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A wide temperature range anti-ablation coating formed on a base material and its preparation method

A base material, anti-ablation technology, applied in the field of high-temperature thermal structure protective coating and preparation, can solve the problems of inability to prepare structure, low porosity, good performance, etc., to improve high-temperature oxidation and ablation resistance, solution Low viscosity, the effect of mitigating thermal expansion coefficient mismatch

Active Publication Date: 2022-03-01
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the relatively low jet temperature of atmospheric plasma spraying, 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 wide temperature range anti-ablation coating formed on a base material and its preparation method
  • A wide temperature range anti-ablation coating formed on a base material and its preparation method

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preparation example Construction

[0048] In a second aspect, the present invention provides a method for preparing the wide temperature range anti-ablation coating described in the first aspect of the present invention, the method comprising the following steps:

[0049] (1) Prepare a SiBCN transition layer on the surface of the base material by polymer impregnation-cracking method (PIP method);

[0050] (2) adopt vacuum plasma spraying method (VPS method) to prepare ZrB on the SiBCN transitional layer that step (1) obtains 2 -SiC-La 2 o 3 ultra-high temperature multiphase ceramic layer; and

[0051] (3) ZrB obtained in step (2) by polymer impregnation-cracking method (PIP method) 2 -SiC-La 2 o 3 A SiBCN sealing layer is prepared on the ultra-high temperature composite ceramic layer, thereby preparing the wide temperature range anti-ablation coating on the base material.

[0052] The method of the present invention adopts the polymer impregnation-cracking method combined with the vacuum plasma spraying m...

Embodiment 1

[0084] This example is in C f Preparation of SiBCN transition layer + ZrB on the surface of SiC ceramic matrix composite material 2 -SiC-La 2 o 3 Ultra-high temperature composite ceramic layer + SiBCN sealing layer.

[0085] ① Preparation C f / SiC ceramic matrix composite material matrix wafer, the size is Φ30×10mm (diameter is 30mm, thickness is 10mm), respectively with 240 # 、600 # 、1000 # Polish the surface with sandpaper, put it in an ethanol solution for ultrasonic cleaning for 10 min, and then put C f Put the / SiC substrate into an oven, raise the temperature to 80°C and keep it warm for 4 hours before use.

[0086] ②C f / SiC composite material is immersed in the SiBCN polymer precursor solution (obtained by diluting the SiBCN precursor (polyborosilazane) with the organic solvent xylene), the vacuum degree of the impregnation process is 0.09MPa, the impregnation pressure is 1MPa, and the impregnation time is 2h . Next, the material was cured with a precursor, ...

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Abstract

The invention relates to a wide temperature range anti-ablation coating formed on a base material and a preparation method thereof. The wide temperature range anti-ablation coating includes a SiBCN transition layer formed sequentially on the base material, made of ZrB 2 , SiC and La 2 o 3 mixed ZrB 2 ‑SiC‑La 2 o 3 Ultra-high temperature composite ceramic layer and SiBCN sealing layer. The method: adopting PIP method to prepare SiBCN transition layer; adopting VPS method to prepare ZrB 2 ‑SiC‑La 2 o 3 Ultra-high temperature composite ceramic layer; SiBCN sealing layer prepared by PIP method. The anti-ablation coating in the wide temperature range of the present invention can prevent the oxidative atmosphere from migrating to the inside of the material, prolong the high-temperature anti-ablation time, and effectively protect the ceramic matrix composite material; the pores of the multi-layer coating prepared by the present invention The rate is small, the surface roughness is low, and it can effectively protect the ceramic matrix composite material for at least 700s in a high temperature environment of 2100°C.

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 wide temperature range anti-ablation coating formed on a base material and a preparation method thereof. Background technique [0002] Continuous fiber reinforced ceramic matrix composites (such as C / SiC, C / SiC-ZrC, etc.) have a series of excellent properties such as high specific strength, high specific modulus, low thermal expansion coefficient, and high comprehensive mechanical properties. The material has advantages that other materials cannot match. However, when the aircraft moves at high speed in the atmosphere, some of its structural parts, such as the nose cone and the leading edge of the wing, will be subjected to severe aerodynamic heating, and the local temperature can reach thousands of degrees Celsius. The combined environmental factors of high temperature, high pressure, high speed and...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B41/89C04B41/87C04B35/58C04B35/622
CPCC04B41/52C04B41/89C04B41/87C04B41/009C04B35/58C04B35/58078C04B35/62222C04B2235/3227C04B2235/3826C04B35/806C04B35/565
Inventor 张宝鹏裴雨辰吴朝军于新民刘伟霍鹏飞
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH