A protecting device for an engine of a turboprop aircraft is connected with a direct-current power source, a storage battery, an engine parking control circuit and an engine feathering pump control circuit, wherein the direct-current power source, the storage battery, the engine parking control circuit and the engine feathering pump control circuit are arranged on the aircraft. A timing power supply circuit and a delay power failure circuit are arranged in the device. The device can solve the problems that when the engine is normally stopped, due to the fact that an operator switches off a power source on the aircraft in advance, consequently the engine is excessively burnt, and in the running state of the engine, when local feathering is inspected, due to failure of a local feathering button, the engine is damaged.


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    Titel :

    Protecting device for engine of turboprop aircraft


    Beteiligte:
    ZHANG XIAOYAN (Autor:in) / ZHANG WEI (Autor:in) / LI KAI (Autor:in) / FENG TAO (Autor:in)

    Erscheinungsdatum :

    22.04.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02B INTERNAL-COMBUSTION PISTON ENGINES , Brennkraftmaschinen mit innerer Verbrennung mit Verdrängerwirkung / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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