Radial and Axial Flow Variable Exhaust Nozzle for a Gas Turbine Engine.
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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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. Author
- Jet and Gas Turbine Engines