METHOD OF VARYING AN ANNULAR FAN EXIT AREA OF A GAS TURBINE ENGINE

A method of varying an annular fan exit area of a gas turbine engine (10) comprising the step of asymmetrically adjusting a first flap assembly segment (44A ... 44D) relative a second flap assembly segment to adjust an annular fan exit throat area.

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Bibliographische Detailangaben
Hauptverfasser:	WINTER, Michael, HANSON, Russell B
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A method of varying an annular fan exit area of a gas turbine engine (10) comprising the step of asymmetrically adjusting a first flap assembly segment (44A ... 44D) relative a second flap assembly segment to adjust an annular fan exit throat area.