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Preparation method of two-dimensional carbon/silicon-silicon carbide composite pin

A composite material, silicon carbide technology, used in the field of corrosion resistance, ceramic matrix composite material preparation and processing, high temperature resistance, high strength, oxidation resistance composite material connection field, can solve the problem of unstable product performance, long production cycle and high cost problems, to achieve the effect of uniform force, improved mechanical properties, and high connection strength

Active Publication Date: 2019-05-10
XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to overcome the shortcomings of the preparation technology of pin-punched C / SiC composite material (CVI process) pins with complex structures, such as long production cycle, high cost, and large differences in product performance, the present invention provides a two-dimensional carbon / silicon-silicon carbide The preparation method of the composite material pin, and also provides the preparation method and structure of the pin prefabricated body

Method used

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  • Preparation method of two-dimensional carbon/silicon-silicon carbide composite pin
  • Preparation method of two-dimensional carbon/silicon-silicon carbide composite pin
  • Preparation method of two-dimensional carbon/silicon-silicon carbide composite pin

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preparation example Construction

[0051] Such as Figure 2-3 As shown, the two-dimensional carbon / silicon-silicon carbide composite pin prefabricated body of the present invention includes a multilayer two-dimensional carbon cloth, and the included angle between the corresponding fibers of two adjacent two-dimensional carbon cloths in the multilayer two-dimensional carbon cloth is 45°, the two-dimensional carbon / silicon-silicon carbide composite pin preform also includes a sewing structure, the sewing structure includes a plurality of U-shaped fibers distributed in a square matrix, and the plurality of U-shaped fibers are obtained from the multi-layer two-dimensional carbon cloth One side vertically penetrates multiple layers of two-dimensional carbon cloth. The four sides of the multi-layer two-dimensional carbon cloth are locked with carbon fibers, and sometimes a U-shaped fiber is provided at the end of two adjacent rows of U-shaped fibers in the square matrix. The preparation method of the two-dimensional...

Embodiment 1

[0059] This embodiment is a method for preparing a two-dimensional carbon / silicon-silicon carbide composite pin, and its specific process is:

[0060] Step 1, making a two-dimensional flat plate preform. Use two-dimensional carbon cloth to lay alternately layer by layer in the direction of flat laying (0°) and oblique laying (45°) (the thickness is guaranteed to be greater than the diameter of the pin and a processing allowance is left), and the surface to be used is punched (8~15× 8 ~ 15mm arrangement) graphite plate flattened the carbon cloth, the bow frame is fixed on the bracket, carbon fiber is used to pass through each hole, and the carbon cloth is vertically sewn to form a two-dimensional flat plate prefabricated body.

[0061] Step 2, depositing a pyrolytic carbon interface layer. The pyrolytic carbon protective layer is infiltrated inside the two-dimensional flat plate preform through a deposition furnace. The process conditions are: the deposition temperature is 700...

Embodiment 2

[0068] Step 1, making a two-dimensional flat plate preform. Use two-dimensional carbon cloth to lay alternately layer by layer in the direction of flat laying (0°) and oblique laying (45°) (the thickness is guaranteed to be greater than the diameter of the pin and a processing allowance is left), and the surface to be used is punched (8~15× 8 ~ 15mm arrangement) graphite plate flattened the carbon cloth, the bow frame is fixed on the bracket, carbon fiber is used to pass through each hole, and the carbon cloth is vertically sewn to form a two-dimensional flat plate prefabricated body.

[0069] Step 2, depositing a pyrolytic carbon interface layer. The pyrolytic carbon protective layer is infiltrated inside the two-dimensional flat plate preform through a deposition furnace. The process conditions are: the deposition temperature is 800°C, the deposition furnace is vacuumed to 3kPa, and the flow rate is 4L / min of propylene gas as the deposition gas, 8L / min min of Ar gas was use...

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Abstract

The invention relates to a 2D carbon / silicon-silicon carbide composite material pin preparation method and a preparation method and structure of a 2D carbon / silicon-silicon carbide composite material pin preform. The pin preparation method comprises 1, preparing a preform through horizontal paving (0 degree)-inclined paving (45 degrees) alternative laying of a 2D carbon fabric, graphite mold-based setting and carbon fiber vertical seaming on the multilayer carbon fabric, 2, depositing a pyrolytic carbon protective layer in the preform, 3, carrying out chemical vapor infiltration (CVI) to obtain a silicon carbide base, 4, cutting a flat blank to obtain a strip-shaped pin blank with the square section, 5, carrying out CVI silicon carbide protection of exposed fibers, 6, carrying out reactive melt infiltration (RMI) treatment, 7, milling the pin blank to obtain a pin with a standard size and 8, carrying out examination to obtain a carbon / silicon-silicon carbide composite material pin finished product. Through combination of CVI and RMI, the preparation method has the advantages of low production cost, short production period, low product porosity, high density and batch production. The ceramic-based composite material prepared by the CVI and RMI has shear strength of 80-100MPa at the room temperature.

Description

technical field [0001] The invention relates to the technical field of preparation and processing of ceramic matrix composite materials, in particular to a preparation process of a two-dimensional carbon / silicon-silicon carbide composite material pin, which is mainly used in high-strength, high-temperature-resistant, corrosion-resistant, and oxidation-resistant composite material connections field. Background technique [0002] Ceramic matrix composites are favored by various aviation and aerospace fields for their high strength, high hardness, high temperature resistance, wear resistance, corrosion resistance, low density and other excellent thermophysical and mechanical properties, especially in the harsh environment of aircraft. For parts, ceramic matrix composites can replace traditional special metal materials and improve the comprehensive performance of parts in this environment. [0003] Due to the limitation of composite material weaving process, it is very difficul...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B9/00B32B9/04B32B5/06B32B37/00B28D1/16C04B35/78C04B35/565C04B35/52C04B35/622
CPCB28D1/16B32B5/06B32B5/26B32B9/007B32B9/047B32B37/00B32B2262/106B32B2605/18C04B35/521C04B35/565C04B35/622C04B35/806C04B2235/483C04B2235/5248C04B2235/5256C04B2235/614C04B2235/96
Inventor 成来飞冯锋左新章邬国平郭拥军王鹏
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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