Carbon fiber reinforced ceramic matrix composite material and preparation method thereof

A technology of ceramic matrix and composite materials, which is applied in the field of carbon fiber reinforced ceramic matrix composite materials and its preparation, can solve the problems of reducing the mechanical properties of composite materials, achieve strong designability, avoid catastrophic failure, and extend the expansion path.

Active Publication Date: 2021-12-17
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In terms of the selection of interfacial phase materials, although the BN interfacial phase has advantages in some aspects, some researchers have studied SiC / BN / SiC CMCs at moderate (700-900°C) and high-temperature (900-1300°C) temperatures. thermomechanical degradation in different atmospheres, such as oxygen, water vapor, or combustion environments, which concluded that humidity from combustion products and / or humidity in the compression environment of aeroengines promotes the degradation of the BN interfacial phase in SiC-based composites, Thereby reducing the mechanical properties of the composite material

Method used

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  • Carbon fiber reinforced ceramic matrix composite material and preparation method thereof
  • Carbon fiber reinforced ceramic matrix composite material and preparation method thereof
  • Carbon fiber reinforced ceramic matrix composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] The preparation of carbon fiber reinforced ceramic matrix composite material comprises the following steps:

[0035] (1) Two perforated plates are used to press and shape the carbon fiber cloth to obtain a size of 40×4×60mm 3 The 2.5d prefabs were cleaned by ultrasonic cleaning, carbonized at 400°C under the protection of argon, ultrasonically cleaned with anhydrous ethanol, and then removed in a muffle furnace at 100°C for 8 hours. Curing glue. The preform was suspended in a vertical chemical vapor deposition furnace with a carbon rope, and the temperature of the chemical vapor deposition furnace was raised to 1100 °C at a heating rate of 7 °C / min under the protection of an Ar gas flow rate of 300 mL / min. Using CH 4 -Ar system deposits pyrolytic carbon (PyC) interface phase, chemical vapor deposition (CVI) process conditions of PyC interface phase: deposition temperature 1000 ° C, deposition pressure maintained at atmospheric pressure, CH 4 The gas flow rates of (99...

Embodiment 2

[0043] The preparation of carbon fiber reinforced ceramic matrix composite material, the steps are as follows:

[0044] (1) Two perforated plates are used to press and shape the carbon fiber cloth to obtain a size of 40×4×60mm 3 The 2.5d prefabs were cleaned by ultrasonic cleaning, carbonized at 300°C under the protection of argon, ultrasonically cleaned with anhydrous ethanol, and then removed in a muffle furnace at 80°C for 10 hours to remove the fiber surface curing glue. The preform was suspended in a vertical chemical vapor deposition furnace with a carbon rope, and the temperature of the chemical vapor deposition furnace was raised to 900 °C at a heating rate of 6 °C / min under the protection of an Ar gas flow rate of 200 mL / min. Using CH 4 -Ar system deposits PyC interface phase, chemical vapor deposition (CVI) process conditions of PyC interface phase: deposition temperature 900 ° C, under normal pressure, CH 4 The gas flow rates of (99.99%) and Ar (99.99%) were 100m...

Embodiment 3

[0049] The preparation of carbon fiber reinforced ceramic matrix composite material comprises the following steps:

[0050] (1) Two perforated plates are used to press and shape the carbon fiber cloth to obtain a size of 40×4×60mm 3 The 2.5d prefabs were cleaned by ultrasonic cleaning, carbonized at 500°C under the protection of argon, ultrasonically cleaned with anhydrous ethanol, and then removed in a muffle furnace at 120°C for 5 hours to remove the Curing glue. The preform was suspended in a vertical chemical vapor deposition furnace with a carbon rope, and the temperature of the chemical vapor deposition furnace was raised to 1000 °C at a heating rate of 10 °C / min under the protection of an Ar gas flow rate of 400 mL / min. Using CH 4 -Ar system deposits pyrolytic carbon (PyC) interface phase, chemical vapor deposition (CVI) process conditions of PyC interface phase: deposition temperature 1100 ° C, under normal pressure, CH 4 The gas flow rates of (99.99%) and Ar (99.99...

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Abstract

The invention discloses a carbon fiber reinforced ceramic matrix composite material and a preparation method thereof, and belongs to the technical field of ceramic matrix composite materials. The composite material comprises a carbon fiber layer containing a carbon interface phase, a SiC-ZrC matrix located on the carbon fiber layer and a SiC layer located on the surface of the SiC-ZrC matrix. The preparation method comprises the following steps: depositing pyrolytic carbon in carbon fiber cloth by adopting a chemical vapor deposition method to obtain a carbon fiber layer containing a carbon interface phase; alternately depositing a SiC layer and a ZrC layer on the obtained sample by adopting a chemical vapor deposition method to obtain a SiC-ZrC matrix, and then depositing a SiC layer on the surface of the matrix by adopting the chemical vapor deposition method to obtain the composite material. The carbon fiber reinforced ceramic matrix composite material provided by the invention is high in density, has good ablation resistance and mechanical properties in a low-temperature environment, and has a wide application prospect in the aspect of ceramic composite material components for high-thrust-ratio aero-engines.

Description

technical field [0001] The invention belongs to the technical field of ceramic matrix composite materials, and in particular relates to a carbon fiber reinforced ceramic matrix composite material and a preparation method thereof. Background technique [0002] Carbon / silicon carbide (C / SiC) composites have been extensively studied due to their low density, high strength, low coefficient of thermal expansion, and good mechanical properties at high temperatures. These properties make them attractive as structural materials for aerospace applications. However, the long-term service temperature of C / SiC composites does not exceed 1650 °C, and the temperature continues to rise. 2 The increased film volatilization and active oxidation of SiC lead to a rapid decrease in strength, which hinders the use of C / SiC composites in higher temperature environments. On the other hand, although C / SiC composites overcome the brittleness of single silicon carbide ceramics, the slightly insuffi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/56C04B35/565C04B35/622
CPCC04B35/80C04B35/5622C04B35/565C04B35/622C04B2235/5248C04B2235/422C04B2235/3826C04B2235/3839C04B2235/656C04B2235/6567C04B2235/658C04B2235/77C04B2235/96C04B2235/9684
Inventor 冯涛石新豪童明德林红娇温世峰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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