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A composite thermal barrier coating and its preparation method and application

A technology of thermal barrier coating and alloy layer, which is applied in the field of materials, can solve problems affecting the normal operation of the engine, and achieve the effect of improving CMAS corrosion resistance, high corrosion resistance, and oxidation resistance

Active Publication Date: 2021-01-05
GUANGDONG INST OF NEW MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Research and investigation after the accident found that the deposits seriously affected the normal operation of the engine

Method used

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  • A composite thermal barrier coating and its preparation method and application
  • A composite thermal barrier coating and its preparation method and application

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preparation example Construction

[0027] The embodiment of the present invention also provides a preparation method of the above-mentioned composite thermal barrier coating, for example, may include the following steps: 2 -Y 2 o 3 The ceramic layer is subjected to vacuum heat treatment, and the vacuum heat treatment system may include: heat preservation at 610-700°C for 1-3 hours, then raise the temperature to 800-900°C at a heating rate of 5-10°C / min, and hold heat for 1-2h. The medium vacuum pressure is less than 1×10 -2 Pa.

[0028] In this application, the heat treatment method is used to plate aluminum on the ceramic surface layer of the thermal barrier coating with a porous structure. On the one hand, during the heat treatment process, the molten aluminum penetrates into the interior of the coating to seal the pores of the coating near the surface; on the other hand On the one hand, the aluminum reacts with the zirconia coating, so that a layer of dense alumina (α-alumina) is formed in situ on the sur...

Embodiment 1

[0052] The nickel-based superalloy is used as the base layer, ultrasonically cleaned with gasoline and alcohol in turn, and then sandblasted with corundum at a pressure of 0.45MPa.

[0053] After polishing, a NiCoCrAlYTa bonding layer with a thickness of about 100 μm is prepared on the surface of the base layer by electron beam-physical vapor deposition method. Among them, the power of electron beam-physical vapor deposition is 120kW, the cabin pressure is 0.01Pa, and the substrate preheating temperature is 800°C.

[0054] Then the electron beam-physical vapor deposition method is used to prepare ZrO with a thickness of about 150 μm on the surface of the bonding layer. 2 -Y 2 o 3 ceramic layer. Among them, the power of the electron beam-physical vapor deposition method is 180kW, the cabin pressure is 0.01Pa, and the substrate preheating temperature is 800°C.

[0055] Using magnetron sputtering technology to prepare an aluminum film layer with a thickness of about 5 μm on t...

Embodiment 2

[0058] The nickel-based superalloy is used as the base layer, ultrasonically cleaned with gasoline and alcohol in turn, and then sandblasted with corundum at a pressure of 0.45MPa.

[0059] A NiCrAlY bonding layer with a thickness of about 100 μm was prepared on the surface of the base layer by supersonic flame spraying technology. Among them, the gasoline flow rate of the supersonic flame spraying method is 13L / h, the oxygen flow rate is 800L / min, and the spraying distance is 400mm.

[0060] Then use the atmospheric plasma spraying method to prepare ZrO with a thickness of about 150 μm on the surface of the bonding layer. 2 -Y 2 o 3 ceramic layer. Among them, the current of the atmospheric plasma spraying method is 680A, the argon gas is 50 SLPM, the hydrogen gas is 12 SLPM, and the spraying distance is 110 mm.

[0061] Using magnetron sputtering technology to prepare an aluminum film layer with a thickness of about 6 μm on the surface of the ceramic layer, in which the m...

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Abstract

The invention relates to a composite thermal barrier coating and a preparation method and an application thereof, and belongs to the field of materials. The composite thermal barrier coating comprisesan alloy layer, a bonding layer, a ZrO2-Y2O3 ceramic layer and an aluminum film layer, the oxygen permeability can be blocked, the oxidation resistance of the coating is increased, the surface porosity factor of the coating is reduced, and the permeation of corrosive substances is obviously reduced, so that the thermal barrier coating has high corrosion resistance. The preparation method comprises the steps of performing vacuum heat treatment on the ZrO2-Y2O3 ceramic layer of which the surface is coated with the aluminum film layer as follows: insulating for 1 to 3 h at 610 to 700 DEG C, heating to 800 to 900 DEG C at the speed of 5 to 10 / min, and insulating for 1 to 2 h, wherein the vacuum pressure is less than 1*10<-2> Pa in a heat treatment process. Nano aluminum fiber can be formed onthe surface of the coating after the heat treatment, so that the CMAS corrosion resistance of the coating is increased. When the composite thermal barrier coating is used for aeroengine, engine components can adapt to poor high-temperature and strong-corrosion working environments.

Description

technical field [0001] The invention relates to the field of materials, and in particular to a composite thermal barrier coating and its preparation method and application. Background technique [0002] Aeroengines are highly complex and sophisticated thermodynamic machines. Important breakthroughs in the history of aviation, such as powered flight, jet propulsion, crossing the sound barrier, vertical takeoff and landing, and supersonic cruise, are all closely related to the advancement of aeroengine technology. As the heart of an aircraft, an aero engine is known as the "Flower of Industry", an important symbol of the strength of a great power, and has extremely high economic and military value. [0003] In 1953, NASA Research Center in the United States first proposed the technical concept of Thermal Barrier Coatings (TBCs). In the 1970s, thermal barrier coating materials were first used on gas turbine blades, successfully reducing the The operating temperature of the eng...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C28/00C23C14/18C23C14/35C23C14/58C23C4/11C23C4/134C23C14/08C23C14/30C23C4/073C23C4/129C23C14/16F01D5/28
CPCC23C14/083C23C14/16C23C14/185C23C14/30C23C14/35C23C14/5806C23C28/321C23C28/3455C23C4/073C23C4/11C23C4/129C23C4/134F01D5/288F05D2300/611
Inventor 张小锋周克崧刘敏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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