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Gradient thermal barrier coating with continuously changing interface composition of double ceramic layers and preparation method thereof

A technology of thermal barrier coating and ceramic layer, which is applied in the direction of coating, metal material coating process, fusion spraying, etc., can solve the problems of multiple coating interfaces, complex thermodynamic behavior, complex preparation process, etc., and achieve thermal shock resistance Effect of life improvement

Active Publication Date: 2020-04-14
BEIJING MINING & METALLURGICAL TECH GRP CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The Shanghai Institute of Ceramics prepared gradient composite coatings by spraying mixed powders of YSZ / zirconate in different proportions. However, in this structure, there are many coating interfaces, the thermodynamic behavior is more complex, and the preparation process is complicated, which is difficult for practical application.

Method used

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  • Gradient thermal barrier coating with continuously changing interface composition of double ceramic layers and preparation method thereof

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specific Embodiment approach

[0015] The gradient thermal barrier coating in which the composition of the double ceramic layer interface of the present invention is continuously changing is preferably implemented as follows:

[0016] Such as figure 1 As shown, it includes a substrate, an adhesive layer, a ceramic bottom layer, a transition layer and a ceramic top layer arranged in sequence from bottom to top, and the composition of the transition layer between the ceramic bottom layer and the ceramic top layer is continuously changed in the following manner:

[0017] The composition of the ceramic bottom layer shows a gradient decrease, and the composition of the ceramic top layer shows a gradient increase.

[0018] The ratio of the thickness of the ceramic bottom layer to the ceramic top layer is 0.1-10, and the thickness of the transition layer is 1 / 10-1 / 3 of the total thickness of the ceramic layer.

[0019] The preparation method of the above-mentioned gradient thermal barrier coating in which the int...

specific Embodiment

[0050] The first step is to prepare the superalloy substrate, which is pretreated by sandblasting;

[0051] The second step is to prepare a NiCoCrAlY bonding layer on the substrate.

[0052] (A) The NiCoCrAlY bonding layer was prepared by low-pressure plasma spraying method. The main process parameters are: spraying power 64KW, vacuum chamber pressure 35mbar, powder feeding rate 80g / min, spraying distance 350mm, main gas flow Ar gas 110L / min, H 2 The air flow rate is 6L / min;

[0053] (B) The NiCoCrAlY bonding layer was prepared by supersonic flame spraying method. The main process parameters are: kerosene 25L / h, oxygen 900L / min, combustion chamber pressure 8.4bar, powder feeding rate 80g / min, spraying distance 350mm.

[0054] Grind the prepared bonding layer on 200#, 400#, 600#, 800# sandpaper in turn, and set aside. If other material bonding layer is prepared, such as NiCoCrAlYX (X: one or more of Hf, Ta, Si), the spraying powder used can be changed to NiCoCrAlYX powder. ...

Embodiment 1

[0072] Supersonic flame spraying NiCoCrAlYTa bonding layer + ultra-low pressure plasma physical multiphase deposition interface composition of YSZ / Gd with continuous change on superalloy substrate 2 Zr 2 o 7 double ceramic layer

[0073] The first step is to prepare the superalloy substrate, which is pretreated by sandblasting;

[0074] The second step is to prepare the NiCoCrAlYTa bonding layer by supersonic flame spraying method. The main process parameters are: kerosene 25L / h, oxygen 900L / min, combustion chamber pressure 8.4bar, powder feeding rate 80g / min, spraying distance 350mm. Grind the prepared bonding layer on 200#, 400#, 600#, 800# sandpaper in turn, and set aside.

[0075] The third step is to use ultra-low pressure plasma physical multiphase deposition method to deposit YSZ / Gd with continuous change in interface composition on the bonding layer 2 Zr 2 o 7 Double ceramic layer. Concrete preparation steps are as follows:

[0076] (1) Prepare spray powder: Y...

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Abstract

The invention discloses a gradient thermal barrier coating with continuous change of compositions at an interface of double ceramic layers and a preparation method of the coating. The gradient thermalbarrier coating has a substrate, a bonding layer, the ceramic underlayer, a transition layer and the ceramic surface layer which are disposed from bottom to top in sequence, wherein the compositionson the transition layer between the ceramic underlayer and the ceramic facing layer are continuously changed. The thermal barrier coating can be prepared by a plasma spraying process, and typical preparation processes include atmospheric plasma spraying, ultra-low pressure plasma physical multiphase deposition and the like. The obtained thermal barrier coating no longer has the problem of crackingand spalling at the interface of the double ceramic layers during thermal cycle, so that the thermal shock resistance life of the thermal barrier coating is greatly prolonged.

Description

technical field [0001] The invention relates to a thermal barrier coating technology, in particular to a gradient thermal barrier coating whose interface composition of double ceramic layers changes continuously and a preparation method thereof. Background technique [0002] Thermal barrier coating technology has become a core key technology in military and civil aero-engines because it can increase the operating temperature of the hot-end parts of the aero-engine, increase the temperature of the front inlet of the turbine, prolong the life of the engine, and reduce fuel consumption. At present, thermal barrier coatings are also widely used in automobiles, ships, and ground gas turbines. [0003] At present, the widely used thermal barrier coating material is mainly yttria partially stabilized zirconia (YSZ), and it has been successfully applied on the turbine blade of a first-stage engine with a thrust-to-weight ratio of 10, but its long-term maximum service temperature can...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/134C23C4/11C23C4/02C23C4/073
CPCC23C4/02C23C4/073C23C4/11C23C4/134
Inventor 于月光高丽华冀晓鹃贾芳彭浩然侯伟骜原慷周恒
Owner BEIJING MINING & METALLURGICAL TECH GRP CO LTD
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