Wide-temperature-range ablation-resistant coating formed on base material and preparation method of wide-temperature-range ablation-resistant coating

A matrix material and anti-ablation technology, which is applied in the field of high-temperature thermal structural protective coating and preparation, can solve the problems of inability to prepare tissue, low porosity, and good performance, and achieve high-temperature anti-oxidation and ablation resistance, and effectively Protective effect, alleviate the effect of thermal expansion coefficient mismatch

Active Publication Date: 2020-11-06
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
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  • 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 powd

Method used

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  • Wide-temperature-range ablation-resistant coating formed on base material and preparation method of wide-temperature-range ablation-resistant coating
  • Wide-temperature-range ablation-resistant coating formed on base material and preparation method of wide-temperature-range ablation-resistant coating

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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 ablation-resistant coating formed on a base material and a preparation method of the wide-temperature-range ablation-resistant coating. The wide-temperature-range ablation-resistant coating comprises a SiBCN transition layer, a ZrB2-SiC-La2O3 ultra-high-temperature complex-phase ceramic layer which is formed by missing of ZrB2, SiC and La2O3, and aSiBCN sealing and filling layer; the above layers are formed on a matrix material successively; wherein the SiBCN transition layer is prepared through PIP method, the ZrB2-SiC-La2O3 ultra-high-temperature complex-phase ceramic layer is prepared through VPS method, and the SiBCN sealing and filling layer is prepared through PIP method. are sequentially formed on a base material. The wide-temperature-range ablation-resistant coating can prevent the oxidizing atmosphere from migrating into the material, prolong the high-temperature anti-ablation time, and effectively protect the ceramic-based composite material; the multi-layer coating prepared by the method is small in porosity and low in surface roughness, and can effectively protect the ceramic-based composite material for at least 700sin a high-temperature environment of 2100 DEG 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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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
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