Improvements in axisymmetric nozzles of variable geometry and orientation of flow propellants aimed at gas turbine.

摘要

Improvements in axisymmetric nozzles orientable variable geometry intended for gas turbine propulsion, which nozzle comprises a convergent zone (2) followed by a divergent zone (3), both formed by master petals (4-5) and slave petals (33- 34), and added to the known functions (simultaneous axisymmetric variation, according to a law predetermined, the throat area A8 and of the outlet area A9; variation of all the geometry of the outlet area A9 independently of the throat area A8 and; axisymmetric orientation of the flow) a fourth function of varying only a part of the geometry of the exit area A9 independently of the throat area A8.