Radial and axial flow variable exhaust nozzle for a gas turbine

Details Radial and axial flow variable exhaust nozzle for a gas turbine Radial and axial flow variable exhaust nozzle for a gas turbine

1980-01-28

1981-07-21

Reeves, Robert B.

Fluid sprinkling, spraying, and diffusing

Processes

Of discharge modification of flow varying

23926525, B05B 1704

Patent

active

042793823

ABSTRACT:
Minimum thrust at idle speed, and maximum thrust with minimum losses at speeds above idle, are provided in a gas turbine engine by the use of a plurality of adjacent, successively overlapping, annularly disposed, pivotable, exhaust nozzle-forming fairings which are opened during idle to direct the exhaust gases overboard in radial directions between the opened fairings, and which are closed during speeds above idle to direct the exhaust gases overboard in an axial direction through an axially aligned rearwardly located exit opening of the exhaust nozzle.

REFERENCES:
patent: 2641104 (1953-06-01), Estabrook
patent: 2812636 (1957-11-01), Kadosch et al.
patent: 3013386 (1961-12-01), Meyer
patent: 3174709 (1965-03-01), Alderson
patent: 3409250 (1968-11-01), Ammer et al.
patent: 3441219 (1969-04-01), Turner
patent: 3685293 (1972-08-01), Shipman
patent: 3982696 (1976-09-01), Gordon

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