Preparation method of thermal barrier coating of lanthanum zirconate fiber doped lanthanum zirconate

A technology of thermal barrier coating and lanthanum zirconate, which is applied in the field of thermal barrier coating preparation, can solve the problems of easy failure and poor erosion resistance of lanthanum zirconate thermal barrier coating, and achieve good repeatability and interface wetting. Good wettability and low production cost

Active Publication Date: 2016-04-13
HARBIN ENG UNIV
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Problems solved by technology

[0005] The invention aims to solve the technical problem that the new lanthanum zirconate thermal barrier coating has poor erosion resistance, and the lanthanum zirconate thermal barrier coating is prone to failure under the impact of foreign particles, and provides a lanthanum zirconate fiber doped with zirconate Preparation method of thermal barrier coating of lanthanum

Method used

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  • Preparation method of thermal barrier coating of lanthanum zirconate fiber doped lanthanum zirconate
  • Preparation method of thermal barrier coating of lanthanum zirconate fiber doped lanthanum zirconate

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specific Embodiment approach 1

[0023] Embodiment 1: In this embodiment, a method for preparing a thermal barrier coating of lanthanum zirconate fiber doped with lanthanum zirconate is carried out according to the following steps:

[0024] 1. Dry the adhesive layer material with a particle size of 20 μm to 120 μm at a temperature of 80°C to 110°C for 2h to 5h to obtain the adhesive layer spray material;

[0025] 2. Grind the superalloy substrate with sandpaper until the surface roughness is below 0.1 μm;

[0026] 3. Put the superalloy substrate treated in step 2 into acetone for ultrasonic degreasing treatment, and then dry it for 10 minutes at a temperature of 50-80°C;

[0027] 4. Sand blast the superalloy substrate treated in step 3, and spray a layer of SiO on the surface 2 , to obtain a matrix with a rough surface;

[0028] 5. Spraying a layer of bonding layer spray material obtained in step 1 on the surface of the substrate treated in step 4 by high-speed flame spraying to obtain a bonding layer with ...

specific Embodiment approach 2

[0032] Embodiment 2: This embodiment is different from Embodiment 1 in that: the material of the bonding layer in step 1 is NiAl or NiCoCrAlY. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0033] Embodiment 3: This embodiment differs from Embodiment 1 or Embodiment 2 in that the superalloy substrate in step 2 is a nickel-based superalloy or a nickel-based single crystal superalloy. Others are the same as in the first or second embodiment.

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Abstract

The invention discloses a preparation method of a thermal barrier coating of lanthanum zirconate fiber doped lanthanum zirconate, and relates to a preparation method of a thermal barrier coating. The technical problems that a novel lanthanum zirconate thermal carrier coating is poor in erosive wear resistance and is likely to lose efficacy when impacted by external particles are solved. The preparation method comprises the steps that a composite lanthanum zirconate ceramic layer spraying powder material is prepared; a bonding layer spraying material is sprayed to the surface of preprocessed matrix metal; a layer of composite lanthanum zirconate ceramic layer spraying material is sprayed to a bonding layer. Compared with a traditional thermal barrier coating which is not reinforced by fiber, the erosive wear resistance of the thermal barrier coating system is higher. The preparation method is applied to the field of composite materials.

Description

technical field [0001] The invention relates to a method for preparing a thermal barrier coating. Background technique [0002] Due to its small size and high efficiency, gas turbines are widely used in various national production fields such as aerospace, power generation, and oil transportation. With the development of science and technology, the requirements for the power and efficiency of gas turbines in aerospace are gradually increasing. Higher power and efficiency means higher gas turbine inlet temperature, which will pose greater challenges to traditional materials. The turbine blades in gas turbines are made of nickel-based superalloys. Since the physical properties of superalloys are not strong enough to withstand long-term work in high-temperature environments, it is necessary to prepare a layer of ceramic thermal barrier coating on the superalloys to protect them. Normal operation at high temperature. The thermal barrier coating is composed of a superalloy subs...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/11C23C4/073C23C4/08C23C4/129C23C4/134C23C4/02
CPCC23C4/02C23C4/08Y02T50/60
Inventor 崔秀芳高宗鸿金国范阳董美伶卢冰文
Owner HARBIN ENG UNIV
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