Variable geometry exhaust nozzle for a turbojet engine

Details Variable geometry exhaust nozzle for a turbojet engine Variable geometry exhaust nozzle for a turbojet engine

1993-11-22

1994-11-01

Bertsch, Richard A.

Power plants

Internal combustion engine with treatment or handling of...

Material from exhaust structure fed to engine intake

23926539, 23926541, F02K 112

Patent

active

053598512

ABSTRACT:
A variable geometry nozzle for a turbojet engine is disclosed wherein the adjustment of the cross-sectional area of the nozzle in a converging-diverging configuration is controlled by a single control system. The single control system varies the positions of both of the inner upstream and downstream flaps, as well as the outer flaps. A second control system operates simultaneously with the first control system to change the configuration of the nozzle to a converging-converging configuration. The inner, upstream flaps, which are pivotally connected to the downstream end of the turbojet exhaust duct, are controlled by an axially movable control ring which is connected to the controlled inner, upstream flaps via a link rod. The positions of the inner, downstream flaps, which have their upstream edges pivotally connected to a downstream edge of a corresponding upstream flap, are controlled by the movement of the upstream flap, as well as a connection with a cowling support via another link rod. The positions of the outer flaps are controlled by a cam which is operatively interposed between the control ring and the controlled, outer flaps.

REFERENCES:
patent: 4000854 (1977-01-01), Konarski et al.

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