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A high-temperature self-healing composite coating formed on a base material and its preparation method and application

A matrix material and self-healing technology, applied in the field of high-temperature self-healing composite coating and its preparation, can solve the problems of good performance, low porosity, low jet temperature, etc., and achieve the effect of prolonging the service time

Active Publication Date: 2019-12-10
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the jet temperature of atmospheric plasma spraying is relatively low, and it is difficult to melt ultra-high temperature ceramic powder, so it is impossible to prepare a high-temperature anti-ablation coating with uniform structure, low porosity and good performance.

Method used

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  • A high-temperature self-healing composite coating formed on a base material and its preparation method and application
  • A high-temperature self-healing composite coating formed on a base material and its preparation method and application

Examples

Experimental program
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preparation example Construction

[0037] In a second aspect, the present invention provides a method for preparing the high-temperature self-healing composite coating described in the first aspect of the present invention, the method comprising the steps of:

[0038] (1) Depositing the SiC transition layer on the surface of the base material by chemical vapor deposition (CVD for short);

[0039] (2) ZrB 2 Powder, LaB 6 Powder and TaSi 2 Mix the powder evenly to obtain a mixed powder, then put the mixed powder into the powder feeder of the vacuum plasma spraying equipment and dry it;

[0040] (3) the base material deposited with the SiC transition layer is fixed on the rotary table in the vacuum chamber of the vacuum plasma spraying equipment; and

[0041] (4) prepare the ZrB on the SiC transition layer of the base material by vacuum plasma spraying method (VPS method for short) 2 -LaB 6 -TaSi 2 Composite surface layer, so that the high-temperature self-healing composite coating is prepared on the base ma...

Embodiment 1

[0065] S1. Prepare C. f / C-SiC ceramic matrix composite matrix original piece, the size is Φ30×10mm, respectively with 240 # 、600 # 、1000 # Polish the surface with sandpaper, put it in an acetone solution for ultrasonic cleaning for 10 minutes, and set it aside.

[0066] S2, the C f / C-SiC composite material is placed in a high-temperature furnace, heated to 1050 ° C, using trichloromethylsilane vapor as the SiC raw material, and the deposition time is 30 h. After the temperature in the furnace drops to room temperature, the sample is taken out, and the f A SiC transition layer with a thickness of 50 μm was obtained on the surface of the / C-SiC composite.

[0067] S3, select ZrB produced after spray granulation 2 -LaB 6 -TaSi 2 Hollow spherical micron powder (mole composition is ZrB 2 : 70%; LaB 6 : 15%; TaSi 2 : 15%, mol%), the particle size range of the hollow spherical micron powder is 15-45 μm.

[0068] S4. Put the spray powder into the powder feeder of the vacu...

Embodiment 2

[0075] Embodiment 2 is basically the same as Embodiment 1, the difference is:

[0076] In S3, ZrB produced after spray granulation was selected 2 -LaB 6 -TaSi 2 Hollow spherical micron powder, wherein the molar composition of the hollow spherical micron powder is ZrB 2 : 60%; LaB 6 : 20%; TaSi 2 : 20%, mol%.

[0077] The SiC / ZrB prepared in this example was tested by the same test method as in Example 1. 2 -LaB 6 -TaSi 2 The porosity, surface roughness and high temperature ablation resistance of the composite ceramic coating were tested, and the test results are shown in Table 1; in the present embodiment, the C f / C-SiC ceramic matrix composites were subjected to high-temperature ablation resistance tests. The surface temperature of the material during the ablation process was 2200°C, and the ablation time was 780s. 2 -LaB 6 -TaSi 2 The multiphase ceramic coating can effectively protect the ceramic matrix composite for at least 780s.

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Abstract

The invention relates to a high-temperature self-healing multiphase coating formed on a base material and a preparation method and an application thereof. The high-temperature self-healing multiphasecoating consists of a SiC transition layer formed on the base material and a ZrB2-LaB6-TaSi2 multiphase surface layer formed by mixing ZrB2, LaB6 and TaSi2 in turn, wherein the ZrB2-LaB6-TaSi2 multiphase surface layer is composed of 60-80% of ZrB2, 10-20% of LaB6 and 10-20% of TaSi2 in mole percent. The method comprises the following steps: preparing a SiC transition layer by a chemical vapor deposition method; preparing the ZrB2-LaB6-TaSi2 multiphase surface layer by the vacuum plasma spraying method. The high-temperature self-healing multiphase coating of the invention has the high-temperature synergistic self-healing performance, can prevent the oxidation atmosphere from migrating into the material, prolong the ablation resistance time of the coating at the high temperature, and plays an effective protective role for the thermal structure material.

Description

technical field [0001] The invention belongs to the technical field of high-temperature thermal structure protective coating and its preparation, and in particular relates to a high-temperature self-healing composite coating formed on a base material and its preparation method and application. Background technique [0002] With the development of the aerospace industry, hypersonic flight technology, one of the core technologies, has attracted more and more attention from all over the world. When the aircraft moves at high speed in the atmosphere, some of its structural parts, such as the nose cone and the front edge of the wing, will be subjected to severe aerodynamic heating, and the operating temperature can reach thousands or even thousands of degrees Celsius. Under severe conditions such as high temperature and air scour, relying on C alone f / SiC,C f Thermal structural composite materials such as / C-SiC are difficult to meet the performance requirements, and the prepa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/89
Inventor 裴雨辰张宝鹏王鹏于艺于新民刘俊鹏
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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