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C/SiC-HfC composite material part transition phase coating preparation method, transition phase coating slurry and member thermal protection method

A composite material and transition phase technology, applied in aircraft parts, transportation and packaging, fuselage, etc., can solve the problems of reduced thermal protection effect and weak combination

Active Publication Date: 2022-04-15
XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the thermal protection caused by the weak combination between the HfC substrate and the SiC coating deposited by CVI during riveting welding when the current ultra-high temperature modified C / SiC-HfC ceramic matrix composite parts are riveted and welded by CVI deposition. To solve the technical problem of reduced effect, a preparation method of transition phase coating for C / SiC-HfC composite parts, a transition phase coating slurry and a thermal protection method for components are proposed

Method used

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  • C/SiC-HfC composite material part transition phase coating preparation method, transition phase coating slurry and member thermal protection method
  • C/SiC-HfC composite material part transition phase coating preparation method, transition phase coating slurry and member thermal protection method

Examples

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Effect test

Embodiment 5

[0031] Embodiment 5 is to prepare a transition phase coating on an ultra-high temperature modified C / SiC-HfC ceramic matrix composite material part that is compatible with an aircraft component, and assemble it on an aircraft component for CVI deposition to verify the actual use SiC coatings produced by CVI deposition combined with transition phase coatings.

Embodiment 1

[0033] Step 1. Introduce HfC into the finely punctured C / SiC prefabricated body by using the precursor impregnation and cracking transformation method to prepare the ultra-high temperature modified C / SiC-HfC ceramic matrix composite prefabricated body. The ultra-high temperature modified C / SiC- HfC ceramic matrix composite material prefabricated body is processed into ultra-high temperature modified C / SiC-HfC ceramic matrix composite material sample;

[0034] Step 2. Prepare a transition phase coating on the ultra-high temperature modified C / SiC-HfC ceramic matrix composite sample in step 1. The specific process is as follows:

[0035] 2.1. According to the mass ratio of polyazide silane: hafnium diboride: dicumyl peroxide = 1: 0.6: 0.01, weigh polyazide silane, hafnium diboride and dicumyl peroxide respectively;

[0036] 2.2. Add the three components of polyazide silane, hafnium diboride and dicumyl peroxide into the beaker in turn, and stir with a magnetic stirrer. Stir at r...

Embodiment 2

[0045] When preparing the transition phase coating slurry in this example, the ratio of each component is polyazide silane: hafnium diboride: dicumyl peroxide = 1:0.9:0.03, and after the transition phase coating slurry is applied, let it dry Dry for 3 hours. When curing in the oven, adjust the oven temperature to 170°C and cure for 4 hours;

[0046] The remaining steps are the same as those in Embodiment 1, and will not be repeated here.

[0047] According to the method in Example 2, after the ultra-high temperature modified C / SiC-HfC ceramic matrix composite sample was prepared with a transition phase coating, the ultra-high temperature modified C / SiC-HfC ceramic matrix composite sample was subjected to CVI to prepare a SiC coating, The surface has no adverse phenomena such as roughening, peeling, and slag, and is still in a smooth and solid state, and the surface quality meets the design and use requirements.

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Abstract

The invention relates to a preparation method of a transition phase coating of a C / SiC-HfC composite material part, transition phase coating slurry and a thermal protection method of a component, aiming at solving the technical problem that the thermal protection effect is reduced due to modulus mismatch between an HfC matrix and a SiC coating deposited by CVI when the C / SiC-HfC composite material part is subjected to CVI deposition rivet welding at present. The transition phase coating slurry is composed of polysilazane, hafnium diboride and dicumyl peroxide according to the mass ratio of 1: (0.6-0.9): (0.01-0.03). The preparation method of the transition phase coating comprises the following steps: preparing an ultrahigh-temperature modified C / SiC-HfC ceramic matrix composite part, preparing the transition phase coating slurry, brushing the transition phase coating slurry on the surface of the ultrahigh-temperature modified C / SiC-HfC ceramic matrix composite part, and curing. The thermal protection method of the component comprises the following steps: preparing the transition phase coating on the surface of the ultrahigh-temperature modified C / SiC-HfC ceramic matrix composite part, fixing the transition phase coating on the component, and carrying out chemical vapor infiltration deposition.

Description

technical field [0001] The invention relates to a method for combining a C / SiC-HfC composite material with a SiC coating, in particular to a method for preparing a transition phase coating of a C / SiC-HfC composite material part, a transition phase coating slurry and a method for thermal protection of components. Background technique [0002] During the flight, the spacecraft will be subjected to thermal loads such as high temperature, high pressure, strong erosion, and high heat flow due to aerothermal effects or the combustion of energetic materials. In order to ensure the normal operation of aircraft component materials, high-temperature resistant thermal Protective materials provide thermal protection for aerospace vehicles. For example, hypersonic vehicles usually require materials at the nose cone or wing leading edge to have long-term ablation resistance above 2400°C. [0003] Carbon fiber toughened silicon carbide (C / SiC) ceramic matrix composites have become one of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87C04B37/00B64C1/38
CPCC04B41/87C04B41/507C04B41/009C04B37/00B64C1/38C04B2237/083C04B2237/365C04B2237/36C04B2237/385C04B2237/55C04B35/80C04B35/565C04B35/5622C04B41/4983C04B41/4539
Inventor 苏海龙赵盟辉陈旭李仁意姜伟光王鹏张少博
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD