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.


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    Title :

    Integrated engine-generator for aircraft secondary power.


    Contributors:

    Conference:

    Joint Propulsion Specialist Conference ; 1972 ; New Orleans, LA, US


    Publication date :

    1972-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English