VERFAHREN ZUR SILIZIERUNG VON THERMOSTRUKTURELLEN VERBUNDWERKSTOFFEN UND SO HERGESTELLTE TEILE

摘要

Treating a porous thermostructural composite material comprises forming an aerogel or xerogel comprising a precursor of a refractory material within the pores of the composite material, converting the precursor to a refractory material by pyrolysis, and impregnating the product with a molten silicon-type phase. Independent claims are also included for: (a) joining pieces of thermostructural composite material by abutting surfaces of the pieces, forming an aerogel or xerogel of refractory material in the pores at the interface between the surfaces and siliciding the product by impregnation with silicon-type phase; (b) sealing a piece of thermostructural composite material by siliciding and coating with ceramic material; (c) a piece of silicided thermostructural composite material produced in the form of an electrode for an ion or plasma engine or a bipolar plate for a fuel cell; (d) a piece of silicided thermostructural composite material comprising a silicon-type phase containing a nanometric network of refractory ceramic material; (e) friction material comprising a carbon/carbon composite material having pores at least partially filled with a silicon-type phase containing a nanometric network of silicon carbide; (f) an aircraft brake disc assembly in which the rotor and stator discs are made of friction material as above; and (g) an aircraft brake disc assembly in which the rotor or stator discs are made of friction material as above and the other discs are made of a non-silicided carbon/carbon composite material.