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Method for manufacturing unit doublet carbide codeposition fibre-reinforced composite

A composite material and fiber-reinforced technology, applied in metal material coating process, gaseous chemical plating, coating, etc., to achieve high temperature strength, simple technical process, and wide application

Inactive Publication Date: 2008-04-02
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the international tendency is to coat refractory carbide (such as HfC, TaC) coatings on C / C composites as engine nozzles, and the coating performance of chemical vapor deposition is the best, but there are still great gaps. difficulty

Method used

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  • Method for manufacturing unit doublet carbide codeposition fibre-reinforced composite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] Embodiment 1: Referring to accompanying drawing 1, Fig. 2, get the C fiber braided body of 3D weaving, cut into the annular sample of Φ (70-100) * 65mm, after weighing, put into chemical vapor deposition furnace; Vacuum to Below 50Pa, heat up to 1100°C, first carry out CVD-C deposition, and pass Ar and C at a ratio of 3:1 3 h 6 Carry out CVD-C deposition, keep the furnace pressure 1000-2000Pa deposition for 20hr; then carry out TaC-SiC co-deposition, use Ar as carrier gas to deposit TaCl 5 introduced into the furnace, while adding C 3 h 6 and reducing gas H 2 , with H 2 CH 3 SiCl 3 (MTS) is brought into the deposition furnace by another pipeline, Ar is used as a dilution gas, and H 2 The ratio with Ar is 1: (1~5), H 2 : MTS ≥ 10, keep the furnace pressure 500 ~ 1000Pa deposition 60hr; stop deposition; continue to pass through Ar for 30min, vacuum cooling; after reaching room temperature, open the furnace to take samples, weigh and test. The carbide crust on the...

Embodiment 2

[0018] Embodiment 2: Referring to accompanying drawing 1, take the SiC fiber braided body of 4D weaving, cut into the annular sample of Φ (70-100) * 65mm, after weighing, put into chemical vapor deposition furnace; Vacuum to below 50Pa, Heating to 1300°C for TaC-HfC co-deposition, using Ar as carrier gas to transfer TaCl 5 Introduced into the furnace while adding CH 4 and reducing gas H 2 , using Ar as the carrier gas to transfer HfCl 4 It is introduced into the deposition furnace through another way, and CH is added at the same time 4 and reducing gas H 2 , Ar as the diluent gas, keep the furnace pressure at 500-1000Pa for deposition for 60 hours; stop the deposition; continue to pass Ar for 30 minutes, vacuumize and cool down; Remove the carbide crust on the inner and outer layers of the diameter by car, ultrasonically clean and dry, put it in a deposition furnace to continue deposition, and repeat TaC-HfC co-deposition several times. A SiC fiber-reinforced TaC-HfC co-d...

Embodiment 3

[0019] Embodiment 3: Referring to accompanying drawing 1, take the boron B fiber (or tungsten W wire) weaving body of 4D weaving, cut into the annular sample of Φ (70-100) * 65mm, after weighing, put into chemical vapor deposition furnace ; Other processes are the same as in Example 2, and the TaC-HfC co-deposition composite material reinforced by dense B fiber (or tungsten W wire) can be obtained.

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Abstract

The invention relates to a preparation method for making unit doublet carbide codeposition fiber reinforcement composite material through chemical gas phase permeation / deposition process, wherein, codeposition unit doublet carbide is obtained inside a preformed billet body made of C fiber, boron fiber, ceramic fiber and metal fiber, etc. by use of the designability of chemical gas phase permeation / deposition process to make fiber-reinforcement unit doublet carbide composite material; the carbide is the combination of any two sorts of carbide of HfC, TaC, ZrC, NbC, WC, TiC, B4C, VC, AlC and SiC, etc. The material made through the method is characterized by high temperature resistance, wear resistance, anti scour, antioxidation, ablation resistance and excellent thermal shock resistance.

Description

Technical field: [0001] The invention relates to a chemical vapor infiltration / deposition process for manufacturing binary carbide co-deposition fiber-reinforced composite materials, which are mainly used for functional structural parts that require high temperature, high hardness, anti-oxidation, anti-ablation and the like. Background technique: [0002] Chemical vapor deposition is chemically synthesizing materials at the atomic and molecular levels, so materials can be designed and prepared at the nanometer level; the preparation process can ensure the controllability and reproducibility of composition and structure; the material preparation and device production are consistent; equipment It is relatively simple, easy to operate, and easy to realize automatic control. Another advantage of preparing materials by chemical vapor deposition is that they can be prepared at temperatures much lower than the melting point of the material. For example, the melting point of TaC is...

Claims

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Application Information

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IPC IPC(8): C23C16/32C23C16/52C23C16/448
Inventor 李国栋熊翔陈昭科黄伯云张红波肖鹏
Owner CENT SOUTH UNIV
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