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Preparation method of SiC/SiC composite material

A composite material and prefabricated technology, which is applied in the preparation of SiC/SiC composite materials and the preparation of high-density SiC/SiC composite materials, can solve the problems of small ceramic retention rate, high porosity of SiC/SiC composite materials, and manufacturing cycle. Long and other problems, to achieve the effect of reducing porosity, increasing the degree of cross-linking, and high ceramic yield

Inactive Publication Date: 2019-01-22
AVIC BASIC TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, in the process of converting the polycarbosilane benzene-based organic solution into a silicon carbide matrix, accompanied by a large volume shrinkage, the ceramic retention rate is small, the manufacturing cycle is long, and the obtained SiC / SiC composite material has a high porosity.

Method used

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  • Preparation method of SiC/SiC composite material

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preparation example Construction

[0021] 1. Preparation of fiber preform: use 2.5D weaving process to weave SiC fiber into SiC fiber preform, the thickness of fiber preform is 2-5mm, and the volume fraction is 35%-50%;

[0022] 2RTM mold preparation: Design the mold for RTM process according to the shape of the SiC fiber preform, and place graphite paper with a thickness of 0.10-0.50mm on the bonding surface of the upper and lower molds of the mold;

[0023] 3RTM Process Vacuum Glue Injection: Perform high-temperature pretreatment on the fiber preform to remove the sizing agent and other impurity components on the fiber surface. In the RTM mold, close the mold, lock the mold, evacuate until the internal pressure of the RTM mold is ≤0.005MPa, inject liquid polycarbosilane into the mold, and evacuate while injecting;

[0024] 4 Heating and curing: place the RTM mold with the SiC fiber prefabricated body in an oven, and after completing the heating and curing, release the mold. The curing process temperature is ...

Embodiment 1

[0030] 1. Preparation of fiber preform: Cansas 3203SiC fiber is used as raw material and 2.5D weaving process is adopted to weave Cansas3203SiC fiber into SiC fiber preform. The thickness of fiber preform is 3mm and the volume fraction is 40%.

[0031] 2. RTM mold preparation: According to the shape of the SiC fiber preform, design the mold for the RTM process, and place graphite paper with a thickness of 0.20mm on the bonding surface of the upper and lower molds of the mold;

[0032] 3. Vacuum glue injection in RTM process: high temperature pretreatment is carried out on the fiber preform to remove the sizing agent and other impurity components on the fiber surface. In the RTM mold, close the mold, lock the mold, evacuate until the internal pressure of the RTM mold is ≤0.005MPa, inject liquid polycarbosilane into the mold, and evacuate while injecting;

[0033] 4. Heat curing: place the RTM mold with the SiC fiber prefabricated body in an oven, and after heat curing is comple...

Embodiment 2

[0039] 1. Design and preparation of fiber preform: KD-II SiC fiber is used as raw material and 2.5D weaving process is adopted to weave SiC fiber into SiC fiber preform. The thickness of fiber preform is 2.5mm and the volume fraction is 44%.

[0040] 2. RTM mold preparation: According to the shape of the SiC fiber preform, design the mold for the RTM process, and place graphite paper with a thickness of 0.30mm on the bonding surface of the upper and lower molds of the mold;

[0041] 3. Vacuum glue injection in RTM process: high-temperature pretreatment is performed on the fiber preform to remove the sizing agent and other impurity components on the fiber surface. The high-temperature pretreatment temperature is 800°C and the treatment time is 1 hour. In the RTM mold, close the mold, lock the mold, evacuate until the internal pressure of the RTM mold is ≤0.005MPa, inject liquid polycarbosilane into the mold, and evacuate while injecting;

[0042] 4. Heat curing: place the RTM m...

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Abstract

The invention belongs to the technical field of composite material manufacturing, relates to a preparation method of a SiC / SiC composite material, and in particular, relates to a preparation method ofa high-density SiC / SiC composite material. The prepared SiC / SiC composite material adopts a 2.5D weaving mode, through interweaving of warp yarns, the disadvantage of poor interlayer performance of a2D weaving process is overcome, and at the same time, the disadvantage that a 3D weaving process has great difference between the weft direction mechanical property and the warp direction mechanicalproperty due to containing of no weft yarns is overcome, so that the SiC / SiC composite material has excellent interlayer bonding strength and toughness in both the warp direction and the weft direction, and better material support is provided for the design of SiC / SiC composite material components. In addition, the liquid polycarbosilane as an impregnant is used as a raw material for preparing a ceramic matrix in the early stage of preparation of the SiC / SiC composite material. Compared with a traditional polycarbosilane benzene based solution impregnant, the SiC / SiC composite material has theadvantages of high ceramic yield and is beneficial to shortening the development cycle of the material.

Description

technical field [0001] The invention belongs to the technical field of composite material manufacturing, and relates to a method for preparing a SiC / SiC composite material, in particular to a method for preparing a high-density SiC / SiC composite material. Background technique [0002] With the gradual increase of the thrust-to-weight ratio of aero-engines, the service environment is more harsh. Hot-end components such as turbines, combustion chambers, and exhaust nozzles need to withstand strong aerodynamic loads and heat flow impacts, so the selected structural materials are required to have the characteristics of high temperature resistance, oxidation resistance, and excellent mechanical properties. The turbine inlet temperature of existing engines with a thrust-to-weight ratio of 10 and 1st has reached 1500°C, far exceeding the service temperature of high-temperature alloys and intermetallic compounds. At present, the maximum working temperature of the nickel-based super...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/622C04B35/84C04B35/565
CPCC04B35/806C04B35/571C04B35/622C04B2235/5244
Inventor 陈明伟张冰玉
Owner AVIC BASIC TECH RES INST
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