Rohr, Inc.

Goodrich Actuation Systems Limited

Shunshen Richard Wang

John Herbert Harvey

Norman John James

Tony Jones

Peter Bacon

Stephen Michael Roberts

Mark Hubberstey

Joel H Frank

David A Baer

Brett John Wharton

Neil Charles Davies

Steven Andrew Wylie

Bryant Lynoel McKleny

Neil C Davies

Joel Hudson Frank

Brett J Wharton

Peter W Bacon

The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. 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 at a leading edge of the ring assembly. The upstream exit 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 partially enclose actuator components for reduced drag.

Variable area fan nozzle with bypass flow

A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge. The nozzle segments are selectively movable between a stowed position and one or more deployed positions. In the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge. The nacelle assembly further includes a guide mechanism for guiding the nozzle segments between the stowed position and the deployed position. A split beavertail failing shields the guide mechanism against air flow when the nozzle segments are in the stowed position.

Translating variable area fan nozzle with split beavertail fairings

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Chula Vista, CA, United States of America

Shunshen Richard Wang