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Preparation method of thermal barrier coating, thermal barrier coating and turbine rotor blade

A technology of thermal barrier coating and spraying method, applied in the direction of coating, superimposed layer plating, blade supporting element, etc., can solve the problem of low deposition rate of EB-PVD coating, unfavorable for preparing thick thermal barrier coating, Not suitable for industrial production and other problems, to achieve the effect of good anti-CMAS corrosion performance and aerodynamic performance, good bonding strength and anti-peeling ability, and improving anti-peeling ability

Active Publication Date: 2022-03-18
BEIHANG UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

However, EB-PVD equipment is more complex and costly than APS equipment, and the deposition rate of EB-PVD coating is relatively low, resulting in the cost of EB-PVD coating being much higher than that of APS, and it is not conducive to the preparation of thickness greater than 200μm. Thermal barrier coating, so it is not suitable for industrial production

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  • Preparation method of thermal barrier coating, thermal barrier coating and turbine rotor blade
  • Preparation method of thermal barrier coating, thermal barrier coating and turbine rotor blade

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preparation example Construction

[0054] An embodiment of the present invention provides a preparation method of a thermal barrier coating, the preparation method comprising the following steps S10 to S60:

[0055] see figure 1 , Step S10: preparing a metal bonding layer 2 on the surface of the substrate 1 .

[0056] The surface of the substrate 1 is first pretreated to clean the surface of the substrate 1 , and then a layer of metal bonding layer 2 is prepared on the surface of the substrate 1 . The material of the metal bonding layer 2 can be PtAl, modified PtAl, NiCoCrAlY or NiCoCrAlYX. Wherein, X is one or more of Hf, Ta, Si, Re.

[0057] Specifically, when the material of the metal bonding layer 2 is PtAl or modified PtAl, a PtAl bonding layer or a modified PtAl bonding layer is prepared on the surface of the substrate 1 by electroplating or vapor phase infiltration; when the metal bonding layer When the material of 2 is NiCoCrAlY or NiCoCrAlYX, a NiCoCrAlY bonding layer or a NiCoCrAlYX bonding layer i...

Embodiment 1

[0092] see figure 1, a method for preparing a low-cost, high-performance thermal barrier coating on the surface of a turbine rotor blade. A dense equiaxed grain structure coating prepared by PS-PVD is selected as a ceramic bonding layer 3 with high bonding strength. The specific steps are as follows:

[0093] The first step: the substrate 1 is prepared, and the substrate 1 is pretreated to clean the surface of the substrate 1;

[0094] The second step: preparing a PtAl bonding layer on the substrate 1 as the metal bonding layer 2, the PtAl bonding layer is prepared by electroplating and vapor phase infiltration;

[0095] Step 3: Carry out magnetic polishing on the metal bonding layer 2, and then use absolute ethanol or acetone cleaning agent to perform ultrasonic cleaning;

[0096] The fourth step: on the surface of the PtAl metal bonding layer 2 treated in the third step, PS-PVD is used to prepare a high bonding strength YSZ ceramic bonding layer 3 with a dense equiaxed crys...

Embodiment 2

[0106] see figure 2 , a method for preparing a low-cost, high-performance thermal barrier coating on the surface of a turbine rotor blade. A dense and fine columnar crystal structure coating prepared by PS-PVD is selected as a high bonding strength ceramic bonding layer 3. The ceramic main layer adopts a two-layer structure. The specific steps are as follows:

[0107] The first step: the substrate 1 is prepared and the substrate 1 is pretreated, so that the surface of the substrate 1 is cleaned;

[0108] The second step: preparing a NiCoCrAlY bonding layer on the substrate 1 as a metal bonding layer 2, and the metal bonding layer 2 is prepared by a low-pressure plasma spraying method;

[0109] Step 3: Carry out magnetic polishing on the metal bonding layer 2, and then use absolute ethanol or acetone cleaning agent to perform ultrasonic cleaning;

[0110] The fourth step: the surface of the NiCoCrAlY metal bonding layer 2 treated in the third step adopts PS-PVD to prepare a ...

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Abstract

The invention provides a preparation method of a thermal barrier coating, a thermal barrier coating and a turbine rotor blade. The preparation method comprises the following steps: preparing a metal bonding layer on a substrate; adopting a plasma physical vapor deposition method to detach from the metal bonding layer A ceramic bonding layer is prepared on the surface of the substrate, and the ceramic bonding layer has a dense equiaxed crystal structure or a dense columnar crystal structure; the first ceramic main body layer is prepared on the surface of the ceramic bonding layer away from the metal bonding layer by an atmospheric plasma spraying method; The plasma physical vapor deposition method prepares a ceramic surface layer on the surface of the first ceramic main body layer away from the ceramic bonding layer, and the density of the ceramic surface layer is greater than that of the first ceramic main body layer. The preparation method of the thermal barrier coating has low production cost, and can obtain the thermal barrier coating with high bonding strength, good peeling resistance, long thermal cycle life, CMAS corrosion resistance and good aerodynamic performance.

Description

technical field [0001] The invention relates to the technical field of preparation of thermal barrier coatings, in particular to a preparation method of thermal barrier coatings, thermal barrier coatings and turbine rotor blades. Background technique [0002] The high-pressure turbine rotor blade is the core component with the most demanding temperature and load bearing in the engine, and it is also a key shortcoming restricting the development of the engine. Superalloys are currently the only feasible structural materials for high-pressure turbine blades. Among them, the temperature-bearing capacity of the most advanced single-crystal alloys is about 1150 °C, which is close to the temperature-bearing limit of superalloys. Even with advanced film cooling technology, the gas temperature reaching the surface of the blade alloy is still higher than the temperature limit of the blade alloy. Therefore, it is internationally recognized that thermal barrier coatings (TBCs) are the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C14/02C23C28/00F01D5/28C23C4/11C23C4/134
CPCC23C14/025C23C4/11C23C4/134C23C28/32C23C28/3455F01D5/282F01D5/284
Inventor 郭洪波高丽华魏亮亮彭徽何健
Owner BEIHANG UNIV