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Ti3SiC2MAX phase interface layer modified SiC/SiC composite material and preparation method thereof

A composite material and phase interface technology, which is applied in the field of aerospace material preparation technology, can solve the problems of insufficient mechanical properties, poor temperature resistance and oxidation resistance of composite materials in high-temperature air environments, and achieve easy crack deflection, stable performance, crystal The effect of high phase stability

Active Publication Date: 2021-03-12
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is that the poor temperature resistance and oxidation resistance of the current fiber interface layer cause insufficient mechanical properties of composite materials in high-temperature air environments

Method used

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  • Ti3SiC2MAX phase interface layer modified SiC/SiC composite material and preparation method thereof
  • Ti3SiC2MAX phase interface layer modified SiC/SiC composite material and preparation method thereof
  • Ti3SiC2MAX phase interface layer modified SiC/SiC composite material and preparation method thereof

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preparation example Construction

[0023] The present invention provides a Ti in the first aspect 3 SiC 2 The preparation method of MAX phase interface layer modified SiC / SiC composite material, described preparation method comprises the following steps:

[0024] (1) SiC fiber prefabricated body is prepared by SiC fiber, and the first sample is obtained;

[0025] (2) Deposit Ti on the surface of the SiC fiber of the first sample by chemical vapor deposition 3 SiC 2 MAX phase interface layer to obtain the second sample;

[0026] (3) Deposit and prepare a SiC interface layer on the outside of the second sample by chemical vapor deposition to obtain a third sample;

[0027] (4) immersing the third sample in the precursor solution to obtain the fourth sample;

[0028] (5) Carry out curing reaction to the 4th sample, obtain the 5th sample;

[0029] (6) Carry out cracking reaction to the 5th sample, obtain the 6th sample;

[0030] (7) Repeat step (4) to step (6) at least once to obtain the seventh sample con...

Embodiment 1

[0060] (1) Weaving the second-generation SiC fibers into a 2.5D preform to obtain the first sample with a fiber volume fraction of 32%, with a warp density of 7 fibers / cm and a weft density of 3 fibers / cm.

[0061] (2) Select titanium tetrachloride and hydrogen as precursors, and deposit on the fiber surface of the sample with a chemical vapor deposition furnace under the conditions of 1000°C and -0.04MPa for 1h to obtain a 500nm thick Ti 3 SiC 2 MAX phase boundary layer to obtain the second sample.

[0062] (3) Move the second sample to a chemical vapor deposition furnace, use trichloromethylsilane as a precursor, and deposit it at 1200 ° C and -0.05 MPa vacuum for 45 hours to obtain a SiC interface layer with a thickness of 3.5 μm. The third sample.

[0063] (4) The konone xylene solution was selected as the impregnation precursor, and the third sample was immersed in the precursor at 70° C. and 2 MPa high pressure for 1.5 h to obtain the fourth sample.

[0064] (5) Unde...

Embodiment 2

[0070] (1) Weaving the second-generation SiC fibers into a 2.5D preform to obtain the first sample with a fiber volume fraction of 39%, with a warp density of 8 fibers / cm and a weft density of 3.5 fibers / cm.

[0071] (2) Select titanium tetrachloride and hydrogen as precursors, and deposit 1.5h on the fiber surface of the sample with a chemical vapor deposition furnace under the conditions of 1000°C and -0.04MPa to obtain 800nm ​​thick Ti 3 SiC 2 MAX phase boundary layer to obtain the second sample.

[0072] (3) Move the second sample to a chemical vapor deposition furnace, use trichloromethylsilane as a precursor, and deposit it at 1200 ° C and -0.05 MPa vacuum for 80 h to obtain the first sample containing a SiC interface layer with a thickness of 4 μm. Three samples.

[0073] (4) Furfural xylene solution was selected as the impregnation precursor, and the third sample was immersed in the precursor at 70° C. and 2 MPa high pressure for 1.5 h to obtain the fourth sample. ...

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Abstract

The invention relates to a preparation method of a Ti3SiC2 MAX phase interface layer modified SiC / SiC composite material, and belongs to the field of aerospace material preparation processes. A chemical vapor deposition method is adopted, a Ti3SiC2 MAX phase interface layer is deposited on the fiber surface in a SiC fiber prefabricated body, and the thickness is 200-1200 nm. And then, a SiC interface layer is deposited on the outer side of the Ti3SiC2 MAX phase interface layer through a chemical vapor deposition method, and the Ti3SiC2 MAX phase interface layer is completely coated with the SiC interface layer with the thickness ranging from 3 micrometers to 5 micrometers. Then a proper resin precursor for repeated dipping, curing and cracking treatment is selected to obtain a green body containing a porous carbon matrix; and finally, liquid silicon melting reaction is performed in a high-temperature infiltration furnace to obtain the SiC / SiC composite material. The Ti3SiC2 MAX phase has excellent chemical stability, heat-conducting property and friction property so that the performance of the SiC / SiC composite material under a high-temperature condition can be effectively improved.

Description

technical field [0001] The invention relates to the technical field of aerospace material preparation technology, in particular to a Ti 3 SiC 2 Preparation method of SiC / SiC composite material modified by MAX phase interface layer. Background technique [0002] At present, the most advanced materials for aviation engine turbine blades are mainly third-generation single crystal superalloys with a density of about 8-9g / cm 3 , The limit use temperature is 1100℃. In order to further increase the temperature before the turbine and reduce the weight of the engine, new ultra-light high-temperature materials must be developed. SiC / SiC ceramic matrix composites have the characteristics of low density, good high-temperature performance, and high service temperature. The density is only about 1 / 3 of the current nickel-based superalloy, and the service temperature can reach above 1500 ° C. It is considered to be the future of high-performance engines. The key material is the fundam...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/573C04B35/577C04B35/80C04B35/622C04B35/628
CPCC04B35/573C04B35/622C04B35/6286C04B35/62863C04B35/62884C04B35/62894C04B2235/616C04B2235/5244C04B2235/3843C04B2235/48C04B2235/428C04B2235/96C04B2235/9607C04B2235/9684
Inventor 宋环君于艺金鑫刘伟李晓东于新民刘俊鹏裴雨辰
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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