Carbon fiber-reinforced (carbon-) silicon carbide base-ultra-high temperature ceramic base compound material and production method thereof

A technology of ultra-high temperature ceramics and composite materials, applied in the field of carbon fiber reinforced silicon carbide-ultra-high temperature ceramic matrix composite materials and its preparation, can solve the problem of low density, high mechanical properties, long-term anti-oxidation and ablation resistance, high density, Low mechanical properties and other problems, to achieve outstanding mechanical properties and meet the effect of ablation resistance

Inactive Publication Date: 2019-07-05
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, most of the currently prepared carbon fiber reinforced ultra-high temperature ceramic matrix composites are based on a single C or SiC matrix, which has relatively low mechanical properties and relatively high density, and it is difficult to meet low density, high mechanical properties, and long-term oxidation resistance and anti-ablation requirements

Method used

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  • Carbon fiber-reinforced (carbon-) silicon carbide base-ultra-high temperature ceramic base compound material and production method thereof
  • Carbon fiber-reinforced (carbon-) silicon carbide base-ultra-high temperature ceramic base compound material and production method thereof
  • Carbon fiber-reinforced (carbon-) silicon carbide base-ultra-high temperature ceramic base compound material and production method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0046] The grades are U~ZCS0.12 composite material preparation method and material properties:

[0047] Choose 380×80×10mm, the density is 0.5g / cm 3 The 2D needle-punched carbon fiber preform; the pyrolytic carbon interface layer was prepared by ICVI process, the temperature was 900°C, and the flow rate of argon gas was 0.1m 3 / h, propane 0.1m 3 / h, the deposition time is 5 hours; the deposition time of the PyC substrate in the PyC-SiC functional layer is 0h; the SiC substrate required for the PyC-SiC functional layer is prepared by the ICVI process, the temperature is 1000 ° C, hydrogen, argon and trichloromethylsilane , the volume ratio is 5:5:1, the deposition time is 500 hours, and the material density is 1.8g / cm 3 ;Using CNC machining and forming, ultrasonic cleaning; using PIP technology to introduce ZrC-SiC ultra-high temperature ceramic phase, after 7 cycles of impregnation and cracking, the specific process parameters are: vacuum degree 2000Pa, impregnation pressure...

Embodiment 2

[0049] The grade is U~ZCS0.91 composite material preparation method and material properties:

[0050] Choose 380×80×10mm, the density is 0.5g / cm 3 The 2D needle-punched carbon fiber preform; the pyrolytic carbon interface layer was prepared by ICVI process, the temperature was 900°C, and the flow rate of argon gas was 0.1m 3 / h, propane 0.1m 3 / h, the deposition time is 5 hours; use the ICVI process to prepare the PyC substrate required for the PyC-SiC functional layer, the temperature is 950 ° C, and the flow rate of argon gas is 0.15m 3 / h, propane 0.15m 3 / h, the deposition time is 200 hours; use the ICVI process to prepare the SiC substrate required for the PyC-SiC functional layer, the temperature is 1000 ° C, hydrogen, argon and trichloromethylsilane, the volume ratio is 5:5:1, and the deposition time is 300 hours , material density 1.65g / cm 3 ; The SiC substrate required for the SiC anti-oxidation layer was prepared by the ICVI process, the temperature was 1050°C, t...

Embodiment 3

[0052] The grade is U~ZCS3.28 composite material preparation method and material properties:

[0053] Choose 380×80×10mm, the density is 0.5g / cm 3 The 2D needle-punched carbon fiber preform; the pyrolytic carbon interface layer was prepared by ICVI process, the temperature was 900°C, and the flow rate of argon gas was 0.1m 3 / h, propane 0.1m 3 / h, the deposition time is 5 hours; use the ICVI process to prepare the PyC substrate required for the PyC-SiC functional layer, the temperature is 950 ° C, and the flow rate of argon gas is 0.15m 3 / h, propane 0.15m 3 / h, the deposition time is 400 hours; use the ICVI process to prepare the SiC substrate required for the PyC-SiC functional layer, the temperature is 1000 ° C, hydrogen, argon and trichloromethylsilane, the volume ratio is 5:5:1, and the deposition time is 200 hours , material density 1.8g / cm 3 ;Using CNC machining and forming, ultrasonic cleaning; using PIP technology to introduce ZrC ultra-high temperature ceramic ph...

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Abstract

The invention discloses a carbon fiber-reinforced (carbon-) silicon carbide base-ultra-high temperature ceramic base compound material and a production method thereof, and belongs to the technical field of ultra-high temperature ceramic base compound materials. According to the compound material, on the basis of the characters of components of carbon fibers, pyrolytic carbon (PyC), silicon carbide(SiC) and ultra-high temperature ceramics (UHTC), the components are combined to form four functional areas, namely a carbon fiber load-carrying skeleton area, a PyC interface layer area, a PyC-SiC load-bearing and anti-oxidation area and an ultra-high temperature anti-oxidation ablation-resistant area, and a CVI-PIP-CVD compound technology is adopted for producing the compound material with excellent mechanical performance and high-temperature-resistant and anti-oxidation performance.

Description

[0001] Technical field: [0002] The invention relates to the technical field of ultra-high temperature ceramic matrix composite materials, in particular to a carbon fiber reinforced (carbon-) silicon carbide-ultrahigh temperature ceramic matrix composite material and a preparation method thereof. [0003] Background technique: [0004] High-speed aircraft must withstand ultra-high temperature (≥1600°C), high heat flow, mechanical stress and thermal load during the reentry process. Therefore, heat-resistant materials are required to have good mechanical properties, oxidation resistance, thermal shock resistance and ablation resistance. performance. At present, C / C composites have excellent mechanical and thermal properties in high-temperature oxygen-free environments, but they begin to oxidize when they exceed 450°C under aerobic conditions; on this basis, C / (C~)SiC composites have been developed. , significantly improved its mechanical properties and oxidation resistance, and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/622
CPCC04B35/806C04B35/565C04B35/622C04B2235/3839C04B2235/6562C04B2235/6567C04B2235/77C04B2235/96
Inventor 汤素芳庞生洋胡成龙王石军李建
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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