| 摘要 |
A turbine engine nozzle comprises a plurality of flap assemblies, each comprising an upstream flap 22, pivotally coupled to a static structure 60, and a downstream flap 26, pivotally coupled to the upstream flap 22 by means of a hinge having an axis 502, and means for actuating articulation of the upstream and downstream flaps to define a range of throat areas. It is stated that this happens while minimising mode-induced changes in throat area at a given design point. Also claimed is a method of retrofitting/reengineering a turbine engine with a convergent flap, divergent flap and actuation linkage permitting an aerodynamically-induced mode change articulation of the divergent flap about a non-fixed instantaneous centre of rotation while allowing a simultaneous rotation of the divergent flap relative to the convergent flap about a non-fixed hinge axis. |
