Variable geometry turbojet engine exhaust nozzle

Details Variable geometry turbojet engine exhaust nozzle Variable geometry turbojet engine exhaust nozzle

1997-06-13

1999-08-10

Freay, Charles G.

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle

With means controlling amount, shape or direction of...

23926533, 60271, B05B 1200

Patent

active

059345640

ABSTRACT:
A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to the rear portion of the turbojet engine, and an inner flap ring having a plurality of inner forward driven flaps and a plurality of inner forward interlock flaps, each having a forward portion pivotally attached to the rear portion of the turbojet engine, the inner flap ring also having a plurality of inner rear driven flaps and a plurality of inner rear interlock flaps, each inner rear flap having a front edge portion pivotally connected to a rear edge portion of a corresponding inner forward flap. The inner and outer flap rings are radially spaced apart and are arranged symmetrically about an axis of symmetry, with a drive collar located in the space between the inner and outer flaps that is movable between forwardmost and rearmost positions in a direction substantially parallel to the axis of symmetry of the nozzle. A plurality of translating levers are each pivotally attached to the drive collar and to one of the inner forward driven flaps. A plurality of interlock levers are each pivotally connected to one of the translating levers and to one of the inner rear driven flaps. Each interlock lever is connected to one of the outer driven flaps by a link rod pivotally connected to the interlock lever and to the outer driven flaps. Actuators are connected to the rear portion of the turbojet engine and to the translating levers to move the drive collar between its forwardmost and rearmost positions, such movement causing the inner flap ring to move between a converging-diverging configuration and a converging--converging configuration. Thus, the nozzle is suitable for both subsonic and supersonic aircraft operation.

REFERENCES:
patent: 2969189 (1961-01-01), Jordan
patent: 4141501 (1979-02-01), Nightingale
patent: 5235808 (1993-08-01), Taylor
patent: 5398499 (1995-03-01), Urrela
patent: 5571262 (1996-11-01), Camboulives

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