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High-temperature antioxidant coating formed on matrix material and preparation method thereof

A high-temperature anti-oxidation and matrix material technology, which is applied in the field of protective coating preparation, can solve the problems of powder high-temperature oxidation deposition rate and other problems, and achieve the effects of excellent high-temperature anti-oxidation ability, thermal stress relief, and excellent high-temperature anti-oxidation performance

Active Publication Date: 2019-02-12
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
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Problems solved by technology

However, when the anti-oxidation coating is prepared by the atmospheric plasma spraying method, there are problems such as high-temperature oxidation of the powder during spraying and low deposition rate.

Method used

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  • High-temperature antioxidant coating formed on matrix material and preparation method thereof
  • High-temperature antioxidant coating formed on matrix material and preparation method thereof
  • High-temperature antioxidant coating formed on matrix material and preparation method thereof

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preparation example Construction

[0036] In a second aspect, the present invention provides a method for preparing the high-temperature oxidation-resistant coating described in the first aspect of the present invention, said method comprising the steps of:

[0037] (1) Put silicon carbide powder and tetratantalum hafnium pentacarbide powder into the powder feeder of the low-pressure plasma spraying equipment respectively and carry out drying treatment;

[0038] (2) fixing the composite material on a turntable in the vacuum chamber of the low-pressure plasma spraying equipment; and

[0039] (3) The silicon carbide layer and the mixed layer are sequentially prepared on the surface of the composite material by a low-pressure plasma spraying method, thereby preparing the high-temperature oxidation-resistant coating on the surface of the composite material.

[0040] In the prior art, the atmospheric plasma spraying method is used to prepare the anti-oxidation coating, but the jet flow of the atmospheric plasma spra...

Embodiment 1

[0061] ① Preparation C f / C-SiC ceramic matrix composite material matrix original piece, the size is Φ25×4mm, the surface is polished on 400#, 800#, 1200# sandpaper respectively, put into acetone and ultrasonically cleaned for 10min before use.

[0062] ②Select SiC and Ta after spray granulation 4 HfC 5 Powder, the particle size of SiC powder is 5-30μm, the fluidity is 210s / 50g, Ta 4 HfC 5 The particle size of the powder is 10-40 μm, and the fluidity is 10s / 50g. The powder particles after granulation are hollow spherical powders composed of nano-sized particles; add the above powders to the powder feeder of the low-pressure plasma spraying equipment, and heat up to 60°C Afterwards, heat-preserve and dry for 4 hours.

[0063] ③The silicon carbide layer was prepared on the substrate by low-pressure plasma spraying method: the pretreated C f / C-SiC ceramic matrix composite material matrix is ​​installed on the automatic workpiece rotating table in the vacuum chamber, and the...

Embodiment 2

[0068] Embodiment 2 is basically the same as Embodiment 1, the difference is:

[0069] In ④, after the jet is stabilized, open the 4 HfC 5 The powder feeder, the powder feeding rate is 3.3g / min and 80g / min respectively, the deposition time is 1min, and the first five tantalum hafnium carbide-silicon carbide layers are obtained; then adjust SiC and Ta 4 HfC 5 The powder feeding rates were 1g / min and 95g / min, respectively, and then deposited for 1min to obtain the second tantalum hafnium carbide-silicon carbide layer, thus obtaining a Ta with a total thickness of 219μm. 4 HfC 5 -SiC gradient layer.

[0070] Adopt the test method identical with embodiment 1 to be coated with the C f / C-SiC ceramic matrix composite material matrix is ​​carried out high-temperature oxidation test, to the Ta that this embodiment makes 4 HfC 5 - The porosity and bonding strength of the SiC gradient layer were tested, and the test results are shown in Table 1.

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Abstract

The invention relates to a high-temperature antioxidant coating formed on a matrix material and a preparation method thereof. The high-temperature antioxidant coating comprises a silicon carbide layerand a mixed layer formed by mixing tetratantalum hafnium pentacarbonate and silicon carbide which are successively formed on the matrix material. The method comprises the following steps: separatelyloading silicon carbide powder and tetratantalum hafnium pentacarbonate powder into a powder feeding device of a low-pressure plasma spraying device to be dried; fixing the matrix material onto a rotating table in a vacuum chamber of the low-pressure plasma spraying device; and successively preparing the silicon carbide layer and the mixed layer on the surface of the matrix material, thus obtaining the high-temperature antioxidant coating. The high-temperature antioxidant coating has the advantages of low porosity, high combination strength and excellent high-temperature antioxidant capacity.The method has the advantages of high deposition efficiency, no high-temperature oxidation of powder when in spraying, and controllable coating thickness and structure, and the compact high-temperature antioxidant coating can be rapidly and integrally prepared on the surface of the matrix material.

Description

technical field [0001] The invention belongs to the technical field of protective coating preparation, and in particular relates to a high-temperature anti-oxidation coating formed on a base material and a preparation method thereof. Background technique [0002] Hypersonic flight technology, as the core technology in the field of aerospace, has received more and more attention from major aerospace countries. When the aircraft moves at high speed, the temperature of its surface nose cone, leading edge stagnation point and other parts can reach thousands or even thousands of degrees Celsius. Under these harsh conditions, carbon / carbon composites alone (C f / C composites), carbon fiber reinforced ceramic matrix composites (such as C f / C-SiC composite materials) and other composite materials themselves are difficult to meet the needs of use, and it is necessary to coat the surface of the composite material with a high-temperature anti-oxidation coating. However, the existin...

Claims

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Application Information

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IPC IPC(8): C04B41/89
CPCC04B41/009C04B41/52C04B41/89C04B41/5059C04B41/5057C04B35/565C04B35/83
Inventor 张宝鹏刘伟王鹏杨冰洋于艺宋环君于新民刘俊鹏
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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