CN115449786B - Thermal barrier coating and preparation method and application thereof - Google Patents
Thermal barrier coating and preparation method and application thereof Download PDFInfo
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- 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
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- 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
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- 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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- 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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- 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
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- 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
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- 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
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- 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
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- 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
Abstract
The invention belongs to the technical field of thermal barrier coating materials, and particularly relates to a thermal barrier coating, a preparation method and application thereof. The thermal barrier coating comprises a YSZ substrate layer and a YSZ surface layer, wherein Y in the YSZ substrate layer 2 O 3 The content is 6 to 8 weight percent of Al 2 O 3 The content is 5 to 10wt.%; y in the YSZ surface layer 2 O 3 The content of Al is 10-12wt.% 2 O 3 The content is 5-10 wt.%. The invention is characterized in that the dispersed phase Al is arranged in the YSZ basal layer and the YSZ surface layer 2 O 3 And stabilizer Y 2 O 3 The content of (2) 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 (c). The thermal barrier coating has the advantages of simple production process, high efficiency, excellent and stable performance, and is suitable for being applied to high-temperature parts such as combustion chamber flame tubes, transition sections, turbines or turbine blades, guard rings and the like of aeroengines, marine gas turbines and power generation gas turbines in a large scale.
Description
Technical Field
The invention belongs to the technical field of thermal barrier coating materials, and particularly relates to a thermal barrier coating, a preparation method and application thereof.
Background
Thermal barrier coatings (Thermal Barrier Coatings, TBCs for short) are coating systems composed of a metallic bond coat (typically composed of nickel-based alloys such as NiAl, niCrAlY, niCoCrAlY, etc.) and a thermally insulating ceramic layer (typically composed of a low thermal conductivity, high coefficient of thermal expansion ceramic such as zirconia, yttria Stabilized Zirconia (YSZ), zirconate, etc.).
The thermal barrier coating can greatly reduce the surface temperature of the alloy matrix due to the excellent heat insulation effect, and is widely applied to the surfaces of hot end components such as aeroengines, gas turbines and the like. At present, the most widely applied thermal barrier coating material is 8YSZ (6% -8%Y) 2 O 3 Partially stabilized ZrO 2 ) As ceramic layers and MCrAlY (m=ni or Co or ni+co) as bonding layers. 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 the thermal barrier coating inevitably cracks and fails, and therefore, the problem of failure of the thermal barrier coating is the focus of research in the current thermal barrier coating field.
In order to solve the technical problems, the prior art has the advantages that the composition between the ceramic layers is continuously changed through the arrangement of the transition layers to avoid failure and falling off, and the expansion coefficient of the ceramic layers is adjusted to avoid failure and falling off, but the method cannot effectively improve the elastic modulus and fracture toughness of the thermal barrier coating, and researches show that the peeling failure of the thermal barrier coating involves a plurality of factors, wherein a plurality of factors have a great relation with the elastic modulus of the coating, and the fracture toughness can quantitatively represent the capability of the coating for inhibiting crack propagation.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the elastic modulus, fracture toughness and the like of the thermal barrier coating cannot be effectively improved in the prior art, so as to provide the thermal barrier coating and the preparation method and application thereof.
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 substrate layer 2 O 3 The content is 6 to 8 weight percent of Al 2 O 3 The content is 5 to 10wt.%; y in the YSZ surface layer 2 O 3 The content of Al is 10-12wt.% 2 O 3 The content is 5 to 10wt.%;
the YSZ substrate layer and the YSZ surface layer are prepared by a spark plasma sintering method.
Optionally, the YSZ base layer and YSZ skin layer have a total thickness of 200-700 μm.
Optionally, the YSZ skin layer has a thickness of 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 adhesive 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 the YSZ substrate layer and the YSZ surface layer on the surface of the substrate alloy by a spark 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 substrate 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 adopting a thermal spraying process such as a flame spraying method, a plasma spraying method or an electron beam-physical vapor deposition method.
Specifically, the preparation method of the thermal barrier coating can comprise the following steps:
(1) Preparing a thermal barrier coating bonding layer: the preparation method comprises the steps of adopting thermal spraying processes such as flame spraying or plasma spraying or electron beam-physical vapor deposition;
(2) And (3) uniformly mixing the thermal barrier coating ceramic layers: weighing Al according to a certain proportion by mass fraction 2 O 3 The powder and YSZ powder are subjected to high-energy ball milling and mixing respectively by utilizing a ball mill;
(3) Discharge plasma sintering: uniformly wrapping the sample sprayed with the bonding layer by using the YSZ substrate layer mixed powder obtained in the step (2) in a graphite mold, and uniformly wrapping the YSZ substrate layer mixed powder by using the YSZ surface layer mixed powder obtained in the step (2); then placing the die into a discharge plasma sintering furnace for sintering treatment, applying pressure of 30-60MPa, heating up at a heating rate of 100-150 ℃/min, sintering at a temperature of 1200-1600 ℃ for 0.5-1h, and obtaining a YSZ substrate layer and a YSZ surface layer two-layer ceramic 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 the hot end component;
typically, but not limited to, the hot end components are high temperature components such as aeroengines, marine gas turbines, combustor cans of gas turbines for power generation, transition sections, turbines or turbine blades, shroud rings, and the like.
The technical scheme of the invention has the following advantages:
the thermal barrier coating provided by the invention comprises a YSZ substrate layer and a YSZ surface layer, wherein Y in the YSZ substrate layer 2 O 3 The content is 6 to 8 weight percent of Al 2 O 3 The content is 5 to 10wt.%; y in the YSZ surface layer 2 O 3 The content of Al is 10-12wt.% 2 O 3 The content is 5-10 wt.%. The invention is characterized in that the dispersed phase Al is arranged in the YSZ basal layer and the YSZ surface layer 2 O 3 And stabilizer Y 2 O 3 The content of (2) 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 (c). The thermal barrier coating has the advantages of simple production process, high efficiency, excellent and stable performance, and is suitable for being applied to high-temperature parts such as combustion chamber flame tubes, transition sections, turbines or turbine blades, guard rings and the like of aeroengines, marine gas turbines and power generation gas turbines in a large scale.
According to the preparation method of the thermal barrier coating, the YSZ substrate layer and the YSZ surface layer are directly prepared by the spark plasma sintering method, so that the porosity of the coating can be effectively reduced, and the mechanical properties of the coating, particularly the bonding strength, can be improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural view of a thermal barrier coating provided by the present invention;
reference numerals:
1. a base alloy; 2. a bonding layer; 3. a YSZ substrate layer; 4. YSZ skin.
Detailed Description
The following examples are provided for a better understanding of the present invention and are not limited to the preferred embodiments described herein, but are not intended to limit the scope of the invention, any product which is the same or similar to the present invention, whether in light of the present teachings or in combination with other prior art features, falls within the scope of the present invention.
The specific experimental procedures or conditions are not noted in the examples and may be followed by the operations or conditions of conventional experimental procedures described in the literature in this field. The reagents or apparatus used were conventional reagent products commercially available without the manufacturer's knowledge.
Example 1
The embodiment provides a thermal barrier coating, as shown in fig. 1, which comprises a YSZ substrate layer 3 and a YSZ surface layer 4, wherein the thermal barrier coating is arranged on the surface of a substrate alloy 1 through a bonding layer 2, and the specific composition and the preparation method of the thermal barrier coating are as follows:
(1) The raw materials comprise:
the matrix alloy adopts DZ411 nickel-based superalloy, and the sample size is thatBy ZrO 2 ·8Y 2 O 3 Ceramic powder (Y in the ceramic powder) 2 O 3 Content of 8 wt.%) and ZrO 2 ·12Y 2 O 3 Ceramic powder (Y in the ceramic powder) 2 O 3 Content of 12 wt.%) was used as the starting material for the YSZ base layer and YSZ surface layer, and the nickel-base superalloy powder of ni23co17cr12al0.5y was used as the starting material for 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 mu m, and the bonding layer is ready for use after the preparation; next, a mixed powder of YSZ base layer and YSZ surface layer was prepared: 92wt.% ZrO 2 ·8Y 2 O 3 Ceramic powder and 8wt.% Al 2 O 3 Powder was mixed to give a total of 500g of mixed powder, 92wt.% ZrO 2 ·12Y 2 O 3 Ceramic powder with 8wt.% Al 2 O 3 The powder was mixed and the total of the mixed powder was 400g. Respectively ball-milling the 2 weighed powder materials with ethanol as a medium at a rotating speed of 300r/min by using a planetary ball mill for 24 hours to prepare mixed powder materials of a YSZ substrate layer and a YSZ surface layer which are uniformly mixed; and respectively placing the 2 evenly mixed powder materials in a water bath at 60 ℃ for rotary evaporation, and placing in a baking 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; then placing the die into a discharge plasma sintering furnace for sintering treatment, applying pressure of 60MPa, heating at a heating rate of 150 ℃/min, sintering at 1400 ℃ for 0.5h, and obtaining a YSZ basal layer (thickness of about 150 μm) and a YSZ surface layer (thickness of about 100 μm) ceramic layer on the surface of the bonding layer after sintering.
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 42MPa; the elastic modulus of the thermal barrier coating is 31.2GPa at 1000 ℃ and the bending strength is 35.62MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.32MPa m at 1100 DEG C 1/2 。
Example 2
This embodiment provides a thermal barrier coating differing from embodiment 1 in that Y in the YSZ substrate layer 2 O 3 The content was 6wt.%, Y in the YSZ skin layer 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 adhesive layer and the ceramic layer is 43.1MPa; the elastic modulus of the thermal barrier coating is 30.5GPa at 1000 ℃ and the bending strength is 34.9MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.14MPa m at 1100 DEG C 1/2 。
Example 3
This example provides a thermal barrier coating differing from example 1 in that the YSZ substrate layer and YSZ surface 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; elastic modulus of thermal barrier coating at 1000 DEG C33.12GPa and 34.5MPa of bending strength; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.54 MPa.m at 1100 DEG C 1/2 。
Example 4
This example provides a thermal barrier coating differing from example 3 in that the YSZ substrate layer and YSZ surface layers are Al 2 O 3 The content was 5wt.%.
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 39MPa; the elastic modulus of the thermal barrier coating is 31.52GPa and the bending strength is 34.72MPa at 1000 ℃; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.27 MPa.m at 1100 DEG C 1/2 。
Example 5
This embodiment provides a thermal barrier coating, which differs from embodiment 3 in that the YSZ substrate layer contains Al 2 O 3 The content was 7wt.%, of Al in the YSZ skin 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 is 33.32GPa at 1000 ℃ and the bending strength is 34.9MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.57 MPa.m at 1100 DEG C 1/2 。
Example 6
This example provides a thermal barrier coating, which differs from example 1 in that the mold is placed in a spark plasma sintering furnace for sintering treatment, a pressure of 30MPa is applied, and the sintering treatment is performed at a temperature of 1600 ℃ for 0.7h at a heating rate of 150 ℃/min.
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 40MPa;the elastic modulus of the thermal barrier coating is 31.5GPa at 1000 ℃ and the bending strength is 34.72MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.12MPa m at 1100 DEG C 1/2 。
Example 7
This example provides a thermal barrier coating, which differs from example 1 in that the mold is placed in a spark plasma sintering furnace for sintering treatment, a pressure of 40MPa is applied, and the sintering treatment is performed at a temperature of 1200 ℃ for 1h at a heating rate of 150 ℃/min.
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 41MPa; the elastic modulus of the thermal barrier coating is 31.7GPa at 1000 ℃ and the bending strength is 34.61MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 2.25MPa m at 1100 DEG C 1/2 。
Comparative example 1
This comparative example provides a thermal barrier coating differing from example 1 in that Y in the YSZ substrate layer 2 O 3 The content of Y in YSZ surface layer was 4wt.% 2 O 3 The content was 14wt.%.
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 29MPa; the elastic modulus of the thermal barrier coating is 28.2GPa and the bending strength is 30.15MPa at 1000 ℃; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 1.82MPa m at 1100 DEG C 1/2 。
Comparative example 2
This comparative example provides a thermal barrier coating that differs from example 1 in that the YSZ substrate layer and the YSZ surface layer are Al 2 O 3 The content was 1wt.%.
The prepared thermal barrier coating is subjected to tensile bonding strength measurement according to ASTM C633 standard requirements, and the test result shows that the bonding layer and the ceramic areThe bonding strength of the porcelain layer is 38MPa; the elastic modulus of the thermal barrier coating is 29.3GPa at 1000 ℃ and the bending strength is 30.23MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 1.55 MPa.m at 1100 DEG C 1/2 。
Comparative example 3
This comparative example provides a thermal barrier coating, which differs from example 1 in that the bond coat is spray coated with a supersonic flame, and in that both the YSZ substrate layer and YSZ skin layer are spray coated with atmospheric plasma.
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 21MPa; the elastic modulus of the thermal barrier coating is 28.7GPa at 1000 ℃ and the bending strength is 29.83MPa; the fracture toughness of the thermal barrier coating material is tested under the high-temperature environment by using a single-side notched beam method, and the fracture toughness of the thermal barrier coating is 1.98MPa m at 1100 DEG C 1/2 。
As can be seen from the comparison of the data of the above examples and comparative examples, a small amount of dispersed phase Al was added to the YSZ base layer and the YSZ surface layer 2 O 3 And for dispersed phase Al 2 O 3 And stabilizer Y 2 O 3 The content of (2) is limited, and the Young modulus, the bending strength and the fracture toughness of the YSZ basal layer and the YSZ surface layer are improved; the YSZ substrate layer and the surface layer are prepared by a spark plasma sintering method, so that the bonding strength of the coating can be remarkably improved.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present invention.
Claims (9)
1. A thermal barrier coating is characterized by comprising a YSZ substrate layer and a YSZ surface layer,
wherein the YSZ substrateY in layer 2 O 3 The content is 6 to 8 weight percent of Al 2 O 3 The content is 5 to 10wt.%; y in the YSZ surface layer 2 O 3 The content of Al is 10-12wt.% 2 O 3 The content is 5 to 10wt.%;
the YSZ substrate layer and the YSZ surface layer are prepared by a spark plasma sintering method;
the total thickness of the YSZ basal layer and the YSZ surface layer is 300-700 mu m;
the thickness of the YSZ surface layer is 100-150 mu m;
the sintering temperature of the spark plasma sintering is 1200-1600 ℃, the pressure is 30-60MPa, and the sintering time is 0.5-1h.
2. The thermal barrier coating of claim 1, wherein the thermal barrier coating is disposed on the surface of the base alloy by a bond coat.
3. The thermal barrier coating of claim 2, wherein the bond coat has a thickness of 150-350 μιη.
4. The thermal barrier coating of claim 2, wherein the bond coat layer comprises MCrAlY, where M is Ni, co, or ni+co.
5. A method of producing a thermal barrier coating as claimed in any one of claims 1 to 4, comprising the steps of: and preparing a YSZ substrate layer and a YSZ surface layer on the surface of the substrate alloy by a spark plasma sintering method.
6. The method of preparing a thermal barrier coating of claim 5, further comprising the step of pre-preparing a bond coat on the surface of the substrate alloy.
7. The method of claim 6, wherein the bond coat is prepared by flame spraying, plasma spraying, or electron beam-physical vapor deposition.
8. Use of a thermal barrier coating according to any one of claims 1-4 or a thermal barrier coating prepared by a method according to any one of claims 5-7 on the surface of a hot end component.
9. Use according to claim 8, characterized in that the hot end component is an aeroengine, a marine gas turbine, a combustor basket, a transition piece, a turbine blade or a shroud of a gas turbine for power generation.
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