Dual self-healing modification method for silicon carbide ceramic matrix composite material

A technology of silicon carbide ceramic matrix and composite materials, which is applied in the field of double self-healing modification of multi-layer amorphous boron carbide matrix combined with borosilicate glass sealing, can solve the problems of no public reports and other problems, and achieve designable Strong resistance, reduced matrix cracks, and low preparation temperature

Inactive Publication Date: 2010-12-15
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

So far, no public reports have been found

Method used

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  • Dual self-healing modification method for silicon carbide ceramic matrix composite material
  • Dual self-healing modification method for silicon carbide ceramic matrix composite material
  • Dual self-healing modification method for silicon carbide ceramic matrix composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] (1) Use carbon fiber with the brand name T700 as the reinforcement of the composite material, and weave it into a 3D fiber prefabricated body using a three-dimensional four-way weaving method. The prefabricated body size is 250.0mm×125.0mm, and the thickness is 2.0mm;

[0028] (2) The prefabricated body is shaped by a high-strength, high-modulus graphite mold, and the thickness of the fiber prefabricated body is 4.0mm;

[0029] (3) Put the carbon fiber preform into the chemical gas phase pyrolysis carbon infiltration furnace, infiltrate the pyrolysis carbon interface layer, infiltration temperature: 750 ° C, holding time: 200h, furnace pressure: 150Pa, precursor body is C 3 h 6 ; its thickness is 150nm;

[0030] (4) High temperature treatment is performed on the preform after the interface layer is prepared, the treatment temperature is 1750°C, the treatment atmosphere is Ar gas, and the treatment time is 2.0 hours;

[0031] (5) Put the preform after high temperature ...

Embodiment 2

[0038] (1) Use carbon fiber with the brand name T300 as the reinforcement of the composite material, and weave the fiber into a 2.5-dimensional fiber prefabricated body. The length and width of the prefabricated body are 250mm×125mm, and the thickness is 4.5mm;

[0039] (2) The 2.5-dimensional carbon fiber braided prefabricated body is directly fixed and formed with a graphite mold;

[0040] (3) Put the carbon fiber prefabricated body into the chemical vapor phase silicon carbide infiltration furnace to infiltrate the pyrolytic carbon interface layer, infiltration temperature: 1000°C, holding time: 80h, furnace pressure: 100Pa, the precursor is CH 4 ; its thickness is 250nm;

[0041] (4) High temperature treatment is performed on the carburized preform, the treatment temperature is 2050°C, the treatment atmosphere is Ar gas, and the treatment time is 1.0 hour;

[0042] (5) Put the preform after high temperature heat treatment into the chemical vapor phase silicon carbide infi...

Embodiment 3

[0049] (1) Using Nicalon silicon carbide (SiC) fiber as the reinforcement of the composite material, the 2-dimensional Nicalon fiber cloth is laid into a 2-dimensional laminated prefabricated body. The length and width of the prefabricated body are 380mm×380mm, and the thickness is 5.0mm ;

[0050] (2) The 2-dimensional laminated prefabricated body is directly fixed and formed with a graphite mold;

[0051] (3) Put the silicon carbide fiber preform into the chemical vapor phase silicon carbide infiltration furnace to infiltrate the pyrolytic carbon interface layer, infiltration temperature: 900°C, holding time: 200h, furnace pressure: 10Pa, the precursor is CH 4 ; its thickness is 300nm;

[0052] (4) Carburizing the preform after high temperature treatment, treatment temperature: 1300°C, treatment atmosphere: Ar gas, treatment time 2.0 hours;

[0053] (5) Put the prefabricated body after high temperature heat treatment into a chemical vapor phase silicon carbide infiltration...

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Abstract

The invention relates to a dual self-healing modification method for a silicon carbide ceramic matrix composite material, which is technologically characterized in that a fiber preform is used as a reinforcement, a pyrolytic carbon interface is prepared by chemical vapor infiltration, a silicon carbide matrix is prepared by the chemical vapor infiltration, and silicon carbide matrixes and amorphous boron carbide matrixes (alpha-B4C) are alternately prepared by the chemical vapor infiltration until the density of the composite material is greater than 2.0 g.cm<-3>; two silicon carbide coatings are formed by chemical vapor deposition, and borosilicate glass is used for sealing and filling by a method of brushing costing and sintering. The method has strong designability, simple process and good repeatability, can obviously improve the oxidation resistance of CMC-SiC and can meet the application requirement of sealing sheets / adjustment sheets, inner cones, floating wall tiles, flame tubes and other members of an aircraft engine with high thrust-weight ratio for long-life CMC-SiC.

Description

technical field [0001] The invention relates to a double self-healing modification method of a silicon carbide ceramic matrix composite material, in particular to a multilayer amorphous boron carbide matrix (α-B 4 C) Dual self-healing modification combined with borosilicate glass encapsulation. Background technique [0002] Fiber-toughened silicon carbide ceramic matrix composite (CMC-SiC) is a new type of high-temperature resistant, low-density, high-performance thermal structural material, which can effectively increase the operating temperature of the engine, reduce the amount of cooling air, reduce the structural weight of components, and reduce NO x and CO 2 It has great application potential in the fields of high thrust-to-weight ratio aero-engines, industrial gas turbines, and nuclear energy. The density of CMC-SiC is 2~2.5g / cm 3 , is 1 / 4 to 1 / 6 of high-temperature metal structural materials, and the potential maximum long-term service temperature is 1650°C, which ...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/565C04B35/622
Inventor 成来飞张立同刘永胜殷小玮董宁栾新刚曾庆丰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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