Converging exhaust nozzle fitted with translating cold flaps

Details Converging exhaust nozzle fitted with translating cold flaps Converging exhaust nozzle fitted with translating cold flaps

1999-07-16

2000-12-26

Thorpe, Timothy S.

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle

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

60271, B05B 1200

Patent

active

06164563&

ABSTRACT:
A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).

REFERENCES:
patent: 4641782 (1987-02-01), Woodward
patent: 4878617 (1989-11-01), Novotny
patent: 4993641 (1991-02-01), Kehret et al.
patent: 5934564 (1999-08-01), Bouiller et al.

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