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A kind of thermal barrier coating and its preparation method and application, aeroengine turbine blade

An aero-engine and thermal barrier coating technology, which is applied in engine components, machines/engines, coatings, etc., can solve problems such as cracking and failure of thermal barrier coatings, achieve resistance to particle erosion, simple preparation methods, and high durability. Effects of CMAS Corrosion Properties

Active Publication Date: 2021-03-05
GUANGDONG INST OF NEW MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Currently, the structural system of thermal barrier coating materials used in the United States is prone to cracking and failure of thermal barrier coatings along the ceramic / metal interface

Method used

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  • A kind of thermal barrier coating and its preparation method and application, aeroengine turbine blade
  • A kind of thermal barrier coating and its preparation method and application, aeroengine turbine blade
  • A kind of thermal barrier coating and its preparation method and application, aeroengine turbine blade

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preparation example Construction

[0041] In addition, the present application also provides a method for preparing the above-mentioned thermal barrier coating, for example, including the following steps: preparing a 7YSZ ceramic layer by using a plasma spraying-physical vapor deposition method; preparing alumina on the surface of the 7YSZ ceramic layer by using magnetron sputtering technology layer and then vacuum treatment.

[0042] When the thermal barrier coating also includes a NiCoCrAlYTa alloy bonding layer, the NiCoCrAlYTa alloy bonding layer is first prepared by the plasma spraying-physical vapor deposition method, and then the plasma spraying-physical vapor deposition method is used on the surface of one side of the NiCoCrAlYTa alloy bonding layer Prepare a 7YSZ ceramic layer; then use magnetron sputtering technology to set an aluminum oxide layer on the surface of the 7YSZ ceramic layer away from the NiCoCrAlYTa alloy bonding layer, and vacuum process.

[0043]The inventors found that the microstruct...

Embodiment 1

[0069] Protect the turbine blades by using No. 60 grit for sandblasting. After sandblasting, use a brush to remove the residual grit, and then clean with high-pressure air and alcohol; protect the blades by spraying with PS-PVD to spray NiCoCrAlYTa alloy bonding layer , where the spraying power is controlled at 47kW, the argon gas is controlled at 93NLPM (standard liters per minute), and the hydrogen gas is controlled at 6NLPM. The thickness of the NiCoCrAlYTa alloy bonding layer formed after spraying is 25 μm.

[0070]After spraying the bonding layer, polish the blades, and then sandblast them with No. 220 grit. After sandblasting, use a brush to remove the residual grit, then clean with high-pressure air and alcohol, and finally use PS-PVD to spray the 7YSZ ceramic layer. Among them, the net spraying power is controlled at 57kW, the argon gas is controlled at 35NLPM, and the hydrogen gas is controlled at 65NLPM. The thickness of the 7YSZ ceramic layer formed after spraying ...

Embodiment 2

[0074] Protect the turbine blades by using No. 60 grit for sandblasting. After sandblasting, use a brush to remove the residual grit, and then clean with high-pressure air and alcohol. Spray the blades for protection by spraying NiCrAlY alloy bonding layer with PS-PVD , wherein the spraying power is controlled at 45kW, the argon gas is controlled at 90NLPM (standard liter per minute), and the hydrogen gas is controlled at 5NLPM. The thickness of the NiCoCrAlYTa alloy bonding layer formed after spraying is 20 μm.

[0075] After the bonding layer is sprayed, the blades are polished. After polishing, sandblast with 220 grit. After sandblasting, use a brush to remove the residual grit, then clean with high-pressure air and alcohol, and finally use PS-PVD to spray the 7YSZ ceramic layer. Among them, the net spraying power is controlled at 50kW, the argon gas is controlled at 30NLPM, and the hydrogen gas is controlled at 60NLPM. The thickness of the 7YSZ ceramic layer formed after ...

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Abstract

The invention relates to a thermal barrier coating, as well as a preparation method and application thereof, and an aero-engine turbine blade, and belongs to the field of aero-engine hot end part protection coatings. The thermal barrier coating comprises a 7YSZ ceramic layer and an aluminum oxide layer arranged on the surface of one side of the 7YSZ ceramic layer, wherein the 7YSZ ceramic layer isin a feather column shape; and aluminum oxide in the aluminum oxide layer is nanocrystals. The thermal barrier coating not only has high thermal insulation and high stress tolerance, but also has favorable fused salt corrosion resistance and resistance to high temperature oxidation and particle erosion. The preparation method comprises the steps of adopting a plasma spraying-physical vapor deposition method for preparing the 7YSZ ceramic layer; adopting a magnetron sputtering technology for preparing the aluminum oxide layer; and then carrying out vacuum treatment. The method is simple, and the uniform thermal barrier coating can be prepared. The thermal barrier coating is applied to be arranged on an aero-engine hot end part such as the surface of a turbine blade, so that the turbine blade has favorable resistance to high temperature oxidation, CMAS corrosion and particle erosion.

Description

technical field [0001] The invention relates to the field of protective coatings for hot end parts of aero-engines, and in particular to a thermal barrier coating, a preparation method and application thereof, and a turbine blade of an aero-engine. Background technique [0002] Thermal barrier coating is a thermal protection technology that uses high-temperature-resistant, low-thermal-conductivity ceramic materials to combine with metals in the form of coatings to reduce the temperature of metal surfaces in high-temperature environments. In advanced aero-engines, thermal barrier coatings can significantly reduce the surface temperature of the blade alloy, greatly prolong the working life of the blade, and improve the thrust and efficiency of the engine. [0003] High thrust ratio is a remarkable symbol of advanced aero-engines. The most direct way to achieve high thrust ratio is to increase the turbine inlet temperature. The main factor limiting the turbine inlet temperature...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C28/00C23C4/134C23C4/11C23C4/073C23C14/08C23C14/35C23C14/58F01D5/28
CPCC23C14/081C23C14/345C23C14/35C23C14/5806C23C28/3215C23C28/3455C23C4/073C23C4/11C23C4/134F01D5/288F05D2230/90
Inventor 张小锋刘敏周克崧邓畅光邓春明宋进兵毛杰张吉阜杨焜徐丽萍陈志坤曾威陈龙飞
Owner GUANGDONG INST OF NEW MATERIALS
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