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The development of C/SiC composite material

  C/SiC composite material is a kind of composite material which is made of SiC fiber as the reinforcing material in the SiC ceramic matrix, and the SiC reinforced fiber is introduced as the dispersed phase and the SiC ceramic matrix as the continuous phase.

  C/SiC composite material retains the advantages of SiC ceramic high temperature resistance, high strength, oxidation resistance, corrosion resistance, impact resistance, while both SiC fiber reinforced and toughening effect, overcomes the congenital defects of low toughness and resistance to external impact load and poor performance of SiC ceramic fracture. This material can be maintained at a temperature of 1316 C in the absence of physical and chemical properties of its degradation. When the SiC/SiC material sprayed with thermal barrier coating, the maximum operating temperature can continue to increase to 1480 degrees C. Although modern commercial engine turbine inlet temperature can reach 1650 DEG C, temperature difference of 170 C still need to use additional compressor bleed cooling to make up, but the bleeding rate compared with traditional high temperature alloy blade has been greatly reduced. According to preliminary calculations, the use of temperature 1480 C CMC high pressure turbine blades can reduce engine fuel consumption by up to 6%. At the same time, the cooling gas combustor liner made of CMC material required is also significantly reduced, the cooling air fuel mixture with incomplete combustion of nitrogen oxide formation and reduce the chance of up to 33%, the reduction potential of nitrogen oxides

  The application of C/SiC composite materials in aviation field mainly includes the engine combustion chamber lining, combustion chamber, nozzle guide vane, wing leading edge, turbine blade and turbine shroud ring.

  The foreign research and application of component silicon carbide ceramic matrix composites, frompointtoarea (based on the first stationary after rotating, from low temperature to high temperature) the development of ideas, first developed in the stationary parts and moderate loads, such as nozzle adjustment sheet / sealing plate and inner vertebral body; the development of high temperature, medium load static parts, such as flame tube, flame stabilizer and turbine outer ring and guide vanes. Higher loads of stationary or rotating parts such as turbine rotors and turbine blades are still in the exploratory stage.