NOZZLE FLAP FOR AIRCRAFT TURBOJETS

摘要

The invention proposes a long life nozzle flap for aircraft turbojets. This flap is remarkable in that it is composed of a hollow tapered body flattened in the transverse direction along straight geometric generating lines, the body forming a thin wall with an approximately constant thickness E, this wall comprising a continuous inner surface with a radius of curvature equal to at least 2xE, the wall being made of a refractory composite material composed of reinforcing fibres embedded in a matrix also made from a refractory material, the reinforcing fibres being arranged in a plurality of continuous layers of fibres stacked on each other, the fibres of a layer crossing the fibres of any adjacent layer.