A kind of cerium phosphate modified silicon carbide fiber reinforced silicon carbide composite material and preparation method thereof

Abstract

The invention relates to a cerium phosphate modified silicon carbide fiber reinforced silicon carbide composite material and a preparation method thereof. The method: (1) alternately prepare cerium phosphate interface layers and silicon carbide interface layers on the surface of the silicon carbide fiber preform until reaching a predetermined thickness or predetermined number of layers to obtain a modified silicon carbide fiber preform; (2) use carbon The precursor solution is impregnated with the modified silicon carbide fiber preform, and then the impregnated modified silicon carbide fiber preform is sequentially subjected to a curing step and a cracking step; (3) repeating step (2) at least once to prepare a porous silicon carbide fiber preform and (4) subjecting the prepared porous silicon carbide fiber preform to liquid silicon infiltration reaction to obtain a cerium phosphate modified silicon carbide fiber reinforced silicon carbide composite material. The cerium phosphate modified silicon carbide fiber-reinforced silicon carbide composite material prepared by the invention has excellent oxidation resistance, temperature resistance, thermal shock resistance, etc., excellent comprehensive performance at high temperature, and long service life.

Description

technical field [0001] The invention belongs to the technical field of aerospace material preparation, and in particular relates to a cerium phosphate modified silicon carbide fiber reinforced silicon carbide composite material and a preparation method thereof. Background technique [0002] Aeroengines are known as the jewel in the crown of the industry. At present, the hot-end parts of the engine are made of high-temperature alloy materials, but with the increase in the thrust-to-weight ratio requirements of the engine, this type of material has reached the limit of use. Silicon carbide fiber-reinforced silicon carbide composites (SiC / SiC ceramic matrix composites) are considered to be ideal materials to replace superalloys due to their high strength, low density, and high temperature resistance. The density of SiC / SiC ceramic matrix composites is only one-third of that of superalloy materials, and it can resist higher temperature thermal oxidation environment, which can si...

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Problems solved by technology

[0004] Since the engine is in an ultra-high temperature aerobic environment, the oxidation resistance of the interface layer becomes very important. However, due to the insufficient oxidation resistance of the PyC interface layer and the BN interface layer, the use temperature and service life of the material are limited.

When the PyC interface layer is above 400°C, the performance of the composite material will be reduced due to oxidation, and the performance of the BN interface layer will also be lost in an oxidizing environment above 800°C.

With the improvement of the performance requirements of aero-engines for ceramic matrix composites, the temperature resistance, oxidation resistance and mechanical properties at high temperatures of current ceramic matrix composites need to be further improved.

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