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

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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

Author(s):
Wilson, Paul
Author Organization(s):
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
Descriptive Note:
Patent Application,
Pagination:
0013

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Availability: This Government-owned Invention Available For U.s. Licensing And, Possibly, For Foreign Licensing. Copy Of Application Available Ntis.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PAT-APPL-115 847
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*Patent applications, *Gas turbines, *Exhaust nozzles, *Fairings, *Thrust vector control systems, Inventions, Thrust, Radial flow, Axial flow, Pivots, Control systems
Field(s)/Group(s):
Jet and Gas Turbine Engines
Report Date:
1980 Jan 28