Orientable axisymmetric nozzle of variable geometry of gas turbine propulsors

An orientable axisymmetric nozzle of variable geometry for a gas turbine engine for orienting the flow of gas through the engine and with respect to a longitudinal axis of the engine, which comprises:

• a convergent section followed, in the direction of gas flow, by a divergent section, both being formed by:
• master petals;
• a plurality of articulations for interconnecting the master petals;
• slave petals;
• and
• a plurality of articulations for interconnecting the slave petals, the master and slave petals being distributed circumferentially around the longitudinal axis of the engine;
• the convergent section defining a variable area throat and the divergent section being of variable geometry in order to orient the flow in any direction on a cone located around the longitudinal axis of the engine;
• an outer annular part;
• control means for regulating the throat area;
• control means for orienting the flow, by axial displacement and inclination of the outer annular part in any direction, with a center of rotation on a point on the longitudinal axis of the engine;
• a plurality of biarticulated bars one for each divergent master petal, each biarticulated bar having a first end and an opposite end;
• a plurality of cylindrical articulations one for each biarticulated bar for connecting the respective first ends of said biarticulated bars to the outer annular part, each cylindrical articulation being tangent to a theoretical circumference concentric to the longitudinal axis of the engine and being located in a theoretical plane perpendicular to such longitudinal axis;
• a plurality of pairs of intermediate bars one pair for each divergent master petal, each pair being comprised of an upstream intermediate bar and a downstream intermediate bar and each intermediate bar having first and second ends;
• a first spherical articulation for connecting the first ends of the intermediate bars of each pair together;
• a second and third spherical articulation for respectively connecting the second ends of the intermediate bars of each pair to longitudinally aligned points on the corresponding divergent master petal;
• and
• a plurality of first cylindrical articulations, one for each pair of intermediate bars, for connecting the upstream intermediate bar of each pair to the corresponding biarticulated bar, each first cylindrical articulation having an axis which, when there is no orientation of the flow, is tangent to a theoretical circumference concentric to the longitudinal axis of the engine and is located in a theoretical plane perpendicular to said longitudinal axis of the engine.