Variable area fan nozzle with bypass flow

The exit area of a nozzle assembly is varied by translating a ring assembly (254,256) located at a rear of the engine nacelle (18). The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translatio...

Full description

Saved in:
Bibliographic Details
Main Authors DAVIES NEIL C, HUBBERSTEY MARK, WYLIE STEVEN ANDREW, WANG SHUNSHEN RICHARD, HARVEY JOHN H, ROBERTS STEPHEN MICHAEL, JAMES NORMAN JOHN, FRANK JOEL HUDSON, WHARTON BRETT J, BAER DAVID A, JONES TONY, BACON PETER W, MCKLENY BRYANT LYNOEL
Format Patent
LanguageChinese
English
Published 24.07.2013
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:The exit area of a nozzle assembly is varied by translating a ring assembly (254,256) located at a rear of the engine nacelle (18). The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit (260) at a leading edge of the ring assembly. The upstream exit (260) can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings (320) partially enclose actuator components (270) for reduced drag.
Bibliography:Application Number: CN200880102315