An integrated engine-generator for aircraft secondary power generation is described. The 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 located in the aircraft. When properly rated, the generator serves as an engine starter as well as a source of electric power. This configuration reduces or eliminates the need for an external gear box on the engine and permits reduction in the nacelle diameter.


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    Title :

    Integrated engine generator for aircraft secondary power


    Contributors:

    Conference:

    Propulsion Specialists Conf. ; 1972 ; New Orleans


    Publication date :

    1972-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English