Turbine engine nozzle

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 u...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	DALE W PETTY, ALEX J O SIMPSON
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	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.