Carbon fiber reinforced silicon carbide (C / SiC) ceramic matrix carbon composites (CMC), the silicon carbide ceramic matrix instead of the carbon matrix, because it has good oxidation resistance, high temperature thermal shock resistance, thermal conductivity and carbon fiber with good compatibility has become in the fields of aviation and aerospace very promising a new generation of high temperature structural materials.
Now, there are different methods to prepare /SiC C ceramic matrix composites, such as hot pressing method (HP), chemical vapor infiltration method (CVI), liquid silicon infiltration method (LSI), precursor conversion method (PIP) and so on.
Most of these methods can not be used to realize the low cost of ceramic matrix composites. The method of liquid silicon infiltration (LSI) is a kind of low cost, simple process with three stages. The process begins with the preparation of carbon fiber reinforced polymer (CFRP) slab, The carbon carbon composite material with pore structure were obtained by high temperature carbonization, and finally the SiC ,carbon carbon composite material were obtained by liquid silicon infiltration.
Its advantage is to avoid a repeat of the infiltration, so as to shorten the process time; the without any coating of fiber preform to reduce the cost of raw materials; in addition, to nearly the size of technology in the preparation of CMC member, to the greatest extent reduce the machining difficulty.
Phenolic resin has the advantages of high carbon residue rate and low thermal deformation under high temperature decomposition, which is very suitable for the matrix precursor of carbon carbon composite material.
Carbon phenolic resin composites were prepared by hot pressing molding method, and then the open porosity was 27%, the density was about 1.27g /cm3 and the carbon carbon composite material with the expected pore structure.