Thrust vectoring variable geometry exhaust nozzle for gas turbin

Details Thrust vectoring variable geometry exhaust nozzle for gas turbin Thrust vectoring variable geometry exhaust nozzle for gas turbin

1993-02-22

1994-07-19

Bertsch, Richard A.

Power plants

Reaction motor

With thrust direction modifying means

60228, 23926519, 23926539, F02K 100

Patent

active

053297636

ABSTRACT:
A thrust vectoring variable geometry exhaust nozzle for gas turbines, which includes a convergent section (2) followed, in the direction of the flow, by a divergent section (3), both formed by master (4 and 5) and slave petals (41 and 42), whose convergent section (2) defines a throat (15) having a variable area. The divergent section (3) has variable geometry in order to orientate the thrust, and includes a governing and external radial support system for regulating the throat area (15), and a governing system for regulating the vectoring of the thrust. Both system are formed by a single governing system consisting of three annular pieces (6,7 and 8), concentric among themselves and with the axis of the turbine, and by a plurality of linear actuators (9). The master petals (5) of the divergent section (3) are transversely subdivided into at least two segments (5a, 5b).

REFERENCES:
patent: 4662556 (1987-05-01), Gidlund
patent: 4690330 (1987-09-01), Robinson et al.
patent: 4994660 (1991-01-01), Hauer
patent: 5039014 (1991-08-01), Lippmeier
patent: 5082182 (1992-01-01), Bruchez et al.
patent: 5150839 (1992-09-01), Reedy
patent: 5174502 (1992-12-01), Lippmeier et al.
PCT Application #9105197; United Technologies Corporation.
Aviation Week and Space Technology, vol. 136, No. 9, Mar. 1992, pp. 44-46 Stanly W. Kandebo, "GE, Pratt Ground Tests Validate Nozzle Concepts".

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