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Gradient thermal barrier coating with continuous change of compositions at interface of double ceramic layers and preparation method of coating

A technology of thermal barrier coating and ceramic layer, applied in the direction of coating, metal material coating process, fusion spraying, etc., can solve the problems of many coating interfaces, difficult practical application, complicated preparation process, etc., and achieve thermal shock resistance Effect of life improvement

Active Publication Date: 2018-08-31
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 continuous change of compositions at interface of double ceramic layers and preparation method of coating

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Effect test

specific Embodiment approach

[0015] The preferred embodiment of the dual ceramic layer interface composition of the present invention is a gradient thermal barrier coating with continuously changing composition:

[0016] Such as figure 1 As shown, it includes a matrix, a bonding layer, a ceramic bottom layer, a transition layer, and a ceramic top layer arranged sequentially from bottom to top, and the composition of the transition layer between the ceramic bottom layer and the ceramic top layer changes continuously in the following manner:

[0017] The composition of the ceramic bottom layer decreases gradually, and the composition of the top ceramic layer increases gradually.

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

[0019] The preferred embodiment of the above-mentioned method for preparing a gradient thermal barrier coating with a continuously changing compo...

specific Embodiment

[0049] The first step is to prepare the superalloy substrate, which is pretreated by sandblasting;

[0050] The second step is to prepare a NiCoCrAlY bonding layer on the substrate.

[0051] (A) The NiCoCrAlY bonding layer is prepared by low-pressure plasma spraying. The main process parameters are: spraying power 64KW, vacuum chamber pressure 35mbar, powder feeding rate 80g / min, spraying distance 350mm, main air flow rate Ar is 110L / min, H 2 Air flow rate is 6L / min;

[0052] (B) The NiCoCrAlY bonding layer is 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.

[0053] Polish the prepared adhesive layer on 200#, 400#, 600#, 800# sandpaper in turn, and set aside. If the bonding layer of other materials is prepared, such as NiCoCrAlYX (X: one or more of Hf, Ta, Si), the spraying powder used can be changed to NiCoCrAlYX powder.

[0054] T...

Embodiment 1

[0071] Supersonic flame spraying NiCoCrAlYTa bonding layer + ultra-low pressure plasma physical multi-phase deposition on superalloy substrate YSZ / Gd with continuous changes in interface composition 2 Zr 2 O 7 Double ceramic layer

[0072] The first step is to prepare the superalloy substrate, which is pretreated by sandblasting;

[0073] The second step adopts supersonic flame spraying method to prepare NiCoCrAlYTa bonding layer. The main process parameters are: kerosene 25L / h, oxygen 900L / min, combustion chamber pressure 8.4bar, powder feeding rate 80g / min, spraying distance 350mm. Polish the prepared adhesive layer on 200#, 400#, 600#, 800# sandpaper in sequence, and set aside.

[0074] In the third step, an ultra-low pressure plasma physical multiphase deposition method is used to deposit YSZ / Gd with continuous changes in interface composition on the bonding layer. 2 Zr 2 O 7 Double ceramic layer. The specific preparation steps are as follows:

[0075] (1) Prepare spray powder: ...

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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 a double ceramic layer changes continuously and a preparation method thereof. Background technique [0002] Thermal barrier coating technology has become a core key technology in military and civil aviation engines because it can increase the temperature of the hot end components of aeroengines, increase the inlet temperature of the turbine, extend 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 to the first-stage engine turbine blades with a thrust-to-weight ratio of 10, but its long-term maximum use temperature cannot exceed 1200℃ , Otherwise it ...

Claims

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Application Information

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Patent Type & Authority Applications(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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