coating, the YSZ substrate layer and the YSZ surface layer are directly prepared by the discharge plasma sintering method, so that the porosity of the coating can be effectively reduced, and the mechanical properties, especially the bonding strength, of the coating are improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural view of a thermal barrier coating provided by the present invention;
reference numerals are as follows:
1. a base alloy; 2. a tie layer; 3. a YSZ base layer; 4. YSZ skin.
Detailed Description
The following examples are provided to better understand the present invention, not to limit the best mode, and not to limit the content and protection scope of the present invention, and any product that is the same or similar to the present invention and is obtained by combining the present invention with other features of the prior art and the present invention falls within the protection scope of the present invention.
The examples do not indicate specific experimental procedures or conditions, and can be performed according to the procedures or conditions of the conventional experimental procedures described in the literature in the field. The reagents or instruments used are not indicated by manufacturers, and are all conventional reagent products which can be obtained commercially.
Example 1
The embodiment provides a thermal barrier coating, as shown in fig. 1, which includes a YSZ substrate layer 3 and a YSZ surface layer 4, and is disposed on the surface of a substrate alloy 1 through a bonding layer 2, and the specific composition and preparation method of the thermal barrier coating are as follows:
(1) The raw materials comprise:
the base alloy adopts DZ411 nickel-base superalloy, and the size of a sample is
Figure BDA0003843657530000051
Using ZrO 2 ·8Y 2 O 3 Ceramic powder (indicating Y in ceramic powder) 2 O 3 Content 8 wt.%) and ZrO 2 ·12Y 2 O 3 Ceramic powder (indicating Y in ceramic powder) 2 O 3 Content of 12 wt.%) was used as the starting material for the YSZ base layer and YSZ surface layer, using ni23co17cr12al0.5y nickel-based superalloy powder as the starting materialIs the original material of the adhesive layer.
(2) The preparation method comprises the following steps:
firstly, preparing a bonding layer by adopting supersonic flame spraying, wherein the thickness of the bonding layer is 150 microns, and the bonding layer is used after being prepared; next, a mixed powder of the YSZ base layer and the YSZ surface layer was prepared: based on the mass fraction, 92wt.% of ZrO 2 ·8Y 2 O 3 Ceramic powder and 8wt.% Al 2 O 3 The powders were mixed so that the total amount of the mixed powders was 500g and 92wt.% of ZrO was added 2 ·12Y 2 O 3 Ceramic powder with 8wt.% of Al 2 O 3 The powders were mixed so that the total amount of the mixed powder was 400g. Ball-milling the weighed 2 kinds of powder for 24 hours by using a planetary ball mill at the rotating speed of 300r/min and ethanol as a medium respectively to prepare mixed powder of a YSZ substrate layer and a YSZ surface layer which are uniformly mixed; and respectively placing the 2 uniformly mixed powder materials in a water bath at 60 ℃ for rotary evaporation to dryness, and placing in a drying oven at 120 ℃ for 24 hours for later use.
Uniformly wrapping the sample sprayed with the bonding layer by using the mixed powder of the YSZ substrate layer, and uniformly wrapping the mixed powder of the YSZ substrate layer by using the mixed powder of the YSZ surface layer; and then placing the die into a discharge plasma sintering furnace for sintering treatment, applying pressure of 60MPa, heating at the heating rate of 150 ℃/min, sintering at the temperature of 1400 ℃ for 0.5h, and obtaining two ceramic layers of a YSZ substrate layer (the thickness is about 150 mu m) and a YSZ surface layer (the thickness is about 100 mu m) on the surface of the bonding layer after sintering.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 42MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 31.2GPa, and the bending strength is 35.62MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.32 MPa.m 1/2 。
Example 2
This example provides a thermal barrier coating, differing from example 1 in that Y is the YSZ base layer 2 O 3 6wt.% of Y in the YSZ surface layer 2 O 3 In an amount of10wt.％。
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 43.1MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 30.5GPa, and the bending strength is 34.9MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.14 MPa-m 1/2 。
Example 3
This example provides a thermal barrier coating, differing from example 1 in that the YSZ substrate layer and YSZ skin layer are Al 2 O 3 The content was 10wt.%.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the ASTM C633 standard requirement, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 45MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 33.12GPa, and the bending strength is 34.5MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.54 MPa-m 1/2 。
Example 4
This example provides a thermal barrier coating, differing from example 3 in that the YSZ substrate layer and YSZ skin layer are Al 2 O 3 The content was 5wt.%.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 39MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 31.52GPa, and the bending strength is 34.72MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.27 MPa-m 1/2 。
Example 5
This example provides a thermal barrier coating, differing from example 3 in that the YSZ base layer comprises Al 2 O 3 7wt.% of Al in the YSZ surface layer 2 O 3 The content was 9wt.%.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the ASTM C633 standard requirement, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 45.3MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 33.32GPa, and the bending strength is 34.9MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.57 MPa.m 1/2 。
Example 6
This example provides a thermal barrier coating, which is different from example 1 in that a mold is placed in a spark plasma sintering furnace to be subjected to a sintering treatment, a pressure of 30MPa is applied, and the sintering treatment is carried out at a temperature of 1600 ℃ at a temperature rise rate of 150 ℃/min for 0.7h.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 40MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 31.5GPa, and the bending strength is 34.72MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.12 MPa.m 1/2 。
Example 7
This example provides a thermal barrier coating, which is different from example 1 in that a mold is placed in a spark plasma sintering furnace to be subjected to a sintering treatment, a pressure of 40MPa is applied, and the sintering treatment is performed at a temperature of 1200 ℃ at a temperature rise rate of 150 ℃/min for 1 hour.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 41MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 31.7GPa, and the bending strength is 34.61MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 2.25 MPa-m 1/2 。
Comparative example 1
This comparative example provides a thermal barrier coating, differing from example 1 in that Y is the YSZ base layer 2 O 3 Content 4wt.%, Y in YSZ surface layer 2 O 3 The content was 14wt.%.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 29MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 28.2GPa, and the bending strength is 30.15MPa; testing the fracture toughness of the thermal barrier coating material under a high-temperature environment by using a single-edge notched beam method, wherein the fracture toughness of the thermal barrier coating at 1100 ℃ is 1.82 MPa.m 1/2 。
Comparative example 2
This comparative example provides a thermal barrier coating, differing from example 1 in that the YSZ substrate layer and the YSZ skin layer are Al 2 O 3 The content was 1wt.%.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 38MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 29.3GPa, and the bending strength is 30.23MPa; testing the fracture toughness of the thermal barrier coating material under a high-temperature environment by using a single-edge notched beam method, wherein the fracture toughness of the thermal barrier coating at 1100 ℃ is 1.55 MPa.m 1/2 。
Comparative example 3
This comparative example provides a thermal barrier coating that differs from example 1 in that the bond coat is sprayed with a supersonic flame and both the YSZ substrate layer and the YSZ surface layer are sprayed with atmospheric plasma.
The tensile bonding strength of the prepared thermal barrier coating is measured according to the standard requirement of ASTM C633, and the test result shows that the bonding strength of the bonding layer and the ceramic layer is 21MPa; the elastic modulus of the thermal barrier coating at 1000 ℃ is 28.7GPa, and the bending strength is 29.83MPa; the fracture toughness of the thermal barrier coating material is tested by using a single-edge notched beam method in a high-temperature environment, and the fracture toughness of the thermal barrier coating at 1100 ℃ is 1.98 MPa.m 1/2 。
From the comparison of the data in the above examples and comparative examples, it can be seen that a small amount of dispersed phase Al is added to the YSZ substrate layer and YSZ surface layer 2 O 3 And for dispersed phase Al 2 O 3 And a stabilizer Y 2 O 3 The content of the composite is limited, and the Young modulus, the bending strength and the fracture toughness of the YSZ substrate layer and the YSZ surface layer are improved; the YSZ substrate layer and the YSZ surface layer are prepared by a discharge plasma sintering method, so that the bonding strength of the coating can be obviously improved.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the scope of the invention.

Claims (10)

1. A thermal barrier coating comprising a YSZ substrate layer and a YSZ surface layer,
wherein Y in said YSZ base layer 2 O 3 6-8 wt.% of Al 2 O 3 The content is 5-10 wt.%; y in the YSZ surface layer 2 O 3 Content of 10-12wt.%, al 2 O 3 The content is 5-10 wt.%;
the YSZ substrate layer and the YSZ surface layer are prepared by a discharge plasma sintering method.
2. The thermal barrier coating of claim 1, wherein the YSZ substrate layer and YSZ skin layer have a combined thickness of 300-700 μ ι η.
3. The thermal barrier coating of claim 2, wherein the YSZ skin has a thickness of 100-150 μ ι η.
4. The thermal barrier coating of any one of claims 1 to 3, characterized in that the thermal barrier coating is provided on the base alloy surface by a bonding layer.
5. The thermal barrier coating of claim 4, wherein the bond layer has a thickness of 150-350 μ ι η.
6. The thermal barrier coating of claim 4, wherein the bond coat is formed as MCrAlY, wherein M is Ni, co, or Ni + Co.
7. Method for the production of a thermal barrier coating according to any one of claims 1 to 6, characterized in that it comprises the following steps: and preparing a YSZ substrate layer and a YSZ surface layer on the surface of the substrate alloy by a discharge plasma sintering method.
8. The method for preparing a thermal barrier coating according to claim 7, wherein the sintering temperature of spark plasma sintering is 1200-1600 ℃, the pressure is 30-60MPa, and the sintering time is 0.5-1h.
9. The method for preparing a thermal barrier coating according to claim 7 or 8, further comprising the step of preparing a bond coat on the surface of the base alloy in advance;
optionally, the bonding layer is prepared by a flame spraying method, a plasma spraying method or an electron beam-physical vapor deposition method.
10. Use of a thermal barrier coating according to any one of claims 1 to 6 or a thermal barrier coating prepared by a method according to any one of claims 7 to 9 on the surface of a hot end component;
optionally, the hot end component is a combustor liner, a transition section, a turbine blade or a shroud ring of an aircraft engine, a marine gas turbine, or a power generation gas turbine.
CN202211112923.7A 2022-09-13 2022-09-13 Thermal barrier coating and preparation method and application thereof Active CN115449786B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211112923.7A CN115449786B (en) 2022-09-13 2022-09-13 Thermal barrier coating and preparation method and application thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211112923.7A CN115449786B (en) 2022-09-13 2022-09-13 Thermal barrier coating and preparation method and application thereof

Publications (2)

Publication Number Publication Date
CN115449786A true CN115449786A (en) 2022-12-09
CN115449786B CN115449786B (en) 2023-07-28

Family

ID=84302062

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211112923.7A Active CN115449786B (en) 2022-09-13 2022-09-13 Thermal barrier coating and preparation method and application thereof

Country Status (1)

Country Link
CN (1) CN115449786B (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6045928A (en) * 1998-02-09 2000-04-04 Pyrogenesis Inc. Thermal barrier coating system having a top coat with a graded interface
CN103556098A (en) * 2013-11-01 2014-02-05 中国科学院上海硅酸盐研究所 Trass volcanic ash erosion resistance multi-layer thermal barrier coating
CN104529498A (en) * 2014-12-17 2015-04-22 南京航空航天大学 One-step preparation method of multi-layer environmental barrier coatings through spark plasma sintering (SPS)
CN106148874A (en) * 2016-09-13 2016-11-23 中国农业机械化科学研究院 Thermal barrier coating that a kind of anti-CMAS smelt deposits corrodes and preparation method thereof
CN107254652A (en) * 2017-06-28 2017-10-17 福州大学 A kind of multilayer thermal barrier coating and preparation method thereof
CN107759218A (en) * 2017-12-11 2018-03-06 内蒙古科技大学 A kind of yttria-stabilized zirconia ceramics and preparation method thereof
CN110205626A (en) * 2019-07-03 2019-09-06 西安热工研究院有限公司 A kind of functionally gradient thermal barrier coating and preparation method thereof

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6045928A (en) * 1998-02-09 2000-04-04 Pyrogenesis Inc. Thermal barrier coating system having a top coat with a graded interface
CN103556098A (en) * 2013-11-01 2014-02-05 中国科学院上海硅酸盐研究所 Trass volcanic ash erosion resistance multi-layer thermal barrier coating
CN104529498A (en) * 2014-12-17 2015-04-22 南京航空航天大学 One-step preparation method of multi-layer environmental barrier coatings through spark plasma sintering (SPS)
CN106148874A (en) * 2016-09-13 2016-11-23 中国农业机械化科学研究院 Thermal barrier coating that a kind of anti-CMAS smelt deposits corrodes and preparation method thereof
CN107254652A (en) * 2017-06-28 2017-10-17 福州大学 A kind of multilayer thermal barrier coating and preparation method thereof
CN107759218A (en) * 2017-12-11 2018-03-06 内蒙古科技大学 A kind of yttria-stabilized zirconia ceramics and preparation method thereof
CN110205626A (en) * 2019-07-03 2019-09-06 西安热工研究院有限公司 A kind of functionally gradient thermal barrier coating and preparation method thereof

Also Published As

Publication number Publication date
CN115449786B (en) 2023-07-28

Similar Documents

Publication Publication Date Title
Gell et al. Higher temperature thermal barrier coatings with the combined use of yttrium aluminum garnet and the solution precursor plasma spray process
CN108101533B (en) Preparation method of ceramic target material for thermal barrier coating
CA2647453C (en) Thermal barrier coating member, method for producing the same, thermal barrier coating material, gas turbine, and sintered body
CN107699840A (en) The preparation method of porous zirconia thermal barrier coating
CN101768380A (en) Thermal protection coating with component gradient change and preparation method
Hu et al. High-temperature mechanical properties and oxidation resistance of SiCf/SiC ceramic matrix composites with multi-layer environmental barrier coatings for turbine applications
JP2006193828A (en) Heat-shielding coating material, heat-shielding member, heat-shielding coating member, and method for production of the heat-shielding coating member
CN113930705B (en) Long-life thermal barrier coating material and preparation process thereof, and thermal barrier coating system and preparation process thereof
EP2767525B1 (en) Ceramic powders and methods therefor
JP5074123B2 (en) High temperature wear resistant member and method for producing high temperature wear resistant member
CN111233446A (en) Hafnium silicate environmental barrier coating for ceramic matrix composite material substrate and preparation method thereof
Guo et al. Thermo-physical properties and thermal shock resistance of segmented La 2 Ce 2 O 7/YSZ thermal barrier coatings
KR20030068054A (en) Hybrid thermal barrier coating and method of making the same
Chen et al. Microstructure and thermal cycling behavior of air plasma-sprayed YSZ/LaMgAl 11 O 19 composite coatings
EP2778250A2 (en) Coating systems and methods therefor
CN112176275B (en) Thermal barrier coating and preparation method and application thereof
Zhu et al. A comparison between novel Gd 2 Zr 2 O 7 and Gd 2 Zr 2 O 7/YSZ thermal barrier coatings fabricated by plasma spray-physical vapor deposition
Avci et al. Microstructure and oxidation behavior of atmospheric plasma-sprayed thermal barrier coatings
Feng et al. Thermophysical properties of solution precursor plasma-sprayed La 2 Ce 2 O 7 thermal barrier coatings
Hu et al. Oxidation resistance of SiCf/SiC composites with three-layer environmental barrier coatings up to 1360° C in air atmosphere
Dhineshkumar et al. Enhanced ablation resistance through laser glazing of plasma sprayed LaTi2Al9O19-based functionally graded thermal barrier coating
Suzuki et al. The current status of environmental barrier coatings and future direction of thermal spray process
Huang et al. Effects of critical plasma spraying parameters on microstructure and mechanical properties of LaPO4-8YSZ thick composite coatings
CN115449786A (en) Thermal barrier coating and preparation method and application thereof
Wang et al. Segmented lanthanum cerium oxide thermal barrier coatings by atmospheric plasma spray

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant