Accession Number : ADD007037

Title :   Radial and Axial Flow Variable Exhaust Nozzle for a Gas Turbine Engine.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Wilson,Paul

Report Date : 28 Jan 1980

Pagination or Media Count : 13

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. (Author)

Descriptors :   *Patent applications, *Gas turbines, *Exhaust nozzles, *Fairings, *Thrust vector control systems, Inventions, Thrust, Radial flow, Axial flow, Pivots, Control systems

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE