General Electric Company

Jack D Wright

Alan Roy Stuart

Ambrose A Hauser

Barton H Snow

Leroy H Smith, Jr

William Carl Ruehr

Joe E Ellis

Jack L Readnour

A thrust reverser for a long duct mixed flow fan jet engine having a nacelle formed by a fixed forward structure surrounding the fan, a rear fixed structure and a translatable inner and outer cowl therebetween, the nacelle surrounds the engine and forms a long by-pass duct therewith, a common actuator fixed to the translatable cowls to simultaneously displace them over the rear structure, blocker doors coupled to the inner translating cowls for deployment during thrust reversal into the by-pass duct into a blocking position to divert the airflow through the cascades placed into an opening uncovered when the translatable cowls are axially displaced.

Thrust reversing arrangement for a long duct mixed flow exhaust turbofan

An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions. At the forward position, the annular member is located between the forward ends of the annular outer and inner structures with the annular outer structure expanded to an enlarged diameter such that the annular member forms therewith an inlet lip having an aerodynamically blunt exterior contour adapted to reduce drag during takeoff and landing operation of the aircraft. At the rearward position, the annular member is spaced rearwardly from the forward ends of the annular outer and inner structures with the annular outer structure contracted to a reduced diameter permitting the annular outer and inner structures at the forward ends thereof to form an inlet lip having an aerodynamically sharp exterior contour adapted to reduce drag during cruise operation of the aircraft.

Variable contour annular air inlet for an aircraft engine nacelle

Aircraft engine or similar article

An afterburning turbofan engine includes amixer for mixing the engine generated hot gas and fan streams prior to discharge through the engine nozzle. The mixer includes a fixed upstream portion and a movable downstream portion which may be indexed to selectively interchange flow communication between the chutes of the two portions to effect a temperature reduction in the downstream mixer portion and, hence, a reduction in infrared radiation.

Gas turbine engine mixer

The angle of the variable blocker door vanes in the bypass duct of a turbofan engine is varied in response to the angle of the variable compressor vanes of the engine. A cam and linkage assembly interconnect the blocker doors with the actuation system of the variable stator vanes such that as the angle of the stator vanes is modulated through a first predetermined range, the angle of the blocker doors is modulated through a second predetermined range.

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Mason, OH, United States of America

Jack D Wright