Rohr, Inc.

Goodrich Actuation Systems Limited

Stephen Michael Roberts

John Herbert Harvey

Tony Jones

Peter Bacon

Mark Hubberstey

Brett John Wharton

Steven Andrew Wylie

Neil Charles Davies

Jihad I Ramlaoui

Norman John James

Joel H Frank

David A Baer

Shunshen Richard Wang

David Forsey

Bryant Lynoel McKleny

Neil Davies

Lynoel Mckleny Bryant

Brett Wharton

Joel Hudson Frank

Shunsen Richard Wang

Brett J Wharton

Peter W Bacon

Neil C Davies

Peter William Bacon

A variable area fan nozzle (VAFN) actuation system is disclosed. The VAFN actuation system is part of an aircraft nacelle, comprising a thrust reverser translating sleeve and a VAFN cowl. The system may translate the VAFN cowl to various positions to optimize engine performance. The system works in two phases. The first phase occurs when the translating sleeve is stowed. During this time, a linear, fluid-pressure VAFN actuator with multiple pistons may translate the VAFN cowl forward and aftward, and hold it in various fixed positions. The second phase occurs when the translating sleeve deploys and then stows. During this time, the actuator may allow the VAFN cowl to travel with the translating sleeve in a controlled manner. When the translating sleeve deploys, the VAFN cowl is pushed aftward by the translating sleeve. When the translating sleeve stows, the VAFN cowl is pulled forward with it.

Variable area fan nozzle actuation system

A variable area fan nozzle actuation ('VAFN') system is disclosed. The VAFN system may include an electrohydrostatic actuator ('EHA') arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

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

The track lock assembly may comprise a translating sleeve, a track beam, a pivoting lock assembly, and a ramp. The pivoting lock assembly may be mounted to the translating sleeve, wherein in response to the pivoting lock being mounted to the translating sleeve, the ramp is mounted to the track beam. The pivoting lock assembly may be mounted to the track beam, wherein in response to the pivoting lock being mounted to the track beam, the ramp is mounted to the translating sleeve.

Pivoting track lock

A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly.

Guide system for nacelle assembly

An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling.

Thrust reverser and VAFN arrangement

A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Growing community of inventors

San Diego, CA, United States of America

Stephen Michael Roberts