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Integrated engine-generator for aircraft secondary power.The integrated engine-generator concept consists of an electric generator located inside a turbojet or turbofan engine and both concentric with and driven by one of the main engine shafts. The electric power-conversion equipment and generator controls are conveniently located in the aircraft. When properly rated, the generator serves as an engine starter as well as a source of electric power. The available generating capacity permits use of electrically driven engine accessories. This reduces or eliminates the need for an external gearbox on the engine, thereby simplifying the engine and nacelle assembly and increasing aircraft design flexibility. The nacelle diameter can then be decreased, resulting in less aerodynamic drag and reduced takeoff gross weight.
Document ID
19730028585
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Secunde, R. R.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1972
Subject Category
Auxiliary Systems
Report/Patent Number
AIAA PAPER 72-1056
Meeting Information
Meeting: Joint Propulsion Specialist Conference
Location: New Orleans, LA
Country: US
Start Date: November 29, 1972
End Date: December 1, 1972
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
73A13387
Distribution Limits
Public
Copyright
Other

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