Abstract: A method of protecting a thermostructural part made of ceramic matrix composite material against wear by coating the part is disclosed. The coating is made by providing a mixture comprising colloidal silica, a powdered silico-aluminous and/or aluminous refractory ceramic material, and water; applying at least one layer of the mixture on the part; drying the layer; and placing the part at a temperature greater than 1000° C., thereby firing the layer and forming an enamel coating. The invention is applicable to SiC moving flaps for a turbojet nozzle.

Abstract: A convergent turbojet exhaust nozzle comprising a ring of hinged flaps made up of controlled flaps and of follower flaps disposed in alternation and co-operating at their upstream ends with a peripheral sealing gasket arranged at the outlet from an afterburner channel, each flap being made out of a ceramic-matrix composite material, and at its upstream end, each flap being made integrally with bearing means for bearing against the above-mentioned peripheral gasket, and with spherical-joint means between their upstream ends.