Preparation method of SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating

A technology of nanowire toughening and chemical vapor phase, which is applied in the field of preparation of nanowire toughened multiphase coatings, can solve the problems of limited coating resistance to oxidation, long diffusion free path, and decreased mechanical properties, and achieve excellent anti-burning corrosion performance, short reaction cycle, and low cost

Active Publication Date: 2019-03-19
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, there is a process of repeated heating in alternate deposition, which is prone to stress concentration.
At the same time, the alternate deposition of coatings cannot solve the problem of cracking of the coating during use, which makes the C/C matrix oxidized and the mechanical properties decline seriously.
In addition, during the anti-oxidation and anti-ablation process

Method used

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  • Preparation method of SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating
  • Preparation method of SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating
  • Preparation method of SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating

Examples

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Example Embodiment

[0027] Preparation method steps of SiC nanowire toughened chemical vapor co-deposition HfC-SiC multiphase coating:

[0028] (1) Before coating preparation, the surface of the C / C composite material sample is polished, cleaned, and dried in an oven for later use. 2 , Si, C powders with a particle size of 300 meshes are mixed uniformly in a ratio of 6:1:2 and dried for later use;

[0029] (2) Use a bunch of carbon fiber ropes to suspend the C / C composite material in step 1 in a graphite crucible with a prepared powder at the bottom, and place the crucible in the constant temperature zone of the argon protective atmosphere electric furnace at 5°C It is energized and heated to 1600℃ at a rate of / min, kept at a constant temperature for 2h, and then cooled with the furnace.

[0030] (3) Use a bunch of carbon fibers to suspend the C / C sample with SiC nanowires on the surface obtained in step 2 in an isothermal chemical vapor deposition (CVD) furnace, and add HfCl 4 The powder is placed in ...

Example Embodiment

[0037] Example 1:

[0038] The selected density is 1.70g / cm 3 Use 320 mesh SiC water sandpaper to smooth the C / C sample and place it at 80℃ for 4h for use; set the particle size to minus 300 mesh SiO 2 , Si, C are put into planetary ball mill for 3 hours at a ratio of about 6:1:2, and dried for later use. Choose HfCl 4 , SiCl 3 CH 3 , CH 4 As a precursor, H 2 As a reducing gas, Ar is used as a protective gas.

[0039] Use carbon fiber to hang the prepared C / C matrix on the inside with prepared SiO 2 , Si, C mixed powder graphite crucible, heat up to 1500 ℃, hold for 2 hours, obtain a C / C matrix with SiC nanowires on the surface, and then hang it in the isothermal zone of a chemical vapor deposition furnace (isothermal vertical vacuum furnace) . Under the protection of the Ar gas flow rate of 600ml / min, the temperature is increased at 7°C / min, and the furnace pressure is maintained at about 30kpa. After the temperature is raised to 1300°C, the powder feeding knob is adjusted to red...

Example Embodiment

[0040] Example 2:

[0041] The selected density is 1.70g / cm 3 Use 320 mesh SiC water sandpaper to smooth the C / C sample and place it at 80℃ for 4h for use; set the particle size to minus 300 mesh SiO 2 , Si, C are put into planetary ball mill for 3 hours at a ratio of about 6:1:2, and dried for later use. Choose HfCl 4 , SiCl 3 CH 3 , CH 4 As a precursor, H 2 As a reducing gas, Ar is used as a protective gas.

[0042] Use carbon fiber to hang the prepared C / C matrix on the inside with prepared SiO 2 , Si, C mixed powder graphite crucible, heat up to 1600 ℃, hold for 2 hours, obtain a C / C matrix with SiC nanowires on the surface, and then hang it in the isothermal zone of a chemical vapor deposition furnace (isothermal vertical vacuum furnace) . Under the protection of Ar gas flow rate of 600ml / min, the temperature is increased at 7°C / min, and the furnace pressure is maintained at about 30kpa. After the temperature is raised to 1400°C, adjust the powder feeding knob to reduce the H...

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Abstract

The invention relates to a preparation method of a SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating. The preparation method comprises the following steps: first, preparing a SiC nanowire on the surface of a C/C composite material by means of a chemical vapor deposition technique; and then depositing an HfC-SiC compound phase coating by means of the chemical vapor deposition technique to further obtain the SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating on the surface of the C/C composite material. By controlling the tissue componentsand the uniform degree of the SiC nanowire toughened chemical gas codeposited HfC-SiC compound phase coating, mismatching of coefficients of thermal expansion between the coating and the C/C composite material is alleviated. Crack generation and expansion are inhibited by means of a nanowire bridging and pulling out mechanism, so that the cracking condition of an HfC-based ceramic coating in an ablating process is inhibited effectively. The prepared coating is uniform in thickness, controllable in tissue, short in process preparation period, simple in process course and low in cost.

Description

technical field [0001] The invention belongs to a method for preparing a nanowire-toughened composite coating, and relates to a method for preparing a SiC nanowire-toughened chemical vapor co-deposition HfC-SiC composite coating. Background technique [0002] Carbon / carbon (C / C) composites have broad application prospects in aerospace materials due to their low density and excellent high-temperature mechanical properties. However, under the ablative environment of oxygen-containing atmosphere, C / C composites will undergo severe oxidation and mechanical erosion, which severely limits their application in key parts of aircraft and spacecraft. In order to solve this problem and after a lot of research by domestic and foreign scholars, coating technology is a technology that can effectively protect C / C composite materials in extreme ablation environments. [0003] Refractory ceramics (HfC, ZrC, TaC, ZrB 2 , HfB 2 ...) has a higher melting point and is suitable as a material f...

Claims

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Application Information

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IPC IPC(8): C04B35/56C04B35/565C04B35/622C04B35/80C04B41/87
CPCC04B35/806C04B35/5607C04B35/565C04B35/62222C04B41/009C04B41/5059C04B41/87C04B2235/3817C04B2235/5244C04B35/83
Inventor 冯涛李贺军付前刚童明德
Owner NORTHWESTERN POLYTECHNICAL UNIV
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