Sintering-resistant long-service-life thermal barrier coating of double-layer structure and preparation method of thermal barrier coating

A technology of thermal barrier coating and double-layer structure, which is applied in coating, metal material coating process, pressure inorganic powder coating, etc., can solve the problems of reducing the heat insulation function of TBCs, achieve rapid engineering application, improve Anti-flaking ability, the effect of enhancing anti-flaking ability

Inactive Publication Date: 2019-04-26
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
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  • Application Information

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Problems solved by technology

As far as its functionality is concerned, TBCs will undergo obvious sintering during long-term heat exposure, which will heal a large nu

Method used

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  • Sintering-resistant long-service-life thermal barrier coating of double-layer structure and preparation method of thermal barrier coating
  • Sintering-resistant long-service-life thermal barrier coating of double-layer structure and preparation method of thermal barrier coating

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preparation example Construction

[0030] see figure 1 As shown, the present invention provides a method for preparing an anti-sintering long-life double-layer structure thermal barrier coating, comprising the following steps:

[0031] Step 1. Prepare a metal bonding layer 2 with a thickness of 150 μm on the surface of the cylindrical superalloy substrate 1 by using a low-pressure plasma spraying process.

[0032] Step 2. On the metal bonding layer 2, 8YSZ smelting and crushing powder with a particle size of 5 μm to 25 μm is used to prepare a toughening layer 3 with a thickness of 150 μm by atmospheric plasma spraying. In the process of spraying, in order to make the interlayer bonding rate of the first sheet unit 5 not lower than 50%, use a heating platform to preheat the substrate to 400°C before spraying; The size of the first sheet is 5 μm to 40 μm, and the size along the direction of heat flow is 0.5 to 5 μm. There are first interlayer micropores 81 between the two adjacent layers of the first sheet unit ...

Embodiment 2

[0040] The difference between this embodiment and embodiment 1 is that in step 1, the thermal spraying method used is vacuum plasma spraying, supersonic flame spraying or cold spraying.

Embodiment 3

[0042] The difference between this embodiment and embodiment 2 is that in step 1, the thickness of the metal bonding layer 2 is 100 μm; in step 2, the temperature of the substrate is preheated to 300° C. during the deposition; During the process, the substrate temperature is controlled to not exceed 180°C.

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Abstract

The invention discloses an sintering-resistant long-service-life thermal barrier coating of a double-layer structure and a preparation process of the thermal barrier coating. The thermal barrier coating comprises a toughening layer located inside and a heat insulating layer located outside. The heat insulating layer is formed by composite stacking of dense sheet layer units and loose nano-particlepiles, the thickness of the toughening layer accounts for 10%-50% of the total thickness of the thermal barrier coating of the double-layer structure, and the fracture toughness of a first thermal barrier coating material is larger than or equal to 2.5 MPa.m1/2. The thickness of the heat insulating layer accounts for 50%-90% of the total thickness of the double layers, and the heat conductivity of a second thermal barrier coating material and a third thermal barrier coating material does not exceed 2.5 W/m.K at the temperature of 1,000-1,600 DEG C. According to the thermal barrier coating ofthe double-layer structure, the purpose of sintering resistance of the ceramic coating in the high-temperature environment can be achieved, by means of the design of the toughening layer, the worsening influences of heat insulating holes on the service life are offset, and therefore collaborative design of sintering resistance and long service life of the thermal barrier coating of the novel structure is achieved.

Description

technical field [0001] The invention belongs to the technical field of coatings, in particular to a thermal barrier coating and a preparation method thereof. Background technique [0002] The materials of the hot end components of aero-engines and gas turbines are mostly high-temperature alloys. At present, the temperature limit of the most advanced single crystal superalloy does not exceed 1000°C, but the service temperature of the hot end components inside the engine has far exceeded the temperature limit of the superalloy. Moreover, with the continuous improvement of the thrust-to-weight ratio of the aero-engine, the service temperature inside the engine will become higher and higher. Therefore, in order to make superalloys work stably in an environment far exceeding their temperature limit, it is necessary to provide thermal insulation "protective clothing" for alloy components, that is, thermal barrier coatings (Thermal barrier coatings, TBCs). TBCs can effectively is...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/06C23C4/11C23C4/129C23C24/04
CPCC23C4/06C23C4/11C23C4/129C23C4/134C23C24/04
Inventor 李广荣王丽爽杨冠军刘梅军刘宏李成新李长久
Owner XI AN JIAOTONG UNIV
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