Tungsten carbide interface layer modified silicon carbide fiber-reinforced silicon carbide composite material and preparation method thereof

Abstract

The invention relates to a tungsten carbide interface layer modified silicon carbide fiber-reinforced silicon carbide composite material and a preparation method thereof. The method comprises the following steps of: (1) depositing a tungsten carbide interface layer and a silicon carbide interface layer on the surface of a silicon carbide fiber prefab in sequence through a chemical vapor depositionmethod, so as to prepare a modified silicon carbide fiber prefab; (2) steeping the modified silicon carbide fiber prefab prepared in the step (1) by using precursor solution of carbon, and carrying out solidification and pyrolysis on the steeped modified silicon carbide fiber prefab in sequence; (3) repeating the step (2) for at least once so as to obtain a porous silicon carbide fiber prefab; and (4) carrying out liquid silicon infiltration reaction on the porous silicon carbide fiber prefab to obtain the tungsten carbide interface layer modified silicon carbide fiber-reinforced silicon carbide composite material. The prepared tungsten carbide interface layer modified silicon carbide fiber-reinforced silicon carbide composite material is excellent in comprehensive properties such as high-temperature oxidation resistance, thermal shock resistance, vapor corrosion resistance and the like.

Description

technical field [0001] The invention belongs to the technical field of aerospace material preparation, and in particular relates to a silicon carbide fiber-reinforced silicon carbide composite material modified by a tungsten carbide interface layer and a preparation method thereof. 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. Silicon carbide fiber reinforced silicon carbide composite material (SiC / SiC composite material) has the characteristics of low density, good high temperature performance and high service temperature. Its density is only about 1 / 3 of the current nickel-based superalloy, and the service temperature can reach ...

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Problems solved by technology

[0004] At present, the commonly used interface layers are pyrolytic carbon (PyC) interface layer and boron nitride (BN) interface layer, among which the performance of PyC interface layer will decrease significantly in the oxidizing environment at 400 ° C; the BN interface layer has strict requirements on the crystal phase, but the BN interface layer The crystal phase of the layer is easy to change at high temperature, and the BN interface layer is easily corroded by the water environment, which will limit the use of SiC / SiC composite materials

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