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A high-temperature anti-ablation coating formed on a base material and its preparation method and application

A matrix material and anti-ablation technology, which is applied in the field of high-temperature thermal protective coatings and preparations, can solve the problems of inability to prepare structures, low porosity, and good performance, and achieve excellent high-temperature ablation resistance, low porosity, and The effect of prolonging the use 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 of atmospheric plasma spraying 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 anti-ablation coating formed on a base material and its preparation method and application
  • A high-temperature anti-ablation coating formed on a base material and its preparation method and application

Examples

Experimental program
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preparation example Construction

[0042] In a second aspect, the present invention provides a method for preparing the high-temperature anti-ablation coating described in the first aspect of the present invention, said method comprising the steps of:

[0043] (1) Depositing the SiC transition layer on the surface of the base material by chemical vapor deposition (CVD for short);

[0044] (2) prepare said ZrC-SiC-Gd on the described SiC transition layer of base material by vacuum plasma spraying method (abbreviation VPS method) 2 o 3 A multi-phase oxygen barrier layer, whereby the high-temperature ablation-resistant coating is prepared on the base material.

[0045] According to some preferred embodiments, the step (2) includes the following sub-steps:

[0046] (a) Gd 2 o 3 Powder and ZrC powder and SiC powder with a molar ratio of (0.8-1.2):1 are mixed evenly to obtain the first mixed powder, and the Gd 2 o 3 Powder and ZrC powder and SiC powder with a molar ratio of (3-5): 1 are uniformly mixed to obtai...

Embodiment 1

[0072] S1. Prepare C. f / C-SiC ceramic matrix composite matrix original piece, the size is Φ30×10mm, respectively with 400 # , 800 # , 1200 # Polish the surface with sandpaper, put it in an acetone solution for ultrasonic cleaning for 10 minutes, and set it aside.

[0073] 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 20 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 40 μm was obtained on the surface of the / C-SiC composite.

[0074] S3. Select ZrC-SiC-Gd produced after spray granulation 2 o 3 Hollow spherical micron powder A (the molar ratio of ZrC to SiC is 1:1) and ZrC-SiC-Gd 2 o 3 Hollow spherical micron powder B (the molar ratio of ZrC to SiC is 4:1), Gd 2 o 3 The doping amount in the hollow spherical micron powder A and the holl...

Embodiment 2

[0082] Embodiment 2 is basically the same as Embodiment 1, the difference is:

[0083] In S3, Gd 2 o 3 The doping amount in hollow spherical micron powder A and hollow spherical micron powder B is constant, and the mole percentage is 10%.

[0084] The SiC / ZrC-SiC-Gd prepared in this example was tested by the same test method as in Example 1. 2 o 3 The porosity, bonding strength and high-temperature ablation resistance of the multiphase coating have been 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. During the ablation process, the surface temperature of the material was 2100°C, and the ablation time was 880s. After ablation, the structure of the material was complete. SiC / ZrC-SiC- Gd 2 o 3 The multiphase coating can effectively protect the ceramic matrix composite for at least 880s.

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Abstract

The invention relates to a high-temperature anti-ablative coating formed on a base material as well as a preparation method and application of the high-temperature anti-ablative coating. The high-temperature anti-ablative coating comprises a SiC transition layer and a ZrC-SiC-Gd2o3 complex phase oxygen barrier layer formed by mixing ZrC, SiC and Gd2o3, which are sequentially formed on the base material, wherein the molar percentage of Gd2o3 in the ZrC-SiC-Gd2o3 complex phase oxygen barrier layer is 10-20%. The method comprises the steps as follows: preparing the SiC transition layer by using achemical vapor deposition method; and preparing the ZrC-SiC-Gd2o3 complex phase oxygen barrier layer by using a vacuum plasma spraying method. The high-temperature anti-ablative coating disclosed bythe invention has a high temperature self-healing property, so that an oxidizing atmosphere can be prevented from migrating to the interior of a material, the anti-ablative service time of the coatingat a high temperature is prolonged and an effective protection role is played on a ceramic matrix composite; and the high-temperature anti-ablative coating has the advantages of small porosity, highbonding strength, excellent high-temperature anti-ablative performance and the like.

Description

technical field [0001] The invention belongs to the technical field of high-temperature thermal protection coating and its preparation, and in particular relates to a high-temperature ablation-resistant coating formed on a base material and a preparation method and application thereof. Background technique [0002] Hypersonic flight technology is one of the core technologies in the field of aerospace, and it has received more and more attention from major aerospace countries. When the aircraft moves at high speed, the temperature of its leading edge surface, tip, combustion chamber and other parts can reach thousands or even thousands of degrees Celsius. Under these harsh conditions, C alone f / SiC,C f Composite materials such as / C-SiC 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-ablation coating. [0003] Ultra-High Temperature Ceramics (UHTCs) still have good stability in harsh en...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/52
CPCC04B41/009C04B41/52C04B41/5059C04B41/4531C04B41/5057C04B41/5045C04B41/4543C04B41/0072C04B35/83C04B35/565
Inventor 裴雨辰张宝鹏刘伟宋环君于新民刘俊鹏
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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