FAN NACELLE TRAILING EDGE

A fan nacelle (104), a gas turbine engine cell assembly (190), and an aircraft are provided. The fan nacelle (104) includes a fan duct skin (110) arranged in a fan duct (112) to direct airflow from the fan of a Turbofan engine toward a fan nozzle (122). An exterior skin (114) of the fan nacelle dire...

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Bibliographische Detailangaben
1. Verfasser:	HOWE, Sean P
Format:	Patent
Sprache:	eng ; fre ; ger
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 fan nacelle (104), a gas turbine engine cell assembly (190), and an aircraft are provided. The fan nacelle (104) includes a fan duct skin (110) arranged in a fan duct (112) to direct airflow from the fan of a Turbofan engine toward a fan nozzle (122). An exterior skin (114) of the fan nacelle directs air flow around an exterior of the engine. The fan duct skin (110) and the exterior skin (114) terminate at a trailing edge (108), and a trailing edge portion of the exterior skin is one of parallel to and diverging from a trailing edge portion of the fan duct skin in an aft direction. In certain aspects, the trailing edge portion of the exterior skin is actuatable or inflatable to selectively divert from the trailing edge portion of the fan duct skin.