Thermal barrier coating material and preparation method and application thereof

Abstract

The invention discloses a thermal barrier coating material and a preparation method and application thereof, and relates to the technical field of thermal barrier coatings. A thermal barrier coating comprises an alloy matrix, a bonding layer, a ceramic transition layer and a ceramic surface layer which are sequentially arranged, the porosity of the ceramic transition layer is 1-8%, and the ceramic surface layer comprises a coating matrix with multiple microcracks and porous ceramic particles embedded in the coating matrix. The transverse deformation compliance of the thermal barrier coating can be improved by forming microcracks in the ceramic surface layer, and the strain tolerance of the coating is improved; and the porous ceramic particles strengthen the heat insulation capacity of the thermal barrier coating and absorb deformation energy, and the stress borne by the thermal barrier coating in the service process is reduced. Therefore, the thermal barrier coating provided by the invention can give full play to the advantages of high strain tolerance and high interface cracking resistance, and the thermal cycle life of the coating is remarkably prolonged.

Description

technical field

[0001] The invention relates to the technical field of thermal barrier coatings, in particular to a thermal barrier coating material, its preparation method and application. Background technique

[0002] Thermal barrier coatings are widely used in hot-end parts of gas turbines and aero-engines. Using the characteristics of ceramic heat insulation and corrosion resistance to protect metal materials can not only improve the fuel efficiency of the engine, but also greatly extend the service life of the engine. At present, thermal barrier coatings have been successfully applied to the thermal protection of combustors, blades, exhaust nozzles and other hot-end components, and have become a key element in the design of advanced gas turbines, and are widely used in various modern in the gas turbine. The practical application of multiple generations of engines has proved that thermal barrier coating technology is the most effective way to protect engine components f...

Examples

preparation example Construction

[0033] An embodiment of the present invention also provides a method for preparing a thermal barrier coating material, which is used to prepare the above thermal barrier coating structure, including: depositing a bonding layer 120 on the alloy substrate 110, and depositing a ceramic transition layer on the bonding layer 120 130 , forming a ceramic surface layer 140 on the ceramic transition layer 130 .

[0034] Wherein, the preparation process of the adhesive layer 120 belongs to the prior art, and will not be described in detail here.

[0035] In some embodiments, the ceramic transition layer 130 is deposited by plasma spraying, and the spraying power is 40-100 kW, so that the ceramic powder can be deposited in a completely molten state to form a dense coating. In actual operation, it is necessary to preheat the sample to be sprayed to 400-700°C before deposition.

[0036] Further, the particle size of the ceramic powder used in the ceramic transition layer 130 is 15-45 μm, an...

Embodiment 1

[0048] This embodiment provides a method for preparing a thermal barrier coating material, which is formed as figure 1 The thermal barrier coating structure shown in , specifically includes the following steps:

[0049] (1) The alloy matrix 110 is made of a cobalt-based superalloy whose material is GH5188, with a thickness of 6mm.

[0050] (2) Depositing the bonding layer 120 on the alloy substrate 110: the bonding layer 120 is formed on the alloy substrate 110 by using NiCrAlY material by plasma surface spraying, and the thickness is controlled to be 120 μm.

[0051] (3) Deposit the ceramic transition layer 130 on the adhesive layer 120: first preheat the sample to be sprayed to about 500° C., use a fused and crushed yttria-stabilized zirconia powder with a particle size of 10-45 μm, and use high-power The deposition is realized in the form of complete melting under the plasma spraying state, the spraying power is controlled to 45 kW, and the thickness of the ceramic transit...

Embodiment 2

[0054] This embodiment provides a method for preparing a thermal barrier coating material, which is formed as figure 1 The thermal barrier coating structure shown in , specifically includes the following steps:

[0055] (1) The alloy matrix 110 is made of a cobalt-based superalloy whose material is GH5188, with a thickness of 6mm.

[0056] (2) Depositing the bonding layer 120 on the alloy substrate 110: the bonding layer 120 is formed on the alloy substrate 110 by using NiCrAlY material by plasma surface spraying, and the thickness is controlled to be 120 μm.

[0057] (3) Deposit the ceramic transition layer 130 on the adhesive layer 120: first preheat the sample to be sprayed to about 500° C., use a fused and crushed yttria-stabilized zirconia powder with a particle size of 10-45 μm, and use high-power The deposition is realized in a completely molten form under the plasma spraying state, the spraying power is controlled to 45kW, and the thickness of the ceramic transition l...

technical field

[0001] The invention relates to the technical field of thermal barrier coatings, in particular to a thermal barrier coating material, its preparation method and application. Background technique

[0002] Thermal barrier coatings are widely used in hot-end parts of gas turbines and aero-engines. Using the characteristics of ceramic heat insulation and corrosion resistance to protect metal materials can not only improve the fuel efficiency of the engine, but also greatly extend the service life of the engine. At present, thermal barrier coatings have been successfully applied to the thermal protection of combustors, blades, exhaust nozzles and other hot-end components, and have become a key element in the design of advanced gas turbines, and are widely used in various modern in the gas turbine. The practical application of multiple generations of engines has proved that thermal barrier coating technology is the most effective way to protect engine components f...

Examples

preparation example Construction

[0033] An embodiment of the present invention also provides a method for preparing a thermal barrier coating material, which is used to prepare the above thermal barrier coating structure, including: depositing a bonding layer 120 on the alloy substrate 110, and depositing a ceramic transition layer on the bonding layer 120 130 , forming a ceramic surface layer 140 on the ceramic transition layer 130 .

[0034] Wherein, the preparation process of the adhesive layer 120 belongs to the prior art, and will not be described in detail here.

[0035] In some embodiments, the ceramic transition layer 130 is deposited by plasma spraying, and the spraying power is 40-100 kW, so that the ceramic powder can be deposited in a completely molten state to form a dense coating. In actual operation, it is necessary to preheat the sample to be sprayed to 400-700°C before deposition.

[0036] Further, the particle size of the ceramic powder used in the ceramic transition layer 130 is 15-45 μm, an...

Embodiment 1

[0048] This embodiment provides a method for preparing a thermal barrier coating material, which is formed as figure 1 The thermal barrier coating structure shown in , specifically includes the following steps:

[0049] (1) The alloy matrix 110 is made of a cobalt-based superalloy whose material is GH5188, with a thickness of 6mm.

[0050] (2) Depositing the bonding layer 120 on the alloy substrate 110: the bonding layer 120 is formed on the alloy substrate 110 by using NiCrAlY material by plasma surface spraying, and the thickness is controlled to be 120 μm.

[0051] (3) Deposit the ceramic transition layer 130 on the adhesive layer 120: first preheat the sample to be sprayed to about 500° C., use a fused and crushed yttria-stabilized zirconia powder with a particle size of 10-45 μm, and use high-power The deposition is realized in the form of complete melting under the plasma spraying state, the spraying power is controlled to 45 kW, and the thickness of the ceramic transit...

Embodiment 2

[0054] This embodiment provides a method for preparing a thermal barrier coating material, which is formed as figure 1 The thermal barrier coating structure shown in , specifically includes the following steps:

[0055] (1) The alloy matrix 110 is made of a cobalt-based superalloy whose material is GH5188, with a thickness of 6mm.

[0056] (2) Depositing the bonding layer 120 on the alloy substrate 110: the bonding layer 120 is formed on the alloy substrate 110 by using NiCrAlY material by plasma surface spraying, and the thickness is controlled to be 120 μm.

[0057] (3) Deposit the ceramic transition layer 130 on the adhesive layer 120: first preheat the sample to be sprayed to about 500° C., use a fused and crushed yttria-stabilized zirconia powder with a particle size of 10-45 μm, and use high-power The deposition is realized in a completely molten form under the plasma spraying state, the spraying power is controlled to 45kW, and the thickness of the ceramic transition l...

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