High-temperature self-healing multiphase coating formed on base material and preparation method and application thereof

A matrix material and self-healing technology, applied in the field of high-temperature self-healing multiphase coating and its preparation, can solve the problems of good performance, low jet temperature, unable to prepare tissue, etc., and achieve the effect of prolonging the use time

Active Publication Date: 2019-05-03
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

Method used

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  • High-temperature self-healing multiphase coating formed on base material and preparation method and application thereof
  • High-temperature self-healing multiphase coating formed on base material and preparation method and application thereof
  • High-temperature self-healing multiphase coating formed on base material and preparation method and application thereof

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0037] In a second aspect, the present invention provides a method for preparing the high-temperature self-healing multiphase coating of the present invention in the first aspect, and the method includes the following steps:

[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 Pink, LaB 6 Powder and TaSi 2 The powder is uniformly mixed to obtain a mixed powder, and then the mixed powder is put into the powder feeder of the vacuum plasma spraying equipment and dried;

[0040] (3) Fixing the base material deposited with the SiC transition layer on the rotating 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 the vacuum plasma spraying method (VPS method for short) 2 -LaB 6 -TaSi 2 A multi-phase surface layer, thereby preparing the high-temperature self-healing multi-phase coating on the ba...

Example Embodiment

[0064] Example 1

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

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

[0067] S3. Select ZrB produced after spray granulation 2 -LaB 6 -TaSi 2 Hollow spherical micron powder (molar 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 sprayed powder into the powd...

Example Embodiment

[0074] Example 2

[0075] Embodiment 2 is basically the same as embodiment 1, except that:

[0076] In S3, select ZrB produced after spray granulation 2 -LaB 6 -TaSi 2 Hollow spherical micron powder, wherein the molar component 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 using the same test method as in Example 1. 2 -LaB 6 -TaSi 2 The porosity, surface roughness and high-temperature ablation resistance of the multiphase ceramic coating were tested. The test results are shown in Table 1. In this example, the C f / C-SiC ceramic matrix composite material is subjected to high temperature ablation resistance test. The temperature of the material surface during the ablation process is 2200℃, the ablation time is 780s, and the material structure is complete after ablation, indicating that SiC / ZrB is in a high temperature environment of 2200℃ 2 -LaB 6 -TaSi 2 The multiphase ceramic coating can ...

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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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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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