Abstract: Axisymmetric nozzles of variable geometry and orientation of flow intended for gas turbine engines, especially for aircraft. The nozzle comprises control means for adjusting the throat area and vectoring the thrust, which means are formed by three rings concentric to the longitudinal axis of the engine, an inner ring, an intermediate ring, and an outer ring, and by a plurality of linear actuators. The outer ring includes two ring segments interarticulated to each other and swingable independently or in unison to vector the thrust of the aircraft, said swinging and corresponding thrust vectoring being limited to a single plane corresponding to the pitch of the aircraft.