Patent ID: 6964169

Claim:
Nozzle flap for aircraft turbojet, characterised in that it is composed of a hollow tapered body ( 10 ) flattened in the transverse direction along straight geometric generating lines ( 11 ), the body ( 10 ) forming a thin wall ( 12 ) with an approximately constant thickness E, this wall ( 12 ) being divided transversely into four adjacent parts namely: a plane “hot” trapezoidal wall ( 13 ); a flat “cold” trapezoidal wall ( 14 ) parallel to the hot wall ( 13 ) and two symmetric side walls ( 15 ) connecting the cold wall ( 13 ) and the hot wall ( 14 ) laterally; the wall ( 12 ) comprising a continuous inner surface ( 17 ) with a radius of curvature equal to at least 2×E, the wall ( 12 ) being made of a refractory composite material composed of continuous reinforcing fibres ( 18 ) made crosswise from a refractory material, the reinforcing fibres ( 18 ) being embedded in a matrix made of another refractory material.